Results
2008-18-09: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires modification of the refuel valve control unit for the reserve fuel tanks. This AD also requires a revision to the FAA-approved maintenance program to incorporate airworthiness limitation (AWL) No. 28-AWL-20 or AWL No. 28-AWL-25, as applicable. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent lightning-induced electrical energy from entering a reserve fuel tank through the refuel valve, which could result in a fuel tank explosion and consequent loss of the airplane.
96-01-04 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to require verification that the auto-ignition system is operational; to define icing conditions at higher ambient temperatures; and to provide the flight crew with limitations and procedures to aid in the avoidance of engine power interruptions. The actions specified by that AD are intended to prevent failure of the auto-ignition system to re-light the engine in the event of power interruptions due to the ingestion of ice and/or slush into the engine, which could result in engine flameout and subsequent shutdown, and to provide the flight crew with guidance to aid in avoidance of such occurrences. This amendment clarifies certain requirements of the AFM revision. This amendment is prompted by communications received from affected operators that certain of the currentrequirements of the AD are unclear.
84-10-07: 84-10-07 GULFSTREAM AEROSPACE CORPORATION (AERO COMMANDER): Amendment 39-4868. Applies to Models 680T, 680V, and 680W (S/N's 1473 through 1850) and Model 681 (S/N's 6001 through 6017, 6020 through 6038, 6040 through 6042, and 6048) airplanes certificated in any category unless Service Bulletin 102 dated March 1, 1971, or Service Bulletin 102A dated September 1, 1983, has previously been accomplished. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless already accomplished. To assure proper operation of the emergency landing gear extension system, accomplish the following: (a) Modify the emergency landing gear extension system in accordance with Gulfstream Aerospace Corporation, Commander Division, Service Bulletin 102A, dated September 1, 1983. (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 ifapproved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective on June 23, 1984.
2008-17-10: We are adopting a new airworthiness directive (AD) for certain Boeing Model 707 airplanes, and Model 720 and 720B series airplanes. This AD requires repetitive detailed inspections to detect cracks and corrosion on any existing repairs and at certain body stations of the visible surfaces of the wing to body terminal fittings including the web, flanges, and ribs; and applicable related investigative and corrective actions. This AD results from reports of cracks found in the wing to body terminal fittings during routine inspections. We are issuing this AD to prevent cracks and corrosion in the body terminal fittings, which could cause loss of support for the wing and could adversely affect the structural integrity of the airplane.
86-02-01: 86-02-01 BOEING: Amendment 39-5214. Applies to Model 767 airplanes, as listed in Boeing Service Bulletin 767-52-0041, dated December 13, 1985, certificated in any category. Compliance is required within 30 days after the effective date of this AD. To ensure proper door opening, accomplish the following, unless already accomplished: \n\n\tA.\tInspect all entry/service door operating mechanisms for integrity of the upper and lower pushrod installations and repair, if necessary, in accordance with Boeing Service Bulletin 767-52-0041 dated December 13, 1985, or later FAA-approved revisions. \n\n\tB.\tAlternate means of compliance which provide 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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this AD who have not already received copies of the service bulletin cited herein may obtain copies upon request from the Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. 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. \n\n\tThis Amendment becomes effective February 3, 1986.
2008-17-09: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A rupture of the alternator and vapour cycle cooling system pulley drive assembly has reportedly been found. Such a failure could lead to the loss of the alternator and vapour cycle cooling systems and could also cause mechanical damage inside the powerplant compartment. We are issuing this AD to require actions to correct the unsafe condition on these products.
82-01-08: 82-01-08 HUGHES HELICOPTERS: Amendment 39-4292. Applies to Model 369 Series helicopters, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent loss of control of engine power due to control rod failure, accomplish the following: (a) Within 25 hours' additional time in service after the effective date of this AD, remove P/N 369A7706-3 RPM Governor Lever Control Rod and replace with P/N 369A7706-5 RPM Governor Lever Control Rod. NOTE: Hughes Helicopters Notice No. DN-87 and HN-169, dated May 15, 1981, refers to this subject. (b) 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 or modifications required by this AD. (c) 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-Pacific Region. This amendment becomes effective January 7, 1982.
2008-16-01: The FAA is adopting a new airworthiness directive (AD) for GE CF34-8E series turbofan engines with certain part number (P/N) full authority digital engine controls (FADECs) installed. This AD requires reprogramming the FADEC software from version 8Ev5.40 to an FAA- approved software version. This AD results from six loss of thrust control events from the same software fault scenario. We are issuing this AD to prevent loss of thrust control and controllability of the airplane.
2008-14-16: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: At least one incident has occurred where, immediately after take-off, the passenger door of a Dornier 328 completely opened. * * * Substantial damage to the door, handrails, door hinge arms and fuselage skin were found. * * * Although final proof could not be obtained, the most likely way in which the door opened was that the door handle was inadvertently operated during the take-off run. * * * * * [T]his Airworthiness Directive (AD) aims to prevent further incidents of inadvertent opening and possible detachment of a passenger door in-flight, likely resulting in damage to airframe and systems and, under less favorable circumstances, loss of control of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
86-03-02: 86-03-02 FOKKER B.V.: Amendment 39-5221. Applies to Model F28 airplanes as indicated in the applicability statement of each service bulletin listed below. Compliance is required within the next 120 days after the effective date of this airworthiness directive, unless already accomplished: A. To prevent loss of the pilot and copilot restraint function of the safety harnesses, replace the inertia reel springs and mounting collars in accordance with Fokker Service Bulletin F28/25-93, dated June 4, 1984, and Teleflex Morse Limited Service Bulletin 25-00-185429, Issue 2, dated September 1983. B. To ensure that instruction placards on the service/emergency door in emergency lighting conditions are legible, modify the emergency lighting system in accordance with Fokker Service Bulletin F28/33-32, dated September 17, 1984. C. Alternate means of compliance which provide 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 used 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 documents from the manufacturer may obtain copies upon request to the Manager, Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. 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. This amendment becomes effective February 28, 1986.