Results
2014-07-52: We are publishing a new airworthiness directive (AD) for certain Airbus Helicopters (previously Eurocopter France) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires repetitively inspecting certain reinforcement angles of the rear structure to tailboom junction frame (reinforcement angles) for a crack, and repairing any cracked reinforcement angle. This AD is prompted by a report that cracks were found in the reinforcement angles on several AS355 helicopters. These actions are intended to detect a crack in the reinforcement angle, which if not corrected, could result in loss of the tailboom and subsequent loss of control of the helicopter.
2014-11-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters to require repetitively inspecting frame number (No.) 9 for a crack. This AD was prompted by a report of a crack in frame No. 9 on an AS365 helicopter. The actions of this AD are intended to detect a crack and prevent loss of structural integrity and subsequent loss of control of the helicopter.
75-23-04: 75-23-04 MOONEY: Amendment 39-2415. Applies to all Mooney Model M20 series airplanes equipped with Mooney Electric Gear Systems incorporating a Dukes electric landing gear actuator, P/N 4196-00-1C. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed the time in service from the last inspection specified in Paragraphs (a) and (b). To prevent further failures of the electric landing gear actuator, Dukes P/N 4196-00-1C, accomplish the following: (a) Within the next 25 hours time in service, accomplish Parts I and III, and thereafter at every 200 hours time in service, accomplish Part I of Mooney Aircraft Corporation Service Bulletin M20-190, dated January 16, 1975, or later FAA approved revision, or by an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. (b) Within the next 25 hours time in service, and thereafter at every 100 hours time in service, accomplish Part II of Mooney Aircraft Corporation Service Bulletin M20-190 dated January 16, 1975, or later FAA approved revision, or by an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain a copy upon request to Mooney Aircraft Corporation, P. O. Box 72, Kerrville, Texas 78028. This document may also be examined at the office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective on December 8, 1975.
2014-11-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a non-connection of the constant speed motor/generator (CSM/G) during a final assembly operational test. This AD requires a detailed inspection of the connector wires for connector 1XE-A of the generator control unit (GCU)-CSM/ [[Page 33046]] G for discrepancies (evidence of arcing or overheating damage), and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct incorrect locking of contacts into connector 1XE-A of the GCU-CSM/G, which could result in a loss of contact continuity and lead to the CSM/G not operating, which, in conjunction with an emergency electrical configuration loss of the main electrical system or total engine flameout, could adversely affect the airplane's safe flight.
2014-11-09: We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a cracked engine mount. We are issuing this AD to require actions to address the unsafe condition on these products.
74-23-05: 74-23-05 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-2008. Applies to AiResearch Model TFE731-2-2B and -2-1C engines installed in, but not limited to, AMD Falcon DA-10 and Lear-Gates Models 35 and 36 aircraft certificated in all categories. (A) Upon receipt of this telegram, except as authorized in (C) below, P/N 3070851-2, -4, -5, and -6 fuel pumps with less than 25 hours total time in service must be replaced before exceeding 25 hours total time in service. Fuel pumps with more than 25 hours total time in service must be replaced before further flight. (B) The maximum service life of P/N 3070851-2, -4, -5, and -6 fuel pumps is 25 hours total time in service since new or overhaul. (C) AiResearch Service Bulletin TFE731-73-3005, dated July 10, 1974, provides instructions for inspecting and re-identifying P/N 3070851-5 and -6 fuel pumps which have been determined to conform to the -7 and -8 configuration. (D) P/N 3070851-7 and -8 fuel pumps are not subject to the service life limit prescribed in (A) above and may be installed in accordance with AiResearch Service Bulletin TFE731-73-3005, dated July 10, 1974, or later FAA-approved revisions. (E) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. (F) Aircraft may be flown to a base for performance of maintenance required by the AD per FAR's 21.197 and 21.199. This supersedes telegram dated June 4, 1974 and AD 74-13-08. This amendment becomes effective November 14, 1974, for all persons except those to whom it was made effective immediately by telegram dated June 4, 1974.
98-11-03 R1: This amendment corrects information in an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires that the FAA-approved maintenance inspection program be revised to include inspections that will give no less than the required damage tolerance rating for each Structural Significant Item (SSI), and repair of cracked structure. The actions specified in that AD are intended to ensure the continued structural integrity of the entire Boeing Model 727 fleet. This amendment corrects the requirements of the current AD by allowing operators not to change their programs if they determine that the existing inspections are effective for the new or affected SSI. This amendment is prompted by a review of the requirements of the existing AD. \n\n\tThe incorporation by reference of a certain publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 23, 1998 (63 FR 27455, May 19, 1998).
2014-11-06: We are adopting a new airworthiness directive (AD) for certain airplanes originally manufactured by Lockheed Martin Aeronautics Company for the military as Model P-3A or P3A airplanes. This AD was prompted by a determination that the existing maintenance or inspection program must be revised to address fatigue cracking of the airplane. This AD requires revising the maintenance or inspection program, as applicable, to incorporate certain limitations. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the airplane.
2014-11-08: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC225LP helicopters to require measuring the operating load of the cockpit fuel shut-off controls and replacing the tangential gearbox if the operating load threshold is exceeded. This AD was prompted by the jamming of the left-hand (LH) side of the fuel shut-off and general cut-off controls (controls). The actions of this AD are intended to prevent the jamming of the controls so that a pilot can shut down an engine during an engine fire or during an emergency landing.
2014-10-03: We are adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332L1 and Model EC225LP helicopters. This AD requires relocating the power supply circuit breaker source of one engine's multi-purpose air intake (MPAI). This AD is prompted by a report that power loss to the MPAI could open the engine air intakes, which could result in engine ice ingestion during flight in icing conditions. These actions are intended to prevent ice ingestion by both engines, which could result in complete loss of engine thrust, and possible loss of control of the helicopter.
2014-10-01: We are superseding airworthiness directive (AD) 2008-24-11 for Vulcanair S.p.A. Model P68 airplanes. This AD results from 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 describes the unsafe condition as cracking and/or corrosion of the wing spar. We are issuing this AD to require actions to address the unsafe condition on these products.
2021-11-18: The FAA is superseding Airworthiness Directive (AD) 2019-03- 10, which applied to all Airbus SAS Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2019-03-10 required repetitive detailed visual inspections of the main landing gear (MLG) leg components and replacement of the MLG leg if cracked components are found. This AD continues to require the actions required by AD 2019-03-10. For certain airplanes, this AD also requires modification of the MLG hinge arm by installing improved MLG hinge arm/barrel pins; an out-of-roundness check of removed pins; repetitive inspections of any affected pins and the associated connecting rod bushes, and replacement of the MLG leg if cracked components are found; and installation of an improved spacer; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference.This AD was prompted by reports of cracks in MLG leg components and a determination that additional actions (including inspections, modifications, and checks) are needed to address the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2014-09-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of bearing damage at certain trailing edge (TE) flap support rib assemblies. This AD requires inspecting certain TE flap support rib assemblies to determine if the bearings have a roller retention feature, and performing corrective actions if necessary; and inspecting for bearing damage of each pair of removed bearings, and performing related investigative and corrective actions if necessary. We are issuing this AD to detect and correct damage to the TE flap support bearings, which could ultimately result in loss of controllability of the airplane.
2014-09-04: We are superseding Airworthiness Directive (AD) 2009-21-08 R1 for Piaggio Aero Industries S.p.A Model P-180 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cases of un-commanded operation of switched off nose-wheel steering system caused by internal leakage of a steering select/bypass valve. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-08-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2003-08-51, which was sent previously to all known U.S. owners and operators of the specified model MD Helicopters, Inc. helicopters by individual letters. This AD requires reducing the retirement life of certain tail rotor blades, performing a one-time visual inspection of each tail rotor blade pitch horn (pitch horn) for a crack or corrosion, and replacing unairworthy tail rotor blades with airworthy tail rotor blades. This AD also requires revising the Airworthiness Limitations section of the helicopter maintenance manual to reflect the reduced retirement life, and reporting information to the FAA within 24 hours following the one- time inspection. The actions specified by this AD are intended to prevent a pitch horn from separating from the tail rotor blade, leading to an unbalanced condition, vibration, loss of tail rotor pitch control, and loss of directional control of thehelicopter.
2014-09-01: We are adopting a new airworthiness directive (AD) for Agusta Model A109C, A109E, A109K2, and A119 helicopters. This AD requires a recurring visual inspection of the tail rotor (T/R) blade retaining bolts (bolts) for a crack, corrosion, damage, or missing cadmium plating in the central part of the bolt and, depending on findings, a liquid penetrant inspection. This AD also requires replacing a cracked or damaged bolt. This AD was prompted by two reported incidents of cracked bolts. The actions of this AD are intended to detect an unairworthy bolt and prevent failure of a bolt, release of a T/R blade, and subsequent loss of control of the helicopter.
2014-09-03: We are superseding Airworthiness Directive (AD) 99-07-11 for SOCATA Model TBM 700 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks on the outboard hinge fittings. We are issuing this AD to require actions to address the unsafe condition on these products.
94-12-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect fatigue-related skin cracks and corrosion of the skin lap joints in the fuselage upper lobe, and repair, if necessary. This amendment also requires modification of certain lap joints and inspections of modified lap joints. This amendment is prompted by a structural review of Model 747 series airplanes. The actions specified by this AD are intended to prevent rapid decompression of the airplane and the inability to carry fail-safe loads, due to the problems associated with fatigue cracking and corrosion.
51-11-02: 51-11-02 CESSNA: Applies to All Models 190 and 195 Aircraft Serial Numbers 7004 to 7474 and 7476 to 7479, Inclusive. Compliance required not later than June 1, 1951, and upon each 100 hours of operation thereafter until reinforcing doublers are installed at outboard hinge fittings. Inspect for fatigue cracks in the elevator spar webs at the outboard hinges. This may be accomplished by loosening the two attaching bolts as necessary to facilitate inspection for cracks at the bolt holes. Cracks extending less than 3/4 inch beyond the hinge fitting should be stop- drilled and reinforcing doublers, Cessna P/N 10008-11-2 and -3, should be installed on the forward side of the spar. If any cracks are longer than 3/4 inch, the spar should be replaced and the reinforcing doublers added. (Cessna Service Letter No. 10 dated November 18, 1949, covers this same subject.)
2021-11-19: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) (Bell) Model 505 helicopters. This AD was prompted by the discovery of a gap between the transmission restraint assembly aft attachment hardware lower washer and mating airframe truss assembly (truss assembly) clevis lower lug. This AD requires inspecting the transmission restraint aft attachment hardware installation for a gap and corrective action depending on the inspection results. The FAA is issuing this AD to address the unsafe condition on these products.
98-26-01: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires various inspections to detect fatigue cracks at certain locations on the fuselage, horizontal stabilizer, and wings and tail, and repair or modification, if necessary; and installation of doublers. This amendment also adds new inspections and reduces certain inspection intervals. This amendment is prompted by results of full-scale fatigue testing of a Model A310 series airplane, which revealed fatigue cracks at those locations. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage, horizontal stabilizer, and wings.
2014-09-02: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LLC Models SA26-T, SA26-AT, SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-TT, SA227-BC (C-26A), SA227-CC, and SA227-DC (C-26B) airplanes. This AD was prompted by reports of jamming of the aileron control cable chain in the pilot and copilot control columns due to inadequate lubrication and maintenance of the chain. This AD requires repetitively replacing and lubricating the aileron chain, sprocket, and bearings in the control columns. We are issuing this AD to correct the unsafe condition on these products.
2003-13-10: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) models 250-C30R/3, -C30R/ 3M, -C47B, and -C47M turboshaft engines. This AD requires initial and repetitive electrical signal inspections of the hydromechanical unit (HMU) Power Lever Angle (PLA) potentiometer. This AD is prompted by an investigation by the National Transportation Safety Board (NTSB), which revealed that a potential undetected failure of the PLA potentiometer electrical signal could cause uncommanded and sudden changes in engine power. The actions specified in this AD are intended to prevent uncommanded and sudden changes in engine power.
87-08-01: 87-08-01 AVIONS PIERRE ROBIN: Amendment 39-5601. Applies to Model R2160 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To preclude the loss of rudder control, accomplish the following: (a) Within the next 10 hours time-in-service (TIS) after the effective date of this AD, visually inspect for cracks the area of each rudder bar adjacent to the point where the vertical and horizontal tubes are joined in accordance with the instructions of Avions Pierre Robin Service Bulletin (S/B) No. 109, dated April 28, 1986 (hereinafter referred to as APR S/B No. 109). If any crack is found, before further flight, reinforce all the rudder bars in accordance with the modification specified in APR S/B No. 109. (b) Within the next 100 hours TIS after the effective date of this AD, unless previously modified in accordance with paragraph (a) of this AD, reinforce all the rudder bars in accordance withthe modification specified in APR S/B No. 109. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 1000 Brussels, Belgium. All persons affected by this directive may obtain a copy of the document referred to herein upon request to Avions Pierre Robin, Aerodrome de DIJON-Val-Suzon, Darois, Fontaine-Les-Dijon, France F-21121; or may examine the document referred to herein at FAA, office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on April 20, 1987.
2014-08-01: We are superseding Airworthiness Directive (AD) 2014-03-08 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014- 03-08 required an inspection to determine the part number of the interconnecting struts installed on the wings, identifying the part number and the serial number of the associated target and proximity sensor if applicable, and replacing or re-identifying the flap interconnecting strut if applicable. This new AD corrects a typographical error that affects the definition of a serviceable interconnecting strut. This AD was prompted by a report that an investigation showed that when a certain combination of a target/ proximity sensor serial number is installed on a flap interconnecting strut, a ``target FAR'' signal cannot be detected when it reaches the mechanical end stop of the interconnecting strut. We are issuing this AD to detect and correct a latent failure of the flap down drive disconnection due to an already-failed interconnecting strut sensor, which could result in asymmetric flap panel movement and consequent loss of control of the airplane.