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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.