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(3) Cold weather starting procedures are exactly the same as for normal starting except:
(a) Before cranking the engine, pull the starting aid control (24, Fig. 1) OUT to the full extent of its
travel. Hold for 2 to 3 seconds. (This allows the starting aid valve chamber to fill with pressurized
ethyl ether.)
(b) Push the control IN. (This step sprays starting fluid into the engine intake manifold.)
(c) Push starter switch (28) to crank engine.
(d) Follow normal starting procedures and CAUTIONS above [steps (5) through (7), para. 2, B].
(e) In extremely cold weather it may be necessary to repeat steps (a) and (b) above.
CAUTION: USE STARTING AID ONLY FOR STARTING. DO NOT OPERATE
WHILE ENGINE IS RUNNING.
WARNING: DO NOT "FLOOD" THE ENGINE WITH STARTING FLUID. A SERI-
OUS EXPLOSION COULD RESULT.
D. Preparation for Power Delivery (Normal Automatic Voltage Control)
The following are power delivery preparation procedures to be followed after the engine is started.
(1) Check and position switches and controls.
(a) Loosen fastener (3, Fig. 1) and pull generator control tray outward. Place automatic-manual
switch (33) in AUTOMATIC position. Close tray and secure.
(b) Loosen fastener (3) and pull protective relay tray outward. Place test bank switch (34) in AIR-
CRAFT position if the aircraft being serviced is equipped with 28.5-V DC interlock relay system.
(If not, place in TEST BANK position.) Slide tray in and secure.
(c) Meter switch (5) may be in any position except pointing straight DOWN.
(2) Connect output cable plug connector to aircraft receptacle. Be sure connectors are mated fully
and securely.
E. Power Delivery (Automatic Voltage Control)
(1) Place engine-generator control switch (18, Fig. 1) in BUILD-UP-VOLTAGE position momentarily,
then allow it to position itself in GEN position. The electric governor will immediately increase engine
speed to 2000 RPM and maintain it.
(2) Observe generator instruments. Frequency meter (1, Fig. 1) should indicate exactly 400 Hz. Volt-
meter (2) should indicate 115 V AC when line switch (6) is in LINE-TO-NEUTRAL position.
(3) The final step in delivering power is closing the load contactor. When satisfactory frequency and
voltage values are indicated by the instruments, close the load contactor by momentarily placing the
load contactor control switch (20) in the top (spring loaded), CLOSE position. The green indicating
light (22) should glow at once to indicate that the load contactor is closed and power is available at
the aircraft. As soon as the light glows, release the switch. It will automatically return to the center ON
position.
October 1/95 Revised
OM-2031
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