Results
2012-14-08: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the main gearbox (MGB) for a crack. This AD is prompted by a crack in the cored passage of the MGB housing, which may be indicated by oil on the housing. These actions are intended to detect a crack in the MGB housing, which could result in loss of oil, failure of the MGB, and subsequent loss of control of the helicopter.
2022-12-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of multiple in-service events where, following a STAB TRIM FAULT advisory message and auto-pilot disconnect, flightcrew commands for a nose-up trim resulted in nose-down trim movement of the horizontal stabilizer instead. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with instructions for an expanded pre-flight check of the pitch trim, trim malfunction procedures, and revised ''AP STAB TRIM FAIL'' caution and ''STAB TRIM FAULT'' advisory procedures. The FAA is issuing this AD to address the unsafe condition on these products.
71-25-08: 71-25-08 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1356. Applies to Fairchild Hiller UH-12 helicopters certificated in all categories. Compliance required as indicated. Following an immediate visual inspection and within 10 hours time in service after the effective date of this airworthiness directive inspect main rotor blade P/N 53100 for cracks, using dye penetrant. Any blades found defective are to be removed from service prior to further flight and S/Ns reported to Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, JFK International Airport, Jamaica, New York 11430. Approval of this reporting procedure has been obtained from the Bureau of Budget in accordance with Federal Reports Act. Reporting approved by Bureau of Budget under BOB Number 04-R0174. This amendment is effective December 14, 1971 and was effective upon receipt by owners and operators of the letter dated November 9, 1971 which contained this amendment.
99-18-23: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas MD-90-30 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness (MD-90-30 Airworthiness Limitations Instructions (ALI)) to incorporate certain replacement times for safe-life limited parts. This amendment is prompted by analysis of data that identified reduced replacement times for certain safe-life limited parts. The actions specified by this AD are intended to prevent fatigue cracking of various safe-life limited parts; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2013-05-16: We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369D, 369E, 369F, and 369FF helicopters with certain serial-numbered tailboom assemblies. This AD requires measuring the distance between aft longeron rivets and the outboard edge of frame rings. If the distance is too short to ensure a safe flight, the AD requires installing a doubler. This AD was prompted by the discovery of short-edge margin conditions on two tailboom assemblies. The actions are intended to detect a short-edge margin condition, prevent failure of the tailboom and loss of control of the helicopter.
2012-12-06: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by a design review which revealed the absence of electrical insulation material between a wing or integral center wing tank (ICWT) fuel quantity indication system (FQIS) probe and the bottom of the tank structure. This AD requires for all airplanes, applying sealant below the FQIS probes in the wing tanks; and for certain airplanes, applying sealant below the FQIS probes in the ICWT. This AD also requires revising the aircraft maintenance program by revising the fuel airworthiness limitations and incorporating critical design configuration control limitations (CDCCLs). We are issuing this AD to prevent an ignition source in the tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
2022-11-11: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited (type certificate previously held by Bombardier, Inc.) Model DHC-8-401 and -402 airplanes. This AD was prompted by reports of a certain bolt at the pivot pin link being found missing or having stress corrosion cracking. This AD requires a modification to the nose landing gear (NLG) shock strut assembly. The FAA is issuing this AD to address the unsafe condition on these products.
96-18-13: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 series turbofan engines, that requires removing certain fan rotor disks from service in accordance with a drawdown schedule, and would establish new fan rotor disk life limits. This amendment is prompted after additional analyses revealed that stress levels in the fan rotor disk dovetail slots for the applicable engine models are higher than initially calculated. The actions specified by this AD are intended to prevent uncontained failure of the fan rotor disk due to fatigue cracking in the dovetail slots, which can result in inflight engine shutdowns, severe secondary damage, and fan rotor assembly separation from the engine.
99-18-16: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-400, 757-200, 767-200, and 767-300 series airplanes. This action requires repetitive checks to detect certain failures in the warning electronic unit (WEU) or modular avionic warning electronic assembly (MAWEA); repetitive tests to detect any failure of tactile, visual, or aural alert generated by the WEU or MAWEA; and corrective action, if necessary. This AD also provides for an optional terminating action for the repetitive checks and tests. This amendment is prompted by a report of a MAWEA power supply failure due to inadequate over-voltage protection. The actions specified in this AD are intended to detect and correct such a failure, which could result in loss of visual, aural, and tactile alerts to the flightcrew. Absence of such alerts could result in the flightcrew being unaware that an immediate or appropriate action should be taken in the event of an unsafecondition.
2012-08-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD was prompted by a report of an electrical arc and hydraulic haze in the wheel bay of the left-hand main landing gear (MLG) possibly resulting from chafing between the hydraulic high pressure hose and electrical wiring of the green electrical motor pump (EMP). This AD requires temporarily prohibiting in-flight use of the green EMPs; temporarily revising the airplane flight manual (AFM) limitations section; temporarily installing a placard in the cockpit overhead panel; doing a one-time general visual inspection for correct condition and installation of hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices; and corrective action if necessary. We are issuing this AD to detect and correct chafing of hydraulic pressure hoses and electrical wiring of the green EMPs, which in combination with a system failure, could cause an uncontrolled and undetected fire in the MLG bay.
68-03-01: 68-03-01 FAIRCHILD-HILLER: Amdt. 39-547 as amended by Amendment 39-987. Applies to FH-227 Type Aircraft. Compliance required within the next 5 hours' time in service after the effective date of this AD unless already accomplished within the last 20 hours' time in service and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. The repetitive inspections also apply to repaired and replacement parts. In view of flutter of the elevator trim tab, accomplish the following: (a) Inspect the elevator trim tab for trailing edge free play not to exceed 0.100 inch max. travel. Compliance with this limit must be met prior to further flight. (b) Visually inspect all elevator tab hinge bearings for damage. Replace damaged bearings, prior to further flight, with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (c) Visually inspectthe entire elevator tab structure for loose rivets, cracks, or any structural deformation. Prior to further flight, remove and replace loose rivets, replace deformed trim tabs, and repair or replace cracked trim tabs with a part of the same part number that has been inspected in accordance with this directive prior to installation or with an equivalent part or repair approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Inspect the elevator trim tab clevis bolts, elevator trim tab horn, elevator trim tab actuator, rod end and rod assembly rivets, for looseness and damage. Prior to further flight, loose items must be properly secured and damaged parts replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (e) Visually inspect the 3 elevator trim tab hinges for elongated holes in the clevis holes of the aluminum blocks located behind the3 elevator trim tab hinges. Replace blocks containing elongated holes prior to further flight with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA approved equivalent part. (f) Inspect the elevator trim tab spar area around the 3 hinges for cracks. If cracks are found, prior to further flight, the cracked parts must be repaired in accordance with an FAA approved repair, or replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation, or with an FAA-approved equivalent part. (g) Cut a one-inch hole in the lower tab skin in line chordwise with the existing access hole in the lower tab skin at tab station 14.662, and located spanwise 11.4 inches outboard of the most inboard tab rib. Fabricate a circular doubler 2 inch O.D. by 1 inch I.D. from 0.025 inch thick 2024T3 alclad material specification QQ-A-250/5. Finish with alodine or anodizeand apply zinc chromate primer to the faying surface only. Install doubler over hole and secure the doubler with six equally spaced MS20600AD4 rivets or use an equivalent method for inspection approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (1) Inspect the tab ribs adjacent to the 3 tab hinges and also the tab ribs supporting the tab horn for cracks paying particular attention to rib flange radii using a borescope or light and mirror through the access holes or use an FAA-approved equivalent inspection method. The x-ray inspection procedure specified in Fairchild Hiller Alert Service Bulletin No. 27-17A (FH-227) Revision 1 dated January 5, 1968, is considered equivalent to the borescope or light and mirror inspection. If cracks are found, prior to further flight, the cracked parts must be repaired in accordance with an FAA approved repair, or replaced with a part of the same part number that has been inspected in accordance with this directive prior to installation or with an FAA-approved equivalent part. (2) After each inspection, cover the access holes with permacelle tape or equivalent. (h) For aircraft with a modified elevator trim tab approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, comply with paragraphs (a), (b), (c), and (d), prior to accumulating 600 hours' time in service on the modified tab, and thereafter at intervals not to exceed 600 hours' time from the last inspection. If the inspections of (a), (b), (c), or (d), reveal a discrepancy, then the requirements of paragraphs (e), (f), and (g)(1) and (g) (2), must be complied with prior to further flight. (i) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent repairs and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (j) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-547 is effective February 2, 1968, for all persons except those to whom it was made effective immediately by telegram dated January 9, 1968. This Amendment (39-987) is effective May 27, 1970.
2022-11-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK117 A-1, MBB- BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, MBB-BK117 B-2, MBB-BK117 C-1, MBB-BK117 C-2, and MBB-BK117 D-2 helicopters. This AD was prompted by the FAA's determination that aging of the elastomeric material of certain tension torsion straps (TT-Straps), during the period since manufacturing date up to first flight on a helicopter, may affect its structural characteristics. This AD requires the replacement of certain TT-Straps, implementation of storage life limits for TT-Straps, a prohibition on installing certain TT-Straps, and conditions for installation of certain other TT-Straps, 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.
68-10-05: 68-10-05\tBOEING: Amendment 39-622. Applies to Model 727 Series airplanes.\n \n\t(a)\tWithin 1600 hours time in service after the effective date of this AD unless already accomplished, modify the thrust reverser deflector doors in accordance with Boeing Service Bulletin No. 78-51, Revision 1, dated April 2, 1968, (or later FAA approved revision). Within 800 hours time in service after the effective date of this AD unless already accomplished, modify the thrust reverser deflector doors in accordance with Boeing Service Letter 6-7132-3375, dated March 1, 1967, (or later revision). \n\n\t(b)\tWithin 3,500 hours time in service after accomplishing the modifications required in (a), and thereafter at intervals not to exceed 3,500 hours time in service, replace bolt P/N BAC- B30EK8-48 or P/N BAC-B30EK8-48C. \n\n\tThis amendment effective May 14, 1968. \n\n\tRevised July 20, 1969.
59-12-08: 59-12-08 de HAVILLAND: Applies to All Model 104 "Dove" Aircraft. Compliance required not later than July 20, 1959. A case has been reported where a powerplant fire extinguisher spray pipe P/N 4M-99ND had been installed without having the spray holes drilled in it. (1) Spray pipe P/N 4M99ND must be inspected to ascertain whether it has the spray holes drilled in it as follows: (a) Open the engine cowlings and inspect the spray pipe running from the distributor unit round the blower casing. (b) If the pipe has not had the spray holes drilled in it remove the pipe and replace with a serviceable item; or (c) The unserviceable pipe may be rendered serviceable by working to the details shown in de Havilland Technical News Sheet CT (104) No. 163. (2) The above inspection, and replacement or rework action where necessary, must be accomplished on all spare powerplants and spares stock before installation in aircraft. The British Air RegistrationBoard considers this mandatory. (de Havilland TNS CT (104) No. 163 covers the same subject.)
2022-11-02: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) LEAP-1B21, LEAP-1B23, LEAP-1B25, LEAP- 1B27, LEAP-1B28, LEAP-1B28B1, LEAP-1B28B2, LEAP-1B28B2C, LEAP-1B28B3, LEAP-1B28BBJ1, and LEAP-1B28BBJ2 model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, high pressure turbine (HPT) rotor mid seals, HPT rotor stage 2 disks, low pressure turbine (LPT) stage 2 disks, and LPT stage 3 disks. This AD requires revising the airworthiness limitations section (ALS) of the applicable CFM LEAP-1B Engine Shop Manual (ESM), and the operator's existing approved maintenance or inspection program, as applicable, to incorporate reduced life limits for these parts. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-03R1: The FAA is revising an existing airworthiness directive (AD) for General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines with certain serial numbers (SNs) of stage 5 low pressure turbine (LPT) disks, part number (P/N) 6078T92P01, and/or certain SNs of stage 6 LPT disks, P/N 6078T89P01. That AD currently requires initial and repetitive visual and eddy current inspections of those disks. That AD also allows as optional terminating action to the repetitive inspections, replacement of those SN disks. Also, that AD requires replacement of certain stage 5 and stage 6 LPT disks. This ad requires the same actions. This AD results from the discovery that an incorrect part number for stage 6 LPT disks was published in the existing AD and from the need to allow credit for actions completed per previous releases of Alert Service Bulletin CF34-AL S/B 72-A0173. We are issuing this AD to prevent LCF failure of stage 5 LPT disks and stage 6 LPT disks, which could lead to uncontained engine failure.
73-15-02: 73-15-02 PRATT & WHITNEY: Amdt. 39-1687 as amended by Amendment 39-1712. Applies to all JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3 and JT3D-3B model engines containing turbine nozzle case Part Numbers 399065, 496859, 570618, 626669, 669045, 669047, 694937, 694938, 390197, 694935 and 691326 incorporating vented 2nd stage outer airseals. Compliance required as follows: To preclude possible turbine blade or disc failures resulting from turbine case lug failures, inspect the turbine nozzle case for missing lugs by performing Ultrasonic, Isotope or Visual inspection at the time intervals specified below. First inspection, 1,000 hours time in service after the effective date of this AD unless already accomplished. (a) If there are no missing lugs, repeat the inspection every 1,000 hours time in service thereafter. (b) If one lug is found missing, repeat the inspection every 100 hours time in service. (c) If two or three lugs are found missing, remove the engine within the next 50 hours time in service. (d) If four or more lugs are missing, remove from service immediately. Turbine cases may be repaired in accordance with the procedures outlined in the Overhaul Manual, Section 72-51-2, or replaced. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time. NOTE: Pratt & Whitney Service Bulletin 3993, or later FAA approved revisions pertain to this same subject. Amendment 39-1687 became effective August 18, 1973. This Amendment 39-1712 becomes effective September 14, 1973.
2004-15-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with low pressure (LP) compressor fan blades part number (P/N) FW18548, installed. This AD requires LP compressor fan blade replacement with new or previously reworked blades, or rework of the existing LP compressor fan blades. This AD results from a number of new production LP compressor fan blades found with surfaces formed outside of design intent. Findings included sharp edges, burrs, and damage present in the area at the top of the shear key slots. We are issuing this AD to prevent possible multiple uncontained LP compressor fan blade failure, due to cracking in the blade root caused by increased stresses in the shear key slots.
47-43-11: 47-43-11 LOCKHEED: (Was Mandatory Note 22 of AD-723-3.) Applies to All Model 18 Serial Numbers. Compliance required prior to next periodic inspection. Remove bolts connecting the elevator push-pull rod to the elevator horn and bellcrank and ascertain that the shank diameter falls within the limits of 0.248 to 0.250. Bolts outside these limits should be replaced with NAS 54-12 bolts. In view of the similarity of the Lockheed bolts with standard AN bolt, it is suggested that they be replaced with close tolerance bolts, NAS 54-12 and the push-pull rod. P/N 72149 placarded "Use NAS 54-12 bolt".
2022-11-09: The FAA is adopting a new airworthiness directive (AD) for all Viking Air Limited (Viking) (type certificate previously held by Bombardier Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC- 6-200, DHC-6-300, and DHC-6-400 airplanes. 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 identifies the unsafe condition as cracks and corrosion damage to the aileron internal structure. This AD requires visually inspecting the entire aileron internal structure, correcting any damage found, and reporting the inspection results to Viking. The FAA is issuing this AD to address the unsafe condition on these products.
2013-05-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of stiff operation of the elevator pitch control system and jammed elevator controls. This AD requires replacing pressure seal assemblies; doing repetitive inspections for dirt, loose particles, or blockage of the flanged tube and drain hole for the pressure seals, and corrective action if necessary; replacing the aft air-intake duct assembly with a new or modified assembly and installing a dripshield; and installing gutters on the horizontal stabilizer center section and modifying the side brace fittings. We are issuing this AD to prevent moisture from collecting and freezing on the elevator control system components, which could limit the ability of the flightcrew to make elevator control inputs and result in reduced controllability of the airplane.
2004-16-02: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires installing a new warning annunciator light on the central warning panel and revising the Normal Procedures Section of the Aircraft Flight Manual to provide the flightcrew with procedures related to the new light. This action is necessary to prevent an engine shut-down in icing conditions, which could result in loss of control of the airplane and consequent injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.
72-01-03: 72-01-03 BELLANCA: Amdt. 39-1373. Applies to Models 17-30A (Serial Numbers 30394, 30395, 30396, 30397, 30398, 30399, 30400, 30401, 30402, 30403 and 30405); 17-31A (Serial Number 32-53); and 17-31ATC (Serial Numbers 31022, 31023, 31024 and 31025) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent loss of engine power due to fuel starvation, accomplish the following: Prior to next flight replace hose Aeroquip P/N 359-8D-0153, located between the firewall and engine driven fuel pump, with hose Bellanca P/N 198003-10, or an equivalent method of compliance approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Bellanca Service Letter No. 68 dated December 3, 1971, pertains to this subject. This amendment becomes effective January 5, 1972, to all persons except those to whom it was made effective by telegram dated December 17, 1971.
69-14-03: 69-14-03 BRITISH AIRCRAFT CORPORATION: Amdt. 39-794. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required within the next 1,500 hours' time in service after the effective date of this AD, unless already accomplished. To prevent the failure of the windshield heating circuit, install 20K ohm resistors and 1 mfd capacitors into both phases of the heating circuit for pilot's and copilot's main windshield in accordance with British Aircraft Corporation Modification Bulletin No. 30-PM 3092, Revision 8, dated July 22, 1968 or later ARB-approved revision or an FAA approved equivalent. This amendment becomes effective August 10, 1969.
2022-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-600TP airplanes. This AD was prompted by testing that showed that the wing splice assembly could fail before the assembly reaches its established life limit. This AD requires revising the Airworthiness Limitations section (ALS) of the existing maintenance manual (MM) or instructions for continued airworthiness (ICA) to reduce the life limit of the wing splice assembly. The FAA is issuing this AD to address the unsafe condition on these products.