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46-12-02: 46-12-02 DOUGLAS: (Was Service Note 12 of AD-669-3.) Applies to DC3A Aircraft. \n\n\tInspection required immediately and every 100 hours thereafter on all aircraft which have beryllium copper engine mount to firewall attach fittings installed. \n\n\tInspect the engine mount to firewall attach fittings, P/N 5-81486-4 (with 4-power magnifying glass min.) in the fillet of the spot face for cracks or flaws in the material. If evidence of defects are found, replace with P/N 1042764. If cracks are not found, inspect every 100 hours until next engine change. P/N 5-81486-4 should be replaced with P/N 1042764 at engine change. \n\n\t(Douglas Service Bulletin No. 238 covers this same subject.)
94-08-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires installation of fusible trunnion pins in the shock struts and drag braces of the main landing gear (MLG). This amendment is prompted by a report of incorrectly manufactured trunnion pins that may cause the MLG to compromise the structural integrity of the wing fuel tanks. The actions specified in this AD are intended to prevent damage to the wing fuel tanks and the resultant fuel spillage and fire hazard when the maximum intended design load limits are exceeded during landing.
94-24-09 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive inspections to detect damage to the overwing fairings, and replacement or repair of structurally damaged fairings. That AD was prompted by a report indicating that an overwing fairing detached from an airplane. The actions specified by that AD are intended to prevent reduced controllability of the airplane due to loss of an overwing fairing. This amendment adds an optional terminating action for the currently required inspections, and limits the applicability of the rule.
95-03-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to detect cracks in the cleats at certain rib stations of the wing, and replacement of the cracked cleats with new cleats. This amendment is prompted by a report that, during manufacture of the wings of these airplanes, cracks were discovered in the cleats at the left- and right-hand rib station 8200 of the wing due to improper installation of certain bolts. The actions specified by this AD are intended to prevent cracking of the cleats, which could result in reduced structural integrity of the wing.
92-06-04: 92-06-04 BRITISH AEROSPACE: Amendment 39-8184. Docket No. 91-NM-206-AD. Applicability: Model BAe 125-800A series airplanes, Post-Modification 253191A and Pre-Modification 253247A, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent internal arcing in the dimmer units and smoke emission into the cockpit, accomplish the following: (a) Within 60 days after the effective date of this AD, modify the instrument integral lighting system by installing dimmer units having Page Modification AR1477 incorporated, and perform functional tests of the pilot's and co-pilot's instrument integral lighting dimmer system, in accordance with British Aerospace Service Bulletin 33-44-7670A, Revision 1, dated April 4, 1991. (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 modification shall be done in accordance with British Aerospace Service Bulletin 33- 44-7670A, Revision 1, dated April 4, 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, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on April 21, 1992.
95-02-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of the fixed engine cowling at the forward and aft crane beam attachment; and an inspection of the forward and aft crane beam to detect surface damage, and repair, if necessary. This amendment is prompted by several reports of rear cabin noise (engine rumble) during flight and while taxiing, which may have been caused by the interference between the forward and aft crane beams and the fasteners in the fixed engine cowling. The actions specified by this AD are intended to prevent chafing due to normal engine vibration, which could result in structural damage to the engine mount and possible separation of the engine from the airplane.
93-19-04: 93-19-04 PRECISION AIRMOTIVE (formerly Facet Aerospace Products (formerly Marvel-Schebler)): Amendment 39-8700. Docket 93-ANE-61. Supersedes Priority Letter AD 92-15-16 issued on July 9, 1992. Applicability: Precision Airmotive (formerly Facet Aerospace Products (formerly Marvel-Schebler)) Model MA3, MA3A, MA3PA, MA3SPA, and MA4SPA carburetors installed on but not limited to Textron Lycoming Model O-235, O-290, and O-320 series engines, and Teledyne Continental A-65, A-75, C-75, C-85, C-90, C-115, C-125, C-145, O-200, and O-300 series engines installed on but not limited to normally aspirated piston engine powered aircraft manufactured by Cessna, Piper, Beechcraft, and Mooney. Compliance: Required as indicated, unless accomplished previously. To prevent a disruption of fuel flow to the engine, resulting in engine power loss, engine failure, and damage to the aircraft, accomplish the following: (a) Prior to further flight, for carburetors repaired or rebuiltfrom November 1, 1991, through July 15, 1992, accomplish the following: (1) Visually inspect the float for Consolidated Fuel Systems (CFS) Part Number (P/N) CF 30-766 and remove the float if the date "10 91" is stamped on the top of the float lever arm, and replace with a serviceable float. NOTE: CFS Mandatory Service Bulletin CF-1-92, Revision 1, dated July 6, 1992, gives a listing of those known carburetors repaired or rebuilt during the suspect time period. NOTE: Guidance on replacing floats is contained in either Precision Airmotive (Facet) Aircraft Carburetor Service Manual, dated September 1984, or CFS Carburetor Float Kit Installation Instructions, CF 666-915. (2) Floats identified with Precision Airmotive P/N 30-766 with any date stamped on the float lever arm, or CFS P/N CF 30-766 with dates 8 89, 12 89, 1 90, 2 90, 8 90, 10 90, 1 91, 2 91, 4 91, 4 92, or 7 92 stamped on the float lever arm do not need to be removed. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on October 18, 1993.
94-08-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F-28 Mark 0100 series airplanes, that requires the installation of modified Flight Warning Computers and Flight Augmentation Computers. This amendment is prompted by reports of nuisance yaw-damper fault warnings and undetected horizontal trim motion, and the development of improved computers that eliminate these problems. The actions specified by this AD are intended to prevent nuisance warnings in the cockpit and undetected trim motion, both of which could compromise the safe takeoff of the airplane.
95-13-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Costruzioni Aeronautiche Giovanni Agusta S.p.A. (Agusta) Model A109A, A109AII, and A109C helicopters, that requires a modification of the tail boom vertical fin to create inspection openings that permit initial and repetitive visual inspections for cracks in the vertical fin rear spar attachment area. This amendment is prompted by four reports of cracks in the tail boom vertical fin rear spar attachment area. The actions specified by this AD are intended to prevent failure of the vertical fin attachment caused by cracks in the tail boom vertical fin rear spar attachment area, and subsequent loss of control of the helicopter.
95-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that requires modification of the fuel tank jettison system. This amendment is prompted by a quality survey which revealed that the electrical bonding of the fuel jettison system has insufficient protection from a lightning strike. The actions specified by this AD are intended to prevent electrical arcing and resultant fire in the event of a lightning strike.