Results
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.
2005-08-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas series airplanes. That AD currently requires repetitive inspections of the electrical connectors of the explosive cartridge wiring of the engine fire extinguisher containers to verify if the identification number labels are installed and legible; repetitive electrical tests of all explosive cartridge wiring of the engine fire extinguisher containers to verify proper installation and function; and corrective actions if necessary. This new AD requires an inspection of the emergency shut off wire assembly; installation of lanyards on the electrical connectors for the engine fire extinguishing agent containers and for the auxiliary power unit fire extinguishing agent containers if applicable; and related investigative/corrective actions, as applicable. This AD is prompted by reports of cross-wired electrical connectors of the engine fire extinguishing agent containers. We are issuing this AD to detect and correct cross-wired electrical connectors of the fire extinguishing system, which could release fire extinguishing agent into the incorrect engine nacelle in the event of an engine fire.
2024-10-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by the determination that reliance on design assurance level (DAL) D software for flight-critical fly-by-wire (FBW) rigging functions may result in undetected inaccurate positioning of the primary flight control surfaces. This AD requires the use of specific issues of the aircraft maintenance publication (AMP) for electrical rigging procedures, and an electrical rigging confirmation check of primary flight control surfaces for certain airplanes, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2024-09-02: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AW169 helicopters. This AD was prompted by manufacturing defects in certain forward and aft float assemblies. This AD requires replacing certain aft float assemblies or, as an alternative, deactivating the emergency flotation system (EFS). This AD also prohibits installing certain forward and aft float assemblies. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
85-26-02: 85-26-02 MESSERSCHMITT-BOLKOW-BLOHM: Amendment 39-5226. Applies to Model BO-105 series helicopters, through serial No. 750, certificated in any category that are equipped with one of the following tandem hydraulic units: Part Numbers (P/N) 105-45021, 105- 45023, 105-45028, 105-83001, 105-83011, D133-3073, and DSK1-30142. Compliance is required as indicated, unless previously accomplished. To detect or prevent possible jamming of the helicopter main rotor control system, accomplish the following: (a) Before the first flight of each day after the effective date of this AD, operate the System II hydraulic actuators to detect binding of the control. If binding is detected, clean and seal the System II hydraulic actuators in accordance with paragraph (b) of this AD. (b) Within the next 10 hours time in service after the effective date of this AD, clean and seal the System II hydraulic actuators in accordance with MBB BO-105, ASB No. 26, Part 2B, dated December 12, 1985, or with an equivalent approved in accordance with paragraph D of this AD. After sealing, the operational check in paragraph (a) is no longer required. (c) The operational check in paragraph (a) may be performed by the pilot. NOTE: For the requirements regarding recording compliance and method of compliance with this AD in the aircraft's permanent maintenance records, see FAR Section 91.173. (d) Upon request, an equivalent means of compliance with this AD may be used when approved by the Manager, Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, APO NY 09667-1011. (e) The aircraft may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the actuators may be sealed in accordance with paragraph (b) of this AD. 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 upon request to MBB Helicopter Corp., P.O. Box 2349, West Chester, Pennsylvania 19380. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, Southwest Region, Room 158, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective February 25, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-26-02, issued December 23, 1985, which contained this amendment.
86-21-11: 86-21-11 EMPRESA BRASILEIRA DE AERONAUTICA S.A.: Amendment 39-5535. Applies to Embraer Model EMB-120 series airplanes; serial numbers 12004, 12006 through 120028, 120033, and 120034; equipped with engine oil coolers, part numbers 160282-1 or 160282-2, which have accumulated more than 200 hours time-in-service; certificated in any category. Compliance is required within the next 10 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent oil loss and in-flight engine shutdown, accomplish the following: A. Fabricate and install on the instrument panel near the altimeter, in full view of the pilot, a placard that reads: "MAXIMUM OPERATING LIMITATION 10,000 FEET MSL." B. Installation of engine oil cooler part number 160282-3 or subsequent, constitutes terminating action for the requirements of this AD. This amendment becomes effective February 17, 1987, as to all persons, except those persons to whom it was made immediatelyeffective by Priority Letter AD 86-21-11, issued October 22, 1986.
2005-08-13: The FAA adopts a new airworthiness directive (AD) for all Glaser-Dirks Flugzeugbau GmbH (DG Flugzeugbau) Model DG-800B sailplanes equipped with a SOLO 2625 engine or a Mid-West AE 50T engine. This AD requires you to modify the coolant pump and fuel pump electrical circuits, remove the non-resettable digital engine indicator (DEI) circuit breaker (4-ampere) and replace with a resettable 5-ampere circuit breaker, secure (for sailplanes with a SOLO 2625 engine) the choke butterfly valve axis, install edge protection at the sharp edges of the resettable 5-ampere DEI circuit breaker, and incorporate changes in the FAA-approved sailplane flight manual. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent electrical failure of the fuel and coolant pumps if a non-resettable circuit breaker trips. This could result in power loss with the inability to restart the fuel pump during a critical phase of flight (for example, takeoff under own power).