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2007-10-10 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A300-600 series airplanes. That AD currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. 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 prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD is effective December 28, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 28, 2009. On June 27, 2007 (72 FR 28827, May23, 2007), 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 January 25, 2010.
76-20-03: 76-20-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-2731 as amended by Amendment 39-3070. Applies to all Pratt & Whitney Models JT9D-3A, -7, -7H, -7A, -7AH, -7F and -20 turbofan engines incorporating labyrinth solid land seals P/N's 589733, 589741, 647189 or 729774. I. To prevent possible engine fires due to excessive No. 3 bearing compartment labyrinth seal clearances, accomplish the following: A. Measure the breather air temperature in accordance with Pratt & Whitney Alert Service Bulletin No. 4391, dated February 19, 1975, or later FAA approved revision, or Service Bulletin No. 4703, dated July 1, 1977, or later FAA approved revision, whenever any of the following major engine sections have been or are removed or replaced: 1. Intermediate case. 2. Rear compressor rotor and stator assembly. 3. Rear compressor drive turbine rotor assembly due to: a. Turbine blade root fracture. b. Multiple turbine blade airfoil fracture. c. Failure that causes release of any other rotating part. 4. Front compressor drive turbine rotor assembly due to loss of complete blade. 5. Turbine exhaust case due to loose or missing tailcone. 6. Diffuser case. B. Compare the measured breather air temperature with the limit defined by Pratt & Whitney Curve 4391, for on-ground temperature checks, or Curve 4703, for in-flight temperature checks, and accomplish the following: 1. If the measured breather air temperature is above the limit, remove the engine from service prior to further flight. 2. If the measured breather air temperature is below the limit, accomplish a repetitive temperature check in accordance with the following schedule, or 200 hours after the effective date of this revision, whichever is later: TEMPERATURE MARGIN INSPECTION INTERVAL Less than 5 degrees C 200 hours 5 degrees C but less than 10 degrees C 500 hours 10 degrees C or greater 1000 hours II. To improve the capability of promptly detecting compartment fires, replace main bearing breather tube steel elbow P/N 708237 with magnesium elbow P/N 613265 in accordance with Pratt & Whitney Service Bulletin 4560, dated March 9, 1976, or later FAA approved revision, no later than March 31, 1977. Upon request of the operator, an equivalent method of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the repetitive inspection intervals 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. The manufacturer's specifications and procedures identified and described in this directive areincorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at New England Region. Amendment 39-2731 supersedes Amendment 39-2109 (40 FR 8544), AD 75-05-16, as amended by Amendment 39-2137 (40 FR 12773). Amendment 39-2731 became effective 30 days after publication in the Federal Register. This amendment 39-3070 becomes effective November 16, 1977.
94-17-06: This amendment adopts a new airworthiness directive (AD) that applies to GROB Luft und Raumfahrt (Grob) Models G102, G103, G109, and G109B gliders. This action requires inspecting (one-time) the airbrake stops for cracks in the surrounding gelcoat and to ensure that the outer airbrake swivel levers are in contact with the stops during operation, and repairing any gelcoat cracks or any airbrake stops not in contact with the swivel levers. Excessive wear caused the airbrake fence to jam on the upper shell of the wing on one of the affected gliders, resulting in an accident. The actions specified by this AD are intended to prevent airbrake failure caused by jamming of the airbrake fence, which could result in loss of control of the glider.
84-24-51 R1: 84-24-51 R1 THE DeHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5030 as amended by Amendment 39-5661. Applies to all Model DHC-7 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To ensure correct operation of the airplane during flight in icing conditions, accomplish the following: A. Within 60 days after the effective date of this AD, revise Section 2 of the FAA- approved DHC-7 Airplane Flight Manual (AFM), Revision 29, dated July 26, 1985, as follows, and provide this information to the flight crews: 1. Change the title of paragraph 2.21 to read: "2.21. Flight in Icing Conditions (Visible Moisture and/or Precipitation at Temperatures Below Plus 5 Degrees Centigrade True Outside Air Temperature, or Plus 13 Degrees Centigrade Indicated Outside Air Temperature When Correction Chart Figure 4-4-4 is Not Used)." 2. Change item 8 in paragraph 2.21.1 toread: "8. Ignition switch - Manual (if required)." 3. Add the following note at the end of paragraph 2.21.1: "NOTE: Manual (continuous) engine ignition is an automatic function when AIRFRAME - FAST/SLW switch is at fast or slow position." B. Special 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. C. An 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, New York Aircraft Certification Office, FAA, New England Region. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to de Havilland Aircraft Company of Canada, A Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. Amendment 39-5030 became effective April 16, 1985. This amendment, 39-5661, becomes effective August 3, 1987.
80-26-02: 80-26-02 GATES LEARJET: Amendment 39-4015. Applies to 23, 24, 25, 28 and 29 series airplanes certificated in all categories. COMPLIANCE: Required as indicated, unless previously accomplished in accordance with AD 80-22-10. A) Before further flight: 1. Deactivate the pitch function of the FC-110 Automatic Flight Control System (AFCS) or Automatic Flight Control Stability System (AFC/SS), as indicated below, by pulling the AFCS Pitch DC Circuit Breaker to the off position, banding it to prevent use of this function and checking to assure this function is the only deactivated circuit or control: SERIES SERIAL NUMBERS LOCATION 23 003 thru 014 015 thru 099 Pilot's Switch Panel Pilot's Sub Panel 24 100 thru 139 (except 131, 132, & 134) 131, 132, & 134 140 thru 229 230 and up Pilot's Sub Panel Pilot's circuit breaker panel Autopilot computer rack (under pilot's seat) Pilot's circuit breaker panel 25 003 thru 069 (except 032) 032070 and up Autopilot computer rack (under pilot's seat) Pilot's Sub Panel Pilot's circuit breaker panel 28 001 and up Pilot's circuit breaker panel 29 001 and up Pilot's circuit breaker panel 2. Install a locally fabricated placard on or near the autopilot control head in clear view of the crew, using letters at least 3/32 inch high, which reads: AUTOPILOT PITCH AXIS INOPERATIVE OBSERVE APPROPRIATE AFM AIRSPEED LIMITATIONS FOR INOPERATIVE AUTOPILOT and operate the airplane in accordance with this placard. 3. Insert in the appropriate section of the existing Airplane Flight Manual (AFM) the FAA approved temporary Airplane Flight Manual Change dated October 22, 1980, pertaining to emergency procedures for pitch axis malfunction. B) On or before April 1, 1981, accomplish all of the following at a Gates Learjet authorized service center holding appropriate FAA repair station ratings. 1. Visually inspect the elevator control system to assurethat Pitch Axis Servo (D.C. Torquer), P/N 6600163-( ) is installed. a) If installed, modify the airplane by incorporating autopilot pitch trim monitor test switch in accordance with Gates Learjet Airplane Modification Kit AMK 80- 16B, Change 2. b) If not installed, modify the airplane by replacing the pitch servo actuator and capstan and incorporating autopilot pitch trim monitor test switch in accordance with Gates Learjet Airplane Modification Kits AMK 80-3, Change 4, and AMK 80-16B, Change 2, respectively. 2. Insert in the appropriate sections of the existing Airplane Flight Manual (AFM) the FAA approved temporary Airplane Flight Manual changes dated October 22, 1980, for autopilot trim monitor. C) When paragraph B of this AD has been accomplished, the requirements of paragraphs A)1. and 2. of this AD are no longer applicable. D) Airplanes may be flown in accordance with FAR 21.197 to a location where the requirements of this AD can be accomplished provided the autopilot is not operative during that flight. E) Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Program, FAA, Central Region, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This AD supersedes AD 80-22-10. This amendment becomes effective on January 15, 1981, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated December 11, 1980, and is identified as AD 80-26-02.
2009-25-13: 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 3 reported occurrences of uncontrolled excessive heat from the left hand baggage bay sidewall heater, [part number] P/N 3436-06-1/0, that resulted in the affected sidewall heater panels sustaining heat discoloration and/or scorching of the liner material. The affected sidewall heater is equipped with a thermostat to regulate heating. These reported occurrences are the subject of further investigation. As a preventive measure, until such time as the cause of the occurrences have been determined, deactivation of the left hand baggage bay heater is necessary to avoid the potential for uncontrolled excessive heat by the heater panel, and on the baggage bay compartment, that could lead to flammability issues. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2009-22-13: We are adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, -300F, and -400ER series airplanes. This AD requires an inspection to determine if certain motor operated valve actuators for the fuel tanks are installed, and related investigative and corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source inside the fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
92-01-06: 92-01-06 BOEING: Amendment 39-8130. Docket No. 91-NM-153-AD. \n\n\tApplicability: Model 757 series airplanes, as listed in Boeing Service Letter 757-SL-28- 8-A, dated June 5, 1991, certificated in any category. \n\n\tCompliance: Required within the next 3,000 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo assure that the fuel crossfeed valve and fuel shutoff valves close fully, accomplish the following: \n\n\t(a)\tPerform a visual inspection or a functional test of the fuel crossfeed valve and fuel shutoff valves to determine if the valves are correctly installed, in accordance with Boeing Service Letter 757-SL-28-8-A, dated June 5, 1991. If an incorrectly installed valve is found, prior to further flight, remove and re-install it correctly, in accordance with the service letter.\n \n\t(b)\tWithin 30 days after accomplishing the inspection or functional test required by paragraph (a) of this AD, submit a report of the inspection ortest findings from which it is determined that the fuel crossfeed valve or fuel shutoff valves were incorrectly installed, to: Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 1601 Lind Avenue SW., Renton, Washington 98055; rapid fax: (206) 227-1181; telex 756366. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provision of the Paperwork Reduction Act of 1980 (P.L. 96-511) and have been assigned OMB Control Number 2120-0056. \n\n\t(c)\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\t(d)\tSpecial flight permitsmay 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(e)\tThe inspection/test requirements of this AD shall be done in accordance with Boeing Alert Service Letter 757-SL-28-8-A, dated June 5, 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 SW., Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\t(f)\t This amendment (39-8130, AD 92-01-06) becomes effective on February 17, 1992.
77-12-07: 77-12-07 BOEING: Amendment 39-2924. Applies to Model 747 airplanes certificated in all categories and equipped with fuel valve actuator assemblies, Boeing P/N 60B92406-27 (ITT General Controls P/N MA11A1173, serial numbers H78442 through H98252 and J00047 through J34689) or Boeing P/N 60B92406-28 (ITT General Controls P/N MA11A1174, serial numbers H95059 through H95074 and J04218 through J37314) installed or manufactured between April 30, 1975, and April 1, 1977. Compliance required as indicated. \n\tTo prevent loss of control of fuel shutoff, crossfeed and required fuel management capability, accomplish the following: \n\tA.\tWithin 145 days or 1300 hours time in service after the effective date of this Airworthiness Directive whichever occurs first, remove fuel valve actuator assembly, Boeing P/N 60B92406-27 (ITT General Controls P/N MA11A1173) or Boeing P/N 60B92406-28 (ITT General Controls P/N MA11A1174) from the No. 1, 2, 3 and 4 engine fuel shutoff valves, AND \n\t\t(1)\treplace with actuator assembly Boeing P/N 60B92406-32 (ITT General Controls P/N MA11A1173-1) or Boeing P/N 60B92406-33 (ITT General Controls P/N MA11A1174-1): OR \n\t\t(2)\treplace with an actuator assembly which has been inspected and reworked to incorporate a properly heat treated armature shaft in accordance with ITT General Controls Service Bulletins MA11A1173-24-01 or MA11A1174-24-01, both dated March 30, 1977, and 107728A101-24-01, dated June 10, 1977, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tB.\tWithin 1 year or 3200 hours time in service after the effective date of this Airworthiness Directive whichever occurs first, replace or rework the actuator assemblies Boeing P/N 60B92406-27 (ITT General Controls P/N MA11A1173) or Boeing P/N 60B92406-28 (ITT General Controls P/N MA11A1174) which are installed on the No. 1, 2, 3 and 4 crossfeed valves, the No. 1 and 4 reserve tank gravity transfer valves, the center wing tank fuel jettison valves and, if installed, the No. 2 and 3 reserve tank gravity transfer valves in accordance with A.(1) or A.(2) above. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to ITT General Controls, Aerospace Products, 1200 South Flower Street, Burbank, California 91502. These documents may also be examined at the Engineering and Manufacturing Branch, FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective June 20, 1977.
85-18-05 R2: 85-18-05 R2 SIKORSKY AIRCRAFT: Amendment 39-5129 as amended by Amendment 39-5525 is further amended by Amendment 39-6098. Applicability: Model S-61L, S-61N, S-61NM, and S-61R series helicopters, certificated in all categories, and S-61A (S/N's 61083, 61087, 61094, and 61161) and S-61V (S/N 61271) helicopters, certificated in the restricted category, which are engaged in more than six external cargo lifts per flight hour under Part 133, Class B, Rotorcraft external load combination operations. Compliance: Required as indicated (unless already accomplished). To prevent operation with a main rotor spar crack and possible loss of the helicopter, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, remove main rotor blades from the rotorcraft that are not approved for use in Part 133 (Class B, Rotorcraft-external load combination operations), and replace with approved blades. The approved main rotor blades are as follows: (1) The following blades are approved for Model S-61L, transport category helicopters operating up to a combined vehicle and cargo gross weight of 22,000 lbs., provided the main rotor blades have been altered and maintained in accordance with Service Bulletin (SB) 61B15-6, Rev. P, or later FAA-approved revisions, excluding Section 2, Part II: (i) P/N's S6115-20501-041 and -042. (ii) P/N's S6115-20601-042, -047, and -048. (iii) P/N's 61170-20201-055, -056, -058, -059, -060, -061, -062, -065, and -067. (iv) P/N's S6117-20101-041, -046, -050, -051, -054, -055, -056, -057, and 058. (2) The following blades are approved for Model S-61N, transport category helicopters operating up to a combined vehicle and cargo gross weight of 22,000 lbs., or Model S-61NM, transport category helicopters operating up to a combined vehicle and cargo gross weight of 20,500 lbs., provided the main rotor blades have been altered and maintained in accordance with SB No. 61B15-6, Rev. P, or later FAA-approved revisions, excluding Section 2, Part II: (i) P/N's S6115-20501-041, and -042. (ii) P/N's S6115-20601-041, -042, -045, -046, -047, and -048. (iii) P/N's S6188-15001-041 and -045. (iv) P/N's 61170-20201-054, -055, -056, 058, -059, 060, -061, -062, -065, -067. (v) P/N's S6117-20101-041, -046, -050, -051, -054, -055, -056, -057, and -058. (3) P/N's 61170-20201-062 blades are approved for the Model S-61A (S/N's 61083 and 61094), restricted category helicopters, operating up to a combined vehicle and cargo gross weight of 22,000 lbs. (4) P/N's S6115-20201-2 and -3 blades are approved for the Model S-61A (S/N's 61087 and 61161), restricted category helicopter, operating up to a combined vehicle and cargo gross weight of 19,000 lbs. (5) P/N 61170-20201-060 blades are approved for the Model S-61V (S/N 61271), restricted category helicopter, operating up to a combined vehicle and cargo gross weight of 19,100 lbs. (6) The following blades are approved for Model S-61R transport category helicopters operating up to a combined aircraft and cargo gross weight of 19,500 pounds: (i) P/N's S6115-20501-041 and -042. (ii) P/N's S6115-20601-042, and -045 through -048. (iii) P/N's S6117-20101-041, -050, -051, -054, -056, -057, and -058. (iv) P/N's 61170-20201-055, -056, -058 through -062, -064, -065, and -067. (b) Within the next 1 1/2 hours time in service after the effective date of this AD, unless already accomplished, inspect main rotor blades equipped with approved visual blade pressure indicators (VBIM) but not equipped with an in-cockpit blade inspection system (CBIM) in accordance with paragraph (c). After the initial inspection, conduct further inspections in accordance with paragraph (c) prior to the first flight of each day and conduct subsequent visual inspections of the VBIM indicators in accordance with Section 2, Part IV, paragraph la of Sikorsky Service Bulletin No. 61B15-6, Revision P, or later FAA-approved revisions, at intervals not to exceed 1 1/2 hours time in service from the last inspection. (c) Inspect the VBIM indicators of the main rotor blades in accordance with procedures set forth in Section 2, Part IV, of Sikorsky SB No. 61B15-6 Rev. P, or later FAA-approved revisions. (1) Conduct visual inspection of blade-mounted VBIM indicators from the transmission work platform of the helicopter or equivalent to ensure that an accurate visual check is conducted. (2) The visual inspection of blade-mounted VBIM indicators shall be conducted by either an individual who holds a pilot certificate with appropriate rating, or a mechanic certificate with airframe rating, or by an appropriately certificated maintenance entity. The person performing this inspection or check shall make entries of the results in the aircraft maintenance record including a description and date of the inspection and the name of the individual performing the inspection along with the certificate number, kind of certificate, and signature. (d) For helicopters equipped with in-cockpit CBIM (reference Sikorsky SB No. 61B15-20D). (1) Prior to the first flight of the day, after the effective date of this AD, unless already accomplished, and every 8 hours time in service thereafter. (i) Visually inspect the main rotor blade VBIM pressure indicators in accordance with paragraph (c). (ii) Test the VBIM pressure indicators and the in-cockpit CBIM transducers in accordance with the procedures set forth in Section 2, Part IV, of Sikorsky SB No. 61B15-6, Rev. P, or later FAA-approved revisions. (2) Check the in-cockpit blade inspection system electrical circuit and CBIM warning light in flight by activating the (cockpit) BIM test switch located on the left overhead quarter panel at least once each (1) hour time in service during flight operations in accordance with the Rotorcraft Flight Manual (RFM). (i) If the (cockpit) BIM warning light illuminates, continue operations in a normal manner. (ii) If the (cockpit) BIM warning light does not illuminate, immediately check the BIM circuit breaker and reset if tripped. (A) Repeat check of (cockpit) BIM test switch to verify if warning light illuminates. Continue with normal operations if BIM warning light functions properly. (B) If the (cockpit) BIM warning light fails to illuminate, discontinue external load operations and land as soon as practical. Investigate and correct malfunction prior to further flight. (3) If the (cockpit) BIM warning light illuminates during flight, discontinue external load operations and follow the appropriate emergency flight procedures in Part I, Section III, of the SA 4045-30 (S-61L) SA4045-100 (S-61L), or SA4045-82 (S-61N) RFM's. NOTE: For Model S-61 helicopters not engaged in Part 133 external load operations, AD 74-20-07, Rev. 5, main rotor blade inspection requirements are applicable. (e) Each blade with any black or red indication visible in the blade VBIM pressure indicator (or whose transducer activates the cockpit BIM warning light) is restricted from further flight until the cause of the indication is determined and corrected in accordance with procedures given in Sikorsky SB 61B15-6, Rev. P, or later FAA-approved revisions. (f) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety may be approved by the Manager, Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. (g) Rotorcraft may be flown in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the AD can be accomplished, except when a VBIM or CBIM indication exists. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a) (1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies, North Main Street, Stratford, Connecticut 06601, Attn: S-61 Commercial Product Support Department. These documents also may be examined at the Office of the Regional Counsel, Southwest Region, FAA, Bldg. 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment revises Amendment 39-5129 (50 FR 38506; September 23, 1985), AD 85-18-05, as amended by Amendment 39-5525 (52 FR 8582; March 19, 1987), AD 85-18-05 R1 which was effective on April 13, 1987. This amendment (39-6098, AD 85-18-05 R2) becomes effective February 8, 1989.