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91-06-18: 91-06-18 AIRBUS INDUSTRIE: Amendment 39-6940. Docket No. 90-NM-225-AD. Applicability: All Model A310-200 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the wing rear spar and prevent reduced structural integrity of the wings, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 1,000 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) rototest inspection of the wing rear spar at certain bolt holes where the main landing gear (MLG) forward pick-up fittings are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A310-57-2046, dated March 5, 1990. 1. If no cracks are found at the first inspection and no cold working of the holes concerned is carried out, repeat the HFEC rototest inspection at intervals not to exceed 4,500 landings. 2. If no cracksare found at the first inspection and a spar life extension by cold working of the holes concerned is carried out in accordance with the paragraph 2.3.(1)(b) of the Accomplishment Instructions of the above service bulletin or Airbus Industrie Service Bulletin A310-57-2049, dated April 10, 1990; repeat the HFEC rototest inspection within the next 18,000 landings, and thereafter at intervals not to exceed 12,000 landings. B. If cracks are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Repeat the HFEC rototest inspection at an interval approved by the Manager, Standardization Branch, ANM-113. C. 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 theManager, 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. D. 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 documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6940, AD 91-06-18) becomes effective on April 22, 1991.
96-21-13: This amendment adopts a new airworthiness directive (AD) that is applicable to LITEF GmbH Attitude and Heading Reference System (AHRS) Unit Model LCR-92, LCR-92S, and LCR-92H installed on but not limited to Sikorsky Aircraft Model S-76 helicopters, McDonnell Douglas Helicopter Systems Model MD-900 helicopters, Bell Helicopter Textron, Inc. Model 412 helicopters, and Pilatus Model PC-12 airplanes. This action requires either installing a placard adjacent to each primary attitude indicator which states that flight is limited to Visual Flight Rules (VFR) operations only, or modifying and inspecting the AHRS wiring cables, requiring a repetitive inspection of the cable shielding, and inserting a statement into the aircraft flight manual. This amendment is prompted by a field report and verified by laboratory tests that shows there is an unusual AHRS reaction to certain radio frequency signals. The actions specified by this AD are intended to prevent reliance on or to correct the cause of misleading roll and pitch information produced by the AHRS when encountering certain radio frequency signals.
2004-20-03: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. This amendment requires a detailed inspection of the wing leading edge de-icer boots to determine if they comply with certain patch limits in the critical zone; and corrective action, if necessary. This action is necessary to prevent reduced aerodynamic smoothness of the wing leading edge de-icer boots and possible reduced stall margin, which could result in a significant increase in stall speeds, leading to a possible stall prior to activation of the stall warning. This action is intended to address the identified unsafe condition.
76-12-01: 76-12-01 BELL: Amendment 39-2636. Applies to Bell Models 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, and 47H-1 helicopters certificated in all categories. Compliance required within 300 hours' time in service after the effective date of this AD unless already accomplished. To prevent possible fatigue failure of tail rotor hub bolt, Part Numbers 47-641-052-3 or - 5, accomplish the following: (a) Remove and disassemble the tail rotor hub and blade assembly. (b) Remove the metal grease seal from each tail rotor blade grip and install the seal, Part Number 47-641-042-3, in each blade grip to clear the head of the hub bolt. (c) Remove the hub assembly bolts, Part Numbers 47-641-052-3 or -5, from the tail rotor hub assembly. Install hub bolts, Part Number 47-641-194-1, in the tail rotor hub as specified in paragraph 6-16.e., Section IV, Models 47D-1, 47G, and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or as specified by equivalent FAAapproved procedures. (d) Assemble and track and balance the tail rotor hub and blade assembly as specified in the pertinent Model Maintenance and Overhaul Instruction Manual or as specified in FAA approved equivalent procedures. (e) Compliance with Bell Helicopter Company Service Bulletin No. 47-76-1 dated January 5, 1976, or later approved revision fulfills compliance with this AD. This amendment becomes effective July 14, 1976.
2022-17-12: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) LEAP-1A model turbofan engines. This AD was prompted by reports of two in-flight shutdowns (IFSDs) and subsequent investigation by the manufacturer that revealed cracks in the high-pressure turbine (HPT) rotor stage 1 blades. This AD requires initial and repetitive borescope inspections (BSIs) of the HPT rotor stage 1 blades. Depending on the results of the BSIs, this AD requires either additional BSIs at reduced intervals or replacement of the HPT rotor stage 1 blades. This AD also requires sending the inspection results to CFM if any unserviceable finding is found. The FAA is issuing this AD to address the unsafe condition on these products.
78-08-04: 78-08-04 BOEING: Amendment 39-3187. Applies to Model 747 series airplanes certificated in all categories and equipped with pressurization system outflow valve assemblies, Boeing P/N 60B00025-3, -11, -12, and -17 (Hamilton Standard P/N 719201-2, -3, -4, -5, -6, -7, - 8, and -9). Compliance required as indicated. To prevent rapid loss of pressurization in flight accomplish the following: \n\n\tA.\tWithin 350 hours time in service after the effective date of this airworthiness directive, unless already accomplished, and thereafter at intervals not to exceed 900 hours time in service until modified in accordance with part B of this airworthiness directive, inspect forward and aft gates of each outflow valve assembly in accordance with the instructions contained in Boeing Service Bulletin No. 747-21-2139, Revision 1 dated April 7, 1978, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Gates found with delamination or cracks in the hinge-to-gate bonds must be removed and replaced with a part free of delamination or cracks. Removed gates may be forwarded to Hamilton Standard for further evaluation or modified in accordance with part B of this airworthiness directive, as applicable, prior to being returned to service. \n\tB.\tWithin 4000 hours time in service after the effective date of this airworthiness directive, modify the outflow valve assemblies in accordance with the instructions contained in Hamilton Standard Service Bulletin H.S. Code 747 AC-114, Revision 1 dated March 15, 1978, or later FAA approved revision, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tC.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the inspection compliance time and/or modification compliance time specified in this airworthiness directive to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. \n\tThe 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). \n\n\tAD 77-25-06, Amendment 39-3098 (42 FR 63637) is hereby superseded. \n\tThis amendment becomes effective May 10, 1978.
2004-19-08: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 800 series turbofan engines. This AD requires revising the Time Limits Manual for RR RB211 Trent 800 series turbofan engines. These revisions include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD results from the need to require enhanced inspection of selected critical life-limited parts of RB211 Trent 800 series turbofan engines. We are issuing this AD to prevent failure of critical life- limited rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.
2013-12-06: We are adopting a new airworthiness directive (AD) for Eurocopter Model MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, and MBB- BK117 C-2 helicopters with a Metro Aviation (Metro) vapor-cycle air conditioning kit installed in accordance with Supplemental Type Certificate (STC) No. SH3880SW. This AD requires repetitively inspecting the air conditioning drive pulley (pulley) for looseness and properly installed lockwire, and also requires reinstalling the pulley. This AD is prompted by two reports of the pulley detaching from the rotor brake disc on the tail rotor (T/R) driveshaft. These actions are intended to prevent separation of the pulley, damage to the T/R driveshaft, and subsequent loss of control of the helicopter.
2022-16-07: The FAA is superseding Airworthiness Directive (AD) 2016-26-05 and AD 2019-21-02, which applied to certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2016-26-05 and AD 2019-21-02 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, and that new airplanes have been added to the applicability. This AD continues to require the actions in AD 2019-21-02, 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) The FAA is issuing this AD to address the unsafe condition on these products.
2022-16-08: 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 a dual-engine automatic shutdown on landing. This AD requires revising the existing airplane flight manual (AFM) to incorporate a new normal procedure and revised non-normal procedures, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.