Results
95-18-14: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6 series turbofan engines. This action requires a more detailed fluorescent penetrant inspection process for GE CF6 series high pressure compressor rotor (HPCR) stage 3-9 spools. This amendment is prompted by an uncontained failure of the HPCR stage 3-9 spool attributed to a material defect located in the hub to web transition area of the stage 6 disk. The actions specified in this AD are intended to prevent an uncontained HPCR engine failure, which can result in damage to the aircraft.
2008-13-10: 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: Investigation following incidents on the production line has shown that power feeders inside the Secondary Power Distribution Boxes (SPDB) may be damaged because of interference with other internal parts. This condition, if not corrected, may lead to losing essential feeders. The resulting power shortage may reduce aircraft operability and affect flight safety margins. * * * * * Damaged secondary power distribution boxes could lead to loss of electrical power resulting in depressurization with loss of passenger oxygen supply and uncommanded slat retraction. This AD requires actions that are intended to address the unsafe condition described in theMCAI.
95-17-08: This amendment adopts a new airworthiness directive (AD) that applies to Stemme GmbH (Stemme) S10 gliders. This action requires modifying the rudder control cable system. Rupture of a turnbuckle eye bolt in the rudder control cable system on one of the affected gliders prompted this action. The actions specified by this AD are intended to prevent rudder control cable system failure caused by rupture of the turnbuckle eye bolt, which, if not detected and corrected, could result in loss of rudder control and eventual loss of control of the glider.
2001-19-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) Dart 525, 525F, 528, 528D, 529, 529D, 530, 532, 535, 542, and 552 series turboprop engines. This action requires the removal of certain part number (P/N) high pressure turbine (HPT) discs and replacement with serviceable discs. This \namendment is prompted by three reports of uncontained HPT disc failures and the manufacturer's investigation into disc failure. The actions specified in this AD are intended to prevent HPT disc failure, which could result in an uncontained engine failure and damage to the airplane.
95-18-01: This amendment adopts a new airworthiness directive (AD) that applies to Scheibe Flugzeugbau GmbH SF34 and SF34B gliders. This action requires adding armature (supportive covering) to both wings, modifying the root rib of the left wing and incorporating changes and operating limitations to the flight manual. Failure of the left wing root rib on one of the affected gliders while in flight prompted this action. The actions specified by this AD are intended to prevent fatigue failure of the wing, which could result in loss of control of the glider.
2008-12-16: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LP SA226 and SA227 series airplanes. This AD requires you to inspect electrical wires/components, hydraulic and bleed air tube assemblies at left-hand (LH) and right-hand (RH) inboard wing leading edge/battery box areas, LH/RH wing stations 51.167 to 81.174, and at all feed-through locations into the LH/RH inboard keelson. If chafing/ arcing is found, this AD requires you to reposition, repair, and/or replace all chafed electrical wires, components, and hydraulic and bleed air tube assemblies, as required. This AD also requires you to reposition the battery lead cables, cover four-gauge wires leaving the battery box with firesleeving and secure with clamps, and protect the battery power cable. This AD results from five reports of chafing between the bleed air tube and the electrical starter cables with one incident resulting in a fire. We are issuing this AD to detect and correct chafing/arcing of electrical wires, components, and bleed air lines. This condition could result in arcing of the exposed wires and burn a hole in the bleed air line or the nearby hydraulic line, and lead to a possible hydraulic fluid leak and fire in the engine nacelle compartment.
2001-19-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) models RB211-535C-37, RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, with radial drive steady bearing, part number (P/N) LK76084. This action requires the replacement of certain radial drive steady bearings, installed in the high speed gearbox drive. This amendment is prompted by five reports of radial drive steady bearing failures. The actions specified in this AD are intended to reduce the risk of engine in-flight shutdown, due to failure at low life of radial drive steady bearings.
2020-20-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B2 helicopters. This AD requires performing a test of the main rotor RPM (NR) indicator, and depending on the results, altering the wiring. This AD was prompted by reports of some NR indicators displaying incorrect information. The actions of this AD are intended to address an unsafe condition on these products.
95-17-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Jetstream Model ATP airplanes, that currently requires revising the Airplane Flight Manual (AFM) to prohibit flight in freezing precipitation conditions. This amendment adds a requirement to install modifications of the engine air intake system. This amendment is prompted by the development of modifications of the engine air intake system intended to permit operation of these airplanes in freezing precipitation conditions. The actions specified by this AD are intended to prevent engine power rollback in flight during freezing precipitation conditions.
2021-17-13: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report of a damaged wheel braking system pneumatic line fitting installed on the left-hand (LH) main landing gear (MLG) leg. This AD requires modifying the LH MLG leg. The FAA is issuing this AD to address the unsafe condition on these products.
2008-12-17: The FAA is superseding an existing airworthiness directive (AD), which applies to all Lockheed Model L-1011 series airplanes. That AD currently requires an inspection of the fuel level control switch, the fuel level control switch wiring harness, and the wiring harness conduit for damage, wear or chafing, broken or missing O-rings, or indications of electrical arcing. That AD also requires replacement of a certain conduit in the fuel level control switch wiring harness, installation of electrical sleeving over the fuel level control switch wiring harness, and installation of the fuel level control switch that has been so modified. This new AD requires an inspection of the fuel level control switch, wiring harnesses, and harness conduit for any visible damage, wear or chafing, broken or missing O-rings, or indications of electrical arcing; an inspection to determine the part number of the wiring harness conduit; and corrective actions if necessary. This new AD also requires replacing certain sleeving with new, improved sleeving over the wiring harness of the fuel level control switch. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent chafing of the fuel level control switch wiring harness, which could cause arcing and result in a fire in the fuel tank. DATES: This AD becomes effective July 23, 2008. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in the AD as of July 23, 2008. On June 1, 2001 (66 FR 21072, April 27, 2001), the Director of the Federal Register approved the incorporation by reference of a certain service bulletin.
2020-18-13: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by the FAA's analysis of the Model 737 fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. This AD also provides alternative actions for cargo airplanes. \n\n((Page 60049)) \n\nThe FAA is issuing this AD to address the unsafe condition on these products.
95-17-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 707 and 720 series airplanes, that currently requires repetitive visual and dye penetrant inspections to detect cracks in areas of the upper forward skin panels of the wing center section, and repair, if necessary. It also provides an optional terminating modification for the repetitive inspections. This amendment requires repetitive visual and eddy current inspections to detect cracks in areas of the upper forward skin panels of the wing center section, and repair, if necessary. This amendment is prompted by reports indicating that the inspections required by the existing AD are not effective in detecting fatigue cracks in a timely manner. The actions specified by this AD are intended to prevent fatigue cracking and subsequent failure of the upper forward skin panels of the wing center section.
95-12-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to determine the torque value of all wing slat track stop pins, and correction of discrepancies. This amendment is prompted by a report of a fuel leak that was caused by an incorrectly torqued slat track stop pin that punctured the slat canister. The actions specified in this AD are intended to prevent such fuel leakage conditions, which could result in inadequate fuel for completing a flight and could pose a fire hazard.
2008-11-11: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Cracks have been reported in the front spar center web of the tailplane at the pick-up bracket and at lightening holes. If not detected early and repaired, these cracks may lead to failure of the tailplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-06-02: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 series airplanes. This AD requires modifying the wiring of the test ground signal for the master dim and test system circuit in the flight compartment. This AD is prompted by a report that the master dim and test system circuit does not have wiring separation of the test ground signal for redundant equipment in the flight compartment. We are issuing this AD to prevent a single fault failure during flight, which could result in test patterns instead of the selected radio frequencies showing on the communications panel. These conditions could adversely affect voice and transponder communication capability between the flightcrew and air traffic control, which could result in increased pilot workload.
95-16-07: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D series turbofan engines, that currently requires initial and repetitive inspections of 9th through 12th stage high pressure compressor (HPC) disks at the tierod holes. This amendment eliminates an optional on-wing ultrasonic inspection of the 10th stage high pressure compressor (HPC) disk. This amendment is prompted by a report of an uncontained failure of a 10th stage HPC disk that was previously inspected using the on-wing ultrasonic inspection method. The actions specified by this AD are intended to prevent uncontained fractures of 9th through 12th stage HPC disks and engine failure.
2008-12-18: 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: During a flight test performed on an EASy aircraft, subsequently to an air data probe failure, the crew realized that the Flight path vectors and the Vertical speeds that were displayed on pilot's and co-pilot's PDU (primary display unit) were identically wrong. A review of the EASy architecture reveals that * * * One single ADS (air data system) unflagged air data error may lead to the computation and display on both pilot's and co-pilot's display units of unnoticed and misleading flight information. At take-off or during go-around this situation might considerably reduce flight safety. We are issuing this AD to require actions to correctthe unsafe condition on these products.
2001-19-03: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) Model AE 3007A and AE 3007C turbofan engines with a certain part number high pressure turbine (HPT) 1st to 2nd stage turbine spacer installed. This amendment requires removal and replacement of that HPT 1st to 2nd stage turbine spacer before it reaches its new reduced engine cycle life limit.This amendment is prompted by the results of a detailed component analysis that indicates that the HPT 1st to 2nd stage turbine spacer stresses are higher than predicted. The actions specified by this AD are intended to prevent HPT 1st to 2nd stage turbine spacer failure which could result in an uncontained engine failure and damage to the airplane.
2020-19-11: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. (Leonardo) Model A119 and AW119 MKII helicopters. This AD requires repetitive borescope inspections of the tail rotor gearbox (TGB) and depending on the inspection results, removing the TGB from service. \n\n((Page 59405)) \n\nThis AD was prompted by reports of corrosion on the internal surface of the 90-degree TGB output shaft. The actions of this AD are intended to address an unsafe condition on these products.
95-17-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011 series airplanes, that currently requires a visual inspection to detect cracks of the forward or aft side of the aft pressure bulkhead, and repair, if necessary. This amendment requires various inspections to detect cracks or other discrepancies of the aft pressure bulkhead, and repair, if necessary. This amendment is prompted by a recent report of in-flight loss of cabin pressure on a Model L-1011-385 series airplane due to a rupture of the aft pressure bulkhead as a result of fatigue-related cracking. The actions specified in this AD are intended to prevent such fatigue cracking, which could result in rupture of the aft pressure bulkhead and subsequent depressurization of the cabin.
2008-12-04: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires various repetitive inspections to detect cracks along the chemically milled steps of the fuselage skin or missing or loose fasteners in the area of the preventative modification or repairs, replacement of the time-limited repair with the permanent repair if applicable, and applicable corrective actions if necessary, which would end certain repetitive inspections. This AD results from a fatigue test that revealed numerous cracks in the upper skin panel at the chemically milled step above the lap joint. We are issuing this AD to detect and correct such fatigue-related cracks, which could result in the crack tips continuing to turn and grow to the point where the skin bay flaps open, causing decompression of the airplane.
2001-13-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-13-51, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 206L-4, 407, and 427 helicopters by individual letters. This AD requires visually inspecting certain driveshafts for a crack, a loose bolt or nut, or red powder residue. If a crack, a loose bolt or nut, or red powder residue is found, replacing the driveshaft before further flight and notifying the FAA within 10 days is also required. This amendment is prompted by a driveshaft failure on a BHTC Model 407 helicopter that resulted in an engine shutdown and an emergency landing. Failure of the driveshaft was due to cracking of the flexframe on the forward end of the driveshaft. In addition, three other incidents of a cracked flexframe on the forward end of the driveshaft on other Model 407 helicopters have been reported. The actions specified by this AD are intended to prevent failure of a driveshaft, loss of drive to the main rotor system, and a subsequent emergency forced landing.
2020-19-07: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. Model AW169 helicopters. This AD requires modifying the weight on wheels (WoW) support installation on the main landing gear (MLG). This AD was prompted by a report that an inappropriately tightened WoW support could result in a rotation of the support and improper WoW switch performance. The actions of this AD are intended to address an unsafe condition on these products.
95-16-08: 95-16-08 AlliedSignal, Inc.: Amendment 39-9328. Docket 94-ANE-10. Applicability: AlliedSignal, Inc. (formerly Allied-Signal, Inc., Garrett Engine Division, Garrett Turbine Engine Company, and AiResearch Manufacturing Co. of Arizona), TPE331-25, -43, -1, -2, -3, -5, -6, -8, -10, -11, and -12 series, and -55B and -61A Model turboprop engines; and TSE331-3U Model turboshaft engines. These engines are installed on but not limited to Mitsubishi MU-2B series (MU-2 series); Construcciones Aeronauticas, S.A. (CASA) C-212 series; Jetstream 3101 and 3201 series; Fairchild SA226 and SA227 series; Prop-Jets, Inc. Model 400; Cessna Model 441; Twin Commander Aircraft Corp. 680, 690, and 695 series, and Model 681; Rockwell Commander or Ayres Corp. S-2R series; Short Brothers and Harland, Ltd. SC7; Dornier 228 Series; Beech Aircraft Corp. 18 and 45 series and Models JRB-6, 3N, 3NM, 3TM, and B100; Pilatus PC-6 series; DeHavilland DH 104 Dove series; Grumman Model TS-2A; Grumman American ModelG-164C; and Schweizer Aircraft Corp. Model G-164 series aircraft. NOTE: This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent uncontained failure of turbine rotors, fire, or loss of aircraft control, accomplish the following: (a) Within 400 cycles in service (CIS) after the effective date of this AD, review engine life limited part logs, engine repair and maintenance records, maintenance purchase receipts, and aircraft maintenance records (collectively referred to as "records") to identify any engine repair, assembly, or modification that was performed by, or any life limited turbine components received from Fliteline Maintenance, located in Wharton, Texas, domestic repair station certificate number GR2R856K; or Mr. Eugene E. Shanks, mechanic certificate number 1914482; or Mr. Carl Ramirez, mechanic certificate number 466432551 (collectively referred to as "Fliteline"). (b) Within 400 CIS after the effective date of this AD, for engines or components identified in accordance with paragraph (a) of this AD, accomplish the following: (1) If records or other pertinent information indicate that the engine was disassembled beyond aft turbine mainshaft nut removal from the tie bolt by Fliteline, verify life limited turbine components and take appropriate action by the following methods: (i) Remove, disassemble the engine, compare, and match each component's part number (P/N) and serial number (S/N) against that engine's issued life limited part logs. Engine hot section inspection or overhaul normally requires comparing and matching of turbine components with the life limited part logs. An engine hot section inspection or overhaul, subsequent to maintenance by Fliteline, and performed by the engine manufacturer, an FAA certified repair station, or an FAA certified mechanic, other than Fliteline, constitutes compliance with paragraph (b)(1)(i) of this AD. (ii) Validate all Fliteline life limited part log entries by utilizing the component's hourly and cyclic life immediately before the Fliteline entry, as determined byrecords of the engine manufacturer or FAA certified repair stations other than Fliteline. A life limited part log entry is defined as a removal or installation record. Photocopied life limited part logs may be used provided component history can be established. NOTE: Engine manufacturer record and service information referred to in the AD can be attained by calling AlliedSignal Engines Customer Information Center, telephone (800) 338-3378 or (602) 231-5287. (iii) If the P/N, S/N, hourly and cyclic lives or the life limited part log of each life limited turbine component do not match or can not be validated, remove the component from service prior to further flight and replace with a serviceable component. (2) Verify that any requirements of AD's signed off by Fliteline were actually accomplished by visual examination or reinspection of the affected components in accordance with the applicable AD. A complete engine overhaul or other maintenance necessary to accomplishapplicable AD requirements, subsequent to maintenance by Fliteline, and performed by the engine manufacturer, an FAA certified repair station, or an FAA certified mechanic, other than Fliteline, constitutes compliance with paragraph (b)(2) of this AD. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Los Angeles Aircraft Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (e) This amendment becomes effective on September 5, 1995.