Results
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.
76-07-14: 76-07-14 AERONAUTICA MACCHI: Amendment 39-2578. Applies to Models AL-60 and AL-60B airplanes, certificated in all categories. Compliance is required as indicated. To detect cracks in the engine mounting plates and to prevent possible failure of the engine mount, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours time in service from the last inspection until modified in accordance with paragraph (d) of this AD, comply with the following: (1) Inspect the areas around the periphery of each of the four engine mounting plates for cracks using a dye-penetrant method. (2) Inspect the surfaces inside the concavity of each of the four engine mounting plates, where the lower shock mounts and attaching bolts are inserted, for cracks, using a dye penetrant method, in accordance with Aeronautica Macchi Mandatory Service Bulletin SB-L-0003, dated October 29, 1974, or an FAA-approved equivalent. (b) If a crack is found during an inspection required by paragraph (a) of this AD, before further flight, comply with paragraph (d) of this AD. (c) If no cracks are found during any of the inspections required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, or before the accumulation of 1200 hours total airplane time in service, whichever occurs later, comply with paragraph (d) of this AD. (d) Modify each of the four engine mounting plates by adding a reinforcement plate, P/N 6070-47, and replacing the mounting plate shim, P/N 6005, with a new designed shim, P/N 6005A, in accordance with Aeronautica Macchi Mandatory Modification Bulletin, MB-L-0001, Change 1, dated March 5, 1975, or an FAA- approved equivalent. This amendment becomes effective April 26, 1976.
2024-05-05: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by a report of incorrect marking and assembly of the two-way valves for the left- and right-hand engine fire extinguishing systems. This AD requires accomplishing a functional check of an affected part; replacing an affected part if necessary; reporting the functional check results; and prohibiting the installation of affected parts; 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.
2005-07-20: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -800, and -900 series airplanes. This AD requires installing and testing an updated version of the operational program software of the flight control computers. This AD is prompted by a report of an airplane pitching up with rapidly decreasing indicated airspeed after the flightcrew set a new altitude into the autopilot. We are issuing this AD to prevent anomalous autopilot operation that produces a hazardous combination of airplane attitude and airspeed, which could result in loss of control of the airplane.
78-12-11: 78-12-11 BRITISH AEROSPACE, INC.: Amendment 39-3237. Applies to (Hawker Siddeley) Model HS-125 Series 700A Airplanes, serial numbers NA 0201 thru NA 0210 and NA 0218, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent electrical overload and possible fire, accomplish the following in accordance with Section 2, "ACCOMPLISHMENT INSTRUCTIONS" of British Aerospace (formerly Hawker Siddeley Aviation Ltd.) Service Bulletin 24-203 (2653), dated December 14, 1977, or an FAA approved equivalent. (a) Within 10 hours time in service after the effective date of this AD, replace the existing Minyvin 20 beacon light cable and associated marker sleeves and terminal lugs with Minyvin 16 cable and associated B25Y marker sleeves and 36151 terminal lugs or with parts specified in paragraph (b) of this AD. (b) Nyvin 16 or MIL-W-5086 Series 2 cable may be used as alternate replacement cables. Also, FAA approved equivalent marker sleeves including single sleeves with indelible coding may be used in lieu of B25Y sleeves. This amendment becomes effective June 26, 1978.