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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.
90-06-10: 90-06-10 SCHWEIZER AIRCRAFT CORPORATION: Amendment 39-6529. Docket No. 88-ASW-37. Applicability: All Schweizer Model 269A, 269A-1, 269B, and 269C helicopters, certificated in any category, with Serial Numbers 0004 through 0819 and those subsequent to 0819, which have had throttle cables replaced. Compliance: Required as indicated, unless already accomplished. To prevent loss of throttle control, accomplish the following: (a) Within the next 25 hours' time in service or within 30 days, whichever occurs first after the effective date of this AD, identify, inspect, and replace as indicated, the throttle cable assembly as follows: (1) Determine if aluminum fittings are installed as follows: (i) Check both end fittings of the cable assembly with a magnet to determine whether they are magnetic. Cables which incorporate magnetic fittings (magnet adheres to fitting) do not require the hardness test specified by paragraph (a)(1)(ii) below. For these cableassemblies, omit step (a)(1)(ii), and continue inspection with step (a)(2) below. (ii) If the magnet does not adhere to the fitting, perform a hardness test on the fitting. If Rockwell hardness is less than B-85, remove and replace the cable assembly with a swaged steel cable assembly in accordance with paragraph (c) of this AD before further flight. Performance of the hardness test will require removal of the throttle cable assembly from the helicopter in accordance with standard maintenance instructions. (2) Visually check both ends of the cable to determine whether the cable incorporates swaged or threaded steel end fittings. NOTE: Throttle cables which incorporate swaged end fittings may be identified by six evenly spaced flat spots around the barrel of the fitting just behind the lug. Threaded end fittings incorporate a cylindrical barrel (no flat spots). (3) If the cable incorporates swaged steel end fittings (as determined from steps (a)(1) and (2) above), further compliance is not required except to record compliance in the helicopter log book as "THROTTLE CABLE WITH SWAGED STEEL END FITTINGS INSTALLED." (4) If cable incorporates a threaded steel end fitting (as determined from steps (a)(1) and (2) above), perform an inspection before further flight and perform repetitive daily inspections in accordance with paragraph (b) of this AD until the cable is replaced in accordance with paragraph (c) of this AD. (5) Record compliance with paragraph (a) of this AD in the compliance record of the helicopter log book. (b) Prior to the first flight of each day, conduct a visual check of throttle cable assemblies with threaded steel end fittings as follows: (1) Inspect cable end fittings for general condition and security of attachment. If any abnormality or damage is noted, replace cable assembly in accordance with paragraph (c) of this AD. (2) Using a flashlight, visually inspect cable push rod for exposed threads adjacent to end fitting (both ends of cable assembly). NOTE: The cable push rod is the moveable rod that is attached directly to the cable end fitting (lug). (3) If threads are visible, replace cable assembly before further flight in accordance with paragraph (c) of this AD. (4) Record compliance with paragraph (b) of this AD in the compliance record of the helicopter log book. (c) Within the next 400 hours' time in service from the effective date of this AD, or within 12 months, whichever occurs first, replace with swaged steel end fittings all threaded steel end fittings which were not replaced during the inspections and rework required by paragraphs (a) and (b) of this AD. Replacement parts applicability is as follows: Model Swaged Steel Cable Assembly Part Numbers (P/N) 269A 269A4683-9 269A-1 269A4683-9 269B 269A4683-7 269C 269A4683-7 (1) Remove throttle control cable (reference Basic Helicopter Maintenance Instructions (HMI), paragraph 4-11). Donot bend throttle cable support tubes more than 8 degrees from centerline of cable; doing so could cause deformation of the support tubes, premature failure of the cable, and loss of throttle control. NOTE: The cable support tube is the stationary cylinder on the end of the cable through which the cable push rod slides. (2) Install P/N 269A4683-7 or -9 throttle control cable assembly (reference Basic HMI, paragraph 4-11). (3) Rig throttle control (reference Basic HMI). (4) Check idle speed and idle mixture in accordance with appropriate maintenance instructions, and adjust as required. Installation of the upgraded cable assembly, P/N 269A4683-7 or -9, cancels the repetitive inspection required by paragraph (b) of this AD. (5) Record compliance with paragraph (c) of this AD in the compliance record and in the maintenance record of the helicopter log book. NOTE: The instructions in this AD are similar to those contained in Schweizer SIN N-210, dated April15, 1988. An alternate method of compliance which provides an equivalent level of safety with this AD may be used upon the submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (e) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. This amendment (39-6529, AD 90-06-10) becomes effective on April 6, 1990.