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64-12-02: 64-12-02 BOEING: Amdt. 743 Part 507 Federal Register June 5, 1964. Applies to All Model 727 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\tAs an interim safety measure pending development and accomplishment of final corrective modifications, the following is required: \n\n\t(a) Initial compliance required within 20 hours' time in service after May 19, 1964. Before each flight when the thrust reversers have been used on the previous flight, conduct a close visual inspection of each reverser to ascertain that each deflector door is in the fully closed position and that the thrust reverser indicator light is out. If the doors are not fully closed or if the indicator light is not out corrections shall be made before further flight. Upon compliance with (b) and (c) of this directive the visual inspection required by this paragraph may be discontinued.\n \n\t(b) Within 20 hours' time in service after the effective date of this AD, unless previously accomplished, inspectthe thrust reverser locking pin for freedom of action and the reverser operating light switch for proper adjustment and rigging. If the locking pin is bent or binding or if the operating light is out of adjustment, necessary correction shall be made before further flight. (Boeing Service Bulletin No. 78-10R1 covers this subject.) \n\n\t(c) Within 150 hours' time in service after the effective date of this AD, unless already accomplished, modify the thrust reverser lockout actuator rocker, including rework of the switch actuating tine, in accordance with Boeing Service Bulletin No. 78-10R1. \n\n\tNOTE. - The original issue of this bulletin did not include information for rework of the tine. \nThis rework is necessary to prevent interference and damage to the locking pin. \n\n\t(d) Prior to compliance with (b) and (c) the inspection required by (a) shall also be made before flight when any reverser is again actuated on the ground during engine runup or during taxiing. Upon compliance with (b) and (c) further inspections under paragraph (a) need not be made. \n\n\t(e) Approval of any equivalent means of compliance with this directive shall be processed through the Aircraft Engineering Division, FAA Western Region, Los Angeles, California. \n\n\t(Boeing's telegram to all 727 operators dated May 20, 1964, covers this subject.) \n\n\tThis directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated May 22, 1964, superseding the telegram dated May 18, 1964. \n\n\tRevised July 7, 1964. \n\n\tRevised August 29, 1964.
2017-13-08: We are superseding Airworthiness Directive (AD) 2015-23-13, for all Airbus Model A318 and A319 series airplanes, Model A320-211, - 212, -214, -231, -232, and -233 airplanes, and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. AD 2015-23-13 required modification of the pin programming of the flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. This new AD, for certain airplanes, also requires accomplishment of additional modification instructions to install the minimum FWC and FAC configuration compatible with SRIW activation. This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. We are issuing this AD to address the unsafe condition on these products.
78-24-05 R1: 78-24-05 R1 BOEING: Amendment 39-3355 as amended by Amendment 39-3871. Applies to Boeing Model 727 and 727-100 series passenger airplanes, and Model 727-51C airplanes operating in the passenger mode. To detect possible interference between the mid-cabin galley door and the emergency escape slide girt bar, accomplish the following: \n\tA.\tWithin the next 300 flight hours time-in-service after the effective date of this AD or prior to January 1, 1979, whichever occurs first, unless accomplished within the last 1200 flight hours time-in-service, inspect the mid-cabin galley door for interference with the girt bar in accordance with Boeing Alert Service Bulletin 727-25-A247. \n\tB.\tDoors with interference are to be reworked prior to further passenger flight in accordance with Boeing Alert Service Bulletin 727-25-A247. \n\tC.\tRepeat the inspections, described in paragraph A, at intervals not to exceed 1,500 flight hours time-in-service or one (1) year from the last inspection, whichever comes first, unless the galley door is modified as described in Boeing Service Bulletin 727-25-A247, Revision 2, paragraph III, part II, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. This modification is terminating action for this AD. \n\tD.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive 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. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\tAmendment 39-3355 became effective December 1, 1978. \n\tThis Amendment 39-3871 becomes effective August 18, 1980.
63-23-02: 63-23-02 LYCOMING: As amended by Amendment 39-627 - is corrected as follows: Applies to all O-320 type engines which incorporate the 7/16" diameter exhaust valve stem with camshaft assembly P/N 68769. Compliance with (d) required at the times indicated in (a), (b), or (c) as applicable. (a) Engines used for aerial dusting or chemical application service since new or since replacement of all exhaust valves and valve guides. (1) As of the effective date of this AD, engines with more than 200 hours' time in service since new or since replacement of all exhaust valves and valve guides, shall comply within the next 100 hours' time in service and every 300 hours' time in service thereafter. (2) As of the effective date of this AD, engines with 200 hours' or less time in service since new or since replacement of all exhaust valves and valve guides, shall comply prior to the accumulation of 300 hours' time in service since new or since exhaust valve and valve guidereplacement and every 300 hours' time in service thereafter. (b) Engines used in all operations other than those covered in paragraph (a). (1) New engines and engines which have a record of at least No. 3 and No. 4 exhaust valve and valve guide replacement. (i) As of the effective date of this AD, engines with more than 400 hours' time in service since new or since the replacement of No. 3 and No. 4 exhaust valves and valve guides, shall comply within the next 100 hours' time in service and every 500 hours' time in service thereafter. (ii) As of the effective date of this AD, engines with 400 hours' or less time in service since new or since replacement of No. 3 and No. 4 exhaust valves and valve guides shall comply prior to the accumulation of 500 hours' time in service since new or since No. 3 and No. 4 exhaust valve and valve guide replacement and every 500 hours' time in service thereafter. (2) Engines which have a record of exhaust valve replacement of at least No. 3 and No. 4 valves but no record of valve guide replacement. (i) As of the effective date of this AD, engines with more than 200 hours' time in service since replacement of No. 3 and No. 4 exhaust valves shall comply within the next 100 hours' time in service and every 500 hours' time in service thereafter. (ii) As of the effective date of this AD, engines with 200 hours' or less time in service since replacement of No. 3 and No. 4 exhaust valves shall comply prior to the accumulation of 300 hours' time in service since exhaust valve replacement and every 500 hours' time in service thereafter. (c) Engines whose usage is changed between inspections. (1) Engines whose usage is changed from that specified in (a) to that specified in (b) will comply as originally required in (a) for the first inspection after usage change. Subsequent inspections will be as required in (b). (2) Engines whose usage is changed from that specified in (b)to that specified in (a) will comply with the requirements of (a) for the first inspection after usage change and for subsequent inspections. (d) Inspect and, where necessary, replace exhaust valves and guides in accordance with Lycoming Service Bulletin No. 293B or other alternative method approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region. This amendment is effective Dec. 9, 1963. Revised August 6, 1968.
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.