Federal Aviation Administration June 2005 – Federal Register Recent Federal Regulation Documents

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400F series airplanes. This AD requires initial detailed and open-hole high frequency eddy current inspections for cracking of the web, upper chord, and upper chord strap of the upper deck floor beams, and repair of any cracking. This AD also requires a preventive modification of the upper deck floor beams, and repetitive inspections for cracking after accomplishing the modification. This AD is prompted by reports of fatigue cracking found on the upper deck floor beam to frame attachment points. We are issuing this AD to prevent fatigue cracks in the upper chord, upper chord strap, and the web of the upper deck floor beams and resultant failure of the floor beams. Failure of a floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent loss of controllability of the airplane. Failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane.

The FAA proposes to supersede Airworthiness Directive (AD) 97- 24-09, which applies to Burkhart Grob Model G 103 C Twin III SL sailplanes. AD 97-24-09 currently requires repetitively inspecting the propeller bearing and upper pulley wheel for increased play and, if increased play is found, modifying the propeller bearing and pulley wheel. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this proposed AD to prevent loss of the sailplane propeller caused by increased play in the current design propeller bearing and upper pulley wheel. This could result in loss of control of the sailplane.

The FAA is adopting a new airworthiness directive (AD) for Rockwell International (Aircraft Specification No. A-2-575 previously held by North American and recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) airplanes. This AD contains the same information as emergency AD 2005-12-51 and publishes the action in the Federal Register. It requires immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. This AD is the result of a report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD to detect and correct any fatigue crack in the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of either wing, which could result in failure of the wing. This failure could lead to loss of control of the aircraft.

These special conditions are issued to AMSAFE, Inc. for the installation of an AMSAFE, Inc., Inflatable Four-Point Restraint Safety Belt with an Integrated Airbag Device on the Adam Model A500. These airplanes, as modified by the installation of this Inflatable Safety Belt, will have novel and unusual design features associated with the upper-torso restraint portions of the four-point safety belt, which contains an integrated airbag device. 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.

This action establishes Class E airspace at Sutton, WV. Controlled airspace extending upward from 700 feet Above Ground Level (AGL) is needed to contain aircraft operating into Braxton County Airport, Sutton, WV, under Instrument Flight Rules (IR).

The FAA is issuing this notice to advise the public of a meeting of RTCA Special Committee 202: Portable Electronic Devices.

This notice announces the availability of and requests comments on proposed changes to AC 27-1B, Certification of Normal Category Rotorcraft, and AC 29-2C, Certification of Transport Category Rotorcraft. These proposed changes will revise AC paragraph 27.351 and AC paragraph 29.351B, Yawing Conditions, dated 2/12/03. This notice is necessary to give all interested persons an opportunity to comment on the proposed AC change.

The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD requires modifying the auxiliary power unit (APU) exhaust duct in the environmental control system (ECS) bay; installing new, improved insulation on this APU exhaust duct; and replacing the existing drain pipe with a new exhaust drain pipe blank. This AD is prompted by a determination that the temperature of the skin of the APU exhaust duct in the ECS bay is higher than the certificated maximum temperature for this area. We are issuing this AD to prevent the potential for ignition of fuel or hydraulic fluid, which could leak from pipes running through the ECS bay. Ignition of these flammable fluids could result in a fire in the ECS bay.

The FAA is adopting a new airworthiness directive (AD) for certain AvCraft Dornier Model 328-100 and -300 airplanes. This AD requires operators to install colored identification strips on the pulley brackets, fairlead bracket assemblies, operational assemblies, and flight control cables. This AD is prompted by a report that the flight control systems do not have elements that are distinctively identified. We are issuing this AD to prevent the incorrect re-assembly of the flight control system during maintenance, which could result in reduced controllability of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain The Lancair Company (Lancair) Model LC41-550FG airplanes. This AD requires both visual and dye penetrant inspections of the elevator torque tube assembly for cracks. If a crack is found, this AD requires replacement with a modified assembly that incorporates a steel doubler. This AD also requires replacement of the modified elevator torque tube assembly every 300 hours time-in-service or 18 months (whichever occurs first). This AD results from cracks found in the weld area of the elevator torque tube assembly. We are issuing this AD to detect and correct cracks in the elevator torque tube assembly, which could result in failure of the elevator torque tube assembly and subsequent loss of control of the airplane.

The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires inspecting the electrical connectors of the fire extinguisher bottles for the forward and aft baggage compartments and for the auxiliary power unit and engine nacelles to determine if they are connected correctly; and doing related investigative and corrective actions, if necessary. This AD is prompted by reports of the electrical connectors for the fire bottles in the forward and aft baggage compartments being cross connected. We are issuing this AD to detect and correct cross connection of the fire extinguisher bottles, which could result in failure of the fire bottles to discharge and consequent inability to extinguish a fire in the affected areas.

This amendment adopts miscellaneous amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Hartzell Propeller Inc. HC, BHC, and PHC series propellers; and McCauley Propeller Systems controllable propellers serviced by Oxford Aviation Services Limited, doing business as CSE Aviation, in the United Kingdom between September 1998 and October 2003. This proposed AD would require inspecting the propeller blades and other critical propeller parts for wear and mechanical damage. This proposed AD results from findings that CSE Aviation failed to perform specific inspections and repairs. We are proposing this AD to detect unsafe conditions that could result in a propeller blade separating from the hub and loss of control of the airplane.

This action raises the ceiling of Restricted Area 2211 (R- 2211), Blair Lakes, AK, from the current 18,000 feet above mean sea level (MSL) to Flight Level (FL) 310. The expanded airspace is required to fulfill United States Air Force (USAF) training requirements. The current restricted airspace at Blair Lakes is too small to allow aircrew training in high altitude weapons delivery tactics. Specifically, the training requirements call for practicing the release of weapons from higher altitudes than are currently available within the existing restricted airspace.

The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 series airplanes. This AD requires modifying the frequency converters located in the closet assembly in the passenger compartment, and making various wiring changes in and between the closet assembly and forward purser work station. This AD also requires modifying the in-flight entertainment system prior to or concurrently with the modification of the frequency converters. This AD is prompted by a certification review that revealed a frequency converter failure mode not identified in the original system design. We are issuing this AD to prevent a short circuit between the frequency converter output and the distribution circuit breakers, which could result in overheating and failure of adjacent wiring and consequent adverse effects on other systems sharing the affected wire bundle.

The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires a one-time ultrasonic inspection for certain airplanes, and repetitive detailed inspections for all airplanes, for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. This AD also provides for optional terminating actions. This AD is prompted by a report of a crack found in the forward lug of the right-hand MLG rib 5 fitting during greasing of both MLG pintle bearings. We are issuing this AD to find and fix cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during landing.

The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires revising the Airworthiness Limitation section of the Instructions for Continued Airworthiness of the Dash 8 400 Series (Bombardier) Maintenance Requirements Manual to reduce the life limits of the main landing gear (MLG) orifice support tube, upper bearing, and piston plug; and to reduce the threshold for initiating repetitive detailed inspections for cracking of the engine isolator brackets. This AD is prompted by the discovery of fatigue failures, during type certification fatigue testing, at the engine isolator bracket and at the orifice support tube, upper bearing, and piston plug in the shock strut assembly of the MLG, which are principal structural elements. We are issuing this AD to prevent the development of cracks in these principal structural elements, which could reduce the structural integrity of the engine installation and the MLG. Reduced structural integrity of the engine installation could result in separation of the engine from the airplane, and reduced structural integrity of the MLG could result in collapse of the MLG.

Pursuant to FAA's rulemaking provisions governing the application, processing, and disposition of petitions for exemption part 11 of Title 14, Code of Federal Regulations (14 CFR), this notice contains a summary of certain petitions seeking relief from specified requirements of 14 CFR. The purpose of this notice is to improve the public's awareness of, and participation in, this aspect of FAA's regulatory activities. Neither publication of this notice nor the inclusion or omission of information in the summary is intended to affect the legal status of any petition or its final disposition.

The FAA proposes to adopt a new airworthiness directive (AD) for certain Bombardier Model DHC-8-401 and -402 airplanes. This proposed AD would require a one-time inspection of the fuel and hydraulic tubes, and corrective actions if necessary. This proposed AD would also require modifying fairlead plate assemblies. This proposed AD is prompted by reports of chafing between fuel and hydraulic tubes and the fairlead plate where the tubes pass through the firewall. We are proposing this AD to prevent chafing of the fuel and hydraulic tubes, which could lead to fuel and/or hydraulic fluid leakage in the engine nacelle area and consequent fire or explosion.

The FAA proposes to revise an earlier proposed airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic Company and Fairchild Heli Porter) Model PC-6 airplanes. The earlier NPRM proposed to require you to repetitively inspect the stabilizer-trim attachment and structural components for cracks, corrosion, and discrepancies and replace any defective part with a new part. The earlier NPRM also proposed to require you to replace all Fairchild connecting pieces with a Pilatus connecting piece. The earlier NPRM resulted from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. This proposed AD would retain the actions from the earlier NPRM and would require you to replace fittings without an index after the part number (P/N) with an improved part. This proposed AD results from incorporating revised manufacture service information to include a procedure for replacing certain fittings with an improved part and to correct the allowable limits of the actuator attachment hole diameters. This proposed AD also clarifies the applicability. Since this action imposes an additional burden over that proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on this additional action.

This statement summarizes the major changes and the implications of publishing the revised policy, and background on the need for a revised policy. The revised FIS Policy updates the existing 1998 FAA Airborne FIS Policy to reflect the current FIS data link status and provides the basis for transition from the current (FAA) industry Flight Information Services Data Link (FISDL) service to the planned evolution of an FAA FIS data link service using National Airspace System (NAS) technologies such as the Universal Access Transceiver (UAT) and/or Next Generation Air-Ground Communication (NEXCOM). During the transition, the revised FIS Policy supports continuation of the FISDL service by temporarily extending the current use of VHF channels through FAA-industry agreement. In 1998 the FAA Administrator published the current Airborne Flight Information Services Policy Statement (see attachment). That policy provided the basis for implementing the existing FISDL service through FAA-industry agreement. Under the agreement, FAA provides two VHF frequencies and management oversight while industry (Honeywell) provides the FISDL network and cockpit products. In 2002 the FAA published the Automatic Dependent Surveillance-Broadcast (ADS-B) Link Decision which includes providing FIS-B services via the UAT network. The Safe Flight 21 program is developing the ADS-B technology and has intalled a ``pocket'' UAT network along the East Coast. The major purpose for publishing the revised FIS Policy is to establish a strategy for transitioning from the existing industry- government FIS data link service to one or more FAA-only FIS data link services. The existing industry-government service, called FIS Data Link (FISDL), is owned and operated by Honeywell Inc. The replacement FAA-only system(s) will be the Universal Access Transceiver (UAT) and/ or NEXCOM. During the transition to an FAA FIS data link service, the FAA will provide temporary extension of two VHF channels for continuation of the FISDL service.

The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to repetitively inspect the nose landing gear (NLG) assembly, paying special attention to the NLG swivel tube and the engine truss in the area of the NLG attachment, for cracks and damaged (defective) welding seams. If you find cracks or defects during any inspection, this AD requires you to replace the cracked or defective part. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct cracks and defects in the NLG assembly, which could result in failure of the NLG. This failure could lead to a hard landing and/or loss of control of the airplane during landing operations.

The FAA is adopting a new airworthiness directive (AD) to supersede AD 79-10-15, which applies to all Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 402B, 411, and 411A airplanes. AD 79-10-15 currently requires repetitive inspections of the right and left wing spar lower cap areas for fatigue cracks and requires wing spar cap repair or replacement as necessary. This AD is the result of fatigue and crack growth analyses of the wings of these airplanes, recent cracks found on similar design Model 402C airplanes, and the FAA's determination that repetitive inspections and a wing spar modification are necessary to address the unsafe condition. Consequently, this AD would require repetitive inspections and a spar strap modification on each wing. The actions specified by this AD are intended to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing with consequent loss of airplane control. FAA is also issuing AD 2005-12-13 to require the spar strap modification and long-term inspections on Models 402C and 414A airplanes.

The FAA is superseding an existing airworthiness directive (AD) for Teledyne Continental Motors (TCM) (formerly Bendix) S-20, S- 1200, D-2000, and D-3000 series magnetos equipped with impulse coupling assemblies. That AD currently requires replacing riveted-impulse coupling assemblies and snap-ring coupling assemblies, which are worn beyond limits, with serviceable riveted-impulse coupling assemblies or snap-ring impulse coupling assemblies. This ad requires a reduced inspection interval for magnetos with riveted-impulse coupling assemblies installed on certain Lycoming engine models. This AD does not lower the inspection interval for magnetos with snap-ring impulse coupling assemblies. This AD also limits the applicability to certain Lycoming engine models. This AD results from data provided by the manufacturer that shows a need to reduce the inspection intervals for riveted-impulse coupling assemblies used on certain Lycoming engine models. We are issuing this AD to prevent failure of the magneto impulse coupling assembly and possible engine failure.