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DC service receptacle located on the underside of the fuselage tail section.
The battery master switch must be ON for all types of start.
NOTE
APU BATTERY OFF caution message may appear momentarily during APU
start.
2. ABNORMALITIES DURING APU START
A. APU Fails to Start
If the starter does not engage and the APU fails to start, stop the start sequence by pressing
the APU START/STOP switch. The permitted APU start cycles are as follows:
(1) Using airplane batteries on the ground or for normal in-flight starts:
• Three start attempts, each of 30 seconds continuous cranking,
• Followed by a 20 minute off-time,
• Followed by two further attempts, each of 30 seconds continuous cranking.
(2) Using ground power source:
• Two start attempts, each of 15 seconds continuous cranking,
• Followed by a 20 minute off-time,
• Followed by two further attempts, each of 15 seconds continuous cranking.
(3) If, in either case (1) or (2) above, a successful start is not obtained, a further start must
not be attempted for a period of at least 35 minutes.
B. Hung Start
During start, if the APU rpm is not greater than 30%, within 60 seconds, stop the start
sequence by pressing the APU START/STOP switch.
On airplanes 5301 to 5630 not incorporating Service Bulletin 604–49–006 or
604–49–009:
During start, if the APU rpm stays below 60% for more than 20 seconds, or if it stays
between 60% and 95% for more than 10 seconds, stop the start sequence by pressing the
APU START/STOP switch.
3. FAILURE OF APU TO SHUTDOWN
If the APU fails to shutdown when the START/STOP switch is pressed, push the APU FIRE
PUSH switch/light on the glareshield to stop the APU. Keep in mind that the APU fire
extinguishing SQUIBS will be armed for as long as the fire switch is pressed in. After the APU
has stopped, reset the APU FIRE PUSH switch/light to the normal position.
SUPPLEMENTARY PROCEDURES
Auxiliary Power Unit
Vol. 1 06−04−1
REV 73, May 14/08
CL−604 Operating Manual
PSP 604−6
SUPPLEMENTARY PROCEDURES
Auxiliary Power Unit
Vol. 1 06−04−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
1. CREW COORDINATION IN THE EVENT OF FLIGHT CONTROL JAM
In the event of a jam in one of the ailerons’ cable runs, the control wheels can be disconnected
using the ROLL DISC handle on the centre pedestal. When the ROLL DISC handle is pulled, the
pilot has control over the left aileron and the copilot controls the right aileron.
In the event of a jam in one of the elevator’s cable runs, the control columns can be disconnected
using the PITCH DISC handle on the centre pedestal. When the PITCH DISC handle is pulled,
the pilot has control over the left elevator and the copilot controls the right elevator.
In the event of a jam in one of the rudder’s cable runs, an anti-jam breakout mechanism enables
the operation of the unaffected side. A cross-coupling mechanism synchronizes the movements
of the pilot’s and copilot’s breakout mechanisms. The rudder pedals should be overpowered in
this case, and the anti-jam breakout and summing mechanisms in the system will compensate for
this situation, enabling full travel and unimpeded movement of the rudder pedals.
The flight crew should keep these facts in mind while adhering to standard cockpit management
procedures, and strive to be as coordinated as possible during all maneuvers. Trims should be
adjusted, as required, and appropriate procedures performed.
SUPPLEMENTARY PROCEDURES
Flight Controls
Vol. 1 06−05−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
SUPPLEMENTARY PROCEDURES
Flight Controls
Vol. 1 06−05−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
1. REFUELING/DEFUELING
A. Operation
The Fuel System Computer Unit (FSCU) Channel 1 facilitates automatic refueling operation.
In the event of Channel 1 failure, Channel 2 will take over. If the fuselage refuel/defuel panel
sends faulty transmission data, the FSCU will detect the fault, and send the information to the
Refuel/Defuel panel.
The airplane may be refueled or defueled by pressure/suction or by gravity, using standard
ground equipment. A single point adapter, located in the right hand wing leading edge filler,
permits pressure fueling and defueling. All pressure fueling/defueling operations are
controlled from a refuel/defuel panel.
NOTE
During the refueling/defueling operation, check for fuel spillage from
　
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