Results
99-08-21: This amendment adopts a new airworthiness directive (AD) that applies to any aircraft equipped with Puritan-Bennett Aero Systems Company (Puritan-Bennett) C351-2000 series passenger oxygen masks and portable oxygen masks. This AD requires inspecting the passenger and portable oxygen masks for tears around the face cushion adjacent to the inner mask housing, and replacing or repairing any torn passenger or portable oxygen mask. This AD is the result of reports received from three airplane manufacturers of defective oxygen masks. The actions specified by this AD are intended to prevent reduced oxygen consumption when passengers are required to use defective oxygen masks, which could result in passenger injury.
99-08-20: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires a one-time inspection to detect cracking of the bulkhead at fuselage station (FS) 1363 at butt line 42.5, and repair or additional inspections, if necessary. This amendment adds repetitive inspections to detect cracking of the bulkhead web and bulkhead cap (frame cap) at FS 1363, and repair, if necessary. This amendment is prompted by reports that additional, more extensive, fatigue cracking was found in the bulkhead web and cap. The actions specified by this AD are intended to detect and correct cracking of the bulkhead web and cap, which could result in reduced structural integrity of the fuselage.
2013-19-23: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a new revision to the airworthiness limitations of the maintenance planning data (MPD) document. This AD requires revising the maintenance program to update inspection requirements to detect fatigue cracking of principal \n\n((Page 61174)) \n\nstructural elements (PSEs). We are issuing this AD to detect and correct fatigue cracking of various principal structural elements (PSEs), which could adversely affect the structural integrity of these airplanes.
99-08-11: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Airworthiness Limitations Section (ALS) and Maintenance Scheduling Section (MSS) of the Instructions for Continued Airworthiness (ICA) in the Time Limits Manual (Chapter 05-10-00) of the Engine Manuals for International Aero Engines AG (IAE) V2500-A1/-A5/-D5 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2013-19-21: We are superseding airworthiness directive (AD) AD 2012-04-13, for all Rolls-Royce plc (RR) model RB211 Trent 553-61, 553A2-61, 556- 61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61; and RB211 Trent 768-60, 772-60, and 772B-60; and RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17; and RB211-524G2-T-19, -524G3-T- 19, -524H-T-36, and -524H2-T-19 turbofan engines that have a high- pressure (HP) compressor stage 1 to 4 rotor disc installed, with a certain part number (P/N) installed. AD 2012-04-13 required repetitive inspections of the axial dovetail slots and follow-on corrective action depending on findings. This new AD expands the population of affected parts. This AD also changes, for the purposes of this AD, the definition of ``engine shop visit.'' This AD was prompted by reports of additional affected HP compressor rotor discs that require the same action. We are issuing this AD to detect cracks in the HP compressor stage 1 and 2 disc posts, which could result in failure of the disc post and HP compressor blades, damage to the engine, and damage to the airplane.
92-22-04: 92-22-04 BRITISH AEROSPACE: Amendment 39-8390. Docket No. 92-NM-58-AD. Applicability: Model DH/HS/BH 125 series airplanes, excluding all turbo fan engine-powered Model 125-600A, 125-700A, 125-800A, and 125-1000A series airplanes; as listed in British Aerospace Service Bulletin SB 28-87, dated December 31, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent an in-flight fire hazard in the rear equipment bay, accomplish the following: (a) Within 6 months after the effective date of this AD, accomplish a visual inspection for proper alignment of fuel feed pipes at pipe joint couplings, in accordance with British Aerospace Service Bulletin SB 28-87, dated December 31, 1991. (1) If misalignment is detected outside the specifications cited in the service bulletin, prior to further flight, correct the alignment by installing an "O" ring modification and fuel pipe clamping modification, in accordancewith the service bulletin. (2) If misalignment is not detected outside the specifications cited in the service bulletin, no further action is necessary. (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 may add 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, 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) The inspection and modification shall be done in accordance with British Aerospace Service Bulletin SB 28-87, dated December 31, 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 November 24, 1992.
2010-10-06: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Uncontained APU [auxiliary power unit] generator failures on ground have occurred on Airbus A330 aircraft in service. APU generator design is common to all A330 and A340 aircraft. Preliminary investigations confirmed that these failures have resulted in structural damage to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU firewall, reducing its fire extinguishing capability and potentially leading to a temporary uncontrolled fire. Although the root cause has not yet been determined, the investigation showed a sequence of events where a collapse of the Drive End Bearing (DEB) leads to an uncontained failure. Evidence has also shown that the DEB failures are not instantaneous, and therefore, the detection of small debris could indicate early stage of a DEB failure. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 17, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 17, 2010. On June 26, 2007 (72 FR 31973, June 11, 2007), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.
91-12-10: 91-12-10 BEECH: Amendment 39-7021. Docket No. 90-CE-57-AD. Applicability: Models B200, B200C, and B200T airplanes (serial numbers (S/N) BB-1158, S/N BB-1167, S/N BB-1193 through BB-1203, S/N BB-1207 through BB-1312, S/N BB-1314 through BB- 1334, S/N BL-124 through BL-132, and S/N BT-33), and Models 300 and 300LW airplanes (S/N FA-2 through FA-190), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent in-service fatigue failures and to allow continued operation of the interim safe life limit of 15,000 hours TIS for the lower forward wing attach fittings, accomplish the following: (a) For Model 300LW airplanes, upon the accumulation of 8,300 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, modify the wing spar attachment by installing Beech Kit No. 101-4050. (b) For Model 300 airplanes, upon the accumulation of 9,000 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, modify the wing spar attachment by installing Beech Kit No. 101-4050. (c) For Models B200, B200C, and B200T airplanes, upon the accumulation of 9,500 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, modify the wing spar attachment by installing Beech Kit No. 101-4050. NOTE: Section 4-00-00 of the Beech 200 and 300 series maintenance manuals contains information related to this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (f) All persons affected by this directive may obtain the service kit and maintenance manual information referred to herein upon request to the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine information that is applicable to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-7021, AD 91-12-10) becomes effective on July 15, 1991.
95-10-07: 95-10-07 BELL HELICOPTER TEXTRON, INC. : Amendment 39-9224. Docket No. 95-SW-02-AD. Applicability: Model 205A, 205A-1, and 204B helicopters, with a 42-degree tail rotor drive gearbox assembly (42-degree gearbox), part number (P/N) 204-040-003-023, or -037, installed, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (e) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the 42-degree gearbox, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, after the effective date of this AD, verify that the tail rotor control system is rigged in accordance with the applicable maintenance manual. (b) Before further flight, and thereafter at intervals not to exceed 400 torque events, disassemble the affected 42-degree gearbox and inspect for cracks at the roots of the gear teeth on the pinion, P/N 204-040-500-007 or -009, and gear, P/N 204-040-500-008 or -010, using a fluorescent penetrant inspection method in accordance with the applicable maintenance manual. Only post emulsified fluorescent penetrant inspection materials (Type I, Method B or D, Sensitivity Level 3 or greater) are approved for use. A torque event is defined as a takeoff or a lift (internal or external). (c) If any crack is found at the roots of the gear teeth on the pinion or gear, replace the pinion or gear with an airworthy pinion or gear in accordance with the applicable maintenance manual. (d) Create a component history card for the 42-degree gearbox. Record the number of torque events on a daily basis. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when approved by the Manager, Rotorcraft Certification Office, FAA, Rotorcraft Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager,Rotorcraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) This amendment becomes effective on May 26, 1995.
96-04-09: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to detect the presence of a drain hole in certain mounting frames of the auxiliary power unit (APU). If a drain hole is present, the AD requires an inspection to detect corrosion of the mounting frame, and eventual replacement of the mounting frame. This amendment is prompted by a report indicating that corrosion was found on a number of mounting frames of the APU. The actions specified by this AD are intended to prevent such corrosion, which could lead to failure of the frame and consequently render the APU inoperative and/or create a potential fire hazard.