Results
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.
2001-24-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; and Model DC-9-81, -82, and -83 series airplanes. This AD requires modification of the light switch for the cargo compartment(s). This action is necessary to prevent generation of smoke and fire in a cargo compartment due to an illuminated light with a missing cover contacting cargo contents for an extended period of time. This action is intended to address the identified unsafe condition.
2025-03-06: The FAA is superseding Airworthiness Directive (AD) 2017-22- 03, AD 2023-13-10, and AD 2024-04-03, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2017-22-03, AD 2023-13-10, and AD 2024-04-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD continues to require certain actions in AD 2023-13-10 and all actions in AD 2024-04- 03, and 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.
2020-23-03: The FAA is superseding Airworthiness Directive (AD) 2017-09-05 for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2017-09-05 required repetitively checking screws in the emergency flotation gear. This new AD retains the requirements of AD 2017-09-05 but also requires installing a modification (MOD), which is a terminating action for the repetitive checks. This AD was prompted by the development of the MOD by Airbus Helicopters that addresses the unsafe condition. The actions of this AD are intended to address an unsafe condition on these products.
2003-15-01: The FAA is adopting a new airworthiness directive (AD) for certain McCauley Systems, Inc. propellers that are installed on BAE Systems (Operations) Limited Jetstream Model 4101 airplanes. This AD requires a fluorescent penetrant inspection (FPI) of the propeller blades for cracks. This AD is prompted by a report of a significant crack in a propeller blade shank and two reports of cracks in the hubs of the same propeller model. We are issuing this AD to detect cracks in the propeller blade shank that could cause a failure of the propeller blade and loss of control of the airplane.
81-10-09: 81-10-09 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4106. Applies to Model SA 365C series helicopters, certificated in all categories, which have skid type landing gear P/N 365A82.1370 and/or P/N 365A82.1400 installed, and either do not have tail ballast installed in accordance with Aerospatiale Drawing 365MR0351, or are not modified in accordance with Aerospatiale Service Bulletin Dauphin No. 53.04, dated May 10, 1979. Compliance required as indicated, unless already accomplished. To prevent failure of the tail rotor gearbox tripod mount assembly, accomplish the following: (a) Within the next five hours time in service after the effective date of this AD, and every five hours thereafter, and prior to the first flight of each day, inspect the tail rotor gearbox tripod mount assembly, P/N 360A23.0024 (hereinafter referred to as TRGB mount assembly) for cracks in accordance with Aerospatiale Work Card No. 53.10.605, dated March 1979, or an FAA- approved equivalent. (b) If any crack or cracks are found, remove the TRGB mount assembly from service and replace with a new TRGB mount assembly, and thereafter inspect in accordance with paragraph (a) until compliance with paragraph (c) is accomplished. (c) Within the next 100 hours time in service: (1) Incorporate a tail ballast weight in accordance with Aerospatiale Dauphin Service Bulletin NO. 53.04, dated May 10, 1979, or an FAA-approved equivalent. (2) Remove the tail rotor and tail rotor gearbox in accordance with Aerospatiale Work Card No. 65.42.401, dated March 1979, or an FAA-approved equivalent. (3) Inspect the three leg-to-ring junction welds of the TRGB with Aerospatiale Standard Practice Manual, Section 02.80, dated August 1976, or an FAA-approved equivalent, and - (i) If no cracks are found, reinstall the tail rotor and tail rotor gearbox in accordance with Aerospatiale Work Card No. 65.42.401, dated March 1979, or an FAA-approved equivalent, and return to service. (ii) If any cracks are found, remove the TRGB mount assembly from service, replace with a new TRGB mount assembly, reinstall the tail rotor and tail rotor gearbox in accordance with Aerospatiale Work Card No. 65.42.401, or an FAA-approved equivalent, and return to service. (d) After accomplishment of paragraph (c) of this AD, the inspection requirements of this AD may be discontinued. (e) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to SocieteNationale Industrielle Aerospatiale (SNIAS), 37, blvd. de Montmorency, 75781 Paris Cedex 16, France. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment becomes effective April 30, 1981, as to all persons except those persons to whom it was made immediately effective by the telegraphic AD issued May 25, 1979, which contained this amendment.
2001-24-30: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200C and -200F series airplanes, that requires installation of drip shields over certain shelves in the main equipment bay. This action is necessary to prevent water from dripping through floor panels of the main deck cargo bay onto wire bundles and electronic components, which could lead to the loss of function of multiple electronic components and, consequently, could reduce the flight crew's ability to operate in adverse conditions. This action is intended to address the identified unsafe condition.
2025-03-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reported events of annunciated horizontal stabilizer trim actuator (HSTA) jams occurring at the end of the cruise phase of flight. This AD requires lubricating the HSTA using an improved method, at a reduced interval, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-13-08: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 2000EX airplanes. This AD requires revising the airplane flight manual to include a procedure for addressing minimum fan speed rotation (N1) values during stand-alone engine anti-ice system operation for engines equipped with certain air inlets. This AD was prompted by a quality review of recently delivered airplanes which identified a manufacturing deficiency of some engine air inlet anti-ice piccolo tubes. We are issuing this AD to detect and correct reduced performance of the engine anti-ice protection system, leading to ice accretion and ingestion into the engines, which could result in dual engine power loss and consequent reduced controllability of the airplane.
2000-12-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect fatigue cracking or loose or missing fasteners of the aft torque bulkheads of the outboard nacelle struts; and repair, if necessary. This amendment expands the applicability of the existing AD to include certain additional airplanes, and removes certain other airplanes from the applicability of the existing AD. For all airplanes subject to this AD, this amendment also requires accomplishment of a new terminating action. This action is necessary to prevent fatigue cracking and loose or missing fasteners in the aft torque bulkheads of the outboard nacelle struts, which could result in failure of an outboard nacelle strut diagonal brace load path and possible separation of the nacelle from the wing. This action is intended to address the identified unsafe condition.
2025-03-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400F, 747-8F, and 747-8 series airplanes. This AD was prompted by a report that, during potable water servicing, there were multiple engine indicating and crew alerting system messages. The cause was the separation of a fitting and steel water supply tube above an electronics equipment cooling air filter, behind the forward cargo compartment left sidewall. This AD requires, depending on configuration, installing at certain locations: conduits on exposed potable water supply lines, envelope assemblies over all exposed potable water line fittings and exposed potable water supply lines, a slitted spray shield, a two-piece deflector shield around the equipment cooling system (ECS) air inlet, and/or a shroud on exposed potable water supply lines. The FAA is issuing this AD to address the unsafe condition on these products.
2024-04-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a 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.
2015-12-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report of corrosion found during the manufacturing process for some oxygen pipe assemblies that are used to supply oxygen to the flightcrew. This AD requires an inspection to determine the batch number or installation date of the oxygen pipe assembly that is installed at the end of the right-hand crew distribution line, and, if necessary, replacement of the pipe. We are issuing this AD to detect and correct corrosion, which could lead to blocked or reduced oxygen supply to a flightcrew member during a decompression event or a smoke/ fire event in the cockpit. Under certain conditions, corrosion particles could increase the risk of fire in the cockpit.
97-10-03: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires repetitive ultrasonic inspections to detect cracking of the lugs of the engine mounting beams, and replacement of the beam with a serviceable part, if necessary. This amendment is prompted by reports of fatigue cracking of the lugs of the engine mounting beams. The actions specified by this AD are intended to detect and correct such cracking of the engine mounting lugs, which could result in reduced structural capability of the engine mount.
2001-24-23: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes, that requires modification of the battery ground cable installation in the center accessory compartment (CAC). The actions specified by this AD are intended to prevent a loose ground stud and/or cable attachments, and consequent chafing of adjacent structure and electrical arcing, which could result in smoke/fire in the CAC in the event of fuel leakage. This action is intended to address the identified unsafe condition.
2023-13-10: The FAA is superseding Airworthiness Directive (AD) 2020-20-05 and AD 2022-09-16, which applied to certain Airbus SAS Model A318 series; A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, and -153N; A320 series; and A321 series airplanes. AD 2020-20-05 and AD 2022-09-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2022-09-16, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate additional 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.
2015-12-06: We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by reports of non-conforming windshield supports (coupe rails). This AD requires a general visual inspection of the coupe rails to detect gouging and scratches, and to determine if a radius has been removed; an ultrasound inspection to measure the dimensions of the lower coupe rails; an eddy current inspection to detect cracks of the lower coupe rails; replacement of [[Page 34259]] the lower coupe rails if necessary; and revision of the maintenance or inspection program, as applicable. We are issuing this AD to detect and correct non-conforming windshield supports, which could result in uncontrolled cabin depressurization and compromise of the capability of the windshield to withstand a bird strike.
98-21-34: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive inspections to detect corrosion and cracks on the bottom area of the wing skin, and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion and cracks on the bottom area of the wing skin, which could result in reduced structural integrity of the airplane.