Results
2008-06-24: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, and -500 series airplanes. This AD requires an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service unit and the lavatory and attendant box assemblies, corrective action if necessary, and other specified action. This AD results from a report that several passenger masks with broken in-line flow indicators were found following a mask deployment. We are issuing this AD to prevent the in-line flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event.
2001-15-13: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires repetitive inspections of the metallic vapor seals in the center fuel tank to detect holes, tears, or a change in shape; corrective action, if such damage is detected; and follow-up tests for leaks. This amendment is prompted by reports of damaged metallic vapor seals observed during routine maintenance. This action is necessary to detect and correct damage to the metallic vapor seal in the center fuel tank, which could lead to leakage of fuel from the center tank into the air conditioning pack bay located below the center tank, providing a potential for fuel to be in contact with fuel ignition sources. This action is intended to address the identified unsafe condition.
2020-11-13: The FAA is superseding Airworthiness Directive (AD) 2010-23- 04, which applied to all De Havilland Aircraft of Canada Limited Model DHC-8-400 series airplanes. AD 2010-23-04 required repetitive detailed inspections of the nacelle attachment fittings for cracks, a conductivity inspection of the nacelle attachment fittings, and replacement if necessary. This AD continues to require these inspections and replacement if necessary, removes a certain inspection requirement for certain airplanes, and adds a new requirement to replace the rear spar fitting and nacelle attaching structure with a new nacelle attachment fitting. This AD was prompted by a determination that it is necessary to do a replacement with new nacelle attachment fittings. The FAA is issuing this AD to address the unsafe condition on these products.
2008-06-25: 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: Two A330 operators have reported that the guide shaft of the Refuel Isolation Valve has been broken away from the main casting and entered the fuel tank. The Supplier Investigation evidenced that water builds-up in the cavity of the Refuel Isolation Valve and freezes during flight. When refuel pressure is applied to the piston, the ice restricts the piston travel on one side leading to an asymmetric movement of the piston resulting in breakage of the guide shaft. A non-bonded metallic object within the fuel tank can result [in] a potential ignition source, which in combination with a lightning strike constitutes an unsafe condition. We are issuing this AD to require actions to correct the unsafe condition on these products.
2018-18-13: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking in certain flanges, and the adjacent web, of the wing outboard flap track at certain positions, and a determination that new inspections of certain flap track flanges and webs forward of the rear spar attachment are necessary. This AD requires an inspection to determine the part number of the wing outboard flap track assembly; repetitive inspections of each affected wing outboard flap track for discrepancies, and applicable on-condition actions; and repetitive overhaul of each wing outboard flap track. We are issuing this AD to address the unsafe condition on these products.
95-02-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT8D series turbofan engines, that currently requires initial and repetitive inspections of the Number 7 fuel nozzle and support assembly, replacement of the Number 7 fuel nozzle and support assembly with a more leak-resistant configuration, and replacement of aluminum oil pressure and scavenge tube fittings with steel fittings. This amendment adds a requirement incorporated in a new revision of a PW Alert Service Bulletin (ASB) that was omitted from the existing AD to replace an additional aluminum oil scavenge line bolt with a steel bolt. This amendment also makes a correction to a note in the compliance section to apply only to PW JT8D-200 series engines. This amendment is prompted by the need to make these corrections. The actions specified by this AD are intended to prevent fuel leakage from the Number 7 fuel nozzle and support assembly, ignition of that leaking fuel, and liberation of oil from melted oil line fittings, which can result in an uncontained engine fire and damage to the aircraft.
2017-20-09: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF34-8E model turbofan engines. This AD was prompted by a report that using a certain repair procedure for the fan outlet guide vane (OGV) frame could alter the strength capability of the fan OGV frame. This AD requires replacement of all fan OGV frames [[Page 46670]] repaired using this procedure. We are issuing this AD to address the unsafe condition on these products.
95-02-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires replacement of the bolts, nuts, and washers that attach the support bracket at the Number 4 and Number 5 transmissions to the wing flap structure. This amendment is prompted by a report of damage to the left inboard trailing edge flap. The actions specified in this AD are intended to prevent these airplanes from taking off with broken bolts that attach the transmission bracket to the wing flap track structure, which could result in the airplane rolling at liftoff.
95-02-02: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and Model C-9 (military) airplanes, that requires inspection of the tailcone release locking cable fitting assembly, and replacement or modification of the assembly, if necessary. This amendment is prompted by reports of the inability of the tailcone to deploy because the swaged ball on the cable had jammed after passing into the release handle hole. The actions specified by this AD are intended to prevent the inability of the tailcone to deploy, which could impede the egress of passengers from the airplane during an emergency evacuation.
94-26-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes. This action requires modification of the leading edge slat access panel and internal structure at Front Spar Station (FSS) 250.663. This amendment is prompted by reports that fuel leaking from the fuel line at FSS 250.663 flowed through a drain hole in a slat access panel and leaked into the turbine exhaust area. The actions specified in this AD are intended to prevent drainage from such a fuel leak into the turbine exhaust area, which could cause an external fire under the wing.
2008-06-17: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Some operators have reported occurrences where the rear stick- pusher cable clamp shifted forward on the elevator cable. This condition, if not corrected, may reduce the effectiveness of the stick-pusher and/or limit elevator control movement. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2005-01-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD requires modifying the wire routing of electrical harness 636VB in the right-hand wing. This AD is prompted by the manufacturer's analysis for compliance with Special Federal Aviation Regulation No. 88, which has shown that wiring 2M of the 115V anti-collision white strobe lights and wiring 2S of the fuel quantity indication system (FQIS) should be rerouted into separate conduits. We are issuing this AD to prevent chafing damage to wiring 2M and 2S, which could result in a short circuit and consequently introduce an electrical current into the wiring of the FQIS and create an ignition source in the fuel tank.
2008-06-13: 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: On 23 November 2006, Emergency Airworthiness Directive (EAD) Nr. (number) 2006-0351-E was published requiring an inspection to be performed on C-212 aeroplanes having been used for Maritime Patrol or other similar low altitude operations, due to the fact that, after initial examination of the evidences of a recent C-212 Maritime Patrol aircraft accident, cracks had been found in the centre wing lower skin at STA Y=1030. At the time of the accident, the aircraft had accumulated 17,000 flight hours and 7,300 flight cycles. The cracks were suspected to be caused by fatigue. A more detailed examination in the laboratory, led to think that the initiation of the fatigue cracks was produced by fretting, and EAD 2006-0365-E, superseding EAD 2006-0351-E, was published on 4 December 2006 to address the new situation. Further examination in the laboratory has allowed to establish that crack initiation was due to fatigue and the fretting was posterior. * * * * * * * The above mentioned cracks, if not timely detected, could lead to reduced structural integrity of the aircraft.* * * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 17, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 17, 2008. The Director of the Federal Register approved the incorporation by reference of EADS-CASA All Operator Letter 212-018, Revision 1, dated December 1, 2006, listed in this AD as of March 14, 2007 (72 FR 8610, February 27, 2007).
2001-15-18: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT8D series turbofan engines. This amendment requires removing certain 2nd stage compressor disks, specified by part number (P/N) and serial number (SN), from service. This amendment is prompted by a report from PW of a number of JT8D engine 2nd stage compressor disks that were delivered to the field with potential machining damage to the tie rod, counterweight, and pin holes. The actions specified by this AD are intended to prevent rupture of the 2nd stage compressor disk caused by machining damage, which could result in an uncontained engine failure and damage to the airplane.
2020-12-03: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG Trent XWB-97 model turbofan engines. This AD requires updating electronic engine control (EEC) software. This AD was prompted by the manufacturer's finding that a P30 (air pressure) sense line could become partially blocked with a mixture of ice and water, which would cause a time-lag in the P30 signal, interfering with the fuel flow limit calculations. The FAA is issuing this AD to address the unsafe condition on these products.
2005-01-10: The FAA adopts a new airworthiness directive (AD) that supersedes Airworthiness Directive (AD) 74-06-01, which applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-23-235, PA-23-250, and PA-E23-250 airplanes equipped with Garrett Aviation Services (Garrett) (formerly AiResearch) turbosuperchargers installed under supplemental type certificate (STC) SA852WE, SA909WE, or SA978WE; or installed under Piper Aircraft Drawing Number 32016. AD 74-06-01 currently requires you to replace turbosupercharger oil tanks, install fire shrouds, seal all openings in the fire shrouds, and add drainage provisions in the oil tank fairings for airplane serial numbers 27-1 through 27-2504; and add drainage provisions in the air scoops on serial numbers 27-2505 and higher. This AD requires you to replace the oil reservoir and related hoses with a fireproof oil tank and fire-shielded hoses. This AD results from a report of a fatal accident related to the breakdown of the turbocharger oilreservoir following a fire in the engine nacelle. We are issuing this AD to prevent turbosupercharger oil reservoirs with inadequate fire resistance from failing when exposed to flame or exhaust gases. This failure could lead to an in-flight fire within the nacelle area penetrating the firewall and subsequent failure of the wing spar.
95-01-02: This amendment supersedes three existing airworthiness directives (AD), applicable to Hartzell Model HC-B4TN-5(D,G,J)L/LT10282(B,K)-5.3R and HC-B4TN-5(D,G,J)L/LT10282N(B,K)-5.3R propellers installed on Mitsubishi MU-2 series aircraft. These AD's currently require replacement of existing LT10282(B,K)-5.3R propeller blades with LT10282N(B,K)-5.3R improved "N" configuration propeller blades, and repetitive inspection and rework when required of the inner hub arm bore. This amendment requires new repair limits, shot peening procedures, and retirement at 10,000 hours time in service for the "N" configuration blades. Additionally, this action requires replacement of existing propeller hubs with new improved fatigue strength steel hubs and requires inspection, and specified rework as necessary, of the new steel hubs at a repetitive interval of 3,000 hours time in service. This amendment is prompted by a determination that the current hub design and blade repair limits do not adequately protect against initiation of fatigue cracks in the propeller hub arm bore and do not prevent the resonant speed of the propeller from shifting into the permitted ground idle operating range. The actions specified by this AD are intended to prevent initiation of fatigue cracks in propeller assemblies and subsequent progression to propeller failure, with departure of the blade, or hub arm and blade, that may result in loss of aircraft control.
95-01-07: This amendment supersedes Airworthiness Directive (AD) 83-12-01, which currently requires repetitively inspecting the lower wing skin panel for cracks on certain Fairchild Aircraft Models SA227-AC and SA227-AT airplanes, and installing wing skin reinforcement doublers if any wing skin crack is found. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate, or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action requires installing wing skin reinforcement doublers or wing skin stringer ties as terminating action for the repetitive inspections that are currently required by AD 83-12-01. The actions specified by this AD are intended to prevent fatigue failure of the lower wing skin panels, which could result in loss of control of the airplane.
2008-06-15: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Defective burner hoses have been identified which might develop a leak. A significant leak, if it was ignited, could hazard the balloon and occupants. Since the issue of AD G-2003-0010 there have been occurrences of hose failure in batches not identified in the earlier bulletins. LHAB Service Bulletin (SB) No 11 supersedes the earlier SBs and revises the applicability as required. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2001-15-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires performing a general visual inspection of the outer handle flap mechanisms of the passenger doors for the presence of corrosion inhibitor and for correct operation; cleaning, if necessary; and greasing. The actions specified by this AD are intended to prevent blockage of the outer handle flap in an intermediate pushed-in position, which may prevent a passenger door from opening from the inside of the airplane, thereby delaying an emergency evacuation. This action is intended to address the identified unsafe condition.
2020-10-10: The FAA is superseding Airworthiness Directive (AD) 2016-07- 28, which applied to all The Boeing Company Model DC-9-81 (MD-81), DC- 9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. AD 2016-07-28 required repetitive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center wing lower skin, and repair if any crack was found. This AD continues to require repetitive ETHF inspections for any cracking in the left and right side center wing lower skin, and repair if any crack is found. This AD also requires expanding the inspection area to include adjacent stringers with similar stress levels and to perform repetitive inspections with increased sensitivity for crack detection. This AD was prompted by a report of a crack at a certain stringer not addressed by AD 2016-07-28, and cracks at certain other \n\n((Page 31047)) \n\nstringers and associated end fittings, and skins in the center wing fuel tank wherethe stringers meet the end fittings addressed by AD 2016-07-28. The FAA is issuing this AD to address the unsafe condition on these products.
2018-18-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by several reports of cracks in a certain floor beam lower chord at door stop fitting No. 1 of the forward airstair door cutout. This AD requires repetitive inspections for any cracks and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2008-06-02: 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards * * *. [A]ssessment showed that supplemental maintenance tasks [for certain bonding jumpers, wiring harnesses, and hydraulic systems, among other items] are required to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2014-05-29: We are superseding airworthiness directive (AD) 2009-16-03 for certain Continental Motors, Inc. (CMI) IO-520, TSIO-520, and IO-550 series reciprocating engines, with certain SAP replacement parts manufacturer approval (PMA) investment cast cylinder assemblies installed. AD 2009-16-03 required initial and repetitive inspections and compression tests to detect cracks in those cylinders. This new AD requires that additional engines be added to the applicability. This AD was prompted by the need to add to the applicability all other engine models approved for the use of CMI 520 and 550 cylinder assemblies, such as the CMI 470 series engines when modified by supplemental type certificate (STC), with affected SAP investment cast cylinder assemblies installed. We are issuing this AD to prevent the separation of the cylinder head, damage to the engine, and damage to the airplane.
95-01-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires a revision to the FAA-approved Airplane Flight Manual to include procedures to perform periodic engine run-ups during ground operation in icing conditions in order to shed ice before it accumulates, sheds, and is ingested into the engine, which could cause damage to the core of the engine. This action provides procedures for a visual check to detect ice build-up on the first stage of the low pressure compressor (LPC) stator and removal of any ice, as necessary. This amendment is prompted by reports of damage to the high pressure compressor of the engines due to ice ingestion. The actions specified in this AD are intended to prevent damage to engines due to the ingestion of ice into the compressor, which can result in the loss of power from the affected engine.