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commenced.
If icing conditions are encountered while the ADG is the only source of
electrical power, the WING anti-ice system must be operated only in
the standby (STBY) mode.
For flight planning, a fuel burn correction of 5% should be used when
the ADG is deployed.
2. MANUAL DEPLOYMENT OPERATIONAL CHECK
A. Before Flight
(1) ADG bay ........................................................................................................... Check
• Clear of foreign objects.
(2) Aft electrical bay ............................................................................................... Check
• Verify that ADG AUTO and MAN circuit breakers (5B10 and 5B11) are closed.
B. In-Flight Procedures
(1) BATTERY MASTER ................................................................................... Check ON
(2) APU ..................................................................................................................... Start
(3) APU GEN............................................................................................................. OFF
IN-FLIGHT CHECKS
Air-Driven Generator Checks
Vol. 1 09−02−1
REV 74, Nov 07/08
▼
CL−604 Operating Manual
PSP 604−6
2. MANUAL DEPLOYMENT OPERATIONAL CHECK (CONT'D)
B. In-Flight Procedures (Cont’d)
(4) VHF Comm, VHF Nav, ADF and transponder .............................................. Set to #1
NOTE
The No. 2 VHF Comm, VHF Nav, ADF and transponder
become inoperative when the main generators (GEN 1 and
GEN 2) are turned off in the steps to follow.
(5) HYDRAULIC, 1 and 2 switches ............................................................................. ON
(6) Airspeed............................................................................ Maintain between 180 and
210 KIAS
(7) Flaps ............................................................................................................Set to 20°
(8) Altitude ....................................................................................Maintain 10,000 feet or
below
(9) ADG DEPLOY CONT – AUTO circuit breaker (2N6)..........................................Open
(10) Landing gear lever .................................................................................. Select to DN
(11) HYDRAULIC, 3A and 3B switches ...................................................................... OFF
• Bleed off No. 3 system pressure and check that HYD 3 LO PRESS caution message
comes on.
(12) AC ELECTRICAL synoptic page .......................................................................Select
(13) ADG manual deploy handle...................................................................................Pull
• Pull the handle for one (1) second, to ensure proper opening of the uplock.
(14) ADG manual deploy handle.................................................................................Stow
CAUTION
Damage to electronic components may occur if ADG manual deploy
handle is not stowed promptly.
IN-FLIGHT CHECKS
Air-Driven Generator Checks
Vol. 1 09−02−2
REV 73, May 14/08
▼
CL−604 Operating Manual
PSP 604−6
2. MANUAL DEPLOYMENT OPERATIONAL CHECK (CONT'D)
B. In-Flight Procedures (Cont’d)
(15) AC ELECTRICAL page..................................................................................... Check
• Verify that within six (6) seconds, the following indications occur:
• ADG voltage ..................................................... 115 ±5 VAC
• Frequency.......................................................... 400 ±40 Hz
On airplanes 5301 to 5407:
• Frequency......................................................... 400 ±20 Hz
• AC ESS BUS ......................................................... Powered
AC essential bus temporarily not powered (AC ESS BUS
caution message on EICAS comes on briefly, then out).
On airplanes 5408 to 5572 not incorporating Service Bulletin 604–24–013:
NOTE
When operating on emergency power only, the AC ESS
BUS caution message may remain on, or be intermittent.
• ADG output.................................................................Green
(16) DC ELECTRICAL synoptic page ...................................................................... Check
• Verify the following indications:
• ESS TRU 1, DC ESS BUS
and BATT BUS ...................................................... Powered
(17) HYDRAULIC synoptic page.............................................................................. Check
• That system pressure shows 3,000 ±200 psi.
　
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