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APU POWER PLANT - DESCRIPTION AND OPERATION
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 1.  General
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 A.  The APU power plant is installed in a compartment in the tail section of the airplane. The APU power plant is made up of the APU engine, APU electrical generator and the engine mount brackets. The description and operation of the APU engine is given in AMM 49-21-00/001. This section gives the general data for the APU power plant and the operation of the APU systems.
 2.  APU Power Plant
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 A.  The APU power plant is closed in a fire-resistant shroud. The APU shroud also decreases the noise from the APU power plant. The description and operation of the APU shroud is found in AMM 49-12-00/001. The upper shroud attaches to the shroud rings in the APU compartment. The APU engine also attaches to the shroud rings with the APU engine mounts. The ring mounts, shroud rings and APU engine mounts are the APU mounts. The description and operation of the APU mounts is given in AMM 49-13-00/001. The air supply for the APU is supplied by the air inlet system for the APU. The description and operation of the air inlet system is found in AMM 49-15-00/001.
 B.  It is not necessary to remove the APU from the airplane to do maintenance on the APU power plant. For the maintenance of the APU power plant, it is necessary to open the APU cowl door and remove the lower shroud. This will give the access to the APU electrical generator, APU engine accessories and line replaceable units (LRUs). It is easier to remove the APU electrical generator if the APU power plant is lowered to a maintenance stand. The lubrication oil can be added to the APU power plant directly in the APU oil tank through the oil filler port. The description and operation of the APU lubrication system is found in AMM 49-91-00/001.
 C.  The design of the APU power plant permits a fast removal and installation. To remove the APU power plant, the APU cowl door and lower shroud must be removed. The steps to remove and to install the APU power plant are found in AMM 49-11-00/401.
 3.  Operation
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 A.  The power for the APU control circuits is 28 Vdc. The switched hot battery bus or the transformer-rectifier for the APU generator control unit (GCU) supply the power to the APU. When the APU is started, the switched hot battery bus supplies the power. The transformer-rectifier for the APU GCU supplies the power to the APU if the APU loses battery bus power during operation. The APU starter motor gets the 28 Vdc power directly from the airplane battery. If the power from the airplane battery is too low, the starter motor and the switched hot battery bus can get power from a dc power supply. The dc power supply is external. The receptacle for the dc power supply is found on the J9 battery shield. The circuit breakers for the external power and the battery charger are also installed on the J9 battery shield.
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 49-11-00
 ALL  ú ú 01 Page 1 ú Nov 15/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / GTCP85-129 SERIES /737-300/400/500/ ENGINES /MAINTENANCE MANUAL ////////////////////////
APU ENGINE AT 95% OF THE SERVICE SPEED: . IGNITION SYSTEM DE-ENERGIZED . THE HOURMETER ON . 3-WAY SOLENOID VALVE ENERGIZED TO
LOAD CONTROL MODE . THE RTL ON . GEN BUS ON
APU ENGINE AT 50% APU ENGINE AT 100%OF THE SERVICE SPEED: OF THE SERVICE SPEED. THE STARTER MOTOR APU MASTER SWITCH TO THE OFFAND 42,000 RPM
DE-ENERGIZED
POSITION: APU MASTER SWITCH . THE FUEL SOLENOID VALVE TO THE START POSITION: DE-ENERGIZED TO THE . POWER TO THE CLOSED POSITION
AIR INLET DOOR . GEN BUS OFF . POWER TO THE . THE RTL OFF FUEL VALVE . THE HOURMETER OFF . POWER TO THE ETC 1 . THE ETC DE-ENERGIZED

 

TIME

APU ENGINE AT 10% OF THE SERVICE SPEED: . SEQUENCING SWITCH FOR APU ENGINE STOPPED:
THE OIL PRESSURE CLOSES
BATTERY SWITCH . THE AIR INLET
WHEN OIL PRESSURE IS
TO THE ON POSITION DOOR CLOSED
4 PSIG (29 kPa)
. THE FUEL VALVE
. IGNITION SYSTEM ENERGIZED
CLOSED
. THE FUEL SOLENOID VALVE ENERGIZED TO THE OPEN POSITION
APU ENGINE STARTS:
. THE AIR INLET DOOR IN THE FULLY OPEN POSITION
. THE FUEL VALVE IN THE FULLY OPEN
POSITION
. THE STARTER MOTOR ENERGIZED
. 3-WAY SOLENOID VALVE DE-ENERGIZED
TO ACCELERATION MODE

1 AIRPLANES WITH THE ETC
Events for the APU Start Sequence
Figure 1

C94739
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