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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.
2025-11-06: The FAA is superseding Airworthiness Directive (AD) 2025-07- 04, which applied to all Airbus Canada Limited Partnership Model BD- 500-1A11 airplanes. AD 2025-07-04 required a review and disposition of all existing repairs and damage assessments for affected structure, corrective actions if necessary, and the prohibition of certain repair engineering orders (REOs). Since the FAA issued AD 2025-07-04, the FAA determined that the list of acceptable generic repair engineering orders (GREOs) specified in table 1 to paragraph (h)(3) of AD 2025-07- 04 was added in error. This AD continues to require review and disposition of all existing repairs and damage assessments for affected structure, which includes GREOs that were identified in AD 2025-07-04, corrective actions if necessary, and the prohibition of certain REOs. 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.
2025-10-10: The FAA is superseding Airworthiness Directive (AD) 2023-26- 05, which applied to certain Pilatus Aircraft Ltd. (Pilatus) Model PC- 24 airplanes. AD 2023-26-05 required periodic replacement of affected titanium threaded bolts, a one-time inspection of the rudder mass balance arm and other elements of the rudder trim tab installation for correct attachment, damage (gouges), cracks, deformation, surface finish, and corrosion on any surrounding parts and, depending on findings, the accomplishment of applicable corrective actions. Since the FAA issued AD 2023-26-05, it was determined that some batches of titanium bolts had variations in the microstructure that could affect the fatigue characteristics. This AD requires replacing affected short rudder-trim control rod assemblies with serviceable rudder-trim control rod assemblies having threaded steel bolts and prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
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.
2017-25-04: We are superseding Airworthiness Directive (AD) 2014-22-08, which applied to all Airbus Model A318 and A319 series airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-22-08 required revising the maintenance or inspection program to incorporate new or revised airworthiness limitation requirements. This new AD requires revising the maintenance or inspection program to incorporate new or revised airworthiness limitation requirements, and removes airplanes from the applicability. This AD was prompted by a determination that more restrictive maintenance instructions and airworthiness limitations are necessary. We are issuing this AD to address the unsafe condition on these products.
2007-23-12: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires accomplishing an airplane survey to define the configuration of certain system installations, and repair of any discrepancy found. This AD also requires modifying the fuel system by installing lightning protection for the fuel quantity indication system (FQIS), ground fault relays for the fuel boost pumps, and additional power relays for the center tank fuel pumps and uncommanded on- indication lights at the flight engineer's panel. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent certain failures of the fuel pumps or FQIS, which could result in a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
93-06-06: 93-06-06 HAMILTON STANDARD: Amendment 39-8531. Docket No. 92-ANE-51. Applicability: Hamilton Standard Models 14RF-9, 14RF-19, and 14RF-21, and Models 14SF-5, 14SF-7, 14SF-11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23 propellers, and Hamilton Standard-British Aerospace Model 6/5500/F-1 propellers installed on but not limited to Embraer EMB-120 and EMB-120RT; SAAB-SCANIA AB SAAB 340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72-101, ATR72-210; DeHavilland DHC-8-100, DHC-8-300, DHC-8-314; Construcciones Aeronauticas SA (CASA) CN-235 and CN-235-100; Canadair CL215T; and British Aerospace ATP airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent loss of control of the propeller blade pitch due to propeller control unit (PCU) ballscrew quill wear, accomplish the following: (a) Within 10 hours time in service (TIS) after the effective date of this AD, for propeller assemblies equipped with titanium nitrided transfer tubes (identifiable by gold-colored spline area), remove the titanium nitrided transfer tubes from service, replace the PCU ballscrew quill with a new quill or a quill that has never been mated with a titanium nitrided transfer tube, and install an A-1 nitrided transfer tube (identifiable by a grey-colored spline area) that has been marked in accordance with the applicable SB listed in paragraph (c) of this AD. (b) Within 30 hours TIS after the effective date of this AD, for propeller assemblies equipped with an A-1 nitrided transfer tube and a PCU ballscrew quill that either has been mated to a titanium nitrided transfer tube, or that have no records showing to which transfer tube type the PCU ballscrew quill was mated, replace the PCU ballscrew quill with a new quill or a quill that has never been mated with a titanium nitrided transfer tube. (c) Within 60 days after the effective date of this AD, mark all A-1 nitrided transfer tubes with a new part number in accordance with the following Hamilton Standard Alert Service Bulletins (ASB), all dated October 27, 1992: ASB No. 14RF-21-61-A39, applicable to Hamilton Standard Model 14RF-21 propellers; ASB No. 14RF-9-61-A57, applicable to Hamilton Standard Model 14RF-9 propellers; ASB No. 14RF-19-61-A26, applicable to Hamilton Standard Model 14RF-19 propellers; ASB No. 14SF-61-A61, applicable to Hamilton Standard 14SF series propellers; and ASB No. 6/5500/F-61-A12, applicable to Hamilton Standard-British Aerospace Model 6/5500/F-1 propellers. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The replacement, and marking of transfer tubes shall be accomplished in accordance with the following service documents: Document No. Page Issue Date Hamilton Standard ASB No. 14RF-21-61-A39 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 14RF-9-61-A57 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 14RF-19-61-A26 1-6 Original October 27, 1992 Total pages: 6 Hamilton Standard ASB No. 14SF-61-A61 1-7 Original October 27, 1992 Total pages: 7 Hamilton Standard ASB No. 6/5500/F-61-A12 1-7 Original October 27, 1992 Total pages: 7 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Hamilton Standard Division of United Technologies Corporation, One Hamilton Road, Windsor Locks, Connecticut 06096-1010. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment supersedes AD T91-11-51 issued on May 22, 1991. (h) This amendment becomes effective on July 6, 1993.
93-21-06: 93-21-06 ISRAEL AIRCRAFT INDUSTRIES, LTD.: Amendment 39-8720. Docket 93-NM-96-AD. Supersedes AD 92-12-07, Amendment 39-8268, which superseded AD 90-10-08, Amendment 39-6597. Applicability: Model 1125 Westwind Astra series airplanes on which horizontal stabilizer aft spar splice fitting, part number 453005-509, has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the horizontal stabilizer assembly, accomplish the following: (a) Within the next 50 hours time-in-service after July 31, 1992 (the effective date of AD 92- 12-07, amendment 39-8268), unless previously accomplished within the last 150 hours time-in-service prior to July 31, 1992, perform a visual inspection of the horizontal stabilizer hinge fitting to detect cracks in the outer lug root radius and fore and aft surfaces, and around the hinge pin head and nut of the lugs, in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. (1) If no cracks are found during this inspection, repeat the inspection at intervals not to exceed 200 hours time-in-service until the inspection required by paragraph (b) is accomplished. (2) If any crack is found during this inspection, prior to further flight, replace the hinge fitting in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. After replacement, repeat the visual inspection required by this paragraph at intervals not to exceed 200 hours time-in-service until the inspection required by paragraph (b) is accomplished. (b) Within 25 hours time-in-service after the effective date of this AD, unless previously accomplished within the last 75 hours time-in-service, perform a visual inspection of the horizontal stabilizer hinge fitting, including the horizontal stabilizer aft spar splice fitting, part number 453005-503 (aluminum), to detect cracks in the outer lug root radius and fore and aft surfaces, and around the hinge pin head and nut of the lugs, in accordance with the Accomplishment Instructions of IAI Service Bulletin 1125- 55-017, Revision 1, dated April 24, 1991. Accomplishment of this inspection terminates the requirements of paragraph (a) of this AD. (1) If no crack is found during this inspection, repeat the inspection at intervals not to exceed 100 hours time-in-service. (2) If any crack is found during this inspection, prior to further flight, replace the splice fitting, part number 453005-503 (aluminum), with an improved splice fitting, part number 453005- 509 (titanium), in accordance with procedures in the IAI Model 1125 Westwind Astra maintenance manual. Such replacement constitutes terminating action for the inspection requirements of this AD. (c) Within one year after the effective date of this AD, replace the splice fitting, part number 453005-503 (aluminum), with an improved splice fitting, part number 453005-509 (titanium), in accordance with the IAI Model 1125 Westwind Astra maintenance manual. Such replacement constitutes terminating action for the inspection requirements of this AD. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections and replacements shall be done in accordance with Astra Service Bulletin 1125-55-017, Revision 1, dated April 24, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on December 13, 1993.
2017-24-08: We are superseding airworthiness directive (AD) 2014-24-08 for all Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211- 535E4-C-37 turbofan engines with certain low-pressure (LP) fuel filter- to-high-pressure (HP) fuel pump tube assemblies, or HP fuel pump-to- fuel flow governor (FFG) or FFG-to-HP pump inlet overspill return tube assemblies and flanged adaptor, installed. AD 2014-24-08 required replacing certain LP fuel filter-to-HP fuel pump tube assemblies. This AD retains the requirement in AD 2014-24-08 to remove the LP fuel filter-to-HP fuel pump tube, adds new compliance thresholds, and requires installation of new HP fuel pump-to-FFG and FFG-to-HP pump inlet overspill return tube assemblies and flanged adaptor. This AD was prompted by fuel leaks that have occurred at the flanged joints of the HP fuel pump-to-FFG tube assembly and FFG-to-HP pump inlet overspill return tube assembly. We are issuing this AD to correct the unsafe condition on these products.
2002-04-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections for cracking of the upper chord of the rear spar of the wing, and corrective action, if necessary. This action is necessary to find and fix such cracking, which could result in fuel leaking through the cracks, reduced structural integrity of the wing, and separation of the wing from the airplane. This action is intended to address the identified unsafe condition.
84-24-53 R1: 84-24-53 R1 EMBRAER: Amendment 39-4975. Applies to Models EMB-110P1 and EMB- 110P2 airplanes certificated in any category. Compliance: Required within the next ten (10) hours time-in-service, unless previously accomplished within the last fifty (50) hours time-in-service. To preclude possible structural failure of the empennage assembly, accomplish the following: (a) Unless the structural reinforcements and rivet replacements specified in paragraphs (d) and (e) of AD 83-14-09 (Amendment 39-4692) have already been accomplished, repeat the inspections of the horizontal stabilizer front attachment and fuselage bulkhead 33 area in accordance with paragraph (a) of AD 83-14-09. (b) If loose rivets or cracks of any length are found during the inspections required by paragraph (a), prior to further flight, replace the rivets in accordance with paragraph (b) of AD 83- 14-09 and repair the cracks in accordance with paragraph (c)(2) of AD 83-14-09 notwithstanding the three inch crack criteria of that paragraph. (c) Visually inspect the following components for loose attachments, excessive wear, corrosion, cracks and structural deformation: (1) Forward horizontal stabilizer attachment, including the fuselage and stabilizer attach fittings and attachment hardware. (2) Aft horizontal stabilizer attachment, including the fuselage and stabilizer attach fittings, attach links and all attachment hardware. (3) All elevator to stabilizer hinge fittings, including all bearings/bushings and attachment hardware. (4) Security of elevator mass balance weight assemblies. (5) Left and right elevator Bellcrank assemblies and attachment hardware. (6) Left and right elevator torque tube assemblies and all attachment hardware. (7) Elevator trim tab hinges. (8) Elevator trim tab actuator, bearings, push rod assembly and all attachment hardware. (9) Elevator trim tab free play, measured at the trailing edge, shouldnot exceed airplane maintenance manual limits. (d) Prior to further flight, correct any unsatisfactory conditions found as a result of the inspections required by paragraph (c) in accordance with the airplane maintenance manual. (e) Report any unsatisfactory conditions, within 24 hours, to the FAA, Airframe Branch, Atlanta Aircraft Certification Office; Telephone (404) 763-7407. (Reporting authorized by OMB clearance number 21200056.) (f) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337. This amendment becomes effective on January 17, 1985, to all persons except those to whom it has already been made effective immediately by telegraphic AD T84-24-53 issued December 9, 1984.
75-01-01: 75-01-01 PRATT & WHITNEY AIRCRAFT: Amendment 39-2055 as amended by Amendment 39-2358. Applies to all Pratt & Whitney JT8D-1, -1A, -7, and -7A model turbofan engines. Compliance required as indicated. To prevent failure of the low turbine shaft spline accomplish the following: 1. Remove from service thin wall low turbine shafts not incorporating Pratt & Whitney Aircraft Service Bulletin 2452 (P/Ns 479796, 493412, 511215, 524958, 528365, 528366, 538951, 540354, 540355, 540452, 562503, 562504, 576305, 576312, 576313, 576314, and 587879) prior to the accumulation of 6700 cycles in service since new, or within the next 2000 cycles in service after January 8, 1975, whichever is later. 2. Inspect thin wall low turbine shafts incorporating Pratt & Whitney Aircraft Service Bulletin 2452 (P/Ns 540354-S/B2452, 540355-S/B2452, 540452-S/B2452, 676276, 676277, 676278, 676279, 676280, 676282, 676283, 676284, 676285, 676286, and 676287) for cracked splines in accordance with thePratt & Whitney Service Bulletin 2452, Revision 10, or later FAA approved revision, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, prior to the accumulation of 6700 cycles in service since last inspection or within the next 2000 cycles in service after January 8, 1975, whichever is later, unless already accomplished in accordance with Pratt & Whitney Service Bulletin No. 2452, Revision No. 10, or in accordance with the eddy current inspection of Pratt & Whitney Service Bulletin No. 2452, Revision Nos. 5 thru 9. Inspect thereafter at intervals not to exceed 6700 cycles in service from the last inspection. Remove shafts with cracks from service before further flight. 3. Inspect all No. 2 compressor hub splines plated per Pratt & Whitney Service Bulletins 2964 and 4193, in accordance with Pratt & Whitney Alert Service Bulletin 4357, Paragraphs IV.D.2 and IV.D.3, or later FAA approved revision, as applicable, when the low turbine shafts are removed or inspected in accordance with Paragraph 1 or 2 above. Remove hubs with plate peeling from service before further flight. 4. Inspect nonplated titanium No. 2 compressor hub splines, run with low turbine shafts requiring inspection under Paragraphs 1 or 2 of this AD, for taper wear in accordance with Pratt & Whitney JT8D manual, P/N 481672, Revision 76, Section 72-33-6, or later FAA approved revision, prior to the accumulation of 6700 cycles in service or within the next 2000 cycles in service after January 8, 1975, whichever is later, unless already accomplished. Inspect thereafter at intervals not to exceed 6700 cycles in service since last inspection. Remove hubs with taper wear in excess of .010 inch from service before further flight. The manufacturer's service bulletins identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, 400 Main Street, East Hartford, Ct. 06108. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, MA 01803, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington D.C., and at the New England Regional Office in Burlington, MA. Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time. NOTE: Pratt & Whitney Alert Service Bulletin 4357 pertains to this subject. Amendment 39-2055 became effective January 8, 1975. This amendment 39-2358 becomes effective September 17, 1975.
2017-25-05: We are superseding Airworthiness Directive (AD) 2012-23-10, which applied to all Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2012-23-10 required modifying the affected slide rafts. This AD retains the requirements of AD 2012-23-10. This AD also requires replacing each escape slide pack assembly having a certain part number with a new escape slide pack assembly. This AD was prompted by reports of the escape raft inflation system not deploying when activated due to the rotation of the cable guide in a direction that resulted in jamming of the inflation control cable. We are issuing this AD to address the unsafe condition on these products.
2017-25-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of a vertical strut penetrating through the cabin floor during an emergency water landing and on airframe ground contact at certain speeds/accelerations. This AD requires modification of the fuselage structure at a certain frame. We are issuing this AD to address the unsafe condition on these products.
2002-04-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that currently requires a visual check to determine the part and serial numbers of the upper lock link assembly of the nose landing gear (NLG); repetitive inspections of certain upper lock link assemblies to detect fatigue cracking; and modification of the NLG. The existing AD also provides for terminating action for the repetitive inspections. This amendment requires, among other actions, expanding the applicability of the existing AD, revising compliance times; and adding new inspection requirements. This amendment is prompted by a report indicating that an NLG upper lock link fractured prior to landing and jammed against the NLG shock strut, restricting the NLG from fully extending. The actions specified by this AD are intended to prevent the upper lock link assembly fromfracturing due to fatigue cracking, and the NLG consequently failing to extend fully; this condition could result in injury to passengers and flight crew, and damage to the airplane.
2023-04-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that the surface protection is missing between certain aluminum brackets and the struts to which they are attached in the flight deck air distribution system. This AD requires applying surface protection to the affected aluminum brackets and struts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits modifying an airplane using certain service information. The FAA is issuing this AD to address the unsafe condition on these products.