Results
2015-06-02: We are adopting a new airworthiness directive (AD) for GA 8 Airvan (Pty) Ltd Model GA8-TC320 airplanes. This AD results from [[Page 14811]] 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 missing required engine mount fire seal washers, which could reduce the engine retention capability in the event of a fire. We are issuing this AD to require actions to address the unsafe condition on these products.
2015-06-01: We are superseding an airworthiness directive (AD) 2014-06-03 for British Aerospace Regional Aircraft Model Jetstream Series 3101 and Jetstream Model 3201 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 stress corrosion cracking of the main landing gear spigot housing. We are issuing this AD to require actions to address the unsafe condition on these products.
2015-06-03: We are adopting a new airworthiness directive (AD) for Stemme AG TSA-M Models S6 and S6-RT gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a bending defect of the fork head installed in the aileron, speed brake, and flap control systems. We are issuing this AD to require actions to address the unsafe condition on these products.
2015-05-06: We are adopting a new airworthiness directive (AD) for Flugzeugwerke Altenrheim AG (FFA) Models AS 202/15 ``BRAVO'', AS 202/ 18A ``BRAVO'', and AS 202/18A4 ``BRAVO'' airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion on the upper forward fuselage stringers. We are issuing this AD to require actions to address the unsafe condition on these products.
2025-04-04: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R[eacute]gional Model ATR72 airplanes. This AD was prompted by reports of the main landing gear (MLG) rear hinge pin being ruptured. This AD requires replacing affected parts and prohibits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2025-04-05: The FAA is superseding Airworthiness Directive (AD) 2023-11- 08, which applied to all Airbus SAS Model A330-841 and -941 airplanes. AD 2023-11-08 required maintenance actions, including a high-pressure valve (HPV) seal integrity test, repetitive replacement of the HPV clips, revision of the existing airplane flight manual (AFM), and implementation of updates to the FAA-approved operator's minimum equipment list (MEL). This AD was prompted by the determination that the replacement intervals required by AD 2023-11-08 must be reduced to address the unsafe condition. This AD continues to require the actions in AD 2023-11-08. This AD also reduces the HPV clip replacement intervals, requires an additional revision of the existing AFM for certain airplanes, and limits the installation of HPV clips, 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.
2015-05-04: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This AD requires inspecting the aft fuselage upper skin (upper skin) for a crack and the upper left longeron assembly (longeron assembly) for a crack, corrosion, or defect. This AD requires replacing or repairing a part or section, depending on the inspection's outcome. This AD was prompted by reports of cracks in the upper left-hand longeron. This AD's actions are intended to prevent failure of the longeron assembly or the upper skin, which could lead to a structural failure and loss of helicopter control.
75-15-04: 75-15-04 DOWTY ROTOL: Amendment 39-2265. Applies to Dowty Rotol Type (c) R212/4-30-4/22 propellers incorporating hub and driving center assemblies. P/N's 601022294, 601022211, 601022105, and RA 64883, that have not been modified in accordance with Dowty Rotol Modification Nos. (c) VP2388-(SB61-604) or (c) VP2779(SB 61-767). These propellers are installed on, but not necessarily limited to, Hawker Siddeley Model H.S. 748 Series 2A airplanes. Compliance is required as indicated. To detect cracking of the propeller hub front wall/snout radius areas between the eyebolt guides, accomplish the following: (a) Inspect the propeller hubs in accordance with Paragraph 2.A. of Dowty Rotol Service Bulletin No. 61-828, dated September 10, 1973, or an FAA-approved equivalent as follows: (1) For those operators required to perform propeller overhauls, inspect at the next propeller overhaul and at each propeller overhaul thereafter. (2) For all other operators, inspect within the next 4000 hours' time in service after the effective date of this AD, and thereafter inspect at intervals not to exceed 4000 hours' time in service since last inspection. (b) Inspect those propeller hubs that have accumulated more than 10,000 hours' time in service on the effective date of this AD in accordance with Paragraph 2.B. of Dowty Rotol Service Bulletin No. 61-828, dated September 10, 1973, or an FAA-approved equivalent, unless already accomplished, as follows: (1) For those propeller hubs that have never been inspected or that have accumulated more than 1400 hours' time in service since last inspected in accordance with Paragraph 2.A. or 2.B. of Dowty Rotol Service Bulletin No. 61-828, dated September 10, 1973, inspect within the next 600 hours time in service. (2) For those propeller hubs that have accumulated not more than 1400 hours' time in service since last inspected in accordance with Paragraph 2.A. or 2.B. of Dowty Rotol Service Bulletin No.61-828, dated September 10, 1973, inspect prior to the accumulation of 2000 hours' time in service since last inspected. (c) If a cracked hub is found during an inspection required by this AD, accomplish the following: (1) Before further flight, replace the cracked hub with a serviceable part of the same part number or a part number approved for installation on the propeller. (2) Inspect all the operator's propeller hubs covered by this AD in accordance with Paragraph 2.B. of Dowty Rotol Service Bulletin No. 61-848, dated September 10, 1973 or an FAA-approved equivalent as follows: (i) For those propeller hubs that have accumulated more than 1400 hours' time in service since last inspected in accordance with paragraph (a) or (b) of this AD or that have never been inspected and have accumulated over 1400 hours' time in service, inspect within the next 600 hours' time in service; and, thereafter, continue to inspect at intervals not to exceed 2,000 hours' time inservice since last inspection (ii) For those propeller hubs that have accumulated not more than 1400 hours' time in service since new or since last inspected in accordance with paragraph (a) or (b) of this AD, inspect prior to the accumulation of 2000 hours' time in service since last inspected or since new, as applicable, and, thereafter, continue to inspect at intervals not to exceed 2000 hours' time in service since last inspection. (d) The inspections required by paragraphs (a), (b), and (c) of this AD may be discontinued upon the incorporation of Dowty Rotol Modification Nos. (c) VP 2388(SB61-604) or (c) VP 2779(SB61-767) or FAA-approved equivalent modifications. (e) Upon request of an operator, an FAA maintenance inspector subject to prior approval of the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator, if the request contains substantiating data to justify the adjustment. This amendment becomes effective August 15, 1975.
2015-04-05: We are adopting a new airworthiness directive (AD) for certain Sikorsky Model S-76A, B, C, and D helicopters. This AD requires inspecting the tail rotor drive shaft (TDS) flange-to-shaft attachment hardware for correct assembly and correct torque of the fasteners. If there is a discrepancy, this AD requires, before further flight, applying an index mark to the flange and TDS, inspecting the flange and shaft for a crack, fracture, wear, and certain measurements, and replacing any part that does not meet the approved criteria before further flight. This AD is prompted by a partial loss of tail rotor drive resulting in a forced landing. The actions specified by this AD are intended to prevent failure at the flange-to-shaft attachment, loss of a tail rotor drive, and subsequent loss of control of the helicopter.
2025-04-06: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and Model ATR72 airplanes. This AD was prompted by the insufficient accuracy of a certain Angle of Attack (AoA) probe at low airspeeds which could lead to a delayed activation of the stick pusher in a flaps-extended configuration. This AD requires replacing each affected part with a serviceable part, and also prohibits 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.