Results
2011-18-18: 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: Several operators have reported pitch oscillations and/or elevator asymmetry caution lights illumination when flying with the autopilot engaged. Investigations revealed that loose rivets in the torque tube assemblies caused relative motion between the crank arms and torque tubes. Loose rivets could result in excessive wear and subsequent significant backlash in the driving crank arms. This condition, if left uncorrected, will progressively get worse and degrade the controllability of the aeroplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-12-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer 18A; and repair or replacement of cracked parts. This amendment is prompted by reports of fatigue cracks in those outboard chords. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the outboard chords, and subsequent rapid decompression of the airplane.
2008-11-07: We are adopting a new airworthiness directive (AD) for all Boeing Model 757 airplanes. This AD requires installation of an automatic shutoff system for the center tank fuel boost pumps, and installation of a placard in the airplane flight deck if necessary. This AD also requires revisions to the Limitations and Normal Procedures sections of the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automated center tank fuel pump shutoff control. This AD also requires a revision to the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness to incorporate AWLs No. 28-AWL-20 and No. 28-AWL-26. This AD also requires replacement of the fuel control panel assembly with a modified part, installation of two secondary pump control relays for the center tank fuel pumps, other specified actions, and concurrent modification of the fuel control panel assembly. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent center tank fuel pump operation with continuous low pressure, which could lead to friction sparks or overheating in the fuel pump inlet that could create a potential ignition source inside the center fuel tank; these conditions, in combination with flammable fuel vapors, could result in a center fuel tank explosion and consequent loss of the airplane.
2001-18-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Goodyear Tire and Rubber Company (Goodyear) Flight Eagle tires, 34X9.25-16 18PR 210MPH, Part Number (P/N) 348F83-2, that are installed on aircraft. This AD requires you to inspect these tires to determine if they are within a certain serial number range and replace any tires within this serial number range. This AD is the result of several instances of main landing gear (MLG) tire tread separations on Gulfstream aircraft. The actions specified by this AD are intended to remove these tires from service to prevent the potential of these tires experiencing tread separations during operation. These tread separations could result in structural damage to the aircraft, including damage to the flaps, engine nacelles, and wheel wells.
2008-11-04: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracking in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways, and corrective actions if necessary. This AD results from multiple reports of cracks found in the skin, bearstrap, and/or frame outer chord in the hinge cutout areas of the forward entry and forward galley service doorways. We are issuing this AD to detect and correct such cracking, which could result in rapid decompression of the airplane.
2017-22-13: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 970-84 and RB211-Trent 972-84 turbofan engines. This AD requires an inspection of the drains mast. This AD was prompted by cracks found in the transition duct area of the drains mast. We are issuing this AD to address the unsafe condition on these products.
2003-20-07: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80E1A2 turbofan engines with forward engine mount platforms part numbers (P/Ns) 1520M53G04 and 1846M24G15 installed. This AD requires initial and repetitive fluorescent penetrant inspections of cast material forward engine mount platforms. This AD is prompted by the airframe manufacturer's revised analyses of loads on the forward engine mount. We are issuing this AD to prevent engine separation that could result from cracking of the forward engine mount platform.
2001-17-31: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) AE 2100 turboprop and AE 3007 turbofan series engines. This amendment requires a one-time acid etch inspection of the 2nd stage high pressure turbine (HPT) wheel for evidence of damaged material indicating that a higher probability of cracking in future service exists. If the etch inspection reveals damage, this AD requires replacement of the turbine wheel with a serviceable part. This amendment is prompted by a report of a 2nd stage HPT wheel that was returned from the field with cracks in the aft bore face. The actions specified by this AD are intended to detect and prevent early development of cracks due to low cycle fatigue of the 2nd stage HPT wheel in the aft bore face that can lead to wheel failure, power loss, and possible damage to the airplane.
95-14-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Model ATR72-100 and -200 series airplanes, that requires a one-time dye penetrant inspection to detect cracking in certain hinge pins of the nose landing gear (NLG), and replacement of cracked pins with crack-free pins. This amendment is prompted by reports of cracking of certain hinge pins in the NLG. The actions specified by this AD are intended to prevent collapse of the NLG due to cracking of the hinge pins.
2008-11-01: We are adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, -300F, and -400ER series airplanes. This AD requires revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD would also require the initial inspection of certain repetitive AWL inspections to phase in those inspections, and repair if necessary. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2021-17-16: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by fatigue testing and analyses. This AD requires establishing a life limit for a certain part-numbered tail gearbox fitting. The FAA is issuing this AD to address the unsafe condition on these products.
2020-18-07: The FAA is superseding Airworthiness Directive (AD) 2016-18- 09, which applied to certain Airbus SAS Model A318, A319, and A320 series airplanes. AD 2016-18-09 required repetitive detailed inspections for damage on the fuselage skin at certain frames, and applicable related investigative and corrective actions. This AD continues to require repetitive inspections of the fuselage skin for chafing damage at certain frames using a new inspection process, and corrective actions if necessary; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of additional chafing of the forward fuselage found underneath the fairing structure. Investigation revealed the cause as contact between the belly fairing nut plate and the fuselage. The FAA is issuing this AD to address the unsafe condition on these products.
2008-11-05: 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: Based on some recent in-service findings for fluid ingress and/ or inner skin disbond damage on rudders, AIRBUS decided to introduce some further structural inspections to specific rudder areas. This type of damage could result in reduced structural integrity of the rudder. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-17-30: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney JT9D-7R4 series turbofan engines. This amendment requires initial and repetitive fluorescent penetrant inspection (FPI) of the high pressure turbine (HPT) 1st stage disk aft lugs, and if the aft lug(s) are cracked, replacement of the HPT 1st stage disk and HPT 1st stage airseals. Also, for certain configuration HPT disk assemblies, this amendment requires replacement of the HPT 1st stage airseals with newly designed airseals at the next accessibility. This amendment is prompted by reports of cracks in HPT 1st stage disk firtrees and failure of firtree lugs. The actions specified by this AD are intended to prevent 1st stage HPT disk firtree fracture, which could result in an uncontained engine failure, and damage to the airplane.
2020-17-14: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model Falcon 10 airplanes. This AD was prompted by a report of hydraulic fluid on the ground near the main landing gear (MLG) brake assembly. The hydraulic leakage started in a cracked hydraulic pipe, with the crack likely due to chafing between two \n\n((Page 54889)) \n\nhydraulic pipes or between hydraulic pipes and structure. This AD requires an inspection for chafing or interference of certain hydraulic pipes and certain rib passage holes, and, depending on findings, modification or repair, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-05-02: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-90-30 airplanes. This AD requires a general visual inspection in the electrical/electronics (E/E) compartment for damage of the wire bundle and aft right radio rack structure at station 160.000, and corrective actions if necessary. This AD also requires modifying the radio rack structure and wire bundle routing. This AD is prompted by a report indicating that burnt wiring was discovered in the wire bundle at station 160.000 in the E/E compartment. We are issuing this AD to detect and correct chafing of the wire bundle at station 160.000 against the support bracket located on the aft right radio rack, which could lead to shorted or burnt wires and consequent smoke and fire in the E/E compartment.
2008-11-03: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, and -200C series airplanes. This AD requires revising the FAA-approved maintenance inspection program to include inspections that will give no less than the required damage tolerance rating for each structural significant item (SSI), doing repetitive inspections to detect cracks of all SSIs, and repairing cracked structure. This AD results from a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective. We are issuing this AD to maintain the continued structural integrity of the entire fleet of Model 737-100, -200, and -200C series airplanes. \n\nDATES: This AD is effective June 25, 2008. \n\n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 25, 2008. \n\n\tThe Director of the Federal Register approved the incorporation byreference of Boeing Document D6-37089, "Supplemental Structural Inspection Document for Model 737-100/200/200C Airplanes," Revision E, dated May 2007, as listed in this AD, on May 27, 2008 (73 FR 21237, April 21, 2008).
2005-04-15: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Model Falcon 2000EX and 900EX series airplanes. This AD requires prohibiting dispatch with certain equipment inoperative; and revising the airplane flight manual to facilitate recovery of the cockpit display units in the event of an avionics standard communication bus (ASCB) failure and to inform the flightcrew what equipment is inoperative during an ASCB failure. This AD also requires doing an integrity check of the ASCB for any faults and corrective action if necessary, and installing an avionics software update to the Honeywell Primus Epic system. This AD is prompted by a report that an analysis and tests of the Honeywell Primus Epic systems installed on the Model Falcon 2000EX and 900EX series airplanes revealed that all information displayed on the cockpit display units could become invalid during flight. We are issuing this AD to prevent a loss of data from all four of the cockpit display units,and loss of all radio communications (with the exception of VHF emergency frequency and last frequency used), primary navigation instruments, autopilot, auto- throttle, central alerting system, aural alarms, and normal braking (on Model Falcon 2000EX series airplanes only). These losses could reduce the flightcrew's situational awareness, increase flightcrew workload, and consequently reduce the ability to maintain safe flight and landing of the airplane.
2001-17-33: This amendment adopts a new airworthiness directive (AD) for Agusta Model AB412 helicopters. This action prohibits use of the hoist until certain modifications are accomplished. This amendment is prompted by the loss of a hoist hook during flight due to an uncommanded firing of the cable cutter cartridge caused by wire chafing. The actions specified in this AD are intended to prevent wire chafing, inadvertent firing of the cable cutter cartridge, loss of a hoist hook and section of cable, impact with the main or tail rotor, and subsequent loss of control of the helicopter.
2001-17-32: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model AS350B, B1, B2, B3, BA, D, AS355E, F, F1, F2, and N helicopters. That AD requires inspecting certain versions of the tail rotor pitch change spider assembly (spider assembly) for the proper rotational torque, axial play, and any brinelling of the bearing. This AD requires identifying the spider assembly with index marks to detect bearing spacer rotation, visually checking to ensure that the index marks are aligned before the first flight of each day, and subsequently modifying the spider assembly. This AD also adds the ECF Model AS350D1 helicopters to the applicability. This AD is prompted by operator reports that the spider assembly bearing spacers are rotating. The actions specified by this AD are intended to detect rotation of the spider assembly bearing spacers, prevent seizure of the bearing, loss of tail rotor control, and subsequent loss of control of the helicopter.
2008-10-15: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires an inspection to determine if acceptable external skin doublers are installed at the stringer 6 (S-6) lap splices, between station (STA) 340 and STA 400. For airplanes without the acceptable external skin doublers, this AD requires repetitive related investigative actions and corrective actions if necessary. This AD also provides an optional terminating modification for the repetitive related investigative actions. This AD results from a report of cracked fastener holes at the right S-6 lap splice between STA 340 and STA 380. We are issuing this AD to detect and correct cracking in the fuselage skin, which could result in rapid decompression and loss of structural integrity.
95-14-02: This amendment supersedes Airworthiness Directive (AD) 91-24-15, which currently requires modifying the instrument air plumbing system on Beech Aircraft Corporation (Beech) Models 1900 and 1900C airplanes. This action requires an additional modification to the plumbing of the instrument air system on the Models 1900 and 1900C airplanes, and adds the Model 1900D airplanes to the applicability. Eight reports of moisture freezing in this system on airplanes with the modification required by AD 91-24-15 incorporated prompted this action. In addition, recent testing on the Model 1900D indicates that the design of the instrument air system on these airplanes is also conducive to moisture freeze-ups. The actions specified by this AD are intended to prevent ice formation in the plumbing of the instrument air system, which, if not detected and corrected, could result in aerodynamic problems and subsequent loss of control of the airplane.
2001-17-29: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 B2 and B4 series airplanes, and certain Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes. This action requires a one-time inspection to detect cracks in gear rib 5 (left and right) of the main landing gear (MLG) attachment fittings at the lower flange and vertical web, and repair if necessary. This action is necessary to detect and correct fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2001-17-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707 and 720 series airplanes, that requires a preventive modification of the front spar fitting on the outboard engine nacelle. This action is necessary to prevent fatigue cracking of the front spar fitting on the outboard engine nacelle, which could reduce the structural integrity of the nacelle, and result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
95-12-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747SP series airplanes, that currently requires repetitive inspections for cracks in the web of the wing front spar over engine numbers 2 and 3, and repair, if necessary. This amendment requires additional inspections in an area beyond that specified in the existing AD. This action also would provide for a new, optional modification, which, if accomplished, would constitute terminating action for the repetitive inspections. This amendment is prompted by a report of cracking in the web in an area outside the inspection zone specified in the existing AD. A crack in the web that is not detected before it extends outside the chord footprints can allow fuel leakage. The actions specified by this AD are intended to prevent fuel leakage onto an engine and a resultant fire due to cracking in the web of the wing front spar.