Results
2021-13-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD was prompted by a report that a production design change to certain insulation blankets inadvertently opened up leakage paths for halon and smoke to escape from the aft cargo compartment in the event of a fire. This AD requires installation of an insulation blanket assembly on top of existing insulation blankets in certain areas of the forward endwall in the aft cargo compartment. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam found in certain locations on the airplane; investigation revealed that the fire-retardant properties degrade with age. This AD requires inspecting the insulation blankets in certain areas of the forward cargo compartment for exposed BMS 8-39 urethane foam, not encapsulated by a protective fire resistant barrier, and for seal integrity, and replacing the BMS 8-39 urethane foam and seal if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
48-08-01: 48-08-01 BEECH: Applies to Model 35 Airplanes Having Serial Numbers Below D-1095 Except D-923, D-925, D-940, D-954, D975, D-983, D-1003, D-1006, D-1013, D-1025, D-1031, D-1038, D-1042, D-1048 Through D-1050, D-1052, D-1053, D-1056 Through D-1062, D-1064, D-1066 Through D-1068, D-1071, D-1072, D-1074, D-1075, D-1077 Through D-1081, D-1083, and D-1085 Through D-1093. Compliance required by November 1, 1948. To preclude possible engine malfunctioning as a result of starter gear chipping caused by improper engagement of the starter mechanism, accomplish the following: (1) Remove the starter assembly from the engine and replace the original starter pinion and clutch assembly with the new assembly, P/N DR1885537. Check the solenoid linkage adjustment to ascertain that the pinion and clutch assembly can move rearward to contact the starter adapter. If the linkage prevents full disengagement of the pinion, remove the toggle link pin and turn the plunger shaft outward untilfull retraction is obtained. Check to make sure that at least two threads are still engaged. Reinstall the starter assembly. (2) Install the new resistor coil, P/N DR 1885541, on the starter battery and ground power terminals. The coil must hang downward from the terminals. (3) Make all electrical connections as covered in Beech Starter Latching Relay Installation Instructions. (Continental Service Bulletin No. M47-19 dated August 31, 1947, and Beech Service Letter No. 10, Model 35, cover this same subject.)
98-03-16: This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft Corporation (Piper) Model PA-38-112 airplanes. This action requires repetitively replacing the upper rudder hinge bracket. Reports of fatigue cracks occurring on the upper rudder hinge bracket, and the manufacture of a new upper rudder hinge bracket with a life limited improved design prompted this action. The actions specified by this AD are intended to prevent cracks in the upper rudder hinge bracket, which could result in separation of the rudder from the airplane and loss of control of the airplane.
2011-12-06: 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: An inspection by the vendor revealed that a number of Rubber Bull Gears (RBG) in the Horizontal Stabilizer Trim Actuator (HSTA) of the CL-600-2C10, CL-600-2D15 and CL-600-2D24 aeroplanes were installed with a wheel material hardness out of specification. This non-conformity has a direct impact on the HSTA life limit. The teeth of these non-conformant RBGs could break and in extreme cases, could lead to uncontrolled HSTA movement without the ability to re-trim the aeroplane. If not corrected, this condition could result in a difficulty to control the pitch and subsequent loss of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-04-09: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires a one-time visual inspection to detect cracking of the brake torque tube lever, and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the brake torque tube lever, which could result in a disconnection between the brake pedal and brake system, and consequent reduced directional controllability of the airplane during landing.
90-25-08: 90-25-08 BOEING: Amendment 39-6816. Docket No. 90-NM-107-AD. \n\tApplicability: Model 747 and 767 series airplanes, equipped with Class "C" lower lobe cargo compartments that do not have complete cargo compartment floors, certificated in any category. \n\tCompliance: Required within 30 months after the effective date of this AD, unless previously accomplished; except that, for airplanes that are subject to the requirements of Federal Aviation Regulation (FAR) 121.314, the modifications required by this AD shall not be accomplished prior to the accomplishment of the modifications required by FAR 121.314. \n\tTo prevent a cargo compartment fire from migrating up behind the cargo liner, accomplish the following: \n\tA.\tInstall a fire stop near the bottom of the sloping sidewall cargo compartment liner, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Transport Airplane Directorate. Fire stop material must meet the requirements of FAR Part25, Appendix F, Part III. \n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\tThis amendment (39-6816, AD 90-25-08) becomes effective on January 2, 1991.
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.