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2008-11-01 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain Model 767-200, -300, -300F, and -400ER series airplanes. That AD currently requires revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on- airplane fuel tank system components. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
93-08-10: 93-08-10 BRITISH AEROSPACE, REGIONAL AIRCRAFT LIMITED: Amendment 39-8557. Docket No. 93-CE-29-AD. Applicability: Jetstream Models 3101 and 3201 airplanes (all serial numbers), certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent main cabin door failure and separation of the door in flight, which could result in occupant decompression injuries, ejection of the occupant from the airplane, or loss of control of the airplane, accomplish the following: (a) Incorporate whichever of the following Jetstream Aircraft Limited advance amendment bulletins (AAB) that applies into the appropriate sections of the applicable airplane flight manual (AFM): Model AFM AAB Jetstream 3101 HP.4.10 8 Jetstream 3201 HP.4.16 5 These AAB's specify procedures for certain preflight main cabin door checks, and correction of any problem found. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Brussels Aircraft Certification Office. (d) The documents referenced in this AD may be obtained from Jetstream Aircraft Limited, Manager Product Support, Prestwick Airport, Ayrshire, KA9 2RW Scotland; or Jetstream Aircraft Inc., Librarian, P.O. Box 16029, Dulles International Airport, Washington, DC, 20041-6029. This information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on May 14, 1993.
93-21-01: 93-21-01 FOKKER: Amendment 39-8715. Docket 92-NM-154-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11363, inclusive, and 11408; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the occurrence of overheated brakes and blown tires, which would lead to loss of braking performance and may cause the loss of directional control of the airplane while it is on the ground, accomplish the following: (a) For the airplane having serial number 11408: Within 7 months after the effective date of this AD, remove the hydraulic system 1 return filter, having part number QA05775; and install an improved system 1 return filter, having part number QA07236; in accordance with Fokker Service Bulletin SBF100-29-021, Revision 2, dated December 22, 1992. (b) For airplanes having serial number 11244 through 11363, inclusive: Within 7 months after the effective date of this AD, removethe hydraulic systems 1 and 2 return filters, having part numbers QA05775 and QA05777, respectively; and install improved systems 1 and 2 return filters, having part numbers QA07236 and QA07237, respectively; in accordance with Fokker Service Bulletin SBF100-29- 021, Revision 1, dated July 3, 1992; or Revision 2, dated December 22, 1992. (c) As of the effective date of this AD, no person shall install hydraulic systems 1 and 2 return filters, part numbers QA05775 and QA05777, respectively, on any airplane. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approvedalternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The removal and installation shall be done in accordance with Fokker Service Bulletin SBF100-29-021, Revision 1, dated July 3, 1992; and Fokker Service Bulletin SBF100-29-021, Revision 2, dated December 22, 1992; as applicable. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.(g) This amendment becomes effective on November 26, 1993.
90-13-10: 90-13-10 FOKKER: Amendment 39-6636. Docket No. 90-NM-43-AD. Applicability: Model F27 series airplanes, Serial Numbers 10102 through 10684, 10686, 10687, and 10689 through 10692, certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless previously accomplished. To prevent loss of cockpit voice recorder and flight data recorder information, accomplish the following: A. Modify the voice recorder by installing wiring, an impact switch, a power relay, and a circuit breaker, in accordance with Fokker Service Bulletin F27/23-27, dated August 14, 1989. B. Modify the flight data recorder by installing wiring, an impact switch, a power relay, and a circuit breaker, in accordance with Fokker Service Bulletin F27/31-11, dated August 14, 1989. C. 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. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region, and a copy sent to the cognizant FAA Principal Maintenance Inspector (PMI). The PMI will then forward comments or concurrence to the Standardization Branch, ANM-113. D. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6636, AD 90-13-10) becomes effective on July 23, 1990.
2010-01-09: We are adopting a new airworthiness directive (AD) for certain Model 737-300, -400, and -500 series airplanes. This AD requires repetitive external non-destructive inspections to detect cracks in the fuselage skin along the chem-mill step at stringers S-1 and S-2 right, between station (STA) 827 and STA 847, and repair if necessary. This AD results from a report of a hole in the fuselage skin common to stringer S-1 and S-2 left, between STA 827 and STA 847 on an airplane that diverted to an alternate airport due to cabin depressurization and subsequent deployment of the oxygen masks. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-milled steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.
98-11-27: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of the existing pressure dump and relief valves in the main and auxiliary hydraulic systems with new valves. 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 failure of the pressure dump and relief valves in the main and auxiliary hydraulic systems, which could cause a loss in hydraulic pressure for roll control spoilers and brakes, and consequent reduced controllability of the airplane.
93-01-01: 93-01-01 DE HAVILLAND, INC.: Amendment 39-8454. Docket 92-NM-133-AD. Applicability: Model DHC-7 series airplanes; serial numbers 3 and subsequent, having Modification No. 7/2093 installed, except airplanes fitted with Customer Special Installation 78358 (flap indication rework); certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a takeoff with an incorrect flap indication, which could lead to insufficient lift and increased takeoff distance, resulting in reduced controllability of the airplane, accomplish the following: (a) Within 60 days after the effective date of this AD, perform a one-time inspection to detect incorrect ohm readings of the flap position trim control box assembly, in accordance with paragraph III. of de Havilland Alert Service Bulletin S.B. A7-27-86, dated December 19, 1991. If any discrepancies are detected, prior to further flight, modify the assembly in accordance with the service bulletin. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection and modification shall be done in accordance with de Havilland Alert Service Bulletin S.B. A7-27-86, dated December 19, 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 25, 1993.
88-06-03: 88-06-03 AIRBUS INDUSTRIE: Amendment 39-5871. Applies to certain Model A310 series airplanes, as listed in Service Bulletin A310-53-2025, Revision 3, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the rear pressure bulkhead, accomplish the following: A. Prior to the accumulation of 9,000 landings or within the next 3,000 landings after the effective date of this AD, whichever occurs later, accomplish the following: 1. Inspect the rear pressure bulkhead for cracks, using x-ray procedures, in accordance with paragraph 2., Accomplishment Instructions, of Airbus Industrie Service Bulletin A310-53-2024, Revision 1, dated June 20, 1986; or using eddy current procedures, in accordance with paragraph 2., Accomplishment Instructions, of Airbus Industrie Service Bulletin A310-53- 2024, Revision 3, dated February 17, 1987. If any cracks are detected, repair prior to further flight in accordance with paragraph 2.C., Repair, of the applicable service bulletin. 2. Modify the attachment of the rear pressure bulkhead to FR 80/82 in accordance with paragraph 2., Accomplishment Instructions, of Airbus Industrie Service Bulletin A310-53-2025, dated April 21, 1986, or Airbus Industrie Service Bulletin A310-53-2025, Revision 3, undated. B. For airplanes that were modified in accordance with paragraph A.2., above, after the accumulation of 6,000 landings: Within 6,000 landings after the modification, and thereafter at intervals not to exceed 12,000 landings, repeat the x-ray or eddy current inspection, as applicable, of the rear pressure bulkhead required by paragraph A.1., above. C. 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.D. 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 documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective April 22, 1988.
2009-26-05: 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: This Airworthiness Directive (AD) is prompted due to the discovery of cracks caused by stress corrosion in the main-gear support struts. All the main-gear support struts that had cracks were made from material AA2024-T351 which has a lower resistance to stress corrosion cracking. Such cracks, if undetected, could lead to the failure of the strut during landing which could then cause the Main Landing Gear (MLG) to collapse. We are issuing this AD to require actions to correct the unsafe condition on these products.
91-02-05: 91-02-05 GQ SECURITY PARACHUTES, INC.: Amendment 39-6854. Docket No. 90-NM-246-AD. Applicability: Model No. 79A1684-( ) parachute canopies approved under TSO C23b. Compliance: Required as indicated, unless previously accomplished. To prevent the failure of parachute canopy due to deteriorating canopy material, accomplish the following: A. Prior to further use after June 17, 1988 (the effective date of Amendment 39-5942, AD 88-05-08), remove or obliterate the TSO C23b marking from the parachute canopy and remove the canopy from service. B. For canopies previously granted an alternate means of compliance with AD 88-05-08 and subsequently returned to service: At the next repack after the effective date of this amendment, remove the canopy from service until the requirements of paragraph B.1. and B.2. of this AD are accomplished 1. Determine that canopy fabric tensile strength is acceptable in accordance with Parachute Industry Association PublicationPIA - Technical Standard 108, Parachute Canopy Fabric Tensile Test, Non-Destructive Method, dated January 25, 1989. 2. Test the mesh (netting) material, using Bromocresol Green Solution, to determine if it is acidic. If it is acidic, the canopy cannot be returned to service unless the acidic condition is neutralized. NOTE: Washing the canopy in detergent has been found to be effective in acid neutralization. C. Acidity tests and fabric tensile tests conducted as an approved alternate means of compliance with AD 88-05-08 meet the requirements of paragraphs B.1. and B.2. of this AD. D. 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. A copy of all documents applicable to this AD may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. Airworthiness Directive 91-02-05 supersedes AD 88-05-08, Amendment 39-5942. This amendment (39-6854, AD 91-02-05) becomes effective on January 14, 1991.