Results
2024-04-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report of possible chafing of a power harness at fuselage frame (FR) 65. This AD requires rerouting the power harness, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2024-05-51: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CT7-2E1, CT7-2F1, CT7-8A, CT7-8E, CT7-8F5 engines, and various restricted category helicopters with GE Model T700-GE-700,-701A, -701C, -701D/CC, -701D, -401, -401C, CT7-2D or CT7-2D1 engines installed. This AD was prompted by at least four reports of failures of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly within the last several months. This AD requires a phase array ultrasonic inspection of the torque reference tube magnetic insert braze joint of the power turbine drive shaft assembly for inadequate braze coverage, and repair or replacement of the power turbine drive shaft assembly if necessary. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and helicopters and is now issuing this AD to address the unsafe condition on these products.
2000-25-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model AS-350B, BA, B1, B2, and D; and AS-355E, F, F1, F2, and N helicopters. That AD currently requires inspecting the main gearbox suspension bi-directional cross beam (cross beam) for cracks, replacing the cross beam if a crack is found, and adding time intervals for repetitive dye-penetrant inspections on cross beams with 5,000 or more hours time-in-service (TIS). This amendment requires the same inspections as the existing AD but would delete repetitive dye-penetrant inspections on cross beams with 5,000 or more hours TIS. This amendment is prompted by the discovery that repetitive dye-penetrant inspections were erroneously required in the existing AD. The actions specified by this AD are intended to prevent failure of the cross beam that could lead to rotation of the main gearbox, severe vibrations, and a subsequent forced landing.
2024-04-05: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracks in the lateral mounts of the main transmission support case. This AD requires repetitive visual inspections and fluorescent penetrant inspections (FPI) and, depending on the results, corrective action, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2010-10-21: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Bombardier Aerospace has completed a system safety review of the CL-600-2C10/CL600-2D15/CL-600-2D24 aircraft fuel system against the new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525-001 to determine if mandatory corrective action was required. The assessment showed that certain hydraulic system failure scenarios could lead to a rapid overheat in the hydraulic lines without giving flight crew sufficient time to react before the No. 1 and No. 2 hydraulic system tubing inside the fuel tank reaches the fuel auto ignition temperature. This could result in a fuel tank explosion. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
76-18-10: 76-18-10 MESSERSCHMITT-BOLKOW-BLOHM (MBB): Amendment 39-2719. Applies to Model BO-105A and BO-105C helicopters, Serial Numbers 1 through 280, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the engine mount assembly, accomplish the following: (a) For helicopters with 500 hours or less total time in service on the effective date of this AD, comply with paragraph (c) of this AD before the accumulation of 600 hours total time in service. (b) For helicopters with more than 500 hours total time in service on the effective date of this AD, comply with paragraph (c) of this AD within the next 100 hours time in service. (c) Determine the part numbers of the existing right outboard engine mount flanges and washers and their corresponding replacement flanges and washers and replace the existing flanges and washers with the new flanges and washers in accordance with paragraph 2 entitled "Accomplishment Instructions" of MBB BO-105 Service Bulletin No. 60-25, Revision 1, dated October 13, 1975 or an FAA-approved equivalent. This amendment becomes effective on October 1, 1976.
2005-07-25: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, A300 B4-600R, A300 C4-605R Variant F, and A300 F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. That AD currently requires replacement of the transformer rectifier units (TRUs) in the avionics compartment with new, improved TRUs. This new AD requires replacement of the TRUs installed according to the existing AD with different TRUs that are improved. This AD is prompted by analysis that has revealed that certain diodes installed in the TRUs are the main factor contributing to the continuing TRU failures. We are issuing this AD to prevent failure of the TRUs. Failure of multiple TRUs could result in loss of the thrust reversers, autothrottle, flaps, and various systems (wing/ cockpit window anti-ice, trim tank pumps, and windshield wipers) on the airplane; or display of incorrect information to the flightcrew.
97-09-08: This amendment supersedes Airworthiness Directive AD 82-25-09 which currently requires repetitively inspecting the pilot and co-pilot control wheel sub-assemblies for cracks, and if cracked, modifying the cracked part on the AeroSpace Technologies of Australia, Limited (ASTA), formerly Government Aircraft Factories (GAF) Nomad Models N22S, N22B, and N24A airplanes. This action would retain the repetitive inspection of the pilot and co-pilot control wheel sub-assemblies for cracks, but would include a modification that would terminate the repetitive inspections by replacing or re-working the control wheel sub-assembly with a part of improved design. This superseding action is prompted by cracking in the control wheel sub-assemblies and the manufacture of an improved part that would terminate the repetitive inspection. The actions specified by this AD are intended to prevent failure of the pilot's and co-pilot's control wheels, which, if not detected and corrected, could result in loss of control of the airplane.
2005-07-27: The FAA is superseding an existing airworthiness directive (AD), that is applicable to Aviointeriors S.p.A. (formerly ALVEN), series 312 seats. That AD requires initial and repetitive inspections of the seat central crossmember for cracks, and if necessary, replacing the crossmember with a new crossmember. This ad requires the same actions and adds other crossmember part numbers for inspection. In addition, this AD replaces the original design crossmembers with reinforced design crossmembers as optional terminating actions to the repetitive inspections. This AD results from reports of 88 cracked seat central crossmembers and 60 aisle side crossmembers, to date; and, from the introduction of reinforced optional seat crossmembers by the manufacturer. We are issuing this AD to prevent the loss of the structural integrity of the seat due to cracks in seat crossmembers, which could lead to passenger injury.
2005-07-12: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the body station 291.5 frame at stringer 16R, and corrective actions if necessary. This AD is prompted by reports of fatigue cracks in the web of the body station 291.5 frame near the forward galley door. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door.