Results
92-07-01: 92-07-01 SAAB-SCANIA: Amendment 39-8197. Docket No. 91-NM-53-AD. Applicability: Model SF-340 series airplanes, Serial Numbers 003 through 138, certificated in any category. Compliance: Required within one year after the effective date of this AD, unless previously accomplished. To prevent unexpected loss of nose wheel steering and brakes during taxi, accomplish the following: (a) Remove main/emergency dual pressure indicator 3DB, Part Number (P/N) 522796 and install main/emergency dual pressure indicator 3DB, P/N 523250, in accordance with SAAB Service Bulletin SF340-29-004, Revision 1, dated November 9, 1990. (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 shall 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 airplanes to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with SAAB-Scania Service Bulletin SF340- 29-004, Revision 1, dated November 9, 1990, which includes the following list of effective pages: Page Number Revision Level Date 1, 2, 4, 5 1 November 9, 1990 3 (Original) September 15, 1988 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 SAAB-Scania AB, Product Support, S- 581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) Thisamendment becomes effective on April 28, 1992.
2013-22-12: We are adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-800A, DG-800B, DG-500MB gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a defective starter motor control unit, which could activate the starter motor without pressing the starter button. We are issuing this AD to require actions to address the unsafe condition on these products. [[Page 67014]]
99-12-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T99-12-52 that was sent previously to all known U.S. owners and operators of all Boeing Model 727 series airplanes by individual telegrams. This AD requires a boost pump dry bay inspection to detect leakage of fuel through an arced-through conduit, and corrective action, as necessary. This AD also requires repetitive detailed visual inspections of the in-tank fuel boost pump wiring to detect chafing of the wire insulation, evidence of electrical arcing, or arc-through of the conduit wall on Model 727 series airplanes, and applicable corrective action; and installation of sleeving over the in- tank fuel boost pump wires as a method to protect the wiring from chafing. This action is prompted by reports of severe wear of in-tank fuel boost pump wiring, and arc-through of the surrounding conduit on two Model 727 series airplanes. The actions specified by this AD are intended toprevent fuel tank explosion resulting from arc-through of the fuel boost pump wiring conduits.
99-13-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires repetitive inspections to detect cracking of the upper cutout and lower flange of the outboard support assembly of the flaperons on the wings; and corrective actions, if necessary. This amendment also provides an optional terminating action for the repetitive inspections. This amendment is prompted by results of flight testing conducted by the manufacturer indicating that high engine thrust conditions during takeoff cause excessive cyclic loads and could lead to fatigue cracking of the outboard support of the flaperon. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in fracture of the flaperon support structure, loss of the flaperon, and consequent reduced controllability of the airplane.
2013-20-13: We are adopting a new airworthiness directive (AD) for certain Bell Model 206B and 206L helicopters. This AD requires installing a placard beneath the engine power dual tachometer and revising the operating limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady- state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.
99-13-02: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters, that currently requires conducting a filter clogging warning test, and, if necessary, replacing a jammed valve with an airworthy valve. This amendment requires the same corrective actions required by the existing AD; however, the applicability is reduced to encompass only certain part-numbered fuel filters. This amendment is prompted by jammed fuel filter by-pass valves and new information that justifies a reduction in the applicability of the superseded priority letter AD. The actions specified by this AD are intended to prevent engine power loss due to fuel starvation, which could cause one or both engines to flameout and a subsequent forced landing.
89-22-07: 89-22-07 PRATT & WHITNEY: Amendment 39-6344. Applicability: Pratt & Whitney (PW) JT3D-3B and JT3D-7 turbofan engines approved for return to service by Jet Power, Inc (JPI), FAA Repair Station No. 705-70, located at 4275 Northwest 77th Avenue, Miami, Florida, identified by serial number (S/N) as follows: 630197 631540 631996 632276 632282 632285 632339 632340 632346 632351 632408 632478 632481 632487 632749 632842 632846 632852 632962 632966 632968 632973 633040 633495 633541 633558 633564 633607 633609 633615 633669 633732 633742 633744 634616 642390 642490 642512 642901 642910 642914 643332 643471 642715 643803 643812 643899 643904 643973 644047 644071 644131 644200 644218 644306 644359 644667 644756 644953 644973 645017 645030 645051 645088 645128 645145 645177 645214 645294 645370 645401 645407 645570 645675 645753 645769 645785 645854 645865 645913 645915 645977 645999 646001 667054 667677 667736 667792 667879 667932 667979 668042 668103 668229 668312 668331 668373 668430 668557 668594 668603 668609 668658 668678 668827 668877 669156 669252 669324 669360 669375 669377 669411 669425 669484 669564 669583 669644 669690 669793 669797 669801 670744 671102 671133 671141 671233 671254 671340 671391 671425 675803 678988 678994 678999 688430 Compliance: Required within the next 30 calendar days after the effective date of this AD, unless already accomplished. To ensure the continuing structural integrity and certificated performance capabilities of JT3D-3B and JT3D-7 turbofan engines, accomplish the following: (a) Remove from service those engines identified above. (b) Engines removed from service in accordance with paragraph (a) above may be returned to revenue service by accomplishing either one of the two following requirements: (1) Accomplish the overhaul manual requirements on all parts, sub-assemblies, accessories, and components installed on the engine and, if any of the engines or components of the engines referred in paragraph (a) have been in an accident, accomplish the pertinent overhaul manual special check and inspection requirements. The engine overhaul and special inspection requirement must be accomplished in accordance with the requirements of Pratt & Whitney JT3D-3B Overhaul Manual, Part Number (P/N) 411568, Revision 78, dated December 15, 1988, or Pratt & Whitney JT3D-7 Overhaul Manual P/N 615105, Revision 50, dated December 15, 1988, as applicable. NOTE: The Light Overhaul Manual requirements, included in the above overhaul manuals, are not applicable in this case. (2) Submit to the FAA, Manager, Engine Certification Office, through the cognizant FAA Airworthiness Inspector, all the pertinent records identified below for review, and obtain a written FAA approval prior to returning an engine to service: (i) If the parts, sub-assemblies, accessories, or other components of an engine approved for return to service by JPI were subjected to overhaul or maintenance activities during the last shop visit at JPI, provide records establishing the origin and/or the prior service history of the subject parts. If the determination of the origin of such parts leads to other engines, the records for reason of removal from service, and if available, trend monitoring data for those engines must also be included. Provide records of accomplishment of the required inspections, checks, tests, as applicable in accordance with engine manual requirements that establish the components' airworthiness. (ii) A list of all life limited components by S/N, service history, and current status as required by FAR Part 121, Section 380, or FAR Part 91, Section 173, as appropriate. (iii) All repair or overhaul records, concerning the last shop visit at JPI, as required by FAR Part 121, Section 380, or FAR Part 91, Section 173, as appropriate. (iv) Substantiating evidence that the work performed during the last shop visit at JPI was done in accordance with FAA approved data as required by the FAR's. (v) Engine acceptance test data or engine "on-wing" test data, accomplish after repair or overhaul, whichever is applicable. (vi) Engine operation trend monitoring data, if available, for the current engine installation. (vii) A list by P/N or S/N of any engine, part, sub-assembly, accessory, or component acquired from JPI that has been known to have been involved in an accident. NOTE: If engine owners, operators, or cognizant Civil Aviation Authorities outside the United States wish to have the FAA's assistance in this effort, they may contact the FAA at the following address: Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, Attention: Manager, Engine Certification Office, ANE-140, 12 New England Executive Park, Burlington, Massachusetts 01803. Information collection requirements contained in the amendment to Section 39.13 have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96-511) and have been assigned OMB Control No. 2120-0056. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times in this AD, may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England ExecutivePark, Burlington, Massachusetts 01803. The engine overhaul and special inspection requirements shall be done in accordance with PW JT3D-3B Overhaul Manual P/N 411568, Revision 78, dated December 15, 1988, or JT3D-7 Overhaul Manual P/N 615105, Revision 50, dated December 15, 1988, as applicable. The sections of these manuals pertinent to Light Overhaul are not applicable. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Pratt & Whitney, Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803. This amendment (39-6344, AD 89-22-07) becomes effective on October 31, 1989.
99-12-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-200C series airplanes, that currently requires a one-time external detailed visual inspection to detect cracks of the fuselage skin in the lower lobe cargo compartment; repetitive internal detailed visual inspections to detect cracks of the frames in the lower lobe cargo compartment; and repair of cracked parts. That AD also provides for an optional preventative modification that constitutes terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating modification. This amendment is prompted by reports of cracking in the body frames between stringers 19 left and 25 left and at body stations 360 to 500B. The actions specified by this AD are intended to prevent opening or loss of the cargo door during flight, and consequent rapid decompression of the airplane.
83-07-12 R1: 83-07-12 R1 PILATUS BRITTEN-NORMAN LTD.: Amendment 39-4615. Applies to BN-2, BN2A, and BN-2B Islander Series equipped with wing tip fuel tanks and BN-2A MK. III Trislander Series (all Serial Numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To detect erosion of the wing tip tank fuel transmitter floats, which could restrict fuel flow and result in the loss of power, accomplish the following: a) Within the next 100 hours time-in-service after the effective date of this Airworthiness Directive (AD) and thereafter at intervals not to exceed 100 hours time-in-service: 1) Remove and visually inspect the wing tip tank fuel transmitter floats for evidence of cracking, fretting, or erosion in accordance with the instructions provided in the "Inspection and Rectification" section of Pilatus Britten-Norman Service Bulletin (SB) No. BN- 2/SB.154, Issue 1, dated February 12, 1982, (hereinafter referred to as the SB) or an FAA approved equivalent. 2) If any fuel transmitter float is found with cracks, fretting, or erosion during the accomplishment of the visual inspection in accordance with paragraph a)1) of this AD, prior to further flight, replace the float with a serviceable unit of the same part number and continue the repetitive visual inspections in accordance with paragraph a)1) of this AD. 3) If any fuel transmitter float is found with excessive erosion during accomplishment of the visual inspection in accordance with paragraph a)1) of this AD, prior to further flight, drain the affected tank and clean the filters, including also the fuel supply system, through the auxiliary pumps, to the engine together with all fuel filters enroute. 4) Reinstall wing tip tank fuel transmitters in accordance with instructions provided in the "Inspection and Rectification" section of the SB. b) The intervals between repetitive inspections required by this AD may be adjustedup to 10 percent of the specified inspection intervals to allow them to be accomplished concurrent with other scheduled maintenance on these airplanes. c) Aircraft may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 11, 1983.
88-04-03: 88-04-03 AEROSPATIALE: Amendment 39-5846. Applies to Model ATR-42 series airplanes, as listed in Service Bulletin ATR42-23-0002, Revision No. 1, dated March 11, 1987, certificated in any category. Compliance is required within one year of the effective date of this AD, unless previously accomplished. To prevent the loss of recorded information by continued operation of the Digital Flight Data Recorder (DFDR) and Cockpit Voice Recorder (CVR) after an accident, accomplish the following: A. Modify the DFDR and CVR power supply logic in accordance with Aerospatiale Service Bulletin ATR42-23-0002, Revision No. 1, dated March 11, 1987. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued inaccordance 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, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 21, 1988.