Results
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.
2002-03-05: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires, among other things, repetitive leak tests of the lavatory drain systems and repair, if necessary; installation of a lever lock cap, vacuum breaker check valve, or flush/fill line ball valve on the flush/fill line; periodic seal changes; and replacement of "donut" type waste drain valves installed in the waste drain system. This amendment is prompted by continuing reports of damage to engines, airframes, and property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
2002-02-11: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III series airplanes. This AD requires you to repetitively inspect certain oleo attachment brackets for cracks and replace any cracked bracket found during any inspection. In working with the United Kingdom, we have determined that the bracket may, as an option, be replaced with a newly designed steel bracket, increasing the length of time between the repetitive inspections. The actions specified by this AD are intended to detect and correct cracked oleo attachment brackets. Such a condition could cause the attachment bracket to fail, which could result in detachment of the main landing gear.
2002-02-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-200, -200C, -300, and -500 series airplanes, that requires replacement of the bolt and self- locking nut on the primary support pin of the main landing gear (MLG) support beam with a new bolt, castellated nut, washer, and cotter pin. This action is necessary to prevent the loosening and loss of the support pin retaining bolt on the MLG, which could result in the loosening and movement of the support pin and consequent cracked support fittings and collapse of the MLG. This action is intended to address the identified unsafe condition.