Flight Simulation Training Device Qualification Standards for Extended Envelope and Adverse Weather Event Training Tasks, 32015-32177 [C1-2016-05860]

Download as PDF Vol. 81 Friday, No. 98 May 20, 2016 Part II Department of Transportation mstockstill on DSK3G9T082PROD with RULES2 Federal Aviation Administration 14 CFR Part 60 Flight Simulation Training Device Qualification Standards for Extended Envelope and Adverse Weather Event Training Tasks (Correction); Final Rule VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4717 Sfmt 4717 E:\FR\FM\20MYR2.SGM 20MYR2 32016 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration March 30, 2016, make the following corrections: 1. Correct the table appearing on page 18240 to read as follows: ■ 14 CFR Part 60 [Docket No.: FAA–2014–0391; Amdt. No. 60—4] RIN 2120–AK08 Flight Simulation Training Device Qualification Standards for Extended Envelope and Adverse Weather Event Training Tasks Correction 14 CFR PART 60 [CORRECTED] In FR Rule Doc. No. 2016–05860 beginning on page 18178 in the issue of TABLE A1B—TABLE OF TASKS VS. SIMULATOR LEVEL QPS Requirements Entry No. * 3. Inflight Maneuvers. Information Subjective requirements In order to be qualified at the simulator qualification level indicated, the simulator must be able to perform at least the tasks associated with that level of qualification * * * * B C Notes D * * * * Upset Prevention and Recovery Training (UPRT) ................... * A * * * * * 3.b. High Angle of Attack Maneuvers 3.b.1 .......................... Approaches to Stall ................................................................... 3.b.2 .......................... Full Stall .................................................................................... * 3.g. ............................ Simulator levels * * * X * * * X X X X X X X * Stall maneuvers at angles of attack above the activation of the stall warning system. Required only for FSTDs qualified to conduct full stall training tasks as indicated on the Statement of Qualification. * * Upset recovery or unusual attitude training maneuvers within the FSTD’s validation envelope that are intended to exceed pitch attitudes greater than 25 degrees nose up; pitch attitudes greater than 10 degrees nose down, and bank angles greater than 45 degrees. * * 2. Correct the table appearing on pages 18242–18282 to read as follows: mstockstill on DSK3G9T082PROD with RULES2 ■ VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4701 Sfmt 4700 E:\FR\FM\20MYR2.SGM 20MYR2 * mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 Test Entry Number 1. Performance. Tolerance Title Flight Conditions Ground. l.a.2 ±10% or ±2°/s of tum rate. Ground. Fmt 4701 Rate of tum versus nosewheel steering angle (NWA). l.b. Takeoff. l.b.l Ground acceleration time and distance. ±1.5 s or ±5% of time; and ±61 m (200ft) or ±5% of distance. Takeoff. l.b.2 Minimum control speed, ground (VmoJ using aerodynamic controls only per applicable airworthiness requirement or alternative engine inoperative test to ±25% of maximum airplane lateral deviation reached or ±1.5 m (5 ft). Takeoff. Sfmt 4725 ±0.9 m (3 ft) or ±20% of airplane tum radius. Notes A B c D X X X X X X X X X X May be combined with normal takeoff(l.b.4.) or rejected takeoff (l.b. 7.). Plotted data should be shown using appropriate scales for each portion of the maneuver. X X X X If a Vmog test is not available, an acceptable alternative is a flight test snap engine deceleration to idle at a speed between V, and Vr I 0 kt, followed by control of heading using aerodynamic control only and recovery should be achieved with the Taxi. Minimum radius tum. Frm 00003 PO 00000 l.a. l.a.l Test Details INFORMATION Simulator Level E:\FR\FM\20MYR2.SGM 20MYR2 For airplanes with reversible flight control systems: Plot both main and nose gear loci and key engine parameter(s). Data for no brakes and the minimum thrust required to maintain a steady tum except for airplanes requiring asymmetric thrust or braking to achieve the minimum radius tum. Record for a minimum of two speeds, greater than minimum turning radius speed with one at a typical taxi speed, and with a spread of at least 5 kt. Note.- All airplane manufacturer commonly-used certificated take-offflap settings must be demonstrated at least once either in minimum unstick speed (l.b.3), normal take-off (J.b.4), critical engine failure on take-off(I.b.5) or crosswind take-off (1. b. 6). Acceleration time and distance must be recorded for a minimum of 80% of the total time from brake release to V,. Preliminary aircraft certification data may be used. Engine failure speed must be within ±I kt of airplane engine failure speed. Engine thrust decay must be that resulting from the mathematical model for the engine applicable to the FSTD under test. If the modeled engine is not the same as the airplane manufacturer's flight test engine, a further test may be run with the same initial conditions using the thrust from the flight test Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A - Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS 32017 ER20MY16.000</GPH> mstockstill on DSK3G9T082PROD with RULES2 32018 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title demonstrate ground control characteristics. Flight Conditions Test Details INFORMATION Simulator Level A B c main gear on the ground. data as the driving parameter. ±2.2 daN (5lbt) or±lO% of rudder pedal force. To ensure only aerodynamic control, nosewheel steering should be disabled (i.e. castored) or the nosewheel held slightly off the ground. PO 00000 Frm 00004 l.b.3 Fmt 4701 Minimum unstick speed (Vmu) or equivalent test to demonstrate early rotation take-off characteristics. ±3 kt airspeed. ±1.5° pitch angle. Takeoff. Record time history data from I 0 knots before start of rotation until at least 5 seconds after the occurrence of main gear lift-off. X X X X Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 l.b.4 Normal take-off. ±3 kt airspeed. ±1.5° pitch angle. ±1.5° AOA. ±6 m (20 ft) height. For airplanes with ER20MY16.001</GPH> Notes D Takeoff. Data required for near maximum certificated takeoff weight at mid center of gravity location and light takeoff weight at an aft center of gravity location. If the airplane has more than one certificated takeoff configuration, a different configuration must be used for each weight. Record takeoff profile from brake release to at least 61 m (200ft) AGL. X X X X Vmu is defmed as the minimum speed at which the last main landing gear leaves the ground. Main landing gear strut compression or equivalent air/ground signal should be recorded. If a Vmu test is not available, alternative acceptable flight tests are a constant highattitude takeoff run through main gear lift-off or an early rotation takeoff. If either of these alternative solutions is selected, aft body contact/tail strike protection functionality, if present on the airplane, should be active. The test may be used for ground acceleration time and distance (I. b.!). Plotted data should be shown using appropriate scales for each portion of the maneuver. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level PO 00000 A B c X X X X X X X X Notes D reversible flight control systems: l.b.5 Critical engine failure on take-off. ±2.2 daN (51bt) or ±10% of column force. ±3 kt airspeed. Takeoff. ±1.5° pitch angle. Frm 00005 ±1.5° AOA. Record takeoff profile to at least 61 m (200 ft) AGL. Engine failure speed must be within ±3 kt of airplane data. ±6 m (20 ft) height. Fmt 4701 Sfmt 4725 For airplanes with reversible flight control systems: E:\FR\FM\20MYR2.SGM ±2° roll angle. ±2° side-slip angle. ±2.2 daN (5 lbt) or ±I 0% of column force; Test at near maximum takeoff weight. ±3° heading angle. ±1.3 daN (3 lbt) or ±10% of wheel force; and 20MYR2 l.b.6 Crosswind takeoff. ±2.2 daN (5lbt) or ±I 0% of rudder pedal force. ± 3 kt airspeed. Takeoff. Record takeoff profile from brake release to at least 61 m (200ft) AGL. ±1.5° pitch angle. ±6 m (20 ft) height. This test requires test data, including wind profile, for a crosswind component of at least 60% of the airplane performance data value measured at 10m (33 ft) above the runway. ±2° roll angle. In those situations where a maximum crosswind or a maximum demonstrated crosswind is not known, contact the NSPM. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS Wind components must be provided as headwind ±1.5° AOA. 32019 ER20MY16.002</GPH> mstockstill on DSK3G9T082PROD with RULES2 32020 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details c X X X Notes D and crosswind values with respect to the runway. ±3° heading angle. PO 00000 Correct trends at ground speeds below 40 kt for rudder/pedal and heading angle. Frm 00006 For airplanes with reversible flight control systems: Fmt 4701 ±2.2 daN (5lbt) or ±10% of column force; Sfmt 4725 E:\FR\FM\20MYR2.SGM A B ±2° side-slip angle. ±1.3 daN (3 lbt) or ±10% of wheel force; and l.b.7. Rejected Takeoff. ±2.2 daN (5lbt) or ±10% of rudder pedal force. ±5% of time or ±1.5 s. 20MYR2 ±7.5% of distance or ±76 m (250ft). Takeoff. Record at mass near maximum takeoff weight. Speed for reject must be at least 80% ofV1. Maximum braking effort, auto or manual. Where a maximum braking demonstration is not available, an acceptable alternative is a test using approximately 80% braking and full reverse, if applicable. Time and distance must be recorded from brake release to a full stop. ER20MY16.003</GPH> INFORMATION Simulator Level X Autobrakes will be used where applicable. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number l.b.8. Title Dynamic Engine Failure After Takeoff. ±2°/s or ±20% of body angular rates. Flight Conditions Takeoff. Test Details INFORMATION Simulator Level Engine failure speed must be within ±3 kt of airplane data. c X Engine failure may be a snap deceleration to idle. PO 00000 Record hands-off from 5 s before engine failure to +5 s or 30° roll angle, whichever occurs first. Frm 00007 CCA: Test in Normal and Non-normal control state. Climb. Normal Climb, all engines operating. Fmt 4701 I.e. l.c.l. ±3 kt airspeed. Clean. ±0.5 m/s (100 ftl min) or ±5% of rate of climb. Flight test data are preferred; however, airplane performance manual data are an acceptable alternative. Sfmt 4725 E:\FR\FM\20MYR2.SGM X X X X X X X X X X Record at nominal climb speed and mid initial climb altitude. FSTD performance is to be recorded over an interval of at least 300 m (I 000 ft). l.c.2. One-engineinoperative 2nd segment climb. ±3 kt airspeed. 2nd segment climb. 20MYR2 ±0.5 m/s (100 ftl min) or ±5% of rate of climb, but not less than airplane performance data requirements. Flight test data is preferred; however, airplane performance manual data is an acceptable alternative. Record at nominal climb speed. FSTD performance is to be recorded over an interval of at least 300m (1,000 ft). Test at WAT (weight, altitude or temperature) limiting condition. l.c.3. One Engine Inoperative En route Climb. ±10% time, ±10% distance, ±10% fuel used Clean Flight test data or airplane performance manual data may be used. Notes D X A B For safety considerations, airplane flight test may be performed out of ground effect at a safe altitude, but with correct airplane configuration and airspeed. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Fli2ht Simulator (FFS) Ob.iective Tests QPS REQUIREMENTS 32021 ER20MY16.004</GPH> mstockstill on DSK3G9T082PROD with RULES2 32022 VerDate Sep<11>2014 Test Jkt 238001 Entry Number l.c.4. Tolerance Title PO 00000 Frm 00008 One Engine Inoperative Approach Climb for airplanes with icing accountability if provided in the airplane performance data for this phase of flight. Fmt 4701 l.d. Level flight acceleration Approach ±0.5 m/s (100 ftl min) or ±5% rate of climb, but not less than airplane performance data. Test for at least a 1,550 m (5,000 ft) segment. Flight test data or airplane performance manual data may be used. Simulator Level A B c X X X Notes D X FSTD performance to be recorded over an interval of at least 300m (1,000 ft). Airplane should be configured with all anti-ice and de-ice systems operating normally, gear up and goaround flap. All icing accountability considerations, in accordance with the airplane performance data for an approach in icing conditions, should be applied. Test near maximum certificated landing weight as may be applicable to an approach in icing conditions. ±5%Time Cruise Sfmt 4725 E:\FR\FM\20MYR2.SGM l.d.2. Level flight deceleration. Cruise performance. Idle descent. 20MYR2 l.d.3. l.d.4. ±5%Time ±.05 EPR or ±3% Nl or ±5% of torque. ±5% of fuel flow. ±3 kt airspeed. Cruise Cruise. Clean. ±1.0 m/s (200ft/min) or ±5% of rate of descent. l.d.5. ER20MY16.005</GPH> Test Details Cruise I Descent. l.d.l. ±3 kt airspeed. Flight Conditions INFORMATION Emergency descent. ±5 kt airspeed. As per airplane Time required to increase airspeed a minimum of 50 kt, using maximum continuous thrust rating or equivalent. For airplanes with a small operating speed range, speed change may be reduced to 80% of operational speed change. Time required to decrease airspeed a minimum of 50 kt, using idle power. X X X X X X X X X X For airplanes with a small operating speed range, speed change may be reduced to 80% of operational speed change. The test may be a single snapshot showing instantaneous fuel flow, or a minimum of two consecutive snapshots with a spread of at least 3 minutes in steady flight. Idle power stabilized descent at normal descent speed at mid altitude. FSTD performance to be recorded over an interval of at least 300m (1,000 ft). FSTD performance to be recorded over an X X X X X X X X Stabilized descent to be Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details performance data. Time and distance must be recorded for at least 80% of the total time from touchdown to a full stop. A B c conducted with speed brakes extended if applicable, at mid altitude and near Vmo or according to emergency descent procedure. ±1.5 m/s (300ft/min) or ±5% of rate of descent. PO 00000 Frm 00009 Stopping. Deceleration time and distance, manual wheel brakes, dry runway, no reverse thrust. Fmt 4701 l.e. l.e.l. ±1.5 s or±5% of time. For distances up to 1,220 m (4, 000 ft), the smaller of ±61 m (200 ft) or ±10% of distance. Sfmt 4725 E:\FR\FM\20MYR2.SGM l.e.2. Deceleration time and distance, reverse thrust, no wheel brakes, dry runway. X X X X X X X X X X Position of ground spoilers and brake system pressure must be plotted (if applicable). For distances greater than 1,220 m (4, 000 ft), ±5% of distance. Data required for medium and near maximum certificated landing mass. ±1.5 s or ±5% of time; and Engineering data may be used for the medium mass condition. Time and distance must be recorded for at least 80% of the total time from initiation of reverse thrust to full thrust reverser minimum operating speed. Landing the smaller of ±61 m (200ft) or ±10% of distance. 20MYR2 Position of ground spoilers must be plotted (if applicable). Data required for medium and near maximum certificated landing mass. l.e.3. Stopping distance, wheel brakes, wet runway. ±61 m (200ft) or ±10% of distance. Landing. Engineering data may be used for the medium mass condition. Either flight test or manufacturer's performance manual data must be used, where available. Notes D interval of at least 900 m (3,000 ft). Landing. INFORMATION Simulator Level Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS 32023 ER20MY16.006</GPH> mstockstill on DSK3G9T082PROD with RULES2 32024 VerDate Sep<11>2014 Test Jkt 238001 Entry Number PO 00000 l.e.4. Title Stopping distance, wheel brakes, icy runway. ±61 m (200ft) or ±10% of distance. Flight Conditions Landing. Test Details Engineering data, based on dry runway flight test stopping distance and the effects of contaminated runway braking coefficients, are an acceptable alternative. Either flight test or manufacturer's performance manual data must be used, where available. Frm 00010 Fmt 4701 c X X Notes D X A B Engineering data, based on dry runway flight test stopping distance and the effects of contaminated runway braking coefficients, are an acceptable alternative. Sfmt 4725 l.f. Engines. l.f.l. Acceleration. ±10% Ti or ±0.25 s; and ±10% Tt or ±0.25 s. Approach or landing Total response is the incremental change in the critical engine parameter from idle power to goaround power. X X See Appendix F ofthis part for definitions ofTi. and T,. l.f.2. Deceleration. ±10% Ti or ±0.25 s; and Ground Total response is the incremental change in the critical engine parameter from maximum takeoff power to idle power. X X X X See Appendix F of this part for definitions ofTi. and T,. ±10% Tt or ±0.25 s. X E:\FR\FM\20MYR2.SGM 2. Handling Qualities. 2.a. 20MYR2 2.a.l.a. ER20MY16.007</GPH> Tolerance INFORMATION Simulator Level Static Control Tests. Note.l - Testing ofposition versus force is not applicable ifforces are generated solely by use of airplane hardware in the FSTD. Note 2- Pitch, roll and yaw controller position versus force or time should be measured at the control. An alternative method in lieu of external test fixtures at the flight controls would be to have recording and measuring instrumentation built into the FSTD. The force and position data from this instrumentation could be directly recorded and matched to the airplane data. Provided the instrumentation was verified by using external measuring equipment while conducting the static control checks, or equivalent means, and that evidence of the satisfactory comparison is included in the MQTG, the instrumentation could be usedfor both initial and recurrent evaluations for the measurement of all required control checks. Verification of the instrumentation by using external measuring equipment should be repeated if major modifications and/or repairs are made to the control loading system. Such a permanent installation could be used without any time being lost for the installation of external devices. Static and dynamic flight control tests should be accomplished at the same feel or impact pressures as the validation data where applicable. Note 3 - FSTD static control testing from the second set ofpilot controls is only required if both sets of controls are not mechanically interconnected on the FSTD. A rationale is required from the data provider if a single set of data is applicable to both sides. lf controls are mechanically interconnected in the FSTD, a single set of tests is su.t 1cient. Record results for an uninterrupted control sweep Pitch controller Ground. ±0.9 daN (2 lbt) X X X X Test results should be position versus force to the stops. validated with in-flight data breakout. and surface position from tests such as Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title calibration. Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D longitudinal static stability, stalls, etc. ±2.2 daN (Slbt) or ±10% of force. PO 00000 ±2° elevator angle. (Reserved) 2.a.2.a. Roll controller position versus force and surface position calibration. Frm 00011 2.a.l.b. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM Ground. Record results for an uninterrupted control sweep to the stops. X X X X Test results should be validated with in-flight data from tests such as engine-out trims, steady state side-slips, etc. Ground. Record results for an uninterrupted control sweep to the stops. X X X X Test results should be validated with in-flight data from tests such as engine-out trims, steady state side-slips, etc. Ground. Record results of an uninterrupted control sweep to X the stops. X X X ±2°NWA. Ground. Record results of an uninterrupted control sweep to X the stops. X X X ±0.5° trim angle. Ground. X X X X ±0.9 daN (2 lbt) breakout. ±1.3 daN (3 lbt) or ±10% of force. ±2° aileron angle. ±3 o spoiler angle. 2.a.2.b. (Reserved) 2.a.3.a. Rudder pedal position versus force and surface position calibration. ±2.2 daN (Slbt) breakout. ±2.2 daN (Slbt) or ±10% of force. ±2° rudder angle. (Reserved) 2.a.4. Nosewheel Steering Controller Force and Position Calibration. 20MYR2 2.a.3.b. ±0.9 daN (2 lbt) breakout. ±1.3 daN (3 lbt) or ±10% of force. ±2°NWA. 2.a.5. 2.a.6. Rudder Pedal Steering Calibration. Pitch Trim Indicator Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS The purpose of the test is to 32025 ER20MY16.008</GPH> mstockstill on DSK3G9T082PROD with RULES2 32026 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Test Details A B c PO 00000 2.a.7. Pitch Trim Rate. Notes D vs. Surface Position Calibration. compare FSTD surface position and indicator against the flight control model computed value. ±10% of trim rate Cis) or Ground and approach. Trim rate to be checked at pilot primary induced trim rate (ground) and autopilot or pilot primary trim rate in-flight at go-around flight conditions. Frm 00012 X X X X X X X X ±0.1 °/s trim rate. 2.a.8. Fmt 4701 Alignment of cockpit throttle lever versus selected engine parameter. When matching engine parameters: Ground. ±5° ofTLA. Sfmt 4725 E:\FR\FM\20MYR2.SGM ±3% Nl or ±.03 EPR or ±3% torque, or equivalent. 2.a.9. 20MYR2 Brake pedal position versus force and brake system pressure calibration. Stick Pusher System Force Calibration (if applicable) Where the levers do not have angular travel, a tolerance of ±2 em (±0.8 in) applies. ±2.2 daN (5lbt) or ±10% of force. Ground. Relate the hydraulic system pressure to pedal position in a ground static test. Data from a test airplane or engineering test bench are acceptable, provided the correct engine controller (both hardware and software) is used. In the case of propeller-driven airplanes, if an additional lever, usually referred to as the propeller lever, is present, it should also be checked. This test may be a series of snapshot tests. X X X X FFS computer output results may be used to show compliance. X X Aircraft manufacturer design data may be utilized as validation data as determined Both left and right pedals must be checked. ±1.0 MPa (150 psi) or ±10% of brake system pressure. ±10% or ±5 lb (2.2 daN)) Stick/Column force For CCA, representative flight test conditions must be used. Simultaneous recording for all engines. The tolerances apply against airplane data. For airplanes with throttle detents, all detents to be presented and at least one position between detents/ endpoints (where practical). For airplanes without detents, end points and at least three other positions are to be presented. When matching detents: 2.a.10 ER20MY16.009</GPH> Flight Conditions INFORMATION Simulator Level Ground or Flight Test is intended to validate the stick/column transient forces as a result of a stick pusher system activation. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Fli2ht Simulator (FFS) Ob.iective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D acceptable by the NSPM. PO 00000 This test may be conducted in an on-ground condition through stimulation of the stall protection system in a manner that generates a stick pusher response that is representative of an in-flight condition. Test requirement may be met through column force validation testing in conjunction with the Stall Characteristics test (2.c.8.a.). Frm 00013 This test is required only for FSTDs qualified to conduct full stall training tasks. Fmt 4701 2.b. Sfmt 4725 2.b.l. Dynamic Control Tests. E:\FR\FM\20MYR2.SGM Note.- Tests 2.b.l, 2.b.2 and 2.b.3 are not applicable for FSTDs where the control forces are completely generated within the airplane controller unit installed in the FSTD. Power setting may be that required for level flight unless otherwise specified. See parawaph 4 of this attachment.. Pitch Control. Takeoff, Cruise, and Data must be for normal control displacements in For underdamped Landing. systems: both directions (approximately 25% to 50% of full throw or approximately 25% to 50% of T(Po) ±10% ofP0 or maximum allowable pitch controller deflection for flight conditions limited by the maneuvering ±0.05 s. load envelope). T(P 1) ±20% ofP 1 or ±0.05 s. Tolerances apply against the absolute values of each period (considered independently). T(P2) ±30% ofP2 or ±0.05 s. 20MYR2 T(Pn) ±lO*(n+ 1)% ofPn or ±0.05 s. T(An) ±10% of Amax, where Amax is the largest amplitude or ±0.5% of the total control travel (stop to stop). X X n =the sequential period of a full oscillation. Refer to paragraph 4 of this Attachment. For overdamped and critically damped systems, see Figure A2B of Appendix A for an illustration of the reference measurement. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS 32027 ER20MY16.010</GPH> mstockstill on DSK3G9T082PROD with RULES2 32028 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Test Details A B c X X Notes D PO 00000 T(A.i) ±5% of A.!= residual band or ±0.5% of the maximum control travel = residual band. Frm 00014 ±I significant overshoots (minimum of 1 significant overshoot). Steady state position within residual band. Fmt 4701 Sfmt 4725 Note 1.- Tolerances should not be applied on period or amplitude after the last significant overshoot. E:\FR\FM\20MYR2.SGM Note2.Oscillations within the residual band are not considered significant and are not subject to tolerances. 20MYR2 2.b.2. ER20MY16.011</GPH> Flight Conditions INFORMATION Simulator Level Roll Control. For overdamped and critically damped systems only, the following tolerance applies: T(Po) ±10% of Po or ±0.05 s. Same as 2.b.l. Takeoff, Cruise, and Landing. Data must be for normal control displacement (approximately 25% to 50% of full throw or approximately 25% to 50% of maximum Refer to paragraph 4 of this Attachment. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Fli2ht Simulator (FFS) Ob.iective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c allowable roll controller deflection for flight conditions limited by the maneuvering load envelope). PO 00000 2.b.3. Yaw Control. Same as 2.b.l. Takeoff, Cruise, and Landing. Data must be for normal control displacement (approximately 25% to 50% of full throw). X Notes D X For overdamped and critically damped systems, see Figure A2B of Appendix A for an illustration of the reference measurement. Refer to paragraph 4 of this Attachment. Frm 00015 Fmt 4701 For overdamped and critically damped systems, see Figure A2B of Appendix A for an illustration of the reference measurement. 2.b.4. Small Control Inputs -Pitch. Sfmt 4725 ±0.15°/s body pitch rate or ±20% of peak body pitch rate applied throughout the time history. Approach or Landing. Control inputs must be typical of minor corrections made while established on an ILS approach (approximately 0.5 to 2°/S pitch rate). X X X Test in both directions. E:\FR\FM\20MYR2.SGM 20MYR2 X Show time history data from 5 s before until at least 5 s after initiation of control input. If a single test is used to demonstrate both directions, there must be a minimum of 5 s before control reversal to the opposite direction. 2.b.5. Small Control Inputs -Roll. ±0.15°/s body roll rate or ±20% of peak body roll rate applied throughout the time history. Approach or landing. CCA: Test in normal and non-normal control state. Control inputs must be typical of minor corrections made while established on an ILS approach (approximately 0.5 to 2°/S roll rate). Test in one direction. For airplanes that exhibit non-symmetrical behavior, test in both directions. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS Show time history data from 5 s before until at least 5 s after initiation of control input. 32029 ER20MY16.012</GPH> mstockstill on DSK3G9T082PROD with RULES2 32030 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details PO 00000 Frm 00016 2.b.6. Small Control Inputs -Yaw. Fmt 4701 ±0.15°/s body yaw rate or ±20% of peak body yaw rate applied throughout the time history. Approach or landing. 20MYR2 D CCA: Test in normal and non-normal control state. Control inputs must be typical of minor corrections made while established on an ILS approach (approximately 0.5 to 2°/s yaw rate). X X X Test in both directions. Show time history data from 5 s before until at least 5 s after initiation of control input. Sfmt 4725 E:\FR\FM\20MYR2.SGM c X A B If a single test is used to demonstrate both directions, there must be a minimum of 5 s before control reversal to the opposite direction. If a single test is used to demonstrate both directions, there must be a minimum of 5 s before control reversal to the opposite direction. CCA: Test in normal and non-normal control state. 2.c. Longitudinal Control Tests. Power setting is that required for level flight unless otherwise specified. 2.c.l. Power Change Dynamics. ±3 kt airspeed. ±30m (100ft) altitude. ±1.5° or ±20% of pitch angle. Approach. Power change from thrust for approach or level flight to maximum continuous or go-around power. Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the power change to the completion of the power change + 15 s. ER20MY16.013</GPH> INFORMATION Simulator Level X X Notes Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.c.2. Tolerance Title PO 00000 Flap/Slat Change Dynamics. ±3 kt airspeed. ±30 m (100ft) altitude. Flight Conditions Takeoff through initial flap retraction, and approach to landing. Frm 00017 ±1.5° or ±20% of pitch angle. 2.c.3. Spoiler/Speedbrake Change Dynamics. ±3 kt airspeed. Cruise. Fmt 4701 Sfmt 4725 ±1.5° or ±20% of pitch angle. E:\FR\FM\20MYR2.SGM Gear Change Dynamics. ±3 kt airspeed. Takeoff (retraction), and Approach (extension). ±1.5° or ±20% of pitch angle. 20MYR2 Longitudinal Trim. ±I o elevator angle. ±0. 5o stabilizer or trim surface angle. ±I o pitch angle. c D X X X X Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the configuration change to the completion of the configuration change+ 15 s. X X X X X X X X X X X X Results required for both extension and retraction. ±30 m (100ft) altitude. 2.c.5. CCA: Test in normal and non-normal control mode Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the reconfiguration change to the completion of the reconfiguration change+ 15 s. A B CCA: Test in normal and non-normal control mode ±30 m (100ft) altitude. 2.c.4. Test Details INFORMATION Simulator Level Cruise, Approach, and Landing. CCA: Test in normal and non-normal control mode Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the configuration change to the completion of the configuration change + 15 s. CCA: Test in normal and non-normal control mode Steady-state wings level trim with thrust for level flight. This test may be a series of snapshot tests. CCA: Test in normal or non-normal control mode, as applicable. Notes Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS ±5% of net thrust or 32031 ER20MY16.014</GPH> mstockstill on DSK3G9T082PROD with RULES2 32032 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.c.6. Tolerance Title PO 00000 Longitudinal Maneuvering Stability (Stick Force/g). equivalent. ±2.2 daN (5lbt) or ±10% of pitch controller force. Flight Conditions Cruise, Approach, and Landing. Continuous time history data or a series of snapshot tests may be used. Simulator Level ±I o or ±10% of the change of elevator angle. Frm 00018 c X X X X X X X X X X Notes D Force tolerance not applicable if forces are generated solely by the use of airplane hardware intheFSTD. Fmt 4701 Alternative method applies to airplanes which do not exhibit stick-force-per-g characteristics. Sfmt 4725 E:\FR\FM\20MYR2.SGM A B Test up to approximately 30° of roll angle for approach and landing configurations. Test up to approximately 45° of roll angle for the cruise configuration. Alternative method: 2.c.7. Longitudinal Static Stability. ±2.2 daN (5lbt) or ±10% of pitch controller force. Approach. CCA: Test in normal or non-normal control mode Data for at least two speeds above and two speeds below trim speed. The speed range must be sufficient to demonstrate stick force versus speed characteristics. Alternative method: This test may be a series of snapshot tests. ±I o or ±10% of the change of elevator angle. 20MYR2 Force tolerance is not applicable if forces are generated solely by the use of airplane hardware intheFSTD. Alternative method applies to airplanes which do not exhibit speed stability characteristics. 2.c.8.a ER20MY16.015</GPH> Test Details INFORMATION Stall Characteristics ±3 kt airspeed for stall Second Segment Climb, CCA: Test in normal or non-normal control mode, as applicable. Each of the following stall entries must be Buffet threshold of perception Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title warning and stall speeds. PO 00000 Frm 00019 ±2.0° angle of attack for buffet threshold of perception and initial buffet based upon Nz component. Fmt 4701 Control inputs must be plotted and demonstrate correct trend and magnitude. Sfmt 4725 Approach to stall: ±2.0° pitch angle; ±2.0° angle of attack; and ±2.0° bank angle E:\FR\FM\20MYR2.SGM Stall warning up to stall: ±2.0° pitch angle; ±2.0° angle of attack; and Correct trend and magnitude for roll rate and yaw rate. 20MYR2 Stall Break and Recovery: SOC Required (see Attachment 7) Additionally, for those simulators with reversible flight control systems or equipped with stick pusher Flight Conditions Test Details High Altitude Cruise (Near Performance Limited Condition), and Approach or Landing demonstrated in at least one of the three flight conditions: Stall entry at wings level (I g) Stall entry in turning flight of at least 25° bank angle (accelerated stall) Stall entry in a power-on condition (required only for propeller driven aircraft) . . . The cruise flight condition must be conducted in a flaps-up (clean) configuration. The second segment climb flight condition must use a different flap setting than the approach or landing flight condition. Record the stall warning signal and initial buffet, if applicable. Time history data must be recorded for full stall through recovery to normal flight. The stall warning signal must occur in the proper relation to buffet/stall. FSTDs of airplanes exhibiting a sudden pitch attitude change or "g break" must demonstrate this characteristic. FSTDs of airplanes exhibiting a roll off or loss of roll control authority must demonstrate this characteristic. Numerical tolerances are not applicable past the stall angle of attack, but must demonstrate correct trend through recovery. See Attachment 7 for additional requirements and information concerning data sources and required angle of attack ranges. CCA: Test in normal and non-normal control states. For CCA aircraft with stall envelope protection systems, the normal mode testing is only required to an angle of attack range necessary to demonstrate the correct operation of the system. These tests may be used to satisfy the required INFORMATION Simulator Level A B c Notes D should be based on 0.03 g peak to peak normal acceleration above the background noise at the pilot seat. Initial buffet to be based on normal acceleration at the pilot seat with a larger peak to peak value relative to buffet threshold of perception (some airframe manufacturers have used 0.1 g peak to peak). Demonstrate correct trend in growth of buffet amplitude from initial buffet to stall speed for normal and lateral acceleration. The FSTD sponsor/FSTD manufacturer may limit maximum buffet based on motion platform capability/limitations or other simulator system limitations. Tests may be conducted at centers of gravity and weights typically required for airplane certification stall testing. This test is required only for FSTDs qualified to conduct full stall training tasks. In instances where flight test validation data is limited due to safety of flight considerations, engineering simulator validation data may Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32033 ER20MY16.016</GPH> mstockstill on DSK3G9T082PROD with RULES2 32034 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions PO 00000 systems: ±10% or ±5 lb (2.2 daN)) Stick/Column force (prior to the stall angle of attack). Test Details INFORMATION Simulator Level A B c (angle of attack) flight maneuver and envelope protection tests (test 2.h.6.). Non-normal control states must be tested through stall identification and recovery. be used in lieu of flight test validation data for angles of attack that exceed the activation of a stall protection system or stick pusher system. Where approved engineering simulation validation is used, the reduced engineering tolerances (as defined in paragraph 11 of this appendix) do not apply. Tests may be conducted at centers of gravity and weights typically required for airplane certification stall testing. Frm 00020 Fmt 4701 2.c.8.b f'\pproach to Stall ~haracteristics Sfmt 4725 ±2.0° angle of attack for initial buffet. Second Segment Climb, High Altitude Cruise (Near Performance Limited Condition), and Approach or Landing E:\FR\FM\20MYR2.SGM Control displacements and flight control surfaces must be plotted and demonstrate correct trend and magnitude. 20MYR2 Additionally, for those simulators with reversible flight control systems: ±10% or ±5 lb (2.2 daN)) Stick/Column force Phugoid Dynamics. ±10% of period. Each of the following stall entries must be demonstrated in at least one of the three flight conditions: • Approach to stall entry at wings level (!g) • Approach to stall entry in turning flight of at least 25° bank angle (accelerated stall) • Approach to stall entry in a power-on condition (required only for propeller driven aircraft) X X Tolerances on stall buffet are not applicable where the first indication of the stall is the activation of the stall warning system (i.e. stick shaker). The cruise flight condition must be conducted in a flaps-up (clean) configuration. The second segment climb flight condition must use a different flap setting than the approach or landing flight condition. ±2.0° pitch angle; ±2.0° angle of attack; and ±2.0° bank angle 2.c.9. ER20MY16.017</GPH> ±3 kt airspeed for stall warning speeds. Cruise. CCA: Test in Normal and Non-normal control states. For CCA aircraft with stall envelope protection systems, the normal mode testing is only required to an angle of attack range necessary to demonstrate the correct operation of the system. These tests may be used to satisfy the required (angle of attack) flight maneuver and envelope protection tests (test 2.h.6.). Test must include three full cycles or that Notes D X X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions PO 00000 Short Period Dynamics. ±1.5° pitch angle or ±2°/s pitch rate. Frm 00021 Fmt 4701 c X X X X X X X X X X X X X X X X Notes D Cruise. CCA: Test in non-normal control mode. CCA: Test in normal and non-normal control mode. ±0.1 g normal acceleration 2.c.ll. 2.d. (Reserved) Lateral Directional Tests. Power setting is that required for level flight unless otherwise specified. 2.d.l. Sfmt 4725 E:\FR\FM\20MYR2.SGM A B necessary to determine time to one half or double amplitude, whichever is less. ±10% of time to one half or double amplitude or ±0.02 of damping ratio. 2.c.10 Test Details INFORMATION Simulator Level 2.d.2. Minimum control speed, air (II mea) or landing (IImel), per applicable airworthiness requirement or low speed engineinoperative handling characteristics in the air. Roll Response (Rate). ±3 kt airspeed. Takeoff or Landing (whichever is most critical in the airplane). Time history or snapshot data may be used. 20MYR2 Step input of flight deck roll controller. Minimum speed may be defined by a performance or control limit which prevents demonstration of v mea or v mel in the conventional manner. CCA: Test in normal or non-normal control state, as applicable. ±2°/s or ±10% of roll rate. Cruise, and Approach or Landing. For airplanes with reversible flight control systems: 2.d.3. Takeoff thrust must be set on the operating engine(s). ±1.3 daN (3 lbt) or ±10% of wheel force. ±2° or ±10% of roll angle. Test with normal roll control displacement (approximately one-third of maximum roll controller travel). This test may be combined with step input of flight deck roll controller test 2.d.3. Approach or Landing. This test may be combined with roll response (rate) test 2.d.2. With wings level, apply a step roll control input using approximately one-third of Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32035 ER20MY16.018</GPH> mstockstill on DSK3G9T082PROD with RULES2 32036 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c CCA: Test in normal and non-normal control mode the roll controller travel. When reaching approximately 20° to 30° of bank, abruptly return the roll controller to neutral and allow approximately 10 seconds of airplane free response. PO 00000 Frm 00022 2.d.4. Spiral Stability. Correct trend and ±2° or ±10% of roll angle in 20 s. Cruise, and Approach or Landing. Fmt 4701 Sfmt 4725 Engine Inoperative Trim. E:\FR\FM\20MYR2.SGM ±I o rudder angle or ±I o tab angle or equivalent rudder pedal. X X X X X X X X Test for both directions. As an alternative test, show lateral control required to maintain a steady tum with a roll angle of approximately 30°. If alternate test is used: correct trend and ±2 o aileron angle. 2.d.5. Airplane data averaged from multiple tests may be used. Second Segment Climb, and Approach or Landing. CCA: Test in non-normal control mode. This test may consist of snapshot tests. Test should be performed in a manner similar to that for which a pilot is trained to trim an engine failure condition. ±2° side-slip angle. 2nd segment climb test should be at takeoff thrust. Approach or landing test should be at thrust for level flight. 20MYR2 2.d.6. Rudder Response. ±2°/s or ±10% of yaw rate. Approach or Landing. Test with stability augmentation on and off. X X X X X X X Test with a step input at approximately 25% of full rudder pedal throw. 2.d.7. ER20MY16.019</GPH> Notes D Dutch Roll ±0.5 s or ±I 0% of Cruise, and Approach or CCA: Test in normal and non-normal control mode Test for at least six cycles with stability Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title period. Flight Conditions Landing. PO 00000 ±10% of time to one half or double amplitude or ±. 02 of damping ratio. Test Details INFORMATION Simulator Level Frm 00023 Fmt 4701 A B c D X X X augmentation off. CCA: Test in non-normal control mode. ±1 s or ±20% of time difference between peaks of roll angle and side-slip angle. 2.d.8. Steady State Sideslip. For a given rudder position: Sfmt 4725 ±2° roll angle; ±1 a side-slip angle; E:\FR\FM\20MYR2.SGM ±2° or ±10% of aileron angle; and ±5° or ±10% of spoiler or equivalent roll controller position or force. 20MYR2 For airplanes with reversible flight control systems: ±1.3 daN (3 lbt) or ±10% ofwheel force. Approach or Landing. This test may be a series of snapshot tests using at least two rudder positions (in each direction for propeller-driven airplanes), one of which must be near maximum allowable rudder. X Notes Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS ±2.2 daN (5 lbt) or 32037 ER20MY16.020</GPH> mstockstill on DSK3G9T082PROD with RULES2 32038 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level PO 00000 A B c X X X X X ±10% of rudder pedal force. 2.e. Landings. 2.e.l. Normal Landing. ±3 kt airspeed. Landing. Test from a minimum of61 m (200ft) AGL to nosewheel touchdown. Frm 00024 ±1.5° pitch angle. CCA: Test in normal and ±1.5° AOA. Fmt 4701 Sfmt 4725 For airplanes with reversible flight control systems: E:\FR\FM\20MYR2.SGM ±2.2 daN (5lbt) or ±10% of column force. ±3 kt airspeed. non-normal control mode, if applicable. ±3m (10ft) or ±10% of height. 2.e.2. Minimum Flap Landing. ±1.5° pitch angle. Minimum Certified Landing Flap Configuration. Test from a minimum of 61 m (200ft) AGL to nosewheel touchdown. Test at near maximum certificated landing weight. ±1.5° AOA. 20MYR2 ±3m (10ft) or ±10% of height. For airplanes with reversible flight control systems: ±2.2 daN (5lbt) or ±10% of column force. ER20MY16.021</GPH> Notes D Two tests should be shown, including two normal landing flaps (if applicable) one of which should be near maximum certificated landing mass, the other at light or medium mass. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.e.3. Tolerance Title Crosswind Landing. ±3 kt airspeed. Flight Conditions Landing. ±1.5° pitch angle. PO 00000 ±1.5° AOA. Test Details Test from a minimum of 61 m (200 ft) AGL to a 50% decrease in main landing gear touchdown speed. INFORMATION Simulator Level X X X X X X ±2° side-slip angle. ±3° heading angle. Sfmt 4725 For airplanes with reversible flight control systems: E:\FR\FM\20MYR2.SGM ±2.2 daN (5lbt) or ±10% of column force. ±1.3 daN (3 lbt) or ±10% ofwheel force. 20MYR2 2.e.4. One Engine Inoperative Landing. ±2.2 daN (5lbt) or ±10% of rudder pedal force. ±3 kt airspeed. ±1.5° pitch angle. Landing. Test from a minimum of61 m (200ft) AGL to a 50% decrease in main landing gear touchdown speed. Notes D Wind components must be provided as headwind and crosswind values with respect to the runway. ±2° roll angle. Fmt 4701 c Test data is required, including wind profile, for a crosswind component of at least 60% of airplane performance data value measured at 10m (33 ft) above the runway. ±3m (10ft) or ±10% of height. Frm 00025 A B In those situations where a maximum crosswind or a maximum demonstrated crosswind is not known, contact the NSPM. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS ±1.5° AOA. 32039 ER20MY16.022</GPH> mstockstill on DSK3G9T082PROD with RULES2 32040 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details Simulator Level 2.e.5. Autopilot landing (if applicable). ±3° heading angle. ±1.5 m (5 ft) flare height. Landing. X X Normal all-engine autopilot go-around must be demonstrated (if applicable) at medium weight. X X X Engine inoperative go-around required near maximum certificated landing weight with critical engine inoperative. X X X If autopilot provides roll-out guidance, record lateral deviation from touchdown to a 50% decrease in main landing gear touchdown speed. ±0.5 s or± 10% ofTf. Time of autopilot flare mode engage and main gear touchdown must be noted. ±0.7 m/s (140ft/min) rate of descent at touchdown. Sfmt 4725 20MYR2 X Notes D ±2° side-slip angle. Fmt 4701 E:\FR\FM\20MYR2.SGM c ±2° roll angle. PO 00000 Frm 00026 A B ±3m (10ft) or ±10% of height. 2.e.6. All-engine autopilot go-around. ±3m (10ft) lateral deviation during rollout. ±3 kt airspeed. As per airplane performance data. ±1.5° pitch angle. 2.e.7. One engine inoperative go around. ±1.5° AOA. ±3 kt airspeed. ±1.5° pitch angle. ±1.5° AOA. As per airplane performance data. Provide one test with autopilot (if applicable) and one without autopilot. ±2° roll angle. ±2° side-slip angle. ER20MY16.023</GPH> INFORMATION CCA: Non-autopilot test to be conducted in nonnormal mode. See Appendix F of this part for definition of Tr. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 PO 00000 Frm 00027 Entry Title Number 2.e.8. Directional control (rudder effectiveness) with symmetric reverse thrust. 2.e.9. Directional control (rudder effectiveness) with asymmetric reverse thrust. 2.f. Tolerance ±5 kt airspeed. Flight Conditions A B c Notes D X X X Landing. With full reverse thrust on the operating engine(s), maintain heading with rudder pedal input until maximum rudder pedal input or thrust reverser minimum operation speed is reached. X X X Landing. A rationale must be provided with justification of results. X X X See paragraph 5 of this Attachment for additional information. X X See Attachment 5 of this appendix for information related to Level A and B simulators. ±3° heading angle. ±1 o elevator angle. ±0.5° stabilizer angle. ±5% of net thrust or equivalent. Sfmt 4725 E:\FR\FM\20MYR2.SGM Apply rudder pedal input in both directions using full reverse thrust until reaching full thrust reverser minimum operating speed. Ground Effect. Test to demonstrate Ground Effect. Fmt 4701 Landing. ±2°/s yaw rate. ±5 kt airspeed. Test Details INFORMATION Simulator Level CCA: Test in normal or non-normal control mode, as applicable. ±1° AOA. ±1.5 m (5 ft) or ±10% of height. ±3 kt airspeed. ±1 o pitch angle. Wind shear. 2.h. Four tests, two See Attachment 5 of this Takeoff and Landing. appendix. takeoff and two landing, with one of each conducted in still air and the other with windshear active to demonstrate windshear models. Flight Maneuver and Envelope Protection Functions. 20MYR2 2.g. Requires windshear models that provide training in the specific skills needed to recognize windshear phenomena and to execute recovery procedures. See Attachment 5 of this appendix for tests, tolerances, and procedures. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Fli2ht Simulator (FFS) Ob.iective Tests QPS REQUIREMENTS 32041 ER20MY16.024</GPH> mstockstill on DSK3G9T082PROD with RULES2 32042 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details PO 00000 Frm 00028 2.h.l. Note. - The requirements of 2.h are only applicable to computer-controlled airplanes. Time history results of response to control inputs during entry into each envelope protection jUnction (i.e. with normal and degraded control states if their jUnction is different) are required. Set thrust as required to reach the envelope protection jUnction. ±5 kt airspeed. Cruise. Overspeed. 2.h.2. Minimum Speed. 2.h.3. Load Factor. ±O.lg normal load factor Takeoff, Cruise, and Approach or Landing. Takeoff, Cruise. 2.h.4. Pitch Angle. ±1.5° pitch angle Cruise, Approach. ±3 kt airspeed. Fmt 4701 2.h.5. Bank Angle. ±2° or ±10% bank angle Angle of Attack. ±1.5° angle of attack Sfmt 4725 2.i. c Notes D X X X X X X X X X X X X X X X Engine and Airframe Icing Effects Engine and Airframe Icing Effects Demonstration (High Angle of Attack) A B X X X X Second Segment Climb, and Approach or Landing. 2.i. Simulator Level X Approach. 2.h.6. INFORMATION Takeoff or Approach or Landing E:\FR\FM\20MYR2.SGM [One flight conditiontwo tests (ice on and oft)] Time history of a full stall and initiation of the recovery. Tests are intended to demonstrate representative aerodynamic effects caused by inflight ice accretion. Flight test validation data is not required. Two tests are required to demonstrate engine and airframe icing effects. One test will demonstrate the FSTDs baseline performance without ice accretion, and the second test will demonstrate the aerodynamic effects of ice accretion relative to the baseline test. 20MYR2 The test must utilize the icing model(s) as described in the required Statement of Compliance in Table AlA, Section 2.j. Test must include rationale that describes the icing effects being demonstrated. Icing effects may include, but are not limited to, the following effects as applicable to the particular airplane type: • Decrease in stall angle of attack • Changes in pitching moment • Decrease in control effectiveness Tests will be evaluated for representative effects on relevant aerodynamic and other parameters such as angle of attack, control inputs, and thrust/power settings. Plotted parameters must include: • Altitude Airspeed Normal acceleration • Engine power • Angle of attack • Pitch attitude • Bank angle • Flight control inputs • Stall warning and stall buffet onset • • Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 ER20MY16.025</GPH> Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D PO 00000 • Changes in control forces • Increase in drag • Change in stall buffet characteristics and threshold of perception • Engine effects (power reduction/variation, vibration, etc. where expected to be present on the aircraft in the ice accretion scenario being tested) Frm 00029 3. Motion System. 3.a. Frequency response. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM As specified by the sponsor for FSTD qualification. 3.c 3.d. Appropriate test to demonstrate required frequency response. X X X X See paragraph 6 of this Attachment. As specified by the sponsor for FSTD qualification. 3.b. Not applicable. Not applicable. Appropriate test to demonstrate required smooth tum-around. X X X X See paragraph 6 of this Attachment. X X X X Refer to Attachment 3 of this Appendix on subjective testing. X X X X Ensure that motion system hardware and software (in normal FSTD operating mode) continue to perform as originally qualified. Performance changes from the original baseline can be readily identified with this information. Turn-around check. Motion effects. Motion system repeatability. Motion system repeatability ±0.05 g actual platform linear accelerations. None. 20MYR2 See paragraph 6.c. of this Attachment. 3.e. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS Motion cueing fidelity 32043 ER20MY16.026</GPH> mstockstill on DSK3G9T082PROD with RULES2 32044 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 3.e.l. Tolerance Title Motion cueing fidelity- Frequencydomain criterion. As specified by the FSTD manufacturer for initial qualification. Flight Conditions Ground and flight. Notes PO 00000 Frm 00030 c D X X Testing may be accomplished by the FSTD manufacturer and results provided as a statement of compliance. X For the motion system as applied during training, record the combined modulus and phase of the motion cueing algorithm and motion platform over the frequency range appropriate to the characteristics of the simulated aircraft. A B The recorded test results for characteristic buffets should allow the comparison of relative amplitude versus frequency. This test is only required for initial FS TD qualification. Reserved 3.f Characteristic motion vibrations. The following tests with recorded results and an SOC are required for characteristic motion vibrations, which can be sensed at the flight deck where applicable by airplane type. Thrust effect with brakes set. Fmt 4701 3.e.2. Sfmt 4725 E:\FR\FM\20MYR2.SGM 3.f.l. 20MYR2 3.f.2. ER20MY16.027</GPH> Test Details INFORMATION Simulator Level Buffet with landing gear extended. None. Ground and flight. See also paragraph 6.e. of this Attachment. The FSTD test results must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" being present within ± 2 Hz of the airplane data. The FSTD test results must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" Ground. Test must be conducted at maximum possible thrust with brakes set. X Flight. Test condition must be for a normal operational speed and not at the gear limiting speed. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D being present within ± 2 Hz of the airplane data. Buffet with flaps extended. 3.f.4. Buffet with speedbrakes deployed. 3.f.5. Stall buffet PO 00000 3.f.3. Frm 00031 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 3.f.6. Buffet at high The FSTD test results must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" being present within ± 2 Hz of the airplane data. The FSTD test results must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" being present within ± 2 Hz of the airplane data. The FSTD test results must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" being present within ± 2 Hz of the airplane data. The FSTD test results Flight. Test condition must be at a normal operational speed and not at the flap limiting speed. X Flight. Test condition must be at a typical speed for a representative buffet. X Cruise (High Altitude), Second Segment Climb, and Approach or Landing Tests must be conducted for an angle of attack range between the buffet threshold of perception to the pilot and the stall angle of attack. Post stall characteristics are not required. Flight. X X X If stabilized flight data between buffet threshold of perception and the stall angle of attack are not available, PSD analysis should be conducted for a time span between initial buffet and the stall angle of attack. Test required only for FSTDs qualified for full stall training tasks or for those aircraft which exhibit stall buffet before the activation of the stall warning system. Test condition should be for Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32045 ER20MY16.028</GPH> mstockstill on DSK3G9T082PROD with RULES2 32046 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number Title airspeeds or high Mach. PO 00000 Frm 00032 3.f.7. In-flight vibrations for propeller driven airplanes. Fmt 4701 Sfmt 4725 must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" being present within ± 2 Hz of the airplane data. The FSTD test results must exhibit the overall appearance and trends of the airplane data, with at least three (3) of the predominant frequency "spikes" being present within ± 2 Hz of the airplane data. Flight Conditions Test Details INFORMATION Simulator Level A B Notes D high-speed maneuver buffet/wind-up-tum or alternatively Mach buffet. Flight (clean configuration). E:\FR\FM\20MYR2.SGM X Test should be conducted to be representative of in-flight vibrations for propellerdriven airplanes. X Field of view should be measured using a visual test pattern filling the entire visual scene (all channels) consisting of a matrix of black and white so squares. 4. Visual System. 4.a. Visual scene quality 4.a.l. Continuous collimated crosscockpit visual field of view. Cross-cockpit, collimated visual display providing each pilot with a minimum of 176° horizontal and 36° vertical continuous field of view. Not applicable. Required as part ofMQTG but not required as part of continuing evaluations. X 20MYR2 Continuous collimated crosscockpit visual field of view. ER20MY16.029</GPH> c Continuous collimated field-of-view providing at least 45° horizontal and 30° vertical fieldof-view for each pilot seat. Both pilot seat Not applicable. Required as part ofMQTG but not required as part of continuing evaluations. X X Installed alignment should be confirmed in an SOC (this would generally consist of results from acceptance testing). A vertical field-of-view of 30° may be insufficient to meet visual ground segment requirements. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number PO 00000 4.a.2. Tolerance Title System geometry Frm 00033 visual systems must be operable simultaneously. so even angular spacing within ±I oas measured from either pilot eye point and within l.S 0 for adjacent squares. Flight Conditions Not applicable. Test Details The angular spacing of any chosen so square and the relative spacing of adjacent squares must be within the stated tolerances. INFORMATION Simulator Level A B c X X X X Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 4.a.3 Surface resolution (object detection). Not greater than 2 arc minutes. Not applicable. An SOC is required and must include the relevant calculations and an explanation of those calculations. 20MYR2 This requirement is applicable to any level of simulator equipped with a daylight visual system. Notes D X X The purpose of this test is to evaluate local linearity of the displayed image at either pilot eye point. System geometry should be measured using a visual test pattern filling the entire visual scene (all channels) with a matrix of black and white so squares with light points at the intersections. For continuing qualification testing, the use of an optical checking device is encouraged. This device should typically consist of a hand-held go/no go gauge to check that the relative positioning is maintained. Resolution will be demonstrated by a test of objects shown to occupy the required visual angle in each visual display used on a scene from the pilot's eyepoint. The object will subtend 2 arc minutes to the eye. This may be demonstrated using threshold bars for a horizontal test. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32047 ER20MY16.030</GPH> mstockstill on DSK3G9T082PROD with RULES2 32048 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 4.a.4 Tolerance Title Light point size. PO 00000 Not greater than 5 arc minutes. Flight Conditions Not applicable. Test Details An SOC is required and must include the relevant calculations and an explanation of those calculations. INFORMATION Simulator Level A B c X Notes D X Frm 00034 This requirement is applicable to any level of simulator equipped with a daylight visual system. A vertical test should also be demonstrated. Light point size should be measured using a test pattern consisting of a centrally located single row of white light points displayed as both a horizontal and vertical row. Fmt 4701 It should be possible to move the light points relative to the eyepoint in all axes. Sfmt 4725 4.a.5 E:\FR\FM\20MYR2.SGM Raster surface contrast ratio. Not less than 5: 1. Not applicable. This requirement is applicable to any level of simulator equipped with a daylight visual system. X X At a point where modulation is just discernible in each visual channel, a calculation should be made to determine the light spacing. Surface contrast ratio should be measured using a raster drawn test pattern filling the entire visual scene (all channels). 20MYR2 The test pattern should consist of black and white squares, 5° per square, with a white square in the center of each channel. Measurement should be made on the center bright square for each channel using a 1o spot photometer. This value should have a minimum brightness of 7 cd/m2 (2 ft- ER20MY16.031</GPH> Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D lamberts). Measure any adjacent dark squares. Frm 00035 Note I. -During contrast ratio testing, FSTD aft-cab andflight deck ambient light levels should be as low as possible. Fmt 4701 PO 00000 The contrast ratio is the bright square value divided by the dark square value. Sfmt 4725 E:\FR\FM\20MYR2.SGM 4.a.6 Light point contrast ratio. Not less than 25:1. Not applicable. An SOC is required and must include the relevant calculations. X X Note2.Measurements should be taken at the center of squares to avoid light spill into the measurement device. Light point contrast ratio should be measured using a test pattern demonstrating an area of greater than I o area filled with white light points and should be compared to the adjacent background. 20MYR2 Note. -Light point modulation should be just discernible on calligraphic systems but will not be discernable on raster systems. Measurements of the background should be taken such that the bright square is Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32049 ER20MY16.032</GPH> mstockstill on DSK3G9T082PROD with RULES2 32050 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c just out of the light meter FOV. PO 00000 Note. -During contrast ratio testing, FSTD aft-cab andflight deck ambient light levels should be as low as practical. Frm 00036 4.a.7 Fmt 4701 Light point contmst ratio. Light point brightness. Not less than 10:1. Not applicable. Not less than 20 cd/m2 (5.8 ft-lamberts). Not applicable. X X X X Light points should be displayed as a matrix creating a square. Sfmt 4725 On calligraphic systems the light points should just merge. E:\FR\FM\20MYR2.SGM 4.a.8 Surface brightness. Not less than 20 cd/m2 (5.8 ft-lamberts) on the display. Not applicable. This requirement is applicable to any level of simulator equipped with a daylight visual system. X X On raster systems the light points should overlap such that the square is continuous (individual light points will not be visible). Surface brightness should be measured on a white raster, measuring the brightness using the 1o spot photometer. 20MYR2 Light points are not acceptable. 4.a.9 ER20MY16.033</GPH> Notes D Black level and sequential contrast. Black intensity: Not applicable. X X X X Use of calligraphic capabilities to enhance raster brightness is acceptable. All projectors should be turned off and the cockpit Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D Frm 00037 environment made as dark as possible. A background reading should be taken of the remaining ambient light on the screen. Sequential contrast: PO 00000 Background brightness - Black polygon brightness< 0.015 cd/m2 (0.004 ftlamberts). The projectors should then be turned on and a black polygon displayed. A second reading should then be taken and the difference between this and the ambient level recorded. Fmt 4701 Maximum brightness (Background brightness - Black polygon brightness)> 2,000:1. Sfmt 4725 A full brightness white polygon should then be measured for the sequential contrast test. E:\FR\FM\20MYR2.SGM 4.a.10 Motion blur. 20MYR2 When a pattern is rotated about the eyepoint at 10'/s, the smallest detectable gap must be 4 arc min or less. Not applicable. X X X X This test is generally only required for light valve pro_jectors. A test pattern consists of an array of 5 peak white squares with black gaps between them of decreasing width. The range of black gap widths should at least extend above and below the required detectable gap, and be in steps of 1 arc min. The pattern is rotated at the required rate. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32051 ER20MY16.034</GPH> mstockstill on DSK3G9T082PROD with RULES2 32052 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Flight Conditions Tolerance Title Test Details INFORMATION Simulator Level A B c PO 00000 Two arrays of squares should be provided, one rotating in heading and the other in pitch, to provide testing in both axes. Frm 00038 A series of stationary numbers identifies the gap number. Fmt 4701 Note.- This test can be limited by the display technology. Where this is the case the NSPM should be consulted on the limitations. Sfmt 4725 E:\FR\FM\20MYR2.SGM 4.a.ll Speckle test. 4.b Head-Up Display (HUD) Static Alignment. 4.b.l Speckle contrast must be< 10%. Not applicable. Static alignment with displayed image. An SOC is required describing the test method. X X 20MYR2 System display. Tolerance+/- 6 arc min. All functionality in all flight modes must be demonstrated. This test is generally only required for light valve projectors. This test is generally only required for laser projectors. X X N/A X X Alignment requirement applies to any HUD system in use or both simultaneously if they are used simultaneously for training. N/A X X A statement of the system capabilities should be provided and the capabilities HUD bore sight must align with the center of the displayed image spherical pattern. 4.b.2 ER20MY16.035</GPH> Notes D Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D demonstrated 4.b.3 PO 00000 4.c Frm 00039 4.c.l HUD attitude versus FSTD attitude indicator (pitch and roll of horizon). Enhanced Flight Vision System (EFVS) Registration test. Fmt 4701 Sfmt 4725 4.c.2 E:\FR\FM\20MYR2.SGM 4.c.3 EFVS RVRand visibility calibration. Thermal crossover. 20MYR2 4.d Visual ground segment (VGS). Flight. X X Alignment between EFVS display and out of the window image must represent the alignment typical of the aircraft and system type. The scene represents the EFVS view at 350m (1,200 ft) and 1,609 m (1 sm) RVR including correct light intensity. Takeoff point and on approach at 200 ft. X X Note.- The effects of the alignment tolerance in 4. b.l should be taken into account. Flight. X X Infra-red scene representative of both 350m (1,200 ft), and 1,609 m (1 sm) RVR. Demonstrate thermal crossover effects during day to night transition. Day and night. Near end: the correct number of approach lights within the computed VGS must be visible. Trimmed in the landing configuration at 30m (1 00 ft) wheel height above touchdown zone on glide slope at an RVR setting of300 m (1,000 ft) or 350m (1,200 ft). X X X X Visual ground segment 4.d.1 Pitch and roll align with aircraft instruments. Far end: ±20% of the computed VGS. This test is designed to assess items impacting the accuracy of the visual scene presented to a pilot at DH on an ILS approach. These items include: 1) RVR/Visibility; X X Visual scene may be removed. The scene will correctly represent the thermal characteristics of the scene during a day to night transition. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A - Full Fli2ht Simulator (FFS) Ob.iective Tests QPS REQUIREMENTS 2) glide slope (GIS) and localizer modeling 32053 ER20MY16.036</GPH> mstockstill on DSK3G9T082PROD with RULES2 32054 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B D X X accuracy (location and slope) for an ILS; The threshold lights computed to be visible must be visible in the FSTD. PO 00000 3) for a given weight, configuration and speed representative of a point within the airplane's operational envelope for a normal approach and landing; and Frm 00040 4) Radio altimeter. Note. -If non-homogeneous jog is used, the vertical variation in horizontal visibility should be described and included in the slant range visibility calculation used in the VGS computation. Fmt 4701 Sfmt 4725 c Notes 4.e 4.e.l Visual System Capacity System capacityDay mode. E:\FR\FM\20MYR2.SGM 20MYR2 4.e.2 System capacityTwilight/night mode. Not less than: 10,000 visible textured surfaces, 6,000 light points, 16 moving models. Not less than: 10,000 visible textured surfaces, 15,000 light points, 16 moving models. Not applicable. Not applicable. X X Demonstrated through use of a visual scene rendered with the same image generator modes used to produce scenes for training. The required surfaces, light points, and moving models should be displayed simultaneously. Demonstrated through use of a visual scene rendered with the same image generator modes used to produce scenes for training. The required surfaces, light points, and moving models should be displayed simultaneously. ER20MY16.037</GPH> Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Notes D PO 00000 Frm 00041 5. Sound System. The sponsor will not be required to repeat the airplane tests (i.e., tests 5.a.l. through 5.a.8. (or 5.b.l. through 5.b.9.) and S.c., as appropriate) during continuing qualification evaluations if frequency response and background noise test results are within tolerance when compared to the initial qualification evaluation results, and the sponsor shows that no software changes have occurred that will affect the airplane test results. If the frequency response test method is chosen and fails, the sponsor may elect to fix the frequency response problem and repeat the test or the sponsor may elect to repeat the airplane tests. If the airplane tests are repeated during continuing qualification evaluations, the results may be compared against initial qualification evaluation results or airplane master data. All tests in this section must be presented using an unweighted 1/3-octave band format from band 17 to 42 (50 Hz to 16kHz). A minimum 20 second average must be taken at the location corresponding to the airplane data set. The airplane and flight simulator results must be produced using comparable data analysis techniques. Turbo-jet airplanes. 5.a. Fmt 4701 All tests in this section should be presented using an unweighted 1/3-octave band format from at least band 17 to 42 (50 Hz to 16kHz). Sfmt 4725 A measurement of minimum 20 s should be taken at the location corresponding to the approved data set. E:\FR\FM\20MYR2.SGM The approved data set and FSTD results should be produced using comparable data analysis techniques. 20MYR2 5.a.l. Ready for engine start. Initial evaluation: ± 5 dB per 1/3 octave band. Recurrent evaluation: carmot exceed ±5 dB difference on three consecutive bands when compared to initial Ground. Normal condition prior to engine start. The APU should be on if appropriate. X Refer to paragraph 7 of this Attachment For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS 32055 ER20MY16.038</GPH> mstockstill on DSK3G9T082PROD with RULES2 32056 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number Tolerance Title Test Details A B c PO 00000 Frm 00042 5.a.2. All engines at idle. Fmt 4701 Initial evaluation: ± 5 dB per 1/3 octave band. Ground. Normal condition prior to takeoff. Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 X Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. X Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. 5.a.3. All engines at maximum allowable thrust with brakes set. Initial evaluation: ± 5 dB per 1/3 octave band. Ground. Normal condition prior to takeoff. Notes D evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the ER20MY16.039</GPH> Flight Conditions INFORMATION Simulator Level Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry -1 Number Title Flight Conditions Test Details INFORMATION Simulator Level A B c PO 00000 average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Frm 00043 5.a.4. Climb Initial evaluation: ± 5 dB per 1/3 octave band. En-route climb. Medium altitude. X Fmt 4701 Sfmt 4725 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. E:\FR\FM\20MYR2.SGM 5.a.5. Cruise 20MYR2 Initial evaluation: ± 5 dB per 1/3 octave band. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between Cruise. Normal cruise configuration. Notes D X Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS Where initial evaluation 32057 ER20MY16.040</GPH> mstockstill on DSK3G9T082PROD with RULES2 32058 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number Tolerance Title PO 00000 Test Details Simulator Level A B c 5.a.6. Speed brake/spoilers extended (as appropriate). Initial evaluation: ± 5 dB per 1/3 octave band. Cruise. Normal and constant speed brake deflection for descent at a constant airspeed and power setting. X Fmt 4701 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Sfmt 4725 E:\FR\FM\20MYR2.SGM 5.a.7 Initial approach. Initial evaluation: ± 5 dB per 1/3 octave band. 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent Approach. Constant airspeed, gear up, flaps/slats as appropriate. Notes D initial and recurrent evaluation results cannot exceed 2 dB. Frm 00044 ER20MY16.041</GPH> Flight Conditions INFORMATION X employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 Test PO 00000 Entry .1 Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Frm 00045 evaluation results cannot exceed 2 dB. Fmt 4701 5.a.8 Final approach. Initial evaluation: ± 5 dB per 1/3 octave band. Sfmt 4725 E:\FR\FM\20MYR2.SGM Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Landing. Constant airspeed, gear down, landing configuration flaps. Notes D X tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. 20MYR2 Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS 32059 ER20MY16.042</GPH> mstockstill on DSK3G9T082PROD with RULES2 32060 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number 5.b Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c Propeller-driven airplanes All tests in this section should be presented using an unweighted 1/3-octave band format from at least band 17 to 42 (50 Hz to 16kHz). PO 00000 A measurement of minimum 20 s should be taken at the location corresponding to the approved data set. Frm 00046 Fmt 4701 The approved data set and FSTD results should be produced using comparable data analysis techniques. Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.043</GPH> Notes D 5.b.l. Ready for engine start. Initial evaluation: ± 5 dB per 1/3 octave band. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Ground. Normal condition prior to engine start. The APU should be on if appropriate. X Refer to paragraph 3. 7 of this Appendix. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number 5.b.2 Tolerance Title PO 00000 All propellers feathered, if applicable. Initial evaluation: ± 5 dB per 1/3 octave band. Flight Conditions Ground. Test Details Normal condition prior to takeoff. INFORMATION Simulator Level A B c X Frm 00047 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 5.b.3. Ground idle or equivalent. Initial evaluation: ± 5 dB per 1/3 octave band. 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Ground. Normal condition prior to takeoff. Notes D X For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within ± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32061 ER20MY16.044</GPH> mstockstill on DSK3G9T082PROD with RULES2 32062 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number 5.b.4 Tolerance Title Flight idle or equivalent. Ground. Test Details Normal condition prior to takeoff. A B c PO 00000 Frm 00048 Fmt 4701 Sfmt 4725 5.b.5 E:\FR\FM\20MYR2.SGM All engines at maximum allowable power with brakes set. Initial evaluation: ± 5 dB per 1/3 octave band. Ground. Normal condition prior to takeoff. X X 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Climb. Initial evaluation: ± 5 dB per 1/3 octave En-route climb. Medium altitude. Notes D Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. 5.b.6 ER20MY16.045</GPH> Initial evaluation: ± 5 dB per 1/3 octave band. Flight Conditions INFORMATION Simulator Level X For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c D octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within ± 7 dB from approved reference data, providing that the overall trend is correct. band. PO 00000 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Frm 00049 Fmt 4701 Sfmt 4725 5.b.7 Cruise Initial evaluation: ± 5 dB per 1/3 octave band. Cruise. Normal cruise configuration. X E:\FR\FM\20MYR2.SGM 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. 5.b.8 Initial approach. Initial evaluation: ± 5 dB per 1/3 octave band. Notes Approach. Constant airspeed, gear up, flaps extended as appropriate, RPM as per operating manual. X Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS 32063 ER20MY16.046</GPH> mstockstill on DSK3G9T082PROD with RULES2 32064 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number Tolerance Title Test Details A B c PO 00000 Frm 00050 Fmt 4701 5.b.9 Final approach. Sfmt 4725 Initial evaluation: ± 5 dB per 1/3 octave band. that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Landing. Constant airspeed, gear down, landing configuration flaps, RPM as per operating manual. X E:\FR\FM\20MYR2.SGM Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. 20MYR2 Special cases. Initial evaluation: ± 5 dB per 1/3 octave band. Recurrent evaluation: cannot exceed ±5 dB Notes D Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. S.c. ER20MY16.047</GPH> Flight Conditions INFORMATION Simulator Level As appropriate. X Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. For initial evaluation, it is acceptable to have some 1/3 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations. This applies to special steady· state cases identified as particularly significant to the pilot, important in training, or unique to a specific airplane type or model. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry .1 Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B c PO 00000 difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Frm 00051 For initial evaluation, it is acceptable to have some 113 octave bands out of± 5 dB tolerance but not more than 2 that are consecutive and in any case within± 7 dB from approved reference data, providing that the overall trend is correct. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM S.d FSTD background noise Initial evaluation: background noise levels must fall below the sound levels described in Paragraph 7.c (5) of this Attachment. Results of the background noise at initial qualification must be included in the QTG document and approved by the NSPM. The measurements are to be made with the simulation running, the sound muted and a dead cockpit. X 20MYR2 Frequency response Initial evaluation: not applicable. Recurrent evaluation: cannot exceed ±5 dB Where initial evaluation employs approved subjective tuning to develop the approved reference standard, recurrent evaluation tolerances should be used during recurrent evaluations The simulated sound will be evaluated to ensure that the background noise does not interfere with training. Refer to paragraph 7 of this Attachment. Recurrent evaluation: ±3 dB per 113 octave band compared to initial evaluation. 5.e Notes D This test should be presented using an unweighted 113 octave band format from band 17 to 42 (50 Hz to 16kHz). Ground (static with all systems switched oft) X Only required if the results are to be used during continuing qualification evaluations in lieu of airplane tests. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table A2A- Full Flight Simulator (FFS) Ob_jective Tests QPS REQUIREMENTS 32065 ER20MY16.048</GPH> mstockstill on DSK3G9T082PROD with RULES2 32066 Test Jkt 238001 .1 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION Simulator Level A B PO 00000 Frm 00052 Fmt 4701 6 6.a. Sfmt 4700 6.a.l SYSTEMS INTEGRATION System response time Transport delay. E:\FR\FM\20MYR2.SGM Motion system and instrument response: 100 ms (or less) after airplane response. Notes D difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. The results must be approved by the NSPM during the initial qualification. This test should be presented using an unweighted 1/3 octave band format from band 17 to 42 (50 Hz to 16kHz). Pitch, roll and yaw. X X One separate test is required in each axis. Where EFVS systems are installed, the EFVS response should be within + or - 30 ms from visual system response, and not before motion system response. Visual system response: 120 ms (or less) after airplane response. 20MYR2 Note.- The delay from the airplane EFVS electronic elements should be added to the 30 ms tolerance before comparison with visual system r~ference. Transport delay. ER20MY16.049</GPH> c 300 milliseconds or less after controller movement. Pitch, roll and yaw. X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 3. Correct the tables appearing on pages 18284–18300 to read as follows: ■ VerDate Sep<11>2014 Table A2A- Full Fli2ht Simulator (FFS) Ob.iective Tests QPS REQUIREMENTS Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32067 Table A3A - Functions And Subjective Tests QPS REQUIREMENTS "~ -= = 1-o z 1. l.a. l.a.l l.a.2 l.a.3 2. 2.a. 2.a.l. 2.a.2. 2.a.3. 2.b. 2.b.1 2.b.2. 2.b.3. 2.b.4. 2.b.5. 2.b.6. 2.b.7. 2.c. 2.c.l. 2.c.2. 2.d mstockstill on DSK3G9T082PROD with RULES2 3. 3.a. 3.a.l. 3.a.2. 3.a.3.a 3.a.3.b 3.a.4. 3.a.4.a 3.a.4.b 3.a.4.c 3.a.4.d VerDate Sep<11>2014 Simulator Level Operations Tasks A B c D Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List or the level of simulator qualification involved. Items not installed or not functional on the simulator and, therefore, not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ. Preparation For Flight Pre-flight. Accomplish a functions check of all switches, indicators, systems, and equipment at all crew members' and instructors' stations and determine that: The flight deck design and functions are identical to that of the X X X X airplane being simulated. Reserved Reserved Surface Operations (pre-flight). En2ine Start Normal start X X X X Alternate start procedures X X X X Abnormal starts and shutdowns (e.g., hot/hung start, tail pipe X X X X fire) Taxi Pushback/powerback X X X Thrust response X X X X Power lever friction X X X X Ground handling X X X X Nosewheel scuffing X X Taxi aids (e.g. taxi camera, moving map) X X Low visibility (taxi route, signage, lighting, markings, etc.) X X Brake Operation Brake operation (normal and alternate/emergency) X X X X Brake fade (if applicable) X X X X Other Take-off. Normal Airplane/engine parameter relationships, including run-up X X X X Nosewheel and rudder steering X X X X Crosswind (maximum demonstrated) X X X X Gusting crosswind X X Special performance Reduced V1 X X X X Maximum engine de-rate X X X X Soft surface X X Short field/short take-off and landing (STOL) operations X X X X 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00053 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.050</GPH> ~ a 32068 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3A - Functions And Subjective Tests QPS REQUIREMENTS 1-o =z = ~ 3.a.4.e 3.a.5. 3.a.6. 3.a.7. 3.a.8. 3.b. 3.b.l. 3.b.2. 3.b.3. 3.b.4. 3.b.5. 3.b.6. 4. 4.a. 4.b. 4.c. 4.d. 5. 5.a. 5.a.l. 5.a.2. 5.a.3. 5.a.4. mstockstill on DSK3G9T082PROD with RULES2 5.a.5. 5.a.6. 5.a.7. 5.b. 5.b.l. 5.b.l.a 5.b.l.b VerDate Sep<11>2014 Simulator Level Operations Tasks c A B Obstacle (performance over visual obstacle) X Low visibility take-off X X X Landing gear, wing flap leading edge device operation X X X Contaminated runway operation X Other Abnormal/emergency Rejected Take-off X X X Rejected special performance (e.g., reduced Vt, max de-rate, X X X short field operations) Rejected take-off with contaminated runway X Takeoff with a propulsion system malfunction (allowing an X X X analysis of causes, symptoms, recognition, and the effects on aircraft performance and handling) at the following points: (i) Prior to Vl decision speed; (ii) Between Vl and Vr (rotation speed); and (iii)Between Vr and 500 feet above ground level. Flight control system failures, reconfiguration modes, manual X X X reversion and associated handling. Other Climb. Normal. X X X One or more engines inoperative. X X X Approach climb in icing (for airplanes with icing X X X accountability). Other Cruise. Performance characteristics (speed vs. power, confi2uration, and attitude) Straight and level flight. X X X Change of airspeed. X X X High altitude handling. X X X High Mach number handling (Mach tuck, Mach buffet) and X X X recovery (trim change). Overspeed warning (in excess ofVmoor Mm0 ). X X X High lAS handling. X X X Other Maneuvers High Angle of Attack High angle of attack, approach to stalls, stall warning, and stall X X buffet (take-off, cruise, approach, and landing configuration) including reaction of the auto flight system and stall protection system. High angle of attack, approach to stalls, stall warning, stall X buffet, and stall (take-off, cruise, approach, and landing 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00054 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 D X X X X X X X X X X X X X X X X X X X ER20MY16.051</GPH> t>~ ..... a 32069 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3A - Functions And Subjective Tests QPS REQUIREMENTS 1-o t>~ ..... a 5.b.2. 5.b.3. 5.b.4. 5.b.5. 5.b.6. 5.b.7. 5.b.8. 5.b.9. S.b.lO. S.b.ll. 5.b.12. 5.b.l3 5.b.14 5.b.l4.a 5.b.l4.b 5.b.14.c 5.b.14.d 5.b.l4.e 5.b.l5 6. 6.a. 6.b. 6.c. 6.d. 6.e. mstockstill on DSK3G9T082PROD with RULES2 7. 7.a. 7.a.l 7.a.l.a VerDate Sep<11>2014 c A B D configuration) including reaction of the auto flight system and stall protection system. Slow flight X X Upset prevention and recovery maneuvers within the FSTD's X X validation envelope. Flight envelope protection (high angle of attack, bank limit, X X X X overspeed, etc.) Turns with/without speedbrake/spoilers deployed X X X X Normal and standard rate turns X X X X Steep turns X X X X Performance tum X X In flight engine shutdown and restart (assisted and windmill) X X X X Maneuvering with one or more engines inoperative, as X X X X appropriate Specific flight characteristics (e.g. direct lift control) X X X X Flight control system failures, reconfiguration modes, manual X X X X reversion and associated handling Gliding to a forced landing X X Visual resolution and FSTD handling and performance for the following (where applicable by aircraft type and training program): Terrain accuracy for forced landing area selection; X X Terrain accuracy for VFR Navigation; X X Eights on pylons (visual resolution); X X Turns about a point; and X X S-tums about a road or section line. X X Other. Descent. Normal X X X X Maximum rate/emergency (clean and with speedbrake, etc.). X X X X With autopilot. X X X X Flight control system failures, reconfiguration modes, manual X X X X reversion and associated handling. Other Instrument Approaches And Landing. Those instrument approach and landing tests relevant to the simulated airplane type are selected from the following list. Some tests are made with limiting wind velocities, under windshear conditions, and with relevant system failures, including the failure of the Flight Director. If Standard Operating Procedures allow use autopilot for nonprecision approaches, evaluation of the autopilot will be included. Level A simulators are not authorized to credit the landing maneuver. Precision approach CAT I published approaches. Manual approach with/without flight director including X X X X 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00055 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.052</GPH> =z = ~ Simulator Level Operations Tasks 32070 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3A - Functions And Subjective Tests QPS REQUIREMENTS -a = C'] ~i 7.a.l.c 7.a.l.d 7.a.l.e 7.a.2 7.a.2.a 7.a.2.b 7.a.2.c 7.a.3 7.a.3.a 7.a.3.b 7.a.3.c 7.a.3.d 7.a.3.e 7.a.4 7.a.4.a 7.a.4.b.l 7.a.4.b.2 7.a.4.c.l 7.a.4.c.2 7.a.5 7.a.6 mstockstill on DSK3G9T082PROD with RULES2 7.b. 7.b.l 7.b.2 VerDate Sep<11>2014 A landing. Autopilot/autothrottle coupled approach and manual landing. Autopilot/autothrottle coupled approach, engine(s) inoperative. Manual approach, engine(s) inoperative. HUD/EFVS CAT II published approaches. Autopilot/autothrottle coupled approach to DH and landing (manual and autoland). Autopilot/autothrottle coupled approach with one-engineinoperative approach to DH and go-around (manual and autopilot). HUD/EFVS CAT III published approaches. Autopilot/autothrottle coupled approach to landing and rollout (if applicable) guidance (manual and auto land). Autopilot/autothrottle coupled approach to DH and goaround (manual and autopilot). Autopilot/autothrottle coupled approach to land and roll-out (if applicable) guidance with one engine inoperative (manual and autoland). Autopilot/autothrottle coupled approach to DH and goaround with one engine inoperative (manual and autopilot). HUD/EFVS Autopilot/autothrottle coupled approach (to a landing or to a goaround): With generator failure; With maximum tail wind component certified or authorized; With 10 knot tail wind; With maximum crosswind component demonstrated or authorized; and With 10 knot crosswind. PAR approach, all engine( s) operating and with one or more engine(s) inoperative MLS, GBAS, all engine( s) operating and with one or more engine(s) inoperative B c D X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X Non-precision approach. Surveillance radar approach, all engine(s) operating and with one or more engine(s) inoperative NDB approach, all engine(s) operating and with one or more engine(s) inoperative 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00056 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.053</GPH> 7.a.l.b Simulator Level Operations Tasks 32071 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3A - Functions And Subjective Tests QPS REQUIREMENTS 1-o c~ ... e = ~ = z 7.b.3 7.b.4 7.b.5 7.b.6 7.c 7.c.l 7.c.2 8. Simulator Level Operations Tasks VOR, VOR/DME, TACAN approach, all engines(s) operating and with one or more engine(s) inoperative RNAV I RNP I GNSS (RNP at nominal and minimum authorized temperatures) approach, all engine(s) operating and with one or more engine(s) inoperative ILS LLZ (LOC), LLZ back course (or LOC-BC) approach, all engine(s) operating and with one or more engine(s) inoperative ILS offset localizer approach, all engine(s) operating and with one or more engine(s) inoperative Approach procedures with vertical guidance (APV), e.g. SBAS, fli2ht path vector APV/baro-VNAV approach, all engine(s) operating and with one or more engine(s) inoperative Area navigation (RNAV) approach procedures based on SBAS, all engine(s) operating and with one or more engine(s) inoperative Visual Approaches (Visual Segment) And Landings. A X B c D X X X X X X X X X X X X X X X X X X X Flight simulators with visual systems, which permit completing a special approach procedure in accordance with applicable regulations, may be approved for that particular approach procedure. 8.b. S.c. 8.d.l 8.d.2 8.e. 8.e.l. 8.e.l.a 8.e.l.b 8.f. mstockstill on DSK3G9T082PROD with RULES2 8.g. 8.h. 8.i. 8.j. 8.k. VerDate Sep<11>2014 Maneuvering, normal approach and landing, all engines operating with and without visual approach aid guidance Approach and landing with one or more engines inoperative Operation of landing gear, flap/slats and speedbrakes (normal and abnormal) Approach and landing with crosswind (max. demonstrated) Approach and landing with gusting crosswind Approach and landing with flight control system failures, reconfiguration modes, manual reversion and associated handling (most significant degradation which is probable) Approach and landing with trim malfunctions Longitudinal trim malfunction Lateral-directional trim malfunction Approach and landing with standby (minimum) electrical/hydraulic power Approach and landing from circling conditions (circling approach) Approach and landing from visual traffic pattern Approach and landing from non-precision approach Approach and landing from precision approach Other 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00057 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 20MYR2 ER20MY16.054</GPH> 8.a. 32072 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3A - Functions And Subjective Tests QPS REQUIREMENTS ~ = z 9. 9.a. 9.b. 9.c. 9.d. 9.e. 10. lO.a lO.a.l 10.a.2. 10.a.3. 10.a.4. lO.a.S. 10.a.6. 10.a.6.a 10.a.6.b 10.a.6.c 10.a.6.d 10.a.7 lO.b lO.b.l 10.b.2 10.b.3 mstockstill on DSK3G9T082PROD with RULES2 11. ll.a. ll.a.l. ll.a.2. ll.a.3. ll.a.4. ll.a.S. ll.a.6. ll.a.7. ll.a.8. ll.a.9. ll.a.lO. ll.a.ll. ll.a.12. ll.a.13. VerDate Sep<11>2014 Simulator Level Operations Tasks A Missed Approach. All engines, manual and autopilot. Engine(s) inoperative, manual and autopilot. Rejected landing With flight control system failures, reconfiguration modes, manual reversion and associated handling Bounced landing recovery Surface Operations (landing, after-landing and post-flight). Landing roll and taxi HUD/EFVS Spoiler operation Reverse thrust operation Directional control and ground handling, both with and without reverse thrust Reduction of rudder effectiveness with increased reverse thrust (rear pod-mounted engines) Brake and anti-skid operation Brake and anti-skid operation with dry, patchy wet, wet on rubber residue, and patchy icy conditions Reserved Brake operation Auto-braking system operation Other En2ine shutdown and parkin2 Engine and systems operation Parking brake operation Other Any Fli2ht Phase. Airplane and engine systems operation (where fitted) Air conditioning and pressurization (ECS) De-icing/anti-icing Auxiliary power unit (APU). Communications Electrical Fire and smoke detection and suppression Flight controls (primary and secondary) Fuel and oil Hydraulic Pneumatic Landing gear Oxygen Engine 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00058 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM B c D X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 20MYR2 ER20MY16.055</GPH> - ... e "~ = 32073 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3A - Functions And Subjective Tests QPS REQUIREMENTS ~ = z 11.a.14. 11.a.15. 11.a.16. 11.a.17. 11.a.18. 11.a.19. 11.a.20. 11.a.21. 11.a.22. 11.a.23. 11.a.24. 11.a.25. 11.a.26. 11.a.27. 11.a.28. 11.b. 11.b.1. 11.b.2. mstockstill on DSK3G9T082PROD with RULES2 11.b.3. 11.b.3.a 11.b.3.b 11.b.3.c 11.b.3.d 11.b.4. VerDate Sep<11>2014 Simulator Level Operations Tasks A Airborne radar Autopilot and Flight Director Terrain awareness warning systems and collision avoidance systems (e.g. EGPWS, GPWS, TCAS) Flight control computers including stability and control augmentation Flight display systems Flight management computers Head-up displays (including EFVS, if appropriate) Navigation systems Stall warning/avoidance Wind shear avoidance/recovery guidance equipment Flight envelope protections Electronic flight bag Automatic checklists (normal, abnormal and emergency procedures) Runway alerting and advisory system Other Airborne procedures Holding Air hazard avoidance (traffic, weather, including visual correlation) Windshear Prior to take-off rotation At lift-off During initial climb On final approach, below 150m (500ft) AGL Effects of airframe ice 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00059 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM B c D X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 20MYR2 X ER20MY16.056</GPH> - ... e "~ = 32074 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3B - Functions and Subjective Tests QPS REQUIREMENTS -a= = "" C>~ z Simulator Level Class I Airport Models A B c D This table specifies the minimum airport model content and functionality to qualify a simulator at the indicated level. This table applies only to the airport models required for simulator qualification; i.e., one airport model for Level A and Level B simulators; three airport models for Level C and Level D simulators. Begin QPS Requirements 1. Functional test content requirements for Level A and Level B simulators. The following is the minimum airport model content requirement to satisfy visual capability tests, and provides suitable visual cues to allow completion of all functions and subjective tests described in this attachment for simulators at Levels A and B. A minimum of one ( 1) representative airport model. This model l.a. X X identification must be acceptable to the sponsor's TPAA, selectable from the lOS, and listed on the SOQ. The fidelity of the airport model must be sufficient for the X X l.b. aircrew to visually identify the airport; determine the position of the simulated airplane within a night visual scene; successfully accomplish take-offs, approaches, and landings; and maneuver around the airport on the ground as necessary. Runways: l.c. X X Visible runway number. X X l.c.l. Runway threshold elevations and locations must be modeled to l.c.2. X X provide sufficient correlation with airplane systems (e.g., altimeter). Runway surface and markings. X X l.c.3. Lighting for the runway in use including runway edge and l.c.4. X X centerline. Lighting, visual approach aid and approach lighting of X X l.c.S. appropriate colors. Representative taxiway lights. X X l.c.6. 2.a. Additional functional test content requirements Airport scenes 2.a.1 A minimum of three (3) real-world airport models to be 2.a.l.a X X consistent with published data used for airplane operations and capable of demonstrating all the visual system features below. Each model should be in a different visual scene to permit assessment ofFSTD automatic visual scene changes. The model identifications must be acceptable to the sponsor's TPAA, selectable from the IOS, and listed on the SOQ. Reserved 2.a.l.b Reserved 2.a.l.c 2.a.l.d Airport model content. X X X X For circling approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing. If all runways in an airport model used to meet the requirements of this VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00060 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.057</GPH> mstockstill on DSK3G9T082PROD with RULES2 ~ For Qualification At The Stated Level 32075 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3B - Functions and Subjective Tests QPS REQUIREMENTS -a= = "" C>~ z 2.a.2 2.a.2.a 2.a.2.b 2.a.2.c 2.a.3 2.a.3.a 2.a.3.b 2.a.3.c 2.a.4 2.a.5 2.a.6 mstockstill on DSK3G9T082PROD with RULES2 2.a.7 2.a.7.a 2.a.7.b 2.a.7.c 2.a.7.d VerDate Sep<11>2014 Class I Airport Models Simulator Level A B c D attachment are not designated as "in use," then the "in use" runways must be listed on the SOQ (e.g., KORD, Rwys 9R, 14L, 22R). Models of airports with more than one runway must have all significant runways not "in-use" visually depicted for airport and runway recognition purposes. The use of white or off white light strings that identify the runway threshold, edges, and ends for twilight and night scenes are acceptable for this requirement. Rectangular surface depictions are acceptable for daylight scenes. A visual system's capabilities must be balanced between providing airport models with an accurate representation of the airport and a realistic representation of the surrounding environment. Airport model detail must be developed using airport pictures, construction drawings and maps, or other similar data, or developed in accordance with published regulatory material; however, this does not require that such models contain details that are beyond the design capability of the currently qualified visual system. Only one "primary" taxi route from parking to the runway end will be required for each "in-use" runway. Visual scene fidelity. The visual scene must correctly represent the parts of the airport X X X X and its surroundings used in the training program. Reserved Reserved Runways and taxiways. Airport specific runways and taxiways. X X X X Reserved Reserved If appropriate to the airport, two parallel runways and one X X crossing runway displayed simultaneously; at least two runways must be capable of being lit simultaneously. Runway threshold elevations and locations must be modeled to X X provide correlation with airplane systems (e.g. HUD, GPS, compass, altimeter). Slopes in runways, taxiways, and ramp areas must not cause X X distracting or unrealistic effects, including pilot eye-point height variation. Runway surface and markings for each "in-use" runway must include the following, if appropriate: Threshold markings. X X X X Runway numbers. X X X X Touchdown zone markings. X X X X Fixed distance markings. X X X X 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00061 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.058</GPH> ~ For Qualification At The Stated Level 32076 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations =a Table A3B - Functions and Subjective Tests QPS REQUIREMENTS ~~ ...... For Qualification At The Stated Level ~i Class I Airport Models 2.a.8.a 2.a.8.b 2.a.8.c 2.a.8.d 2.a.8.e 2.a.8.f 2.a.8.2 2.a.8.h 2.a.9 2.a.9.a 2.a.9.b 2.a.9.c 2.a.9.d 2.a.9.e 2.a.10 mstockstill on DSK3G9T082PROD with RULES2 2.a.10.a 2.a.10.b 2.a.10.c 2.a.11 2.a.11.a VerDate Sep<11>2014 c D A B Edge markings. X X X X Center line markings. X X X X Distance remaining signs. X X X X Signs at intersecting runways and taxiways. X X X X Windsock that gives appropriate wind cues. X X Runway lighting of appropriate colors, directionality, behavior and spacing for the "in-use" runway includin2 the followin2: Threshold lights. X X X X Edge lights. X X X X End lights. X X X X Center line lights. X X X X Touchdown zone lights. X X X X Lead-off lights. X X X X Appropriate visual landing aid(s) for that runway. X X X X Appropriate approach lighting system for that runway. X X X X Taxiway surface and markine;s (associated with each "in-use" runway): Edge markings X X X X Center line markings. X X X X Runway holding position markings. X X X X ILS critical area markings. X X X X All taxiway markings, lighting, and signage to taxi, as a X minimum, from a designated parking position to a designated runway and return, after landing on the designated runway, to a designated parking position; a low visibility taxi route (e.g. surface movement guidance control system, follow-me truck, daylight taxi lights) must also be demonstrated at one airport model for those operations authorized in low visibilities. The designated runway and taxi routing must be consistent with that airport for operations in low visibilities. The qualification of surface movement guidance control systems (SMGCS) is optional at the request of the FSTD sponsor. For the qualification of SMGCS, a demonstration model must be provided for evaluation. Taxiway lighting of appropriate colors, directionality, behavior and spacing (associated with each "in-use" runway): Edge lights. X X X Center line lights. X X X Runway holding position and ILS critical area lights. X X X Required visual model correlation with other aspects of the airport environment simulation. The airport model must be properly aligned with the navigational X X X aids that are associated with operations at the runway "in-use". 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00062 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 X X X X ER20MY16.059</GPH> 2.a.7.e 2.a.7.f 2.a.7.2 2.a.7.h 2.a.7.i 2.a.8 Simulator Level Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32077 Table A3B - Functions and Subjective Tests QPS REQUIREMENTS 1-o C>~ ...... For Qualification At The Stated Level =a ~ = z Simulator Level Class I Airport Models A B c D The simulation of runway contaminants must be correlated with X the displayed runway surface and lighting. 2.a.12 Airport buildin2s, structures and li2htin2. Buildings, structures and lighting: 2.a.12.a X X 2.a.12.a.l Airport specific buildings, structures and lighting. 2.a.12.a.2 Reserved 2.a.12.a.3 Reserved At least one useable gate, set at the appropriate height (required 2.a.12.b X X only for those airplanes that typically operate from terminal gates). Representative moving and static airport clutter (e.g. other 2.a.12.c X X airplanes, power carts, tugs, fuel trucks, additional gates). Gate/apron markings (e.g. hazard markings, lead-in lines, gate 2.a.12.d X X numbering), lighting and gate docking aids or a marshaller. 2.a.13 Terrain and obstacles. Terrain and obstacles within 46 km (25 NM) of the reference 2.a.13.a X X airport. Reserved 2.a.13.b 2.a.14 Si2nificant, identifiable natural and cultural features and movin2 airborne traffic. Significant, identifiable natural and cultural features within 46 2.a.14.a X X km (25 NM) of the reference airport. Note.- This refers to natural and cultural features that are typically used for pilot orientation in flight. Outlying airports not intendedfor landing need only provide a reasonable facsimile of runway orientation. Reserved 2.a.14.b Representative moving airborne traffic (including the capability 2.a.14.c X X to present air hazards - e.g. airborne traffic on a possible collision course). Visual scene mana2ement. ~.b All airport runway, approach and taxiway lighting and cultural 2.b.l X X lighting intensity for any approach must be capable of being set to six (6) different intensities (0 to 5); all visual scene light points should fade into view appropriately. Airport runway, approach and taxiway lighting and cultural X X 2.b.2 lighting intensity for any approach must be set at an intensity representative of that used in training for the visibility set; all visual scene light points should fade into view appropriately. The directionality of strobe lights, approach lights, runway edge 2.b.3 X X X X lights, visual landing aids, runway center line lights, threshold lights, and touchdown zone lights on the runway of intended landing must be realistically replicated. Visual feature reco2nition. ~.c VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00063 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.060</GPH> mstockstill on DSK3G9T082PROD with RULES2 2.a.11.b 32078 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations For Qualification At The Stated Level C>] ~ = z 2.c.l 2.c.2 2.c.2.a 2.c.2.b 2.c.3 2.c.4 2.c.5 2.c.6 ~.d 2.d.l 2.d.2 2.d.3 2.d.4 2.d.5 ~.e mstockstill on DSK3G9T082PROD with RULES2 2.e.l 2.e.2 2.e.2.a 2.e.2.b VerDate Sep<11>2014 Simulator Level Class I Airport Models c A B D Note.- The following are the minimum distances at which runway features should be visible. Distances are measured from runway threshold to an airplane aligned with the runway on an extended 3-degree glide slope in suitable simulated meteorological conditions. For circling approaches, all tests below apply both to the runway usedfor the initial approach and to the runway of intended landing. Runway definition, strobe lights, approach lights, and runway X X X X edge white lights from 8 km (5 sm) of the runway threshold. Visual approach aids lights. Visual approach aids lights from 8 km (5 sm) of the runway X X threshold. Visual approach aids lights from 4.8 km (3 sm) of the runway X X threshold. Runway center line lights and taxiway definition from 4.8 km X X X X (3 sm). Threshold lights and touchdown zone lights from 3.2 km (2 sm). X X X X Runway markings within range of landing lights for night scenes; X X X X as required by the surface resolution test on day scenes. For circling approaches, the runway of intended landing and X X X X associated lighting must fade into view in a non-distracting manner. Selectable airport visual scene capability for: Night. X X X X Twilight. X X Day. X X Dynamic effects - the capability to present multiple ground and X X air hazards such as another airplane crossing the active runway or converging airborne traffic; hazards should be selectable via controls at the instructor station. Illusions - operational visual scenes which portray X representative physical relationships known to cause landing illusions, for example short runways, landing approaches over water, uphill or downhill runways, rising terrain on the approach path and unique topographic features. Note.- Illusions may be demonstrated at a generic airport or at a specific airport. Correlation with airplane and associated equipment. Visual cues to relate to actual airplane responses. X X X X Visual cues durin2 take-off, approach and landin2. Visual cues to assess sink rate and depth perception during X X X landings. Visual cueing sufficient to support changes in approach path by X X X X using runway perspective. Changes in visual cues during take-off, approach and landing should not distract the pilot. 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00064 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.061</GPH> -a = Table A3B - Functions and Subjective Tests QPS REQUIREMENTS 32079 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3B - Functions and Subjective Tests QPS REQUIREMENTS ~ z 2.e.3 2.e.4 2.e.5 2.f 2.f.l 2.f.l.a 2.f.l.b 2.f.2 2.f.3 2.f.4 2.f.5 2.g 2.g.l 2.g.2 2.g.3 2.g.4 2.g.5 mstockstill on DSK3G9T082PROD with RULES2 2.g.6 VerDate Sep<11>2014 For Qualification At The Stated Level Simulator Level Class I Airport Models A Accurate portrayal of environment relating to airplane attitudes. The visual scene must correlate with integrated airplane systems, where fitted (e.g. terrain, traffic and weather avoidance systems and HUD/EFVS). The effect of rain removal devices must be provided. Scene quality. Quantization. Surfaces and textural cues must be free from apparent quantization (aliasing). Surfaces and textural cues must not create distracting quantization (aliasing). System capable of portraying full color realistic textural cues. The system light points must be free from distracting jitter, smearing or streaking. System capable of providing representative focus effects that simulate rain (e.g. reduced visibility and object resolution in the out the window view as a result of rain). System capable of providing light point perspective growth (e.g. relative size of runway and taxiway edge lights increase as the lights are approached). Environmental effects. The displayed scene must correspond to the appropriate surface contaminants and include runway lighting reflections for wet, partially obscured lights for snow, or suitable alternative effects. Special weather representations which include the sound, motion and visual effects of light, medium and heavy precipitation near a thunderstorm on take-off, approach and landings at and below an altitude of 600 m (2 000 ft) above the airport surface and within a radius of 16 km (10 sm) from the airport. One airport with a snow scene to include terrain snow and snowcovered taxiways and runways. In-cloud effects such as variable cloud density, speed cues and ambient changes should be provided. The effect of multiple cloud layers representing few, scattered, broken and overcast conditions giving partial or complete obstruction of the ground scene. Gradual break-out to ambient visibility/RVR, defmed as up to 10% of the respective cloud base or top, 20 ft ~ transition layer ~ 200 ft; cloud effects should be checked at and below a height of 600 m (2 000 ft) above the airport and within a radius of 16 km (1 0 sm) from the airport. Transition effects should be complete when the IOS cloud base or top is reached when exiting and start when entering the cloud, i.e. transition effects should occur 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00065 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM B c D X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 20MYR2 ER20MY16.062</GPH> -a= = "" C>~ 32080 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table A3B - Functions and Subjective Tests QPS REQUIREMENTS == For Qualification At The Stated Level t'] ..... = z ~ 2.g.7 2.g.8 2.2.9 2.g.10 2.g.ll Class I Airport Models A within the IOS defined cloud layer. Visibility and RVR measured in terms of distance. Visibility/RVR must be checked at and below a height of 600 m (2 000 ft) above the airport and within a radius of 16 km (10 sm) from the airport. Patchy fog (sometimes referred to as patchy RVR) giving the effect of variable RVR. The lowest RVR should be that selected on the IOS, ie. variability is only greater than the IOS RVR. Effects of fog on airport lighting such as halos and defocus. Effect of ownship lighting in reduced visibility, such as reflected glare, to include landing lights, strobes, and beacons. Wind cues to provide the effect of blowing snow or sand across a dry runway or taxiway should be selectable from the instructor station. End QPS Requirement B c D X X X X X X X X X X X X -- Be2in Information An example of being able to "combine two airport models to achieve two "in-use" runways: One runway designated as the "in use" runway in the frrst model of the airport, and the second runway designated as the "in use" runway in the second model of the same airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right. Two airport visual models might be used: the first with Runway 27 designated as the "in use" runway for the approach to runway 27, and the second with Runway 18 Right designated as the "in use" runway. When the pilot breaks off the ILS approach to runway 27, the instructor may change to the second airport visual model in which runway 18 Right is designated as the "in use" runway, and the pilot would make a visual approach and landing. This process is acceptable to the FAA as long as the temporary interruption due to the visual model change is not distracting to the pilot, does not cause changes in navigational radio frequencies, and does not cause undue instructor/evaluator time. Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within the capabilities of the system. End Information 3. 4. ***** VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00066 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.063</GPH> mstockstill on DSK3G9T082PROD with RULES2 Simulator Level mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 ~ ~ e = z Motion System Effects A B c D INFORMATION Notes PO 00000 Frm 00067 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 This table specifies motion effects that are required to indicate when a flight crewmember must be able to recognize an event or situation. Where applicable, flight simulator pitch, side loading and directional control characteristics must be representative of the airplane. 1. Taxiing effects such as lateral, longitudinal, and directional X X cues resulting from steering and braking inputs. Runway contamination with associated anti-skid and taxiway characteristics. 2. Runway rumble, oleo deflection, ground speed, uneven X X X Different gross weights can also be selected, which may runway, runway/taxiway centerline light characteristics: also affect the associated Procedure: After the airplane has been pre-set to the takeoff vibrations depending on position and then released, taxi at various speeds with a smooth airplane type. The associated runway and note the general characteristics of the simulated motion effects for the above runway rumble effects of oleo deflections. Repeat the maneuver tests should also include an with a runway roughness of 50%, then with maximum assessment of the effects of roughness. Note the associated motion vibrations affected by rolling over centerline lights, ground speed and runway roughness. surface discontinuities of uneven runways, and various taxiway characteristics. 3. Buffets on the ground due to spoiler/speedbrake extension X X X X and reverse thrust: Procedure: Perform a normal landing and use ground spoilers and reverse thrust- either individually or in combination - to Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 . t>~ Table A3D - Functions and Subjective Tests QPS REQUIREMENTS Simulator Level 32081 ER20MY16.064</GPH> mstockstill on DSK3G9T082PROD with RULES2 32082 VerDate Sep<11>2014 Jkt 238001 ~ ~ PO 00000 Motion System Effects A B c D 4. decelerate the simulated airplane. Do not use wheel braking so that only the buffet due to the ground spoilers and thrust reversers is felt. Bumps associated with the landing gear: X X X X 5. Procedure: Perform a normal take-off paying special attention to the bumps that could be perceptible due to maximum oleo extension after lift-off. When the landing gear is extended or retracted, motion bumps can be felt when the gear locks into position. Buffet during extension and retraction of landing gear: X X X X X X X X Frm 00068 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.065</GPH> e 6. = z Procedure: Operate the landing gear. Check that the motion cues of the buffet experienced represent the actual airplane. Buffet in the air due to flap and spoiler/speedbrake extension: Procedure: Perform an approach and extend the flaps and slats with airspeeds deliberately in excess of the normal approach speeds. In cruise configuration, verify the buffets associated with the spoiler/speedbrake extension. The above effects can also be verified with different combinations of spoiler/speedbrake, flap, and landing gear settings to assess the interaction effects. INFORMATION Notes Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 . t>~ Table A3D - Functions and Subjective Tests QPS REQUIREMENTS Simulator Level mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 ~ ~ 7. PO 00000 8. e = z Motion System Effects Buffet due to atmospheric disturbances (e.g. buffet due to turbulence, windshear, proximity to thunderstorms, gusting winds, etc.). Approach to stall buffet and stall buffet (where applicable): B c D X A Frm 00069 Fmt 4701 X X X X X X X For FSTDs qualified for full stall training tasks, modeling that accounts for any increase in buffet amplitude from initial buffet threshold of perception to critical angle of attack or deterrent buffet as a function of angle of attack. The stall buffet modeling should include effects ofNz, as well as Nx and Ny if relevant. X X X X Sfmt 4725 E:\FR\FM\20MYR2.SGM 10. Procedure: Conduct several normal approaches with various rates of descent. Check that the motion cues for the touchdown bumps for each descent rate are representative of the actual airplane. Nosewheel scuffing: 20MYR2 Touchdown cues for main and nose gear: Procedure: Taxi at various ground speeds and manipulate the nosewheel steering to cause yaw rates to develop that cause the Notes X Procedure: Conduct an approach-to-stall with engines at idle and a deceleration of 1 knot/second. Check that the motion cues of the buffet, including the level ofbuffet increase with decreasing speed, are representative of the actual airplane. 9. INFORMATION Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 . t>~ Table A3D - Functions and Subjective Tests QPS REQUIREMENTS Simulator Level 32083 ER20MY16.066</GPH> mstockstill on DSK3G9T082PROD with RULES2 32084 VerDate Sep<11>2014 Jkt 238001 ~ ~ e = z Motion System Effects 12. Procedure: Set the brakes on at the take-off point and increase the engine power until buffet is experienced. Evaluate its characteristics. Confirm that the buffet increases appropriately with increasing engine thrust. Mach and maneuver buffet: 13. Procedure: With the simulated airplane trimmed in 1 g flight while at high altitude, increase the engine power so that the Mach number exceeds the documented value at which Mach buffet is experienced. Check that the buffet begins at the same Mach number as it does in the airplane (for the same configuration) and that buffet levels are representative of the actual airplane. For certain airplanes, maneuver buffet can also be verified for the same effects. Maneuver buffet can occur during turning flight at conditions greater than 1 g, particularly at higher altitudes. Tire failure dynamics: PO 00000 11. nosewheel to vibrate against the ground ("scuffing"). Evaluate the speed/nosewheel combination needed to produce scuffing and check that the resultant vibrations are representative of the actual airplane. Thrust effect with brakes set: Frm 00070 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.067</GPH> INFORMATION Notes A B c X X X X This effect is most discernible with wing-mounted engines. X X X X X The pilot may notice some yawing with a multiple tire D Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 . t>~ Table A3D - Functions and Subjective Tests QPS REQUIREMENTS Simulator Level mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 ~ ~ e = z Motion System Effects A B c D PO 00000 Procedure: Simulate a single tire failure and a multiple tire failure. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 15. Engine failures, malfunction, engine, and airframe structural damage: Procedure: The characteristics of an engine malfunction as stipulated in the malfunction definition document for the particular flight simulator must describe the special motion effects felt by the pilot. Note the associated engine instruments varying according to the nature of the malfunction and note the replication of the effects of the airframe vibration. Tail strikes, engine pod/propeller, wing strikes: Procedure: Tail-strikes can be checked by over-rotation ofthe airplane at a speed below Vr while performing a takeoff. The Notes failure selected on the same side. This should require the use of the rudder to maintain control of the airplane. Dependent on airplane type, a single tire failure may not be noticed by the pilot and should not have any special motion effect. Sound or vibration may be associated with the actual tire losing pressure. Frm 00071 14. INFORMATION X X X X X X The motion effect should be felt as a noticeable bump. If the tail strike affects the airplane angular rates, the Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 . t>~ Table A3D - Functions and Subjective Tests QPS REQUIREMENTS Simulator Level 32085 ER20MY16.068</GPH> mstockstill on DSK3G9T082PROD with RULES2 * 32086 * * VerDate Sep<11>2014 * Jkt 238001 PO 00000 Frm 00072 Fmt 4701 ~ ~ e Sfmt 4700 = z Motion System Effects effects can also be verified during a landing. E:\FR\FM\20MYR2.SGM Excessive banking of the airplane during its take-off/landing roll can cause a pod strike. A B c D INFORMATION Notes cueing provided by the motion system should have an associated effect. 20MYR2 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations * 18:26 May 19, 2016 ER20MY16.069</GPH> . t>~ Table A3D - Functions and Sub_jective Tests QPS REQUIREMENTS Simulator Level mstockstill on DSK3G9T082PROD with RULES2 * VerDate Sep<11>2014 * * * '"' Jkt 238001 Q~ .... e == Special Effects Simulator Level ~z Frm 00073 Fmt 4701 Sfmt 4700 E:\FR\FM\20MYR2.SGM 3. Correct the tables appearing on pages 18308–18326 to read as follows: ■ PO 00000 1. 2. A B c This table specifies the minimum special effects necessary for the specified simulator level. X Braking Dynamics: Representations of the dynamics of brake failure (flight simulator pitch, side-loading, and directional control characteristics representative of the airplane), including antiskid and decreased brake efficiency due to high brake temperatures (based on airplane related data), sufficient to enable pilot identification of the problem and implementation of appropriate procedures. X Effects of Airframe and Engine Icing: Required only for those airplanes authorized for operations in known icing conditions. 20MYR2 Procedure: With the simulator airborne, autopilot on and autothrottles off, engine and airfoil anti-ice/de-ice systems deactivated; activate icing conditions at a rate that allows monitoring of simulator and systems response. Icing recognition will typically include airspeed decay, change in simulator pitch attitude, change in engine performance indications (other than due to airspeed changes), and change in data from pitot/static system. Activate heating, anti-ice, or de-ice systems independently. Recognition will include proper effects of these systems, eventually returning the simulated airplane to normal flight. See Table AlA, section 2.j. and Attachment 7 for additional requirements. D X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations * 19:04 May 19, 2016 Table A3F - Functions and Sub.iective Tests QPS REQUIREMENTS 32087 ER20MY16.070</GPH> mstockstill on DSK3G9T082PROD with RULES2 32088 VerDate Sep<11>2014 Jkt 238001 Entry Number INFORMATION General FTD Requirements 4 PO 00000 Frm 00074 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 1. General Flight deck Configuration. The FTD must have a flight deck that is a replica of the airplane simulated l.a. with controls, equipment, observable flight deck indicators, circuit breakers, and bulkheads properly located, functionally accurate and replicating the airplane. The direction of movement of controls and switches must be identical to that in the airplane. Pilot seat(s) must afford the capability for the occupant to be able to achieve the design "eye position." Equipment for the operation of the flight deck windows must be included, but the actual windows need not be operable. Fire axes, extinguishers, and spare light bulbs must be available in the flight FTD, but may be relocated to a suitable location as near as practical to the original position. Fire axes, landing gear pins, and any similar purpose instruments need only be represented in silhouette. 20MYR2 The use of electronically displayed images with physical overlay or masking for FTD instruments and/or instrument panels is acceptable provided: (1) All instruments and instrument panel layouts are dimensionally correct with differences, if any, being imperceptible to the pilot; (2) Instruments replicate those of the airplane including full instrument functionality and embedded logic; (3) Instruments displayed are free of quantization (stepping); (4) Instrument display characteristics replicate those of the airplane including: resolution, colors, luminance, brightness, fonts, fill patterns, line styles and symbology; FTD Level 5 6 7 Notes X X For FTD purposes, the flight deck consists of all that space forward of a cross section of the fuselage at the most extreme aft setting of the pilots' seats including additional, required flight crewmember duty stations and those required bulkheads aft of the pilot seats. For clarification, bulkheads containing only items such as landing gear pin storage compartments, fire axes and extinguishers, spare light bulbs, aircraft documents pouches are not considered essential and may be omitted. For Level6 FTDs, flight deck window panes may be omitted where non-distracting and subjectively acceptable to Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 ER20MY16.071</GPH> Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number INFORMATION General FTD Requirements Jkt 238001 4 FTD Level 5 6 7 PO 00000 (5) Overlay or masking, including bezels and bugs, as applicable, replicates the airplane panel(s); (6) Instrument controls and switches replicate and operate with the same technique, effort, travel and in the same direction as those in the airplane; (7) Instrument lighting replicates that of the airplane and is operated from the FSTD control for that lighting and, if applicable, is at a level commensurate with other lighting operated by that same control; and (8) As applicable, instruments must have faceplates that replicate those in the airplane; and Frm 00075 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 l.b. Level 7 FTD only; The display image of any three dimensional instrument, such as an electromechanical instrument, should appear to have the same three dimensional depth as the replicated instrument. The appearance of the simulated instrument, when viewed from the principle operator's angle, should replicate that of the actual airplane instrument. Any instrument reading inaccuracy due to viewing angle and parallax present in the actual airplane instrument should be duplicated in the simulated instrument display image. Viewing angle error and parallax must be minimized on shared instruments such and engine displays and standby indicators. The FTD must have equipment (e.g., instruments, panels, systems, circuit breakers, and controls) simulated sufficiently for the authorized training/checking events to be accomplished. The installed equipment must be located in a spatially correct location and may be in a flight deck or an open flight deck area. Additional equipment required for the authorized Notes conduct qualified training tasks. X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32089 ER20MY16.072</GPH> mstockstill on DSK3G9T082PROD with RULES2 32090 VerDate Sep<11>2014 Entry Number General FTD Requirements Jkt 238001 4 PO 00000 Frm 00076 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM training/checking events must be available in the FTD, but may be located in a suitable location as near as practical to the spatially correct position. Actuation of equipment must replicate the appropriate function in the airplane. Fire axes, landing gear pins, and any similar purpose instruments need only be represented in silhouette. Those circuit breakers that affect procedures or result in observable flight l.c. deck indications must be properly located and functionally accurate. 2. Pro2rammin2. The FTD must provide the proper effect of aerodynamic changes for the 2.a.l combinations of drag and thrust normally encountered in flight. This must include the effect of change in airplane attitude, thrust, drag, altitude, temperature, and configuration. Level 6 additionally requires the effects of changes in gross weight and center of gravity. Level 5 requires only generic aerodynamic programming. 2.a.2 20MYR2 An SOC is required. A flight dynamics model that accounts for various combinations of drag and thrust normally encountered in flight must correspond to actual flight conditions, including the effect of change in airplane attitude, thrust, drag, altitude, temperature, gross weight, moments of inertia, center of gravity location, and configuration. The effects of pitch attitude and of fuel slosh on the aircraft center of gravity must be simulated. ER20MY16.073</GPH> INFORMATION FTD Level 5 6 7 X X X X Notes Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number Jkt 238001 2.b. PO 00000 Frm 00077 2.c.l Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 2.c.2. INFORMATION General FTD Requirements 4 An SOC is required. The FTD must have the computer capacity, accuracy, resolution, and dynamic response needed to meet the qualification level sought. An SOC is required. Relative responses of the flight deck instruments must be measured by latency tests, or transport delay tests, and may not exceed 300 milliseconds. The instruments must respond to abrupt input at the pilot's position within the allotted time, but not before the time when the airplane responds under the same conditions. (1) Latency: The FTD instrument and, if applicable, the motion system and the visual system response must not be prior to that time when the airplane responds and may respond up to 300 milliseconds after that time under the same conditions. (2) Transport Delay: As an alternative to the Latency requirement, a transport delay objective test may be used to demonstrate that the FTD system does not exceed the specified limit. The sponsor must measure all the delay encountered by a step signal migrating from the pilot's control through all the simulation software modules in the correct order, using a handshaking protocol, finally through the normal output interfaces to the instrument display and, if applicable, the motion system, and the visual system. Relative responses of the motion system, visual system, and flight deck instruments, measured by latency tests or transport delay tests. Motion onset should occur before the start of the visual scene change (the start of the scan of the first video field containing different information) but must occur before FTD Level 5 6 7 Notes X X X X X X The intent is to verify that the FTD provides instrument cues that are, within the stated time delays, like the airplane responses. For airplane response, acceleration in the appropriate, corresponding rotational axis is preferred. Additional information regarding Latency and Transport Delay testing may be found in Appendix A, Attachment 2, paragraph 15. X The intent is to verify that the FTD provides instrument, motion, and visual cues that are, within the stated time Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32091 ER20MY16.074</GPH> mstockstill on DSK3G9T082PROD with RULES2 32092 VerDate Sep<11>2014 Entry Number General FTD Requirements Jkt 238001 4 the end of the scan of that video field. Instrument response may not occur prior to motion onset. Test results must be within the following limits: PO 00000 Frm 00078 2.d.l. Ground effect. 2.d.2. Ground reaction. Ground handling characteristics, including aerodynamic and ground reaction modeling including steering inputs, operations with crosswind, gusting crosswind, braking, thrust reversing, deceleration, and turning radius. Fmt 4701 2.d. 100 ms for the motion (if installed) and instrument systems; and 120 ms for the visual system. Ground handling and aerodynamic programming must include the following: 2.d.3. Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.075</GPH> INFORMATION FTD Level 5 6 7 Notes delays, like the airplane responses. For airplane response, acceleration in the appropriate, corresponding rotational axis is preferred. X Ground effect includes modeling that accounts for roundout, flare, touchdown, lift, drag, pitching moment, trim, and power while in ground effect. X Ground reaction includes modeling that accounts for strut deflections, tire friction, and side forces. This is the reaction of the airplane upon contact with the runway during landing, and may differ with changes in factors such as gross weight, airspeed, or rate of descent on touchdown. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number Jkt 238001 2.e. INFORMATION General FTD Requirements 4 PO 00000 Frm 00079 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM If the aircraft being simulated is one of the aircraft listed in§ 121.358, Lowaltitude windshear system equipment requirements, the FTD must employ windshear models that provide training for recognition of windshear phenomena and the execution of recovery procedures. Models must be available to the instructor/evaluator for the following critical phases of flight: (1) Prior to takeoff rotation; (2) At liftoff; (3) During initial climb; and (4) On final approach, below 500 ft AGL. The QTG must reference the FAA Windshear Training Aid or present alternate airplane related data, including the implementation method(s) used. If the alternate method is selected, wind models from the Royal Aerospace Establishment (RAE), the Joint Airport Weather Studies (JAWS) Project and other recognized sources may be implemented, but must be supported and properly referenced in the QTG. The addition of realistic levels ofturbulence associated with each required windshear profile must be available and selectable to the instructor. 20MYR2 In addition to the four basic windshear models required for qualification, at least two additional "complex" windshear models must be available to the instructor which represent the complexity of actual windshear encounters. These models must be available in the takeoff and landing configurations and must consist of independent variable winds in multiple simultaneous components. The Windshear Training Aid provides two such example "complex" windshear models that may be used to satisfy this requirement. FTD Level 5 6 7 X Notes Windshear models may consist of independent variable winds in multiple simultaneous components. The FAA Windshear Training Aid presents one acceptable means of compliance with FTD wind model requirements. The FTD should employ a method to ensure the required survivable and non-survivable windshear scenarios are repeatable in the training environment. For Level 7 FTDs, windshear training tasks may only be qualified for aircraft equipped with a synthetic stall warning system. The qualified windshear profile(s) are evaluated to ensure the synthetic stall warning (and not the stall buffet) is first indication of the stall. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32093 ER20MY16.076</GPH> mstockstill on DSK3G9T082PROD with RULES2 32094 VerDate Sep<11>2014 Entry Number Jkt 238001 2.f. PO 00000 Frm 00080 2.g. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.077</GPH> 2.h. 2.i. General FTD Requirements 4 The FTD must provide for manual and automatic testing of FTD hardware and software programming to determine compliance with FTD objective tests as prescribed in Attachment 2 of this appendix. An SOC is required. The FTD must accurately reproduce the following runway conditions: (1) Dry; (2) Wet; (3) Icy; (4) Patchy Wet; (5) Patchy Icy; and (6) Wet on Rubber Residue in Touchdown Zone. An SOC is required. The FTD must simulate: (1) brake and tire failure dynamics, including anti skid failure; and (2) decreased brake efficiency due to high brake temperatures, if applicable. An SOC is required Engine and Airframe Icing Modeling that includes the effects of icing, where appropriate, on the airframe, aerodynamics, and the engine(s). Icing models must simulate the aerodynamic degradation effects of ice accretion on the airplane lifting surfaces including loss of lift, decrease in stall angle of attack, change in pitching moment, decrease in control effectiveness, and changes in control forces in addition to any overall increase in drag. Aircraft systems (such as INFORMATION FTD Level Notes 5 6 7 X Automatic "flagging" of outof-tolerance situations is encouraged. X X FTD pitch, side loading, and directional control characteristics should be representative of the airplane. X SOC should be provided describing the effects which provide training in the specific skills required for recognition of icing phenomena and execution of recovery. The SOC should describe the Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number General FTD Requirements Jkt 238001 4 the stall protection system and autoflight system) must respond properly to ice accretion consistent with the simulated aircraft. PO 00000 Frm 00081 Aircraft OEM data or other acceptable analytical methods must be utilized to develop ice accretion models that are representative of the simulated aircraft's performance degradation in a typical in-flight icing encounter. Acceptable analytical methods may include wind tunnel analysis and/or engineering analysis ofthe aerodynamic effects of icing on the lifting surfaces coupled with tuning and supplemental subjective assessment by a subject matter expert pilot. Fmt 4701 Sfmt 4725 SOC required. E:\FR\FM\20MYR2.SGM 20MYR2 2.j. INFORMATION The aerodynamic modeling in the FTD must include: (1) Low-altitude level-flight ground effect; (2) Mach effect at high altitude; (3) Normal and reverse dynamic thrust effect on control surfaces; (4) Aeroelastic representations; and (5) Nonlinearities due to sideslip. FTD Level 5 6 7 Notes source data and any analytical methods used to develop ice accretion models including verification that these effects have been tested. Icing effects simulation models are only required for those airplanes authorized for operations in icing conditions. Icing simulation models should be developed to provide training in the specific skills required for recognition of ice accumulation and execution of the required response. See Attachment 7 of this Appendix for further guidance material. X See Attachment 2 of this appendix, paragraph 5, for further information on ground effect. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32095 ER20MY16.078</GPH> mstockstill on DSK3G9T082PROD with RULES2 32096 VerDate Sep<11>2014 Entry Number Jkt 238001 PO 00000 2.k. General FTD Requirements 4 An SOC is required and must include references to computations of aeroelastic representations and of nonlinearities due to sideslip. The FTD must have aerodynamic and ground reaction modeling for the effects of reverse thrust on directional control, if applicable. Frm 00082 Fmt 4701 Sfmt 4725 An SOC is required. 3. Equipment Operation. All relevant instrument indications involved in the simulation of the airplane 3.a. must automatically respond to control movement or external disturbances to the simulated airplane; e.g., turbulence or windshear. Numerical values must be presented in the appropriate units. E:\FR\FM\20MYR2.SGM 3.b.l. 20MYR2 3.b.2. For Level 7 FTDs, instrument indications must also respond to effects resulting from icing. Navigation equipment must be installed and operate within the tolerances applicable for the airplane. Levels 6 must also include communication equipment (inter-phone and air/ground) like that in the airplane and, if appropriate to the operation being conducted, an oxygen mask microphone system. Level 5 need have only that navigation equipment necessary to fly an instrument approach. Communications, navigation, caution, and warning equipment must be installed and operate within the tolerances applicable for the airplane. Instructor control of internal and external navigational aids. Navigation aids ER20MY16.079</GPH> INFORMATION FTD Level 5 6 7 Notes X X X X X X X See Attachment 3 of this appendix for further information regarding longrange navigation equipment. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number Jkt 238001 PO 00000 3.b.3. Frm 00083 3.c.l. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 3.c.2. INFORMATION General FTD Requirements 4 FTD Level 5 6 7 Notes 20MYR2 must be usable within range or line-of-sight without restriction, as applicable to the geographic area. Complete navigation database for at least 3 airports with corresponding X precision and non-precision approach procedures, including navigational database updates. Installed systems must simulate the applicable airplane system operation, both X X X on the ground and in flight. Installed systems must be operative to the extent that applicable normal, abnormal, and emergency operating procedures included in the sponsor's training programs can be accomplished. Level 6 must simulate all applicable airplane flight, navigation, and systems operation. Level 5 must have at least functional flight and navigational controls, displays, and instrumentation. Level 4 must have at least one airplane system installed and functional. Simulated airplane systems must operate as the airplane systems operate X Airplane system operation under normal, abnormal, and emergency operating conditions on the ground should be predicated on, and and in flight. traceable to, the system data supplied by the airplane Once activated, proper systems operation must result from system manufacturer, original management by the crew member and not require any further input from the equipment manufacturer or instructor's controls. alternative approved data for the airplane system or component. At a minimum, alternate approved data should validate Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32097 ER20MY16.080</GPH> mstockstill on DSK3G9T082PROD with RULES2 32098 VerDate Sep<11>2014 Entry Number General FTD Requirements 4 Jkt 238001 PO 00000 Frm 00084 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.081</GPH> INFORMATION 3.d. The lighting environment for panels and instruments must be sufficient for the operation being conducted. 3.e. The FTD must provide control forces and control travel that corresponds to the airplane being simulated. Control forces must react in the same manner as in the airplane under the same flight conditions. FTD Level 5 6 7 Notes the operation of all normal, abnormal, and emergency operating procedures and training tasks the FSTD is qualified to conduct. X X X X Back-lighted panels and instruments may be installed but are not required. X X For Level 7 FTDs, control systems must replicate airplane operation for the normal and any non-normal modes including back-up systems and should reflect failures of associated systems. Appropriate cockpit indications and messages must be replicated. The FTD must provide control forces and control travel of sufficient precision 3.f. X to manually fly an instrument approach. FTD control feel dynamics must replicate the airplane. This must be X 3.e. determined by comparing a recording of the control feel dynamics of the FTD to airplane measurements. For initial and upgrade qualification evaluations, the control dynamic characteristics must be measured and recorded directly from the flight deck controls, and must be accomplished in takeoff, cruise, and landing flight conditions and configurations. 4. Instructor or Evaluator Facilities. In addition to the flight crewmember stations, suitable seating arrangements These seats need not be a 4.a.l. X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number General FTD Requirements Jkt 238001 4 for an instructor/check airman and FAA Inspector must be available. These seats must provide adequate view of crewmember's panel(s). PO 00000 4.a.2. Frm 00085 Fmt 4701 4.b.l. Sfmt 4725 E:\FR\FM\20MYR2.SGM 4.b.2. 20MYR2 4.c. 4.d. INFORMATION FTD Level 5 6 7 Notes replica of an aircraft seat and may be as simple as an office chair placed in an appropriate position. X The NSPM will consider alternatives to this standard for additional seats based on unique flight deck configurations. In addition to the flight crewmember stations, the FTD must have at least two suitable seats for the instructor/check airman and FAA inspector. These seats must provide adequate vision to the pilot's panel and forward windows. All seats other than flight crew seats need not represent those found in the airplane, but must be adequately secured to the floor and equipped with similar positive restraint devices. The FTD must have instructor controls that permit activation of normal, X X X abnormal, and emergency conditions as appropriate. Once activated, proper system operation must result from system management by the crew and not require input from the instructor controls. The FTD must have controls that enable the instructor/evaluator to control all X required system variables and insert all abnormal or emergency conditions into the simulated airplane systems as described in the sponsor's FAAapproved training program; or as described in the relevant operating manual as appropriate. The FTD must have instructor controls for all environmental effects expected X to be available at the lOS; e.g., clouds, visibility, icing, precipitation, temperature, storm cells and microbursts, turbulence, and intermediate and high altitude wind speed and direction. The FTD must provide the instructor or evaluator the ability to present ground X For example, another airplane crossing the active runway or and air hazards. converging airborne traffic. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32099 ER20MY16.082</GPH> mstockstill on DSK3G9T082PROD with RULES2 32100 VerDate Sep<11>2014 Entry Number General FTD Requirements Jkt 238001 4 PO 00000 Frm 00086 Fmt 4701 Sfmt 4725 5. Motion System. The FTD may have a motion system, if desired, although it is not required. If 5.a. a motion system is installed and additional training, testing, or checking credits are being sought on the basis of having a motion system, the motion system operation may not be distracting and must be coupled closely to provide integrated sensory cues. The motion system must also respond to abrupt input at the pilot's position within the allotted time, but not before the time when the airplane responds under the same conditions. If a motion system is installed, it must be measured by latency tests or 5.b. transport delay tests and may not exceed 300 milliseconds. Instrument response may not occur prior to motion onset. E:\FR\FM\20MYR2.SGM 6. Visual System. The FTD may have a visual system, if desired, although it is not required. If a visual 6.a. system is installed, it must meet the following criteria: The visual system must respond to abrupt input at the pilot's position. 6.a.l. 6.a.2. 20MYR2 6.a.3. 6.a.4. An SOC is required. The visual system must be at least a single channel, non-collimated display. An SOC is required. The visual system must provide at least a field-of-view of 18° vertical I 24° horizontal for the pilot flying. An SOC is required. The visual system must provide for a maximum parallax of 10° per pilot. An SOC is required. ER20MY16.083</GPH> INFORMATION FTD Level 5 6 7 Notes X X X The motion system standards set out in part 60, Appendix A for at least Level A simulators is acceptable. X X The motion system standards set out in part 60, Appendix A for at least Level A simulators is acceptable. X X X X X X X X X X X X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number INFORMATION FTD Level General FTD Requirements Jkt 238001 4 PO 00000 Frm 00087 6.a.5. The visual scene content may not be distracting. 6.a.6. An SOC is required. The visual system must provide for a minimum resolution of 5 arc-minutes for both computed and displayed pixel size. 6 Notes 7 An SOC is required. The minimum distance from the pilot's eye position to the surface of a direct view display may not be less than the distance to any front panel instrument. 6.a.7. 5 Fmt 4701 6.b. Sfmt 4725 E:\FR\FM\20MYR2.SGM 6.c. 6.d. An SOC is required. If a visual system is installed and additional training, testing, or checking credits are being sought on the basis of having a visual system, a visual system meeting the standards set out for at least a Level A FFS (see Appendix A of this part) will be required. A "direct-view," non-collimated visual system (with the other requirements for a Level A visual system met) may be considered satisfactory for those installations where the visual system design "eye point" is appropriately adjusted for each pilot's position such that the parallax error is at or less than 1oo simultaneously for each pilot. 20MYR2 An SOC is required. The FTD must have a visual system providing an out-of-the-flight deck view. The FTD must provide a continuous visual field-of-view of at least176° horizontally and 36° vertically or the number of degrees necessary to meet the visual ground segment requirement, whichever is greater. The minimum horizontal field-of-view coverage must be plus and minus one-half(Yz) ofthe minimum continuous field-of-view requirement, centered on the zero degree azimuth line relative to the aircraft fuselage. X X X X X X X Directly projected, noncollimated visual displays may prove to be unacceptable for dual pilot applications. X X The horizontal field-of-view is traditionally described as a 180° field-of-view. However, the field-of-view is technically no less than 176°. Additional field-of-view capability may be added at the sponsor's Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32101 ER20MY16.084</GPH> mstockstill on DSK3G9T082PROD with RULES2 32102 VerDate Sep<11>2014 Entry Number General FTD Requirements Jkt 238001 4 An SOC is required and must explain the system geometry measurements including system linearity and field-of-view. PO 00000 Frm 00088 6.e. Collimation is not required but parallax effects must be minimized (not greater than 10° for each pilot when aligned for the point midway between the left and right seat eyepoints). The visual system must be free from optical discontinuities and artifacts that create non-realistic cues. Fmt 4701 Sfmt 4725 6.f. E:\FR\FM\20MYR2.SGM 6.g. 20MYR2 6.h. 6.i. ER20MY16.085</GPH> INFORMATION FTD Level 5 6 7 The FTD must have operational landing lights for night scenes. Where used, dusk (or twilight) scenes require operational landing lights. The FTD must have instructor controls for the following: (1) Visibility in statute miles (km) and runway visual range (RVR) in ft.(m); (2) Airport selection; and (3) Airport lighting. The FTD must provide visual system compatibility with dynamic response programmmg. The FTD must show that the segment of the ground visible from the FTD flight deck is the same as from the airplane flight deck (within established tolerances) when at the correct airspeed, in the landing configuration, at the appropriate height above the touchdown zone, and with appropriate visibility. Notes discretion provided the minimum fields of view are retained. X Non-realistic cues might include image "swimming" and image "roll-off," that may lead a pilot to make incorrect assessments of speed, acceleration, or situational awareness. X X X X This will show the modeling accuracy ofRVR, glideslope, and localizer for a given weight, configuration, and speed within Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number INFORMATION General FTD Requirements Jkt 238001 4 FTD Level 5 6 7 Notes the airplane's operational envelope for a normal approach and landing. PO 00000 6.j. Frm 00089 6.k. Fmt 4701 Sfmt 4725 6.1. E:\FR\FM\20MYR2.SGM 6.m. 6.n. 20MYR2 6.o. The FTD must provide visual cues necessary to assess sink rates (provide depth perception) during takeoffs and landings, to include: (1) Surface on runways, taxiways, and ramps; and (2) Terrain features. The FTD must provide for accurate portrayal of the visual environment relating to the FTD attitude. The FTD must provide for quick confirmation of visual system color, RVR, focus, and intensity. An SOC is required. The FTD must be capable of producing at least 10 levels of occulting. Night Visual Scenes. When used in training, testing, or checking activities, the FTD must provide night visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a pilot to successfully accomplish a visual landing. Scenes must include a definable horizon and typical terrain characteristics such as fields, roads and bodies of water and surfaces illuminated by airplane landing lights. Dusk (or Twilight) Visual Scenes. When used in training, testing, or X X Visual attitude vs. FTD attitude is a comparison of pitch and roll of the horizon as displayed in the visual scene compared to the display on the attitude indicator. X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS X 32103 ER20MY16.086</GPH> mstockstill on DSK3G9T082PROD with RULES2 32104 VerDate Sep<11>2014 Entry Number Jkt 238001 General FTD Requirements 4 5 6 Notes 7 checking activities, the FTD must provide dusk (or twilight) visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a pilot to successfully accomplish a visual landing. Dusk (or twilight) scenes, as a minimum, must provide full color presentations of reduced ambient intensity, sufficient surfaces with appropriate textural cues that include self-illuminated objects such as road networks, ramp lighting and airport signage, to conduct a visual approach, landing and airport movement (taxi). Scenes must include a definable horizon and typical terrain characteristics such as fields, roads and bodies of water and surfaces illuminated by airplane landing lights. If provided, directional horizon lighting must have correct orientation and be consistent with surface shading effects. Total night or dusk (twilight) scene content must be comparable in detail to that produced by 10,000 visible textured surfaces and 15,000 visible lights with sufficient system capacity to display 16 simultaneously moving objects. PO 00000 Frm 00090 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.087</GPH> INFORMATION FTD Level 6.p. An SOC is required. Daylight Visual Scenes. The FTD must provide daylight visual scenes with sufficient scene content to recognize the airport, the terrain, and major landmarks around the airport. The scene content must allow a pilot to successfully accomplish a visual landing. Any ambient lighting must not "washout" the displayed visual scene. Total daylight scene content must be comparable in detail to that produced by 10,000 visible textured surfaces and 6,000 visible lights with sufficient system capacity to display 16 simultaneously moving objects. The visual display must be free of apparent and distracting quantization and other distracting visual effects while the FTD X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Entry Number INFORMATION General FTD Requirements Jkt 238001 4 FTD Level 5 6 7 Notes is in motion. PO 00000 6.q. An SOC is required. The FTD must provide operational visual scenes that portray physical relationships known to cause landing illusions to pilots. Frm 00091 Fmt 4701 6.r. Sfmt 4725 E:\FR\FM\20MYR2.SGM 6.s. 6.t. 6.u. 20MYR2 The FTD must provide special weather representations of light, medium, and heavy precipitation near a thunderstorm on takeoff and during approach and landing. Representations need only be presented at and below an altitude of 2,000 ft. (610 m) above the airport surface and within 10 miles (16 km) of the airport. The FTD must present visual scenes of wet and snow-covered runways, including runway lighting reflections for wet conditions, partially obscured lights for snow conditions, or suitable alternative effects. The FTD must present realistic color and directionality of all airport lighting. The following weather effects as observed on the visual system must be simulated and respective instructor controls provided. (1) Multiple cloud layers with adjustable bases, tops, sky coverage and scud effect; (2) Storm cells activation and/or deactivation; (3) Visibility and runway visual range (RVR), including fog and patchy fog effect; (4) Effects on ownship external lighting; X For example: short runways, landing approaches over water, uphill or downhill runways, rising terrain on the approach path, unique topographic features. X X X X Scud effects are low, detached, and irregular clouds below a defined cloud layer. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32105 ER20MY16.088</GPH> mstockstill on DSK3G9T082PROD with RULES2 32106 VerDate Sep<11>2014 Entry Number Jkt 238001 PO 00000 Frm 00092 6.v. General FTD Requirements 4 Fmt 4701 (5) Effects on airport lighting (including variable intensity and fog effects); (6) Surface contaminants (including wind blowing effect); (7) Variable precipitation effects (rain, hail, snow); (8) In-cloud airspeed effect; and (9) Gradual visibility changes entering and breaking out of cloud. The simulator must provide visual effects for: (1) Light poles; (2) Raised edge lights as appropriate; and (3) Glow associated with approach lights in low visibility before physical lights are seen, Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 7. Sound System. The FTD must provide flight deck sounds that result from pilot actions that 7.a. correspond to those that occur in the airplane. The volume control must have an indication of sound level setting which 7.b. meets all qualification requirements. 7.c. ER20MY16.089</GPH> INFORMATION FTD Level The FTD must accurately simulate the sound of precipitation, windshield wipers, and other significant airplane noises perceptible to the pilot during normal and abnormal operations, and include the sound of a crash (when the FTD is landed in an unusual attitude or in excess of the structural gear 5 Notes 6 7 X Visual effects for light poles and raised edge lights are for the purpose of providing additional depth perception during takeoff, landing, and taxi training tasks. Three dimensional modeling of the actual poles and stanchions is not required. X X X This indication is of the sound level setting as evaluated during the FTD's initial evaluation. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 PO 00000 Frm 00093 Entry Number INFORMATION General FTD Requirements 4 FTD Level 5 6 7 Fmt 4701 limitations); normal engine and thrust reversal sounds; and the sounds of flap, gear, and spoiler extension and retraction. Sfmt 4725 Sounds must be directionally representative. E:\FR\FM\20MYR2.SGM 7.d. An SOC is required. The FTD must provide realistic amplitude and frequency of flight deck noises and sounds. FTD performance must be recorded, subjectively assessed for the initial evaluation, and be made a part of the QTG .. X Notes 20MYR2 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table BlA- Minimum FTD Requirements QPS REQUIREMENTS 32107 ER20MY16.090</GPH> mstockstill on DSK3G9T082PROD with RULES2 32108 VerDate Sep<11>2014 Jkt 238001 PO 00000 Frm 00094 Fmt 4701 Sfmt 4725 the end of the Table 1. Prefli!!;ht Procedures. Preflight Inspection (flight deck only) l.a. Engine Start l.b. Taxiing l.c. Pre-takeoff Checks l.d. 2. Takeoff and Departure Phase. Normal and Crosswind Takeoff 2.a. Instrument Takeoff 2.b. Engine Failure During Takeoff 2.c. Rejected Takeoff (requires visual system) 2.d. Departure Procedure 2.e. 3. Inflight Maneuvers. Steep Turns 3.a. Approaches to Stalls 3.b E:\FR\FM\20MYR2.SGM 20MYR2 3.c. 3.d. 3.e. Engine Failure-Multiengine Airplane Engine Failure-Single-Engine Airplane Specific Flight Characteristics incorporated into the user's FAA approved flight training program. 3.f. ER20MY16.091</GPH> Notes 7 A A A A X X A A X X X T X X A X T T T X X X A X X X X A A A X X A X X A Windshear Recovery 4. Instrument Procedures. Standard Terminal Arrival I Flight Management System Arrivals Procedures 4.a. INFORMATION A T A X X Approach to stall maneuvers qualified only where the aircraft does not exhibit stall buffet as the first indication of the stall. Level 4 FTDs have no minimum requirement for aerodynamic programming and are generally not qualified to conduct in-flight maneuvers. For Level 7 FTD, windshear recovery may be qualified at the Sponsor's option. See Table B lA for specific requirements and limitations. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Entry Number Table BlB - Table of Tasks vs. FTD Level QPS REQUIREMENTS FTD Subjective Requirements In order to be qualified at the FTD qualification level indicated, the FTD must be able to Level perform at least the tasks associated with that level of qualification. See Notes 1, 2 and 3 at 4 5 6 mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 the end of the Table Holding Precision Instrument All engines operating. PO 00000 4.c.2. One engine inoperative. 4.d. Non-precision Instrument Approach Frm 00095 Jkt 238001 4.b. 4.c. 4.c.l. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 Circling Approach (requires visual system) 4.e. Missed Approach 4.f. Normal. 4.f.l. One engine Inoperative. 4.f.2. S. Landings and Approaches to Landings. Normal and Crosswind Approaches and Landings S.a. Landing From a Precision I Non-Precision Approach S.b. Approach and Landing with (Simulated) Engine Failure - Multiengine Airplane S.c. Landing From Circling Approach S.d. Rejected Landing S.e. Landing From a No Flap or a Nonstandard Flap Configuration Approach S.f. 6. Normal and Abnormal Procedures. Engine (including shutdown and restart) 6.a. Fuel System 6.b. Electrical System 6.c. Hydraulic System 6.d. Environmental and Pressurization Systems 6.e. Fire Detection and Extinguisher Systems 6.f. Navigation and Avionics Systems 6.g. Automatic Flight Control System, Electronic Flight Instrument System, and 6.h. Related Subsystems INFORMATION Notes 7 A X X A X X T A X A A X X X X T T T T T T T A A A A A A A A A A A A A A A A X X X X X X X X X X X X X X X X e.g., Autopilot, Manual (Flt. Dir. Assisted), Manual (Raw Data) e.g., Manual (Flt. Dir. Assisted), Manual (Raw Data) e.g., NDB, VOR, VOR/DME, VOR/TAC, RNAV, LOC, LOC/BC, ADF, and SDF. Specific authorization required. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Entry Number Table BlB - Table of Tasks vs. FTD Level QPS REQUIREMENTS FTD Subjective Requirements In order to be qualified at the FTD qualification level indicated, the FTD must be able to Level perform at least the tasks associated with that level of qualification. See Notes 1, 2 and 3 at 4 5 6 32109 ER20MY16.092</GPH> mstockstill on DSK3G9T082PROD with RULES2 32110 Jkt 238001 INFORMATION Notes Frm 00096 Fmt 4701 Sfmt 4700 X X X X X X X X IX I Note 1: An "A" in the table indicates that the system, task, or procedure, although not required to be present, may be examined if the appropriate airplane system is simulated in the FTD and is working properly. ■ ■ 20MYR2 A. Revise paragraph 2.e; B. Revise Table B2A; E:\FR\FM\20MYR2.SGM 15. Amend Attachment 2 to Appendix B as follows: ■ PO 00000 7 Note 2: Items not installed or not functional on the FTD and not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ. Note 3: A "T" in the table indicates that the task may only be qualified for introductory initial or recurrent qualification training. These tasks may not be qualified for proficiency testing or checking credits in an FAA approved flight training program.</PHOTO> Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 4. On page 18327, correct amendatory instruction 15 to read as follows: ■ VerDate Sep<11>2014 ER20MY16.093</GPH> Table BlB - Table of Tasks vs. FTD Level QPS REQUIREMENTS FTD Subjective Requirements Entry In order to be qualified at the FTD qualification level indicated, the FTD must be able to Level perform at least the tasks associated with that level of qualification. See Notes 1, 2 and 3 at Number 4 5 6 the end of the Table Flight Control Systems 6.i. A A X Anti-ice and Deice Systems 6.j. A A X Aircraft and Personal Emergency Equipment 6.k. A A X 7. Emergency Procedures. Emergency Descent (Max. Rate) 7.a. A X Inflight Fire and Smoke Removal 7.b. A X Rapid Decompression 7.c. A X Emergency Evacuation 7.d. A A X 8. Postflight Procedures. After-Landing Procedures 8.a. A A X I Parking and Securing 8.b. I A IA IX Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations mstockstill on DSK3G9T082PROD with RULES2 ■ ■ ■ ■ C. Revise Table B2B; D. Revise Table B2C; E. Revise Table B2D; and F. Revise Table B2E. VerDate Sep<11>2014 18:26 May 19, 2016 The revisions and additions read as follows: * * * * * Jkt 238001 PO 00000 Frm 00097 Fmt 4701 Sfmt 4700 32111 5. Correct the tables appearing on pages 18329–18375 to read as follows: ■ E:\FR\FM\20MYR2.SGM 20MYR2 mstockstill on DSK3G9T082PROD with RULES2 32112 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number Title Flight Conditions 5 6 Notes 7 1. Performance. Taxi. Ground. l.a.2 ±10% or ±2°/s of tum rate. Ground. Fmt 4701 Rate of tum versus nosewheel steering angle (NWA). Lb. Takeoff. l.b.l Ground acceleration time and distance. ±1.5 s or ±5% of time; and ±61 m (200ft) or ±5% of distance. Takeoff. Sfmt 4725 ±0.9 m (3 ft) or ±20% of airplane tum radius. Frm 00098 PO 00000 l.a. l.a.l Minimum radius tum. E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.094</GPH> Test Details INFORMATION FTD Level Plot both main and nose gear loci and key engine parameter(s). Data for no brakes and the minimum thrust required to maintain a steady tum except for airplanes requiring asymmetric thrust or braking to achieve the minimum radius tum. Record for a minimum of two speeds, greater than minimum turning radius speed with one at a typical taxi speed, and with a spread of at least 5 kt Note.- For Level7 FTD, all airplane manufacturer commonly-used certificated takeoffflap settings must be demonstrated at least once either in minimum unstick speed (l.b.3), normal take-off(l.b.4), critical engine failure on take-off(l.b.5) or crosswind take-off(l.b.6). Acceleration time and distance must be recorded for a minimum of 80% of the total time from brake release to V,. Preliminary aircraft certification data may be used. X X X X For Level 6 FTD: ±1.5 s or ±5% of time. l.b.2 Minimum control speed, ground (VmcJ using aerodynamic controls only per applicable airworthiness ±25% of maximum airplane lateral deviation reached or ±1.5 m (5 ft). For airplanes with Takeoff. Engine failure speed must be within ±1 kt of airplane engine failure speed. Engine thrust decay must be that resulting from the mathematical model for the engine applicable to the FTD under test If the modeled engine is not the same as the airplane manufacturer's flight test engine, a X May be combined with normal takeoff ( 1. b. 4.) or rejected takeoff(Lb.7.). Plotted data should be shown using appropriate scales for each portion of the maneuver. For Level6 FTD, this test is required only ifRTO training credit is sought If a Vmeg test is not available, an acceptable alternative is a flight test snap engine deceleration to idle at a speed between v, and v,-10 kt, followed by control of heading using aerodynamic Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Fli2ht Trainin2 Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title PO 00000 requirement or alternative engine inoperative test to demonstrate ground control characteristics. Frm 00099 l.b.3 Fmt 4701 Minimum unstick speed (Vmu) or equivalent test to demonstrate early rotation take-off characteristics. Flight Conditions reversible flight control systems: Test Details INFORMATION FTD Level 5 6 Notes 7 control only and recovery should be achieved with the main gear on the ground. further test may be run with the same initial conditions using the thrust from the flight test data as the driving parameter. ±I 0% or ±2.2 daN ( 5 lbt) rudder pedal force. ±3 kt airspeed. ±1.5° pitch angle. Takeoff. Record time history data from 10 knots before start of rotation until at least 5 seconds after the occurrence of main gear lift-off. X Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 l.b.4 Normal take-off. ±3 kt airspeed. ±1.5° pitch angle. ±1.5° AOA. ±6 m (20 ft) height. For airplanes with Takeoff. Data required for near maximum certificated takeoff weight at mid center of gravity location and light takeoff weight at an aft center of gravity location. If the airplane has more than one certificated take-off configuration, a different configuration must be used for each weight. X To ensure only aerodynamic control, nosewheel steering must be disabled (i.e. castored) or the nosewheel held slightly off the ground. vmu is defined as the minimum speed at which the last main landing gear leaves the ground. Main landing gear strut compression or equivalent air/ground signal should be recorded. If a V mu test is not available, alternative acceptable flight tests are a constant highattitude takeoff run through main gear lift-off or an early rotation takeoff. If either of these alternative solutions is selected, aft body contact/tail strike protection functionality, if present on the airplane, should be active. The test may be used for ground acceleration time and distance (I. b.!). Plotted data should be shown using appropriate scales for each portion of the maneuver. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS Record takeoff profile from brake release to at least 61 m (200ft) AGL. 32113 ER20MY16.095</GPH> mstockstill on DSK3G9T082PROD with RULES2 32114 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 reversible flight control systems: PO 00000 l.b.S Critical engine failure on take-off. ±2.2 daN ( 5 lbt) or ±I 0% of column force. ±3 kt airspeed. Takeoff. ±1.5° pitch angle. Frm 00100 ±1.5° AOA. Record takeoff profile to at least 61 m (200ft) AGL. X Engine failure speed must be within ±3 kt of airplane data. ±6 m (20ft) height. Fmt 4701 ±2° roll angle. Test at near maximum takeoff weight ±2° side-slip angle. ±3° heading angle. Sfmt 4725 For airplanes with reversible flight control systems: E:\FR\FM\20MYR2.SGM ±2.2 daN ( 5 lbt) or ±I 0% of column force; ± 1.3 daN (3 lbt) or ±10% of wheel force; and 20MYR2 l.b.6 Crosswind take-off. ±2.2 daN ( 5 lbt) or ±10% of rudder pedal force. ± 3 kt airspeed. Takeoff. Record takeoff profile from brake release to at least 61 m (200ft) AGL. ±1.5° pitch angle. ±6 m (20 ft) height. This test requires test data, including wind profile, for a crosswind component of at least 60% of the airplane performance data value measured at 10m (33ft) above the runway. ±2° roll angle. Wind components must be provided as headwind ±1.5° AOA. ER20MY16.096</GPH> X In those situations where a maximum crosswind or a maximum demonstrated crosswind is not known, contact theNSPM. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 and crosswind values with respect to the runway. ±2° side-slip angle. PO 00000 ±3° heading angle. Frm 00101 Correct trends at ground speeds below 40 kt for rudder/pedal and heading angle. Fmt 4701 For airplanes with reversible flight control systems: Sfmt 4725 ±2.2 daN ( 5 lbt) or ±I 0% of column force; E:\FR\FM\20MYR2.SGM ± 1.3 daN (3 lbt) or ±10% of wheel force; and l.b.7.a. Rejected Takeoff. ±2.2 daN (5 lbt) or ±I 0% of rudder pedal force. ±5% of time or ±1.5 s. 20MYR2 ±7.5% of distance or ±76 m (250ft). For Level 6 FTD: ±5% oftime or ±1.5 s. Takeoff. Record at mass near maximum takeoff weight. Speed for reject must be at least 80% ofV 1. Maximum braking effort, auto or manual. Where a maximum braking demonstration is not available, an acceptable alternative is a test using approximately 80% braking and full reverse, if applicable. X Autobrakes will be used where applicable. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS Time and distance must be recorded from brake release to a full stop. 32115 ER20MY16.097</GPH> mstockstill on DSK3G9T082PROD with RULES2 32116 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number Title Flight Conditions Test Details PO 00000 l.b.7.b. Rejected Takeoff. ±5% of time or ±1.5 s. Takeoff Dynamic Engine Failure After Takeoff. ±2°/s or ±20% of body angular rates. Takeoff. 6 Engine failure speed must be within ±3 kt of airplane data. Notes 7 X X Engine failure may be a snap deceleration to idle. Frm 00102 Record hands-off from 5 s before engine failure to +5 s or 30° roll angle, whichever occurs first. For Level6 FTD, this test is required only ifRTO training credit is sought. For safety considerations, airplane flight test may be performed out of ground effect at a safe altitude, but with correct airplane configuration and airspeed. Fmt 4701 CCA: Test in Normal and Non-normal control state. I.e. l.c.l. Climb. Sfmt 4725 Normal Climb, all engines operating. ±3 kt airspeed. Clean. ±0.5 m/s (100 ftl min) or ±5% of rate of climb. Flight test data are preferred; however, airplane performance manual data are an acceptable alternative. X X X E:\FR\FM\20MYR2.SGM Record at nominal climb speed and mid initial climb altitude. FTD performance is to be recorded over an interval of at least 300m (1, 000 ft). l.c.2. One-engineinoperative 2nd segment climb. ±3 kt airspeed. 20MYR2 ±0.5 m/s (100 ftl min) or ±5% of rate of climb, but not less than airplane performance data requirements. 2nd segment climb. Flight test data is preferred; however, airplane performance manual data is an acceptable alternative. Record at nominal climb speed. FTD performance is to be recorded over an interval of at least 300m (1,000 ft). Test at WAT (weight, altitude or temperature) limiting condition. ER20MY16.098</GPH> 5 Record time for at least 80% of the segment from initiation of the rejected takeoff to full stop. l.b.8. INFORMATION FTD Level X For Level 5 and Level 6 FTDs, this may be a snapshot test result. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions PO 00000 One Engine Inoperative En route Climb. ±10% time, ±10% distance, ±10% fuel used Clean l.c.4. One Engine Inoperative Approach Climb for airplanes with icing accountability if provided in the airplane performance data for this phase of flight. ±3 kt airspeed. Approach Frm 00103 l.c.3. Fmt 4701 Sfmt 4725 l.d. Level flight acceleration Flight test data or airplane performance manual data may be used. Test for at least a 1,550 m (5,000 ft) segment. Flight test data or airplane performance manual data may be used. 5 6 Notes 7 X X FTD performance to be recorded over an interval of at least 300 m (1,000 ft). E:\FR\FM\20MYR2.SGM l.d.2. Level flight deceleration. 20MYR2 l.d.3. Cruise performance. l.d.4. Idle descent. ±5%Time ±5%Time ±.05 EPR or ±3% Nl or ±5% oftorque. ±5% of fuel flow. ±3 kt airspeed. ±1.0 m/s (200ft/min) or ±5% of rate of descent. Cruise Cruise Cruise. Clean. Time required to increase airspeed a minimum of 50 kt, using maximum continuous thrust rating or equivalent. For airplanes with a small operating speed range, speed change may be reduced to 80% of operational speed change. Time required to decrease airspeed a minimum of 50 kt, using idle power. For airplanes with a small operating speed range, speed change may be reduced to 80% of operational speed change. The test may be a single snapshot showing instantaneous fuel flow, or a minimum of two consecutive snapshots with a spread of at least 3 minutes in steady flight. Idle power stabilized descent at normal descent speed at mid altitude. Airplane should be configured with all anti-ice and de-ice systems operating normally, gear up and go-around flap. All icing accountability considerations, in accordance with the airplane performance data for an approach in icing conditions, should be applied. Test near maximum certificated landing weight as may be applicable to an approach in icing conditions. Cruise I Descent. l.d.l. ±0.5 m/s (100 ftl min) or ±5% rate of climb, but not less than airplane performance data. Test Details INFORMATION FTD Level X X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS FTD performance to be recorded over an interval 32117 ER20MY16.099</GPH> mstockstill on DSK3G9T082PROD with RULES2 32118 VerDate Sep<11>2014 Test Jkt 238001 Entry Number l.d.S. Tolerance Title Emergency descent. ±5 kt airspeed. Flight Conditions As per airplane performance data. of at least 300 m (1,000 ft). FTD performance to be recorded over an interval of at least 900 m (3,000 ft). 5 6 Notes 7 X PO 00000 ±1.5 m/s (300 ft:lmin) or ±5% of rate of descent. Frm 00104 I.e. l.e.l. Stopping. Fmt 4701 Deceleration time and distance, manual wheel brakes, dry runway, no reverse thrust. ±1.5 s or ±5% of time. Landing. For distances up to 1,220 m (4,000 ft), the smaller of ±61 m (200 ft) or ±10% of distance. Time and distance must be recorded for at least 80% of the total time from touchdown to a full stop. Sfmt 4725 E:\FR\FM\20MYR2.SGM l.e.2. Deceleration time and distance, reverse thrust, no wheel brakes, dry runway. X Position of ground spoilers and brake system pressure must be plotted (if applicable). For distances greater than 1,220 m (4,000 ft), ±5% of distance. Data required for medium and near maximum certificated landing weight. ±1.5 s or ±5% of time; and Engineering data may be used for the medium weight condition. Time and distance must be recorded for at least 80% of the total time from initiation of reverse thrust to full thrust reverser minimum operating speed. Landing the smaller of ±61 m (200ft) or ±10% of distance. X 20MYR2 Position of ground spoilers must be plotted (if applicable). Data required for medium and near maximum certificated landing weight. l.e.3. ER20MY16.100</GPH> Test Details INFORMATION FTD Level Stopping distance, wheel brakes, wet ±61 m (200ft) or ±10% of distance. Landing. Engineering data may be used for the medium weight condition. Either flight test or manufacturer's performance manual data must be used, where available. X Stabilized descent to be conducted with speed brakes extended if applicable, at mid altitude and near Vmo or according to emergency descent procedure. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Fli~ht Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions runway. PO 00000 l.e.4. Stopping distance, wheel brakes, icy runway. Frm 00105 Fmt 4701 l.f. Acceleration. Landing. 5 6 Engineering data, based on dry runway flight test stopping distance and the effects of contaminated runway braking coefficients, are an acceptable alternative. Either flight test or manufacturer's performance manual data must be used, where available. Notes 7 X Engineering data, based on dry runway flight test stopping distance and the effects of contaminated runway braking coefficients, are an acceptable alternative. Engines. l.f.l. ±61 m (200ft) or ±10% of distance. Test Details INFORMATION FTD Level For Level 7 FTD: ±10% Ti or ±0.2S s; and ±10% Tt or ±0.2S s. Sfmt 4725 E:\FR\FM\20MYR2.SGM Approach or landing Total response is the incremental change in the critical engine parameter from idle power to goaround power. X X X See Appendix F of this part for definitions ofTi. and T,. Ground Total response is the incremental change in the critical engine parameter from maximum take-off power to idle power. X X X See Appendix F of this part for definitions ofTi, and T1. For Level 6 FTD: ±10% Tt or ±0.2S s. l.f.2. Deceleration. For LevelS FTD: ±1 s For Level 7 FTD: ±10% Ti or ±0.2S s; and ±10% Tt or ±0.2S s. For Level 6 FTD: ±10% Tt or ±0.2S s. 20MYR2 For LevelS FTD: ±1 s 2. Handling Qualities. 2.a. Static Control Tests. Note.] - Testing ofposition versus force is not applicable ifforces are generated solely by use of airplane hardware in the FTD. Note 2- Pitch, roll and yaw controller position versus force or time should be measured at the control. An alternative method in lieu of external test.fixtures at the flight controls would be to have recording and measuring instrumentation built into the FTD. The force and position data from this instrumentation could be directly recorded and matched to the airplane data. Provided the instrumentation was verified by using external measuring equipment while conducting the static control checks, or equivalent means, and that evidence of the satisfactory comparison is included in the MQTG, the instrumentation could be usedfor both initial and recurrent evaluations for the measurement of all required control checks. Verification of the instrumentation by usinf( external measurinf( equipment Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32119 ER20MY16.101</GPH> mstockstill on DSK3G9T082PROD with RULES2 32120 VerDate Sep<11>2014 Test Jkt 238001 Entry Number PO 00000 2.a.l.a. Tolerance Title Test Details 5 6 Notes 7 Frm 00106 should be repeated if major modifications and/or repairs are made to the control loading system. Such a permanent installation could be used without any time being lost for the installation of external devices. Static and dynamic flight control tests should be accomplished at the same feel or impact pressures as the validation data where applicable. Note 3- (Level 7 FTD only) FTD static control testing from the second set ofpilot controls is only required if both sets of controls are not mechanically interconnected on the FTD. A rationale is requiredfrom the data provider if a single set of data is applicable to both sides. If controls are mechanically interconnected in the FTD, a single set of tests is sufficient. Ground. Record results for an uninterrupted control sweep Pitch controller ±0.9 daN (2 lbt) X X Test results should be validated with in-flight data from tests to the stops. position versus force breakout. and surface position such as longitudinal static calibration. stability, stalls, etc. ±2.2 daN ( 5 lbt) or ±10% of force. Fmt 4701 2.a.l.b. Pitch controller position versus force ±2° elevator angle. ±0.9 daN (2 lbt) breakout. Sfmt 4725 E:\FR\FM\20MYR2.SGM As determined by sponsor Record results during initial qualification evaluation for an uninterrupted control sweep to the stops. The recorded tolerances apply to subsequent comparisons on continuing qualification evaluations. Ground. Record results for an uninterrupted control sweep to the stops. As determined by sponsor Record results during initial qualification evaluation for an uninterrupted control sweep to the stops. The recorded tolerances apply to subsequent comparisons on continuing qualification evaluations. ±2.2 daN ( 5 lbt) or ±10% of force. 2.a.2.a. Roll controller position versus force and surface position calibration. ±0.9 daN (2 lbt) breakout. X X ± 1.3 daN (3 lbt) or ±10% of force. X Applicable only on continuing qualification evaluations. The intent is to design the control feel for Level 5 to be able to manually fly an instrument approach; and not to compare results to flight test or other such data. Test results should be validated with in-flight data from tests such as engine-out trims, steady state side-slips, etc. 20MYR2 ±2° aileron angle. 2.a.2.b. Roll controller position versus force ±3 o spoiler angle. ±0.9 daN (2 lbt) breakout. ± 1.3 daN (3 lbt) or ±10% of force. ER20MY16.102</GPH> Flight Conditions INFORMATION FTD Level X Applicable only on continuing qualification evaluations. The intent is to design the control feel for Level 5 to be able to manually fly an instrument approach; and not to compare results to flight test or other such Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.a.3.a. PO 00000 Frm 00107 2.a.3.b. Tolerance Title Rudder pedal position versus force and surface position calibration. Rudder pedal position versus force ±2.2 daN ( 5 lbt) breakout. Flight Conditions Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM Nosewheel Steering Controller Force and Position Calibration. 5 Notes 6 7 X X 20MYR2 Ground. Record results for an uninterrupted control sweep to the stops. As determined by sponsor Record results during initial qualification evaluation for an uninterrupted control sweep to the stops. The recorded tolerances apply to subsequent comparisons on continuing qualification evaluations. Ground. Record results of an uninterrupted control sweep to the stops. Ground. Record results of an uninterrupted control sweep to the stops. ±2° rudder angle. ±2.2 daN ( 5 lbt) breakout. ±0.9 daN (2 lbt) breakout. Record results of an uninterrupted control sweep to the stops. X X X X data. Test results should be validated with in-flight data from tests such as engine-out trims, steady state side-slips, etc. X ±2.2 daN ( 5 lbt) or ±10% of force. ±2.2 daN ( 5 lbt) or ±10% of force. 2.a.4.a. Test Details INFORMATION FTD Level Applicable only on continuing qualification evaluations. The intent is to design the control feel for Level 5 to be able to manually fly an instrument approach; and not to compare results to flight test or other such data. X X ± 1.3 daN (3 lbt) or ±10% of force. 2.a.4.b. Nosewheel Steering Controller Force ±2°NWA. ±0.9 daN (2 lbt) breakout. ± 1.3 daN (3 lbt) or ±10% of force. 2.a.S. ±2°NWA. Ground. 2.a.6. Rudder Pedal Steering Calibration. Pitch Trim Indicator vs. Surface Position Calibration. ±0.5° trim angle. Ground. 2.a.7. Pitch Trim Rate. ±10% of trim rate (0 /s) Ground and approach. Trim rate to be checked at pilot primary induced The purpose of the test is to compare FSTD surface position indicator against the FSTD flight controls model computed value. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS X 32121 ER20MY16.103</GPH> mstockstill on DSK3G9T082PROD with RULES2 32122 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions or Test Details INFORMATION FTD Level 5 Notes PO 00000 6 7 X X trim rate (ground) and autopilot or pilot primary trim rate in-flight at go-around flight conditions. ±0.1 °/s trim rate. 2.a.8. Frm 00108 Aligmnent of cockpit throttle lever versus selected engine parameter. When matching engine parameters: Ground. For airplanes with throttle detents, all detents to be presented and at least one position between detents/ endpoints (where practical). For airplanes without detents, end points and at least three other positions are to be presented. ±5° ofTLA. Fmt 4701 When matching detents: Sfmt 4725 ±3% Nl or ±.03 EPR or ±3% torque, or ±3% maximum rated manifold pressure, or equivalent. E:\FR\FM\20MYR2.SGM 2.a.9.a. Brake pedal position versus force and brake system pressure calibration. 20MYR2 2.a.9.b. Brake pedal position versus force Where the levers do not have angular travel, a tolerance of ±2 em (±0.8 in) applies. ±2.2 daN ( 5 lbt) or ±10% of force. Ground. Data from a test airplane or engineering test bench are acceptable, provided the correct engine controller (both hardware and software) is used. In the case of propeller-driven airplanes, if an additional lever, usually referred to as the propeller lever, is present, it should also be checked. This test may be a series of snapshot tests. X Relate the hydraulic system pressure to pedal position in a ground static test. FTD computer output results may be used to show compliance. Both left and right pedals must be checked. ±1.0 MPa (150 psi) or ± 10% of brake system pressure. ±2.2 daN ( 5 lbt) or ±10% of force. For CCA, representative flight test conditions must be used. Simultaneous recording for all engines. The tolerances apply against airplane data. Ground. Two data points are required: zero and maximum deflection. Computer output results may be used to show compliance. X FTD computer output results may be used to show compliance. Test not required unless RTO credit is sought. ER20MY16.104</GPH> Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flieht Trainine Device (FTD) Ob.iective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Title Number 2.b. Dynamic Control Tests. PO 00000 2.b.l. Tolerance Flight Conditions Test Details Frm 00109 Fmt 4701 Sfmt 4725 Note.- Tests 2.b.l, 2.b.2 and 2.b.3 are not applicable for FTDs where the control forces are completely generated within the airplane controller unit installed in the FTD. Power setting may be that required for level flight unless otherwise specified. See paragraph 4 ofAppendix A, Attachment 2. Pitch Control. Takeoff, Cruise, and For underdamped Data must be for normal control displacements in Landing. systems: both directions (approximately 25% to 50% of full throw or approximately 25% to 50% of T(Po) ±10% ofP0 or maximum allowable pitch controller deflection ±0.05 s. for flight conditions limited by the maneuvering load envelope). T(P 1) ±20% ofP 1 or ±0.05 s. Tolerances apply against the absolute values of each period (considered independently). T(P2) ±30% ofP2 or ±0.05 s. T(Pn) ±10*(n+ 1)% ofPn or ±0.05 s. E:\FR\FM\20MYR2.SGM T(An) ±10% of Amax, where Amax is the largest amplitude or ±0.5% of the total control travel (stop to stop). 20MYR2 T(A.i) ±5% of A.!= residual band or ±0.5% of the maximum control travel = residual band. ±I significant overshoots (minimum of 1 significant overshoot). INFORMATION FTD Level 5 6 Notes 7 X n = the sequential period of a full oscillation. Refer to paragraph 4 of Appendix A, Attachment 2 for additional information. For overdamped and critically damped systems, see Figure A2B of Appendix A for an illustration of the reference measurement. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flieht Trainine Device (FTD) Ob.iective Tests QPS REQUIREMENTS Steady state position 32123 ER20MY16.105</GPH> mstockstill on DSK3G9T082PROD with RULES2 32124 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions 5 6 Notes 7 within residual band. PO 00000 Note 1.- Tolerances should not be applied on period or amplitude after the last significant overshoot. Frm 00110 Fmt 4701 Note2.Oscillations within the residual band are not considered significant and are not subject to tolerances. Sfmt 4725 E:\FR\FM\20MYR2.SGM 2.b.2. Roll Control. For overdamped and critically damped systems only, the following tolerance applies: T(Po) ±10% of Po or ±0.05 s. Same as 2.b.l. Takeoff, Cruise, and Landing. 20MYR2 2.b.3. ER20MY16.106</GPH> Test Details INFORMATION FTD Level Yaw Control. Same as 2.b.l. Takeoff, Cruise, and Landing. Data must be for normal control displacement (approximately 25% to 50% of full throw or approximately 25% to 50% of maximum allowable roll controller deflection for flight conditions limited by the maneuvering load envelope). X Data must be for normal control displacement (approximately 25% to 50% of full throw). X Refer to paragraph 4 of Appendix A, Attachment 2 for additional information. For overdamped and critically damped systems, see Figure A2B of Appendix A for an illustration of the reference measurement. Refer to paragraph 4 of Appendix A, Attachment 2 for additional information. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Ob.iective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 PO 00000 For overdamped and critically damped systems, see Figure A2B of Appendix A for an illustration of the reference measurement. 2.b.4. Small Control Inputs -Pitch. Frm 00111 ±0.15°/s body pitch rate or ±20% of peak body pitch rate applied throughout the time history. Approach or Landing. Control inputs must be typical of minor corrections made while established on an ILS approach (approximately 0.5 to 2°/S pitch rate). X Test in both directions. Fmt 4701 Show time history data from 5 s before until at least 5 s after initiation of control input. Sfmt 4725 If a single test is used to demonstrate both directions, there must be a minimum of 5 s before control reversal to the opposite direction. E:\FR\FM\20MYR2.SGM 2.b.5. Small Control Inputs -Roll. ±0.15°/s body roll rate or ±20% of peak body roll rate applied throughout the time history. Approach or landing. CCA: Test in normal and non-normal control state. Control inputs must be typical of minor corrections made while established on an ILS approach (approximately 0.5 to 2°/S roll rate). Test in one direction. For airplanes that exhibit non-symmetrical behavior, test in both directions. 20MYR2 Show time history data from 5 s before until at least 5 s after initiation of control input. If a single test is used to demonstrate both directions, there must be a minimum of 5 s before control reversal to the opposite direction. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS CCA: Test in normal and non-normal control 32125 ER20MY16.107</GPH> mstockstill on DSK3G9T082PROD with RULES2 32126 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.b.6. Tolerance Title Small Control Inputs -Yaw. PO 00000 ±0.15°/s body yaw rate or ±20% of peak body yaw rate applied throughout the time history. Flight Conditions Approach or landing. FTD Level 5 6 state. Control inputs must be typical of minor corrections made while established on an ILS approach (approximately 0.5 to 2°/S yaw rate). Notes 7 X Test in both directions. Frm 00112 Show time history data from 5 s before until at least 5 s after initiation of control input. Fmt 4701 If a single test is used to demonstrate both directions, there must be a minimum of 5 s before control reversal to the opposite direction. Sfmt 4725 CCA: Test in normal and non-normal control state. 2.c. Longitudinal Control Tests. Power setting is that required for level flight unless otherwise specified. E:\FR\FM\20MYR2.SGM 2.c.l.a. Power Change Dynamics. ±3 kt airspeed. ±30 m (I 00 ft) altitude. ±1.5° or ±20% of pitch angle. Approach. X Power change from thrust for approach or level flight to maximum continuous or go-around power. 20MYR2 Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the power change to the completion of the power change + 15 s. 2.c.l.b. ER20MY16.108</GPH> Test Details INFORMATION Power Change Force. ±5 lb (2.2 daN) or, ±20% pitch control force. Approach. CCA: Test in normal and non-normal control mode May be a series of snapshot test results. Power change dynamics test as described in test 2.c.l.a. will be accepted. CCA: Test in Normal and Non-normal control mode. X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.c.2.a. Tolerance Title Flap/Slat Change Dynamics. ±3 kt airspeed. ±30 m (I 00 ft) altitude. Flight Conditions Takeoff through initial flap retraction, and approach to landing. PO 00000 ±1.5° or ±20% of pitch angle. Frm 00113 Fmt 4701 Flap/Slat Change Force. ±5 lb (2.2 daN) or, ±20% pitch control force. Takeoff through initial flap retraction, and approach to landing. 2.c.3. Spoiler/Speedbrake Change Dynamics. ±3 kt airspeed. Cruise. Sfmt 4725 ±30m (100ft) altitude. E:\FR\FM\20MYR2.SGM ±1.5° or ±20% of pitch angle. Gear Change Dynamics. ±3 kt airspeed. Takeoff (retraction), and Approach (extension). 20MYR2 ±1.5° or ±20% of pitch angle. Gear Change Force. ±5 lb (2.2 daN) or, ±20% pitch control force. 6 7 X Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the reconfiguration change to the completion of the reconfiguration change + 15 s. May be a series of snapshot test results. Flap/Slat change dynamics test as described in test 2.c.2.a. will be accepted. CCA: Test in Normal and Non-normal control mode. Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the configuration change to the completion of the configuration change+ 15 s. X X X Results required for both extension and retraction. ±30m (100ft) altitude. 2.c.4.b. 5 Notes CCA: Test in normal and non-normal control mode 2.c.2.b. 2.c.4.a. Test Details INFORMATION FTD Level Takeoff (retraction) and Approach (extension). CCA: Test in normal and non-normal control mode Time history of uncontrolled free response for a time increment equal to at least 5 s before initiation of the configuration change to the completion of the configuration change + 15 s. CCA: Test in normal and non-normal control mode May be a series of snapshot test results. Gear change dynamics test as described in test 2.c.4.a. will be accepted. CCA: Test in Normal and Non-normal control mode. X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32127 ER20MY16.109</GPH> mstockstill on DSK3G9T082PROD with RULES2 32128 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.c.5. Tolerance Title Longitudinal Trim. ± 1o elevator angle. Flight Conditions Cruise, Approach, and Landing. Test Details Steady-state wings level trim with thrust for level flight. This test may be a series of snapshot tests. FTD Level Notes 7 X X X X X X X ± 1o pitch angle. CCA: Test in normal or non-normal control mode, as applicable. ±5% of net thrust or equivalent. 2.c.6. Fmt 4701 Longitudinal Maneuvering Stability (Stick Force/g). ±2.2 daN ( 5 lbt) or ±10% of pitch controller Cruise, Approach, and Landing. Continuous time history data or a series of snapshot tests may be used. force. Test up to approximately 30° of roll angle for approach and landing configurations. Test up to approximately 45° of roll angle for the cruise configuration. Alternative method: Sfmt 4725 ±1 o or ±10% of the change of elevator angle. Force tolerance not applicable if forces are generated solely by the use of airplane hardware in the FTD. E:\FR\FM\20MYR2.SGM 20MYR2 6 Level 5 FTD may use equivalent stick and trim controllers in lieu of elevator and trim surface. surface angle. PO 00000 Frm 00114 5 ±0. 5o stabilizer or trim Alternative method applies to airplanes which do not exhibit stick-force-per-g characteristics. 2.c.7. Longitudinal Static Stability. ±2.2 daN ( 5 lbt) or ±10% of pitch controller force. Approach. CCA: Test in normal or non-normal control mode Data for at least two speeds above and two speeds below trim speed. The speed range must be sufficient to demonstrate stick force versus speed characteristics. Alternative method: This test may be a series of snapshot tests. ±1 o or ±10% of the change of elevator angle. ER20MY16.110</GPH> INFORMATION Force tolerance is not applicable if forces are generated solely by the use of airplane hardware X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Fli2ht Trainin2 Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 in the FTD. PO 00000 Alternative method applies to airplanes which do not exhibit speed stability characteristics. Level 5 must exhibit positive static stability, but need not comply with the numerical tolerance. Frm 00115 Fmt 4701 2.c.8.a. Approach to Stall characteristics ±3 kt airspeed for initial buffet, stall warning, and stall speeds. Sfmt 4725 Control inputs must be plotted and demonstrate correct trend and magnitude. Second Segment Climb, High Altitude Cruise (Near Performance Limited Condition), and Approach or Landing E:\FR\FM\20MYR2.SGM 20MYR2 2.c.8.b. X . . . The required cruise condition must be conducted in a flaps-up (clean) configuration. The second segment climb and approach/landing conditions must be conducted at different flap settings. ±2.0° pitch angle ±2.0° angle of attack ±2.0° bank angle ±2.0° sideslip angle Additionally, for those simulators with reversible flight control systems: ±10% or ±5 lb (2.2 daN)) Stick/Column force (prior to "g break" only). Stall Warning (actuation ±3 kts. airspeed, of stall warning device.) ±2° bank for speeds greater than actuation of stall warning device or initial buffet. CCA: Test in normal or non-normal control mode, as applicable. Each of the following stall entry methods must be demonstrated in at least one of the three required flight conditions: Stall entry at wings level (!g) Stall entry in turning flight of at least 25° bank angle (accelerated stall) Stall entry in a power-on condition (required only for turboprop aircraft) For airplanes that exhibit stall buffet as the first indication of a stall, for qualification of this task, the FTD must be equipped with a vibration system that meets the applicable subjective and objective requirements in Appendix A of this Part. Second Segment Climb, and Approach or Landing. The stall maneuver must be entered with thrust at or near idle power and wings level (lg). Record the stall warning signal and initial buffet if applicable. X X Tests may be conducted at centers of gravity typically required for airplane certification stall testing . Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS 32129 ER20MY16.111</GPH> mstockstill on DSK3G9T082PROD with RULES2 32130 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.c.9.a. Tolerance Title Phugoid Dynamics. Cruise. PO 00000 ±I 0% oftime to one half or double amplitude or ±0.02 of damping ratio. Frm 00116 Fmt 4701 Phugoid Dynamics. ±I 0% period, Representative damping. Cruise. 2.c.10 Short Period Dynamics. ±1.5° pitch angle or ±2°/s pitch rate. Cruise. Sfmt 4725 2.c.9.b. E:\FR\FM\20MYR2.SGM 2.c.ll. Test Details 5 6 7 X X X CCA: Test in Normal and Non-normal control states. Test must include three full cycles or that necessary to determine time to one half or double amplitude, whichever is less. CCA: Test in non-normal control mode. The test must include whichever is less of the following: Three full cycles (six overshoots after the input is completed), or the number of cycles sufficient to determine representative damping. Notes X X CCA: Test in non-normal control mode. CCA: (Level 7 FTD) Test in normal and nonnormal control mode. (Level 6 FTD) Test in non-normal control mode. ±0.1 g normal acceleration (Reserved) 2.d. Lateral Directional Tests. 2.d.1. Minimum control speed, air (Vmea) or landing (Vmel), per applicable airworthiness requirement or low speed engineinoperative handling characteristics in the air. Roll Response (Rate). Power setting is that required for level flight unless otherwise specified. 20MYR2 2.d.2. ER20MY16.112</GPH> ±10% of period. Flight Conditions INFORMATION FTD Level ±3 kt airspeed. Takeoff or Landing (whichever is most critical in the airplane). X Takeoff thrust must be set on the operating engine(s). Time history or snapshot data may be used. CCA: Test in normal or non-normal control state, as applicable. ±2°/s or ±10% of roll rate. Cruise, and Approach or Landing. Test with normal roll control displacement (approximately one-third of maximum roll controller travel). X X X Minimum speed may be defined by a performance or control limit which prevents demonstration of v mea or v mel in the conventional manner. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions PO 00000 Frm 00117 2.d.3. Step input of flight deck roll controller. Notes 6 7 X 5 X This test may be combined with step input of flight deck roll controller test 2.d.3. For airplanes with reversible flight control systems (Level 7 FTD only): ± 1.3 daN (3 lbt) or ±10% of wheel force. ±2° or ±10% of roll angle. Test Details INFORMATION FTD Level Approach or Landing. This test may be combined with roll response (rate) test 2.d.2. Fmt 4701 CCA: (Level 7 FTD) Test in normal and nonnormal control mode. (Level 6 FTD) Test in non-normal control mode. Sfmt 4725 2.d.4.a. Spiral Stability. E:\FR\FM\20MYR2.SGM Correct trend and ±2° or ±10% of roll angle in 20 s. Cruise, and Approach or Landing. Test for both directions. As an alternative test, show lateral control required to maintain a steady tum with a roll angle of approximately 30°. If alternate test is used: correct trend and ±2° aileron angle. 2.d.4.b. Spiral Stability. 20MYR2 Correct trend and ±3 o or ±10% of roll angle in 20 s. X Airplane data averaged from multiple tests may be used. Cruise CCA: Test in non-normal control mode. Airplane data averaged from multiple tests may be used. X Test for both directions. As an alternative test, show lateral control required to maintain a steady tum with a roll angle of approximately 30°. 2.d.4.c. Spiral Stability. Correct trend Cruise CCA: Test in non-normal control mode. Airplane data averaged from multiple tests may With wings level, apply a step roll control input using approximately one-third of the roll controller travel. When reaching approximately 20° to 30° of bank, abruptly return the roll controller to neutral and allow approximately I 0 seconds of airplane free response. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flieht Trainine Device (FTD) Ob.iective Tests QPS REQUIREMENTS X 32131 ER20MY16.113</GPH> mstockstill on DSK3G9T082PROD with RULES2 32132 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Test Details FTD Level 5 6 Notes 7 be used. PO 00000 2.d.5. Engine Inoperative Trim. ±1 o rudder angle or ±1 o tab angle or equivalent rudder pedal. Second Segment Climb, and Approach or Landing. CCA: Test in non-normal control mode. This test may consist of snapshot tests. X Test should be performed in a manner similar to that for which a pilot is trained to trim an engine failure condition. Frm 00118 ±2° side-slip angle. Fmt 4701 2nd segment climb test should be at takeoff thrust. Approach or landing test should be at thrust for level flight. 2.d.6.a. Rudder Response. Sfmt 4725 ±2°/s or ±10% of yaw rate. Approach or Landing. For Level 7 FTD: Test with stability augmentation on and off. X X E:\FR\FM\20MYR2.SGM Test with a step input at approximately 25% of full rudder pedal throw. Not required if rudder input and response is shown in Dutch Roll test (test 2.d. 7). CCA: Test in normal and non-normal control mode 2.d.6.b. Rudder Response. 20MYR2 2.d.7. Dutch Roll Roll rate ±2°/sec, bank angle ±3°. ±0.5 s or ±1 0% of period. ± 10% oftime to one half or double amplitude or ±. 02 of damping ER20MY16.114</GPH> Flight Conditions INFORMATION Approach or Landing. May be roll response to a given rudder deflection. Cruise, and Approach or Landing. CCA: Test in Normal and Non-normal control states. Test for at least six cycles with stability augmentation off. CCA: Test in non-normal control mode. May be accomplished as a yaw response test, in which case the procedures and requirements of test 2.d.6.a. will apply. X X X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level Notes 6 7 X X X (Level 7 FTD only): ±I s or ±20% of time difference between peaks of roll angle and side-slip angle. PO 00000 Frm 00119 5 ratio. 2.d.8. Steady State Sideslip. For a given rudder position: Fmt 4701 ±2° roll angle; ± 1o side-slip angle; Sfmt 4725 ±2° or ±10% of aileron angle; and E:\FR\FM\20MYR2.SGM ±5° or ±1 0% of spoiler or equivalent roll controller position or force. 20MYR2 For airplanes with reversible flight control systems (Level 7 FTD only): ± 1.3 daN (3 lbt) or ±10% of wheel force. ±2.2 daN ( 5 lbt) or ±10% of rudder pedal force. Approach or Landing. This test may be a series of snapshot tests using at least two rudder positions (in each direction for propeller-driven airplanes), one of which must be near maximum allowable rudder. (Level 5 and Level 6 FTD only): Sideslip angle is matched only for repeatability and only on continuing qualification evaluations. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS 32133 ER20MY16.115</GPH> mstockstill on DSK3G9T082PROD with RULES2 32134 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title 2.e. Normal Landing. 5 6 Notes 7 ±3 kt airspeed. Landing. Test from a minimum of61 m (200ft) AGL to nosewheel touchdown. X PO 00000 ±1.5° pitch angle. CCA: Test in normal and ±1.5° AOA. non-normal control mode, if applicable. Frm 00120 Two tests should be shown, including two normal landing flaps (if applicable) one of which should be near maximum certificated landing mass, the other at light or medium mass. ±3m (10ft) or ±10% of height. Fmt 4701 For airplanes with reversible flight control systems: Sfmt 4725 2.e.2. E:\FR\FM\20MYR2.SGM Minimum Flap Landing. ±2.2 daN ( 5 lbt) or ±I 0% of column force. ±3 kt airspeed. ±1.5° pitch angle. Minimum Certified Landing Flap Configuration. Test from a minimum of61 m (200ft) AGL to nosewheel touchdown. X Test at near maximum certificated landing weight. ±1.5° AOA. ±3m (10ft) or ±10% of height. 20MYR2 For airplanes with reversible flight control systems: 2.e.3. Crosswind Landing. ±2.2 daN ( 5 lbt) or ±I 0% of column force. ±3 kt airspeed. ±1.5° pitch angle. ER20MY16.116</GPH> Test Details Landings. 2.e.l. Flight Conditions INFORMATION FTD Level Landing. Test from a minimum of61 m (200ft) AGL to a 50% decrease in main landing gear touchdown speed. X In those situations where a maximum crosswind or a maximum demonstrated crosswind is not known, contact Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 theNSPM. It requires test data, including wind profile, for a crosswind component of at least 60% of airplane performance data value measured at 10m (33 ft) above the runway. ±1.5° AOA. PO 00000 ±3m (10ft) or ±10% of height. Wind components must be provided as headwind and crosswind values with respect to the runway. ±2° roll angle. Frm 00121 ±2° side-slip angle. ±3° heading angle. Fmt 4701 Sfmt 4725 For airplanes with reversible flight control systems: E:\FR\FM\20MYR2.SGM ±2.2 daN (Slbt) or ±10%of column force. ± 1.3 daN (3 lbt) or ±10% of wheel force. 20MYR2 2.e.4. One Engine Inoperative Landing. ±2.2 daN ( 5 lbt) or ± 10% of rudder pedal force. ±3 kt airspeed. ±1.5° pitch angle. ±1.5° AOA. ±3m (10ft) or ±10% of height. Landing. Test from a minimum of61 m (200ft) AGL to a 50% decrease in main landing gear touchdown speed. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS 32135 ER20MY16.117</GPH> mstockstill on DSK3G9T082PROD with RULES2 32136 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions 5 6 Notes 7 ±2° roll angle. ±2° side-slip angle. PO 00000 2.e.5. Autopilot landing (if applicable). ±3° heading angle. ±1.5 m (5 ft) flare height. Landing. Frm 00122 If autopilot provides roll-out guidance, record lateral deviation from touchdown to a 50% decrease in main landing gear touchdown speed. X ±0.5 s or± 10% ofTf. Time of autopilot flare mode engage and main gear touchdown must be noted. Fmt 4701 ±0.7 m/s (140 ftlmin) rate of descent at touchdown. Sfmt 4725 2.e.6. E:\FR\FM\20MYR2.SGM All-engine autopilot go-around. ±3m (10ft) lateral deviation during rollout. ±3 kt airspeed. As per airplane performance data. Normal all-engine autopilot go-around must be demonstrated (if applicable) at medium weight. X As per airplane performance data. Engine inoperative go-around required near maximum certificated landing weight with critical engine inoperative. X ±1.5° pitch angle. 2.e.7. One engine inoperative go around. ±1.5° AOA. ±3 kt airspeed. ±1.5° pitch angle. 20MYR2 Provide one test with autopilot (if applicable) and one without autopilot. ±1.5° AOA. ±2° roll angle. CCA: Non-autopilot test to be conducted in nonnormal mode. ±2° side-slip angle. 2.e.8. ER20MY16.118</GPH> Test Details INFORMATION FTD Level Directional control (rudder effectiveness) with symmetric ±5 kt airspeed. ±2°/s yaw rate. Landing. Apply rudder pedal input in both directions using full reverse thrust until reaching full thrust reverser minimum operating speed. X See Appendix F of this part for definition ofTr. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 2.e.9. PO 00000 2.f. Flight Conditions Tolerance Title reverse thrust. Directional control (rudder effectiveness) with asymmetric reverse thrust. ±5 kt airspeed. Test Details INFORMATION FTD Level 5 6 Notes 7 With full reverse thrust on the operating engine(s), maintain heading with rudder pedal input until maximum rudder pedal input or thrust reverser minimum operation speed is reached. X Landing. A rationale must be provided with justification of results. X ±3° heading angle. Ground Effect. Test to demonstrate Ground Effect. Frm 00123 Landing. ± 1o elevator angle. ±0.5° stabilizer angle. CCA: Test in normal or non-normal control mode, as applicable. Fmt 4701 ±5% of net thrust or equivalent. Sfmt 4725 ±1° AOA. ±1.5 m (5 ft) or ±10% of height. E:\FR\FM\20MYR2.SGM ±3 kt airspeed. ± 1o pitch angle. Reserved 2.h. Flight Maneuver and Envelope Protection Functions. 2.h.l. Note. - The requirements of 2.h are only applicable to computer-controlled airplanes. Time history results of response to control inputs during entry into each envelope protectionfonction (i.e. with normal and degraded control states if their jUnction is different) are required. Set thrust as required to reach the envelope protection fUnction. Overspeed. ±5 kt airspeed. Cruise. 2.h.2. Minimum Speed. ±3 kt airspeed. 2.h.3. Load Factor. ±O.lg normal load factor Takeoff, Cruise, and Approach or Landing. Takeoff, Cruise. 2.h.4. Pitch Angle. ±1.5° pitch angle Cruise, Approach. 2.h.5. Bank Angle. ±2° or ±1 0% bank angle Approach. 2.h.6. 20MYR2 2.g. Angle of Attack. ±1.5° angle of attack Second Segment Climb, X X X X X X See paragraph on Ground Effect in this attachment for additional information. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32137 ER20MY16.119</GPH> mstockstill on DSK3G9T082PROD with RULES2 32138 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 and Approach or Landing. 3. Reserved PO 00000 4. Visual System. Visual scene quality 4.a.l. Continuous crosscockpit visual field of view. Frm 00124 4.a. Fmt 4701 Visual display providing each pilot with a minimum of 176° horizontal and 36° vertical continuous field of view. Not applicable. Required as part ofMQTG but not required as part of continuing evaluations. X Field of view should be measured using a visual test pattern filling the entire visual scene (all channels) consisting of a matrix of black and white 5° squares. Sfmt 4725 Installed alignment should be confirmed in an SOC (this would generally consist of results from acceptance testing). E:\FR\FM\20MYR2.SGM 4.a.2. System Geometry 4.a.3 Surface resolution (object detection). Geometry of image should have no distracting discontinuities. Not greater than 4 arc minutes. X Not applicable. X Resolution will be demonstrated by a test of objects shown to occupy the required visual angle in each visual display used on a scene from the pilot's eyepoint. 20MYR2 The object will subtend 4 arc minutes to the eye. This may be demonstrated using threshold bars for a horizontal test. A vertical test should also be demonstrated. The subtended angles should be ER20MY16.120</GPH> Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Fli2ht Trainin2 Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number 4.a.4 Tolerance Title Light point size. PO 00000 Not greater than 8 arc minutes. Flight Conditions Not applicable. Test Details INFORMATION FTD Level 5 6 Notes 7 X Frm 00125 confirmed by calculations in an SOC. Light point size should be measured using a test pattern consisting of a centrally located single row of white light points displayed as both a horizontal and vertical row. Fmt 4701 It should be possible to move the light points relative to the eyepoint in all axes. Sfmt 4725 At a point where modulation is just discernible in each visual channel, a calculation should be made to determine the light spacing. E:\FR\FM\20MYR2.SGM 4.a.5 Raster surface contrast ratio. Not less than 5: 1. Not applicable. X An SOC is required to state test method and calculation. Surface contrast ratio should be measured using a raster drawn test pattern filling the entire visual scene (all channels). 20MYR2 The test pattern should consist of black and white squares, 5° per square, with a white square in the center of each channel. Measurement should be made on the center bright square for each channel using a 1o spot photometer. This value should have a minimum brightness of 7 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32139 ER20MY16.121</GPH> mstockstill on DSK3G9T082PROD with RULES2 32140 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 cd/m2 (2 ft-lamberts). Measure any adjacent dark squares. PO 00000 The contrast ratio is the bright square value divided by the dark square value. Frm 00126 Note I. -During contrast ratio testing, FTD aft-cab and flight deck ambient light levels should be as low as possible. Fmt 4701 Sfmt 4725 4.a.6 Light point contrast ratio. Not less than 10: I. Not applicable. X E:\FR\FM\20MYR2.SGM Note 2. -Measurements should be taken at the center of squares to avoid light spill into the measurement device. Light point contrast ratio should be measured using a test pattern demonstrating an area of greater than I o area filled with white light points and should be compared to the adjacent background. 20MYR2 Note. -Light point modulation should be just discernible on calligraphic systems but will not be discemable on raster systems. Measurements of the background should be taken such that the bright square is just out of the light meter FOV. ER20MY16.122</GPH> Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number PO 00000 4.a.7 Tolerance Title Light point brightness. Not less than 20 cd/m2 (5.8 ft-lamberts). Flight Conditions Not applicable. Test Details INFORMATION FTD Level 5 6 Notes 7 X Note. -During contrast ratio testing, FTD aft-cab and flight deck ambient light levels should be as low as practical. Light points should be displayed as a matrix creating a square. Frm 00127 On calligraphic systems the light points should just merge. Fmt 4701 Sfmt 4725 4.a.8 Surface brightness. Not less than 14 cd/m2 (4.1 ft -lamberts) on the display. Not applicable. X E:\FR\FM\20MYR2.SGM On raster systems the light points should overlap such that the square is continuous (individual light points will not be visible). Surface brightness should be measured on a white raster, measuring the brightness using the I o spot photometer. Light points are not acceptable. Use of calligraphic capabilities to enhance raster brightness is acceptable. 4.b 20MYR2 4.b.l Head-Up Display (HUD) Static Alignment. Static alignment with displayed image. HUD bore sight must align with the center of the displayed image spherical pattern. X Alignment requirement only applies to the pilot flying. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS 32141 ER20MY16.123</GPH> mstockstill on DSK3G9T082PROD with RULES2 32142 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title PO 00000 Frm 00128 Fmt 4701 4.b.2 System display. 4.b.3 HUD attitude versus FTD attitude indicator (pitch and roll of horizon). Enhanced Flight Vision System (EFVS) Registration test. 4.c 4.c.l Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 EFVSRVRand visibility calibration. 4.c.3 Thermal crossover. 4.d Visual ground segment (VGS). Test Details Tolerance+/- 6 arc min. All functionality in all flight modes must be demonstrated. 5 6 Notes 7 X Pitch and roll align with aircraft instruments. Flight X Alignment between EFVS display and out of the window image must represent the alignment typical of the aircraft and system type. The scene represents the EFVS view at 350 m (1,200 ft) and 1,609 m (1 sm) RVR including correct light intensity. Demonstrate thermal crossover effects during day to night transition. Takeoff point and on approach at 200 ft. X Near end: the correct number of approach lights within the computed VGS must be visible. Trimmed in the landing configuration at 30m (100 ft) wheel height above touchdown zone on glide slope at an RVR setting of300 m (1,000 ft) or 350m Flight X Day and night X A statement of the system capabilities should be provided and the capabilities demonstrated Alignment requirement only applies to the pilot flying. Alignment requirement only applies to the pilot flying. Note.- The effects of the alignment tolerance in 4.b.l should be taken into account. Infra-red scene representative of both 350m (1,200 ft), and 1,609 m (1 sm) RVR. Visual ground segment 4.d.l ER20MY16.124</GPH> 4.c.2 Flight Conditions INFORMATION FTD Level This test is designed to assess items impacting the accuracy of the visual scene presented to a pilot at DH on an ILS approach. These items include: 1) RVR/Visibility; X Visual scene may be removed. The scene will correctly represent the thermal characteristics of the scene during a day to night transition. Pre-position for this test is encouraged but may be achieved via manual or autopilot control to the desired position. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Far end: ±20% ofthe computed VGS. Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 (1,200 ft). 2) glide slope (GIS) and localizer modeling accuracy (location and slope) for an ILS; PO 00000 The threshold lights computed to be visible must be visible in the FTD. Frm 00129 3) for a given weight, configuration and speed representative of a point within the airplane's operational envelope for a normal approach and landing; and 4) Radio altimeter. Fmt 4701 Note.- If non-homogeneous jog is used, the vertical variation in horizontal visibility should be described and included in the slant range visibility calculation used in the VGS computation. Sfmt 4725 4.e E:\FR\FM\20MYR2.SGM 4.e.l 20MYR2 4.e.2 Visual System Capacity System capacity Day mode. System capacity Twilight/night mode. Not less than: 10,000 visible textured surfaces, 6,000 light points, 16 moving models. Not less than: I 0,000 visible textured surfaces, 15,000 light points, 16 moving models. Not applicable Not applicable X X Demonstrated through use of a visual scene rendered with the same image generator modes used to produce scenes for training. The required surfaces, light points, and moving models should be displayed simultaneously. Demonstrated through use of a visual scene rendered with the same image generator modes used to produce scenes for training. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS The required surfaces, light points, and moving models 32143 ER20MY16.125</GPH> mstockstill on DSK3G9T082PROD with RULES2 32144 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 should be displayed simultaneously. PO 00000 Frm 00130 Fmt 4701 5. Sound System. The sponsor will not be required to repeat the operational sound tests (i.e., tests S.a.l. through 5.a.8. (or S.b.l. through 5.b.9.) and S.c., as appropriate) during continuing qualification evaluations if frequency response and background noise test results are within tolerance when compared to the initial qualification evaluation results, and the sponsor shows that no software changes have occurred that will affect the FTD' s sound system. If the frequency response test method is chosen and fails, the sponsor may elect to fix the frequency response problem and repeat the test or the sponsor may elect to repeat the operational sound tests. If the operational sound tests are repeated during continuing qualification evaluations, the results may be compared against initial qualification evaluation results. All tests in this section must be presented using an unweighted 1/3-octave band format from band 17 to 42 (50 Hz to 16kHz). A minimum 20 second average must be taken at a common location from where the initial evaluation sound results were gathered. Turbo-jet airplanes. S.a. Sfmt 4725 All tests in this section should be presented using an unweighted 1/3-octave band format from at least band 17 to 42 (50 Hz to 16 kHz). E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.126</GPH> A measurement of minimum 20 s should be taken at the location corresponding to the approved data set. Refer to paragraph 7 of Appendix A, Attachment 2. S.a.l. Ready for engine start. Initial evaluation: Subjective assessment of 113 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between Ground. Normal condition prior to engine start. The APU must be on if appropriate. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flieht Trainine Device (FTD) Ob.iective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number PO 00000 5.a.2. Title All engines at idle. Frm 00131 Fmt 4701 Sfmt 4725 5.a.3. E:\FR\FM\20MYR2.SGM All engines at maximum allowable thrust with brakes set. 20MYR2 5.a.4. Climb initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 113 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 113 octave bands. Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 Ground. Normal condition prior to takeoff. X Ground. Normal condition prior to takeoff. X En-route climb. Medium altitude. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32145 ER20MY16.127</GPH> mstockstill on DSK3G9T082PROD with RULES2 32146 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number Title PO 00000 Frm 00132 Fmt 4701 5.a.5. Cruise Sfmt 4725 E:\FR\FM\20MYR2.SGM 5.a.6. 20MYR2 Speed brake/spoilers extended (as appropriate). Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute ER20MY16.128</GPH> Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 Cruise. Normal cruise configuration. X Cruise. Normal and constant speed brake deflection for descent at a constant airspeed and power setting. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Ob.iective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number PO 00000 5.a.7 Tolerance Title Initial approach. Frm 00133 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 5.a.8 Final approach. differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 113 octave bands. 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 Approach. Constant airspeed, gear up, flaps/slats as appropriate. X Landing. Constant airspeed, gear down, landing configuration flaps. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32147 ER20MY16.129</GPH> mstockstill on DSK3G9T082PROD with RULES2 32148 VerDate Sep<11>2014 Test Jkt 238001 Entry Title Number Propeller-driven airplanes S.b Tolerance Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 PO 00000 All tests in tbis section should be presented using an unweighted 1/3-octave band format from at least band 17 to 42 (50 Hz to 16kHz). Frm 00134 A measurement of minimum 20 s should be taken at tbe location corresponding to tbe approved data set. Fmt 4701 Refer to paragraph 7 of Appendix A, Attachment 2. S.b.l. Sfmt 4725 Ready for engine start. E:\FR\FM\20MYR2.SGM 20MYR2 5.b.2 All propellers feathered, if applicable. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on tbree consecutive bands when compared to initial evaluation and tbe average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on tbree consecutive bands when ER20MY16.130</GPH> Ground. Normal condition prior to engine start. X The APU must be on if appropriate. Ground. Normal condition prior to take-off. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Fli2ht Trainin2 Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title PO 00000 Frm 00135 5.b.3. Ground idle or equivalent. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 5.b.4 Flight idle or equivalent. compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 113 octave bands. 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 Ground. Normal condition prior to takeoff. X Ground. Normal condition prior to takeoff. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32149 ER20MY16.131</GPH> mstockstill on DSK3G9T082PROD with RULES2 32150 VerDate Sep<11>2014 Test Tolerance Jkt 238001 Entry Number S.b.S Title PO 00000 All engines at maximum allowable power with brakes set. Frm 00136 Fmt 4701 Sfmt 4725 5.b.6 Climb. E:\FR\FM\20MYR2.SGM 20MYR2 5.b.7 Cruise Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 113 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three ER20MY16.132</GPH> Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 Ground. Normal condition prior to takeoff. X En-route climb. Medium altitude. X Cruise. Normal cruise configuration. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A- Flight Training Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title PO 00000 Frm 00137 S.b.S Initial approach. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM S.b.9 Final approach. consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. 20MYR2 Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 Approach. Constant airspeed, gear up, flaps extended as appropriate, RPM as per operating manual. X Landing. Constant airspeed, gear down, landing configuration flaps, RPM as per operating manual. X Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS 32151 ER20MY16.133</GPH> mstockstill on DSK3G9T082PROD with RULES2 32152 VerDate Sep<11>2014 Test Jkt 238001 Entry Number S.c. Tolerance Title Special cases. PO 00000 Frm 00138 Fmt 4701 Sfmt 4725 S.d FTD background noise cannot exceed 2 dB. Initial evaluation: Subjective assessment of 1/3 octave bands. E:\FR\FM\20MYR2.SGM Recurrent evaluation: cannot exceed ±5 dB difference on three consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Initial evaluation: background noise levels must fall below the sound levels described in Appendix A, Attachment 2, Paragraph 7 .c ( 5). Test Details As appropriate. 5 6 Notes 7 X Results of the background noise at initial qualification must be included in the QTG document and approved by the NSPM. The measurements are to be made with the simulation running, the sound muted and a dead cockpit. This applies to special steadystate cases identified as particularly significant to the pilot, important in training, or unique to a specific airplane type or model. X The simulated sound will be evaluated to ensure that the background noise does not interfere with training. Refer to paragraph 7 of this Appendix A, Attachment 2. 20MYR2 Recurrent evaluation: ±3 dB per 113 octave band compared to initial evaluation. S.e Frequency response Initial evaluation: not applicable. Recurrent evaluation: cannot exceed ±5 dB difference on three ER20MY16.134</GPH> Flight Conditions INFORMATION FTD Level This test should be presented using an unweighted 113 octave band format from band 17 to 42 (50 Hz to 16kHz). X Only required if the results are to be used during continuing qualification evaluations in lieu of airplane tests. The results must be approved by Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flight Training Device (FTD) Objective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 PO 00000 consecutive bands when compared to initial evaluation and the average of the absolute differences between initial and recurrent evaluation results cannot exceed 2 dB. Frm 00139 6 6.a. Fmt 4701 6.a.l SYSTEMS INTEGRATION System response time Transport delay. Sfmt 4725 Instrmnent response: 100 ms (or less) after airplane response. the NSPM during the initial qualification. This test should be presented using an unweighted 113 octave band format from band 17 to 42 (50 Hz to 16kHz). Pitch, roll and yaw. X Where EFVS systems are installed, the EFVS response should be within+ or- 30 ms from visual system response, and not before motion system response. E:\FR\FM\20MYR2.SGM Visual system response: 120 ms (or less) after airplane response. 20MYR2 6.a.2 Transport delay. 300 milliseconds or less after controller movement. One separate test is required in each axis. Pitch, roll and yaw. X X Note.- The delay from the airplane EFVS electronic elements should be added to the 30 ms tolerance before comparison with visual system reference. If transport delay is the chosen method to demonstrate relative responses, the sponsor and the NSPM will use the latency values to ensure proper FTD response when reviewing those existing tests where latency can Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Flieht Trainine Device (FTD) Ob.iective Tests QPS REQUIREMENTS 32153 ER20MY16.135</GPH> mstockstill on DSK3G9T082PROD with RULES2 32154 VerDate Sep<11>2014 Test Jkt 238001 Entry Number Tolerance Title Flight Conditions Test Details INFORMATION FTD Level 5 6 Notes 7 PO 00000 be identified (e.g., short period, roll response, rudder response). Frm 00140 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.136</GPH> Entry Number 1. l.c l.c.l. l.f. l.f.l. l.f.2. 2. 2.c. 2.c.l. Table B2B - Alternative Data Source for FTD Level 5 Small, Single Engine (Reciprocating) Airplane QPS REQUIREMENT The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD. Applicable Test Authorized Performance Range Title and Procedure Performance. Climb. Normal climb with nominal gross weight, at best rate-of-climb airspeed. Engines. Acceleration; idle to takeoff power. Deceleration; takeoff power to idle. Handling Qualities. Longitudinal Tests. Power change force. (a) Trim for straight and level flight at 80% of normal cruise airspeed with necessary power. Reduce power to flight idle. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. OR Climb rate= 500- 1200 fpm (2.5- 6 rn!sec). 2 - 4 Seconds. 2 - 4 Seconds. 5- 15 lbs (2.2- 6.6 daN) of force (Push). Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2A - Fli~ht Trainin~ Device (FTD) Ob_jective Tests QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 2.c.7. Longitudinal static stability. PO 00000 2.c.5. (b) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Add power to maximum setting. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. Flap/slat change force. (a) Trim for straight and level flight with flaps fully retracted at a constant airspeed within the flaps-extended airspeed range. Do not adjust trim or power. Extend the flaps to 50 percent of full flap travel. After stabilized, record stick force necessary to maintain original airspeed. OR b) Trim for straight and level flight with flaps extended to 50% of full flap travel, at a constant airspeed within the flaps-extended airspeed range. Do not adjust trim or power. Retract the flaps to zero. After stabilized, record stick force necessary to maintain original airspeed. Gear change force. (a) Trim for straight and level flight with landing gear retracted at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Extend the landing gear. After stabilized, record stick force necessary to maintain original airspeed. OR (b) Trim for straight and level flight with landing gear extended, at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Retract the landing gear. After stabilized, record stick force necessary to maintain original airspeed. Longitudinal trim. Frm 00141 2.c.2. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 2.c.4. 5- 15 lbs (2.2- 6.6 daN) of force (Pull). 5- 15 lbs (2.2- 6.6 daN) of force (Push). 5- 15 lbs (2.2- 6.6 daN) of force (Pull). 2- 12lbs (0.88- 5.3 daN) of force (Push). 20MYR2 2- 12lbs (0.88- 5.3 daN) of force (Pull). Must be able to trim longitudinal stick force to "zero" in each of the following configurations: cruise; approach; and landing. Must exhibit positive static stability. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Entry Number Table B2B - Alternative Data Source for FTD Level 5 Small, Single Engine (Reciprocating) Airplane QPS REQUIREMENT The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD. Applicable Test Authorized Performance Range Title and Procedure 32155 ER20MY16.137</GPH> mstockstill on DSK3G9T082PROD with RULES2 32156 VerDate Sep<11>2014 Jkt 238001 PO 00000 Frm 00142 Fmt 4701 2.c.9.b. Sfmt 4725 2.d. 2.d.2. E:\FR\FM\20MYR2.SGM 2.d.4.c. 2.d.6.b. 20MYR2 2.d.8. 6. 6.a. ER20MY16.138</GPH> Stall warning (actuation of stall warning device) with nominal gross weight; wings level; and a deceleration rate of not more than three (3) knots per second. a) Landing configuration. b) Clean configuration. Phugoid dynamics. Lateral Directional Tests. Roll response (rate). Roll rate must be measured through at least 30 degree of roll. Aileron control must be deflected 1/3 (33.3 percent) of maximum travel. Spiral stability. Cruise configuration and normal cruise airspeed. Establish a 20 degree- 30 degree bank. When stabilized, neutralize the aileron control and release. Must be completed in both directions of turn. Rudder response. Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.) Steady state sideslip. Use 50 percent rudder deflection. (Applicable to approach and landing configurations.) FTD System Response Time. Flight deck instrument systems response to an abrupt pilot controller input. One test is required in each axis (pitch, roll, yaw). 40- 60 knots;± 5° of bank. Landing configuration speed + 10 - 20%. Must have a phugoid with a period of 30 - 60 seconds. May not reach Yz or double amplitude in less than 2 cycles. Must have a roll rate of 4°- 25°/second. Initial bank angle(± 5°) after 20 seconds. 2° - 6° /second yaw rate. 2 percent - 10 percent of bank; 4 percent - 10 percent of sideslip; and 2 percent -10 percent of aileron. 300 milliseconds or less. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Entry Number 2.c.8. Table B2B - Alternative Data Source for FTD Level 5 Small, Single Engine (Reciprocating) Airplane QPS REQUIREMENT The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD. Applicable Test Authorized Performance Range Title and Procedure mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD. Jkt 238001 Applicable Test Entry Number PO 00000 1. l.c l.c.l. Frm 00143 Fmt 4701 Sfmt 4725 l.f. l.f.l. l.f.2. 2. 2.c. 2.c.l. Authorized Performance Range Title and Procedure Performance. Climb. Normal climb with nominal gross weight, at best rate-of-climb airspeed. Climb airspeed= 95- 115 knots. Climb rate= 500- 1500 fpm (2.5 -7.5 m/sec) Engines. Acceleration; idle to takeoff power. Deceleration; takeoff power to idle. 2 - 5 Seconds. 2 - 5 Seconds. Handling Qualities. Longitudinal Tests. E:\FR\FM\20MYR2.SGM Power change force. (a) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Reduce power to flight idle. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. 10- 25 lbs (2.2- 6.6 daN) of force (Push). OR 20MYR2 2.c.2. (b) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Add power to maximum setting. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. Flap/slat change force. (a) Trim for straight and level flight with flaps fully retracted at a constant airspeed within the flaps-extended airspeed range. Do not adjust trim or power. Extend the flaps to 50 percent of full flap travel. After stabilized, record stick force necessary to maintain original airspeed. 5- 15 lbs (2.2- 6.6 daN) of force (Pull). 5- 15 lbs (2.2- 6.6 daN) of force (Push). Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2C - Alternative Data Source for FTD Level 5 Small, Multi-Engine (Reciprocating) Airplane QPS REQUIREMENT 32157 ER20MY16.139</GPH> mstockstill on DSK3G9T082PROD with RULES2 32158 VerDate Sep<11>2014 The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD. Jkt 238001 Applicable Test Entry Number Authorized Performance Range PO 00000 OR Frm 00144 Fmt 4701 2.c.4. Sfmt 4725 E:\FR\FM\20MYR2.SGM (b) Trim for straight and level flight with flaps extended to 50 percent of full flap travel, at a constant airspeed within the flapsextended airspeed range. Do not adjust trim or power. Retract the flaps to zero. After stabilized, record stick force necessary to maintain original airspeed. Gear change force. (a) Trim for straight and level flight with landing gear retracted at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Extend the landing gear. After stabilized, record stick force necessary to maintain original airspeed. 5- 15 lbs (2.2- 6.6 daN) of force (Pull). 2- 12lbs (0.88- 5.3 daN) of force (Push). OR 20MYR2 2.c.5. 2.c.7. 2.c.8. ER20MY16.140</GPH> Title and Procedure (b) Trim for straight and level flight with landing gear extended, at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Retract the landing gear. After stabilized, record stick force necessary to maintain original airspeed. Longitudinal trim. Longitudinal static stability. Stall warning (actuation of stall warning device) with nominal gross weight; wings level; and a deceleration rate of not more than three (3) knots per second. 2- 12lbs (0.88- 5.3 daN) of force (Pull). Must be able to trim longitudinal stick force to "zero" in each of the following configurations: cruise; approach; and landing. Must exhibit positive static stability. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2C - Alternative Data Source for FTD Level 5 Small, Multi-En2ine (Reciprocatin2) Airplane QPS REQUIREMENT mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 Jkt 238001 The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD. Applicable Test PO 00000 Entry Number Frm 00145 2.c.9.b. Fmt 4701 2.d. 2.d.2. Sfmt 4725 2.d.4.c. E:\FR\FM\20MYR2.SGM 2.d.6.b. 20MYR2 2.d.8. 6. 6.a. Title and Procedure (a) Landing configuration. (b) Clean configuration. Phugoid dynamics. Authorized Performance Range 60- 90 knots;± 5 degree of bank. Landing configuration speed + 10 - 20%. Must have a phugoid with a period of 30 - 60 seconds. May not reach Y2 or double amplitude in less than 2 cycles. Lateral Directional Tests. Roll response. Roll rate must be measured through at least 30 degree of roll. Aileron control must be deflected 1/3 (33.3 percent) of maximum travel. Spiral stability. Cruise configuration and normal cruise airspeed. Establish a 20 degree- 30 degree bank. When stabilized, neutralize the aileron control and release. Must be completed in both directions of turn. Rudder response. Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.) Steady state sideslip. Use 50 percent rudder deflection. (Applicable to approach and landing configurations.) FTD System Response Time. Flight deck instrument systems response to an abrupt pilot controller input. One test is required in each axis (pitch, roll, yaw). Must have a roll rate of 4- 25 degree /second. Initial bank angle(± 5 degree) after 20 seconds. 3 - 6 degree /second yaw rate. 2- 10 degree ofbank; 4- 10 degrees of sideslip; and 2 - 10 degree of aileron. 300 milliseconds or less. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2C - Alternative Data Source for FTD Level 5 Small, Multi-Engine (Reciprocating) Airplane QPS REQUIREMENT 32159 ER20MY16.141</GPH> mstockstill on DSK3G9T082PROD with RULES2 32160 VerDate Sep<11>2014 The performance parameters in this table must be used to program the FTD if flight test data is not used to Jrogram the FTD. Jkt 238001 Applicable Test Entry Number PO 00000 1. l.c l.c.l. Frm 00146 Fmt 4701 Sfmt 4725 l.f. l.f.l. l.f.2. 2. 2.c. 2.c.l. E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.142</GPH> 2.c.2. Authorized Performance Range Title and Procedure Performance. Climb. Normal climb with nominal gross weight, at best rate-of-climb airspeed. Climb airspeed= 95- 115 knots. Climb rate = 800 - 1800 fpm (4 - 9 m/sec) Engines. Acceleration; idle to takeoff power. Deceleration; takeoff power to idle. 4 - 8 Seconds. 3 - 7 Seconds. Handling Qualities. Longitudinal Tests. Power change force. a) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Reduce power to flight idle. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. OR b) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Add power to maximum setting. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. Flap/slat change force. a) Trim for straight and level flight with flaps fully retracted at a constant airspeed within the flaps-extended airspeed range. Do not adjust trim or power. Extend the flaps to 50 percent of full flap travel. After stabilized, record stick force necessary to maintain original airspeed. OR 8 lbs (3.5 daN) of Push force- 8 lbs (3.5 daN) of Pull force. 12- 22lbs (5.3- 9.7 daN) of force (Pull). 5- 15 lbs (2.2- 6.6 daN) of force (Push). Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2D - Alternative Data Source for FTD Level 5 Small, Single Engine (Turbo-Propeller) Airplane QPS REQUIREMENT mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 The performance parameters in this table must be used to program the FTD if flight test data is not used to Jrogram the FTD. Jkt 238001 Applicable Test Entry Number PO 00000 Frm 00147 2.c.4. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 2.c.5. 20MYR2 2.c.7. 2.c.8. 2.c.9.b. Title and Procedure b) Trim for straight and level flight with flaps extended to 50 percent of full flap travel, at a constant airspeed within the flapsextended airspeed range. Do not adjust trim or power. Retract the flaps to zero. After stabilized, record stick force necessary to maintain original airspeed. Gear change force. a) Trim for straight and level flight with landing gear retracted at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Extend the landing gear. After stabilized, record stick force necessary to maintain original airspeed. OR b) Trim for straight and level flight with landing gear extended, at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Retract the landing gear. After stabilized, record stick force necessary to maintain original airspeed. Longitudinal trim. Longitudinal static stability. Stall warning (actuation of stall warning device) with nominal gross weight; wings level; and a deceleration rate of not more than three (3) knots per second. a) Landing configuration. b) Clean configuration. Phugoid dynamics. Authorized Performance Range 5- 15 lbs (2.2- 6.6 daN) of force (Pull). 2- 12lbs (0.88- 5.3 daN) of force (Push). 2- 12lbs (0.88- 5.3 daN) of force (Pull). Must be able to trim longitudinal stick force to "zero" in each of the following configurations: cruise; approach; and landing. Must exhibit positive static stability. 60- 90 knots;± 5 degree of bank. Landing configuration speed + 10 - 20 percent. Must have a phugoid with a period of 30 - 60 seconds. May not reach Yz or double amplitude in less than 2 cycles. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2D - Alternative Data Source for FTD Level 5 Small, Sin2le En2ine (Turbo-Propeller) Airplane QPS REQUIREMENT 32161 ER20MY16.143</GPH> mstockstill on DSK3G9T082PROD with RULES2 32162 VerDate Sep<11>2014 Jkt 238001 PO 00000 The performance parameters in this table must be used to program the FTD if flight test data is not used to Jrogram the FTD. Applicable Test Frm 00148 Entry Number 2.d. 2.d.2. Fmt 4701 2.d.4.c. Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.144</GPH> 2.d.6.b. 2.d.8. 6. 6.a. Title and Procedure Authorized Performance Range Lateral Directional Tests. Roll response. Roll rate must be measured through at least 30° of roll. Aileron control must be deflected 1/3 (33.3 percent) of maximum travel. Spiral stability. Cruise configuration and normal cruise airspeed. Establish a 20° 30° bank. When stabilized, neutralize the aileron control and release. Must be completed in both directions of turn. Rudder response. Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.) Steady state sideslip. Use 50 percent rudder deflection. (Applicable to approach and landing configurations.) Must have a roll rate of 4 - 25 degree /second. Initial bank angle(± 5 degree) after 20 seconds. 3 - 6 degree /second yaw rate. 2- 10 degree ofbank; 4- 10 degree of sideslip; and 2 - 10 degree of aileron. FTD System Response Time. Flight deck instrument systems response to an abrupt pilot controller input. One test is required in each axis (pitch, roll, yaw). 300 milliseconds or less. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2D - Alternative Data Source for FTD Level 5 Small, Single Engine (Turbo-Propeller) Airplane QPS REQUIREMENT mstockstill on DSK3G9T082PROD with RULES2 VerDate Sep<11>2014 The performance parameters in this table must be used to program the FTD if flight test data is not used to Jrogram the FTD. Jkt 238001 Applicable Test Entry Number Authorized Performance Range Title and Procedure PO 00000 Frm 00149 1. l.c Performance. l.c.l. Normal climb with nominal gross weight, at best rate-of-climb airspeed. Fmt 4701 Sfmt 4725 l.f. l.f.l. l.f.2. 2. 2.c. 2.c.l. E:\FR\FM\20MYR2.SGM 20MYR2 2.c.2. Climb. Climb airspeed= 120- 140 knots. Climb rate= 1000-3000 fpm (5- 15m/sec) Engines. Acceleration; idle to takeoff power. Deceleration; takeoff power to idle. 2 - 6 Seconds. 1 - 5 Seconds. Handling Qualities. Longitudinal Tests. Power change force. a) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Reduce power to flight idle. Do not change trim or configuration. After stabilized, record column force necessary to maintain original airspeed. OR b) Trim for straight and level flight at 80 percent of normal cruise airspeed with necessary power. Add power to maximum setting. Do not change trim or configuration. After stabilized, record colunm force necessary to maintain original airspeed. Flap/slat change force. a) Trim for straight and level flight with flaps fully retracted at a constant airspeed within the flaps-extended airspeed range. Do not adjust trim or power. Extend the flaps to 50 percent of full flap travel. After stabilized, record stick force necessary to maintain original airspeed. OR 8 lbs (3.5 daN) of Push force to 8 lbs (3.5 daN) of Pull force. 12- 22lbs (5.3- 9.7 daN) of force (Pull). 5- 15 lbs (2.2- 6.6 daN) of force (Push). Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2E - Alternative Data Source for FTD Level 5 Multi-Engine (Turbo-Propeller) Airplane QPS REQUIREMENT 32163 ER20MY16.145</GPH> mstockstill on DSK3G9T082PROD with RULES2 32164 VerDate Sep<11>2014 The performance parameters in this table must be used to program the FTD if flight test data is not used to Jrogram the FTD. Jkt 238001 Applicable Test Entry Number PO 00000 Frm 00150 2.c.4. Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 2.c.5. Title and Procedure b) Trim for straight and level flight with flaps extended to 50 percent of full flap travel, at a constant airspeed within the flapsextended airspeed range. Do not adjust trim or power. Retract the flaps to zero. After stabilized, record stick force necessary to maintain original airspeed. Gear change force. a) Trim for straight and level flight with landing gear retracted at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Extend the landing gear. After stabilized, record stick force necessary to maintain original airspeed. OR b) Trim for straight and level flight with landing gear extended, at a constant airspeed within the landing gear-extended airspeed range. Do not adjust trim or power. Retract the landing gear. After stabilized, record stick force necessary to maintain original airspeed. Longitudinal trim. 2.d. 20MYR2 2.c.9.b. ER20MY16.146</GPH> Longitudinal static stability. Stall warning (actuation of stall warning device) with nominal gross weight; wings level; and a deceleration rate of not more than three (3) knots per second. a) Landing configuration. b) Clean configuration. Phugoid dynamics. Lateral Directional Tests. 2.c.7. 2.c.8. Authorized Performance Range 5- 15 lbs (2.2- 6.6 daN) of force (Pull). 2- 12lbs (0.88- 5.3 daN) of force (Push). 2- 12lbs (0.88- 5.3 daN) of force (Pull). Must be able to trim longitudinal stick force to "zero" in each of the following configurations: cruise; approach; and landing. Must exhibit positive static stability. 80- 100 knots;± 5° ofbank. Landing configuration speed + 10 - 20 percent. Must have a phugoid with a period of 30 - 60 seconds. May not reach Yz or double amplitude in less than 2 cycles. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 Table B2E - Alternative Data Source for FTD Level 5 Multi-En~ine (Turbo-Propeller) Airplane QPS REQUIREMENT mstockstill on DSK3G9T082PROD with RULES2 Jkt 238001 PO 00000 The performance parameters in this table must be used to program the FTD if flight test data is not used to Jrogram the FTD. Applicable Test Frm 00151 Entry Number 2.d.2. Fmt 4701 Sfmt 4700 2.d.4.c. E:\FR\FM\20MYR2.SGM 2.d.6.b. 2.d.8. 20MYR2 6. 6.a. Title and Procedure Authorized Performance Range Roll response. Roll rate must be measured through at least 30 degree of roll. Aileron control must be deflected 1/3 (33.3 percent) of maximum travel. Must have a roll rate of 4 - 25 degree /second. Spiral stability. Cruise configuration and normal cruise airspeed. Establish a 20 30 dgree bank. When stabilized, neutralize the aileron control and release. Must be completed in both directions of turn. Rudder response. Use 25 percent of maximum rudder deflection. (Applicable to approach or landing configuration.) Steady state sideslip. Use 50 percent rudder deflection. (Applicable to approach and landing configurations.) FTD System Response Time. Flight deck instrument systems response to an abrupt pilot controller input. One test is required in each axis (pitch, roll, yaw). Initial bank angle(± 5°) after 20 seconds. 3 - 6 degree /second yaw rate. 2- 10 degree ofbank; 4 - 10 degree of sideslip; and 2 -10 degree of aileron. 300 milliseconds or less. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 18:26 May 19, 2016 6. Correct the tables appearing on pages 18377–18387 to read as follows: ■ VerDate Sep<11>2014 Table B2E - Alternative Data Source for FTD Level 5 Multi-Engine (Turbo-Propeller) Airplane QPS REQUIREMENT 32165 ER20MY16.147</GPH> 32166 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry Operations Tasks Number Tasks in this table are subject to evaluation if appropriate for the airplane simulated as indicated in the SOQ Configuration List or the level of FTD qualification involved. Items not installed or not functional on the FTD and, therefore, not appearing on the SOQ Configuration List, are not required to be listed as exceptions on the SOQ. Preparation For Flight l.a. 1.a.1 2. 2.a. 2.a.1. 2.a.2. 2.a.3. 2.b. 2.b.1 2.b.2. 2.b.3. 2.b.4. 2.b.5. 2.b.6. 2.b.7. 2.c. 2.c.1. 2.c.2. mstockstill on DSK3G9T082PROD with RULES2 3. 3.a. 3.a.1. 3.a.2. 3.a.3. 3.a.4. 3.a.4.a 3.a.4.b 3.a.4.c 3.a.4.d 3.a.4.e 3.a.5. 3.a.6. 3.a.7. 3.b. VerDate Sep<11>2014 18:26 May 19, 2016 Pre-flight. Accomplish a functions check of all switches, indicators, systems, and equipment at all crew members' and instructors' stations and determine that: The flight deck design and functions are identical to that of the airplane simulated. Surface Operations (pre-flight). Engine Start. Normal start. Alternate start procedures. Abnormal starts and shutdowns (e.g., hot/hung start, tail pipe fire). Taxi. Pushback/powerback Thrust response. Power lever friction. Ground handling. Reserved Taxi aids (e.g. taxi camera, moving map) Low visibility (taxi route, signage, lighting, markings, etc.) Brake Operation Brake operation (normal and alternate/emergency). Brake fade (if applicable). Take-off. Normal. Airplane/engine parameter relationships, including run-up. Nosewheel and rudder steering. Crosswind (maximum demonstrated and gusting crosswind). Special performance Reduced V1 Maximum engine de-rate. Soft surface. Short field/short take-off and landing (STOL) operations. Obstacle (performance over visual obstacle). Low visibility take-off. Landing gear, wing flap leading edge device operation. Contaminated runway operation. Abnormal/emergency. Jkt 238001 PO 00000 Frm 00152 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.148</GPH> 1. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32167 Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry 3.b.3. 3.b.4. 3.b.5. 4. 4.a. 4.b. 4.c. 5. 5.a. 5.a.l. 5.a.2. 5.a.3. 5.a.4. mstockstill on DSK3G9T082PROD with RULES2 5.a.5. 5.a.6. 5.b. 5.b.l. 5.b.l.a 5.b.l.b 5.b.2. 5.b.3. 5.b.4. 5.b.5. 5.b.6. 5.b.7. 5.b.8. 5.b.9. 5.b.l0. 5.b.ll. 5.b.12. 5.b.13 VerDate Sep<11>2014 18:26 May 19, 2016 Operations Tasks Rejected Take-off. Rejected special performance (e.g., reduced V1, max de-rate, short field operations). Rejected take-off with contaminated runway. Takeoff with a propulsion system malfunction (allowing an analysis of causes, symptoms, recognition, and the effects on aircraft performance and handling) at the following points: . (iii) Prior to VI decision speed. (iv) Between VI and Vr (rotation speed). (iii)Between Vr and 500 feet above ground level. Flight control system failures, reconfiguration modes, manual reversion and associated handling. Climb. Normal. One or more engines inoperative. Approach climb in icing (for airplanes with icing accountability). Cruise. Performance characteristics (speed vs. power, configuration, and attitude) Straight and level flight. Change of airspeed. High altitude handling. High Mach number handling (Mach tuck, Mach buffet) and recovery (trim change). Overspeed warning (in excess ofV moor Mm0 ). High lAS handling. Maneuvers. High Angle of Attack High angle of attack, approach to stalls, stall warning, and stall buffet (take-off, cruise, approach, and landing configuration) including reaction of the autoflight system and stall protection system. Reserved Slow flight Reserved Flight envelope protection (high angle of attack, bank limit, overspeed, etc.). Turns with/without speedbrake/spoilers deployed. Normal and standard rate turns. Steep turns Performance tum In flight engine shutdown and restart (assisted and windmill). Maneuvering with one or more engines inoperative, as appropriate. Specific flight characteristics (e.g., direct lift control). Flight control system failures, reconfiguration modes, manual reversion and associated handling. Gliding to a forced landing. Jkt 238001 PO 00000 Frm 00153 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.149</GPH> Number 3.b.l. 3.b.2. 32168 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS 5.b.14.a 5.b.14.b 5.b.14.c 5.b.14.d 5.b.14.e 6. 6.a. 6.b. 6.c. 6.d. 7. 7.a. 7.a.l 7.a.1.a 7.a.1.b 7.a.1.c 7.a.1.d 7.a.1.e 7.a.2 7.a.2.a 7.a.2.b 7.a.2.c 7.a.3 7.a.3.a 7.a.3.b 7.a.3.c mstockstill on DSK3G9T082PROD with RULES2 7.a.3.d 7.a.3.e 7.a.4 VerDate Sep<11>2014 18:26 May 19, 2016 Operations Tasks Visual resolution and FSTD handling and performance for the following (where applicable by aircraft type and training program): Terrain accuracy for forced landing area selection. Terrain accuracy for VFR Navigation. Eights on pylons (visual resolution). Turns about a point. S-tums about a road or section line. Descent. Normal. Maximum rate/emergency (clean and with speedbrake, etc.). With autopilot. Flight control system failures, reconfiguration modes, manual reversion and associated handling. Instrument Approaches And Landing. Those instrument approach and landing tests relevant to the simulated airplane type are selected from the following list. Some tests are made with limiting wind velocities, under windshear conditions, and with relevant system failures, including the failure of the Flight Director. If Standard Operating Procedures allow use autopilot for non-precision approaches, evaluation of the autopilot will be included. Precision approach CAT I published approaches. Manual approach with/without flight director including landing. Autopilot/autothrottle coupled approach and manual landing. Autopilot/autothrottle coupled approach, engine(s) inoperative. Manual approach, engine(s) inoperative. HUD/EFVS CAT II published approaches. Autopilot/autothrottle coupled approach to DH and landing (manual and auto land). Autopilot/autothrottle coupled approach with one-engine-inoperative approach to DH and go-around (manual and autopilot). HUD/EFVS CAT III published approaches. Autopilot/autothrottle coupled approach to landing and roll-out (if applicable) guidance (manual and autoland). Autopilot/autothrottle coupled approach to DH and go-around (manual and autopilot). Autopilot/autothrottle coupled approach to land and roll-out (if applicable) guidance with one engine inoperative (manual and autoland). Autopilot/autothrottle coupled approach to DH and go-around with one engine inoperative (manual and autopilot). HUD/EFVS Autopilot/autothrottle coupled approach (to a landing or to a go-around): Jkt 238001 PO 00000 Frm 00154 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.150</GPH> Entry Number 5.b.14 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32169 Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS 7.a.6 7.b. 7.b.l 7.b.2 7.b.3 7.b.4 7.b.5 7.b.6 7.c 7.c.l 7.c.2 s. S.a. S.b. S.c. S.d. mstockstill on DSK3G9T082PROD with RULES2 S.e. S.e.l. S.e.l.a S.e.l.b VerDate Sep<11>2014 18:26 May 19, 2016 Operations Tasks With generator failure. With maximum tail wind component certified or authorized. Reserved With maximum crosswind component demonstrated or authorized. Reserved PAR approach, all engine(s) operating and with one or more engine(s) inoperative. MLS, GBAS, all engine(s) operating and with one or more engine(s) inoperative. Non-precision approach. Surveillance radar approach, all engine( s) operating and with one or more engine( s) inoperative. NDB approach, all engine(s) operating and with one or more engine(s) inoperative. VOR, VOR/DME, TACAN approach, all engines(s) operating and with one or more engine(s) inoperative. RNAV I RNP I GNSS (RNP at nominal and minimum authorized temperatures) approach, all engine(s) operating and with one or more engine(s) inoperative. ILS LLZ (LOC), LLZ back course (or LOC-BC) approach, all engine(s) operating and with one or more engine( s) inoperative. ILS offset localizer approach, all engine(s) operating and with one or more engine(s) inoperative. Approach procedures with vertical guidance (APV), e.g. SBAS, flight path vector. APV/baro-VNAV approach, all engine(s) operating and with one or more engine(s) inoperative. Area navigation (RNAV) approach procedures based on SBAS, all engine(s) operating and with one or more engine( s) inoperative. Visual Approaches (Visual Segment) And Landings. Flight simulators with visual systems, which permit completing a special approach procedure in accordance with applicable regulations, may be approved for that particular approach procedure. Maneuvering, normal approach and landing, all engines operating with and without visual approach aid guidance. Approach and landing with one or more engines inoperative. Operation of landing gear, flap/slats and speedbrakes (normal and abnormal). Approach and landing with crosswind (max. demonstrated and gusting crosswind). Approach and landing with flight control system failures, reconfiguration modes, manual reversion and associated handling (most significant degradation which is probable). Approach and landing with trim malfunctions. Longitudinal trim malfunction. Lateral-directional trim malfunction. Jkt 238001 PO 00000 Frm 00155 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.151</GPH> Entry Number 7.a.4.a 7.a.4.b.l 7.a.4.b.2 7.a.4.c.l 7.a.4.c.2 7.a.5 32170 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS Entry 9.e. 10. lO.a lO.a.l 10.a.2. 10.a.3. 10.a.4. lO.a.S. 10.a.6. 10.a.6.a 10.a.6.b 10.a.6.c 10.a.6.d lO.b lO.b.l 10.b.2 mstockstill on DSK3G9T082PROD with RULES2 11. ll.a. ll.a.l. ll.a.2. ll.a.3. ll.a.4. ll.a.S. ll.a.6. ll.a.7. ll.a.8. ll.a.9. ll.a.lO. ll.a.ll. ll.a.12. ll.a.13. VerDate Sep<11>2014 18:26 May 19, 2016 Operations Tasks Approach and landing with standby (minimum) electrical/hydraulic power. Approach and landing from circling conditions (circling approach). Approach and landing from visual traffic pattern. Approach and landing from non-precision approach. Approach and landing from precision approach. Missed Approach. All engines, manual and autopilot. Engine(s) inoperative, manual and autopilot. Rejected landing With flight control system failures, reconfiguration modes, manual reversion and associated handling. Reserved Surface Operations (landin2, after-landin2 and post-fli2ht). Landing roll and taxi. HUD/EFVS. Spoiler operation. Reverse thrust operation. Directional control and ground handling, both with and without reverse thrust. Reduction of rudder effectiveness with increased reverse thrust (rear podmounted engines). Brake and anti-skid operation Brake and anti-skid operation with dry, patchy wet, wet on rubber residue, and patchy icy conditions. Reserved Reserved Auto-braking system operation. En2ine shutdown and parkin2. Engine and systems operation. Parking brake operation. Any Flight Phase. Airplane and en2ine systems operation (where fitted). Air conditioning and pressurization (ECS). De-icing/anti-icing. Auxiliary power unit (APU). Communications. Electrical. Fire and smoke detection and suppression. Flight controls (primary and secondary). Fuel and oil Hydraulic Pneumatic Landing gear. Oxygen. Engine. Jkt 238001 PO 00000 Frm 00156 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.152</GPH> Number 8.f. 8.2. 8.h. 8.i. 8._j. 9. 9.a. 9.b. 9.c. 9.d. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32171 Table B3D - Table of Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS mstockstill on DSK3G9T082PROD with RULES2 11.a.17. 11.a.18. 11.a.19. 11.a.20. 11.a.21. 11.a.22. 11.a.23. 11.a.24. 11.a.25. 11.a.26. 11.a.27. 11.b. 11.b.1. 11.b.2. 11.b.3. 11.b.3.a 11.b.3.b 11.b.3.c 11.b.3.d 11.b.4. VerDate Sep<11>2014 18:26 May 19, 2016 Operations Tasks Airborne radar. Autopilot and Flight Director. Terrain awareness warning systems and collision avoidance systems (e.g. EGPWS, GPWS, TCAS). Flight control computers including stability and control augmentation. Flight display systems. Flight management computers. Head-up displays (including EFVS, if appropriate). Navigation systems Stall warning/avoidance Wind shear avoidance/recovery guidance equipment Flight envelope protections Electronic flight bag Automatic checklists (normal, abnormal and emergency procedures). Runway alerting and advisory system. Airborne procedures. Holding. Air hazard avoidance (traffic, weather, including visual correlation). Windshear. Prior to take-off rotation. At lift-off During initial climb. On final approach, below 150m (500ft) AGL. Reserved Jkt 238001 PO 00000 Frm 00157 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.153</GPH> Entry Number 11.a.14. 11.a.15. 11.a.16. 32172 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS -== C'] ~ Airport Modeling Requirements 6 z This table specifies the minimum airport model content and functionality to quality a simulator at the indicated level. This table applies only to the airport models required for FTD qualification. Be2in QPS Requirements 1. Reserved 2.a.l 2.a.l.a 2.a.l.b 2.a.l.c 2.a.l.d mstockstill on DSK3G9T082PROD with RULES2 2.a.2 2.a.2.a 2.a.2.b 2.a.2.c 2.a.3 2.a.3.a 2.a.3.b 2.a.3.c 2.a.4 2.a.5 VerDate Sep<11>2014 Functional test content requirements Airport scenes A minimum of three (3) real-world airport models to be consistent with published data used for airplane operations and capable of demonstrating all the visual system features below. Each model should be in a different visual scene to permit assessment ofFSTD automatic visual scene changes. The model identifications must be acceptable to the sponsor's TPAA, selectable from the lOS, and listed on the SOQ. Reserved Reserved Airport model content. For circling approaches, all tests apply to the runway used for the initial approach and to the runway of intended landing. If all runways in an airport model used to meet the requirements of this attachment are not designated as "in use," then the "in use" runways must be listed on the SOQ (e.g., KORD, Rwys 9R, 14L, 22R). Models of airports with more than one runway must have all significant runways not "in-use" visually depicted for airport and runway recognition purposes. The use of white or off white light strings that identify the runway threshold, edges, and ends for twilight and night scenes are acceptable for this requirement. Rectangular surface depictions are acceptable for daylight scenes. A visual system's capabilities must be balanced between providing airport models with an accurate representation of the airport and a realistic representation of the surrounding environment. Airport model detail must be developed using airport pictures, construction drawings and maps, or other similar data, or developed in accordance with published regulatory material; however, this does not require that such models contain details that are beyond the design capability of the currently qualified visual system. Only one "primary" taxi route from parking to the runway end will be required for each "in-use" runway. Visual scene fidelity. The visual scene must correctly represent the parts of the airport and its surroundings used in the training program. Reserved Reserved Runways and taxiways. Reserved Representative runways and taxiways. Reserved Reserved Runway threshold elevations and locations must be modeled to provide correlation with airplane systems (e.g. HUD, GPS, compass, altimeter). 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00158 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.154</GPH> 2.a. Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32173 Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS -a= = "" C>~ ~ Airport Modeling Requirements z Reserved Runway surface and markings for each "in-use" runway must include the following, if appropriate: Threshold markings. 2.a.7.a Runway numbers. 2.a.7.b Touchdown zone markings. 2.a.7.c Fixed distance markings. 2.a.7.d Edge markings. 2.a.7.e Center line markings. 2.a.7.f Reserved 2.a.7.2 Reserved 2.a.7.h Windsock that gives appropriate wind cues. 2.a.7.i 2.a.8 Runway lighting of appropriate colors, directionality, behavior and spacing for the "in-use" runway including the following: Threshold lights. 2.a.8.a Edge lights. 2.a.8.b End lights. 2.a.8.c Center line lights. 2.a.8.d Touchdown zone lights. 2.a.8.e Lead-off lights. 2.a.8.f 2.a.8.g Appropriate visual landing aid(s) for that runway. Appropriate approach lighting system for that runway. 2.a.8.h 2.a.9 Taxiway surface and markin2s (associated with each "in-use" runway): Edge markings 2.a.9.a Center line markings. 2.a.9.b Runway holding position markings. 2.a.9.c ILS critical area markings. 2.a.9.d Reserved 2.a.9.e 2.a.10 Taxiway lighting of appropriate colors, directionality, behavior and spacing (associated with each "in-use" runway): Edge lights. 2.a.10.a Center line lights. 2.a.10.b Runway holding position and ILS critical area lights. 2.a.10.c 2.a.11 Required visual model correlation with other aspects of the airport environment simulation. The airport model must be properly aligned with the navigational aids that are associated 2.a.11.a with operations at the runway "in-use". Reserved 2.a.11.b Airport buildings, structures and lighting. 2.a.12 Buildings, structures and lighting: 2.a.12.a 2.a.12.a.1 Reserved VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00159 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.155</GPH> mstockstill on DSK3G9T082PROD with RULES2 2.a.6 2.a.7 32174 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS == t'] ..... 2.a.12.a.2 2.a.12.a.3 2.a.12.b 2.a.12.c 2.a.12.d 2.a.13 2.a.13.a 2.a.13.b 2.a.14 2.a.14.a 2.a.14.b 2.a.14.c ~.b 2.b.l 2.b.2 2.b.3 ~.c mstockstill on DSK3G9T082PROD with RULES2 2.c.l 2.c.2 2.c.2.a 2.c.2.b 2.c.3 2.c.4 2.c.5 2.c.6 ~.d VerDate Sep<11>2014 Airport Modeling Requirements = z Representative airport buildings, structures and lighting. Reserved Reserved Representative moving and static airport clutter (e.g. other airplanes, power carts, tugs, fuel trucks, additional gates). Reserved Terrain and obstacles. Reserved Representative depiction of terrain and obstacles within 46 km (25 NM) of the reference airport. Significant, identifiable natural and cultural features. Reserved Representative depiction of significant and identifiable natural and cultural features within 46 km (25 NM) of the reference airport. Note.- This refers to natural and cultural features that are typically used for pilot orientation in flight. Outlying airports not intended for landing need only provide a reasonable facsimile of runway orientation. Representative moving airborne traffic (including the capability to present air hazardse.g. airborne traffic on a possible collision course). Visual scene management. Reserved Airport runway, approach and taxiway lighting and cultural lighting intensity for any approach should be set at an intensity representative of that used in training for the visibility set; all visual scene light points must fade into view appropriately. Reserved Visual feature recognition. Note.- The following are the minimum distances at which runway features should be visible. Distances are measured from runway threshold to an airplane aligned with the runway on an extended 3-degree glide slope in suitable simulated meteorological conditions. For circling approaches, all tests below apply both to the runway used for the initial approach and to the runway of intended landing Runway definition, strobe lights, approach lights, and runway edge white lights from 8 km (5 sm) of the runway threshold. Visual approach aids li~hts. Reserved Visual approach aids lights from 4.8 km (3 sm) of the runway threshold. Runway center line lights and taxiway definition from 4.8 km (3 sm). Threshold lights and touchdown zone lights from 3.2 km (2 sm). Reserved For circling approaches, the runway of intended landing and associated lighting must fade into view in a non-distracting manner. Selectable airport visual scene capability for: 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00160 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.156</GPH> ~ Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations 32175 Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS "~ = ;... a Airport Modeling Requirements ~i 2.d.l 2.d.2 2.d.3 2.d.4 2.d.5 2.e 2.e.l 2.e.2 2.e.2.a 2.e.2.b 2.e.3 2.e.4 2.e.5 2.f 2.f.l 2.f.l.a 2.f.l.b 2.f.2 2.f.3 2.f.4 2.f.5 2.2.8 2.g.9 2.g.10 2.2.11 Begin Information VerDate Sep<11>2014 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00161 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.157</GPH> mstockstill on DSK3G9T082PROD with RULES2 2.g 2.2.1 2.g.2 2.g.3 2.2.4 2.g.5 2.g.6 2.g.7 Night. Twilight. Day. Dynamic effects - the capability to present multiple ground and air hazards such as another airplane crossing the active runway or converging airborne traffic; hazards must be selectable via controls at the instructor station. Reserved Correlation with airplane and associated equipment. Visual cues to relate to actual airplane responses. Visual cues durin2 take-off, approach and landin2. Visual cues to assess sink rate and depth perception during landings. Reserved Accurate portrayal of environment relating to airplane attitudes. The visual scene must correlate with integrated airplane systems, where fitted (e.g. terrain, traffic and weather avoidance systems and HUD/EFVS). Reserved Scene quality. Quantization. Surfaces and textural cues must be free from apparent quantization (aliasing). Reserved System capable of portraying full color realistic textural cues. The system light points must be free from distracting jitter, smearing or streaking. Reserved System capable of providing light point perspective growth (e.g. relative size of runway and taxiway edge lights increase as the lights are approached). Environmental effects. Reserved Reserved Reserved Reserved Reserved Reserved Visibility and RVR measured in terms of distance. Visibility/RVR must be checked at and below a height of600 m (2 000 ft) above the airport and within a radius of 16 km (10 sm) from the airport. Reserved Reserved Reserved Reserved End QPS Requirement 32176 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Table B3E - Functions And Subjective Tests Level7 FTD QPS REQUIREMENTS -a= = "" C>~ 3. mstockstill on DSK3G9T082PROD with RULES2 4. VerDate Sep<11>2014 Airport Modeling Requirements z An example of being able to "combine two airport models to achieve two "in-use" runways: One runway designated as the "in use" runway in the frrst model of the airport, and the second runway designated as the "in use" runway in the second model of the same airport. For example, the clearance is for the ILS approach to Runway 27, Circle to Land on Runway 18 right. Two airport visual models might be used: the first with Runway 27 designated as the "in use" runway for the approach to runway 27, and the second with Runway 18 Right designated as the "in use" runway. When the pilot breaks off the ILS approach to runway 27, the instructor may change to the second airport visual model in which runway 18 Right is designated as the "in use" runway, and the pilot would make a visual approach and landing. This process is acceptable to the FAA as long as the temporary interruption due to the visual model change is not distracting to the pilot, does not cause changes in navigational radio frequencies, and does not cause undue instructor/evaluator time. Sponsors are not required to provide every detail of a runway, but the detail that is provided should be correct within the capabilities of the system. End Information 18:26 May 19, 2016 Jkt 238001 PO 00000 Frm 00162 Fmt 4701 Sfmt 4725 E:\FR\FM\20MYR2.SGM 20MYR2 ER20MY16.158</GPH> ~ mstockstill on DSK3G9T082PROD with RULES2 PO 00000 Frm 00163 "" C>~ Fmt 4701 - a == ~z Sfmt 9990 E:\FR\FM\20MYR2.SGM 1. 2. 3. 4. 5. Sound System Requirements The following checks are performed during a normal flight profile. Precipitation. Reserved Significant airplane noises perceptible to the pilot during normal operations. Abnormal operations for which there are associated sound cues including, engine malfunctions, landing gear/tire malfunctions, tail and engine pod strike and pressurization malfunction. Sound of a crash when the flight simulator is landed in excess of limitations. 20MYR2 Federal Register / Vol. 81, No. 98 / Friday, May 20, 2016 / Rules and Regulations Jkt 238001 [FR Doc. C1–2016–05860 Filed 5–19–16; 8:45 am] 18:26 May 19, 2016 BILLING CODE 1505–01–D VerDate Sep<11>2014 Table B3F - Functions and Subjective Tests Level7 FTD QPS REQUIREMENTS 32177 ER20MY16.159</GPH>

Agencies

[Federal Register Volume 81, Number 98 (Friday, May 20, 2016)]
[Rules and Regulations]
[Pages 32015-32177]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: C1-2016-05860]



[[Page 32015]]

Vol. 81

Friday,

No. 98

May 20, 2016

Part II





Department of Transportation





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Federal Aviation Administration





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14 CFR Part 60





Flight Simulation Training Device Qualification Standards for Extended 
Envelope and Adverse Weather Event Training Tasks (Correction); Final 
Rule

Federal Register / Vol. 81 , No. 98 / Friday, May 20, 2016 / Rules 
and Regulations

[[Page 32016]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 60

[Docket No.: FAA-2014-0391; Amdt. No. 60--4]
RIN 2120-AK08


Flight Simulation Training Device Qualification Standards for 
Extended Envelope and Adverse Weather Event Training Tasks

Correction

14 CFR PART 60 [CORRECTED]

    In FR Rule Doc. No. 2016-05860 beginning on page 18178 in the issue 
of March 30, 2016, make the following corrections:

0
1. Correct the table appearing on page 18240 to read as follows:

                                  Table A1B--Table of Tasks vs. Simulator Level
----------------------------------------------------------------------------------------------------------------
                                                     QPS Requirements                           Information
                                --------------------------------------------------------------------------------
                                 Subjective requirements  In order    Simulator levels
                                  to be qualified at the simulator ----------------------
           Entry No.               qualification level indicated,
                                   the simulator must be able to                                   Notes
                                     perform at least the tasks       A     B    C    D
                                   associated with that level of
                                           qualification
----------------------------------------------------------------------------------------------------------------
 
                                                  * * * * * * *
3. Inflight Maneuvers.
 
                                                  * * * * * * *
3.b. High Angle of Attack Maneuvers
3.b.1..........................  Approaches to Stall..............  X     X     X    X
3.b.2..........................  Full Stall.......................              X    X    Stall maneuvers at
                                                                                           angles of attack
                                                                                           above the activation
                                                                                           of the stall warning
                                                                                           system.
                                                                                          Required only for
                                                                                           FSTDs qualified to
                                                                                           conduct full stall
                                                                                           training tasks as
                                                                                           indicated on the
                                                                                           Statement of
                                                                                           Qualification.
 
                                                  * * * * * * *
3.g............................  Upset Prevention and Recovery                  X    X    Upset recovery or
                                  Training (UPRT).                                         unusual attitude
                                                                                           training maneuvers
                                                                                           within the FSTD's
                                                                                           validation envelope
                                                                                           that are intended to
                                                                                           exceed pitch
                                                                                           attitudes greater
                                                                                           than 25 degrees nose
                                                                                           up; pitch attitudes
                                                                                           greater than 10
                                                                                           degrees nose down,
                                                                                           and bank angles
                                                                                           greater than 45
                                                                                           degrees.
 
                                                  * * * * * * *
----------------------------------------------------------------------------------------------------------------

0
2. Correct the table appearing on pages 18242-18282 to read as follows:

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[[Page 32065]]


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[[Page 32066]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.049

0
3. Correct the tables appearing on pages 18284-18300 to read as 
follows:

[[Page 32067]]

[GRAPHIC] [TIFF OMITTED] TR20MY16.050


[[Page 32068]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.051


[[Page 32069]]


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[GRAPHIC] [TIFF OMITTED] TR20MY16.069

* * * * *

[[Page 32087]]

[GRAPHIC] [TIFF OMITTED] TR20MY16.070

* * * * *
0
3. Correct the tables appearing on pages 18308-18326 to read as 
follows:

[[Page 32088]]

[GRAPHIC] [TIFF OMITTED] TR20MY16.071


[[Page 32089]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.072


[[Page 32090]]


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[[Page 32110]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.093

0
4. On page 18327, correct amendatory instruction 15 to read as follows:
0
15. Amend Attachment 2 to Appendix B as follows:
0
A. Revise paragraph 2.e;
0
B. Revise Table B2A;

[[Page 32111]]

0
C. Revise Table B2B;
0
D. Revise Table B2C;
0
E. Revise Table B2D; and
0
F. Revise Table B2E.
    The revisions and additions read as follows:
* * * * *
0
5. Correct the tables appearing on pages 18329-18375 to read as 
follows:

[[Page 32112]]

[GRAPHIC] [TIFF OMITTED] TR20MY16.094


[[Page 32113]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.095


[[Page 32114]]


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[[Page 32165]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.147


0
6. Correct the tables appearing on pages 18377-18387 to read as 
follows:

[[Page 32166]]

[GRAPHIC] [TIFF OMITTED] TR20MY16.148


[[Page 32167]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.149


[[Page 32168]]


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[[Page 32177]]


[GRAPHIC] [TIFF OMITTED] TR20MY16.159

[FR Doc. C1-2016-05860 Filed 5-19-16; 8:45 am]
BILLING CODE 1505-01-D