Results
2022-11-51: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Type Certificate previously held by Yabor[atilde] Ind[uacute]stria Aeron[aacute]utica S.A.; Embraer S.A.) Model ERJ 170- 200 STD, ERJ 170-200 LR, ERJ 170-200 SU, and ERJ 170-200 LL airplanes. This AD was prompted by a report of an in-flight detachment of a right- hand wing tip and the subsequent determination that cracks could develop on the wing tip connection area that can affect its structural integrity to the point of an in-flight detachment. This AD requires a detailed inspection for cracks of the affected wing tip connections, corrective action if necessary, and revision of the existing maintenance or inspection program, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA previously sent an emergency AD to all known U.S. owners and operators of these airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
2020-21-13: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life limits of certain high-pressure turbine (HPT) rotor stage 2 disks and certain rotating compressor discharge pressure (CDP) HPT seals. This AD requires the replacement of the affected HPT rotor stage 2 disks and rotating CDP HPT seals. The FAA is issuing this AD to address the unsafe condition on these products.
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.
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.
2005-07-02: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 777-200 and -300 series airplanes. This AD requires inspection of the outer cylinder of the main landing gear (MLG) to determine the serial number; an ultrasonic inspection of the outer cylinder of the MLG for cracks if necessary; and applicable specified and corrective actions if necessary. This AD is prompted by reports indicating that two outer cylinders were found fractured in the weld area. We are issuing this AD to detect and correct cracks or defects that could result in a fracture of the outer cylinder of the MLG, which could lead to collapse of the MLG during landing.
95-19-06: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model ATP series airplanes, that currently requires inspections to detect cracking of the aft end of the wing rib boom angles on the left and right engine, and repair or replacement of the wing rib boom angle assemblies, if necessary. That AD was prompted by the detection of cracks in the engine outboard rib boom angles at the main landing gear (MLG) actuator attachment point. The actions specified by that AD are intended to prevent structural failure of the actuator attachment point, which could lead to collapse of the MLG. This amendment limits the applicability of the rule to only a certain number of airplanes; revises the initial inspection threshold, depending on whether or not certain modifications have been accomplished on the boom angles; and requires that modified boom angles be installed whenever replacement is necessary.
2001-21-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Dornier Luftfahrt GmbH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes. This AD requires you to repetitively inspect the horizontal stabilizer skin and ribs for damage and cracks and repair any damaged skin or cracked ribs. 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 detect and correct damage and fatigue cracks in the horizontal stabilizer skin and ribs. This condition could cause in-flight separation of the horizontal stabilizer skin with consequent loss of control of the airplane.
2008-13-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330 airplanes and Model A340-200 and -300 series airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit the flightcrew from performing CAT 2 and CAT 3 automatic landings and roll-outs at certain airports. This AD also provides an optional terminating action for the AFM revision. This AD results from data showing that the magnetic variation table installed in certain Honeywell and Northrop Grumman air data inertial reference units (ADIRUs) is obsolete at certain airports. We are issuing this AD to prevent the airplane from departing the runway during a CAT 2 or CAT 3 automatic landing or roll-out, due to differences between actual magnetic variation and the values in the ADIRU magnetic variation tables.
2008-13-32: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: It has been determined that the currently used values for Arms of front and rear fuel tanks, and luggage compartment from the CAP 10B Airplane Flight Manuals (AFM), must be rectified. If left uncorrected, these weight and balance data could lead to erroneous determination of the location of the Center of Gravity (CG) and possibly cause operation with the CG outside the approved limits which may result in control difficulty. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-20-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that currently requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. This amendment removes certain airplanes and adds certain other airplanes to the applicability of the existing AD. The actions specified in this AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight. \n\nThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of September 19, 2000 (65 FR 49728, August 15, 2000), and as of November 13, 2000 (65 FR 59707, October 6, 2000). \n\n\tComments for inclusion in the Rules Docket must be received on or before December 17, 2001.
2008-13-31: 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: In service events have shown that, after implementation of Dassault Aviation SB (service bulletin) F2000-133 and F2000-166, a risk of engine cowlings separation from the airplane still exists, and may cause potential damages to the engine itself and to the horizontal stabilizer. It is suspected that on-ground improper latching may lead to a radial deformation of engine cowlings in flight and to their eventual escape out of their locking devices. This situation may represent a hazard to the aircraft propulsive system and/or its structural integrity. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-10-06: The FAA is superseding Airworthiness Directive (AD) 2017-06- 07, which applied to all Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes; and A340-200, -300, -500, and -600 series airplanes. AD 2017-06-07 required identification of potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. This AD was prompted by a determination that, even if affected inboard flaps were not installed on airplanes during production, affected inboard flaps could be installed on airplanes as spare parts. This AD continues to require the actions in AD 2017-06-07, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also reduces the allowance for the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
95-19-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100 and -200 series airplanes, that requires replacing the attaching nutplates on certain engine nose cowls with washers and self-locking nuts. This amendment is prompted by reports indicating that nose cowls separated (or nearly separated) from the engines of certain airplanes following failure of the engine fan blade and subsequent vibration of the engine, which caused loosening of the attach bolts on the nose cowl of the engine. The actions specified by this AD are intended to prevent the attach bolts from becoming loose, which could result in subsequent separation of the nose cowl from the engine.
95-19-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. This action requires an inspection to detect damage, burn marks, or discoloration at certain electrical plugs and receptacles of the sidewall lighting in the passenger cabin, and correction of discrepancies. This action also requires modification of the electrical connectors, which would terminate the inspection requirement. This amendment is prompted by reports of failures of the electrical connectors in the sidewall fluorescent lighting, which resulted in smoke or lighting interruption in the passenger cabin. The actions specified in this AD are intended to prevent failures of the electrical connectors, which could result in poor socket/pin contact, excessive heat, electrical arcing, and subsequently, connector burn through and smoke in the passenger cabin.