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95-26-15: This document publishes in the Federal Register an amendment adopting an airworthiness directive that was sent previously by individual letters to all known U.S. owners and operators of various transport category airplanes equipped with Allied Signal Commercial Avionics Systems CAS-81 TCAS. This amendment is prompted by reports of failure of the audio output of the CAS-81 TCAS. This AD requires a revision to the Airplane Flight Manual to provide the flightcrew with procedures to cycle power to the TCAS processor via the circuit breaker or power bus, and to perform a TCAS functional test to verify proper operation of the TCAS. The actions specified by this AD are intended to ensure that the flightcrew is advised of the potential hazard associated with failure of the audio output of the CAS-81 TCAS, and of the procedures necessary to address it.
72-03-07: 72-03-07 CESSNA: Amdt. 39-1391. Applies to Models 310 (Serial Numbers 310Q0074 through 310Q0425, except 310Q0261, 0271, 0279, 0402, 0409, 0411, 0416, 0420, 0424); Models 340 (Serial Numbers 340-0001 through 340-0009, except 340-0005); Models 401 (Serial Numbers 401B0029 through 401B0204); Models 402 (Serial Numbers 402B0007 through 402B0201); Models 414 (Serial Numbers 414-0052 through 414-0173, except 414-0152, 0153, 0168, 0172); and Models 421 (Serial Numbers 421B0001 through 421B0209, except 421B0144, 0201, 0205, 0208); and all other 300 and 400 series airplanes which may have the original barrel assemblies replaced with new or used assemblies shipped by the manufacturer between January 1, 1970, and December 15, 1971. Compliance: Required as indicated, unless already accomplished. To prevent landing gear failure accomplish the following in accordance with Cessna Service Letter ME71-28 dated December 24, 1971, and Supplement No. 1 dated January 28, 1972, or any equivalent methods approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region: A) Within the next 5 hours' time in service after the effective date of this AD, visually inspect barrel assemblies of the main landing gear upper struts for hydraulic leaks and surface cracks. If such discrepancies are noted, prior to further flight, replace the appropriate barrel assemblies. B) To accomplish the inspection required by Paragraph A the airplane may be flown in accordance with FAR 21.197 to a base where the inspection may be performed. C) Within the next 25 hours' time in service after the effective date of this AD, conduct chemical tests to determine if barrel assemblies of the main landing gear upper struts are composed of dissimilar or incorrect metals. If such discrepancies are noted, prior to further flight, replace with appropriate and correct barrel assemblies. D) Report all defects found in complying with this AD. Such reports must be made in writing and sent to Chief, Engineering and Manufacturing Branch, FAA, Central Region, and should include such items as aircraft serial number, total time in service and nature of defect. (Report approved by the Bureau of the Budget under BOB No. 04-R0174.) This amendment becomes effective February 9, 1972.
92-16-02: 92-16-02 BOEING: Amendment 39-8311. Docket No. 92-NM-119-AD. Supersedes AD 92-06-13, Amendment 39-8193. \n\n\tApplicability: Model 767 series airplanes equipped with General Electric CF6-80C2 engines, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent inadvertent deployment of a thrust reverser during flight, accomplish the following: \n\n\t(a)\tFor airplanes listed in Boeing Alert Service Bulletin 767-78A0052, Revision 1, dated February 14, 1992: Within 60 days after March 18, 1992 (the effective date of AD 92-06-13, Amendment 39-8193), revise the wiring in certain panels, the wing-body disconnects, and the wing-strut disconnects, in accordance with Boeing Alert Service Bulletin 767-78A0052, Revision 1, dated February 14, 1992. \n\n\t(b)\tFor airplanes listed in Boeing Alert Service Bulletin 767-78A0052, Revision 2, dated May 28, 1992: Within 60 days after the effective date of this AD, revise the wiring in certain panels, the wing-body disconnects, and the wing-strut disconnects, in accordance with Boeing Alert Service Bulletin 767-78A0052, Revision 2, dated May 28, 1992. Procedures that were accomplished previously in accordance with Revision 1 of the service bulletin, and that have not changed in Revision 2 of the service bulletin, need not be repeated. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, 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 sent 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(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.\n \n\t(e)\tThe modification shall be done in accordance with Boeing Service Bulletin 767-78A0052, Revision 2, dated May 28, 1992, which includes the following list of effective pages: \n\n\nPage Number\nRevision Level\nDate \n1, 3-4, 7-8, 12-14\n2\nMay 28, 1992 \n2, 5, 10\n1\nFebruary 14, 1992 \n6, 9, 11\nOriginal\t\nDecember 10, 1991 \n\t\t\t\t\t\t\t\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. The incorporation by reference of Boeing Service Bulletin 767-78A0052, Revision 1, dated February 14, 1992, was approved previously by the Director of the Federal Register as of March 18, 1992 (57 FR 9381, March 18, 1992). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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(f)\tThis amendment becomes effective on July 27, 1992.
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.