Results
2002-22-11: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Turbomeca Artouste III series turboshaft engines with injection wheels part numbers (P/N's) 218.25.700.0, 218.25.704.0, 243.25.709.0, 243.25.713.0, 0.218.27.705.0, 0.218.27.709.0, and 0.218.27.713.0 installed. That AD currently requires smoke emission checks after every ground engine shutdown. If smoke is detected, that AD requires inspecting for fuel flow. If fuel flow is not detected, the engine may have injection wheel cracks, which requires removing the engine from service for repair. If fuel flow is detected, the engine may have a malfunctioning electric fuel cock, which requires removing the electric fuel cock from service and replacing with a serviceable part. This amendment has similar requirements as the original AD, except that the smoke emissions are to be checked after the last flight of the day, as opposed to after every flight, as required by the original AD. This amendmentalso requires inspection of central labyrinths not previously inspected or not replaced after the engine logged 1,500 operating hours, and, replacement of these labyrinths if necessary. This amendment is prompted by reports and analyses of in-flight shutdowns (IFSD's) occurring since the issuance of AD 2000-06-12. The actions specified by this AD are intended to prevent injection wheel cracks and excessive central labyrinth wear, which could result in an IFSD.
2019-10-02: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD was prompted by an event where the airplane did not respond to the flightcrew's flight control inputs because the pitch trim switches did not disconnect the autopilot. This AD requires modifying the wiring installation for the autopilot disconnect logic. We are issuing this AD to address the unsafe condition on these products.
2019-12-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of low clearance between the variable frequency generator (VFG) power feeder cables and adjacent hydraulic lines and/or fuel lines in the aft equipment bay, which could cause chafing damage. This AD requires modifying the routing of the VFG power feeder cables and harnesses in the aft equipment bay. The FAA is issuing this AD to address the unsafe condition on these products.
99-01-01: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-80C2 series turbofan engines. This action requires a one-time visual inspection to ensure the correct accessory gearbox (AGB) idler adapter inserts are installed, and, if necessary, removal of AGB idler adapters with the improper inserts. This amendment is prompted by a report of a failure of a fuel tube flange connection due to improper AGB idler adapter inserts that resulted in a high pressure fuel leak and engine fire. The actions specified in this AD are intended to identify and remove AGB idler adapters with improper inserts, which can result in an engine fire and damage to the aircraft.
63-14-02: 63-14-02 BOEING: Amdt 581 Part 507 Federal Register July 2, 1963. Applies to All Model 720 Series Aircraft Serial Numbers 17907 through 17917, 18013 Through 19037, 18041 Through 18050, 18057, 18059 Through 18066, 18072 Through 18082, 18086 and 18087, 18154 Through 18167, 18240 through 17917, 18013 Through 18037, 18041, 18351 Through 18353, 18355 and 18356, 18376 Through 18384, 18416 Through 18425, 18451 Through 18455 and 18581.\n \n\tCompliance required within the next 450 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tIn order to correct for the presence of any improperly heat-treated main landing gear actuator beam terminal attach bolts, P/N 63-9587-1, accomplish the following: \n\n\t(a)\tConduct a heat-treat check on the attach bolts, P/N 63-9587-1 (two per actuator beam). \n\n\t(b)\tBolts testing within the heat-treat range of 180,000 p.s.i. to 2000,000 p.s.i. are acceptable for further use and may be continued in service provided they are not otherwise defective. \n\n\t(c)\tBolts testing outside the heat-treat range of 180,000 p.s.i. to 200,000 p.s.i. shall be replaced with bolts of proper heat-treat before further flight. \n\n\t(d)\tIf holes in either the actuator beam or the terminal are damaged during bolt removal, the bolt holes, or the bolts may be reworked in accordance with Boeing Service Bulletin No. 1827, or an FAA equivalent approved method. \n\n\t(Boeing Service Bulletin No. 1827 covers this same subject.) \n\n\tThis directive effective August 1, 1963.
88-13-06: 88-13-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION (AMD-BA): Amendment 39-5949. Applies to Model Fan Jet Falcon series airplanes as listed in AMD-BA Service Bulletin FJF-32-45(502), Revision 1, dated May 27, 1987, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent the inability to extend the main landing gear (MLG) due to the lateral door rear lock jamming, accomplish the following: A. Install a stop on each MLG lateral door rear lock in accordance with AMD-BA Fan Jet Falcon Service Bulletin FJF-32-45(502), Revision 1, dated May 27, 1987. B. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may addany comments and then send it to the Manager, Standardization Branch, ANM-113. C. 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 modification required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Falcon Jet Corporation, 77737 Terrace Avenue, Hasbrouck Heights, New Jersey 07604. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5949, becomes effective July 11, 1988.
2005-26-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires an inspection of the laminated shims for cracks, damage, or extrusion between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer; a torque check of the attachment bolts in the attachment fittings of the front, middle, and rear spars; and corrective actions if necessary. This AD results from a report indicating that delaminated shims extruded from the interface between the forward attaching fittings of the horizontal stabilizer and the top rib of the vertical stabilizer, and that inadequate torque values of some bolts were found. We are issuing this AD to prevent reduced structural integrity of the horizontal stabilizer, and consequent loss of controllability of the airplane.
99-01-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires replacing the left and right rudder bars with improved design rudder bars. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent distortion of the original design rudder bars during operation, which could result in reduced or loss of control of the airplane.
99-01-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Westland Helicopters Ltd. (Westland) 30 Series 100 and 100-60 helicopters. This action requires the removal and replacement of conformal pinion quill shafts installed in certain main rotor gearboxes that fail to pass a magnetic drain plug inspection. This amendment is prompted by a report of a forced landing that occurred when a single conformal pinion quill shaft failed in a main rotor gearbox (MRGB). This condition, if not corrected, could result in the failure of a MRGB, and a subsequent forced landing or loss of control of the helicopter.
80-25-01: 80-25-01 HUGHES HELICOPTERS: Amendment 39-3980. Applies to Model 369 Series Helicopters certified in all categories. Compliance is required as indicated unless already accomplished. To prevent possible fatigue failure of the Hughes couplings in the tail rotor drive shaft and loss of tail rotor power, accomplish the following: (a) Within 25 hours' time in service from the effective date of this AD, inspect the fore and aft tail rotor drive shaft couplings to determine the serial numbers of the installed couplings. The serial number is on the Bendix part number decal. (b) For those helicopters with the following couplings installed, prior to further flight, remove couplings from service and label couplings "Unairworthy." Hughes Part No. 369H92564, serial numbers 0883U, 0932U, 0933U, 0935U, 0940U, 0950U, 0957U, 0961U, 0971U; and for Hughes Part No. 369A5501, serial numbers 10670U and 10672U. Replace removed coupling with like serviceable part. (c) Installation of any coupling listed in paragraph (b) will render the helicopter unairworthy. (d) Report the serial number of each suspect coupling listed in paragraph (b) found as a result of the inspection of paragraph (a) to the Chief, Engineering and Manufacturing Branch, FAA, Western Region, P.O. Box 92007, World Way Postal Center, Los Angeles, California 90009. Negative reports are not necessary. Reporting approved by Office of Management and Budget, OMB No. 04/R0174. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections required by this AD. (f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective December 4, 1980.