Results
2022-09-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report of smoke in the aft cabin during a maintenance activity, which an investigation determined was caused by a faulty drain line ribbon heater. This AD requires a general visual inspection of all affected potable water-line ribbon heater installations and corrective actions and other specified actions. The FAA is issuing this AD to address the unsafe condition on these products.
2004-16-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires repetitive inspections for cracking of the chromed area of the left and right piston rods for the main landing gear (MLG) retraction actuators, and related investigative and corrective actions if necessary. This AD is prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We are issuing this AD to detect and correct corrosion pitting and cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG.
99-15-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-200 and -300 series airplanes, that currently requires various inspections and functional tests to detect discrepancies of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment reduces the repetitive interval for one certain functional test. This amendment is prompted by reports indicating that several center drive units (CDU) were returned to the manufacturer of the CDU's because of low holding torque of the CDU cone brake. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
99-15-13: This amendment supersedes Airworthiness Directive (AD) 98-09-09, which currently requires replacing the internal cooling air fan with a fan that incorporates a white impeller on all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASH 26E sailplanes. This AD requires inspecting the internal cooling air fan for damage, and replacing any fan that does not incorporate a black impeller with a fan that incorporates a black impeller either immediately or at a certain time period, depending on the results of the inspection. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the internal cooling system air fan caused by a certain design configuration of the impeller, which could cause the engine to overheat with possible engine failure.
2022-08-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-800 series airplanes. This AD was prompted by the determination that insufficient sealing may allow water to enter the lower lobe electronic equipment (EE) bay through the main deck floor structure at the rigid cargo barrier (RCB), which could cause damage to EE bay line replacement units (LRUs) in the E5 rack. This AD requires detailed inspections for the presence and condition of sealant at certain locations and applicable on-condition actions. This AD also requires replacing the moisture barrier tape at a certain location, replacing the weather seal at a certain location, and installing seat track fillers. The FAA is issuing this AD to address the unsafe condition on these products.
70-12-01: 70-12-01 GENERAL DYNAMICS: Amdt. 39-1000. Applies to all Model 340 and 440 Series airplanes including those modified in accordance with STC SA4-1100 or STC SA1096WE. Compliance required as indicated. Within the next 50 hours time in service, after the effective date of this AD, unless already accomplished within the last 450 hours time in service, visually inspect MLG beam webs P/N 340-1650551-7, -8, -53 and -54 for crack indications in the upper flange radius area by dye penetrant inspection procedures, in accordance with General Dynamics 640-(340D) Service Bulletin No. 57-3, dated April 17, 1970, or later FAA approved revision, or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (a) If no cracks are found, repeat the inspection procedure outlined above at intervals not to exceed 500 hours time in service from the last inspection. (b) If cracks are found as a result of any of the inspections outlined above, accomplish one of the following before further flight: (1) If MLG beam web cracking exceeds seven inches total length and/or extends more than two inches forward or aft of the 340-8510109 MLG trunnion fitting, the beam web must be replaced. (2) If MLG beam web cracking is less than 2.75 inches long and oriented in a wing chordwise direction along the web flange bend radius, either: (i) Stop drill the crack in accordance with Section 2(B)(3) of S.B. 57-3 or an equivalent rework approved by the Chief, Aircraft Engineering Division, FAA Western Region, and reinspect for further crack propagation at intervals not to exceed 50 hours time in service until the beam is reinforced per (3) below or replaced per (1) above, or (ii) Replace the beam web. (3) If cracks are between 2.75 inches and 7.00 inches in length and do not extend more than two inches forward or aft of the 340-8510109 MLG trunnion fitting, either replace the beam web or stop drill and reinforce the beam web per Section 2(B)(4) of S.B. 57-3 or an equivalent rework approved by the Chief, Aircraft Engineering Division, FAA Western Region. If the beam web is stop drilled and reinforced, it must be reinspected for further crack propagation at intervals not to exceed 500 hours time in service or until the beam web is replaced. (c) Cracks propagating beyond a stop drill hole may be restop drilled providing the crack length remains within the limits outlined above. (d) Normal inspection intervals may be resumed when the beam web is replaced. This amendment becomes effective June 4, 1970.
2022-08-10: The FAA is superseding Airworthiness Directive (AD) 2020-12-07 for certain Hamilton Sundstrand Corporation (Hamilton Sundstrand) 54H model propellers. AD 2020-12-07 required initial and repetitive eddy current inspections (ECI) of certain propeller blades and replacement of the propeller blades that fail the inspection. This AD was prompted by a report of the separation of a 54H60 model propeller blade installed on a United States Marine Corps Reserve (USMCR) KC-130T airplane during a flight in July 2017. This AD requires initial and repetitive ECI of all propeller blades installed on Hamilton Sundstrand 54H60 propeller hubs and replacement of any propeller blade that fails inspection. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-21: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109K2 helicopters. This action requires dye-penetrant inspecting the tail rotor trunnion (trunnion) assembly for a crack at specified intervals, replacing any cracked trunnion with an airworthy trunnion, and reporting any failed trunnion. This amendment is prompted by the report of an accident involving a tail rotor hub and blade assembly separating from the helicopter due to fatigue failure of the trunnion. The cause for the crack in the trunnion has not been determined and is still under investigation. This condition, if not detected, could result in failure of the trunnion, loss of the tail rotor hub and blade assembly, and subsequent loss of control of the helicopter.
2022-08-13: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PT6A-34, -34B, -34AG, -114, and - 114A model turboprop engines. This AD was prompted by several reports of low-time fractures of compressor turbine (CT) blades resulting in loss of power or in-flight shutdown (IFSD) of the engine. This AD requires replacement of certain CT vanes. This AD also requires removal from service of certain CT blades when these blades have been operated with certain CT vanes. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-22: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires installing a Number 5 bearing chip detector in each engine, installing an on-board chip detector annunciation system, and revising the Rotorcraft Flight Manual (RFM) to add procedures for crew response to an on-board chip detector annunciation. This amendment is prompted by reports of the failure of the engine's Number 5 bearing that resulted in erratic movement of the high-speed engine-to-transmission shaft (shaft), oil leakage, an in-flight fire and an emergency landing. The actions specified by this AD are intended to detect an impending engine bearing (bearing) failure, which, if undetected and not addressed by appropriate crew action, may result in oil leakage, severing of the shaft housing, an uncontained in-flight fire, and a subsequent emergency landing.