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80-12-07 R2: 80-12-07 R2 FOKKER: Amendment 39-8023. Docket No. 91-NM-172-AD. Revises AD 80- 12-07 R1.
Applicability: Model F-27 series airplanes, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent the unsafe conditions identified below, accomplish the following:
(a) Within the next 100 hours time-in-service after August 7, 1980 (the effective date of AD 80-12-07 R1), except as specifically provided in paragraphs (a)(40), (a)(43), and (a)(53) of this AD, accomplish the following:
(1) Applies to airplanes S/N 10105 through 10110. To prevent jamming of the nose landing gear in the retracted position due to leakage of the shock absorber, install cam, P/N 27.1-5101-001-162, at Station 1400 in accordance with the Accomplishment Instructions of Fokker F-27 Modification No. 72, dated April 22, 1959.
(2) Applies to airplanes S/N 10105 through 10108. To prevent partial loss of electrical power capacity in flight due to inadequate attachment of bus bars on panels 1, 2, and 3, modify the bus bar attachment in accordance with the Accomplishment Instructions of Fokker F-27 Modification No. 71, Issue 2, dated September 30, 1959.
(3) Applies to airplanes S/N 10105 through 10119, except S/N 10115. To prevent failure of the nose gear steering system due to trapped air in the steering motor, install by- pass lines with non-return valves over the nosewheel steering circuit follow-up valve in accordance with Fokker Modification No. 86, Issue 2, dated September 14, 1959.
(4) Applies to airplanes S/N 10105 through 10110. To prevent loss of electrical DC generator power in flight as a consequence of a single failure resulting in inadequate grounding of generator master switches, replace the grounding cable serving both switches with two separate grounding cables for the port and starboard generator switches, respectively, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. J-14, Issue 2, dated October 1, 1959.
(5) Applies to airplanes S/N 10105 through 10110 and 10116, 10118 and 10119. To prevent the loss of electrical DC generator power in flight as a consequence of a single failure resulting in inadequate grounding of the generator control panel, install additional grounding provisions for generator control panels in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. J-19, Issue 2, dated October 1, 1959.
(6) Applies to airplanes S/N 10111 through 10114 and 10120 through 10122. To prevent jamming of an emergency door as a consequence of the guide rollers springing from the guide plates, enlarge the door rollers and strengthen the guide plates in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-22, dated October 21, 1959.
(7) Applies to airplanes S/N 10105 through 10122 and 10126 through 10135. To prevent unsatisfactory operation of the control systems for controlling engine power, elevator and rudder trim tabs, gust lock, emergency shut-off valves, and fuel crossfeed, reinforce the attachment of the control cable guide assemblies in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-23, dated November 30, 1959.
(8) Applies to airplanes S/N 10105 through 10122, 10127 through 10136, 10138, and 10139. To prevent cracks in the elevator main spar web which could affect attachment of the elevator outer hinge, reinforce the elevator main spar at station 3979 in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-26, Issue 3, dated January 27, 1960.
(9) Applies to airplanes S/N 10105 through 10122 and 10126 through 10141. To prevent fatigue failure of engine control levers, install levers of improved design in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. F5, Issue 3, dated May 30, 1960.
(10) Applies to airplanes S/N 10105 through 10122, 10126, 10127, 10131 through 10136, 10138, and 10139. To prevent damage to the flap limit switches due to overtravel, relocate the flap system limit switches in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. C-17, Issue 2, dated February 2, 1960.
(11) Applies to airplanes S/N 10109 through 10122 and 10127 through 10135. To prevent asymmetric extension of wing flaps due to certain failures of the mechanical drive system, modify the flap control system in accordance with the Accomplishment Instructions of Fokker F-27 Modification No. 74, Issue 2, dated March 4, 1960.
(12) Applies to airplanes S/N 10105 through 10122 and 10126 through 10140. To prevent reduced control due to play in pilot and copilot control wheels, modify the control wheel attachment provisions in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. C-18, dated February 3, 1960.
(13) Appliesto airplanes S/N 10105 through 10122 and 10126 through 10141. To avoid internal short circuits in electrical connectors, replace the connectors with connectors of improved design in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. J-23, Issue 4, dated February 14, 1961.
(14) Applies to airplanes S/N 10105 through 10122 and 10126 through 10141 with elevators not reinforced in accordance with Fokker F-27 Service Bulletin No. B-76. To prevent failure of elevator hinge brackets which could jeopardize control of the airplane, replace the elevator hinge brackets at Stations 3979 and 2460 in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-28, Issue 2, dated July 13, 1960.
(15) Applies to airplanes S/N 10105 through 10122 and 10126 through 10141, having elevators not reinforced in accordance with Fokker F-27 Service Bulletin No. B-76. To prevent cracks in the elevator main spar web which could affect theelevator center hinge attachment, reinforce the elevator main spar at Station 2460 in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-27, Issue 2, dated July 13, 1960.
(16) Applies to airplanes S/N 10105 through 10122, 10126 through 10141, and 10143 through 10148. To prevent undue vibration stresses in propeller blades which could result in failure of a propeller blade in flight, restrict the engine idling speed to values above 7,000 rpm by revising the dial marking on the rpm indicators in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. N-3, dated April 11, 1960.
(17) Applies to airplanes S/N 10105 through 10148. To prevent failure of aileron hinge brackets, inspect the aileron hinge brackets, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-32, Issue 4, dated January 18, 1961.
(18) Applies to airplanes S/N 10105 through10122, 10126 through 10141, 10143 through 10148, 10151, and 10153. To prevent a dormant electrical failure which could result in the inability to extend the landing gear following a single failure in the landing gear electrical control circuit, modify the landing gear electrical control circuit in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. J-26, dated July 26, 1960.
(19) Applies to airplanes S/N 10105 through 10122 and 10126 through 10153. To prevent malfunction of the gust lock/engine interference system which possibly could result in takeoff with the flights controls locked, modify the gust lock system in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. F-9, Issue 2, dated November 24, 1960.
(20) Applies to airplanes S/N 10105 through 10179. To prevent blockage of the pitot-static system due to accumulation and freezing of water which could cause erroneous indications of airspeed and altitude, modify the pitot-static system in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. N-7, Issue 2, dated May 19, 1961.
(21) Applies to airplanes S/N 10105 through 10188. To prevent deformation of the H.P.C. control lever rub plate which could impair controllability by preventing feathering of the associated propeller, install a rub plate of improved design in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. F-11, Issue 2, dated November 27, 1961.
(22) Applies to all Fokker F-27 airplanes incorporating Fokker F-27 Service Bulletin No. H-10. To prevent malfunction of the engine water/methanol system due to malfunction of the non-return valve, P/N 27.1-8420-018-001, which could result in power deficiency during takeoff, dismantle and inspect the non-return valves, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. H-24, dated October 29,1962.
(23) Applies to airplanes S/N 10105 through 10213. To prevent blockage of the pitot-static system due to the accumulation and freezing of water which could cause erroneous indications of airspeed and altitude, modify the pitot-static system in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. N-19, dated December 20, 1962, and Amendment No. 1, dated July 15, 1964.
(24) Applies to airplanes S/N 10145 through 10223. To prevent unwanted propeller auto-feathering in flight due to ingress of moisture in electrical connectors V2609 and V2610, install electrical connectors of improved design in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. J-71, dated May 1, 1963.
(25) Applies to all Fokker F-27 airplanes not incorporating Fokker F-27 Service Bulletin No. G-7. To prevent failure of the propeller feathering system due to malfunction of the H.P.C. switches located on the engine firewall, inspect and test the switches, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. G-5, Issue 2, dated October 8, 1963.
(26) Applies to all Fokker F-27 airplanes not incorporating Fokker F-27 Service Bulletin No. B-146. To detect, arrest, and to prevent possible internal corrosion of the failsafe steel tubular structures of the empennage, the wing flap track support assembly, and the engine mounts, conduct X-ray inspections, and rectify as appropriate, in accordance with Section A, Planning Information, and Section B, Accomplishment Instructions, of Fokker F-27 Service Bulletin No. B-146, dated July 26, 1963, including Amendment No. 1, dated July 30, 1964.
(27) Applies to airplanes up to and including S/N 10240. To prevent damage of flight control rods due to the accumulation of water and consequent corrosion or bursting due to freezing, inspect the flight control rods, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. C-61, Issue 3, dated October 30, 1964, as amended by Amendment No. 1, dated January 20, 1965, and Amendment No. 2, dated November 24, 1966.
(28) Applies to airplanes S/N 10105 through 10253. To prevent failure of the horizontal stabilizer spar web, inspect the front and rear spar areas for cracks and loose rivets between Station 227.5 LH and RH, rectify as appropriate, and apply structural reinforcement in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-150, dated June 18, 1964, and Amendment No. 1, dated January 26, 1965.
(29) Applies to airplanes S/N 10105 through 10274. To prevent fatigue failure of structure supporting the rudder trim tab control brackets which possibly could lead to flutter of the trim tab, replace bracket, P/N 27.1-3401-026-005, with a new bracket of improved design, and reinforce the bracket supporting structure, in accordance withthe Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-169, Issue 2, dated June 10, 1965.
(30) Applies to airplanes S/N 10105 through 10274. To prevent fatigue failure of structure supporting the elevator trim tab control brackets which possibly could lead to flutter of the trim tab, replace bracket, P/N 27.1-3201-041-002, with a new bracket of improved design, and reinforce the bracket supporting structure in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. B-170, dated May 31, 1965.
(31) Applies to airplanes S/N 10249 through 10274 incorporating Fokker F-27 Service Bulletin No. I-26. To prevent failure of the brazed high-pressure tube assemblies, PNEU 370 and PNEU 371, of the pneumatic system (which operates the landing gear, brakes, and nose- wheel steering), modify the pneumatic system in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. I-30, dated July 30, 1965.
(32) Applies to airplanes S/N 10105 through 10293. To prevent jamming of nose gear doors due to deterioration of the door seals which has resulted in failure to extend the nose gear, inspect the nose wheel door seals, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 53-67, (B-185), Revision 1, dated August 15, 1967.
(33) Applies to airplanes S/N 10105 through 10316. To prevent possible distortion of the horizontal stabilizer nose section, inspect the nose section for damaged sandwich structure, and the attachment angles on the front stabilizer spar for cracks and correct location, and rectify as appropriate, in accordance with the Accomplishment Instructions, Part II, of Fokker F- 27 Service Bulletin No. 55-39, (B-204), Revision 3, dated May 15, 1967.
(34) Applies to all Fokker F-27 airplanes not incorporating Fokker F-27 Service Bulletin No. D-56. To prevent failure of the nose gear lock in the extended position due to failure of the light-alloy actuator piston, replace the light-alloy piston with a new stainless steel piston in accordance with the Accomplishment Instructions of Dunlop Service Bulletin No. 36- 95, Revision 1, dated October 21, 1966.
(35) Applies to all Fokker F-27 airplanes not incorporating Dowty Rotol Accessory Gearbox Modification No. GB 2294. To prevent failure of an accessory gearbox due to failure of the input bevel gear which could interrupt electrical and pneumatic power, incorporate an input bevel gear of improved design in accordance with Dowty Rotol Service Bulletin No. 83-291, Revision 2, dated October 1966, or Fokker F-27 Service Bulletin No. 83-12 (E-35), dated May 15, 1967.
(36) Applies to airplanes S/N 10105 through 10264 incorporating Graviner fire extinguisher top caps, P/N A126. To prevent malfunction of the engine fire extinguishing systems due to material defects in the top caps, replace top caps, P/N A126, with caps of improved material, identified as P/N A126(2), in accordance with the Embodiment Instructions of Graviner Service Bulletin No. 26-A20, dated September 30, 1964.
(37) Applies to airplanes S/N 10162 through 10355 incorporating a cargo door. To prevent possible failure of the pneumatic system due to inadequate wall thickness of the pneumatic tube located between the main bottle and the pneumatic panel, replace the pneumatic tube, PNEU 341, with a new tube of increased wall thickness, PNEU 428, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 36-23, (I-33), dated October 2, 1967.
(38) Applies to airplanes S/N 10105 through 10350. To prevent failure of an accessory gearbox front mounting flexible link due to misalignment which could result in loss of power, inspect the flexible links of the gearbox front mountings, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 83-14, dated June 24, 1968.(39) Applies to all Fokker F-27 airplanes with pneumatic systems incorporating Dunlop Dehydrator (bottle P/N ACM 16773), or Dunlop Oil & Watertrap (bottle P/N ACM 16772) manufactured prior to 1959. (Date of manufacture is marked on bottle.) To prevent pneumatic system failure due to stress corrosion of pressurized bottles, replace bottles P/N ACM 16772 and P/N ACM 16773, manufactured prior to 1959 with serviceable bottles of the same part number but manufactured in 1959 or subsequent, in accordance with Dunlop Service Bulletin No. 36-187, Revision 3, dated July 27, 1970.
(40) Applies to all Fokker F-27 airplanes. To detect and repair cracks in the rabbet area of fuel tank access doors of the lower outer wing area which possibly could reduce structural strength of the wing, inspect for cracks in the areas of the lower wing skin cut-outs of the fuel tank access doors, and rectify as appropriate, in accordance with the Compliance and Accomplishment Instructions of FokkerF-27 Service Bulletin No. 57-46, Revision 5, dated March 1, 1978.
(41) Applies to all Fokker F-27 airplanes not incorporating Fokker F-27 Service Bulletin No. 55-49. To detect and repair cracks and corrosion in fittings which attach the vertical stabilizer to the fuselage, inspect fittings for cracks and corrosion, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 55-48, Revision 2, dated February 7, 1977.
(42) Applies to all Fokker F-27 airplanes that are equipped with AiResearch aileron trim tab actuator (RH), P/N 525458, 540604-1, or 540604-2-1, but that do not incorporate Fokker F-27 Service Bulletin No. 27-105 or AiResearch Service Bulletin F27/20-12. To prevent malfunction of the RH aileron trim tab actuator due to failure of the actuator setscrew which possibly could reduce the airplane's lateral trim capability, modify the RH aileron trim tab actuator in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 27-105, dated October 19, 1973.
(43) Applies to all Fokker F-27 airplanes. To detect and repair corrosion and cracks in fittings which attach the rear spar of the horizontal stabilizer to the fuselage, inspect fittings for cracks and corrosion and rectify as appropriate, in accordance with the Compliance and Accomplishment Instructions of Fokker F-27 Service Bulletin No. 55-50, dated March 22, 1974.
(44) Applies to airplanes S/N 10446 through 10504 incorporating passenger interior. To prevent unwanted unlatching of the hatrack service panels as the result of a hard landing which could cause consequent possible interference in an emergency evacuation situation, install panel fasteners of improved design in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 25-40, dated August 8, 1974.
(45) Applies to Fokker F-27 airplanes incorporating an engine mount P/N 27.1-8101-000-403 with a serialnumber between 590 and 725. To prevent failure of the engine mount due to use of improper material when manufactured, inspect the engine mount upper tubes for cracks adjacent to the welds, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 71-25, Revision 1, dated January 30, 1975.
(46) Applies to airplanes S/N 10105 through 10522. To prevent cable slippage from drum of aileron control due to inadequate flange on aileron cable drum, inspect cable drums, P/N 27.1-5133-002-702, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 27-109, Revision No. 1, dated October 4, 1976.
(47) Applies to airplanes S/N 10105 through 10516 incorporating aileron control rod P/N 27.1-1333-004. To prevent possible disconnection of an aileron control rod from the differential sector due to failure of the control rod bearing, install washers and bearings of improved design in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 27-110, Revision 1, dated February 16, 1976.
(48) Applies to airplanes S/N 10512 and below incorporating the large cargo door. To prevent unwanted opening of the large cargo door in flight due to wear and distortion, inspect the locking and signaling provisions, and rectify as appropriate, in accordance with Part I of the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 52-55, Revision 1, dated December 22, 1975, and reinforce the door stiffening profile in accordance with Part II of that
Service Bulletin.
(49) Applies to airplanes S/N 10529, 10534, 10536 through 10541, having IPECO crew seats not incorporating IPECO Service Bulletin No. A001-25-2. To prevent unwanted movement of crew seats in flight due to wear of the track lock stopblock, incorporate track lock stopblocks of improved design in accordance with the Accomplishment Instructions, Part II, ofFokker F-27 Service Bulletin No. 25-43, dated September 6, 1976.
(50) Applies to airplanes S/N 10505 and 10507 through 10515. To prevent instability of the DC generator control system due to interaction with the static inverters which could result in malfunction of required navigation and communication equipment, modify the AC lighting conversion system in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 24-63, dated October 11, 1976.
(51) Applies to airplanes S/N 10408 through 10510. To prevent loosening of the aileron stops due to improper design which possibly could adversely affect aileron deflection and lateral control, modify the aileron stop installations in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 27-112, dated October 18, 1976.
(52) Applies to airplanes S/N 10458 and below not incorporating Fokker F-27 Service Bulletin No. 36-26 (Dunlop Service Bulletin No. 36-156). To prevent possible failure of the pneumatic system due to cracking of isolating valve bodies P/N ACM 16724 or ACM 26573 which could deprive the airplane of normal wheel braking and nosewheel steering, modify the isolating valve body in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 36-26, dated June 13, 1977, or Dunlop Service Bulletin No. 36-156, Revision 4.
(53) Applies to all Fokker F-27 airplanes that have accumulated more than 10,000 flights. Compliance is required within the next 1,000 hours time-in-service after August 7, 1980. To prevent possible fatigue cracks and loose rivets in the upper surface of the RH horizontal stabilizer torsion box, inspect the torsion box structure, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 55-53, dated October 3, 1977.
(54) Applies to airplanes S/N 10505 through 10521, 10525 through 10531, 10534 through 10557, 10559, and 10561 through 10564. To prevent loss of the main instrument panel fluorescent lighting system due to short circuiting, inspect the fluorescent lamps, and rectify as appropriate, in accordance with the Accomplishment Instructions of Fokker F-27 Service Bulletin No. 33-24, dated January 30, 1978.
(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.
NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
(c) 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 fromthe manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314.
Airworthiness Directive 80-12-07 R2 revises AD 80-12-07 R1, Amendment 39-3855.
This amendment (39-8023, AD 80-12-07 R2) becomes effective on September 10, 1991.
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90-17-10: 90-17-10 BRITISH AEROSPACE, PLC: Amendment 39-6698. Docket No. 90-NM-73-AD.
Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To detect cracks in the right and left main landing gear (MLG) pintle forward reaction rod lug and the rear bearing spigot, and to prevent a collapse of the MLG, accomplish the following:
A. Prior to the accumulation of 30,000 landings or within 1,400 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,400 landings, perform an ultrasonic inspection of the forward reaction rod lug on all pintles Pre-Modification PM3247, in accordance with British Aerospace Alert Service Bulletin 32-A-PM5492, Issue 2, dated October 18, 1989 (Reference Appendix 1, and Figures 1 and 2). If cracks are suspected as a result of this inspection, perform a dye penetrant inspection with thefront reaction rod disconnected and the spherical bearing housing and bushing removed from the pintle lug in accordance with the service bulletin.
B. Prior to the accumulation of 30,000 landings or within 1,400 landings after the effective date of this AD, whichever occurs later, unless accomplished within the last 2,800 landings, and thereafter at intervals not to exceed 4,200 landings, perform a dye penetrant inspection of the forward reaction rod lug on all pintles Pre-Modification PM3247, with the front reaction rod disconnected and the spherical bearinghousing and bushing removed from the pintle lug, in accordance with British Aerospace Alert Service Bulletin 32-A-PM5492. Issue 2, dated October 18, 1989.
C. Perform the initial and repetitive ultrasonic inspections of the right and left MLG pintle rear bearing spigots, in accordance with British Aerospace Alert Service Bulletin 32-A-PM5492, Issue 2, dated October 18, 1989, at the following intervals:
1. Prior tothe accumulation of 25,000 landings, or within 1,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,000 landings, perform an inspection of pintles having part numbers identified in paragraph 2.3 of the service bulletin.
2. Prior to the accumulation of 30,000 landings, or within 1,400 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,400 landings, perform an inspection of pintles having part numbers identified in paragraph 2.4 of the service bulletin.
3. Prior to the accumulation of 40,000 landings, or within 1,400 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,400 landings, perform an inspection of pintles having part number identified in paragraph 2.5 of the service bulletin.
D. If cracked pintles are found as a result of the inspections required by paragraphs A., B., or C. of this AD, replace the pintles prior to further flight, in accordance with British Aerospace Alert Service Bulletin 32-A-PM5492, Issue 2, dated October 18, 1989.
E. All right and left MLG pintles must be replaced prior to reaching the life limits (scrap life) identified in Appendix 1 of British Aerospace Alert Service Bulletin 32-A-PM5492, Issue 2, dated October 18, 1989.
F. 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.
G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to abase 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington.
This amendment (39-6698, AD 90-17-10) becomes effective on September 17, 1990.
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