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88-06-06: 88-06-06 MCDONNELL DOUGLAS: Amendment 39-5879. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, and KC-10A (Military) series airplanes that do not have a secondary retention system installed in accordance with AD 87-07-04, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent structural damage to the airplane due to engine core cowl door separation, accomplish the following: \n\n\tA.\tWithin ten days after the effective date of this AD, check the core cowl door latches in accordance with McDonnell Douglas Model DC-10 Alert Service Bulletin A71-150, Revision 1, dated January 27, 1988, or later FAA-approved revision, once each day for engine Numbers 1 and 3 (wing mounted engines) and after each core cowl door is opened and subsequently closed. \n\n\tB.\tIf the latch is open, before further flight, properly close the latch; if the latch will not engage, adjust the latch in accordance with Maintenance Manual Chapter 71-13-01, paragraph entitled "Adjustment/test core cowl doors"; if the latch cannot be properly adjusted, replace the latch prior to further flight. \n\n\tC.\tThe checks required by paragraph A., above, may be discontinued after the secondary retention system is installed in accordance with AD 87-07-04. \n\n\tD.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\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 information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective April 4, 1988.
89-23-02: 89-23-02 BOEING: Amendment 39-6373. Docket No. 89-NM-100-AD. \n\n\tApplicability: Model 757 and 767 series airplanes, as listed in Boeing Alert Service Bulletins 757-29A0037, Revision 1, and 767-29A0035, Revision 1, both dated November 23, 1988, certificated in any category. \n\n\tCompliance: Required within the next 6,000 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the possible complete loss of hydraulic power, accomplish the following: \n\n\tA.\tRemove and rework or replace the Ram Air Turbine (RAT) Ground Checkout Module (GCM) in accordance with Boeing Service Bulletin 757-29A0037, Revision 1, dated November 23, 1988, or Revision 2, dated August 3, 1989 (for Model 757 airplanes); or Boeing Service Bulletin 767-29A0035, Revision 1, dated November 23, 1989, or Revision 2, dated August 3, 1989 (for Model 767 airplanes); as appropriate. Prior to returning the airplane to service: \n\n\t\t1.\tIf the RAT has been operated ortested since the airplane delivery, prior to returning the airplane to service, inspect the downstream filter screen of the removed GCM. \n\n\t\t2.\tIf the screen is damaged or missing, or if GCM has been removed previously without inspecting the screen, prior to further flight, either test the RAT hydraulic pump or replace it in accordance with the applicable service bulletins. \n\n\t\t3.\tIf the RAT hydraulic pump is tested and found to be damaged, prior to further flight, replace it with a serviceable pump in accordance with the applicable service bulletin. \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 (39-6373, AD 89-23-02) becomes effective on December 1, 1989.
2021-22-10: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109E helicopters. This AD was prompted by reports that certain tail rotor gearbox assemblies were installed on Model A109E helicopters and those parts are not approved for installation on that helicopter model. Because those assemblies are not part of the type design for Model A109E helicopters, there are no overhaul or life limits included in the applicable maintenance manuals. This AD requires replacement of each affected tail rotor gearbox assembly with a serviceable part, 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.
90-24-11: 90-24-11 BOEING: Amendment 39-6814. Docket No. 90-NM-81-AD. \n\n\tApplicability: All Model 727 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect cracks in the Body Station 1183 pressure bulkhead web and strap, accomplish the following: \n\n\tA.\tFor airplanes with 40,000 or more flight cycles on February 6, 1986 (the effective date of Amendment 39-5222), within the next 300 flight cycles, unless accomplished within the last 3,200 flight cycles, and thereafter at intervals not to exceed 3,500 flight cycles, inspect and repair, if necessary, in accordance with paragraph D. of this AD. \n\n\tB.\tFor airplanes with 33,000 or more flight cycles and less than 40,000 flight cycles on February 6, 1986, within the next 1,500 flight cycles, unless accomplished within the last 2,000 flight cycles, and thereafter at intervals not to exceed 3,500 flight cycles, inspect and repair, if necessary, in accordance withparagraph D. of this AD. \n\n\tC.\tFor airplanes with fewer than 33,000 flight cycles on February 6, 1986, prior to the accumulation of 30,000 flight cycles or within the next 3,500 flight cycles after February 6, 1986, whichever occurs later, and thereafter at intervals not to exceed 3,500 flight cycles, inspect and repair, if necessary, in accordance with paragraph D. of this AD. \n\n\tD.\tAccomplish a close visual inspection of the web in accordance with Figure 1 of Boeing Alert Service Bulletin 727-53A0171, Revision 1, dated January 17, 1986, or Revision 2, dated December 14, 1989. If cracks are detected, prior to further flight, repair in accordance with paragraph E. or F. of the Accomplishment Instructions of the service bulletin. \n\n\tE.\tFor airplanes repaired by the installation of the doubler in accordance with Boeing Service Bulletin 727-53A0171, Original Issue, within the next 15,000 flight cycles after that repair, incorporate the vertical reinforcing strap and spacers described in paragraph F. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0171, Revision 1, dated January 17, 1986, or Revision 2, dated December 14, 1989. \n\n\tF.\tThe following constitutes terminating action for the repetitive inspections required by paragraphs A., B., and C. of this AD: \n\n\t\t1.\tThe preventive modification described in paragraph D. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0171, Revision 1, dated January 17, 1986, or Revision 2, dated December 14, 1989. \n\n\t\t2.\tThe repairs described in paragraphs E. and F. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0171, Revision 1, dated January 17, 1986, or Revision 2, dated December 14, 1989. \n\n\tG.\tFor airplanes repaired or modified with blind fasteners: Within 3,500 flight cycles after the effective date of this AD, and thereafter at intervals not to exceed 3,500 flight cycles, accomplish a visual inspection for cracks and loose or missing fasteners, in accordance with Boeing Alert Service Bulletin 727- 53A0171, Revision 2, dated December 14, 1989. If cracks are detected, prior to further flight, repair in accordance with the service bulletin. If loose or missing fasteners are detected, prior to further flight, replace with protruding head solid fasteners. Replacement with protruding head solid fasteners constitutes terminating action for the repetitive inspections required by this paragraph. \n\n\tH.\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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tI.\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\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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tAirworthiness Directive 90-24-11 supersedes AD 86-02-06 R1, Amendment 39-5331. \n\tThis amendment (39-6814, AD 90-24-11) becomes effective on December 26, 1990.
92-17-13: 92-17-13 McDONNELL DOUGLAS: Amendment 39-8342. Docket No. 92-NM-139-AD. \n\n\tApplicability: Model DC-10-10, -15, -30, -40, and KC-10 (military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of the wing pylon aft bulkhead and subsequent separation of the engine and pylon from the airplane, accomplish the following: \n\n\t(a)\tExcept as provided by paragraph (b) of this AD: Prior to or upon the accumulation of 4,000 total flight cycles, or within 10 days after the effective date of this AD, whichever occurs later, visually inspect the left and right wing pylon aft bulkhead and the upper spar web to detect cracks, in accordance with McDonnell Douglas DC-10 Alert Service Bulletin A54-106, dated July 9, 1992. \n\n\t(b)\tThe inspection specified in paragraph (a) of this AD is not required to be accomplished on airplanes on which a visual inspection of the left and right wing pylon aft bulkheadand the upper spar web has been accomplished within 45 days prior to the effective date of this AD, in accordance with one of the methods specified in either paragraph (b)(1) or (b)(2) of this AD: \n\n\t\t(1)\tthe inspection method specified in McDonnell Douglas DC-10 Alert Service Bulletin A54-106, dated July 9, 1992; or \n\n\t\t(2)\tthe inspection required by paragraph (g)1. of AD 80-11-05 R1 (Amendment 39-3981). \n\n\t(c)\tIf any cracks are found in the wing pylon aft bulkhead, prior to further flight, replace the wing pylon aft bulkhead in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(d)\tIf any cracks are found in the upper spar web, prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(e)\tSubmit a report of inspection findings to the Manager, Los Angeles ACO, 3229 East Spring Street, Long Beach, California 90806-2425, (fax (310) 988-5210), at the applicable time specified in paragraph (e)(1) or (e)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t\t(1)\tFor airplanes on which the inspection is accomplished after the effective date of this AD: Submit the report within 10 days after performing the inspection required by paragraph (a) of this AD. \n\n\t\t(2)\tFor airplanes on which the inspection has been accomplished prior to the effective date of this AD: Submit the report within 10 days after the effective date of this AD. \n\n\t(f)\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 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(g)\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(h)\tThe inspection shall be done in accordance with McDonnell Douglas DC-10 Alert Service Bulletin A54-106, dated July 9, 1992. 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 Corporation, P.O. Box 1771, Long Beach, California 90801, Attention: Business Unit Manager, Technical Publications & Technical Administrative Support C1-L5B (56-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC. \n\n\t(i)\tThis amendment becomes effective on September 1, 1992.
91-03-11: 91-03-11 BRITISH AEROSPACE: Amendment 39-6873. Docket No. 90-NM-193-AD. Applicability: Model BAe 146 100A and 200A series airplanes, as listed in British Aerospace Service Bulletin 55-7-00955D, Revision 2, dated January 22, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent oscillations (flutter) of the elevators, accomplish the following: A. Within 180 days after the effective date of this AD, install additional mass balance weights to the elevators forward of the hinge line, in accordance with British Aerospace Service Bulletin 55-7-00955D, Revision 2, dated January 22, 1990. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, 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. C. 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. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6873, AD 91-03-11) becomes effective on March 4, 1991.
2009-24-14: 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: It has been found the possibility of elevator mass balance fasteners becoming slack under certain conditions. The loose of at least two fasteners may lead to an unbalance condition, which may induce flutter on airplane elevators. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-17-02: 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: During refueling, the ground crew detected smoke from the refuel/defuel panel illuminated placard 160VU. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-17-03: 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: The airbrake upper crossbeam on an airplane failed in-flight. The crossbeam failure caused damage to the rudder control system, resulting in loss of rudder control. Loss of rudder control will cause handling difficulties particularly during take-off, approach, and landing phases in cross winds. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
92-08-11: 92-08-11 BOEING: Amendment 39-8222. Docket No. 91-NM-212-AD.\n\n\tApplicability: Model 737-300, 737-400, and 737-500 series airplanes, and Model 757-200 series airplanes; equipped with TransAero P/N 91465 series single flight attendant seats identified in TransAero Service Bulletin No. 192, Revision C, dated August 12, 1991, certificated in any category. \n \n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo prevent failure of the seat pans and possible injury to flight attendants, accomplish the following:\n\n\t(a)\tWithin 60 days after the effective date of this AD, inspect the front edge of the affected seat pans for areas of abnormal flexibility in accordance with paragraph C. of TransAero Service Bulletin No. 192, Revision C., dated August 12, 1991.\n\n\t\t(1)\tIf no damage is detected, repeat the inspection at intervals not to exceed 375 flight hours.\n\n\t\t(2)\tIf damage is detected, prior to further flight, accomplish either subparagraph (a)(2)(i) or (a)(2)(ii):\n\n\t\t\t(i)\tInstall a placard stating that the damaged seat is not to be occupied; or\n\n\t\t\t(ii)\tReplace the seat pan with a serviceable seat pan of the same part number, and continue to inspect thereafter at intervals not to exceed 375 flight hours in accordance with paragraph (a) of this AD.\n\n\t(b)\tWithin 18 months after the effective date of this AD, modify all single flight attendant seat pans in accordance with TransAero Service Bulletin No. 192, Revision C, dated August 12, 1991.\n\n\t(c)\tThe inspections required by paragraph (a) of this AD may be terminated upon accomplishing the modification described in TransAero Service Bulletin 192, Revision C, dated August 12, 1991.\n\n\t(d)\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.\n\n\tNOTE: The request should be forwarded through anFAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(e)\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(f)\tThe inspection and modification shall be done in accordance with TransAero Service Bulletin No. 192, Revision C, dated August 12, 1991, which contains the following list of effective pages:\n\n\tPage number\tRevision level\tDate\n\n\tCover\tC\tAugust 12, 1991\n\n\tSheets i, ii,\tC\t(Not dated)\n\tand iii\n\n\tiv\t(None)\t(Not dated)\n\n\t1 - 24\t(None)\t(Not dated)\n\nThis 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 TransAero Industries, Inc., 502 North Oak Street, Inglewood, California 90302-2942. 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(g)\tThis amendment becomes effective on May 29, 1992.