Results
90-25-10: 90-25-10 BOEING: Amendment 39-6822. Docket No. 90-NM-145-AD. \n\n\tApplicability: Model 747 series airplanes, line numbers 001 through 635, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent loss of redundancy in the elevator control, accomplish the following: \n\n\tA.\tFor airplanes identified as Group 1 in Boeing Alert Service Bulletin 747-27A2253, Revision 4, dated January 25, 1990, accomplish the following inspections, in accordance with the service bulletin: \n\n\t\t1.\tPrior to the accumulation of 6 years time-in-service, or within the next 6 months after the effective date of this AD, whichever occurs later, visually inspect the inboard elevator power control package (PCP) input rods, inboard elevator control rods, and elevator aft quadrant for corrosion, cracking, and deformation; and repeat thereafter at intervals not to exceed 15 months. \n\n\t\t2.\tWithin 15 months after the visual inspection required by paragraph A.1. of this AD, internally borescope inspect the inboard elevator PCP input rods, inboard elevator control rods, and elevator aft quadrant tube for corrosion, cracking, and deformation; and repeat thereafter at intervals not to exceed 30 months. \n\n\tB.\tFor airplanes identified as Group 2 in Boeing Alert Service Bulletin 747-27A2253, Revision 4, dated January 25, 1990, accomplish the following inspections in accordance with the service bulletin: \n\n\t\t1.\tPrior to the accumulation of 6 total years time-in-service, or within the next 6 months after the effective date of this AD, whichever occurs later, visually inspect the inboard elevator control rods and elevator aft quadrant for corrosion, cracking, and deformation; and repeat thereafter at intervals not to exceed 15 months. \n\n\t\t2.\tWithin 15 months after the visual inspection required by paragraph B.1. of this AD, internally borescope inspect the inboard elevator control rods and elevator aft quadrant tube for corrosion, cracking, and deformation; and repeat thereafter at intervals not to exceed 30 months. \n\n\tC.\tFor airplanes identified as Group 3 in Boeing Alert Service Bulletin 747-27A2253, Revision 4, dated January 25, 1990, accomplish the following inspections in accordance with the service bulletin: \n\n\t\t1.\tPrior to the accumulation of 6 total years time-in-service, or within the next 6 months after the effective date of this AD, whichever occurs later, visually inspect the elevator aft quadrant for corrosion, cracking, and deformation; and repeat thereafter at intervals not to exceed 15 months. \n\n\t\t2.\tWithin 15 months after the visual inspection required by paragraph C.1. of this AD, internally borescope inspect the elevator aft quadrant tube for corrosion, cracking, and deformation; and repeat thereafter at intervals not to exceed 30 months. \n\n\tD.\tIf corrosion is found as a result of the inspections required by paragraphs A., B., or C. of this AD, prior to further flight, accomplish the following: \n\n\t\t1.\tIf corrosion is found to be in excess of the allowable limits specified in Boeing Alert Service Bulletin 747-27A2253, Revision 4, dated January 25, 1990, accomplish the terminating modification for the affected component specified in paragraph F. of this AD. \n\n\t\t2.\tIf corrosion is found to be within the allowable limits specified in Boeing Alert Service Bulletin 747-27A2253, Revision 4, dated January 25, 1990, refinish in accordance with the service bulletin. \n\n\tE.\tIf cracks or deformations are found as a result of the inspections required by paragraphs A., B., or C., of this AD, prior to further flight, accomplish the terminating modification for the affected component defined in paragraph F. of this AD. \n\n\tF.\tAccomplishment of the terminating modification for all affected components, as specified in Boeing Alert Service Bulletin 747-27A2253, Revision 4, dated January 25, 1990, constitutes termination for the inspections required by paragraphs A., B., and C. of thisAD. \n\n\tG.\tAn alternate means 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 submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tH.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind AvenueS.W., Renton, Washington. \n\n\tAirworthiness Directive 90-25-10 supersedes AD 85-13-01, Amendment 39-5084. \n\tThis amendment (39-6822, AD 90-25-10) becomes effective on January 7, 1991.
91-12-08: 91-12-08 BOEING: Amendment 39-7019. Docket 91-NM-102-AD. \n\n\tApplicability: All Model 747-400 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated within 10 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the use of erroneous DME information, decreased enroute RNAV accuracy, decreased terminal area navigation capabilities, and an increase in missed approaches, accomplish the following: \n\n\t(a)\tInspect the airplane or airplane records to determine if Collins distance measuring equipment (DME) part number 622-4540-120 is installed. \n\n\t\t(1)\tIf that Collins DME part number is not installed on the airplane, no further action is required. \n\n\t\t(2)\tIf that Collins DME part number is installed, prior to further flight, add the following statements to the Limitations Section of the FAA-approved airplane flight manual (AFM). This may be accomplished by placing a copy of this AD in the AFM. \n\n\t\t\t\tELECTRONICSYSTEMS \n\nFLIGHT MANAGEMENT COMPUTER SYSTEM \n\nIf the FMS-CDU message "IRS NAV ONLY" is displayed in an area where radio updating is expected, terminal area and enroute RNAV operations using the affected FMC are prohibited and the associated DME must be considered inoperative. RNAV operations may be resumed if radio updating is reestablished by the affected FMC. \n\nDISTANCE MEASURING EQUIPMENT \n\nDuring approaches requiring DME, left and right DMEs must be tuned to the same station and monitored. If a difference is noted, only that DME which results in a display of "DD" or "VD" on the navigational display may be used for approach. \n\n\t(b)\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 Operations Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\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\tThis amendment (39-7019, AD 91-12-08) becomes effective on June 17, 1991.
92-01-03: 92-01-03 McDONNELL DOUGLAS: Amendment 39-8126. Docket No. 91-NM-137-AD. Supersedes AD 91-07-06, Amendment 39-6934. \n\n\tApplicability: Model DC-9-80 (MD-80) series airplanes and Model MD-88 airplanes, operating in a passenger or passenger/cargo configuration, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tNOTE: The requirements of this AD become applicable at the time an airplane in an all-cargo configuration is converted to a passenger or passenger/cargo configuration. \n\n\tTo prevent failure of the tailcone release system, accomplish the following: \n\n\t(a)\tPrior to 12 months in service since new, or within 90 days after March 26, 1991 (the effective date of AD 91-07-06, Amendment 39-6934), whichever occurs later, accomplish a tailcone release system functional test and inspection in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53-244, Revision 1, dated February 8, 1991. \n\n\t(b)\tDiscrepancies in the operation of the tailcone release system found as a result of the functional test must be repaired prior to further flight. \n\n\t(c)\tRepeat the tailcone release system functional test and inspection required by paragraph (a) of this AD at intervals not to exceed 3,500 flight hours or 18 months, whichever occurs first. \n\n\t(d)\tWithin 30 days after discovery, report any discrepancies found during the accomplishment of the inspection and functional tests required by paragraph (a) of this AD to the Manager, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1990 (Public Law 96-511) and have been assigned OMB Control Number 2120-0056. \n\n\t(e)\tWithin 9 months after the effective date of this AD, replace or modify the externaltailcone release system cable and handle assemblies in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin 53-245, Revision 1, dated June 12, 1991. Accomplishment of such replacement or modification constitutes terminating action for the repetitive inspection of the exterior tailcone release handle for cracks, as required by paragraph (c) of this AD. However, the repetitive functional tests and inspections of the tailcone release system required by paragraph (c) of this AD must continue to be accomplished. \n\n\tNOTE: The following portions of the continuing repetitive functional tests and inspections of the tailcone release system are not necessary to accomplish once the replacement/modification of the cable and handle assembly is completed: Those procedures are specified in Paragraph Q. and the second paragraph of the Notes of Paragraph O., of the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53-244, Revision 1, datedFebruary 8, 1991. \n\n\t(f)\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, Los Angeles Aircraft Certification Office (ACO). \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, Los Angeles ACO. \n\n\t(g)\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\t(h)\tThe functional test and inspection requirements of this AD shall be accomplished in accordance with McDonnell Douglas Alert Service Bulletin A53-244, Revision 1, dated February 8, 1991. The replacement or modification requirements shall be accomplished in accordance with McDonnell Douglas Service Bulletin 53-245, Revision 1, dated June 12, 1991. This incorporation by reference was approved by the Director ofthe Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from McDonnell Douglas Corporation, Post Office Box 1771, Long Beach, California 90801, ATTN: Business Unit Manager, Technical Publications, Technical Administration Support, C1-L5B(45-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(i)\tAirworthiness Directive 92-01-03 supersedes AD 91-07-06, Amendment 39-6934. \n\n\t(j)\tThis amendment (39-8126, AD 92-01-03) becomes effective on February 14, 1992.
89-21-05: 89-21-05 BOEING: Amendment 39-6329. Docket No. 89-NM-172-AD. \n\n\tApplicability: Model 747-400 series airplanes, with Integrated Display System (IDS) software installed as identified in Boeing Telegraphic Maintenance Tip (M-7201-89-1141), dated July 27, 1989, certificated in any category. \n\n\tCompliance: Required within 10 days after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude the possibility of airplane status messages not being properly latched into memory which may prevent maintenance from properly dispatching the airplane, accomplish the following: \n\n\tA.\tChange the FAA-approved maintenance program, with concurrence of the assigned FAA Principal Maintenance Inspector, to include the following special procedures, as described in Boeing Telegraphic Maintenance Tip 747-400 MT 31-12 (transmitted by Boeing message M-7201-89-1141, dated July 27, 1989): \n\n\t\t1.\tIf preparation of the airplane involved erasing any EICAS messages, as the final maintenance action prior to dispatch, simultaneously cycle power to the three electronic interface units (EIU). \n\n\t\t2.\tPull the following circuit breakers: \n\n\t\t\tLOCATION\t\t\tNOMENCLATURE \n\t\t\tP7-1 F09\t\t\tEIU L \n\t\t\tP7-1 F10\t\t\tEIU C \n\t\t\tP7-2 F15\t\t\tEIU R \n\n\t\t3.\tAfter three seconds, restore all three circuit breakers to the power-on position. \n\n\tB.\tAdd the following to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t\t"Due to an IDS anomaly, information necessary for dispatch of subsequent flights may be lost if EICAS status messages are erased. To preclude this possibility, do not erase any EICAS status messages." \n\n\tC.\tAn alternate means 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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \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\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6329, AD 89-21-05) becomes effective on October 17, 1989.
2009-01-06 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain 328 Support Services GmbH Dornier Model 328- 300 airplanes. That AD currently requires modifying the electrical wiring of the fuel pumps; installing insulation at the flow control and shut-off valves, and other components of the environmental control system; installing markings at fuel wiring harnesses; replacing the wiring harness of the auxiliary fuel system with a new wiring harness; and installing insulated couplings in the fuel system; as applicable. That AD also currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new inspections of the fuel tank system. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD is effective November 23, 2009. On April 3, 2009 (74 FR 8853, February 27, 2009), the Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD. On September 6, 2005 (70 FR 44046, August 1, 2005), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. We must receive any comments on this AD by December 21, 2009.
75-17-31: 75-17-31 MCDONNELL DOUGLAS: Amendment 39-2319. Applies to all DC-8 Series airplanes as listed on McDonnell Douglas DC-8 Service Bulletin 32-168, Rev. 2 dated July 25, 1975, or later FAA-approved revisions, and certificated in all categories. \n\n\tCompliance required as indicated. \n\n\tTo prevent failure of the Nose Landing Gear (NLG) orifice support tube from fatigue and possible nose gear collapse, accomplish the following: \n\n\t(a)\tWithin the next 1000 landings after the effective date of this AD, unless already accomplished, remove the NLG orifice support tube P/N 5598184 or 5717019 and perform a penetrant inspection of the upper O-ring groove in accordance with McDonnell Douglas DC-8 Service Bulletin 32-168, Rev. 2 dated July 25, 1975, or later FAA-approved revisions, or by an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t\t(1)\tIf cracks are found, discard the support tube and either replace with a reworked orifice support tube, P/N 5598184-SC2465 or 5717019-SC2465 or replace with a new orifice support tube, P/N 5598184-503 or 5717019-503, in accordance with DC-8 Service Bulletin 32-168, Rev. 2 dated July 25, 1975, or later FAA approved revision, or an equivalent rework approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t\t(2)\tAll tubes found to be free of cracks must either be reworked and replaced in accordance with DC-8 Service Bulletin 32-168 Rev. 2 dated July 25, 1975, or later FAA-approved revisions, or an equivalent rework procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region, or they must be replaced by new orifice support tubes, P/N 5598185-503 or 5717019-503. \n\n\t(b)\tUnless already accomplished by (a)(1) or (a)(2), above, within the next 8000 landings after the installation of reworked orifice support tube, replace with a newly reworked tube, P/N 5598184-SC2465 or 5717019-SC2465, or with a new orifice support tube, P/N 5598184-503 or 5717019-503, in accordance with DC-8 Service Bulletin 32-168, Rev. 2 dated July 25, 1975, or later FAA-approved revisions. \n\n\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the initial inspection compliance time specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. \n\n\tThis amendment becomes effective August 20, 1975.
90-08-13: 90-08-13 BOEING: Amendment 39-6571. Docket No. 89-NM-169-AD.\n \n\tApplicability: Model 767 series airplanes as listed in Boeing Alert Service Bulletin 767- 21A0074, dated July 13, 1989, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent inadvertent damage to aft equipment/lavatory/galley ventilation fan wire bundles and the potential for a fire behind the aft cargo compartment wall, accomplish the following: \n\n\tA.\tReroute the aft equipment/lavatory/galley ventilation fan wire bundles along the frame assembly at station 1540 in accordance with Boeing Alert Service Bulletin 767-21A0074, dated July 13, 1989, or Revision 1, dated January 25, 1990. \n\n\tB.\tAn alternate means 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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6571, AD 90-08-13) becomes effective on May 14, 1990.
2009-23-01: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. This AD requires a one-time visual inspection and repetitive ultrasonic inspections of the left and right main landing gear (MLG) actuators for leaking and/or cracks with replacement of the actuator if leaking and/ or cracks are found. This AD results from reports of leaking and cracked actuators. We are issuing this AD to detect and correct leaking and cracks in the MLG actuators, which could result in loss of hydraulic fluid. This condition could lead to an inability to extend or lock down the landing gear, which could result in a gear up landing or a gear collapse on landing.
2009-12-06: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900 series airplanes. This AD requires installing a new circuit breaker, relays, and wiring to allow the flightcrew to turn off electrical power to the in-flight entertainment (IFE) systems and other non-essential electrical systems through a switch in the flight compartment, and doing other specified actions. This AD results from an IFE systems review. We are issuing this AD to ensure that the flightcrew is able to turn off electrical power to IFE systems and other non-essential electrical systems through a switch in the flight compartment. The flightcrew's inability to turn off power to IFE systems and other non- essential electrical systems during a non-normal or emergency situation could result in the inability to control smoke or fumes in the airplane flight deck or cabin.
2009-22-11: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 407 and 427 helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the aviation authority of Canada. The MCAI AD states that, during a preflight check, it was observed that the swashplate link assembly bearing had moved in the lever race, making contact with the swashplate support. The MCAI also states that further investigation revealed that the bearing had not been staked correctly during manufacture. That condition, if not detected, could result in failure of a bearing, failure of the swashplate link assembly, and subsequent loss of control of the helicopter.