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86-07-07: 86-07-07 GARLICK HELICOPTERS, HAWKINS AND POWERS AVIATION, INC.. INTERNATIONAL HELICOPTERS, INC., PILOT PERSONNEL INTERNATIONAL, INC., WILCO AVIATION: Amendment 39-5274. Applies to Model UH-1B helicopters modified by Garlick Helicopters, Hawkins and Powers Aviation, Inc., International Helicopters, Inc., Pilot Personnel International, Inc., and Wilco Aviation certified in any category that have a Bell Helicopter Textron, Inc., Part Number (P/N) 204-011-128-1 universal on the main rotor pitch change link. Unless already accomplished, compliance is required within 15 days after the effective date of this AD or the next 10 hours time in service, whichever occurs first. To prevent loss of main rotor control, accomplish the following: (a) Inspect the P/N 204-011-128-1 universal assembly on the pitch change control link of the main rotor for Arko Precision Machinists' supplier P/N "DW-6ZZ." If found, replace before further flight with a serviceable assembly. (b) If the P/N "DW-6ZZ" is missing or cannot be seen, apply MIL-G-81322 grease to each of the two grease fittings on the universal. If the grease does not purge past the seals, replace the P/N 204-011-128-1 universal before further flight with a serviceable assembly. (c) P/N 212-010-412-1 universal is an acceptable alternate replacement for P/N 204-011-128-1 and may be considered interchangeable. (d) Any alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective April 25, 1986.
2004-13-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3-SHERPA series airplanes, that requires a repetitive detailed inspection of the stub wing shear decks for corrosion and abnormal wear on and around the retaining pin in the main landing gear (MLG) forward pintle pin; and corrective action, if necessary. This AD also provides an optional terminating action. These actions are necessary to detect and correct corrosion and abnormal wear to the top and bottom shear decks, which could result in damage to the MLG and consequent reduced controllability of the airplane on landing. This action is intended to address the identified unsafe condition.
87-15-51: 87-15-51 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5701. Applies to Lockheed-California Model L-1011-385 series airplanes, certificated in any category, which have stainless steel bushings installed in the retract lugs of the left and/or the right main landing gear (MLG) shock strut cylinder. Compliance required as indicated, unless previously accomplished. To detect cracks and prevent structural failure of the MLG shock strut cylinder, accomplish the following: A. Within 10 days after the effective date of this AD, unless previously accomplished within the last 400 landings, and thereafter at intervals not to exceed 400 landings, perform an ultrasonic inspection of the inboard retract lugs of both the left and right MLG shock strut cylinder, following the procedure specified in Section 2, Accomplishment Instructions, of Lockheed-California L-1011 Service Bulletin 093-32-A211, Revision 1, dated October 26, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Any MLG shock strut cylinders that are found cracked must be repaired or replaced prior to further flight, in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. 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 inspection requirements of this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept, 65-33, U-33, B-1. This document may be examined at theFAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or 4344 Donald Douglas Drive, Long Beach, California. This amendment, 39-5701, becomes effective August 24, 1987, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T87-15-51 issued July 22, 1987.
2022-02-10: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X, FALCON 900EX, and FALCON 2000EX airplanes. This AD was prompted by a report of an improper heat treatment process applied during the manufacturing of certain titanium screws. This AD requires replacement of certain titanium screws, 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.
94-17-15: This amendment adopts a new airworthiness directive (AD) that is applicable to The Enstrom Helicopter Corporation (Enstrom) Model F-28A, F-28C, F-28C2, F-28F, 280, 280C, 280F, and 280FX series helicopters. This action requires initial and repetitive inspections for delamination of the main rotor feathering elastomeric Lamiflex bearing (Lamiflex bearing). This amendment is prompted by several reported failures of the Lamiflex bearing. The actions specified in this AD are intended to prevent failure of the Lamiflex bearing, abnormal vibrations in the airframe and flight control system, and subsequent loss of control of the helicopter.
2004-12-18: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires installing three new vertical cargo nets in cargo-configured cabins. This action is necessary to prevent significant movement of cargo during operation, which could result in loss of control of the airplane or injury to the flightcrew. This action is intended to address the identified unsafe condition.
2004-06-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2004-06-51, which was sent previously to all known U.S. owners and operators of Boeing Defense and Space Group (Boeing) Model 234 helicopters by individual letters. This AD requires, before further flight, inspecting the upper shaft extension for a crack and modifying the aft vertical shaft assembly (assembly). Thereafter, this AD requires, before the first flight of each day, inspecting the upper shaft extension for any crack. If any crack is found during any of the inspections, replacing the assembly with an airworthy assembly is required before further flight. This amendment is prompted by the discovery of a crack in the upper shaft extension of an assembly. The actions specified by this AD are intended to detect a crack in the upper shaft extension, which could result in catastrophic failure of the assembly and subsequent loss of control of the helicopter.
2016-20-11: We are superseding Airworthiness Directive (AD) 2014-12-06 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. AD 2014-12-06 required repetitive ultrasonic or detailed inspections of the external area of the aft cargo door sill beam for cracking, and repair if necessary, and provided an optional one-time high frequency eddy current (HFEC) inspection that would terminate the repetitive inspections. This new AD requires the previously optional terminating HFEC inspection, and requires that it be done repetitively. This AD was prompted by findings of multiple fatigue cracks in the aft cargo door that indicated the need for additional, repetitive, HFEC inspections. We are issuing this AD to address the unsafe condition on these products.
2018-09-10: We are adopting a new airworthiness directive (AD) for all CFM International S.A. (CFM) Model CFM56-7B engines. This AD requires initial and repetitive inspections of the concave and convex sides of the fan blade dovetail to detect cracking and replacement of any blades found cracked. This AD was prompted by a recent engine failure due to a fractured fan blade, that resulted in the engine inlet cowl disintegrating and debris penetrating the fuselage, causing a loss of pressurization, and prompting an emergency descent. We are issuing this AD to address the unsafe condition on these products.
84-23-04: 84-23-04 FOKKER B.V.: Amendment 39-4944. Applies to Model F27 airplanes as indicated in the applicability statement of each service bulletin listed below. Compliance is required within the time interval specified in each of the following paragraphs, unless already accomplished: A. To assure proper operation of the portable fire extinguishers, within 90 days after the effective date of this AD, inspect the cartridge holders in accordance with Fokker Service Bulletin F27/26-18 dated September 28, 1981 (reference Walter Kidde Service Bulletin 26-20-240, revised April 28, 1981). B. To assure that proper rubber sleeves have been installed in the fuel vent system, within 90 days after the effective date of this AD, inspect the fuel tank ventilation system in accordance with Fokker Service Bulletin F27/28-55 dated April 15, 1981. Replace unsatisfactory parts in accordance with the service bulletin. C. To eliminate leakage from the fluid dampers in the main and nose landinggear actuating rams, within 180 days after the effective date of this AD, modify the actuating rams in accordance with Fokker Service Bulletin F27/32-143 dated May 22, 1981, or in accordance with Dunlop Service Bulletins 36-262 and 36-263 as an alternate means of compliance. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 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. This amendment becomes effective December 7, 1984.