Results
2002-17-02: This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney JT8D series turbofan engines. That AD currently requires revisions to the Time Limits Section (TLS) of the manufacturer's Engine Manuals (EM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment requires modification of the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. A Federal Aviation Administration (FAA) study of in- service events involving uncontained failures of critical rotating engine parts indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD areintended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2021-19-10: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE) PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G- JM, PW1133GA-JM, and PW1133G-JM model turbofan engines. This AD was prompted by a root cause analysis of an event involving an uncontained failure of a high-pressure turbine (HPT) disk that resulted in high- energy debris penetrating the engine cowling on an Airbus Model A321- 231 airplane, powered by IAE V2533-A5 model turbofan engines. This AD requires removing certain HPT 1st-stage and HPT 2nd-stage disks from service. The FAA is issuing this AD to address the unsafe condition on these products.
95-05-03: This amendment supersedes an existing airworthiness directive (AD), applicable to Hamilton Standard 14RF series, 14SF series, and Hamilton Standard/British Aerospace 6/5500/F series propellers, that currently requires a one-time ultrasonic shear wave inspection for cracks in the propeller blade taper bore. This amendment requires initial and repetitive ultrasonic shear wave inspections, and a one-time visual and borescope inspection of the taper bore for corrosion as a terminating action to the ultrasonic shear wave inspections. This amendment is prompted by reports of two incidents where a portion of the propeller blade was lost in flight. The actions specified by this AD are intended to prevent loss of a propeller blade due to cracks initiating in the blade taper bore, that can result in possible aircraft damage, and possible loss of aircraft control.
63-05-02: 63-05-02 SIKORSKY: Amdt. 542 Part 507 Federal Register March 6, 1963. Applies to All S-55 Series Helicopters. Compliance required as indicated. There has been a fatigue fracture of the main rotor blade spar. For this reason, accomplish the following: (a) All S14-10-2000 Series main rotor blades with 975 or more hours' time in service as of the effective date of this AD shall be retired from service within the next 25 hours' time in service. (b) All S14-10-2000 Series main rotor blades with less than 975 hours' time in service as of the effective date of this AD shall be retired from service prior to the accumulation of 1,000 hours' time in service. This directive effective March 6, 1963.
2002-17-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires pulling the FOOT WARM circuit breaker located on the copilot's circuit breaker panel, and installing a collar on that circuit breaker. This action is necessary to prevent an electrical short circuit between the pilot's and copilot's foot warmers and the composite floorboards, which could result in outgassing of the faceply material of the composite floorboards, and consequent smoke in the cockpit. This action is intended to address the identified unsafe condition.
2023-21-06: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to certain Embraer S.A. (Embraer) Model EMB-505 airplanes. As published, two references to an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD in the preamble Background section are incorrect. This document corrects those errors. In all other respects, the original document remains the same.
2002-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires various modifications of the airstair (main passenger) door. This action is necessary to prevent failure of the airstair door to open after a landing, which could result in a blocked escape route during an emergency evacuation. This action is intended to address the identified unsafe condition.
86-22-09: 86-22-09 UNIVAIR AIRCRAFT CORPORATION: Amendment 39-5457. Applies to Model (Ercoupe) 415, -C, -CD, -D, -E, -G (all serial numbers), and (Forney) Models F1 and F1A (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD or at the next annual inspection whichever occurs first, unless already accomplished. To prevent possible fuel leakage and loss of engine power, accomplish the following: (a) Visually inspect the fuel line nipple located between the gascolator and the carburetor for cracks, incorrect alignment or over torque and prior to further flight replace as necessary, the nipple from a AN911-2D (aluminum) to a AN911-02 (brass or steel) fitting as described in Univair Aircraft Corporation, Ercoupe Bulletin No. 24A dated August 22, 1986. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Denver Aircraft Certification Office, Northwest Mountain Region, 10455 East Avenue, Suite 307, Aurora, Colorado 80010. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on November 13, 1986.
2014-05-06 R1: We are revising Airworthiness Directive (AD) 2014-05-06 for Eurocopter Deutschland GmbH Model EC135 and MBB-BK 117C-2 helicopters. AD 2014-05-06 required repetitive inspections of the flight-control bearings, replacing any loose bearings with airworthy flight-control bearings, and installing bushings and washers. This new AD retains the requirements of AD 2014-05-06 but removes the repetitive inspections. The actions of this AD are intended to correct an unsafe condition on these products.
2023-23-01: The FAA is superseding Airworthiness Directive (AD) 2022-01- 05, which applied to certain Airbus Helicopters Model EC130T2 helicopters. AD 2022-01-05 required repetitive visual inspections of the rivets on the rear transmission shaft bearing support, inspections of the local structure, and rivet heads on the left-hand and right-hand sides of the rear transmission shaft bearing support for cracking, missing, loose, or sheared rivets. AD 2022-01-05 also required reporting the results of those inspections and depending on the results, applicable corrective action. Since the FAA issued AD 2022-01- 05, Airbus Helicopters revised its service information to add procedures to improve visual inspections of the rivets on the rear transmission shaft bearing support. This AD was prompted by the determination that certain modified helicopters may have finishing paint applied to the gutter, which could prevent detection of cracks during inspections. This AD also extends the repetitive compliance time interval for certain inspections. This AD continues to require certain actions in AD 2022-01-05 and requires a one-time visual inspection for paint in the gutter area, and removal of paint if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-21-07: The FAA is superseding Airworthiness Directive (AD) 2018-03-13 for certain General Electric Company (GE) Model CT7-5A2, CT7-5A3, CT7- 7A, CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C, and CT7-9C3 engines. AD 2018-03-13 required initial and repetitive visual inspections and fluorescent penetrant inspections (FPIs) of the main propeller shaft. This AD was prompted by an in-flight failure of a main propeller shaft on a GE Model CT7-9B engine, resulting in the loss of the propeller. This AD requires initial and repetitive visual inspections, FPIs, and ultrasonic inspections (USIs) of the main propeller shaft. Depending on the results of these inspections, this AD requires replacement of the main propeller shaft. As an optional terminating action to these inspections, this AD requires revising the airworthiness limitations section (ALS) of the existing maintenance manual (MM) and the operator's existing approved maintenance program or inspection program, as applicable, to incorporate incorporating the tasks and reduced inspection thresholds for the main propeller shaft. The FAA is issuing this AD to address the unsafe condition on these products.
2002-16-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires revising the Limitations Section of the FAA-approved Airplane Flight Manual to ensure the flightcrew is advised of the proper procedures in the event of uncommanded movement of a spoiler during flight. Such uncommanded movement could result in reduced controllability of the airplane, and consequent significant increased fuel consumption during flight, which could necessitate an in-flight turn-back or diversion to an unscheduled airport destination. This action is intended to address the identified unsafe condition.
2017-03-01: We are superseding airworthiness directive (AD) 2014-05-06 for Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters to correct an error in the compliance time. AD 2014-05-06 required inspecting the flight- control bearings and installing bushings and washers. This AD requires the same actions. These actions are intended to prevent an unsafe condition on these products.
2002-16-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and 328-300 series airplanes, that requires replacement of the bolts with new bolts with wirelocking on the Support One of the rudder spring tab. This action is necessary to ensure replacement of improper bolts installed on the rudder spring tab that could back out over time, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2023-20-11: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE LLC) Model PW1124G1-JM, PW1127G-JM, PW1127GA-JM, PW1129G-JM, PW1130G-JM, PW1133G-JM, and PW1133GA-JM engines. This AD was prompted by a manufacturer investigation which revealed that Maintenance, Repair, and Overhaul (MRO) shops were misinterpreting accepted knife edge coating wear limits on the high-pressure compressor (HPC) rear hub. This AD requires replacement of the HPC rear hub with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2006-15-01: We are adopting a new airworthiness directive (AD) for all Twin Commander Aircraft Corporation (Twin Commander) Models 690, 690A, and 690B airplanes. This AD requires you to inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks and replace any cracked support structure. This AD requires you to reinforce the support structures for the inboard and center aileron hinge fittings on both wings. This AD results from reports that cracks were found in the support structures for the inboard and center aileron hinge fittings on both wings. We are issuing this AD to detect and correct cracks in the support structures for the inboard and center aileron hinge fittings on both wings, which could result in aileron failure. This failure could lead to reduced controllability or loss of control of the airplane.
94-20-06: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines, that requires a repetitive oil quantity check after engine start-up but prior to taxi, and installation of a flame arrestor plug support (FAPS) in the aft end of the center vent tube as a terminating action to the repetitive oil quantity checks. This amendment is prompted by three reports of uncontained engine failure due to separation of the fan mid shaft. The actions specified by this AD are intended to prevent an uncontained engine failure and inflight engine shutdown due to fuel contamination of the oil system.
2003-08-53: This document publishes in the Federal Register an amendment adopting a superseding Airworthiness Directive (AD) 2003-08-53, sent previously to all known U.S. owners and operators of the specified Eurocopter France (Eurocopter) model helicopters by individual letters. This AD requires, in addition to the checks and tapping test inspections required in the existing AD, adding the Eurocopter Model AS 365 N3 to the applicability and correcting tail rotor blade (blade) part numbers. Also, this AD requires doing tapping tests for bonding separation on blades and removing certain blades at specified intervals. The actions specified by this AD are intended to prevent failure of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter. \n\nDATES: Effective June 20, 2003, to all persons except those persons to whom it was made immediately effective by Emergency AD 2003-08-53, issued on April 23, 2003, which contained the requirements of this amendment.
95-03-12: 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 series helicopters, that currently requires an initial and repetitive visual inspections of the clutch control spring assembly for component wear and replacement of affected unairworthy parts. This amendment requires the same initial and repetitive visual inspections and replacements required by the existing Priority Letter AD, but references a revised service bulletin and provides replacement procedures for the aluminum spring retainer thermofit tube (plastic sleeve). This amendment is prompted by a recent accident involving a Model 269C helicopter that reportedly lost engine drive power at 100 feet above ground level (AGL) with a resulting unsuccessful autorotative landing, and the manufacturer's issuance of revised service information that provides more detailed instructions for replacementof two components of the belt drive clutch control assembly. The actions specified by this AD are intended to prevent failure of the aluminum spring retainer, loss of power to the rotor drive system, and a subsequent forced landing.
2003-04-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time general visual inspection to find wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This action is necessary to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin. This action is intended to address the identified unsafe condition.
2017-26-09: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR 42-500 airplanes and Model ATR 72-212A airplanes. This AD requires a one-time inspection for damage of the engine fire extinguishing pipes and incorrect pipe installation, and corrective actions if necessary. This AD was prompted by a report of damage to an engine fire extinguishing pipe due to chafing between the pipe and a fastener assembly; the chafing occurred as a result of incorrect installation of the pipe. We are issuing this AD to address the unsafe condition on these products.
2002-16-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain serial numbers (SN's) of Bombardier-Rotax GmbH type 912 F, 912 S and 914 F series reciprocating engines. This action requires replacement of the valve spring retainers, part number (P/N) 854.182, with the new-reinforced valve spring retainers, P/N 854.184. This amendment is prompted by reports of several cracked valve spring retainers discovered in-service. The actions specified in this AD are intended to prevent cracking of the valve spring retainers resulting in possible engine failure while in-flight.
95-03-13: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Company and Hughes Helicopters, Inc. Model 369 and OH-6A series helicopters with certain main rotor (M/R) blade assemblies or certain M/R hub lead-lag assemblies installed, that currently requires repetitive inspections and checks for cracks. This amendment requires the same inspections as the superseded AD, but would eliminate pilot checks, expand the areas of inspection, and require the application of slippage marks on each M/R blade root fitting lug and related bushings. This amendment is prompted by additional reports of cracks in the M/R blade root fittings, lugs, and adjacent blade skin, and movement of the root fitting bushings. The actions specified by this AD are intended to prevent failure of a M/R blade assembly or a M/R hub lead-lag link assembly, loss of a M/R blade, and subsequent loss of control of the helicopter.
47-49-03: 47-49-03 LOCKHEED: (Was Mandatory Note 36 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2080, Except 2033, 2058 and 2071 Through 2075. Compliance required at next engine change period. Inspect all attachments of rudders to torque tube flanges for evidence of stripped threads or elongated holes. (This does not require removal of rudders.) When such evidences are found, redrill holes to next larger size and/or install new nuts as required. (LAC Service Bulletin 49/SB-256 covers this same subject.)
2017-26-08: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72- 212A airplanes. This AD requires revising the airplane flight manual (AFM) to provide procedures to the flight crew for operational restrictions affecting in-flight use of the autopilot (AP) or yaw damper (YD) during dual-engine operation. This AD also provides an optional software modification, which would terminate the AFM requirement. This AD was prompted by flight test evaluations that revealed that after engine failure during AP or YD re-engagement, the YD unit commanded the rudder to return to neutral position, leading to inadequate balancing of the asymmetric power. We are issuing this AD to address the unsafe condition on these products.