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79-15-02: 79-15-02 AVCO LYCOMING: Amendment 39-3516. Applies to Avco Lycoming O-360-A1G6D engines with Serial Numbers prior to L-26456-36A except L-23465-36A, L-23783-36A, L-23865-36A, L-24278-36A, L-25075-36A, L-25129-36A, L-25131-36A, L-25998-36A, L-26069-36A through L-26071-36A, L-26073-36A through L-26076-36A, L-26123-36A through L-26128-36A, L-26130-36A, L-26131-36A, L-26139-36A, L-26205-36A through L-26207-36A, L-26236-36A through L-26242-36A, L-26278-36A, L-26281-36A through L-26283-36A, and to the Avco Lycoming LO-360-A1G6D engines with Serial Numbers prior to L-296-71A except L-102-71A, L-107-71A, L-109-71A, L-113-71A, L-158-71A, L-171-71A, L-237-71A, L-246-71A, L-250- 71A, L-255-71A, L-256-71A, L-259-71A through L-273-71A, L-275-71A through L-282-71A, L-284-71A through L-286-71A, L-289-71A. Compliance required within the next 10 hours in service after the effective date of this AD, unless previously accomplished. To prevent inflight power loss due to loosening of the internal economizer channel plug in the Model HA-6 carburetor, remove the P/N 80-150 plug and replace with P/N 80-364 plug in accordance with Avco Lycoming Service Bulletin No. 434 or FAA approved equivalent. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD. Note. Marvel-Schebler/Tillotson Service Bulletin A1-79 and Beechcraft Service Instructions No. 1045 also pertains to this subject. This amendment is effective July 20, 1979.
2019-16-14: The FAA is superseding airworthiness directive (AD) 2018-25-01 for all Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H turbofan model engines. AD 2018-25-01 required initial and repetitive inspections of the intermediate-pressure compressor (IPC) stage 1 rotor (R1) blades, IPC stage 2 rotor (R2) blades, and IPC shaft stage 2 dovetail posts, and removing any cracked parts from service. This AD retains those inspections, revises certain reinspection intervals, and adds certain engine models to the applicability. This AD was prompted by a determination by the manufacturer of the need to revise inspection intervals for certain affected engines. In addition, the FAA added recently validated additional engine models to the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
82-20-51: 82-20-51 AVCO LYCOMING: Telegram issued September 22, 1982. The following AD is issued and applicable to Avco Lycoming Model LTP101-600 and LTP101-600A turboprop engines (all serial numbers), Model LTP101-600A-1A turboprop engines prior to S/N 50095, and Model LTP101-700A-1A turboprop engines prior to S/N 51009. Within the next 25 hours time in service after receipt of this telegraphic AD unless already accomplished, remove the N2 accessory idler gear assembly in accordance with the accomplishment instructions contained in Avco Lycoming Service Bulletin Numbers LTP101A-72-0021 Rev. 1 and LTP101-72-0025 Rev. 1. This assembly is shown as Item 147 in Figure 2, Section 72-00-00, of Lycoming Maintenance Manual No. LTP101-2 and as Items 770, 750, 785, 775, 765, 760, and 755 in Figure 1, Section 72-60-00, of Lycoming Illustrated Parts Catalog Number LTP101-4. Replace with Avco Lycoming Kit P/N TLW-18823 in accordance with the accomplishment instructions contained in Avco Lycoming Service Bulletin Numbers LTP101A-72-0021 Rev. 1 and LTP101-72-0025 Rev. 1. The manufacturer's procedures identified and described in this directive are available upon request to Avco Lycoming, Williamsport, Pennsylvania. These documents may also be examined at FAA New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD is maintained by the FAA at the New England Region Headquarters, Burlington, Massachusetts. This directive is effective immediately upon receipt of this telegram.
60-19-01: 60-19-01 SIKORSKY: Amdt. 199 Part 507 Federal Register September 10, 1960. Applies to All S-52-3 Helicopters. Compliance required as indicated. As a result of further investigation of the service history of the HO5S-1 (S-52-3) helicopters, the following retirement, replacement and inspection schedules must be accomplished at the times indicated: (a) Effective immediately the following components must be retired from service at the hours of time in service indicated: P/N S11-10-2200 Main Rotor Blade Assembly -1,100 hours. P/N S11-15-1100 Tail Rotor Blades - 1,700 hours. (b) Effective October 14, 1960, the following components must be replaced with the redesigned components indicated, if not already accomplished: P/N S11-35-2006, Clutch Spindle, replace with P/N S11-35-2009. P/N S11-35-2013, Clutch Spring, replace with P/N S11-35-2013-1. P/N S11-35-2019, Free Wheel Unit Spring, replace with P/N S11-35- 2019-1. P/N 13273, Bolt, Engine Fan, replacewith AN 76-10 Bolt. (c) Effective October 14, 1960, the following shall be accomplished at the times indicated: (1) The torque of the AN 76-10 bolts in the engine fan must be checked every 30 hours' time in service and retorqued if necessary to a minimum value of 370 inch- pounds. Bolts found with less than 300 inch-pounds torque must be replaced with new bolts. (Sikorsky Service Information Circular 1135-22 covers this subject.) (2) Within the next 30 hours' time in service and every 30 hours' time in service thereafter, inspect the DSP4 bearing in the rotating scissors in accordance with Sikorsky Service Information Circular 1110-46 and replace bearing every 100 hours' time in service with new bearing. When DSP4 bearing is replaced by DSRP4 bearing, the DSP4 inspection and replacement schedule no longer applies. (3) Within the next 30 hours' time in service and every 30 hours' time in service thereafter, inspect the DSP4 bearing in the damper arm in accordance withSikorsky Service Information Circular 1110-46 and replace bearing every 300 hours' time in service with new bearing. When DSP4 bearing is replaced by DSRP4 bearing, the DSP4 inspection and replacement schedule no longer applies. This supersedes AD 60-04-06.
2019-14-12: The FAA is adopting an airworthiness directive (AD) for certain The Boeing Company Model 737-8 and 737-9 airplanes. This AD requires a maintenance records check to determine if any main slat track assembly has been removed, an inspection of the main slat track assemblies for a suspect lot number or a lot number that cannot be determined, and applicable on-condition actions. This AD was prompted by a report that certain main slat track assemblies were manufactured incorrectly and are affected by hydrogen embrittlement. The FAA is issuing this AD to address the unsafe condition on these products.
82-09-53: 82-09-53 BELL HELICOPTER TEXTRON, INC.: Amendment 39-4434. Applies to Model 222 helicopters certificated in all categories that are equipped with swashplate drive links, Part No. 222-010-460-101. (Airworthiness Docket No. 82-ASW-24.) Compliance required as indicated, unless already accomplished. To prevent possible link failure due to excessive bearing wear in the main rotor swashplate drive links and possible link cracks, accomplish the following installation. Before further flight, after the effective date of this AD, install swashplate drive links, Part No. 222-011-416 or 222-018-034 in place of swashplate drive links 222-010-460-101 as prescribed in Bell Helicopter Textron, Inc. Technical Bulletin 222-81-41, dated September 1, 1981, or by an equivalent procedure approved by Chief, Aircraft Certification Division, Federal Aviation Administration, Southwest Region. This AD supersedes and cancels AD No. T82-09-52. This amendment becomes effective August 19, 1982, to all persons except those to whom it was made immediately effective by telegraphic AD T82-09-53 issued April 27, 1982, which contained this amendment.
2019-13-03: The FAA is adopting a new airworthiness directive (AD) for certain Trig Avionics Limited TT31, Avidyne Corporation AXP340, and BendixKing/Honeywell International KT74 Mode S transponders. This AD was prompted by the discovery that the retaining cam that engages in the mounting tray may not withstand g-forces experienced during an emergency landing. This AD requires one-time inspection of the transponder installation and, depending on the findings, removal of the affected transponder for modification. The FAA is issuing this AD to address the unsafe condition on these products.
83-14-10: 83-14-10 CANADAIR: Amendment 39-4688. Applies to Model CL-600-1A11 airplanes certificated in all categories. To prevent decompression of the aircraft, within the next 100 hours time in service after the effective date of this AD, accomplish the following, unless previously accomplished: A. For airplanes with serial numbers listed in Canadair Service Bulletin 600-0147, Revision 2, dated September 24, 1982, modify and inspect the windshield and side window glazing in accordance with the Accomplishment Instructions of this service bulletin. B. If cracks are detected replace the affected glazing prior to further flight except as noted in paragraph E. below. C. For airplanes with serial numbers listed in Canadair Service Bulletin 600-0225, Revision 1, dated September 24, 1982, modify in accordance with the Accomplishment Instructions of this service bulletin. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by theManager, 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 unpressurized to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective July 28, 1983.
2019-12-04: The FAA is superseding Airworthiness Directive (AD) 2018-19- 18, which applied to certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4- 605R Variant F airplanes; and Model A300 F4-605R airplanes. AD 2018-19- 18 required, depending on airplane configuration, a modification of certain angle fitting attachment holes; repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel, and a certain junction area; and related investigative and corrective actions if necessary. This new AD retains those actions, expands the applicability, and, for certain airplanes, requires repetitive inspections for cracking of certain holes of the center wing box (CWB) lower angle fittings and the CWB lower panel, and corrective actions if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracking of a certain frame (FR) angle fitting. The FAA is issuing this AD to address the unsafe condition on these products.
84-01-01: 84-01-01 GENERAL ELECTRIC COMPANY: Amendment 39-4790. Applies to CF6-45 and CF6-50 series model turbofan engines. Unless already accomplished, to preclude the possibility of uncontained titanium fires, replace as follows prior to June 1, 1984: (a) Compressor stator assembly, including the compressor case, and stage 6 vanes in accordance with FAA approved General Electric CF6-45 and CF6-50 Service Bulletin 72-549. (b) Compressor inlet stator vanes and stage 1 and 2 stator vanes in accordance with FAA approved General Electric CF6-45 and CF6-50 Service Bulletin 72-550. (c) Compressor blades, stages 3 through 9, and the stage 3-9 spool in accordance with FAA approved General Electric CF6-45 and CF6-50 Service Bulletin 72-551. The 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). All persons affected by this directive who have not already receivedthese documents from the manufacturer may obtain copies upon request from the General Electric Company, Neumann Way, Cincinnati, Ohio 45215. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. A historical file on this AD is maintained by the FAA, New England Region Office, Burlington, Massachusetts. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Engine Certification Branch, FAA, New England Region, may adjust the compliance date(s) 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. This amendment becomes effective on February 10, 1984.