Results
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.
94-26-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires an initial servicing or overhaul of the ram air turbine (RAT), and incorporating repetitive overhaul actions into the FAA-approved maintenance program. This amendment is prompted by reports indicating that, during routine maintenance of the RAT, the turbine blade assembly separated during spin tests. The actions specified by this AD are intended to prevent separation of the turbine blade assembly, which could damage the airplane structure and systems, and, under certain circumstances, could lead to reduced controllability of the airplane. DATES: Effective February 3, 1995. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 3, 1995.
2008-05-17: This document supersedes an existing airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. That AD currently requires interim initial and repetitive inspections of tailboom parts, installing six inspection holes in the aft fuselage skin panels, installing tailboom attachment bolt washers, modifying both access covers, and replacing broken attachment bolts. The current AD also provides for modifying the fuselage aft section as an optional terminating action. This amendment requires modifying the fuselage aft section within the next 24 months to strengthen the tailboom attachment fittings and upper longerons. The actions specified by this AD are intended to prevent failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter.
2008-06-04: 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: Three cases of outer deflector panel found detached or broken during ground inspection have been reported to Airbus. * * * [A]n operator has also reported a missing portion of hinge on one panel. * * * Mishandling or failure of the small portion of hinge located inboard of the affected deflector panel is suspected to be the main cause of the deflector damage. This can cause misalignment of the deflector panel followed by hinge pin migration and possible further damages to the deflector on flap retraction. If not corrected, such situation could lead to the loss of deflector panel and injured people on the ground. We are issuing this AD to requireactions to correct the unsafe condition on these products.
2001-14-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections to detect fatigue cracking of the vertical beam webs and chords of the nose wheel well (NWW) and of the inner chord and web of the fuselage frames at body station (BS) 300 and BS 320, and repair, if necessary. This amendment expands the applicability of the existing AD to include additional airplanes, and adds new requirements for repetitive inspections to detect fatigue cracking of the NWW vertical beam webs and frames from BS 260 to BS 320, and follow-on actions, if necessary, which would end the currently required inspections for airplanes subject to them. This amendment also provides terminating action for the new repetitive inspections. The actions specified by this AD are intended to detect and correct fatigue cracking of the NWW vertical beam webs and frames, which could result in collapse of the NWW pressure bulkhead and subsequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
94-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382 series airplanes, that requires inspection of a kingpin riser on the lower surface of the outer wing to determine fastener placement. This AD would also require repetitive inspections for fatigue cracks in the kingpin riser if the fasteners are positioned outside certain limits, and repair, if necessary. This amendment is prompted by reports of insufficient distance between the center of the outermost fastener on the kingpin riser and the edge of the riser, which can adversely affect the fatigue resistance of the outer wing assembly. The actions specified by this AD are intended to prevent structural failure of the lower surface of the outer wing due to fatigue cracks in the kingpin riser.
2008-06-09: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-200 series airplanes. This AD requires repetitive inspections to detect cracking of the support fittings of the Krueger flap actuators, and corrective actions if necessary. This AD also requires eventual replacement of any existing aluminum support fitting on each wing with a steel fitting, and modification of the aft attachment of the actuator. Doing these actions terminates the repetitive inspection requirements. This AD results from reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. We are issuing this AD to prevent cracking of the support fittings, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, resultant loss of hydraulic fluids, and consequent reduced controllability of the airplane.
2001-14-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) AD 2001-14-51 that was made available previously to all known U.S. owners and operators of General Aviation aircraft equipped with certain UPS Aviation Technologies, Inc., Model Apollo SL30 VHF NAV/COMM radios. This AD requires determination of the version of software being used by the UPS Aviation Technologies, Inc., Model Apollo SL30 VHF NAV/COMM radio, and installation of a placard to prohibit use of the radio's very-high-frequency omnirange (VOR) function for navigation, if necessary. This action is prompted by a report that, during installation of a subject radio, an installer noted that the radio was providing incorrect radial bearing information. The actions specified by this AD are intended to prevent use of incorrect bearing information by the pilot, which could result in inaccurate navigation information.
2020-09-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD was prompted by a report of vibrations around the 12Hz frequency due to the specific helicopter configuration. This AD requires removing the removable parts of the dual hoist installation or removing the de-icing system. This AD also allows, for certain helicopters, revising the Rotorcraft Flight Manual (RFM) for your helicopter and installing a placard as an optional method of compliance. The FAA is issuing this AD to address the unsafe condition on these products.
94-26-02: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8 series airplanes, that requires repetitive inspections of the passenger service unit (PSU) printed circuit boards and power supply connectors to detect corrosion and evidence of overheating; repair or replacement of the circuit boards or replacement of connectors, if necessary; and eventual installation of a terminating modification. This amendment is prompted by reports that certain PSU printed circuit boards and power supply connectors have overheated in service. The actions specified by this AD are intended to prevent overheating of the PSU printed circuit board and power supply connectors, which could lead to a fire in the PSU.
2008-05-15: We are adopting a new airworthiness directive (AD) for Eurocopter France Model EC130 B4 helicopters. 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 European Safety Agency (EASA), the Technical Agent for France, with which we have a bilateral agreement, states in the MCAI: This Airworthiness Directive (AD) is issued following the discovery of several cases of loosened rivets in the tube-to-flange attachment of the tail rotor drive center section shaft. In one case, this loosening of rivets was associated with a crack in the tube which started from a loosened-rivet hole. These occurrences can lead to failure of the tail rotor drive center section shaft. We are issuing this AD to correct the unsafe condition caused by cracks and loosened rivets in the tube-to-flange attachment of the tail rotor and the unsafecondition caused by the out-of-perpendicularity of the No. 1 bearing.
2001-14-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes. For certain airplanes this AD requires rework of the bonding jumper assemblies on the drain tube assemblies of the slat track housing of the wings. For certain other airplanes, this AD requires repetitive inspections of the drain tube assemblies of the slat track housing of the wings to find discrepancies, and corrective actions, if necessary. This AD also provides for terminating action for the repetitive inspections. These actions are necessary to find and fix discrepancies of the bonding jumper assemblies, which could result in an in-tank ignition source due to electrostatic discharge or lightning. The actions also are necessary to find and fix discrepancies of the slat track drain tubes, which could result in fuel migrating into the tubes and leaking onto an engine or exhaust nozzle, and consequent risk of a fire when the airplane is stationary or during low speed taxiing. This action is intended to address the identified unsafe conditions.
2014-04-14: We are adopting a new airworthiness directive (AD) for AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters to require removing certain rod end assemblies from service. This AD was prompted by reports of fractures on the rod end assemblies that could damage the main rotor assembly and lead to loss of control of the helicopter.