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85-18-04: 85-18-04 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5135. Applies to Lockheed Model L-1011-385 series airplanes, certificated in any category. To prevent the potential for electrical arcing in the cockpit windshield heating electrical wire bundle, accomplish the following within six months after the effective date of this AD, unless already accomplished: A. Re-route the C38 wire harness in accordance with Part 2, Accomplishment Instructions, of Lockheed-California Company L-1011 Service Bulletin 093-30-056, dated April 30, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. 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 these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective October 12, 1985.
76-12-06: 76-12-06 PRATT & WHITNEY AIRCRAFT: Amendment 39-2639. Applies to all Pratt and Whitney Aircraft JT8D-9, -11, -15 and -17 engines containing second stage fan blade pin, P/N 520456, rivet, P/N 520457, and bushing, P/N 520458. Compliance required as indicated unless already accomplished. A. To preclude liberation of second stage fan blades, inspect the blade pin rivet, P/N 520457, for loss of head or for missing bushing, P/N 520458, in accordance with P&WA Service Bulletin No. 4577 dated April 26, 1976, or later FAA approved revision or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, prior to the accumulation of 1200 hours time in service since new blade pin rivets were installed or within the next 300 hours time in service after the effective date of this AD, whichever is later. Inspect thereafter at intervals not exceeding 600 hours time in service since the last inspection. Remove engines from service with failed second stage fan blade pin rivets before further flight. B. Remove from service second stage fan blade pin, P/N 520456, rivet, P/N 520457, and bushing, P/N 520458, and replace with pin, P/N 758242, and rivet, P/N 760187, or other FAA parts prior to January 1, 1979. The manufacturer's service bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Pratt and Whitney Aircraft, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includesthe incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective thirty days after publication in the Federal Register.
90-08-02: 90-08-02 SUD-SERVICE (FORMERLY SUD AVIATION): Amendment 39-6558. Docket No. 89-NM-247-AD. Applicability: All Sud-Service Caravelle SE 210 Model III and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To identify and correct fatigue cracks in the nose landing gear well angles, which could result in reduction of the structural integrity within that area of the airplane, accomplish the following: A. Prior to the accumulation of 32,500 landings or within 30 days after the effective date of this AD, whichever occurs later, perform the following inspections in accordance with Sud-Service Service Bulletin 53-49, Revision 3, dated June 2, 1986: 1. Perform a visual and dye penetrant inspection of doublers and fuselage skin bordering doublers (fitted in accordance with Sud-Service Service Bulletins 53-15 and 53-36) at frame 9 and frame 17, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings. 2. Perform an X-ray inspection or low frequency eddy current inspection of skin panels under doublers at frame 9 and at frame 17, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 5,000 landings. 3. Perform a visual inspection and dye penetrant inspection of the front angles at frame 15 on airplanes not fitted with doublers in this area, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings. 4. Perform an X-ray inspection of the front angles at frame 15, on airplanes fitted with repair doublers, in accordance with the service bulletin. Repeat this inspection at intervals not to exceed 5,000 landings. B. If cracks are found, repair prior to further flight, in accordance with Sud-Service Service Bulletin 53-49, Revision 3, dated June 2, 1986. Repeat inspections thereafter at intervalsspecified in paragraph A., above. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it 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 Rue de Bayonne, 31060 Toulouse Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6558, AD 90-08-02)) becomes effective on May 4, 1990.
76-12-08: 76-12-08 WEATHERLY AVIATION COMPANY: Amendment 39-2643. Applies to Model 201B aircraft, all serial numbers which are equipped with Cleveland wheels and brakes, and Model 201C aircraft Serial Nos. 1001, 1002, and 1003 which are also equipped with Cleveland wheels and brakes, certificated in all categories.\n\n\tCompliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished.\n\n\tTo prevent failure of the weld attachment of the landing gear ring P/N 40213-14 to the wrap plate P/N 40213-15 and tube P/N 40213-16, or use of improperly ground bolt heads, which may result in jamming of the brake and loss of airplane control during ground operation, accomplish the following:\n\n\t(a)\tInspect the welding skips of the weld of the 40213-14 ring to the 40213-15 wrap plate and 40213-16 tube. If the weld skip exceeds 3/8 inch max. at the upper bolt hole or exceeds 1/2 inch max. at any other bolt hole as shown in Figure 1, before further flight replace with a P/N 40213 landing gear strut that does not exceed the weld skip limits as shown in Figure 1. Field repair by welding is not acceptable because the part is heat treated.\n\n\t(b)\tInspect the bolt heads of the AN-5-10A bolts which attach the brake to the 40213-14 ring and if any bolt head is ground off in excess of the max. 1/16 inch limit shown in Figure 2, before further flight replace with an AN-5-10A bolt that does not exceed max. 1/16 inch grind limit shown in Figure 2.\n\n\t(c)\tAircraft may be flown to a base for accomplishment of the inspections required by this AD per FAR's 21.197 and 21.199.\n\n\tNOTE 1: Weatherly Aviation Company Service Note No. 3 dated March 31, 1976 refers to this same subject.\n\n\tNOTE 2: For the requirements regarding the listing of compliance and method of compliance with this AD in the airplane's permanent maintenance record, see FAR 91.173.\n\n\tThis amendment becomes effective June 21, 1976.
92-09-07: 92-09-07 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8232. Docket No. 91-ASW-33. Applicability: All Bell Helicopter Textron, Inc., Model 206A and 206B helicopters, serial numbers (S/N) 4 through 1163, certificated in any category, equipped with a vertical fin assembly that has an external doubler, part number (P/N) 206-020-113-109, installed on the lefthand side adjacent to the supports. Compliance: Required within 30 days or 100 hours' time in service, whichever comes first, after the effective date of this AD, unless previously accomplished. To prevent failure of the vertical fin supports, which could result in loss of the vertical fin and loss of control of the helicopter, accomplish the following: (a) Inspect for cracks and modify the vertical fin supports in accordance with Part I of Bell Helicopter Alert Service Bulletin No. 206-91-60, dated June 28, 1991. (b) Prior to reinstalling the fin assembly, inspect for any gaps between the tailboomand the fin mounted inserts. If any gaps are found, comply with PART II of Bell Helicopter Alert Service Bulletin No. 206-91-60, dated June 28, 1991. If gaps are not found reassemble the aircraft in accordance with the manufacturer's maintenance manual. (c) 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, Rotorcraft Certification Office, ASW-170, 4400 Blue Mound Road, Fort Worth, Texas, 76193-0170. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (e) The inspections and modifications to the vertical fin assembly and supports, and the inspection for gaps shall be done in accordance with Bell Helicopter Alert Service Bulletin No. 206-91-60, Parts I and II, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, FAA, 4400 Blue Mound Road, Bldg. 3B, Room 158, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (f) This amendment becomes effective June 29, 1992.
75-16-01: 75-16-01 CESSNA: Amendment 39-2273. Applies to all Models 180, 182, 185, A185, U206, TU206, P206, TP206, T207 and 207 series airplanes and Model A188 series airplanes with wing fuel tanks regardless of airworthiness category. Compliance: Required as indicated, unless already accomplished. To preclude inadvertent fuel exhaustion due to incorrect fuel placarded capacities, within the next 100 hours' time in service after the effective date of this AD: A) Replace the existing fuel system placards with those specified on the following chart: PLACARD PART NUMBER AIRCRAFT MODEL (1973 thru 1975) FUEL CONFIGURATION SELECTOR VALVE WING FILLER OPENING 180J S/N 52364 thru 52554 Landplane Standard Range Long Range S1286-6 S1286-5 0705023-8 0705023-9 Floatplane Option Standard Range Long Range S1286-6 S1286-5 0705023-8 0705023-9 (Otbd.) 0705023-13 (Inbd.) 182P S/N 62251 thru 63590 Standard Range Long Range0705048-25 0705048-26 0705023-8 0705023-9 185F S/N 02263 thru 02653 Landplane & AgCarryall Standard Range Standard Range Long Range 0705019-7 (Fuel Valve) 0705019-5 (Fuel Valve) 0716113-3 0705019-6 (Fuel Valve) 0716113-4 0705023-10 0705023-10 0705023-12 Floatplane Option Standard Range Long Range 0705019-5 (Fuel Valve) 0716113-3 0705019-6 (Fuel Valve) 0716113-4 0705023-10 0705023-11 (Inbd.) 0705023-12 (Otbd.) A188B S/N 01347 thru 02027* Wing Cell Only 1605023-5 (Fuel Valve) 0705023-14 U206F & TU206F S/N 02127 thru 02675 Landplane Standard Range Long Range 0705048-21 0705048-22 0705023-10 0705023-12 Floatplane Option Standard Range Long Range 0705048-21 0705048-22 0705023-10 0705023-11 (Inbd.) 0705023-12 (Otbd.) 207 & T207 S/N 00226 thru 00283 Standard Range Long Range 0705048-23 0705048-24 0705023-10 0705023-12 With ON-OFF Fuel Valve Only ** Also applies to aircraft incorporating suffix "T" in S/Ns. NOTE: Cessna Aircraft Company provides instructions in Service Letter SE75-7 for revision of the pages of the owner's manuals affected by the reduced fuel system capacity. To avoid discrepancies between these manuals and the aircraft placards, the manuals should be revised in accordance with Cessna's instructions. B) On all models of aircraft manufactured in and prior to 1973 review the aircraft records to determine if new fuel bladder(s) have been installed since June 1, 1973, and if so, comply with Paragraph A of this AD unless it is established that the fuel cells installed were manufactured prior to June 1, 1973, and this fact is entered in the permanent aircraft records. NOTE: The owner may review the aircraft records and if he determines that new fuel bladder(s) have not been installed since June 1, 1973, may enter such information in the aircraft records. C) Alternate methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective July 30, 1975.
67-28-02: 67-28-02 BRITISH AIRCRAFT: Amdt. 39-490 as amended by Amdt. 39-911. Applies to Model BAC 1-11, 200 and 400 Series airplanes. Compliance required as indicated. To prevent deterioration of the secondary flap transmission system due to corrosion in the magnesium bearing housings, accomplish the following: (a) Within the next 250 hours' time in service after the effective date of this AD for airplanes with 2,750 or more hours' time in service, or for airplanes with less than 2,750 hours' time in service as of the effective date of this AD before the accumulation of 3,000 hours' time in service, and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, visually inspect the support bearings in the flap secondary transmission shafting for signs of corrosion or stiffness in accordance with British Aircraft Corporation BAC 1-11 Alert Service Bulletin No. 27-A-PM 2757, Issue 1, or later ARB-approved issue, or an FAA-approved equivalent. (b) If signs of corrosion or stiffness are found during the inspection required by paragraph (a), remove and dismantle the affected bearing assembly and inspect the interior of the bearing housing. If any corrosion is found, replace bearing housing before further flight with an unused magnesium bearing housing of the same part number or with an aluminum alloy bearing housing, in accordance with BAC 1-11 Service Bulletin No. 27-PM 2757 or later ARB-approved issue, or an FAA-approved equivalent. (c) The repetitive inspections required by paragraph (a) may be made at intervals not to exceed 3,000 hours' time in service from the last inspection after the bearing assembly has been inspected in accordance with paragraph (b) and reassembled with the original magnesium bearing housing or an unused replacement magnesium bearing housing and the space between the bushings is coated with Jointing Compound J.C. 5A (VX3-100/200) or U.S. equivalent Hylomar SQ32(L) or SQ32(M). (d) When a particular magnesium bearing housing is replaced with an aluminum alloy bearing housing in accordance with BAC 1-11 Service Bulletin 27-PM 2757 or later ARB- approved issue, or an FAA-approved equivalent, the repetitive inspection of that support bearing required by paragraph (a) may be discontinued. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the Amendment 39-490 effective November 4, 196 This amendment (39-911) becomes effective January 11, 1970.
92-15-10: 92-15-10 BRITISH AEROSPACE: Amendment 39-8304. Docket No. 91-NM-278-AD. Supersedes AD 91-01-02, Amendment 39-6846. Applicability: British Aerospace Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent erroneous stick shake and stick push occurrences, which could adversely affect the controllability of the airplane, accomplish the following: (a) Within 600 hours time-in-service or within 120 days after January 28, 1991 (the effective date of AD 91-01-02, Amendment 39-6846), whichever occurs first, measure the voltage and frequency outputs of Static Inverters No. 1 and No. 2, in accordance with the Accomplishment Instructions in British Aerospace Alert Service Bulletin 27-A-PM6005, Issue 1, dated March 28, 1990, or Issue 2, dated June 17, 1991. If the measured voltage and/or frequency do not conform with the tolerances as detailed in the Maintenance Manual, Paragraph E, "Stall Protection - Simulated Flight Condition Check," prior to further flight, remove the inverter from the airplane and recalibrate it in accordance with the service bulletin. (b) Repeat the measurements required by paragraph (a) of this AD at the later of the times specified in subparagraphs (b)(1) and (b)(2) of this AD: (1) Within 600 hours time-in-service or 4 months after performing the measurement required by paragraph (a) of this AD, whichever occurs first; or (2) Within 100 hours time-in-service after the effective date of this AD. (c) After performing the measurements required by paragraph (b) of this AD, repeat the measurements thereafter at intervals not to exceed 600 hours time-in-service or 4 months, whichever occurs first. (d) Within 12 months after the effective date of this AD, install Modification PM6005 in the number 1 and 2 inverters, in accordance with British Aerospace Service Bulletin 27-PM6005, dated June 11, 1991. Installation of Modification No. PM6005 in the number 1 and 2 inverters constitutes terminating action for the requirements of this AD. (e) 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. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (f) 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. (g) The measurements and recalibrations shall be done in accordance with British Aerospace Alert Service Bulletin 27-A-PM6005, Issue 1, dated March 28, 1990, or British Aerospace Alert Service Bulletin 27-A-PM6005, Issue 2, dated June 17, 1991. The modifications shall be done in accordance with British Aerospace Alert Service Bulletin 27-PM6005, dated June 11, 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 SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment becomes effective on September 8, 1992.
75-06-05 R2: 75-06-05 R2 LOCKHEED: Amendment 39-2123 as amended by Amendment 39-2684 is further amended by Amendment 39-4782. Applies to all Model 1329 airplanes Serial Numbers 5001 through 5007, 5009 through 5029, 5031 through 5034, 5036 through 5162, certificated in all categories. Compliance within the next 50 hours time in service after the effective date of this amendment to AD 75-06-05, unless a second inspection has already been accomplished in accordance with Lockheed Service Bulletin 329-269 and Supplemental Service Bulletin 329-269A during the period since the effective date of AD 75-06-05, March 14, 1975, and the effective date of this amendment, August 10, 1976. (a) To detect cracks in the fuselage main frames, inspect the frames in accordance with Lockheed Service Bulletin 329-269 and Supplemental Service Bulletin 329-269A, or later FAA approved revision, or in an equivalent manner approved by the Manager, Atlanta Aircraft Certification Office, FAA Central Region, 1075 Inner Loop Road, College Park, Georgia 30337. (b) In the event a crack or cracks are found, repair or replace the cracked frames in accordance with Lockheed Service Bulletin 329-269B, and Supplemental Service Bulletin 329- 269C, or in an equivalent manner approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. (c) Reinspect the main frames at intervals not to exceed 12 months after accomplishing paragraph (a). (d) The repetitive inspections required by paragraph (c) may be discontinued if replacement frames, part numbers JF265-2 or -3, JF266-2 or -3, JF267-2 or -3, JF268-2 or -3, and JF269-3 or -4 are installed at FS's 410, 430, 450, 470, or 490, respectively, or existing frames are modified or replaced in a manner approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. (e) Special 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. Amendment 39-2123 became effective March 14, 1975. Amendment 39-2684 became effective August 10, 1976. This Amendment 39-4782 becomes effective December 21, 1983.
93-25-14: 93-25-14 SAAB-SCANIA: Amendment 39-8778. Docket 93-NM-137-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159 inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 325 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of AC electrical power, and local area damage that may lead to further electrical failures and smoke in the cockpit, accomplish the following: (a) Within 6 months after the effective date of this AD, replace the left- and right-hand AC generator control relays, part number (P/N) SM15CXD1, with new relays, P/N SM15CXD4, at generator control positions 7XA and 8XA, in accordance with SAAB 340 Service Bulletin SAAB 340-24-022, dated October 21, 1992. (b) As of the effective date of this AD, no person shall install an AC generator control relay, P/N SM15CXD1, at generator control positions 7XA or 8XA on any airplane.(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 SAAB 340 Service Bulletin SAAB 340- 24-022, dated October 21, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordancewith 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from SAAB-SCANIA AB, SAAB Aircraft Support Product, S-581.88, Linkoping, Sweden. 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 February 14, 1994.