Results
2002-06-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300; A300-600; and A310 series airplanes. This action requires certain inspections of the airplane (including the vertical stabilizer, horizontal stabilizer, pylons, wing, and fuselage areas) following an in-flight incident resulting in extreme lateral loading. This action is necessary to detect and correct reduced structural integrity of the airplane following any future event. This action is intended to address the identified unsafe condition.
2025-07-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of engine-driven pump hydraulic pressure hoses for hydraulic systems number 1 and 2 chafing against the pylon in the aft equipment bay. This AD requires an inspection of the engine-driven pump pressure hoses for any damage and minimum clearance between the engine-driven pump hydraulic pressure hose and case drain, suction pressure hose, and surrounding pylon structure; and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-03-09 R1: This amendment revises an existing airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) LTS101 series turboshaft and LTP101 series turboprop engines. The existing AD will become effective on March 27, 2002, and requires a one-time visual inspection for surface finish and a one-time fluorescent penetrant inspection for cracks of certain impellers installed on LTS101 series turboshaft and LTP101 series turboprop engines. This amendment requires the same inspections, and in addition, allows installation of impellers that pass those inspections. This revision to the existing AD is prompted by an inadvertent omission in the existing AD to include allowance of installation of impellers that pass inspections required by the AD. The actions specified by this AD are intended to prevent impeller failure from cracks in the impeller back face area, which could result in an uncontained engine failure.
2002-03-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-03-52, sent previously to all known U.S. owners and operators of Eurocopter France (ECF) helicopters by individual letters. This AD requires checking for a gap between the adhesive bead and the metal bushing bonded on each STARFLEX star arm end (arm end) and, if a gap is found, replacing the STARFLEX with an airworthy part. This AD is prompted by reports of bonding failure between the metal bushing and the arm end that led to severe vibrations resulting in several emergency landings. The actions specified in this AD are intended to detect bonding failure between the metal bushing and each arm end, severe lateral vibrations, and subsequent loss of control of the helicopter.
2002-06-04: This amendment adopts a new airworthiness directive (AD) for specified Eurocopter France (ECF) helicopters that requires replacing the tail rotor hub pitch change plate "SNR" bearing (bearing). This amendment is prompted by fatigue cracks found in the bearings. The actions specified by this AD are intended to prevent seizure of the bearing, loss of tail rotor effectiveness, and subsequent loss of control of the helicopter.
74-06-02: 74-06-02 CESSNA AND PIPER: Amendment 39-1798. Applies to Cessna Models 150, 170, 172 and 175 and Piper Model PA-28-140 airplanes modified in accordance with STCs SA750CE, SA806CE, SA807CE, SA777CE or SA 793CE respectively utilizing Avcon Industries, Inc., kits incorporating defective mufflers. Compliance: Required as indicated, unless already accomplished. To prevent possible leakage of carbon monoxide into the cabin heater system, accomplish the following: A) Prior to further flight, except that the aircraft may be flown in accordance with FAR 21.197 to a base where the inspection may be performed provided that the cabin heater system is in the "Off" position and the cabin fresh air vents are open, and at repetitive intervals not to exceed 5 hours' time in service thereafter, inspect the muffler inner shroud as follows: 1) Remove muffler outer shroud assembly. 2) Visually inspect the inner shroud flare and tail pipe weld area for evidence of cracks orleakage. If cracks or leaks are found, replace the muffler prior to further flight with a serviceable unit. 3) If no cracks or leakage are found during the inspection, safety wire the cabin heat control in the "Off" position. B) Within the next 25 hours' time in service after the effective date of this AD, replace the existing muffler with a serviceable unit, at which time compliance with Paragraph A is no longer required. C) Any alternate method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Avcon Industries Service Letter No. 1, dated February 19, 1974, pertains to this subject matter. NOTE: The defective mufflers are contained in Avcon Kits of the following serial numbers: 556, 557, 562, 565, 580, 583, 584, 585, 588, 589, 591, 596, 597, 598, 599, 603, 604, 605, 608, 612, 618, 621, 623, 624, 627, 628, 632, 640, 642, 643, 644, 649, 650, 656, 659, 668, 669, 674 and 690. Confirmation ofaffected aircraft can be obtained by comparing the Avcon serial number stamped on the STC Kit I.D. tag with the Avcon serial number noted above. STC Kit I.D. tags are mounted near the aircraft manufacturer's I.D. tag. This amendment becomes effective March 18, 1974, to all persons except those to whom it was made effective by letter dated February 22, 1974.
2025-10-08: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by a report of potential use of improper material during the production of vertical tail plane (VTP) fittings. This AD requires, for certain airplanes, an inspection for the material of affected fuselage-to-VTP fittings, an inspection report, and corrective actions, and, for certain other airplanes, part replacement, 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.
73-11-02: 73-11-02 PIPER: Amdt. 39-1639 as amended by Amendment 39-1649 is further amended by Amendment 39-1747. Applies to Model PA-34-200 airplanes Serial Numbers 34-E4 and 34-7250001 through 34-7450039 certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours time in service from the last inspection. To detect weakening of the main landing gear support structure, accomplish the following: (a) Visually check both left and right wing lower surface skins for wrinkling immediately outboard of the wheel well openings. (b) If wrinkles are present, visually check the wing ribs located at the outer end of the wheel wells (wing station 69.24) for cracks and/or wrinkles in the web. These cracks or wrinkles emanate from the forward lower corner where the rib attaches to the main spar and may propagate toward the aft upper corner of the web. (c) If wrinkles are present and Aft Wing Modification Kit, Piper Part No. 760 696V, has not been installed, check the area where the main landing gear aft trunnion fitting attaches to the aft false spar for cracks. (d) If cracks or wrinkles are present in the areas described in (b) or (c), replace affected parts with serviceable parts of the same part number or make an FAA approved repair before further flight. The checks required by paragraphs (a), (b) and (c) should also be accomplished after unusually fast and/or hard landings. Piper Service Bulletin No. 369 pertains to this subject. The initial inspection and repetitive inspections at 10 hours intervals are still required after compliance with Piper Service Bulletin No. 369, and/or after repair/replacement of the rib has been accomplished. The checks required by paragraph (a) may be performed by the pilot. When aft wing modification kit Piper Part No. 760 696V has been installed and the inspection and reservicing of the main landing gear oleo struts has been accomplished in accordance with the "Instructions" section of Piper Service Bulletin No. 406, the repetitive inspections in (a), (b), and (c) above are no longer necessary. NOTE: Serial Numbers 34-7250023; 34-7250090; 34-7250203; 34-7250262; 34- 7250275; 34-7250282; 34-7250290; 34-7250296; 34-7250316; 34-7250317; 34-7250319; 34- 7250322; 34-7250325; 34-7250326; 34-7250328; 34-7250330; 34-7250331; 34-7250333; 34- 7250334; and 34-7250336 and up have had Piper Kit No. 760696V installed at the factory. Amendment 39-1639 became effective May 21, 1973. Amendment 39-1649 became effective May 31, 1973. This Amendment 39-1747 becomes effective December 3, 1973.
2023-06-11: The FAA is adopting a new airworthiness directive (AD) for Viking Air Limited (type certificate previously held by Bombardier Inc. and de Havilland Inc.) Model DHC-2 Mk. I airplanes with Supplemental Type Certificate (STC) No. SA01324CH installed. This AD was prompted by a report of damage in the main wing spar. This AD requires inspecting the wing structure for damage (drill starts, corrosion, cracks, and improperly installed fasteners), repairing damage, and reporting the inspection results if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2023-04-11: The FAA is superseding Airworthiness Directive (AD) 2012-02-07 for certain General Electric Company (GE) CF6-45 and CF6-50 series model turbofan engines with a specified low-pressure turbine (LPT) rotor stage 3 disk installed. AD 2012-02-07 required inspections of high-pressure turbine (HPT) and LPT rotors, engine checks, vibration surveys, an optional LPT rotor stage 3 disk removal after a failed HPT blade borescope inspection (BSI) or a failed engine core vibration survey, established a lower life limit for the affected LPT rotor stage 3 disks, and required removing these disks from service at times determined by a drawdown plan. This AD was prompted by the occurrence of four events of separation of the LPT rotor assembly, which resulted in the LPT rotor assembly departing the rear of the engine. This AD requires inspections of HPT and LPT rotor stage 1 and stage 2 blades, vibration surveys, and use of a lower life limit for the affected LPT rotor stage 3 disks and, as terminating action to the inspections, engine checks, and vibration surveys, this AD requires removal and replacement of the LPT rotor stage 3 disk with a redesigned LPT rotor stage 3 disk. This AD also requires revising the compliance time of the drawdown plan for the removal and replacement of the LPT rotor stage 3 disk and prohibits the installation or reinstallation of certain LPT rotor stage 3 disks. The FAA is issuing this AD to address the unsafe condition on these products.