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47-49-04: 47-49-04 LOCKHEED: (Was Mandatory Note 37 of AD-763-3.) Applies to Model 49 Serials 2068 to 2088, Inclusive. Compliance required within next 50 hours of operation unless the 1 3/16-inch headless drive pin has been installed. Inspect attachments of rudder pedal lever arms to the clip assembly in the 284587 rudder pedal slot cover guide assemblies to determine whether it is possible for the flat head pin to cause jamming of the system. If any possibility of jamming exists, the flat head pin should be replaced with a headless drive pin 1 3/16 inches long. (LAC Service Bulletin 49/SB-260 covers this same subject.)
47-06-01: 47-06-01 GLOBE: (Was Service Note 1 of AD 766-5.) Applies to Models GC-1A and GC-1B Aircraft. To be accomplished prior to April 1, 1947, and upon each 100 hours operation thereafter. Inspect main landing gear retraction system to determine that adjustments are as follows: (1) When the side brace is against the down stop the middle joint should be 1/8 inch to 1/4 inch above dead center (3/16 inch to 5/16 inch if measured from edges of links in accordance with Globe Customer Service Maintenance Bulletin No. 7). (2) When the side brace is against the down stop and the down lock plunger is fully extended, covering at least 1/2 of the adjustment screw head, the clearance between the plunger and the screw head should be from 0.001 inch to 0.005 inch. (3) When the side brace is against the down stop the limit switch plunger should be depressed approximately 1/32 inch beyond the cutoff point. (4) The turnbuckle in the emergency extension cable should be adjusted so that on manual extension of the gear both down locks operate before the handcrank has been wound to the full down position. After it has been determined that the turnbuckle adjustment is satisfactory in this respect it should be determined also that with the handcrank wound to the full up position the cable length is sufficient to permit the up limit switches to cut off. (Globe Customer Service Maintenance Bulletin No. 7 covers this same subject.)
47-42-09: 47-42-09 DOUGLAS: (Was Mandatory Note 6 of AD-781-1.) Applies to DC-6 Serial Numbers 42854, 42855, 42858 Through 42865, 42869 Through 42880, 42882 Through 42891, 43000 Through 43009, 43055 and 43056. \n\nTo be accomplished not later than next No. 3 inspection (or not later than next 150 hours for noncarrier operations). \n\nCertain cases have been found where the aileron hinge plates at wing Stations 421, 485, 585, and 675 were fabricated from overgage stock resulting in an interference fit between the plate and the clevis fitting. The following hinge plates and fittings should be inspected to determine whether or not they conform with the tolerances listed below. If plates are found which exceed the widths noted below, they should be reworked with emery cloth to specified limits and touched up with zinc chromate primer. Fittings which have been installed over an oversize plate should be anodized and carefully inspected before being reinstalled. \n\n\n\nHinge\n\n\n\n\nStation\nNo.\nPlate\nThickness\nFitting\nWidth\n421\n1\n3320118\n0.249 \n4334619\n0.249\n\n\n\n0.237\n\n0.254\n485\n2\n3323460\n0.238*\n4345756\n0.334\n\n\n\n0.243\n\n0.350\n585\n3\n3323461\n0.311\n4345755\n0.311\n\n\n\n0.297\n\n0.316\n575\n4\n3323462\n0.249\n4345754\n0.249\n\n\n\n0.237\n\n0.254\n\n*Thickness of 0.093 angle not included.\nTotal thickness should not exceed 0.334. \n\n(Douglas Service Letter A-214-529.004/RLT dated July 21, 1947, and attached sketches cover this same subject.)
47-33-02: 47-33-02\tDOUGLAS: (Was Mandatory Note 14 of AD-618-3, Supplement 2; and Mandatory Note 15 of AD-669-3, Supplement 2.) Applies to All DC3 Series Aircraft. \n\nTo be accomplished not later than the first engine change after September 1, 1947, but in any event not later than December 1, 1947. \n\nIn order to preclude cowl flap hydraulic line failures and possible subsequent fires, replace grommets and lines forward of the firewall with AN 833-4 elbows and AN 924-4 nuts, or equivalent, and new fire resistant flexible hose assemblies of proper length.
47-27-04: 47-27-04 DOUGLAS: (Was Mandatory Note 18 of AD-762-7.) Applies to All C-54 and DC-4 Series Airplanes Having Exhaust Collector Rings Made Up of Top Segments P/N 5174842-56 L.H. and 5174529-56 R.H. \n\n\tTo be accomplished not later than the first engine change subsequent to July 15, 1947, but in any event not later than October 15, 1947. \n\n\tSeveral reports have been received of cracking failure of the collector ring "Y" outlet assembly due to breathing of the exhaust stack. This induces failure which creates a fire hazard. This type of exhaust collector "Y" is not reinforced with a flange and is shown on page 4, Douglas Service Bulletin No. DC-4 No. 31. To correct this condition weld a scalloped stiffener flange on the exhaust collector aft of the "Y" outlet assembly. \n\n\t(Douglas Service Bulletin No. DC-4 No. 68 covers this same subject.) \n\n\tUntil this repair is accomplished, inspection for cracks should be made immediately and at periods not to exceed 50 hours of operation.
47-07-04: 47-07-04 FAIRCHILD: (Was Mandatory Note 6 of AD-724-2.) Applies to M-62 Series Aircraft. Compliance required at next periodic inspection. In order to eliminate the possibility of the control sticks becoming disengaged, both front and rear control sticks should be reworked by drilling through stick and socket, and installing and safetying an AN393-51 clevis pin. Washer AN 960-10L and cotter AN 380-2-2. (Fairchild Service Bulletin 44-62-2 dated October 31, 1944, covers this same subject.)
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.