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80-07-06: 80-07-06 BEECH: Amendment 39-3730. Applies to Model 76 (Serial Numbers ME-1 through ME-252, ME-254, ME-256 through ME-261, ME-263 through ME-267, ME-269 through ME- 274, ME-279, ME-283, ME-284, ME-286, ME-288 through ME-295, ME-297, ME-299, ME-300, ME-302 through ME-307, ME-309, ME-311 through ME-313, ME-315 and ME-316) and Model 77 (Serial Numbers WA-1 through WA-76) airplanes certified in all categories. COMPLIANCE: Required as indicated unless already accomplished. To prevent a possible unbalanced rudder condition that could induce flutter, accomplish the following: A) Prior to further flight, fabricate and install a temporary placard in plain view of the pilot which reads as follows: "BEFORE EACH FLIGHT CHECK RUDDER AND RUDDER TRIM TAB (IF INSTALLED) FOR TRAPPED WATER BY: (1) MOVING RUDDER RAPIDLY USING RUDDER PEDALS AND HAVING A SECOND PERSON LISTEN FOR SOUND OF WATER (IF AMBIENT TEMPERATURE IS LESS THAN 32 DEGREES FAHRENHEIT MOVE AIRPLANE TO HEATED HANGER UNTIL ANY POSSIBLE WATER ACCUMULATION HAS MELTED) (2) DO NOT OPERATE AIRCRAFT UNTIL TRAPPED WATER IS REMOVED" and comply with the instructions in said placard. B) Within the next 25 hours time-in-service, (1) incorporate additional drainage in the rudder and rudder trim tab (if installed) by drilling new drain holes and (2) seal gaps in the top of the rudder and trim tab (if installed), all in accordance with Beechcraft Service Instructions No. 1116. C) When Paragraph B) has been accomplished, Paragraph A) is no longer applicable. D) The airplane may be flown in accordance with FAR 21.197 to a location where Paragraph B) can be accomplished, provided there is no trapped water in the rudder and trim tab (if installed). E) Any equivalent method of compliance with this letter must be approved by the Chief, Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209.This amendment becomes effective on April 3, 1980, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated March 12, 1980.
62-21-01: 62-21-01 CANADAIR: Amdt. 488 Part 507 Federal Register September 27, 1962. Applies to all Model CL-44D4 aircraft equipped with Rolls Royce Tyne Engines. Compliance required within the next 350 hours' time in service after the effective date of this AD. To preclude bearing failure resulting from sludge deposited in oil ways which feed the high pressure turbine bearing, accomplish the following: (a) Install high pressure turbine bearing scavenge oil temperature indicating system in accordance with Rolls Royce Modification 959 (Service Bulletin Ty72-384) and Canadair Service Information Circular No. 216-CL44D4. (b) If the oil flow through the scavenge line has not been checked within 100 hours prior to the installation of the temperature indicating system specified in (a), check the oil flow in accordance with the procedures outlined in Sections 2A and 2B of Rolls Royce Alert Service Bulletin No. A-Ty79-15 at the time the temperature indicating system is installed.(c) Appropriate changes to the airplane flight manual shall be made covering the applicable provisions of Section 2D of Service Bulletin A-Ty79-15 regarding feathering of an engine if the turbine bearing scavenge oil corrected temperature exceeds 180 degrees C. during cruise. (d) When the oil temperature indicating system is installed per paragraph (a) the inspections required in AD 62-9-2 as amended, may be discontinued. This directive effective October 29, 1962.
2019-18-09: The FAA is adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes; and Model C-130A, HP-C-130A, EC-130Q, and C-130B airplanes. This AD requires a visual inspection of the center wing upper and lower rainbow fittings for cracks, an eddy current inspection of the center wing lower rainbow fittings for cracks, and replacement if necessary. This AD was prompted by reports of cracked inner tangs of the center wing lower rainbow fittings. The FAA is issuing this AD to address the unsafe condition on these products.
2019-16-07: The FAA is superseding Airworthiness Directive (AD) 2016-12- 09, which applied to certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2016-12-09 requirements included removing existing and installing new fasteners, inspecting for and, if necessary, repairing cracking. This new AD requires repetitive inspections of the fastener holes at a certain frame and applicable on-condition actions, and, for certain airplanes, requires a modification, as specified in European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. Also as specified in the EASA ADs, this AD also provide an optional terminating action for certain airplanes, which terminates the inspections. This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB) and a determination that the compliance time specified in AD 2016-12-09 for the modification of the insideCWB must be revised. The FAA is issuing this AD to address the unsafe condition on these products.
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.