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60-16-02: 60-16-02\tBOEING: Amdt. 184 Part 507 Federal Register August 2, 1960. Applies to the Following 707-100, -200, -300 Aircraft Only: Serial Numbers 17586 Through 17605, 17609 Through 17616, 17623 Through 17625, 17628 Through 17652, 17658 Through 17680, 17692 Through 17702, 17925 Through 17927. \n\tCompliance required by December 31, 1960. \n\tWhen the fuel dump chutes are in the stowed position, the dump chute roller may not be fully engaged and the dump chute not locked in position. This has resulted in thirteen incidents of the fuel dump chutes inadvertently extending in flight. In five cases all or part of the chute and/or door was lost. In eight cases some damage was done to the chute and/or door. In order to eliminate this problem a new uplatch assembly has been designed which incorporates a position lock for the dump chute roller and a mechanism to indicate the position of the latch when the dump chute is stored. As a result of the above, the following modifications shall be accomplished as indicated: \n\t(a)\tRemove the fuel dump chute uplatch assembly and rework or install new uplatch assemblies in accordance with Boeing Service Bulletin Nos. 689 (R-3), 895 and 895A. \n\t(b)\tAfter completion of item (a) conduct the pressure check-out procedure as outlined in item (a1) of Boeing Service Bulletin No. 689 (R-3). This pressure check procedure must be conducted each time the fuel dump chute is removed and reinstalled. \n\t(c)\tA placard must be added on the exterior side of the dump chute closure panel adjacent to the indicator hole. For nomenclature and method of fabricating this placard follow procedure outlined in item (am) of Boeing Service Bulletin No. 689 (R-3). \n\t(d)\tPerform functional test as outlined in Boeing Service Bulletin Nos. 689 (R-3), 895 and 895A.
91-09-15: 91-09-15 BOEING: Amendment 39-6974. Docket No. 90-NM-250-AD. \n\n\tApplicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-79- 0008, dated August 11, 1988, equipped with engine oil filter differential pressure switches on JT9D-7R4 engines and all Model 767 series airplanes equipped with engine oil filter differential pressure switches on PW4000 engines, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent false oil filter bypass indication or loss of oil quantity from failed pressure switches, accomplish the following: \n\n\tA.\tWithin the next 60 days after the effective date of this AD, or prior to the accumulation of 10,000 total service hours, whichever occurs later, and thereafter at intervals not to exceed 10,000 total service hours, replace the engine oil filter differential pressure switch, as follows: \n\n\t\t1.\tFor Pratt & Whitney PW4000 engines: replace part number (P/N) S332T004-23 with a new -23 switch. \n\n\t\t2.\tFor Pratt & Whitney JT9D-7R4 engines: replace P/N's S332T004-2, - 25, or -29, with a new -29 switch. If a -2 or -25 switch is currently installed, modification in accordance with Boeing Service Bulletin 767-79-0008, dated August 11, 1988, is required in order to install a -29 switch configuration. \n\n\tNOTE: Reworking, modifying, or overhauling a used switch does not zero time the switch. \n\n\tB.\tPressure switches removed following the accumulation of 10,000 total service hours shall not be re-installed on any airplane. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tD.\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 SW., Renton, Washington. \n\n\tThis amendment (39-6974, AD 91-09-15) becomes effective on May 28, 1991.
2009-08-05 R1: We are correcting the address, telephone, and fax information for the reporting requirement in Airworthiness Directive (AD) 2009-08- 05, which applies to certain Liberty Aerospace Incorporated Model XL-2 airplanes. AD 2009-08-05 currently requires repetitively inspecting the exhaust muffler for cracks, replacing the exhaust muffler when cracks are found, and reporting the results of the inspections to the FAA. Since AD 2009-08-05 became effective, the FAA's Atlanta Aircraft Certification Office (ACO) moved, which has caused the office personnel problems in receiving fax and mailed copies of the inspection result reports. This document corrects the mailing address, telephone number, and fax information of the Atlanta ACO. \n\nDATES: This final rule is effective April 19, 2010. The compliance date of this AD is April 20, 2009, which is the same as the effective date of AD 2009-08-05. \n\tAs of April 20, 2009 (74 FR 16117, April 9, 2009), the Director of the Federal Register approved the incorporation by reference of Liberty Aerospace, Inc. Service Document Critical Service Bulletin (CSB) CSB- 09-001, Revision Level B, Revised on March 18, 2009.
90-09-51: 90-09-51 BOEING: Amendment 39-6659. Docket No. 90-NM-72-AD. Final copy of telegraphic AD T90-09-51, issued April 19, 1990.\n \n\tApplicability: All model 767 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent unacceptable asymmetric slat deployment, accomplish the following: \n\n\tA.\tWithin the next 20 days after the effective date of this AD, conduct a one-time inspection of the leading edge slat drive mechanism to check for torque tube damage, check for proper coupling installation, and ensure that screws on the couplings are in place and lockwired. Perform this inspection in accordance with Part I of Boeing Alert Service Bulletin 767-27A0095, Revision 1, dated February 22, 1990. \n\n\tB.\tRepair all discrepancies that are revealed by the inspection required by paragraph A., above, prior to further flight, in accordance with Boeing Alert Service Bulletin 767-27A0095, Revision 1, dated February 22, 1990. \n\n\tC.\tWithin 10 days after the completion of the inspection required by paragraph A., above, submit a report of findings of discrepancies in the leading edge slat drive mechanism to the Manager, Seattle Aircraft Certification Office, ANM-100S, 17900 Pacific Highway South, C- 68966, Seattle, Washington 98168. Reports must include a description of the defective parts, their location with regard to the drive system, the airplane serial number, and the total flight hours and flight cycles on that airplane. \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, FAA, Transport Airplane Directorate. \n\n\tNote: 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, Seattle Aircraft Certification Office. \n\n\tE.\tSpecial flight permits maybe 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 Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6659, AD 90-09-51) becomes effective on July 31, 1990, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T90-09-51, issued April 19, 1990, which contained this amendment.
92-17-04: 92-17-04 BOEING: Amendment 39-8333. Docket No. 91-NM-235-AD. Supersedes AD 91-18-09, Amendment 39-8012. \n\n\tApplicability: Model 757 series airplanes, equipped with brake part numbers (P/N) identified in paragraphs (a) and (c) of this AD, certificated in any category. \n\n\tCompliance required as indicated, unless accomplished previously. \n\n\tTo prevent loss of main landing gear braking effectiveness, accomplish the following: \n\n\t(a)\tWithin 180 days after November 12, 1991 (the effective date of Amendment 39-8012, AD 91-18-09), incorporate the maximum brake wear limits, shown below, into the FAA-approved maintenance inspection program. \n\n\n\nBrake Mfr.\nBrake P/N\nBoeing P/N\nMax. Wear Limit \nDunlop\t\nAHA 1301\nS160N020-1\n2.46 inches \nDunlop\t\nAHA 1637\nS160N020-5\n2.46 inches \nDunlop\t\nAHA 1676\nS160N020-7\n2.46 inches\nDunlop\t\nAHA 1693\nS160N020-8\n2.46 inches \nDunlop\t\nAHA 1884\nS160N020-14\n2.80 inches\nBFGoodrich\n2-1510\nS160N020-11\n1.70 inches \n\n\t(b)\tFor BFGoodrich brake P/N 2-1510 (Boeing P/N S160N020-11), in lieu of the limit specified in paragraph (a) of this AD, the maximum allowable brake wear may be extended to 2.2 inches when it is placed into the FAA-approved maintenance inspection program. \n\n\t(c)\tWithin 180 days after the effective date of this AD, accomplish the following: \n\n\t\t(1)\tFor airplanes equipped with BFGoodrich Brake P/N's 2-1457 and 2-1457-1, (Boeing P/N S160N010-43 AND S160N010-45): Accomplish the procedures specified in Section 2.B.(1) of BFGoodrich Service Bulletin 2-1457-32-13, dated January 30, 1991, or Revision 1, dated December 16, 1991 (issued February 28, 1991). Brakes found worn more than the 1.4-inch allowable brake wear must be removed and replaced, prior to further flight, with either a brake built in accordance with Section 2.B.(1)c. of the service bulletin, or a brake with more than 1.4 inches of allowable wear remaining. \n\n\t\t(2)\tFor airplanes equipped with BFGoodrich Brake P/N's 2-1457, 2-1457-1,and 2-1457-2, (Boeing P/N S160N010-43, S160N010-45, and S160N010-46): Incorporate either Figure 1 and/or Figure 2 of Section 2.B.(1)c. of BFGoodrich Service Bulletin 2-1457-32-13, dated January 30, 1991, or Revision 1, dated December 16, 1991 (issued February 28, 1991), into the FAA-approved maintenance inspection program. \n\n\t(d)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \n\n\tNOTE: 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(e)\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\t(f)\tThe procedures relative to BFGoodrich Brake P/N's 2-1457 and 2-1457-1, and 2-1457-2 shall be done in accordance with BFGoodrich Service Bulletin 2-1457-32-13, dated January 30, 1991; or BFGoodrich Service Bulletin 2-1457-32-13, Revision 1, dated December 16, 1991 (issued February 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124; and BFGoodrich Aerospace, Aircraft Wheels and Brakes, P.O. Box 340, Troy, Ohio 45373. 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., 7th Floor, Suite 700, Washington, DC. \n\n\t(g)\tThis amendment becomes effective on September 28, 1992.
91-07-19: 91-07-19 BOEING: Amendment 39-6926. Docket No. 89-NM-263-AD. \n\n\tApplicability: Model 707/720 series airplanes, listed in Boeing Document No. D6-54996, Revision B, dated December 11, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent structural failure, accomplish the following: \n\n\tA.\tAccomplish the structural modifications listed in Section 3 of Boeing Document No. D6- 54996, "Aging Airplane Service Bulletin Structural Modification Program-Model 707/720," Revision B, dated December 11, 1990, at the earlier of the following times: \n\n\t\t1.\tPrior to reaching the incorporation thresholds listed in the Boeing Document or within the next 4 years after the effective date of this AD, whichever occurs later; or \n\n\t\t2.\tPrior to reaching the incorporation thresholds specified as calendar dates in the Boeing Document. \n\n\tNOTE: The modifications required by this paragraph do not terminate the inspection requirements of any other AD unless that AD specifies that any such modification constitutes terminating action for the inspection requirements. \n\n\tB.\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, Northwest Mountain Region. \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\tC.\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\tThe modifications shall be done in accordance with Boeing Document No. D6-54996, "Aging Airplane Service Bulletin Structural Modification Program - Model 707/720," Revision B, dated December 11, 1990, which incorporates the following list of effective pages: \n\nTABLE OF EFFECTIVE PAGES\n\nPage Number\nRevision Number\nDate\n Page a \t\t\nRevision B \nDecember 11, 1990\nPage b \t\t\nInitial Release\nNovember 7, 1989\nPages c.1-d.5 \n Revision B \t\nDecember 11, 1990\nPage e \nRevision A\t\nSeptember 14, 1990 \nPages f-1.0.1 \nInitial Release\nNovember 7, 1989\nPage 1.0.2 \nRevision B \nDecember 11, 1990\nPages 1.0.3-2.0.2 \nInitial Release\nNovember 7, 1989\nPages 3.0.1-3.1.8 \nRevision B\nDecember 11, 1990\nPage 3.1.9\nInitial Release \nNovember 7, 1989\nPages 3.1.10-3.4.1 \t\nRevision B\nDecember 11, 1990\nPages 3.4.2-3.6.1 \nInitial Release \nNovember 7, 1989\nPages 4.0.1-5.1.5 \t\nRevision A\nSeptember 14, 1990\nPages 5.1.6-5.1.8 \t\nRevision B\nDecember 11, 1990\nPages 5.1.9-5.1.11 \t\nRevision A \nSeptember 14, 1990 \n\n\tBoeing Document No. DC-54996, "Aging Airplane Service Bulletin Structural Modification Program - Model 707/720," was issued by The Boeing Company on November 7, 1989. The Boeing Company has made two revisions to the November 7, 1989, document: "Revision A" was issued on September 14, 1990, and "Revision B" was issued on December 11, 1990. The preceding Table of Effective Pages depicts the original and revised pages that have received incorporation by reference approval. \n\n\tThis 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street S.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-6926, AD 91-07-19) becomes effective on April 29, 1991.
68-23-01: 68-23-01 GODFREY: Amendment 39-673. Applies to Godfrey Cabin Superchargers Type 15 Marks 6, 9, and 14, installed on, but not necessarily limited to, British Aircraft Corporation Viscount Models 744, 745D, and 810; Armstrong Whitworth Arogsy AW-650; Fokker F-27 Marks 100 and 300; Fairchild Hiller Models F27 and FH227 all series; Nihon Model YS-11; and Grumman Model G159 airplanes. Compliance required as indicated. To prevent the loss of oil from the Godfrey Cabin Compressor due to the oil metering unit or bearing covering plate becoming loose, accomplish the following unless already accomplished: (a) For British Aircraft Corporation Viscount Models 744, 745D and 810 airplanes - Within the next 50 hours' time in service after the effective date of this AD and thereafter at intervals whenever the gear box oil contents are checked, inspect the oil metering unit and bearing cover plate for security, i.e., nuts are tight and spring washers fully compressed. Secure asnecessary. (b) For all the applicable airplanes - At the next overhaul of the Supercharger or within the next 1500 hours' time in service, whichever occurs earlier, after the effective date of this AD, replace and lockwire the oil metering unit and bearing cover retaining nuts, in accordance with Godfrey Precision Products, Ltd. Service Bulletin No. 21-116-1195, Revision 2, dated February 1, 1968, or later ARB - approved revision or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (c) The repetitive inspections required by paragraph (a) may be discontinued following the incorporation of the modification required by paragraph (b). This amendment becomes effective November 21, 1968.
2010-08-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: It has been found the possibility of missing points of sealant application on the vapor barrier assembly in the wing stub rear box. In the event of fuel tank leak in this region associated with an unsealed vapor barrier assembly, migration of flammable vapors and fluids to middle electronic bay may occur, which then could lead to an uncontained fire event if the flammable vapors finds an ignition source. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
90-22-07: 90-22-07 BOEING: Amendment 39-6779. Docket No. 90-NM-105-AD. \n\n\tApplicability: Model 767 series airplanes, equipped with Pratt and Whitney JT9D-7R4 engines, as listed in Boeing Alert Service Bulletin 767-71A0057, dated February 22, 1990, certificated in any category. \n\n\tCompliance: Required within 9 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent possible engine fires and potential in-flight engine shutdowns due to oil loss, accomplish the following: \n\n\tA.\tModify the drain system on each engine in accordance with Boeing Alert Service Bulletin 767-71A0057, dated February 22, 1990. \n\n\tB.\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\tC.\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 98055-4056. \n\n\tThis amendment (39-6779, AD 90-22-07) becomes effective on November 26, 1990.
91-14-21: 91-14-21 BOEING: Amendment 39-7062. Docket No. 91-NM-33-AD. Supersedes AD 90-20-12.\n\n\tApplicability: Model 757 series airplanes, listed in Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent failure of the fixed trailing edge upper panel support beam clips and consequent damage to airplane structure and hydraulic lines, accomplish the following: \n\n\tA.\tFor airplanes line numbers 1 through 140 and 151:\n\n\t\t1.\tPrior to the accumulation of 600 total landings, or within the next 30 days after October 23, 1990, (the effective date of Amendment 39-6732, AD 90-20-12), whichever occurs later, unless previously accomplished within the last 600 landings, and thereafter at intervals not to exceed 600 landings, perform a detailed visual inspection for cracks in the fixed trailing edge upper panel support beam clips, in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. Replace cracked clips with the newly designed clips in kit number 012N8660-1 or clips in kit number 012N8546-1 after modifying, in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. Upon completion, this action terminates the inspections required above, for those clips replaced.\n\n\t\t2.\tWithin 3,000 landings after October 23, 1990, replace all affected clips with newly designed or modified clips and spacers, in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. Accomplishment of this replacement constitutes terminating action for the inspection requirements of this AD. \n \n\tB.\tFor airplanes line numbers 141 through 150 and 152 through 163:\n\n\t\t1.\tPrior to the accumulation of 600 total landings or within the next 30 days after the effective date of this amendment, whichever occurs later, unless previously accomplished within the last 600 landings, and thereafter at intervals not to exceed 600 landings, perform a detailed visual inspection for cracks in the fixed trailing edge upper panel support beam clips, in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. Replace cracked clips with the newly designed clips in kit number 012N8660-1 or clips in kit number 012N8546-1 after modifying, in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. Upon completion, this action terminates the inspections required above, for those clips replaced.\n\n\t\t2.\tWithin 3,000 landings after the effective date of this AD, replace all affected clips with newly designed or modified clips and spacers, in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. Accomplishment of this replacement constitutes terminating action for the inspection requirements of this AD.\n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\tD.\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\tE.\tThe inspections and repairs shall be done in accordance with Boeing Service Bulletin 757-57-0027, Revision 1, dated March 15, 1990. \n\n\tThis 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW.,Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.\n\n\tAirworthiness Directive 91-14-21, supersedes AD 90-20-12, Amendment 39-6732.\n\tThis amendment (39-7062, AD 91-14-21) becomes effective on August 9, 1991.