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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.
88-24-04 R1: 88-24-04 R1 MCDONNELL DOUGLAS: Amendment 39-6066 as revised by Amendment 39-6510. Docket No. 89-NM-199-AD. \n\n\tApplicability: McDonnell Douglas Model DC-9, C-9 (Military), and DC-9-80 (MD-80) series airplanes, and Model MD-88 airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fire in the aft accessory compartment, accomplish the following: \n\n\tA.\tWithin 30 days or 300 flight hours time-in-service after December 2, 1988 (the effective date of AD 88-24-04, Amendment 39-6066), whichever occurs first, or upon the accumulation of 3,000 flight hours time-in-service since new, whichever occurs later, accomplish the following: \n\n\t\t1.\tCheck for evidence of fuel on the APU exhaust ducting and in the surrounding area in the aft accessory compartment, including the insulation blankets. Remove any fuel before the next APU start attempt. \n\n\t\t2.\tInstall a placard on or above the center instrument panel in a location that allows it to be in full view of both pilot and co-pilot, and on the aircraft logbook, stating the following: "DO NOT ATTEMPT TO RESTART APU AFTER A FALSE START UNTIL CHECK OF AFT ACCESSORY COMPARTMENT FOR FUEL IS ACCOMPLISHED." \n\n\t\t3.\tAdd the following to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM: "DO NOT ATTEMPT TO RESTART APU AFTER A FALSE START UNTIL CHECK OF AFT ACCESSORY COMPARTMENT FOR FUEL IS ACCOMPLISHED." \n\n\tB.\tWithin 36 months from the effective date of this amendment, inspect, modify, and repair the APU exhaust duct assembly in accordance with procedures described in Figures 3, 4, and 5 of McDonnell Douglas DC-9 Service Bulletin A49-40, Revision 1, dated May 16, 1989. Once the actions required by this paragraph are accomplished, the placard and AFM change required by paragraph A., above, may be removed. \n\n\tC.\tWithin 36 months from the effective date of this amendment, trim the ends of the APU forward lower frame and modify the aft pressure bulkhead insulation blanket, in accordance with procedures described in McDonnell Douglas DC-9 Service Bulletin 53-229, dated July 6, 1989. \n\n\tD.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tE.\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 uponrequest to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Group Leader, DC-9/MD-80, Technical Publications, C1-HCP (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis AD revises AD 88-24-04, Amendment 39-6066. \n\n\tThis amendment (39-6510, AD 88-24-04 R1) becomes effective on March 19, 1990.
2008-13-20: We are adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes equipped with Rolls Royce RB211-535E engines. This AD requires repetitive inspections for signs of damage of the aft hinge fittings and attachment bolts of the thrust reversers, and related investigative and corrective actions if necessary. This AD results from reports of several incidents of bolt failure at the aft hinge fittings of the thrust reversers due to, among other things, high operational loads. We are issuing this AD to prevent failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during flight, which could result in structural damage to the airplane.
87-26-04: 87-26-04 BRITISH AEROSPACE (BAe): Amendment 39-5804. Applies to Model BAe- 146 series airplanes listed in BAe Service Bulletin 24-30-00757A, Revision 1, dated September 5, 1986, certificated in any category. Compliance is required within 6 months after the effective date of this AD, unless previously accomplished. To prevent battery depletion and subsequent loss of Essential DC and Emergency DC busbars accomplish the following: A. Modify the DC power distribution in accordance with British Aerospace BAe-146 Aircraft Modification Service Bulletin 24-30-00757A, Revision 1, dated September 5, 1986. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197and 21.199 to operate airplanes to a base for the accomplishment of the 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 British Aerospace, Inc., Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 February 1, 1988.