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60-02-04: 60-02-04\tBOEING: Amdt. 86 Part 507 Federal Register January 21, 1960. Applies to the following Model 707 Series aircraft only: Serial Numbers 17586 through 17591, 17609 through 17612, 17628 through 17652, 17658 through 17672, 17691, 17696 through 17702, 17925 through 17927. \n\n\tTo increase the capabilities and reliability of the Mach trim warning lights and the Mach warning and fire warning bell systems the following modification(s) shall be accomplished as indicated: \n\n\tUnless already completed, the following shall be accomplished by April 30, 1960. \n\n\t(a)\tRemove Mach and fire warning bell support bracket, Boeing P/N 69-1640, from below flight engineer's table and rework to accept redesigned warning bell assembly Boeing P/N 69-50013 or equivalent. Install reworked bracket and redesigned components as shown in Boeing Drawing 65-2801. (Boeing Service Bulletin No. 444 pertains to this same subject.) \n\n\t(b)\tInstall two diodes, Boeing assembly 69-43070-6, in the Mach trim systemresistor box and revise the indicating light circuitry such that this light will indicate when the system is not turned on as well as indicating Mach trim system malfunctions. (Boeing Service Bulletin No. 474 (R-1) describes a satisfactory modification.)
99-11-01: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-145 series airplanes. This action requires repetitive replacement of the bleed-air check valve and associated gaskets on the bleed low-pressure line of the engine, with new parts. 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 prevent failure of the bleed-air check valve on the bleed low-pressure line of the engine. Such failure could result in engine compressor stall and consequent flameout of the affected engine.
2008-06-16: 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: DCA/750XL/3A is prompted by a report from the manufacturer of the possibility that wiring loom protective sleeving is not fitted to aircraft S/N 107 through to 134. AD applicability revised to include aircraft up to S/N 134. To prevent fretting damage to the wiring loom that may lead to arcing in proximity to the fuel vent lines and the possibility of fire * * *. We are issuing this AD to require actions to correct the unsafe condition on these products.
92-06-10: 92-06-10 SOCATA GROUPE AEROSPATIALE: Amendment 39-8190; Docket No. 91-CE-81-AD. Applicability: Morane Saulnier Models MS892A150, MS892E150, MS893A, MS893E, MS894A, and MS894E airplanes (all serial numbers); and Rallye Models 235C and 235E airplanes (all serial numbers), certificated in any category. Compliance: Required initially upon the accumulation of 500 hours time-in-service (TIS) or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, and thereafter as indicated, unless already accomplished. To prevent nose wheel axle fatigue failure, accomplish the following: (a) Dye penetrant inspect the nose wheel axle assembly for cracks in accordance with the instructions in DESCRIPTION: 1) of SOCATA Groupe AEROSPATIALE Service Bulletin No. 150, dated June 1991. (1) If cracks are found, prior to further flight, replace the nose wheel axle assembly in accordance with the applicable maintenance manual, and reinspect thereafterat intervals not to exceed 500 hours TIS. (2) If no cracks are found, reinspect thereafter at intervals not to exceed 500 hours TIS. (b) At every 4th repetitive inspection interval (2,000 hours TIS) mandated in paragraphs (a)(1) and (a)(2) of this AD, replace the nose wheel axle attaching screws instead of reinstalling the existing screws as specified in the instructions of DESCRIPTION: 2) of SOCATA Groupe AEROSPATIALE SB No. 150, dated June 1991. (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) An alternative method of compliance or adjustment of the compliance times 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. (e) The inspections and replacements required by this AD shall be done in accordance with SOCATA Groupe AEROSPATIALE Service Bulletin No. 150, dated June 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 SOCATA Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France. Copies may be inspected 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, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8190) becomes effective on April 17, 1992.
2020-06-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report of cracking found on the frame of the right-hand side sliding window in the flight deck. This AD requires repetitive inspections for cracking of the vertical stiffeners of the left- and right-hand sides of the window frames and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-06-11: The FAA is adopting a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model 600N helicopters. This AD requires establishing a life limit for the main rotor (M/R) blade upper control collective/longitudinal link assembly (link assembly). This AD was prompted by the discovery that the life limit was omitted from the maintenance manual. The actions of this AD are intended to prevent an unsafe condition on these products.
82-10-03: 82-10-03 BOEING: Amendment 39-4375. Applies to Boeing Model 727 airplanes, line number 1 through 1612, certificated in all categories. Compliance is required within the next 2500 hours time-in-service from the effective date of this AD, unless already accomplished. To minimize the possibility of cross-connecting the ground spoiler hydraulic tube assemblies, accomplish either one of the following, unless already accomplished: \n\n\tA.\tReplace the ground spoiler hydraulic tube assemblies per figure 1 of Boeing Service Bulletin 727-27-202, Revision 1, dated December 18, 1981, or later revisions approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\tB.\tColor code the ground spoiler hydraulic tube assemblies per figure 2 of the same bulletin. \n\n\tAlternate means of compliance with the 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. \n\n\tSpecial 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. \n\n\tThis Amendment becomes effective June 11, 1982.
99-05-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 17, 18, 19, 23, 24, 33, 35, 36/A36, A36TC/B36TC, 45, 50, 55, 56, 58, 58P, 58TC, 60, 65, 70, 76, 77, 80, 88, and 95 series airplanes. This AD requires installing a placard on the fuel tank selector to warn of the no-flow condition that exists between the fuel tank detents. This AD is the result of reports of engine stoppage on the affected airplanes where the cause was considered to be incorrect positioning of the fuel selector. The actions specified by this AD are intended to help prevent a lack of fuel flow to the engine caused by incorrect positioning of the fuel selector, which could result in loss of engine power.
92-01-09: 92-01-09 BRITISH AEROSPACE: Amendment 39-8133. Docket 91-NM-266-AD. Applicability: Model series airplanes; as listed in British Aerospace Service Bulletin 28-86, dated June 28, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent an in-flight fire hazard in the rear equipment bay, accomplish the following: (a) Within 60 days after the effective date of this AD, accomplish a visual inspection for proper alignment of fuel feed pipes at pipe joint couplings, in accordance with British Aerospace Service Bulletin SB 28-86, dated June 28, 1991. If misalignment is detected outside the specifications cited in the service bulletin, prior to further flight, correct the alignment by installing an "O" ring modification and a fuel pipe clamping modification, in accordance with the service bulletin. (b) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. (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 realignment required by this AD shall be done in accordance with British Aerospace Service Bulletin SB 28-86, dated June 28, 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. (e) This amendment (39-8133, AD 92-01-09) becomes effective on January 24, 1992.
2020-05-17: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318-112, A319-111, A319-112, A319-113, A319- 114, A319-115, A319-131, A319-132, A319-133, A320-211, A320-212, A320- 214, A320-216, A320-231, A320-232, A320-233, A320-251N, and A320-271N airplanes. This AD was prompted by a report of marginal clearance between certain fuel sensor covers on both left-hand (LH) and right- hand (RH) wings. This AD requires the replacement of certain fuel level sensor brackets, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.