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2000-08-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive inspections to detect damage of certain taxi light assemblies, and replacement with a new or serviceable part, if necessary. This AD also requires eventual replacement of certain taxi light assemblies with improved parts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report that a damaged taxi light detached from an airplane and was ingested into the airplane engines. The actions specified by this AD are intended to prevent damage to the taxi light assembly, which could result in detachment of the taxi light assembly from the airplane, ingestion of taxi light debris into an engine, and consequent loss of thrust from one or both engines.
90-08-11: 90-08-11 BRITISH AEROSPACE: Amendment 39-6568. Docket No. 89-NM-234-AD. Applicability: Model BAe 146-100A, Serial Numbers E1002 and subsequent; Model BAe 146-200A, Serial Numbers E2012 and subsequent; and Model BAe 146-300A, Serial Numbers E3118 and subsequent; certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless previously accomplished. To prevent loss of wing flap asymmetry protection and reduced airplane controllability, accomplish the following: A. Install an improved wing flap electronic control unit (ECU) in accordance with British Aerospace Service Bulletin 27-95-70420A, dated April 27, 1989. NOTE: The British Aerospace Service Bulletin references Dowty Rotol Service Bulletin 146-27-75 for additional instructions. B. Install a warning placard on the front face of the ECU, in accordance with British Aerospace Service Bulletin 27-95-70420A, dated April 27, 1989. The warning placard states: "WARNING - This equipment must not be removed or re-racked in flight." 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it 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 British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6568, AD 90-08-11) becomes effective on May 14, 1990.
2000-08-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing 777 series airplanes, that requires a one-time inspection to detect cracking of the fastener holes common to the upper wing skins and trailing edge panels of both wings, and corrective actions, if necessary. This amendment also requires coldwork of the fastener holes and installation of new or serviceable fasteners. This amendment is prompted by a report indicating that fatigue cracks have been found in the upper wing skin of both wings. The actions specified by this AD are intended to prevent fatigue cracking of the upper wing skin, which could result in reduced structural integrity of the wing.
89-25-13: 89-25-13 AIRBUS INDUSTRIE: Amendment 39-6413. Docket No. 89-NM-118-AD. Applicability: All Models A300, A310, and A300-600 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent collapse of the nose landing gear (NLG), accomplish the following: A. Prior to the accumulation of 26,000 landings or within 30 days after the effective date of this AD, whichever occurs later, modify the NLG barrel, in accordance with one of the following service bulletins, as applicable: Airplane Model Service Bulletins A300 A300-32-385, Rev. 1, dated October 15, 1988 A310 A310-32-2039, Rev. 1, dated October 15, 1988 A300-600 A300-32-6022, Rev. 1, dated October 15, 1988 NOTE: The above-referenced service bulletins reference Messier-Hispano-Bugatti Service Bulletin 470-32-577 for additional modification procedures. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it 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 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, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6413, AD 89-25-13) becomes effective on January 12, 1990.
2000-08-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines, that currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer s Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional eddy current inspections (ECI) for the high pressure turbine rotor (HPTR) Stage 1 and 2 disks for all affected engine models, and would add fan forward shaft inspections for the CF6-80C2 engine model only. This amendment is prompted by additional focused inspection procedures for critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
88-24-13: 88-24-13 FOKKER B.V.: Amendment 39-6070. Applies to Model F-28 series airplanes, Serial Numbers 11003 to 11241 inclusive, 11991, and 11992, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent structural failure in the flap or rear spar web and fuel leakage, accomplish the following: A. Prior to the accumulation of either 10,000 flight hours or 20,000 flight cycles (landings), or within 500 flight cycles (landings) after the effective date of this AD, whichever occurs later: Conduct an external visual inspection of the flap track beam support bracket for position in accordance with Part 1 of Fokker Service Bulletin F28/57-81, dated May 27, 1988. B. If the flanges of the flap track beam support bracket are found during the inspection specified in A., above, to be parallel to the rear spar, no further action is required. C. If the flanges of the flap track beam support bracket are found during the inspection specified in A., above, not to be parallel to the rear spar, inspect for cracks in the web of the rear spar, in accordance with Part 2 of service Bulletin F28/57-81, dated May 27, 1988, before further flight. 1. If no cracks are found, repeat the inspection every 1,000 flight cycles (landings) until an internal inspection is conducted in accordance with Part 3 of Service Bulletin F28/57-81, dated May 27, 1988. 2. If, during the inspections accomplished in accordance with Part 3 of Service Bulletin F28/57-81, dated May 27, 1988, it is determined that the bolts are installed properly, a spotface is not found, and cracking does not exist, reseal or reinstall the bolts in accordance with Part 3 of that service bulletin. No further action, other than restoration to normal, is required. 3. If cracks are found during the inspections required by paragraph C., C.1., or C.2., above, or if a spotface is found during the inspections required by paragraph C.1., or C.2., priorto further flight, repair in a manner approved by the Manager, FAA Brussels Aircraft Certification Office, AEU-100. Under conditions noted in the Service Bulletin F28/57-81, dated May 27, 1988, temporary repairs may be made in accordance with Part 4 and the associated table and figures of that service bulletin. D. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by 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 Fokker Aircraft U.S.A., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-6070, becomes effective December 27, 1988.
76-22-02: 76-22-02 BEECH: Amendment 39-2755 as amended by Amendment 39-2909. Applies to the airplane models and serial numbers listed below having inverted "Y" type shoulder harnesses installed, except those airplanes that have previously complied with AD 76-22-02 (Amendment 39-2755): MODELS SERIAL NUMBERS F33A CE-490 thru CE-633 F33C CJ-49 thru CJ-120 V35B D-9582 thru D-9861 A36 E-515 thru E-824 95-B55 & 95-B55A TC-1653 thru TC-1946 E55 and E55A TE-966 thru TE-1077 58 and 58A TH-425 thru TH-732 65-B80 LD-477 thru LD-505 C90 LJ-626 thru LJ-682 and LJ-684 E90 LW-93 thru LW-171, LW-173, LW-174, and LW-178 B99 U-157 thru U-164 A100 B-199 thru B-226 B100 BE-1 thru BE-7 200 BB-7, BB-8, BB-12, BB-18 thru BB-87, BB-89 thru BB-128, BB-130 thru BB-136 Compliance: Required as indicated, unless already accomplished in accordance with AD 76-22-02 (Amendment 39-2755). To prevent slippage during normal use of the lap belt assembly installed with the inverted "Y" type shoulder harness, within 100 hours' time in service after the effective date of this AD, accomplish the following in accordance with Beechcraft Service Instructions No. 0850-313, Rev. I, or later approved revisions: NOTE: Belt roller adjuster part numbers are stamped on the tang of the "male" half of lap belt assembly. A) On all aircraft visually inspect the "male" half of the lap belt assembly on the pilot and co-pilot seats to determine if a P/N 500535 roller adjuster is installed and if so replace it with a P/N 500535-401 roller adjuster. B) On Model 200 (Serial Numbers BB-7, BB-8 and BB-34) airplanes visually inspect the "male" half of the lap belt assembly on the toilet seat to determine if a P/N 500535 roller adjuster is installed and if so replace it with a P/N 500535-401 roller adjuster. C) On Model 200 (Serial Numbers BB-12, BB-20, BB-25, BB-33, BB-35, BB-37, BB-41, BB-46, BB-49, BB-55, BB-56, BB-72, BB-77, BB-82, BB-92, BB-97, BB-107,BB-111, BB-113, BB-116, BB-130, BB-133, BB-135 and BB-136) airplanes visually inspect the "male" half of the Beech P/Ns 101-530314-9 and -13 lap belt assembly on all seats located aft of the cabin door to determine if a P/N 500535 roller adjuster is installed and if so replace it with a P/N 500535-401 roller adjuster. D) The 100 hour compliance time required by this AD may be adjusted up to 110 hours' time in service to allow inspection and modification at regularly scheduled maintenance periods. E) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-2755 became effective November 4, 1976. This amendment 39-2909 becomes effective June 2, 1977.
2015-04-04: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Inc. (Bell) Model 412 and 412EP helicopters with certain static inverters (inverters) installed. This AD requires revising the Rotorcraft Flight Manual (RFM) and installing a placard in full view of the pilot to limit flight to visual flight rules (VFR) only and prohibit night operations. This AD is prompted by failures of certain inverters, most of which resulted in smoke in the cockpit. The actions specified by this AD are intended to restrict flight to VFR only and prohibit night operations to allow safe operation in the event of failure of an affected inverter. This failure would increase pilot workload during instrument flight rules (IFR) and could result in loss of certain pilot information displays and subsequent loss of control of the helicopter.
2000-08-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires a one-time inspection to detect cracking of the rear spar stiffeners in the wing center section; and modification of crack-free stiffeners, or repair of cracked stiffeners. This amendment is prompted by a report of severed rear spar stiffeners of the center wing, which resulted in cracking in the adjacent keel beam structure. The actions specified in this AD are intended to prevent failure of the keel beam structure.
2000-08-09: This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R22 helicopters. This action requires replacing certain serial number sprag clutches with an airworthy sprag clutch as specified in this AD. This amendment is prompted by several reports of clutch assemblies with cracked or fractured sprag ends. The actions specified by this AD are intended to prevent a sprag clutch failure, loss of main rotor RPM during autorotation, and subsequent loss of control of the helicopter.