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87-08-05: 87-08-05 BEECH: Amendment 39-5598. Applies to Model A36TC (Serial Numbers EA-1 through EA-241, and EA-243 through EA-272) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To reduce the possibility of engine flooding caused by inadvertent pilot action, accomplish the following: (a) Modify the fuel system as described in Beechcraft Mandatory Service Bulletin No. 2033, dated August 1985. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on May 14, 1987.
2019-17-02: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD requires inspecting certain part-numbered actuators for corrosion, and removing them from service as necessary. This AD also requires reporting certain information to Airbus Helicopters. This AD is prompted by a hard landing of a helicopter and discovery of a ruptured and displaced tie bar inside the piston of the longitudinal single-axis actuator of the main rotor actuator (MRA). The actions of this AD are intended to address an unsafe condition on these products.
83-24-11 R1: 83-24-11 R1 MCCAULEY ACCESSORY DIVISION: Amendment 39-4768 as amended by Amendment 39-5240. Applies to certain McCauley Model 2A34C66/90AT-2, E2A34C73/90AT- 8, and 2A36C23/84B-0 constant speed propellers with specific serial numbers listed in McCauley Service Bulletin No. 151A dated December 6, 1985, or FAA approved equivalent, installed on, but not limited to, Cessna 180, 180A through 180J, Cessna 188, 188A, and 188B, Cessna P206, P206A through P206E, Cessna 210E through 210L, and Beech 33, 35, and 36 series aircraft certificated in any category. Compliance is required as indicated unless already accomplished. To prevent propeller blade failure, accomplish the following: 1. For propellers with 400 or more hours time in service since new, disassemble the propeller and inspect the retention threads on the blades and ferrules in accordance with McCauley Service Bulletin 151A dated December 6, 1985, within the next 25 hours time in service or within the next 30 days after the effective date of this AD, whichever occurs earlier. 2. For propellers with less than 400 hours time in service since new, disassemble the propeller and inspect the retention threads on the blades and ferrules in accordance with McCauley Service Bulletin 151A dated December 6, 1985, prior to accumulating 425 hours time in service. 3. If no scratch(es) or unairworthy conditions are observed, the blade retention threads must be dye penetrant inspected to confirm visual observations, before return to service. 4. Blades showing evidence of scratch(es) within the first four outboard threads or other unairworthy condition(s) must be replaced with an airworthy blade. Blades showing evidence of scratch(es) from the fifth thread and inboard, must be repaired before returning blade to service. Ferrules showing evidence of sharp edges on the threads must be repaired and replated in accordance with McCauley Service Bulletin 151A dated December 6, 1985, before returning to service. 5. A special flight permit may be issued in accordance with Federal Aviation Regulations 21.197 to operate the aircraft to a base where the AD can be accomplished. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. McCauley Service Bulletin No. 151A dated December 6, 1985, identified and described in this directive, 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 McCauley Accessory Division, Cessna Aircraft Company, 3535 McCauley Drive, P.O. Box 430, Vandalia, Ohio 45377. This document also may be examined at the Office of the Regional Counsel, FAA, Attn: Rules Docket No. 83-ANE-27, 12 New England Executive Park, Burlington,Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. Amendment 39-4768 became effective December 23, 1983. This Amendment 39-5240 becomes effective on March 12, 1986.
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.