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2. Flaps ......................................................................................SET FOR LANDING
3. Emergency Batteries (EMERG POWER)........................................................ON
4. Ground Spoilers (GND SPLR) .......................................................................OFF
5. Power Setting...........................MAINTAIN 67% HP RPM UNTIL TOUCHDOWN
NOTE:
Once the airplane is on the ground, there is no need to
continue to maintain 67% HP RPM. The Standby
Electrical Power system should stay on line during
normal taxi maneuvers. If the Standby Electrical
Power system is interrupted, cycle the STANDBY
ELECTRICAL POWER switch (STBY ELEC) OFF,
then ON, to regain power.
6. Reverse Thrust................................................................................DO NOT USE
ON TOUCHDOWN:
7. Flight Spoilers ................MANUALLY DEPLOY SLOWLY (APPROXIMATELY 5
SECONDS)
8. Airplane .........................................................STOP USING NORMAL BRAKING
OPERATING MANUAL
05-17-00 EXPANDED ABNORMAL / EMERGENCY PROCEDURES
Page 4
October 11/02
Revision 8
INDICATING / RECORDING SYSTEM
05-18-10: Display Unit Failure
1. General:
The pilot’s flight instrumentation consists of two 8”×8” Cathode Ray Tube (CRT)
Display Units (DUs), DU 1 and DU 2. DU 1 displays the pilot’s Primary Flight
Display (PFD) and is used to present basic flight attitude, air data and flight
director information. It is located directly in front of the pilot’s control yoke. DU 2
normally displays the pilot’s Navigation Display (ND) and is used to present radio
navigation information, weather radar and FMS map/navigation information. DU 2
is located immediately inboard of DU 1.
The copilot’s instrumentation is similar, with DU 5 used for ND and located
immediately inboard of DU 6. DU 6 is used for the copilot’s PFD and is located
directly in front of the copilot’s control yoke.
DUs 3 and 4, mounted vertically on the centerline of the cockpit instrument panel,
are used for Engine Instrument (EI) display and Crew Alerting System (CAS)
display. DUs 3 and 4 together comprise the Engine Instrument and Crew Alerting
System (EICAS).
2. For SPZ-8000 Equipped Aircraft:
A. DU Switching Options:
In the event of a DU failure, the following switching options are available:
(1) NORM: Normal presentation
(2) PFD XFER: Display of PFD information on DU normally used as ND
(3) ND OFF: Blanks the ND
B. EICAS Switching Options:
EICAS switching options are:
(1) NORM: Normal presentation
(2) TOP CMPT: “Top Compacted” display of both Engine Instrument (EI)
display and Crew Alerting System (CAS) display on the upper DU
(DU 3).
(3) BOT CMPT: “Bottom Compacted” display of both Engine Instrument
(EI) display and Crew Alerting System (CAS) display on the lower
DU (DU 4).
C. DISPLAY SWITCHING Control Panel:
The DISPLAY SWITCHING control panel (upper section of the
Reversionary Controller), is located on the cockpit overhead panel. It
consists of three (3) rotary knobs, (PILOT, EICAS and COPILOT) which
permit the PFD, ND and EICAS selections listed above. There is no
capability to transfer PFD or ND information to the EICAS display, or vice
versa.
3. For SPZ-8400 Equipped Aircraft:
In the event of a DU failure, automatic switching of displays occurs to the next
available DU. Manual switching is also available with the following options:
A. Pilot Display (PFD and ND):
(1) NORM: Normal presentation
OPERATING MANUAL
EXPANDED ABNORMAL / EMERGENCY PROCEDURES 05-18-00
Page 1
May 30/02
Revision 7
(2) PFD: Display of PFD information on DU 2
(3) ENG / EICAS (With DU 3 Failed): Engine data is displayed on DU 2
(4) ENG / EICAS (With Both DU 3 and 4 Failed): “Compacted” display
of EICAS is displayed on DU 2
B. Copilot Display (PFD and ND):
(1) NORM: Normal presentation
(2) PFD: Display of PFD information on DU 5
(3) CAS / EICAS (With DU 4 Failed): Normal CAS display is displayed
on DU 5
(4) CAS / EICAS (With Both DU 3 and 4 Failed): “Compacted” display of
EICAS is displayed on DU 5
05-18-20: Symbol Generator Failure
Three (3) Symbol Generators (SGs) are used to generate all information appearing on all
six (6) Display Units (DUs). Each SG can generate Primary Flight Display (PFD),
Navigation Display (ND), Engine Instruments (EI) and Crew Alerting System (CAS)
display formats. SG switching determines which type of information is taken from a SG
for presentation on the proper set of DUs. Since any one (1) SG can generate all four (4)
　
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