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86-04-08: 86-04-08 BOEING: Amendment 39-5238. Applies to Model 767 series airplanes, as specified in Boeing Service Bulletin 767-52-0029 dated August 2, 1985, certificated in any category. \n\n\tTo assure proper entry/service door operation during emergency evacuation, accomplish the following within nine months after the effective date of this AD, unless previously accomplished: \n\n\tA.\tModify the counterbalance gearbox assemblies in accordance with Boeing Service Bulletin 767-52-0029 dated August 2, 1985, or later FAA-approved revisions. \n\n\tB.\tAn alternate means of compliance 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\tC.\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 and/or modifications required by this AD. \n\n\tAll persons affected by this proposal who have not alreadyreceived copies of the manufacturer's service bulletin may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective March 27, 1986.
88-01-13: 88-01-13 BOEING: Amendment 39-5825. Applies to Model 757 series airplanes, as listed in Boeing Alert Service Bulletin 757-29A0032, dated July 9, 1987, certificated in any category. Compliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent inadvertent ram air turbine deployment on the ground while parked, and to ensure proper deployment in flight, accomplish the following: \n\n\tA.\tModify the ram air turbine wiring in accordance with Boeing Alert Service Bulletin 757-29A0032, dated July 9, 1987, or later FAA-approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \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 Airplane Company, P. O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective February 19, 1988.
77-05-02: 77-05-02 BELL: Amendment 39-2846. Applies to Bell Model 212 helicopters certificated in all categories. Compliance required as indicated. To prevent possible failure of certain main rotor blades having possible corrosion or fretting in the blade weight bolt holes or other defects in the spar, accomplish the following for main rotor blades, P/N 204-012-001-23 and -29. For blades with less than 1475 hours' total time in service on the effective date of this AD, remove these blades from further service prior to attaining 1500 hours' total blade time in service. For blades with 1475 or more hours' total blade time in service on the effective date of this AD, remove these blades from further service within 25 hours' time in service. This AD does not apply to blades, P/N 204-012-001-33. (Bell Helicopter Textron message dated February 17, 1977, to all Model 212 operators pertains to this subject.) This amendment becomes effective March 10, 1977.
90-05-04: 90-05-04 CESSNA: Amendment 39-6512. Applicability: Models 208 and 208A (Serial Numbers 20800001 through 20800130), and Model 208B (Serial Numbers 208B0001 through 208B0086) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent nose landing gear shimmy and failure of the engine mount ring, accomplish the following: (a) Visually inspect the lower portion of the engine mount ring for misalignment and cracks. (1) If any ring has a visible misalignment, or has a crack longer than 1.7 inches, prior to further flight replace the ring with a serviceable part. (2) If any ring has a crack less than 1.7 inches, prior to further flight repair the ring in accordance with the Cessna Model 208 Maintenance Manual, Part Number (P/N) 02076-2-13. (b) Replace the shimmy dampener (Part Number 2643007-1 or -2) with a Part Number 2643090-1 shimmy dampener in accordance with the instructions in Cessna Caravan Service Bulletin CAB88-14, dated April 8, 1988. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.This amendment (39-6512, AD 90-05-04) becomes effective on March 23, 1990.
90-17-07: 90-17-07 BOEING: Amendment 39-6695. Docket No. 90-NM-58-AD. \n\n\tApplicability: Model 747-400 series airplanes, listed in Boeing Service Bulletin 747-25- 2853, dated March 1, 1990, certificated in any category. \n\n\tCompliance: Required within the next 90 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent injury to passengers by falling PSU closure panels, accomplish the following: \n\n\tA.\tModify the PSU rails in accordance with Boeing Service Bulletin 747-25-2853, dated March 1, 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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle Aircraft Certification Office (ACO), and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments orconcurrence to the ACO. \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, 1601 Lind Avenue, S.W., Renton, Washington. \n\n\tThis amendment (39-6695, AD 90-17-07) becomes effective on September 17, 1990.
77-14-09: 77-14-09 CESSNA: Amendment 39-2964. Applies to Models 182P (serial numbers 18262466 through 18264713, 18264715 through 18265081, 18265083 through 18265175) and 182Q (serial numbers 18265177 through 18265213, 18265215 through 18265222, 18265224 through 18265237, 18265239 through 18265305, 18265307 through 18265320, and 18265322 through 18265327) airplanes certificated in all categories. Compliance: Required as indicated, unless already accomplished. To assure aircraft controllability when operating at maximum gross weight and aft center of gravity location, accomplish the following: A. Within 25 hours time-in-service after the effective date of this AD: 1. Fabricate a placard having 3/16 inch or larger letters reading "AFT C.G. LOCATION LIMITED TO 46.0 INCHES". 2. Install the placard fabricated in A.1. above in clear view of the pilot and operate the airplane in accordance with this limitation until paragraph B. of this AD is accomplished. B. Within100 hours time-in-service after the effective date of this AD in accordance with Cessna Service Letter SE77-11, dated April 25, 1977, or later approved revisions: 1. Using a steel straight edge, visually inspect the right and left horizontal stabilizer upper skin immediately aft of the stabilizer rear spar upper flange rivet line for evenness along the entire span of the spar. 2. If the inspection required by paragraph B.1. of this AD shows that unevenness exists, support the right and left stabilizer tips and fuselage tail cone and, using a mallet and a 6" x 1" x 1" phenolic block, reform the stabilizer rear spar upper flange to eliminate any unevenness. C. After complying with paragraphs B.1. and B.2. of this AD, the aft center of gravity location is no longer limited to 46.0 inches aft of the datum and the placard installed in accordance with paragraph A. of this AD may be removed. D. The 100 hour compliance time in paragraph B. may be extended to a maximum of110 hours time-in-service when necessary to allow compliance at a regularly scheduled maintenance period. E. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective July 18, 1977.
77-10-03: 77-10-03 LOCKHEED: Amendment 39-2896. Applies to Lockheed Model 18 airplanes, certificated in all categories, using Hamilton standard propellers. Compliance required by the first engine change after the effective date of this AD or October 1, 1977, whichever occurs earlier, unless previously accomplished in accordance with AD 55-15-03 as amended by Amendment 55-24 to Part 507. To increase fire resistance integrity of the propeller feathering system against damage by a powerplant fire, all flexible hose components of propeller feathering lines forward of the firewall must be replaced with lines and fittings which will meet the fire resistance requirements of the hose assemblies specified in (a) through (g) herein. However, if the feathering lines in Zone I include a section of steel tubing, flexible hose assemblies located forward of the cylinders and connecting to the governor are not affected by this directive. The following flexible hose assemblies are acceptable foruse in this application: (a) Resistoflex SSFR-3800-10 hose assemblies. (b) Aeroquip 680-10S hose assemblies with Aeroquip 304 protective sleeves over end fittings (Aeroquip Assembly P/N 304000). (c) Aeroquip 309009 hose assemblies. (d) Aeroquip 309009-8S hose assemblies (where feathering system requires this size). (e) Aeroquip 634000-8 or -10, as applicable, hose assemblies. (f) Aeroquip AE2460001 hose assemblies. (g) Hose assemblies that fully comply with FAR 37.140 (TSO-C42) and have a pressure rating equal to or greater than that of the propeller feathering system installed on the airplane. (h) Equivalent hose assemblies or other means of compliance may be used when approved by the Chief Aircraft Engineering Division, FAA Western Region. Special flight permits may be issued in accordance with FAR's 21.97 and 21.199 to operate the airplane to a base for the accomplishment of this AD. This supersedes AD 55-15-03, as amended by Amendment 55-24to Part 507. This Amendment becomes effective June 16, 1977.
76-25-03: 76-25-03 BOEING VERTOL: Amendment 39-2784. Applies to Boeing Vertol Model 107-11 Helicopters Certificated in all Categories. Compliance required as follows: To detect corrosion which could lead to cracking of the main rotor blade spars accomplish the following within the next 60 days unless already accomplished within the past 34 months and every 36 months thereafter. a) Inspect for corrosion, and alter if necessary, main rotor blades P/N's 107R1202 and SK24790 series in accordance with Boeing Vertol Company Service Bulletin No. 107-333 (R-1) dated July 1, 1976, Section 2 (Accomplishment Instructions" or Boeing Vertol Company Service Bulletin No. 107-334 dated October 29, 1976, Section 2 "Accomplishment Instructions" or equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. b) If spar corrosion exceeds the limits in either of the above service bulletins or those approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, replace the main rotor blade with one that has been inspected and altered if necessary, in accordance with one of the above service bulletins and/or an acceptable equivalent procedure. This amendment is effective December 10, 1976.
2008-17-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2008-17-51, which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires, before further flight, fluorescent magnetic particle inspecting the aft threads of the forward directional control cable (control cable) for a crack and replacing the control cable with an airworthy part if you find a crack. If you do not find a crack, this AD requires that you demagnetize the cable threads until you reach a certain gauss level. This AD also requires visually inspecting the aft cable attach bracket for a crack and for interference with movement of the control cable or for deformation of the aft cable attach bracket. If a crack or interference with movement of the control cable or deformation of the aft cable attach bracket exists, this AD requires replacing the bracket with an airworthy part.This AD also requires modifying the control cable conduit and the rotating cone control rod and identifying the rotating cone control rod with a certain part number. This amendment is prompted by three reports of in-flight failure of the control cable and loss of yaw control resulting in emergency landings and subsequent damage to the helicopter. The actions specified by this AD are intended to prevent loss of yaw control and subsequent loss of control of the helicopter.
2008-26-01: We are adopting a new airworthiness directive (AD) to supersede AD 2008-11-17, which applies to certain Air Tractor, Inc. Models AT-200, AT-300, AT-400, AT-500, AT-600, and AT-800 series airplanes. AD 2008-11-17 currently requires you to install an overturn skid plate kit or a modification to the overturn skid plate already installed. Since we issued AD 2008-11-17, the manufacturer has notified us that Model AT-401B airplanes also need a modification to the overturn skid plate. Consequently, this AD would retain the actions of AD 2008-11-17 and add the requirement to modify the overturn skid plate installed on Model AT-401B airplanes. We are issuing this AD to prevent the front and rear connections of the overturn skid plate to the airplane from breaking, which could allow foreign debris to enter the cockpit during an airplane overturn. This condition, if not corrected, could lead to pilot injury.
2008-26-11: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-46-350P, PA-46R-350T, and PA-46- 500TP airplanes. This AD requires you to install a stall warning heat control modification kit. This AD results from ice forming on the stall vane heater during flights into icing conditions with the landing gear down. We are issuing this AD to prevent ice from forming on the stall vane, which may result in failure of the stall warning system. This failure could result in the pilot being unaware of an approaching stall situation.
2008-25-02: 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: * * * * * The aim of * * * [Special Federal Aviation Regulation (SFAR) 88] is to require all holders of type certificates * * * to carry out a definition review against explosion hazards. The unsafe condition is 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. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-25-04: 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: * * * [S]ome aircraft could have experienced wing overpressure consecutive to the latent failure of both [pressure relief] valve units. Overpressure although not sufficient to cause static damages could have impaired the fatigue damage tolerance of the wing structure. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-24-13: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (P&W) PW4052, PW4056, PW4060, PW4062, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engines. This AD requires a onetime visual inspection of all EEC-131 model electronic engine controls (EECs). This AD also requires the EECs to be identified, categorized by group number, marked, and replaced using a fleet management plan. This AD results from a report of an uncommanded engine in-flight shutdown due to defective EEC pulse width modulator (PWM) microcircuits. We are issuing this AD to prevent uncommanded in-flight engine shutdowns which could result in loss of thrust and prevent continued safe flight or landing.
2008-25-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Recent analysis of the low-pressure turbine (LPT) discs 1-5 carried out by Rolls-Royce plc concluded that it is necessary to reduce the declared safe cyclic life of all Trent 500 LPT stage 3 discs, part number (P/N) FK29581. Rolls-Royce plc has reduced the declared safe cyclic life of these LPT stage 3 discs to 7,990 cycles-since-new (CSN). This AD requires actions that are intended to address the unsafe condition described in the MCAI, which could result in uncontained failure of LPT stage 3 discs, resulting in damage to the airplane.
2008-24-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: The Safe Fatigue Limits (SFL) of the Wing Structure in the P68 Series aircraft have been redefined from the current 8,500 Flight Hours to a new value to be calculated up to a maximum of 17,500 Flight Hours. This has been developed by Vulcanair under Change No. MOD.P68/79 Rev. 1 and approved by EASA with No. EASA.A.C.02482 on 07 June 2006. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-22-52: This document supersedes AD 2008-18-52 and publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2008-22-52 which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model 500N and 600N helicopters by individual letters. This AD requires turning OFF the Yaw Stability Augmentation System (YSAS); installing a placard that limits airspeed to 100 KTS or VNE, whichever is less; and revising the limitations section of the Rotorcraft Flight Manual (RFM) to reflect that limitation. Finally, replacing the adapter tubes with airworthy adapter tubes that have a production date code stamp is required. This AD is prompted by several occurrences of failed adapter tubes on the Model MD900 helicopter which uses the same adapter tubes. The actions specified by this AD are intended to prevent loss of yaw control and subsequent loss of control of the helicopter.
2008-24-03: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines that have not incorporated RR Service Bulletin (SB) No. RB.211-72-E708, SB No. RB.211-72-F227, or SB No. RB.211-72-E965, at original issue or later revision. That AD currently requires initial and repetitive borescope inspections of the high-pressure/intermediate-pressure (HP/IP) turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for wear and cracking, and removing tubes from service if found with any cracks beyond serviceable limits. That AD also currently requires installation of a new or modified HP/IP turbine bearings support as terminating action for the repetitive borescope inspections. This AD has the same requirements, and adds a repetitive inspection of the vent flow restrictor for blockage. This AD results from RR revising their alert service bulletin for inspection of the HP/IPturbine bearing internal oil vent tube, scavenge tube, and tube heat shields for damage, to include a repetitive inspection of the vent flow restrictor for blockage. We are issuing this AD to prevent oil ejecting from the HP/IP turbine bearings chamber and igniting. Burning oil can cause the intermediate-pressure (IP) shaft to fracture, the IP turbine to overspeed, and possible uncontained failure of the engine.
2008-23-18: 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: There have been several incidents of shorting and sparks due to de-icing fluid ingress into the cockpit of CL-600-2C10 and CL-600- 2D24 aircraft. De-icing fluid can enter between the windshields and side windows, leading to possible damage to the electrical components and wires as it comes into contact with cockpit floodlight electrical connections. De-icing fluid in contact with cockpit floodlight electrical connections can result in possible arcing and fire. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-24-06: This amendment supersedes an existing airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) model helicopters. This AD results from a revised mandatory continuing airworthiness information (MCAI) issued by an aviation authority to identify and correct an unsafe condition on an aviation product. The aviation authority of Italy, with which we have a bilateral agreement, reports that the previous MCAI should not apply to newly redesigned and improved tail rotor blades. This AD requires the same inspections as the current AD but limits the applicability to only three part-numbered tail rotor blades. This AD requires actions that are intended to prevent fatigue failure of a tail rotor blade (blade), loss of a tail rotor, and subsequent loss of control of the helicopter.
2005-13-02 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2C10 (Regional Jet series 700 & 701) series airplanes and Model CL-600-2D24 (Regional Jet series 900) series airplanes. That AD currently requires revising the Airworthiness Limitations section of the Instructions of Continued Airworthiness by incorporating new repetitive inspections and an optional terminating action for the repetitive inspections, and repairing any crack. This new AD clarifies the applicability of the existing AD. This AD results from reports of hydraulic pressure loss in either the number 1 or number 2 hydraulic system due to breakage or leakage of hydraulic lines in the aft equipment bay and reports of cracks on the aft pressure bulkhead web around the feed-through holes. We are issuing this AD to prevent loss of hydraulic pressure, which could result in reduced controllability of the airplane, and to detect and correct cracks on the aft pressure bulkhead web, which could result in reduced structural integrity of the aft pressure bulkhead. DATES: This AD is effective December 3, 2008. On July 27, 2005 (70 FR 35987, June 22, 2005), the Director of the Federal Register approved the incorporation by reference of Bombardier CRJ 700/900 Series Temporary Revision MRM2-129, dated June 1, 2004.
2008-22-03: We are superseding an existing 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards * * *. [A]ssessment showed that supplemental maintenance tasks [for certain bonding jumpers, wiring harnesses, and hydraulic systems, among other items] are required to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-21-08: We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-402, AT-402A, and AT-402B airplanes. This AD requires you to repetitively visually inspect the rudder and vertical fin hinge attaching structure for loose fasteners and inspect the rudder or vertical fin skins, spars, hinges, or brackets for cracks and/or corrosion. This AD also requires you to replace any damaged parts found as a result of the inspections and install an external doubler at the upper rudder hinge. Installation of the external doubler at the upper rudder hinge is terminating action for the repetitive inspection requirements. This AD results from a report of a Model AT-402 airplane with a loose upper rudder hinge caused by fatigue. We are issuing this AD to detect and correct loose fasteners; any cracks in the rudder or vertical fin skins, spars, hinges, or brackets; or corrosion of the rudder and vertical fin hinge attaching structure. Hinge failure adversely affects ability to control yaw and has led to the rudder folding over in flight. This condition could allow the rudder to contact the elevator and affect ability to control pitch with consequent loss of control.
2008-21-09: The FAA is superseding an existing airworthiness directive (AD) that applies to all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes and Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes. The existing AD currently requires revising the airplane flight manuals (AFMs) to include new cold weather operations limitations and procedures. This AD requires revising the AFMs to include a requirement for flightcrew training regarding enhanced take-off procedures and winter operations. This AD results from reports of uncommanded roll during take-off. We are issuing this AD to prevent possible loss of control on take-off resulting from even small amounts of frost, ice, snow, or slush on the wing leading edges or forward upper wing surfaces. DATES: This AD becomes effective October 31, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed inthe AD as of October 31, 2008. On April 21, 2008 (73 FR 19989, April 14, 2008), the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. We must receive any comments on this AD by November 17, 2008.
2008-21-06: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-400, 747-400D, and 747-400F series airplanes. This AD requires installing an extension tube to the existing pump discharge port of the scavenge pump on the outboard side of the center fuel tank in the main fuel tank 2. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent a fire or explosion in the fuel tank and consequent loss of the airplane.