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86-16-04 R1: 86-16-04 R1 BRITISH AEROSPACE: Amendment 39-5383 as amended by 39-5416. Applies to Jetstream Model 3101 (all serial numbers) airplanes which have incorporated Arkansas Modification Center, Inc. (AMC) baggage pod Modification STC No. SA5900SW using baggage pod Serial Numbers 003 through 026, 028, 034, 035, 037, and 038. Compliance: Required within the next 50 landings after the effective date of this AD, unless already accomplished. NOTE: If landings are not recorded, one hour time-in-service (TIS) equals two landings. To prevent possible scoring and failure of the two flap torque tubes, and subsequent loss of control of the aircraft, accomplish the following: (a) Inspect the flap torque shaft in accordance with BAe Alert Service Bulletin (ASB) No. 27-JA850949 dated January 8, 1986, Section 2 B, "Inspection/Repair", Subparagraph (1) (1) If scored in excess of 0.030 inches in depth, before further flight replace torque shaft with a serviceable shaft.(2) If scoring does not exceed 0.030 inches in depth, (i) Before further flight repair in accordance with BAe ASB No. 27- JA850949 dated January 8, 1986, Section 2B, "Inspection/Repair", Subparagraph (3), and (ii) Inspect for cracks using a dye penetrant inspection to establish integrity of the shaft. If cracks are found, before further flight, replace torque shaft with a serviceable shaft. (b) Rework panels F21 and F22 in accordance with Arkansas Modification Center, Inc. (AMC) Mandatory Service Bulletin (MSB) No. 25-0001(-1) dated May 13, 1986, Section 2A, "ACCOMPLISHMENT INSTRUCTIONS". (c) Airplanes may be flown with the flap system rendered inoperative in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Southwest Region, Special Programs Branch, ASW-190, 4400 Blue Mound Road, Post Office Box 1689, Fort Worth, Texas 76101. Allpersons affected by this AD may obtain copies of Arkansas Modification Center, Inc., (AMC) Mandatory Service Bulletin (MSB) No. 25-0001(-1) dated May 13, 1986, referred to herein upon request to the Arkansas Modification Center, Inc., Post Office Box 3356, Adams Field, Little Rock, Arkansas 72203, and Alert Service Bulletin No. 27-JA85-0949 dated January 8, 1986, referred to herein upon request to the British Aerospace, Engineering Department, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5383 became effective on August 13, 1986. This amendment, 39-5416, becomes effective September 20, 1986.
2016-09-03: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000, FALCON 2000EX, MYSTERE-FALCON 900, and FALCON 900EX airplanes. This AD was prompted by reports of a co- pilot sliding aft on his seat during take-off at rotation. This AD requires replacement of certain springs installed on the pilot and co- pilot seats. We are issuing this AD to prevent fatigue wear, which, if not corrected, could cause the seat to slide and the pilot or co-pilot to lose contact with the controls, leading to an inadvertent input on the flight control commands during take-off or climb, possibly resulting in loss of control of the airplane.
2015-09-04 R1: We are revising Airworthiness Directive (AD) 2015-09-04 for DG Flugzeugbau GmbH Model DG-1000T gliders equipped with a Solo Kleinmotoren Model 2350 C engine. 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 engine shaft failure and consequent propeller detachment. We are issuing this AD to require actions to address the unsafe condition on these products.
2001-03-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires replacement of nuts on the clevis assemblies that support the auxiliary tracks of the inboard leading edge slats. This amendment is necessary to prevent loose or missing nuts on the clevis assemblies, which could cause the inboard leading edge slats to be loose or in an incorrect position and result in partial or total failure or loss of the slats. This action is intended to address the identified unsafe condition.
58-13-05: 58-13-05 WRIGHT: Applies to All TC18DA and TC18EA Series Engines Except as Noted. Compliance required as indicated. To improve engine reliability, the following items must be accomplished: 1. At first overhaul after August 1, 1958, but no later than March 1, 1959, install either (a) piston compression ring, Wright Aeronautical Division P/N 147414 or subsequently approved ring in the No. 2 ring groove (WAD Service Bulletins Nos. TC18-269B or TC18E-81B covers this same subject), or (b) install steel, chrome-plated compression ring, Wright Aeronautical Division P/N 139619 or subsequently approved ring in the No. 2 ring groove. In connection with this piston ring, the cylinder barrel finish, piston ring fit, and crankcase oil manifold diverter valve configuration must be in accordance with the instructions contained in WAD Service Bulletins Nos. TC18-363 and TC18E-182. 2. At first overhaul after July 1, 1958, and each succeeding overhaul, install only new, resin graphite coated pistons in the master rod cylinders (1 and 2). In other locations, continued time pistons may be used provided they are recoated with either resin or spray graphite and are otherwise satisfactory for reuse. In addition, prior to reuse, the top and second grooves of all these pistons must be inspected for ring groove step wear and contouring of the ring groove wall. If any of these conditions are found, the piston must be regrooved. WAD Repair Instruction Nos. 860468 and 72-5-12 cover this same subject. 3. Applies to TC18EA Series engines only. At the next overhaul and each succeeding overhaul, the fuel injection pump timing and fuel injection line configuration must be in accordance with either Wright Aeronautical Service Bulletins Nos. TC18E-118 or TC18E-199. 4. At next overhaul but not later than March 1, 1959, the spark advance relays used in the ignition distributors on the subject engines must be assembled with increased relay spring pressures. Detailed instructions for setting the required spring pressure are contained in Scintilla Division Service Bulletin No. 408A. 5. At first overhaul after July 1, 1958, but not later than March 1, 1959, the valve springs used in all TC18 engines must have the coil ends contoured per WAD Service Bulletins Nos. TC18-339 or TC18E-159. 6. Superseded by AD 60-08-05. 7. To insure proper retention of the power recovery turbine wheel, the shaft and shaft nut threads must be inspected for wear and distortion at every power recovery turbine overhaul. WAD Service Bulletins Nos. TC18-327 and TC18E-146 detail the techniques and limits for such inspections. In addition, at first overhaul after September 1, 1958, but not later than March 1, 1959, the power recovery turbine must be assembled with WAD P/N 147555 nut or subsequently approved turbine wheel retaining system. 8. Superseded by AD 60-03-10. 9. To insure proper retention of the power recovery turbine nozzle, WAD P/N 492D21, nozzle tonozzle support attaching screws should be removed at next PRT overhaul and replaced with either WAD P/N 6043D8 or 492D65 screws. Until this is accomplished, a daily check of the tightness of the nozzle must be made in accordance with the instructions contained in WAD letter to all operators dated June 10, 1958. 10. At first overhaul after August 1, 1958, but not later than March 1, 1959, the rocker box drain manifold and sumps must be removed in accordance with WAD Service Bulletins Nos. TC18-347 or TC18E-166.
2016-09-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of fatigue cracking of a certain chord of the pivot bulkhead. This AD requires repetitive inspections for cracking of the left side and right side forward outer chords of the pivot bulkhead, and related investigative and corrective actions if necessary. This AD also provides a modification of the pivot bulkhead, which would terminate the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the outer flanges of the left and right side forward outer chords of the pivot bulkhead, which could result in a severed forward outer chord and consequent loss of horizontal stabilizer control.
2001-01-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-01-51, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, 230, and 430 helicopters by individual letters. This AD requires visually inspecting the main rotor hydraulic actuator support (support) to verify the presence of all dowel pins and sealant between the support and transmission and verifying the proper torque of each attaching nut (nut). This amendment is prompted by the failure of a support resulting in an accident of a BHTC Model 222U helicopter. All retaining studs and shear pins were found sheared or pulled out at the junction between the support and the transmission case. The actions specified by this AD are intended to prevent failure of the support and subsequent loss of control of the helicopter.
93-13-06: 93-13-06 SHORT BROTHERS, PLC: Amendment 39-8619. Docket 92-NM-176-AD. Applicability: Model SD3-60 series airplanes; equipped with main landing gear (MLG) actuator part number (P/N) 104796004, having serial number DRG/4729/86, DRG/4730/86, DRG/5057/86, DRG/5059/86, DRG/5060/86, or DRG/5061/86; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the MLG actuator to unlock, which would prevent the extension of the MLG, accomplish the following: (a) Within 6 months after the effective date of this AD, replace the MLG actuator with a serviceable actuator that is marked "32-69SD" in accordance with Dowty Aerospace Hydraulics - Cheltenham Service Bulletin 32-69SD, Revision 2, dated January 20, 1993. (b) As of the effective date of this AD, no person shall install on any airplane a MLG actuator P/N 104796004, having serial number DRG/4729/86, DRG/4730/86, DRG/5057/86, DRG/5059/86, DRG/5060/86, or DRG/5061/86, that is not marked "32-69SD." (c) 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. (d) 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. (e) The replacement shall be done in accordance with Dowty Aerospace Hydraulics - Cheltenham Service Bulletin 32-69SD, Revision 2, dated January 20, 1993. 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 Short Brothers, PLC, 2011 Crystal Drive, suite 713, Arlington, Virginia 22202-3719. 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. (f) This amendment becomes effective on August 18, 1993.
2016-08-14: We are superseding Airworthiness Directive (AD) 2014-03-14 for all Airbus Model A330-200 and -300 series airplanes, and Model A340- 200, -300, -500, and -600 series airplanes. AD 2014-03-14 required removing bulb-type maintenance lights; installing a drain mast on certain airplanes; and installing muffs on connecting bleed elements on certain airplanes. For certain Model A340-200 and -300 series airplanes, this new AD also requires replacing certain insulation sleeves with new insulation sleeves. This AD results from fuel system reviews conducted by the airplane manufacturer. We are issuing this AD to prevent ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
77-13-10: 77-13-10 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2935. Applies to Hawker Siddeley Aviation, Ltd., Model DH/BH-125 airplanes, all series, with manufacturer's serial numbers 256056 and below and serial number 256061, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect excessive boss thickness that may exist on certain aileron inner hinge brackets (R/H and L/H) which can result in insufficient engagement and prevent self locking of the cable guard in the thread insert, accomplish the following: (a) Within 100 hours time in service after the effective date of this AD, measure the thickness of the boss of the upper and lower flange of the aileron inner hinge bracket at the point where the cable guard, P/N 25CW593-1 or -3, is mounted, in accordance with paragraphs (A)(1) and (2) of the Section titled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin SB 57-51, dated April 20, 1976, or an FAA-approved equivalent. (b) If the boss thickness at the cable guard mounting, measured in accordance with paragraph (a) of this AD, is found to be more than .35 inches at the top flange or more than .31 inches at the bottom flange, inspect the cable guards before further flight for proper security and accomplish the following: (1) Replace cable guards found improperly secured, loose, or missing, before further flight, with new cable guards fabricated and installed in accordance with paragraph (A)(3)(b) of the Section entitled "Accomplished Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin SB 57-51, dated April 20, 1976, or an FAA-approved equivalent. New cable guards fabricated and installed in accordance with this paragraph must have an exposed thread length tolerance in the range of .31 to .32 inches to provide sufficient engagement of the thread insert locking device mounted in the boss. (2) Cable guards found to be secure must be replacedwith the new cable guard in accordance with paragraph (b)(1) of this paragraph within 300 hours time in service after the inspection required by this paragraph. (c) Prior to the installation of an aileron inner bracket assembly, or a cable guard that is part of an assembly held as a spare, measure the boss thickness in accordance with paragraph (a) of this AD and if the dimensions exceed the limits specified in the lead-in sentence of paragraph (b) of this AD, replace the cable guards with new cable guards in accordance with paragraph (b)(1) of this AD. This amendment becomes effective July 25, 1977.