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91-12-06: 91-12-06 GROB LUFT UND RAUMFAHRT: Amendment 39-7017. Docket No. 91- CE-05-AD. Applicability: Model G 109B motor gliders (serial numbers 6200 through 6362), certificated in any category. Compliance: Required within the next 3 calendar months after the effective date of this AD, unless already accomplished. To prevent separation of the studs in the root rib stud plate that could result in loss of the aileron and airbrake control systems, accomplish the following: (a) Inspect the security of the studs in the root rib stud plate (part number 109B- 4108) in accordance with the instructions in GROB Service Bulletin No. TM-817-29, dated August 6, 1990. If any loose studs are found, prior to further flight, repair the stud plate in accordance with the instructions in the referenced SB. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the motor glider 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, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 1000 Brussels, Belgium; Telephone (322) 513.38.30. 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. (d) All persons affected by this directive may obtain copies of the document discussed in this AD upon request to GROB Luft und Raumfahrt, D-8939 Mattsies, Federal Republic of Germany; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-7017, AD 91-12-06) becomes effective on July 5, 1991.
2009-24-05: 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: Under certain ambient conditions, ice can accumulate on the walls of the fuel pipes within the aircraft fuel system, which can then be released downstream when fuel flow demand is increased. This released ice can then collect on the fuel-to-oil heat exchanger (FOHE) front face and limit fuel flow through the FOHE. We are issuing this AD to prevent ice from blocking the FOHE, which could result in an unacceptable engine power loss, and loss of control of the airplane.
77-14-05: 77-14-05 BRITISH AIRCRAFT CORPORATION: Amendment 39-2953. Applies to BAC 1- 11 200 and 400 series airplanes, certificated in all categories, with Garrett AiResearch Models GTCP 85-115, -115C or -115CK APU's installed, that do not have British Aircraft Corporation Modification PM 5217 incorporated. Compliance is required as indicated. To prevent excessive fuel contamination of the Auxiliary Power Unit oil contents, accomplish the following: (a) Within the next 60 APU hours' time in service after the effective date of this AD, unless accomplished within the last 20 APU hours' time in service, and thereafter at intervals not to exceed 80 APU hours' time in service from the last inspection, inspect for fuel leakage in accordance with paragraph 2.1 of the Accomplishment Instructions of British Aircraft Corporation Model BAC 1-11 Service Bulletin 49-PM 5217, or an FAA-approved equivalent. (b) If the fuel leakage rate exceeds one drop per minute, prior to further use of the APU, rectify the leakage, drain and refill the oil system with fresh oil, and thereafter continue the inspections required by paragraph (a) of this AD. (c) Upon the request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667, may adjust the repetitive inspection intervals specified in paragraph (a) of this AD if the request contains substantiating data to justify the change. This amendment becomes effective August 5, 1977.
98-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 and -211 series airplanes. This action requires repetitive inspections to detect fatigue cracking of the frames of the sliding windows in the cockpit, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct fatigue cracking of the frames of the sliding windows in the cockpit, which could result in reduced structural integrity of the pressure vessel of the fuselage of the airplane.
2009-26-02: 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: It has been found the occurrence of engine anti-ice system valve failure, where the valve spring seat has broken and obstructed the anti-ice system venturi tube. * * * Therefore, should the aircraft encounter icing conditions, ice may accrete in the engine inlet lip and be ingested through the air inlet, resulting in possible engine damage and flame-out. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-19-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires revising the Limitations Section of the Airplane Flight Manual (AFM) to provide the flight crew with procedures to check the travel range of the aileron. That AD also requires inspection for damage of the shear pins of the aileron flutter damper and aileron hinge fittings, and various follow-on actions. This amendment adds a requirement for accomplishment of an installation that eliminates the need for the AFM revision. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by reports of failure of shear pins in the aileron flutter damper. The actions specified by this AD are intended to prevent damage to the aileron hinge fittings due to failed shear pins, and consequent reduced controllability of the airplane.
93-22-08: 93-22-08 JETSTREAM AIRCRAFT, LIMITED: Amendment 39-8732. Docket 93-NM-176-AD. ` Applicability: All Model 4101 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent high current arcing and overheating of certain earth post assemblies and their associated earth (ground) wires, thus creating an in-flight fire hazard, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, conduct a visual and hands-on inspection to detect discrepancies (i.e., overheating, looseness, etc.) of earth post EP2 (left) and earth post EP4 (right) and their attached earth cables, in accordance with the Accomplishment Instructions of Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993. (1) If no discrepancy is detected, no further action is required. (2) If any discrepancy is detected, prior to further flight, replace the discrepant earth post with a new earth post and earth cables in accordance with paragraph B. of the Accomplishment Instructions of Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993. (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, 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 approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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 inspections and replacement shall be done in accordance with Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3, 6 1 September 13, 1993 2, 4-5, 7, Original September 8, 1993 8, 9 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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. (e) This amendment becomes effective on December 3, 1993.
77-15-04: 77-15-04 ENSTROM: Amendment 39-2973. Applies to Enstrom Models F28C and 280C helicopters with wide chord (4.4 inch) tail rotor blades certificated in all categories. Before further flight perform a dye penetrant inspection around the circular hub including the arm base of the pitch link retainer assembly P/N 28-16320 unless already accomplished in the last ten hours time in service. Within ten (10) hours time in service after the receipt of this airmail letter, unless already accomplished, replace the wide chord tail rotor pitch link assembly P/N 28- 16320 and two (2) guide bolts P/N 28-16307 with a new wide chord tail rotor pitch link retainer assembly P/N 28-16325 and two (2) guide bolts P/N 28-16324. Enstrom Service Directive Bulletin Number 0040 pertains to this same subject. This amendment is effective July 26, 1977, and was effective immediately for all recipients of airmail letters dated June 15, 1977 which contained this amendment.
2004-13-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200B, and -200F series airplanes. This action requires initial and repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary. This action is necessary to find and fix such discrepancies, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. This action is intended to address the identified unsafe condition.
76-13-04: 76-13-04 MCDONNELL DOUGLAS: Amendment 39-2652. Applies to Douglas Model DC-10-10 and -30 series airplanes, certificated in all categories, incorporating lower galleys. \n\n\tCompliance required within the next 3000 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo provide better access to the portable oxygen units in the lower galley, relocate the two portable oxygen units originally installed outboard of the forward escape ladder in the lower galley to the port side of the forward bulkhead and adjacent to the attendant seats. Additional installations and/or other locations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tSpecial flight permits may be issued per FAR's 27.197 and 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\n\tThis amendment becomes effective August 3, 1976.