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71-24-01: 71-24-01 MCDONNELL DOUGLAS: Amdt. 39-1336 as amended by Amendment 39-1413. Applies to all DC-9 Series (except All-freighter) certified in all categories. \n\n\tCompliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failure of the cabin ceiling lights rotary switch and circuit, accomplish the following: \n\n\tModify the ceiling light control wiring in accordance with either Douglas Aircraft Company Alert Service Bulletin A33-55, dated October 8, 1971, or later FAA-approved revisions, or Douglas Aircraft Company Service Bulletin No. 33-56, dated February 25, 1972, or later FAA-approved revisions, or other modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-1336 was effective November 20, 1971. \n\n\tThis amendment 39-1413 is effective March 24, 1972.
2013-08-17: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD requires an initial and recurring inspection of the 9-degree frame for a crack, and repair of the frame if there is a crack. This AD was prompted by the discovery of a crack in the 9-degree frame of a Eurocopter Model AS-365N2 helicopter, and these cracks could develop on the other specified model helicopters because they contain the same 9-degree frame. The actions specified by this AD are intended to detect a crack in the 9-degree frame to prevent loss of structural integrity and subsequent loss of control of the helicopter.
75-18-05: 75-18-05 TAYLORCRAFT AVIATION CORPORATION: Amendment 39-2344. Applies to Model F19, all serial numbers. Before further flight, unless already accomplished: 1. Remove engine mount bolts (P/N AN6-44), spacer (P/N 530627), hose (P/N AN8848-6), bushings (P/N 53074), cup washers (P/N 530741), nut (P/N AN310-6), pin (P/N AN380-3-3), and engine mount seats (P/N 530626) on each of four (4) bolt assemblies, and inspect for damages. (Note: The AN6-44 bolt strength is suspect.) Remove any burr and sharp edges on engine mount and engine bosses. Replace bolt, spacer, and cup washers with those supplied by Taylorcraft Kit #SK75-001 dated May 15, 1975, or subsequent FAA approved parts. Replace other parts found defective with parts supplied by Taylorcraft or subsequent FAA approved parts. Taylorcraft Service Bulletin #75-002 dated March 20, 1975, or subsequent FAA approved revisions, concerns this same subject. Torque bolts to 180-190 inch-lb by tightening nut. Do not overtorque. Caution: Do not apply torque wrench on bolt head. Tightening bolt head will give incorrect value of torque due to presence of shank friction. Also turning of bolt may scratch the bolt shank, causing stress riser and premature failure. 2. Check after torquing for proper alignment of rubber (shock) bushing. 3. Between twenty-five (25) and fifty (50) hours time in service after initial accomplishment of Items 1 and 2, remove engine mount bolts, spacer, hose, bushings, cup washers, nut, pin, and engine mount seats on each of four (4) bolt assemblies and inspect for any signs of wear and deterioration. If evidence of such is found, replace with parts furnished by Taylorcraft. Reassemble using the procedures of Items 1 and 2. 4. Every one hundred (100) hours time in service after accomplishment of Item 3, repeat the actions required in Item 3. 5. A special flight permit per FAR 21.197 may be issued to allow ferrying of the aircraft to a qualified inspection and repair facility. This amendment is effective August 25, 1975, and was effective upon receipt for all recipients of the air mail letter dated May 19, 1975, which contained this amendment.
2013-08-05: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 525 airplanes equipped with certain part number (P/N) air conditioning (A/C) compressor motors. This AD was prompted by reports of smoke and/or fire in the tailcone caused by brushes wearing beyond their limits on the A/C motor. This AD requires inspection of the number of hours on the A/C compressor hour meter, inspection of the logbook, replacement of the brushes on certain P/N A/C compressor motors or deactivation of the A/C system until replacement of the brushes, and reporting of airplane information related to the replacement of the brushes. We are issuing this AD to correct the unsafe condition on these products.
75-15-06: 75-15-06 GATES LEARJET: Amendment 39-2267. Applies to 23 (Serial Numbers 23- 003 thru 23-099); 24 (Serial Numbers 24-100 thru 24-297); and 25 (Serial Numbers 25-003 thru 25-182) series airplanes. Compliance: Required as indicated, unless already accomplished in accordance with Gates Learjet Service Bulletin No. SB 23/24/25-259A or later approved revisions. To check for flaws in the upper main landing gear struts, accomplish the following: A) Within the next 600 hours' time in service after the effective date of this AD, but not later than September 30, 1976, using eddy current or ultrasonic inspection equipment and procedures, inspect the left and right upper main landing gear struts for flaws in accordance with the instructions and sketches outlined in Gates Learjet Service Bulletin No. SB 23/24/25-259A or later approved revisions, or alternatively, remove the left and right upper landing gear struts from the airplane, disassemble, clean, and inspect the struts forflaws in accordance with the aforementioned Service Bulletin. B) If, as a result of the inspections referred to in Paragraph A, flaws are detected, within the next 50 hours' time in service, accomplish the following: 1. Remove any flaw in an upper main landing gear strut with a depth less than .025 inches in accordance with the procedures outlined in the aforementioned Service Bulletin. a. After flaw removal, reinspect using eddy current or ultrasonic methods to assure complete removal of the flaw and then treat and paint the affected area in accordance with the aforementioned Service Bulletin. 2. For flaws that exceed a depth of .025 inches, modify the upper main landing gear strut in accordance with instructions provided by the manufacturer or alternatively, replace with an airworthy part. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. NOTE: Aircraft inspected and in compliance with Gates Learjet Service Bulletin SB 23/24/25-259 (i.e., the original Service Bulletin on this subject) are considered to have complied with the requirements of this AD. This amendment becomes effective July 25, 1975.
75-12-02: 75-12-02 CANADAIR: Amendment 39-2220. Applies to Canadair CL-215-1A10 airplanes certificated in all categories. Compliance required with the next twenty-five hours' time in service after the effective date of this AD unless already accomplished. To preclude the possibility of incorrect connection being made to the engine Firex bottles, accomplish the following: Modify the routing of the wire harness to the engine Firex bottles in accordance with Canadair Service Information Circular No. 66-CL-215, Revision A, dated August 13, 1974, or an equivalent modification approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective May 30, 1975.
2013-08-07: We are adopting a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332C, L, and L1 helicopters to require an initial and repetitive inspections of the outer skin, butt strap, and fuselage frame for a crack and modification of the helicopter. This AD was prompted by an AD issued by the [[Page 23108]] European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, which states that a crack was discovered in a fuselage frame during a daily check. The actions of this AD are intended to detect a crack, to prevent loss of airframe structural integrity and subsequent loss of control of the helicopter.
75-26-17: 75-26-17 PILATUS AIRCRAFT LTD: Amendment 39-2466. Applies to Pilatus Model PC-6/A airplanes up to and including S/N 659 (all variants) with Astazou engine installations manufactured by Pilatus Aircraft Ltd. NOTE: This AD does not apply to Pilatus Model PC-6/A airplanes manufactured by Fairchild Hiller. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of the engine mount to fuselage attachment, reinforce the U-channel, P/N 6201.992, by installing a steel plate, P/N 112.35.06.337, to each U-channel lug and rework the engine strut heads, P/N 6501.106, in accordance with paragraph 2.2 of Pilatus Aircraft Ltd. Service Bulletin No. 83A dated February 1971, or an FAA-approved equivalent. This amendment becomes effective on January 17, 1976.
75-27-04: 75-27-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2476. Applies to Model SA-341G "Gazelle" helicopters, certificated in all categories, serial numbers 1062 and lower, incorporating standard fuel tank P/N 341A.55.1065.1065.20, or .22, or .24. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Gazelle Service Bulletin No. 28.01. To prevent interruption of fuel flow to the engine during execution of approved flight maneuvers, modify the fuel system to provide for increased fuel sump capacity and an improved booster pump location in accordance with subparagraph 2(B) of Gazelle Service Bulletin No. 28.01, as revised November 21, 1973, or an FAA-approved equivalent. This amendment becomes effective on January 19, 1976.
2013-07-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of an incorrect procedure used to apply the wear and corrosion protective surface coating to attach pins of the horizontal stabilizer rear spar. This AD requires inspecting to determine the part number of the attach pins of the horizontal stabilizer rear spar, and replacing certain attach pins with new, improved attach pins. We are issuing this AD to prevent premature failure of the attach pins, which could cause reduced structural integrity of the horizontal stabilizer to fuselage attachment, resulting in loss of control of the airplane.