Results
98-26-24: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that currently requires replacement of certain outboard and inboard wheel halves with improved wheel halves; cleaning and inspecting certain outboard and inboard wheel halves for corrosion, missing paint in large areas, and cracks; and repair or replacement of the wheel halves with serviceable wheel halves, if necessary. That AD was prompted by a review of the design of the flight control systems on Model 737 series airplanes. This amendment requires that the actions be accomplished in accordance with revised service information. The actions specified by this AD are intended to prevent failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures; and consequent reduced controllability of the airplane.
99-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney (PW) JT8D and JT3D series turbofan engines. This action requires operators to remove and replace with serviceable parts, certain stage 7 through stage 15 high-pressure compressor (HPC) disks identified by part number and serial number. This amendment is prompted by a report of an uncontained failure of a stage 8 HPC disk during a takeoff roll that resulted in damage to the airplane. The actions specified in this AD are intended to prevent the failure of a high-pressure compressor disk due to Cadmium embrittlement, resulting in uncontained engine failure and damage to the airplane. Comments for inclusion in the Rules Docket must be received on or before March 1, 1999.
92-17-12: 92-17-12 BRITISH AEROSPACE: Amendment 39-8341. Docket No. 92-NM-64-AD. Applicability: Model HS/BH 125-600A, HS 125-700A, and BAe 125-800A series airplanes; as listed in British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing and a resultant fire, accomplish the following: (a) Within 180 days after the effective date of this AD, modify the cabin and toilet fluorescent lighting systems, in accordance with British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who mayadd comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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) The modification shall be done in accordance with British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 28, 1992.
88-03-53: 88-03-53 PRATT & WHITNEY: Amendment 39-6270. Final copy of telegraphic AD T88-03-53 which was issued on February 3, 1988. Applicability: Pratt & Whitney (PW) PW4152 turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent the inability to reduce engine thrust that can lead to asymmetrical power and possible aircraft directional control problems, accomplish the following: (a) For fuel metering units (FMU), Part Number (P/N) 51T217 or 53T419, with 140 operating hours or greater on the effective date of this Airworthiness Directive (AD), since new or since refurbished with new sector gears and a new or reconditioned resolver pinion gear, accomplish the following: Remove and replace the FMU with a new or serviceable unit in accordance with the instructions in Appendix I of this AD within 10 operating hours after the effective date of this AD. (Appendix I refers to Pratt & Whitney Alert Service Bulletin Number PW4ENG A73-37, Revision 1, dated January 26, 1988, which is not reprinted in this AD.) (b) For FMU's, P/N 51T217 or 53T419, with less than 140 operating hours on the effective date of this AD, since new or since refurbished with new sector gears and a new or reconditioned resolver pinion gear, accomplish the following: Remove and replace the FMU with a new or serviceable unit in accordance with the instructions in Appendix I of this AD on or before accumulating 150 operating hours since new or since refurbished with new sector gears and a new or reconditioned resolver pinion gear. (c) Thereafter, remove the FMU, P/N 51T217 or 53T419, and install a new or serviceable unit in accordance with the instructions in Appendix I of this AD at intervals not to exceed 150 FMU operating hours in service. NOTE: PW ASB Number PW4ENG A73-37, Revision 1, dated January 26, 1988, further recommends removal and replacement of the FMU whenever the engine parameters indicate an impending hot start or excessive ground idle rotor speed (N2 in excess of 68 percent at normal bleed air extraction). FMU removal and replacement due to these operating characteristics are not mandated by this AD at this time. (d) 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. (e) 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 specified in this AD may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The FMU replacement shall be done in accordance with the instructions in Appendix I of this AD. This amendment (39-6270, AD 88-03-53) becomes effective on September 1, 1989, as to all persons except those persons to whom it was made immediately effective by individual Telegraphic AD T88-03-53, issued February 3, 1988, which contained this amendment.
2013-14-10: We are superseding airworthiness directive (AD) 2010-11-02 for all Gulfstream Aerospace LP (Type Certificate Previously Held by Israel Aircraft Industries, Ltd.) Model Gulfstream 100 airplanes, and Model Astra SPX and 1125 Westwind Astra airplanes. AD 2010-11-02 required amending the airplane flight manuals (AFMs) to include additional procedures for verifying complete closure and locking of the main entry door (MED). AD 2010-11-02 also required modifying the warning and caution lights panel (WACLP), changing the WACLP and MED wiring, changing the wiring harness connecting the MED to the WACLP, and revising the log of modification of the AFM if necessary. This new AD revises the compliance time and removes an airplane from the applicability. This AD was prompted by a report of a MED opening in flight on an unmodified airplane. We are issuing this AD to prevent incomplete closure of the MED, which may result in the door opening in flight and possible separation of the door, causing damage to the airplane structure and left engine by flying debris and objects.
2013-15-02: We are superseding Airworthiness Directive (AD) 2008-10-03 for Bell Helicopter Textron Helicopters (Bell) Model 204B, 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters. AD 2008-10-03 required certain checks and inspections of each tail rotor blade assembly (T/R blade) at specified intervals and repairing or replacing, as applicable, any cracked or damaged T/R blade. Since we issued AD 2008-10-03, an accident attributed to a T/R failure occurred. This new AD retains the requirements of AD 2008-10-03 and adds a second, more detailed inspection that allows for an earlier detection of a crack or other damage in a T/R blade. These actions are intended to prevent a failure of the T/R blade and subsequent loss of helicopter control.
86-03-03: 86-03-03 PRATT & WHITNEY: Amendment 39-5219. Applies to Pratt & Whitney model JT9D-7R4D, 7R4E, and -7R4E4 turbofan engines. Compliance is required as indicated unless already accomplished. To prevent deterioration of fuel nozzle flow and spray cone angle characteristics which could lead to engine surge, overtemperature, or the inability to restart inflight, accomplish the following: (a) Conduct a flow check on JT9D-7R4 series engine incorporating PW P/N 792842 and/or 794731 fuel nozzles following any on-wing cleaning procedure prior to returning the aircraft to service in accordance with PW Maintenance Manual P/N 785050, Chapter 73-13-07, Cleaning/Painting Section as revised by Temporary Revision 73-3, or FAA approved equivalent. (1) A flow reduction of 10 percent or less is acceptable. (2) A flow reduction greater than 10 percent but less than 20 percent requires selected fuel nozzles to be replaced with new or ultrasonically cleaned nozzles within 300flight cycles. The fuel nozzles may be replaced in quantities and locations as needed to restore the flow to 10 percent flow reduction or less. (3) A flow reduction of 20 percent or greater requires selected fuel nozzles to be replaced with new or ultrasonically cleaned nozzles within 25 flight cycles. If there have been any unresolved aborted ground starts (since the last cleaning and flow check) that are not attributed to an ignition system fault or a mechanical problem which is unrelated to the fuel nozzles, fuel nozzles must be selectively replaced within 5 cycles. The fuel nozzles may be replaced in quantities and locations as needed to restore the flow to 10 percent flow reduction or less. (b) Ground starts must be initiated using single ignition, either ignition selector position 1 or 2. If an aborted start is experienced using single ignition that is related to a fuel nozzle problem, the engine may be started on the opposite ignition system or dual ignition and the fuel nozzles must be cleaned and flow checked within 25 flight cycles in accordance with PW Maintenance Manual P/N 785050, Chapter 73-13-07, Cleaning/Painting Section as revised by Temporary Revision 73-3, or FAA approved equivalent. The flow check limits in Paragraph (a) are applicable to Paragraph (b). 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, may adjust the compliance time specified in this AD. PW Maintenance Manual P/N 785050, Chapter 73-13-07, Cleaning/Painting Section as revised by Temporary Revision 73-3 is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a)(1). (Boeing Maintenance Manual, Chapter 73-11-05, Cleaning/Painting Section is an equivalent means of compliance.) All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. This document also may be examined at the Office of the Regional Counsel, Rules Docket 85-ANE-8, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on March 14, 1986.
99-01-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect discrepancies of the diagonal brace lugs of the engine strut, and rework of the diagonal brace lugs, if necessary. That AD also provides an option to defer the rework for certain cases by accomplishing repetitive inspections and resealing the bushing. That AD also provides for an optional terminating modification for the repetitive inspections. This amendment adds a requirement to repetitively inspect a new area of the diagonal brace of the engine strut. For certain airplanes, this amendment also adds new repetitive inspections of the subject area and requires that certain previously required repetitive inspections be accomplished at reduced intervals. This amendment is prompted by reports of fatigue or stress corrosion cracking in new areas of the diagonal brace. The actions specified inthis AD are intended to prevent such fatigue or stress corrosion cracking, which could result in failure of the strut and consequent separation of the engine from the airplane.
2013-15-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD requires either removal or inspection of the Honeywell fixed emergency locator transmitter (ELT), and corrective action if necessary. This AD was prompted by a report of a fire involving a Honeywell fixed ELT. We are issuing this AD to prevent a fire in the aft crown of the airplane, or to detect and correct discrepancies within the ELT that could cause such a fire.
92-10-04: 92-10-04 BRITISH AEROSPACE: Amendment 39-8238. Docket No. 91-NM-261-AD. Applicability: Model DH/BH/HS 125 series airplanes, excluding Model 125-700A, -800A, and -1000A series airplanes; as listed in British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wings, accomplish the following: (a) Within 3 months after the effective date of this AD, visually inspect left and right wing upper skins for corrosion beneath the boundary layer fence, in accordance with British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991. (1) If any corroded parts are found in which the corrosion is within the limits specified in British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991, prior to further flight, repair in accordance with that service bulletin. (2) If any corroded parts are found in which the corrosion exceeds the limits specified in British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) Within 10 days after accomplishing the inspection required by paragraph (a) of this AD, submit a report of inspection findings to British Aerospace, in accordance with Appendix A of British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991. Report all findings, including nil defects to: Service Support Manager, BAe 125, British Aerospace (Commercial Aircraft) Ltd., Corporate Aircraft Division (H121), Customer Support Department, Comet Way, Hatfield, Hertfordshire, AL 10 9TL, England; fax 0707 251216; telex 21429 (BAA HPS-G). Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork ReductionAct of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) 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. 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. (d) 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. (e) The inspections and repairs shall be done in accordance with British Aerospace Service Bulletin S.B. 57-73, dated July 30, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 20041-0414. 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. (f) This amendment becomes effective on June 11, 1992.