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47-51-16: 47-51-16 DOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42880, Inclusive; 42882 Through 42891, Inclusive; and 43000 Through 43009, Inclusive; 43055; and 43056. \n\nTo be accomplished not later than August 1, 1948. \n\nIn order to increase the strength of the flap support assembly at wing Station 378 and to replace the temporary rework outlined in Douglas Co. Service Letter of May 12, 1947, which was necessitated by failure of the flap hinge support assembly on an airplane in flight, the following must be accomplished: \n\n(a)\tRemove the two Shafer bearings, P/N AB-4A from flap link assembly, P/N 4325008 and press in new Shafer bearings, P/N AB-5A and stake in place. \n\n(b)\tRemove outboard flap link support assembly, P/N 5107188, and line ream (0.312-0.313) diameter through to permit use of 5/16-inch bolt for attachment of upper end of link assembly, P/N 4325008. Assembly, P/N 5107188 becomes P/N 5107188-500 after rework. \n\n(c)\tPress out old bushing, P/N 1338719, two places in flap hinge bracket assembly, P/N 3320998, and press in new bushings, P/N 1338719-500. \n\n(d)\tAfter replacing P/N 5107188-500 replace P/N 4325008, using bolts, P/N 2356375-22; washers, P/N 124682-5-12-6 and P/N AN 960-516; nut, P/N AN 310-5 and cotter pin, P/N AN 380-2-3. \n\n(Douglas Service Bulletin DC-6 No. 66 covers this same rework.)
93-19-01: 93-19-01 Dowty Rotol (now Dowty Aerospace Gloucester Ltd.): Amendment 39-8694. Docket 93-ANE-10. Supersedes AD 87-21-51, Amendment 39-5929. Applicability: Dowty Rotol (now Dowty Aerospace Gloucester Ltd.) Propeller Models (c)R354/4-123-F/13, (c)R354/4-123-F/20, and (c)R375/4-123-F/21 installed on SAAB-SF340A, and SAAB-SF340B series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent possible loss of the propeller, accomplish the following: (a) For Dowty Rotol (now Dowty Aerospace Gloucester Ltd.) Model (c)R354/4- 123-F/13 propellers, perform Dowty Aerospace Gloucester Ltd. Modification (C) VP3336 by installing interface shim Part Number (P/N) 660712669 in accordance with Dowty Aerospace Gloucester Ltd. Service Bulletin (SB) No. SF340-61-57, dated February 15, 1991, within 500 hours time in service (TIS) since the last torque check and inspections accomplished in accordance with AD 87-21-51. (b) For Dowty Rotol (now Dowty Aerospace Gloucester Ltd.) Model R354/4- 123-F/13 propellers, perform a torque check of the propeller retention bolts for low torque and a magnetic particle inspection of the propeller retention bolts for cracks; perform dye penetrant, ultrasonic, and eddy current inspections of the propeller hub backface for cracks. If propeller retention bolts or hubs are found to have cracks, remove from service prior to further flight, and replace with serviceable propeller retention bolts and hubs, within 500 hours TIS since the last torque check and cracking inspections accomplished in accordance with AD 87-21-51. These actions must be accomplished in accordance with Dowty Aerospace Gloucester Ltd. SB No. SF340-61-58, Revision 1, dated July 18, 1991. (c) For Dowty Rotol (now Dowty Aerospace Gloucester Ltd.) Model (c)R354/4- 123-F/20 and (c)R375/4-123-F/21 propellers, perform Dowty Aerospace Gloucester Ltd. Modification (C) VP3336 by installing interface shim P/N 660712669 in accordancewith Dowty Aerospace Gloucester Ltd. SB No. SF340-61-57, dated February 15, 1991, within 100 hours TIS after the effective date of this AD; or 500 hours TIS since the last torque check and inspections accomplished in accordance with Dowty Aerospace Gloucester Ltd. SB No. SF340-61-58, Revision 1, dated July 18, 1991, or Dowty Aerospace Gloucester Ltd. SB No. SF340-61-21, Revision 4, dated October 1, 1987; or 500 hours TIS since new, whichever occurs latest. (d) For Dowty Rotol (now Dowty Aerospace Gloucester Ltd.) Model (c)R354/4- 123-F/20 and (c)R375/4-123-F/21 propellers, perform a torque check of the propeller retention bolts for low torque; a magnetic particle inspection of the propeller retention bolts for cracks; and dye penetrant, ultrasonic, and eddy current inspections of the propeller hub backface for cracks. Remove from service prior to further flight cracked propeller retention bolts and hubs, and replace with serviceable propeller retention bolts or hubs, within 100 hours TIS after the effective date of this AD; or 500 hours TIS since the last torque check and inspections accomplished in accordance with Dowty Aerospace Gloucester Ltd. SB No. SF340-61-58, Revision 1, dated July 18, 1991, or Dowty Rotol (now Dowty Aerospace Gloucester Ltd.) SB No. SF340-61-21, Revision 4, dated October 1, 1987; or 500 hours TIS since new, whichever occurs latest. These actions must be accomplished in accordance with Dowty Aerospace Gloucester Ltd, SB No. SF340-61-58, Revision 1, dated July 18, 1991. (e) Thereafter, for propeller models identified in paragraphs (a) and (c) of this AD, perform a torque check of the propeller retention bolts for low torque; a magnetic particle inspection of the propeller retention bolts for cracks; and dye penetrant, ultrasonic, and eddy current inspections of the propeller hub backface for cracks. Remove from service prior to further flight cracked propeller retention bolts and hubs, and replace with serviceable propeller retention bolts or hubs at intervals not to exceed 1500 hours TIS since the last torque check and inspections performed in accordance with paragraphs (b) or (d), as applicable, of this AD. These actions must be accomplished in accordance with Dowty Gloucester Aerospace Ltd. SB No. SF340-61-58, Revision 1, dated July 18, 1991. (f) Installation of newly designed Dowty Aerospace Gloucester Ltd. propeller hub assembly P/N 660714241 and remarking of the propeller in accordance with Dowty Aerospace Gloucester Ltd. SB No. SF340-61-61, Revision 1, dated October 19, 1992, constitutes terminating action to the inspection requirements of this AD. (g) 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, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, BostonAircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (h) 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. (i) The inspections shall be done in accordance with the following Dowty Aerospace Gloucester service bulletins: Document No. Pages Revision Date SF340-61-57 1-5 Original February 15, 1991 Total pages: 5. SF340-61-58 1-2 1 July 18, 1991 3-5 Original February 15, 1991 Appendix A 1-3 Original February 15, 1991 Appendix B 1-3 Original February 15, 1991 Appendix C 1-2 1 July 18, 1991 3-4 Original February 15, 1991 Total pages: 15. SF340-61-61 1-3 1 October 19, 1992 4-8 Original September 9, 1992Total pages: 8. 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 Dowty Aerospace Gloucester Ltd., Anson Business Park, Cheltenham Road East, Gloucester GL2 9QN England. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on October 29, 1993.
94-17-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A340-211 and -311 series airplanes. This action requires replacement of certain circuit breakers for the toilet system vacuum generator. This amendment is prompted by reports of excessive vacuum generator overloads or blocked rotor conditions, in which the thermal protection device and/or related aircraft circuit breakers do not interrupt the power supply. The actions specified in this AD are intended to prevent a fire in the event of excessive current in the electrical circuit due to overheating of the vacuum generator.
95-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Model A320-231 series airplanes, that requires repetitive functional checks to detect leakage of the distribution piping of the engine fire extinguishing system, and repair, if necessary; and modification of the piping, which would terminate the inspection requirements. This amendment is prompted by reports of cracking of the engine fire extinguisher pipe, which resulted in leakage of the fire extinguisher agent. The actions specified by this AD are intended to prevent leakage of the fire extinguishing agent, which could prevent the proper distribution of the agent within the nacelle in the event of a fire.
95-24-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada (BHT), Model 206B and 206L helicopters, that currently requires a revision to the Limitations section of the FAA-approved Supplemental Type Certificate (STC) Rotorcraft Flight Manual Supplement (RFMS) until replacement of the engine power-out warning sensor on BHT Model 206B and 206L helicopters equipped with Allison 250-C20R engines in accordance with certain supplemental type certificates. This amendment requires a revision to the Limitations section of the STC RFMS, but removes the requirement for replacement of the engine power-out warning sensor. This amendment is prompted by a reevaluation of the need for an engine power-out warning sensor based on the lack of reported operational occurrences of the false engine-out warnings. The actions specified by this AD are intended to maintain a heightened pilot awareness that false engine-out warnings may occur when practicing autorotations and could result in an unnecessary emergency autorotative landing.
91-10-05: 91-10-05 O2 CORPORATION (FRANK MCGOWAN CO.): Amendment 39-6989. Docket No. 90-CE-43-AD. Applicability: The following Mask Presentation Unit Part Numbers that are installed on, but not limited to, British Aerospace 125-800A airplanes; Challenger CL600-1A11, CL600-2B16, and CL600-2A12 airplanes; Gulfstream G-1159, G-1159A, G-1159B, and G-IV airplanes; and Falcon 20 airplanes, certificated in any category: 121-040-04 150-004-03 151-020 150-002 150-004-04 151-020-02 150-002-01 150-004-05 151-020-04 150-002-02 150-004-06 152-001 150-002-03 150-004-07 152-001-01 150-002-04 150-004-08 152-001-04 150-002-05 150-004-12 152-001-05 150-002-08 150-005 152-001-08 150-003T 150-006 152-001-13 150-003-04T 150-022 152-003 150-004 151-010 152-004 150-004-01 151-010-02 152-004-05 150-004-02 151-010-04 Compliance: Required within the next 3 calendar months after the effective date of this AD, unless already accomplished. To prevent malfunctioning of the lanyard release pin that could prevent the flow of oxygen to a passenger in an emergency situation, accomplish the following: (a) With the oxygen system activated, perform a test of the lanyard release pins by accomplishing the following: (1) Open the passenger mask presentation units of the airplane and allow the mask assemblies to drop out. (2) Make up a 7.5 pound weight with an attached string and hook, (e.g., spring, clip, etc.). (3) Attach the hook to the lanyard attaching point of each actuator pin without dropping the weight and allow the weight to hang from the lanyard attaching point. (b) If the pin pulls free from the oxygen actuator valve at 7.5 pounds or less of hanging weight, then the pin is satisfactory and the unit may be returned to service. (c) If the pin does not pull free from the oxygen actuator valve using the test required by paragraph (a) of this AD, prior to further flight accomplish the following:(1) Replace the pin with either part number 100-111-2 or 100-111-3, which has a 20-degree angle and a rounded nose. NOTE 1: The pin is available from the manufacturer by contacting Mr. Burt Parry, O2 Corporation, 3522 N. Comotara, Wichita, Kansas 67226; Telephone (316) 634-1240; Facsimile (316) 634-1061. (2) Test the replacement pin installation in accordance with the test requirements of paragraph (a) of this AD to assure that the lanyard pin can be removed with a pull of 7.5 pounds or less. If the pin pulls free from the oxygen actuator valve at 7.5 pounds or less of hanging weight, then the pin is satisfactory and the unit may be returned to service. (d) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; Telephone (316) 946-4419. The request should be forwardedthrough an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (e) All persons affected by this directive may obtain copies of any information that is applicable to this AD from the FAA, Central Region, Office of the Assistant Chief Counsel, Attention: Rules Docket No. 90-CE-43-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Replacement parts that might be needed to complete the actions of this AD may be obtained from Mr. Burt Parry, O2 Corporation, 3522 N. Comotara, Wichita, Kansas 67226; Telephone (316) 634-1240; Facsimile (316) 634-1061. This amendment (39-6989, AD 91-10-05) becomes effective on June 3, 1991.
81-22-01: 81-22-01 McDONNELL DOUGLAS: Amendment 39-4244. Applies to all McDonnell Douglas Model DC-9-80 Series airplanes, certificated in all categories. \n\n\tCompliance required as indicated in the body of this AD, unless previously accomplished. To prevent failure of the slat drive mechanism, accomplish the following: \n\n\tA.\tUpon the accumulation of 600 landings, or within the next 200 landings after the effective date of this AD, whichever occurs later perform a one-time inspection of the slat control valve assembly to verify "correct" flow direction installation of check valves and restrictors as shown on Douglas Service Sketch 3303 of Douglas DC-9 Super 80 Alert Service Bulletin A27-225, Revision 1, dated September 22, 1981, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA, Northwest Mountain Region. Correct the installation of check valve/restrictor if necessary. \n\n\tNOTE: Directional arrow on restrictors and check valves may be in a position requiring additional visual aids to view. \n\n\tB.\tIf slat control valve assembly check valves and restrictors are installed properly, no further action is required. \n\n\tC.\tIf slat control valve assembly check valves and/or restrictors were improperly installed, accomplish the following in accordance with Douglas DC-9 Super 80 Alert Service Bulletin A27-225, Revision 1, dated September 22, 1981, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region, unless already accomplished: \n\n\t\t1.\tPerform dye penetrant or eddy current inspections of the slat drive cylinder support brackets per Paragraph 2.E of the service bulletin. \n\n\t\t2.\tConduct a visual inspection of the slat drive mechanism per Paragraph 2.F of the service bulletin. \n\n\t\t3.\tIf no cracks or other indications of distress are detected, conduct repetitive inspections per Paragraph 2.G of the service bulletin, at intervals not to exceed 350 landings.4.\tIf cracked or failed support brackets or other indications of distress in the slat drive mechanism are detected, remove the slat drive mechanism per Paragraph 2.H of the service bulletin. \n\n\t\t5.\tReplace cracked support brackets per Paragraph 2.I of the service bulletin. \n\n\t\t6.\tIf a slat drive cylinder support bracket is failed, or other indications of distress are detected, accomplish the following: \n\n\t\t\ta.\tInspect and repair per the instructions of paragraph 2.J(1) of the service bulletin. \n\n\t\t\tb.\tInspect wing spar per the instructions of paragraph 2.J(2) of the service bulletin. \n\n\t\t7.\tIf inspection of the wing spar reveals any indication of damage, repair in a manner approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\t\t8.\tInstall repaired slat drive mechanism per the installation instructions of Paragraph 2.K of the service bulletin. \n\n\t\t9.\tFor slat drive mechanisms which have not had both slat drive support cylinder support brackets replaced, conduct repetitive inspections per paragraph C.3 of this AD. \n\n\t\t10.\tInstallation of new slat drive cylinder support brackets terminates the requirements for repetitive inspections per this AD. \n\n\tD.\tSpecial flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate airplanes to a base in order to comply with the inspection requirements of this AD. \n\n\tE.\tIf the number of landings on an aircraft is not known, for the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing the airplane's hours time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tF.\tAlternative means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof 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 upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 4344 Donald Douglas Drive, Long Beach, California 90808. \n\n\tThis amendment becomes effective November 5, 1981.
77-22-04: 77-22-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (S.N.I.A.S.): Amendment 39-3068. Applies to Models SA341G "Gazelle" helicopters, certificated in all categories, equipped with any of the following landing gear: Low-skid, low-frequency landing gear P/Ns 341A.41.5200.00 to .04 not incorporating Mod. AMS 07.1349/S.371. P/Ns 341A.41.5200.05 to .11 incorporating Mod. AMS 07.1349 but not incorporating Mod. AMS 07.1578/S.440. High-skid, low-frequency landing gear P/N 341A.41.5300.00 not incorporating Mod. AMS 07.1350. P/Ns 341A.41.5300.01 to .11 incorporating Mod. AMS 07.1350 but not incorporating Mod. AMS 07.1579. Compliance is required within the next 500 hours time in service after the effective date of this AD, but not later than January 31, 1978, unless already accomplished. To prevent possible excessive corrosion remove the landing gear, inspect for corrosion, and if corrosion is found, replace, or turn 180 degrees and thereafter replace, the landing gear members, as necessary and reinstall all in accordance with Paragraph C of "Gazelle" Service Bulletin No. 01.10 dated September 12, 1975, revised December 13, 1976 and the Models SA341G "Gazelle" Repair Manual or an FAA approved equivalent. This Amendment becomes effective November 28, 1977.
84-09-02: 84-09-02 AIRBUS INDUSTRIE: Amendment 39-4853. Applies to Model A300 B2 and B4 series airplanes, certificated in all categories. Compliance is required within the next 750 hours time in service after the effective date of this AD, unless already accomplished. To prevent breakage of the fuel and hydraulic line attaching clamps in the engine pylons, which could result in line breakage and a consequent fire hazard, accomplish the following: A. Remove the existing fuel and hydraulic line attaching clamps and brackets, and install new reinforced teflon-lined clamps and redesigned brackets in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Airbus Industrie Service Bulletin A300-54-007, Revision 5, dated December 22, 1978. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special 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. This amendment becomes effective June 1, 1984.
86-04-08: 86-04-08 BOEING: Amendment 39-5238. Applies to Model 767 series airplanes, as specified in Boeing Service Bulletin 767-52-0029 dated August 2, 1985, certificated in any category. \n\n\tTo assure proper entry/service door operation during emergency evacuation, accomplish the following within nine months after the effective date of this AD, unless previously accomplished: \n\n\tA.\tModify the counterbalance gearbox assemblies in accordance with Boeing Service Bulletin 767-52-0029 dated August 2, 1985, or later FAA-approved revisions. \n\n\tB.\tAn alternate means of compliance 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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this proposal who have not alreadyreceived copies of the manufacturer's service bulletin may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. 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 March 27, 1986.