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80-05-03: 80-05-03 MCDONNELL DOUGLAS: Amendment 39-3705. Applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, -50 series, and C-9, C-9A, and VC-9 airplanes certificated in all categories, having the cabin aft pressure bulkhead fitted with a ventral door. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tTo prevent elevator control cable binding resulting from interference with insulation blanket material, accomplish the following: \n\n\t(a)\tWithin the next 200 hours' time in service from the effective date of this AD, and thereafter at intervals not to exceed 200 hours' time in service since the last inspection, visually inspect the insulation blanket located in the aft entrance stairway area, left side, (looking forward), for security and to establish that there is no interference with the elevator control cable or pulley identified in Part 2 of McDonnell Douglas Service Bulletin 25-222, Revision 1, dated November 6, 1979. \n\n\t(b)\tIf evidence of insulation blanket sagging and/or interference with the elevator control cables or pulley is detected, rework the blanket as shown in Service Bulletin 25-222, Revision 1, dated November 6, 1979, prior to return to service. \n\n\t(c)\tThe repetitive inspection of paragraph (a) may be discontinued after accomplishment of the insulation blanket rework per paragraph (b) of this AD. \n\n\t(d)\tAlternative 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. \n\n\t(e)\tSpecial 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 required by this AD. \n\n\tThis amendment becomes effective March 10, 1980.
80-22-52: 80-22-52 MCDONNELL DOUGLAS: Amendment 39-4081. Applies to DC-9-80 series airplanes certificated in all categories with Walter Kidde fire extinguisher systems installed. Compliance required as prescribed in the body of this AD unless already accomplished. To prevent the loss of fire fighting capability due to failure of the fire extinguisher cartridge P/N 876296-01E to discharge the fire extinguishing agent container, accomplish the following: \n\n\tA.\tWithin 24 hours following the effective date of this AD, inspect each cartridge installed in the engine and APU fire extinguishing systems. Identify date stamp and lot number located on the wrench flats of the cartridge. \n\n\t\t1.\tCartridges with date and lot number prior to calendar year 1980 (XX-80) are acceptable and need not be removed. Document inspection in Aircraft Log Book. No further action required. \n\n\t\t2.\tIf either date is calendar year 1980 (XX-80), remove the cartridge and inspect for part number. If the part numberindicated by rubber stamp on the inside shank is "01E," remove from service and dispose of in a proper manner. If the part is indicated as "D" on the shank or P/N 876296 (basic P/N), these cartridges may be reinstalled per maintenance procedures and returned to service. \n\n\tB.\tReplace defective cartridges with cartridges having acceptable part numbers. APU installation may be placarded inoperative if appropriate cartridges are not available. \n\n\tC.\tAll P/Ns 876296-01E should be removed from stock and properly disposed of or returned to vendor. \n\n\tD.\tSpecial flight permits may be issued in accordance with Sections 21.197 and 21.199 of Part 21 of the Federal Aviation Regulations to operate airplanes to a base for the accomplishment of inspections required by this AD. \n\n\tE.\tAlternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. \n\n\tThis amendment becomes effective April 20, 1981, to all persons, except those to whom it was made immediately effective by telegram dated October 18, 1980.
2005-20-13: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires a one-time inspection of the lower lobe frames of body section 43 to find open holes between stringers 17L and 17R and to record their location; repetitive high frequency eddy current (HFEC) inspections for cracks of all open holes; and related investigative and corrective actions if necessary. This AD also includes an optional terminating action of installing rivets in all open tooling holes and all unused lining holes, which would terminate the repetitive open-hole HFEC inspections once a hole is plugged with a rivet. This AD results from reports of cracks at open tooling holes in the lower lobe frames of body section 43. We are issuing this AD to detect and correct cracks in the frames, which could result in cracks in the skin panels and rapid decompression of the airplane.
2017-11-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by several reports of nose wheel steering failures in service. This AD requires a part verification and replacement of certain steering manifolds. We are issuing this AD to address the unsafe condition on these products.
2017-11-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by reports of cracks in certain pivot fittings of a CFM56 engine's thrust reverser (T/R). This AD requires repetitive inspections for cracking and corrosion of certain pivot fittings of a CFM56 engine's T/R, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
78-23-14 R1: 78-23-14 R1 LET BLANIK: Amendment 38-3349 as amended by Amendment 39-4894. Applies to Model L-13 gliders, Serial Numbers 170101 through 174730, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent tow release malfunction due to structural cracks at the attach point of the tow release system countershaft bracket, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, inspect the No. 1 bulkhead for cracks at the attach points of the tow release system countershaft brackets in accordance with Let Mandatory Bulletin No. L13/047 dated January 11, 1978, and Note 2 in Bulletin No. L13/047 (Supplement), dated April 1, 1978, or an equivalent procedure approved by the Manager, Aircraft Certification Staff, Europe, Africa and Middle East Office. (b) If cracks are found during inspection in accordance with paragraph (a) of this AD, before further flight: (1) Where cracks do not exceed 6 mm in length, repair and reinforce the No. 1 bulkhead in accordance with paragraph A, "Reinforcement of bulkhead No. 1" of Let Mandatory Bulletin No. L13/047 dated January 11, 1978, and Bulletin L13/047 (Supplement) dated April 1, 1978, or equivalent approved by the Manager, Aircraft Certification Staff, Europe, Africa and Middle East Office; or, (2) Where cracks exceed 6 mm in length, repair and reinforce the No. 1 bulkhead in accordance with the metal repair procedures, Section 3 of FAA Advisory Circular 43.13-1A, or equivalent approved by the Manager, Aircraft Certification Staff, Europe, Africa, and Middle East Office. (c) If no cracks are found during the inspection required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, reinspect, repair, and reinforce the No. 1 bulkhead as follows: (1) If no cracks have developed, in accordance with the method specified in paragraph (b)(1) ofthis AD; or (2) If cracks have developed, in accordance with the applicable method specified in paragraph (b) of this AD. Amendment 38-3349 became effective November 27, 1978. This Amendment 39-4894 becomes effective August 17, 1984.
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.