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2010-02-05: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2010-02-05 that was sent previously by individual notices to the known U.S. owners and operators of affected airplanes identified above. This AD requires modifying the flight deck door. This AD was prompted by a report indicating that certain equipment of the flight deck door is defective. We are issuing this AD to prevent failure of this equipment, which could jeopardize flight safety.
2005-16-08: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires repetitively replacing and testing a certain relay in the passenger oxygen release system in the forward cabin. This AD results from reports of a failed relay in the passenger oxygen release system. We are issuing this AD to prevent failure of the relay, which could result in the oxygen masks failing to deploy and deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization.
87-26-03: 87-26-03 BOEING: Amendment 39-5803. Applies to Model 737 series airplanes, specified in Boeing Service Bulletin 737-34A1208, Revision 1, dated May 14, 1987, certificated in any category. Compliance required within the next year after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the possibility of misleading localizer deviation indication to the flight crew caused by electromagnetic interference, accomplish the following: \n\n\tA.\tReplace the existing weather radar receiver-transmitters with modified receiver- transmitters; install 10 db attenuators in line with the localizer coaxial cables; if Bendix VHF navigation receivers are installed, replace with modified receivers; and, for Model 737-300 airplanes equipped with electronic flight instrument system (EFIS), modify specific wire bundles and their routing, in accordance with Boeing Service Bulletin 737-34A1208, Revision 1, dated May 14, 1987, or later FAA-approved revision.\n \n\tB.\tAn alternatemeans 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\tC.\tSpecial 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 modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\tThis amendment becomes effective February 1, 1988.
2002-02-07: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires repetitive inspections and operational checks of the spring function of the emergency exit door slider mechanism, and corrective action if necessary. This action is necessary to prevent failure of the spring locking function of the slider mechanism due to corrosion, which could result in the escape slide detaching from the airplane in an emergency evacuation. This action is intended to address the identified unsafe condition.
2002-02-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); and A310 series airplanes. This AD requires repetitive overhaul, including associated modifications, of the ram air turbine (RAT). This action is necessary to prevent failure of the RAT to deploy or operate properly in the event of an emergency, which could result in reduced hydraulic pressure or electrical power on the airplane. This action is intended to address the identified unsafe condition.
92-20-03: 92-20-03 BRITISH AEROSPACE: Amendment 39-8377. Docket No. 92-NM-98-AD. Applicability: Model DH/HS 125 series airplanes; as listed in British Aerospace Service Bulletin SB 57-76, dated December 31, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural integrity and possible collapse of the main landing gear (MLG) on landing or take-off, accomplish the following: (a) Within 12 months after the effective date of this AD, perform a one-time visual inspection to detect corrosion on the MLG support brackets, rear spar sections, inboard flap hinge arms, and associated attachment hardware, in accordance with British Aerospace Service Bulletin SB 57-76, dated December 31, 1991. (b) If no corrosion is found on the MLG support brackets, rear spar sections, inboard flap hinge arms, and associated attachment hardware, no further action is necessary. (c) If any corrosion is found on the MLG support brackets, rear spar sections, and inboard flap hinge arms, prior to further flight, replace any corroded parts found, or repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) If corrosion is found on any associated attachment hardware that is within the limitations specified in the Structural Repair Manual (SRM) Chapter 51 10, prior to further flight, replace or repair in accordance with the SRM. (e) If corrosion is found on any associated attachment hardware that is beyond the limitations specified in the Structural Repair Manual (SRM) Chapter 51 10, prior to further flight, replace or repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (f) 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. (g) 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. (h) The inspection shall be done in accordance with British Aerospace Service Bulletin SB 57-76, 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. (i) This amendment becomes effective on November 17, 1992.
2017-22-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of fuel leaks in the engine and auxiliary power unit (APU) electrical fuel pump (EFP) cartridge/canister electrical connectors and conduits. This AD requires repetitive inspections for fuel leakage at the engine and APU fuel pumps, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-02-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-243, -341, -342, and -343 series airplanes. This action requires modifying the rear engine mount by replacing the existing fail-safe link with a new, improved fail-safe link. This action is necessary to prevent failure of the fail-safe link of the rear engine mount, which, in combination with failure of the primary load path for the engine, could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
85-25-01: 85-25-01 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5181. Applies to Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, certificated in any category. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent failure of the cyclic control stick, accomplish the following: (a) Perform the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) 206-85-29, dated June 21, 1985, for the Model 206A or 206B; or ASB 206L-85-36, dated June 21, 1985, for the Model 206L, 206L-1, or 206L-3, as appropriate. (b) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Helicopter Certification Branch, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101. (c) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspection and repair procedures required by this AD may be accomplished. 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined in Room 158, Building 3B, Office of Regional Counsel, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, between 8 a.m. and 4 p.m., weekdays, except Federal holidays. This amendment becomes effective December 30, 1985.
2017-22-01: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires adding operating limitations to a rotorcraft flight manual (RFM). This AD is prompted by test results showing decoupling of the flight director (FD) in certain flight conditions. The actions of this AD are intended to address an unsafe condition on these products.