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beside the nose gear and is deployed automatically or manually. Once deployed, the ADG can
only be restowed when the aircraft is on the ground.
ELECTRICAL
Description
Vol. 2 07−10−14
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
Air−Driven Generator (Wet ADG Shown)
Figure 07−10−12
Components and Operation
Air-Driven Generator
The ADG consists of an AC generator mounted on a pivoted support leg, and a variable-pitch
two-bladed propeller that turns in the airstream. There are two versions of the ADG.
ELECTRICAL
Description
Vol. 2 07−10−15
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
Airplanes 5301 to 5407:
On airplanes 5301 to 5407, constant speed of the generator is achieved by hydraulically
controlling the propeller pitch angle. This ADG is commonly referred to as the “wet ADG”. Wet
ADG operation is airspeed-limited (refer to the Airplane Flight Manual; Chapter 2,
Limitations).
NOTE
On landing with the wet ADG deployed, use gentle deceleration
to prevent the ADG from swinging forward and contacting the
fuselage.
Airplanes 5408 and Subsequent:
On airplanes 5408 and subsequent, the constant speed of the ADG is achieved by using a
counterweight system to control the propeller pitch angle. This ADG is commonly referred to
as the “dry ADG”.
ADG Generator Control Unit
The ADG generator is controlled and monitored by the ADG generator control unit (GCU). The
ADG GCU provides the following functions:
• Monitors and controls ADG voltage output
• Protects against overvoltage, overfrequency and underfrequency to the ADG BUS
• Provides a signal to the ADG auto deploy control unit to energize the HYD PUMP 3B
transfer contactor, emergency AC transfer contactor, and emergency DC transfer
contactor when the ADG voltage and frequency are within limits
ADG AUTO DEPLOY CONTROL Unit
Located on the lower center pedestal, the ADG AUTO DEPLOY CONTROL unit controls the
automatic deployment of the ADG.
Automatic deployment of the ADG occurs when:
• Both AC BUS 1 and AC BUS 2 become unpowered, and
• The aircraft is in flight.
Another ADG deployment prerequisite is that one of the three main generators must be on line
prior to both AC main buses going off. This prevents the ADG from deploying during ground
maintenance tests with external power being connected and disconnected with the aircraft on
jacks.
The red EMER PWR ONLY warning EICAS message appears to indicate loss of all normal
electrical power and ADG deployment.
When the ADG unit is fully extended, the two-blade propeller is unlocked and rotates in the
airstream. Once the ADG voltage and frequency are within normal limits, the AUTO DEPLOY
CONTROL unit energizes the appropriate transfer contactors, and allows the ADG to provide
power to the AC ESS BUS and to hydraulic pump 3B via the ADG BUS.
ELECTRICAL
Description
Vol. 2 07−10−16
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
Airplanes 5301 to 5407:
On airplanes 5301 to 5407, the ADG AUTO DEPLOY CONTROL unit deploys the ADG by
sending an electrical signal to fire the squib cartridge in the ADG uplock mechanism.
Airplanes 5408 and Subsequent:
On airplanes 5408 and subsequent, the ADG AUTO DEPLOY CONTROL unit sends a signal
to release the solenoid of the ADG uplock mechanism.
ADG Manual Deploy Handle and ADG AUTO DEPLOY CONTROL Panel
Figure 07−10−13
PWR TXFR OVERRIDE
With the ADG deployed, it may be possible to restore normal AC electrical power by resetting
an engine-driven generator or by using the APU generator. If AC electrical power is restored,
the PWR TXFR OVERRIDE switch (see Figure 07−10−13) should be selected to reset the
three transfer contactors and regain normal AC distribution. This returns the AC ESS BUS to
AC BUS 1 and the 3B hydraulic pump to normal operation.
NOTE
The ADG manual deploy handle must be stowed to allow the
transfer contactors to reset.
ADG LAMP/UNIT Switch
The ADG auto deploy control unit may be tested using the two-position ADG LAMP/UNIT
switch located on the ADG AUTO DEPLOY CONTROL panel.
Selecting the switch to the UNIT position tests the continuity of the uplock circuit, the three
transfer contactors, and the ADG AUTO DEPLOY CONTROL unit internal logic circuitry. Both
engine generators must be operating and AC BUS 1 and AC BUS 2 must be powered to
　
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