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75-13-06: 75-13-06 BRITISH AIRCRAFT CORPORATION: Amendment 39-2236. Applies to Viscount Model 700 Series airplanes certificated in all categories. Compliance required as indicated. To prevent the possible in-flight fatigue failure of the horizontal stabilizer, accomplish the following: (a) For horizontal stabilizer rear spars with more than 25,000 landings on the effective date of this AD, comply with paragraphs (c) and (d) of this AD within the next 10 landings or 50 hours time in service, whichever occurs first, unless already accomplished. (b) For all horizontal stabilizer rear spars not covered in paragraph (a) of this AD, comply with paragraphs (c) and (d) of this AD before the accumulation of 20,000 total landings or the lesser of 100 landings or 300 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished. (c) Inspect the rear spar of the left and right horizontal stabilizer for cracks and corrosion, and repairor replace as necessary, in accordance with CAA-approved British Aircraft Corporation (BAC) Alert Preliminary Technical Leaflet (PTL) No. 298, Issue 1, dated August 16, 1974, or an FAA-approved equivalent. (d) Accomplish BAC Modification Leaflet D.3268 or D.3269, or an FAA-approved equivalent of either, as provided in BAC PTL NO. 298, Issue 1. (e) Spar booms on which the corrosion damage exceeds the limits set forth in BAC PTL No. 298, Issue 1, may not be returned to service unless the repair of such damage is approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region of the FAA. (f) The service life limitation of the rear spar assembly of a spar boom modified in accordance with BAC Modification Leaflet D.3268, or an FAA-approved equivalent, is 2000 landings after modification or 30,000 total pre-modification and post-modification landings, whichever occurs first. (g) The service life limitation of the rear spar assembly of a spar boom modified in accordance with BAC Modification Leaflet D.3269, or an FAA-approved equivalent, is 30,000 total pre-modification and post- modification landings. (h) For the purpose of this AD, the number of landings may be determined by actual count, or, subject to the acceptance of the assigned FAA maintenance inspector, by dividing the horizontal stabilizer spar total time in service by an average flight time determined from the airplane log book to be representative for that airplane. Operators who have not kept records of landings or time in service for individual horizontal stabilizers must substitute total number of airplane landings or time in service in place thereof. This amendment becomes effective June 6, 1975.
2002-01-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arrius 1A turboshaft engines. This action requires replacement of the 10 main fuel injectors in Arrius 1A engines with new or overhauled injectors. This amendment is prompted by routine inspections conducted in the repair workshop demonstrating that some main fuel injectors were partially or totally blocked. The actions specified in this AD are intended to prevent blocked main fuel injectors that could lead to engine flameout during engine deceleration or that could prevent the engine from obtaining the 2 1/2 minute one engine inoperative (OEI) power.
82-15-04: 82-15-04 FOKKER B.V.: Amendment 39-4418. Applies to Model F28 Series 1000 and 4000 airplanes certificated in all categories, serial numbers as indicated below. Note: Some serial numbers listed may actually be 2000, 3000, 5000, or 6000 airplanes that are not presently eligible for U.S. certification. Those serial numbers may be disregarded insofar as this AD is concerned. 1. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to F28 airplanes S/N 11003-11064 and 11991-11993 inclusive. Compliance required within six months after the effective date of this AD. Install an inspection window in the passenger door per Fokker Service Bulletin F28/52-43, Part IV, dated April 16, 1974. B. Applies to F28 airplanes S/N 11003-11070, 11072-11074, and 11991- 11993 inclusive. Compliance required within six months after the effective date of this AD. Replace sliding pins inthe passenger door per Fokker Service Bulletin F28/52-44 dated April 9, 1974. C. Applies to F28 airplanes S/N 11021-11062 and 11991-11993 inclusive for the rear cargo door and 11003-11062 and 11991-11993 inclusive for the front and center cargo doors. Compliance required within six months after the effective date of this AD. Install the improved switch operating mechanism in the rear, forward, and center cargo door rabbets per Parts I & II of Fokker Service Bulletin F28/52-49, Revision 1, dated March 1, 1976. D. (1) Applies to F28 airplanes S/N 11003-11081 and 11991-11993 inclusive. Compliance required within six months after the effective date of this AD. Install a reinforced safety catch and stop assembly on the front cargo door and the center cargo door, if installed, per Part I of Fokker Service Bulletin F28/52-51 dated September 3, 1974. (2) Applies to F28 airplanes S/N 11021-11052, 11054-11061 and 11063-11076 inclusive, and S/N 11078, 11079, and 11191-11193 inclusive. Compliance required within six months after the effective date of this AD. Install a new safety catch and stop assembly on the rear cargo door per Part II of the service bulletin. E. Applies to F28 airplanes S/N 11003-11081 and 11991-11993 inclusive. Compliance required within 500 flight hours time in service after the effective date of this AD. Inspect the cargo door locking mechanism per Fokker Service Bulletin F28/52-53 dated May 10, 1974. F. Applies to F28 airplanes S/N 11003-11020 inclusive. Compliance required within 500 flight hours time in service after the effective date of this AD. Inspect and adjust the cargo door lock warning and locking mechanism for correct functioning per Fokker Service Bulletin F28/52-54 dated July 1, 1974. G. Applies to F28 airplanes S/N 11003-11081 and 11991-11993 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Inspect the cargo door latching mechanism and adjust, if necessary, per Fokker Service Bulletin F28/52-56 dated July 26, 1974. H. Applies to F28 airplanes S/N 11003-11020 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Install a safety catch on the rear cargo door per Fokker Service Bulletin F28/52-61 dated May 21, 1975. I. Applies to F28 airplanes S/N 11003-11110 and 11991-11993 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Modify the shape of the secondary guide rails at fuselage station 3870 (if in post SB F28/52- 55, Part I Configuration) and at station 4610 per Fokker Service Bulletin F28/52-66 dated April 12, 1976. J. Applies to F28 airplanes S/N 11003-11112, 11115, 11116, 11120, and 11991-11993. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Modify the actuating mechanism of the cargo door lock warning switches per Fokker Service Bulletin F28/52-80, Revision 1, dated October 23, 1978. K. Applies to F28 airplanes forward and center cargo doors - S/N 11003- 11081, 11991-11993, and 11082-11101 inclusive if S/B F28/52-51 has been incorporated; rear cargo door - S/N 11053, 11062, 11077, 11080, and 11081 if S/B F28/52-51 has been incorporated and S/N 11090-11093, 11108-11112, and 11114-11116 inclusive, and S/N 11118, 11120-11124, and 11126-11128 inclusive, S/N 11130, 11133, 11135, and 11138-11141 inclusive. Compliance required within the next 500 flight hours time in service after the effective date of this AD. Reinforce the cargo door locking handle access panels per Fokker Service Bulletin F28/52-81 dated October 1, 1977. L. Applies to F28 airplanes S/N 11003-11016 inclusive. Compliance required within 500 flight hours time in service after the effective date of this AD. Reinforce the speed brake accumulator brackets per Fokker Service Bulletin F28/53-4dated May 19, 1970. M. Applies to F28 airplanes S/N 11003-11020 inclusive and S/N 11991. Compliance required within 500 flight hours time in service after the effective date of this AD. Install a plastic separation screen and add ventilation provisions per Fokker Service Bulletin F28/53-21 dated October 11, 1971. N. Applies to F28 airplanes S/N 11003 through 11037 and 11991 through 11994. Compliance required within 500 hours time in service after the effective date of this AD. Inspect for cracks and rework if necessary the speedbrake attach hinge fitting per Fokker Service Bulletin F28/53-26, Revision 1, dated January 2, 1975. O. (1) Applies to F28 airplanes S/N 11020-11055, 11057-11061, and 11063-11071 inclusive, and S/N 11073, 11075, 11078, and 11991-11993 inclusive. Compliance required within 500 hours time in service after the effective date of this AD and at intervals of 250 flight hours thereafter until the modification in paragraph 2 has been carried out.Inspect the PLI washers in the rear cargo compartment latch brackets for correct installation per Part I of Fokker Service Bulletin F28/53-54, Revision 3, dated October 11, 1976. If one or more washers per latch fitting are incorrectly installed, proceed with paragraph 2 of this AD within the next ten hours time in service. (2) Applies to F28 S/N 11020-11090 inclusive, 11092, and 11991- 11993 inclusive. Compliance required within the next 1000 hours time in service after the effective date of this AD or within ten hours time in service if required by paragraph O.(1), above. Install MS washers and bolts in the cargo door latch fittings per the service bulletin. (3) Applies to F28 airplanes S/N 11003-11055, 11057-11061, and 11063-11071 inclusive, and S/N 11073, 11075, 11078, and 11991-11993 inclusive. Compliance required within the next 500 hours time in service after the effective date of this AD. Install MS washers and shorter bolts in the forward and center cargo doorlatch fittings per the service bulletin. P. Applies to F28 airplanes S/N 11003-11091 and 11991-11993 inclusive. Compliance required within 500 hours time in service after the effective date of this AD. To ensure the proper torquing of the MS 21250 bolts in the main entry door latch fittings, replace the dural washers with MS 20002 washers per Part V of Fokker Service Bulletin F28/51-10, Revision 1, dated July 11, 1975. Q. Applies to F28 airplanes S/N 11003-11025 inclusive and S/N 11991, 11992, and 11994. Compliance required within 500 flight hours after the effective date of this AD. To prevent stringer cracks, install connecting angles in the stabilizer torsion box at rib station 3800 per Fokker Service Bulletin F28/55-8, Revision 1, dated October 16, 1972. R. Applies to F28 airplanes S/N 11003-11064 and 11991-11993 inclusive. Compliance required within six months after the effective date of this AD. To ensure proper functioning of the horizontal stabilizer hinge bearings, inspect the bearings per Part I of Fokker Service Bulletin F28/55-14, Revision 1, dated March 15, 1974. If relative rotation does not occur between the bearings ball and the outer ring, modify the hinge bearing installation per Part II of the service bulletin within nine months of the inspection. If relative rotation does occur between the ball and the outer ring, the Part II modification must be accomplished within two years after the effective date of this AD. S. Applies to F28 airplanes S/N 11003-11020, 11022-11025, and 11991- 11993 inclusive. Compliance required within six months after the effective date of this AD. To prevent stress corrosion cracks, install bronze bushings in the stabilizer hinge brackets per Fokker Service Bulletin F28/55-17 dated October 27, 1975. T. Applies to F28 airplanes as follows: S/N 11003-11145 inclusive and S/N 11147, 11150, 11151, 11991, and 11992. Compliance required within six months after the effective date of this AD. To prevent the loss of the stabilizer hinge bolts if the nut has backed off, install an additional retaining device per Fokker Service Bulletin F28/55-21 dated May 19, 1980. U. Applies to F28 airplanes S/N 11003-11038, 11040, and 11991-11994 inclusive. Compliance required within six weeks after the effective date of this AD. Balance the aileron servo tabs per Fokker Service Bulletin F28/57-33, Revision 1, dated February 24, 1972. V. Applies to F28 airplanes S/N 11003-11123 inclusive, 11126, 11991, and 11992 which have accumulated 15,000 landings. Compliance required within two months after the effective date of this AD. To detect cracks in wing rear spar brackets, inspect per Fokker Service Bulletin F28/57-58, Revision 3, dated October 9, 1979. Repair cracks in accordance with the service bulletin. W. Applies to F28 airplanes S/N 11003-11123 inclusive and S/N 11126, 11991, and 11992. Compliance required within six months after the effective date ofthis AD. To minimize the chance of cracking bracket lugs, install chromium plated bolts and bronze bushings and inspect left-hand and right-hand rear spar bracket lugs per Fokker Service Bulletin F28/57-59 dated July 25, 1979. Repair cracked lugs in accordance with the service bulletin. X. Applies to F28 airplanes S/N 11111-11145 inclusive and S/N 11147, 11148, 11150, and 11151. Compliance required within three months after the effective date of this AD. To prevent performance deterioration, reseal the butt straps and boundary layer fences on the wing leading edge sections per Fokker Service Bulletin F28/57-61 dated April 14, 1980. 2. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. 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. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective August 23, 1982.
86-15-02: 86-15-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 5355. Applies to Model Mystere-Falcon 50 series airplanes, serial numbers 24 through 146, 148 through 158, 160, 161, and 162. Compliance is required as indicated below. To prevent engine failure due to fuel starvation, accomplish the following, unless previously accomplished: A. Within the next 21 days after the effective date of this AD, replace the actuators in the distributor blocks of the crossfeed valves and install a placard in accordance with Avion Marcel Dassault-Breguet Aviation Service Bulletin F52-28-17 (AMD-BA F50-182), dated April 4, 1986. B. 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. C. 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 bulletin from the manufacturer, may obtain copies upon request to Falcon Jet Corporation, Customer Support Department, 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 July 28, 1986.
2017-16-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by reports of cracks on the underwing longerons. This AD requires repetitive inspections of the left and right side underwing longerons for any crack, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2010-26-13: 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: Several cases of aileron terminal quadrant support brackets that were manufactured using sheet metal have been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the support bracket was due to fatigue. Failure of the aileron terminal quadrant support bracket could result in an adverse reduction of aircraft roll control. * * * * * These conditions could result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-02-09: The FAA is superseding Airworthiness Directive (AD) 2007-10- 04, which applied to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9- 82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. AD 2007-10-04 required repetitive inspections to detect cracks in the horizontal stabilizer, and related investigative and corrective actions if necessary. Since the FAA issued AD 2007-10-04, it has been determined that certain compliance times and repetitive intervals must be reduced to address the unsafe condition. This AD continues to require the actions specified in AD 2007-10-04 with revised compliance times for certain actions. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-06: 91-21-06 BRITISH AEROSPACE: Amendment 39-8053. Docket No. 91-NM-122-AD. Applicability: Model BAe 146-100A series airplanes, Serial Numbers up to and including E1152; Model BAe 146-200A series airplanes, Serial Numbers up to and including E2156; and Model BAe 146-300A series airplanes, Serial Numbers up to and including E3157; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure engine fire extinguisher medium is discharged to proper locations in the event of an engine fire, accomplish the following: (a) Within 30 days after the effective date of this AD, perform a visual inspection to detect chafing of the extinguisher pipe and clamp assemblies between the two fire extinguisher bottles in the engine nose cowls; and ensure that adequate clearance exists between the three pipe assemblies and the adjacent equipment and structure; in accordance with the instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (b) Prior to the installation of any nose cowl or engine/nose cowl combination on an operational airplane, perform a visual inspection to detect chafing of the extinguisher pipe and clamp assemblies between the two fire extinguisher bottles in the engine nose cowls; and ensure that adequate clearance exists between the three pipe assemblies and the adjacent equipment and structure; in accordance with the instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (c) If any damaged extinguisher pipe and clamp assembly is identified as a result of the inspection required by paragraph (a) or (b) of this AD, prior to further flight, repair or replace the damaged assembly in accordance with instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (d) An alternative method 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 forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (e) 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. (f) The inspection and repair or replacement requirements shall be done in accordance with British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8053, AD 91-21-06) becomes effective on November 19, 1991.
2001-26-24: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and C-9 airplanes that requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
2001-26-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires, for certain airplanes, a one-time torque test (inspection) of the attachment bolts of the forward engine mount vibration isolators to determine if the bolts are adequately torqued, and corrective action, if necessary. For all airplanes, this amendment prohibits installation of an attachment bolt on the forward engine mount vibration isolators, unless the attachment bolt is torqued within certain limits. These actions are necessary to prevent failure of the engine mount, which could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.