Results
2023-14-08: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVII-G600 airplanes. This AD was prompted by an addition of a life limit in the Airworthiness Limitations Section (ALS) for GVII-G600 flap yokes. The life limit for the GVII-G600 flap yokes was informed by a GVII-G500 flap yoke failure that occurred during flight testing and, ultimately, resulted in additional test and analysis to establish more accurate life limits reflective of each model's design features and stress levels. The FAA is issuing this AD to require revising the existing ALS to prevent the GVII-G600 inboard flap yoke from remaining in service beyond its life limit. The FAA is issuing this AD to address the unsafe condition on these products.
2023-13-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by reports of inoperative manual and alternate horizontal stabilizer trim switches. This AD requires repetitive inspections for immersion of each limit switch and position transmitter module (LSPTM) and of the LSPTM electrical wiring, repetitive inspections for blockage of the drain holes and cleaning of each drain hole, repetitive inspections for loose or cracked leveling compound, and applicable on-condition actions. For certain airplanes, this AD also requires installing two new drain holes, performing repetitive inspections for blockage of the drain holes and cleaning each drain hole, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-20: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by reports of oxygen leaks caused by cracked, brittle, or broken oxygen hoses that were found during scheduled maintenance tests of the airplane oxygen system. This AD requires replacing oxygen system hoses having any part number in the O2C20T1 and O2C20T14 series. This AD also prohibits installation of affected oxygen hoses. The FAA is issuing this AD to address the unsafe condition on these products.
2002-11-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that currently requires repetitive inspections to detect cracking of the cove skin on the outboard leading edge slats, and corrective actions, if necessary. The existing AD also provides for an optional modification that significantly increases the repetitive inspection interval. This amendment expands the applicability of the existing AD by mandating the currently required inspections, and corrective actions, if necessary, for additional airplanes. Also, for airplanes on which the optional modification has been accomplished, this action requires a new one-time inspection for undersized seal inserts in the spanwise bulb seals on certain slats, and replacement of seal assemblies with new assemblies, if necessary. The actions specified by this AD are intended to detect and correct cracking or missing pieces of the cove skin, or undersized seal inserts installed in the spanwise bulb seals, on the outboard leading edge slats on the wings, which could result in skin separation or structural damage to the leading edge slats and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 10, 2000 (65 FR 57282, September 22, 2000).\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 777-57A0034, Revision 2, dated November 19, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 8, 1999 (64 FR 8230, February 19, 1999).
2023-12-19: The FAA is superseding Airworthiness Directive (AD) 2013-07- 03, which applied to all Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. AD 2013-07-03 required repetitive inspections for degradation of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main and central landing gear; an inspection of the affected bogie pivot pins for corrosion and base metal cracks; and repairing or replacing bogie pivot pins and pivot pin bushes, if necessary. This AD was prompted by development of a modification that address the unsafe condition and a determination that a parts installation prohibition is necessary. This AD continues to require certain actions in AD 2013-07-03, add an optional modification that would terminate the repetitive inspections, and add a parts installation prohibition, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-17-05: The FAA is adopting a new airworthiness directive (AD) for certain GE CF6-80C2 and CF6-80E1 turbofan engines. This AD requires you to inspect the high pressure compressor rotor (HPCR) stage 11-14 spool shaft for circumferential repair cuts, and to repair or replace the spool shaft if you find certain circumferential cuts. This AD results from an updated stress analysis. We are issuing this AD to prevent failure of the HPCR stage 11-14 spool shaft due to low-cycle fatigue that could result in an uncontained engine failure.
2002-11-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-502, AT-502A, AT-502B, and AT-503A airplanes. This AD lowers the safe life for the wing lower spar cap established in AD 2001-10-04 R1 and further reduces the safe life for airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets. This AD also requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification to detect and correct any crack in a bolthole before it extends to the modified center section of the wing and report the results of this inspection to the Federal Aviation Administration (FAA). This AD is the result of reports of several cracks originating in the outboard 3/8-inch hole of the main spar lower cap on Air Tractor Models AT-502, AT-502A, AT-502B, and AT-503A airplanes at times lower than the established safe life. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight. \n\n\tThe Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulation as of June 8, 2001 (66 FR 27014, May 16, 2001). \n\n\tThe FAA must receive any comments on this rule on or before July 5, 2002.
94-03-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires inspections of the brake rod inner cylinder bolts on the main landing gear (MLG) wheels and brakes; inspections of certain MLG bushings; installation of retainer plates at each MLG brake disconnect; inspection and modification of the brake rod pin assembly at each MLG wheel; repair or replacement of discrepant parts; and revision of the Airplane Flight Manual (AFM), as necessary. This amendment is prompted by numerous reports of brake failure during landing and during a low energy rejected takeoff. The actions specified in this AD are intended to prevent failure of two or more MLG brakes, which could adversely affect the stopping performance of the airplane.
2023-13-04: The FAA is superseding Airworthiness Directive (AD) 2021-16- 18, which applied to all Airbus SAS Model A330-200 Freighter, A330-200, A330-300, A330-800, A330-900, A340-200, A340-300, A340-500, and A340- 600 series airplanes. AD 2021-16-18 required repetitive inspections of certain fuel pumps for cavitation erosion, replacement if necessary, revision of the operator's existing minimum equipment list (MEL), and accomplishment of certain maintenance actions related to defueling and ground fuel transfer operations. This AD was prompted by reports of a fuel pump showing cavitation erosion that exposed the fuel pump power supply wires, and a determination that affected fuel pumps must be replaced with new, more erosion resistant pumps. This AD continues to require the actions in AD 2021-16-18, and also requires replacement of affected parts, which would terminate the repetitive inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of certain affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
94-04-01: This amendment supersedes two existing airworthiness directives (AD's) that currently require repetitively inspecting the wing attachment fittings and the wing front fittings for cracks on certain de Havilland DHC-6 series airplanes, and replacing any cracked part. The Federal Aviation Administration's policy on aging commuter class aircraft is to eliminate or, in certain instances, reduce the number of repetitions of certain short-interval inspections when improved parts or modifications are available. This action requires incorporating a modification that would eliminate the need for the repetitive inspections currently required by the two existing AD's. The actions specified by this AD are intended to prevent loss of control of the airplane caused by cracked wing attachment fittings.
93-05-10: 93-05-10 PIPER AIRCRAFT CORPORATION: Amendment 39-8514; Docket No. 92- CE-37-AD. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers PA-32R-300 32R-7680001 through 32R-7880068 PA-32RT-300 32R-7885001 through 32R-7985105 PA-32RT-300T 32R-7887001 through 32R-7987126 PA-32R-301 32R-8013001 through 32R-8613005 and 3213001 through 3213037 PA-32R-301T 32R-8029001 through 32R-8629006 and 3229001 through 3229003 Compliance: Required within the next 100 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information. To prevent the inability to retract or extend the nose landing gear, which could result in substantial damage to or loss of control of the airplane, accomplish the following: (a) Inspect the engine mount as specified in and in accordance with the INSTRUCTIONS: PART I section of Piper Service Bulletin (SB) No. 955, dated March 3, 1992. Prior to further flight, repair any cracks in accordance with Piper SB No. 955. (b) Modify the airframe structure and strengthen the landing gear and engine mount attach areas in accordance with the instructions contained in either Engine Mount Drag Link Installation Kit, Piper Part No. 766-252 (for turbocharged models); or Engine Mount Drag Link Installation Kit, Piper Part No. 766-253 (for normally aspirated models). These kits are referenced in Piper SB No. 955, dated March 3, 1992. (c) Inspect the nose gear actuator attachment bracket for correct rivet dimensions in accordance with the INSTRUCTIONS: PART III section of Piper SB No. 955, dated March 3, 1992. If any rivets are found that are not of the dimensions referenced in Piper SB No. 955, prior to further flight, reinforce the nose gear actuator attachment bracket in accordance with the referenced service information. (d) If the parts that are required to accomplish the modification specified in paragraph (b) of this AD have been ordered, but are not available from the manufacturer, reinspect the engine mount as required by paragraph (a) of this AD at intervals not to exceed 100 hours TIS until parts become available. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (g) The inspections required by this AD shall be done in accordance with Piper Service Bulletin No. 955, dated March 3, 1992. The modification required by this AD shall be done in accordance with the instructions to Engine Mount Drag Link Installation Kit, Piper Part No. 766-252 (for turbocharged models); or Engine Mount Drag Link Installation Kit, Piper Part No. 766-253 (for normally aspirated models), which are referenced in Piper Service Bulletin No. 955. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on April 30, 1993.
2002-11-05: This amendment supersedes Airworthiness Directive (AD) 2001-10-04 R1, which lowered the safe life for the wing lower spar cap on certain Air Tractor, Inc. (Air Tractor) AT-400, AT-500, and AT-800 series airplanes. AD 2001-10-04 R1 resulted from numerous reports of cracks in the 3/8-inch bolthole of the wing lower spar cap on the affected airplanes. This AD retains the safe life for the wing lower spar cap and requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification in order to detect and correct any crack in a bolthole before it extends to the modified center section of the wing. This AD further reduces the safe life for certain Models AT-401, AT-401B, AT-402, AT-402A, AT-402B, and AT-501 airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets and removes the Models AT-502, AT-502A, AT-502B, and AT-503A airplanes from the applicability. We are issuing another AD action to cover these airplanes.The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight. \n\n\tThe Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulation as of June 8, 2001 (66 FR 27014, May 16, 2001).
2023-12-25: The FAA is adopting a new airworthiness directive (AD) for certain Survitec Group Limited (RFD Beaufort Ltd.) Type 102 Mk 3, 102 Mk 4, and 105 Mk 1 life jackets. This AD was prompted by a report that some life jackets were found packed in the wrong valise (container). This AD requires an inspection for a discrepancy (mismatch of the valise/container description and life jacket type) of life jackets and, if necessary, replacement of the life jacket. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
94-03-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada PW100 series turboprop engines. This action requires a life limit reduction for affected high pressure turbine (HPT) disks, and establishes a drawdown schedule for disks currently near, at, or greater than the new reduced service life. This amendment is prompted by reports of two HPT disk failures, one of which was uncontained. The actions specified in this AD are intended to prevent an uncontained HPT disk failure and damage to the aircraft.
2002-11-01: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland (Eurocopter) Model EC135 helicopters with Turbomeca Arrius 2B1 engines installed. This action requires modifying the engine electrical control unit (FADEC) software and the collective linear transducer (LVDT). This amendment is prompted by a parameter discrepancy within the engine fuel main metering unit that is transmitted to the FADEC. This condition, if not corrected, could result in deactivation of the engine main fuel-metering valve, loss of automatic control of the affected engine, and subsequent loss of control of the helicopter.
2002-10-15: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines. This amendment requires reapplication of dry film lubricant to low pressure compressor (LPC) fan blade roots. This amendment is prompted by an aborted take-off resulting from LPC fan blade loss. Since this event, four additional cracked LPC fan blade roots have been reported. The actions specified by this AD are intended to prevent LPC fan blade loss, which could result in an uncontained engine failure and possible aircraft damage.
2002-10-07: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines. This amendment requires fluorescent penetrant inspection of the high pressure turbine (HPT) second stage airseal knife edges for cracks, each time the airseal is accessible. This amendment is prompted by reports of cracks found in the knife edges of HPT second stage airseals during HPT disassembly. The actions specified by this AD are intended to prevent failure of HPT second stage airseals due to cracks in the knife edges, which if not detected could result in uncontained engine failure and damage to the airplane.
2023-11-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by multiple reports of erratic electrical system status on the push button annunciators (PBAs) and the engine instrument and crew alerting system (EICAS) while on-ground and during flight. This AD requires a records check and replacement of affected left-hand (LH) direct current power center (DCPC) units. The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-16: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000 engines. This AD was prompted by reports of excessive wear on the inner seal fins of certain high-pressure turbine (HPT) triple seals. This AD requires an inspection of the HPT triple seal for excessive wear and, depending on the results of the inspection, replacement of the HPT triple seal and the intermediate-pressure turbine (IPT) disk, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-10-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires repetitive inspections for cracking and corrosion of the pressure bulkhead at body station (BS) 1016, and follow-on actions. This amendment expands the applicability of the existing AD, and requires new repetitive inspections to detect cracking and corrosion of the aft pressure bulkhead at BS 1016, and follow-on actions. This action is necessary to detect and correct corrosion or cracking of the aft pressure bulkhead at BS 1016, which could result in loss of the aft pressure bulkhead web and stiffeners and consequent rapid decompression of the fuselage. This action is intended to address the identified unsafe condition.
93-23-13: 93-23-13 PIPER AIRCRAFT CORPORATION: Amendment 39-8749. Docket No. 93-CE- 32-AD. Supersedes AD 93-02-13, Amendment 39-8496 which superseded AD 92-26-02, Amendment 39-8429 and AD 80-20-04, Amendment 39-3925. Applicability: Model PA31, PA31-300, and PA31-325 airplanes (serial numbers 31-2 through 31-8012089), and Model PA31-350 airplanes (serial numbers 31-5001 through 31-8052199), certificated in any category. Compliance: Required initially within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished (compliance with AD 80-20-04, Amendment 39-3925, AD 92-26-02, Amendment 39-8429, or AD 93-02-13, Amendment 39- 8496), and thereafter as indicated. To prevent improper sealing of the baffle seals to the engine cowling, which could result in high engine operating temperatures, accomplish the following: (a) Visually inspect the engine baffle seals for proper positioning by using a light and looking in air inlets andaccess doors to ensure that forward seals and lower aft seals are all facing forward and not blown back. (b) If baffle seals are improperly positioned (blown back), prior to further flight, accomplish one of the following: (1) Install thicker baffle seals in accordance the instructions to Piper Kit 764 093, dated November 10, 1980; or NOTE 1: Piper Kit 764 093 includes the entire baffle assembly consisting of both baffles and baffle seals. Replacing the baffle seals included in this kit is the only requirement of paragraph (b)(1) or (c)(2) of this AD. (2) Install baffles of one of the following materials in accordance with Figure 1 of this AD: (i) Brown Aircraft Supply Engine Baffle Material, part number (P/N) BA71646-1 and BA71646-2, temperature range -40 to 300 degrees Fahrenheit. (ii) Brown Aircraft Supply, Fiber Reinforced High Temperature Silicone Engine Baffle Material (red), P/N T-95182, temperature range -65 to 550 degrees Fahrenheit; and(iii) Brown Aircraft Supply, Engine Baffle Material, P/N T-8071, temperature range -40 to 300 degrees Fahrenheit. FIGURE 1 BROWN AIRCRAFT SUPPLY BAFFLE SEAL INSTALLATION PROCEDURES 1. Inspect the existing baffle seals through the front of the cowl to ensure existing seals are of sufficient length to provide at least 1-inch of contact with upper and lower cowls when properly positioned. Mark areas that need lengthening, and note the minimum length needed to meet requirements. 2. Remove the cowls in accordance with the applicable maintenance manual. Remove rivets, wire, and screws, as applicable, that secure baffle seals (fabric) to the engine baffles (metal). Retain any metal strips that are used to secure seals to the engine baffles. 3. Remove existing baffle seals and lay against Brown Aircraft Supply baffle seal material. 4. Cut new seals around the layout, ensuring that seals are lengthened as noted in procedure 1. 5. Reattach new seals to the engine baffles with the original screws, rivets, and wires, as applicable, or new hardware of the same part number. NOTE: The front upper cowl baffle seal is most critical, especially at the inboard and outboard corners. If the old material can be removed intact, and the curve can be transferred to the new flat material, then it may not be necessary to slit the material where it curves from vertical to horizontal contact with the cowl. If the curve requires a slit in the material at the corner, then it is recommended that the slit be tied with ty-raps or safety wire to ensure contact with the cowl around the radius. (c) If baffle seals are properly positioned (not blown back), within the next 50 hours TIS, accomplish one of the following: (1) Reinspect the engine baffle seals as specified in paragraph (a) of this AD, and continue to reinspect thereafter at intervals not to exceed 50 hours TIS; or (2) Install thicker baffle seals as specified in either paragraph (b)(1) or (b)(2) of this AD. This installation terminates the inspection requirements of this AD. (d) The inspections required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by FAR 43.7, and must be entered into the aircraft records showing compliance with this AD in accordance with FAR 43.11. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (g) The installation (using Piper Aircraft Corporation parts) required by this AD shall be done in accordance with Piper Kit 764 093, dated November 11, 1980. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment (39-8749) supersedes AD 93-02-13, Amendment 39-8496 which superseded AD 92-26-02, Amendment 39-8429 and AD 80-20-04, Amendment 39-3925. (i) This amendment becomes effective on January 21, 1994.
94-01-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Allied Signal Aerospace Company, Air Transport Avionics (Allied Signal) Traffic Alert and Collision Avoidance System (TCAS) II processors that are installed on aircraft. This action requires replacing the existing TCAS II processor with a new processor that incorporates updated computer logic. The development of candidate enhancements to TCAS II logic that improves its utility and increases its overall operational acceptance prompted the proposed action. The actions specified by this AD are intended to prevent collisions or near misses caused by incompatibility between the TCAS II processors and the current air traffic control system.
93-06-02: 93-06-02 PIPER AIRCRAFT CORPORATION: Amendment 39-8527. Docket No. 92- CE-48-AD. Applicability: Models PA-23-150, PA-23-160, PA-23-235, and PA-23-250 airplanes (all serial numbers) that have Met-Co-Aire 48-gallon fuel tip tanks installed in accordance with Supplemental Type Certificate SA1480WE, certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. NOTE 1: The compliance time referenced in this AD takes precedence over that referenced in Met-Co-Aire (MCA) Service Bulletin No. 23-001, dated July 1992. To prevent fuel leakage and possible fire, which could result in passenger injury, accomplish the following: (a) Replace any existing Parker "Push-Lok" flexible fuel hose, MCA part number (P/N) 11059-4 or Parker-Hannifin P/N 801-6/250PSI, with a Stratoflex hose, MCA P/N 11059-10 or Parker-Hannifin P/N 130001-6S-0154, in accordance with the instructionsin Met-Co-Aire Service Bulletin No. 23-001, dated July 1992. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Los Angeles Aircraft Certification Office, FAA, 3229 E. Spring Street, Long Beach, California 90806-2425. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles Aircraft Certification Office. (d) The replacement required by this AD shall be done in accordance with Met-Co-Aire Service Bulletin No. 23-001, datedJuly 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Met-Co-Aire, P.O. Box 2216, Fullerton, California 92633. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on May 12, 1993.
2002-10-08: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1 series turbofan engines installed on Airbus Industrie A330 series airplanes. This action requires initial and repetitive thrust reverser inspections and checks, and allows extended threshold and repetitive inspection intervals for certain inspections if an optional double p-seal configuration is installed. This amendment is prompted by reports of service-induced hardware deterioration that reduces the overall thrust reverser system protection against inadvertent deployment, which can result in loss of control of the airplane. The actions specified in this AD are intended to prevent inadvertent in-flight thrust reverser deployment, which can result in loss of control of the airplane.
92-18-08: 92-18-08 BENDIX/KING: Amendment 39-8352. Docket No. 92-CE-07-AD. Applicability: KAP 150/KFC 150 Flight Control Systems installed on Piper Models PA-46-310P and PA-46-350P airplanes, certificated in any category. Compliance: Required within the next 90 calendar days after the effective date of this AD, unless already accomplished. To prevent moisture from entering the electronic circuit board through the pitch servo, which could possibly lead to undesired movement of the elevator, accomplish the following: (a) Install a pitch servo cover kit, part number 050-03007-0000, in accordance with the instructions in Bendix/King Installation Bulletin No. 312, dated March 19, 1990. NOTE 1: Installation of the yaw servo cover kit, part number 050-03006-0000, which is referenced in Bendix/King Installation Bulletin No. 312, is not required by this AD action. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (d) The installation required by this AD shall be done in accordance with Bendix/King Installation Bulletin No. 312, dated March 19, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Bendix/King, Product Support Department, 400 N. Rogers Road, Olathe, Kansas 66062-0212. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (e) This amendment becomes effective on October 2, 1992.