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to display the STALL WARN ADVANCE
mode of operation.
NOTE
Only pilot action can return the SPS from advance mode to normal
mode.
Pilot command interface on EMS/CDU:
· Command mode change from the control page.
· Either pilot’s EMS/CDU can command mode changes.
NOTE
The pilot cannot override advanced mode for detected failures.
Advanced mode indication on EICAS and EMS/CDU:
· “STALL WARN ADVANCE” EICAS advisory message.
· “ADVANCE” on EMS/CDU.
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−56
STALL SYSTEM PILOT ACTIVATED TEST (ON GROUND ONLY)
Effectivity:
· Airplanes 9002 thru 9122 not incorporating Service Bulletin:
· SB 700−24−045, AC and DC Power Distribution − Unit Change and Activation of Build 4
Electrical System.
STALL SYSTEM PILOT ACTIVATED TEST
The pilot activated test is initiated by the pilot during preflight.
It takes approximately 20 seconds to
complete the test. The test is initiated through the EMS/CDU. Refer to Chapter 7 ELECTRICAL
SYSTEM for the pilot activated testing procedure.
SWITCH CONTROL 1/1
TEST
OFF
STALL TEST
AURAL WARNING TEST 2
FIRE TEST
AURAL WARNING TEST 1 OFF
OFF
STALL TEST:
button to initiate test. Test duration
Press the STALL TEST activation
approximately 20 seconds.
LAMP TEST 1 OFF
LAMP TEST 2 OFF
GF1010_070
The pilot activated test will accomplish the following:
· Checks each shaker individually.
· Checks audio and visual warnings.
· Activates and monitors pitch disconnect lock for proper operation.
· Checks pusher for activation only under correct conditions (computer logic).
· Simulates a stall event and verifies AOA serviceability electronically (no AOA movement).
· Pushes both columns forward at the end of test.
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−57
STALL SYSTEM PILOT ACTIVATED TEST (ON GROUND ONLY) (CONT'D)
Stall Protection Computer
A dualchannel
stall protection computer (avionics bay) monitors the following inputs:
· LH, RH Angleofattack
(AOA) transducers − Angle of attack
· LH, RH Lateral accelerometers − Lateral acceleration
· LH, RH Flap/slat − Flap/slat position
· #1, #2 weight on wheels (WOW) − WOW and SPS inhibit
· #1, #2 and #3 ADC, MACH Transducer − Airspeed, altitude and Mach
· Inertial Reference Unit (IRU) − Normal and lateral acceleration
· WOW Fail − Weight on wheels
The SPC receives data input from the bleed management controller, landing gear electronic
control unit, heater brake monitor unit and EMS CDU through the data acquisition units. The
EGPWS uses the AOA for windshear requirements.
Low speed awareness output is a function of the SPC to the Electronic Flight Instrument System
(EFIS).
· Red line − Shaker or stall warning speed.
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−58
STALL PROTECTION COMPUTER SCHEMATIC
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−59
STALL PROTECTION EICAS MESSAGES
STALL PROTECT FAIL
STALL WARN ADVANCE
STALL WARN BASIC
PITCH DISC FAULT
MACH XDUCER FAIL
SHAKER 12
FAIL
SHAKER 12
FAIL
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−60
CB - FLT CONTROLS SYSTEM
STAT SYS BUS PREV CNTL TEST
PAGE
NEXT
PAGE
EMER
CNTL
BUS
CIRCUIT BREAKER − SYSTEM 1/2
CIRCUIT BREAKER SYSTEM
AFCS
AIR COND/PRESS
APU
BLEED
CAIMS
COMM
DOORS
ELEC
ENGINE
FIRE
FLT CONTROLS
FUEL
BRT
CB − FLT CONTROLS SYSTEM 1/4
CB − FLT CONTROLS SYSTEM 2/4
CB − FLT CONTROLS SYSTEM 3/4
CB − FLT CONTROLS SYSTEM 4/4
FLIGHT CONTROLS
EMS CIRCUIT PROTECTION
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−20−1
FLIGHT CONTROLS
EMS CIRCUIT PROTECTION
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−20−2
　
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