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80-15-01: 80-15-01 LOCKHEED-CALIFORNIA: Amendment 39-3840. Applies to Lockheed Model L- 1011-385 Series Airplanes certified in all categories. Compliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a possible burst type failure of the landing gear alternate brake/alternate landing gear down accumulator, accomplish the following: (a) Unless previously accomplished within 2200 hours' time in service prior to the effective date of this AD, (1) Inspect all accumulators Lockheed P/N 672273-101 (Bendix P/N 3186608) and Lockheed P/N 672273-103 (Bendix P/N 3186608-2) in accordance with Lockheed Alert Service Bulletin 093-32-A121 dated November 11, 1976, or, (2) Replace accumulators with accumulators reworked per Lockheed Service Bulletin 093-32-121 dated October 17, 1977. (b) Accumulators which fail the inspection, prior to further flight operations, must be either: (1) Removedand replaced with an accumulator which has passed the inspection or, (2) Removed and replaced with an accumulator which has been reworked per (a)(2) above or, (3) Remove the affected accumulator and accomplish the following actions in accordance with Lockheed Alert Service Bulletin 093-32-A121, dated November 11, 1976. (i) Cap pneumatic and hydraulic lines. (ii) Install landing gear alternate brake/alternate landing gear down accumulator inoperative placard in cockpit; (iii) Incorporate FAA-approved Appendix 11 dated November 17, 1976, in the FAA-approved AFM, LR 25925. Appendix 11 provides special procedures for operation of the L-1011 with landing gear alternate brake/alternate landing gear down accumulator removed. (c) Accumulators which passed inspection per (a)(1) or which were used as a replacement accumulator per (b)(1) must be reinspected per (a)(1) every 2200 hours' time in service until replaced with accumulators reworked per (a)(2).(d) Equivalent inspections and/or modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This supersedes Amendment 39-2783 (41 FR 53779), AD 76-25-01. This Amendment 39-3840 becomes effective July 17, 1980.
2017-11-06: We are superseding Airworthiness Directive (AD) 2014-05-32 for all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-100 turbofan engines. AD 2014-05-32 required one-time eddy current inspection (ECI) of affected engines with certain diffuser and high-pressure turbine (HPT) cases installed. AD 2014-05-32 also required a fluorescent-penetrant inspection (FPI) of the diffuser case rear flange and the HPT case front flange. This AD requires additional repetitive, on-wing ECI inspections. This AD was prompted by the manufacturer determining through analysis that the inspections required by AD 2014-05-32 are not adequate to maintain safety for certain diffuser cases. We are issuing this AD to correct the unsafe condition on these products.
80-06-03: 80-06-03 CESSNA: Amendment 39-3713. Applies to the following models and serial number airplanes certificated in all categories: MODELS SERIAL NUMBERS 150M 15078506 through 15079405 A150M A1500685 through A1500734 152 15279406 through 15283354 A152 A1500433, A1520735 through A1520867 172N 17261445, 17267585 through 17272447 R172K R1722000 through R1723127 COMPLIANCE: Required as indicated unless already accomplished. To assure continued structural integrity of the wing flap direct cable, thereby preventing possible sudden unexpected retraction of the left wing flap accomplish the following: A) Prior to or upon accumulation of 1000 hours time-in-service for airplanes with less than 900 hours time-in-service on the effective date of this AD or within the next 100 hours time-in-service after the effective date of this AD for airplanes having 900 hours or more time-in-service on the effective date of this AD: Install a new Cessna Part Number 0560037-1 flap follow-up cable clamp and associated hardware in accordance with instructions in Cessna Single Engine Customer Care Service Information Letters SE79-16 and SE79-16 (Supplement #1) and Cessna Service Kit SK172-60A dated May 3, 1979. B) A special flight permit, in accordance with FAR 21.197, is permitted for the purpose of moving affected airplanes to a location where the modification required by this AD can be accomplished. C) Any equivalent means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office #43, Wichita, Kansas, Telephone (316) 942-4219. This amendment becomes effective April 21, 1980.
60-06-02: 60-06-02\tBOEING: Amdt. 113 Part 507 Federal Register March 11, 1960. Applies to all 707 series aircraft operating in accordance with Parts 40, 41, and 42 of the Civil Air regulations. \n\n\tCompliance required as indicated. \n\n\tAs a result of detailed examinations of flight recorder data subsequent to recent incidents involving 707 series aircraft, it has been determined that the prime power switch for the flight recorder, now actuated by the displacement of a landing gear oleo strut, does not insure all elements of the flight recorder to be operating at the start of the takeoff roll and continuing until the landing is completed at an airport. Therefore the following modification shall be accomplished as indicated. \n\n\tUnless already accomplished, compliance required not later than May 15, 1960. \n\n\tInstall a three-position switch, AN 3027-8 type or equivalent, in the pilot compartment and connect to appropriate circuits in the flight recorder for "TEST-OFF-ON" functions. Switchpositions shall be appropriately marked. \n\n\tRemoval of the presently installed oleo actuated power switch is optional, and if not removed, it shall not be considered as an equivalent to the required three-position manually operated switch. \n\n(Boeing Service Bulletin No. 77 (R-1) pertains to the circuitry revision.)
2017-11-14: We are superseding Airworthiness Directive (AD) 2011-26-03, which applied to certain The Boeing Company Model 777-200, -200LR, - 300, and -300ER series airplanes. AD 2011-26-03 required installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks. This AD requires certain inspections for certain airplanes, corrective actions if necessary, and installation of Teflon sleeves under certain wire bundle clamps. This AD was prompted by a report indicating that additional airplanes are affected by the identified unsafe condition. We are issuing this AD to address the unsafe condition on these products.
86-22-11: 86-22-11 BOEING: Amendment 39-5449. Applies to the Model 767 series airplanes specified in the Boeing service bulletins listed below, certificated in any category. To ensure proper entry/service door operation during emergency evacuation, accomplish the following within 12 months after the effective date of this AD, unless previously accomplished: \n\n\tA.\tFor airplanes listed in Boeing Service Bulletin 767-52-0032, dated September 13, 1985, remove and replace the entry/service door trolley roller and side track roller assemblies in accordance with Boeing Service Bulletin 767-52-0032, dated September 13, 1985, or later FAA- approved revisions. \n\n\tB.\tFor airplanes listed in Boeing Service Bulletin 767-52-0037, dated March 21, 1986, replace the counterbalance cable pulleys in accordance with Boeing Service Bulletin 767- 52-0037, dated March 21, 1986, or later FAA-approved revisions. \n\n\tC.\tFor airplanes listed in Boeing Service Bulletin 767-52-0044, dated June 27, 1986, modify the aft roller side tracks in accordance with Boeing Service Bulletin 767-52-0044, dated June 27, 1986, or later FAA-approved revisions. \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, Northwest Mountain Region. \n\n\tE.\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 copies of the manufacturer's service bulletins may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. 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 November 28, 1986.
81-26-02: 81-26-02 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4278. Applies to Models SA360C and SA365C series helicopters certificated in all categories. Compliance is required as indicated. To improve fatigue resistance and prevent possible cracks in the tail boom stabilizer spar attachment structure and to detect possible cracks in the stabilizer spar, accomplish the following: (a) For Model SA360C series helicopters S/N up to and including 1034 and SA365C helicopter S/N 5003 only, comply with the following within 200 hours' time in service after the effective date of this AD unless already accomplished. Modify the tail boom at the stabilizer tube mount in accordance with Aerospatiale Service Bulletin No. 53.01 dated July 17, 1978, by installing modification AMS 365A.07.1310 or by installing an equivalent modification approved by Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office. (b) For all Model SA360C seriesand SA365C series helicopters equipped with spar tubes, P/N 360A13.0012.01, comply with the following within 10 hours' time in service after the effective date of this AD unless already accomplished and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. (1) Remove the stabilizer spar tube from the helicopter and inspect the spar tube for cracks at the location of the weld beads for spacers and spar tube junction using a dye penetrant or equivalent inspection method. (2) If the spar tube is cracked, discard the tube and install a serviceable tube before further flight and conduct repetitive inspections as specified in subparagraph (b). (c) Equivalent means of compliance with the AD may be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Offices. (Aerospatiale SA360 Dauphin Service Bulletin No. 05.01 pertains to tail boom inspections. Telex Service 05-06 Dauphin pertains to the stabilizer spar tube inspections. Modification No. AMS07-3255 may improve the spar tube to spacer weld joint.) This amendment becomes effective December 21, 1981.
2017-10-21: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin is subject to widespread fatigue damage (WFD). This AD requires modification of the lap joint and repetitive inspections for cracking of the skin at critical fastener rows. We are issuing this AD to address the unsafe condition on these products.
81-21-04: 81-21-04 SIKORSKY AIRCRAFT: Amendment 39-4228. Applies to S-76A series helicopters certificated in all categories. To prevent fatigue failures of the main rotor scissors assembly: 1. Replace P/Ns 76104-08020-044, -045, and -046, and P/N 76070-10005-042 main rotor rotating scissors assemblies with a serviceable part prior to the accumulation of 500 hours time in service or within 25 hours time in service after the effective date of this AD, whichever occurs later. 2. Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the last 50 hours time in service, and thereafter at intervals not to exceed 100 hours from the last inspection, conduct inspections of the hub/scissors bearings for play and wear and the scissors center pivot bolt for fretting, scoring, and corrosion pits in accordance with Temporary Revision No. 5-24, dated September 8, 1981, or an FAA approved equivalent, Items 42A (Inspection Check 65-14-00, Page 207, dated February 16, 1980, including Temporary Revision No. 65-15, dated September 8, 1981, or an FAA approved equivalent) and 42B of the Sikorsky S-76A Maintenance Manual, 5A 4047-76-2. NOTE: "FAA approved" means approved by the Chief, Engineering and Manufacturing Branch, New England Region. The manufacturer's specifications and procedures identified and described 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 Sikorsky Aircraft, Division of United Technologies Corporation, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. This amendment becomes effective October 8, 1981.
83-04-04: 83-04-04 ENSTROM HELICOPTER CORPORATION: Amendment 39-4566. Applies to Enstrom Models F-28A and 280 helicopters certificated in all categories equipped with main rotor gearboxes (P/N 28-13101) having the following serial numbers: 2A, 3A, 6, 8, 9, 10, 12, 13, 14, 15, 20, 21, 25, 26, 28, 29, 30, 31, 32, 34, 35, 36, 38, 39, 40, 41, 42, 43, 44, 46, 47, 48, 49, 51, 53, 56, 70, 72, 73, 74, 75, 76, 77, 78, 86, 95, 100, 07, 012, 016, 017, 019, 020, 027, 032, 037, 050, 057, 060, 063, 067, 081, 082, 084, 085, 087, 088, 089, 093, 094, 097, 098, 099, 01-001-71, 01-073-69, 02-001-71, 02-02-71, 02-13-70, 03-001-72, 03-002-72, 04- 001-72, 05-001-72, 05-003-72, 06-001-72, 07-001-72, 07-002-72, 07-004-72, 07-005-72, 07-006- 72, 08-001-72, 08-002-72, 09-001-72, 09-001-73, 09-002-72, 09-01-69, 09-02-69, 09-04-69, 09- 06-69, 09-07-69, 10-001-72, 10-002-72, 11-001-72, 11-002-72, 12-001-72, 13-002-72, 13-003- 72, 13-004-73, 14-001-72, 14-002-72, 14-005-72, 14-006-72, 15-001-72, 15-002-72, 16-001-72,16-002-72, 17-001-72, 20-001-72, 21-001-72, 21-002-72, 21-003-72, 22-001-73, 23-001-73, 23- 003-73, 25-002-73, 26-001-73, 27-001-73, 27-002-73, 27-003-73, 27-004-73, 28-001-73, 28-003- 73, 30-001-73, 31-001-73, 31-002-73, 32-001-73, 32-002-73, 32-004-73, 32-006-73, 32-007-73, 33-001-73, 33-002-73, 33-003-73, 33-006-73, 33-007-73, 34-001-73, 34-002-73, 35-001-73, 35- 002-73, 35-003-73, 35-004-73, 36-001-73, 36-002-73, 36-003-73, 37-001-73, 37-003-73, 37-005- 73, 38-001-73, 39-001-73, 39-002-73, 40-001-73, 43-001-73, 43-002-73. To prevent the possible loss of power to the main rotor, accomplish the following: Within the next 25 hours' time in service from the effective date of this AD: a. Drain the oil from the transmission, and remove the oil filter cap assembly. b. Rotate the main rotor shaft until the core hole in the upper surface of ring gear carrier (P/N 28-13106) is aligned with the oil filler port. This may be ascertained by looking through the oil filler port. c. If no hole can be observed in the bottom web of the ring gear carrier, the wall thickness of the carrier is satisfactory and the inspections of steps d., e., and f. do not apply. d. If a hole can be observed in the bottom web of the ring gear carrier, the thickness of the lower web must be determined to establish airworthiness. e. Inspection tool, T-0125, is provided with Enstrom Service Directive Bulletin 0017, Revision C. Insert this inspection tool through the oil filler port and core hole and determine the thickness of the ring gear carrier lower web as shown in Figure 1 of Enstrom Service Directive Bulletin 0017, Rev. C., or FAA approved equivalent. NOTE: T-0125 IS A GO/NO-GO GAUGE. IF IT WILL FIT OR GO OVER THE LOWER WEB, THE WEB IS TOO THIN AND IS UNAIRWORTHY. IF IT WILL NOT FIT OR GO OVER THE LOWER WEB, THE WEB IS SUFFICIENTLY THICK, AND IS AIRWORTHY. f. Repeat steps b., d., and e. for each of the three holes in the ring gear carrier's lower web. If inspection tool T-0125 will slip over the web in any one of the three (3) lower web hole locations, the ring gear carrier is unairworthy. g. Replace unairworthy ring gear carriers with new or serviceable ring gear carrier P/N 28-13106, Revision F, or later revision. h. Service the transmission with oil in accordance with the Maintenance Manual and reinstall the oil filler cap assembly. i. Any equivalent method of compliance with this AD must be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 Devon Avenue, Des Plaines, Illinois 60018. j. In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished. This supersedes Amendment 39-1794, as amended by Amendments 39-1850 and 39- 1922 (AD 74-05-03). This amendment becomes effective March 1, 1983.