Special Conditions: Bombardier Inc., Model BD-700-2A12 and BD-700-2A13 Series Airplanes, Electronic Flight Control System: Lateral-Directional and Longitudinal Stability, and Low-Energy Awareness, 14126-14128 [2017-05327]

Download as PDF 14126 Federal Register / Vol. 82, No. 51 / Friday, March 17, 2017 / Rules and Regulations interfaced with a diverse set of functions, including: • Flight-safety-related control, communication, and navigation systems (airplane-control domain); • Operator business and administrative support (operatorinformation domain); and • Passenger information and entertainment systems (passengerentertainment domain). Discussion The Textron Model 700 airplane allows connection to airplane electronic systems and networks, and access from airplane external sources (e.g., operator networks, wireless devices, Internet connectivity, service-provider satellite communications, electronic flight bags, etc.) to the airplane’s previously isolated, internal, electronic components. These airplane internal electronic components include electronic equipment and systems, instruments, networks, servers, software and electronic components, fieldloadable software and hardware applications, and databases. This proposed design may otherwise result in network security vulnerabilities, if not appropriately protected, from intentional or unintentional corruption of data and systems required for the safety, operation, and maintenance of the airplane. The existing regulations and guidance material did not anticipate this type of system architecture, nor external wired and wireless electronic access to airplane electronic systems. Furthermore, regulations, and current system safety-assessment policy and techniques, do not address potential security vulnerabilities that could be caused by unauthorized access to airplane electronic systems and networks. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. mstockstill on DSK3G9T082PROD with RULES Applicability As discussed above, these special conditions are applicable to the Textron Model 700 airplane. Should Textron apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only a certain novel or unusual design feature on one VerDate Sep<11>2014 19:31 Mar 16, 2017 Jkt 241001 model of airplane. It is not a rule of general applicability. The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. Therefore, because a delay would significantly affect the certification of the airplane, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon publication in the Federal Register. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Textron Model 700 airplanes. 1. The applicant must ensure that the airplane electronic systems are protected from access by unauthorized sources external to the airplane, including those possibly caused by maintenance activity. 2. The applicant must ensure that electronic system-security threats are identified and assessed, and that effective electronic system-security protection strategies are implemented to protect the airplane from all adverse impacts on safety, functionality, and continued airworthiness. 3. The applicant must establish appropriate procedures to allow the operator to ensure that continued airworthiness of the airplane is maintained, including all post-typecertification modifications that may have an impact on the approved electronic systemsecurity safeguards. Issued in Renton, Washington, on February 10, 2017. Michael Kaszycki, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–05332 Filed 3–16–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA–2016–9296; Special Conditions No. 25–647–SC] Special Conditions: Bombardier Inc., Model BD–700–2A12 and BD–700– 2A13 Series Airplanes, Electronic Flight Control System: LateralDirectional and Longitudinal Stability, and Low-Energy Awareness Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: These special conditions are issued for the Bombardier Inc. (Bombardier) Model BD–700–2A12 and BD–700–2A13 series airplanes. These airplanes will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transportcategory airplanes. This design feature is lateral-directional and longitudinal stability, and low-energy awareness, provided through an electronic flightcontrol system (EFCS). The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. DATES: This action is effective on Bombardier on March 17, 2017. We must receive your comments by May 1, 2017. ADDRESSES: Send comments identified by docket number FAA–2016–9296 using any of the following methods: • Federal eRegulations Portal: Go to http://www.regulations.gov/ and follow the online instructions for sending your comments electronically. • Mail: Send comments to Docket Operations, M–30, U.S. Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room W12–140, West Building Ground Floor, Washington, DC 20590–0001. • Hand Delivery or Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: Fax comments to Docket Operations at 202–493–2251. Privacy: The FAA will post all comments it receives, without change, SUMMARY: E:\FR\FM\17MRR1.SGM 17MRR1 Federal Register / Vol. 82, No. 51 / Friday, March 17, 2017 / Rules and Regulations to http://www.regulations.gov/, including any personal information the commenter provides. Using the search function of the docket Web site, anyone can find and read the electronic form of all comments received into any FAA docket, including the name of the individual sending the comment (or signing the comment for an association, business, labor union, etc.). DOT’s complete Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477–19478), as well as at http://DocketsInfo. dot.gov/. Docket: Background documents or comments received may be read at http://www.regulations.gov/ at any time. Follow the online instructions for accessing the docket or go to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and Flightcrew Interface, ANM–111, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–2011; facsimile 425–227–1320. SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and opportunity for prior public comment on, these special conditions is impracticable because these procedures would significantly delay issuance of the design approval and thus delivery of the affected airplanes. In addition, the substance of these special conditions has been subject to the public comment process in several prior instances with no substantive comments received. The FAA therefore finds that good cause exists for making these special conditions effective upon publication in the Federal Register. mstockstill on DSK3G9T082PROD with RULES Comments Invited We invite interested people to take part in this rulemaking by sending written comments, data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data. We will consider all comments we receive by the closing date for comments. We may change these special conditions based on the comments we receive. Background On May 30, 2012, Bombardier applied for an amendment to Type Certificate VerDate Sep<11>2014 19:31 Mar 16, 2017 Jkt 241001 No. T00003NY to include the new Model BD–700–2A12 and BD–700– 2A13 series airplanes. The Model BD– 700–2A12 and BD–700–2A13 series airplanes, which are derivatives of the BD–700 currently approved under Type Certificate No. T00003NY, are ultralong-range, executive-interior business jets, with a passenger capacity of 19. Type Certification Basis Under the provisions of Title 14, Code of Federal Regulations (14 CFR) 21.101, Bombardier must show that the Model BD–700–2A12 and BD–700–2A13 series airplanes meet the applicable provisions of the regulations listed in Type Certificate No. T00003NY, or the applicable regulations in effect on the date of application for the change, except for earlier amendments as agreed upon by the FAA. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Bombardier Model BD–700– 2A12 and BD–700–2A13 series airplanes because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Bombardier Model BD– 700–2A12 and BD–700–2A13 series airplanes must comply with the fuelvent and exhaust-emission requirements of 14 CFR part 34 and the noisecertification requirements of 14 CFR part 36. The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.101. Novel or Unusual Design Features The Bombardier Model BD–700–2A12 and BD–700–2A13 series airplanes will incorporate the following novel or unusual design feature: Lateral-directional and longitudinal stability, and low-energy awareness, through an electronic flight-control system. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 14127 Discussion The EFCS on the Bombardier Model BD–700–2A12 and BD–700–2A13 series airplanes contain fly-by-wire control laws that can impact static stability; therefore, the conventional requirements in the regulations are not always met. Positive static-directional stability is defined as the tendency to recover from a skid with the rudder free. Positive static-lateral stability is defined as the tendency to raise the low wing in a sideslip with the aileron controls free. These control criteria are intended to accomplish the following: • Provide additional cues of inadvertent sideslips and skids through control-force changes. • Ensure that short periods of unattended operation do not result in any significant changes in yaw or bank angle. • Provide predictable roll and yaw response. • Provide an acceptable level of pilot attention (workload) to attain and maintain a coordinated turn. Static longitudinal stability on airplanes with mechanical links to the pitch-control surface means that a pull force on the controller results in a reduction in speed relative to the trim speed, and a push force on the controller results in higher than trim speed. Longitudinal stability is required by the regulations for the following reasons: • Speed change cues are provided to the pilot through increased and decreased forces on the controller. • Short periods of unattended control of the airplane do not result in significant changes in attitude, airspeed, or load factor. • A predictable pitch response is provided to the pilot. • An acceptable level of pilot attention (workload) to attain and maintain trim speed and altitude is provided to the pilot. • Longitudinal stability provides gust stability. Past experience on airplanes fitted with a flight-control system providing neutral longitudinal stability reveals insufficient feedback cues to the pilot for excursion below normal operational speeds. The maximum angle-of-attack protection system limits the airplane angle of attack and prevents stall during normal operating speeds, but this system is not sufficient to prevent stall at low-speed excursions below normal operational speeds. Until intervention, the pilot receives no stability cues because the airplane remains trimmed. Additionally, due to thrust variation, E:\FR\FM\17MRR1.SGM 17MRR1 14128 Federal Register / Vol. 82, No. 51 / Friday, March 17, 2017 / Rules and Regulations flight-control laws reduce feedback from the pitching moment. Low-speed excursions may become more hazardous without the typical longitudinal stability, and recovery may become more difficult when the low-speed situation is associated with a low altitude, and with the engines at low thrust or in performance-limiting conditions. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. Applicability As discussed above, these special conditions are applicable to Bombardier Model BD–700–2A12 and BD–700– 2A13 series airplanes. Should Bombardier apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. mstockstill on DSK3G9T082PROD with RULES Conclusion This action affects only a certain novel or unusual design feature on Bombardier Model BD–700–2A12 and BD–700–2A13 series airplanes. It is not a rule of general applicability. The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. Therefore, because a delay would significantly affect the certification of the airplane, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon publication in the Federal Register. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: conditions are issued as part of the type certification basis for Bombardier Inc. Model BD–700–2A12 and BD–700– 2A13 series airplanes. In lieu of the requirements of §§ 25.171, 25.173, 25.175 and 25.177(c), the following special conditions apply: 1. The airplane must be shown to have suitable static lateral, directional, and longitudinal stability in any condition normally encountered in service, including from the effects of atmospheric disturbance. The showing of suitable static lateral, directional, and longitudinal stability must be based on the airplane handling qualities, including pilot workload and pilot compensation, for specific test procedures during the flight-test evaluations. 2. The airplane must provide to the pilot adequate awareness of a lowenergy (low speed, low thrust, low height) state when fitted with flightcontrol laws presenting neutral longitudinal stability significantly below the normal operating speeds. ‘‘Adequate awareness’’ means warning information that alerts the flightcrew of unsafe operating conditions, allowing the flightcrew to take appropriate corrective action. 3. The following requirement must be met for the configurations and speed specified in paragraph (a) of § 25.177. In straight, steady sideslips over the range of sideslip angles appropriate to the operation of the airplane, the ruddercontrol movements and forces must be substantially proportional to the angle of sideslip in a stable sense. This factor of proportionality must lie between limits found necessary for safe operation. The range of sideslip angles evaluated must include those sideslip angles resulting from the lesser of: a. One-half of the available ruddercontrol input; and b. A rudder-control force of 180 pounds. Issued in Renton, Washington, on February 10, 2017. Michael Kaszycki, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–05327 Filed 3–16–17; 8:45 am] BILLING CODE 4910–13–P Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special VerDate Sep<11>2014 19:31 Mar 16, 2017 Jkt 241001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA–2015–7689; Special Conditions No. 25–645–SC] Special Conditions: Lufthansa Technik AG; Boeing Model 747–8 Series Airplanes, Large Non-Structural Glass in the Passenger Compartment Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions. AGENCY: These special conditions are issued for the Boeing Model 747–8 airplane. This airplane, as modified by Lufthansa Technik AG (Lufthansa), will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transportcategory airplanes. This design feature is the installation of large, nonstructural glass panels in the cabin area of an executive interior occupied by passengers and crew. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. DATES: Effective April 17, 2017. FOR FURTHER INFORMATION CONTACT: Jayson Claar, FAA, Airframe and Cabin Safety, ANM–115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–2194; facsimile 425–227–1320. SUPPLEMENTARY INFORMATION: SUMMARY: Background On March 8, 2012, Lufthansa Technik AG applied for a supplemental type certificate for large, non-structural glass panels in the passenger compartment in a Boeing Model 747–8 airplane. The Model 747–8 airplane is a derivative of the Boeing Model 747–400 airplane approved under type certificate no. A20WE. The airplane, as modified by Lufthansa Technik AG, is a four-engine, transport-category airplane that will have a maximum takeoff weight of 970,000 lbs, capacity for 24 crewmembers, and seating for 143 passengers. Type Certification Basis The certification basis for the Boeing Model 747–8 airplane, as defined in PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\17MRR1.SGM 17MRR1

Agencies

[Federal Register Volume 82, Number 51 (Friday, March 17, 2017)]
[Rules and Regulations]
[Pages 14126-14128]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05327]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2016-9296; Special Conditions No. 25-647-SC]


Special Conditions: Bombardier Inc., Model BD-700-2A12 and BD-
700-2A13 Series Airplanes, Electronic Flight Control System: Lateral-
Directional and Longitudinal Stability, and Low-Energy Awareness

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for the Bombardier Inc. 
(Bombardier) Model BD-700-2A12 and BD-700-2A13 series airplanes. These 
airplanes will have a novel or unusual design feature when compared to 
the state of technology envisioned in the airworthiness standards for 
transport-category airplanes. This design feature is lateral-
directional and longitudinal stability, and low-energy awareness, 
provided through an electronic flight-control system (EFCS). The 
applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. These special 
conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: This action is effective on Bombardier on March 17, 2017. We 
must receive your comments by May 1, 2017.

ADDRESSES: Send comments identified by docket number FAA-2016-9296 
using any of the following methods:
     Federal eRegulations Portal: Go to http://www.regulations.gov/ and follow the online instructions for sending 
your comments electronically.
     Mail: Send comments to Docket Operations, M-30, U.S. 
Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room 
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
     Hand Delivery or Courier: Take comments to Docket 
Operations in Room W12-140 of the West Building Ground Floor at 1200 
New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
     Fax: Fax comments to Docket Operations at 202-493-2251.
    Privacy: The FAA will post all comments it receives, without 
change,

[[Page 14127]]

to http://www.regulations.gov/, including any personal information the 
commenter provides. Using the search function of the docket Web site, 
anyone can find and read the electronic form of all comments received 
into any FAA docket, including the name of the individual sending the 
comment (or signing the comment for an association, business, labor 
union, etc.). DOT's complete Privacy Act Statement can be found in the 
Federal Register published on April 11, 2000 (65 FR 19477-19478), as 
well as at http://DocketsInfo.dot.gov/.
    Docket: Background documents or comments received may be read at 
http://www.regulations.gov/ at any time. Follow the online instructions 
for accessing the docket or go to Docket Operations in Room W12-140 of 
the West Building Ground Floor at 1200 New Jersey Avenue SE., 
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and 
Flightcrew Interface, ANM-111, Transport Airplane Directorate, Aircraft 
Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; telephone 425-227-2011; facsimile 425-227-1320.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and 
opportunity for prior public comment on, these special conditions is 
impracticable because these procedures would significantly delay 
issuance of the design approval and thus delivery of the affected 
airplanes.
    In addition, the substance of these special conditions has been 
subject to the public comment process in several prior instances with 
no substantive comments received. The FAA therefore finds that good 
cause exists for making these special conditions effective upon 
publication in the Federal Register.

Comments Invited

    We invite interested people to take part in this rulemaking by 
sending written comments, data, or views. The most helpful comments 
reference a specific portion of the special conditions, explain the 
reason for any recommended change, and include supporting data.
    We will consider all comments we receive by the closing date for 
comments. We may change these special conditions based on the comments 
we receive.

Background

    On May 30, 2012, Bombardier applied for an amendment to Type 
Certificate No. T00003NY to include the new Model BD-700-2A12 and BD-
700-2A13 series airplanes. The Model BD-700-2A12 and BD-700-2A13 series 
airplanes, which are derivatives of the BD-700 currently approved under 
Type Certificate No. T00003NY, are ultra-long-range, executive-interior 
business jets, with a passenger capacity of 19.

Type Certification Basis

    Under the provisions of Title 14, Code of Federal Regulations (14 
CFR) 21.101, Bombardier must show that the Model BD-700-2A12 and BD-
700-2A13 series airplanes meet the applicable provisions of the 
regulations listed in Type Certificate No. T00003NY, or the applicable 
regulations in effect on the date of application for the change, except 
for earlier amendments as agreed upon by the FAA.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 25) do not contain adequate or 
appropriate safety standards for the Bombardier Model BD-700-2A12 and 
BD-700-2A13 series airplanes because of a novel or unusual design 
feature, special conditions are prescribed under the provisions of 
Sec.  21.16.
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, or should any other model already included on 
the same type certificate be modified to incorporate the same novel or 
unusual design feature, these special conditions would also apply to 
the other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special 
conditions, the Bombardier Model BD-700-2A12 and BD-700-2A13 series 
airplanes must comply with the fuel-vent and exhaust-emission 
requirements of 14 CFR part 34 and the noise-certification requirements 
of 14 CFR part 36.
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38, and they become part of the type 
certification basis under Sec.  21.101.

Novel or Unusual Design Features

    The Bombardier Model BD-700-2A12 and BD-700-2A13 series airplanes 
will incorporate the following novel or unusual design feature:
    Lateral-directional and longitudinal stability, and low-energy 
awareness, through an electronic flight-control system.

Discussion

    The EFCS on the Bombardier Model BD-700-2A12 and BD-700-2A13 series 
airplanes contain fly-by-wire control laws that can impact static 
stability; therefore, the conventional requirements in the regulations 
are not always met.
    Positive static-directional stability is defined as the tendency to 
recover from a skid with the rudder free. Positive static-lateral 
stability is defined as the tendency to raise the low wing in a 
sideslip with the aileron controls free. These control criteria are 
intended to accomplish the following:
     Provide additional cues of inadvertent sideslips and skids 
through control-force changes.
     Ensure that short periods of unattended operation do not 
result in any significant changes in yaw or bank angle.
     Provide predictable roll and yaw response.
     Provide an acceptable level of pilot attention (workload) 
to attain and maintain a coordinated turn.
    Static longitudinal stability on airplanes with mechanical links to 
the pitch-control surface means that a pull force on the controller 
results in a reduction in speed relative to the trim speed, and a push 
force on the controller results in higher than trim speed. Longitudinal 
stability is required by the regulations for the following reasons:
     Speed change cues are provided to the pilot through 
increased and decreased forces on the controller.
     Short periods of unattended control of the airplane do not 
result in significant changes in attitude, airspeed, or load factor.
     A predictable pitch response is provided to the pilot.
     An acceptable level of pilot attention (workload) to 
attain and maintain trim speed and altitude is provided to the pilot.
     Longitudinal stability provides gust stability.
    Past experience on airplanes fitted with a flight-control system 
providing neutral longitudinal stability reveals insufficient feedback 
cues to the pilot for excursion below normal operational speeds. The 
maximum angle-of-attack protection system limits the airplane angle of 
attack and prevents stall during normal operating speeds, but this 
system is not sufficient to prevent stall at low-speed excursions below 
normal operational speeds. Until intervention, the pilot receives no 
stability cues because the airplane remains trimmed. Additionally, due 
to thrust variation,

[[Page 14128]]

flight-control laws reduce feedback from the pitching moment. Low-speed 
excursions may become more hazardous without the typical longitudinal 
stability, and recovery may become more difficult when the low-speed 
situation is associated with a low altitude, and with the engines at 
low thrust or in performance-limiting conditions.
    These special conditions contain the additional safety standards 
that the Administrator considers necessary to establish a level of 
safety equivalent to that established by the existing airworthiness 
standards.

Applicability

    As discussed above, these special conditions are applicable to 
Bombardier Model BD-700-2A12 and BD-700-2A13 series airplanes. Should 
Bombardier apply at a later date for a change to the type certificate 
to include another model incorporating the same novel or unusual design 
feature, these special conditions would apply to that model as well.

Conclusion

    This action affects only a certain novel or unusual design feature 
on Bombardier Model BD-700-2A12 and BD-700-2A13 series airplanes. It is 
not a rule of general applicability.
    The substance of these special conditions has been subjected to the 
notice and comment period in several prior instances and has been 
derived without substantive change from those previously issued. It is 
unlikely that prior public comment would result in a significant change 
from the substance contained herein. Therefore, because a delay would 
significantly affect the certification of the airplane, the FAA has 
determined that prior public notice and comment are unnecessary and 
impracticable, and good cause exists for adopting these special 
conditions upon publication in the Federal Register.
    The FAA is requesting comments to allow interested persons to 
submit views that may not have been submitted in response to the prior 
opportunities for comment described above.

List of Subjects in 14 CFR Part 25

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for Bombardier Inc. Model BD-700-2A12 and 
BD-700-2A13 series airplanes.
    In lieu of the requirements of Sec. Sec.  25.171, 25.173, 25.175 
and 25.177(c), the following special conditions apply:
    1. The airplane must be shown to have suitable static lateral, 
directional, and longitudinal stability in any condition normally 
encountered in service, including from the effects of atmospheric 
disturbance. The showing of suitable static lateral, directional, and 
longitudinal stability must be based on the airplane handling 
qualities, including pilot workload and pilot compensation, for 
specific test procedures during the flight-test evaluations.
    2. The airplane must provide to the pilot adequate awareness of a 
low-energy (low speed, low thrust, low height) state when fitted with 
flight-control laws presenting neutral longitudinal stability 
significantly below the normal operating speeds. ``Adequate awareness'' 
means warning information that alerts the flightcrew of unsafe 
operating conditions, allowing the flightcrew to take appropriate 
corrective action.
    3. The following requirement must be met for the configurations and 
speed specified in paragraph (a) of Sec.  25.177. In straight, steady 
sideslips over the range of sideslip angles appropriate to the 
operation of the airplane, the rudder-control movements and forces must 
be substantially proportional to the angle of sideslip in a stable 
sense. This factor of proportionality must lie between limits found 
necessary for safe operation. The range of sideslip angles evaluated 
must include those sideslip angles resulting from the lesser of:
    a. One-half of the available rudder-control input; and
    b. A rudder-control force of 180 pounds.

    Issued in Renton, Washington, on February 10, 2017.
Michael Kaszycki,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. 2017-05327 Filed 3-16-17; 8:45 am]
BILLING CODE 4910-13-P