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Fuel Page (Figure 2-5) ........................................................................ 2-30
Fuel System Schematic (Figure 2-6) .................................................. 2-31
STBY Switches...................................................................................... 2-33
XFLOW Switch and Crossflow Shutoff Valve................................. 2-33
Fuel Indicating System ....................................................................... 2-34
Refueling Control Panel.................................................................. 2-34
Fuel Quantity Signal Conditioner and Probes............................ 2-35
Fuel Indicating System Schematic (Figure 2-7) .............................. 2-36
Ram Air Fuel Vent System ................................................................. 2-37
Single-Point Pressure Refueling (SPPR) System............................. 2-37
Precheck Valve.................................................................................. 2-38
Fuel Additives...................................................................................... 2-38
Refueling............................................................................................... 2-38
Fuel Drains (Figure 2-8)...................................................................... 2-39
Auxiliary Power Unit (APU)................................................................. 2-40
APU Cockpit Control Panel ............................................................... 2-42
APU Cockpit Control Panel (Figure 2-9).......................................... 2-42
APU Maintenance Panel..................................................................... 2-43
APU Maintenance Panel (Figure 2-10) ............................................. 2-43
APU Fire Warning System ................................................................. 2-44
APU Bleed Air .................................................................................... 2-44
APU Generator ................................................................................... 2-44
Operational Procedures...................................................................... 2-45
APU Pre-Start Check ....................................................................... 2-45
APU Start-Up ................................................................................... 2-46
APU Shutdown ................................................................................ 2-47
APU Shutdown Features (Automatic) ............................................ 2-48
APU Circuit Breakers.......................................................................... 2-48
Change
Pilot’s Manual
PM-126A 2-1
ENGINES
The aircraft is powered by two TFE731-20 turbofan engines manufactured
by Honeywell. These engines are two-spool, geared transonicstage,
front-fan, jet-propulsion engines. Each engine is rated at 3500
pounds (15.56 kN) thrust at sea level.
A spinner and an axial-flow fan are located at the forward end of the
engine and are gear driven by the low-pressure (N1) rotor. The fan gearbox
output-to-input speed ratio is 0.556. The low-pressure rotor consists
of a four-stage low-pressure axial compressor and a three-stage
low-pressure axial turbine, mounted on a common shaft. The highpressure
(N2) rotor consists of a single-stage centrifugal compressor
and a single-stage air-cooled axial turbine, mounted on a common
shaft. The high-pressure rotor drives the accessory gearbox through a
transfer gearbox. The rotor shafts are concentric, so that the low-pressure
rotor shaft passes through the high-pressure rotor shaft.
An annular duct serves to bypass fan air for direct thrust and also diverts
a portion of the fan air to the low-pressure compressor. Air from
the low-pressure compressor flows through the high-pressure compressor
and is discharged into the annular combustor. Combustion
products flow through the high- and low-pressure turbines and are discharged
axially through the exhaust duct to provide additional thrust.
SECTION II
ENGINES & FUEL
Pilot’s Manual
2-2 PM-126A
PAMB —
TLA
(Secondary)
AIR DATA
COMPUTER
P3
DIGITAL
ELECTRONIC
ENGINE
CONTROL
CABLE
RVDT
WF/P3
WF
MACH, ALTITUDE, TAMB, PAMB
TLA (Primary)
FUEL
AIR
ELECTRICAL
MECHANICAL
AB — AREA BLEED
N1 — LOW PRESSURE ROTOR (FAN) SPEED
N2 — HIGH PRESSURE ROTOR (TURBINE) SPEED
P3 — COMPRESSOR DISCHARGE PRESSURE
PT2 — ENGINE INLET TOTAL PRESSURE
TT2 — ENGINE INLET TOTAL TEMPERATURE
ITT — INTERSTAGE TURBINE TEMPERATURE
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