(h)
Make sure the left and right Ram Deflector doors move to the flight full closed position.
(i)
Make sure the RAM DOOR FULL OPEN lights extinguish
(j)
Set the TE flaps to 1 unit.
(k)
Make sure the left and right Ram Inlet doors move to the flight full open position.
(l)
Make sure the RAM DOOR FULL OPEN lights come on.
(m)
Release the AIR sensing test switch.
(n)
Make sure that the Ram Air Deflector doors open and lock in the full extended position.
S 865-028
(3)
Remove system B hydraulic power (Ref 29-15-00/201).
S 435-029
(4)
Connect electrical connectors D486 and D490 to the left and right Pack Valves.
S 865-030
(5)
Set the circuit breakers to their initial positions.
F. Power Transfer Unit (PTU) Interface Test
S 865-031
(1) Close the circuit breakers, shown below, on the P6-2 panel:
(a)
PTU/LG BYP V CONT 1
(b)
ALT T.E. FLAP DRIVE AC
(c)
FLAP
(d)
FLAP POS IND T.E.
S 865-032
(2) Open the circuit breaker, shown below, on the P6-3 panel:
(a) NOSE GEAR AIR/GND
S 725-033
(3) Do the steps that follow to do a test of the Power Transfer Unit Interface:
(a)
Set the Alternate Flap Master Arm switch on the P5-3 panel to the ARM position .
(b)
Move the Alternate Flap switch to the UP position until the flaps stop in the full up position.
(c)
Make sure that the PTU Control Valve is in the CLOSED position (Ref 29-22-31/401 for location).
(d)
Move the Alternate Flap switch to the DOWN position until the flaps are at 5 units.
(e)
Make sure that the PTU Control Valve is in the OPEN position.
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737-300/400/500MAINTENANCE MANUAL
(f)
Move the Alternate Flap switch to the UP position until the flaps stop in the full up position.
(g)
Make sure that the PTU Control Valve is in the CLOSED position.
S 865-034
(4)
Set the Alternate Flap Master Arming switch to the OFF position.
S 865-035
(5)
Set the circuit breakers to their initial positions.
G. Put the Airplane Back to its Initial Condition
S 865-036
(1) Remove electrical power if it is not necessary (Ref 24-22-00/201, Manual Control).
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737-300/400/500MAINTENANCE MANUAL
AUTOTHROTTLE SYSTEM - DESCRIPTION AND OPERATION
_______________________________________________
1. General (Fig. 1 and 2)_______
A. The Autothrottle is a computer-controlled electro-mechanical system which controls engine thrust within engine design parameters. Throttle position for each engine is controlled to maintain a specific engine thrust (N1), or a target airspeed, for all flight regimes from takeoff to touchdown. It is designed to operate primarily in conjunction with the Digital Flight Control System (DFCS) and the Flight Management Computer (FMC); interfacing also takes place with the IRS and several other systems and components.
B. The desired mode of operation is selected on the DFCS mode control panel, and the engine thrust limit is selected through the FMCS control display unit.
C. The Autothrottle system consists of a digital computer, two Authothrottle servo mechanisms, an Autothrottle arm (engage) switch, Autothrottle disengage and takeoff/go-around switches and two Power Lever Angle (PLA) synchros.
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