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80-14-03: 80-14-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3810. Applies to the following airplanes certificated in all categories equipped with Bendix, King or Narco transmitters with factory installed control wheel push-to-talk switches. \n\n\nModels Affected\nSerial Numbers Affected \nPA-28-161 Warrior II\n28-7816001 through 28-8016289 \nPA-28-181 Archer II\n28-7890001 through 28-8090266 \nPA-28-201T Turbo Dakota\n28-7921001 through 28-7921091 \nPA-28-236 Dakota\n28-7911001 through 28-8011096\nPA-28R-201 Arrow III\n28R-7837001 through 28R-7837317 \nPA-28RT-201 Arrow IV\n28R-7918001 through 28R-8018049 \nPA-28R-201T Turbo Arrow III\n28R-7803001 through 28R-7803373 \nPA-28RT-201T Turbo Arrow IV\n28R-7931001 through 28R-8031074 \nPA-32-260 Six\n32-7800001 through 32-7800008\nPA-32-300 Six 300\n32-7840001 through 32-7940290 \nPA-32-301 Saratoga\n32-8006001 through 32-8006015 \nPA-32-301T Turbo Saratoga\n32-8024001 through 32-8024007 \nPA-32R-300 Lance\n32-7880001 through 32-7880068 \nPA-32RT-300 Lance II\n32R-7885001 through 32R-7985105\nPA-32RT-300T Turbo Lance II\n32R-7787001, 32R-7887002 through 32R-7987126 \nPA-32R-301 Saratoga SP\n32R-8013001 through 32R-8013071 \nPA-32R-301T Turbo Saratoga SP\n32R-802900 1 through 32R-8029068 \nPA-34-200T Seneca II\n34-7870001 through 34-8070150 \nPA-44-180 Seminole\n44-7995001 through 44-8095020 \n\n\tCompliance is required as indicated unless already accomplished to prevent disruption of radio communication. \n\n\t(a)\tWithin the next 10 hours time in service after the effective date of this AD, comply with the following: \n\n\t\t(1)\tLocate the audio adapter connector in the main radio harness behind the radio stack. This is the interconnect for individual radios in the audio selector panel. \n\t\n\t\t(2)\tLocate the muting relay plug in this connector. It is a three (3) pin plug containing wires ASP-1, ASP-2, and ASP-3 and is positioned at one end of the adapter connector. \n\n\t\t(3)\tDisconnect the muting relay plug and attach securely to the harness in accordance with Advisory Circular AC43.13-1A. \n\n\t\t(4)\tConduct complete operational check of all radios. \n\n\t\t(5)\tMake a maintenance record entry. \n\n\t(b)\tWithin the next 100 hours time in service after the effective date of this AD, comply with the following: \n\n\t\t(1)\tOn PA-32-260, PA-32-3O0, PA-32-301, PA-32-301T, PA-32R-300, PA- 32RT-300, PA-32RT-300T, PA-32R-301, PA-32R-301T and PA-34-200T model aircraft gain access by removing four (4) screws from the speaker grille ring. On all other affected models, gain access by lowering the overhead dome panel. \n\n\t\t(2)\tRemove the 22 mfd capacitor, part number 454-045, soldered to the muting relay, noting polarity, and install diode as shown in figure 1. Diode is not required on Bendix avionics systems. \n\n\t\t(3)\tReconnect the muting relay plug and conduct radio check for proper operation. \n\n\t\t(4)\tMake a maintenance record entry. \n\n\tPiper Service Bulletin No. 681 applies to the same subject. \n\n\tAny equivalent method of compliance with this Airworthiness Directive may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. \n\n\tThis amendment becomes effective July 1, 1980.
80-13-10: 80-13-10 DEHAVILLAND: Amendment 39-3812. Applies to DeHavilland Model DHC- 6 airplanes fitted with main landing gear legs which have not been inspected in accordance with DeHavilland Modification No. 6/1660. To prevent possible failure of the main landing gear legs at the Y-joint weld, accomplish the following: (a) Within the next 10 hours in service, unless accomplished within the last 590 hours in service, inspect the weld juncture at the Y-joint of the main landing gear legs for cracks using dye penetrant or X-Ray inspection methods. If dye penetrant inspection is used, all paint must be removed from the Y-joint weld junction area, and the area must be reprotected after completion of the inspection. If X-Ray inspection is used, paint removal is not required. An acceptable X-Ray method calls for a Phillips 300 KVA constant potential unit or equivalent with exposure of 250 KV and 10 milliamps (MA) for 2.5 minutes. The film to focal spot distance is to be 48 inches with a focal spot size of 4 mm square. Use Kodak Type AA film or equivalent sandwiched between .010 inch thick lead screens in flexible cassettes. The leg material is HY-TUF to AMS 6418B specifications. (b) If no cracks are found, repeat the inspection in Paragraph (a) at intervals not to exceed 600 hours in service or six months, whichever occurs first, until the "D" inspection or equivalent, per DeHavilland Maintenance Manual PSM 1-6-2, is accomplished by 6000 hours in service. (c) Within the next 50 hours in service, unless accomplished within the last 2350 hours in service, inspect the inside of the leg assembly around the crevice location at the Y-joint in accordance with the method noted in Paragraph (e)(1) of this directive for the presence of corrosion and integrity of the internal finish coat. If no corrosion or failure of the inner coat is found, repeat the inspection at intervals not to exceed 2400 hours in service or one year, whichever occurs first, until the "D"inspection, or equivalent, of the leg is accomplished. (d) When complying with Paragraphs (a), (b), or (c) of this directive, (1) If cracks are found, repair in accordance with a method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or replace before next flight with a part satisfactorily inspected in accordance with Paragraphs (a) and (c) of this directive. (2) If irregularities are found in the internal finish coat integrity, or if internal corrosion is detected, repair in accordance with DeHavilland Overhaul Manual PSM 1-6- 6, Chapter 32-10-11, revised December 15, 1978, or equivalent, before next flight. (e) For inspection and repair of the main landing gear leg: (1) For an internal inspection, a borescope requiring removal of the leg assembly may be used. X-Ray inspection, or equivalent, which does not require removal of the leg assembly, also may be used. X-Ray inspection is to be accomplished in accordance with Paragraph (a) of this directive. (2) Remove and install the main landing gear leg in accordance with procedures specified in DeHavilland Maintenance Manual PSM 1-6-2 Part 2 or PSM 1-63-2 Chapter 32-00-00, or an equivalent. (3) For local removal of the leg finish and details of a "D" inspection of the leg, comply with Maintenance Manual PSM 1-6-2 Temporary Revision No. 85 or PSM 1-63-2 Chapter 32-10-11, Temporary Revision No. 32-8 dated December 15, 1978, or an equivalent. (4) Disassemble the leg, clean and remove internal and external protective treatment in accordance with Overhaul Manual PSM 1-6-6 Chapter 32-10-11, revised December 15, 1978, or an equivalent. (f) After accomplishment of the "D" inspection, or equivalent, no further action is required for compliance with this AD. (g) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance times specified in this AD. (h) Equivalent inspection procedures and repairs may be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (i) The aircraft may be flown in accordance with FAR 21.197 to a base where the inspection or repairs can be performed. This amendment is effective July 1, 1980.
80-15-05: 80-15-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 3845. Applies to Model AS 350 series and Model SA 365C series helicopters with spherical thrust bearing rear block P/N 704A-33-633-27 or P/N 704A-33-633-30 installed, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent the failure of the spherical thrust bearing rear block, accomplish the following: (a) Within the next five hours time in service after the effective date of this AD, unless already accomplished, inspect the spherical thrust bearing rear block, P/N 704A-33-633-27 or P/N 704A-33-633-30 (hereinafter referred to as the block) to determine the serial number of the block and, if appropriate, comply with paragraph (b) of this AD. (b) If as a result of the inspection required by paragraph (a) of this AD, the block is found to have a serial number other than one listed in paragraph 1A, "Effectivity", of Aerospatiale Service Bulletin AS350 No. 01-03, dated July 4, 1979, or an FAA-approved equivalent, or Aerospatiale Service Bulletin SA 365 No. 01-04, dated July 4, 1979, or an FAA- approved equivalent, as appropriate (hereinafter referred to as the applicable service bulletin), return the block to service. (c) If as a result of the inspection required by paragraph (a) the block is found to have a serial number listed in paragraph 1A, "Effectivity", of the applicable service bulletin, before further flight - (1) Remove the block from service; (2) Return the block to the factory in accordance with paragraph 1C(2) of the applicable service bulletin; and (3) Replace the block with a serviceable block of the same part number which has a serial number not listed in paragraph 1A of the applicable service bulletin, or a serviceable block of the same part number which has a serial number listed in paragraph 1A, but which is also marked as noted in paragraph 1C(2) of the applicable service bulletin.(d) Before installation of blocks held as spares, inspect them and - (1) Return to the factory those blocks which have serial numbers listed in paragraph 1A of the applicable service bulletin in accordance with paragraph 1C(2) of the applicable service bulletin; and (2) Retain as serviceable those blocks which have serial numbers listed in paragraph 1A of the applicable service bulletin but are also marked as noted in paragraph 1C(2) of the applicable service bulletin. (e) For purposes of complying with this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This amendment supersedes telegraphic AD T79EU-9, issued August 14, 1979. This amendment becomes effective July 14, 1980.
2023-09-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that certain environmental control system (ECS) pre-cooler clamp assemblies may not conform to specifications. This AD requires an inspection of the pre-cooler clamps and replacement of non- conforming pre-cooler clamps. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-11: This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney JT9D series turbofan engines. That AD currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
80-01-08: 80-01-08 PIPER: Amendment 39-3653. Applies to Models PA-31T serial numbers 31T-7920001 thru 7920068, 7920070 thru 7920080; and PA-31T1 serial numbers 31T-7904001 thru 7904044. Compliance required within the next 25 hours of operation as indicated unless already accomplished. To preclude the necessity of inflight engine shutdown due to oil loss caused by leakage of the oil cooler inlet hose assembly, accomplish the following on each engine: Remove engine cowlings and remove oil cooler inlet hose, P/N 80026-05. Cap engine outlet immediately upon removal of hose. Remove the band clamp from the 90-degree fitting end of the fire sleeve and pull fire sleeve back as far as possible to inspect steel braiding for kinking. If kinking is found, replace hose. (Note: Kinking will usually be noticed on the steel braiding between the midpoint of the hose and the 90-degree fitting end.) If no evidence of kinking is found and with band clamp still removed, pressure test hose to 500 psi using dry nitrogen with hose submerged in water. (Note: A suitable pressure test arrangement is to cap both ends of the hose with appropriate AN hardware items, one of which has been drilled and fitted with a Schrader valve.) If leakage is observed, replace hose with a new oil inlet hose, P/N 80026-05. If test indicates no leakage, install new band clamp on fire sleeve. Reinstall tested hose or new hose as required per above instructions. Reinstall support clamp, maintaining the maximum possible bend ratios to prevent kinking of hose, check engine oil supply, and replenish if necessary. Run engine; insure that no oil leaks exist, and reinstall cowling. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration (FAA), Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. Piper Telex F.L.31-22A dated August 17, 1979, and Emergency Airworthiness Directive dated August 13, 1979, pertain to this subject. This amendment is effective January 14, 1980, and was effective upon receipt by all addressees of an airmail letter, dated August 13, 1979, on this same matter.
80-09-04: 80-09-04 PIPER AIRCRAFT CORPORATION: Amendment 39-3749. Applies to Model PA-34-200, serial numbers 34-E4, 34-7250001 through 34-7450220, Model PA-34-200T, serial numbers 34-7570001 through 34-7770441, airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent elongation or cracking of fitting holes and wearing of attaching nuts and bolts of the vertical fin attachment fittings and stabilator attachment and stabilator hinge assembly, accomplish the following within 25 hours time in service after the effective date of this AD: a. Inspect, replace parts and modify, as necessary, the vertical fin attachment fittings and stabilator attachment and stabilator hinge assembly in accordance with Piper Aircraft Corporation Service Bulletin No. 579, dated November 14, 1977, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. b. Make appropriate maintenancerecord entry. This amendment becomes effective April 24, 1980.
79-26-05: 79-26-05 AIRCRAFT METAL PRODUCTS CORPORATION: Amendment 39-3645. Applies to all general aviation airplanes with Aircraft Metal Products oil and fuel system hoses P/N 762506 installed. The subject hose is known to be installed on, but not limited to, certain Piper Model PA-28 and PA-32 aircraft. To prevent possible fire or explosion in the engine compartment or engine failure due to loss of engine oil, accomplish the following within 10 hours time in service from the effective date of this AD: (a) Inspect hoses for fluid leakage, excessive abrasion or excessive length. Replace hose if fluid leakage, excessive abrasion or excessive length exists. (b) Loosen each coupling fitting and notice if hose moves in direction of fitting, indicating a pre-existing hose twist. Replace the hose if there is evidence of a pre-existing hose twist. (c) Retighten each coupling fitting, gripping the collar just behind the fitting with pliers with just enough force to keep the hose from turning with the retightened fitting. If the hose turns with the retightened fitting, loosen the coupling fitting and repeat the retightening procedure. (d) Inspect the hose installation for adequate separation between metal hose and other parts of the airplane. If there is contact between metal parts, then complete insulation must be provided using AN742 cushion clamps and/or KOROSEAL lacing or equivalent. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective January 3, 1980.
2023-09-11: The FAA is superseding Airworthiness Directive (AD) 2019-24- 13, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-24-13 required repetitive high-frequency eddy current (HFEC) inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions. This AD was prompted by a determination that certain inspection times need to be revised. This AD retains the requirements of AD 2019-24-13, with amended compliance times, 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.
2023-09-12: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12, PC-12/45, PC-12/ 47, and PC-12/47E airplanes. This AD is prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as insufficient grounding of the vapor cycle cooling system (VCCS) compressor/condenser. This AD requires inspecting the power return and chassis grounding cable attachment points at frame 37, including the attachment parts, and depending on the inspection results, corrective action. This AD also requires modifying the installation of the VCCS compressor/condenser power return cables and installing an additional isolated VCCS chassis ground cable. The FAA is issuing this AD to address the unsafe condition on these products.