Results
92-08-10: 92-08-10 AIRBUS: Amendment 39-8221. Docket No. 91-NM-201-AD. Applicability: Model A310 and A300-600 series airplanes; equipped with pilot and copilot seats manufactured by Sogerma-Socea, as listed in Sogerma-Socea Service Bulletin 25- 188, Revision 1, dated July 2, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced ability of the flight crew to control the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, accomplish paragraphs (a)(1) and (a)(2) in accordance with Sogerma-Socea Service Bulletin 25-188, Revision 1, dated July 2, 1991: (1) Perform a visual inspection to detect damage to the aft electrical stop switch (switch reference 3 in Figure 1 of the service bulletin). Prior to further flight, replace any damaged switches found, in accordance with the service bulletin. (2) Determine the manufacturer's serial number on the pilot's andcopilot's seats. If the seats have serial numbers that are less than number 261, or if the horizontal actuator has been replaced, accomplish the following: (i) Measure the amount of clearance between the electrical stop and the mechanical stop of the horizontal actuator. (ii) If the clearance is less than 4mm, prior to further flight, adjust the clearance to more than 4mm in accordance with the service bulletin. (iii) If there is no clearance, prior to further flight, replace the horizontal actuator and adjust the clearance to the proper dimension when fitting the new horizontal actuator, 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 commentand then send it 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 the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection shall be done in accordance with Sogerma-Socea Service Bulletin 25-188, Revision 1, dated July 2, 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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 May 29, 1992.
2004-13-05: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter Deutschland (ECD) model helicopters that requires inspecting the vertical fin skin paneling to determine if it was manufactured with the correct wall thickness. This amendment is prompted by a report from the manufacturer that some vertical fins may have been produced with the wrong vertical fin skin thickness. The actions specified by this AD are intended to prevent failure of the vertical fin and subsequent loss of control of the helicopter.
2010-24-10: 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: Damages to the rudder bar locking adjustment tube of a non- reinforced version have been reported to Soci[eacute]t[eacute] Nouvelle (SN) Centrair. This tube had been reinforced in 1984 with a modification. Gliders produced before the introduction of this modification have not been systematically retrofitted. In case of rudder bar locking adjustment tube breaking in flight when adjusting the rudder pedals position, it might interfere with the rudder pedals which could lead to rudder jam or a restricted rudder movement and consequently, to reduced control of the sailplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
93-17-51: 93-17-51 BOEING: Amendment 39-8699. Docket 93-NM-152-AD. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes, line positions 2288 through 2515 inclusive, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent loss of the horizontal stabilizer, which could severely affect controllability of the airplane, accomplish the following: \n\n\t(a)\tFor airplanes having line positions 2288 through 2347 inclusive: Within 24 hours after the effective date of this AD, perform a detailed visual inspection of the left and right horizontal stabilizer hinge fitting to verify installation of the retention devices on the inner and outer hinge pins. For the purposes of this AD, retention devices are cotter pins, nuts, washers, and bushing retainers. \n\n\t(b)\tFor airplanes having line positions 2348 through 2515 inclusive: Within 15 days after the effective date of this AD, perform a detailed visual inspection of the leftand right horizontal stabilizer hinge fitting to verify installation of the retention devices on the inner and outer hinge pins. \n\n\t(c)\tIf no part is missing, no further action is required by this AD. \n\n\t(d)\tIf any part is missing, prior to further flight, replace the outer pin, inner pin, and all associated retention devices on the affected side of the horizontal stabilizer, in accordance with the procedures described in Boeing 737 Maintenance Manual. \n\n\t(e)\tWithin 24 hours after completion of the inspection required by this AD, submit a report of any finding(s) of discrepancies to the Manager, Seattle Manufacturing Inspection District Office, ANM-108S, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (206) 227-1181. 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.) andhave been assigned OMB Control Number 2120-0056. \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, Seattle 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, Seattle ACO.\n \n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle 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)\tThis amendment becomes effective on October 14, 1993, to all persons except those persons to whom it was made immediately effective by telegraphic AD T93-17-51, issued on August 27, 1993, whichcontained the requirements of this amendment.
79-25-01: 79-25-01 MCDONNELL DOUGLAS: Amendment 39-3627 as amended by Amendment 39-3702. Applies to McDonnell Douglas Model DC-10-10, -10F, -30, -30F, and -40 series airplanes certificated in all categories. \n\n\tCompliance required as indicated, unless already accomplished. \n\n\tTo preclude contamination from preventing proper operation of the AiResearch Positive Pressure Relief Valves, accomplish the following: \n\n\t(1)\tWithin the next 300 hours time in service after the effective date of this AD, \n\n\t\t(a)\tModify and reidentify the AiResearch P/N 103506-2 cabin pressure relief valves by the addition of an improved filter in accordance with Douglas Service Bulletin 21-87 dated December 3, 1975 (AiResearch Service Bulletin 103506-21-2271, Revision #1, dated May 15, 1979) or AiResearch Service Bulletin 103506-21-2307, dated June 15, 1978 immediately following cleaning of the valve metering system in accordance with Douglas Service Bulletin A21-103, Revision 1, dated August 7, 1978; or(b)\tUnless already accomplished within the preceding 3,000 flight-hours prior to the effective date of this AD, \n\n\t\t\t(i)\tDisassemble, clean and reassemble the AiResearch P/N 103506-2 cabin pressure relief valves metering systems and adjust/test valves in accordance with Douglas Service Bulletin A21-103, Revision 1, dated August 7, 1978; or \n\n\t\t\t(ii)\tReplace the AiResearch P/N 103506-2 cabin positive pressure relief valves with P/N 103506-2 valves having clean metering systems and test valves in accordance with Douglas Service Bulletin A21-103, Revision 1, dated August 7, 1978. \n\n\t(2)\tIf paragraph (1)(a) above is accomplished, at intervals not to exceed 8,000 hours' time in service thereafter, change the relief valve filter elements and functionally check per the maintenance manual. For airplanes with relief valve filters installed per paragraph (1)(a) of this AD, with total filter time in service of 8,000 or more hours on January 7, 1980; within the next 1,000 hours' time in service after January 7, 1980, and thereafter, at intervals not to exceed 8,000 hours' time in service change the relief valve filter elements and functionally check the valve per the maintenance manual. \n\n\t(3)\tUnless paragraph (1)(a) is accomplished, paragraph (1)(b)(i) or (1)(b)(ii) must be accomplished within 3,000 hour intervals since previous accomplishment, and the original delivery design positive pressure relief valve filter elements must be changed per the Maintenance Manual within 1,500 hour intervals since previous accomplishment. \n\n\t(4)\tIf AiResearch P/N 103624-1 or -2 cabin positive pressure relief valves are installed, prior to the accumulation of 8,000 hours' time in service on the relief valve filter elements, and at intervals not to exceed 8,000 hours' time in service thereafter, change the relief valve filter elements and functionally check valve per the maintenance manual. \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 required by this AD. \n\n\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-3627 became effective January 7, 1980. \n\n\tThis Amendment 39-3702 becomes effective March 3, 1980, and was effective earlier to all recipients of telegraphic AD T80WE-1 dated January 4, 1980.
89-08-12 R1: 89-08-12 R1 BOEING: Amendment 39-6187 as revised by Amendment 39-6462. Docket No. 89-NM-128-AD. \n\n\tApplicability: Model 737-200, -300, and -400 series airplanes, as listed in Boeing Service Bulletin 737-26-1063, dated May 18, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo reduce the potential for dispatching an airplane with an inoperative fire/overheat system, accomplish the following: \n\n\tA.\tWithin 10 days after April 24, 1989 (effective date of Amendment 39-6187), inspect the engine fire/overheat detection module to determine the part number. \n\n\t\t1.\tIf part number 10-61096-41, -71, -81, -91, -92, or 10-62061-1, -2, -3, - 11, or -12 is installed, add the following Engine Fire Detection System Test Procedure to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM: \n\n\t\t\ta.\tPrior to engine start, accomplish fire/overheat warning system test. \n\n\t\t\tb.\tAfter engine start, and with the electrical power supply system in the flight configuration, accomplish the fire/overheat warning system test. \n\n\t\t\tc.\tIn the event of an electrical power supply configuration change in flight (e.g., generator failure), perform the fire/overheat warning system test. In the event that this test is unsuccessful, land at the nearest suitable airport. \n\n\t\t2.\tIf part numbers other than those listed in paragraph A.1., above, are installed, no further action is required. \n\n\tB.\tWithin 120 days after the effective date of this amendment, modify the engine fire/overheat detection module, in accordance with Boeing Service Bulletin 737-26-1063 dated May 18, 1989. Once this modification is accomplished, the limitation required by paragraph A.1., above, may be removed from the AFM. \n\n\tC.\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\tD.\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 AD revises AD 89-08-12, Amendment 39-6187. \n\tThis amendment (39-6462, AD 89-08-12 R1) becomes effective on February 12, 1990.
99-02-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires installation of a rubber strip and replacement of connection sheets and the seal retainer on the avionics compartment access door with new parts; and installation of drip pans and additional drain gutters on the avionics racks. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the trickling of water into the avionics compartment, which could result in avionics computer and equipment malfunctions.
2010-23-27: 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: An A340-642 operator reported [fault messages "Main Fuel Pump 4'' and "Eng 4 Stall/Surge''] * * * and finally the engine had an auto shutdown [along] with [fault message "Engine 4 Fail''] * * *. * * * * * Simultaneous loss of at least two Main Pumps along with other potential failures related to the in-service event may lead to a dual engine loss. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
87-17-03: 87-17-03 MCDONNELL DOUGLAS: Amendment 39-5704. Applies to McDonnell Douglas Model DC-9-81, -82, and -83 series airplanes, fuselage numbers 909 through 1208, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude the potential of main landing gear wheel assembly separation from the airplane, accomplish the following: \n\n\tA.\tWithin 6 months after the effective date of this AD, inspect the main landing gear axle nut retainer in accordance with the accomplishment instructions of McDonnell Douglas Corporation Alert Service Bulletin A32-206 Revision 1, dated July 18, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. Any retainer assembly found to be improperly installed must be replaced prior to further flight, in accordance with the service bulletin. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles 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 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective September 13, 1987.
86-05-06: 86-05-06 BOEING: Amendment 39-5244. Applies to all Model 757-200 series airplanes listed in Boeing Service Bulletin 757-27-0057, Revision 1, dated October 17, 1985, certificated in any category. \n\n\tTo eliminate the possibility of the elevator forward override mechanism becoming jammed, accomplish the following, unless already accomplished: \n\n\tA.\tWithin the next 60 days after the effective date of this AD, remove and replace the elevator control forward override assembly cam with a revised cam in accordance with Boeing Service Bulletin 757-27-0057, Revision 1, dated October 17, 1985, or later FAA- approved revision. \n\n\tB.\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 modifications required by this AD. \n\n\tAll persons affected by this proposal who have not already received 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 April 10, 1986.