Honeywell TFE731-5 User manual

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
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Nov 11/0
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72-00-00
EHoneywell International Inc. Do not copy without express permission of Honeywell.
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) 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 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.

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
4
Jan 31/0
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72-00-00
EHoneywell International Inc. Do not copy without express permission of Honeywell.
CAUTION: DO NOT EXCEED MANUFACTURER’S RECOMMENDED DUTY
CYCLE FOR STARTER.
2. A. (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) It is recommended that digital electronic engine control (DEEC) (76-10-02) be placed in
air-tight bag containing desiccant for storage.
B. 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 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.

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
5
Jan 16/0
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72-00-00
EHoneywell International Inc. Do not copy without express permission of Honeywell.
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) Drain engine lubricating oil observing procedures in Oil Servicing.
(3) Remove engine from aircraft and install inlet and tailpipe plugs.
(4) Wrap engine in barrier material (MIL-PRF-121) and seal all openings to prevent en-
trance of foreign material.
(5) 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.
(6) 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) Record preservation in Engine Log Book.
(8) 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.

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
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Sept 26/9
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EHoneywell International Inc. Do not copy without express permission of Honeywell.
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) Perform normal engine shutdown in accordance with Aircraft Flight Manual and/or
appropriate aircraft document.
(3) 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.

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
7
Jan 31/0
0
72-00-00
EHoneywell International Inc. Do not copy without express permission of Honeywell.
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) 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.

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
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Jan 31/0
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72-00-00
EHoneywell International Inc. Do not copy without express permission of Honeywell.
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) Verify that ITT indicator reads 100°C or less.
(b) 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.

LIGHT MAINTENANCE MANUAL
TFE731-5/-5AR/-5R (ATA NUMBER 72-02-75)
Page 30
9
Jan 31/0
0
72-00-00
EHoneywell International Inc. Do not copy without express permission of Honeywell.
2. F. (5) Restore engine to operational status.
(a) Remove protective cover (or tape) from inlet pressure and temperature sensor
and starter/generator.
(b) Reverse blow compressed air (approximately 50 psig) through disconnected P3
tubes removed from fuel control P3 pressure limiter valve fitting.
(c) 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) Perform normal engine start in accordance with Aircraft Flight Manual and/or
appropriate aircraft document.
(b) [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) [5A, 5-1H] Operate engine at idle speed for approximately 10 minutes.
(d) Perform normal engine shutdown in accordance with Aircraft Flight Manual
and/or appropriate aircraft document.