Black Box ME262C Instrucciones de operaciones descargar pdf (Pagina 5)

HYDRAULIC SYSTEM CONTROLS

a. The engine driven hydraulic pump is in operation whenever the

port engine, to which it is attached, is operating. Because

of the low capacity of the pump, operation of the landing gear

is slow, and time allowance must be considered when approaching

for a landing.

b. Hydraulic power is used to operate the flaps and landing gear.

c. A compressed air emergency system is incorporated to be used

for lowering flaps and landing gear in event of failure of the

hydraulic system.

ELECTRICAL CONTROLS

a. The electrical system is in operation whenever the battery

switch, (See fig. 4-13) and the generator switches, (See

fig. 4-11 and 12) are in the "on position.

b. A circuit breaker is located to the left side of the cockpit,

(See fig. 3-1) and relieves the entire electrical system in

the event of an overload. The circuit breaker can be reset by

pushing the button (See fig. 3-1).

c. The external power supply plugs into a socket on the right

hand side of the fuselage just above the wing.

d. The inverter switch is located in the main switch panel. (See

fig. 4-10).

FUEL SYSTEM CONTROLS

a. The capacities of the four (4) fuel tanks are as listed:

1. Front main fuel tank 240 gal.

2. Rear main fuel tank 204 gal.

3. Front auxiliary tank 53 gal.

4. Rear auxiliary tank 158 gal.

Total 655 gal.

b. Fuel is supplied to the engines from the two main fuel tanks,

one located in front of the pilot and one in back of the pilot.

Either engine can be supplied from either tank, depending upon

the position of the fuel selector and shut off controls located

next to the throttles. (See fig. 2-10). The fuel pumps are

put into operation by the push button switches located in the

main switch panel. (See fig. 4-3 and 4.)

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Black Box ME262C Instrucciones de operaciones Pagina 5