Results
97-18-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive inspections to detect fatigue cracking in the midspar fuse pins; replacement with new or refinished fuse pins, if necessary; and repetitive inspections of newly installed fuse pins. This AD requires earlier initial inspections and replacements; more frequent repetitive inspections of certain fuse pins; and replacement with new fuse pins, if necessary. This amendment is prompted by reports of fatigue cracking of the midspar fuse pins and by fatigue test data indicating that current inspection thresholds and intervals for repetitive inspections are inadequate to detect fatigue cracking in a timely manner. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could lead to separation of the strut and engine from the wing of the airplane.
97-18-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive inspections to detect cracking in the midspar fuse pins; replacement with new or refinished fuse pins, if necessary; and repetitive inspections of newly installed fuse pins. This AD requires earlier initial inspections and replacements; more frequent repetitive inspections of certain fuse pins; and replacement with new fuse pins, if necessary. This amendment is prompted by reports of fatigue cracking of the midspar fuse pins and by fatigue test data indicating that current inspection thresholds and intervals for repetitive inspections are inadequate to detect fatigue cracking in a timely manner. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could lead to separation of the strut and engine from the wing of the airplane.
92-03-09: 92-03-09 SAAB-SCANIA: Amendment 39-8164. Docket 91-NM-159-AD. Applicability: Model SF-340A and 340B series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a fire during the refueling process, accomplish the following: (a) Within 30 days after the effective date of this AD, disconnect the lighting to the refuel/defuel panel lights as follows: (1) Remove the refuel/defuel panel assembly, P/N 7239160-502, -503, or -504, as applicable, in accordance with the Airplane Maintenance Manual (AMM) 28-21-05. (2) With the refuel/defuel panel removed, loosen the four screws securing the lighting panel to the front, and remove the rear cover. (3) Locate the lighting panel Jack 30 QA under the rear cover, and remove the screw securing the wire QA636-20. Remove the wire from Jack 30 QA, and reinstall the screw. (4) Cap and stow wire QA636-20, and reassemble the refuel/defuel panel.(5) Placard the lighting panel with "Lights inop." (6) Reinstall and test the refuel/defuel panel in accordance with AMM 28-21-05. (b) An 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may 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 the airplane to a location where the requirements of this AD can be accomplished. (d) This amendment (39-8164, AD 92-03-09) becomes effective on March 18, 1992.
2001-26-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of a main deck cargo door hinge; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier; as applicable. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
77-16-10: 77-16-10 EDO-AIRE MITCHELL: Amendment 39-3002. Applies to Model NSD-360 Navigation Systems containing any of the following Navigation Situation Display instruments: 52D136-0020, 52D136-0120, 52D136-0220, 52D136-1020, 52D136-1120, 52D136-1220, 52D137-1020, 52D137-1120, and 52D137-1220, when used with VOR/LOC converters other than the Edo-Aire Mitchell 1C707 and 1C707-1 converters. Compliance with (a) or (c) is required within the next 50 hours in service after the effective date of this AD, unless already accomplished. (a) Install a placard stating "NSD-360 NOT APPROVED AS PRIMARY VOR DISPLAY FOR IFR NAVIGATION PRIOR TO COMPLIANCE WITH EAM MB-13." (b) The placard described in subparagraph (a) is to be installed as close as practical to the affected navigation situation display and remain there until EAM NAV Flag Adapter P/N 1C775 is installed as in (c) below, at which time the placard is to be removed. EAM placard, P/N 13A895 specified by EAM Service Bulletin MB-13, is to be used to comply with (a). (c) Install EAM NAV Flag Adapter, P/N 1C775, in accordance with installation instruction items 1 through 5, pages 2 and 3 of EAM Service Bulletin MB-13 revised May 3, 1977. (d) The manufacturer's instructions identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(l). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Director, Products and Service, Edo-Aire Mitchell, P.O. Box 610, Municipal Airport, Mineral Wells, Texas 76067, Telephone No. 817-325-2517. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, 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 Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective September 8, 1977.
77-21-01: 77-21-01 BELL HELICOPTER TEXTRON: Amendment 39-3054. Applies to all Model 47 helicopters with tail rotor gear boxes, part number 47-640-075-1 or 47-640-075-5, installed. NOTE: Retrofit kits incorporating these gear boxes or the associated internal gears and bearings delivered from Bell Helicopter Textron after December 1, 1976, have been verified to be in compliance with this airworthiness directive and will not require inspection and/or further retrofit. Compliance is required within the next 100 hours time in service after the effective date of this Airworthiness Directive, unless already accomplished. To minimize the possibility of loss of directional control of the helicopter resulting from failure of the bearing, part number 47-620-629-3 or 47-620-629-5, or failure of the input pinion shaft, part number 47-645-205-3, located in the tail rotor gear box, part number 47-640-075-1 or 47-640-075-7, conduct the inspection and replacement activities prescribed by paragraphs 1, 2, 2a, 2b, 3, and 4 of Bell Helicopter Textron Service Bulletin No. 47-77-1, dated February 14, 1977, or later FAA approved revision. Comments in paragraph 5 and 6 of this bulletin involving warranties, replacement part sources, or reporting activities, are not a part of this Airworthiness Directive. After accomplishment of paragraphs 1, 2, 3, and 4 of Service Bulletin No. 47-77-1, reassemble and reinstall the tail rotor gear box in accordance with the Maintenance and Overhaul Instruction for the applicable model helicopters. 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 by requesting same from Service Manager, Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas, 76101. These documents may also be examined at Officeof the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, 76106, and the Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C., 20591. Equivalent means of compliance with the modifications prescribed by this Airworthiness Directive may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas, 76101. This amendment becomes effective November 14, 1977.
2016-21-01: We are adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron (Bell) Model 430 helicopters. This AD requires establishing a life limit for a certain main rotor hub attachment bolt (bolt) and removing from service each bolt that has met or exceeded its life limit. This AD was prompted by a documentation error that omitted the life limit of a certain part-numbered bolt from the Airworthiness Limitations section of the maintenance manual. The actions of this AD are intended to establish a life limit for a certain part-numbered bolt to prevent failure of a bolt, failure of a main rotor hub, and subsequent loss of control of a helicopter.
89-24-05: 89-24-05 BOEING: Amendment 39-6395. Docket No. 89-NM-213-AD. \n\n\tApplicability: Model 767 series airplanes, listed in Boeing Alert Service Bulletin 767- 31A0029, dated March 23, 1989, certificated in any category. \n\n\tCompliance: Required within 45 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent binding of the pilot's control wheel, accomplish the following: \n\n\tA.\tDeactivate the control wheel Aircraft Integrated Data System (AIDS) by removing the position transducer, crank assembly, and rod assembly in accordance with Boeing Alert Service Bulletin 767-31A0029, dated March 23, 1989. \n\n\tB.\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, Seattle 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 concuror comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6395, AD 89-24-05) becomes effective on December 1, 1989.
2005-16-13: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. This AD requires a one-time general visual inspection for any damaged wiring, splice, connector, and pins for the fuel standby feed pumps and replacement of any damaged wiring, splice, connector, or pin. This AD also requires replacement of the power and ground wires for the fuel standby feed pumps. This AD results from reports of evidence of overheating found on the feeder wires of the left and right fuel standby feed pumps. We are issuing this AD to detect and correct damaged wiring for the fuel standby feed pumps, which could result in an ignition source in an area where fuel vapor may be present, and a consequent fire or explosion.
2016-19-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by a determination that a certain fastener type in the fuel tank walls has insufficient bond to the structure, and an electrical wiring short could cause arcing to occur at the ends of fasteners in the fuel tanks. This AD requires the installation of new clamps and polytetrafluoroethylene (TFE) sleeves on the wire bundles of the front spars and rear spars of the wings. This AD also requires inspecting the existing TFE sleeves under the wire bundle clamps for correct installation, and replacement if necessary. We are issuing this AD to prevent potential ignition sources in the fuel tank in the event of a lightning strike or high-powered short circuit, and consequent fire or explosion.