Honeywell Work Light TFE731 5 5AR 5R User Manual

LIGHT MAINTENANCE MANUAL  
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)  
2. Preservation  
Table 302. Equipment and Materials  
Equipment or Material  
Manufacturer  
NOTE: Equivalent substitutes may be used for listed items.  
Barrier material (MIL-PRF-121)  
Commercially available  
Barrier material (MIL-PRF-131, Type I, Class III) Commercially available  
Desiccant (MIL-D-3464, Type I)  
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)  
(SAE AS26860) or (HUM 2156)  
Commercially available  
Mineral base oil (Grade 1010) (MIL-PRF-6081)  
(Alternate for Oil (Univolt 60 Preservative))  
Commercially available  
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,  
WI 54017-1745  
A. Installed Engine Preservation Instructions (Six Months or Less)  
WARNING: MOST PRESERVATIVE SOLUTIONS ARE FLAMMABLE AND  
SHOULD NOT BE USED EXCESSIVELY NOR APPLIED TO A  
HOT ENGINE. ALLOW ENGINE TO COOL FOR A MINIMUM OF  
10 MINUTES BEFORE USING PRESERVATIVE MATERIAL ON  
ANY PART OF THE ENGINE.  
(1)  
(2)  
Allow engine to cool.  
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 PARKED 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.  
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LIGHT MAINTENANCE MANUAL  
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)  
CAUTION: TO PREVENT LOSS OF PRESERVATION OIL FROM FUEL CON-  
TROL, DO NOT OPEN FUEL SHUTOFF VALVE OR MOVE  
THROTTLE WHILE MOTORING ENGINE.  
2. B. (7)  
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.  
(8)  
It is recommended that digital electronic engine control (76-10-02) be placed in air-tight  
bag containing desiccant for storage.  
C. Engine Preservation Instructions (Engine Removed from Aircraft)  
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)  
Prior to removing engine from aircraft perform fuel control preservation procedures as  
outlined in Steps B.(1) through B.(5).  
(2)  
(3)  
(4)  
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.  
(5)  
(6)  
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 barrier  
material (MIL-PRF-131, Type I, Class III). Seal barrier material (MIL-PRF-131, Type I,  
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 I, 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.  
(7)  
(8)  
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.  
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LIGHT MAINTENANCE MANUAL  
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)  
2. C. (9)  
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.  
(10) Engines received from manufacturer have been preserved prior to shipment. Preserva-  
tion is good for two years. Inspection of preserved engines shall be as stated in Steps  
(8) and (9).  
(11)  
It is recommended that digital electronic engine control (76-10-02) be placed in air-tight  
bag containing desiccant for storage.  
D. If Aircraft is Not Sheltered During Extreme Wet Conditions  
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.  
(1)  
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.  
(2)  
(3)  
Perform normal engine shutdown in accordance with Aircraft Flight Manual and/or  
appropriate aircraft document.  
Preserve engine in accordance with Paragraph 2.A.  
E. 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.  
(2)  
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 moisture and salt residue.  
(3)  
Perform normal engine shutdown in accordance with Aircraft Flight Manual and/or  
appropriate aircraft document.  
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LIGHT MAINTENANCE MANUAL  
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)  
2. F. If Aircraft is Operated Over Saltwater Below 4000 Feet for More Than 30 Minutes, Perform  
Compressor Rinse  
(1)  
Prepare aircraft for compressor rinse.  
(a)  
(b)  
Position aircraft into wind in order to carry exhaust discharge away from aircraft.  
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.  
Page 307  
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LIGHT MAINTENANCE MANUAL  
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)  
CAUTION: ALLOW THE ENGINE TO COOL APPROXIMATELY ONE HOUR  
OR UNTIL ITT INDICATOR READS 100°C OR LESS.  
NOTE:  
Caution should be exercised during cold weather (below 0°C (32°F))  
since equipment has no provisions to prevent freezing.  
2. F. (4)  
Perform compressor rinse procedure.  
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.  
(a)  
(b)  
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.)  
(c)  
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 duty  
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.  
(d)  
Allow starter to cool in accordance with Aircraft Maintenance Manual. Allow  
engine to drain induced water.  
Page 308  
Jan 31/00  
72-00-00  
E Honeywell International Inc. Do not copy without express permission of Honeywell.  
 
LIGHT MAINTENANCE MANUAL  
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)  
2. F. (5)  
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.)  
(6)  
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 instructions  
relative to dry-out procedure.  
(a)  
(b)  
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.  
(c)  
(d)  
[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.  
Page 309  
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72-00-00  
E Honeywell International Inc. Do not copy without express permission of Honeywell.  
 

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