Results
2020-14-01: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. (Bell) Model 214ST helicopters. This AD was prompted by the discovery of bolts with nonconforming external thread root radii. This AD requires removing the affected bolts from service and prohibits installing an affected bolt on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
85-03-05: 85-03-05 BRITISH AEROSPACE: Amendment 39-5001. Applies to Model HS 748 airplanes, certificated in all categories, which are listed in the British Aerospace service bulletins specified below. Compliance is required within the time interval specified in each of the following paragraphs, unless previously accomplished: A. To ensure the baggage door properly locks from the interior, within 180 days after the effective date of this airworthiness directive (AD), modify the baggage door in accordance with British Aerospace HS 748 Service Bulletin 52/94, dated May 14, 1982. B. To ensure the passenger and crew/freight doors properly lock, within 180 days after the effective date of this AD, modify the doors in accordance with British Aerospace HS 748 Service Bulletin 52/95, dated May 14, 1982. C. To prevent false door warnings on baggage, passenger, and crew/freight doors, within 180 days after the effective date of this AD, modify the doors in accordance with British Aerospace HS 748 Service Bulletin 52/96, dated May 14, 1982. D. To ensure passenger, baggage, and crew/freight doors properly lock, within 90 days after the effective date of this AD, install warning decals to the interior trim of the doors in accordance with British Aerospace HS 748 Service Bulletin 52/97, dated May 14, 1982. E. To prevent false door warnings on baggage and crew/freight doors, within 180 days after the effective date of this AD, modify the doors in accordance with British Aerospace HS 748 Service Bulletin 52/99, dated May 14, 1982. F. To ensure the large freight door properly locks, within 90 days after the effective date of this AD, install warning decals to the interior trim of the door in accordance with British Aerospace HS 748 Service Bulletin 52/100, dated May 14, 1982. G. To prevent failure of the crew/freight door locking mechanism swivel lever, within 90 days after the effective date of this AD, inspect the swivel levers in accordance withBritish Aerospace HS 748 Service Bulletin 52/101, Revision 1, dated December 1983. If necessary, replace parts in accordance with the service bulletin instructions. Repetitive inspections must be performed in accordance with the service bulletin instructions. H. To ensure the integrity of door sills and secondary locking mechanisms, inspect the passenger, baggage, and crew/freight doors (including the large freight door), within 180 days after the effective date of this AD, in accordance with British Aerospace HS 748 Service Bulletin 52/106, dated November 1982. If necessary, replace parts in accordance with the service bulletin instructions. Repetitive inspections must be performed in accordance with the service bulletin instructions. I. To provide an audible door unsafe warning on all airplanes, except Model 235, within 180 days after the effective date of this AD, install an audible warning system in accordance with British Aerospace HS 748 service bulletin 52/109,dated October 13, 1982. J. To provide an audible door unsafe warning on Model 235 airplanes, within 180 days after the effective date of this AD, install an audible warning system in accordance with British Aerospace HS 748 Service Bulletin 52/110, dated October 13, 1982. K. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. L. 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. This amendment becomes effective March 11, 1985.
2003-18-03: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the hydraulic brake hose (hose) for crazing, pinching, distortion, or leaks at the torque link hinge and replacing the hose, if necessary. This amendment also requires inspecting the hose and the emergency flotation gear pipe to ensure adequate clearance, and adjusting the landing gear leg, if necessary. This amendment is prompted by a report of a hose compression due to interference with a clamp that attaches the emergency flotation gear pipe. The actions specified by this AD are intended to prevent failure of the hose, resulting in failure of hydraulic pressure to the brakes on the affected landing gear wheel, and subsequent loss of control of the helicopter during a run-on landing.
2003-18-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires, among other actions, a detailed inspection of the rudder travel limitation unit for proper adjustment, measurement of the desynchronization of rudder servo-controls, installation of rigging placards for rudder servo-controls, and follow-on and corrective actions if necessary. This action is necessary to prevent desynchronization of the rudder servo-controls, which could result in high load factors on the rudder servo-controls, and consequent reduced structural integrity of the attachment fittings for the rudder servo- controls. This action is intended to address the identified unsafe condition.
92-12-10: 92-12-10 TEXTRON LYCOMING: Priority Letter issued on June 5, 1992. Docket No. 92-ANE-27 Applicability: Textron Lycoming Model TIO-540-S1AD engines installed on but not limited to Piper PA-32 Series Aircraft (Turbo Saratoga, Turbo Saratoga SP and Turbo Lance II aircraft). Compliance: Required as indicated, unless accomplished previously. To prevent failure of the fuel injector lines that can result in engine fire, accomplish the following: (a) Within 10 hours after the effective date of this AD inspect the fuel injector fuel lines between the fuel manifold and the fuel injector nozzles as follows: (1) Visually inspect each fuel injector fuel line for missing support clamps or support clamps with a loose, worn or missing support sleeve or cushion. Each fuel injector fuel line must be supported by at least one clamp. (2) Visually inspect each fuel injector fuel line for evidence of physical damage, including dents and chaffing, and for stains caused by fuel leakage. (b) Prior to further flight, replace any fuel injector fuel line that does not have a supporting clamp, has a clamp with a loose, worn, or missing support sleeve or cushion, or if the line itself is damaged or has evidence of fuel leakage. (c) After the effective date of this AD, reinspect the fuel lines in accordance with paragraphs (a)(1) and (2) of this AD and replace as necessary any fuel injector fuel lines in accordance with paragraph (b) of this AD at each annual inspection, at each 100-hour inspection, at each engine overhaul, and after any maintenance has been performed on the engine where the fuel injector fuel lines have been disconnected or disturbed. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office, ANE-170, 180 South Franklin Street, Valley Stream, New York. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (g) Copies of the applicable service information may be obtained from Textron Lycoming, Williamsport, Pennsylvania. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (h) Priority letter AD 92-12-10, issued June 5, 1992, becomes effective upon receipt.
60-10-10: 60-10-10 VERTOL: Amdt. 140 Part 507 Federal Register May 4, 1960. Applies to all 44 series helicopters. Compliance required as indicated. All forward rotor blades P/N 42R1002-9, -13, -15, -19, -90, -130, -131, -132, -150, and - 152 must be retired at 800 hours of service time. All forward rotor blades P/N 42R1002-137 AND -139 and all aft rotor blades P/N 42R1002-2, -4, -20, and -40 must be retired at 1,350 hours of service time. When the above blades are modified to 42R1002-42, -133, or -135 the provisions of this airworthiness directive no longer apply. This supersedes AD 59-25-02.
2003-18-01: This amendment supersedes an existing airworthiness directive (AD), applicable to various surplus military airplanes manufactured by Consolidated, Consolidated Vultee, and Convair, that currently requires repetitive inspections to find fatigue cracks in the lower rear cap of the wing front spar, front spar web, and lower skin of the wings; repair or replacement of any cracked part with a new part; and follow- on inspections at new intervals. This amendment continues to require those actions and revises and clarifies the applicability of the existing AD. The actions specified in this AD are intended to find and fix fatigue cracking, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2020-13-06: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW150A model turboprop engines. This AD was prompted by a determination by the manufacturer that certain PW150A engine high-pressure (HP) centrifugal impellers may exhibit a material microstructure anomaly that has a potential to adversely affect the low cycle fatigue characteristics of the part. This AD requires replacement of the affected HP centrifugal impellers. The FAA is issuing this AD to address the unsafe condition on these products.
2000-24-21: This amendment adopts a new airworthiness directive (AD), for Siam Hiller Holdings, Inc. (Hiller), formerly Rogerson Hiller Corporation, Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, UH-12E-L, UH-12L, and UH-12L4 helicopters, that requires replacing all undrilled-shank bolts at pivoting joints in the control system linkage with drilled-shank bolts and installing castellated nuts and cotter pins. This amendment is prompted by an accident caused by separation of the control system linkage of a Model UH-12E helicopter. The actions specified by this AD are intended to prevent separation of the control system attachments at pivoting points and subsequent loss of control of the helicopter.
80-22-53: 80-22-53 AVCO LYCOMING: Amendment 39-3995. Applies to Avco Lycoming ALF5O2L and L2 engines except those installed in aircraft operated under an experimental airworthiness certificate. Compliance required as indicated, unless already accomplished. Prior to further flight, rework or replace the following parts and reassemble in accordance with Avco Lycoming Service Bulletin No. ALF502-72-0008, Revision No. 1, dated October 14, 1980, "Replacement of No. 4 and 5 Bearing Oil Inlet Tubes," and Service Bulletin No. ALF502-72- 0010, dated October 14, 1980, "Introduction of Improved Fourth Turbine Nozzle and Fire Shield," or an FAA approved equivalent: a. Remove number 4 and 5 oil inlet tube assembly P/N 2-141-380-07/-08/-11/-12 and replace with P/N 2-141-380-13/-14. b. Remove adapter assembly P/N 2-141-640-01 and replace with P/N 2-141-640-02. c. If not previously incorporated, install: Bracket P/N 2-143-049-01, spacer P/N 2-143-051-01, two bolts P/N STD3061-11, Clamp P/N TA1501H05, Bolt P/N MS9565-06, Nut P/N STD3073-3, and Washer P/N STD3035C2. d. Rework fourth stage turbine nozzle P/N 2-141-150-38 to P/N 2-141-150-42, or P/N 2-141-150-39 to P/N 2-141-150-41 in accordance with Service Bulletin No. ALF502-72-0010. e. Rework upper half of fire shield P/N 2-163-990-04 to 2-163-990-07, or P/N 2-163-990-05 to 2-163- 990-08 in accordance with Service Bulletin No. ALF502-72-0010. f. Install: Washer P/N 2-163-585-01, and Spring P/N 2-163-586-01, and Retainer P/N 2-163-584-01. g. Remove oil feed line P/N 2-173-240-02 and replace with P/N 2-303-377-01. h. Remove jam nut P/N R44118P05W. (The function of the jam nut is accomplished by the parts in "f" and "g" above.) (i) Remove oil inlet support bracket P/N 2-141-335-02 and replace with P/N 2-141-335-03. After replacement of the number 4 and 5 bearing oil inlet tube and associated hardware in accordance with this AD, inspect the number 4 and 5 bearing oil inlet tube every 100 engine operating hours thereafter for chafing in accordance with Avco Lycoming Service Bulletin No. ALF502-72-0008, Revision No. 1, or an FAA approved equivalent. Oil inlet tubes which exhibit chafing in excess of 0.010 inch deep must be replaced with like serviceable parts prior to further flight. Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA New England Region. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Themanufacturer's 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 Avco Lycoming, Stratford, Connecticut 06497. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at the FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective December 31, 1980 as to all persons except those persons to whom it was made immediately effective by the telegram of October 23, 1980.