Results
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.