Results
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.
2008-13-12: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, and other specified and corrective actions if necessary. This AD also provides for an optional preventive modification, which terminates the repetitive inspections. This AD results from a report that the upper frame of the fuselage was severed between stringers S-13L and S-14L at station 747, and the adjacent frame at station 767 had a 1.3-inch-long crack at the same stringer location. We are issuing this AD to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane.
2005-07-04: This amendment supersedes an existing airworthiness directive (AD), applicable to the airplane models listed above. That AD currently requires repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA), and corrective action if necessary. This amendment expands the applicability of the existing AD; and requires new repetitive inspections for discrepancies of the ball screw assembly; corrective action if necessary; repetitive greasing of the THSA ball nut, and replacement of the THSA if necessary; and a modification or replacement (as applicable) of the ball nut assembly, which would end certain repetitive inspections. The actions specified by this AD are intended to prevent degraded operation of the THSA due to the entrance of water into the ball nut. Degraded operation could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
95-20-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections for cracking in the inboard strut-to-diagonal brace attach fittings, and repair or replacement, if necessary. This amendment requires an additional inspection of those attach fittings, and additional inspections in an area beyond that specified in the existing AD. This amendment also provides an optional terminating action for the required inspections, and expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by reports of cracking and severing of the attach fittings. The actions specified by this AD are intended to prevent failure of the strut and separation of an engine from the airplane due to cracking of the inboard strut-to-diagonal brace attach fittings.