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2001-25-04: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) Models LTS101-600A-2 and LTS101-600A-3 turboshaft engines; and LTP101-600A-1A and LTP101-700A-1A turboprop engines. This amendment requires replacing certain fuel controls that have beryllium-copper bellows with improved fuel controls that incorporate Inconel 718 stainless steel welded bellows. This amendment is prompted by a report of an uncommanded power loss on a Textron Lycoming LTS101 engine due to a corrosion damaged fuel control bellows. The actions specified by this AD are intended to prevent the engine from reducing the fuel flow to minimum flow resulting in an uncommanded power loss.
2001-24-32: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200B, 747-200C, 747-200F, 747SP, and 747SR series airplanes. This AD requires a one-time inspection for chafing of certain wire bundles behind the flight engineer's panel; repairs, if necessary; and a modification to reroute a certain electrical wire bundle to ensure sufficient clearance between that wire bundle and an adjacent flood light support bracket. This action is necessary to prevent chafing of certain electrical wire bundles, which could result in smoke in the cockpit, and uncommanded discharge of fire extinguishing bottles for the No. 4 engine and consequent reduction of the ability to fight a fire in the No. 4 engine. This action is intended to address the identified unsafe condition.
51-16-01: 51-16-01\tBELLANCA: Applies to All Models 14-13 and 14-13-2 Airplanes. \n\n\tCompliance required within the next 25 hours of operation, but not later than August 1, 1951. \n\n\tAs a result of a recent failure of the elevator trim tab in flight, the modification of the trim tab attachment to the elevator as shown in Figure 1 should be made. \n\n\n\n\nFIGURE 1 \n\n\t(Bellanca Service Bulletin No. 14, Models 14-13 and 14-13-2, covers this same subject.)
66-01-03: 66-01-03 PILATUS: Amdt. 39-173, Part 39, Federal Register December 24, 1965. Applies to Model PC-6 Series Airplanes, Serial Numbers 515, 522, and 524 through 580. Compliance required as indicated, unless already accomplished. To prevent further instances of fuel flow restriction, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, inspect fuel shutoff valve P/N 321-ITX 6D for correct installation of the valve plug in accordance with Pilatus Service Bulletin No. 36, dated September 1965, or later Swiss Federal Air Office- approved revision. If the valve plug protrudes more than 2mm. (0.078 inch), before further flight, replace the valve with a new valve P/N 6238.124. (b) Within the next 60 hours' time in service after the effective date of this AD, replace fuel shutoff valve P/N 321-ITX 6D with a new valve P/N 6238.124, in accordance with Pilatus Service Bulletin No. 36, dated September 1965, or later Swiss Federal Air Office- approved revision.
69-19-06: 69-19-06 GENERAL DYNAMICS: Amdt. 39-842. Applies to all Model 22 Aircraft equipped with axle beam P/N 9729-68-1 and Model 22M Aircraft equipped with axle beam P/N 1057-68-1. Compliance required within the next 2000 hours' time in service after the effective date of this AD or before the accumulation of 9000 hours' total time in service, whichever occurs later, unless already accomplished. Several failures of the main landing gear axle beam have been attributed to cracks originating near the center jack pad on the beam lower surface. The crack then progresses upward until complete failure of the beam occurs at a point above the axle beam pivot pin. The initial crack in the beam develops due to stress corrosion or hydrogen embrittlement. To prevent further failures of this nature, accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (a) Inspect and rework each Model 22 Aircraft axle beam assembly P/N 9729-68-1 in accordance with General Dynamics/Convair 880 Service Bulletin Number 32-87, dated February 7, 1966, (or later FAA approved revision), and each Model 22M Aircraft axle beam assembly P/N 1057-68-1 in accordance with General Dynamics/Convair 880M Service Bulletin Number 32-56, dated February 7, 1966, (or later FAA approved revision). (b) Removal of beam material extending below .006 inch depth from the original beam surface will require individual evaluation by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective October 18, 1969.
70-05-06: 70-05-06 HARTZELL PROPELLERS: Amdt. 39-954. Applies to Hartzell T10176( ) and T10176H( ) type blades installed on Hartzell HC-B3TN-5C series propellers used on AiResearch TPE331-( ) type engines. Compliance required as indicated, unless already accomplished. a. Propellers with 700 or more total hours in service, inspect in accordance with paragraphs (c) and (d) within the next 50 hours after the effective date of this AD, and reinspect in accordance with paragraph (c) every 1500 hours in service from the last inspection. b. Propellers with less than 700 total hours in service inspect in accordance with paragraphs (c) and (d) prior to the accumulation of 750 hours in service and reinspect in accordance with paragraph (c) every 1500 hours in service from the last inspection. c. Remove the blades from the propeller and the smaller needle bearing from the bottom of the blade pilot tube hole. In accordance with Hartzell Bulletin No. 95 dated 7 January 1970, or FAA approved equivalent procedure, clean and inspect the inner surface of the pilot tube hole for cracks by dye penetrant method and visually inspect for scratches, gouges or tool marks in the area of minimum wall thickness. Replace before further flight any cracked blade or blade having scratches, gouges, or tool marks in the critical radius with a blade which has been inspected in accordance with this AD and found satisfactory. d. Inspect the blade for minimum wall thickness in the shank area in accordance with Hartzell Bulletin No. 95 dated 7 January 1970. Replace before further flight any blade having a wall thickness less than that noted in Bulletin No. 95 with a blade inspected in accordance with this AD and found satisfactory. e. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust repetitive inspection intervals specified in this AD. (Hartzell Bulletin No. 95 dated7 January 1970 and Manual 118A cover this subject.) This amendment is effective March 11, 1970.
67-30-02: 67-30-02 BRITISH AIRCRAFT: Amdt. 39-507, Part 39, Federal Register November 4, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes which incorporate Modification PM 1558 part (c). Compliance required as indicated unless already accomplished. To prevent fatigue damage of the lower sidestay pin retaining bolt, P/N AC43-267, accomplish the following: (a) Within the next 200 landings after the effective date of this AD or before the accumulation of 5,000 landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings from the last inspection, inspect the main landing gear lower sidestay retaining bolts, P/N AC43-267, for cracks, using the magnetic particle procedure or an FAA-approved equivalent, in accordance with British Aircraft Corporation BAC 1-11 Alert Service Bulletin 32- A-PM 2898, Issue 1, dated April 14, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (b) If defective retaining bolts, P/N AC43-267, are found during the inspection required by paragraph (a), before further flight replace the bolts with serviceable bolts of the same part number or new bolts, P/N AC43-399, in accordance with BAC 1-11 Service Bulletin No. 32-PM 2898 Revision 1, dated April 10, 1967, or later ARB-approved issue, or an FAA- approved equivalent. (c) Before the accumulation of 15,000 landings, replace retaining bolts, P/N AC43- 267, with serviceable bolts of the same part number or new bolts, P/N AC43-399. If bolts P/N AC43-267 are used as replacement bolts, inspect the bolts at intervals not to exceed 5,000 landings in accordance with paragraph (a) and replace the bolts at intervals not to exceed 15,000 landings. (d) The repetitive inspections and replacements required by paragraphs (a) and (c) may be discontinued after the new bolts, P/N AC43-399, are installed. Retaining bolt P/N AC43- 399 does not have a service life limitation. (e) 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 each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This amendment effective December 4, 1967.
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.)