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75-02-03: 75-02-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2066. Applies to Piper Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-32-260 and PA-32-300 airplanes, modified by installing a large nose wheel fork (Tibbetts-Herre Airmotive P/N PA-32-1) and an 8.00-6 nose wheel tire in accordance with Supplemental Type Certificate SA281AL, certificated in all categories. Compliance is required prior to the accumulation of 25 landings after the effective date of this AD, unless already accomplished. To prevent possible failure of the nose wheel fork assembly, accomplish the following: (a) Visually inspect the nose wheel fork for bends in the legs which are not part of the STC design. (b) Straighten any bends found in the inspection required by paragraph (a) of this AD, prior to the inspection required by paragraph (c) of this AD. (c) Inspect those nose wheel forks that have at any time been straightened in the past for cracks in the vicinity of the nosewheel axle holes, using a standard dye or fluorescent penetrant inspection procedure. To determine whether a nose wheel fork has been straightened in the past - (1) Check the aircraft maintenance records; and (2) Visually inspect the fork for any evidence of it having been straightened. (d) If no cracks are found in the inspection required by paragraph (c) of this AD, or the nose wheel fork is a fork excepted from the inspection required by paragraph (c) of this AD, chamfer and heat treat the nose wheel fork before further flight in accordance with paragraphs (f) and (g) of this AD. (e) If cracks are found in the inspection required by paragraph (c) of this AD, before further flight, replace the nose wheel fork with a serviceable nose wheel fork of the same part number which has been chamfered and heat treated in accordance with paragraphs (f) and (g) of this AD. (f) Chamfer the outside edge of each nose wheel fork axle hole at 45 degrees to a minimum depthof 1/32-inch prior to heat treating. (g) Heat treat the nose wheel fork to Ftu of 180,000 PSI in accordance with MIL-H- 6875 or an FAA approved equivalent. (h) Permanently stamp the letter "H" on each nose wheel fork heat treated in accordance with paragraph (g) of this AD, adjacent to the serial and part number stamps. (i) Replace each Piper P/N 20825-00 cap assembly with a Tibbetts-Herre P/N PA- 32-5 cap assembly or an equivalent approved by the Chief, Engineering and Manufacturing Field Office, FAA, Alaskan Region. (j) Replace the Tibbetts-Herre P/N PA-32-4 axle rod with a Tibbetts-Herre P/N PA- 32-6 axle rod or equivalent approved by the Chief, Engineering and Manufacturing Field Office, FAA, Alaskan Region, using AN365-624 nuts and AN960-616 washers. Note: 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 bythe operator's fleet average time from takeoff to landing for the airplane type. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made effective upon receipt of the airmail letter dated November 26, 1974, that contained this amendment.
2017-25-09: We are superseding Airworthiness Directive (AD) 2012-21-04, which applied to all Airbus Model A300 series airplanes; Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2012-21-04 required repetitive inspections for, and replacement of, any cracked hood halves of fuel pump canisters. Since we issued AD 2012-21-04, we allowed inspections of the wing-outer tank and trim tank fuel pump canister hood halves to be terminated. This new AD retains the requirements of AD 2012-21-04, reinstates the terminated inspections, and adds optional terminating actions. This AD was prompted by reports of cracked fuel pump canister hoods located in fuel tanks and new in-service events of wing-outer tank fuel pump canister hood cracking. We are issuing this AD to address the unsafe condition on these products.
2002-06-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-06-51 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes by individual notices. This AD requires revising the Airplane Flight Manual to provide procedures for addressing uncommanded transfer of fuel from wing fuel tanks to center fuel tank. This action also requires revising the Minimum Equipment List (MEL); limiting operation of the airplane to flight within 60 minutes of a suitable alternative airport; and ensuring that normal mission fuel requirements are increased by 3,000 pounds. This action was prompted by reports of uncommanded fuel transfer between the wing fuel tanks and the center fuel tank. The actions specified by this AD are intended to ensure that the flight crew has the procedures necessary to address such uncommanded fuel transfer, which could cause the center tank to overfill, and fuel to leak from the center tank vent system or to become inaccessible, and result in engine fuel starvation.
63-17-02: 63-17-02 FAIRCHILD: Amdt. 602 Part 507 Federal Register August 14, 1963. Applies to Model F-27 Series Aircraft on which a Walter Kidde Spur Gear Nose Wheel Steering Actuator Assembly, P/N 891800 (STC SA1-574), has been installed. Compliance required as indicated. Due to failures of the mounting bolts, P/N's 244241 and 245804 in the nose gear pivot bracket, accomplish the following: (a) On all affected aircraft that have not had the subject steering actuator assembly modified in accordance with Walter Kidde and Company, Inc., Service Bulletin No. 143 dated October 1962, or FAA approved equivalent, accomplish the following within the next 250 hours' time in service after the effective date of this AD and at intervals thereafter not to exceed 250 hours' time in service from the last inspection: (1) Inspect the 4 mounting bolts, P/N's 244241 and/or 245804, for cracks using dye penetrant methods in conjunction withat least a 10-power magnifying lens, or FAA approved equivalent inspection. Give particular attention to the necked-down area of the bolt where the shank meets the threads. Inspection may be accomplished without jacking-up the aircraft only if one bolt at a time is removed, inspected, and then replaced and properly torqued, before inspection of the second bolt is attempted. (b) If a crack is found, accomplish one of the following before further flight except that a ferry flight may be made in accordance with the provisions of CAR 1.76. (1) Replace any cracked bolt with a new one of the same type or an FAA approved equivalent and continue inspecting in accordance with (a) or (2) Modify the subject steering actuator assembly in accordance with Walter Kidde and Company, Inc., Service Bulletin No. 143 dated October 1962, or an FAA approved equivalent. (c) The repetitive inspections of the steering actuator assembly, as prescribed in (a) may be discontinued on aircraft modified in accordance with (b)(2) or an FAA approved equivalent. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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. (Walter Kidde and Company, Inc. Service Bulletin No. 143 dated October, 1962, covers this subject.) This directive effective September 13, 1963.
74-26-04: 74-26-04 PIPER: Amendment 39-2044. Applies to Models PA-31 & PA-31-300 S/N 31- 2 to 31-7401258 inclusive. Compliance required as indicated unless already accomplished: In order to eliminate explosion hazards associated with fuel leaking from the heater manual shut-off and solenoid shut-off valves in the nose compartment, accomplish the following: a. Within 25 hours time in service after the effective date of this AD, conduct a pressure check of the P/N 492107 manual heater shut-off valve and P/N 756513 solenoid fuel regulator shut-off valve. This may be accomplished by operating the right electric fuel pump, turning on the heater manual fuel valve and visually inspecting for fuel seepage around the valve body and connecting line fittings of both shut-off valves. If any leakage is observed, the valve must be replaced or repaired and the pressure check repeated. b. Within 125 hours time in service after the effective date of this AD for Serial Numbers 31-2to 31-7401258 inclusive, remove manual heater fuel shut-off valve P/N 492107 and bracket P/N 41948-00 in accordance with Piper Service Bulletin No. 417 and subsequent approved revisions. c. Within 125 hours time in service after the effective date of this AD for Serial Numbers 31-2 to 31-103 inclusive, install shroud assembly Piper P/N 43493 with associated cover, overboard drain tube, sealing grommets and clamp over heater solenoid shut-off valve P/N 756513 in accordance with Piper installation drawing No. 41923 and Parts Catalog No. 753703 Fig. 38. d. Alternate equivalent modifications to those described above must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Aircraft may be flown to a base where the maintenance required by this Airworthiness Directive may be performed per FAR's 21.197 and 21.199. (Piper Service Bulletin No. 417 dated August 26, 1974, pertains to this subject.) This amendment is effective December 19, 1974.
2023-05-07: The FAA is superseding Airworthiness Directive (AD) 2020-21- 07, which applied to all Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-21-07 required replacement of affected passenger oxygen masks (which includes re-identifying the parts). This AD was prompted by a determination that additional parts are subject to the unsafe condition. This AD continues to require the actions in AD 2020-21-07, and also requires replacing additional affected parts; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2025-07-09: The FAA is superseding Airworthiness Directive (AD) 2020-19- 13, which applied to certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. AD 2020-19-13 required a check to identify the manufacturer and part number of the portable oxygen bottle installation, and, if necessary, modification of the portable oxygen bottle installation. This AD continues to require the actions specified in AD 2020-19-13 and expands the applicability. This AD was prompted by a report indicating that the portable oxygen bottle installation's upper bracket latch assembly can catch on the pressure gauge tube or on the pressure gauge bezel of the portable oxygen bottle. This AD was also prompted by the determination that additional airplanes may be subject to the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
73-13-01: 73-13-01 PIPER: Amendment 39-1665 as amended by Amendment 39-1936 is further amended by Amendment 39-1964. Applies to all Piper Model PA-34-200 "Seneca" airplanes, S/Ns 34-E4, 34-7250001 and up. Compliance required as indicated. (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, determine the rudder trim tab "free play" as follows: (1) Adjust rudder trim tab to neutral position with rudder trim wheel. (2) Index tab to rudder. Use straight edge at trailing edge, making marks on rudder and tab that coincide. (3) Hold light finger pressure against rudder tab in one direction and measure distance between marks. (4) Reverse direction of finger pressure on rudder tab and measure distance between marks. (5) "Free play" of the rudder tab is the sum of the distances measured in (3) and (4) above and should not exceed .125 inches. (b) If rudder tab "free play" exceeds .125 inches, check the travel control arm assembly, P/N 96220-00 (Ref. Fig. 60, PA-34 parts catalog), for wear at the center bolt and at the bolt attaching the rudder trim rod assembly to the control arm. Replace the arm assembly and associated hardware if there is any noticeable wear or elongation of the bolt holes. (c) Also check for end play in the rudder trim barrel, P/N 96596-00 (Ref. Fig. 34, PA-34 parts catalog). If end play exists, shim between the forward barrel mount support assembly and barrel. Reduce end play to the minimum amount attainable without causing excessive system friction. Note: Shim (P/N 62833-18V) is a laminate made of 10 pieces of .002 inch brass shim stock, although it appears to be one solid piece. The proper thickness of shim material may be obtained by pealing off layers as required. (d) Upon completion of any adjustments, re-check "free play" in accordance with the procedures of (a)(3), (a)(4), and (a)(5) to ascertain that travel is less than .125 inches.(e) Repeat the above inspection every 100 hours time in service after the initial inspection. Piper Service Bulletin No. 390A pertains to this same subject. When the airplane is modified with Piper Rudder Trim Mechanism Kit, Piper P/N 760800V, the repetitive inspections of (e) are no longer required. Piper Service Letter No. 714 pertains to this same subject. Amendment 39-1665 became effective June 18, 1973. Amendment 39-1936 became effective August 30, 1974. This Amendment 39-1964 becomes effective September 30, 1974.
2002-06-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to replace the metered connector and oxygen tubing and related components in the rear seat bench. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to correct the potential for insufficient oxygen quantity that is available to occupants of the rear seat bench in some emergency conditions. This condition could result in reduced occupant safety at the rear bench seat location.
2023-05-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.