Results
94-08-10: This amendment supersedes Airworthiness Directive (AD) 88-13-11, which currently requires repetitively inspecting both wing main spar lower cap angles for corrosion, and repairing or replacing any corroded part. This action retains these inspection and possible repair or replacement requirements, but eliminates the dual compliance time of both hours time-in-service (TIS) and calendar time. The Federal Aviation Administration (FAA) has determined that, since corrosion occurs regardless of whether the airplane is in service, the best compliance method for the proposed action is calendar time. The actions specified by this AD are intended to prevent failure of the wing structure because of corroded wing main spar lower cap angles.
2007-23-13: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Model 560 airplanes. This AD requires installing new minimum airspeed placards to notify the flightcrew of the proper airspeeds for operating in both normal and icing conditions. This AD also requires revising the airplane flight manual to provide limitations and procedures for operating in icing conditions, for operating with anti-ice systems selected "on'' independent of icing conditions, and for recognizing and recovering from inadvertent stall. This AD also provides an optional terminating action for the placard installation. This AD results from an evaluation of in-service airplanes following an accident. The evaluation indicated that some airplanes may have an improperly adjusted stall warning system. We are issuing this AD to prevent an inadvertent stall due to the inadequate stall warning margin provided by an improperly adjusted stall warning system, which could result in loss of controllabilityof the airplane.
2019-22-08: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.A. Model AW169 and AW189 helicopters. This AD requires inspecting certain part-numbered and serial-numbered tail rotor (T/R) actuators, reporting information, and depending on the inspection outcome, marking a part, performing an additional inspection, and removing the T/R actuator from service. This AD also prohibits the installation of affected T/R actuators. This AD is prompted by reports of incorrect installations of the T/R actuator back-end input lever. The actions of this AD are intended to address an unsafe condition on these products.
2011-10-01: 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: A design review has revealed a potential dormant failure of the Ram Air Turbine (RAT) heating system. If this failure occurs, it could lead to the freezing of the RAT mechanism [the potential consequence of this heater being inoperative relates primarily to generator rotor/turbine assembly rotation--either the ability to rotate or to rotate at rated RPM for a given airspeed], and the consequent * * * [non-functioning] of the RAT when needed. * * * * * Non-functioning of the RAT could result in insufficient electrical power to operate the fly-by-wire system, and subsequent loss of control of the airplane. We are issuing this AD to require actionsto correct the unsafe condition on these products.
76-14-05: 76-14-05 BELL: Amendment 39-2669. Applies to Model 206L helicopters, Serial Numbers 45006 through 45020, with fuel valve Part Number 206-063-640-1 installed, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent failure of fuel system components due to excessive pressure from thermal expansion of the fuel after engine shutdown, remove fuel shutoff valve P/N 206-063-640-1 and replace it with fuel shutoff valve P/N 206-063-640-3. Bell Helicopter Textron Service Bulletin No. 206L-76-2 pertains to this subject and provides approved instructions for this replacement activity. This amendment becomes effective August 19, 1976.
94-06-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Short Brothers PLC Model SD3-30, SD3-60, and SD3-SHERPA series airplanes, that currently requires an inspection to detect corrosion on the distance piece associated with the wing strut pick up on the stub wing, and repair of corroded parts. This amendment requires repetitive inspections to detect corrosion of repaired or reworked distance pieces and adjacent side plates; and provides a terminating action for the repetitive inspections. This amendment is prompted by reports of corrosion on the distance pieces and adjacent side plates of the wing strut pick up. The actions specified by this AD are intended to prevent failure of the distance piece and adjacent side plates, which could result in reduced strength of the wing strut attachment to the stub wing on the fuselage and, subsequently, reduced structural strength of the main wing.
94-07-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracked or fractured H-11 steel bolts, replacement of discrepant bolts with ones made of Inconel 718 material, and eventual replacement of all H-11 steel bolts installed at certain critical locations with Inconel 718 material bolts. This amendment is prompted by reports of cracked and fractured H-11 steel bolts installed at certain critical locations of the airframe structure. The actions specified by this AD are intended to prevent the failure of attachment bolts in critical locations, which could lead to severe airframe damage.
2007-23-08: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400, 747-400D, 747-400F, 757-200, 767-200, 767-300, and 767-300F series airplanes. This AD requires inspecting to determine the date code of the time delay relay for the cargo fire suppression system, and \nreplacing the relay if necessary. This AD results from a report indicating that failure of a time delay relay on an ELMS (electrical load management system) panel led to testing of other time delay relays at Boeing and at the supplier. Similar relays are used in the cargo fire suppression system. The time delay relay controls when the secondary fire bottles discharge. We are issuing this AD to ensure there is sufficient fire suppressant to control a cargo fire if the airplane is more than the relay delay time from a suitable airport, which could result in an uncontrollable fire in the cargo compartment.
2001-09-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires inspections for fatigue cracking of the horizontal stabilizer pivot bulkhead, and repetitive inspections or other follow-on actions. This action also provides a permanent repair, which is optional for airplanes with no cracks, and, if accomplished, ends the repetitive inspections. This action is necessary to find and fix fatigue cracking of the horizontal stabilizer pivot bulkhead and adjacent structure, which could result in loss of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
90-20-03: 90-20-03 WYTWORNIA SPRZETU KOMUNIKACYJNEGO PZL-MIELEC: Amendment 39-6723. Docket No. 90-CE-16-AD. Applicability: Models M18 and M18A (Dromader) (Serial Numbers 1Z00-101 through 1Z021-07) airplanes, certificated in any category. Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD and thereafter at intervals of 500 hours TIS until the aileron hinge is replaced with improved parts, unless already accomplished. To prevent failure of the aileron control system, accomplish the following: (a) Visually inspect with a 5x magnifying glass, or with fluorescent penetrant or magnetic crack detection methods, as appropriate, all aileron control system hinges for cracks and deformation in accordance with the instructions in PZL-Mielec, Mandatory Engineering Bulletin (MEB) No.K/02.132/89, approved September 7, 1989; Revised April 4, 1990. (1) If cracks or damage are found on any aileron hinge, prior to further flight remove the aileron and replace the aileron hinge with an aileron hinge having Engineering Change Notice (ECN) 9183 or ECN 9187, incorporated in accordance with the MEB referenced in paragraph (a) of this AD. (2) If no cracks or damage are found to any aileron hinge, repeat the above inspection every 500 hours TIS until all aileron hinges are replaced with an aileron having ECN 9183 or ECN 9187, incorporated in accordance with the MEB referenced in paragraph (a) of this AD. (b) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30 extension 2710/2711; Facsimile (322) 230.05.34. NOTE:The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to Wytwornia Sprzetu Komunikacyjnego PZL-Mielec 39-301 Mielec, Poland; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6723, AD 90-20-03) becomes effective on October 17, 1990.
94-06-03: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines, that requires an inspection for cracks in the stage 1 high pressure turbine (HPT) disk rim bolt holes, and replacement, if necessary, with serviceable parts. This amendment is prompted by a report of an uncontained stage 1 HPT disk failure which resulted in an aborted takeoff. The actions specified by this AD are intended to prevent an uncontained stage 1 HPT disk failure, which could result in an inflight engine shutdown, rejected takeoff, or damage to the aircraft.
2007-23-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800 and -900 series airplanes. This AD requires an inspection of the fillet sealant at the inboard and outboard sides of the receptacles in the wheel wells of the main landing gear, and related investigative/corrective actions if necessary. This AD results from reports of in-production airplanes with missing or insufficient fillet sealant around the receptacles at the disconnect bracket. We are issuing this AD to prevent corrosion damage due to missing or insufficient fillet sealant. Such corrosion could result in insufficient electrical bonding between the connectors and the disconnect bracket, and consequent loss of the shielding that protects the wire bundles from lightning, electromagnetic interference (EMI), and high intensity radiated field (HIRF). Loss of lightning, EMI, and HIRF protection at those receptacles could cause failure of multiple electrical systems and subsequent loss of several critical control systems that are necessary for safe flight. In addition, a lightning strike could cause arcing in the fuel tank; this potential ignition source, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2001-09-11: This amendment supersedes an existing airworthiness directive (AD) that applies to certain serial-numbered Bell Helicopter Textron, Inc. (Bell) Model 412 helicopters and Agusta S.p.A. (Agusta) Model AB412 helicopters. That AD currently requires a temporary reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required. This amendment requires the same actions as the previous AD but expands the applicability of the AD to all Bell Model 412, 412CF, 412EP, and Agusta Model AB412 helicopters. This amendment is prompted by the determination that the unsafe condition exists on all Bell Model 412 and all Agusta Model AB412 helicopters, regardless of serial number. The actions specified by this AD are intended to prevent static and dynamic overloaddamage to the yoke that could result in loss of the tail rotor and subsequent loss of control of the helicopter. The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of April 8, 1998 (63 FR 14026, March 24, 1998), as corrected on July 20, 1998 (63 FR 38742).
2019-23-18: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model MYSTERE FALCON 50, MYSTERE FALCON 900, and FALCON 900EX airplanes; and Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by a report that the Dassault maintenance planning document (MPD) of the related Dassault aircraft maintenance manual (AMM) states that the ``combined service/storage life'' of the fire extinguisher percussion cartridges is longer than it should be, and could have a safety impact in case of fire. This AD requires replacing the fire extinguisher percussion cartridges with serviceable parts. The FAA is issuing this AD to address the unsafe condition on these products.
92-15-11: 92-15-11 PRATT & WHITNEY CANADA: Amendment 39-8305. Docket No. 91-ANE-06. Applicability: Pratt & Whitney Canada (PWC) PT6A-6, PT6A-6/C20, PT6A-20, PT6A-20A, PT6A-21, PT6A-27, PT6A-28, PT6A-34, PT6A-34B, and PT6A-36 turboprop engines installed on Beech Aircraft Corporation Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, 99, 100, 99A, B90, C90, C90A, E90, H90, A99, A99A, B99, and C99 aircraft. Compliance: Required within the next 180 days after the effective date of this AD, unless accomplished previously. To prevent excessive engine acceleration time that could result in an aircraft's inability to safely perform the balked landing maneuver required by Federal Aviation Regulations (FAR) part 23, paragraphs 23.75(d), 23.77 and 23.143(a)(5), accomplish the following: (a) Perform a visual inspection to determine if a compressor delivery air line (P3) filter assembly has been installed on the engine. NOTE: The compressor delivery air line assembly may have been installed on the engine as original equipment, or may have been installed per any of the following PWC Service Bulletins: 1205, 1253, 1290, 1294, 1330, 1343, or 1378. (b) Remove from service, if installed, the P3 filter assembly. NOTE: The engine compressor delivery air line assembly can be returned to an approved configuration without a P3 filter. For information, refer to the applicable PWC Maintenance Manual and Parts Catalog. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office, FAA, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained fromthe Engine Certification Office. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) This amendment becomes effective on August 17, 1992.
2007-23-05: 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-06-04: This amendment adopts a new airworthiness directive (AD), applicable to EROS series MF10-( )-( ) full face quick donning mask regulators, that requires replacement of the face piece and the mask shell securing screw. This amendment is prompted by reports of the plastic pin breaking which secures the mask shell with the face piece. The actions specified by this AD are intended to prevent the failure of the pin securing the mask shell to the face piece, which could result in a mask leaking oxygen and the crew losing consciousness.
2001-09-08: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires installing a second electrical connector in the electrical Master Central Unit. The actions specified by this AD are intended to prevent the loss of electrical power, other than that provided by the emergency system, in the event of disconnection of the single electrical connector within the electrical Master Central Unit. This action is intended to address the identified unsafe condition.
2019-23-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports that the nose landing gear (NLG) retracted on the ground, with weight on the airplane's wheels, due to the incorrect installation of an NLG downlock pin in the apex pin inner bore of the NLG lock link assembly. This AD requires installing an insert to prevent installation of the pin in the incorrect location. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-02: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon (Beech) Model MU-300-10, 400, 400A, and 400T series airplanes; and certain Raytheon (Mitsubishi) Model Beech MU-300 airplanes. This AD requires a one-time inspection of certain panels in the spoiler mixer bay for the presence of drain holes, and the addition of at least one new drain hole; and a one-time inspection for discrepancies of the sealant on the relief cutout on the aft pressure bulkhead, and on certain baffles; and corrective actions if necessary. This AD is prompted by a report of fuel leaking from components in the spoiler mixer bay of several Raytheon (Beech) Model 400A series airplanes. We are issuing this AD to prevent the accumulation of fuel and/or fuel vapor in the spoiler mixer bay and/or the aft fuselage compartment, which could result in a fire in the airplane.
2001-09-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to verify the proper configuration of the drive assemblies for the low-pressure and, for certain airplanes, the cross-feed fuel valves; and corrective action, if necessary. This action is necessary to prevent failure of the low-pressure and/or cross-feed fuel valves, which could result in the inability to shut off the fuel supply to the engine and exacerbate an engine fire, or the inability to cross-feed fuel when required. This action is intended to address the identified unsafe condition.
2001-09-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -300 series airplanes, that requires repetitive clearing of the drain passage at the aft end of the main landing gear (MLG) truck beam to ensure moisture and contaminants within the truck beam can properly drain; and, for certain airplanes, an internal inspection of the truck beam to detect discrepancies, and follow-on actions. This amendment is prompted by reports of fracture of MLG truck beams. The actions specified by this AD are intended to prevent stress corrosion cracking, leading to fracture of a MLG truck beam during ground operations, which could result in either reduced controllability of the airplane or a fire.
2001-09-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires replacement of certain existing bushings of the aft trunnion of the outer cylinder of the main landing gear (MLG) with new bushings, and replacement of grease in an undercut on the aft trunnion, if necessary. The actions specified by this AD are intended to prevent stress corrosion cracking and consequent fracture of the aft trunnion of the outer cylinder of the MLG, which could result in collapse of the MLG. This action is intended to address the identified unsafe condition.
2004-18-03: The FAA is superseding an existing airworthiness directive (AD) for certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701), and CL-600-2D24 (Regional Jet Series 900) series airplanes. That AD currently requires revising the airplane flight manual to advise the flightcrew to monitor the fuel quantity in the center fuel tank throughout the flight. That AD also requires repetitive tests to detect a fuel leak between the wing fuel tanks and the center fuel tank; and further related investigative and corrective actions, if necessary. For certain airplanes, that AD also requires installation of flexible hoses and brackets in the fuel feed system. This AD reduces the compliance times for the repetitive checks, requires replacement of primary fuel feed ejectors with new ejectors, and provides an optional center fuel tank empty procedure. This AD is prompted by reports of cracking in the primary fuel ejector. We are issuing this AD to detect and correct cracking in any primary fuel ejector, which could cause fuel leakage into the center fuel tank, and could result in engine shutdown during flight. DATES: Effective September 17, 2004. The incorporation by reference of certain publications listed in the AD was approved previously by the Director of the Federal Register as of April 15, 2004 (69 FR 16780, March 31, 2004). We must receive any comments on this AD by November 1, 2004.
2001-09-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dornier Model 328-300 series airplanes. This action requires repetitive inspections of motive flow check valves and adjacent parts for fuel leaks, and replacement of the valves, if leaks are detected. This action is necessary to prevent leakage of fuel from the motive flow check valves, which could result in fuel vapors coming into contact with fuel ignition sources. This action is intended to address the identified unsafe condition.