Results
2005-20-11: 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) (RRC) Models 250-C28, - C28B, and -C28C turboshaft engines. This AD requires a onetime visual inspection of the seal joint in each passage between airfoils at the hub and shroud of third-stage turbine wheels, part number (P/N) 6899383. This AD results from reports of three failed third-stage turbine wheels and from the manufacturer's analysis of those failures. We are issuing this AD to prevent loss of power and uncommanded engine shutdown due to failure of the third-stage turbine wheel.
2017-10-23: We are adopting a new airworthiness directive (AD) for certain Airbus Model A321 series airplanes. This AD was prompted by a determination that cracks could develop on holes at certain fuselage frame locations. This AD requires repetitive inspections for cracking on holes at certain fuselage frame locations, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-10-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a report indicating that a portion of the sealant above the engine pylon between the wing skin and the vapor barrier might have been omitted. This AD requires an inspection for missing sealant in the seam on the outside and inside of the engine struts, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2003-17-07 R1: The FAA is revising an existing airworthiness directive (AD) that applies to various transport category airplanes manufactured by McDonnell Douglas. We issued that AD to require a one-time test of the fire extinguishers for the engine and auxiliary power unit (APU), as applicable, to determine the capability of the Firex electrical circuits to fire discharge cartridges, and troubleshooting actions if necessary. This new AD removes certain transport category airplanes from the applicability of the existing AD. This AD results from reports indicating that fire extinguishers for the engine and auxiliary power unit had failed to discharge when commanded. We are issuing this AD to prevent failure of the fire extinguishers to fire discharge cartridges, which could result in the inability to put out a fire in an engine or in the APU. \n\nDATES: The effective date of this AD is September 24, 2003. \n\n\tOn September 24, 2003 (68 FR 50058, August 20, 2003), the Director of the Federal Register approved the incorporation by reference of certain service bulletins listed in the AD.
80-13-08: 80-13-08 VARGA (Morrisey): Amendment 39-3808. Applies to Varga (Morrisey) Model 2150 and 2150A airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible reversal of throttle command, accomplish the following: (a) Within 50 hours' time in service from the effective date of this AD, or at the next annual inspection, whichever occurs sooner, install a throttle stop to limit the allowable throttle movement in accordance with Varga Service Letter SL 2150A-1 dated April 29, 1980. Adjust throttle linkage so that the crank arm does not come closer than 1/8 inch to the stop with the throttle in the most forward position. After installation, conduct engine ground power test to determine that full engine take off power is available. (b) 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 June 27, 1980.
2009-01-07: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Bombardier Aerospace has completed a system safety review of the CL-600-2C10/CL-600-2D24 aircraft fuel system against new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525-001 to determine if mandatory corrective action is required. This assessment showed that rupture of the fuel tank climb vent loop pipe or leakage from pipe couplings could result in fuel coming in contact with hot anti-ice ducts, creating potential fire on top of the centre fuel tank. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-07-20: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, and L1 helicopters that have not been modified in accordance with Eurocopter France Modifications 332A07-41.569 and 332A07-66.150. This action requires revisions to the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit flight into meteorological conditions that may produce lightning for helicopters that are not equipped with lightning-resistant tail rotor blades. A terminating action is provided in the AD by the installation of tail rotor blades having a lightning-resistant system. This amendment is prompted by the forced ditching of a Model AS 332 helicopter after experiencing a lightning strike. The actions specified in this AD are intended to prevent damage to the tail rotor blades that could result in loss of a tail rotor blade and subsequent loss of control of the helicopter.
61-25-02: 61-25-02 CONVAIR: Amdt. 373 Part 507 Federal Register November 29, 1961. Applies to All Model 22 (880) and Model 22M (880M) Aircraft. Compliance with paragraphs (a) and (b) required within 4,000 hours' time in service after effective date of this directive. Compliance with paragraph (c) is required on effective date of this directive. An inflight engine pod explosion occurred on a Model 22 airplane causing the loss of a nose cowl and portions of the side cowl panel doors. This incident has been attributed to an open starter bleed air supply valve causing continued rotation and subsequent overheating and disintegration of the air turbine starter. The following modifications and procedures are required to prevent the recurrence of this incident: (a) Provide a FAA approved cockpit indicating means by which it can be determined that each engine starter is de-energized. Approval of this item shall be processed through the FAA, Flight Standards Service, Engineeringand Manufacturing Branch, Western Region. (b) Concurrently with the incorporation of the modification described in paragraph (a), the Normal Procedures Section of the Models 22 and 22M FAA Approved Airplane Flight Manual, under that portion entitled "Engine Starting Procedure - Ground", shall be revised to include a provision that the flight crew determine that the cockpit indicating means required by paragraph (a) indicates that the starter is de-energized after each engine start. (c) Pending completion of the modifications required by paragraph (a) of this AD either install placard in the flight compartment on the pilot's start switch panel to read as follows: "Engine ground starts shall be made according to Convair Alert Service Bulletin No. 80-3", or revise the Normal Procedures Section of the Models 22 and 22M FAA Approved Airplane Flight Manual, under that portion entitled "Engine Starting Procedure - Ground", to provide for engine ground starts to be made according toConvair Alert Service Bulletin No. 80-3 or FAA Approved equivalent. This directive effective December 29, 1961.
2005-19-03: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAe Systems (Operations) Limited Model ATP airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This new AD requires a revision to the ALS of the Instructions for Continued Airworthiness to incorporate new inspections to detect fatigue cracking of certain significant structural items (SSIs) and to revise life limits for certain equipment and various components. This AD is prompted by a determination that existing inspection techniques are not adequate for certain SSIs and by the revision of certain life limits. We are issuing this AD to detect and correct fatigue cracking of certain structural elements, which could adversely affect the structural integrity of these airplanes.
2010-24-06: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. * * * * * Weare issuing this AD to require actions to correct the unsafe condition on these products.