Results
73-19-04: 73-19-04 BELL: Amdt. 39-1711. Applies to Model 47 series helicopters certificated in all categories that are equipped with main rotor blade grips, P/N 47-120-135-1, -2, -3 or P/N 47- 120-252-1, -3. Compliance required within the next 100 hours' time in service after the effective date of this A.D., unless already accomplished. To prevent possible fatigue cracks from developing, accomplish the following for each main rotor blade grip: (a) Inspect the grip thread relief fillet. The inboard radius and bottom of the fillet must have a smooth finish and be free of nicks or sharp tool marks (Ref. Figure 1-22 of Bell 47D- 1, 47G and 47G-2 Maintenance and Overhaul Instructions). (b) Inspect the root radius of the 4 1/2 inch diameter threads for sharp notches. The root radius must be smooth and free of sharp notches or grooves. (c) If the grip thread relief fillet is not as specified in subparagraph (a) or has nicks or sharp tool marks, or if the thread root radius has a sharp notch or groove, replace the affected grip prior to next flight, except the helicopter may be flown in accordance with FAR 21.197 to a base where the grip may be replaced. This amendment becomes effective October 10, 1973.
2013-11-09: We are superseding an existing airworthiness directive (AD) for Turbomeca S.A. Arrius 2B, 2B1, and 2F turboshaft engines. That AD currently requires replacement of injector manifolds and borescope- inspection of the flame tube and the high-pressure (HP) turbine area for possible damage. This new AD requires, depending on the engine model, repetitive replacements of fuel injection manifolds and the privilege injector, or, repetitive replacements of the privilege injector. This AD was prompted by a report that the corrective actions of the existing AD were insufficient to eliminate the unsafe condition. We are issuing this AD to prevent an uncommanded in-flight shutdown of Arrius 2B1 and 2F turboshaft engines and damage to the helicopter.
2013-10-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340- 300, A340-500, and A340-600 series airplanes. This AD was prompted by several reports of a burning smell and/or smoke in the cockpit during cruise phase leading, in some cases, to diversion to alternate airports. This AD requires an inspection to identify the installed windshields and replacement of any affected windshield. We are issuing this AD to prevent significantly increased workload for the flightcrew, which could, under some flight phases and/or circumstances, constitute an unsafe condition.
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.
74-20-04: 74-20-04 HUGHES HELICOPTERS: Amendment 39-1968. Applies to Hughes Model 369, 369A, 369H, 369HE, 369HS and 369HM helicopters certificated in all categories. Compliance required within the next 25 hours' of helicopter operation after the effective date of this AD, unless already accomplished within the last 75 hours' of helicopter operation, and thereafter at intervals not to exceed 100 hours' of helicopter operation from the last inspection. To detect cracks, gouges, nicks and scratches in the main rotor blade trailing edge, accomplish the following: (a) Inspect the main rotor blade trailing edge in accordance with Hughes Service Information Notice. No. HN-73, dated August 19, 1974, or later FAA-approved revisions. (1) If cracks are found remove blade from service prior to further flight. (2) If gouges, nicks and/or scratches are found replace or repair blade prior to further flight in accordance with Hughes Service Information Notice, No. HN-73. (b)Equivalent inspection and repair procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region upon submittal of adequate substantiating data. (c) Aircraft may be flown to a base for performance of the inspections required by this AD per FAR's 21.197 and 21.199. This amendment becomes effective September 25, 1974.
2013-07-05: We are adopting a new airworthiness directive (AD) for Eurocopter France EC130B4 helicopters. This AD requires visually checking the center windscreen panel (center windscreen) for a crack and replacing the center windscreen if there is a crack, if the windscreen distorts during flight, or within 12 months. This AD was prompted by in-flight cracking and failure of a center windscreen. The actions of this AD are intended to detect a crack in the blending radii of the center windscreen to prevent failure of the windscreen, injury to the flight crew, and subsequent loss of control of the helicopter.
72-16-08: 72-16-08 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: (S.N.I.A.S.) formerly Sud Aviation): Amendment 39-1490. Applies to Alouette Astazou SA3180, SA318B, and SA318C helicopters which have not been modified in accordance with Aerospatiale Service Bulletin No. 65.82 dated October 25, 1971, or an FAA-approved equivalent. Compliance required as indicated. To prevent possible cracks or failures of the half sleeves fitted on the flexirac unions on the main gear box to cooler oil line, accomplish the following in accordance with Aerospatiale Service Bulletin No. 05.39, amended November 10, 1971, or an FAA-approved equivalent. (a) For helicopters fitted with half sleeves, P/N L.16.06, on-flexirac union assemblies, P/N L.16.03, before further flight unless already accomplished within the last 100 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service on the half sleeves, replace the half sleeves, P/N L.16.06, by replacing the assembly, P/N L.16.03, with a new assembly of the same part number. (b) For helicopters fitted with half sleeves, P/N LS.16.06, on flexirac union assemblies, P/N LS.16.03, before further flight unless already accomplished within the last 800 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service on the half sleeves, replace the half sleeves, P/N LS.16.06, by replacing the assembly, P/N LS.16.03, with a new assembly of the same part number. (c) Replacement of the half sleeves in accordance with paragraphs (a) and (b) may be discontinued when the flexirac union on the main gear box oil pump is reinforced in accordance with Aerospatiale Service Bulletin No. 65.82 dated October 25, 1971, or an FAA- approved equivalent. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective upon receipt of the telegram dated June 15, 1972, which contained this amendment.
2013-05-14: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 412 and 412EP helicopters. This AD requires establishing a lower life limit on certain swashplate outer ring assemblies (outer ring), revising the retirement life on the components' history card or equivalent record, and revising the maintenance manual or Instructions for Continued Airworthiness (ICA). This AD also prohibits installing these outer rings on any helicopter. This AD was prompted by reports of cracking in the outer rings. The actions are intended to prevent failure of an outer ring because of cracking, which could lead to the loss of main rotor (M/R) blade pitch control and subsequent loss of helicopter control.
70-08-03: 70-08-03 SIKORSKY: Amdt. 39-974. Applies to Sikorsky type S-61A/L/N/R helicopters certificated in all categories. Accomplish the following within the next 10 heater hours in service, unless already accomplished, and every 15 heater hours in service thereafter: A. Remove and inspect combustion air inlet duct backfire check valve Bobrick Co. P/N 9660-1-1 or 40064-32 for distortion, missing flappers, or other obvious damage. B. Replace defective valves before further operation of the heater with a part inspected in accordance with paragraph A above. Upon replacement inspect all heater inlet air ducting for evidence of fuel contamination. Any fuel contamination must be eliminated before further heater operation. C. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator. D. For the purpose of this AD, compliance time may be based on helicopter hours in service if the owner or operator cannot document heater operating time. This amendment is effective April 23, 1970, and was effective March 17, 1970 for all recipients of the telegram dated March 17, 1970 which contained this amendment.
2013-05-13: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710 series turbofan engines. This AD requires replacement of the affected fuel pump splined couplings. This AD was prompted by service experience that demonstrated premature wear of the splined coupling on the fuel pump. We are issuing this AD to prevent failure of the engine and loss of the airplane.
2013-05-20: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Spey 511-8 turbojet engines. This AD requires inspection and, if necessary, replacement of affected bolts and, if any bolt is found broken, inspection of the adjacent disc(s) for damage. This AD was prompted by a recent quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.
76-01-07: 76-01-07 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2491. Applies to Lockheed-California Company Model L-1011-385 series airplanes certificated in all categories. Compliance required within the next 300 hours' time in service after effective date of this AD, unless already accomplished: To prevent possible emergency evacuation system hard container release cable assembly failures, accomplish the following: (a) Inspect each slide, slide/raft evacuation system to determine if a modified cable assembly has been installed in accordance with Lockheed Alert Service Bulletin No. 093-25-A239, dated October 23, 1975, and Air Cruisers Company Service Bulletin 25-29, dated October 23, 1975, or later FAA-approved revisions or an FAA-approved equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. Modified cable assemblies are identified by either blue or green paint on the parachute pin in the swaged area. (b) Replace all unmodified cableassemblies located during the inspections required by paragraph (a) with a modified cable assembly in accordance with Air Cruisers Company Service Bulletin 25-29, dated October 23, 1975, and Lockheed Alert Service Bulletin No. 093-25-A239, dated October 23, 1975, or later FAA-approved revisions, or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Inspect each slide, slide/raft evacuation system hard container latching parts which interrelate with the hard container release cable parachute pins for burrs and/or sharp edges and replace or rework as necessary in accordance with Lockheed Alert Service Bulletin No. 093-25- A239, dated October 23, 1975, and Air Cruisers Company Service Bulletin No. 25-29, dated October 23, 1975, or later FAA-approved revisions or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Reidentify slide, slide/raft evacuation assemblies having modifiedcable assemblies which have been installed as required by paragraph (b), in accordance with Lockheed Alert Service Bulletin No. 093-25-A239 dated October 23, 1975, or later FAA-approved revisions, or equivalent means of reidentification approved by the Chief, Aircraft Engineering Division, FAA Western Region. This paragraph supersedes the reidentification requirement of paragraph (e), AD 75-03- 07. This amendment becomes effective February 20, 1976.
2012-26-06: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now under the Erickson Air-Crane Incorporated (Erickson) Model S-64F type certificate. This AD supersedes an existing AD which requires inspections, rework, and replacement, if necessary, of the main gearbox (MGB) second stage lower planetary plate (plate). Since we issued that AD, the manufacturer has conducted a configuration review and analysis, and a review of the service history of certain components. The actions of this AD are intended to establish life limits for certain components, remove various parts from service, and require consistency in the part numbers of certain four bladed tail rotor (T/R) assemblies to prevent fatigue cracking, failure from static overload, and subsequent loss of control of the helicopter.
2013-04-03: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 750 airplanes. This AD was prompted by reports of loss of displayed airspeed. This AD requires inspecting certain logic modules to determine if certain cabin altitude/pitot static heater module assemblies are installed and replacing those assemblies with a new assembly; and revising the Non-Normal Procedures Section of the airplane flight manual (AFM) to include procedures for resetting the pitot switch in the event of pitot heater failure and for total loss of airspeed indication. We are issuing this AD to prevent the loss of all displayed airspeed, which could result in reduced ability to control the airplane.
75-09-12: 75-09-12 LOCKHEED-CALIFORNIA: Amendment 39-2186 as amended by Amendment 39-2703. Applies to Lockheed L-1011-385 series airplanes, except models L-1011- 385-1-14 and L-1011-385-1-15, certificated in all categories with Collins FCS-110 autopilot installed. To preclude exceeding the go-around pitch limits during autopilot coupled go-arounds accomplish the following: 1. Operators shall, by the most immediate and practicable means, notify flight crews of Lockheed Operating Information Letter (OIL) 86. 2. Effective 48 hours after receipt of this telegram the following operating limitation applies: 'Autopilot must be disconnected for go-around' and a placard must be installed in plain view of the pilots stating: 'Autopilot must be disconnected for go-around.' 3. The operating limitation specified in paragraph 2. no longer applies and the cockpit placard may be removed by accomplishment of the following: i. Replacing the AFCS Trim Augmentation Computer, Lockheed P/N 672443-109 or -113 with 672443-115 computer, in accordance with Lockheed Service Bulletin 093-22-077, dated December 11, 1975, or later FAA-approved revisions; and ii. Replacing both AFCS Pitch Computers, Lockheed P/N 672314-177, - 179, -181, -183 and -185 with 672314-157, -159, -161, -163 and -165 computers, respectively, in accordance with Lockheed Service Bulletin 093-22-082, dated May 5, 1976, or later FAA- approved revisions. Amendment 39-2186 became effective April 28, 1975, for all persons except those to whom it was made effective by telegram, dated March 28, 1975. This amendment 39-2703 becomes effective September 2, 1976.
2012-25-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by a report of in-flight fracture of the right windshield (window 1) on the flight deck and multiple reports of electrical arcs at the terminal blocks of the flight deck windshields resulting in smoke and fire. This AD requires repetitive inspections of electrical heat terminals on the left and right windshields for damage, and corrective actions if necessary. This AD allows replacing an affected windshield with a windshield equipped with different electrical connections, which would terminate the repetitive inspections for that windshield. We are issuing this AD to prevent smoke and fire in the flight deck, which can lead to loss of visibility, and injuries to or incapacitation of the flightcrew.