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2017-12-05: We are superseding Airworthiness Directive (AD) 2007-26-04 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2007-26-04 required repetitive inspections for cracking of certain fasteners, and repair if necessary; and a preventive modification, which terminated the repetitive inspections. This AD removes the mandatory modification; adds repetitive inspections of the skin for cracking, a one-time inspection for defects of the production countersunk rivets, and corrective actions if necessary; and adds an optional skin trim-out repair, which will terminate certain inspections. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain skin panels are subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products.
84-04-03: 84-04-03 THE BALLOON WORKS: Amendment 39-4821. Applies to Model Firefly 7B (Twelve Gore) (Serial Numbers F7B-009, F7B-011 through F7B-044, and F7B-046 through F7B- 080) Hot Air Balloons certificated in any category. Compliance: Required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent breakage of jumper cords, which may result in uncontrollable descent, accomplish the following: (a) Lengthen each envelope jumper cord, shorten each centering cord, inflate envelope and examine valve fit and adjust, if necessary, in accordance with The Balloon Works Service Bulletin No. B20, dated June 29, 1983. (b) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, FAA Central Region, 1075 Inner Loop Road, College Park, Georgia 30337. This amendment becomes effective on April 9, 1984.
83-01-06: 83-01-06 SWITLIK PARACHUTE COMPANY, INC.: Amendment 39-4541. Applies to inflatable life preservers and individual flotation devices, all models and part numbers, manufactured between June 1, 1981, and March 22, 1982. Compliance required within the next 24 months after the effective date of this AD, unless previously accomplished. To detect life preservers and flotation devices which have CO2 inflation valve manifolds that may operate improperly, and to correct the deficiency, perform the following in accordance with the Accomplishment Instructions, Paragraph 2, of Switlik Parachute Company, Inc., Service Bulletin 25-00-16, dated April 1, 1982: 1. Inspect the lower shoulder of the valve stem for a thin groove (1/16 to 1/32 inch wide). If the groove is not present, the air check valve is acceptable. 2. If the groove is present, the air check valve must be replaced and the faulty valve discarded. 3. After installation of the replacement air check valve, inflate the life vest cell and test the operation of the air check valve. An equivalent method of compliance may be approved upon request to the Manager, New York Aircraft Certification Office, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the compliance time of this AD may be adjusted upon request to the Manager, New York Aircraft Certification Office, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. All persons affected by this directive who have not already received the manufacturer's service bulletin may obtain a copy upon request to Switlik Parachute Company, Inc., 1325 East State Street, Trenton, New Jersey 08607. This document may also be examined at Federal Aviation Administration, New England Region, Office of the Regional Counsel, 12 New England Executive Park,Burlington, Massachusetts 01803. This amendment becomes effective February 28, 1983.
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.