Results
2017-08-08: We are adopting a new airworthiness directive (AD) for certain CFE Company (CFE) turbofan engines. This AD was prompted by a quality escape for high-pressure compressor (HPC) impellers made from forgings with nonconforming material grain size. This AD requires removal of the HPC impeller. We are issuing this AD to correct the unsafe condition on these products.
2005-20-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, and -200C series airplanes. This AD requires a one-time detailed inspection for cracking of the lugs of the inboard attach fittings of the wing leading edge slat tracks at slat numbers 2 and 5; prior or concurrent actions for certain airplanes; repetitive high-frequency eddy current (HFEC) inspections for cracking of the lug surfaces of those inboard attach fittings if necessary; and replacement of the attach fittings with new, improved fittings. This AD results from reports of damage to the lugs of certain inboard attach fittings of the leading edge slat tracks. We are issuing this AD to prevent a lifted slat, which, if the airplane performs any non-normal maneuver during takeoff or landing at very high angles of attack, could lead to the loss of the slat and reduced control of the airplane.
98-08-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, -200, and -300 series airplanes. This action requires repetitive detailed visual and/or borescope inspections to detect discrepancies of certain areas of the wing strut. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by reports that fatigue cracking was found in the vertical chords, midspar webs, and canted closure webs. The actions specified in this AD are intended to detect and correct fatigue cracking and stress corrosion of the wing strut, which could result in failure of the strut-to-wing interface, and consequent separation of the engine and strut from the airplane.
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.
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.
98-07-19: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369F and 369FF helicopters, that requires removing the tail rotor control rod assembly (rod assembly) and replacing it with an airworthy rod assembly. This amendment is prompted by a failure of a rod assembly during a proof-load test conducted by the manufacturer. The actions specified by this AD are intended to prevent buckling of the rod assembly when subjected to ultimate jam loads, loss of tail rotor control, and subsequent loss of control of the helicopter.
79-23-02: 79-23-02 BOEING: Amendment 39-3605. Applies to all Model 727 and 737 series airplanes with the "carry-all" interior. Compliance required as indicated. Accomplish the following: \n\n\tWithin the next 1,200 hours time-in-service or six (6) months after the effective date of this AD, whichever comes first, unless already accomplished, replace the straight orifice fittings on the Boeing part number 10-60513-18, -19, and -20 latch valves and manifold assemblies of the PSU with the redesigned barbed orifice fitting and O-ring in accordance with Boeing Service Bulletin 727-35-A18 dated July 6, 1979, or Boeing Service Bulletin 737-35-A1014 dated July 6, 1979, as applicable, and Puritan-Bennett Service Letter 210780-35-1 dated May 25, 1979, or later FAA-approved revisions. These passenger oxygen service unit manifolds are to be renumbered and functionally tested in accordance with the applicable service bulletin after the new barbed orifice fittings and O-rings have been installed. Thecompliance time prescribed above may be extended to 2,400 hours time-in-service or one (1) year after the effective date of this AD, whichever comes first, by limiting the operational altitude of the airplane to 25,000 feet. \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). All 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. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective November 15, 1979.
2005-20-11: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) Models 250-C28, - C28B, and -C28C turboshaft engines. This AD requires a onetime visual inspection of the seal joint in each passage between airfoils at the hub and shroud of third-stage turbine wheels, part number (P/N) 6899383. This AD results from reports of three failed third-stage turbine wheels and from the manufacturer's analysis of those failures. We are issuing this AD to prevent loss of power and uncommanded engine shutdown due to failure of the third-stage turbine wheel.
2017-10-23: We are adopting a new airworthiness directive (AD) for certain Airbus Model A321 series airplanes. This AD was prompted by a determination that cracks could develop on holes at certain fuselage frame locations. This AD requires repetitive inspections for cracking on holes at certain fuselage frame locations, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-10-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by a report indicating that a portion of the sealant above the engine pylon between the wing skin and the vapor barrier might have been omitted. This AD requires an inspection for missing sealant in the seam on the outside and inside of the engine struts, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2003-17-07 R1: The FAA is revising an existing airworthiness directive (AD) that applies to various transport category airplanes manufactured by McDonnell Douglas. We issued that AD to require a one-time test of the fire extinguishers for the engine and auxiliary power unit (APU), as applicable, to determine the capability of the Firex electrical circuits to fire discharge cartridges, and troubleshooting actions if necessary. This new AD removes certain transport category airplanes from the applicability of the existing AD. This AD results from reports indicating that fire extinguishers for the engine and auxiliary power unit had failed to discharge when commanded. We are issuing this AD to prevent failure of the fire extinguishers to fire discharge cartridges, which could result in the inability to put out a fire in an engine or in the APU. \n\nDATES: The effective date of this AD is September 24, 2003. \n\n\tOn September 24, 2003 (68 FR 50058, August 20, 2003), the Director of the Federal Register approved the incorporation by reference of certain service bulletins listed in the AD.