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2008-06-20: 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * . * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actions to correct the unsafe condition on these products.
90-19-06: 90-19-06 AEROSPATIALE: Amendment 39-6727. Docket No. 90-NM-101-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes, Serial Numbers 003 through 164, which have not been modified in accordance with Aerospatiale Service Bulletin ATR42-32-0023, Revision 1, dated April 20, 1989; or ATR42-53-0045, Revision 1, dated April 21, 1989; or ATR42-53-0050 (Modification 2221), dated January 25, 1990; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the main landing gear (MLG) actuator fitting bolts due to an incorrect perpendicularity between the bolt hole axis and the fitting surface, accomplish the following: A. For airplanes Serial Numbers 003 through 155: Within 90 days after December 21, 1989 (the effective date of AD 89-24-08, Amendment 39-6396), inspect the MLG actuator fitting bolt holes for correct perpendicularity, elongation, and alignment between the bolthole axis and the fitting surface, in accordance with Aerospatiale Service Bulletin ATR42-53-0045, Revision 1, dated April 21, 1989, or Revision 2, dated January 21, 1990. 1. If no discrepancies are found, reassemble in accordance with the service bulletin. 2. If discrepancies are found, prior to further flight, rework the fitting surface and replace the bolts in accordance with the service bulletin. B. For airplanes Serial Numbers 156 through 164: Within 90 days after the effective date of this amendment, inspect the MLG actuator fitting bolt holes for correct perpendicularity, elongation, and alignment between the bolt hole axis and the fitting surface, in accordance with Aerospatiale Service Bulletin ATR42-53-0045, Revision 1, dated April 21, 1989, or Revision 2, dated January 21, 1990. 1. If no discrepancies are found, reassemble in accordance with the service bulletin.2. If discrepancies are found, prior to further flight, rework the fitting surface and replace the bolts in accordance with the service bulletin. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 90-19-06 supersedes AD 89-24-08, Amendment 39-6396. This amendment (39-6727, AD 90-19-06) becomes effective on October 23, 1990.
77-07-11: 77-07-11 PRATT & WHITNEY AIRCRAFT: Amendment 39-2872. Applies to Pratt & Whitney Aircraft JT8D-9 and -9A turbofan engine models with the following serial numbers: 665158, 665161, 665165, 665169, 665179, 665180, 665181, 665194, 665197, 665201, 665202, 665207, 665208, 665213, 665215, 665216, 665218, 665220, 665221, 665231, 665244, 665246, 665252, 665254, 665258, 665279, 665282, 665283, 665285, 665288, 665303, 665304, 665311, 665312, 665315, 665317, 665318, 665321, 665323, 665328, 665329, 665331, 665335, 665336, 665338, 665340, 665345, 665358, 665364, 665370, 665375, 665377, 665380, 665381, 665384, 665386, 665388, 665389, 665392, 665393, 665402, 665406, 665408, 665410, 665416, 665417, 665418, 665421, 665429, 665434, 665436, 665437, 665438, 665440, 665441, 665442, 665443, 665448, 665455, 665459, 665463, 665467, 665468, 665481, 665489, 665519, 665520, 665521, 665528, 665529, 665531, 665532, 665533, 665536, 665538, 665547, 665548, 665549, 665551, 665552, 665560, 665562, 665563, 665630, 665631, 665636, 665637, 665659, 665661, 665662, 665663, 665664, 665665, 665666, 665667, 665668, 665681, 665682, 665683, 666789, 666803, 666807, 666810, 666838, 666882, 666884, 666892, 666901, 666913, 674162, 674344, 674399, 674401, 674250, 674262, 674266, 674314, 674325, 674333, 674335, 674354, 674355, 674359, 674361, 674374, 674376, 674379, 674380, 674384, 674391, 674400, 674404, 674422, 674482, 674487, 674489 Compliance required as indicated prior to the accumulation of 6000 hours time in service after February 20, 1975, unless already accomplished. To preclude interference between the fourth stage turbine stator and rotor as a result of possible intermixing of different material stators, inspect for and replace all fourth stage stator vanes not FAA approved for that engine model. This supersedes Amendment 39-1835, AD 74-10-12, as amended by Amendment 39-2088. This Amendment becomes effective April 15, 1977.
76-05-07 R2: 76-05-07 R2 PIPER: Amendment 39-2540 as amended by Amendment 39-2768 is further amended by Amendment 39-4253. Applies to: PA-36-285 and PA-36-300 Serial Number 7360001 thru 8160001, 8160003, 8160009 and 8160019; PA-36-375 Serial Number 7802001 thru 8102004 inclusive, certificated in all categories. Compliance required prior to further flight, unless already accomplished, for all aircraft at a servicing facility. Aircraft located in a non-servicing area may be flown to a service area for compliance with this airworthiness directive after the pilot has inspected the three rudder horn attach bolts for adequate tightness. To prevent loss of the rudder control system, accomplish the following: 1. Remove the three bolts which attach the rudder control horn to the rudder. (Reference Piper PA-36 Service Manual, Section IV, Figure 4-3, page 4-7, Sketch "G".) 2. Verify that all three bolts are AN3-6A, Piper P/N 400440. (Note: Shank length is 25/32 minimum to 13/16 maximum.) 3. If incorrect bolts are found, replace with AN3-6A with one AN960-10 washer, Piper P/N 407564, under the head of each bolt and torque to 20 to 25 inch-pounds. Make appropriate log book entry. 4. If bolts removed are AN3-6A, reinstall with one AN960-10 washer under the head of each bolt and torque to 20 to 25 inch-pounds. Make appropriate log book entry. Piper Service Bulletins 495, 495A and 495B pertain to this subject. Amendment 39-2540 became effective March 12, 1976. Amendment 39-2768 became effective November 17, 1976. This amendment 39-4253 is effective November 16, 1981.
2020-09-03: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5 model turbofan engines with a certain diffuser case assembly installed. This AD was prompted by a report of a manufacturing quality escape that could impact the life of the diffuser case assembly. This AD requires removal of the affected diffuser case assembly from service and replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
77-04-08: 77-04-08 SWEARINGEN : Amendment 39-2840. Applies to Models SA26-T and SA26-AT. Compliance required as indicated. To prevent failures of spar brackets, P/N 26-31060-1, 26-31060-3, 26-31063-1, and 26-31063-3, accomplish the following inspections and modifications: (a) Within the next ten flight hours, unless already accomplished within the last 100 flight hours, inspect the spar brackets in accordance with Swearingen Aviation Corporation Service Bulletin A57-00-27, revised January 14, 1977, or later FAA approved revisions. (b) If cracks were found, before further flight, incorporate repair in accordance with Swearingen Aviation Corporation Service Bulletin A57-00-27, revised January 14, 1977, or later FAA approved revisions. (c) If no cracks are found at initial inspection, inspect the aircraft each 100 flight hours thereafter or until the repair is incorporated. (d) Alternate methods of spar bracket repair must be approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA. This amendment becomes effective March 1, 1977.
77-12-04: 77-12-04 MCDONNELL DOUGLAS: Amendment 39-2921. Applies to Model DC-10-10F and DC-10-30F airplanes certificated in all categories. \n\n\tCompliance required within the next 1000 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo reduce the possibility that operational errors could result in dispatch of an aircraft with the upper cargo door unlatched or unlocked, accomplish (a) and either (b) or (c) as follows: \n\n\t(a)\tInstall a lock mechanism viewing window on the upper cargo door and add a new instruction placard per McDonnell Douglas DC-10 Service Bulletin No. 52-120, dated September 4, 1974, or later FAA approved revision. \n\n\t(b)\tInstall an upper cargo door vent door with integral blockers for the torque tube and lock tube and add instruction placard per McDonnell Douglas DC-10 Service Bulletin No. 52-137, dated July 9, 1976, or later FAA approved revision, or \n\n\t(c)\tAfter each operation of the upper cargo door, prior to flight verify that the door is flush with the fuselage, that lock pin engagement has occurred by observing through the viewing port, and secure the upper cargo door by accomplishing (1) and either (2) or (3) as follows: \n\n\t\t(1)\tInstall bolt (NAS 6304-17 or NAS 6404U17) with locknut in lieu of pip pin in lock tube hole. \n\n\t\t(2)\tOpen and secure with positive lock-out devices, the upper cargo door power circuit breakers (B1-1341, B1-1342, and B1-1343) located on the flight engineer's lower main circuit breaker panel and "upper cargo door power control" circuit breaker (B1-1340) located on the forward left cabin equipment panel; or \n\n\t\t(3)\tRemove or hydraulically disconnect lock tube actuator (P/N 477667-5503). \n\n\t(d)\tEquivalent modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to base for the accomplishment of the modificationsrequired by this AD. \n\n\tThis amendment becomes effective July 22, 1977.
2020-07-19: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R(eacute)gional Model ATR72 airplanes. This AD was prompted by occurrences of smoke in the flight deck and flap extension difficulties due to wire chafing on the electrical harness under a certain panel. This AD requires modifying the clamp installation of the electrical routing on a certain rib of the left- and right-hand side of the wing rear spars, 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.
78-04-02: 78-04-02\tBOEING: Amendment 39-3140 as amended by Amendment 39-3267. Applies to all Boeing Model 737-100/200/200C/T43A series airplanes, listed in Boeing Service Bulletin No. 737-53-1048 which have not had the bolt replacement accomplished per figure 1 of that service bulletin, certificated in all categories. \n\tA.\tWithin the next 75 flight hours time-in-service after January 16, 1978, unless accomplished within the last 3,000 flight hours time-in-service, accomplish paragraph B below. \n\tB.\tRemove panels 9126 L.H. and 9226 R.H. and check all attach bolts (16 per side) of the two horizontal stabilizer hinge outboard fittings for looseness. If found loose, before further flight, tighten bolt(s) to 65-80 in.-lbs. or accomplish the bolt replacement of figure 1 of Boeing Service Bulletin No. 737-53-1048, or later FAA approved revisions, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. In the event it is impracticable to perform the inspection within 75 flight hours time-in-service after January 16, 1978, permission to ferry an airplane to a location where the inspection can be accomplished, may be obtained by contacting the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tC.\tWithin the next 3,000 flight hours time-in-service after the inspection accomplished per paragraph A of this AD, and thereafter at intervals not to exceed 3,000 flight hours time-in- service, accomplish the inspection of paragraph B. \n\tD.\tTerminating action to this AD consists of replacement of the attach bolts of the horizontal stabilizer hinge outboard fittings in accordance with Figure 1 of Boeing Service Bulletin No. 737-53-1048, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe 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). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\tAmendment 39-3140 became effective February 14, 1978. \n\tThis amendment 39-3267 becomes effective August 16, 1978.
81-09-06: 81-09-06 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4161. Applies to Model AS350 series helicopters certificated in all categories which have Bevel Gear Module P/N 350A32.0300.00 or -.01 installed, except bevel gear modules which include nitrided shaft P/N 350A32.3107.23 or -.24. (Bevel Gear Module P/N 350A32.0300.02 includes nitrided shaft, P/N 350A32.3107.23 or -.24 and is exempt from this application.) Compliance required as follows, unless already accomplished: a. For bevel gear modules with 580 or more hours' time in service since new or last overhaul, comply within 20 hours time in service after the effective date of this AD, or b. For bevel gear modules with less than 580 hours' time in service since new or last overhaul on the effective date of this AD, comply prior to accumulation of 600 hours' time in service, and c. Thereafter at intervals not to exceed 300 hours' time in service. To prevent loss of mechanical drive between the bevel gear module and the epicyclic module of the main transmission gearbox, inspect the bevel gear module for wear in accordance with procedures specified in paragraph EE of Aerospatiale TELEX Service No. 05.05 (TELEX No. 22316) dated December 24, 1980, or paragraph BB of Aerospatiale TELEX Service No. 05.06 as it applies to measuring actual spline wear, or other FAA approved equivalent. If the maximum wear depth at the level of the step on the spline exceeds 1.0 mm (0.039 inch) or if the distance between two rods of 6.35 mm (.250 inch) exceeds 72.2 mm (2.84 inches), the bevel gear module must be replaced with a serviceable module before further flight. Report defects to the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to fly aircraftto a base where this AD can be accomplished. Equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101, or by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belguim. NOTE: Aerospatiale TELEX 22316, paragraph EE, is as follows: EE. Remove main rotor mast and sun gear according to Work Cards 65 13 401 and 65 30 404. Check the wear of vertical shaft splines either by mold print, (maximum wear depth at the level of the step, 1mm (0.039 inches)) or by measurement of distance between two rods of 6.35 mm diameter. Distance between two opposite rods shall be less than 72.2 mm. If the value obtained by either one of the above methods is out of limit, return bevel gear module to an approved repair station. This AirworthinessDirective supersedes AD 81-01-05. This amendment becomes effective July 23, 1981, for all persons except those to whom it was made immediately effective by priority mail AD No. 81-09-06 dated April 23, 1981.