Results
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.
46-36-02: 46-36-02 PIPER: (Was Mandatory Note 3 of AD-780-3.) Applies to PA-12 Aircraft Serial Numbers 12-1 to 12-207, Inclusive. Compliance required prior to November 1, 1946. Several instances have been reported of loosening of the cap screws attaching the air scoop to the carburetor on these aircraft, thus creating a hazard. These cap screws should be removed and drilled for safety wire. They should then be reinserted and safety wire installed. (Piper Service Bulletin No. 90 dated July 17, 1946, covers this same subject.)
63-22-02: 63-22-02 GRUMMAN: Amdt. 634 Part 507 Federal Register October 26, 1963. Applies Only to Model G-164 Series Aircraft Equipped With Continental W670 Series Engines, Serial Numbers 1 through 229 Inclusive. Compliance required as indicated. As a result of excessive wear of the throttle control pivot bolt, which can cause loss of throttle control, accomplish the following: (a) (1) Within 25 hours' time in service after the effective date of this AD, remove and visually inspect the throttle control pivot bolt (AN 23-13) for wear. If the bolt is worn, measure bolt shank. (2) If wear in excess of 0.020 inch is detected on any surface of the bolt, rework the carburetor throttle arm for a 0.250 diameter reamed hole, and installation of an A1658-1 bushing, AN 3-10A bolt, AN 960-10 washers and AN 365-1032 self-locking nut per Grumman Service Bulletin No. 25 dated August 29, 1963. (Grumman Engineering Change Order No. S164-1292.) (3) If no wear is found on the AN 23-13 bolt, thepivot bolt may be continued in service provided that the bolt is repetitively inspected at intervals of 50 hours' time in service. (b) Repetitive inspections required by (a) (3) may be discontinued when the modifications established by a (a)(2) are accomplished. (Grumman Service Bulletin No. 25 dated August 29, 1963, with enclosure (a) Grumman Engineering Change Order No. S164-1292 covers this same subject.) This directive effective October 26, 1963.
2013-26-13: We are adopting a new airworthiness directive (AD) for Sikorsky Model S-70, S-70A, S-70C, S-70C (M), and S-70C (M1) helicopters with General Electric (GE) T700-GE-401C or T700-GE-701C engines installed. This AD requires establishing new fatigue life limits for certain GE engine gas generator turbine (GGT) rotor parts. This AD was prompted by a reevaluation of the method for determining the life limit for certain GE engine GGT rotor parts and the determination that these life limits should be based on low cycle fatigue (LCF) events instead of hours time-in-service (TIS). The actions are intended to prevent fatigue failure of a GGT rotor part, engine failure, and subsequent loss of control of the helicopter.