TM 1-1510-218-10
2-106
Table 2-10. DC Electrical System T2 (Continued)
INST INDIRECT
RECOG
LANDING LIGHTS
RADIO PANEL
ENVIRONMENTAL
TEMP CONTR
LEFT BLEED AIR CONTR
AIR COND CONTR
ELECTRICAL
#1 GEN RESET
#6 DUAL FED BUS
FLIGHT
RUDDER BOOST
FLAP CONTR
LIGHTS
EMERG LIGHTS
FLT INST
NAV
OVHD LIGHTS & EDGELIGHT
TAXI LIGHTS
CABIN LTS
PANEL LIGHTS
READING LIGHTS – SIGNS
ENVIRONMENTAL
PRESS CONTR
RIGHT BLEED AIR CONTR
AUTOMATIC OXYGEN CONTROL
RADIANT HEAT CARGO
DOOR
ELECTRICAL
#2 GEN RESET
AVIONICS
AVIONICS MASTER CONTR
COMPASS SWITCHING
TRANSPONDER EMERG MODE
AVIONICS ANNUNCIATOR
TVSI
HOT BATTERY BUS
#1 FIREWALL SHUTOFF
VALVE
#2 FIREWALL SHUTOFF VALVE
#1 ENGINE FIRE
EXTINGUISHER
#2 ENGINE FIRE EXTINGUISHER
#1 STANDBY FUEL PUMP
#2 STANDBY FUEL PUMP
CABIN LIGHT
BATTERY RELAY
2-83. DC POWER SUPPLY.
a. Description. One nickel-cadmium battery
furnishes dc power when the engines are not
operating. This 24-volt, 34-ampere hour battery,
located in the right wing center section, is accessible
through a panel on the top of the wing. DC power is
produced by two engine-driven 28-volt, 250-ampere
starter-generators. Controls and indicators associated
with the dc supply system are located on the overhead
control panel and consist of a single BATT / ON /
RESET switch, two generator switches (#l GEN and
#2 GEN), C D T1 and BATTERY OFF / RESET
switch, two generator switches (#1 / #2 GENERATOR)
T2 , and two volt-loadmeters. Refer to Figure 2-15.
b. Battery Switch. A switch, placarded BATT
C D T1 BATTERY T2 , is located on the overhead
control panel under the MASTER SWITCH. The
BATT / BATTERY s witch controls the dc power to the
aircraft bus system through the battery relay, and must
be ON to allow external power to enter aircraft circuits.
When the MASTER SWITCH is placed aft, the BATT /
BATTERY switch is forced OFF.
c. Generator
Switches.
Two
switches,
placarded #1 GEN / #2 GEN C D T1 and #1 / #2
