Results
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.
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.