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54-15-01: 54-15-01 de HAVILLAND: Applies to All Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 680 Inclusive. Compliance required by August 30, 1954. Inspect all rudder, elevator and aileron control cable terminals for damaged threads at the turnbuckle. Most reported defects have concerned the right-hand threads on turnbuckle terminals but all threaded terminals at turnbuckles should be inspected at the following locations: Control Cable Circuit Location Number of turn-Buckles 1. Base of control column. 2 Ailerons 2. Outboard wing inspection panels. 4 Elevators 3. Hatch on underside of rear fuselage. 2 Rudder 4. Rear fuselage interior. 2 Damaged or defective cables must be replaced. If any evidence of defects is found, de Havilland will supply replacement cables. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet Series B, No. 76 dated June 23, 1954, available from de Havilland Aircraft of Canada, Limited, Postal Station "L," Toronto, Canada, covers this same subject.)
2020-17-09: The FAA is adopting a new airworthiness directive (AD) for GA8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 a design change to the fuselage strut pick up ribs No. 5 and 6 that requires a reduced life limit. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
2020-17-12: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. This AD was prompted by reports of loose or missing nuts on the pilot and co-pilot ventral seat belt attachment points. This AD requires a detailed inspection of certain seat belt attaching point nuts for any loose or missing nuts and replacement, 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.
2020-16-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by reports of cracking found at certain fuselage frames. This AD requires repetitive inspections for discrepancies of certain locations in and around the fuselage and applicable corrective actions, 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.
2008-23-02: 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: One Part Number (P/N) LM-219-92 Centre Bracket from a P/N LM- 219-SA28 Aft Engine Mounting assembly was found to be cracked while installed on the aircraft. This reduces the effectiveness of the mounting assembly and could eventually cause it to fail. * * * * * A failed mounting assembly, if not corrected, could result in loss of the engine. We are issuing this AD to require actions to correct the unsafe condition on these products.
2006-08-09: The FAA is adopting a new airworthiness directive (AD) for all Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to repetitively inspect (using the eddy current method) the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repair or replace any cracked spar cap. This AD results from in-service fatigue cracking of the wing main spar lower cap at the center splice joint outboard fastener hole at hours time-in-service below the safe life limit established for these airplanes in AD 2002-11-05. We are issuing this AD to detect and correct cracks in the wing main spar lower cap at the center splice joint, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane.
69-25-06: 69-25-06 HAWKER SIDDELEY AVIATION, LTD: Amdt. 39-887. Applies to Model DH-104 Dove Airplanes which have aileron lever P/N 4 WA.315 installed. Compliance is required as indicated unless already accomplished. To prevent fatigue failure of the aileron lever, accomplish the following: (a) Visually inspect the aileron lever, P/N 4 WA.315 for cracks at the lugs for the attachment of the connecting rod and in the counterbored portion which receives the mass balance arm within the next 50 hours' time in service after the effective date of this AD unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. If evidence of cracks is found, verify using dye penetrant or other FAA-approved equivalent inspection methods. (b) If cracks are found during the inspection required by paragraph (a), before further flight, install a new forged aileron lever, P/N 4 WA.491 in accordance with Hawker Siddeley Aviation, Ltd. Dove Modification No. 967, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region. (c) If no cracks are found during the inspections required by paragraph (a), within the next 1,000 hours' time in service after the effective date of this AD, install a new forged aileron lever P/N 4 WA.491 in accordance with Hawker Siddeley Aviation, Ltd. Dove Modification No. 967, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region. (d) The inspection required in paragraph (a) may be discontinued after the new aileron lever, P/N 4 WA.491 or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region is installed. (Hawker Siddeley Aviation, Ltd. Technical News Sheet CT (104) No. 151, Issue 4, dated 14 July 1969 covers this subject.) This supersedes Amendment 454, Part 507 (27 F.R. 5793) AD 62-14-02. This amendment becomes effective January 3, 1970.
2006-08-08: The FAA is adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-400, AT-401, AT-401B, AT-402, AT-402A, and AT-402B airplanes. This AD requires you to lower the safe life for the wing lower spar cap for certain Models AT-402A and AT-402B airplanes and those that incorporate or have incorporated Marburger Enterprises, Inc. (Marburger) winglets. For Models AT-400, AT-401, AT-401B, AT-402, and certain AT-402A, airplanes, this AD requires you to repetitively inspect the wing lower spar cap in order to reach the safe life. We also developed an alternative method of compliance (AMOC) to the requirements of this AD for certain Models AT- 402A and AT-402B airplanes. The AMOC includes repetitive eddy current inspections, modification of the center splice connection, and lower spar cap replacement. This AD is the result of reports of cracks in the 3/8-inch bolt hole of the wing lower spar cap before reaching the approved safe life. We are issuing this AD to prevent fatigue cracks from occurring in the wing lower spar cap before the originally established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in wing separation and loss of control of the airplane.
2020-16-06: The FAA is adopting a new airworthiness directive (AD) for all Aviat Aircraft Inc. Models A-1, A-1A, A-1B, A-1C-180, and A-1C-200 airplanes. \n\tThis AD requires repetitive inspections of the forward horizontal stabilizer support assembly and the rear horizontal stabilizer support tube and reporting information to the FAA. This AD was prompted by field reports of complete failure of both the forward support assembly and the rear support tube due to fatigue. The FAA is issuing this AD to address the unsafe condition on these products.
99-25-12: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron (Bell)-manufactured Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters; and Southwest Florida Aviation SW204, SW204HP, SW205, and SW205A-1 helicopters, that currently requires modification and inspections of the tailboom vertical fin spar (vertical fin spar). This amendment requires the same modification and inspections plus two additional inspections and replacement of the vertical fin spar. This amendment is prompted by 6 accidents, 2 of which involved fatalities, involving fatigue cracks in the vertical fin spar that have occurred since the issuance of AD 97-20-09. The actions specified by this AD are intended to prevent in-flight failure of the vertical fin spar and subsequent loss of control of the helicopter.