Results
2008-06-16: 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: DCA/750XL/3A is prompted by a report from the manufacturer of the possibility that wiring loom protective sleeving is not fitted to aircraft S/N 107 through to 134. AD applicability revised to include aircraft up to S/N 134. To prevent fretting damage to the wiring loom that may lead to arcing in proximity to the fuel vent lines and the possibility of fire * * *. We are issuing this AD to require actions to correct the unsafe condition on these products.
92-06-10: 92-06-10 SOCATA GROUPE AEROSPATIALE: Amendment 39-8190; Docket No. 91-CE-81-AD. Applicability: Morane Saulnier Models MS892A150, MS892E150, MS893A, MS893E, MS894A, and MS894E airplanes (all serial numbers); and Rallye Models 235C and 235E airplanes (all serial numbers), certificated in any category. Compliance: Required initially upon the accumulation of 500 hours time-in-service (TIS) or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, and thereafter as indicated, unless already accomplished. To prevent nose wheel axle fatigue failure, accomplish the following: (a) Dye penetrant inspect the nose wheel axle assembly for cracks in accordance with the instructions in DESCRIPTION: 1) of SOCATA Groupe AEROSPATIALE Service Bulletin No. 150, dated June 1991. (1) If cracks are found, prior to further flight, replace the nose wheel axle assembly in accordance with the applicable maintenance manual, and reinspect thereafterat intervals not to exceed 500 hours TIS. (2) If no cracks are found, reinspect thereafter at intervals not to exceed 500 hours TIS. (b) At every 4th repetitive inspection interval (2,000 hours TIS) mandated in paragraphs (a)(1) and (a)(2) of this AD, replace the nose wheel axle attaching screws instead of reinstalling the existing screws as specified in the instructions of DESCRIPTION: 2) of SOCATA Groupe AEROSPATIALE SB No. 150, dated June 1991. (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) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (e) The inspections and replacements required by this AD shall be done in accordance with SOCATA Groupe AEROSPATIALE Service Bulletin No. 150, dated June 1991. 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 SOCATA Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8190) becomes effective on April 17, 1992.
2020-06-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report of cracking found on the frame of the right-hand side sliding window in the flight deck. This AD requires repetitive inspections for cracking of the vertical stiffeners of the left- and right-hand sides of the window frames and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-06-11: The FAA is adopting a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model 600N helicopters. This AD requires establishing a life limit for the main rotor (M/R) blade upper control collective/longitudinal link assembly (link assembly). This AD was prompted by the discovery that the life limit was omitted from the maintenance manual. The actions of this AD are intended to prevent an unsafe condition on these products.
82-10-03: 82-10-03 BOEING: Amendment 39-4375. Applies to Boeing Model 727 airplanes, line number 1 through 1612, certificated in all categories. Compliance is required within the next 2500 hours time-in-service from the effective date of this AD, unless already accomplished. To minimize the possibility of cross-connecting the ground spoiler hydraulic tube assemblies, accomplish either one of the following, unless already accomplished: \n\n\tA.\tReplace the ground spoiler hydraulic tube assemblies per figure 1 of Boeing Service Bulletin 727-27-202, Revision 1, dated December 18, 1981, or later revisions approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\tB.\tColor code the ground spoiler hydraulic tube assemblies per figure 2 of the same bulletin. \n\n\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\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\tThis Amendment becomes effective June 11, 1982.
99-05-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 17, 18, 19, 23, 24, 33, 35, 36/A36, A36TC/B36TC, 45, 50, 55, 56, 58, 58P, 58TC, 60, 65, 70, 76, 77, 80, 88, and 95 series airplanes. This AD requires installing a placard on the fuel tank selector to warn of the no-flow condition that exists between the fuel tank detents. This AD is the result of reports of engine stoppage on the affected airplanes where the cause was considered to be incorrect positioning of the fuel selector. The actions specified by this AD are intended to help prevent a lack of fuel flow to the engine caused by incorrect positioning of the fuel selector, which could result in loss of engine power.
92-01-09: 92-01-09 BRITISH AEROSPACE: Amendment 39-8133. Docket 91-NM-266-AD. Applicability: Model series airplanes; as listed in British Aerospace Service Bulletin 28-86, dated June 28, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent an in-flight fire hazard in the rear equipment bay, accomplish the following: (a) Within 60 days after the effective date of this AD, accomplish a visual inspection for proper alignment of fuel feed pipes at pipe joint couplings, in accordance with British Aerospace Service Bulletin SB 28-86, dated June 28, 1991. If misalignment is detected outside the specifications cited in the service bulletin, prior to further flight, correct the alignment by installing an "O" ring modification and a fuel pipe clamping modification, in accordance with the service bulletin. (b) An alternative method 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, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. (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 inspection and realignment required by this AD shall be done in accordance with British Aerospace Service Bulletin SB 28-86, dated June 28, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (e) This amendment (39-8133, AD 92-01-09) becomes effective on January 24, 1992.
2020-05-17: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318-112, A319-111, A319-112, A319-113, A319- 114, A319-115, A319-131, A319-132, A319-133, A320-211, A320-212, A320- 214, A320-216, A320-231, A320-232, A320-233, A320-251N, and A320-271N airplanes. This AD was prompted by a report of marginal clearance between certain fuel sensor covers on both left-hand (LH) and right- hand (RH) wings. This AD requires the replacement of certain fuel level sensor brackets, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-05-24: The FAA is superseding Airworthiness Directive (AD) 2010-26- 01, which applied to certain The Boeing Company Model 777-200 series airplanes. AD 2010-26-01 required installing a new insulation blanket on the latch beam firewall of each thrust reverser (T/R) half. This AD requires retaining the requirements of 2010-26-01. This AD also adds airplanes to the applicability. For those airplanes, this AD requires an inspection to determine if the installed T/R has an affected part number and, if an affected part number is found, installation of a new insulation blanket. This AD was prompted by a report of an in-flight shutdown due to an engine fire indication and a determination that additional airplanes are affected. The FAA is issuing this AD to address the unsafe condition on these products.
79-13-04: 79-13-04 PIPER AIRCRAFT CORPORATION: Amendment 39-3500. Applies to Model PA-32RT-300T, serial numbers 32R-7887001 through 32R-7987124 airplanes certificated in all categories. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent possible fuel leakage and engine power loss, accomplish the following: a. Remove the lower cowling. b. Remove the 1/8-inch copper fuel flow indicator tube attached to the fuel servo and to the left rear baffle. c. Install the 1/8-inch stainless steel tube, Piper part number 67700-348 between the fuel servo and the left rear baffle. d. Pressurize the fuel system by positioning the mixture control to idle cut-off, turning the master switch on, and turning the fuel boost pump on. e. Check the tube fittings for leaks and correct discrepancies as necessary. f. Replace the lower cowling. g. Make an appropriate maintenance record entry. h. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. NOTE: Piper Service Bulletin 652 pertains to this subject. This amendment becomes effective June 27, 1979.
93-02-08: 93-02-08 BOEING: Amendment 39-8490. Docket 92-NM-117-AD. \n\n\tApplicability: Model 727 series airplanes equipped with Bendix brakes fitted with NASCO rotors installed in accordance with Supplemental Type Certificate (STC) SA3948NM; and equipped with the brake part numbers identified in paragraph (a) of this AD; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent the loss of main landing gear braking effectiveness, accomplish the following: \n\n\t(a)\tWithin 180 days after the effective date of this AD, inspect brakes having the brake part numbers specified 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 this limit. \n\n\n\n\nBendix Brakes Fitted with NASCO Rotors \nInstalled In Accordance with STC SA3948NM \n\nBendix P/N\n\nBoeing P/N\nMaximum Wear \nLimit (inches) \n2601182-5\n10-61287-22\n1.8 \n2601182-6\n10-61287-23\n1.7 \n\n\t(b)\tWithin 180 days after the effective date of this AD, incorporate the maximum brake wear limits specified in paragraph (a) of this AD, into the FAA-approved maintenance inspection program. \n\n\t(c)\tAn 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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThis amendment becomes effective on March 15, 1993.
78-14-08: 78-14-08 DETROIT DIESEL ALLISON: Amendment 39-3264 as amended by Amendment 39-3592. Applies to 250-C18/250-C18A/250-C18B/250-C18C/250-C20, and 250-C20B engines equipped with fuel pump P/Ns 6854292, 6856250, 6857548, 6876803, and 6877719, installed in aircraft certificated in all categories. Compliance required as follows unless previously accomplished. To preclude possible engine flameout resulting from fuel pump drive spline failure: Remove and inspect the fuel pump drive splines in accordance with the procedures specified in Detroit Diesel Allison Commercial Service Letter 61 for the 250-C18 series engines and 1007 for the 250-C20 series engines, revision 3 or later FAA approved revisions and the compliance times specified in (a) and (b) below. (a) For fuel pumps with 200 or more hours time in service on the effective date of this AD, compliance is required within 25 hours time in service and again each 200 hours time in service thereafter. (b) For fuel pumps with less than 200 hours time in service on the effective date of this AD, compliance is required prior to reaching 225 hours time in service and again each 200 hours time in service thereafter. If the pump drive splines exceed the wear criteria specified in the above Commercial Service Letters, the pump shall be removed from service before further flight except that the aircraft may be flown in accordance with FAR 21.197 to a base where the repair can be performed. Unacceptable spline wear may be corrected by replacing worn parts or by modifying the pump in accordance with Detroit Diesel Allison Commercial Engine Bulletins No. 161 for 250-C18 series engines and 1051 for 250-C20 series engines revision 1, or later FAA approved revisions. All affected fuel pumps shall be modified in accordance with the procedures specified in the above referenced Commercial Engine Bulletins and the compliance times specified in (c) through (e) below. Upon completion of this modification the need and requirement for the above recurring inspection is eliminated. "Time in service" as specified in (c) and (d) below is the time since the last pump overhaul, or since new if the pump has never been overhauled. (c) For fuel pumps with less than 1475 hours time in service on the effective date of this AD, compliance is required prior to reaching 1500 hours time in service. (d) For fuel pumps with greater than 1475 hours time in service after the effective date of this AD, compliance is required within 25 hours time in service. (e) All fuel pumps disassembled for heavy maintenance or overhaul shall be modified regardless of time in service, before being returned to service. Operators who have not kept time in service records on individual pumps shall substitute engine hours time in service in lieu thereof. The Detroit Diesel Allison commercial service information identified in this directive is incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). The Detroit Diesel Allison Co. commercial service information incorporated herein may be obtained upon request to Detroit Diesel Allison, Division of General Motors Corporation, P.O. Box 894, Indianapolis, Indiana 46206. This document may also be examined at the FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 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 at its headquarters in Washington, D.C. and the Great Lakes Region. Amendment 39-3264 became effective July 20, 1978. This Amendment 39-3592 becomes effective October 24, 1979.
2020-05-23: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires inspecting the attachment screws of each main gearbox (MGB) suspension bar rear attachment fitting, and depending on the outcome, applying a sealing compound, performing further inspections, and replacing affected parts. This AD was prompted by reports of an elongated attachment screw and loss of tightening torque of the nut. The actions of this AD are intended to address an unsafe condition on these products.
77-02-07: 77-02-07 BEECH: Amendment 39-2817. Applies to Model 200 (Serial Numbers BB-2, BB-6 thru BB-18 and BB-20 thru BB-50) airplanes. Compliance: Required within 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent unintentional feathering of a propeller due to failure of the secondary low pitch stop amplifier, accomplish either Paragraph A or B: A) Replace both P/N 101-364171-1 and P/N 101-364171-9 printed circuit board assemblies with P/N 101-364170-15 printed circuit board assemblies in accordance with Beechcraft Service Instruction No. 0745-354, notwithstanding its supersedence by Beechcraft Service Instruction No. 0808-247. B) Remove secondary low pitch stop system in accordance with Beechcraft Service Instruction No. 0808-247, or later approved revisions. C) Airplanes which have accumulated 100 hours' time in service after the effective date of this AD may be flown in accordance with FAR 21.197 to a place where a replacement or removal can be performed, providing the existing amplifiers have not malfunctioned. D) Any equivalent method of compliance with this AD, must be approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. NOTE: The manufacturer has advised the FAA that sufficient replacement parts are available to accomplish Paragraph A of this AD. This amendment becomes effective March 1, 1977.
2008-04-08: We are adopting a new 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: Bombardier Aerospace has completed a system safety review of the CL-600-2B19 aircraft fuel system against new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525-001 to determine if mandatory corrective action is required. The assessment and lightning tests showed that certain fuel tube self-bonded couplings do not provide sufficient lightning current capability. The assessment also showed that single failure of the integral bonding wire of the self-bonded couplings or excessive axial clearance at the reducer ferrules of certain self-bonded couplings could affect electrical bonding between fuel tubes. Insufficient electrical bonding between fuel tubes or insufficient current capability of fuel tube couplings, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-04-14: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD requires inspecting the wheel speed transducer (WST) wiring harness, replacing the wiring harness if necessary, installing wiring hardware, and rerouting the WST wiring harness on both the left and right brake assemblies. This AD also requires revising the Abnormal Procedures section of the airplane flight manual (AFM) and quick reference handbook (QRH). This AD was prompted by reports of damage to the wiring harness due to excessive slack in the wiring harness assembly that allows contact with the main landing gear tire and by the determination that the AFMs and QRHs contain incorrect procedures for anti-skid braking system failures. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-06: 78-12-06 PIPER: Amendment 39-3242 as amended by amendment 39-3461. Applies to Piper Aircraft Corporation Model PA-31T aircraft, S/N 31-7620012 and up, certificated in all categories, equipped with nose landing gear wheel assembly, Piper P/N 551-778, Cleveland P/N 40-120A. To detect cracks in the nose landing gear wheel, accomplish the following: (a) Prior to next flight visually check the nose wheel cup and flange area for cracks. If a crack is found, replace the wheel with an airworthy part of the same P/N or Piper P/N 551- 758, B. F. Goodrich P/N 3-1331, equipped with a tubeless tire, size 18 x 4.4, 6 ply rating or Piper P/N 551-782, B. F. Goodrich P/N 3-1076. Check may be accomplished by pilot. (b) Repeat paragraph (a) prior to each flight. (c) When wheel of Piper P/N 551-758, B. F. Goodrich P/N 3-1331 or Piper P/N 551- 782, B. F. Goodrich P/N 3-1076 is installed, repeat inspections of paragraph (b) may be discontinued. (d) Record results of each check in aircraft log or continuous inspection manual. Amendment 39-3242 was effective June 22, 1978. This amendment 39-3461 is effective May 9, 1979.
2020-06-02: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines, LLC (IAE) PW1122G-JM, PW1124G1-JM, PW1124G- JM, PW1127GA-JM, PW1127G1-JM, PW1127G-JM, PW1133G-JM, PW1133GA-JM, PW1130G-JM, and PW1129G-JM model turbofan engines with a certain low- pressure turbine (LPT) 3rd-stage blade installed. This AD requires initial and repetitive borescope inspections (BSI) of the turbine stator intermediate outer rear air seal (turbine piston seal) and, depending on the results of the inspection, replacement with a part eligible for installation. This AD was prompted by reports of failure of turbine piston seals leading to fracture of the LPT 3rd-stage blades. The FAA is issuing this AD to address the unsafe condition on these products.
76-09-04: 76-09-04 HAMBURGER FLUGZEUGBAU GmbH: Amendment 39-2594. Applies to Model HFB-320 Hansa airplanes, S/N 1021 thru 1023, 1026 thru 1028, 1030 thru 1040, 1045, and 1049 thru 1055, certificated in all categories. Compliance is required as indicated. To prevent possible abrupt unwanted deflection of nose wheel steering, caused by a disengaged torque coupling, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished - (1) Inspect the nose landing gear steering torque coupling to ensure that it is in the proper engaged position; (2) Apply paint markings to the shaft (screw head and nut) and housing of the nose landing gear steering torque coupling in accordance with Figure 1 of HFB 320 Hansa Alert Service Bulletin 32-24A dated September 26, 1975, or an FAA-approved equivalent; and (3) Install an operating limitations placard in full view of the pilot that reads - "Prior to each takeoff, check for proper nose wheel marking alignment" NOTE: It is possible that the nose landing gear torque coupling may become overloaded and disengaged if the maximum steering angle is exceeded in maintenance or taxiing. This condition can be detected by an increased resistance felt at the control wheel. (b) Prior to each takeoff after the paint markings have been applied in accordance with paragraph (a) of this AD, check the markings for proper alignment. This check may be carried out by the pilot. (c) If improper alignment is detected during a check required by paragraph (b) of this AD, before further flight, repair the nose wheel steering unit. This amendment becomes effective, May 10, 1976.
92-10-11: 92-10-11 BOEING: Amendment 39-8245. Docket No. 91-NM-192-AD.\n\n\tApplicability: Model 757 series airplanes, listed in Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991, certificated in any category.\n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless previously accomplished.\n\n\tTo prevent damage to the floor beam at body station (BS) 1640, hydraulic system components, and flight control functions in the event of a sudden decrease in air pressure aft of the bulkhead lining, accomplish the following:\n\n\t(a)\tModify the soft bulkhead support structure at BS 1640 and replace the bulkhead lining in accordance with Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991.\n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.\n\n\t(d)\tThe modification shall be done in accordance with Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on June 1, 1992.
2020-05-20: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and AS332L2 helicopters. This AD requires removing the drain plugs from the fuel tank compartments located under the bottom structure. This AD was prompted by the discovery that a modification to the fuel tank could lead to fuel accumulating in an area containing electrical equipment and subsequent ignition of fuel vapors. The actions of this AD are intended to address an unsafe condition on these products.
78-02-01: 78-02-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3124 as amended by amendment 39-3460. Applies to model PA-31T airplanes, serial numbers 31T-7400002 through 31T-7820077, and Model PA-31T1 airplanes, serial numbers 31T-7804001 through 31T-780-4006, certificated in all categories. Compliance required within the next fifty hours in service after the effective date of this AD, unless already accomplished. (a) To preclude possible failure of the main landing gear actuating cylinder rod end bearing assemblies, accomplish the inspection and replacement where required, described in the "Instruction" portion of Piper Aircraft Corporation Service Bulletin No. 57A, dated August 30, 1978. (b) Equivalent alterations or methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-3124 was effective January 18, 1978. This amendment 39-3460 is effective May 9, 1979.
84-12-51: 84-12-51 WESTLAND HELICOPTERS LIMITED: Amendment 39-4904. Applies to Westland Model 30 Series 100 helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent possible hazards in flight associated with cracking of the main rotor blades, accomplish the following: (a) Before the next flight and thereafter before the first flight of each day, visually inspect the main rotor blades in accordance with Westland Service Bulletin W30-05-23 dated July 16, 1984, or FAA-approved equivalent. (b) Within 15 hours after the effective date of this AD, unless already accomplished, conduct an eddy current inspection of the main rotor blade and thereafter at intervals not to exceed every 15 hours time in service since the last inspection in accordance with Westland Service Bulletin W30-05-23, or FAA-approved equivalent. (c) Remove from service any main rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with the AD may be used when approved by the Manager, Brussels Aircraft Certification Office, Federal Aviation Administration, c/o American Embassy, APO New York 09667. This amendment becomes effective September 11, 1984, as to all persons except those person to whom it was made immediately effective by telegraphic AD T84-12-51, issued June 5, 1984, which contained this amendment.
64-25-01: 64-25-01\tBOEING: Amdt. 39-1 Part 507 Federal Register November 6, 1964. Applies to Models 707 and 720 Series Aircraft Equipped With Pratt & Whitney JT3D Engines. \n\n\tCompliance required as indicated.\n \n\tThere have been a number of engine fires in service due to fuel accumulation in the aft thrust reverser sleeve and the side cowl panel as a result of false starts.\n \n\tTo correct this condition, unless already accomplished, provide additional fluid drainage in the left-hand side cowl panel and aft thrust reverser sleeve on each engine in accordance with either (a) or (b) or an equivalent approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tWithin 3,100 hours' time in service after the effective date of this AD accomplish the following: \n\n\t\t(1)\tDrill or cut four 1/2 inch-diameter holes through lower skin of the aft thrust reverser sleeve at Station 222.30 as shown on page 5 of Boeing Service Bulletin No. 1908. \n\n\t\t(2)\tDrill or cut two 1/4 inch-diameterholes through lower skin of aft thrust reverser sleeve at Station 222.30, one hole outboard of each channel section E-E and F-F at the locations shown on page 6 of Boeing Service Bulletin No. 1908. \n\n\t\t(3)\tDrill or cut two 1/2-inch diameter holes through lower skin of the aft thrust reverser sleeve at Station 241.75 as shown on page 4 of Boeing Service Bulletin No. 1908. \n\n\t\t(4)\tDrill or cut two 1/4 inch-diameter holes, one hole outboard of each rib, through lower skin on the aft thrust reverser sleeve, 1.3 inches outboard and 0.1 inch forward of each hole drilled in accordance with (a)(3). \n\n\t\t(5)\tDrill or cut two 1/2 inch-diameter holes through lower skin on left-hand side cowl nacelle Station 197.51 and bend trailing edge of each hole as shown on page 8 of Boeing Service Bulletin No. 1908. \n\n\t(b)\tWithin 3,100 hours' time in service after the effective date of this AD, drill or cut additional 1/2 inch-diameter drain holes in the aft thrust reverser sleeve and in the left sidecowl panel in accordance with Boeing Service Bulletin No. 1908. \n\n\tNOTE. - American Airlines, Inc. Fleet Campaign Directive No. 810B is an equivalent which has been approved by the Aircraft Engineering Division, FAA Western Region. \n\n\t(Boeing Service Bulletin No. 1908 dated January 16, 1964, covers this same subject.) \n\n\tThis directive effective December 7, 1964.
2020-05-16: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115 airplanes; Model A320-214, -216, - 232, -251N, and -271N airplanes; and Model A321-211, -231, -251N, - 251NX, -253N, -271N, -271NX, and -272N airplanes. This AD was prompted by reports of incomplete installations of the over wing panel lug attachments in the production assembly line. This AD requires a one- time detailed inspection of certain attaching points on the left-hand and right-hand wings for the correct installation of certain hardware, and, depending on findings, accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.