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2015-17-25: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of chafing of the fuel lines due to contact with the surrounding structures in the fuel tank. This AD requires replacing and modifying fuel lines, revising the maintenance or inspection program, as applicable, to include critical design configuration control limitations (CDCCL) and airworthiness limitation (AWL) items, and, for certain airplanes, removing certain clamps and mounting hardware. We are issuing this AD to prevent chafing of the fuel lines in the fuel tank, which could result in potential ignition sources in the fuel tank in the event of a lightning strike and consequent fire or explosion.
2025-02-04: The FAA is superseding Airworthiness Directive (AD) 2022-22- 10, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2022-22-10 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2022- 22-10 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
93-02-02: 93-02-02 FOKKER: Amendment 39-8484. Docket 92-NM-190-AD. Applicability: Model F27 series airplanes; serial numbers 10102 through 10433, inclusive; 10435 through 10443, inclusive; and 10446 through 10450, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural capability of the wings, accomplish the following: (a) Within 8,000 flight hours after the effective date of this AD, or within 60 months after the effective date of this AD, whichever occurs first, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD. (1) Replace currently installed nuts having non-metallic locking inserts, installed at the wing spar attachment brackets at wing station 1040, with all-metal self-locking nuts, in accordance with Fokker Service Bulletin F27/57-23, Revision 6, dated August 13, 1991. (2) Replace the lower 14 Hi-shear pins at the rear spar attachment bracket with Hi-lok fasteners, in accordance with Fokker Service Bulletin F27/57-23, Revision 6, dated August 13, 1991. (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: 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 FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacements shall be done in accordance with Fokker Service Bulletin F27/57-23, Revision 6, dated August 13, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 18, 1993.
2002-06-07: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1 series turbofan engines, installed on Airbus Industrie A330 series airplanes. This action requires initial and repetitive pressure testing of the directional pilot valve (DPV) assembly, with replacement of DPV assemblies that fail the pressure test, or, replacing the DPV assembly without performing pressure testing, with a serviceable DPV assembly, or, deactivating the fan reverser for no longer than 10 days until replacement of the DPV assembly is done. This amendment is prompted by a review of thrust reverser safety analyses following a report of inadvertent thrust reverser deployment on another make and model engine. The actions specified in this AD are intended to prevent inadvertent thrust reverser deployment, which, if it occurred in-flight, could result in loss of control of the airplane.
92-17-07: 92-17-07 BRITISH AEROSPACE: Amendment 39-8336. Docket No. 92-NM-53-AD. Supersedes AD 91-14-19, Amendment 39-7060. Applicability: All Model BAe 146-100A, -200A, and -300A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent in-flight separation of a landing gear door from the airplane, accomplish the following: (a) Prior to the accumulation of 9,000 landings, or within 30 days after the effective date of this AD; or if previously inspected in accordance with AD 91-14-19 (56 FR 30314, July 2, 1991), within 3,000 landings after the last inspection in accordance with that AD; whichever occurs later; and thereafter at intervals not to exceed 3,000 landings; accomplish the following: (1) Perform a visual inspection of the left and right main landing gear (MLG) door rear hinge bracket assemblies to detect cracks and/or corrosion, in accordance with British Aerospace Inspection ServiceBulletin 32-A119, Revision 1, dated December 2, 1991. (2) Prior to further flight, replace any cracked hinge bracket with a serviceable part, in accordance with British Aerospace Inspection Service Bulletin 32-A119, Revision 1, dated December 2, 1991; or temporarily repair cracked brackets in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (3) Prior to further flight, remove any corrosion found, in accordance with the British Aerospace Model 146 Structural Repair Manual, and accomplish the following: (i) If less than 0.100 inch of corrosion was removed, re-protect the hinge bracket in accordance with the maintenance manual; and obtain a life limit for the hinge bracket from the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (ii) If 0.100 inch, but less than 0.150 inch, of corrosion was removed, re-protect the hinge bracket in accordance with the maintenance manual; and, within 300 landings after accomplishing the re-protection procedure, replace the hinge bracket with a new part. (iii) If 0.150 inch or more of corrosion was removed, prior to further flight, replace the hinge bracket with a new part. (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 inspections shall be done in accordance with British Aerospace Inspection Service Bulletin 32-A119, Revision 1, dated December 2, 1991, which includes the following list of effective pages: Pages Revision Level Date 1-4 1 December 2, 1991 5 Original November 14, 1990 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, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC. (e) This amendment becomes effective on September 28, 1992.
90-17-09: 90-17-09 BRITISH AEROSPACE: Amendment 39-6693. Docket No. 90-NM-53-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, as listed in British Aerospace Alert Service Bulletin 27-A-PM587l, Issue No. 1, dated October 4, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a reduction in airplane stability and controllability, accomplish the following: A. Within 60 days after the effective date of this AD, unless accomplished within the last 12 months, and thereafter at intervals not to exceed 18 months, perform a visual inspection of both elevator lower control levers, in accordance with paragraphs 2.1 and 2.3 through 2.9 of British Aerospace Alert Service Bulletin 27-A-PM5871, Issue No. 1, dated October 4, 1989. B. If cracks are found, prior to further flight, replace the elevator control lever(s) in accordance with the British Aerospace Alert Service Bulletin 27-A-PM5871, Issue No.1, dated October 4, 1989. C. Replacement of both elevator lower control levers with levers manufactured from L64 or L99 material constitutes terminating action for repetitive inspections required by paragraph A. of this AD. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. 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 British Aerospace, PLC, Librarian for Service Bulletins, P. O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington. This amendment (39-6693, AD 90-17-09) becomes effective on September 17, 1990.
2015-17-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Pratt and Whitney engines. This AD was prompted by reports of blocked drain lines at the engine forward strut that caused flammable fluid to accumulate in a flammable leakage zone. This AD requires repetitive functional checks for blockage of the forward strut drain line and doing corrective actions if necessary, and a one-time cleaning of certain forward strut drain lines. This AD also provides an optional replacement of the drain lines and installation of insulation blankets, and a revision of the maintenance or inspection program, as applicable, to incorporate a certain airworthiness limitation, which would terminate the repetitive checks of the forward strut drain line. We are issuing this AD to detect and correct blockage of forward strut drain lines, which could cause flammable fluids to collect in the \n\n((Page 52949)) \n\nforward strut area and potentially cause an uncontrolled fire or cause failure of engine attachment structure and consequent airplane loss.
87-17-02: 87-17-02 BOEING: Amendment 39-5703. Applies to Model 767 series airplanes specified in Boeing Alert Service Bulletin 767-24A0039, dated March 12, 1987, certificated in any category. Compliance is required as indicated unless previously accomplished. \n\n\tTo minimize the fire hazard associated with overheating of the transformer rectifier unit (TRU) of the auxiliary power unit (APU) starter motor, accomplish the following within 3 months after the effective date of this AD: \n\n\tA.\tReplace the 50-ampere circuit breaker used for the APU starter TRU with a 35- ampere circuit breaker in accordance with Boeing Service Bulletin 767-24A0039, dated March 12, 1987, or later FAA-approved revision. \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\tC.\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 the modification required by this AD. \n\tAll persons affected by this directive who have not already received copies of the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 13, 1987.
96-12-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires reinforcing the lower right-hand wing skin at the fueling adapter. This amendment is prompted by results of tests, which revealed that fatigue cracks can develop in the lower right-hand wing skin at the attachment bolt holes of the fueling adapter. The actions specified by this AD are intended to prevent reduced structural capability of the wing and fuel leakage.
77-16-08: 77-16-08 EIRIAVION OY (FORMERLY MOLINO OY): Amendment 39-3005. Applies to Model PIK-20D sailplanes with serial numbers 20510 through 20532, 20534 through 20540, 20542 through 20544, 20546, 20548, 20552, 20555, and 20556. To prevent separation of wing upper panel spar cap and wing main spar shear web, before further flight, unless already accomplished, comply with paragraph (a), (b), or (c). (a) Replace wing panels with new wing panels identified by the manufacturer as serviceable replacements. (b) Repair existing wing panels in accordance with appendix 1 of Eiriavion Service Bulletin No. M 17, dated June 17, 1977, at an FAA certificated repair station that is a manufacturer's authorized repair facility. Following rebonding, visually inspect the affected area to ensure that the new resin forms a continuous bond on both sides of the wing shear web for its full length. (c) Repair in accordance with an alternate means of compliance which must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, Brussels, Belgium. NOTE: Copies of the applicable service bulletin are available at the following manufacturer's authorized repair facilities: Smitty's Soaring Service Deansboro Road Route 12B Clinton, New York 13323 Sailplane Repair Service, Inc. Rich Roberts 216 Commerce Drive P.O. Box 1462 Fort Collins, Colorado 80522 This amendment is effective August 8, 1977, as to all persons except those persons to whom it was made immediately effective by the telegram dated July 7, 1977, which contained this amendment.