Results
2004-05-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires a one-time inspection to detect abrasion damage and installation discrepancies of the wire bundles located below the P37 panel, and corrective action if necessary. For airplanes already subject to the existing AD, this amendment requires inspecting to determine whether the existing location of a certain wire support standoff is adequate, relocating the wire support standoff if necessary, installing protective sleeving over the wire bundles, and installing wire bundle support clamps if necessary. This amendment also expands the applicability of the existing AD to include additional airplanes, and require inspecting the sleeving on certain wire bundles, and accomplishing corrective action if necessary, on those airplanes. The actions specified by this AD are intended to detect and prevent abrasion damage and correct installation discrepancies of the wire bundles located below the P37 panel, which could result in arcing to structure and consequent fire or loss of function of affected systems. This action is intended to address the identified unsafe condition.
2001-09-10: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes equipped with Pratt & Whitney Model PW4400 series engines, that currently requires revising the Airplane Flight Manual (AFM) to advise the flight crew of applicable operational limits. This amendment corrects a typographical error in one paragraph of the existing AD that resulted in a reference to an incorrect engine fan blade which is not subject to the requirements of that paragraph. The actions specified in this AD are intended to ensure that the flight crew is informed of applicable limitations in airplane performance, and to prevent reduced acceleration and climb performance relative to performance data in the AFM, which could result in the airplane overrunning the end of the runway during takeoff or landing, or impacting obstacles or terrain. This action is intended to address the identified unsafe condition.
2024-10-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports of operators finding frequent and severe damage to the blowout vent grilles throughout the lower lobe cargo compartment. This AD requires repetitive detailed inspections of certain decompression panels and pressure equalization valves, as applicable, in the forward and aft lower lobe cargo compartments for damage, and applicable on- condition actions. For certain airplanes, this AD also requires installation of decompression panels with billet grilles. For other certain airplanes, this AD also requires replacement of a certain soft bulkhead with a rigid bulkhead. For certain other airplanes, this AD requires installation of doublers to a certain bulkhead assembly panel. The FAA is issuing this AD to address the unsafe condition on these products.
86-25-52 R1: 86-25-52 R1 AEROSPATIALE: Telegram issued December 19, 1986, as amended by Amendment 39-5655. Applies to all Model ATR-42 airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To minimize the potential hazards associated with in-flight icing conditions or the operation of ice removal systems, accomplish the following before further flight into known or forecast icing conditions: A. Revise the Airplane Flight Manual (AFM) as follows: 1. Replace AFM Limitations, Power Plant, 2-04, Page 4, with the Revision dated December 1986, and 2. Replace AFM Normal Procedures, Flight Conditions, 3-02, Page 1, with the Revision dated December 1986. B. Revise Panel 24.VU to change the definition of airframe ice protection system as originally designated "Deicing" by permanently covering the term "deicing" on panel 24.VU. C. Or, as an alternate means of compliance: 1. Modify the stall warning system in accordance with Aerospatiale Service Bulletin ATR-42-30-0011, dated March 19, 1987. 2. Remove permanent cover of term "Deicing" on panel 24.VU. 3. Replace AFM Limitations Power Plant, 2-04, Page 4, with the Revision dated October 1986, or FAA-approved AFM revisions dated later than December 1986. 4. Replace AFM Normal Procedures Flight Conditions, 3-02, Page 1, with the Revision dated October 1986, or FAA approved AFM revisions dated later than December 1986. D. 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. E. 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 modifications required by this AD. All persons affected by this directive who have not already received the appropriate 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 the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5655, becomes effective July 10, 1987, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T86-25-52, issued December 19, 1986.
85-13-02: 85-13-02 BOEING: Amendment 39-5085. Applies to Boeing Model 767 series airplanes certificated in all categories, as enumerated in Boeing Service Bulletin No. 767-21-0041, Revision 1, dated February 15, 1985. To assure the effectiveness of the cargo compartment fire protection system, accomplish the following, unless already accomplished. \n\n\tA.\tWithin 90 days after the effective date of this AD, revise the wiring and test the operation of the aft equipment/lavatory/galley ventilation fans and the left and right air conditioning pack flow controls in accordance with Boeing Service Bulletin 767-21-0041, Revision 1, dated February 15, 1985, or later FAA approved revision. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base forthe accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the above specified service bulletin from the manufacturer may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, WA 98124. It may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis Amendment becomes effective July 28, 1985.
2005-08-12: The FAA adopts a new airworthiness directive (AD) for certain CENTRAIR 101 series gliders. This AD requires you to replace non- strengthened rudder pedals with reinforced rudder pedals. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to replace the non-strengthened rudder pedals and to prevent failure of the rudder controls. This failure could lead to loss of directional control of the glider.
2024-11-03: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, AG (IAE AG) Model V2500 engines. This AD was prompted by an analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA-JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7) separation that resulted in an aborted takeoff. This AD requires performing an angled ultrasonic inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage hubs and HPT 2nd-stage hubs for cracks and replacing if necessary. This AD also requires accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage hubs. The FAA is issuing this AD to address the unsafe condition on these products.
2024-08-09: The FAA is adopting a new airworthiness directive (AD) for certain GA8 Airvan (Pty) Ltd Model GA8 and GA8-TC320 airplanes. This AD is prompted by reports of insufficient electrical bonding of the solenoid (relay) box assembly that could result in degraded performance, errors, or intermittent failures of equipment connected to electrical Bus 1, Bus 2, associated electrical control, and protective devices fitted within or attached to the solenoid box. This AD requires inspecting for an existing wire connecting the relay box earth point to the ground power socket, and if one is not present, installing a mechanical connection. The FAA is issuing this AD to address the unsafe condition on these products.
88-14-07: 88-14-07 BOEING: Amendment 39-5966. Applies to Model 737 series airplanes, line numbers 001 through 1425, equipped with non-modular aft lavatories, certificated in any category. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tNOTE: "Non-modular" refers to lavatories which are not stand-alone components, and are assembled on the airplane. \n\n\tTo prevent accumulation of combustible materials behind the airplane sidewall, accomplish the following: \n\n\tA.\tWithin 3 months after the effective date of this AD, inspect the area behind the towel and cup dispenser for the presence of a shroud enclosing the dispenser back. \n\n\t\t1.\tIf the dispenser is equipped with a shroud which prevents material from falling behind the lavatory sidewall and is acceptable to the Manager, Seattle Aircraft Certification Office, or an FAA Principal Maintenance Inspector, no further action is required. \n\n\t\t2.\tIf an acceptable existing shroud has not been installed, inspect the area behind the towel and cup dispenser in the aft lavatories and remove all foreign material. Repeat this inspection at intervals not to exceed 3 months, until the requirements of paragraph B., below, are accomplished. \n\n\tB.\tWithin 15 months after the effective date of this amendment, install a shroud behind the towel and cup dispenser in the aft lavatories, which encloses the dispenser back and prevents material from falling behind the sidewall, in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, or an FAA Principal Maintenance Inspector. \n\n\tC.\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 may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\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\tThis amendment, 39-5966, becomes effective August 11, 1988.
85-12-10: 85-12-10 SLINGSBY SAILPLANES: Amendment 39-5079. Applies to Slingsby T.53.B gliders certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent structural failure due to fatigue cracks, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, install a placard on the instrument panel in full view of the pilot reading: "CLOUD FLYING AND AEROBATIC MANEUVERS PROHIBITED." (b) (1) Within the next 10 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 5 hours time in service from the last inspection, visually inspect the welded frame P/N T53B-1079, which joins the forward spar member with the rear spar member of the fuselage center section, for cracks at the forward extremity of the lower two tubes where they are welded to the thin vertical channels. (2) Within the next 10 hours time in service after the effectivedate of this AD, and thereafter at intervals not to exceed 5 hours time in service from the last inspection, inspect the two aft brackets (welded brackets - P/N T53B-10-168, Issue 1-4; riveted brackets - P/N T53B-10-168, Issue 5) that attach the wing center section to fuselage frame No. 6 for fatigue cracks using the dye penetrant crack detection method in accordance with Slingsby Engineering Limited Technical Instruction No. 100/T53, Issue 1, dated October 20, 1981, or an FAA- approved equivalent. (c) If cracks are found as a result of the inspections required by paragraph (b)(1), prior to further flight, modify the tubular structure in accordance with Slingsby Sailplanes Technical Instruction No. 68, dated August 14, 1974, or an FAA-approved equivalent. (d) If cracks are found as a result of the inspections required by paragraph (b)(2), prior to further flight, replace the aft two brackets in accordance with Slingsby Sailplanes Technical Instruction No. 70, dated September11, 1974, or an FAA-approved equivalent, and Slingsby Engineering Limited Technical Instruction No. 100/T53, Issue 1, dated October 20, 1981, or an FAA-approved equivalent. (e) The placard required by paragraph (a) may be removed, and the inspections required by paragraph (b) may be discontinued, after the modification of the tubular structure, in accordance with Slingsby Sailplanes Technical Instruction No. 68, dated August 14, 1974, or an FAA-approved equivalent, has been accomplished, and when the aft two brackets have been replaced in accordance with Slingsby Sailplanes Technical Instruction No. 70, dated September 11, 1974, or an FAA-approved equivalent, and Slingsby Engineering Limited Technical Instruction No. 100/T53, Issue 1, dated October 20, 1981, or an FAA-approved equivalent. (f) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the past 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, comply with the following: (1) Dye penetrant inspect the metal lugs P/N T53B-10-115, and channel section P/N T53B-10-118, on fuselage frame No. 6, in accordance with Slingsby Engineering Limited Technical Instruction No. 100/T53, Issue 1, dated October 20, 1981, or an FAA- approved equivalent. (2) If cracks are found as a result of the inspections required by paragraph (f)(1) of this AD, prior to further flight, replace the metal lugs and/or channel section in accordance with Slingsby Engineering Limited Technical Instruction No. 100/T53, Issue 1, dated October 20, 1981, or FAA-approved equivalent. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium, telephone 513.38.30 ext. 2710. Slingsby Sailplane Technical Instruction No. 70 dated September 11, 1974, Slingsby Sailplane Technical Instruction No. 68 dated August 14, 1974, and Slingsby Engineering Limited Technical Instruction dated October 20, 1981, 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 upon request to Slingsby Engineering Limited, Ings Lane, Kirbymoorside, York, Y06, 6EZ, England. These documents also may be examined at the Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. This AD supersedes Amendment 39-2308 (40 FR 32318), AD 75-17-07. This Amendment 39-5079 becomes effective on July 22, 1985.