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81-16-02: 81-16-02 DOWTY ROTOL, LTD.: Amendment 39-4170. Applies to the 7 Dowty Rotol propeller types listed which have Mod. No. (c)VP2833 (Service Bulletin 61-838) or Mod. No. (c)VP2866 (Service Bulletin 61-889) incorporated, as installed on, but not limited to the airplane models shown, and pitch lock cylinders and lock support sleeves, P/N 601027277, held as spares. (Note: This AD does not apply to propellers Serial No. DRG 67/78 and subsequent or any pitch lock assembly having a 3/4 inch white paint spot on the cylinder cover.) Propeller Type Installed Airplane Model R184/4-30-4/50 Grumman G-159 R193/4-30-4/50 & 61 Fairchild F-27A, F, G, and J Fokker F-27 Mks 200, 400, 500 & 600 Fairchild Hiller FH-227 Series R257/4-30-4/60 Fairchild F-27M Fairchild Hiller FH-227 B, C, D & E R209/4-40-4.5/2 YS11 & 11A R245/4-40-4.5/13 GD/Convair 240 with STC # SA1054WE installed GD/Convair 340/440 with STC # SA1096WE installed R259/4-40-4.5/17 GD/Convair 340/440 with STC #SA1096WE installed R179/4-20-4/33 Viscount 810 Series Compliance is required as indicated, unless already accomplished. To prevent cracks in the propeller pitch lock cylinder, accomplish the following one-time only actions: (a) Within the next 1,000 hours time in service after the effective date of this AD, or at the next propeller overhaul, whichever occurs first, inspect the propeller pitch lock cylinder for cracks in accordance with paragraph 2.A., "Accomplishment Instructions," of Dowty Rotol Service Bulletin 61-906, Revision 4, dated June 12, 1980 (hereinafter referred to as service bulletin), or an FAA-approved equivalent, and - (1) If any cracks are found, before further flight, remove the pitch lock cylinder from service and replace it with a crack-free pitch lock cylinder of the same part number, which has been inspected and, if necessary, reworked and reprotected in accordance with paragraphs (b) and (c) of this AD. (2) If no cracks are found, comply with paragraphs (b) and (c) of this AD before further flight. (b) Inspect the chamfer around the snout adjacent to the radius at the base of the bore at the forward end of the pitch lock cylinder in accordance with paragraph 2.A.(5) of the service bulletin, or an FAA-approved equivalent, and - (1) If the chamfer is found to be within the dimensions shown in Figure 2 of the service bulletin, or an FAA-approved equivalent, the pitch lock cylinder may be returned to service. (2) If the chamfer is found to be outside the dimensions shown in Figure 2 of the service bulletin, or an FAA-approved equivalent, rework and reprotect it in accordance with paragraph 2.A.(5) of the service bulletin or an FAA-approved equivalent, before returning the pitch lock cylinder to service. (c) Inspect the large internal chamfer at the rear end of the lock support sleeve, P/N 601027277, in accordance with Paragraph 2.A.(6) of the service bulletin, or an FAA-approved equivalent, and - (1) If the dimensions are found to be within the dimensions shown in Figure 3 of the service bulletin, or an FAA-approved equivalent, the lock support sleeve may be returned to service. (2) If the dimensions are found to be outside the dimensions shown in Figure 3 of the service bulletin, or an FAA-approved equivalent, rework and reprotect the lock support sleeve, P/N 601027277, in accordance with paragraph 2.A.(6) of the service bulletin, or an FAA- approved equivalent, before returning the lock support sleeve to service. (d) Before releasing to service any pitch lock cylinders held as spares, irrespective of part number, inspect them and remove from spares or rework and reprotect, as required, in accordance with paragraphs (a) and (b) of this AD. (e) Before releasing to service any support sleeves, P/N 601027277, held as spares, inspect them and remove from spares or rework and reprotect, as required, in accordance with paragraph (c) of this AD. Upon request of an operator, the Chief, Engineering and Manufacturing Branch, AGL- 210, Federal Aviation Administration, Great Lakes Region, may adjust the compliance time specified in paragraph (a) of this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator. For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Engineering and Manufacturing Branch, AGL-210, Federal Aviation Administration, Great Lakes Region. The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer may obtain copies upon request to Dowty Rotol, Inc., Staverton West, Sulley Road, Box 5000, Sterling, VA 22170 or Dowty Rotol, Ltd., Cheltenham Road, Gloucester, England GL2 9QH. These documents may also be examined at the Great Lakes Regional Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. This amendment becomes effective July 28, 1981.
2013-01-05: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B3 and EC130B4 helicopters. This AD requires revising the Limitations section of the Rotorcraft Flight Manual (RFM) to reduce the starter generator operating current to 180 amperes (amps) and installing a placard in the instrument panel indicating the revised limitation. This AD was prompted by the determination that the manufacturer-installed Aircraft Parts Corporation (APC) starter generator has exceeded the shaft horse power extractions allowed for Turbomeca engines. The actions of this AD are intended to prevent the engine surge margin being reduced, which can result in engine failure.
98-18-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in reduced structural integrity of the airframe.
90-10-05: 90-10-05 CALIFORNIA DEPARTMENT OF FORESTRY; GARLICK HELICOPTERS; HAWKINS AND POWERS AVIATION, INC.; HERCULES; INTERNATIONAL HELICOPTERS, INC.; OFFSHORE CONSTRUCTION; OREGON HELICOPTERS; PILOT PERSONNEL INTERNATIONAL, INC.; SMITH HELICOPTERS; SOUTHERN AERO CORPORATION; SOUTHWEST FLORIDA AVIATION; AND WEST COAST FABRICATIONS (these helicopters were manufactured by Bell Helicopter Textron, Inc under military contract): Amendment 39-6596. Docket No 89-ASW-52. Applicability: Model UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and TH-1L helicopters, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the tail rotor duplex bearing which could result in loss of tail rotor control and subsequent loss of the helicopter, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, determine if the tail rotor gearbox duplex bearing sets, P/N 204-040-424-001, havingthe following serial numbers are installed in the tail rotor gearbox output quill, P/N 204-040-012-009: Serial Numbers 1 thru 182 MB183 thru MB382 MB442 MB486 MB513 MB518 MB519 MB524 MB530 MB531 MB544 MB545 MB548 MB549 MB551 MB553 MB554 MB561 MB659 MB743 MB744 MB760 thru MB769 MB927 thru MB936 If a part with any of the listed serial numbers is installed, replace with a serviceable part before further flight. (b) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the requirements of this AD may be accomplished. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be used when approved by the Manager, Rotorcraft Certification Office, ASW-170, Rotorcraft Directorate, FAA, Southwest Region, Fort Worth, Texas. This amendment (39-6596, AD 90-10-05) becomes effective on June 5, 1990.
2022-09-04: The FAA is superseding airworthiness directive (AD) for 2021- 05-05 which applied to all Airbus Helicopters Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2021-05-05 required modifying the helicopter by replacing the tail rotor gearbox (TGB) control shaft guide bushes; repetitive inspections (checks) of the oil level of the TGB and, if necessary, filling the oil to the maximum level; repetitive inspections of the TGB magnetic plug and corrective actions if necessary; repetitive replacements of a certain control rod double bearing (bearing); and modifying the helicopter by replacing the TGB. This AD was prompted by a report where during a landing phase, a helicopter lost tail rotor pitch control, which was caused by significant damage to the TGB bearing. This AD retains some of the requirements of AD 2021-05-05, and reduces the intervals of the magnetic plug inspection, revises the corrective actions if particles are detected, and revises the compliance time for replacement of the affected part, 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.
2013-02-13: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft Inc.) PA-28, PA-32, PA-34, and PA-44 airplanes. This AD was prompted by reports of control cable assembly failures that may lead to failure of the horizontal stabilator control system and could result in loss of pitch control. This AD requires inspections of the stabilator control system and replacement of parts as necessary. We are issuing this AD to correct the unsafe condition on these products.
98-18-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection to measure the clearance between a certain wiring harness and the crew oxygen bottle; corrective actions, if necessary; and eventual relocation of the crew oxygen bottle and rework of the lines and tubing associated with the crew and passenger oxygen bottles. This amendment is prompted by a report indicating that interference between the wiring harness and the crew oxygen bottle was found on a production airplane. The actions specified in this AD are intended to prevent chafing of the wiring harness against the crew oxygen bottle, which could result in electrical shorting and possible fire in the underfloor structure of the airplane.
2006-13-05: We are adopting a new airworthiness directive (AD) that supersedes AD 2005-26-53, which applies to certain Pacific Aerospace Corporation Ltd. (PAC) 750XL airplanes. AD 2005-26-53 currently requires you to insert text into the Limitations Section of the Airplane Flight Manual (AFM) that reduces the maximum takeoff weight from 7,500 pounds to 7,125 pounds. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand and the FAA's decision that the actions correct an unsafe condition. Consequently, this AD would require you to remove rivets that have not been fully age hardened and replace them with bolts, washers, and nuts in specific locations where reduction in rivet strength affects overall structural capability. This AD retains the actions of the previous AD until the rivets are replaced with the bolts, washers, and nuts. We are issuing this AD so that wing ultimate load requirements are met. If wing ultimate load requirements are not met, wing failure could result with consequent loss of control of the airplane.
86-11-02: 86-11-02 BRITISH AEROSPACE: Amendment 39-5323. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in any category. To detect overspeeding of the cold air unit, accomplish the following within the next 120 days after the effective date of the AD, or prior to reaching the threshold indicated in each paragraph below, whichever is the later, unless already accomplished: A. Prior to the accumulation of 10,000 flight hours or 8 years in service, whichever is the earlier, and thereafter at intervals not to exceed 3,000 flight hours or 14 months, whichever occurs first, perform a functional test of the cold air unit overheat protection circuits in accordance with paragraph 2.1 of the accomplishment instructions of British Aerospace BAC 1-11 Alert Service Bulletin 21-A-PM5863, Revision 2, dated June 12, 1984. If found faulty, the overheat protection circuits must be repaired before further flight. B. For aircraft not incorporating Graviner 156D overheat detectors, prior to 300 flight hours after the effective date of this AD, perform a workshop calibration and functional test of the overheat detectors; thereafter, repeat this test at intervals not to exceed 3,000 flight hours or 14 months, whichever occurs first. C. For aircraft incorporating Graviner 156D overheat detectors which have accumulated 7,000 flight hours or 4 years since new or from last calibration, perform a workshop calibration and functional test of the overheat detectors within the next 3,000 flight hours or fourteen (14) months, whichever is the earlier; thereafter, repeat this test at intervals not to exceed 10,000 flight hours or 6 years, whichever occurs first. D. Overheat detectors that do not pass the tests of paragraphs B. or C., above, must be replaced before further flight. E. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety may be used when approved by the Manager, StandardizationBranch, ANM-113, FAA, Northwest Mountain Region. F. 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. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective July 3, 1986.
98-18-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires a one-time detailed visual inspection to detect damage or chafing of certain electrical wire bundles, and to verify adequate clearance exists between the wire bundles and adjacent disconnect bracket; and repair, if necessary. This amendment is prompted by a report indicating that damaged wires caused an electrical short in the electrical panel, which resulted in a shower of sparks from the overhead panel. The actions specified in this AD are intended to prevent failure of essential electrical systems and a potential fire hazard for passengers and crewmembers, due to damage or chafing of electrical wire bundles.