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83-24-04: 83-24-04 BRITISH AEROSPACE: Amendment 39-4776. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories. To prevent collapse of the nose landing gear, accomplish the following, unless previously accomplished: A. For pre-modification PM5766 up/down lock jacks: (1) Tonks spring discs - P/N AK43-1283. (i) Must be replaced prior to the accumulation of 4,000 landings or within 500 landings after the effective date of this AD, whichever comes later. (ii) Must be functionally tested in accordance with paragraphs 2.3 and 2.4 of Service Bulletin 32-A-PM5191, Issue 5, dated May 15, 1981, prior to the accumulation of 4,000 landings or within 100 landings after the effective date of this AD, whichever comes later. (2) Terry discs - P/N AB43-2579 and Spring Master discs - P/N AB43-2745: (i) Must be replaced prior to the accumulation of 8,000 landings or within 500 landings after the effective date of this AD, whichever comes later. (ii) Must be functionally tested in accordance with paragraphs 2.3 and 2.4 of the service bulletin prior to the accumulation of 6,000 landings or within 500 landings after the effective date of this AD, whichever comes later; and thereafter at intervals not to exceed 500 landings, until replaced in accordance with paragraph A(2)(i), above. B. For post-modification PM5766 up/down lock jacks: (1) Tonks spring discs - P/N AK43-1283. (i) Must be replaced prior to the accumulation of 8,000 landings or within 500 landings after the effective date of this AD, whichever comes later. (ii) Must be functionally tested in accordance with paragraphs 2.3 and 2.4 of the service bulletin prior to the accumulation of 4,000 landings or within 500 landings after the effective date of this AD, whichever comes later; and thereafter at intervals not to exceed 500 landings, until replaced in accordance with paragraph B(1)(i), above. (2) Terry discs - P/N AB43-2579 and Spring Master Discs - P/N AB43- 2745. (i) Must be replaced prior to the accumulation of 10,000 landings or within 500 landings after the effective date of this AD, whichever comes later. (ii) Must be functionally tested in accordance with paragraphs 2.3 and 2.4 of the service bulletin prior to the accumulation of 8,000 landings or within 500 landings after the effective date of this AD, whichever comes later; and thereafter at intervals not to exceed 500 landings, until replaced in accordance with paragraph B(2)(i), above. C. Terminating action for this AD is accomplished by incorporation of helical coil springs into the up/down lock jack, BAe Modification 32-PM5191. D. For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours time in service by the operator's fleet average time from takeoff to landingfor the airplane type. E. 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. F. 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 January 9, 1984.
2003-19-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections for discrepancies of certain areas of the forward and aft sides of the body station 2598 bulkhead, and repair if necessary. This action is necessary to find and fix such discrepancies of the bulkhead structure, which could result in failure of the structure to carry flight loads of the horizontal stabilizer, and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2008-22-53: This document supersedes AD 2008-18-52 and publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2008-22-53 which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires turning ON both Vertical Stabilizer Control System (VSCS) switches and turning OFF the autopilot (AP/SAS) switch; pulling certain AP/SAS circuit breakers; installing a placard near the AP/SAS master switch; installing an airspeed limitation placard on the instrument panel; and making changes to the Rotorcraft Flight Manual (RFM). This AD is prompted by 4 occurrences in which the left VSCS adapter tubes failed on the MD900 helicopters and the vertical stabilizer became uncontrollable, resulting in reduced yaw control of the helicopter. There were no injuries, but in one occurrence, due to the high speed quick yaw, the helicopter lost a window and a door. The actions specified by this AD are intended to prevent loss of yaw control and subsequent loss of control of the helicopter.
94-11-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400A and 400T airplanes, that requires inspection to detect damage of the wire harness in the wheel well of the main landing gear (MLG), and modification, if necessary. This amendment is prompted by reports of damage to wire harnesses due to abrasion. The actions specified by this AD are intended to prevent loss of control of the fuel supply to the engine or loss of control of the retraction/extension system for the MLG and MLG door.
2020-13-01: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. The AD applies to all Daher Aircraft Design, LLC (type certificate previously held by Quest Aircraft Design, LLC), Model KODIAK 100 airplanes. As published, the type certificate (TC) holder in the regulatory heading that identifies the AD is incorrect. This document corrects that error. In all other respects, \nthe original document remains the same; however, for clarity, the FAA is publishing the entire rule in the Federal Register.
94-11-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes. This action requires modification of the external power feeder cable clamping installation. This amendment is prompted by reports of damage to the external power feeder cables located under the forward cargo compartment floor, which was caused by excessive cable length and/or maintenance personnel stepping on the cables. The actions specified in this AD are intended to prevent arcing from occurring under the forward cargo compartment floor as a result of damaged external power feeder cables, a situation that could lead to a fire at this location.
2008-24-09: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: An A330 operator reported a shroud box bottom panel missing during a routine inspection. The same panel detached from an A330 aircraft during take-off, causing damage to the surrounding structure and to the Trimmable Horizontal Stabilizer (THS) tip fairing. The inspection indicated the blind rivets used to attach the panel worked loose causing fatigue damage with crack propagation through the fastener line resulting in panel detachment * * *. * * * Three additional events of panel loss have been experienced on in service aircraft already inspected in accordance with the AD requirements * * *. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-24-10: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as follows: There have been several reported incidents of high altitude, dual engine flameout on JT15D-5 engine powered aircraft operating in certain meteorological conditions. Subsequent to the investigation of incidents, review of the engine design has revealed that the Fuel Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to excessive moisture and freezing. We are issuing this AD to prevent engine flameouts of one or both engines, caused by excessive moisture and freezing in the P3 servo during certain flight conditions.
83-22-03: 83-22-03 CANADAIR: Amendment 39-4756. Applies to Canadair Model CL-600-1A11 airplanes, serial numbers 1005 through 1008 and 1010 through 1056, certificated in all categories. Compliance required as indicated, unless already accomplished. A. To ensure the structural integrity of the bulkhead at F.S. 409.00, incorporate modifications in accordance with Canadair Service Bulletin 600-0124, dated March 23, 1982, within the next 25 hours time in service after the effective date of this AD or upon accumulation of 1175 total flying hours, whichever is later. B. 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. C. 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 November 7, 1983.
82-08-05 R1: 82-08-05 R1 WING: Amendment 39-4370 as amended by Amendment 39-4428. Applies to Model D-1 (S/Ns 003 and 005 through 009) airplanes certificated in any category. COMPLIANCE: Required prior to further flight, unless already accomplished. To prevent a potential cabin fire hazard, accomplish the following: (a) Deactivate the cabin heater by removing wire H3A18 from the main electrical bus. Stow and insulate the removed wire end. (b) Install a placard in full view of the pilot adjacent to the cabin heater control in letters 1/8-inch high which reads as follows: "DO NOT USE CABIN HEATER" (c) Upon incorporation of the modifications contained in Wing Aircraft Company Service Bulletin No. SB 1033, dated April 9, 1982, the requirements of paragraphs (a) and (b) of this AD are not necessary and the cabin heater may be returned to service by reconnecting wire H3A18 to the main electrical bus and removing the placard "DO NOT USE CABIN HEATER." (d) A special flight permit may be issued in accordance with FAR 21.197 to operate aircraft with cabin heater OFF to a base for the accomplishment of this AD. (e) Any equivalent method of compliance with this AD, if used, must be approved by the Chief, Federal Aviation Administration, Western Aircraft Certification Field Office, Northwest Mountain Region, P.O. Box 92007, World Way Postal Center, Los Angeles, California 90009; telephone (213) 536-6352. Amendment 39-4370 became effective on May 3, 1982, to all persons except those to whom it had already been made effective by a priority letter from the FAA dated April 6, 1982, and is identified as AD 82-08- 05. This Amendment 39-4428 becomes effective August 4, 1982.