Results
2007-24-04: The FAA is superseding an existing airworthiness directive (AD) for CFM International, S.A. CFM56-5C4/1 series turbofan engines. That AD currently requires that the low pressure turbine (LPT) conical support, part number (P/N) 337-002-407-0, be removed from service at or before reaching the cyclic life limit of 9,350 cycles-since-new (CSN). This AD requires that the same P/N LPT conical support be removed from service before reaching the new, relaxed cyclic life limit of 20,000 CSN. This AD results from CFM International, S.A. performing a life extension study of the LPT conical support, P/N 337-002-407-0. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane.
2004-22-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and -400F series airplanes. This AD requires a detailed inspection(s) for cracks and fractures of the side guide support fittings in the lower lobe cargo compartments; and applicable investigative/corrective actions and operational limitations, if necessary. This AD also requires a terminating action for the repetitive inspections. This AD is prompted by reports of cracked/fractured side guide support fittings in the aft, lower lobe cargo compartment. We are issuing this AD to prevent cracked/fractured side guide support fittings in the lower lobe cargo compartments, which could result in unrestrained cargo shifting in flight and damaging the airplane structure or systems, and consequent reduced controllability of the airplane.
2000-03-03 R1: This amendment revises an existing airworthiness directive (AD), applicable to General Electric Company CF34 series turbofan engines, that currently requires revisions to the Engine Maintenance Program specified in the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF34 series turbofan engines. Those revisions require enhanced inspection of selected critical life-limited parts at each piece-part exposure. The existing AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment removes inspection requirements for parts removed from engines mounted on-wing. This amendment is prompted by the high removal rate and subsequent piece-part exposure of fan disks due to certain maintenance procedures. This additional exposure has resulted in fan disk focused inspection rates that exceed the intent of the focused inspection initiative. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2017-24-01: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes and Model ATR72-212A airplanes. This AD requires an inspection for routing attachments of electrical harness bundles and for wire damage, and corrective actions if necessary. This AD was prompted by reports of electrical harness bundle chafing with a window blinding panel in the fuselage due to missing routing attachments. We are issuing this AD to address the unsafe condition on these products.
94-08-14: This amendment adopts a new airworthiness directive (AD), applicable to all Corporate Jets Model BAe 125-1000A series airplanes, that requires replacement of the white 'EMERG CONTCTRS' annunciator screen on roof panel 'CG' of the flight deck with an amber screen. This amendment is prompted by a report that the annunciator screen currently installed on these airplanes is not a color that would alert the flight crew that corrective action may be necessary. The actions specified by this AD are intended to ensure that the flight crew is alerted to conditions when standby electrical power is not available.
2007-23-17: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A and 206B helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The aviation authority of Canada, with which we have a bilateral agreement, states in the MCAI: Reevaluation of the structural analysis indicates the need for the removal from service of bolts in this application. The removal of certain main rotor latch bolts is required because these bolts do not have a mandatory retirement life. Further evaluation has shown that these bolts fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of control of the helicopter. We are issuing this AD to require actions to correct this unsafe condition on these products.
2007-19-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-19-52, which was sent previously to all known U.S. owners and operators of the specified Bell Helicopter Textron Canada Limited (BHTC) model helicopters by individual letters. This AD requires replacing each affected tail rotor blade (blade) with an airworthy blade with a serial number not listed in the Rotor Blades, Inc. (RBI), attachment to the BHTC Alert Service Bulletin (ASB), listed in the applicability section of this AD. This amendment is prompted by three incidents in which blade tip weights were slung from blades during flight causing significant vibration. The actions specified are intended to prevent loss of a blade tip weight, loss of a blade, and subsequent loss of control of the helicopter.
2001-10-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires applying torque to certain tubing fittings of the fire extinguishing systems of various areas of the airplane, and applying torque paint to the fittings. This action is necessary to ensure that certain tubing fittings of the fire extinguishing systems are properly torqued. Improperly torqued tubing fittings of the fire extinguishing systems of the baggage compartment, auxiliary power units (APU), and engines, if not corrected, could become loose and cause the fire extinguisher to inadvertently discharge. Inadvertent discharge of a fire extinguisher could result in reduced fire protection or the inability to extinguish a fire in the baggage compartment, APU, or engine. This action is intended to address the identified unsafe condition.
94-09-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect damage of the auxiliary power unit (APU) power feeder cable installation, repair of damaged cables, and modification of the cable installation. This amendment requires an inspection of previously modified airplanes to determine whether a spacer or "stand off" has been installed, and installation of those items, if necessary. This amendment is prompted by reports of generator power feeder cables electrically shorting to the airplane structure due to chafing. The actions specified by this AD are intended to prevent the APU power feeder cable from chafing against adjacent structures, which could result in electrical shorting and arcing, and a fire below the cabin floor.
2007-22-10: We are superseding an existing 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: During MLG (main landing gear) lubrication, a crack was found visually in the MLG rib 6 aft bearing forward lug on one A330 in service aircraft. * * * This condition, if not detected and corrected, could affect the structural integrity of the MLG attachment. Failure of the forward lug could result in collapse of the MLG upon landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 16, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 16, 2007. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD as of February 15, 2007 (72 FR 4416, January 31, 2007). We must receive comments on this AD by December 3, 2007.
2001-09-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Airbus Model A330-243, -341, -342, and -343 series airplanes equipped with Rolls Royce Trent 700 series engines. This action requires repetitive inspections of certain components, and corrective action, if necessary. This action is necessary to detect and correct fatigue cracking of the hinge assemblies and the 12 o'clock beam structure of the thrust reverser C-duct, which could cause failure of the thrust reverser hinge, resulting in separation of the thrust reverser from the airplane. This action is intended to address the identified unsafe condition.
2019-24-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes, Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that during a maintenance check, cracks were found in a stiffener of a certain lateral window frame. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions, 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.
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).