Results
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.