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92-10-11: 92-10-11 BOEING: Amendment 39-8245. Docket No. 91-NM-192-AD.\n\n\tApplicability: Model 757 series airplanes, listed in Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991, certificated in any category.\n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless previously accomplished.\n\n\tTo prevent damage to the floor beam at body station (BS) 1640, hydraulic system components, and flight control functions in the event of a sudden decrease in air pressure aft of the bulkhead lining, accomplish the following:\n\n\t(a)\tModify the soft bulkhead support structure at BS 1640 and replace the bulkhead lining in accordance with Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991.\n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(c)\tSpecial 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.\n\n\t(d)\tThe modification shall be done in accordance with Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on June 1, 1992.
2020-05-20: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and AS332L2 helicopters. This AD requires removing the drain plugs from the fuel tank compartments located under the bottom structure. This AD was prompted by the discovery that a modification to the fuel tank could lead to fuel accumulating in an area containing electrical equipment and subsequent ignition of fuel vapors. The actions of this AD are intended to address an unsafe condition on these products.
78-02-01: 78-02-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3124 as amended by amendment 39-3460. Applies to model PA-31T airplanes, serial numbers 31T-7400002 through 31T-7820077, and Model PA-31T1 airplanes, serial numbers 31T-7804001 through 31T-780-4006, certificated in all categories. Compliance required within the next fifty hours in service after the effective date of this AD, unless already accomplished. (a) To preclude possible failure of the main landing gear actuating cylinder rod end bearing assemblies, accomplish the inspection and replacement where required, described in the "Instruction" portion of Piper Aircraft Corporation Service Bulletin No. 57A, dated August 30, 1978. (b) Equivalent alterations or methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-3124 was effective January 18, 1978. This amendment 39-3460 is effective May 9, 1979.
84-12-51: 84-12-51 WESTLAND HELICOPTERS LIMITED: Amendment 39-4904. Applies to Westland Model 30 Series 100 helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent possible hazards in flight associated with cracking of the main rotor blades, accomplish the following: (a) Before the next flight and thereafter before the first flight of each day, visually inspect the main rotor blades in accordance with Westland Service Bulletin W30-05-23 dated July 16, 1984, or FAA-approved equivalent. (b) Within 15 hours after the effective date of this AD, unless already accomplished, conduct an eddy current inspection of the main rotor blade and thereafter at intervals not to exceed every 15 hours time in service since the last inspection in accordance with Westland Service Bulletin W30-05-23, or FAA-approved equivalent. (c) Remove from service any main rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with the AD may be used when approved by the Manager, Brussels Aircraft Certification Office, Federal Aviation Administration, c/o American Embassy, APO New York 09667. This amendment becomes effective September 11, 1984, as to all persons except those person to whom it was made immediately effective by telegraphic AD T84-12-51, issued June 5, 1984, which contained this amendment.
64-25-01: 64-25-01\tBOEING: Amdt. 39-1 Part 507 Federal Register November 6, 1964. Applies to Models 707 and 720 Series Aircraft Equipped With Pratt & Whitney JT3D Engines. \n\n\tCompliance required as indicated.\n \n\tThere have been a number of engine fires in service due to fuel accumulation in the aft thrust reverser sleeve and the side cowl panel as a result of false starts.\n \n\tTo correct this condition, unless already accomplished, provide additional fluid drainage in the left-hand side cowl panel and aft thrust reverser sleeve on each engine in accordance with either (a) or (b) or an equivalent approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tWithin 3,100 hours' time in service after the effective date of this AD accomplish the following: \n\n\t\t(1)\tDrill or cut four 1/2 inch-diameter holes through lower skin of the aft thrust reverser sleeve at Station 222.30 as shown on page 5 of Boeing Service Bulletin No. 1908. \n\n\t\t(2)\tDrill or cut two 1/4 inch-diameterholes through lower skin of aft thrust reverser sleeve at Station 222.30, one hole outboard of each channel section E-E and F-F at the locations shown on page 6 of Boeing Service Bulletin No. 1908. \n\n\t\t(3)\tDrill or cut two 1/2-inch diameter holes through lower skin of the aft thrust reverser sleeve at Station 241.75 as shown on page 4 of Boeing Service Bulletin No. 1908. \n\n\t\t(4)\tDrill or cut two 1/4 inch-diameter holes, one hole outboard of each rib, through lower skin on the aft thrust reverser sleeve, 1.3 inches outboard and 0.1 inch forward of each hole drilled in accordance with (a)(3). \n\n\t\t(5)\tDrill or cut two 1/2 inch-diameter holes through lower skin on left-hand side cowl nacelle Station 197.51 and bend trailing edge of each hole as shown on page 8 of Boeing Service Bulletin No. 1908. \n\n\t(b)\tWithin 3,100 hours' time in service after the effective date of this AD, drill or cut additional 1/2 inch-diameter drain holes in the aft thrust reverser sleeve and in the left sidecowl panel in accordance with Boeing Service Bulletin No. 1908. \n\n\tNOTE. - American Airlines, Inc. Fleet Campaign Directive No. 810B is an equivalent which has been approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(Boeing Service Bulletin No. 1908 dated January 16, 1964, covers this same subject.) \n\n\tThis directive effective December 7, 1964.
2020-05-16: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115 airplanes; Model A320-214, -216, - 232, -251N, and -271N airplanes; and Model A321-211, -231, -251N, - 251NX, -253N, -271N, -271NX, and -272N airplanes. This AD was prompted by reports of incomplete installations of the over wing panel lug attachments in the production assembly line. This AD requires a one- time detailed inspection of certain attaching points on the left-hand and right-hand wings for the correct installation of certain hardware, and, depending on findings, accomplishment of applicable corrective actions, 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.
79-05-11: 79-05-11 PIPER AIRCRAFT CORPORATION: Amendment 39-3433. Applies to Model PA-44-180, serial numbers 44-7995001 through 44-7995144, 44-7995146 through 44-7995180, 44-7995182 through 44-7995186, 44-7995190, 44-7995192, 44-7995193, 44-7995195, and 44-7995197 airplanes certificated in all categories. \n\n\tCompliance is required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent loss of engine power control due to a damaged or binding throttle control cable or restricted carburetor throttle arm movement, on both engines, accomplish the following: \n\n\t(a)\tRemove upper and lower cowling. \n\n\t(b)\tDisconnect the throttle cable at the carburetor end and inspect the throttle control cable movement for full and free travel. If the throttle control cable movement exhibits stiffness or binding, replace the cable assembly with a serviceable unit. \n\n\t(c)\tInspect the carburetor throttle arm movement for full and free travel. If the throttle arm movement exhibits stiffness or restricted movement, take the necessary corrective action. \n\n\tNOTE: Marvel-Schebler/Tillotson Service Bulletin A2-78, dated October 1978, pertains to this condition. \n\n\t(d)\tRemove both left and right engine throttle control supports, and modify the part as shown in Figure No. 1 (dimensions are in inches). Re-mark the modified part as Part No. 86574-04. \n\n\t(e)\tReinstall the modified support as shown in Figure No. 1 (dimensions are in inches). Apply torque in accordance with the Piper Maintenance Manual. \n\n\t(f)\tRe-rig the throttles in accordance with Figures No. 2 and No. 3 (dimensions are in inches). \n\n\t(g)\tReinstall upper and lower cowling. \n\n\t(h)\tAdjust the throttle quadrant gear warning micro switch in accordance with Piper's Maintenance Manual. \n\n\t(i)\tMake an appropriate maintenance record entry. \n\n\t(j)\tAn equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tNOTE: Piper Service Bulletin 639, dated January 10, 1979, pertains to this subject. \n\n\tThis amendment becomes effective March 15, 1979.
97-24-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11, -2A12, and -2B16 series airplanes. This action requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking in the pressure bulkhead at frame station (FS) 409.00, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
61-11-01: 61-11-01 BRANTLY: Amdt. 288 Part 507 Federal Register May 23, 1961. Applies to All B-2 Helicopters. \n\n\tCompliance required within the next 10 hours' time in service after effective date of this directive. \tA failure in the skid landing gear drag brace rod end bearing (Kahr Bearing Co. P/N HE-3SFN) occurred during ground handling resulting in collapse of the landing gear. This failure occurred through the area of the lubrication fitting. \n\n\tTo preclude the possibility of additional failures, check the shoulder dimension of the two (2) Kahr P/N HE-3SFN rod end bearings at the forward ends of the Brantly P/N B2-259-1 and B2-259-2 landing gear drag struts. If the dimension shown in the sketch is less than 0.5 inch, the part must be replaced before further flight with a new bearing, Brantly P/N B2-259-11, or an FAA approved equivalent. \n\n\n\n\t(Brantly Service Bulletin No. 11 covers this subject. NOTE: Service Bulletin No. 11 refers to P/N B2-259-11 as "new type.") \n\n\tThis directive effective May 31, 1961.
2020-05-28: The FAA is superseding Airworthiness Directive (AD) 2019-11-08 for all International Aero Engines, LLC (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1129G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G- JM, PW1124G1-JM, and PW1122G-JM model turbofan engines. AD 2019-11-08 required the removal of the main gearbox (MGB) assembly and electronic engine control (EEC) software and the installation of a part and software version eligible for installation for engines that operate on extended operations (ETOPS) flights. This AD retains the requirements of AD 2019-11-08 and requires replacement of the MGB assembly and EEC software on engines that do not operate on ETOPS flights. This AD was prompted by multiple reports of in-flight engine shutdowns as the result of high-cycle fatigue causing fracture of certain parts of the MGB assembly. The FAA is issuing this AD to address the unsafe condition on these products.