Results
2022-15-09: The FAA is superseding Airworthiness Directive (AD) 2019-23- 06, which applied to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2019-23-06 required, depending on configuration, a general visual inspection for any previous repair, such as any reinforcing repair or local frame replacement repair, repetitive open hole high frequency eddy current (HFEC) inspections for any crack of the fuselage frame web fastener holes, on the left and right side of the airplane, and applicable on-condition actions. This AD was prompted by a determination that certain compliance times must be reduced. This AD requires the actions specified in AD 2019-23-06 with reduced compliances times for certain actions. The FAA is issuing this AD to address the unsafe condition on these products.
2007-17-10: 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: It has been found cases in which the drain mast of the water and waste system does not meet the SFAR-88 (Special Federal Aviation Regulation No. 88) requirements. In case of fuel leakage or fuel vapor release, the proximity of this mast with the fuel tank may cause fuel ignition, leading to a possible tank explosion. We are issuing this AD to require actions to correct the unsafe condition on these products.
2022-15-04: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) LEAP-1A model turbofan engines. This AD was prompted by reports of non-synchronous vibrations resulting in more open clearances and potential hot gas ingestion into the high- pressure turbine (HPT) rotor cavity, which may result in thermal degradation of the HPT rotor interstage seal and HPT rotor stage 2 disk. This AD requires inspection of the stage 2 HPT nozzle assembly honeycomb and HPT stator stationary seal honeycomb. Depending on the results of the inspection, this AD requires replacement of the stage 2 HPT nozzle assembly honeycomb, HPT stator stationary seal, HPT rotor interstage seal, and HPT rotor stage 2 disk. The FAA is issuing this AD to address the unsafe condition on these products.
2007-16-18: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires repetitive detailed inspections of the wire bundles, power drive unit (PDU) wiring, and wire attaching hardware, supports, and sleeving located in the forward and aft lower lobe cargo compartments, and corrective actions as necessary. This AD results from a fire in the forward lower lobe cargo compartment found shortly after airplane arrival. We are issuing this AD to detect and correct damage to wires in the forward and aft lower lobe cargo compartments, which could result in a potential short circuit and consequent fire in the forward and aft lower lobe cargo compartments.
2022-14-12: The FAA is adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, and M601F model turboprop engines. This AD was prompted by the absence of life limits for propeller shaft part number (P/N) M601-6081.6 in the airworthiness limitations section (ALS) of the applicable GEAC M601 Engine Shop Manual. This AD was also prompted by a report that operators may not have been provided with enough data to determine the accumulated life of certain propeller shafts. For M601F model turboprop engines, this AD requires removal and replacement of the propeller shaft before the propeller shaft accumulates 12,000 flight hours (FHs) since first installation on an engine, or before accumulating 350 FHs after the effective date of this AD, whichever occurs later, with a part eligible for installation. For M601D-11, M601E-11, M601E-11A, M601E-11AS, and M601E-11S model turboprop engines, this AD requires calculation of the accumulated life of the propeller shaft and, depending on the number of accumulated FHs removal and replacement of the propeller shaft with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2007-17-09: We are adopting a new airworthiness directive (AD) to supersede 93-07-11 and AD 94-04-16, which apply to certain Mitsubishi Heavy Industries MU-2B series airplanes. AD 93-07-11 and AD 94-04-16 currently require you to reduce the maximum deflection of the elevator nose-down trim to a 1-degree to 3-degree range. When the above AD actions were issued, there was no associated elevator trim indicator change. Without such change, the trim reaches the maximum nose-down limit and the indicator still shows additional nose-down trim available. In attempting to force additional nose-down trim, pilots have manually jammed the trim system preventing subsequent electric trim changes until the pilot manually freed the trim wheel. Consequently, this AD retains the actions from AD 93-07-11 and AD 94- 04-16 and adds the action of modifying the elevator trim indicator scale dial to be consistent with the reduced elevator trim capability. We are issuing this AD to prevent the above scenarios fromoccurring with consequent loss of control. DATES: This AD becomes effective on September 25, 2007. On September 25, 2007, the Director of the Federal Register approved the incorporation by reference of Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 091/27-011, dated August 6, 1998; and Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 228, dated July 13, 1998 listed in this AD. As of June 1, 1993, the Director of the Federal Register approved the incorporation by reference of Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 079/27-010, dated August 28, 1992, listed in this AD. As of April 11, 1994, the Director of the Federal Register approved the incorporation by reference of Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 216, dated September 11, 1992, listed in this AD.
2022-14-11: The FAA is adopting a new airworthiness directive (AD) for certain Stemme AG (type certificate previously held by Stemme GmbH & Co. KG) Model Stemme S 12 gliders. This AD was prompted by 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 identifies the unsafe condition as a deviation in the construction of the connection of the inner wing to the outer wing, resulting in a wrong positioning of the glass-fiber reinforced plastic (GFRP) blocks. This AD requires inspecting the left-hand (LH) and right-hand (RH) outer wing spars for correct positioning of the GFRP blocks and, if incorrect positioning is found, repairing of the reinforcement blocks. The FAA is issuing this AD to address the unsafe condition on these products.
2007-17-01: The FAA is superseding an existing airworthiness directive (AD) for General Electric (GE) CF6-80E1 series turbofan engines. That AD currently requires removing electronic control unit (ECU) software version E.1.M. or earlier installed software, and installing improved software for the ECU. This AD requires removing software version E.1.N or earlier from the engine ECU. Engines with the new version software will have increased margin to flameout. This AD results from reports of engine flameout events during flight, including reports of events where all engines simultaneously experienced a flameout or other adverse operation. Although the root cause investigation is not yet complete, we believe that exposure to ice crystals during flight is associated with these flameout events. We are issuing this AD to minimize the potential of an all-engine flameout event caused by ice accretion and shedding during flight.
2022-13-12: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE Passport 20-17BB1A, GE Passport 20- 18BB1A, and GE Passport 20-19BB1A model turbofan engines. This AD was prompted by fuel leakage from the fuel nozzle to fuel manifold coupling nut connections. This AD requires a visual inspection of the core compartment, a re-torque of the core compartment coupling nuts, a ground power assurance check, and a borescope inspection. Depending on the results of the inspections, this AD requires operators to perform applicable maintenance in accordance with their FAA-approved instructions for continued airworthiness. The FAA is issuing this AD to address the unsafe condition on these products.
2007-16-16: 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: It has been found the occurrence of smoke on the passenger cabin originated from the valance panel lighting system wiring. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-16-14: The FAA is adopting a new airworthiness directive (AD) for all Taylorcraft A, B, and F series airplanes. This AD requires you to initially inspect the left and right wing front and aft lift struts for corrosion and cracks, replace any cracked strut or strut with corrosion that exceeds certain limits with either sealed or non-sealed struts, and repetitively inspect any non-sealed struts. This AD results from inspections where several different struts were found with moderate to severe corrosion and required strut replacement. We are issuing this AD to detect and correct corrosion or cracks in the right and left wing front and aft lift struts. This condition, if not corrected, could result in failure of the lift strut and lead to in-flight separation of the wing with consequent loss of control.
2022-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. This AD was prompted by a determination that certain service information specified in AD 2018-20-19 contained instructions that could be misleading, resulting in a necessary inspection not being accomplished on certain airplanes. This AD requires a rototest for certain modified airplanes for any crack around the right-side upper and lower bulk door support or door latch fitting holes at certain bulk cargo door frames, or repetitive inspections for any crack at certain fittings, and on- condition 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.
2007-16-19: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200B, 747-300, and 747-400 series airplanes. This AD requires doing repetitive detailed inspections for cracking of the aft tension tie channels from body station (BS) 1120 to BS 1220 and from BS 880 to BS 1100, and corrective actions if necessary. This AD results from cracks found in the aft tension tie channels at four station locations, on a Model 747-200B series airplane that had been modified to a special freighter. We are issuing this AD to detect and correct cracking of the aft tension tie channels; failure of more than one tension tie could result in rapid depressurization of the airplane.
2022-11-16: The FAA is adopting a new airworthiness directive (AD) for all British Aerospace (Operations) Limited Model Jetstream Model 3101 airplanes and British Aerospace Regional Aircraft Model Jetstream Model 3201 airplanes. This AD was prompted by 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 identifies the unsafe condition as stress corrosion cracking of the primary flight control cable terminals. This AD requires repetitively inspecting the turnbuckle type control cable terminals in the rudder and elevator primary flight control circuits for corrosion, pitting, and cracking and, depending on the inspection results, replacing an affected cable assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2007-16-13: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 757-200, -200PF, and -200CB series airplanes. The existing AD currently requires repetitive inspections of the shim installation between the vertical flange and bulkhead, and repair if necessary. This new AD adds, for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary. This AD results from reports of cracking in the pylon under bolts that appear to be undamaged during the existing AD inspections. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut- to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
2022-11-06: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109S and AW109SP helicopters. This AD was prompted by a report of a protective sheath, installed around a fixed flight control rod, which should have been removed during assembly. This AD requires borescope inspecting certain parts, and removing any foreign object if detected, 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.
2007-16-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-100 and A320-200 series airplanes. This AD requires repetitive inspections of the wing-tank fuel pumps, canisters, and wing fuel tanks for detached identification labels, and corrective action if necessary. This AD also requires modification of the fuel strainers at the fuel pump and suction bypass intakes, which would end the repetitive inspections. This AD results from several incidents of detached plastic identification labels found floating in the wing fuel tanks. We are issuing this AD to prevent plastic identification labels being ingested into the fuel pumps and consequently entering the engine fuel feed system, which could result in an engine shutdown.
87-10-07: 87-10-07 ALEXANDER SCHLEICHER: Amendment 39-5603. Applies to Model ASK 21 gliders serial numbers 21001 through 21312 certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent the failure of the rudder pedal support fitting P/N 99.000.2173 which could result in the glider becoming uncontrollable, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD unless compliance with paragraph (c) has been accomplished, visually inspect the rudder pedal support fitting P/N 99.000.2173 using a 10 power or greater magnifying glass, for cracks. (b) If a cracked fitting is found during the inspection required by paragraph (a) of this AD, before further flight, replace the rudder pedal support fitting with a serviceable fitting, P/N 99.000.2174, in accordance with the action instructions of Alexander Schleicher ASK 21 Technical Note No. 19, dated October 22, 1986. (c) Prior to July 15, 1987, replace any rudder pedal support fitting not replaced in accordance with paragraph (b) of this AD, with a serviceable fitting, P/N 99.000.2174, in accordance with Alexander Schleicher ASK 21 Technical Note No. 19, dated October 22, 1986. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o America Embassy, 15 Rue de la Loi B-1040 Brussels, Belgium; telephone number 513.38.30 ext. 2710 or the Manager, New York Aircraft Certification Office, Federal Aviation Administration, New England Region, Aircraft Certification Division, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone number 516-791-6680. Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office or Manager, New York Aircraft Certification Office may adjust the compliance time specified in this AD. Alexander Schleicher ASK 21 Technical Note No. 19, dated October 22, 1986, identified and described in this document is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain a copy upon request to Eastern Sailplanes, Heath Stage Route, Shelburne Falls, Massachusetts 01370. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment 39-5603 becomes effective May 13, 1987.
2022-11-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 series airplanes, Model A300 B4-600, B4- 600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports of cracking in the main landing gear (MLG) support rib 5 lower flange. This AD requires a one-time detailed inspection (DET) of the affected area, and applicable 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.
2007-16-03: We are adopting a new airworthiness directive (AD) to supersede AD 98-19-15 R1 and AD 2000-03-17, which apply to M7 Aerospace LP SA226 and SA227 series airplanes equipped with certain pitch trim actuators. AD 98-19-15 R1 currently requires you to incorporate changes into the Limitations Section of the FAA-approved airplane flight manual (AFM) if certain part number (P/N) pitch trim actuators are installed. AD 2000-03-17 requires repetitive inspections and repetitive replacements of the pitch trim actuator. The repetitive inspection and repetitive replacement times vary depending on the combination of airplane model and pitch trim actuator P/N installed. Since we issued AD 98-19-15 R1 and AD 2000-03-17, we have determined that reliance on critical repetitive inspections on aging commuter-class airplanes carries an unnecessary safety risk when a design change exists that could eliminate or, in certain instances, reduce the number of those critical inspections. Consequently, thisAD retains all of the actions of the previously referenced ADs, places life limits on certain P/N pitch trim actuators, and requires the replacement of certain P/N pitch trim actuators with one of an improved design. Once installed, the improved design pitch trim actuator will terminate the AFM limitations in this AD and reduce the repetitive inspection and repetitive replacement requirements. We are issuing this AD to detect excessive freeplay or rod slippage in the pitch trim actuator, which, if not detected and corrected, could result in pitch trim actuator failure. We are also issuing this AD to lessen the severity of pitch upset if a pitch trim actuator mechanical failure occurs. These conditions could lead to possible loss of control. DATES: This AD becomes effective on September 7, 2007. As of April 10, 2000 (65 FR 8037, February 17, 2000), the Director of the Federal Register approved the incorporation by reference of the following Fairchild Aircraft service information listed in this AD: Fairchild Aircraft SA226 Series Service letter (SL) 226- SL-005, Revised: August 3, 1999; Fairchild Aircraft SA227 Series SL 227-SL-011, Revised August 3, 1999; Fairchild Aircraft SA227 Series SL CC7-SL-028, Issued: August 12, 1999; Fairchild Aircraft SA226 Series SL 226-SL-014, Revised: February 1, 1999; Fairchild Aircraft SA227 Series SL 227-SL-031, Revised: February 1, 1999; and Fairchild Aircraft SA227 Series SL CC7-SL-021, Revised: February 1, 1999.
2022-09-10: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 model turbofan engines. This AD was prompted by findings during engine overhaul of corrosion on the low-pressure compressor (LPC) front case assembly. This AD requires inspection of the LPC front case assembly and, depending on the result of the inspection, accomplishment of the applicable corrective action(s), 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.
2007-15-08: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited Model ATP airplanes. The existing AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures; to incorporate new inspections to detect fatigue cracking of certain significant structural items (SSIs); and to revise life limits for certain equipment and various components. This new AD requires revising the ALS of the ICA to include revised requirements. This AD results from the determination that additional and revised inspections of the fuselage are needed. We are issuing this AD to detect and correct fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane.
2022-06-06: The FAA is superseding Airworthiness Directive (AD) 2017-14- 13, which applied to certain The Boeing Company Model 737-600, -700, - 700C, -800, -900, and -900ER series airplanes. AD 2017-14-13 required a torque check of the screws in the cover assembly of the heel rest for both the captain's and the first officer's rudder pedals, and corrective action if necessary. This AD was prompted by a report of an aborted takeoff because the rudder pedals were not operating correctly, and subsequent reports of loose rudder pedal cover fasteners on airplanes on which the actions required by AD 2017-14-13 were done and on additional airplanes that were not included in the applicability of AD 2017-14-13. This AD requires modifying the rudder pedal cover and shroud assemblies, and applies to all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes and Model 737-8 and 737-9 airplanes. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2007-14-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes. This AD requires inspecting to identify the part number and serial number of the selector valves of the nose landing gear (NLG) and the nose gear door, and doing related investigative and corrective actions if necessary. This AD results from reports of uncommanded partial retractions of the NLG. We are issuing this AD to prevent internal leakage of the selector valve, which, under certain conditions, could result in an uncommanded retraction of the NLG with consequent damage to the airplane and possible serious injury to ground personnel.
2022-10-04: The FAA is adopting a new airworthiness directive (AD) for certain Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. This AD was prompted by a manufacturer investigation that revealed certain stages 7-9 compressor rotor spools were manufactured from a billet of material suspected of having foreign material embedded. This AD requires the replacement of the affected stages 7-9 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products.