Results
2000-01-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires the replacement of fuse pins in the attachment fittings and support fittings of the main landing gear with new, improved fuse pins. This amendment is prompted by a report of corrosion of a fuse pin of a similar design on the main landing gear of a Boeing Model 767 series airplane. The actions specified by this AD are intended to prevent corrosion and subsequent fracture of the fuse pins, which could result in collapse of the main landing gear and the loss of the inboard flap and spoilers.
2006-19-10: We are adopting a new airworthiness directive (AD) that supersedes AD 2005-17-19, which applies to certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. AD 2005-17-19 currently requires you to measure and adjust the crew seat break-over bolts and to replace the crew seat recline locks on both crew seats. Since we issued AD 2005-17-19, CDC developed new crew seat break-over pins to replace the old crew seat break-over bolts. Consequently, this AD retains the action from AD 2005-17-19 of replacing the crew seat recline locks on both seats and adds the action of replacing the crew seat break-over bolts with the new crew seat break-over pins on both seats. We are issuing this AD to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury. DATES: This AD becomes effective on October 24, 2006. As of October 24, 2006 the Director of the Federal Register approved the incorporation by reference of CirrusDesign Corporation Service Bulletin SB 2X-25-17 R1, Issued: December 15, 2005, Revised: January 20, 2006. As of October 13, 2005 (70 FR 51999, September 1, 2005), the Director of the Federal Register previously approved the incorporation by reference of Cirrus Design Corporation Service Bulletin SB 2X-25-06 R4, Issued: August 13, 2004; Revised: May 5, 2005.
96-07-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires inspection(s) to verify that the position indicator of the fuel balance transfer valve (FBTV) is in the closed position, and closing the FBTV, if necessary; and deactivation of the fuel balance transfer system (FBTS). This amendment is prompted by a report that, under certain failure conditions, the actuator of the FBTV could remain in the open position without a flight deck indication. The actions specified by this AD are intended to ensure that the FBTV is not in the open position during flight, which could lead to the reduction of fuel supply to the engines during cross-feed operation and consequent engine fuel starvation.
2006-18-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B16 (CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. These models may be referred to by their marketing designations as RJ100, RJ200, CRJ100, CRJ200, and CL-65. This AD requires revising the Emergency Procedures section of the airplane flight manual (AFM) to advise the flightcrew of additional procedures to follow in the event of stabilizer trim runaway. For certain airplanes, this AD also requires revising the Abnormal Procedures section of the AFM to advise the flightcrew of procedures to follow in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions. This AD results from reports of uncommanded horizontal stabilizer trim motion. We are issuing this AD to ensure that the flightcrew is advised of appropriate procedures to follow in the event of stabilizer trim runaway. Failure to follow these procedures could result in excessive uncommanded movement of the horizontal stabilizer trim actuator (HSTA) and loss of ability to use trim switches to override uncommanded movement or yoke disconnect switches to disconnect the HSTA, which could result in reduction of or loss of pitch trim control and consequent reduced controllability of the airplane.
86-14-03: 86-14-03 AVIONS MARCEL DASSAULT - BREGUET AVIATION (AMD): Amendment 39-5342. Applies to all AMD Mystere Falcon 50 airplanes, certificated in any category. Compliance is required as indicated below. To detect and prevent leaks in the refueling system, accomplish the following: A. Within the next 30 days after the effective date of this AD, unless accomplished within the last 30 days, and thereafter at intervals not to exceed 30 days, perform an inspection of the guide rod in the refueling connector for damage, in accordance with AMD Service Bulletin F50-28-11(137), dated December 30, 1982. Replace any damaged or leaking guide rod with a serviceable unit prior to further flight. NOTE: After each refueling under pressure, a visual leak check should be performed. B. Within 6 months after the effective date of this AD, modify the refueling connector by installing a steel guide rod, in accordance with AMD Service Bulletin F50-28-11(137), unless previously accomplished.Accomplishment of this modification provides terminating action for the inspections required by paragraph A., above. C. 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. D. 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 inspections and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to the AMD-BA Representative, 40 FJC, Teterboro Airport, Teterboro, New Jersey 07608. This document 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 becomes effective August 4, 1986.
96-17-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, MU-300-10, and 2000 airplanes, and Model 200, B200, 300, and B300 series airplanes, that requires replacement of outflow/safety valves with serviceable valves. This amendment is prompted by a report of cracking and subsequent failure of outflow safety valves in the pressurization system. The actions specified by this AD are intended to prevent such cracking and subsequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
83-02-02: 83-02-02 DEHAVILLAND: Amendment 39-4553. Applies to DHC-6 Models 1, 100, 200, and 300 (all serial numbers) airplanes certificated in any category. COMPLIANCE: Required on or before May 1, 1983, unless already accomplished. To prevent catastrophic failure of the wing, wing carry through, and attaching structure, accomplish the following: a) Modify and replace the structural components listed in DeHavilland Structural Components Service Life Limits Manual PSM 1-6-11, Revision 2, approved by DOT Canada August 29, 1978 in accordance with the respective schedules listed therein. b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. c) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, ANE- I70, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective on February 4, 1983.
99-21-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319-131, A320-232 and -233, and A321-131 and -231 series airplanes, that requires replacement of all titanium thrust links with steel thrust links. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the titanium thrust links due to the life limit of the thrust links, which in combination with other failures, could result in the separation of an engine from the airplane.
90-16-01: 90-16-01 AIRBUS INDUSTRIE: Amendment 39-6680. Docket No. 90-NM-62-AD. Applicability: Model A300 series airplanes, serial numbers up to and including 253, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent malfunction of the main landing gear in the free fall mode, accomplish the following: A. Within 100 landings after November 27, 1989 (the effective date of AD 89-23-01), inspect both main landing gears (MLG) for defective uplock control bellcrank support bearings, Part Number (P/N) 8116-16 in accordance with All Operators Telex (AOT) 32/88/02, dated December 14, 1988. If a defective bearing is found, replace it with a serviceable bearing prior to further flight. B. Replace both MLG uplock control bellcrank support bearings, P/N 8116-16, with new sealed bearings, P/N 8106-16, in accordance with Airbus Industrie Service Bulletin A300-32- 395, dated November 30, 1989, as follows: 1. Within 30 months after the effective date of this AD, if bearings, P/N 8116-16, were replaced at the time of accomplishing paragraph A., above. 2. Within 15 months after the effective date of this AD, if bearings, P/N 8116-16 were not replaced at the time of accomplishing paragraph A., above. C. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 89-23-01, Amendment 39-6366. This amendment (39-6680, AD 90-16-01) becomes effective on August 31, 1990.
98-03-01: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere Falcon 200 series airplanes, that requires reducing the life limit of the polyurethane foam used in the fuselage fuel tanks. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure replacement of the polyurethane foam in the fuselage fuel tanks when it has reached its maximum life limit; polyurethane foam that is not replaced in a timely manner could result in fuel contamination or increased risk of explosion in the fuselage fuel tank.