Results
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.