Results
2005-07-09: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF34-8E series turbofan engines with certain serial number (SN) master variable geometry (VG) actuators installed. That AD currently requires initial and repetitive reviews of the airplane computer systems for master VG actuator fault messages. That AD also requires replacement of actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This AD requires the same reviews. This AD also prohibits installation of affected master VG actuators onto any CF34-8E series turbofan engine after the effective date of the AD. This AD results from the need to add to the list of affected parts, master VG actuators made by a parts manufacturing approval (PMA) holder. We are issuing this AD to prevent dual-channel electrical signal faults in the master VG actuator which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle, and will result in a multiengine loss of thrust if dual-channel faults occur on more than one engine simultaneously.
2001-22-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires a one-time inspection of the fuselage skin adjacent to the drag splice fitting to detect cracking, and follow-on actions, if necessary. This amendment requires new repetitive inspections for cracking of the fuselage skin adjacent to the drag splice fitting. This amendment is prompted by reports of fatigue cracking in the fuselage skin and adjacent structure. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the fuselage, and consequent rapid depressurization of the airplane. \n\n\tThe incorporation by reference of Boeing Service Bulletin 747-53A2444, Revision 1, dated June 15, 2000, as listed in the regulations, was approved previously by the Director of the Federal Register as of July 28, 2000 (65 FR 43219, July 13, 2000).
83-08-01R2: The FAA is revising an existing airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. (formerly TRW Hartzell Propeller) models HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN- 5, HC-B4MN-5, and HC-B5MP-3 turbopropellers. That AD requires, before further flight, that all new propellers being installed and all serviceable propellers being reinstalled, are attached using part number (P/N) B-3339 bolts and P/N A-2048-2 washers, and that the bolts are properly torqued. That AD also requires a onetime torque-check of P/N A-2047 bolts that are already installed through propellers and replacement of those bolts if necessary, with P/N B-3339 bolts and P/N A-2048-2 washers. This AD requires the same actions, and includes the use of other equivalent FAA-approved serviceable bolts and washers. This AD results from the need to make nonsubstantive wording changes and additions to clarify that terminating action is achieved by attaching propellers with P/N B-3339 bolts and P/N A-2048-2 washers or other equivalent FAA-approved serviceable bolts and washers, to the engine flange, as instructed in the compliance section of this AD. We are issuing this AD to preclude propeller attaching bolt failures or improperly secured propellers, which could lead to separation of the propeller from the airplane.
95-21-02: This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters with certain main rotor (M/R) drive shafts installed, that currently requires a one-time radiographic inspection or other non-destructive inspection of certain M/R drive shafts for cracks, distortion, corrosion, or other surface damage, at specified time intervals or upon the occurrence of specified conditions. This amendment requires the same inspections as the previous AD, but expands the applicability of certain inspections to additional models of the affected helicopters, and excludes certain M/R drive shafts from certain inspections. This amendment is prompted by a reevaluation as a result of a comment to the previous AD suggesting the need to expand the applicability of certain inspections to additional models of the affected helicopters and to exclude certain M/R drive shafts from certain inspections. The actions specified by this AD are intended to prevent structural failure of the M/R drive shaft, separation of the M/R from the helicopter, and subsequent loss of control of the helicopter.
2008-14-13: We are adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to replace the cabin door rod ends with new parts including a redesigned non-binding hinge pin that replaces the existing pin at the upper door hinge. This AD results from two known occurrences of in-flight cabin door separation (one total separation and one retained by the door strut). The rod ends, a component of the door hinges, may fail and result in a door separation from the airplane while in flight. We are issuing this AD to prevent in-flight failure of the cabin door, which could result in door separation from the airplane.
2008-14-01: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, 230 and 430 helicopters that requires rewiring and testing the fuel valve switch on each engine and testing the ignitor system. This amendment is prompted by an in-flight incident in which a fuel valve switch failed, causing the fuel valve to inadvertently close. The actions specified by this AD are intended to prevent interruption of the fuel supply caused by failure of the fuel switch, which could result in loss of engine power and subsequent loss of control of the helicopter.
95-21-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires an inspection to detect damage of the wire bundles in the left side of the flight compartment in the vicinity of the stowage box for the captain's oxygen mask, and repair, if necessary; a continuity check on repaired wires; installation of sleeving over the wire bundles; and rerouting of the wire bundles. This amendment is prompted by reports of chafed wiring and minimal clearance between the oxygen connector and the adjacent wire bundles in the vicinity of the stowage box for the captain's oxygen mask. The actions specified in this AD are intended to prevent such chafing and inadequate clearance, which could result in electrical arcing and consequent oxygen leakage in the vicinity of the stowage box; these conditions, if not corrected, could result in a fire in the flight compartment.
2022-08-06: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C and CF34-8E model turbofan engines. This AD was prompted by an ''Engine Degraded'' message received in-flight from the Engine Indicating and Crew Alerting System (EICAS), and a subsequent investigation by the manufacturer that revealed corrosion of the variable geometry (VG) system actuator, which can cause the full authority digital engine control (FADEC) software to command and lock the engine at idle until it is restarted. This AD requires performing a rotational torque check on the actuating linkage assembly and, depending on the results of the rotational torque check, replacement of the compressor inlet guide vane (IGV) outer shroud bushing and vane spindle bushing with parts eligible for installation. This AD also requires reporting the results of the rotational torque check to GE. The FAA is issuing this AD to address the unsafe condition on these products.
95-21-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 31A and 60 airplanes. This action requires an inspection to identify the serial numbers of the engine fire pull switch assemblies, and replacement of the assembly with a serviceable assembly, if necessary. This amendment is prompted by a report indicating that certain engine fire pull switch assemblies may contain microswitches that were manufactured with internal defects. Such defects could result in electrical failure of the switch in the open or closed position. The actions specified in this AD are intended to prevent failure of the switch, which could result in the inability of the flight crew to shut down certain systems or to arm the fire extinguishers due to inoperation of the fire tee handle, or inadvertent shutdown of one or both engines due to fuel starvation
95-20-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Learjet Model 24, 25, 31, 35, and 36 series airplanes, and all Learjet Model 28, 29, and 55 series airplanes, that currently requires a revision to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to prohibit flight above an altitude of 41,000 feet. The actions specified by that AD are intended to limit the airplane operating altitude due to a possible failure of the outflow/safety valves, which could result in rapid decompression of the airplane. This amendment adds a requirement for replacement of certain outflow/safety valves, which, when accomplished, constitutes terminating action for the previously required AFM limitation.