Results
2004-13-07: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. This AD requires operators to determine the flight cycles accumulated on each component of the main landing gear (MLG) and the nose landing gear (NLG), and to replace each component that reaches its life limit with a serviceable component. This AD also requires operators to revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness in the aircraft maintenance manual to reflect the new life limits. This action is necessary to prevent failure of certain components of the MLG and the NLG, which could result in failure of either or both landing gears, and consequent damage to the airplane and injury to passengers or crewmembers. This action is intended to address the identified unsafe condition.
2012-14-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of fatigue cracks in the lap joints, which initiated at scribe lines that were made during production when maskant was removed from the affected skin panels during the chemical milling process. This AD requires repetitive external phased-array ultrasonic inspections to detect cracks of the affected fuselage skin lap splices in Sections 41, 43, and 44, as applicable, and repair if necessary. We are issuing \n\n((Page 42963)) \n\nthis AD to detect and correct such fatigue cracking, which could grow large and cause sudden decompression and the inability to sustain limit flight and pressure loads.
2021-26-06: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90 model turbofan engines. This AD was prompted by two separate in-flight shutdowns (IFSDs) resulting from failure of the transfer gearbox (TGB) radial bevel gear (TGB radial gearshaft). This AD requires visual inspection of the TGB radial gearshaft and, depending on the results of the inspection, replacement of the TGB radial gearshaft. The FAA is issuing this AD to address the unsafe condition on these products.
49-27-03: 49-27-03 DOUGLAS: Applies to All Models C54-DC and DC-4 Series Aircraft. \n\n\tTo be accomplished as indicated below: \n\n\t1.\tPrior to 5,000 hours total airplane time, or at next scheduled inspection at which necessary facilities are available, on airplanes with more than 5,000 hours total time, inspect nose gear yoke and fittings, P/N 5087950 and either 5087951 or 5180402 to determine if the 1/2-inch radius fairs in properly with the journal. All parts having a poor radius condition must be replaced immediately with parts having the correct radius fairing into the journal. This inspection does not have to be repeated if already accomplished. \n\n\t2.\tParts having a good radius must be replaced at each 17,500 hours airplane operation time. If the replacement parts have been shotpeened, as per Douglas Aircraft Co. recommendations, the replacement time may be extended to 30,000 hours airplane operation time. \n\n\t3.\tUnused parts having a poor radius may be used, after being reworkedaccording to Douglas Aircraft Co. recommendations. \n\n\t4.\tAll used nose hear yoke end fittings having not more than 17,500 hours total time may be reinstalled and used for a total time of 30,000 hours if Zyglo inspection reveals no cracks; the radius of the journal is properly reworked to meet the limiting dimensions of Douglas E. C. 1361954 and the part is shotpeened in accordance with Douglas Aircraft Co. standards. \n\n\t5.\tAt the time of replacement of parts as per item 1, or at the next major aircraft overhaul period, rework bushing, P/N 1087938, to incorporate a 1/8-inch radius on the inside diameter at the flanged end of the bushing. Rework ring, P/N 2103390, by providing a 0.031-inch radius on the inside edges. \n\n\t(Douglas Service Letters A-214-T.51/WBM dated January 7, 1948; A-214 TS2249/WBM dated November 25, 1947; and A-214-TS-1572/WBM dated October 20, 1947, cover the above.) \n\n\tThis supersedes AD 48-24-02.
2004-13-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes, that requires rework/retrofit of the wardrobe shelf assembly. This action is necessary to prevent the wardrobe shelf and attached equipment separating from the attachment in the event of a hard landing, which could impede the egress of passengers in the event of an emergency evacuation. This action is intended to address the identified unsafe condition.
2021-26-18: The FAA is superseding Airworthiness Directive (AD) 2020-21-01 for certain Airbus Helicopters Model AS-365N2, AS 365N3, EC 155B, EC155B1, and SA-365N1 helicopters. AD 2020-21-01 required modifying the main gearbox (MGB) tail rotor (T/R) drive flange installation. This AD was prompted by several reported occurrences of loss of tightening torque of the Shur-Lok nut, which serves as a retainer of the MGB T/R drive flange. This AD continues to require modifying the MGB T/R drive flange installation, and includes additional helicopters in the applicability for the required actions. The FAA is issuing this AD to address the unsafe condition on these products.
2012-14-07: We are adopting an airworthiness directive (AD) superseding an existing airworthiness directive for Bell Helicopter Textron Canada (Bell) Model 407 and 427 helicopters. The existing AD requires inspecting certain hydraulic servo actuators (servo) to determine whether the shaft turns independently of the nut or the clevis assembly, and additional actions based upon the inspection's outcome. The AD also requires reidentifying the servo. Since we issued that AD, Bell has learned that additional servos may need repair or removal. This AD expands the scope of the current AD to include inspections for all servos, and requires that servos meeting inspection requirements be marked with the letter ``V'' after the part number on the data plate. The actions are intended to detect any loose or misaligned parts in the servo that could lead to failure of the servo and subsequent loss of helicopter control.
2021-24-12: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by significant changes, including new or more restrictive requirements, made to the airworthiness limitations (AWLs) and Critical Design Configuration Control Limitations (CDCCLs) related to fuel tank ignition prevention, the engine fuel suction feed system, and the nitrogen generation system. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-07 R1: This amendment revises an existing airworthiness directive (AD), for the Agusta S.p.A. (Agusta) Model A109C, A109E, and A109K2 helicopters, that currently requires inspecting the main rotor blade (blade) tip cap for bonding separation and a crack, and also requires a tap inspection of the tip cap for bonding separation in the blade bond area and a dye-penetrant inspection of the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack. This amendment requires those same actions, but corrects a blade part number (P/N) that was stated incorrectly in the Applicability section of the existing AD. This amendment is prompted by the need to correct a blade P/N. The actions specified by this AD are intended to prevent failure of a blade tip cap, excessive vibration, and subsequent loss of control of the helicopter.
2004-05-12 R1: The FAA is revising an existing airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires repetitive inspections of the left and right engine throttle control gearboxes for wear, and corrective action if necessary. This AD limits the applicability of the existing AD, extends the compliance time for the initial inspection, and clarifies the reporting requirement. This AD is prompted by numerous failures of the engine throttle control gearbox, some of which resulted in an in-flight engine shutdown. We are issuing this AD to prevent excessive wear of the gearboxes and subsequent movement or jamming of the engine throttle; movement of the throttle towards the idle position brings it close to the fuel shut-off position, which could result in an in-flight engine shutdown.