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If caution message persists:
(2) Manual control .........................Resume
(3) Approach ................................Continue to Category I minima.
If below 200 feet AGL and non-visual:
(1) Go-around ..................................Initiate
SUPPLEMENT 4A
Category II Operations
07−04A−01−9
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
6. ABNORMAL PROCEDURES (CONT'D)
C. System Failures: (Cont’d)
SYSTEM INDICATION
AUTOPILOT
DISCONNECT
Autopilot fails to disengage when intentionally disconnected.
ACTION
Autopilot fails to disconnect using AP/SP DISC switch on control wheel
during approach to landing:
(1) Autopilot.............................. Disconnect using AP ENG switch on
FCP, or AP DISC switch
on FCP, or TOGA
switch, or AP/SP DISC
switch on other control
wheel.
(2) Airplane .........................................Trim manually using stabilizer
trim switch.
If unable to disconnect autopilot, expect higher than normal control feel
force loads during landing.
SYSTEM INDICATION
ILS LOCALIZER
or GLIDESLOPE
ILS deviation error is greater than Category II “window”. Flashing
localizer or glideslope scale and pointer.
ACTION
Failure during approach:
If above 200 feet AGL, on a stabilized approach:
(1) Approach ................................Continue to Category I minima, or
initiate go-around.
If below 200 feet AGL and non-visual:
(1) Go-around ..................................Initiate
SUPPLEMENT 4A
Category II Operations
07−04A−01−10
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
6. ABNORMAL PROCEDURES (CONT'D)
C. System Failures: (Cont’d)
SYSTEM INDICATION
HYDRAULICS Any hydraulic system(s) failure(s) annunciated as caution messages
displayed on EICAS (See Chapter 5; ABNORMAL PROCEDURES –
HYDRAULIC POWER).
ACTION
Failure during approach:
If above 200 feet AGL, on a stabilized approach:
(1) Applicable procedure..........Accomplish Refer to Chapter 5;
ABNORMAL
PROCEDURES –
HYDRAULIC POWER.
(2) Approach ................................Continue to Category I minima, or
initiate go-around.
If below 200 feet AGL and non-visual:
(1) Go-around ..................................Initiate
SYSTEM INDICATION
MAIN
GENERATOR
Generator failure; GEN 1 (2) OFF caution message displayed on EICAS.
ACTION
NOTE
AP will disconnect if AFCS 2 is active.
YD 1 or YD 2 may disengage.
(1) Approach ................................Continue to Category I minima, or
initiate go-around.
SUPPLEMENT 4A
Category II Operations
07−04A−01−11
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
7. PERFORMANCE
The performance data in Chapter 6 are applicable, except as modified by the following:
A. Maximum Landing Weight Limited By Climb Requirements – Approach Flaps
20°/Landing Flaps 45°
The maximum landing weight limited by climb requirements for varying conditions of airport
pressure altitude and temperature for the flaps 20° approach climb configuration and a
subsequent landing flaps 45° configuration, are given in Figure 07−04A−1. The chart
incorporates all applicable anti-icing and 10th stage bleeds combinations.
NOTE
If ice accumulation is suspected on unprotected surfaces, then reduce
the maximum landing weight values derived from Figure 07−04A−1 by
800 kg (1,764 lb).
Example: ANTI-ICE ON
Associated Conditions:
Temperature = −8° C
Airport pressure altitude = 4,000 ft
Cowl anti-ice = On
10th stage bleeds = Closed
As shown in the example Figure 07−04A−1, Anti-ice On), the maximum landing weight limited
by climb requirements is 24,100 kg (53,131 lb). The landing weight in this case is greater than
the maximum approved landing weight (Refer to Chapter 2; LIMITATIONS – STRUCTURAL
WEIGHT) and is not considered limiting.
Example: ANTI-ICE OFF
Associated Conditions:
Temperature = 27° C
Airport pressure altitude = 4,000 ft
Wing and cowl anti-ice = Off
10th stage bleeds = Closed
As shown in the example Figure 07−04A−1, Anti-ice Off), the maximum landing weight limited
by climb requirements is 23,700 kg (52,250 lb). The landing weight in this case is greater than
the maximum approved landing weight (Refer to Chapter 2; LIMITATIONS – STRUCTURAL
　
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