Results
2025-02-11: The FAA is adopting a new airworthiness directive (AD) for certain FS 2001 Corp, FS 2002 Corporation, FS 2003 Corporation, Piper, and Piper Aircraft, Inc. (Piper) airplanes. This AD was prompted by reports of broken rudders. This AD requires replacing any rudder equipped with a rudder post made from a certain carbon steel with a rudder equipped with a rudder post made from a certain low-alloy steel. The FAA is issuing this AD to address the unsafe condition on these products.
61-01-02: 61-01-02 MARTIN: Amdt. 239 Part 507 Federal Register January 5, 1961. Applies to All Models 202, 202A and 404 Aircraft With Main Landing Gear Torque Arms Having More Than 12,000 Hours' Time In Service. Compliance required as indicated. Failures of Model 404 main landing gear torque arms have occurred in the lower attachment point where the torque scissors attach to the strut. Also, a failure was found in the apex (upper to lower torque arm attach point). As a result, the following must be accomplished within the next 225 hours' time in service, unless already accomplished within the last 225 hours' time in service, and every 450 hours' time in service thereafter. Inspect all surfaces of the torque arm lugs which attach the torque scissors to the strut for cracks or corrosion, using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Beginning with the first repetitive inspection, also inspect all surfaces of the torque arm apex using dye penetrant, ultrasonic or radiographic method, or FAA approved equivalent. Removal of bolts and bushings is required only if dye penetrant is used. If cracks or corrosion are found, the torque arm must be replaced before the next flight. This directive effective January 6, 1961.
2015-06-02 R1: We are revising an airworthiness directive (AD) 2015-06-02 for GA 8 Airvan (Pty) Ltd Model 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 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.
78-26-10 R1: 78-26-10 R1 GREAT LAKES: Amendment 39-3384 as amended by Amendment 39-5460. Applies to Models 2T-1A-1 and 2T-1A-2 airplanes. COMPLIANCE: Required as indicated unless already accomplished. To preclude contamination of cockpit heater air with carbon monoxide, accomplish the following: A) Within the next 25 hours time-in-service after the effective date of this AD: 1. Determine if the airplane is equipped with a P/N 50146 cockpit heater system and, if not, make an entry in the airplane's maintenance record that the airplane complies with Paragraph A)1 and that further compliance with this AD is not required. This determination and maintenance record entry may be made by the owner or holder of a valid pilot certificate. 2. If the airplane is equipped with a P/N 50146 cockpit heater system, prior to further flight, install a revision in the walk around inspection (Section II C. 2) of the Flight Manual adding an inspection of the exhaust system hanger (Figure1 of this AD). 3. If the airplane is equipped with a P/N 50146 cockpit heater system, prior to further flight, and within each 25 hours time-in-service thereafter: a) Remove the cowl to gain access to the engine installation. b) Disconnect the two cockpit air heater ducts from the heater shroud and remove the shroud. c) Visually inspect the support plates of the heat exchanger at both ends for cracks between the five tube cluster. d) If no cracks are found, return the heat exchanger to service. e) If cracks are found, either replace the heat exchanger system with an airworthy part or, in the alternative, comply with Paragraph B) of this AD. B) Remove the optional heat exchanger system and: 1) Install P/N 50126-1 stack assembly on all aircraft and P/N 50172-1 shield on aircraft equipped with IO-360-BIF6 and AEIO-360-BIG6 engines using QS100-M32W or equivalent clamps. 2) Block existing cockpit heat control valve in closed position by safety wiring control arm to adjacent aircraft structure. 3) Block the cockpit air supply opening in the left vertical engine cooling baffle per AC 43.13 1 and 2. 4) Remove Aircraft Flight Manual Revision specified in Paragraph A)2 of this AD (if installed). C) The actions and inspections specified in paragraphs A)2. and A)3. of this AD may be discontinued upon either removal of the P/N 50146 cockpit heater system per paragraph B) of this AD, or replacement of the P/N 50146 cockpit heater system with a different FAA approved cockpit heater system. D) Any equivalent method of compliance with this AD must be approved by the Manager, Boston Aircraft Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Great Lakes Aircraft Company (GLAC) Service Bulletin No. 9, dated November 17, 1978, or later revisions, pertain to portions of this subject. This amendment revises AD 78-26-10, Amendment 39-3384, which became effective January 4, 1979. This amendment, 39-5460, becomes effective on December 17, 1986. FIGURE 1 AIRPLANE FLIGHT MANUAL REVISION (AD 78-26-10 requires this revision to remain in the below designated airplane flight manual when the airplane is equipped with the optional P/N 50146 cockpit heater system. MODEL N S/N In addition to the presently specified preflight procedures, prior to each flight: 1. Inspect the left engine exhaust tail pipe hanger for deformation or failure. 2. If found failed, the hanger must be repaired prior to further flight.
98-05-12: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model ATP airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2015-14-07: We are adopting a new airworthiness directive (AD) for certain airplanes. This AD was prompted by reports of deficiencies in the flight control module (FCM) software. This AD requires installing certain FCM software. We are issuing this AD to correct deficiencies in the FCM software, which, if not corrected, could prevent continued safe flight and landing.
2015-14-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by an analysis, which indicated that in a limited flight envelope with specific conditions, divergent flutter could occur during a high g-load maneuver in combination with certain system failures. This AD requires replacing the lateral control electronic (LCE) modules, replacing the inboard elevator power control packages (PCPs), installing new external compensators for the PCPs, and revising the maintenance or inspection program. We are issuing this AD to prevent certain system failures from resulting in divergent flutter, and subsequent loss of continued safe flight and landing.
2001-26-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration, that requires, among other actions, modification of the main deck cargo door structure and fuselage structure; replacement of fasteners in the two door-side hinge elements; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
2001-26-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier; as applicable. These actions are necessary to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
98-05-01: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-366G1 helicopters, with certain main rotor head frequency adapters (frequency adapters) installed. This proposal requires inspecting the frequency adapter to determine if a certain frequency adapter is installed, and if so, removing and discarding the frequency adapter and replacing it with an airworthy frequency adapter before further flight. This amendment is prompted by a report of disbonding of the metal center section of a frequency adapter from the elastomer, caused by a lack of adherence during the production process. The actions specified by this AD are intended to prevent vibrations caused by disbonding of the center section of a frequency adapter from the elastomer, that could result in loss of control of the helicopter.
97-24-07: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes that have kit JK 2496 and modification JM 7537 installed. This action requires installing magnetic latching relays on the ignition system because of the auto-ignition system becoming disabled when switching from ground power to the airplane s internal power. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent loss of the airplane s internal power connection to the auto-ignition system, which could cause loss of engine power and possible loss of control of the airplane.
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.
2003-14-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes. This action requires modification of the wire bundles of the video control center (VCC) of the passenger address and entertainment system, and an operational test if necessary. This action is necessary to prevent chafing of the wire bundles of the VCC against the rudder and/ or elevator control cables, which could result in arcing of the wires in the wire bundles and severing of the cables. Severed cables, if combined with an engine-out during takeoff, or a high crosswind during takeoff or landing, could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2025-03-07: The FAA is superseding Airworthiness Directive (AD) 2016-20- 12, AD 2018-17-21, and AD 2019-14-04, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2019-14-04 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations and terminated the provisions of AD 2018-17-21, which, in turn, terminated the provisions of AD 2016-20-12. This AD was prompted by the determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
97-23-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes, that requires a one-time inspection for discrepancies of the release cable of the forward and rear passenger doors, and replacement of any discrepant release cable with a new release cable. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the passenger door to open and consequent inability of the slide/slide raft to deploy, which could delay or impede passengers when exiting the airplane during an emergency.
2015-13-10: We are superseding Airworthiness Directive (AD) 2011-17-07 for certain M7 Aerospace LLC (type certificate previously held by M7 Aerospace LP) Models SA226-T, SA226-T(B), SA226-TC, and SA226-AT airplanes. AD 2011-17-07 required repetitive replacement and inspection of certain elevator, rudder, aileron, and aileron-to-rudder interconnect primary control cables, and checking and setting of flight control cable tension. This AD requires repetitively inspecting and replacing the primary flight control rudder cables, repetitively replacing all other primary flight control and trim tab cables, and checking/setting the flight control cable tension. This AD was prompted by a report of extensive damage found on the left hand primary flight control rudder cable located under the cockpit floor on one of the airplanes affected by AD 2011-17-07. We are issuing this AD to correct the unsafe condition on these products.