Results
2015-14-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203 airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD was prompted by reports that side link clevis bolts of the front engine mount do not meet the design service goal (DSG) requirements on airplanes equipped with General Electric Company CF6-80A3 engines. This AD requires repetitive replacement of all side link clevis engine mount bolts. We are issuing this AD to prevent failure of the front engine mount, and consequent possible departure of the engine.
2025-03-09: The FAA is adopting a new airworthiness directive (AD) for certain Costruzioni Aeronautiche Tecnam S.P.A. (Tecnam) Model P2010 and P2010 TDI airplanes. This AD was prompted by the disconnection of a rudder pedals torque tube from one of its hinges. This AD requires modifying the airplane by installing larger diameter retainer washers on both the left-hand (LH) and right-hand (RH) rudder pedals torque tube hinges, installing new self-locking nuts, doing a functional or operating test of the system to ensure the retaining washers are installed properly, and applying a torque stripe on the LH and RH nuts and bolts threads. The FAA is issuing this AD to address the unsafe condition on these products.
2015-14-02: We are adopting a new airworthiness directive (AD) for certain serial number GE Aviation Czech s.r.o. M601E-11, M601E-11A, and M601F turboprop engines. This AD requires inspection of the reduction gearbox and supporting cone. This AD was prompted by the determination that wear or cracking, and subsequent misalignment of the quill shaft of the engine and the power turbine (PT) shaft, may lead to rupture of the quill shaft, overspeed of the PT, and uncontained engine failure. We are issuing this AD to prevent misalignment and rupture of the quill shaft, which could lead to overspeed of the PT, uncontained engine failure, and damage to the airplane.
2025-03-01: The FAA is superseding Airworthiness Directive (AD) 2021-04- 18, which applied to Airbus Helicopters Model EC225LP helicopters. AD 2021-04-18 required repetitively inspecting the bearing in the swashplate assembly of certain main rotor (M/R) mast assemblies and, depending on the findings, replacing the M/R mast assembly. AD 2021-04- 18 also prohibited installing those M/R mast assemblies unless certain requirements were met. Since the FAA issued AD 2021-04-18, it was determined that additional M/R mast assemblies are affected by the same unsafe condition and that it is necessary to distinguish the affected part numbers between M/R mast assemblies and mast swashplate assemblies. This AD continues to require the actions specified in AD 2021-04-18 and adds additional part-numbered M/R mast assemblies and distinguishes the affected part numbers between M/R mast assemblies and mast swashplate assemblies, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also clarifies the possible consequences that could result from the unsafe condition and clarifies a requirement. The FAA is issuing this AD to address the unsafe condition on these products.
2015-14-09: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 747 airplanes equipped with a main deck side cargo door (MDSCD). This AD was prompted by recent testing that indicates that intermodal containers, when loaded as cargo, under certain flight- load conditions, can shift and impact the adjacent fuselage frames. This AD requires revising the airplane flight manual (AFM) to incorporate limitations for carrying certain payloads. We are issuing this AD to prevent intermodal containers loaded in the offset method from shifting during flight gust loads and damaging fuselage frames, which could lead to the structural failure of the aft fuselage in flight and subsequent in-flight breakup of the airplane.
2001-25-08: This amendment adopts a new airworthiness directive (AD) for Sikorsky Model S-70A and S-70C helicopters. This action requires certain inspections of each main landing gear drag beam (beam) for a crack and removing any cracked beam before further flight. This action also requires reducing the torque of the jackpad mounting bolt retention nut (nut) of each beam. This amendment is prompted by failure of a beam due to stress corrosion resulting from sustained tensile stress due partly to excessive torque of the nut. The actions specified in this AD are intended to prevent excessive torque of the nut, failure of a beam, and subsequent loss of control of the helicopter during takeoff or landing.
2001-25-05: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007 series turbofan engines. That AD currently requires removal of certain compressor cone shafts from service before exceeding new cyclic life limits and replacement with serviceable parts. This amendment requires increasing the cyclic life limit for certain serial numbers of new compressor cone shafts, part number (P/N) 23070729, that are used on AE3007A1/3 and AE3007A1P engines. This amendment is prompted by recent approved changes in engineering and manufacturing processes for new compressor cone shafts P/N 23070729. The actions specified by this AD are intended to prevent low-cycle fatigue (LCF) failure of cone shafts, which could result in an uncontained engine failure and damage to the airplane.
2018-07-22: We are superseding Airworthiness Directive (AD) 2017-08-09 for DG Flugzeugbau GmbH Model DG-500MB gliders that are equipped with a Solo 2625 02 engine modified with a fuel injection system following the instructions of Solo Kleinmotoren GmbH Technische Mitteilung Nr. 4600-3 and identified as Solo 2625 02i. 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 the potential of an in-flight shut-down and engine fire due to failure of the connecting stud for the two fuel injector mounts of the engine redundancy system on gliders equipped with a Solo 2625 02i engine. We are issuing this AD to add a model to the applicability and require actions to address the unsafe condition on these products.
2003-14-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. This AD requires modification of the No. 3 electrical equipment panel behind the avionics rack, and modification of the No. 2 propeller de-ice timer. This action is necessary to prevent incorrect altitude information transmitted by the Mode S transponder and simultaneous loss of the Traffic Alert and Collision Avoidance System (TCAS), and increasing the possibility of an air traffic conflict. This action is intended to address the identified unsafe condition.
91-03-06: 91-03-06 BRITISH AEROSPACE: Amendment 39-6868. Docket No. 90-NM-272-AD. Applicability: All Model BAe 125-800A and HS 125-700A series airplanes, pre-Modification 253159; and all pre-Modification 253159 Model DH/HS/BH 125 series airplanes that have been retrofitted with Garrett TFE 731 engines; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the overheating of the battery and loss of the pilot's and co-pilot's primary and standby heading and attitude information displays, accomplish the following: A. Within 30 days after the effective date of this AD, perform a visual inspection of the Generator Control Unit (GCU) earth wire, in accordance with British Aerospace Service Bulletin 24-A278, dated July 26, 1990. 1. If no evidence of damage is found, prior to further flight, perform a continuity check of the earth wire between the starter/generator terminal stud "E" and connector pin "F" on the GCU, in accordance with paragraph 2.A.(6) of the Accomplishment Instructions of the service bulletin. If continuity exists, no further action is required. 2. If evidence of damage or lack of continuity is found or suspected, prior to further flight, replace the earth wire in accordance with the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6868, AD 91-03-06) becomes effective on February 11, 1991.