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2015-19-51: We are publishing a new airworthiness directive (AD) for Sikorsky Aircraft Corporation Model S-76A, S-76B, S-76C, and S-76D helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting the main rotor (M/R) and tail rotor (T/R) pushrod assemblies and the jamnuts, and applying slippage marks across the pushrod tubes and jamnuts. This AD is prompted by an accident of a Sikorsky Aircraft Corporation Model S-76C helicopter. During preliminary investigation, a failed pushrod assembly was identified. These actions are intended to prevent loss of M/R or T/R flight control and subsequent loss of control of the helicopter.
87-03-02: 87-03-02 SAAB FAIRCHILD: Amendment 39-5511. Applies to Model SF-340A series airplanes, serial numbers 03 through 044, certificated in any category. Compliance is required as indicated below, unless previously accomplished. To prevent partial loss of control as a result of an inoperative tail deicing system, accomplish the following: A. Within the next 90 days after the effective date of this AD, install a tail deicer valve heater blanket and its associated equipment in accordance with SAAB Fairchild Service Bulletin SF340-30-015, Revision 1, dated December 13, 1985. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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 the modification 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 SAAB Aircraft, Product Support AB, S-58188, Linkoping, Sweden. This document 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 February 12, 1987.
2021-10-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports indicating that the left- and right-hand elevator torque tube bearings were contaminated with sand and corrosion, restricting free rotation. This AD requires repetitive general visual inspections of the left- and right-hand elevator torque tube bearings for any sand, dust, or corrosion; repetitive functional tests of the elevator control system; and replacement of the elevator torque tube bearings if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
92-01-04: 92-01-04 MCDONNELL DOUGLAS: Amendment 39-8127. Docket No. 91-NM-237-AD. \n\n\tApplicability: Model MD-11 series airplanes; equipped with McDonnell Douglas Electronic Systems Company Central Aural Warning System (CAWS), Part Number H05A0035-50 or Part Number H05A0035-51; certificated in any category. \n\n\tCompliance: Required as indicated unless previously accomplished. \n\n\tTo eliminate the loss of Autopilot Disconnect, Windshear, Altitude, Stabilizer in Motion, Radio Altitude, and Overspeed aural alerts, accomplish the following: \n\n\t(a)\tWithin 5 days after the effective date of this AD, and thereafter prior to the first flight of each day, with the aircraft power active, accomplish the following: \n\n\t\t(1)\tPosition or verify that CAWS circuit breakers B1-1018, B1-1381, and B1-1019 are closed. \n\n\t\t(2)\tCycle all three CAWS circuit breakers to the open position. Leave the circuit breakers open for a minimum of five seconds. \n\n\t\t(3)\tReturn all three circuit breakers to the closed position. \n\n\t(b)\tWithin 60 days after the effective date of this AD, replace the CAWS unit in accordance with McDonnell Douglas Alert Service Bulletin A31-18, dated November 11, 1991. Such replacement constitutes terminating action for the requirements of paragraph (a) of this AD. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Avionics Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(e)\tThe replacement requirement of this AD shall be done in accordance with McDonnell Douglas Alert Service Bulletin A31-18, dated November 11, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California, 90846. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(f)\tThis amendment (39-8127, AD 92-01-04) becomes effective on January 24, 1992.
96-26-05: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires an inspection to detect cracking of the torque tube assembly of the left-hand (LH) elevator and surrounding structure; and to detect loose or sheared rivets in that assembly. This amendment also requires either replacement or repair of discrepant parts, as appropriate. This amendment is prompted by a report of fatigue cracking found on the torque tube support of the LH elevator. The actions specified by this AD are intended to ensure that cracking is detected and corrected in a timely manner so as to prevent failure of the torque tube or its support structure, which could result in reduced controllability of the airplane.
2015-20-12: We are superseding Airworthiness Directive (AD) 98-26-02 for certain Sikorsky Aircraft Corporation (Sikorsky) Model S-61A, D, E, L, N, NM, R, and V helicopters. AD 98-26-02 required determining whether the main rotor shaft (MRS) was used in repetitive external lift (REL) operations, performing a nondestructive inspection (NDI) for cracks, replacing any unairworthy MRS, and establishing retirement lives for each REL MRS. This new AD retains some of the requirements of AD 98-26- 02 but determines a new retirement life for each MRS, expands the applicability to include additional helicopters, and requires removing from service any MRS with oversized dowel pin bores. This AD was prompted by the manufacturer's reevaluation of the retirement life for the MRS based on torque, ground-air-ground (GAG) cycle, and fatigue testing. We are issuing this AD to prevent MRS structural failure, loss of power to the main rotor, and subsequent loss of control of the helicopter.
86-14-09: 86-14-09 BRITISH AEROSPACE AVIATION GROUP: Amendment 39-5348. Applies to all Model BAe HS 748 airplanes on which Modification 6909 has not been incorporated, certificated in any category. Compliance is required within the next 500 flight hours time-in-service after the effective date of this AD, unless accomplished within the last 500 flight hours time-in-service, and thereafter at intervals not to exceed 1000 flight hours time-in-service. To prevent the loss of autofeather capability, accomplish the following: A. Inspect the microswitch rocker arm assemblies in accordance with BAe Service Bulletin 76/15, Revision 3, dated November 1983. Replace any cracked rocker arm assemblies prior to further flight. B. The installation of modified rocker arm assemblies, in accordance with BAe Service Bulletin 76/15, Revision 3, dated November 1983, terminates the requirement for the inspection called for in paragraph A., above. C. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 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 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., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document 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 August 4, 1986.
89-11-07: 89-11-07 McDONNELL DOUGLAS: Amendment 39-6222. \n\n\tApplicability: McDonnell Douglas Model DC-6, -6A, -6B, R6D, C-118A (Military), and DC-7 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect stress corrosion cracks and to prevent failure of the wing center spar main landing gear fittings, accomplish the following: \n\n\tA.\tWithin one month after the effective date of this AD, unless already accomplished within the last five months, and thereafter at intervals not to exceed 500 hours time-in-service or one year, whichever occurs first, perform a dye penetrant inspection of the wing center spar main landing gear fittings around the bore and up to the wing lower skin, paying particular attention to the milled pocket in the outboard fitting, in accordance with Douglas Rework Drawing SR 06578001, "NC." After each inspection, apply LPS-3 corrosion inhibiting oil or equivalent to each fitting. After thefirst dye penetrant inspection, later inspections may be accomplished by using the following procedure: \n\n\t\t1.\tClean the LPS-3 using the best available cleanser, \n\n\t\t2.\tConduct a dye penetrant inspection, and, if unsuccessful, \n\n\t\t3.\tConduct a visual inspection. \n\n\tB.\tIf a crack is found as a result of the inspection required by paragraph A., above, prior to further flight, accomplish the following: \n\n\t\t1.\tIf a crack is found inside the recessed pocket areas, perform an eddy current inspection to determine if the crack extends above or below the recessed pocket areas. \n\n\t\t2.\tIf cracks are found inside the recessed pocket areas which are within the limits shown on McDonnell Douglas Rework Drawing SR 06578001, "NC," dated July 25, 1988, accomplish the trimout rework in accordance with that drawing. For a period of one year thereafter, conduct inspections in accordance with paragraph A. at intervals not to exceed three months. Thereafter, conduct inspections at intervals not to exceed 500 hours time-in-service or one year, whichever occurs first. \n\n\t\t3.\tIf cracks are found in the main landing gear cylinder bore or cracks are found which extend beyond the rework limits shown on McDonnell Douglas Rework Drawing SR 06578001,"NC," dated July 25, 1988, replace the fitting(s) with airworthy parts prior to further flight. If cracked fittings are replaced with new fittings made from 7075-T6 forging material, inspect the fittings in accordance with paragraph A., above, within 60 months after installation and thereafter at intervals not to exceed 12 months. \n\n\tC.\tInstallation of new fittings made of 7050-T7452 hand forging material constitutes terminating action for the inspections required by this AD. \n\n\tD.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base to comply with the repair requirement of this AD when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft CertificationOffice, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6222, AD 89-11-07) becomes effective on June 23, 1989.
2019-14-13: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of uncommanded fore/aft movements of the Captain's and First Officer's seats. This AD requires an identification of the part number, and if applicable the serial number, of the Captain's and First Officer's seats, and applicable on- condition actions. This AD also requires a one-time detailed inspection and repetitive checks of the horizontal movement system of the Captain's and First Officer's seats, and applicable on-condition actions. This AD also provides an optional terminating action for the repetitive checks of the horizontal movement system for certain airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
74-24-04: 74-24-04 LOCKHEED: Amendment 39-2015. Applies to all Model 382 series airplanes, Serial Numbers 3946 and 4101 through 4298, certificated in all categories, except those airplanes which have been modified in accordance with STC ST441SO, or equivalent. Compliance required within the next 200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent cracks in the lower center wing section, modify the wing in accordance with Lockheed Service Bulletin 382-121, or later FAA approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment becomes effective November 20, 1974.