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2005-20-09: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model ATP airplanes. This AD requires doing an inspection of each bolt attaching the aft isolators to both engine subframes and replacing bolts if necessary. This AD results from reports of failures of the bolts attaching the aft isolators to the engine subframe. We are issuing this AD to prevent failure of the bolts attaching the aft isolators to the engine subframe, which may result in an engine separating from the airplane.
83-07-21: 83-07-21 SHORT BROTHERS AND HARLAND, LTD.: Amendment 39-4623. Applies to the following Model/Serial Number airplanes with a one-piece, "flip-type," cargo door installed, certificated in any category. Model Serial Number SC-7 Series 3 SH1855, SH1860, SH1866 through SH1868, SH1875 through SH1880, SH1887 through SH1891, SH1894 through SH1900, SH1902, SH1904 through SH1906, SH1909 through SH1917, SH1919 through SH1924, SH1928 through SH1929, and SH1931 and on. Compliance: Required as indicated, unless already accomplished. To preclude unwanted inflight opening of the cargo door, within the next 100 hours time- in-service after the effective date of this AD, accomplish the following: (a) Examine the cargo door locking pin microswitch assembly per Part "A" of the Accomplishment Instructions in Shorts Service Bulletin No. 52-65 dated November 1, 1980. If an adjusting screw is found to be installed on the microswitch operating lever as shown on Figure 2 of the Service Bulletin, prior to further flight accomplish the following per Part "B" of Service Bulletin No. 52-65: 1) Remove the adjusting screw from the microswitch operating lever. 2) Adjust the length of the locking pin operating rod allowing the pin to act directly on the lever. 3) Adjust the microswitch so that the final configuration of the microswitch and locking pin position are as shown in Figure 5 of the Service Bulletin. (b) Check the operation of the door to assure proper engagement of the locking pins per Step 14 of the Service Bulletin. (c) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 14, 1983.
98-08-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires replacing the horizontal stabilizer rear fittings with parts of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent structural failure of the horizontal stabilizer caused by cracked rear fittings, which could result in loss of sailplane controllability.
83-13-02: 83-13-02 CANADAIR: Amendment 39-4670. Applies to Model CL-600-1A11 airplanes, serial numbers 1024 to 1074 inclusive, certificated in all categories. To ensure that the passenger door latch mechanism and associated fittings properly latch the door, accomplish the following, unless already accomplished. 1. Within the next 10 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours time in service, perform the inspection of the interior handle and adjust, as necessary, in accordance with paragraph 2 of Canadair Alert Service Bulletin No. A600-0203 dated September 13, 1982. 2. Within the next 60 hours time in service after the effective date of this AD, modify the latch mechanism and associated components in accordance with paragraph 2.C. of the service bulletin. Accomplishment of this modification terminates the inspection requirements of paragraph 1. above. 3. Alternate means of compliance which provide an equivalentlevel of safety may be used when approved by the Manager, Settle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective July 5, 1983.
2005-20-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-243, -341, -342, and -343 airplanes. This AD requires revising the airplane flight manual to provide the flightcrew with new, ground ice-shedding procedures during long taxi periods in certain icing conditions. This AD results from reports of engine damage to the blades of the first stage of the intermediate pressure compressor due to ice accumulation. We are issuing this AD to prevent engine damage due to ice accumulation, which could result in an engine shutdown and cause the flightcrew to divert to the nearest available airport.
80-12-01: 80-12-01 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3784. Applies to all Model L-188A and L-188C airplanes incorporating Supplemental Type Certificate SA1754WE or SA1831WE or SA2536WE (cargo door modification), certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent rapid decompression, door warning failure or loss of cargo door, accomplish the following: (a) Within 15 hours' time in service from the effective date of this AD except for those persons to whom it was made effective earlier by telegraphic AD T80WE-11 dated February 22, 1980, install a placard in plain view of the flight crew reading: "Pressurized Flight Prohibited", or: (b) Inspect each cargo door and door sill by visual, magnetic particle, and dye penetrant methods per the instructions specified in paragraph B of Lockheed Alert Bulletin 88/LAS-1A, dated February 14, 1980, and per paragraph B of Lockheed Alert Bulletin 88/LAS- 1B, dated February 21,1980. Repair as required. (c) The placard prohibiting pressurized flight may be removed after the accomplishment of paragraph (b) of this AD. (d) For aircraft operated in the pressurized mode, prior to 1,000 hours' additional time in service since the last such inspection required by paragraph (b) of this AD, install cargo door structural reinforcements in accordance with Lockheed Aircraft Services Drawing 4036900 (No change), re-rig the cargo door per Lockheed Aircraft Services Drawing 4036982, Revision B, (after installation of reinforcements per Drawing 4036900), and inspect per paragraph C of Lockheed Alert Bulletin 88/LA5-1C dated March 24, 1980 within 5,000 hours' additional time in service since door modification and thereafter at intervals not to exceed 5,000 hours' time in service since the last such inspection. (e) For aircraft operated either pressurized or unpressurized, prior to the accumulation of 1,000 hours' additional time in service from the effectivedate of this AD, rewire the cargo door warning light circuitry in accordance with Lockheed Aircraft Services Drawing 4036666, Revision D. (f) For aircraft operated in the unpressurized mode, prior to the accumulation of 5,000 hours' additional time in service from the effective date of this AD, install cargo door structural reinforcements in accordance with Lockheed Aircraft Services Drawing 4036900 (No change), re-rig the cargo door per Lockheed Aircraft Services Drawing 4036982, Revision B, (after installation of reinforcements per Drawing 4036900), and inspect per paragraph C of Lockheed Alert Bulletin 88/LA5-1C dated March 24, 1980, within 5,000 hours' additional time in service since door modification and thereafter at intervals not to exceed 5,000 hours' time in service since the last such inspection. (g) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment supersedes Telegraphic AD T80WE-11 dated February 22, 1980. This amendment becomes effective June 9, 1980.
98-07-26: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a detailed visual inspection(s) for damage or chafing of certain electrical wire bundles and for clearance between the wire bundles and adjacent forward galley air chiller; and follow-on corrective actions. This amendment is prompted by a report indicating that damaged wires caused the tripping of electrical circuit breakers and the display of caution messages by the engine indication and crew alerting system. The actions specified in this AD are intended to prevent failure of essential electrical systems and a potential fire hazard for passengers and crewmembers, due to damage or chafing of the wire bundles that resulted in arcing between exposed conductors and burning of the adjacent electrical bundles.
2005-19-28: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracks in the aft face of the rear spar at the area adjacent to the bolt holes and the end of the build slot, and repair if necessary. The AD also provides an optional terminating action for the repetitive inspections. This AD results from a report that, during fatigue tests of the wing, cracks were found in the vertical web of the rear spar between ribs 1 and 2 having initiated at the build slot. We are issuing this AD to detect and correct fatigue cracking in the vertical web of the wing rear spar, which could result in reduced structural integrity of the wing.
2017-10-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports indicating that on airplanes that received a certain repair following crack findings, cracks can re-initiate. This AD requires repetitive inspections of the center wing frame (FR) 40 lower outboard radius for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2011-03-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Prompted by an accident * * , the FAA published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/12. The design review conducted by Fokker on the F28 in response to these regulations revealed that, in case of a lightning strike, an ignition source can develop in the wing tank vapour space during fuel transfer from bag tank CWT [center wing tank], if the electrical power for refuelling is not switched off after refuelling. Service experience has revealed situations where the power switch of the Fuelling Control Panel (FCP) appeared to be "ON'' with the access panel closed. The cam on the access panel that should operate the power switch, if forgotten by flight crew or maintenance staff, can pivot away during closing of the panel, which may result in the switch staying in the "ON'' position. This condition, if not corrected, could result in a wing fuel tank explosion and consequent loss of the aeroplane. * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.