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80-24-01: 80-24-01 ROBINSON HELICOPTER: Amendment 39-3975. Applies to Model R-22 helicopters serial numbers 0002 through 0082 certificated in all categories. Compliance required as indicated unless already accomplished. To prevent possible loss of the tailcone resulting from supporting framework tube or tube weldment fractures, accomplish the following: (a) Unless accomplished within the previous 90 hours' time in service, in accordance with the methods of Robinson Helicopter Company Service Bulletin B-4 dated September 19, 1980, hereinafter referred to as SB B-4, prior to the accumulation of 100 hours' time in service or within 10 hours time in service from the effective date of this AD and thereafter at intervals not to exceed 100 hours' time in service since the last such inspection, dye penetrant inspect the tubes and weldments for cracks per methods of, and in the areas identified as items 1 through 4 of the figure of SB B-4. (b) If no cracks are found the rotorcraft may be returned to service provided that, on reassembly, the hardware as discussed in paragraphs 7 and 8 of the section of SB B-4 entitled "Removal of the A 023 Tailcone Assembly" is replaced with the following identical new parts: NAS - 679-A4 NUT (5 each) NAS 1304-22 Bolt (4 each) NAS 1304-3 Bolt (1 each) PAL NUTS (5 each) (c) If cracks are detected as a result of the inspections of paragraph (a) of this AD, prior to further flight notify the Chief, Aircraft Engineering Division, FAA Western Region for instructions and disposition of the part. Exact location and extent of crack must be made available to the FAA. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective November 24, 1980.
2014-03-11: We are adopting a new airworthiness directive (AD) for Bell Model 204B helicopters with a certain cable assembly installed. This AD requires inspecting the tail rotor (T/R) cable assembly for an incorrectly machined body. This AD is prompted by a report from Bell that a defective body on the cable prevents the barrel assembly from fully engaging in the body cavity. These actions are intended to prevent disengagement of the cable from the barrel, failure of the T/R pitch control, and subsequent loss of control of the helicopter.
82-11-03 R1: 82-11-03 R1 BRITISH AEROSPACE: Amendment 39-4383 as amended by Amendment 39- 4470. Applies to Model HS-125 Series 700 and all variants serial numbers 25/7001, 7007, 7010, 7013, 7020, 7022, 7025, 7028, 7031, and 7034, 7037, 7040, 7046; NA 0201 - NA 0240 inclusive certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this AD. To prevent improper operation of the elevator pitch trim switch located in the control column handwheel, accomplish the following unless already accomplished. 1. Remount the elevator pitch trim switch in accordance with the accomplishment instructions of British Aerospace Service Bulletin HS-125 27-124 (2705) dated January 1, 1979. 2. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). Amendment 39-4383 became effective May 31, 1982. This amendment 39-4470 becomes effective October 12, 1982.
79-02-01: 79-02-01 ENSTROM HELICOPTERS: Amendment 39-3390. Applies to Enstrom Model F-28C and 280C helicopters certificated in all categories. Compliance required as indicated, unless previously accomplished. In order to prevent damage to the turbocharger and possible engine power loss accomplish the following: \n\n\tWithin 50 hours time in service after the effective date of this AD, accomplish the following: \n\n\tA.\tInspect the Rajay turbocharger. If the turbocharger serial number is 70484 or greater, proceed with step B. If the turbocharger serial number is less than 70484 accomplish the following: \n\n\t\t1.\tRemove the turbocharger from the helicopter in accordance with the Enstrom Maintenance Manual. \n\n\t\t2.\tUsing a 5/32 Allen wrench, remove the six counter-sunk cap screws that secure the compressor housing to the bearing housing assembly. If necessary, gently tap the compressor housing with a plastic hammer to loosen it from the bearing housing assembly. \n\n\t\t3.\tTorque the three bearing housing flange attachment screws on the turbocharger to 90 + 10 inch-pounds. "Stake" the screws in place in accordance with the sketch and notes which follow this AD. \n\n\t\t4.\tReinstall the compressor housing by placing the turbocharger on the compressor housing using a new gasket, Rajay P/N TC6-44. Secure with six cap screws and tighten evenly and alternately to 90 + 10 inch-pounds. \n\n\t\t5.\tReinstall the turbocharger in the helicopter in accordance with the Enstrom Maintenance Manual.\n\n\tB.\tRemove the induction system air inlet filter in accordance with the Enstrom Maintenance Manual. \n\n\tC.\tRemove the AN815-6D union which attaches the fuel nozzle air vent installation to the induction system air inlet filter container. Save the AN924-6D nut which was holding the union in place, for reinstallation, in accordance with step D. \n\n\tD.\tInstall an AN832-6D union, in place of the AN815-6D union, so that the AN924-6D nut is outside of the filter container. \n\n\tE.\tAttach the fuelnozzle air vent line to the AN832-6D union. \n\n\tF.\tReplace the air filter in accordance with the Enstrom Maintenance Manual. \n\n\tEquivalent methods of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA Great Lakes Region. \n\n\tThis amendment becomes effective January 17, 1979.
2014-02-08: We are adopting a new airworthiness directive (AD) for certain Agusta Model A109C, A109E, A109S, A109K2, and AW109SP helicopters. This AD requires inspecting the lock wires securing the tail rotor (T/R) duplex bearing locking nut (locking nut) to determine whether any lock wires are missing or damaged. This AD was prompted by reports of loosening T/R locking nuts. The actions of this AD are intended to prevent failure of the T/R and subsequent loss of control of the helicopter.
2010-21-11: 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: A specific batch of nose landing gear (NLG) and NLG door selector valves, part number (P/N) 601R75146-1 (Kaiser Fluid Technologies P/N 750006000), may have had their end caps incorrectly lock-wired and/or incorrectly torqued during assembly. This condition can lead to the end cap backing off, with consequent damage to a seal and internal leakage within the valve. Subsequently, if electrical power is transferred or removed from the aircraft before the NLG safety pin is installed, any pressure, including residual pressure, in the No. 3 hydraulic system can result in an uncommanded NLG retraction and/or uncommanded opening of the NLG doors. There have beensix cases reported on CL[-]600- 2B19 aircraft, one of which resulted in the collapse of the NLG at the departure gate. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
80-11-07: 80-11-07 ROBINSON HELICOPTER COMPANY: Amendment 39-3834. Applies to Model R22 series helicopters certificated in all categories. Compliance is required as indicated. To prevent main rotor blade structural failure, accomplish the following: (a) Prior to further flight remove from service all main rotor blades Serial numbers 1 through 91 and replace with like serviceable part. (b) Mark all blades Serial numbers 1 through 91 "UNAIRWORTHY" on the blade upper surface at the approximate mid-span with lettering at least 2 inches high and, using a metal stamp, mark "UNAIRWORTHY" on data plate. This supersedes Amendment 39-3751, (45 FR 26032), AD 80-08-08. This amendment becomes effective July 14, 1980, and was effective earlier for all recipients of the telegram T80WE25 dated May 20, 1980.
63-15-05: 63-15-05 PIAGGIO: Amdt. 587 Part 507 Federal Register July 19, 1963. Applies to Model P.166 Aircraft, Serial Numbers 1 through 405. Compliance required within 25 hours' time in service after the effective date of this AD. To prevent failure at the flared end of the Teleflex rod guide tube, in the throttle, fuel cut- off, propeller and hot air controls, accomplish the following: PARTS REQUIRED No. Required Description Part Number 2 Sheath, throttle control guide 66-S. 1107.01 2 Sheath, engine stop control guide 66-S. 1107.02 2 Sheath, propeller control guide 66-S. 1107.03 2 Sheath, hot air control guide 66-S. 1107.04 Unless previously accomplished, remove the aluminum sheath control guides and install new steel control guides as shown in the preceding table, in accordance with Piaggio Service Bulletin No. 166.31 dated November 22, 1962. This directive effective August 20, 1963.
2013-25-13: We are adopting a new airworthiness directive (AD) for Sikorsky Model S-70, S-70A, and S-70C helicopters. This AD establishes a new life limit based on a prorated formula for certain identified components (parts) installed on Model S-70, S-70A, and S-70C helicopters after being previously installed on certain military model helicopters. This AD was prompted by the discovery that certain parts have been interchanged between military helicopter models with different life limits and the possibility that these same parts can be interchanged with civilian models with different life limits. The actions are intended to establish a pro-rated in service life limit for each identified part to prevent fatigue failure of a part and subsequent loss of control of the helicopter.
79-23-07: 79-23-07 BELL HELICOPTER TEXTRON: Amendment 39-3613. Applies to Bell 47G series helicopters certificated in all categories that have been converted to turbine power Soloy Conversions, Ltd., Supplemental Type Certificate SH657NW. A. Within the next 25 hours time-in-service, after the effective date of this AD, inspect the turbine engine mount rod ends with a magnet to determine if the NMB Inc. P/N AH FTL5, or Soloy P/N 100-2205-2B rod ends are installed. These suspect stainless steel rod ends are identified by the fact that they are non-magnetic. B. If the non-magnetic stainless steel rod ends are found to be installed, replace the rod ends with Heim P/N HFL-5M or Soloy P/N 100-2205-1B in accordance with Soloy Conversions, Ltd., Service Bulletin 03-660 dated July 16, 1979, within 25 hours time-in-service after the effective date of this AD. C. Return the suspect stainless steel rod ends to Soloy Conversions, Ltd., for disposal within 30 days after removal. D. Alternate replacements which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Soloy Conversions, Ltd., P.O. Box 60, Chehalis, Washington, 98532. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment is effective November 26, 1979 and was effective earlier, for all recipients of the airmail letter dated August 21, 1979, which contained this Amendment.