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77-15-02: 77-15-02 HAWKER SIDDELEY AVIATION, LIMITED: Amendment 39-2972. Applies to Model HS-748, Series 2A airplanes, certificated in all categories. Compliance is required as indicated. To prevent a possible loss of aileron control, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the aileron hinge structures of the right and left wings in the areas of the outer and center hinges for damage, in accordance with the instructions set forth in Part 2A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA-approved equivalent. (b) If, as a result of an inspection required by paragraph (a) of this AD, damage, in the form of cracks, loose rivets, or corroded support bearings or pivot bolts is found in any of the areas specified in paragraph (a) of this AD, before further flight, perform an internal inspection of the aileron hinge ribs where they attach to the rear spar of the wing in accordance with the instructions set forth in Part 2B of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA- approved equivalent. (c) If, as a result of an inspection required by either paragraph (a) or (b) of this AD, damage, in the form of cracks, loose rivets, or corroded support bearings or pivot bolts is found, before further flight, replace or repair the damaged, loose, or corroded parts in accordance with Part 2C of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA-approved equivalent, and continue to inspect in the areas specified and at the intervals established in paragraphs (a) and (b) of this AD, as required. (d) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install strengthened gusset plates to reinforce the outer and center aileron hinge ribs at both the right and left wings, in accordance with Modification 4873 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/28, dated January 2, 1974, or an FAA-approved equivalent. (e) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install reinforcing straps at the top and bottom surfaces of the aileron spar area of both the right and left wings at the outboard aileron hinge positions, in accordance with Modification 4874 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/27, dated January 2, 1974, or an FAA-approved equivalent. (f) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install the reinforcing plates on the right and left wing tips on the rear diaphragm in accordance with Modification 4875 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/26, dated January 2, 1974, or an FAA-approved equivalent. (g) Upon accomplishment of the modifications specified in paragraphs (d), (e), and (f) of this AD, the inspections required by paragraphs (a) and (b) of this AD, may be terminated. This amendment becomes effective August 15, 1977.
2001-26-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-IV series airplanes. This action requires an inspection of the electrical connections for the fire extinguisher bottles; an inspection after any subsequent maintenance affecting the fire extinguisher bottles; and corrective action, if necessary. This action is prompted by a report indicating that the electrical connections for the fire extinguisher bottle squibs had been improperly installed either during manufacturing or during subsequent maintenance. This action is necessary to prevent fire extinguishing agent from being discharged into the wrong location, which could result in failure to extinguish an in-flight fire on an affected engine and jeopardize operation of the opposite engine.
2010-05-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2010-05-51, which was sent previously to all known U.S. owners and operators of ECF Model EC120B helicopters by individual letters. This AD requires, at specified intervals, inspecting the main rotor head rotor hub (rotor hub) for a crack. If you find scoring, paint flaking or left-over identification plate adhesive, the AD requires sanding the area until the primer coat becomes visible and inspecting the rotor hub for a crack. If you find a crack, the AD requires, before further flight, replacing the rotor hub with an airworthy rotor hub. This amendment is prompted by a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that ECF has been informed of an emergency landing due to excessive vibrations originating from the main rotor. After an investigation, it was determined that the main rotor head rotor hub (rotor hub) had failed in the attachment area of one of the three drag damper fittings. The actions specified by the AD are intended to prevent failure of a hub, excessive vibrations, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2017-14-03: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires an inspection and reduces the retirement lives of certain landing gear components. This AD is prompted by a revised analysis of the fatigue life of the landing gear. The actions of this AD are intended to prevent an unsafe condition on these products.
2001-26-08: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 series airplanes and Model A300 B4-2C, B4-103, and B4-203 series airplanes, that requires identifying the types and areas of repairs on the airplane between frame 10 and frame 80, and performing follow-on actions for certain repairs. These actions are necessary to detect and correct fatigue cracking of certain repairs of the fuselage between frame 10 and frame 80, which could result in reduced structural integrity of the airplane. These actions are intended to address the identified unsafe condition.
2001-26-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of a main deck cargo door hinge; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier. These actions are necessary to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
74-03-04: 74-03-04 GENERAL DYNAMICS: Amdt. 39-1781. Applies to Model 240 series and T- 29B airplanes including those modified for Turbo-propeller power per STC SA1054WE certificated in all categories. Compliance required as indicated. To detect cracks in the Pilot and Copilot direct vision window frame castings, P/N's 240- 3110314-6 and -7 (hereinafter referred to as the casting) which could result in failure in flight and consequent rapid decompression, accomplish the following: (a) Inspect each casting with 4500 or more hours' time in service on the effective date of this AD for cracks in accordance with (c), below, within the next 250 hours' time in service after the effective date of this AD unless already accomplished within the last 750 hours' time in service, and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection. (b) Inspect each casting with less than 4500 hours' time in service on the effective date of this AD for cracks inaccordance with (c), below, prior to the accumulation of 4750 hours' time in service and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection. (c) Inspect the castings in accordance with Paragraph 2B of General Dynamics Service Bulletin 600 (240D), S.B. No. 53-2A, dated December 21, 1973, or later FAA-approved revisions, or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) If a crack is found, comply with (1) or (2), below, as appropriate: (1) If the crack completely severs the frame at any point, replace the casting with a new part, P/N 240-3110314-6 or -7, prior to further flight, except that the airplane may be flown with a zero differential cabin pressure in accordance with FAR 21.197 to a base where the replacement can be accomplished. (2) If the crack does not completely sever the frame at any point, replace the casting with a new part, P/N 240-3110314-6 or -7, within 250 hours' time in service after crack discovery, except that, until such time as the casting is replaced, the following shall apply: (i) The airplane must be operated at a zero differential cabin pressure. (ii) Prior to take off after crack discovery, an operating limitation in the form of a placard must be installed in clear view of the pilot stating: "Operation Limitation. Pressurized Flight Prohibited." (e) Operators who have not kept records of hours' time in service of individual castings shall substitute hours' time in service of the airplane in lieu thereof. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the compliance times herein if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective on February 4, 1947.
2001-26-06: This amendment adopts a new airworthiness directive (AD) that is applicable to CFE Company model CFE738-1-1B turbofan engines. This action requires the removal of certain fan rotor disks from service. This amendment is prompted by a report from a forging manufacturer, of a metallurgical inclusion (contaminant) found in a forging made from a certain ingot of titanium. Fan rotor disks for model CFE738-1-1B engines have been manufactured from this same ingot and are suspect for metallurgical inclusions. The actions specified in this AD are intended to remove from service affected fan rotor disks, which if not removed, could result in uncontained engine failure and damage to the airplane.
74-24-03: 74-24-03 BEECH: Amendment 39-2016. Applies to the following models and serial numbered airplanes if equipped with either Grimes P/N 30-0467-1 or Grimes P/N 30-0467-3 strobe light assemblies: F33A, Serials CE-436 through CE-537 V35B, Serials D-9468 through D-9692 A36, Serials E-424 through E-603, E-605 through E-607 95-B55 and 95-B55A, Serials TC-1526 through TC-1804 and TC-1806 through TC-1811 E55 and E55A, Serials TE-904 through TE-1000, TE-1002 and TE-1003 58 and 58A, Serials TH-303 through TH-482, and TH-484 through TH-527 A60 and B60, Serials P-223 through P-307, P-309 and P-310 70, Serial LB-35 B80, Serials LD-441 through LD-490 C90, Serials LJ-502 through LJ-643 E90, Serials LW-1 through LW-117 B99, Serials U-152 through U-159 100 and A100, Serials B-52 through B-204 200, Serials BB-1 through BB-14, BB-16 through BB-21, and BB-29 Compliance: Required as indicated, unless already accomplished. A. To preclude possible ignition of flammablefluids or vapors by arcing between the strobe lights and the aircraft structure, within the next 25 hours' time in service after the effective date of this AD, deactivate the strobe light system in accordance with Beech Service Instruction No. 0655-362, Rev. I, or later approved revisions and add a temporary placard near the strobe light switch stating "STROBE LIGHT SYSTEM DEACTIVATED". This requirement is only applicable until the strobe light system is modified per Paragraph B of this AD. B. To assure proper electrical bonding of the Grimes Strobe light P/N 30-0467-1 or P/N 30-0467-3, to the aircraft structure so as to eliminate a possible ignition source in an area where fuel/fuel vapor can exist, on or before July 1, 1975, modify the strobe light system in accordance with Beech Service Instructions No. 0655-362, Rev. I, or later approved revisions. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA,Central Region. If an airplane has been modified by the aircraft manufacturer in accordance with Paragraph B above and the aircraft manufacturer has made an entry in the aircraft permanent maintenance record that the modification was "in accordance with AD 74-20-11, as amended", or words to that effect, such modification meets the requirements of Paragraph B of this AD. This AD supersedes Amendment 39-1980, AD 74-20-11. This amendment becomes effective November 22, 1974.
2017-15-07: We are superseding airworthiness directive (AD) 2017-04-51 for all Safran Helicopter Engines, S.A., Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. AD 2017-04-51 required inspecting, wrapping, and replacing the affected drain valve assembly (DV) installed on these Arriel 1 engines. This AD requires inspecting and wrapping affected DVs and replacing those DVs found to be defective. This AD eliminates the terminating action that existed under AD 2017-04-51 and reduces the population of affected parts. This AD was prompted by reports of additional fuel leaks originating from the DV on certain Arriel engines. We are issuing this AD to correct the unsafe condition on these products.