Results
82-12-07: 82-12-07 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4397. Applies to all Model SA330 series helicopters certificated in all categories (Airworthiness Docket No. 82-ASW-9). Compliance is required within 100 hours' time in service after the effective date of this AD unless already accomplished. To detect damaged or cracked tail rotor transmission attachment bolts and to assure proper matching of the bolts and chamfered washers, accomplish the following: a. Remove the tail rotor transmission assembly and remove the three transmission- to-pylon attachment bolts. b. Inspect the bolts visually for dents under the heads, and for scores or fretting corrosion on the bolt stem or shank. Inspect the bolts for cracks using a magnetic particle or equivalent inspection method. c. Remove from further service bolts having dents under the head or scoring or fretting on the stem or shank, or bolts having a crack. d. Install bolts and washers andtail rotor transmission assembly in accordance with SA330 Puma Service Bulletin No. 01.34, dated October 19, 1981, subparagraph C(4)(b), or FAA approved equivalent. e. Equivalent means of complying with this AD must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Compliance with Puma Service Bulletin No. 01.34, dated October 19, 1981, satisfies this AD. This amendment becomes effective on July 8, 1982.
2020-14-06: The FAA is adopting a new airworthiness directive (AD) for Diamond Aircraft Industries Models DA 40, DA 40 F, and DA 40 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as deterioration of the fuel tank \nconnection hoses that could result in restriction of fuel flow leading to fuel starvation and reduced control of the airplane. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
82-26-03: 82-26-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-4523. Applies to Pratt & Whitney Aircraft models. JT9D-7, -7H, -7A, -7AH Engines prior to and including S/N 695827. JT9D-7F Engine S/Ns 695600 through 695614, S/N 702000, S/N 702001, S/N 702550 through 702557 and all engines prior to and including S/N 689635. JT9D-7J Engines prior to S/N 701697. NOTE: This directive does not apply to JT9D engines obtained by conversion which do not incorporate Service Bulletin 3741. Compliance required prior to February 27, 1983, unless already accomplished. To prevent fuel signal manifold cracking in operation replace manifold assembly P/N 711391 with assembly P/N 783391, bracket P/N 5003038-01, and clamp P/N ST1104-06 in accordance with Pratt & Whitney Aircraft Service Bulletin Number 5202, Revision 2, dated August 16, 1982, or later revision approved by the Manager, Engine Certification Branch, New England Region. All persons affected by this directive who have notalready received the referenced service bulletin from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. This document may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD which includes the material in full is maintained by the FAA at the New England Region office. This amendment becomes effective on January 27, 1983.
85-08-04: 85-08-04 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 5037. Applies to all Models P 68, P 68B, P 68C, P 68C-TC and P 68 OBSERVER (Serial Numbers 001 thru 328) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude the failure of the wing spar, within 100 hours time-in-service after the effective date of this AD or upon accumulating 2,100 hours time-in-service, whichever occurs later, and thereafter at intervals not exceeding 500 hours time-in-service since the last inspection, accomplish the following: (a) Visually inspect the front and rear wing spars for cracks as described in Part A of PARTENAVIA S/B No. 65, Revision 1, dated September 27, 1984. (b) If cracks are found as a result of any inspection required by Paragraph (a) of this AD, prior to further flight, accomplish the modification described in Part B of PARTENAVIA S/B No. 65, Revision 1, dated September 27, 1984. (c) The repetitive inspections required by Paragraph (a) of this AD may be discontinued when the modification in Paragraph (b) of this AD is accomplished. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on May 17, 1985.
94-05-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires incorporation of certain structural modifications. This amendment is prompted by an evaluation by the Model 727 Structures Working Group, comprised of aircraft operators, manufacturers, and the FAA. This Working Group evaluated Boeing service bulletins that must be included as part of the "Aging Airplane Structural Modification Program." The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes. The actions also reflect the FAA's decision that long term continued operational safety should be assured by actual modification of the airframe rather than repetitive inspections.
86-07-01: 86-07-01 ROLLS-ROYCE LIMITED: Amendment 39-5273. Applies to Rolls-Royce RB211-535E4 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent an uncontained outer combustion case burst, inspect cases in accordance with the requirements of Rolls-Royce SB RB.211-72-7775, dated June 28, 1985, or FAA approved equivalent, as follows: (a) Inspect cases with 1,500 cycles in service or less since new on the effective date of this AD, prior to accumulating 1,550 cycles in service since new, and reinspect thereafter at intervals as specified in paragraph (c) below. (b) Inspect cases with greater than 1,500 cycles in service on the effective date of this AD, within the next 50 cycles in service after the effective date of this AD, and reinspect thereafter at intervals as specified in paragraph (c) below. (c) Reinspect cases previously inspected per paragraph (a) or (b) above as follows: (1) At intervals not to exceed 500 cycles in service if no cracks are present. (2) At intervals not to exceed 100 cycles in service if cracks of less than or equal to 0.5 inch in length are present. (3) At intervals not to exceed 50 cycles in service if cracks of greater than 0.5 inch but less than or equal to 1.5 inches in length are present. (d) Remove cases from service prior to further flight, if cracks of greater than 1.5 inches in length are present at inspection. NOTE: The crack length is defined as the length of a single crack or the cumulative length of multiple cracks, whichever is greater. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. Aircraft may be ferried in accordance with the provisions of FAR Parts 21.197 and 21.199 to a base where the AD can be accomplished. Rolls-Royce SB RB.211-72-7775 dated June 28, 1985, is 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 this document from the manufacturer may obtain copies upon request to Rolls-Royce Limited, P.O. Box 31, Derby DE2 8BJ, England. This document also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-25, Room Number 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday except Federal holidays. This amendment becomes effective on May 16, 1986.
2020-14-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent 1000-A, Trent 1000-AE, Trent 1000-C, Trent 1000-CE, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H model turbofan engines. This AD requires removing and replacing one or both affected engines, depending on whether the engine pairing combinations are compliant or non-compliant, as described in the service information. This AD was prompted by occurrences of in- service engine surges on affected RRD Trent model turbofan engines with a high number of intermediate pressure compressor (IPC) module flight hours since new (HSN) or cycles since new (CSN). The FAA is issuing this AD to address the unsafe condition on these products.
84-11-02 R2: 84-11-02 R2 BOEING: Amendment 39-4873 as amended by Amendment 39-4979, is further amended by Amendment 39-5117. Applies to the Model 767-200 series airplanes equipped with CF6 engines as listed in Boeing Service Bulletin 767-73-11 dated March 28, 1984, or later FAA approved revision, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent failure of the engine fuel feed hose and engine flame out or engine nacelle fire, accomplish the following: \n\n\tA.\tWithin the next 200 landings or 30 days, whichever occurs first, after the effective date of this AD, and thereafter at intervals not to exceed 200 landings, inspect and replace, as necessary, the engine fuel feed hose in accordance with Boeing Service Bulletin 767-73-11 dated March 28, 1984, or later FAA approved revision. \n\n\tNOTE: It is anticipated that this AD will be amended when a new reinforced hose or equivalent terminating action is available. \n\n\tB.\tAlternate 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. \n\n\tC.\tFor the purpose of this AD, and when approved by an FAA maintenance inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type. \n\n\tD.\tSpecial 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. \n\n\tE.\tInstallation of fuel feed hose P/N S332TO12-11 in accordance with Service Bulletin 767-73-11, Revision 2, dated May 25, 1984, or later FAA-approved revisions, terminates the repetitive inspection requirement of paragraph A., above. \n\n\tAmendment 39-4873 became effective June 4, 1984. \n\tAmendment 39-4979 became effective January 24, 1985. \n\tThis amendment 39-5117becomes effective September 16, 1985.
2003-18-09: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removal from service of certain part numbers of high pressure (HP) compressor rotor shafts, based on a newly established reduced life limit. This AD is prompted by reports of HP compressor drums with small cracks in blade loading slots found at overhaul inspection. The HP compressor drums are an integral part of the HP compressor rotor shaft. We are issuing this AD to prevent possible uncontained HP compressor drum failure, which could result in damage to the airplane.
93-21-04: 93-21-04 CANADAIR: Amendment 39-8801. Docket No. 93-NM-177-AD. Applicability: Model CL-600-2B19 "Regional Jet" series airplanes; serial numbers 7003 and subsequent; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent temporary loss of all braking action, accomplish the following: (a) Within 3 days after the effective date of this AD, and thereafter at intervals not to exceed 3 days, lubricate with grease the sliding shaft of the input plunger of the brake control valve assembly in accordance with Canadair Regional Jet Alert Service Bulletin S.B.A601R- 32-016, dated October 14, 1993. (b) 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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) 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. (d) The lubrication procedure shall be done in accordance with Canadair Regional Jet Alert Service Bulletin S.B.A601R-32-016, dated October 14, 1993. 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 Bombardier, Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 4, 1994, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-21-04, issued October 18, 1993, which contained the requirements of this amendment.
98-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215-6B11 series airplanes. This action requires repetitive ultrasonic inspections to detect cracking of the lower caps of the wing front spar and rear spar, and corrective action, 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 of the lower caps of the wing front spar and rear spar, which could result in reduced structural integrity of the airplane.
2020-14-01: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. (Bell) Model 214ST helicopters. This AD was prompted by the discovery of bolts with nonconforming external thread root radii. This AD requires removing the affected bolts from service and prohibits installing an affected bolt on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
85-03-05: 85-03-05 BRITISH AEROSPACE: Amendment 39-5001. Applies to Model HS 748 airplanes, certificated in all categories, which are listed in the British Aerospace service bulletins specified below. Compliance is required within the time interval specified in each of the following paragraphs, unless previously accomplished: A. To ensure the baggage door properly locks from the interior, within 180 days after the effective date of this airworthiness directive (AD), modify the baggage door in accordance with British Aerospace HS 748 Service Bulletin 52/94, dated May 14, 1982. B. To ensure the passenger and crew/freight doors properly lock, within 180 days after the effective date of this AD, modify the doors in accordance with British Aerospace HS 748 Service Bulletin 52/95, dated May 14, 1982. C. To prevent false door warnings on baggage, passenger, and crew/freight doors, within 180 days after the effective date of this AD, modify the doors in accordance with British Aerospace HS 748 Service Bulletin 52/96, dated May 14, 1982. D. To ensure passenger, baggage, and crew/freight doors properly lock, within 90 days after the effective date of this AD, install warning decals to the interior trim of the doors in accordance with British Aerospace HS 748 Service Bulletin 52/97, dated May 14, 1982. E. To prevent false door warnings on baggage and crew/freight doors, within 180 days after the effective date of this AD, modify the doors in accordance with British Aerospace HS 748 Service Bulletin 52/99, dated May 14, 1982. F. To ensure the large freight door properly locks, within 90 days after the effective date of this AD, install warning decals to the interior trim of the door in accordance with British Aerospace HS 748 Service Bulletin 52/100, dated May 14, 1982. G. To prevent failure of the crew/freight door locking mechanism swivel lever, within 90 days after the effective date of this AD, inspect the swivel levers in accordance withBritish Aerospace HS 748 Service Bulletin 52/101, Revision 1, dated December 1983. If necessary, replace parts in accordance with the service bulletin instructions. Repetitive inspections must be performed in accordance with the service bulletin instructions. H. To ensure the integrity of door sills and secondary locking mechanisms, inspect the passenger, baggage, and crew/freight doors (including the large freight door), within 180 days after the effective date of this AD, in accordance with British Aerospace HS 748 Service Bulletin 52/106, dated November 1982. If necessary, replace parts in accordance with the service bulletin instructions. Repetitive inspections must be performed in accordance with the service bulletin instructions. I. To provide an audible door unsafe warning on all airplanes, except Model 235, within 180 days after the effective date of this AD, install an audible warning system in accordance with British Aerospace HS 748 service bulletin 52/109,dated October 13, 1982. J. To provide an audible door unsafe warning on Model 235 airplanes, within 180 days after the effective date of this AD, install an audible warning system in accordance with British Aerospace HS 748 Service Bulletin 52/110, dated October 13, 1982. K. 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. L. 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 March 11, 1985.
2003-18-03: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the hydraulic brake hose (hose) for crazing, pinching, distortion, or leaks at the torque link hinge and replacing the hose, if necessary. This amendment also requires inspecting the hose and the emergency flotation gear pipe to ensure adequate clearance, and adjusting the landing gear leg, if necessary. This amendment is prompted by a report of a hose compression due to interference with a clamp that attaches the emergency flotation gear pipe. The actions specified by this AD are intended to prevent failure of the hose, resulting in failure of hydraulic pressure to the brakes on the affected landing gear wheel, and subsequent loss of control of the helicopter during a run-on landing.
2003-18-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires, among other actions, a detailed inspection of the rudder travel limitation unit for proper adjustment, measurement of the desynchronization of rudder servo-controls, installation of rigging placards for rudder servo-controls, and follow-on and corrective actions if necessary. This action is necessary to prevent desynchronization of the rudder servo-controls, which could result in high load factors on the rudder servo-controls, and consequent reduced structural integrity of the attachment fittings for the rudder servo- controls. This action is intended to address the identified unsafe condition.
92-12-10: 92-12-10 TEXTRON LYCOMING: Priority Letter issued on June 5, 1992. Docket No. 92-ANE-27 Applicability: Textron Lycoming Model TIO-540-S1AD engines installed on but not limited to Piper PA-32 Series Aircraft (Turbo Saratoga, Turbo Saratoga SP and Turbo Lance II aircraft). Compliance: Required as indicated, unless accomplished previously. To prevent failure of the fuel injector lines that can result in engine fire, accomplish the following: (a) Within 10 hours after the effective date of this AD inspect the fuel injector fuel lines between the fuel manifold and the fuel injector nozzles as follows: (1) Visually inspect each fuel injector fuel line for missing support clamps or support clamps with a loose, worn or missing support sleeve or cushion. Each fuel injector fuel line must be supported by at least one clamp. (2) Visually inspect each fuel injector fuel line for evidence of physical damage, including dents and chaffing, and for stains caused by fuel leakage. (b) Prior to further flight, replace any fuel injector fuel line that does not have a supporting clamp, has a clamp with a loose, worn, or missing support sleeve or cushion, or if the line itself is damaged or has evidence of fuel leakage. (c) After the effective date of this AD, reinspect the fuel lines in accordance with paragraphs (a)(1) and (2) of this AD and replace as necessary any fuel injector fuel lines in accordance with paragraph (b) of this AD at each annual inspection, at each 100-hour inspection, at each engine overhaul, and after any maintenance has been performed on the engine where the fuel injector fuel lines have been disconnected or disturbed. (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, New York Aircraft Certification Office, ANE-170, 180 South Franklin Street, Valley Stream, New York. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (f) 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. (g) Copies of the applicable service information may be obtained from Textron Lycoming, Williamsport, Pennsylvania. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (h) Priority letter AD 92-12-10, issued June 5, 1992, becomes effective upon receipt.
60-10-10: 60-10-10 VERTOL: Amdt. 140 Part 507 Federal Register May 4, 1960. Applies to all 44 series helicopters. Compliance required as indicated. All forward rotor blades P/N 42R1002-9, -13, -15, -19, -90, -130, -131, -132, -150, and - 152 must be retired at 800 hours of service time. All forward rotor blades P/N 42R1002-137 AND -139 and all aft rotor blades P/N 42R1002-2, -4, -20, and -40 must be retired at 1,350 hours of service time. When the above blades are modified to 42R1002-42, -133, or -135 the provisions of this airworthiness directive no longer apply. This supersedes AD 59-25-02.
2003-18-01: This amendment supersedes an existing airworthiness directive (AD), applicable to various surplus military airplanes manufactured by Consolidated, Consolidated Vultee, and Convair, that currently requires repetitive inspections to find fatigue cracks in the lower rear cap of the wing front spar, front spar web, and lower skin of the wings; repair or replacement of any cracked part with a new part; and follow- on inspections at new intervals. This amendment continues to require those actions and revises and clarifies the applicability of the existing AD. The actions specified in this AD are intended to find and fix fatigue cracking, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2020-13-06: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW150A model turboprop engines. This AD was prompted by a determination by the manufacturer that certain PW150A engine high-pressure (HP) centrifugal impellers may exhibit a material microstructure anomaly that has a potential to adversely affect the low cycle fatigue characteristics of the part. This AD requires replacement of the affected HP centrifugal impellers. The FAA is issuing this AD to address the unsafe condition on these products.
2000-24-21: This amendment adopts a new airworthiness directive (AD), for Siam Hiller Holdings, Inc. (Hiller), formerly Rogerson Hiller Corporation, Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, UH-12E-L, UH-12L, and UH-12L4 helicopters, that requires replacing all undrilled-shank bolts at pivoting joints in the control system linkage with drilled-shank bolts and installing castellated nuts and cotter pins. This amendment is prompted by an accident caused by separation of the control system linkage of a Model UH-12E helicopter. The actions specified by this AD are intended to prevent separation of the control system attachments at pivoting points and subsequent loss of control of the helicopter.
80-22-53: 80-22-53 AVCO LYCOMING: Amendment 39-3995. Applies to Avco Lycoming ALF5O2L and L2 engines except those installed in aircraft operated under an experimental airworthiness certificate. Compliance required as indicated, unless already accomplished. Prior to further flight, rework or replace the following parts and reassemble in accordance with Avco Lycoming Service Bulletin No. ALF502-72-0008, Revision No. 1, dated October 14, 1980, "Replacement of No. 4 and 5 Bearing Oil Inlet Tubes," and Service Bulletin No. ALF502-72- 0010, dated October 14, 1980, "Introduction of Improved Fourth Turbine Nozzle and Fire Shield," or an FAA approved equivalent: a. Remove number 4 and 5 oil inlet tube assembly P/N 2-141-380-07/-08/-11/-12 and replace with P/N 2-141-380-13/-14. b. Remove adapter assembly P/N 2-141-640-01 and replace with P/N 2-141-640-02. c. If not previously incorporated, install: Bracket P/N 2-143-049-01, spacer P/N 2-143-051-01, two bolts P/N STD3061-11, Clamp P/N TA1501H05, Bolt P/N MS9565-06, Nut P/N STD3073-3, and Washer P/N STD3035C2. d. Rework fourth stage turbine nozzle P/N 2-141-150-38 to P/N 2-141-150-42, or P/N 2-141-150-39 to P/N 2-141-150-41 in accordance with Service Bulletin No. ALF502-72-0010. e. Rework upper half of fire shield P/N 2-163-990-04 to 2-163-990-07, or P/N 2-163-990-05 to 2-163- 990-08 in accordance with Service Bulletin No. ALF502-72-0010. f. Install: Washer P/N 2-163-585-01, and Spring P/N 2-163-586-01, and Retainer P/N 2-163-584-01. g. Remove oil feed line P/N 2-173-240-02 and replace with P/N 2-303-377-01. h. Remove jam nut P/N R44118P05W. (The function of the jam nut is accomplished by the parts in "f" and "g" above.) (i) Remove oil inlet support bracket P/N 2-141-335-02 and replace with P/N 2-141-335-03. After replacement of the number 4 and 5 bearing oil inlet tube and associated hardware in accordance with this AD, inspect the number 4 and 5 bearing oil inlet tube every 100 engine operating hours thereafter for chafing in accordance with Avco Lycoming Service Bulletin No. ALF502-72-0008, Revision No. 1, or an FAA approved equivalent. Oil inlet tubes which exhibit chafing in excess of 0.010 inch deep must be replaced with like serviceable parts prior to further flight. Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA New England Region. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Themanufacturer's 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 Avco Lycoming, Stratford, Connecticut 06497. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective December 31, 1980 as to all persons except those persons to whom it was made immediately effective by the telegram of October 23, 1980.
2020-14-02: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747- 200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. As published, the AD number and Amendment number specified in the preamble and regulatory text are incorrect. This document corrects that error. In all other respects, the original document remains the same.
94-26-05: 94-26-05 AIRBUS INDUSTRIE: Amendment 39-9101. Docket 93-NM-227-AD. Applicability: Model A300, A300-600, A310, and A320 series airplanes equipped with Messier-Bugatti, BFGoodrich, Allied Signal (ALS) Aerospace Company (Bendix), or Aircraft Braking Systems (ABS) brakes; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of brake effectiveness during a high energy rejected takeoff (RTO), accomplish the following: (a) Within 180 days after the effective date of this AD, accomplish paragraphs (a)(1) and (a)(2) of this AD. (1) Inspect main landing gear brakes having the brake part numbers listed below for wear. Any brake worn more than the maximum wear limit specified below must be replaced, prior to further flight, with a brake within that limit. AIRBUS INDUSTRIE MODEL A300, A300-600, A310, AND A320 SERIES AIRPLANES EQUIPPED WITH MESSIER-BUGATTI, BFGOODRICH, ALLIED SIGNAL (ALS) AEROSPACE COMPANY (BENDIX), OR AIRCRAFT BRAKING SYSTEMS (ABS) BRAKES Maximum Brake Airplane Model/ Brake Brake Wear Limit Series Manufacturer Part No. (inch/mm) A300-B2-100 Messier-Bugatti 286349-115 0.98"(25.0 mm) A300-B2-100 Messier-Bugatti 286349-116 0.98" (25.0 mm) A300-B2-100 BFGoodrich 2-1449 1.4" (35.6 mm) A300-B2-100 BFGoodrich 2-1449 1.1" (27.9 mm) S.C.* A300-B4-100 Messier-Bugatti A21329-41-7 1.1" (28.0 mm) A300-B4-100 Messier-Bugatti A21329-41-17 1.1" (28.0 mm) A300-B4-100 ALS (Bendix) 2606802-3/-4/-5 0.9" (22.9 mm) A300-B4-100 ALS (Bendix) 2606802-3/-4/-5 1.48" (37.6 mm) S.C.* A300-B4-100 BFGoodrich 2-1449 1.4" (35.6 mm) A300-B4-100 BFGoodrich 2-1449 1.1" (27.9 mm) S.C.* A300-B4-200 & Messier-Bugatti C20060-100 1.1" (28.0 mm) A300-600 A300-B4-200 & ALS (Bendix) 2607932-1 0.9" (22.9 mm) A300-600 A300-B4-200 & ALS (Bendix) 2607932-1 1.48" (37.6 mm) S.C.* A300-600 A300-B4-600R Messier-Bugatti C20210000 1.97" (50.0 mm) A300-B4-600R Messier-Bugatti C20210200 1.97" (50.0 mm) A310-200 Messier-Bugatti C20089000 1.1" (28.0 mm) A310-200 ALS (Bendix) 2606822-1 1.26" (32.0 mm) A310-200 ALS (Bendix) 2606822-1 1.5" (38.2 mm) S.C.* A310-300 Messier-Bugatti C20194000 1.97" (50.0 mm) A310-300 Messier-Bugatti C20194200 1.97" (50.0 mm) A310-300 ABS 5010995 1.97" (50.0 mm) A320 Messier-Bugatti C20225000 1.97" (50.0 mm) A320 Messier-Bugatti C20225200 1.97" (50.0 mm) A320 BFGoodrich 2-1526-2 1.97" (50.0 mm) A320 BFGoodrich 2-1526-3/-4 2.68" (68.0 mm) * S.C. represents "Service Configured" brakes, which are marked according to the instructions provided in the brake manufacturer's Component Maintenance Manual. NOTE 1: Measuring instructions that must be revised to accommodate the new brake wear limits specified above can be found in Chapter 32-42-27 of the Airplane Maintenance Manual (AMM), in Chapter 32-32-( ) or 32-44-( ) of the brake manufacturer's Component Maintenance Manual (CMM), or in certain service bulletins (SB), as listed below: Brake Document/ Date/Revision (or Manufacturer Part No. Chapter later revisions) For Model A300-B2-100 series airplanes: Messier-Bugatti 286349-115 CMM 32-42-27 April 1991 Messier-Bugatti 286349-116 CMM 32-42-27 April 1991 BFGoodrich 2-1449 & S.C. CMM 32-44-37 January 1993 SB 567 January 30, 1993 (2-1449-32-4) For Model A300-B4-100 series airplanes: ALS (Bendix) 2606802-3 CMM 32-42-02 September 1993 2606802-4 SB 2606802- March 31, 1993 2606802-5 32-003 & S.C. BFGoodrich 2-1449 & S.C. CMM 32-44-37 January 1993 SB 567 January 30, 1993 (2-1449-32-4) For Model A300-B4-200 and A300-600 series airplanes: ALS (Bendix) 2607932-1 CMM 32-42-27 September 1993 & S.C. SB 2607932-32- March 31,1993 002 & Revision 1, dated October 1, 1993 FOR MODEL A300-B4-600R SERIES AIRPLANES: Messier-Bugatti C20210000 Airbus SB April 6, 1990 & C20210200 470-32-675 For Model A310-200 series airplanes: ALS (Bendix) 2606822-1 CMM 32-42-03 September 1993 & S.B. SB 2606822-32- March 31, 1993 002 FOR MODEL A310-300 SERIES AIRPLANES: Messier-Bugatti C20225000 Airbus SB April 6, 1990 & C20225200 470-32-675 (2) Incorporate into the FAA-approved maintenance inspection program the maximum brake wear limits specified in paragraph (a)(1) of this AD. NOTE 2: Once an operator has complied with the requirements of this AD, paragraphs (a)(1) and (a)(2) of this AD do not require that operators subsequently record accomplishment of this AD each time a brake is inspected or overhauled in accordance with that operator's FAA-approved maintenance inspection program. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on January 23, 1995.
2021-10-22: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 airplanes. This AD was prompted by a report indicating that during installation, a fuel pipe bracket assembly on the intermediate rib in the center fuel tank was mislocated, resulting in an offset between the fitting assembly and the refuel/defuel tube assembly. This AD requires modification of the fuel pipe bracket assembly, including all related investigative actions and corrective actions, if necessary; and performing an operational test of the refuel and defuel system. The FAA is issuing this AD to address the unsafe condition on these products.
2003-17-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 and ATR72 series airplanes, that requires inspecting the wire bundle in the area of electrical rack 90VU to detect damage, verifying that the conduit around the wire bundle is in the proper position, and installing a clamp between the wire bundles and the carbon shelves structure. This action is necessary to prevent chafing of a wire bundle, which could result in an electrical short and potential loss of several functions essential for safe flight. This action is intended to address the identified unsafe condition.