Aircraft-logs.com

Results
74-08-06: 74-08-06 DOUGLAS AIRCRAFT: Amendment 39-1810 as amended by Amendment 39-1855. Applies to Model DC-10, Series 10, 30, and 40 airplanes with the factory serial numbers as indicated in Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions. \n\n\tCompliance required as indicated. \n\n\tTo prevent a failure to actuate of the landing gear alternate freefall system caused by a jamming of the landing gear control valve slide, Part No. AYG7043-1, in the sleeve, Part No. AYG 7039-1, accomplish the following: \n\n\t(a)\tBeginning with the effective date of this AD, on each day in which the aircraft is used, and after any use of the alternate gear extension handle, check the bypass control crank for freedom of movement. The landing gear control valve, Part No. AYG7050, is located in the right hand wheel well, forward center panel of the keel webb. The bypass control crank is next to the keel webb on the forward lower end of the valve. Freedom of movement of the bypass valve is verified by manually moving the crank up and down. If the crank cannot be moved freely by hand, free the crank by exerting a downward force. The downward force exerted must not be excessive. If the crank freedom of movement is not achieved, replace the landing gear control valve, Part No. AYG7050, prior to further flight. Continue these checks for crank freedom of movement until a stop is installed on the landing gear control valve in accordance with Douglas Alert Service Bulletin No. A32-76, Revision 1, dated March 1, 1974, and Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions. Incorporation of both service bulletins is required. \n\n\t(b)\tWithin the next 1500 hours in service after the effective date of this AD, unless previously accomplished, install a stop on the landing gear control valve, Part No. AYG7050, in accordance with Douglas Alert Service Bulletin No. A32-76, Revision 1, dated March 1, 1974, and Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions. Incorporation of both service bulletins is required. This installation of an external stop on the valve housing will prevent the lever moving to a point that would allow internal jamming. \n\n\t(c)\tWithin 24 hours after the effective date of this AD unless previously accomplished, conduct an inspection of the landing gear control valve stop clearance as prescribed in Phase I of Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions if the landing gear control valve stop has been installed as required by paragraph (b) of this AD. If the clearance is .050 inch or less, Phase II of the Douglas Alert Service Bulletin No. A32-82 must be accomplished prior to next flight. \n\n\t(d)\tThe Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent inspection procedures or modifications. \n\n\t(e)\tAircraft may be operated to a base for accomplishment of the maintenance required by this AD per FAR's 21.197 and 21.199. \n\n\tAmendment 39-1810 became effective April 8, 1974. \n\n\tThis amendment 39-1855 becomes effective June 3, 1974.
2009-22-08: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes and certain Boeing Model 757-200, -200PF, and -300 series airplanes. This AD requires replacing the control switches of the forward, aft, and nose cargo doors of Model 747 airplanes; and requires replacing the control switches of cargo doors 1 and 2 of Model 757 series airplanes. This AD results from reports of problems associated with the uncommanded operation of cargo doors. We are issuing this AD to prevent injuries to persons and damage to the airplane and equipment.
90-20-14: 90-20-14 BOEING: Amendment 39-6730. Docket No. 90-NM-25-AD. \n\n\tApplicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-53- 0068, Revision 4, dated September 14, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect cracks in the forward cargo compartment sidewall frames, accomplish the following: \n\n\tA.\tExcept as provided in paragraph B., below, within the next 2,000 flight cycles after the effective date of this AD, or prior to accumulating 15,600 total flight cycles, whichever occurs later, conduct a visual inspection of the forward cargo compartment sidewall frames for cracks, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-53- 0068, Revision 4, dated September 14, 1989. Repeat the inspections at intervals not to exceed 9,000 flight cycles. \n\n\tB.\tRepair cracked structure prior to further flight, in accordance with the Accomplishment Instructions of the Boeing Service Bulletin, 727-53-0068, Revision 4, dated September 14, 1989, or earlier FAA-approved revisions. \n\n\tC.\tModification of the affected structure in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-53-0068, Revision 4, dated September 14, 1989, or earlier FAA-approved revisions, terminates the inspection requirements of paragraph A. of this AD. \n\n\tD.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tE.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tAirworthiness Directive 90-20-14 supersedes AD 83-02-08, Amendment 39-4548. \n\tAmendment 39-6730, AD 90-20-14, becomes effective on October 23, 1990.
93-19-07: 93-19-07 FOKKER: Amendment 39-8706. Docket 93-NM-53-AD. Applicability: Model F28 Mark 0100 series airplanes, equipped with Air Cruisers Company escape slide, part number D31840-(), with a cover having Air Cruisers Company part number 60750-101, 60750-103, or 61862-101; or with a cover having Fokker part number Y00294-401; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failed deployment of escape slides, which could delay or impede the evacuation of passengers during an emergency, accomplish the following: (a) Within 30 days after the effective date of this AD, modify the decorative cover on the L1 passenger door escape slide, in accordance with Fokker Service Bulletin SBF100-25-064, dated February 23, 1993. (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, 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. (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 Fokker Service Bulletin SBF100-25- 064, dated February 23, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (e) This amendment becomes effective on December 17, 1993.
85-22-01: 85-22-01 McDONNELL DOUGLAS: Amendment 39-5157. Applies to McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10A (Military) series airplanes, Fuselage Numbers 1 through 388, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent loss of engine as a result of loose engine mount bolts, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, inspect the engine-to-pylon forward and aft mount for proper clamping and inspect engine mount bolts in accordance with Accomplishment Instructions in McDonnell Douglas DC-10 Alert Service Bulletin A71-133, dated September 20, 1985, or later FAA-approved revision. For newly installed engines, the initial inspection may be 90 days from the date of installation or 30 days after the effective date of this AD whichever is later. \n\n\tB.\tIf a gap greater than .002 inch is found, before further flight, remove and replace bolts and nuts in accordance with Accomplishment Instructions in McDonnell Douglas DC-10 Alert Service Bulletin A71-133, dated September 20, 1985, or later FAA-approved revision. \n\n\tC.\tFor mounts with no gap larger than .002 inch or for mounts with bolts and nuts replaced in accordance with paragraph B., above, ensure that bolts are torqued within proper limits and that torque stripes are painted. Conduct an inspection for torque stripe alignment and take corrective action, as necessary, at intervals not to exceed 90 days, in accordance with Accomplishment Instructions of McDonnell Douglas DC-10 Alert Service Bulletin A73-133, dated September 20, 1985, or later FAA-approved revision. \n\n\tD.\tThe repetitive inspections required by paragraph C., above, may be discontinued after the engine-to-pylon forward and aft mounts are modified in accordance with McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 3, dated July 17, 1985, or later FAA-approved revision. \n\n\tE.\tAlternate means of compliance with this AD which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base for accomplishment of inspections required by this AD. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). 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. \n\n\tThis amendment becomes effective November 4, 1985.
87-24-02: 87-24-02 BOEING: Amendment 39-5768. Applies to Model 747 series airplanes, as listed in Boeing Alert Service Bulletin 747-53A2280, dated April 16, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo detect cracking of the body station (BS) 2598 longeron skin splice fittings and breakage of the tension bolts common to the fittings, accomplish the following: \n\n\tA.\tPrior to the accumulation of 10,000 landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform a detailed visual inspection of BS 2598 longeron skin splice fittings for cracking, and tension bolts common to these fittings for breakage, in accordance with Boeing Alert Service Bulletin 747-53A2280, dated April 16, 1987, or later FAA-approved revision. Reinspect the splice fittings and tension bolts common to stringer 11 longeron at intervals not to exceed 2,000 landings; and reinspect the splice fitting and tension bolts common to stringer 23 longeron at intervals not to exceed 4,000 landings. \n\n\tB.\tIf any longeron skin splice fitting is cracked, prior to further flight replace the fitting and the tension bolt common to that fitting, in accordance with Boeing Alert Service Bulletin 747-53A2280, dated April 16, 1987, or later FAA-approved revision. \n\n\tC.\tIf a tension bolt is broken, but the fitting to which it is common is not cracked, prior to further flight, replace the bolt in accordance with Boeing Alert Service Bulletin 747- 53A2280, dated April 16, 1987, or later FAA-approved revision. This constitutes terminating action for the requirement to inspect the tension bolt. \n\n\tD.\tPrior to the accumulation of 10,000 landings on new (replaced) BS 2598 longeron skin splice fittings, perform a detailed visual inspection of the splice fittings for cracking, in accordance with Boeing Alert Service Bulletin 747-53A2280, dated April 16, 1987, or later FAA-approved revision. Reinspect the splice fittingscommon to stringer 11 longeron at intervals not to exceed 3,000 landings; and reinspect the splice fittings common to stringer 23 longeron at intervals not to exceed 6,000 landings. Replace cracked fittings prior to further flight, in accordance with the service bulletin. \n\n\tE.\tAn alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective December 24, 1987.
87-04-07: 87-04-07 BOEING: Amendment 39-5531. Applies to all Model 747 series airplanes equipped with escape slides, certificated in any category. The applicability of each requirement is listed in the following paragraphs. Compliance required as indicated in the body of the AD. \n\n\tTo detect installation errors and provide satisfactory reliability of the evacuation system, accomplish the following, unless already accomplished: \n\n\tA.\tFor all Model 747 airplane doors equipped with escape slides, within nine months after the effective date of this AD or within 30 months after the date of initial delivery from Boeing, whichever occurs later, inspect the evacuation system in accordance with Boeing Service Letter 747-SL-52-35, Revision A, dated December 16, 1986, or later FAA-approved revisions, or FAA-approved equivalent, except as noted in subparagraphs A.1., A.2., and A.3., below. \n\n\t\t1.\tFor airplanes equipped with Air Cruisers slide/rafts installed in accordance with STC SA1215EA, thefollowing changes must be made to the inspections: \n\n\t\t\ta.\tParagraph 3, Step C: The strap does not require disconnecting. \n\n\t\t\tb.\tParagraph 3, Step P(3): The girt lanyard cables must be installed on both forward and aft pulleys in accordance with a Air Cruisers Installation Instructions P-11751. \n\n\t\t\tc.\tParagraph 3, Step Q(18): This step may be deleted. \n\n\t\t2.\tFor airplanes equipped with BF Goodrich slide/rafts installed in accordance with STC SA574GL or SA575GL, replace Paragraph 3, Step C and Step Q(18), with the survival kit instructions of BFGoodrich Service Bulletin 25-063. \n\n\t\t3.\tThe following records checks need not be accomplished as part of this AD:\n \n\t\tPARAGRAPH\t\t\tSTEP \n\t\t\t3\t\t\tQ(4) \n\t\t\t4\t\t\tW(3) \n\t\t\t5\t\t\t X(3) \n\t\t\t6\t\t\t AJ \n\t\t\t6\t\t\t AU(3) \n\t\t\t6\t\t\t AU(20) \n\t\t\t6\t\t\t AU(23) \n\n\t\tAirplane evacuation systems that do not meet the inspection criteria must be repaired prior to further flight in accordance with the corrective action procedure listed in the Boeing Service Letter or as amended by Air Cruisers installation instructions. \n\n\t\tNOTE: Equivalent inspections may be approved by an FAA Principal Maintenance Inspector. \n\n\tB.\tWithin the next nine months after the effective date of this AD, incorporate the inspections described in paragraph A., above, into the FAA-approved maintenance inspection program. These inspections must be accomplished at intervals not to exceed 30 months from the last inspection. \n\n\t\tNOTE: Equivalent inspections may be approved by an FAA Principal Maintenance Inspector.\n \n\tC.\tWithin 18 months after the effective date of this AD, inspect and/or modify the evacuation system in accordance with the following service bulletins, or later FAA-approved revisions: \n\n\t\t1.\tFor airplanes listed in Boeing Model 747 Service Bulletin 25-2083, dated August 12, 1970, modify the off-wing escape slide compartment latch system in accordance with that Boeing Service Bulletin. \n\n\t\t2.\tFor all Model 747 airplanes equipped with evacuation slide assemblies (Boeing Part Number 60B00006-83 thru -102) and evacuation ramp assemblies (Boeing Part Numbers 60B50076-57 thru -60) modify the slide/ramp packboard release mechanism in accordance with Boeing Model 747 Service Bulletin 25- 2141, Revision 1, dated July 19, 1971.\n \n\t\tNOTE: These units may have been installed on airplanes other than those listed in the service bulletin.\n \n\t\t3.\tFor airplanes listed in Boeing Service Bulletin 747-25-2332 Revision 2, dated September 2, 1977, modify the off-wing escape slide inflation system in accordance with that Boeing Service Bulletin. \n\n\t\t4.\tFor Model 747 airplanes with reservoir assemblies (BF Goodrich Part Numbers 4A3037- 12 and -13, 4A3038, and 4A3038-10 and -11) installed at the off-wing location, replace the actuator assembly portion of the reservoir assembly in accordance with Boeing Service Bulletin 747-25-2423 dated August 25, 1978. \n\n\t\tNOTE: These reservoir assemblies may have been installed on airplanes other than those listed in the service bulletin. \n\n\t\t5.\tFor Model 747 airplanes listed in Boeing Service Bulletin 747-25-2501, Revision 4, dated January 11, 1985, test and inspect the off-wing slide firing cable in accordance with that Boeing Service Bulletin. \n\n\t\t\ta.\tCables not meeting the test and inspection criteria must be replaced prior to further flight. \n\n\t\t\tb.\tRepeat the inspection at intervals not to exceed two years until the cables are replaced in accordance with Paragraph III.J. of Boeing Service Bulletin 747-25-2501, Revision 4, dated January 11, 1985. \n\n\t\t6.\tFor Model 747 airplanes equipped with upper deck evacuation slide assemblies (Boeing Part Numbers 60B50072-31, -32, -39, -41 thru -46, -50 thru -52, -59 thru -61, and -63 thru -65), modify the slide assemblies in accordance with Boeing Service Bulletin 747-25-2465, Revision 1, dated May 25, 1982. \n\n\t\tNOTE: These slide assemblies may have been installed on airplanes other than those listed in the service bulletin. \n\n\t\t7.\tFor Model 747 airplanes listed in Boeing Service Bulletin 747-25-2525, Revision 1, dated May 22, 1981, modify the off-wing escape slide compartment in accordance with that Boeing Service Bulletin. \n\n\t\t8.\tFor Model 747 airplanes equipped with upper deck escape slide packboard assemblies (Boeing Part Number 65B57619-41 and -42), modify the packboard in accordance with Boeing Service Bulletin 747-25-2529, dated July 10, 1981. \n\n\t\tNOTE: These packboards may have been installed on airplanes other than those listed in the service bulletin. \n\n\t\t9.\tFor airplanes listed in Boeing Service Bulletin 747-25-2592, dated June 15, 1982, modify the off-wing latch release and door opening thrusters in accordance with that Boeing Service Bulletin. \n\n\t\t10. For airplanes listed in Boeing Service Bulletin 747-25-2641, dated October 26, 1984, inspect and replace, if necessary, the off-wing door deployment thruster in accordance with that Boeing Service Bulletin. \n\n\tD.\tFor all Model 747 airplanes equipped with a combination slide/raft, within two years after the effective date of this AD, replace the Door No. 5 girt bar lifters and adjust the door floor fittings in accordance with Boeing Service Bulletin 747-52-2171, Revision 1, dated December 3, 1982, or later FAA-approved revisions.\n \n\tE.\tExcept as provided in Paragraph A. and B., an alternate means of compliance, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\tUpon request of an operator, an FAA Principal Maintenance Inspector, subject to approval by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the compliance times specified in this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator.\n \n\tG.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207; BFGoodrich Company, Dept 1809, 500 South Main Street, Akron, Ohio 44318; and Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective March 9, 1987.
2009-10-01: The FAA is superseding an existing airworthiness directive (AD) for PW JT9D-7R4 series turbofan engines. That AD currently requires removing certain reduced cooling flow 2nd stage high-pressure turbine (HPT) vane assemblies installed in certain 2nd stage HPT vane cluster assemblies. It also requires a visual and a fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal assembly, part number (P/N) 815097. This AD requires a visual and FPI of all P/N 2nd stage HPT air seal assemblies that were used with reduced cooling flow 2nd stage HPT vane assemblies. This AD results from PW identifying additional P/N air seal assemblies that are affected by the unsafe condition. We are issuing this AD to prevent uncontained failure of the 2nd stage HPT air seal assembly, leading to engine in-flight shutdown and damage to the airplane.
97-20-01 R1: 97-20-01 R1 BOEING: Amendment 39-10982. Docket 97-NM-308-AD. Revises AD 97-20-01, Amendment 39-10139.\n\n\tApplicability: Model 747 series airplanes, having line numbers 1 through 500 inclusive, equipped with Pratt & Whitney Model JT9D-3, -7, or -7Q engines, or having line numbers 202, 204, 232, or 257, equipped with General Electric Model CF6 series engines; certificated in any category; and on which the strut/wing modification has not been accomplished in accordance with either of the following AD's:\n\n\t AD 95-10-16, amendment 39-9233 (60 FR 27008, May 22, 1995), or\n\n\t AD 95-13-07, amendment 39-9287 (60 FR 33336, June 28, 1995).\n\n\tNOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.\n\n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo detect and correct fatigue cracking in the lower spar fitting lug or the lower spar fitting body, which could result in failure of the strut and separation of the engine from the airplane, accomplish the following:\n\n\t(a)\tWithin 90 days after October 7, 1997 (the effective date of AD 97-20-01, amendment 39-10139), perform a detailed visual inspection and an ultrasonic inspection to detect cracks, corrosion, or damage of the lower spar fitting body and lug, as applicable, in accordance with Figures 9 and 10 of Boeing Service Bulletin 747-54-2062, Revision 8, dated August 21, 1997.\n\n\tNOTE 2: This AD does not require an inspection of the inboard strut-to-diagonal brace attach fitting as described in Figure 1 of Boeing Service Bulletin 747-54-2062, Revision 8, dated August 21, 1997. However, this inspection is required to be accomplished as part of AD 95-20-05, amendment 39-9383 (60 FR 51705, October 10, 1995).\n\n\t\t(1)\tIf no crack, corrosion, or damage is detected, repeat the detailed visual and ultrasonic inspections thereafter at intervals not to exceed 400 landings.\n\n\t\t(2)\tIf any crack, corrosion, or damage is detected, prior to further flight, accomplish either paragraph (a)(2)(i) or (a)(2)(ii) of this AD.\n\n\t\t\t(i)\tReplace the lower spar fitting with a new steel lower spar fitting, in accordance with Part II of the Accomplishment Instructions of the service bulletin. Or\n\n\t\t\t(ii)\tModify the nacelle strut and wing structure in accordance with AD 95-10-16, amendment 39-9233 (60 FR 27008, May 22, 1995), or AD 95-13-07, amendment 39-9287 (60 FR 33336, June 28, 1995).\n\n\t(b)\tReplacement of the lower spar fitting with a new steel lower spar fitting, in accordance with Part II of the Accomplishment Instructions of any of the following service bulletins listed below, or accomplishment of modification of the nacelle strut and wing structure required by AD 95-10-16, amendment 39-9233 (60 FR 27008, May 22, 1995), or AD 95-13-07, amendment 39-9287 (60 FR 33336, June 28, 1995); constitutes terminating action for the repetitive inspection requirements of this AD.\n\n\t Boeing Service Bulletin 747-54-2062, Revision 1, dated November 13, 1980;\n\t Boeing Service Bulletin 747-54-2062, Revision 2, dated March 19, 1981;\n\t Boeing Service Bulletin 747-54-2062, Revision 3, dated August 28, 1981; \n\t Boeing Service Bulletin 747-54-2062, Revision 4, dated June 30, 1982; \n\t Boeing Service Bulletin 747-54-2062, Revision 5, dated June 1, 1984; \n\t Boeing Service Bulletin 747-54-2062,Revision 6, dated October 2, 1986;\n\t Boeing Service Bulletin 747-54-2062, Revision 7, dated December 21, 1994;\n\t Boeing Service Bulletin 747-54-2062, Revision 8, dated August 21, 1997.\n\n\t(c)\t(1)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO.\n\n\t\t(2)\tAlternative methods of compliance, approved previously in accordance with AD 97-20-01, are approved as alternative methods of compliance with the requirements of this AD.\n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.\n\n\t(d)\tSpecial flight permits may be issued in accordancewith sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.\n\n\t(e)\tCertain actions shall be done in accordance with Boeing Service Bulletin 747-54-2062, Revision 8, dated August 21, 1997. The incorporation by reference of this document was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of October 7, 1997 (62 FR 49431, September 22, 1997). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.\n\n\t(f)\tThis amendment becomes effective on February 11, 1999.
94-26-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 series airplanes, that requires inspection to detect cracking in the area of the side stay attachment lugs of the fitting subassembly of the main landing gear (MLG), and replacement of cracked subassemblies with new or serviceable subassemblies. This amendment is prompted by reports of cracking in the subassembly of the MLG. The actions specified by this AD are intended to prevent damage to and/or failure of the support structure of the MLG.