ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ RFM Sec X TOC ]
10–9. OPERATING INSTRUCTIONS: SUPPLEMENTAL FUEL SYSTEM
PART I
GENERAL
The MD900 supplemental fuel system option adds a transfer type auxiliary fuel
tank located below the baggage compartment floor.
PART II
LIMITATIONS
Placards:
AUXILIARY FUEL SYSTEM
USE MAIN FUEL DOWN TO
700 LBS BEFORE SELECTING
AUX FUEL TRANSFER BELOW
MAIN FUEL OF 300 LBS.
LOCATED BY AUXILIARY FUEL GAUGE.
NOTE: LOCATION MAY VARY.
LOCATED ABOVE FUEL FILLER
FAA Approved
Original
F92–172
10–25
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
[ RFM Sec X TOC ]
PART IV
NORMAL PROCEDURES
F
Preflight checks:
F
F
F
Prestart cockpit check:
F
F
F
Inflight operation:
F
F
Fuel transfer switch
ON; VERIFY FUEL TRANSFER LIGHT
‘‘ON’’
F
F
Main fuel tank quantity begins to inĆ
crease and supplemental fuel quantity
gauge begins to decrease.
CHECK
Fuel cap
SECURED
Fuel transfer switch
OFF
NOTE: Fuel transfer time is approximately 20 minutes with a full supplemental fuel tank
while in normal cruise.
F
F
Fuel transfer switch
OFF WHEN TRANSFER IS COMPLETE
NOTE: The auxiliary fuel quantity gauge has been found to be inaccurate (indicates
high) during hover operations.
F
Engine/aircraft shutdown
F
F
Fuel transfer switch
OFF; VERIFY FUEL TRANSFER LIGHT
‘‘OFF’’
NOTE: Transferring fuel to the main tank may be accomplished once main tank
indicated fuel quantity is at or less than approximately 500 LB in normal ground
attitude or approximately 700 LB in normal cruise attitude.
Fuel transfer rate is approximately 600 LB/HR in normal cruise and
approximately 400 LB/HR in normal ground attitude.
10–26
FAA Approved
Original
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ RFM Sec X TOC ]
AUXILIARY FUEL SYSTEM
USE MAIN FUEL DOWN TO
700 LBS BEFORE SELECTING
AUX FUEL TRANSFER. DO NOT
USE AUX FUEL TRANSFER BELOW
MAIN FUEL OF 300 LBS.
ON
FUEL TRANSFER SWITCH
FUEL TRANSFER INDICATOR LIGHT
OFF
E
50 100 150
F
AUX FUEL
AUXILIARY FUEL QUANTITY GAUGE
GAUGE, SWITCH AND INDICATOR LIGHT
F92–173
Figure 10–11. Gauge, Switch and Indicator Light – Location Typical
FAA Approved
Original
10–27
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
[ RFM Sec X TOC ]
PART VI
WEIGHT AND BALANCE DATA
Weight and balance characteristics:
The lateral CG of the supplemental fuel tank is at station -2.0.
Calculate CG as shown in the example below.
EXAMPLE I: Longitudinal CG Determination
WEIGHT
(LB)
ITEM
Basic Weight
STATION
(ARM)
3512.4
MOMENT
(IN–LB)
738045
Pilot
185.0
130.70
24180
Copilot/Passenger
185.0
130.70
24180
Passenger - Rear Facing R/H
175.0
173.0
30275
Passenger - Rear Facing L/H
175.0
173.0
30275
Passenger - FWD Facing R/H
175.0
213.0
30275
Passenger - FWD Facing L/H
175.0
213.0
30275
1. Zero Fuel Weight
4582.4
201.1
30275
2. Add: Fuel - Main Tank Only (Jet-A)
Gross Weight:
1025.0
5607.4
191.2
199.3
195980
1117484
3. Add: Fuel - Supplemental Tank Only
Gross Weight:
200.0
4782.4
244.8
202.9
48960
970464
4. Add: Fuel - Both Tanks
Gross Weight:
1225.0
5807.4
200.9
1166444
10–28
FAA Approved
Original
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ RFM Sec X TOC ]
Table 10–4. Fuel Loading Table – Jet–A (6.8 LB/GAL)
FUEL WEIGHT
(LB)
LONGITUDINAL LONGITUDINAL
STATION
MOMENT
LATERAL
STATION
LATERAL
MOMENT
20
239.4
4789
-2.0
-40
40
240.6
9625
-2.0
-80
60
241.6
14494
-2.0
-120
80
242.3
19387
-2.0
-140
100
242.9
24294
-2.0
-200
120
243.4
29210
-2.0
-240
140
243.8
34133
-2.0
-280
160
244.1
39062
-2.0
-320
180
244.4
44000
-2.0
-360
200
244.8
48951
-2.0
-400
Table 10–5. Fuel Loading Table – Jet–B (6.5 LB/GAL)
FUEL WEIGHT
(LB)
LONGITUDINAL LONGITUDINAL
STATION
MOMENT
LATERAL
STATION
LATERAL
MOMENT
20
239.5
4790
-2.0
-40
40
240.7
9629
-2.0
-80
60
241.7
14501
-2.0
-120
80
242.5
19397
-2.0
-140
100
243.1
24306
-2.0
-200
120
243.5
29224
-2.0
-240
140
243.9
34149
-2.0
-280
160
244.3
39080
-2.0
-320
180
244.6
44022
-2.0
-360
200
244.9
48982
-2.0
-400
FAA Approved
Original
10–29
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
[ RFM Sec X TOC ]
FUEL WEIGHT – LB
JET – A (6.8 LB/GAL)
210
200
190
180
170
160
150
140
130
120
110
100
90
80
70
60
50
40
30
20
10
0
238.0 238.5 239.0 239.5 240.0 240.5 241.0 241.5 242.0 242.5 243.0 243.5 244.0 244.5 245.0
FUSELAGE STATION – INCHES
FUEL WEIGHT – LB
JET – B (6.5 LB/GAL)
210
200
190
180
170
160
150
140
130
120
110
100
90
80
70
60
50
40
30
20
10
0
238.0 238.5 239.0 239.5 240.0 240.5 241.0 241.5 242.0 242.5 243.0 243.5 244.0 244.5 245.0
FUSELAGE STATION – INCHES
F92–174
Figure 10–12. Fuel Station Diagram
10–30
FAA Approved
Original
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ RFM Sec X TOC ]
PART VII
SYSTEM DESCRIPTION
The MD900 supplemental fuel system option adds a transfer type auxiliary fuel
tank with a usable capacity of approximately 29.4 US gallons (200 LB, Jet-A) underĆ
neath the baggage compartment floor. The tank is filled through a gravity fill port
on the right side of the aircraft. Transfer into the main tank is performed using
a fuel transfer pump mounted in the supplemental fuel tank. Overfilling the main
tank is prevented by use of a float-type level control valve mounted in the main
tank. This level control valve prevents transfer into the main tank until the fuel
remaining in the main tank is less than approximately 500 LB in normal ground
attitude or approximately 700 LB in normal cruise attitude. The level control valve
will shut off transfer into the main tank if the fuel in the main tank increases to
approximately 755 LB in normal ground attitude or approximately 832 LB in normal
cruise attitude. The supplemental tank vent is teed into the existing main tank
aft vent tubing. The installation includes a cockpit mounted fuel quantity gauge
for the supplemental tank, a fuel transfer pump switch, and a fuel transfer indicator
light.
Electrical power is supplied from the battery bus through the ``AUX FUEL'' 5 AMP
circuit breaker. A separate 1 AMP ``AUX FUEL XMIT'' circuit breaker provides
power for fuel quantity indicating. These circuit breakers are located on the baggage
compartment circuit breaker panel under ``BATTERY BUS''.
FAA Approved
Original
10–31
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
[ RFM Sec X TOC ]
FUEL VENT ROLL OVER VALVE
SUPPLEMENTAL FILLER NECK
FUEL QUANTITY TRANSMITTER
FUEL VENT LINE
SUPPLEMENTAL FUEL CELL
FUEL TRANSFER LINE
FUEL TRANSFER LINE
FUEL LEVEL CONTROL VALVE
MAIN FUEL TANK (REF.)
SUPPLEMENTAL FUEL SYSTEM INSTALLATION
STA 230.5 BULKHEAD
VENT ROLLOVER VALVE AUX FUEL PORT
CHECK VALVE
CABIN FLOOR (REF)
BAGGAGE
(REF.)
FUEL TRANSFER LINE
FUEL TRANSFER LINE
COMPARTMENT
FLOOR
VENT/ROLLOVER VALVE
VENT LINE
MAIN FUEL TANK
(REF)
GRAVITY FILL PORT
LEVEL CONTROL VALVE
CHECK VALVE
AFT RH VENT LINE
SUPPLEMENTAL FUEL TANK
FLAME ARRESTOR
FUEL QUANTITY XMITTER FLOAT
TRANSFER PUMP
FUEL TANK DRAIN PLUG
AFT VENT FAIRING
FUEL TRANSFER LINE
(SUPPLEMENTAL FUEL TANK ROTATED 90° CW FOR CLARITY)
SUPPLEMENTAL FUEL SYSTEM SCHEMATIC
F92–175
Figure 10–13. Supplemental Fuel System
10–32
FAA Approved
Original
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
[ 902RFM207E Cover Pg ]
[ 902RFM207E Book TOC ]
CSP–902RFM207E–1
Optional Equipment
Supplemental Fuel System
[ RFM Sec X TOC ]
PART VIII
HANDLING SERVICING AND MAINTENANCE
Fuel additives:
Anti-icing additives, if required, must be added to the supplemental fuel tank
during refueling.
FAA Approved
Original
10–33/(10–34 blank)