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58-15-01: 58-15-01 DOUGLAS: Applies to DC-6 and DC-7 Series Aircraft. \n\n\tCompliance required by September 1, 1958. \n\n\tHook assemblies, P/N CSS1000-D, installed in safety belt assemblies, P/N 5610175, have been found to be understrength due to improper heat treat by the vendor. \n\n\tAll DC-6 and DC-7 Series aircraft equipped with these safety belt assemblies that were manufactured during the months of December 1957, January 1958, and February 1958, are affected. These belts can be identified by the manufacturing date (month and year) stamped on the part number tag sewn on the belt (i.e., date manufactured, December 1957, etc.). Belt assemblies manufactured prior to these dates are satisfactory and all future DC-6 and DC-7 aircraft will have safety belts with proper hook assemblies installed. \n\n\tAll hook assemblies that give a Rockwell reading of 36 or above on the "C" scale are satisfactory. Those that show a Rockwell reading below 36 are unsatisfactory and the belt must be replaced.(Douglas Alert Service Bulletin A-779 for the DC-6 Series and A-321 for the DC-7 Series cover the above subject and describe acceptable inspection and replacement procedures.)
69-11-02: 69-11-02 BELL: Amdt. 39-769. Applies to Bell Model 206A Helicopters, Serial Numbers 4 through 408, having the cyclic stick balance spring installed. Compliance required prior to the next flight after the effective date of this AD, unless already accomplished. To prevent a possible restriction of the cyclic control system, accomplish the following one time inspection and readjustment, if necessary: A. Remove the co-pilot's seat, P/N 206-031-141, to expose the cyclic control left pivot and yoke. B. Inspect and readjust, if necessary, the balance spring clip, P/N 206-001-391, for proper mounting on the yoke, left hand, P/N 206-001-322, in accordance with paragraph (C) below. C. The clip, P/N 206-001-391, must be mounted on the left hand outboard side of the clevis of the yoke, P/N 206-001-322, with the .38 by .16 inch tang of the clip against the top surface of the yoke pointing inboard. (Figure 1 in Bell Helicopter Company Service Letter No. 206A-104, Revision B, dated January 17, 1969, and Bell Helicopter Company information letter dated May 16, 1969, pertain to this subject). This amendment becomes effective to all known owners of Bell Model 206A Helicopters upon receipt of this AD and to all others on May 28, 1969.
52-07-01: 52-07-01 BELL: Applies to All Model 47D1 Helicopters Prior to Serial Number 477. Compliance required by May 15, 1952. To provide simplified loading limitations, remove the existing loading chart decal from the left side of the instrument panel and install loading limitation decal 47-796-109-1 at the same location. In addition, provide stowage space and install the fuel tank dip stick 47-686-205. (Bell Service Bulletin No. 86 covers this same subject.)
55-25-01: 55-25-01 BELL: Applies to Model 47G Helicopters Below Serial Number 1450 Which Have Hydraulic Boost System Installed. Compliance required as soon as practical but not later than January 15, 1956. The manufacturer advises that the lateral cyclic bellcrank, P/N 47-725-073-1 attachment bolt P/N AN 174-34 is too short, positioning the threaded area in the forward lateral bellcrank support bracket hole, which may result in the threads flattening out and elongating the support bracket bolt hole. It is therefore requested that the bolt holes in the bellcrank support bracket be inspected for elongation and the bolt replaced with a longer bolt. If the bolt holes are found elongated beyond permissible tolerance (maximum hole diameter of 0.2520 inch) doubler plates must be added. Redrill and line ream new holes. Replace the AN 174-34 bolt with a new longer bolt P/N AN 174-35, unless doubler plates are added, in which case install AN 174-36 bolts. (Bell's Mandatory Service Bulletin No. 104, dated November 11, 1955, covers this same subject.)
67-29-03: 67-29-03 FAIRCHILD-HILLER: Amdt. 39-499 Part 39 Federal Register October 25, 1967. Applies to all F-27J and FH-227 aircraft with installed Solar Auxiliary Power Unit Model T-62T-25, Serial Nos. S-408000 to S-408099 inclusive. Compliance required as indicated unless already accomplished, or unless APU is rendered electrically inoperative and APU controls are placarded to prohibit operation. To provide adequate APU fire detection system reliability and sensitivity, accomplish the following modifications: (a) Within the next 100 operational APU hours following the effective date of this AD, install an additional fire detector, Solar P/N 7447-2, (set at 400 25 degrees F) in accordance with Fairchild-Hiller Service Bulletin Nos. F-27-49-4 Revision 3, dated Sept. 25, 1967 or FH-227-49-4 Revision 3 dated Sept. 25, 1967 as applicable, or later FAA approved revision, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Within the next 100 operational APU hours following the effective date of this AD, install MIL-W-25038B fire resistant wire in the fire detection circuit in accordance with Fairchild-Hiller Service Bulletin Nos. F27-49-6 dated July 10, 1967 or FH227-49-6 dated July 10, 1967 as applicable, or later FAA-approved revision, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Within the next 200 operational APU hours following the effective date of this AD, replace the two existing 700 degree fire detectors, Solar P/N 7447-1 with two 400 + 25 degree F Fire detectors Solar P/N 7447-2. NOTE. - Compliance with paragraph (c) may be accomplished by arranging for the detector manufacturer, Fenwal, Inc. of 900 Main Street, Ashland, Massachusetts 01721, Solar P/N 7447-1 with two 400+25 degree F fire and reidentify the detector by P/N 7447-2. (d) Upon the effective date of this AD, APU operational hours will belogged until such time as the entire AD has been complied with. This amendment effective October 27, 1967.
53-12-02: 53-12-02 de HAVILLAND: Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 451 Inclusive. Compliance required as indicated. Cases have been reported of loss of seals in the flap hydraulic hand pump No. 430RDH. To prevent the above condition a modification (No. 2/926) was incorporated on production aircraft and should be incorporated on aircraft in service as soon as possible but not later than the next 100 hours. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet, Series B, No. 63 dated March 19, 1953, available from de Havilland Aircraft of Canada, Ltd., Toronto, Ontario, Canada, covers this same subject and describes method of repair.)
70-16-09: 70-16-09 AIRESEARCH: Amdt. 39-1064. Applies to Model TPE331-3W-301A engines, S/N P01001 through P-01010 and P-01012, P-01014, and P-01015, installed in but not limited to Handley-Page Model C10A aircraft. This directive necessary because of a serious condition which may be caused by backing off of the high speed pinion retaining nut. To prevent engine failures from this cause, the following is required: Replace the high speed pinion assembly P/N 869441-2 in accordance with AiResearch telegraphic service bulletin No. 622, dated July 24, 1970, or later FAA approved revision, prior to further use. This amendment is effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated July 24, 1970.
47-10-19: 47-10-19 LOCKHEED: (Was Mandatory Note 21 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088, Except as Noted. Compliance required not later than 100 hours of operation after June 10, 1947. (a) In each cabin heater installation, relocate and waterproof the fuel solenoid valve and replace and reroute the fuel pump bypass line. (LAC Service Bulletin 49/SB-73 covers this same subject.) (b) In zone 2 of each nacelle, install heat protective shield between propeller feathering line and cowl diaphragm. Applies to all serials up to and including 2082. (LAC Service Bulletin 49/SB-150 covers this same subject.) (c) In each outboard nacelle main junction box, replace existing mounting nuts (tinnerman) and PK screws with AN 366 nuts and NAS 221 screws. (LAC Service Bulletin 49/SB-152 covers this same subject.) (d) Drill one 1/4-inch drain hole on lower center line of spinner fairing lower panel assembly for each engine. (LAC Service Instruction 49/SI-95 covers this same subject.)
50-13-01: 50-13-01 CONVAIR: Applies to All Model 240 Aircraft. Compliance required as indicated. Failures of the wing portion of the aileron hinge brackets and bracket supports have been experienced on Convair Model 240 aircraft. These failures have been the result of excessive lateral vibration of the ailerons experienced mainly during engine operation between 1,000 to 1,200 r.p.m., in aircraft incorporating Hamilton Standard propellers. In order to preclude the possibility of these failures progressing to such a state that the airworthiness of the airplane is impaired, it is considered necessary that the following be accomplished on Convair Model 240 Series aircraft: A. To be accomplished on all individual CV-240 Series aircraft incorporating Hamilton Standard propellers at every No. 2 operation, until part B, is accomplished. Inspect the aileron in area of hinge brackets, aileron hinge brackets and bracket supports with a 10-power glass, for signs of fatigue cracking. Special attention should be paid to the areas around the rivet holes utilized for attaching the brackets to the bracket supports and to that portion of the bracket supports in the areas at which the bracket supports extend from the wing trailing edge structure. Any failed parts should be adequately repaired or replaced prior to the next flight. B. To be accomplished by January 1, 1951, on airplanes incorporating Hamilton Standard propellers. Incorporate steel aileron hinge brackets and incorporate measures to increase the lateral rigidity of the wing portion of the aileron hinges. (CVAC Service Bulletin 240-289 covers this same subject.)
65-13-06: 65-13-06 LOCKHEED: Amdt. 39-88 Part 39 Federal Register June 23, 1965. Applies to Models 1049C, 1049D, 1049E, 1049G, and 1049H Series aircraft. Compliance required as indicated. To detect cracked beam cap tie-in fittings, accomplish the following: (a) Inspect the beam cap tie-in fittings, Lockheed P/N's 311134L and 311134R, on the upper forward face of the rear spar at Wing Stations 80L and 80R for cracks in the area of the 0.16 inch radius near the center of the fitting, using dye penetrant or an FAA-approved equivalent as specified in (b) or (c) as applicable. (b) Inspect fittings with 20,000 or more hours' time in service on the effective date of this AD in accordance with (a) within the next 350 hours' time in service unless already accomplished within the last 3,150 hours' time in service, and at intervals thereafter not to exceed 3,500 hours' time in service from the last inspection. (c) Inspect fittings with less than 20,000 hours' time in service on the effective date of this AD in accordance with (a) within 350 hours' time in service after the effective date of this AD unless already accomplished, and - (1) If the fittings had 16,850 or more hours' time in service at the time of the inspection, reinspect at intervals not to exceed 3,500 hours' time in service from the last inspection; (2) If the fittings has less than 16,850 hours' time in service at the time of the inspection, reinspect before the accumulation of 20,350 hours' time in service and at intervals thereafter not to exceed 3,500 hours' time in service from the last inspection. (d) Replace any fitting found cracked with a new fitting of the same part number before further flight. (e) Operators who have not kept records of hours' time in service on individual fittings shall substitute airplane hours' time in service in lieu thereof. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This supersedes AD 64-06-05. This directive effective July 23, 1965.