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76-05-06: 76-05-06 HAMILTON STANDARD: Amendment 39-2537. Applies to propeller Models 54H60-63, -81, -91, -111, -117 and -125. Compliance required within the next 200 hours time in service after the effective date of this AD, unless already accomplished within the last 1800 hours time in service, and thereafter at intervals not to exceed 2000 hours. To prevent wear of pitchlock regulator extension sleeve threads resulting in looseness and possible separation of the extension sleeve from the pitchlock regulator accomplish the following: Check the torque required to turn the extension sleeve, P/N 541850, Rev. C or later revision, in a clockwise (tightening direction), in accordance with Hamilton Standard Service Bulletin HS Code 54H60 No. A 73, Rev. 1 dated January 2, 1976 or later revision or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (a) If a running torque is not obtained up to a maximum applied static torque of 130 ft. lb., return pitchlock regulator to service. (b) If the running torque required to turn the extension sleeve is less than 100 ft. lbs., remove extension sleeve and inspect threads for wear. Remove from service extension sleeves with worn threads. The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Hamilton Standard, Division of United Technologies Corporation, Windsor Locks, Connecticut 06096. These documents may also be examined at the office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on March 17, 1976.
66-04-01: 66-04-01 GENERAL ELECTRIC: Amdt. 39-548 Part 39 Federal Register February 5, 1966. Applies to Models CJ805-3, -3A, -3B, -23, -23B, and -23C Turbojet Engines. Compliance required as indicated. To prevent the failure of thrust reverser, accomplish the following: (a) Remove from service second stage turbine discs with less than 7,000 cycles on the effective date of this AD before the accumulation of 7,200 cycles. (b) Remove from service second stage turbine discs with 7,000 or more cycles on the effective date of this AD within the next 200 cycles. (c) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA maintenance inspector, may be calculated by dividing each second stage turbine disc's hours time in service by theoperator's fleet average time per flight (involving an engine operating sequency consisting of engine starting, takeoff operation, landing, and engine shutdown) for airplanes equipped with General Electric CJ805 engines. (d) The disc life specified in this AD may be extended to 10,000 cycles provided the discs meet the criteria outlined in paragraphs 1.k and 2 of General Electric Service Bulletin (880) 72-263 or (990) 72-272. This amendment is effective February 7, 1968. (General Electric telegram to CJ805 operators dated December 1, 1965, pertains to this subject.) This directive effective February 3, 1966.
2017-06-06: We are superseding Airworthiness Directive (AD) 2012-22-15, which applied to all Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 airplanes. AD 2012-22-15 required revising the maintenance program to incorporate the limitations, \n\n((Page 8329)) \n\ntasks, thresholds, and intervals specified in certain revised Fokker maintenance review board (MRB) documents. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by new and more restrictive airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2003-08-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires a one-time detailed inspection to detect discrepancies of all electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. This amendment requires another identical inspection in additional fuselage stations, and corrective actions, if necessary. This amendment is prompted by a report from the airplane manufacturer that it failed to include 41 inches of fuselage in the previously required inspection. The actions specified by this AD are intended to prevent electrical arcing and/or heat damaged wires due to improper wire installations during manufacture and/or maintenance of the airplane, and consequent fire and smoke in various areas of the airplane.
2012-11-04: We are superseding an existing airworthiness directive (AD) for certain Bombardier Inc. Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. That AD currently requires repetitive inspections to detect cracking of the lower cap of the wing front and rear spars at wing station (WS) 51.00, and the wing lower skin. Additional actions, if cracking is found, include reworking the lower cap of the front or rear spar, inspecting for cracking, and repairing any cracking. The existing AD also requires reporting inspection results. This new AD requires extending the inspection area of the rear spar lower cap from WS 51.00 to WS 49.50 and modifying the ultrasonic inspection calibration procedure. This AD was prompted by reports of cracking found outside the inspection area. We are issuing this AD to detect and correct cracking of the lower caps of the wing front and rear spars, and lower wing skin, which could result in reduced structural integrity of the airplane.
65-17-01: 65-17-01\tBOEING: Amdt. 39-108 Part 39 Federal Register July 24, 1965. Applies to Model 727 Series Airplanes. \n\n\tCompliance required within the next 600 hours' time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent inadvertent thrust reversing from failure to the locking pin, replace the thrust reverser lockout actuator piston, P/N 65-37853-2, on each engine, with actuator piston, P/N 65- 37853-3, in accordance with Boeing Alert Service Bulletin No. 78-18, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective August 23, 1965.
2012-11-01: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 800 series turbofan engines. This AD requires removal from service of certain critical engine parts based on reduced life limits. This AD was prompted by RR adding a new flight profile and an associated set of life limits. We are issuing this AD to prevent the failure of critical rotating parts, which could result in uncontained failure of the engine and damage to the airplane.
2021-18-13: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF34-8 model turbofan engines with a certain outer shell combustion liner (combustion outer liner shell) installed. This AD was prompted by two in-flight engine shutdowns (IFSDs) that occurred as a result of failures of the combustion outer liner shell. This AD requires a borescope inspection (BSI) or visual inspection of the combustion outer liner shell and, depending on the results of the inspection, possible replacement of the combustion outer liner shell. The FAA is issuing this AD to address the unsafe condition on these products.
2012-11-07: We are adopting a new airworthiness directive (AD) for all Honeywell International, Inc. ALF502L-2C; ALF502R-3; ALF502R-3A; ALF502R-5; LF507-1F; and LF507-1H turbofan engines. This AD was prompted by two reports of engines experiencing uncontained release of low-pressure (LP) turbine blades. This AD requires operational checks of the engine overspeed trip system. We are issuing this AD to prevent LP turbine overspeed leading to uncontained release of the LP turbine blades and damage to the airplane.
98-24-28: This amendment adopts a new airworthiness directive (AD), applicable to certain Allison Engine Company 250-B and 250-C series turboshaft and turboprop engines, that requires replacing existing beryllium copper main fuel control (MFC) bellows assemblies with Inconel 718 stainless steel welded MFC bellows assemblies. This amendment is prompted by reports of leaking MFC bellows assemblies resulting in an uncommanded minimum fuel flow condition, loss of engine fuel flow control and subsequent forced landing. The actions specified by this AD are intended to prevent MFC bellows assembly leakage, which can result in an uncommanded minimum fuel flow condition and subsequent loss of engine fuel flow control.