.
light is disarmed when APU switch is in OFF position.

APU LOW OIL PRESSURE Light
Illuminated (amber) –
.
during start until the APU oil pressure is normal

.  oil pressure is low causing an automatic shutdown (after start cycle is
complete)

.  
if light is illuminated when APU switch is placed to OFF, light
extinguishes after 5 minutes

.
light is disarmed when APU switch is in OFF position.

APU Switch
OFF – normal position when APU is not running
.  
positioning switch to OFF with APU running trips APU generator off the bus(es), if connected, and closes APU bleed air valve. APU continues to run for a 60 second cooling period

.
APU air inlet door automatically closes after shutdown. ON – normal position when APU is running.

START (momentary) – positioning APU switch from OFF to START and releasing it to ON, initiates an automatic start sequence.
Copyright . The Boeing Company. See title page for details.
Engines, APU -General Controls and Indicators 737 Flight Crew Operations Manual

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Copyright . The Boeing Company. See title page for details.
7.15.8  July 28, 2000

737 Flight Crew Operations Manual

Introduction
The airplane is powered by two CFM56–7 engines. The engine is a dual–rotor, axial–flow turbofan. The N1 rotor consists of a fan, a low–pressure compressor and a low–pressure turbine. The N2 rotor consists of a high–pressure compressor and a high–pressure turbine. The N1 and N2 rotors are mechanically independent. The N2 rotor drives the engine gearboxes. A bleed–air–powered starter motor is connected to the N2 rotor.
A dual–channel electronic engine control (EEC) regulates each engine. The EEC monitors autothrottle and flight crew inputs to automatically set engine thrust.
Each engine has individual flight deck controls. Thrust is set by positioning the thrust levers. The thrust levers are positioned automatically by the autothrottle system or manually by the flight crew. The forward thrust levers control forward thrust from idle to maximum. If the EECs are in the alternate mode, advancing the thrust levers full forward provides some overboost and should be considered only during emergency situations when all other available actions have been taken and terrain contact is imminent. The reverse thrust levers control thrust from reverse idle to maximum reverse
Engine Indications
Primary and secondary engine indications are provided. Engine indications are displayed on the center forward panel upper display unit (DU), lower DU or the Captain’s or First Officer’s inboard DU.
Primary Engine Indications
N1 and EGT are the primary engine indications. The primary engine indications are normally displayed on the center forward panel upper DU. If that unit fails, the display automatically moves to the lower DU. The primary engine indications can also be manually selected to either the Captain’s or First Officer’s inboard DU, or the lower DU, using the respective display select panel.
Secondary Engine Indications
YA686, YA687, YC153, YC154 N2, fuel flow, oil pressure, oil temperature, oil quantity, and engine vibration are the secondary engine indications. The secondary engine indications are manually selected to either the Captain’s or First Officer’s inboard DU, or the lower DU, using the respective display select panel and the ENG switch on the engine display control panel.
Copyright . The Boeing Company. See title page for details.
Engines, APU -Engine System Description 737 Flight Crew Operations Manual

YA613, YA626, YA721 - YA809, YC411 - YK104 N2, fuel flow, oil pressure, oil temperature, oil quantity, and engine vibration are the secondary engine indications. The secondary engine indications, except for fuel flow, are manually selected to either the Captain’s or First Officer’s inboard DU, or the lower DU, using the respective display select panel and the ENG switch on the engine display control panel. Fuel flow is displayed full time on the upper display unit below the primary engine indications.
The secondary engine indications are automatically displayed when:
.
the displays initially receive electrical power

.
in flight when an engine start lever is moved to CUTOFF

.
in flight when an engine N2 RPM is below idle

.
a secondary engine parameter is exceeded.

When the secondary engine indications are automatically displayed, they cannot be cleared until the condition is no longer present.
Normal Display Format
N1, EGT, and N2 are displayed as both digital readouts and round dial/moving pointer indications. The digital readouts display numerical values while the moving pointers indicate relative value.
　
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