Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

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Page 7-3
Pilot’s Operating Manual
Revision A2: Nov, 2004
Sub-section 7
STALL WARNING/IDENTIFICATION
Hawker 800XP Pro Line 21
Section III - SYSTEMS DESCRIPTION
GENERAL
NOTE: This section applies to 800XP Pro Line 21 airplanes prior to Serial No. 258675.
For airplanes Serial Nos. 258675 and subsequent, refer to Section VIII SUPPLEMENTS for
Supplement P/N 140-590032-0041.
A stall warning and identification system is provided to emphasize the airplane’s natural cues available
at the point of stall.
The system functions are
• Stick shaker (warning)
• Stick pusher (identification)
The system consists of
• Two sensing channels, each utilizing an airflow angle sensor vane.
• Two Signal Summing Units (SSUs).
• Two stick shaker motors.
• A hydraulic operated actuator with two electro-hydraulic valves.
• A third sensing channel, which utilizes pitot pressure from the right pitot head, static pressure from
the forward static plates and stall vent pressure from the left and right stall vents.
• A stall identification sensor.
• Annunciators and test switches.
SYSTEM LOGIC
1. It is impossible for a stick push to occur before a stall warning (stick shake).
2. No single active fault of an SSU or relay can cause the operation of a stall valve or the associated
red STALL VALVE annunciator.
3. The autopilot is disengaged when a stall warning signal is initiated. This prevents the autopilot from
attempting to counteract the resulting stick shake operation or a subsequent stick push.
CONTROLS and ANNUNCIATIONS
System faults are indicated on two groups of amber annunciators, one per pilot.
Three STALL switches are located in the TEST section of the overhead roof panel. Anti-icing heating of
the airflow sensor vanes is controlled from the PITOT/VANE HEAT switches.
Indication of failure of the vane heaters is provided by the two amber L and R VANE HTR FAIL
annunciators also located on the overhead roof panel and by the ICE PROT repeat annunciator on the
MWS panel.
There are no control switches, the stall warning part of the system becomes armed on takeoff
(no weight-on-wheels), while the stall identification part of the system becomes armed 6 seconds after
takeoff.