Results
90-09-08: 90-09-08 IPECO: Amendment 39-6486. Docket No. 89-ANE-28. \n\n\tApplicability: IPECO TSO-C39a crew seats, as follows: \n\n\nSeat Part Number\nSerial no. effectivity\nInstalled in but not limited to\n3A090-0021-01-2\nup to and including \nBoeing 737\n3A090-0022-01-2\n11009\n\n3A090-0021-02-2\n\n\n3A090-0022-02-2\n\n\n\n\n\n3A090-0019-01-1\nup to and including\nBoeing 737\n3A090-0020-01-1\n11115 \n\n\n\n\n3A090-0015-01-1\nup to and including\nBoeing 757, 767\n3A090-0016-01-1\n11143\n\n\n\n\n3A090-0025-01-1\nup to and including\nBoeing 757, 767\n3A090-0026-01-1\n11054\n\n\n\n\n3A090-0053-01-1\nup to and including\nBoeing 747-400\n3A090-0054-01-1\n11105\n\n\n\n\n3A090-0027-01-1\nup to and including\nBoeing 747\n3A090-0028-01-1\n11072\n\n\n\n\n3A102-0003-01-1\nup to and including\nBoeing 747-400\n\n11041\n\n\n\n\n3A090-0055-01-1\nup to and including\nBoeing 747-400\n3A090-0056-01-1\n11062\n\n\n\n\n3A103-0003-01-1\nup to and including\nBoeing 747-400\n\n10607 \n\n\n\n\n3A090-0017-01-1\nup to and including\nBoeing 747\n3A090-0018-01-1\n10100\n\n\n\n\n3A090-0065-01-1\nup to and including\nBoeing 747-400\n3A090-0066-01-1\n11635\n\n\n\n\n3A118-0003-01-1\nup to and including\nDeHavilland\n3A118-0004-01-1\n11580\nDHC-7 and DHC-8\n\n\tCompliance: Required as indicated, unless already accomplished. To prevent failure of the seat back structure, accomplish the following: \n\n\t(a)\tWithin the next 30 days after the effective date of this AD, unless already accomplished within the last 100 days and, thereafter, at intervals not to exceed 130 days from the last inspection, visually inspect the seat assembly as follows: \n\n\t\t(1)\tRemove seat pan cushion and back cushion from the seat assembly. Adjust the lumbar mechanism to the fully up, fully back position. Recline seat back to full recline. \n\n\t\t(2)\tBy looking through the lightening holes in the pan and back structure with a flashlight, examine the base of the back structure in the area where it attaches to the reclining mechanism. This area can be identified by the bracket at the base of the back structure. Return the seat back to its upright position and also examine the base of the back structure from the rear of the seat. \n\n\t\t(3)\tIf any crack or deformation of the seat back structure is found, replace the seat assembly with a serviceable unit before further flight. \n\n\t\t(4)\tWhen the repairs and modifications required by paragraph (b) have been accomplished, the repetitive visual inspections may be terminated. \n\n\t(b)\tWithin the next 15 months after the effective date of this AD, perform the repairs and modifications of the IPECO seat assemblies in accordance with the following service bulletins (SB): \n\n\nIPECO SB No.\nApplicable IPECO\nseat part numbers \nA001-25-29\n3A090-0021-01-2 \n\n3A090-0022-01-2 \n\n3A090-0021-02-2 \n\n3A090-0022-02-2 \n\n\nA001-25-30\n3A090-0019-01-1 \n\n3A090-0020-01-1 \n\n\nA001-25-31\n3A090-0015-01-1 \n\n3A090-0016-01-1 \n\n\nA001-25-32\n3A090-0025-01-1 \n\n3A090-0026-01-1 \n\n\nA001-25-33\n3A090-0053-01-1 \n\n3A090-0054-01-1\n\n\nA001-25-34\n3A090-0027-01-1 \n\n3A090-0028-01-1 \n\n\nA001-25-35\n3A102-0003-01-1 \n\n\nA001-25-36\n3A090-0055-01-1 \n\n3A090-0056-01-1 \n\n\nA001-25-37\n3A103-0003-01-1 \n\n\nA001-25-38\n3A090-0017-01-1 \n\n3A090-0018-01-1 \n\n\nA001-25-39\n3A090-0065-01-1 \n\n3A090-0066-01-1 \n\n\nA001-25-40\n3A118-0003-01-1 \n\n3A118-0004-01-1 \n\n\t(c)\tAircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. \n\n\t(d)\tUpon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. \n\n\tThe repair and modification procedures shall be done in accordance with IPECO SB No. A001-25-29, Issue No. 2, pages 1 and 2 dated April 28, 1989, and pages 3 through 18 inclusive, dated August 25, 1988; IPECO SB No. A001-25-30, Issue No. 2, pages 1 and 2 dated April 28, 1989, and pages 3 through 18 inclusive, dated September 9, 1988; and IPECO SB Nos. A001-25-31 through A001-25-40 inclusive, all Issue No. 2, pages 1 and 2 dated April 28, 1989, and pages 3 through 18 inclusive, dated September 13, 1988. 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 IPECO Inc., 15201 South Prarie Avenue, Lawndale, California 90260. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office ofthe Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591. \n\n\tThis amendment (39-6486, AD 90-09-08) becomes effective on May 29, 1990.
2023-22-18: The FAA is adopting a new airworthiness directive (AD) for all Diamond Aircraft Industries Inc. Model DA 62 airplanes. This AD was prompted by reports of baggage nets installed with defective buckles, which may result in failure of the baggage net to restrain the baggage or cargo, which could lead to injury to the occupants in the case of an emergency landing. This AD requires identifying and replacing the affected part. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-04: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires repetitive inspections of the left and right engine throttle control gearboxes for wear, and corrective action if necessary. The existing AD was prompted by numerous failures of the engine throttle control gearbox, some of which resulted in an in-flight engine shutdown. This AD adds airplanes to the applicability of the existing AD. We are issuing this AD to prevent excessive wear of the gearboxes and subsequent movement or jamming of the engine throttle; movement of the throttle towards the idle position brings it close to the fuel shut-off position, which could result in an in-flight engine shutdown. DATES: Effective April 1, 2005. On July 9, 2004 (69 FR 35239, June 24, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 601R-76-019, Revision `A,' dated February 19, 2004. On March 25, 2004 (69 FR 11293, March 10, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 601R-76-019, dated August 21, 2003. We must receive any comments on this AD by May 16, 2005.
2023-23-02: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440), CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of power control unit (PCU) rod end fractures due to pitting corrosion, and a determination that new or more restrictive airworthiness limitations are necessary. This AD requires, for certain airplanes, revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD also requires accomplishing certain aircraft maintenance manual (AMM) tasks and corrective actions following short-term or long-term storage. The FAA is issuing this AD to address the unsafe condition on these products.
78-20-09: 78-20-09 GULFSTREAM AMERICAN CORPORATION (GAC) (FORMERLY GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-3309. Applies to Model GA-7 serial numbers GA7-001 through GA7-0039. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a hazard to the airplane caused by excessive force required to move the fuel selector valve from one position to another position, accomplish the following: (1) Remove the two original fuel selector valves, Gerdes Part Number A980-5, and install two new improved fuel selector valves, Gerdes Part Number A980-7, utilizing the procedures and precautions contained in GA-7 Maintenance Manual, Section 28-2-1, pages 202 and 204, Fuel Selector Valve Removal, and Fuel Selector Valve Installations. (2) After the Gerdes Part Number A980-7 fuel selector valve installation has been completed in accordance with the above Maintenance Manual procedures, set each selector to ON, OFF, and CROSSFEED positions while observing each selector valve to ensure that the valve operates correctly, no fuel leakage occurs, and a positive detent is noted at each position selected on the valve. (Gulfstream American Service Bulletin No. ME-10 dated August 16, 1978 applies to this same subject.) This amendment becomes effective October 9, 1978.
97-08-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires replacement of certain switches in the cabin attendant's panel at door 4 right and door 2 right with new improved switches. This amendment is prompted by reports indicating that fires have occurred on some airplanes due to the internal failure of some of these switches. The actions specified by this AD are intended to prevent the installation and use of switches that could short circuit when they fail, and consequently cause fire and smoke aboard the airplane.
2005-06-03: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-90-30 airplanes. This AD requires replacing, with improved parts, certain existing fluorescent light lamp holders located in the ceiling panels and life raft ceiling support housings, and behind the overhead stowage compartments in the main cabin. This AD is prompted by reports of failure of fluorescent light lamp holders in the main cabin. We are issuing this AD to prevent chafing of the lamp holder power wire against the mounting bracket, and moisture intrusion into the lamp holders, which could result in failure of the lamp holders and consequent smoke and fire in the airplane cabin.
2023-25-02: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-350P, PA-46-500TP, and PA-46-600TP airplanes. This AD was prompted by a report that a bearing fell out of a control column mount during routine handling prior to installation in an affected airplane and the discovery that a quality escape condition could exist on other airplanes. This AD requires inspecting the left and right control column mounts to determine if a retaining ring is installed. If a retaining ring is not installed, this AD requires inspecting the bearing in the mount block for the presence of retaining compound, and depending on the inspection results, installing a retaining ring and applying retaining compound to the bearing, as applicable. The FAA is issuing this AD to address the unsafe condition on these products.
95-19-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP airplanes, that requires modification of certain doors. This amendment is prompted by a report that an operator was unable to unlock a Type I passenger door due to migration of a shootbolt bush. The actions specified by this AD are intended to prevent such migration, which could jam the Type I passenger door, and subsequently could delay or impede the evacuation of passengers during an emergency.
2023-23-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter series airplanes. This AD was prompted by a widespread fatigue damage (WFD) evaluation on Airbus SAS Model A330-200 Freighter series airplanes, which found that the circumferential joint at Frame 58 (near the rear fuselage) is susceptible to WFD. This AD requires a modification to reinforce the circumferential joints at Frame 58 and, if necessary, corrective action, 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.
2005-05-18: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive detailed, low frequency eddy current, and high frequency eddy current inspections of the webs of the aft pressure bulkhead at body station 1016 for cracks, and corrective action if necessary. This AD is prompted by a report of cracks found, during fatigue testing, at several of the fastener rows in the web lap splices at the dome apex of the aft pressure bulkhead. We are issuing this AD to detect and correct fatigue cracks in the webs of the aft pressure bulkhead, which could result in rapid decompression of the airplane.
2023-23-06: The FAA is superseding Airworthiness Directive (AD) 2023-04- 13, which applied to certain Dassault Aviation Model FALCON 2000EX airplanes. AD 2023-04-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2023-04- 13 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; 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.
2000-24-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection to detect chafing or damage of the electrical wires leading to the terminal strips in the center accessory compartment (CAC) area; and corrective actions, if necessary. This amendment also requires revising the wire connection stack up of certain cable terminals at the electrical power center bays in the CAC, and replacing certain terminal strips with new strips and removing applicable nameplates at electrical power center bays. This action is necessary to prevent arcing and sparking damage to the power feeder cables, terminal strips, and adjacent structure, and consequent smoke and fire in the CAC. This action is intended to address the identified unsafe condition.
92-24-06: 92-24-06 FOKKER: Amendment 39-8411. Docket No. 92-NM-74-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11355, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the C-latch bushings from being rendered temporarily inoperable, which could prevent the opening of the forward and rear service/emergency doors during an emergency evacuation, accomplish the following: (a) Within 4 months after the effective date of this AD, remove the existing C-latch mechanisms and bushings of the forward and rear service/emergency doors, and install new C-latch mechanisms and bushings, Modification Kit SBF100-52-039A or SBF100-52-039B, in accordance with Fokker Service Bulletin SBF100-52-039, dated September 17, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) The removal and installation shall be done in accordance with Fokker Service Bulletin SBF100-52-039, dated September 17, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 14, 1992.
2005-05-16: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-622R and A300 F4-622R airplanes. This AD requires doing a one-time inspection to determine if lower guide fittings for the forward doors are installed in the correct positions, and corrective action if necessary. This AD is prompted by reports that lower guide fittings for the forward doors were found installed in the wrong positions at frames 14 and 16A. We are issuing this AD to prevent difficulty opening the forward doors, which could impede an emergency evacuation and result in injury to passengers or crewmembers.
78-20-06: 78-20-06 AIRCRAFT PARTS AND DEVELOPMENT CORPORATION (CALLAIR): Amendment 39-3299 as amended by Amendment 39-3356. Applies to Models A-9, A-9A, and A-9B Airplanes which have the wing struts carry-through tube running through the hopper, certificated in all categories (Airworthiness Docket No. 78-ASW-52). Compliance required within the next 25 hours' time in service after the effective date of this AD except that aircraft added by Amendment 39-3356 must comply within the next 25 hours' time in service from the effective date of such amendment. To prevent failure of the main carry-through tube, P/N 11013, due to corrosion from exposure to corrosive chemicals in airplanes equipped with the large hopper, accomplish the following: (a) Deleted. (b) Remove the hopper top and inspect for a fiberglass wrapped carry-through tube. The main carry- through tube if located in the hopper is located 25 inches aft of the hopper forward bulkhead and six inches below the hopper surface. Visually inspect the fiberglass wrapping for cracks. (c) If the fiberglass wrapping is cracked, remove all the fiberglass wrapping and visually inspect the main carry-through tube for corrosion. (d) Remove all corrosion found on the main carry-through tube. If the corrosion removal exceeds a depth of 0.010 inch in one location or 2 percent of the tube cross-sectional area, the main carry-through tube, P/N 11013, must be replaced. The nominal cross-sectional area is 0.42 square inch. Finish the tube with two coats of zinc chromate primer after corrosion removal. Rewrap the exposed tube inside the hopper with a fiberglass laminate. The fiberglass laminate must include a minimum of three layers of MIL-C-9084 glass cloth of the 181 type with a Volan A or Garan 136 finish. Use a Reichhold 33-402 chemical resistant resin. (e) Aircraft may be flown in accordance with FAR 21.197 to a base where this AD can be accomplished. (f) Equivalent methods of complying withthis AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. (Service information concerning this tubing inspection and replacement may be obtained upon request to Service Manager, Aircraft Parts & Development Corp., L.A.F.B. Building 162, Laredo, Texas 78040.) Amendment 39-3299 became effective October 4, 1978. This amendment 39-3356 becomes effective December 8, 1978.
2023-22-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK 117 D-3 helicopters. This AD was prompted by recalculations of the inspection intervals for certain parts. This AD requires revising the airworthiness limitations section (ALS) of the existing helicopter maintenance manual or instructions for continued airworthiness for your helicopter and the existing approved maintenance or inspection program for your helicopter, as applicable, to reduce the inspection interval of certain parts, 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.
91-07-51: 91-07-51 BOEING: Amendment 39-7004. Docket No. 91-NM-84-AD. \n\n\tApplicability: Model 757 series airplanes, line number 154 through 350, except line numbers 332 and 340, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect improperly installed nuts in the upper and lower attachment of the rudder yaw damper pogo assembly, accomplish the following: \n\n\tA.\tWithin the next 60 flight cycles or 20 days after the effective date of this AD, whichever occurs sooner, inspect the upper and lower attachment of the rudder yaw damper pogo assembly for improper installation of the nuts in accordance with Boeing Telegram M-7272-91- 1886, dated March 22, 1991. If less than one thread from the bolt protrudes through the nut, or if the nut is or appears to be cross threaded, replace both the nut and bolt prior to further flight. \n\n\tB.\tWithin 10 days after completion of the inspection required by paragraph A. of this AD, submit a report of findings of discrepancies to the Manager, Seattle Manufacturing Inspection District Office, ANM-108S, FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056; fax: (206) 227-1181. \n\n\tC.\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tThe inspection shall be done in accordance with Boeing Telegram M-7272-91-1886, dated March 22, 1991. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tThis amendment (39-7004, AD 91-07-51) becomes effective on July 1, 1991, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T91-07-51, issued March 27, 1991, which contained this amendment.
2023-21-10: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by reports of loose fasteners and cracks in the horizontal stabilizer (HS) left- and right- hand leading edge lateral ribs, the box in between, the center box upper panel, and HS forward back-up fitting. This AD requires an inspection of the HS affected areas for discrepancies and applicable corrective action, 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.
95-23-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A airplanes and Model Avro 146-RJ70A, -RJ85A, and RJ-100A airplanes. This action requires inspections to detect cracking and evidence of exhaust leaks in the forward face of the central panel of the forward firewall of the auxiliary power unit (APU) bay, and replacement of the central panel with a new panel, if necessary. This amendment is prompted by a report indicating that cracking due to leakage of hot exhaust gases was found in the forward face of the forward firewall of the APU bay. The actions specified in this AD are intended to prevent such gas leakage and subsequent cracking, which could damage the wiring to the APU fire bottle; this condition could result in failure of the APU fire bottle to discharge in the event of an APU fire.
2005-05-11: The FAA is adopting a new airworthiness directive (AD) for certain Dornier Model 328-300 series airplanes. This AD requires performing repetitive inspections for discrepancies of the heat pack rotor assembly and rotor drive clips of the brake unit of the main landing gear (MLG), and replacing the assembly if any discrepancy is found. This AD is prompted by reports of cracking and breakage of the heat pack rotor assemblies. We are issuing this AD to find and fix discrepancies of the heat pack rotor assembly of the brake unit of the MLG and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing.
2023-23-08: The FAA is superseding Airworthiness Directive (AD) 2019-07- 05, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-07-05 required repetitive inspections for cracking of the 10VU rack fitting lugs and repair of any cracking. This AD continues to require the requirements of AD 2019-07-05, with reduced compliance times and removes airplanes having a certain modification from the applicability. This AD was prompted by a determination that certain repetitive inspection intervals need to be revised. The FAA is issuing this AD to address the unsafe condition on these products.
95-18-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11, CL-600-2A12, CL-600-2B16, and CL-600-2B19 series airplanes, that currently requires an inspection to detect cracking in the rudder control quadrant; replacement of any cracked quadrant with a new assembly; and retorquing of the castellated nut, as necessary. This amendment requires a follow-on inspection of certain rudder control quadrants to detect cracks that start at the inside root radius of the spigot; modification of any cracked quadrant; and eventual modification of certain quadrants. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by the development of a modification, which, when installed, will positively address the identified unsafe condition. The actions specified by this AD are intended to prevent loss of rudder control due to stress corrosion of the rudder control quadrant.
2000-24-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection of the electrical wires routed above the door actuation cables for minimum .50-inch clearance with the door in the open and closed position, damage due to chafing or electrical arcing, or damaged door actuation cables; and corrective actions, if necessary. This action is necessary to prevent damaged electrical wires or damaged door actuation cables due to chafing by the cables during operation of the forward passenger door, which could result in electrical arcing and consequent smoke in the area above the forward passenger door. This action is intended to address the identified unsafe condition.
2005-03-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires initial and repetitive inspections of certain frame stiffeners to detect cracking. If any cracking is found, this AD requires replacement of the stiffener with a new, reinforced stiffener. Replacement of the stiffener constitutes terminating action for certain inspections. This AD also requires a one-time inspection of any new, reinforced stiffener; and repair or replacement of the new, reinforced stiffener if any cracking is found during the one-time inspection. This AD also provides for an optional terminating action for certain requirements of this AD. The actions specified by this AD are intended to prevent fatigue failure of certain frame stiffener fittings, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.