Results
71-12-03: 71-12-03 GRUMMAN AIRCRAFT: Amdt. 39-1224. Applies to Model G21A aircraft certificated in all categories. Within the next 25 flight hours after the effective date of this AD, unless already accomplished, visually inspect, replace or repair P/N 7190Y-OA-1408 (flexible drive shaft, elevator tab control) in accordance with the procedure of Grumman Customer Bulletin G21A No. 71-1 dated 3 March 1971 or with equivalent method. Equivalent methods or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment is effective June 10, 1971.
75-09-15: 75-09-15 LYCOMING: Amendment 39-2187. Applies to Lycoming Model IO-320, AIO-320, IO-360, LIO-360, HIO-360-C Series, IVO-360, TIO-360, AIO-360, IGO-480, IO-540, TIO-540, IVO-540, IGO-540, AND IO-720 Series Engines equipped with the following listed Bendix Fuel Injector Flow Divider part numbers. 2524218-1 thru 2524225-1, 2524227-1, 2524232-1, 2524240-1, 2524248-1, 2524265-1, 2524327-1, 2524342-1, 2524397-1, 2524416-1, 2524421-1, 2524571-1, 2524583-1, 2524610-1. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible fuel starvation to the engine accomplish the following: Remove Bendix P/N 2537013 fuel flow divider cover gasket and install Bendix P/N 2538998 cover gasket in accordance with Lycoming Service Bulletin No. 382 or equivalent procedure approved by Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. (Bendix Energy Controls Division Fuel System Bulletin No. RS43also covers this subject). This amendment is effective April 30, 1975.
2013-03-17: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10 and BR700- 710A2-20 turbofan engines, and certain BR700-710C4-11 model engines. This AD was prompted by RRD performing an evaluation that determined that certain high-pressure turbine (HPT) stage 1 and stage 2 discs from a specific supplier may contain steel inclusions that may cause the discs to fail before they reach their current life limits. This AD requires reducing the life limits for certain HPT stage 1 and stage 2 discs. We are issuing this AD to prevent failure of the HPT stage 1 and stage 2 discs, which could result in uncontained failure of the engine and damage to the airplane.
73-22-02: 73-22-02 AIRCRAFT PARTS and DEVELOPMENT CORP.: Amendment 39-1737. Applies to Models A-9, A- 9A, and A-9B. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent water accumulation in the wing lift struts and associated detrimental effects, accomplish the following: (a) Inspect visually for welds on both sides of the four wing lift struts at the P/N 10671 eye fittings. A 360 degree fillet weld is required around the eye fitting shank on both sides of the lift strut to seal the strut against moisture. These fittings provide for attachment of the lift struts to the stabilizing struts. (b) If the welds between the eye fittings and the lift struts do not provide a complete seal as specified above, the lift strut should be removed and checked for water ingestion visually and for corrosion by x-ray, ultrasonic or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. (1) If no water or corrosion is present in the strut, weld the eye fitting to the strut 360 degrees on both sides of the strut and reinstall the strut. (2) If water is present in the strut (without corrosion), dry the strut, flush with linseed oil, weld the eye fitting to the strut 360 degrees on both sides of the strut and reinstall the strut. (3) If corrosion is found, before further flight, the affected lift strut must be replaced or corrosion must be removed in accordance with a procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. (c) If the welds between the eye fittings and the lift struts provide a complete seal as specified above, no further action is required. (APDC Service Bulletin No. A-23 covers this same subject.) This amendment becomes effective November 20, 1973.
2013-03-13: We are adopting a new airworthiness directive (AD) for certain [[Page 9801]] Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This AD was prompted by reports of the cockpit door falling off the hinges when it is being opened or closed. This AD requires replacing the striker and quick- release pin of the passive lock of the cockpit door, and replacing the upper and lower hinges of the cockpit door. We are issuing this AD to prevent the cockpit door from falling off the hinges, which could cause injury to airplane occupants.
2013-03-07: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (Type Certificate previously held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400A airplanes. This AD was prompted by a report that the wiring for the 5- volt direct current (DC) system is undersized and does not have adequate circuit protection for the smaller gauge wire. This AD requires installing an in-line fuse in the 5-volt DC system for each of the five instrument lighting control power supplies. We are issuing this AD to prevent failure of the wiring, which could result in smoke in the cockpit, loss of cockpit lighting, and potential damage to surrounding wiring for other cockpit equipment such as the stick shaker function or angle-of-attack indicators.
76-01-03: 76-01-03 BOEING: Amendment 39-2487. Applies to all Boeing Model 737 series airplanes certificated in all categories. Compliance required as indicated. \n\tTo assure that passenger seats situated over left hand body station 907 will be restrained if subjected to a minor crash landing as required by FAR 25.561, unless already accomplished, by December 31, 1976, install the floor beam attaching angle in accordance with Boeing Service Bulletin No. 737-53-1044, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. Thedocuments may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective January 23, 1976.
2013-02-02: We are adopting a new airworthiness directive (AD) for CFM International, S.A. CFM56-3, CFM56-3B, and CFM56-3C turbofan engines. This AD requires removal from service of certain high-pressure turbine (HPT) disks manufactured by Global Material Solutions of Pratt & Whitney, at reduced maximum life limits. This AD was prompted by a report of a forging process error during manufacture of these HPT disks. We are issuing this AD to prevent uncontained release of multiple turbine blades, damage to the engine, and damage to the airplane.
73-17-01: 73-17-01 CESSNA: Amdt. 39-1701. Applies to all series of Cessna Models 170, 172, 175, 180 and 182 airplanes equipped with the 18 gallon auxiliary fuel tank manufactured by the Javelin Aircraft Company, Wichita, Kansas. Compliance: Required within 100 hours time in service after the effective date of this AD, unless already accomplished. To advise the pilot concerning proper fuel transfer pump operation, install Javelin Placard 782-14 or an equivalent FAA-approved placard, adjacent to the fuel transfer pump switch which reads as follows: "AUXILIARY FUEL TRANSFER PUMP. PULL ON. PUSH OFF. PLACE PUMP OFF BEFORE CHANGING FROM LEFT TANK." NOTE: Failure to turn off fuel boost pump allows air to enter engine fuel system and may cause engine power failure when fuel selector valve is changed from left tank position. Cessna Service Letter No. SE69-24 dated November 21, 1969, or subsequent FAA-approved revisions cover this subject matter. This amendment becomes effective August 16, 1973.
74-19-06: 74-19-06 BOEING: Amendment 39-1960. Applies to Boeing Model 747 airplanes, certificated in all categories, which are affected by Boeing Service Bulletin 747-52-2090. Compliance required as indicated: \n\t(A)\tWithin the next 1200 hours time in-service after the effective date of this AD, unless already accomplished in the last 800 hours time in-service, and at intervals thereafter not to exceed 2,000 hours time in-service, visually inspect the torque tube cranks, Part Numbers 65B05025-1 and -2, 69B02875-1 and -2, and 65B09704-1 on passenger doors Nos. 2, 4, and 5 right- and left-hand sides for cracks. If cracks are not found, apply LPS-3 and retorque cross bolts in accordance with Paragraph III, Part I of FAA-approved Boeing Service Bulletin 747-52- 2090, dated May 17, 1974, or FAA approved revisions. If cracks are found, repair or replace in accordance with Paragraph (B) below. \n\t(B)\tCracked parts may be repaired by installation of a saddle clamp in accordance with Paragraph III,Part II of FAA-approved Boeing Service Bulletin 747-52-2090, or FAA-approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, and shall be reinspected in accordance with FAA-approved Boeing Service Bulletin 747-52-2090 at intervals thereafter not to exceed 3,200 hours time in-service. As terminating action, cracked parts may be replaced with new parts in accordance with Paragraph III, Part III of FAA-approved Boeing Service Bulletin 747-52-2090, or FAA-approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\t(C)\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection interval of the operator, if the request contains substantiating data to justifythe adjustment. \n\tThis amendment becomes effective thirty days after September 20, 1974.