T-45A UJPT, E2-C2, ADV, & IUT Eng-01
Introduction to NATOPS & T-45A Configuration
b.
It provides torque to drive aircraft
accessories--i.e., generator, hydraulic
pumps, and fuel pumps
c.
It supplies bleed air for the oxygen
system, cockpit and fuel tank
pressurization, and the environmental
control system (air conditioning)
Sg 3, fr 3
B.
Fuel system 1.4.7.3.1.1
FUSELAGE
FUEL
TANK
SHUTOFF VALVE
1.
Description: 443-gallon internal fuel supply
BOOST
L P FUEL
H P FUEL
INTEGRAL WING TANK
PUMP
PUMP
PUMP
carried in fuselage tank and integral wing
GTS
443 GAL. (3012 lbs.) TOTAL
427 GAL. (2904 lbs.) USABLE
MANUAL
FUEL CONTROL
THROTTLE
FUEL SYSTEM
UNIT
BOOST
tank
PUMPS
AIRCRAFT 163629 AND UP;
ENGINE
ALSO 163600-163628 AFTER
AFC-48
T-45A FUEL SYSTEM DIAGRAM
2.
Function
a.
Pressure-fed with boost pump assist to
ensure fuel supply is uninterrupted to
the engine fuel system under negative-
g conditions
b.
Provides fuel for engine and gas
turbine starter
Sg 3, fr 4
C.
Electrical system 1.4.4.3.1.1
ARMAMENTBUS
WARNING LIGHTS
GEN
LEGEND
FWD GENERATOR GENERATOR AFT
GEN
RESET
MSTR
CONTACTOR/
UNDER
ARM
OVERVOLT
VOLT
O
1.
Description
HI-CURRENT
VOLTAGE
UNIT
REG
N
RELAY
SENSING
OFF
UNIT
OFF
NON-ESSENTIAL
OFF
RELAY
SAFE
BUSCONTROL
FUSE
28VDCGENBUS
PWR
CAUTION LIGHTS
FWD
AFT
EXT
FWD
AFT
ISLN
a.
Consists of engine-driven, 28 VDC
RLY
ACINVERTER
ACINVERTER
28VDCESSSERVICESBUS
GENFAILRELAY
INV-2
POWERINPUTRELAY
CWS
A
O
N
ON
28VDCESSENTIALLOADS
ELECT
generator
UNIT
INV
INV
BATT 1
BATT 2
NO.1
NO. 2
28 VDC GEN BUS LOADS
OFF
OFF
A
C
OFF
OFF
RESET
28VDCGROUNDSERVICESBUS
26 VAC
115 VAC
ESS BUS
ESSBUS
26VACNON-ESSENTIALBUS
24VDC
24VDC
b.
Two 24 VDC batteries
18AMP
18AMP
115VACNON-ESSENTIALBUS
BATTERY
BATTERY
ELECTRICAL SYSTEM BLOCK
DIAGRAM
c.
Two AC inverters
d.
Respective essential and nonessential
power distribution buses
2.
Function: The electrical system provides 28
VDC, 26 VAC, and 115 VAC to support on-
board electrical systems, aircraft starting,
and emergency power
(8-03) Original
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