Results
2004-06-04: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76 A, B, and C helicopters with dual channel autopilot and dual inverters installed. This action requires a test to determine if the No. 1 inverter is wired to the DC essential bus, and if so, it requires modifying the wiring so that the No. 1 inverter is wired to the No. 2 DC primary bus and the No. 2 inverter is wired to the DC essential bus. If the wiring modification is required and is not performed before further flight, then revising the Rotorcraft Flight Manual (RFM) before further flight to limit the maximum instrument meteorological conditions (IMC) airspeed and installing a placard near the airspeed indicator is also required. The wiring modification is required within 30 days. This amendment is prompted by three incidents in which a No. 2 generator intermittent malfunction occurred and both autopilots disengaged. The actions specified in this AD are intendedto prevent both autopilots from disengaging following a No. 2 DC generator failure, and subsequent loss of control of the helicopter during IMC operations.
2021-14-03: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 model turbofan engines. This AD was prompted by reports of HPT stage 1 blades failing in service due to sulphidation and subsequent crack initiation. This AD requires removal and replacement of the HPT stage 1 blade and HPT stage 1 blade damper. The FAA is issuing this AD to address the unsafe condition on these products.
2021-15-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 series airplanes as modified by a certain supplemental type certificate (STC). This AD was prompted by a report that the electrical diagram for the C9066 circuit breaker connection (wiring) for the ''Main Deck Oxygen Alert Control'' is erroneous and might have resulted in incorrect installation. This AD requires inspecting the wiring connection common to the C9066 circuit breaker and, if necessary, making changes to the wiring connection and testing the main deck oxygen alert system. The FAA is issuing this AD to address the unsafe condition on these products.
48-13-02: 48-13-02 BELL: Applies to Model 47 Series Equipped With Franklin 6V4-178-B3 and B32 Engines. Compliance required at next preflight inspection. Inspect fuel pump rocker pins to determine type. If pin has retaining rings which snap on each end, replace with new type pin having a head on one end and a staked washer on the other. Until new type pin is installed, daily inspection to determine the condition of the snap ring locks is required. A red paint dab for identification should be placed on all fuel pumps incorporating rocker pin change. Replacement pins are available through Aircooled Motors, Inc. (Franklin Service Bulletin No. 64 covers this same subject.)
2004-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A318, A319, A320, and A321 series airplanes. This action requires a one-time general visual inspection to determine the part number and serial number of both main landing gear (MLG) sliding tubes, and related investigative and corrective actions if necessary. This action is necessary to detect and correct cracking in a MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2011-11-01: We are adopting a new airworthiness directive (AD) for the products listed above. 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: As a result of fatigue-testing programme on Jetstream aeroplanes, cracks have been found on the main landing gear (MLG) fittings that embody modifications JM5218 or JM8003. This condition, if not detected and corrected, could lead to a MLG collapse on the ground or during landing, possibly resulting in a fuel tank rupture, consequent damage to the aeroplane or injury to the occupants. We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires repetitive inspections of the shim installation between the vertical flange and bulkhead. This AD is prompted by reports of cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting. We are issuing this AD to detect and correct such cracks, loose and broken bolts, and shim migration, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
2021-13-19: The FAA is superseding Airworthiness Directive (AD) 2014-11-02 for Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. AD 2014-11-02 required repetitively inspecting frame number (No.) 9 for a crack. This AD was prompted by Airbus Helicopters developing a modification that provides an optional terminating action for the repetitive inspections required by AD 2014-11-02. This AD retains the requirements of AD 2014-11-02, provides an optional terminating action for the repetitive inspections, and reduces the applicability by excluding certain post-modified helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
76-11-04: 76-11-04 DORNIER GmbH: Amendment 39-2631. Applies to Model Do 28D-1 airplanes certificated in all categories, serial numbers 4001 through 4039. Compliance is required as indicated, unless already accomplished. To prevent smoke and fire resulting from the chafing of teleflex engine control cables against electrical cables, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, visually inspect the electrical cable insulation under each engine for chafing damage at those points where the throttle and mixture control teleflex cables cross the electrical cables. Actuate the teleflex dables during the inspection. If a chafed electrical cable is found, repair the cable in accordance with paragraph (c) of this AD before further flight. (b) Within the next 100 hours time in service after the effective date of this AD, unless earlier compliance is required pursuant to paragraph (a) of this AD, comply with paragraph (c) of this AD. (c) Wrap helical Rapidon wear protection material, or FAA-approved equivalent material, around the electrical cables and teleflex cables under each engine in accordance with Dornier Service Bulletin 1031-1901, dated March 25, 1971, or an FAA approved equivalent. This amendment becomes effective June 15, 1976.
97-15-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-15-15, which was sent previously to all known U.S. owners and operators of Eurocopter France Model SA-365N, SA-365N1, and SA-366G1 helicopters by individual letters. This AD requires an inspection of the main gearbox magnetic plug (magnetic plug) and the main gearbox oil filter (oil filter) for ferrous chips; vibration measurements, if necessary; and replacement of the main gearbox if a specified quantity of ferrous chips are discovered, or if abnormal vibrations are identified at a certain frequency. This amendment is prompted by two recent reports of cracks found in planetary gear shafts (gear shafts) in main gearboxes that have not been modified in accordance with MOD 077244. The actions specified by this AD are intended to detect cracks in the gear shaft which could lead to failure of the gear shaft, failure of the transmission, and subsequent loss of control of the helicopter.