Results
87-24-01: 87-24-01 EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-5767. Applies to Model EMB-120 series airplanes, certificated in any category, equipped with outboard main landing gear wheel halves identified by serial numbers in BF Goodrich Service Bulletin 467, Revision 1, dated June 19, 1987. Compliance required as indicated, unless previously accomplished. To prevent failure of the main landing gear outboard wheel half, accomplish the following: A. Within the next 200 landings after the effective date of this AD, inspect the main landing gear outboard wheel halves, part number 300-603, for cracking, using visual and eddy current methods, in accordance with BF Goodrich Service Bulletin 467, Revision 1, dated June 19, 1987. 1. If a crack is found, prior to further flight replace the wheel half with an airworthy FAA-approved assembly. 2. If no cracks are found, repeat the visual and eddy current inspections at intervals not to exceed 300 landings, until such time as an ultrasonic inspection is accomplished and each affected wheel half is found free of cracks and identified with the impression stamping in accordance with Figure 1 of BF Goodrich Service Bulletin 467, Revision 1, dated June 19, 1987. Any wheel found to be cracked must be replaced prior to further flight with an airworthy FAA- approved assembly. B. For the purposes of complying with this AD, the number of landings may be determined by substituting one landing for each 1/2 hour of flight, unless the operator substantiates a different flight hours-to-landing ratio. This substantiation must be submitted to and approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Atlanta Aircraft Certification Office,FAA, Central Region. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to BF Goodrich, Aerospace and Defense Division, Aircraft Wheel and Brake Operations, P.O. Box 340, Troy, Ohio 45373. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Central Region, Atlanta Aircraft Certification Office, Suite 210, 1669 Phoenix Parkway, Atlanta, Georgia. The amendment becomes effective December 24, 1987.
2024-26-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes; Model A310 series airplanes; Model A318, A319, A320, and A321 series airplanes; Model A330-200, -200 Freighter, and -300 series airplanes; Model A330-841 and -941 airplanes; and Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes. This AD was prompted by chemical oxygen generators that failed to activate in service and during maintenance activities. This AD requires replacing affected oxygen generators and prohibits the installation of affected parts, 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.
2002-15-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca Makila 1 A, 1 A1, and 1 A2 turboshaft engines. This action requires replacing certain digital electronic control units (DECU's) and electronic control units (ECU's) with modified DECU's and ECU's. This amendment is prompted by a report of an uncontained engine turbine wheel failure and the subsequent loss of control of the helicopter. The actions specified in this AD are intended to prevent an engine overspeed condition resulting from the failure of two or more NTL channels.
2002-15-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to replace the rudder control cables and fairleads with parts of improved design. This AD is the result of a report that a rudder control cable broke because of wear at the aft fairlead. The actions specified by this AD are intended to prevent the rudder control cable from breaking because of the rudder control cables wearing in the fairlead area. Broken rudder control cables could result in loss of rudder control.
85-08-01: 85-08-01 MESSERSCHMITT-BOLKOW-BLOHM GmbH: Amendment 39-5038. Applies to Model BO-105 series helicopters, S/N's S1 through S350, certificated in all categories, that are equipped with empennage P/N 105-30101. Compliance is required within 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent cracks in the vertical fin spar and skins and possible failure of the vertical fin, accomplish the following modifications: (a) For helicopters with S/N's S1 through S310, incorporate the tail fin modification and reinforcement specified in MBB BO-105 Service Bulletin No. 30-13, Rev. 2, dated April 24, 1978. (b) For helicopters with S/N's S1 through S350, incorporate the gearbox mount and upper fin modification specified in MBB BO-105 Service Bulletin No. 30-18, Rev. 3, dated October 30, 1984. (c) Aircraft may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where compliance may be accomplished. (d)Equivalent means of complying with this AD must be approved by the Manager, Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part thereof 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 of the service bulletins upon request to MBB Helicopter Corporation, P.O. Box 2349, West Chester, Pennsylvania 19380. The documents also may be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective April 26, 1985.
2024-26-07: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model EMB-135ER, -135KE, -135KL, and -135LR airplanes; and Model EMB-145, -145EP, -145ER, -145LR, -145MP, -145MR, and -145XR airplanes. This AD was prompted by a structural assessment that indicated certain central fuselage longitudinal splices are subjected to fatigue damage on multiple sites due to loose fasteners, which may reduce the structural residual strength below the required levels. This AD requires performing repetitive inspections of certain upper central fuselage longitudinal splices and reporting the inspection results, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. This AD also requires performing corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2015-23-04: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B turbofan engine models. This AD was prompted by reports of GEnx-1B engine oil loss. This AD requires removal and replacement of the non-conforming ball valve in the oil filler cap. We are issuing this AD to prevent loss of engine oil, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.
89-13-04: 89-13-04 BOEING: Amendment 39-6238. \n\tApplicability: Model 757 series airplanes specified in Boeing Alert Service Bulletin 757- 27A0063, Revision 1, dated May 17, 1985, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the occurrence of takeoff configuration false warnings, accomplish the following: \n\n\tA.\tModify the circuitry of the Takeoff Configuration Warning Systems (TOCWS) in accordance with Boeing Alert Service Bulletin 757-27A0063, Revision 1, dated May 17, 1985. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6238, AD 89-13-04) becomes effective on July 24, 1989.
87-04-11: 87-04-11 PILATUS BRITTEN-NORMAN LIMITED: Amendment 39-5532. Applies to Model BN-2T Islander (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent the possibility of high engine vibrations and possible propeller whirl flutter, accomplish the following: (a) Within 100 hours time-in-service (TIS) after the effective date of this AD and at each 500 hours TIS thereafter: (1) Inspect the isolator mounting brackets, Barry Part No. 44-9115-0100, for cracks in accordance with the "Inspection (Part A) - Forged Brackets" paragraph of Pilatus Britten-Norman (PBN) Limited Service Bulletin (S/B) No. BN-2/SB.172, Issue 2, dated June 2, 1986, and: (i) If a cracked "thick-ribbed" (0.190 inches) bracket is found, prior to further flight, replace the bracket with a similar serviceable part or (ii) If a cracked "thin-ribbed" (0.150 inches) bracket is found, prior to further flight, replace all three brackets as an engine mounting set with "thick-ribbed"' brackets in accordance with the "Rectification (Part B) - Forged Brackets" paragraph of PBN S/B No. BN-2/SB.172, Issue 2, dated June 2, 1986. (b) Within 100 hours TIS after the effective date of this AD, and at each 100 hours TIS thereafter: (1) Inspect the Barry-manufactured elastomer cores, and: (i) If Part Number (P/N) R20700-2 is installed, prior to further flight, replace such cores with stiffer serviceable cores P/N R20700-15; or, (ii) If P/N R20700-15 is installed, inspect for cracks, tears, or delamination in accordance with the "Inspection and Rectification of Elastomer Cores (Part C)" paragraph of PBN S/B No. BN- 2/SB.172, Issue 2 dated June 2, 1986, and if defective, prior to further flight, replace with a serviceable core. (c) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, England; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 9, 1987.
2022-16-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200, A330-200 Freighter, A330-300, and A330-900 series airplanes; and all Model A340-200 and A340-300 series airplanes. This AD was prompted by recent tests that demonstrated that when the upper secondary load path (SLP) of the trimmable horizontal stabilizer actuator (THSA) is engaged, the THSA might not stall, with consequently no indication of SLP engagement. This AD requires modifying the THSA installation, implementing the electrical load sensing device (ELSD) wiring provisions, and installing and activating the ELSD, 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.
2003-16-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas transport category airplanes listed above. This action requires inspecting the fuel boost/transfer pumps or reviewing the airplane maintenance records to determine the part number of the fuel boost/transfer pumps, and follow-on actions if necessary. This action is necessary to prevent heated localized temperatures within the fuel boost/transfer pumps due to frictional heating, which could result in a potential source of ignition in a fuel tank and consequent fire or explosion. This action is intended to address the identified unsafe condition.
87-18-12 R1: 87-18-12 R1 McDONNELL DOUGLAS HELICOPTER COMPANY (MDHC) (Hughes Helicopter, Inc.): Amendment 39-5700 as amended by amendment 39-5800. Applies to all Model 369D, 369E, 369F, and 369FF helicopters, certificated in any category, incorporating main rotor transmission output shaft assembly ring gear carriers (P/N 369D25132-BSC or -5) in main transmission assemblies P/N 369D25100-BSC, -501 or -503. Compliance is required as indicated unless previously accomplished. To prevent possible loss of power to the main rotor, accomplish the following: (a) For helicopters with metal particles found in the main transmission, excessive noise or vibration experienced in the main transmission, or vibrations felt in the aircraft that cannot be reduced or eliminated by ordinary main rotor blade tracking and balancing procedures, accomplish the inspection of paragraph (d) of this AD prior to further flight after the effective date of this AD and thereafter at intervals not to exceed 300hours time in service from the last inspection. (b) For helicopters that have main transmission assemblies installed with less than 200 hours time in service on the output shaft assembly ring gear carrier on the effective date of this AD, accomplish the inspection of paragraph (d) of this AD prior to accumulating 300 hours time in service and thereafter at intervals not to exceed 300 hours time in service from the last inspection. (c) For helicopters that have main transmission assemblies installed with more than 200 hours time in service on the output shaft assembly ring gear carrier on the effective date of this AD, accomplish the inspection of paragraph (d) of this AD within the next 100 hours time in service after the effective date of this AD and, thereafter, at intervals not to exceed 300 hours time in service from the last inspection. (d) Perform a dye penetrant and visual inspection on the affected ring gear carriers in accordance with the procedures detailed inparagraphs a through g of the "Periodic Visual Inspection" section of McDonnell Douglas Helicopter Company Mandatory Service Information Notice (SIN) DN-148.1/EN-36.1/FN-25.1, dated October 30, 1987. Remove from service prior to further flight:'' (1) OutPut shafts with any bulging or raised surface in the area being inspected on the upper disc surface (see Figure 2 in referenced SIN). (2) OutPut shafts with any crack indication in the area being inspected on the lower and upper disc surfaces (see Figure 3 in referenced SIN). (e) When the main rotor transmission output shaft assembly ring gear carrier P/N 369D25132-3 is installed and the main transmission assembly is reidentified as P/N 369D25100- 505, repetitive inspections are no longer required. (f) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, Hawthorne, California. (g)Special flight permits may be issued in accordance with FAR sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. The procedure shall be done in accordance with MDHC Mandatory Service Information Notice DN-148.1/EN-36.1/FN-25.1, dated October 30, 1987. 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 McDonnell Douglas Helicopter Company, 500 E. McDowell Road, Mesa, Arizona 85205. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment 39-5800 amends Amendment 39-5700 (52 FR 33228; September 2, 1987), AD 87-18-12. This amendment 39-5800 becomes effective January 15, 1988.
67-30-01: 67-30-01 BRITISH AIRCRAFT: Amdt. 39-506, Part 39, Federal Register November 4, 1967. Applies to Model BAC 1-11 200 Series Airplanes. Compliance required as indicated, unless already accomplished. To prevent failure of the Thermal Relief Valve installed in the No. 2 Auxiliary Hydraulic Power System, introduced by Modification PM 1653, and to provide an adequate thermal relief device in all airplanes, accomplish the following: (a) For Post Modification PM 1653 airplanes, within the next 200 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, check No. 2 Auxiliary Hydraulic System Thermal Relief Valve for satisfactory functioning in accordance with BAC One-Eleven Service Bulletin 29-A- PM 2758, Issue 2, or later ARB-approved issue, or FAA-approved equivalent. (b) For Post Modification PM 1653 airplanes, within the next 600 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 600 hours' time in service from the date of the last inspection or when a low maximum pressure is indicated in the No. 2 Auxiliary Hydraulic System or emergency elevator power system, conduct a bench test of Thermal Relief Valve P/N AIR 91186/2 in accordance with British Aircraft Corporation, Ltd., BAC One-Eleven Alert Service Bulletin No. 29-A-PM 2758, Issue 2, or later ARB- approved issue, or FAA-approved equivalent. (c) If defective parts are found during the inspections provided for in paragraphs (a) and (b), either modify the hydraulic system in accordance with paragraph (d), or replace the defective part with a serviceable P/N AIR 91186/2 and continue the inspections required by paragraphs (a) an (b). (d) For Post Modification PM 1653 airplanes, within the next 1800 hours' time in service after the effective date of this AD, remove Thermal Relief Valve P/N AIR 91186/2, Conduit Guide P/N AB58A3967, and Pipe P/N AB58/48/2675, and rework Lockheed Non- Return Valve P/N 91178 to the standard of Choke Valve Assembly P/N AB48A1427 in accordance with British Aircraft Corporation, Ltd. BAC One-Eleven Service Bulletin No. 29-PM 2758, Part C, or FAA-approved equivalent. (e) For Pre Modification PM 1653 airplanes, within the next 1,800 hours' time in service after the effective date of this AD, rework Lockheed Non-Return Valve P/N AIR 91178 to the standard of Choke Valve Assembly P/N AB48A1427 in accordance with British Aircraft Corporation, Ltd., BAC One-Eleven Service Bulletin No. 29-PM 2758, Part B, or FAA-approved equivalent. (f) The repetitive inspections required by paragraphs (a) and (b) of this AD may be discontinued when modifications in accordance with paragraph (d) of this AD have been accomplished. This amendment effective December 4, 1967.
2002-14-06: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires installation of protective sleeving on the right emergency alternating current (AC) wire assembly of the overhead switch panel. This action is necessary to ensure that protective sleeving is installed on the right emergency AC wire assembly of the overhead switch panel. Lack of such sleeving could result in loss of redundant electrical power during certain cockpit overhead wiring faults. This action is intended to address the identified unsafe condition.
2015-22-05: We are superseding Airworthiness Directive (AD) 2009-18-15, for all Airbus Model A300, A310, and 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). AD 2009-18-15 required revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to require additional life limits and/or replacements for certain main landing gear and nose landing gear components. This new AD requires revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by a determination that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. We are issuing this AD to prevent failure of certain system components, which could result in reduced structural integrity of the airplane.
2015-23-03: We are superseding Airworthiness Directive (AD) AD 2014-20-13 for certain Pacific Aerospace Limited Model 750XL airplanes. 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 fatigue cracks on the fin forward pickup plates, which could cause it to fail. We are issuing this AD to require actions to address the unsafe condition on these products.
2002-14-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection to detect discrepancies of the wire bundles in the avionics compartment in the vicinity of the pedestal extension area of the First Officer's seat; and corrective actions, if necessary. This action is necessary to prevent chafing of wiring in the avionics compartment, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
2002-14-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires performing an inspection of the wiring of the Firex bottle discharge cartridge of the No. 2 engine at station Y=2163.00 bulkhead for chafing on adjacent structure and damaged wiring; repairing damaged wires; and repositioning wires, if necessary. This action is necessary to prevent chafing and possible damage to the wiring of the Firex bottle discharge cartridge of the No. 2 engine, which could result in improper distribution of the fire extinguishing agent within the No. 2 engine in the event of a fire. This action is intended to address the identified unsafe condition.
2015-20-11: We are adopting a new airworthiness directive (AD) for Schempp-Hirth Flugzeugbau GmbH Models Duo Discus and Duo Discus T powered sailplanes. 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 excessive load on the air brake system. We are issuing this AD to require actions to address the unsafe condition on these products.
92-14-08: 92-14-08 AEROSPATIALE: Amendment 39-8290. Docket No. 92-NM-118-AD. Supersedes AD 88-26-04, Amendment 39-6094. Applicability: Model ATR42-300 series airplanes; as listed in Aerospatiale Service Bulletins ATR42-76 0002, Revision 1, dated May 16, 1988; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a malfunction of the engine and propeller controls, accomplish the following: (a) Within 60 days after February 3, 1989 (the effective date of AD 88-26-04, Amendment 39-6094), modify the engine and propeller push-pull control cables on the left and right engines by adding a sealing sheath and protective sleeve, in accordance with Aerospatiale Service Bulletin ATR42-76-0002, Revision 1, dated May 16, 1988. (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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the 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 modification shall be done in accordance with Aerospatiale Service Bulletin ATR42-76-0002, Revision 1, dated May 16, 1988, which incorporates the following list of effective pages: Page Number Revision Level Date 1-3 1 May 16, 1988 4 Original January 18, 1988 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 beobtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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. (e) This amendment becomes effective on July 1, 1992.
87-24-04: 87-24-04 AIRBUS INDUSTRIE: Amendment 39-5771. Applicable to Model A300 series airplanes, Serial Number 1 through Serial Number 107, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent decompression of the airplane, accomplish the following: A. Prior to the accumulation of 24,000 landings or 12 years since first revenue flight, whichever occurs first, modify the fuselage lap splices in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986. B. For airplanes with more than 9 years since first revenue flight as of the effective date of this AD: The modification required by paragraph A., above, may be deferred not to exceed 26,000 landings or 15 years since first revenue flight, whichever occurs first, provided the conditions specified in paragraph 1.B. of Airbus Service Bulletin A300-53-206, dated December 1, 1986, are met. C. For airplanes which have had lap splices repaired, as noted below, accomplish the following, as applicable: 1. For airplanes repaired with an external doubler in accordance with Chapter 53-10-20, Revision 46 of the Structural Repair Manual: Inspect the repaired area for corrosion when the modification required by paragraph A., above, is accomplished. If there is any sign of corrosion, remove the repair and modify prior to further flight, in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986. 2. For airplanes repaired by cutout in accordance with Chapter 53-10-20 of the Structural Repair Manual, figure 701, sheet 2, Revision dated July 1, 1986, or previous issues; or repaired by cutout in accordance with the Structural Repair Manual Chapter 53-10-20, figure 701, sheet 3, Revision dated January 30, 1985, or previous issues, and where cutout repair exceeds half a frame bay: Prior to the accumulation of 16,000 landings since the repairs were installed, modify the repaired lap splices in accordance with FAA-approved methods. 3. For airplanes repaired in accordance with Airbus Service Bulletin 53-215 or 53-216: No further action is necessary in the repaired areas. D. Modification of the longitudinal lap joints in Sections 13 and 14 in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986, constitutes terminating action from the inspections required by AD 85-07-09 for the splices which have been modified. E. An alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, 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 in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective December 24, 1987.
77-08-05: 77-08-05 CESSNA: Amendment 39-2876. Applies to 337 Series (Serial Numbers 337-0002 thru 33701783), T337 Series (Serial Numbers 337-0001, 337-0526 thru 33701398 and P3370001 thru P3370271) and M337 Series (Serial Numbers 337-M0001 thru 337-M0467) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent single engine takeoffs, within the next 25 hours' time in service after the effective date of this AD, accomplish the following: A) Install a Cessna P/N 1400019-77 placard right of the tachometer instrument which reads as follows: "DO NOT INITIATE SINGLE ENGINE TAKEOFF" and operate the aircraft in accordance with this limitation. B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. C) Cessna Service Letter ME77-8, dated March 28, 1977, or later approved revisions pertains to the subject matter of this AD. This amendment becomes effective April 28, 1977.
77-19-02: 77-19-02\tGATES LEARJET: Amendment 39-3040 as amended by Amendment 39- 3265. Applies to all serial numbers of Models 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D and 25F airplanes certificated in all categories having a 36- inch wide (as opposed to a 24-inch wide) cabin door. \n\n\tCOMPLIANCE: Required as indicated in accordance with Compliance Table I set forth in this AD, unless already accomplished. \n\n\tTo assure proper locking of the cabin upper door when the inside handle is in the locked position and to prevent possible unwanted door openings that may occur if a pilot disregards the door warning system accomplish the following at the time intervals noted in Table I of this AD: \n\nTABLE I COMPLIANCE TIMES\n\n\n\n\n\n\n\n\n\n\n\nI N S P E C T I O N T I M E S\n\nAirplane Total Time\nIn Service\n(Hours)\n\nParagraph "A" Bolt\nInspection & Replacement\n\nParagraph "B" Locking\nMechanism Inspection \n\nInitial Inspection/\nReplacement\nInterval for Repetitive Inspections/ Replacement\nInitial Inspection\nInterval for \nRepetitive Inspections\n0 - 2,999\nPrior to or upon the accumulation of 3,075 hours' time in service\nEach 3,000 hours' time in service thereafter\nIn accordance with asterisk (*) paragraph below or upon accumulation of 6,075 hours' time in service, whichever occurs first \nIn accordance with asterisk (*) paragraph below or upon accumulation of each 6,000 hours' time in service after initial inspection\n3,000 - 5,999\nWithin 75 hours' time in service after the effective date of this AD\nEach 3,000 hours' time in service thereafter\nIn accordance with asterisk (*) paragraph below or upon accumulation of 6,075 hours' time in service, whichever occurs first\nIn accordance with asterisk (*) paragraph below or upon accumulation of each 6,000 hours' time in service after initial inspection\n6,000 - up\nWithin 75 hours' time in service after the effective date of this AD\nEach 3,000 hours' time in servicethereafter\nWithin 75 hours' time in service after the effective date of this AD\nIn accordance with asterisk (*) paragraph below or upon accumulation of each 6,000 hours' time in service after initial inspection\n* The door locking mechanism inspection must be accomplished any time the bolt inspection required by Paragraph "A" of this AD reveals a cracked, bent, broken or worn bolt. \n\n\tA.\tInspect and replace, at the time intervals noted in Table I above, the bolt or pin identified as (5) in Figure I of this AD in accordance with Gates Learjet Service Bulletin SB 23/24/25-280 dated July 15, 1977 or later approved revisions and as summarized below: \n\n\t\t1.\tRemove the bolt, or if applicable, pin from the upper door rod control assembly and visually inspect it for cracks, breaks, bends, or wear. If any of the aforementioned defects are found accomplish the door locking mechanism inspection required by Paragraph "B" of this AD prior to the next flight; and \n\n\t\t2.\tReplace the bolt orpin removed in Paragraph A.1. of this AD with a new Gates Learjet part number 2311490-8 bolt, or a new AN3-21 bolt modified in accordance with the above noted Service Bulletin, and secure using an AN960D10 Washer and either a new MS20365-1032 Nut or AN310-3 Nut and MS24665-132 Cotter Pin. \n\n\tB.\tInspect, at the time intervals noted in Table I above, the cabin door locking mechanism in accordance with Gates Learjet Service Bulletin SB 23/24/25-280 dated July 15, 1977 or later approved revisions, and as summarized below: \n\n\t\t1.\tDrill out rivets and remove cabin upper door inner panel. \n\n\t\t2.\tRemove and inspect door locking mechanism for wear and defects in accordance with Learjet Service Manual Inspection Requirements. The maximum allowable diameter (measured in any direction) of the hole in which the (5) bolt is installed is .201 inches. Replace any excessively worn or defective parts prior to the next flight. \n\n\n\n\t\t3.\tReinstall door locking mechanism and using rivets, reinstall the inner panel. \n\n\t\t4.\tCheck door locking mechanism for free movement with no binding thru entire operating travel. Correct any binding prior to the next flight. \n\n\t\t5.\tEnergize door warning system and check its operation for proper functioning. \n\n\tC.\tSubmit a written report on any cracked, broken, bent or worn (5) (See Figure I of this AD) bolts or pins discovered during inspections required by this AD to the FAA via a letter to FAA, Chief, Engineering and Manufacturing Branch (ACE-210), 601 E. 12th Street, Kansas City, Missouri 64106 or an FAA M or D report (FAA Form 8330-2). \n\n\tThe report must include airplane model, serial number, airplane total time-in-service, bolt or pin total time-in-service and statements describing the condition of the bolt and the hole including dimensions of the hole determined in accordance with Paragraph B.2. of this AD. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) \n\n\tD.\tThe actions made mandatory by Paragraphs A, B, and C of this AD are no longer required when Gates Learjet Door Modification Kit AMK 78-2 is installed. \n\n\tE.\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD can be accomplished. \n\n\tF.\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tAmendment 39-3040 became effective on September 26, 1977. \n\n\tThis amendment 39-3265 becomes effective July 20, 1978.
2015-22-07: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). This AD requires an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are issuing this AD to prevent loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin and potential loss of the airplane.
2025-01-06: The FAA is superseding Airworthiness Directive (AD) 2019-14- 13, which applies to all The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. AD 2019-14-13 required identifying the part number, and the serial number if applicable, of the Captain's and First Officer's seats, and performing applicable on-condition actions for affected seats. AD 2019-14-13 also required a one-time detailed inspection and repetitive checks of the horizontal movement system (HMS) of the Captain's and First Officer's seats, and applicable on- condition actions. AD 2019-14-13 also provided an optional terminating action for the repetitive actions for certain seats. This AD was prompted by reports of uncommanded fore and aft movement of the Captain's and First Officer's seats. This AD retains the actions in AD 2019-14-13 and adds an inspection of previously omitted part numbers. The FAA is issuing this AD to address the unsafe condition on these products.