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2017-14-15: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of aileron and rudder control cables that may have tensions that are beyond allowable limits. This AD requires a revision to the maintenance or inspection program to incorporate certification maintenance requirement tasks that introduce functional tests of the control cable tension. We are issuing this AD to address the unsafe condition on these products.
2009-05-03: We are adopting a new airworthiness directive (AD) for certain Boeing Model 727 airplanes. This AD requires among other actions, installing new ground fault interrupter (GFI) relays for the main fuel tanks and the auxiliary fuel tank pumps. This AD also requires revising the FAA-approved maintenance program to incorporate new Airworthiness Limitations for the GFI of the boost pumps and for the uncommanded on system for the auxiliary fuel tank pumps. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an electrical fault in the fuel pump system, which might cause a connector or end cap to burn through and a subsequent fire or explosion inside the fuel pump or wing spar area. We are also issuing this AD to prevent uncommanded operation of the auxiliary fuel tank pumps, which can cause them to run dry. This condition will increase pump temperature and could supply an ignition source to fumes in the fuel tank, which can resultin a consequent fire or explosion.
46-40-01: 46-40-01 FAIRCHILD: (Was Mandatory Note 4 of AD-707-2: 3 of AD-706-1: 3 of AD- 667-2; 4 of AD-600-2; 4 of AD-633-2; 4 of AD-535-2.) Applies to All Model 24 Series Aircraft. To eliminate the possibility of engine failure due to air-lock in the fuel system, the fuel tank selector valve should be placarded immediately to specify that fuel be fed from only one tank at a time. This placard should read: "CAUTION. Operate on One Tank at a Time Only." (Fairchild Service Bulletin No. 44-7-C dated February 10, 1944, covers this same subject.)
79-05-06: 79-05-06 GULFSTREAM AMERICAN (Formerly Grumman American Aviation Corporation): Amendment 39-3423. Applies to Model GA-7 airplanes, certificated in all categories, serial numbers GA-7-0001 through GA-7-0076. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent chafing, and possible leakage, of the main fuel feed line by the propeller control cable behind the firewall in the left hand engine nacelle, accomplish the following: (a) Within the next 25 hours' time in service, after the effective date of this AD, determine the clearance between the main fuel line and the propeller control cable in accordance with Gulfstream American Service Bulletin ME-14, dated December 23, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (b) If the clearance measured is less than one-half inch, replace the fuel line before further flight.(c) If the clearance measured is one-half inch or greater, replace the fuel line not later than 100 hours' time in service after the effective date of this AD. (d) Equivalent methods of compliance with this AD may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where the needed inspection and work required by this AD can be accomplished. This amendment becomes effective March 9, 1979.
60-26-04: 60-26-04 LOCKHEED: Amdt. 234 Part 507 Federal Register December 14, 1960. Applies to All 188 Aircraft. Compliance required as indicated. Failure of the clamp or flange of the swirl straightener assembly resulted in at least two cases of overheating the nacelle area causing extensive damage to the nacelle. In addition, there have been a number of failures of the retaining clamp and cracks in the flange area of this assembly caused by dynamic loads imposed by the sugar scoop deflection of exhaust gases. The following modifications shall be accomplished to correct the above conditions at the first engine change after December 14, 1960. (a) Remove the present sugar scoop and the lower bellmouth. Install a new lower bellmouth of extended length to mate properly with the engine after removal of the sugar scoop. When this rework has been accomplished, it will be necessary to relocate the fire sensing elements on the structural shroud. (b) Tack-weld the vanes to the clips located on the perimeter of the straightener assembly. (c) Add rubbing strips on the tailpipe shroud door and drill holes in the nacelle cooling duct assembly to cool the bellmouth. (The above items must be accomplished in accordance with Lockheed S/B No. 430, which covers this same subject.) This directive effective December 14, 1960.
79-25-07: 79-25-07 CESSNA: Amendment 39-3633. Applies to: \n\t180 Series (Serial Numbers 18051762 thru 18052981, except 18052975) airplanes; \n\t182/F182 Series (Serial Numbers 18257446 thru 18266590, F18200001 thru F18200094) airplanes; \n\t185 and A185 Series (Serial Numbers 18501096 thru 18503619) airplanes; \n\t188 and A188 Series (Serial Numbers 18800050 thru 18803240) airplanes; \n\tP206 Series (Serial Numbers P20600280 thru P20600647) airplanes; \n\tU206 and TU206 Series (Serial Numbers 20600634 thru 20604649) airplanes; \n\t207 and T207 Series (Serial Numbers 20700001 thru 20700451) airplanes; \n\t210 and T210 Series (Serial Numbers 21058783 thru 21062649, 21062651 thru 21062661, 21062663 thru 21062666, T210-0001 thru T210-0454) airplanes; \n\tModel P210N (Serial Numbers P21000001 thru P21000026) airplanes. \n\n\tCOMPLIANCE: Required within the next 50 hours' time-in-service after the effective date of this AD unless previously accomplished. \n\n\tTo preclude the possibility of electrical orelectronic component damage or an in-flight fire due to a short between an ungrounded alternator and flammable fluid carrying lines, accomplish the following: \n\n\tA)\tPerform either 1 or 2 below: \n\n\t\t1)\tInstall an additional ground strap, Cessna P/N 1570102-22, between the ground stud on the alternator and the lower left hand mounting stud on the engine auxiliary drive pad in accordance with Cessna Single Engine Service Information Letter SE79-59. An equivalent ground strap fabricated per FAA Advisory Circular 43.13-1A appropriate for the alternator rating is also acceptable. \n\n\t\t2)\tModify the alternator installation by installing a different engine mount leg per Cessna Service Kit SK210-84 (Reference Cessna Single Engine Customer Care Service Information Letter SE79-5, dated February 26, 1979) or for the 182 Series, Cessna Service Kit SK182-55A (Reference Cessna Single Engine Customer Care Service Information Letter SE79-58 dated November 23, 1979). \n\n\t\tNOTE: When accomplishing Paragraph 1) or 2), assure all contact areas are clean and provide good electrical continuity. \n\n\tB)\tVisually inspect the alternator installation for, and if necessary, provide at least 1/2 inch clearance between the alternator installation and adjacent flammable fluid carrying lines, powerplant controls and electrical wiring in accordance with FAA Advisory Circular 43.13-1A. \n\n\tC)\tVisually inspect the existing alternator to airframe ground for proper installation (Reference View A-A of SE79-59), evidence of looseness at the terminal and adequate length to allow for relative motion between the alternator and airframe. Also, visually verify that the ground straps between the engine and airframe mount are installed and provide continuity between the engine and mount. Correct any unsatisfactory conditions noted per FAA Advisory Circular 43.13-1A. \n\n\tD)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\tE)\tAny equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\tCessna Single Engine Customer Care Service Information Letters SE79-5 dated February 26, 1979, SE79-58 dated November 23, 1979, and SE79-59 dated November 23, 1979, pertain to the subject matter of this AD. \n\n\tThis amendment becomes effective December 13, 1979.
2017-15-06: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200 and 3101, and Jetstream Model 3201 airplanes that would supersede AD 97-10-05. 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 cracks in the main landing gear (MLG) fitting at the pintle to cylinder interface, which could cause failure of the MLG during takeoff and landing. We are issuing this AD to require actions to address the unsafe condition on these products.
2017-15-05: We are superseding Airworthiness Directive (AD) 69-13-03 for all Piper Aircraft, Inc. Models PA-23, PA-23-160, PA-23-235, PA-23-250, PA-E23-250, and PA-30 airplanes. AD 69-13-03 required inspection of the heater exhaust extension, replacement of the extension as necessary, and overhaul of the combustion heater assembly. This AD retains the inspection of the heater exhaust extension with replacement of the extension as necessary and removes the overhaul requirement of the combustion heater assembly. This AD was prompted by a recently issued AD that applies to the Meggitt (Troy), Inc. combustion heaters, and the combustion heater AD incorporates corrective actions for the heater that contradict the overhaul requirement of AD 69-13-03. We are issuing this AD to continue to address the unsafe condition on these products and avoid potential contradiction of actions.
50-05-01: 50-05-01 PIPER: Applies to All J3C, PA-11, PA-12 Aircraft Manufactured Between November 1945 and November 1946 Inclusive. Compliance required at next periodic inspection but not later than March 1, 1950. In order to minimize the possibility of understrength Nicopress sleeves in the control system, check the major dimension of the pressed portions of all sleeves. If this dimension exceeds 0.353 inch, the sleeve should be repressed to this dimension by two presses with National Telephone Supply Co.'s hand tool 51-M-850. The go-gage furnished with the tool may be used to check the 0.353-inch dimension. In repressing the sleeves, the hand tool used should be carefully adjusted in accordance with the manufacturer's instructions and the sleeves should be recompressed with the larger axis in the same plane as during the original press. If new Nicopress sleeves are installed, three presses with the hand tool should be used as recommended by the sleeve manufacturer.
88-11-07: 88-11-07 CESSNA: Amendment 39-5971. Final copy of priority letter AD. Applicable to Model S550 and 552 airplanes, Serial Numbers S550-0001 through S550-0153, and 552-0001 through 552-0017, certificated in any category. Compliance is required prior to further flight after the effective date of this amendment, unless already accomplished. To prevent loss of a flap panel, accomplish the following: A. Visually inspect the inboard lower surface of each of the four flap panels to verify that each panel has the three required drain/vent holes, and verify that these holes are unobstructed. If all required holes are installed and unobstructed, no further action is required. NOTE: The drain holes are 3/16-inch diameter and are located approximately one inch outboard of the inboard end of the lower surface of each flap panel. (Reference: Maintenance Manual, Section 5-10-01, "Hour and Calendar Inspection Requirements," Item Z(6), "Flaps;" or Cessna Service Letter SLAS550-57-01, dated May 20, 1988.) B. If any drain/vent hole in any flap panel is not present or is found to be obstructed, repair or replace prior to further flight, in accordance with Cessna Service Bulletin SBS550-57-5 (for Model S550 series airplanes), dated May 24, 1988; Cessna Service Bulletin 552-57-5 (for Model 552 series airplanes), dated May 24, 1988; or an FAA-approved method. 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, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Cessna Aircraft Company, Citation Jet Marketing Division, Technical Services Department, Attention: Roger Hatfield, P.O. Box 7706, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas. Amendment 39-5971 was effective earlier to all recipients of Priority Letter AD 88-11-07, issued May 24, 1988. This amendment, 39-5971, becomes effective July 21, 1988.
80-21-52: 80-21-52 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4380. Applies to Model SA-360C series helicopter, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent loss of main rotor speed due to a failure in the engine to main transmission connection, within 10 hours time in service after the effective date of this AD, accomplish the following: (a) Visually inspect for cracks and other defects in the two half housings and the gimbal ring attachment flange. NOTE: During the inspection required by paragraph (a) of this AD, particular attention should be directed to the attachment points/areas. (b) Remove the upper housing half and visually inspect the flexible couplings on the clutch and main transmission sides at the attachment points for cracks, breaks, distortion, and fretting corrosion. (c) Remove the nut from one of the bolts attaching the flexible coupling and check for correct positioning of the flectors. NOTE: 1. The press-fit area of the flector bushings should be located on the flange side. 2. Upon re-installation of the nut, dry torque the nut to 4 to 5 mdaN. (30-35 ft lbs). (d) Check the condition of the main transmission input coupling flange for marks, scores, and impacts. (e) If during the inspections and checks required by paragraphs (a), (b), (c), and (d) of this AD, a crack is found, inspect the main transmission flange for cracks using the dye penetrant method. (f) If cracks are found during the inspections and checks required by paragraphs (a), (b), or (e) of this AD, before further flight, except as provided by paragraph (h) of this AD, replace the main transmission housing and gimbal ring attachment flange with a serviceable part. (g) If no cracks are found during the inspections and checks required by paragraphs (a), (b), (c), (d), or (e) of this AD, repair other defects as necessary. (h) The helicopter may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the inspections and repairs required by this AD can be accomplished provided paragraph (a) of this AD has been accomplished. (i) Report defects found to the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. Reporting approved by the Office of Management and Budget OMB No. 04-R0174. NOTE: Aerospatiale Work Cards No. 65-31-601, dated November 1976, and No. 65-31- 401, dated June 1975, and Section 02.80 of the Aerospatiale Standard Practices Manual, refer to the inspections and checks required by this AD. This amendment becomes effective May 6, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-21-52, issued October 8, 1980, which contained this amendment.
2017-15-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes. This AD was prompted by wire harness chafing on the electro-mechanical actuators (EMAs) for certain spoilers due to insufficient separation with adjacent structure. This AD requires replacement of affected EMAs. We are issuing this AD to address the unsafe condition on these products.
84-03-03: 84-03-03 BRITISH AEROSPACE: Amendment 39-4812. Applies to Model HS 125 airplanes series 1A with modifications 251867 and 252605, series 400A with modification 252550, series 600A with modification 252468, and series 700A, certificated in all categories. The serial numbers of the affected airplanes are listed in the Planning Information section of British Aerospace 125 series Service Bulletin 24-225-(2747), dated October 17, 1980. Compliance is required as indicated, unless already accomplished. To prevent loss of power to both engine fuel computers by a single fuse failure, accomplish the following: A. Modify the engine fuel computers' direct current power supply electrical circuits within the next 500 hours time in service or one year, whichever occurs first after the effective date of this AD, in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace, HS 125 series Service Bulletin 24-225-(2747), dated October 17, 1980. B. Alternate means ofcompliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special 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. This amendment becomes effective March 22, 1984.
81-21-05: 81-21-05 ARTEX AIRCRAFT SUPPLIES, INC.: Amendment 39-4231. Applies to Artex replacement battery packs, P/N 00-21-006, which are designed for use in the Emergency Beacon Corporation Emergency Locator Transmitter. Within 30 calendar days after the effective date of this AD, inspect the ELT and if the battery is an Artex Battery Pack, P/N 00-21-006, replace it with a battery pack with a different part number which is approved under TSO-C91 for use in this ELT. Note: If no replacement battery pack is immediately available, placard the ELT "Not to be used in salt water." The airplane may be operated for up to 90 days with a placarded ELT. Alternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. This amendment becomes effective October 19, 1981.
82-09-51 R1: 82-09-51 R1 CANADAIR: Amendment 39-4452. Applies to all Canadair CL-600 airplanes certificated in all categories. Because of the possible loss of normal braking, accomplish the following unless already accomplished. 1. Revise flight manual operating procedures as follows before further flight: A. The critical engine failure recognition speed V1 shown in Section 4, page 4-39; Supplement 2, page S2-69; or Supplement 6, page S6-74 of the airplane flight manual shall be reduced by 10 KIAS but shall not be lower than 105 KIAS (VMCG). B. The takeoff distances derived from Section 4, page 4-44; Supplement 2, page S2-73; or Supplement 6, page S6-80 of the airplane flight manual shall be increased by a factor of 1.2 (20 percent). C. The landing distances derived from Section 4, page 4-63; Supplement 2, page S2-94; or Supplement 6, page S6-101 of the airplane flight manual shall be increased by a factor of 1.65 (65 percent). 2. If any suspected braking deficiencyoccurs during the brake operation, immediately release brakes, switch off the anti-skid system, and control the brakes manually as described in paragraph 35.3 of Section 2 of the airplane flight manual. 3. Within the next 50 flights after the effective date of this AD, modify the anti-skid system in accordance with Canadair Service Bulletin A600-0212 dated May 1, 1982. Accomplishment of this modification constitutes terminating action for this AD and authorizes removal of the airplane Flight Manual revisions imposed by item 1. above. 4. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 5. Special 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. 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). This amendment becomes effective September 9, 1982, and was effective earlier to all recipients of telegraphic AD T82-09-51 dated April 14, 1982.
2017-10-10: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires installing an engine flame detector bracket assembly and harness assembly. This AD was prompted by reports of false fire warnings. The actions of this AD are intended to prevent an unsafe condition on these products.
2017-15-03: We are superseding Airworthiness Directive (AD) 2014-08-02 which applied to certain Airbus Model A300 B4-600 and A300 B4-600R series airplanes. AD 2014-08-02 required modifying the profile of stringer run-outs of both wings, including a high frequency eddy current (HFEC) inspection of the fastener holes for defects, and repairs if necessary. This new AD retains the actions required by AD 2014-08-02 and revises the compliance times. This AD was prompted by further analysis in the context of widespread fatigue damage (WFD), which concluded that shorter compliance times are necessary to meet specified requirements to address WFD. We are issuing this AD to address the unsafe condition on these products.
61-15-04: 61-15-04 LOCKHEED: Amdt. 309 Part 507 Federal Register July 21, 1961. Applies to All 188 Series Aircraft Incorporating A Lounge Using Hardman Seats. Compliance required as indicated. Reports have been received that grommets are missing in some of the aft lounge safety belt cable guide brackets. Grommets are required in these brackets to permit the cable to withstand the design load. Within the next 100 hours' time in service inspect the safety belt cable guide bracket, Hardman P/N 5072-1, of the left and right aft lounge seats for presence of nylon grommets. If the nylon grommets are missing, install nylon grommets, P/N 295957-10A (United Carr Fastener Corp.), or equivalent, or restrict occupancy of the left and right aft lounge seats during takeoff and landing until such time as grommets are installed. (Lockheed Service Bulletin 88/SB-541 refers to the same subject.) This directive effective August 2, 1961.
2003-17-05: This amendment adopts a new airworthiness directive (AD) that applies to all Short Brothers and Harland Ltd. (Shorts) Models SC-7 Series 2 and SC-7 Series 3 airplanes. This AD establishes a technical service life for these airplanes and allows you to incorporate modifications, inspections, and replacements of certain life limited items to extend the life limits of these airplanes. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of critical structure of the aircraft caused by fatigue.
2017-14-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of an aborted takeoff because the rudder pedals were not operating correctly. Investigation revealed a protruding screw in the rudder pedal heel rest adjacent to the pedals. This AD requires a torque check of the screws in the cover assembly of the heel rest for both the Captain and the First Officer's rudder pedals, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-14-11: We are superseding Airworthiness Directive (AD) 2007-13-08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-13-08 required repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. This AD expands the applicability of AD 2007-13-08, and includes an optional terminating installation for the repetitive actions. This AD was prompted by a determination that the unsafe condition could occur on additional airplanes. We are issuing this AD to address the unsafe condition on these products.
60-11-03: 60-11-03 LOCKHEED: Amdt. 159 Part 507 Federal Register May 24, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. Due to loose attachments and cracked quick engine change upper cowl panel longerons the following inspections are required. Prior to dispatch from a terminal where inspection facilities are available, unless already accomplished within the last 300 hours' time in service, and thereafter at every 300 hours' time in service, inspect the top cowl panel upper longerons and the attachments at the rear fittings for cracks or loose attachments. (a) Replace loose attachments in the longeron fittings. Acceptable replacements are: (1) One-sixty-fourths-inch diameter oversize Hi-Lok (P/N HL 56-6 pin, P/N HL 64-6-5 pin, P/N HL 85-6 collar). (2) Thirteen-sixty-fourths-inch diameter NAS type close tolerance screw, minimum heat treat 160,000 p.s.i. Ream to oversize hole limits of 0.212-0.2192-inch diameter. (3) Seven-thirty-seconds-inch diameter NAS type close tolerance screws; minimum heat treat 160,000 p.s.i.; minimum edge distance, 1 1/2 diameters. Ream to oversize hole limits of 0.2181-0.2192-inch diameter. (4) It is satisfactory to mix Huck bolts and Hi-Lok fasteners, but it is not acceptable to mix NAS type screws with Huck bolts or Hi-Lok fasteners. (b) Cracked longerons must be replaced or an FAA approved repair incorporated before next flight. The preceding inspections may be discontinued after the incorporation of the modifications contained in Lockheed Service Bulletin 88/SB-500. (Lockheed Alert Service Bulletin No. 467 covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 29, 1960. Revised September 29, 1960. Revised May 13, 1961.
2017-14-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA330J helicopters. This AD requires replacing certain hydraulic pumps and is prompted by reports of broken screws that attach the cover of the hydraulic pump. The actions of this AD are intended to prevent an unsafe condition on these products.
2017-13-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH), which indicates that the main landing gear (MLG) does not comply with certification specifications, which could result in a locking failure of the MLG side stay. This AD requires modification or replacement of certain MLG side stay assemblies. We are issuing this AD to address the unsafe condition on these products.
80-12-51 R2: 80-12-51 R2 PRATT & WHITNEY AIRCRAFT: Amendment 39-3809. Applies to all Pratt & Whitney Aircraft JT3D series turbofan engines. Compliance required as indicated. To prevent possible first stage fan blade failures resulting from low cycle fatigue, perform inspections in accordance with the schedule below: 1. Within 50 cycles after May 27, 1980, unless already accomplished, and every 200 cycles thereafter, perform a visual inspection of the critical area of the fan blade convex airfoil surface, in accordance with Pratt & Whitney Aircraft All Operator Telegram Nos. JT3D/72-00/PSE.WJM.0-5-26-1 and JT3D/72-00/PSE.WJM.0-5- 30-1. Remove from service any blade having a visual indication, crack, lap, or blend in the critical area. Any questionable visual indication may be dye penetrant inspected for verification. If the dye check is positive, remove from service. If there is no positive dye check indication, repeat within the next 50 cycles and every 50 cycles thereafter.2. Within 200 cycles after the effective date of this amendment, unless already accomplished, and every 2,200 cycles thereafter, perform an ultrasonic inspection of the fan blade in accordance with the provisions of Pratt & Whitney Alert Service Bulletin No. 5136, dated May 30, 1980, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. If any crack indications are found, the blade must be removed from service prior to further flight. 3. Once the ultrasonic inspections of Paragraph 2 have been initiated, the visual inspections per Paragraph 1 may be discontinued. 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, FAA, 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 adjustthe 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 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 Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, an 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 the New England Region. This amendment amends TAD No. T 80NE-26 issued May 28, 1980, as amended by TAD No. T 80-12-51 effective June 2, 1980. This Amendment 39-3809 becomes effective July 1, 1980.