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2002-09-03: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332L2 helicopters. This action requires, before further flight, verifying that the air vent is installed on the inflation cylinder of each life raft assembly. If the air vent is missing, this AD also requires replacing the cylinder head with an airworthy part before further flight. This amendment is prompted by the discovery that an inflation cylinder in the life raft did not have an air vent installed. This condition, if not corrected, could result in inadvertent life raft inflation, loss of the life raft, contact with the main or tail rotor, and subsequent loss of control of the helicopter.
81-16-04: 81-16-04 BELLANCA AIRCRAFT CORPORATION: Amendment 39-4172. Applies to Models 8KCAB, 7ECA, 7GCAA, 7GCBC and 7KCAB airplanes certificated in Acrobatic category. \n\n\tTo insure that the competition harness (also referred to as the ACRO harness) is installed properly, accomplish the following before further flight: \n\n\t1.\tUnless previously accomplished, insert figure I of this AD into all applicable aircraft having approved flight manuals. \n\n\t2.\tAttach figure I of this AD to all "Operating Limitation Instructions" (yellow card) for those applicable aircraft where a flight manual is not required (Model 7 Series airplanes). \n\n\t3.\tInspect all competition harness installations to insure that the shoulder straps are installed in accordance with figure I of this AD. Insure that the shoulder straps of the added harness pass on the forward side of the seat back. \n\n\tThis amendment becomes effective July 28, 1981.
2016-15-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600-2D15 (Regional Jet Series 705), Model CL-600-2D24 (Regional Jet Series 900), and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of corrosion found on the slat and flap torque tubes in the slat and flap control system. This AD requires replacement of the slat and flap torque tubes in the slat and flap control system. We are issuing this AD to prevent rupture of a corroded slat or flap torque tube. This condition could result in an inoperative slat or flap system and consequent reduced controllability of the airplane.
2016-15-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200 and -200CB series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer S-14R, lower fastener row, are subject to widespread fatigue damage (WFD). This AD requires external dual frequency eddy current (DFEC) or internal high frequency eddy current (HFEC) inspections of the lap splice, inner skin \n\n((Page 49874)) \n\nfasteners, at stringer S-14R, station (STA) 440 through STA 540, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane.
2001-22-07: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Honeywell International, Inc. (formerly AlliedSignal, Inc. and Textron Lycoming) LTP 101 series turboprop and LTS101 series turboshaft engines. This amendment requires a new life limitation and removal of rigid tube fuel manifold assemblies and replacement with serviceable assemblies. This amendment is prompted by reports of cracking and fuel leakage of rigid tube fuel manifolds. The actions specified by this AD are intended to prevent engine fuel leakage due to low-cycle fatigue (LCF) cracking of the rigid tube fuel manifold, which could result in an in-flight fire.
2009-04-17: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-45 and CF6-50 series turbofan engines. This AD requires replacing certain forward and aft centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly. This AD results from the engine manufacturer issuing new service information. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating due to high imbalance engine conditions, leading to damage to the airplane.
2004-03-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200C and -200F series airplanes, that requires repetitive inspections to find fatigue cracking in the upper chord of the upper deck floor beams, and repair if necessary. For certain airplanes, this amendment also provides an optional repair/ modification, which extends certain repetitive inspection intervals. This action is necessary to find and fix cracking in certain upper deck floor beams. Such cracking could extend and sever floor beams at a floor panel attachment hole location and could result in rapid decompression and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2016-15-01: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of partial loss of no-back brake (NBB) efficiency on the trimmable horizontal stabilizer actuator (THSA). This AD requires an inspection to determine THSA part numbers, serial numbers, and flight cycles on certain THSAs; and repetitive replacement of certain THSAs. We are issuing this AD to prevent loss of THSA NBB efficiency, which, in conjunction with the inability of the power gear to keep the ball screw in its last commanded position, could lead to an uncommanded movement of the horizontal stabilizer, possibly resulting in loss of control of the airplane.
70-06-05: 70-06-05 BRITTEN-NORMAN, LTD: Amdt. 39-956. Applies to BN-2 and BN-2A airplanes. To prevent failure of the elevator trim system final drive lever attachment lugs, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 25 hours' time in service since the last inspection until the modifications of paragraph (b) have been accomplished, visually inspect the elevator trim system final drive lever (P/N NB-45-D-1823) for cracks in accordance with Britten-Norman Service Bulletin No. BN-2/SB.24 dated January 8, 1969, or later ARB-approved issue or an FAA-approved equivalent. (b) If cracks are found on the drive lever during the inspections required by paragraph (a), before further flight replace the affected lever (P/N NB-45-D-1823) with a new lever (P/N NB-45-D-2165) by incorporating Modification NB/M/394 in accordance with Britten- Norman Service Bulletin BN-2/SB.24 dated January 8, 1969, or later ARB-approved issue or an FAA-approved equivalent. (c) The repetitive inspections required by paragraph (a) may be discontinued after compliance with paragraph (b) has been accomplished. This amendment becomes effective March 17, 1970.
88-10-05: 88-10-05 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-5913. Applies to Model 382 series airplanes, Serial Numbers 3946 through 4250, and 4299 through 4303, except those having outer wings installed to a configuration equivalent to Serial Number 4542 or subsequent; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent severe damage to the lower surface panels of the outer wings, accomplish the following: A. Within the next 50 hours time-in-service after the effective date of this AD; or upon the accumulation of 11,000 flight hours total time-in-service for airplanes Serial Numbers 3946 through 4250, or 18,000 flight hours total time-in-service for airplanes Serial Numbers 4299 through 4303; whichever occurs later, perform an inspection of the outer wing lower surface panels 1, 2, 3, and 4, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987, to determine the existence of doublers on those panels between outer wing stations 161 and 195. B. If doublers have been installed on panels 1, 2, 3, and 4, left and right, in accordance with Northwest Industries (NWI) Drawing 3609103, the airplane may be returned to normal service. C. If doublers have been installed on panels 1 and 2 in accordance with Lockheed Service Bulletin 382-152 (382-57-35), dated September 2, 1987, or later FAA-approved revisions, prior to further flight, accomplish either of the following: 1. Inspect the heat shield and nacelle fairing attachment fastener holes from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987. a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours. b. If cracks are found, prior to further flight, repair in accordance with an FAA-approved method. 2. Modify the wing in accordance with Lockheed Service Bulletin 382-57- 73, dated January 28,1988. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph C.1.a., above. D. If doublers have not been installed on panels 1, 2, 3, and 4, prior to further flight, accomplish either of the following: 1. Inspect the heat shield and nacelle fairing attachment fastener from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987. a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours. b. If cracks are found, prior to further flight, repair in accordance with an FAA approved method. 2. Modify the wing in accordance with Northwest Industries (NWI) Drawing 3609103. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph D.1.a., above. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes toa base in order to comply with the requirements of this AD. F. 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, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Aircraft Certification Office. All persons affected by this directive who have not already received the applicable service information from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Department 72-05, Zone 80, 86 South Cobb Drive, Marietta, Georgia 30063. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia. This amendment becomes effective May 25, 1988.