Honeywell TFE731-5-5AR User's Manual
Contents
1. tion is good for two years Inspection of preserved engines shall be as stated in Steps 8 and 9 It is recommended that digital electronic engine control 76 10 02 be placed in air tight bag containing desiccant for storage If Aircraft is Not Sheltered During Extreme Wet Conditions WARNING AREAS IN PROXIMITY OF ENGINE INLET AND EXHAUST ARE 3 EXTREMELY HAZARDOUS TO PERSONNEL WHEN ENGINES ARE OPERATING PERSONNEL SHALL CLEAR THESE AREAS DURING ENGINE START AND OPERATION TO AVOID INJURY Engine conditions permitting perform normal engine start in accordance with Aircraft Flight Manual and or appropriate aircraft document Run engine at idle speed for ten minutes Perform normal engine shutdown in accordance with Aircraft Flight Manual and or appropriate aircraft document Preserve engine in accordance with Paragraph 2 A If Aircraft is Operated in a Salt Atmosphere or On Air Strips Treated With Salt NOTE Refer to Paragraph 3 B for additional recommended procedure 1 Wash engine externally as soon as possible with clean fresh water WARNING AREAS IN PROXIMITY OF ENGINE INLET AND EXHAUST ARE EXTREMELY HAZARDOUS TO PERSONNEL WHEN ENGINES ARE OPERATING PERSONNEL SHALL CLEAR THESE AREAS DURING ENGINE START AND OPERATION TO AVOID INJURY Perform normal engine start in accordance with Aircraft Flight Manual and or appropri ate aircraft document Run engine at idle speed for a minimum of ten minutes to re move m2. CAUTION TO PREVENT LOSS OF PRESERVATION OIL FROM FUEL CON 7 8 TROL DO NOT OPEN FUEL SHUTOFF VALVE OR MOVE THROTTLE WHILE MOTORING ENGINE Every four weeks motor engine with starter sufficiently to obtain N1 rotation observing starter manufacturers recommended duty cycle Ensure fuel shutoff valve is in cut off position It is recommended that digital electronic engine control 76 10 02 be placed in air tight bag containing desiccant for storage Engine Preservation Instructions Engine Removed from Aircraft CAUTION THE COMPRESSOR SECTION SHALL NOT BE SPRAYED WITH 1 2 3 4 7 ANY CORROSION PREVENTIVE COMPOUND NO HYDRO CARBONS OR OILS INCLUDING DE ICING ANTI ICE FLUID SHALL EVER BE SPRAYED INTO INLET EXHAUST SCOOPS VENTS AND DRAINS DURING ENGINE OPERATION UNCON TROLLED COMBUSTION COULD BE A POSSIBLE RESULT AVOID OPERATING ENGINE DURING AIRCRAFT DE ICING Prior to removing engine from aircraft perform fuel control preservation procedures as outlined in Steps B 1 through B 5 Drain engine lubricating oil observing procedures in Oil Servicing Remove engine from aircraft and install inlet and tailpipe plugs Wrap engine in barrier material MIL PRF 121 and seal all openings to prevent en trance of foreign material Install engine into barrier material MIL PRF 131 Type I Class III with four bags of desiccant and two humidity indicator cards Install humidity indicator plug into barri
3. 2 Preservation Equipment or Material Honeywell LIGHT MAINTENANCE MANUAL TFE731 5 5AR 5R ATA NUMBER 72 02 75 Table 302 Equipment and Materials Manufacturer NOTE Equivalent substitutes may be used for listed items Barrier material MIL PRF 121 Commercially available Barrier material MIL PRF 131 Type l Class Ill Commercially available Desiccant MIL D 3464 Type 1 Commercially available Humidity indicator card MX 56789 AGM Container Controls Inc P O Box 40020 3526 E Fort Lowell Tucson AZ 85717 0020 Humidity indicator plug Type II Commercially available SAE AS26860 or HUM 2156 Mineral base oil Grade 1010 MIL PRF 6081 Commercially available Alternate for Oil Univolt 60 Preservative Oil Univolt 60 Preservative Exxon Co USA P O Box 4803 600 Jefferson St Houston TX 77210 4803 Sealer Metric Model HS B Doboy Inc 869 S Knowles Ave New Richmond A WI 54017 1745 Installed Engine Preservation Instructions Six Months or Less WARNING MOST PRESERVATIVE SOLUTIONS ARE FLAMMABLE AND SHOULD NOT BE USED EXCESSIVELY NOR APPLIED TOA HOT ENGINE ALLOW ENGINE TO COOL FOR A MINIMUM OF 10 MINUTES BEFORE USING PRESERVATIVE MATERIAL ON ANY PART OF THE ENGINE 1 Allow engine to cool 2 Inspect engine to assure that inlet area is clean and dry CAUTION AIRCRAFT INLET AND TAILPIPE PLUGS FOR ENGINE SHALL BE INSTALLED PRIOR TO WASHING THE AIRCRAFT OR IF AIRCRAFT IS TO BE PAR
4. AINTENANCE MANUAL TFE731 5 5AR 5R ATA NUMBER 72 02 75 ALLOW THE ENGINE TO COOL APPROXIMATELY ONE HOUR OR UNTIL ITT INDICATOR READS 100 C OR LESS Caution should be exercised during cold weather below 0 C 32 F since equipment has no provisions to prevent freezing Perform compressor rinse procedure a b CAUTION REFER TO AIRCRAFT MAINTENANCE MANUAL FOR STARTER DUTY CYCLE DO NOT EXCEED STARTER DUTY CYCLE AT ANY TIME DURING CLEANING PROCE DURE TO ELIMINATE BATTERY DISCHARGE DUE TO STARTER MOTORING CYCLES IT IS RECOMMENDED THAT A GROUND POWER UNIT BE UTILIZED DURING THESE OPERATIONS Verify that ITT indicator reads 100 C or less Verify that all bleed systems are closed and that power lever is in cut off position NOTE Ensure that power lever is in cut off position no fuel and ignition system is turned off throughout rinse cycles If spray mix applicator nozzle is not properly angled fan rotor assembly will centrifuge fluid See Figure 302 Energize starter and motor engine in accordance with Aircraft Maintenance Manual As engine high pressure spool starts to rotate direct nozzle of spray mix applicator as close as possible to base of fan rotor assembly blades at an angle that is parallel to blade airfoil contour and blade base contour and open water control valve on spray mix applicator to inject fresh water Motor engine to a minimum speed of ten percent N2 indication for 45 seconds or starter dut
5. KED UNSHELTERED WHEN NOT IN SERVICE TO MINIMIZE OR PREVENT CORROSION WATER OR CLEANING SOLUTION SHALL NOT BE PERMITTED TO ENTER THE ENGINE INLET AREA 3 Install inlet and tailpipe plugs 72 00 00 0583 Honeywell International Inc Do not copy without express permission of Honeywell Honeywell LIGHT MAINTENANCE MANUAL TFE731 5 5AR 5R ATA NUMBER 72 02 75 CAUTION DO NOT EXCEED MANUFACTURER S RECOMMENDED DUTY CYCLE FOR STARTER 4 Every four weeks with inlet and tailpipe plugs removed motor engine with starter sufficiently to achieve N1 rotation observing manufacturers recommended duty cycle for starter 5 Repeat Steps 2 and 3 6 Itis recommended that digital electronic engine control DEEC 76 10 02 be placed in air tight bag containing desiccant for storage Installed Engine Preservation Instructions More Than Six Months CAUTION THE COMPRESSOR SECTION SHALL NOT BE SPRAYED WITH ANY CORROSION PREVENTIVE COMPOUND NO HYDRO CARBONS OR OILS INCLUDING DE ICING ANTI ICE FLUID SHALL EVER BE SPRAYED INTO INLET EXHAUST SCOOPS VENTS AND DRAINS DURING ENGINE OPERATION UNCON TROLLED COMBUSTION COULD BE A POSSIBLE RESULT AVOID OPERATING ENGINE DURING AIRCRAFT DE ICING 1 Disconnect fuel control discharge line between oil temperature regulator fuel oil cooler and fuel control and connect a line to the fuel control discharge port to drain overboard 2 Disconnect fuel supply line at inlet
6. connection on fuel pump and connect supply of oil Supply oil under two to five pounds per square inch pressure CAUTION DO NOT EXCEED MANUFACTURER S RECOMMENDED DUTY CYCLE FOR STARTER GENERATOR 3 De energize ignition system Advance power lever to idle position Motor fuel control until clean oil flows from overboard drain line Fuel control may be motored by motor ing engine observing motoring procedures established by the particular installation 4 Stop motoring engine disconnect oil supply lines from fuel inlet port on fuel pump and cap inlet port Allow residual oil to drain from fuel control and lines then disconnect overboard drain line and reconnect fuel line between fuel control and fuel oil cooler NOTE Use of corrosion preventive compound in the engine lubrication sys tem for preservation is not required Specified engine lubricating oil is a satisfactory corrosion preventive 5 Wipe all fuel and oil from engine Secure warning tags to engine and as required to indicate preservation procedures have been performed and that engine shall not be operated except as noted until depreservation procedures are performed Maintain engine motoring record indicating engine shall be motored every four weeks 6 Install inlet and tailpipe plugs 72 00 00 530 Honeywell International Inc Do not copy without express permission of Honeywell Honeywell LIGHT MAINTENANCE MANUAL TFE731 5 5SAR 5R ATA NUMBER 72 02 75
7. er material MIL PRF 131 Type I Class Ill Seal barrier material MIL PRF 131 Type Class III seam using sealer Cut opening into barrier material MIL PRF 131 Type I Class III and insert vacuum line Evacuate air from barrier material MIL PRF 131 Type I Class III until barrier material MIL PRF 131 Type Class III is drawn snugly to engine Remove vacuum line and seal opening in barrier material MIL PRF 131 Type I Class III using heat gun Record preservation in Engine Log Book Check humidity indicator plug and humidity indicator cards every 30 days If indicator plug or card changes from blue to pink bag must be opened and engine inspected for rust or corrosion If rust or corrosion is evident take appropriate corrective action Preserve engine in accordance with Steps 4 through 8 after inspection completed 72 00 00 iaie Honeywell International Inc Do not copy without express permission of Honeywell D 10 11 Honeywell LIGHT MAINTENANCE MANUAL TFE731 5 5AR 5R ATA NUMBER 72 02 75 Engines preserved as stated in Steps 4 through 7 shall be removed from preserva tion storage every two years serviced with oil and motored sufficiently to achieve N1 rotation Ensure fuel control power lever is in cutoff position prior to motoring Pre serve engine in accordance with Steps 2 through 8 after motoring Engines received from manufacturer have been preserved prior to shipment Preserva
8. ns a b d relative to dry out procedure Perform normal engine start in accordance with Aircraft Flight Manual and or appropriate aircraft document 5 1J Operate engine at idle speed for approximately 10 minutes then advance power to 80 percent N1 speed indication Turn on anti ice air When ITT indica tion rises turn off anti ice air 5A 5 1H Operate engine at idle speed for approximately 10 minutes Perform normal engine shutdown in accordance with Aircraft Flight Manual and or appropriate aircraft document 72 00 00 5330 Honeywell International Inc Do not copy without express permission of Honeywell
9. oisture and salt residue Perform normal engine shutdown in accordance with Aircraft Flight Manual and or appropriate aircraft document 72 0 0 00 Sept 36 94 Honeywell International Inc Do not copy without express permission of Honeywell 2 F Honeywell LIGHT MAINTENANCE MANUAL TFE731 5 5AR 5R ATA NUMBER 72 02 75 If Aircraft is Operated Over Saltwater Below 4000 Feet for More Than 30 Minutes Perform Compressor Rinse 1 Prepare aircraft for compressor rinse a Position aircraft into wind in order to carry exhaust discharge away from aircraft b Close all bleed systems anti ice valves cabin pressurization air condition etc and install protective covering over starter generator prior to performing cleaning procedure Refer to Aircraft Maintenance Manual 2 Prepare engine for compressor rinse a Disconnect P3 tube at fuel control P3 pressure limiter valve fitting Leave tube end open to atmosphere Cap fuel control P3 pressure limiter valve fitting See Figure 301 b Place protective cover or tape over inlet pressure and temperature sensor located at engine inlet 3 Prepare equipment and materials for compressor rinse Turn water control valve to OFF and attach supply of clean tap water of drinking purity to spray mix applicator inlet 72 00 00 5300 Honeywell International Inc Do not copy without express permission of Honeywell CAUTION NOTE 4 Honeywell LIGHT M
10. y cycle limit whichever is less De energize starter and continue to inject fresh water until engine rolls down then shut off water control valve on spray mix applicator Success of fresh water inducement is noted by water being discharged from exhaust nozzle Allow starter to cool in accordance with Aircraft Maintenance Manual Allow engine to drain induced water 72 00 00 530 Honeywell International Inc Do not copy without express permission of Honeywell 2 F 5 6 Honeywell LIGHT MAINTENANCE MANUAL TFE731 5 5AR 5R ATA NUMBER 72 02 75 Restore engine to operational status a b c Remove protective cover or tape from inlet pressure and temperature sensor and starter generator Reverse blow compressed air approximately 50 psig through disconnected P3 tubes removed from fuel control P3 pressure limiter valve fitting Remove cap previously installed from fuel control P3 pressure limiter valve fitting Connect P3 tube to fuel control P3 pressure limiter valve fitting See Figure 301 Perform dry out procedure of engine immediately following compressor rinse and resto ration of engine to operational status WARNING AREAS IN PROXIMITY OF ENGINE INLET AND EXHAUST ARE EXTREMELY HAZARDOUS TO PERSONNEL WHEN ENGINES ARE OPERATING PERSONNEL SHALL CLEAR THESE AREAS DURING ENGINE START AND OPERA TION TO AVOID INJURY NOTE Refer to Aircraft Maintenance Manual for any special instructio
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