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89-14-05: 89-14-05 AEROSPATIALE: Amendment 39-6244. Applicability: Model ATR42 series airplanes, Serial Numbers 003 through 138, certificated in any category. Compliance: Required within 10 days after the effective date of this AD, unless previously accomplished. To prevent loss of engine oil and engine shutdown, accomplish the following: A. Replace and lockwire the drain plug and adjacent locknut on the engine oil pressure manifold, in accordance with Aerospatiale Service Bulletin ATR42-79-0006, Revision 1, dated April 18, 1989. 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. NOTE: 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, Standardization Branch, ANM-113. C. Special 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Aerospatiale, 216 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6244, AD 89-14-05) becomes effective on July 5, 1989.
89-08-04: 89-08-04 McDONNELL DOUGLAS: Amendment 39-6179. \n\n\tApplicability: Model DC-9, DC-9-80, and C-9 (Military) series airplanes, certificated in any category, as listed in McDonnell Douglas Model DC-9 Service Bulletin 27-173, Revision 1, dated May 20, 1982, and Service Bulletin 27-257, Revision 1, dated June 20, 1988. \n\n\tCompliance: Required within 12 months after the effective date of this airworthiness directive (AD), unless previously accomplished. \n\n\tTo eliminate lateral control difficulties after liftoff during takeoff, accomplish the following: \n\n\tA.\tFor McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, identified in McDonnell Douglas Model DC-9 Service Bulletin 27-173, Revision 1, dated May 20, 1982, and Service Bulletin 27-257, Revision 1, dated June 20, 1988: Install the Spoiler Position Sensing and Indication System and "spoiler deployed" annunciation takeoff inhibit feature in accordance with the accomplishment instructions of those service bulletins.B.\tFor McDonnell Douglas Model DC-9-81, and DC-9-82, and DC-9-83 series airplanes identified in McDonnell Douglas Model DC-9 Service Bulletin 27-257, Revision 1, dated June 20, 1988: Install the spoiler deployed annunciation takeoff inhibit feature in accordance with the accomplishment instructions of that service bulletin. \n\n\tC.\tFor all McDonnell Douglas Model DC-9-81, DC-9-82, and DC-9-83 airplanes with the production equivalent of McDonnell Douglas Model DC-9 Service Bulletin, 27-257, Revision, dated June 20, 1988, incorporated but presently de-activated: Re-activate the spoiler deployed annunciation takeoff inhibit feature in accordance with the airplane type design configuration. \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 Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tE.\tSpecial flight permits may be used 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\tAll persons affected by this directive who have not already received the appropriate service information 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, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6179, AD 89-08-04) becomes effective on May 4, 1989.
70-21-04: 70-21-04 HAWKER SIDDELEY: Amendment 39-1089. Applies to de Havilland Model DH.114 "Heron" airplanes. Compliance is required as indicated. To prevent failure of the fin to fuselage front attachment brackets at Bulkhead 6, accomplish the following: (a) For all airplanes, within the next 1200 hours' time in service from the effective date of the AD, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, visually inspect Bulkhead 6 for cracking or signs of distortion in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB- approved issue or an FAA-approved equivalent. If cracking or signs of distortion are found, accomplish standard repairs before further flight. (b) For airplanes having right-hand and left-hand forward fin attachment fittings, P/Ns 14FS.1891 and 14FS.1892 (pre-modification No. Heron 609), or right-hand and left-hand forward fin attachment fittings, P/Ns 14FS.5007 and 14FS.5008 (post-modification Heron 609) installed on Bulkhead 6, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service since the last inspection, visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent. If there is doubt as to the results of this inspection, confirm the results of the inspection by a dye penetrant method. (c) For airplanes having right-hand and left-hand forward fin attachment fittings, P/Ns 14 FS.4669 and 14 FS.4670 (post-modification No. Heron 869) installed on Bulkhead 6, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 900 hours' time in service, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent. If there is doubt as to the results of this inspection, confirm the results of the inspection by a dye penetrant method. (d) If cracks are found in a forward fin attachment fitting during the inspections required by paragraphs (b) or (c), accomplish the following before further flight: (1) Replace both the right-hand and left-hand forward attachment fittings in accordance with de Havilland Aircraft Service Modification No. Heron 869, Amendment No. 1, dated May 15, 1959, or later ARB-approved issue or an FAA-approved equivalent. (2) Visually inspect the fin attachment fittings on Bulkhead 7 and the fin attachment fittings on the fin rear spar for cracks or any other signs of damage, and replace any fittings found to be cracked or damaged with new fittings of the same part number. (e) For all airplanes, after accomplishing the replacements and inspections specified in paragraph (d), continue to visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent, at intervals not to exceed 1200 hours' time in service since the last replacements and inspections accomplished in accordance with paragraph (d). If cracks are found during any of these inspections, replace the cracked fittings before further flight in accordance with de Havilland aircraft Service Modification No. Heron 869, Amendment No. 1, dated May 15, 1959, or later ARB-approved issue or an FAA-approved equivalent. This amendment becomes effective November 5, 1970.
2006-06-51: This document publishes in the Federal Register an amendment adopting emergency airworthiness directive (EAD) 2006-06-51 that we sent previously to all known U.S. owners and operators of GEAE CT7-8A turboshaft engines installed on Sikorsky S92 helicopters. This AD requires initial and repetitive inspections of the electrical chip detectors for the No. 3 bearing. This AD results from two failures of the No. 3 bearing in GEAE CT7-8A engines. We are issuing this AD to prevent failures of the No. 3 bearings and possible dual in-flight shutdowns of the engines.
86-21-02: 86-21-02 BRITISH AEROSPACE: Amendment 39-5420. Applies to BAe Model 146 series airplanes, as listed in BAe Service Bulletin 27-42-00671A, dated August 19, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent control column oscillations, accomplish the following: A. Modify the elevator control system in accordance with BAe Service Bulletin 27- 42-00671A, dated August 19, 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 requirements of this AD. All persons affected by this directive who have not already received the appropriate service bulletin 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 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 October 24, 1986.
2020-11-07: The FAA is adopting a new airworthiness directive (AD) for MD \nHelicopters Inc., (MDHI) Model 369D, 369E, 369FF, 369H, 369HE, 369HM, \n369HS, 500N, and 600N helicopters. This AD was prompted by a report of \nnon-conforming main rotor (M/R) hub lead-lag bolts (bolts). This AD \nrequires removing certain bolts from service. The FAA is issuing this \nAD to address the unsafe condition on these products.
2006-04-13 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain Gulfstream Model GIV-X and GV-SP series airplanes. That AD currently requires revising the Limitations section of the airplane flight manual (AFM) by incorporating new procedures to follow in the event that the cockpit displays go blank or malfunction. This AD allows for the use of alternative AFM revisions for a certain subset of the existing applicability. This AD results from a report that all four of the cockpit flight panel display units simultaneously went blank during flight. We are issuing this AD to ensure that the flightcrew is advised of the appropriate procedures to follow in the event that the cockpit displays go blank or malfunction, which could result in a reduction of the flightcrew's situational awareness and possible loss of control of the airplane.
2020-11-04: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 60 airplanes. This AD was prompted by a report of a reverse thrust command accelerating the airplane instead of decelerating the airplane. The acceleration with reverse thrust commanded occurred when the thrust reverser doors were in the stowed position instead of the deployed position. This AD requires installing a thrust reverser (T/R) Voice Command Warning System (VCWS) to alert the crew of a T/R malfunction. The FAA is \n\n((Page 30838)) \n\nissuing this AD to address the unsafe condition on these products.
2006-08-03: The FAA is adopting a new airworthiness directive (AD) for Sicma Aero Seat (formerly Farner) cabin attendant seats series 150 type FN and series 151 type WN. This AD requires installing two protection fairings over the upper seat structure to cover the gap between the upper and lower seats and prevent any contact with the bottom seat folding mechanisms. This AD results from a child catching its fingers in the folding mechanism of the bottom of the attendant seat. We are issuing this AD to prevent injury resulting from contact with the bottom folding mechanism.
89-10-09: 89-10-09 AEROSPATIALE: Amendment 39-6206. Applicability: All Model ATR42-200 and -300 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of a main landing gear wheel due to defective bearings, accomplish the following: A. Within 30 days after the effective date of this AD, inspect outboard bearings, Part Number (P/N) L910349, of the Loral main landing gear wheels, Loral P/N 5006856, 5006856-1, 5006856-2 and 5006856-3, and replace those having a "JV" date code, in accordance with Aerospatiale Service Bulletin ATR42-32-0018, Revision 2, dated November 15, 1988, and Loral Service Bulletin ATR42-32-40-8. Perform torqueing of the main gear axle nut, in accordance with Loral Service Bulletin ATR42-32-40-7. 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, StandardizationBranch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. 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 inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6206, AD 89-10-09) becomes effective on June 9, 1989.