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93-14-18: 93-14-18 GENERAL ELECTRIC COMPANY: Amendment 39-8643. Docket 92-ANE-10. Applicability: General Electric Company (GE) CF6-6/-45/-50/-80A/-80C2 series turbofan engines that contain high pressure turbine (HPT) thermal shields as listed in the applicable service bulletins that are referenced in this AD, installed on but not limited to Airbus A300 and A310 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained engine failure, accomplish the following: (a) Perform either an impression and optical comparitor inspection or an ultrasonic inspection of the HPT thermal shield at the next HPT shop visit, or by December 12, 1995, whichever occurs first, as follows: (1) For GE CF6-6 engines, in accordance with GE CF6-6 Service Bulletin (SB) No. 72-983, Revision 1, dated October 10, 1991. (2) For CF6-45/-50 engines, in accordance with GECF6-50 SB No. 72-1021, Revision 1, dated October 10, 1991. (3) For CF6-80A engines, in accordance with GE CF6-80A SB No. 72-596, Revision 1, dated October 10, 1991. (4) For CF6-80C2 engines, in accordance with GE CF6-80C2 SB No. 72-565, Revision 1, dated October 10, 1991. (b) Remove from service prior to further flight, and replace with a serviceable part, HPT thermal shields that do not meet the service criteria contained in the applicable service bulletins as specified in paragraph (a) of this AD. (c) For the purpose of this AD, a shop visit is defined as the removal of the HPT module from the engine for any reason. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections shall be done in accordance with the following service bulletins: Document No. Pages Revision Date GE CF6-6 SB 1-3 1 October 10, 1991 No. 72-983 4-30 Original September 19, 1991 Total Pages: 30 GE CF6-50 SB 1-3 1 October 10, 1991 No. 72-1021 4-30 Original September 19, 1991 Total Pages: 30 GE CF6-80A SB 1-3 1 October 10, 1991 No. 72-596 4-31 Original September 19, 1991 Total Pages: 31 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFRpart 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, OH 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2000-20-04: This document supersedes an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-90-30 series airplanes. That AD currently requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. The actions specified in that AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight. This amendment is prompted by the Federal Aviation Administration's determination that the existing AD must be revised to ensure that the requirements apply to the appropriate airplane groups. \n\n\tThe incorporation by reference of McDonnell Douglas Service Bulletin MD90-24-062, dated February 3, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of November 13, 2000.The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD90-24A060, Revision 01, dated September 2, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of September 19, 2000 (65 FR 49728, August 15, 2000).
2015-26-04: We are superseding airworthiness directive (AD) 2002-13-11 for Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2002-13-11 required installing front and side covers on the cabin floor to protect the yaw control at both the pilot and co-pilot stations. Since we issued AD 2002-13-11, we have determined that the required actions should apply only to the cabin's right-hand pilot station. This AD retains the requirements of AD 2002-13-11 but for only the pilot station. These actions are intended to prevent an object from sliding between the canopy and the cabin floor, loss of yaw control, and subsequent loss of helicopter control.
2000-20-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires, for certain airplanes, inspection(s) to detect cracks of the doorjamb corners and follow-on actions. For certain other airplanes, this AD requires installation of a preventative modification; an inspection to detect cracks at the corners of the doorjambs of the passenger and service doors; and follow-on actions. This amendment is prompted by reports indicating that fatigue cracks were found in the fuselage skin and doublers at the corners of the doorjambs of the passenger and service doors. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
2000-20-02: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 series turbofan engines. This action requires inspection of the low pressure turbine nozzle lock assemblies, and replacement of the borescope plug with a new design plug. This amendment is prompted by three uncontained engine failures. The actions specified in this AD are intended to detect loose or missing LPT nozzle lock assembly studs that could lead to failure of the locks and subsequent uncontained failure of the engine.
81-09-08: 81-09-08 HILLER AVIATION: Amendment 39-4137. Applies to Models UH-12D, UH-12E, UH-12E4 Series Helicopters, including military Models H-23F, OH-23G, and all models converted by STC SH178WE and STC SH177WE, equipped with main rotor blades Part No. 53200-03, certified in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible main rotor blade failure due to the delamination of the skin at the blade tip, accomplish the following: (a) Prior to further flight, after the effective date of this AD or receipt of the priority mail AD 81-09-08, issued April 27, 1981, whichever occurs first: (1) Remove blade tip cap and visually inspect for skin bond separation in the tip cap area, in accordance with Para. II.D of Hiller Aviation Service Bulletin No. 51-8 dated March 25, 1981. (2) If the skin bond separation is detected, replace blade with like serviceable item or repair in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. Submit data defining exact areas of delamination when requesting repair approval. (3) If no skin bond separation is detected, replace the tip cap and seal, in accordance with Para. II.F of Hiller Aviation Service Bulletin No. 51-8, dated March 25, 1981. (b) Upon the effective date or upon receipt of the priority mail AD 81-09-08, issued April 27, 1981, whichever occurs first, whenever the rotor blade tip cap is removed for whatever reason, comply with the inspection requirements and tip cap reinstallation requirements of Para. (a) of this AD prior to return to service. Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections or modifications required by this AD. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and ManufacturingBranch, FAA Western Region. 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 West Scranton Avenue, Porterville, California 93275. These documents may also be examined at FAA Western Region Office, Rules Docket, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, Rules Docket, Room 916, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA Headquarters in Washington, D.C. and the FAA Western Region Office. This amendment becomes effective June 25, 1981 to all persons, except those to whom it was made immediately effective by priority mail AD 81-09-08, issued April 27, 1981.
2015-25-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and all Model A340-200 and A340-300 series airplanes. This AD was prompted by reports that a bracket that attaches the cockpit instrument panel to the airplane structure does not sustain the fatigue loads of the design service goal. This AD requires repetitive inspections of that bracket for cracking and to determine if both lugs are fully broken, an inspection for cracking of an adjacent bracket if necessary, and corrective actions if necessary. This AD also provides an optional modification, which terminates the repetitive inspections. We are issuing this AD to detect and correct cracking on a bracket of the cockpit instrument panel, which, combined with failure of the horizontal beam, could lead to collapse of the cockpit panel, and reduced controllability of the airplane.
2000-20-06: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109K2 and A109E helicopters. This AD requires replacing a certain main transmission aft support fitting (aft support fitting) with an airworthy aft support fitting within specified time intervals and establishes a retirement life for certain aft support fittings. This AD is prompted by three failures of the engine to main gearbox drive shaft due to fatigue cracks on the aft support fittings. This condition, if not corrected, could result in excessive displacement of the main gearbox, failure of an engine to main gearbox drive shaft, loss of power to the main rotor, and a subsequent forced landing.
76-08-02 R2: 76-08-02 R2 CESSNA: Amendment 39-2582 as amended by Amendment 39-2608 is further amended by Amendment 39-4540. Applies to the following models of airplanes if equipped with strobe lights installed in the wing tip fuel tank nose cap, except those airplanes having Symbolic Displays P/Ns 30-0005, 30-0199-1, 30-0199-2, 30-0199-3, 30-0329, 31-0725-1, and 701133-1, Whelen Engineering Company, Inc., P/N A430, and Grimes Manufacturing Company (Grimes) P/Ns 30-0515-5, 30-1172-1, 30-1172-5, 30-0531-1, and 30-0467-5 strobe lights: Models 310, 310A, Military U-3A, 310B, 310C, 310D, 310E, Military U-3B, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R; 320, 320-1, 320A, 320B, 320C, 320D, 320E, 320F; 340; 401, 401A, 401B; 402, 402A, 402B; 411, 411A; 414; and 421, 421A, and 421B airplanes. Compliance: Required as indicated, unless already accomplished. To preclude wing fuel tip tank nose cap explosions, within the next 100hours' time in service after the effective date of this AD, accomplish the following: A) Visually inspect the strobe lights in the tip tank nose cap area to determine whether Grimes P/N 30-0515-1 strobe light or any other strobe lights other than those excepted above are installed. On those airplanes where Grimes P/N 30-0515-1 strobe lights are installed, determine if the strobe lights have been modified by installing Grimes P/Ns 31-1723-5 or 30-1171-1 cover plates. These cover plates may be identified by the presence of two quench tubes protruding into the light assembly from the end plate. B) On those airplanes having unmodified Grimes P/N 30-0515-1 strobe lights, or strobe lights other than those excepted above, deactivate the strobe light system by installing a guard over the switch and/or by pulling and blocking the circuit breaker so that it cannot be inadvertently reset or by any other suitable means. C) Systems having unmodified Grimes P/N 30-0515-1 strobe lights may be reactivated upon the installation of Grimes P/Ns 31-1723-5 or 30-1171-1 cover plates in accordance with Cessna Service Letter ME75-16, dated July 11, 1975, or later approved revisions. D) Do not reactivate strobe light assemblies, other than Grimes P/N 30-0515-1 strobe lights modified per Paragraph C, until data showing the strobe lights are explosion proof have been submitted to and approved by the Chief, Engineering and Manufacturing Branch, or Division of the FAA Region issuing the original light approval. Amendment 39-2582 became effective April 23, 1976, and superseded Amendment 39-2103, AD 75-05-08. Amendment 39-2608 became effective May 20, 1976. This Amendment 39-4540 becomes effective January 31, 1983.
2015-25-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, 757-200CB, and 757-200PF airplanes. This AD was prompted by a report that a forward-most cam latch of the forward center cam latch pair on a main cargo door (MCD) broke during flight. This AD requires doing a general visual inspection for broken or missing cam latches, latch pins, and latch pin cross bolts; torqueing the cross bolts in the latch pins; measuring the extension of \n\n((Page 79462)) \n\nthe latch pins; replacing all alloy steel cross bolts through the latch pins with corrosion resistant steel (CRES) cross bolts; doing a general visual inspection of all cam latches for lip deformation; doing an inspection of cam latch 1 and cam latch 2 for cracks and replacing all cracked or broken parts; checking the rig of the MCD and re-rigging as applicable; and doing related investigative and corrective actions, if necessary. This AD also requires doing certain repetitive inspections until MCD rigging is done. This AD also requires repetitive MCD post- rigging inspections and corrective actions if necessary. We are issuing this AD to detect and correct discrepancies of the cam latches, latch pins, and latch pin cross bolts, which could reduce the structural integrity of the MCD, and result in potential loss of the cargo door and rapid decompression of the airplane.