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Braking System (HMAB) airplanes, the parking brake must be released.
1. AUX PUMP OFF / ARM Switch................................................ARM
2. Pilot’s Brake Pedals........................................................ DEPRESS
3. Pressure Readings.........................................................OBSERVE
A. AUX Pump Pressure ........................................ 3000 (±300) PSI
B. Applied Brake Pressure.......APPROPRIATE TO DEFLECTION
4. Pilot’s Brake Pedals.........................................................RELEASE
5. AUX Pump Pressure ............................................. 3000 (±300) PSI
6. AUX PUMP OFF / ARM Switch.......................................NOT ARM
7. Pressure Readings.........................................................OBSERVE
A. AUX Pump Pressure .........................................................ZERO
B. Applied Brake Pressure.....................................................ZERO
8. AUX PUMP OFF / ARM Switch................................................ARM
9. Copilot’s Brake Pedals ................................................... DEPRESS
10. Pressure Readings.........................................................OBSERVE
A. AUX Pump Pressure ........................................ 3000 (±300) PSI
B. Applied Brake Pressure.......APPROPRIATE TO DEFLECTION
11. Copilot’s Brake Pedals ....................................................RELEASE
12. AUX Pump Pressure ............................................. 3000 (±300) PSI
For BBW airplanes, perform Steps 13 and 14. For HMAB
airplanes, omit Steps 13 and 14 and proceed to Step 15.
NOTE: Airplane speed should be less than 12 knots for this test.
13. BRAKE TEST Switch ..................................................... DEPRESS
14. Annunciations .................................................................OBSERVE
A. Switch Legend (IN TEST)............ILLUMINATED (3 SECONDS)
B. CAS Messages........................ DISPLAYED, THEN REMOVED
• ANTISKID FAIL (Amber) • BRAKE PEDAL (Amber)
• BRAKE FAIL (Amber) • BRAKE MAINT REQ’D (Blue)
Continued on next page →
Quick Reference Handbook
NORMAL PROCEDURES REVISION 7
Page NH - 6 May 30/02
For HMAB airplanes, perform Steps 15 and 16:
NOTE: Airplane speed should be less than 12 knots for this test.
NOTE: On HMAB airplanes, the AUX pump must be momentarily de-armed
to stop AUX pump operation.
15. ANTI SKID TEST Switch ............................DEPRESS AND HOLD
16. Annunciations................................................................. OBSERVE
A. Switch Legend (IN TEST) ...........ILLUMINATED (3 SECONDS)
B. CAS Messages ........................DISPLAYED, THEN REMOVED
• ANTISKID FAIL (Amber) • BRAKE MAINT REQ’D (Blue)
• BRAKE FAIL (Amber)
END
Elevator Trim System Check OM 2A-27-20
Located on the pilot’s flight panel, the PITCH TRIM ENG / DISENG
switch engages or disengages the electric pitch trim. Pitch trim is also
engaged whenever the autopilot is engaged. With electric pitch trim
engaged (amber DISEN switch legend extinguished), pitch trim can be
adjusted through use of a split-half pitch trim switch installed on the
outboard grip of each control wheel.
Inadvertent actuation of pitch trim, including runaway, is minimized
through the split-half switch design. In order for the pitch trim to be
actuated, both halves of the switch must be simultaneously moved in
the same direction.
During the Before Starting Engines checklist on the first flight of the
day, run the elevator trim fully up and fully down using both halves of
the switch simultaneously. Next, attempt to run the pitch trim using
each half of the switch independently. Any movement resulting from
using either half of the switch independently indicates a malfunction
that should be corrected before flight. Finally, set pitch trim for the
takeoff Center of Gravity (CG) condition as determined using the
Recommended Elevator Trim Tab Settings for Takeoff table, page
NC-5.
END
Quick Reference Handbook
REVISION 7 NORMAL PROCEDURES
May 30/02 Page NH - 7
Ground Spoiler System Check OM 2A-27-70
The ground spoiler system is monitored by a warning circuit that will
detect certain in-flight and on-ground malfunctions within the ground
spoiler system, prompting the following annunciations:
• A red GND SPOILER warning message will be displayed on CAS
and, if installed, the SWLP, should a failure occur within the
ground spoiler system either while airborne or on the ground.
• A red NO GND SPOILERS warning light, located adjacent to the
　
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