Results
87-25-08: 87-25-08 GULFSTREAM AMERICAN (FRAKES AVIATION): Amendment 39-5790. Applies to Model G-73 (Mallard) series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent jamming of the elevator control system, accomplish the following: A. Within 15 days after the effective date of this AD, visually inspect the overlapping contact surface between the elevator control torque tube arm, P/N 109410, and the elevator up stop bolt hex head, P/N G19-5-22, in accordance with Frakes Aviation Service Bulletin G-73-FA26, dated May 1, 1987 (hereinafter referred to as SB G-73-FA26), or later FAA-approved revisions. 1. If the elevator control torque tube arm is not overlapping the stop bolt hex head by one-half or more of the stop bolt hex head dimension, or if the center lines of the stop bolt hex head and the elevator control torque tube arm are not aligned within 1/8 inch (0.125 inch) side to side, prior to further flight install Frakes Aviation Stop Kit, P/N FA112723K1, in accordance with SB G-73-FA26, or later FAA-approved revision. 2. If the elevator control tube arm is overlapping the stop bolt hex head by one-half or more of the stop bolt hex head dimension, and if the center lines of the stop bolt hex head and the elevator control torque tube are aligned within 1/8 inch (0.125 inch) side to side, within the next 100 hours time-in-service install Frakes Aviation Stop Kit, P/N FA112723K1, in accordance with SB G-73-FA26, or later FAA-approved revisions. B. 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 requirements of this AD. C. An alternate means of compliance, which provides an acceptable level of safety, may be used when approved by the Manager, Airplane Certification Branch, FAA, Southwest Region. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Frakes Aviation, Cleburne Airport, Route 3, Box 229-B, Cleburne, Texas 76031. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective January 19, 1988.
98-13-27: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection to detect discrepancies of circuit breaker panels 10VE and 11VE; follow-on corrective actions; modification of the contact points; and installation of a high capacity fuse. This amendment also requires replacement of power relays 32HB and 36HB on relay panel 22VE with new parts. 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 electrical short circuits of the contact points and power relays on the circuit breaker panels, which could result in increased risk of smoke and fire damage in the flight compartment.
2007-26-15: We are adopting a new 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: In some cases the electric motor of the spindle drive detached itself from the spindle drive, causing the powerplant to retract itself after engine shutdown. In another case the attachment fork on the spindle drive failed with the same consequences. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-06-16: We are adopting a new 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 references Alpha Aviation Service Bulletin AA-SB-28-002, dated June 28, 2006, which describes the unsafe condition as: Development of the New Zealand produced Alpha 160A aircraft identified an issue with the fuel shut-off valve, where it may not be possible to switch the valve ON once the valve has been placed in the OFF position. This is due to friction in the shut-off system. The fuel shut-off valve, which is normally ON, is a safety feature to allow the pilot to stop fuel flow to the engine in an emergency situation such as a forced landing without power. The fuel shut-off control is guarded and requires a deliberate action by the pilot to operate. Not withstanding this, a hazardous situation is possible if the fuel shut-off valve is inadvertently switched OFF in flight and the pilot is not able to switch it back ON. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-03-16: The FAA is adopting a new airworthiness directive (AD) for all Textron Aviation Inc. (Textron) (type certificate previously held by Cessna Aircraft Company) Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, and T210M airplanes. This AD requires visual and eddy current inspections of the carry-thru spar lower cap, corrective action if necessary, application of a protective coating and corrosion inhibiting compound (CIC), and reporting the inspection results to the FAA. This AD was prompted by the in-flight break-up of a Model T210M airplane in Australia, due to fatigue cracking that initiated at a corrosion pit, and subsequent reports of other Model 210-series airplanes with widespread and severe corrosion. The FAA is issuing this AD to address the unsafe condition on these products.
84-09-04: 84-09-04 MCDONNELL DOUGLAS: Amendment 39-4855. Applies to McDonnell Douglas Model DC-8-70 series airplanes equipped with P/N C24466000 Thrust Reverser Hydraulic Control Units (HCU's) on the inboard thrust reversers, certificated in all categories. \n\n\tCompliance required as indicated in the body of this AD, unless previously accomplished: \n\n\tA.\tReplace P/N C24466000 HCU's on both inboard (#2 & #3) engine thrust reversers with P/N C24466000-/-2, P/N C24466001-2, or other FAA approved units, within 30 days after the effective date of this AD. The AFM limitations required by AD 82-19-51 R1, Amendment 39-4714 may be removed after HCU's are replaced on all aircraft in each operator's fleet. \n\n\tNote: P/N C24466000 HCU's can be modified to P/N C24466000-/-2 in accordance with CFMI Service Bulletin (CFM-56-2) 78-057, dated March 30, 1982, or later FAA approved revisions. \n\n\tB.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles 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 the airplanes to a base to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis supersedes Amendment 39-4714 (48 FR 40212), AD 82-19-51. \n\n\tThis amendment becomes effective June 1, 1984.
74-17-04: 74-17-04 PIPER: Amendment 39-1919 as amended by Amendment 39-2154 is further amended by Amendment 39-2865. Applies to the following Models which are covered with cotton or linen at the critical area on top of the windshield where the fabric attaches to the channel: PA-12, Serial Numbers 12-2904 and higher, except 12-2907, 12-2911, 12-2914, 12-2915, 12-2917, 12-2925, 12-2950, 12-3028-S and 12-3901 through 12-3903; PA-14; PA-15; PA-16; PA-17; PA-20; and PA-22 airplanes, Serial Numbers 22-1 and up, certificated in all categories. To prevent sudden failure of the fabric at the top of the windshield where the fabric attaches to the channel, accomplish the following: 1. For all airplanes, unless already accomplished, the indicated Piper Kits or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, must be installed within the next 25 hours in service after the effective date of this AD on airplanes which have fabric exceeding three years since installation: (a) Kit 760 799 effective on: PA-12, Serial numbers 12-2904 and higher, except 12-2907, 12-2911, 12-2914, 12-2915, 12-2917, 12-2925, 12-2950, 12-3028-S and 12-3901 through 12-3903; all PA-12S and PA-14 airplanes. (b) Kit 754 404 effective on: All PA-15, PA-16, PA-17 and PA-20 and PA-22 Airplane Serial Numbers 22-1 and up. 2. For all airplanes at every 100 hours in service after accomplishment of 1(a) or 1(b), remove the metallic strip and inspect the fabric over the top surface. (a) If no cracks or fraying are found, reinstall the metallic strip. (b) If any cracks or fraying are found, prior to further flight, add a fabric reinforcement strip (pinked-tape) starting from a line formed by the intersection of the windshield and the leading edge of the channel and extending aft at least three inches from the trailing edge of the channel. Reinstall the metallic strip. 3. For all airplanes which have fabric installed within thelast three years, every 100 hours in service after the effective date of this AD, until three years are accumulated, inspect the fabric over the top surface. If any cracks or fraying are found, prior to further flight, install Piper Kits or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, as in 1(a) or 1(b) as appropriate. Upon request and appropriate substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Piper Service Letter No. 362A pertains to this subject. This AD supersedes AD 61-06-06. Amendment 39-1919 was effective August 16, 1974. Amendment 39-2154 was effective April 9, 1975. This amendment 39-2865 is effective April 11, 1977.
2008-01-04: We are superseding an existing 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: * * * * * The Bombardier CL-600-2B19 airplanes have had a history of flap failures at various positions for several years. Flap failure may result in a significant increase in required landing distances and higher fuel consumption than planned during a diversion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-15-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that requires installation of a reinforcement fitting at the junction of the baggage floor and frame 35 on both the left- and right-hand sides of the airplane. 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 fatigue cracking in the subject area, which could result in reduced structural integrity of the airframe.
77-07-03: 77-07-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2860. Applies to models PA-31, PA-31-325, S/N's 31-7612090, 31-7612091, 31-7612092, 31-7612096, 31-7612098, 31-7612101 thru 31-7612105, 31-7612107 thru 31-7612110, and 31-7712002 thru 31-7712006; PA-31-350, S/N's 31-7652142 thru 31-7652147, 31-7652149, 31-7652151, 31-7652152, 31-7652154 thru 31-7652162, 31-7652164, 31-7652165, 31-7652167, 31-7652168, 31-7652171 thru 31-7652174, 31-7652176, 31-7752002 thru 31-7752007, 31-7752009 thru 31-7752011, 31-7752013, 31-7752014 and 31-7752017 thru 31-7752026. Compliance required within 100 hours in service. To prevent electrical terminals form shorting against the relay cover, accomplish the following: (a) Replace the spacer bushings in accordance with the instructions given in Service Bulletin No. 535, dated December 15, 1976, or with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This Amendment becomes effective April 4, 1977.