Results
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.
65-04-02: 65-04-02\tBOEING: Amdt. 39-34 Part 39 Federal Register February 17, 1965. Applies to Models 707 and 720 Series Aircraft Equipped With an External High Pressure Air Start Connection. \n\n\tCompliance required as indicated. \n\n\tFailures of B-nuts on the high pressure air start system lines have occurred, resulting in whipping lines in the wheel well area. To correct this condition: \n\n\t(a)\tWithin 500 hours' time in service from the effective date of this AD, unless already accomplished, accomplish one of the following or an equivalent approved by the Aircraft Engineering Division, FAA Western Region: \n\n\t\t(1)\tReplace all NAS 596-16 B-nuts on the one-inch high pressure air lines in the 3,000 p.s.i. high pressure air start bottle system with AN 818-16 nuts and MS 20819-16 sleeves in accordance with Boeing Alert Service Bulletin No. 2009 dated May 15, 1964; \n\n\t\t(2)\tRelocate air pressure regulator Boeing P/N 10-3358-1 to a position on the high pressure air start bottle and deactivate the external high pressure air start connection; or \n\n\t\t(3)\tDeactivate the high pressure air start system by removing the high pressure air start bottles and the external high pressure air start lines and connection. \n\n\t(Boeing Alert Service Bulletin No. 2009 dated May 15, 1964, covers this subject.) \n\n\tThis directive effective March 19, 1965.
2017-09-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report indicating that during an airplane inspection in production, the variable frequency starter generator (VFSG) power feeder cables were found to contain terminal lugs incorrectly installed common to terminal blocks located in the wing front spar. This AD requires a general visual inspection of the wings, section 16, terminal lugs at the terminal power block of the VFSG power feeder cable for correct installation and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
61-19-01: 61-19-01\tBOEING: Amdt. 332 Part 507 Federal Register September 14, 1961. Applies to All Model 720 Series Aircraft Which Have Not Previously Been Modified By Installation of Micro P/N 5EN11-6B. \n\n\tCompliance required as indicated. \n\n\tFaults occurring in the fuel dump chute safety switch of the retractable dump chute system have caused burning of the lead wires at the switch and, in one case, caused a fuel dump valve to cycle open and close allowing fuel to enter the fuel dump manifold and leak out through the dump chute secondary seal. To prevent this, the following inspection and modification shall be accomplished: \n\n\t(a)\tCommencing within 10 days after the effective date of this AD unless the lead wire insulation has been reinforced by wrapping with suitable electrical tape at the switch, conduct daily inspections of the fuel dump chute safety switch (Micro P/N 5EN11-6) to determine if the wires are burned or charred where they protrude. If wires are found burned or charred,prior to further flight replace safety switch with improved type Micro P/N 5EN11-6B, after which the daily inspection can be discontinued.\n \n\t(b)\tUnless already accomplished in accordance with paragraph (a), within the next 350 hours' time in service after the effective date of this AD, replace fuel dump valve safety switches Micro P/N 5EN11-6 with switch Micro P/N 5EN11-6B, using standard Boeing Maintenance Manual procedures. Upon installation of switch Micro P/N 5EN11-6B the daily inspection required by (a) can be discontinued. \n\n\t(c)\tUpon request of the operator, an FAA maintenance inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, FAA Western 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 such operator. \n\n\t(Boeing Service Bulletin No. 1305, dated May 22, 1961, covers thismodification.) \n\n\tThis directive effective September 14, 1961.
2017-09-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD requires a detailed inspection of the circuit breakers, replacement of damaged circuit breakers, and installation of a circuit breaker bushing assembly. This AD was prompted by a report of cracks found in the plastic casing of cockpit circuit breaker panels. We are issuing this AD to address the unsafe condition on these products.
86-06-03 R1: 86-06-03 R1 SAAB-FAIRCHILD: Amendment 39-5258 as amended by amendment 39-5917. Applies to Model SF-340A series airplanes, serial numbers 003 through 048, inclusive, certificated in any category. Compliance is required as indicated below, unless previously accomplished. To prevent uncommanded pitch excursions, accomplish the following: 1. Within the next 7 days after the effective date of this AD, incorporate the following into the limitations section of the airplane flight manual: "More than 20 degrees flap is not authorized at any time." This may be accomplished by including a copy of this AD in the airplane flight manual. 2. Within the next 21 days after the effective date of this AD, install a mechanical stop on the flap handle to limit the flap extension to a maximum setting of 20 degrees, in accordance with SAAB-Fairchild Service Bulletin SF340- 27-036, dated February 13, 1986. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections and/or modifications required by this AD. 4. Alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. 5. Installation of Modification 1784 in accordance with SAAB Service Bulletin SF340-27-049, Revision 1, dated July 21, 1987, and Modification 1462 in accordance with SAAB Service Bulletin SF340-55-008, Revision 2, dated March 31, 1988, constitutes terminating action for the requirements of paragraphs 1. and 2., above. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to SAAB-Scania, Product Support, S.58188, Linkoping, Sweden. This document 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. This Amendment 39-5917 amends AD 86-06-03, Amendment 39-5258. This amendment 39-5917 becomes effective June 17, 1988.
2017-08-05: We are superseding Airworthiness Directive (AD) 2016-13-05 for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90- 90B, and GE90-94B turbofan engines. AD 2016-13-05 required eddy current inspection (ECI) of the high-pressure compressor (HPC) stage 8-10 spool at each shop visit for all affected engines and ECI or ultrasonic inspection (USI) for certain affected engines. This new AD requires initial and repetitive on-wing USIs of the HPC stage 8-10 spool for certain engines prior to shop visit and ECI of all affected engines at each shop visit. This AD was prompted by analysis that the risk of the failure of an HPC stage 8-10 spool was excessive without repetitive USI prior to shop visit. We are issuing this AD to correct the unsafe condition on these products.
84-26-02: 84-26-02 INDUCTION AIR FILTERS: Amendment 39-4966. Applies to all paper induction air filters used in small airplanes. Compliance: Required as indicated, unless already accomplished. To prevent possible engine power loss or stoppage caused by engine ingestion of fragments of a deteriorated induction air filter, accomplish the following: Within the next one hundred hours time-in-service after the effective date of this AD or prior to the accumulation of 500 hours time-in-service on the filter, whichever occurs later, and thereafter at intervals not exceeding 500 hours time-in-service on the filter: (a) Replace the air filter with a new filter that is FAA approved for the airplane installation. (b) Within 100 hours time-in-service replace any filter on which the time-in-service cannot be determined utilizing the airplane maintenance records for this determination. NOTE: This AD does not alter current maintenance procedures which require inspection of paper induction air filters at 100 hours time-in-service and annual inspections and replacement as necessary based on filter condition. This amendment becomes effective January 29, 1985.
64-04-06: 64-04-06 PRATT READ: Amdt. 685 Part 507 Federal Register February 12, 1964. Applies to All Model PR-G1 Gliders. Compliance required as indicated. Due to a deteriorating condition of the wood structure supporting the aft elevator bellcrank, resulting in loss of elevator control, accomplish the following within 25 hours' time in service after the effective date of this AD unless already accomplished within the last 75 hours' time in service, and at intervals thereafter not to exceed 100 hours' time in service from the last inspection, or one year, whichever occurs first. (a) Remove the stabilizer and elevators and any other obstructing structure necessary to gain access to the aft internal fuselage area (tail cone section). (b) With the use of a light and mirror, visually inspect for deterioration both the front and rear side of the wood bulkhead in the vicinity of its support of the aft elevator bellcrank. (c) If indications of deterioration of the wood structureare found, repair that bulkhead in accordance with an FAA approved repair before further flight, or replace with a part having the same part number, or an FAA approved equivalent before further flight. NOTE: After installation of a new or repaired bulkhead, it should be ascertained that the elevator is functioning properly throughout the entire range. This directive effective March 13, 1964.
2017-07-01: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LLC Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227- AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. This AD was prompted by detachment of the power lever linkage to the TPE331 engine propeller pitch control. This AD requires repetitively inspecting the propeller pitch control for proper torque, with corrections as necessary until required replacement or rework of the PPC assembly to have a threaded hole in the splined end of the shouldered shaft and installation of a secondary retention device is done. We are issuing this AD to correct the unsafe condition on these products.
61-18-02: 61-18-02 BRANTLY: Amdt. 327 Part 507 Federal Register August 24, 1961. Applies to All Model B-2 Helicopters prior to Serial No. 112. Compliance required within the next 25 hours' time in service after effective date of this directive unless already accomplished. Investigation of a recent Model B-2 helicopter accident indicated evidence of limited tail rotor control. Accordingly, in order to provide directional control over a wider main rotor r.p.m. range, the following modification and rerigging of the tail rotor is required: (a) Modify the rudder control arm P/N B2-284-1 as follows. (1) Disconnect the vertical rudder rod P/N B2-251-5 at its top end by removing the AN 3-10A bolt. (2) Drill a 1/16-inch diameter hole and then enlarge to 0.187-inch diameter 1/2 inch inboard (center to center) from the existing hole in the rudder control arm P/N B2-284-1. Deburr edges. (3) Cut off the end of the rudder control arm P/N B2-284-1 with the old 0.187-inch hole 0.344-inch outboard from the centerline of the new 0.187-inch hole (0.250-inch edge distance from new hole) and perpendicular to the longitudinal axes of the rudder control arm. Break all sharp edges. (4) Rerig the tail rotor in accordance with the manufacturer's instructions, Service Bulletin No. 15. (Brantly Service Bulletin No. 15 dated June 23, 1961, covers this subject.) This directive effective August 29, 1961.
83-25-01: 83-25-01 SHORT BROTHERS LIMITED: Amendment 39-4783. Applies to all Models of the SD3-30 airplane, certificated in all categories, with the serial numbers specified below. To prevent a potential fuel fire hazard, accomplish the following within the next 60 days after the effective date of this AD, unless already accomplished. A. For aircraft serial numbers SH3002 to SH3091 inclusive, modify the fuel vapor exhaust ducting in accordance with paragraph 2, Accomplishment Instructions, of Shorts Service Bulletin No. SD3-53-47, Revision 3, dated June 23, 1983. B. For aircraft serial numbers SH3002 to SH3089 inclusive, replace the existing flexible vapor proof shrouds covering fuel lines in the passenger compartment in accordance with paragraph 2, Accomplishment Instructions of Shorts Service Bulletin No. SD3-28-17, Revision 2, dated June 23, 1983. NOTE: The actions of paragraph A., above, must be accomplished before performing the requirements of paragraph B. C. For aircraft with serial numbers specified in paragraph 1, Planning Information, of Shorts Service Bulletin No. SD3-28-16, Revision 3, dated June 23, 1983, inspect, replace components if necessary, and pressure check the fuel lines as required in accordance with paragraph 2, Accomplishment Instructions, of the service bulletin. NOTE: The actions of paragraphs A. and B., above, must be accomplished before performing the requirements of paragraph C. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special 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. F. This AD supersedes Amendment 39-4677 (48 FR 31631, July 11, 1983), AD 83- 13-07. This amendment becomes effective January 8, 1984.
2017-05-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
86-19-13: 86-19-13 AVCO LYCOMING: Amendment 39-5374. Applies to Avco Lycoming model T5508D turboshaft engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the first stage turbine disk that can cause an uncontained engine failure, accomplish the following: (a) Visual and fluorescent penetrant inspect the first turbine rotor assembly, Part Number (P/N) 2-120- 030-43, within the next 50 hours time in service after the effective date of this AD, in accordance with the Accomplishment Instructions contained in Avco Lycoming Service Bulletin (SB) 5508-0031, Revision 1, dated August 19, 1986, or FAA approved equivalent. (b) Remove and replace with new parts, bolts P/N 2-100-079-05 and their associated locking plates P/N 2-100-078-01, when accomplishing the inspections of Paragraph (a) above, in accordance with the Accomplishment Instructions contained in Avco Lycoming SB 5508-0031, Revision 1, dated August 19, 1986, or FAA approved equivalent.(c) Remove from service and replace with a serviceable part, prior to further flight, all first turbine disks that exhibit fretting on the disk to shaft mating face and/or a crack indication during inspection. (d) Report the following information in writing for each inspection within 30 days of the inspection to the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, (Telex Number 949301 FAANE BURL) (Reporting approved by the Office of Management and Budget (OMB) under OBM Number 2120-0056): (1) Engine serial number (2) Inspection date (3) Disk part number and serial number (4) Disk total time and cycles (5) Disk time and cycles since last installation (6) Breakaway up torque for bolts, P/N 2-100-079-05 (7) Any evidence of oil leakage and/or fire in the Number 2 bearing area (8) Disk disposition (crack indication or, no crack indication, fretting or, no fretting, thread marks inside the boltholes or not) NOTE: For the purpose of this AD fretting is defined as metal removal below the original machined surface that is exemplified by a pitting pattern. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, may adjust the compliance times specified in this AD. Avco Lycoming SB 5508-0031, Revision 1, dated August 19, 1986, identified and described in this document, is incorporated 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 this document from the manufacturer may obtain copies upon request to Avco Lycoming, 550 South Main Street, Stratford, Connecticut 06497. This document also may be examined at the Office of the Regional Counsel, Rules Docket Number 86-ANE-31, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 86-ANE-31, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on October 6, 1986.
2000-22-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP and Hawker 800 (U-125A) series airplanes, that requires inspection of the wire bundle to relay `KT' on panel `JA' for correct routing, adequate clearance from the fuel cross-feed valve operating lever, and the presence of chafing; this amendment also requires corrective action, if necessary. The actions specified by this AD are intended to detect and correct chafing of the wire bundle exiting panel `JA' due to insufficient clearance from the fuel cross-feed valve operating lever. Such chafing of the wire bundle could result in a fire in the area of the fuel system in a confined space. This action is intended to address the identified unsafe condition.
63-24-01: 63-24-01 CURTISS-WRIGHT: Amdt. 647 Part 507 Federal Register November 26, 1963. Applies to All Models C634S-C400 through -C499 and C634S-C500 through -C599 Series Propellers Equipped With P/N 142080-1 Brake Assemblies. (These Propellers May Be Found Installed On Such Aircraft as Lockheed 749 and 1049.) Compliance required within 100 hours' time in service after the effective date of this AD. There have been failures of P/N 142080-1, threaded-type brake assemblies, causing the propellers to malfunction. To correct this unsafe condition, the following shall be accomplished: Replace P/N 142080-1 brake assemblies with P/N's 149252-1, 152908-2, or 161462-2 brake assemblies. (Curtiss Service Bulletins Nos. C-14 and C-32 and Parts Bulletins C-52, C-67, C-80 and C-90 cover this same subject.) This directive effective December 27, 1963.