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81-23-02: 81-23-02 TELEDYNE CONTINENTAL MOTORS: Letter issued October 30, 1981. Applies to Teledyne Continental Motors Models TSIO-360-EB, S/N 311703 and 311704; LTSIO-360-EB, S/N 312685; TSIO-360- KB, S/N 315204, 315209 through 315259, 315262 through 315274, 315277, 315283, 315284, and 315323; LTSIO-360-KB, S/N 314195, 314204, 314208 through 314274, 314276, and 314277; and TSIO-360-GB, S/N 309600, 309601, 309603 through 309618, 309622 through 309627, 309629 through 309641 and 309655 aircraft engines. Compliance required prior to further flight after receipt of this letter. To prevent possible failure of the oil filter adapter gasket, accomplish the following: (a) Inspect the oil filter adapter (TCM P/N 641576) flange at the machined alternator relief cutout in accordance with the inspection procedure described in TCM Special Service Notice 10-81, dated October 19, 1981. (b) If the machined alternator relief cutout intrudes into the shoulder (no matter how little), replace the adapterTCM P/N 641576 with a serviceable part which meets the inspection criteria of TCM Special Service Notice 10-81. (c) Make appropriate maintenance record entries indicating compliance with this AD. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Teledyne Continental Motors Special Service Notice 10-81, dated October 19, 1981, applies to this subject. This Airworthiness Directive becomes effective upon receipt.
2017-18-12: We are superseding Airworthiness Directive (AD) 2016-11-20 for certain B/E Aerospace protective breathing equipment (PBE) that is installed on airplanes. AD 2016-11-20 required replacing part number (P/N) 119003-11 PBE units. Since we issued AD 2016-11-20, we received a report that PBE units, P/N 119003-21, within a certain serial number range are made with candle tube material determined to have a low yield strength and may be volatile upon use or disposal. This AD retains the actions required in AD 2016-11-20 and requires inspecting and replacing P/N 119003-11 and 119003-21 PBE units. We are issuing this AD to address the unsafe condition on these products.
80-20-03: 80-20-03 FOKKER-VFW B.V.: Amendment 39-3923. Applies to Model F-27 series airplanes, serial numbers 10105 through 10248, which have incorporated Fokker Service Bulletin F27/61- 9(G6), serial numbers 10249 through 10518, except for airplanes which have Fokker Service Bulletin F27/61-10(G7) incorporated, and serial numbers 10519 through 10553, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent propeller auto-feathering caused by inadvertent potential being introduced into the propeller auto-feathering circuit, accomplish the following: (a) Within the next 500 hours time in service after the effective date of this AD, for airplane serial numbers 10105 through 10248 if Fokker Service Bulletin F27/61-9(G6) has been incorporated, and for airplane serial numbers 10249 through 10518 if Fokker Service Bulletin F27/61-10(G7) has not been incorporated, rework the cockpit floor and wiring in the receptacles, replace, route, and connect new wiring, and finish shielding in accordance with paragraph 2, "Accomplishment Instructions," General and Part I of Fokker Service Bulletin F27/61-29, revision 2, dated March 1, 1979, or an FAA-approved equivalent. (b) Within the next 500 hours time in service after the effective date of this AD for airplane serial numbers 10249 through 10518 except for airplanes which have Fokker Service Bulletin F27/61-10(G7) incorporated, install new shielded wires between the engine firewall and the partial pressure bulkhead in accordance with Fokker Service Bulletin F27/61-35 dated March 23, 1979, or an FAA-approved equivalent. (c) Within the next 500 hours time in service after the effective date of this AD, for airplane serial numbers 10519 through 10553, rework the cockpit floor and wiring in the receptacles, replace, route, and connect new wiring, and finish shielding in accordance with paragraph 2, "Accomplishment Instructions," General and Part II of Fokker Service Bulletin F27/61-29, revision 2, dated March 1, 1979, or an FAA-approved equivalent. (d) If an equivalent means of compliance is used in complying with paragraphs (a), (b), or (c) of this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. NOTE: There is a typographical error on page 4 of Fokker Service Bulletin F27/61-29, revision 2, dated March 1, 1979. Aircraft serial numbers 10150 to 10248 inclusive listed in the first column of the replacement wire table should be changed to read 10105 to 10248 inclusive. This amendment becomes effective October 22, 1980.
64-16-04: 64-16-04 LOCKHEED: Amdt. 768 Part 507 Federal Register July 21, 1964. Applies to Models 188A and 188C Series Aircraft. Compliance required within 425 hours' time in service after the effective date of this AD, unless accomplished within the last 3,575 hours' time in service, and thereafter at intervals not to exceed 4,000 hours' time in service from the last inspection. As a result of excessive wear and cracks in the aileron control system push-pull tubes, accomplish the following: (a) Visually inspect the wear pattern on the eight aileron push-pull tubes located aft of the wing rear spar, P/N's 810863-1, 810865-1, and 807742-1, and measure the maximum wear from the outside surface of the tube to the depth of the wear mark. When the visual inspection reveals indications of a crack or a lengthwise groove in the push-pull tube, inspect for cracks by using a magnetic particle inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Manually spin and visually inspect all of the aileron push-pull tube support rollers for freedom of rotation and for flat spots. (c) Following the inspections of (a) and (b) accomplish the following before further flight, except that the aircraft may be ferried in accordance with the provisions of CAR 1.76 to the base at which the repairs or replacements are to be accomplished: (1) Replace cracked aileron push-pull tubes with new parts of the same part number or an FAA approved equivalent. Replace aileron push-pull tubes P/N 810865-1 with more than 0.006 inch of wear, P/N 810863-1 with more than 0.008 inch of wear, and P/N 807742-1 with more than 0.012 inch of wear with new parts of the same part number or an FAA approved equivalent. (2) Replace aileron push-pull tube support rollers which do not rotate freely or which have a flat spot with new rollers of the same part number or an FAA approved equivalent. (3) When push-pull tubes orpush-pull tube support rollers are replaced in accordance with (c)(1) or (c)(2), adjust the clearance between the aileron push-pull tubes and their support rollers in accordance with Section 2.B.(4) of Lockheed Alert Service Bulletin 88/SB-607. (d) 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. (Lockheed telegram to operators FS/265688-W dated September 24, 1963, and Lockheed Service Bulletin 88/SB-607 pertain to this same subject.) This directive effective August 21, 1964. Revised March 2, 1965.
63-19-02: 63-19-02 GENERAL DYNAMICS: Amdt. 619 Part 507 Federal Register September 19, 1963. Applies to All Models 30 and 30A Aircraft. Compliance required as indicated. (a) Within the next 50 hours' time in service after the effective date of this AD unless already accomplished within the last 950 hours' time in service, conduct a close visual inspection of the horizontal stabilizer trim control cables in order to detect frayed cable. Pay particular attention to the section of the cable in the vicinity of the aft pressure bulkhead. Replace all frayed or otherwise damaged horizontal stabilizer trim control cables with new cables before further flight. (b) At periods not to exceed 1,000 hours' time in service after the inspection in (a), inspect the horizontal stabilizer nose down trim control cable on the aft side of the pressure bulkhead. This inspection shall include pulling the left-hand cable aft and flexing it several times in the area that normally contacts the pulley guiding the nose down cable. Replace cables having broken or damaged wires before further flight. (c) The repetitive inspection in (b) may be discontinued when the horizontal stabilizer trim cable system has been reworked in accordance with an FAA Western Region approved modification. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, 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 directive effective September 19, 1963.
2017-18-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP airplanes. This AD was prompted by a report of damage found at the lower trailing edge panels of the left wing and a broken fuse pin of the landing gear beam end fitting. This AD requires repetitive replacement or inspection of certain fuse pins, and applicable on- condition actions. We are issuing this AD to address the unsafe condition on these products.
2005-24-07: The FAA adopts a new airworthiness directive (AD) for certain Pacific Aerospace Corporation Ltd Model 750XL airplanes. This AD requires you to inspect the condition of the left and right outer panel attachment lugs for damage (scoring and gouging) and/or cracks (using a fluorescent penetrant inspection procedure for the crack inspection); to inspect the spacing of left and right outer panel attachment lugs; to replace the lugs if damage is found; and to make necessary corrections to the spacing. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to prevent structural failure of the outer panel and spar due to a cracked, bent, or distorted condition of the left and right outer panel attachment lugs; and incorrect spacing of the left and right outer panel attachment lugs. This failure could lead to loss of control of the airplane.
2017-17-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (Airbus) Model AS332L2 \n\n((Page 39507)) \n\nand EC225LP helicopters. This AD requires inspections of the main rotor (M/R) blade attachment pins (attachment pins). This AD was prompted by a report of three cracked attachment pins. The actions of this AD are intended to detect and prevent an unsafe condition on these products.
2005-24-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, and -800 series airplanes. This AD requires inspecting/measuring the length of the attachment fasteners between the nacelle support fittings and the lower wing skin panels, and related investigative/corrective actions if necessary. This AD results from a report from the manufacturer that in production, during the installation of certain attachment fasteners for the nacelle support fittings, only one washer was installed instead of two. We are issuing this AD to prevent inadequate fastener clamp-up, which could result in cracking of the fastener holes, cracking along the lower wing skin panels, fuel leaking from the wing fuel tanks onto the engines, and possible fire.
81-04-01: 81-04-01 HILLER AIRCRAFT: Amendment 39-4034. Applies to Models UH-12D, UH-12E, OH-23G, UH-12L, and all models converted to turbine power in accordance with Supplementary Type Certificate STC 177WE or STC 178WE, certified in all categories. Compliance required within ten (10) calendar days from the effective date of this AD, unless already accomplished. To prevent rudder balance cables from fraying and breaking, accomplish the following: (a) Perform a one time visual inspection of the rudder balance cable assembly, P/N HS 1053-2, in accordance with Hiller Service Bulletin No. 32-2 Part II, Accomplishment Instructions, Subparts A and B, dated December 31, 1980. (b) Remove from service the rudder cable assemblies, P/N HS 1053-2, which do not conform to type design. Type design is 7 x 19 cable. The Hiller Service Bulletin No. 32-2 depicts the acceptable cable. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes or helicopters to a base for the accomplishment of inspections or modifications required by this AD. (d) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective February 9, 1981.