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84-21-01 R1: 84-21-01 R1 BRITISH AEROSPACE: Amendment 39-4932 as amended by Amendment 39- 4993. Applies to all Model DH/HS/BH 125 series airplanes certificated in all categories, with the serial numbers specified in the service bulletins listed below. Compliance is required as indicated. To prevent electrical failures in the 'ZL' panel, accomplish the following within the next 90 days after the effective date of this AD unless previously accomplished: A. Replace the two existing 80 amp fuses on the 'ZL' panel with 100 amp fuses, in accordance with the Accomplishment Instructions of British Aerospace 125 Aircraft Service Bulletin 24-239-(2885), Revision 1, dated February 27, 1984. B. Install covers on the 'ZL' panel as follows: 1. For aircraft that have accomplished STC SA3870WE or STC SA3925WE, in accordance with the Accomplishment Instructions of AiResearch Aviation Company Service Bulletin No. 6-7, dated October 25, 1983. 2. For any other aircraft fitted with Garrett TFE 731-3 engines, in accordance with the Accomplishment Instructions of British Aerospace 125 Aircraft Service Bulletin 24-220-(2749), Revision 3, dated March 3, 1983. C. 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. D. 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. Amendment 39-4932 became effective November 14, 1984. This Amendment 39-4993 becomes effective February 11, 1985.
59-18-02: 59-18-02 BEECH: Applies to All Model C45G, TC45G, C45H, TC45H and D18S Airplanes. Compliance required as indicated. Corrosion of fuel supply lines in the wing root area can result from the flexible cockpit hot air duct touching the aluminum fuel line. Fuel line leaks due to this corrosion may cause fuel system malfunctioning or hazardous accumulations of fuel and fumes in the wings or cabin. To prevent these conditions, accomplish the following: (a) Compliance required not later than October 15, 1959. (1) Inspect the 5/8-inch O.D. fuel line (Beech P/N's 407-189686 LH and 407-189731 RH) beneath each battery installation on both sides of the airplane for indications of corrosion. Replace the lines if damaged. (2) Install 5/8-inch I.D. x 1/16-inch tubing (Tygon tubing manufactured by U.S. Stoneware, Akron 9, Ohio) split lengthwise over the fuel lines (407-189686 LH and 407- 189731 RH) in the area of the cockpit hot air duct. Secure the split tubing by taping. (3) Obtain adequate clearance between the fuel line and the cabin hot air duct by installing a suitable double clamp on the line and duct. (b) Compliance required at each periodic airplane inspection after accomplishment of (a). (1) Remove split Tygon tubing from fuel supply lines (407-189686 LH and 407-189731 RH) and inspect lines for corrosion. Replace fuel lines if necessary. (2) Reinstall split Tygon tubing and double clamp between cabin hot air duct and fuel line as outlined in (a)(2) and (a)(3). (Beech Service Bulletin No. 68, Model D18S issued February 1959, covers this same subject.)
67-25-01 R1: 67-25-01 R1 BRITISH AIRCRAFT: Amendment 39-476 as amended by 39-4217. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated To prevent fatigue failures of the Belleville washers installed in the main undercarriage down lock jacks P/N AB43A15 and AB43A16 (200 Series), P/N AK43A15 and AK43A16 (400 Series), accomplish the following: (a) For airplanes with Belleville washers P/N 1383 No. 12 (Terry) installed in the main undercarriage down lock jacks with less than 4,760 landings on the effective date of this AD, inspect the main undercarriage down lock links P/N AB43A17 (200 Series) or P/N AK43A17 (400 Series) before the accumulation of 5,000 landings, and thereafter at intervals not to exceed 240 landings from the last inspection in accordance with British Aircraft Corporation, BAC 1-11 Alert Service Bulletin 32-A-PM 2437, Issue 3, dated February 1, 1967, or later ARB- approved issue. Replace cracked or broken washers, and remove washersfrom service before the accumulation of 8,000 landings. (b) For airplanes with Belleville washers P/N 1383 No. 12 (Terry) installed in the main undercarriage down lock jacks with 4,760 or more landings but less than 7,760 landings on the effective date of this AD, inspect the main undercarriage down lock links P/N AB43A17 (200 Series) or P/N AK43A17 (400 Series) within the next 240 landings after the effective date of this AD, and thereafter at intervals not to exceed 240 landings from the last inspection, in accordance with BAC 1-11 Alert Service Bulletin 32-A-PM 2437, Issue 3, dated February 1, 1967, or later ARB-approved issue. Replace cracked or broken washers and remove washers from service before the accumulation of 8,000 landings. (c) For airplanes with Belleville washers P/N 1383 No. 12 (Terry) installed in the main undercarriage down lock jacks with 7,760 or more landings on the effective date of this AD, remove washers from service within the next 240 landings.(d) For airplanes with Belleville washers P/N AB44-1791 installed in BAC Modification PM 2437 main undercarriage down lock jacks, with less than 15,800 landings on the effective date of this AD, remove washers from service before the accumulation of 16,000 landings. (e) For airplanes with Belleville washers P/N AB44-1791 installed in BAC Modification PM 2437 main undercarriage down lock jacks with 15,800 or more landings on the effective date of this AD, remove washers from service within the next 200 landings. (f) For airplanes with Tonks spring discs, P/N AK43-1283, installed in BAC Modification PM 4676 main landing gear down lock jacks, unless already accomplished, before accumulating 16,000 landings or within the next 3,000 landings after the effective date of this AD, whichever occurs later, remove the spring discs from service in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of BAC 1-11 Alert Service Bulletin 32-A- PM5700, Issue No. 1, dated May 10, 1979, oran FAA-approved equivalent. (g) 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 landing for the airplane type. (h) Upon request of an operator, an FAA maintenance inspector, subject to the prior approval of the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator or at intervals greater than that specified in this AD if the request contains substantiating data to justify the increase for that operator. NOTE - AD 66-24-03 pertains to Belleville washers installed in the nose undercarriage up/down lock jacks. 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 British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, D.C. 20591. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. Amendment 39-476 became effective September 9, 1967. This amendment 39-4217 becomes effective October 14, 1981.
72-16-04: 72-16-04 SIAI-MARCHETTI: Amendment 39-1488. Applies to Siai Marchetti Models S.205-18/R, S.205-20/R, and S.205-22/R airplanes, Serial Numbers 106 through 239. Compliance required as indicated unless already accomplished. To detect and prevent cracks in the nose gear drag link assembly, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished within the last 15 hours' time in service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection, visually inspect the tubes and welded areas of the nose gear articulated drag brace rear link, P/N 205-9-142-03, using a magnifying glass of 5 power or more. If indications of cracks are found, strip the paint from the area and reinspect using a magnifying glass of 5 power or more. (b) If any cracks or breaks are found during the inspections required by paragraph (a), before further flight, remove the nose gear dragbrace assembly, P/N 205-9-142-01, and accomplish one of the following: (1) Install reinforced nose gear dray brace assembly, P/N 205-9-142-05 or P/N 205-9-142-09, in accordance with SIAI-Marchetti Service Bulletin No. 205B12A, dated January 21, 1972, or an FAA-approved equivalent; or (2) Comply with subparagraph (i) or (ii), as applicable, in accordance with SIAI-Marchetti Service Instruction No. 205SI-16, dated March 29, 1972, or an FAA-approved equivalent. (i) For Model S.205-18/R and -20/R airplanes, install press formed nose gear drag brace assembly, P/N 205-9-142-103. (ii) For Model S.205-22/R airplanes, install press formed nose gear drag brace assembly, P/N 205-9-142-103, and replace the bellcrank, P/N 205-6-062-03, with bellcrank, P/N 205-6-062-107. (c) The repetitive inspections required by paragraph (a) may be discontinued when a reinforced or press formed nose gear drag brace assembly is installed in accordance with paragraph (b)(1) or (b)(2)(i) for Models S.205-18/R and -20/R airplanes, or when a reinforced nose gear drag brace assembly is installed in accordance with paragraph (b)(1) or a press formed nose gear drag brace assembly and a bellcrank, P/N 205-6-062-107, are installed in accordance with paragraph (b)(2)(ii) for the Model S.205-22/R airplanes. This amendment becomes effective July 25, 1972.
2015-12-09 R1: We are revising airworthiness directive (AD) 2015-12-09 for Airbus Helicopters Model EC135P1, EC135T1, EC135P2, EC135T2, EC135P2+, EC135T2+, and MBB-BK 117 C-2 helicopters. AD 2015-12-09 required inspecting certain washers for movement and making the appropriate repairs if the washers move. As published, AD 2015-12-09 referenced an incorrect date for the service information in the Credit for Previous Actions section. This AD corrects the error while retaining the requirements of AD 2015-12-09. These actions are intended to prevent loss of concerned control axis and subsequent loss of control of the helicopter.
2002-23-04: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting the 9-degree frame (frame) for the correct edge distance of the two attachment holes for the reinforced latch support and for a crack and repairing the frame if necessary. This amendment is prompted by the detection of a fatigue crack on the left-hand (LH) side of the frame during maintenance. The actions specified by this AD are intended to prevent failure of the frame due to a crack at the latch support, loss of a passenger door, damage to the rotor system, and subsequent loss of control of the helicopter.
70-11-03: 70-11-03 PRATT & WHITNEY: Amdt. 39-993. Pratt & Whitney Aircraft JT8D series turbofan engines. Applies to Pratt & Whitney JT8D series turbofan engines, incorporating sixth stage compressor discs P/N 586906 (wide rim) which have encountered previous sixth stage blade failures and were not subsequently reworked in accordance with P&WA Service telegram SE:RWJ: 9-6-24-1 dated 24 June 1969. Compliance required as indicated. To preclude sixth stage compressor rotor disc failures as the result of disc rim front face galling caused by blade retention tangs, accomplish the following: a. For engines incorporating any of the previously listed sixth stage compressor rotor disc: 1. With 1200 hours or more in service since a 6th stage compressor blade failure, within the next 600 hours in service after the effective date of this AD replace the suspect sixth stage compressor disc with a new, used or a disc reworked in a manner approved by Chief, Engineering and ManufacturingBranch, Eastern Region, New York. 2. With 1200 hours or less in service since a 6th stage compressor blade failure, prior to accumulation of 1800 hours time in service since 6th stage blade failure replace the suspect sixth stage compressor disc with a new, used or disc reworked in a manner approved by Chief, Engineering Branch, Eastern Region, New York. b. For the purposes of this AD a blade failure is defined as one in which any portion of the blade root is separated from the blade. c. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, may adjust the compliance time. This amendment is effective June 12, 1970.
2002-23-14: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT8D-200 series turbofan engines. This amendment requires initial and repetitive visual inspections, fluorescent magnetic particle inspections (FMPI), and fretting wear inspections of high pressure compressor (HPC) front hubs that have operated with PWA-110 coating in the interface between the hub and the stage 8-9 spacer. This amendment is prompted by the discovery of cracked tierod holes found during routine engine overhauls. The actions specified by this AD are intended to prevent a rupture of the HPC front hub that could result in an uncontained engine failure and damage to the airplane.
2016-01-13: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 and 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). This AD was prompted by a report of skin disbonding and damage found on the composite side panel of the rudder, located between the rudder core and skin of a previously repaired area. This AD requires an inspection for disbonding or damage of certain rudders, and related investigative actions and corrective actions if necessary. We are issuing this AD to detect and correct disbonding and damage of the rudder, which could result in reduced structural integrity of the rudder and consequent reduced controllability of the airplane.
87-06-51: 87-06-51 BRITISH AEROSPACE: Amendment 39-5670. Applies to Model BAe 146 series airplanes, as listed in BAe Service Bulletin 32-A74, dated March 17, 1987, certificated in any category. To prevent loss of braking capability due to failure of the stator drives, accomplish the following, unless previously accomplished: A. Within 24 hours after the effective date of this AD, inspect the pressure stator and brake wear pin in accordance with BAe Service Bulletin 32-A74 dated March 17, 1987. Replace heat packs worn beyond the limits set forth in the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, 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 the 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 British Aerospace, Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5670, becomes effective July 25, 1987. This AD was effective earlier to all recipients of telegraphic AD T87-06-51 dated March 20, 1987.