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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.
49-06-02: 49-06-02\tDOUGLAS: Applies to DC-6 Aircraft. \n\n\tTo be accomplished at every 8,000 hours of total flight time.\n \n\tReplace the following attachment bolts: (1) fuselage to center wing, (2) outer wing to center wing, (3) vertical stabilizer to fuselage, (4) horizontal stabilizer to fuselage and, (5) engine mount to firewall. The 8,000-hour period may be extended to 16,000 hours when studs 2325933 or 2340697, 2353832, 4329243 and 4333164 are replaced with studs 2361992, 2361993, 4361995 and 4361994, respectively, having letter "R" stamped on thread end and bolts in all other attachments listed are placed with NAS bolts with threads rolled after heat treatment. Bolts and studs removed from the airplane are to be scrapped and are not to be used again. \n\n\t(Douglas Service Bulletin DC-6 No. 410 contains a list of all studs and bolts affected and their replacements.)
2000-22-17: This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA - Groupe AEROSPATIALE (Socata) Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150T, Rallye 150ST, Rallye 235C, and Rallye 235E airplanes. This AD requires you to repetitively inspect, and, if necessary, replace elevator clevis and rudder governor control clevis that are too thin. 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 correct rudder and elevator control clevis that are too thin because of abnormal wear, with consequent failure of the rudder and elevator clevis. Such failure could lead to loss of directional or pitch control.
2008-14-02: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model AB 139 and AW 139 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) issued by the European Aviation Safety Agency (EASA), the Technical Agent for Italy, with which we have a bilateral agreement, which indicates that the Agusta AB 139's and AW 139's Fuselage Frame 5700 middle section is prone to fatigue damage. The actions are intended to detect cracks in the fuselage frame structure and to prevent structural failure in this area.
50-08-01: 50-08-01 SIKORSKY: Applies to All Model S-51 Helicopters. Compliance required at each 25-hour inspection. Inspect the upper longerons, Drawing S-520879, of the S-10-20-3003 tail cone mounting assembly for cracks in the area adjacent to the generator support plate and clamps, and in all the welds on the longerons adjacent to the clamps. If cracks are found, the defective member should be reinforced or replaced prior to continuing flight. (Sikorsky Service Information Circular No. 38, Revision A, dated January 4, 1950, covers this same subject.) This supersedes AD 48-11-03.
88-10-03: 88-10-03 MCDONNELL DOUGLAS: Amendment 39-5906. Applies to McDonnell Douglas Model DC-10 and KC-10 series airplanes, as listed in McDonnell Douglas Service Bulletin A24-140, dated March 24, 1988, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent fire and smoke resulting from chafing of the DC Ground Service Bus power feeder cable against the forward right cabin entrance door push-pull cable, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this airworthiness directive (AD), inspect the DC power feeder cable for evidence of chafing and inspect for minimum clearance between the DC power feeder cable and the forward right cabin entrance door push-pull cable, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin A24-140, dated March 24, 1988. \n\n\t\t1.\tIf the clearance is less than the minimum allowable, modify the installation in accordance with the service bulletin. \n\n\t\t2.\tIf there is evidence of chafing on the DC power feeder cable, repair the power cable in accordance with the service bulletin. \n\n\tB.\tAlternate means of compliance or adjustment of the compliance time, which provide an acceptable 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 airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective May 20, 1988.
2008-14-08: We are adopting a new airworthiness directive (AD) for all Boeing Model 747 airplanes listed above. This AD requires repetitive inspections for broken or missing fasteners in the single-row hinge fasteners of the forward and aft cargo doors, and related investigative/corrective actions. This AD results from reports of broken and missing fasteners in the hinges of the forward and aft cargo doors in both the body hinge segments and the door hinge segments. We are issuing this AD to detect and correct broken or missing fasteners in the hinge segments with a single fastener row, which could lead to opening of the cargo door during flight and result in rapid decompression of the airplane.