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70-09-02: 70-09-02 PIPER: Amdt. 39-977 as amended by Amendment 39-1376. Applies to PA-28R-180 airplanes serial numbers 28R-31071 and 28R-31073 through 28R-31266, and PA-28R-200 airplanes serial numbers 28R-35001 through 28R-35698, 28R-35700, 28R-35702, 28R- 35704, 28R-35705, 28R-35709, and 28R-35711 through 28R-35713. Compliance required as indicated. To insure that cracks are not present in the propeller spinners used on the referenced aircraft, comply with paragraph (a) or (b). (a) Within the next 25 hours' time in service after the effective date of this airworthiness directive, unless already accomplished remove spinner body Piper Part No. 66786- 00, 68713-00, or 760290 as applicable; spinner cap Piper Part No. 66785-00 if applicable; and spinner bulkhead Piper Part No. 68734-00 if desirable. Spinner bulkhead removal requires removal of the propeller, which must be accomplished by authorized individuals or repair facilities. NOTE: These airplanes are approved forflight with the spinner removed and the bulkhead installed; or with the spinner and bulkhead both removed. (b) Within the next 25 hours' time in service after the effective date of this airworthiness directive, unless already accomplished, and thereafter at intervals not to exceed 25 hours' time in service, remove the spinner cap and/or body and visually check them and the bulkhead for cracks starting from blade cut-outs, attachment holes, pilot holes, plate nuts, etc. The bulkhead need not be removed for this inspection. Remove from further service all parts on which cracks are found. If no cracks are found, the spinner may be reinstalled. New parts may be installed to replace those found cracked. (c) The checks required by this airworthiness directive may be performed by pilots, including pilots of aircraft engaged in air carrier operations, except removal and replacement of the bulkhead. Removal and replacement of the bulkhead requires removal and replacement of the propeller, which must be accomplished by authorized individuals or repair facilities. NOTE: For the requirements regarding the listing of compliance and method of compliance with this airworthiness directive in the airplane's permanent maintenance record, see FAR 91.173. (d) Time intervals for the visual checks may be adjusted up to a maximum of 10 hours to coincide with aircraft annual or 100 hour scheduled inspections. (e) The recurrent inspections required in paragraphs (a), (b), and (d) may be discontinued upon installation of Piper spinner kit No. 760410V. Piper Service Bulletin No. 309 or later approved revision covers this same subject. Amendment 39-977 became effective April 24, 1970. This Amendment 39-1376 becomes effective January 20, 1972.
2023-04-14: The FAA is superseding Airworthiness Directive (AD) 2020-12- 01, which applied to certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent XWB-75, Trent XWB-79, Trent XWB-79B, and Trent XWB-84 model turbofan engines. AD 2020-12-01 required initial and repetitive inspections of the low pressure compressor (LPC) outlet guide vane (OGV) outer mount ring assembly and, depending on the results of the inspections, possible replacement of the LPC OGV outer mount ring assembly. Since the FAA issued AD 2020-12-01, the FAA determined that these inspections are also necessary for RRD Trent XWB-97 model turbofan engines. This AD was prompted by analysis by the manufacturer of the LPC OGV assembly and LPC OGV outer mount ring assembly which predicted that when the front engine mount is in the fail-safe condition, the most highly stressed LPC OGV assembly has a life that could be substantially less than one shop visit interval. This AD requires initial and repetitive inspections of the LPC OGV outer mount ring assembly and, depending on the results of the inspections, replacement of the LPC OGV outer mount ring assembly, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
70-26-04: 70-26-04 PIPER: Amdt. 39-1134 as amended by Amendment 39-1196 is further amended by Amendment 39-1232. Applies to PA-28-140, Serial Numbers 28-20000 through 28- 26946 and 28-7125000 through 28-7125334. PA-28-150-160-180 and PA-28S-180, Serial Numbers 28-1 through 28-5859 and 28- 7105001 through 28-7105126. PA-28-235, Serial Numbers 28-10001 through 28-11378 and 28-7110001 through 28- 7110011. PA-28R-180, Serial Numbers 28R-30001 through 28R-31270 and 28R-7130001 through 28R-7130005. PA-28R-200, Serial Numbers 28R-30482, 28R-35001 through 28R-35820, and 28R- 7135001 through 28R-7135104. PA-32-260, Serial Numbers 32-04, 32-1 through 32-1297, and 32-7100001 through 32- 7100016. PA-32-300 and PA-32S-300, Serial Numbers 32-15, 32-21, 32-40000 through 32-40974, and 32-7140001 through 32-7140050. Compliance required as indicated, unless already accomplished: I. Aircraft with less than 500 hours total time in service: Inspect in accordancewith instructions below at 500 hours total time or within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. II. Aircraft with 500 hours through 1000 hours total time in service: Inspect in accordance with instructions below within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. III. Aircraft with more than 1000 hours time in service: Inspect in accordance with instructions below within the next 25 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. To detect cracks in the stabilator balance weight tube in the area of the attachment bolt holes accomplish the following: 1. Remove tail cone assembly and bulkhead close out plate if so equipped. 2. In the tail cone section, remove safeties from stabilator cable turnbuckles and release cable tension. 3. Disconnect stabilator cables at the balance weight tube assembly. NOTE: Care should be taken as not to misplace the bushing fitted in the tube/cable attachment lugs. 4. Remove the stabilator balance weight tube assembly attachment bolts. 5. Pull stabilator balance weight tube assembly forward and remove from stabilator. (It is not necessary to remove balance weight from tube.) 6. Remove paint from balance weight tube in areas of the stabilator attachment bolt holes. NOTE: Use any commercial paint remover or caustic soda to remove paint; wash part in gasoline to remove any wax. 7. Inspect tube for cracks in this area using dye penetrant. If a crack or cracks are detected replace the balance weight tube assembly with new part. If cracks are not detected, the part may be reinstalled on the airplane after the tube has been cleaned, primed with zinc chromate primer, and painted. NOTE: When a new balance weight tube assembly, Part Number 63578-00V, 65310-00V, or 68432-00V is installed, an initial inspection after 500 hours time in service on the assembly and repetitive inspections at 200 hour intervals will still be required. 8. Inspect stabilator mounting points for possible stabilator side movement. Should side movement be evident, install combination of AN960-416L (Piper code no. 407 585) and AN960-416 (Piper code no. 407 565) washers, as many as necessary to center the stabilator assembly and eliminate any side movement. 9. Visually inspect stabilator fittings (part no. 63567-03) for evidence of cracks and/or loose rivets. a. Should the fitting(s) be cracked, replace with new stabilator fitting(s), part no. 63567-03. b. Remove loose rivets and replace with new rivets. Piper Service Bulletin No. 327 dated 9 December 1970 pertains to this same subject. The installation of a new stabilator balance weight support tube, Part Number 69623-04V, 69623-02V, or 69624-02V, in accordance with Piper Service Letter No. 576 will eliminate the necessity for the initial and repetitive inspections required in Paragraphs I, II and III. NOTE: The above referenced new tubes may be identified by the presence of green paint on the cable attachment lugs. Amendment 39-1134 became effective December 28, 1970. Amendment 39-1196 became effective April 30, 1971. This Amendment 39-1232 becomes effective June 24, 1971.
70-15-17: 70-15-17 PIPER AIRCRAFT: Amdt. 39-1044. Applies to Piper PA-30 type airplanes, serial numbers 30-1 through 30-852 and 30-854 through 30-901, certificated in all categories. Before further flight, attach the following operating limitation placard to the airspeed indicator in full view of the pilot: "DO NOT EXCEED 230 MPH CAS." This amendment is effective August 4, 1970 and was effective for all recipients of the airmail notice, dated 2 July 1970, which contained this amendment.
2002-04-09: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires modifying the engine start circuit. This action is necessary to prevent overheating of the soft start resistor of the engine start circuit, which could result in smoke and fumes in the cabin and consequent injury to passengers and crew. This action is intended to address the identified unsafe condition.
2022-22-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 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.
70-22-02: 70-22-02 AIRBORNE MANUFACTURING CO.: (formerly Airborne Mechanisms). Amdt. 39-1095. Applies, except as noted, to all model 1H7, 1H10, 1H16, and 1H26 series fuel selector valves installed on, but not necessarily limited to: Piper PA-28-235 Piper PA-32-260 Piper PA-32-300 Piper PA-32S-300 Piper PA-30 Piper PA-39 NOTE: 1H7 series valves identified with a number 4-R, 5-R, etc. and subsequent letter codes, (appearing on manufacturer's plate directly underneath the valve model number) and 1H26 series valves with a number 6-R, 7-R, etc. and subsequent letter codes, (appearing at same location noted above) are equipped with a production roll pin retaining sleeve and are not affected by this AD. Additionally, some earlier manufactured valves have slotted keyway control arms and shafts. These valves are also not affected by this AD. The alpha-numeric representation identifies the month and year a valve was manufactured. For example, 4-R indicates that the valve was manufactured during April, 1970. Compliance required within the next 50 hours in service after the effective date of this AD, unless already accomplished. To prevent the possibility of engine fuel starvation resulting from the inability to operate the fuel selector valve due to loss of the control arm roll pin, accomplish the following: a. Inspect the fuel selector valve control arm and ascertain that the roll pin is in place. b. Install pin retaining kit, Airborne P/N 2T18-1 (Piper P/N 760444 or 760438V), consisting of spring clip, Airborne P/N D1-61-1 (Piper P/N 757638) and sleeve, Airborne P/N A9-78-1 (Piper P/N 757639), as follows: 1. Lift quick drain shaft and insert slot of sleeve around shaft ensuring that groove in sleeve faces downward. Then press protruding portion of spring clip against hub and slide the entire assembly down over the hub. NOTE: Do not attempt to retract the spring clip by prying with pointed tool. 2. Rotate sleeveand spring clip assembly around the hub until protruding portion of the spring clip snaps into the bore of the roll pin. 3. Paint 1/4" diameter red dot, using indelible ink, on fuel selector arm immediately adjacent to the newly installed retaining sleeve. Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region may adjust the compliance time specified in this Airworthiness Directive. (Piper Aircraft Corporation Service Bulletin Nos. 311 and 314 both dated 5 June 1970 pertain to this same subject.) This amendment is effective November 4, 1970.
2002-04-07: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS350BA and B2 helicopters modified with a Eurocopter Canada Limited (ECL) Left-side-Pilot Configuration kit in accordance with Canadian Supplemental Type Certificate (STC) SH96-32 or United States STC SR00429 NY. This action requires replacing the collective locking device with a newly-designed locking device. This amendment is prompted by a report of a locking device that engaged during flight. The actions specified in this AD are intended to prevent inadvertent engagement of a locking device, the collective pitch control locking in the full-down position, and subsequent loss of control of the helicopter.
2002-04-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 series airplanes; certain Model A300 F4-605R airplanes and Model A300 B4-600 and A300 B4-600R series airplanes; and certain Model A310 series airplanes, that requires repetitive inspections to detect damage of the fillet seals and feeder cables, and of the wiring looms in the wing/pylon interface area; and corrective action, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent wire chafing and short circuits in the wing leading edge/pylon interface area, which could result in loss of the power supply generator and/or system functions. This action is intended to address the identified unsafe condition.
83-13-01: 83-13-01 CESSNA: Amendment 39-4672. Applies to Models 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q (all serial numbers except 66590 and on) and R182 (S/N R18200002 through R18200583) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To alert the pilot to the potential effects of improper fuel cap sealing: a) Within the next 12 calendar months after the effective date of this AD install a placard adjacent to the fuel quantity gauges which states: "CAUTION Leaking fuel caps can cause loss of fuel and erroneously high fuel quantity indications." This placard may be fabricated by the owner/operator of the airplane. The person accomplishing this must make the prescribed entry in the aircraft maintenance records reflecting compliance with paragraph a) of this AD. b) Within the next 12 calendar months after the effective date of this AD and each 12 calendar months thereafter: 1) Visually inspect, the surface of the wing aft of the fuel cap for evidence of leakage, the fuel cap seals for cracks, distortion and or any condition which may prevent sealing and the sealing surface of the adapter for scratches, corrosion, distortion or other conditions which may prevent sealing. If any of these conditions are noted inspect the fuel tank for wrinkles in the bottom and proper attachment of the retaining snaps to the compartment. Prior to further flight, correct any unsatisfactory conditions in accordance with the manufacturers maintenance manuals or service information which should include inspection of the fuel tank installation in accordance with Cessna Service Letter SE82-34A. Fuel cap repairs should be accomplished in accordance with Cessna Service Letter SE80-59 Supplement 1. 2) On airplanes having Cessna P/N C156001-0106 plastic cap installed, visually inspect the adapter for presence and legibility of the Cessna P/N 1205253-1 FuelCap Alignment Placard and prior to further flight install new placards if required. 3) Check the tension of the fuel cap locking mechanism by operating the tab. If necessary, prior to further flight adjust in accordance with the manufacturers service manuals/information to obtain proper sealing pressure between the cap and adapters. c) Airplane may be flown per FAR 21.197 to a location where this AD may be accomplished. d) An equivalent method of compliance with this AD may be used if it is approved by Manager, Wichita Aircraft Certification Office, Room 238, Terminal building 2299, Mid-Continent Airport, Wichita, Kansas 67209. Cessna Service Information Letter SE79-45, SE8O-59, Supplement 1 and SE82-34A and Owner Advisories SE80-59A and SE82-34A pertain to the subject matter of this AD. This amendment becomes effective on August 1, 1983.