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AOA probes

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AOA display and approach indexer

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Stall warning computers

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Pilot and copilot control column shaker motors

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Stall barrier system

AOA becomes fully functional as the aircraft becomes airborne, i.e., when
the nutcracker shifts to the AIR mode. The control column shaker, however,
is disabled for the first five seconds following rotation to eliminate nuisance
activity. Pulling the SHAKER #1 and / or SHAKER #2 circuit breakers, as
appropriate, is the only way to disable a control column shaker in flight;
however, such action completely disables the associated stall warning
computer(s). System design is such that either stall warning computer is
capable of operating the control column shaker and control column pusher
should the other computer become disabled.

(1) AOA Probes:

An AOA probe / transducer assembly is installed on the left and right
forward fuselage. The cone-shaped probes freely rotate in the
airstream to provide AOA reference data for the stall warning / stall
barrier systems and AOA display data for the flight crew. The left
AOA probe provides data the No. 1 stall warning computer while the
right AOA probe provides data the No. 2 stall warning computer.
Heating elements prevent ice accumulation on the probe and
condensation within the transducer case.

(2) AOA Display and Approach Indexer:

AOA display data supplied by the probes includes the normalized
AOA display and the approach indexer. Normalized AOA display is
shown on the lower left portion of the Primary Flight Display (PFD)
and consists of a vertical scale marked from 0.2 to 1.1 in 0.1
increments. At the bottom of the scale is a three-digit display
surrounded by a pointer that provides AOA indication within a 0.01
resolution. As AOA changes, the display / pointer moves up and
down to correspond with the indication on the scale.

An AOA approach indexer on either side of the windshield center
post indicates the optimum AOA for approach and landing. The No.
1 AOA system drives the pilot’s indexer while the No. 2 AOA system
drives the copilot’s indexer. During approach and landing, the AOA
system illuminates each indexer’s red chevron if AOA is too high, a
green circle if AOA is correct or an amber chevron if AOA is too low.

(3) Stall Warning Computers:

The No. 1 and No. 2 stall warning computers receive the following
inputs and then provide outputs to the control column shaker motors
and stall barrier system:

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AOA reference data from the associated probes

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Altitude data from the DADCs

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Nutcracker mode from the nutcracker relays

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Flaps position from the 39° flap relay

(4) Control Column Shaker Motors:

OPERATING MANUAL

PRODUCTION AIRCRAFT SYSTEMS

2A-27-00

Page 11

January 31/02

Revision 6

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Содержание IV

Страница 1: ...light controls shown in Figure 1 include flaps ground spoilers and speedbrakes These flight controls are hydraulically powered and electrically or mechanically controlled The mechanically operated horizontal stabilizer moves in conjunction with the flaps to maintain longitudinal trim An Angle of Attack AOA system provides outputs to the control column shakers control column pusher approach indexer...

Страница 2: ...OPERATING MANUAL THIS PAGE IS INTENTIONALLY LEFT BLANK PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 2 January 31 02 ...

Страница 3: ...GIV Flight Controls Aerodynamic Axes Figure 1 OPERATING MANUAL 2A 27 00 Page 3 4 January 31 02 ...

Страница 4: ...GIV Flight Controls Fluid Power Diagram Figure 2 OPERATING MANUAL 2A 27 00 Page 5 6 January 31 02 ...

Страница 5: ...ontrol column pusher approach indexers normalized AOA display and stall barrier system The control column shakers provides early warning of a stall scenario by vibrating the control column before the stall while the control column pusher automatically initiates lowering the nose if the stall is imminent On CAA certified aircraft a flight control automatic failure detection system compares control ...

Страница 6: ...low airspeeds C Hydraulic Boost System The elevator actuator is a dual tandem actuator consisting of two pistons secured to a common shaft The pistons move inside a common cylinder divided to create two separate cylinders One cylinder receives Flight hydraulic system pressure while the other cylinder receives Combined hydraulic system pressure Mechanical movement of the actuator input lever moves ...

Страница 7: ...power shutoff valve With the valve closed operating pressure is removed from the actuator allowing the piston to idle The resultant advantage of the flight power shutoff provision is the ability to bypass a malfunctioning actuator such as would be the need in the unlikely event of an actuator jam and manually fly the aircraft Although control column effort and response time to inputs are increased...

Страница 8: ...ormally checked by the flight crew on the first flight of the day during the Before Starting Engines checklist A check usually consists of running the elevator trim fully up then fully down using normal methods i e using both halves of the switch simultaneously This is followed by attempting to run the pitch trim using each half of the switch alone Any movement resulting from using either half of ...

Страница 9: ...ndensation within the transducer case 2 AOA Display and Approach Indexer AOA display data supplied by the probes includes the normalized AOA display and the approach indexer Normalized AOA display is shown on the lower left portion of the Primary Flight Display PFD and consists of a vertical scale marked from 0 2 to 1 1 in 0 1 increments At the bottom of the scale is a three digit display surround...

Страница 10: ...tuating cylinder As the cylinder extends it applies an input to the elevator actuator input sector This input causes the elevator actuator to drive the elevator trailing edges down the control column drives forward accordingly to approximately one inch forward of neutral When AOA has decreased more than one degree the stall barrier system disengages The force generated by the stall barrier system ...

Страница 11: ...o activate the control column pusher NOTE Another momentary push of the TEST function key may be required to ensure the AOA indicator is in the normal area prior to takeoff G Failure Detection System CAA Certified Aircraft Only A flight control automatic failure detection system monitors flight control inputs from the control columns and compares them to the elevator actuator outputs If the system...

Страница 12: ...RRIER 1 CPO A 9 Essential DC Bus STALL BARRIER 2 CPO B 9 R Main DC Bus STALL WARN CMPTR 1 CPO A 11 Essential DC Bus STALL WARN CMPTR 2 CPO B 11 R Main DC Bus ELEV COMB HYD S O 1 CPO B 15 Essential DC Bus ELEV FLT HYD S O 1 CPO A 15 Essential DC Bus ELEV TRIM TAB ACTR HTR 2 CP L 9 L Main AC Bus φC NOTE S 1 CAA certified aircraft only 2 SN 1380 subs SN 1000 1379 having ASC 342 B Warning Red Messages...

Страница 13: ...Attack AOA may be used as reference but does not replace airspeed as the primary reference 2 Indication Parameters AOA indication must be within white band once forward airspeed is attained during takeoff roll 3 Use As A Speed Reference AOA shall not be used as a speed reference for takeoff rotation B Stall Barrier Stall Warning 1 Takeoff Requirements Both stall warning stall barrier systems must ...

Страница 14: ...1 000 ft D Mach Trim Electric Elevator Trim Inoperative Speed With both mach trim compensators inoperative or electric elevator trim inoperative the maximum operating limit speed is 0 75 MT OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 16 January 31 02 Revision 6 ...

Страница 15: ...Pitch Flight Control System Simplified Block Diagram Figure 3 OPERATING MANUAL 2A 27 00 Page 17 18 January 31 02 ...

Страница 16: ...Stall Barrier Angle of Attack Wiring Schematic Figure 4 OPERATING MANUAL 2A 27 00 Page 19 20 January 31 02 ...

Страница 17: ...Pitch Trim Controls Figure 5 OPERATING MANUAL 2A 27 00 Page 21 22 January 31 02 ...

Страница 18: ...Stall Barrier Angle of Attack Controls and Indications Figure 6 OPERATING MANUAL 2A 27 00 Page 23 24 January 31 02 ...

Страница 19: ...Control Columns Figure 7 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 25 January 31 02 Revision 6 ...

Страница 20: ...FLIGHT POWER SHUT OFF Handle Figure 8 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 26 January 31 02 Revision 6 ...

Страница 21: ...Yaw Damper Pitch Trim Control Panel Figure 9 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 27 January 31 02 Revision 6 ...

Страница 22: ...Stall Barrier Simplified Block Diagram Figure 10 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 28 January 31 02 Revision 6 ...

Страница 23: ...Stall Barrier Angle of Attack Warning Parameters Figure 11 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 29 January 31 02 Revision 6 ...

Страница 24: ...ransparent to the flight crew and can be made simultaneously with other inputs from the flight crew On CAA certified aircraft a flight control automatic failure detection system compares rudder pedal inputs to rudder actuator outputs If a malfunction is detected the system shuts off either or both hydraulic power sources to the actuator The yaw flight control system consists of the following subsy...

Страница 25: ... actuator servo control valve through an input crank arm C Hydraulic Boost System See Figure 12 The rudder actuator is a dual tandem actuator consisting of two pistons secured to a common shaft The pistons move inside a common cylinder divided to create two separate cylinders One cylinder receives Flight hydraulic system pressure while the other cylinder receives Combined hydraulic system pressure...

Страница 26: ...f the flight power shutoff provision is the ability to bypass a malfunctioning actuator such as would be the need in the unlikely event of an actuator jam and manually fly the aircraft Although rudder pedal effort and response time to inputs are increased while in manual reversion the aircraft remains capable of positive and harmonious control E Rudder Load Limiting System See Figure 12 Load limit...

Страница 27: ...ndency within the aircraft The system is referred to as a series mode system in that no feedback is provided through the rudder pedals The yaw damper system consists of a solenoid operated shutoff valve transfer valve servo ram and summing lever transducer Electrical power is supplied to the system through the Right Main and Essential 28 VDC buses Hydraulic power is supplied to the system by the F...

Страница 28: ... 10 units 7 5 NOSE R right of rudder deflection from the neutral position H Failure Detection System CAA Certified Aircraft Only A flight control automatic failure detection system monitors flight control inputs from the rudder pedals and compares them to the rudder actuator outputs If the system detects a failure it automatically shuts off hydraulic pressure to the actuator and triggers the appro...

Страница 29: ... the rudder actuator SNGL RUDDER LIMIT Failure of input pressure load limiter with Flight and Combined Hydraulic System pressure normal YAW DAMPER OFF Yaw damper YAW DAMP ENG DISENG switch is OFF OR Yaw damper failure NOTE S 1 CAA certified aircraft only C Advisory Blue Messages and Annunciations CAS Message Cause or Meaning RUDDER LIMIT Rudder actuator torque limiter is in operation 4 Limitations...

Страница 30: ...ion must be ON during all flight operations except as provided for in Section 05 03 40 Mach Trim Compensation Failure 2 If mach trim compensation failure is coupled with yaw damper failure When mach trim compensation failure is coupled with yaw damper failure observe speed limitations for both failures and limit altitude to 41 000 ft OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 36 Ja...

Страница 31: ...Yaw Flight Control System Simplified Block Diagram Figure 12 OPERATING MANUAL 2A 27 00 Page 37 38 January 31 02 ...

Страница 32: ...Rudder Pedals Forward Linkage Figure 13 OPERATING MANUAL 2A 27 00 Page 39 40 January 31 02 ...

Страница 33: ...Yaw Trim Roll Trim Control Wheels Figure 14 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 41 January 31 02 Revision 6 ...

Страница 34: ...in flush to the wing as the opposite aileron travels downward Spoiler travel varies in proportion to the degree of the roll to maximum extension of 26 2 55 4 3 with speed brakes extended The flight spoiler system is solely a hydraulically powered system thus reversion to manual control is not possible A roll trim system is used to position a trim tab attached to the trailing edge of the left ailer...

Страница 35: ...r consisting of two pistons secured to a common shaft The pistons move inside a common cylinder divided to create two separate cylinders One cylinder receives Flight hydraulic system pressure while the other cylinder receives Combined hydraulic system pressure Mechanical movement of the actuator input lever moves the servo control valve from its neutral position The servo control valve then direct...

Страница 36: ...l control If the speed brakes are extended the flight spoilers extend up to a maximum of 55 4 3 As the aileron control mechanism commands an aileron to deflect upward the mixing linkage transmits an extend command to the flight spoiler actuator control valve through push pull rods bellcranks and cables The control valve then shifts to direct pressure to the flight spoiler actuator The normally ext...

Страница 37: ...reased control inputs being applied by the flight crew If these control inputs exceed approximately 20 pounds the force link limit switch closes to energize an associated time delay relay If the time delay relay remains energized for more than second it energizes a shutoff relay The shutoff relay in turn powers the actuator s Combined and Flight hydraulic system shutoff valves to the closed positi...

Страница 38: ...4 Limitations There are no limitations established for the roll flight control system at the time of this revision OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 46 January 31 02 Revision 6 ...

Страница 39: ...Roll Flight Control System Simplified Block Diagram Figure 15 OPERATING MANUAL 2A 27 00 Page 47 48 January 31 02 ...

Страница 40: ...ue shafts preventing whiplash as they rotate B Torque Limiter A torque limiter is installed at the input side of the central gearbox If the gearbox dwell box or stabilizer actuator should jam or fail the torque limiter spring jams to lock the torque shafts This stalls the central gearbox hydraulic motor stopping further flap and horizontal stabilizer movement If a torque shaft fails the flaps are ...

Страница 41: ...idence and FLAP STAB indicator position relative to flap position is outlined in the following table FLAP POSITION FLAP STAB INDICATOR STABILIZER ANGLE OF INCIDENCE 0 UP UP 1 leading edge down 10 T O 2 2 leading edge down 20 T O APPR APP 3 2 leading edge down 39 DOWN LDG 4 6 leading edge down A limit switch below the stabilizer position transmitter provides a warning if the stabilizer fails to mov...

Страница 42: ...Horizontal Stabilizer System Simplified Block Diagram Figure 16 OPERATING MANUAL 2A 27 00 Page 51 52 January 31 02 ...

Страница 43: ...Flaps Horizontal Stabilizer System Controls and Indications Figure 17 OPERATING MANUAL 2A 27 00 Page 53 54 January 31 02 ...

Страница 44: ...andle located on the copilot s right console Flap position is displayed on the FLAP STAB position indicator located on the copilot s skirt panel Extending the flaps normally results in a nose pitch down movement as the flaps increase wing lift To compensate for nose pitch down the horizontal stabilizer leading edge moves down corresponding to flap extension Horizontal stabilizer operation is descr...

Страница 45: ...s the valve is energized open to allow fluid flow to the selector valve If an asymmetrical flap condition occurs the flap asymmetry switches open the flap control relay to de energize the flap shutoff valve and stop hydraulic pressure flow to the flap selector valve Flap movement ceases at this point C Flap Selector Valve The solenoid operated flap selector valve directs hydraulic pressure flow to...

Страница 46: ...eased to allow flap retraction F Flap Follow Up Switches Twelve follow up switches actuated by a cam on the central gearbox open and close as the flaps extend and retract Once the flaps reach a selected position the cam opens one of the switches to control the flaps and provide signals to other systems that require flap position information Six of the twelve switches S1 through S6 control flap pos...

Страница 47: ...an unsafe configuration is detected A red ACFT CONFIGURATION warning message will be displayed on CAS along with the associated warning tone whenever the following conditions exist Extending the flaps to DOWN 39 in flight with the SPEED BRAKE handle not in the RETRACT detent Extending the landing gear in flight with the SPEED BRAKE handle not in the RETRACT detent Advancing either power lever abov...

Страница 48: ... the appropriate side of the hydraulic motor As the hydraulic motor turns it drives the flaps in the desired direction through the central gearbox torque shafts and screwjacks The central gearbox at the same time also drives the horizontal stabilizer to the desired setting to maintain longitudinal stability When the flaps reach the desired position the follow up switch opens breaking the circuit t...

Страница 49: ...E S 1 For SPZ 8400 equipped aircraft having ASC 69A Flap Asymmetry Indicator Installation Annunciation Cause or Meaning FLAP ASYM indicator under FLAP STAB position indicator illuminated amber 1 Flap position asymmetry detected Flaps have stopped moving toward selected position NOTE S 1 For SPZ 8000 aircraft having ASC 69A Flap Asymmetry Indicator Installation 4 Limitations A Maximum Landing Flaps...

Страница 50: ...Flaps Simplified Block Diagram Figure 18 OPERATING MANUAL 2A 27 00 Page 61 62 January 31 02 ...

Страница 51: ...Flaps Simplified Electrical Diagram Figure 19 OPERATING MANUAL 2A 27 00 Page 63 64 January 31 02 ...

Страница 52: ...Flaps Horizontal Stabilizer System Hydraulic Control Diagram Figure 20 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 65 January 31 02 Revision 6 ...

Страница 53: ...Configuration Warning System Simplified Electrical Diagram Figure 21 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 66 January 31 02 Revision 6 ...

Страница 54: ... six spoiler panels extend automatically extend on touchdown to dump lift and increase braking effectiveness functioning as ground spoilers Panel function and position is summarized in the following table INPUT CONDITION PANEL POSITION Maximum Aileron No Speed Brakes Two Down Wing Flight Spoilers Extended 23 All Other Panels Retracted Maximum Speed Brakes No Aileron All Six Panels Extended 26 Maxi...

Страница 55: ...to the actuator piston The pistons extends and the attached mechanical linkage drives all six spoiler panels to a position commensurate with SPEED BRAKE handle position Speed brake position is infinitely variable between fully retracted 0 and fully extended 26 2 depending on handle position With speed brakes extended rotation of the control wheel repositions the mechanical linkage between the aile...

Страница 56: ...are retracted by selection of the GND SPLR switch to OFF Switch selection to OFF also causes a blue GND SPOILER UNARM advisory message to be displayed on CAS NOTE The GND SPLR switch is normally selected to ARMED on lineup before takeoff If either power lever is advanced above idle after the spoilers are armed the electrical circuit to the primary and secondary solenoid operated hydraulic control ...

Страница 57: ... hydraulic signal that overrides any input to the servo valve through the SPEED BRAKE handle The override signal is supplied by Combined or Utility or Auxiliary hydraulic pressure to both actuators through normally closed solenoid valves Since the override signal is common to both the left and right actuators the possibility of asymmetrical extension is virtually eliminated In the unlikely event t...

Страница 58: ...id operated hydraulic control valve nutcracker relay No 6 Failure of the secondary solenoid operated hydraulic control valve nutcracker relay No 1 Additionally the red GND SPOILER warning message will be displayed should any of the following events occur while on the ground Primary solenoid operated hydraulic control valve failure with the power levers not in ground idle Unlocked ground spoiler wi...

Страница 59: ...out of idle f Retard the left power lever to idle Verify the following indications Ground spoilers remain stowed visually check NO GND SPOILERS light is extinguished GND SPOILER warning message is not displayed on CAS g Select the GND SPLR switch to OFF Verify the following indications GND SPOILER UNARM advisory message is displayed on CAS h Press and hold the GND SPLR TEST switch See Notes 2 and ...

Страница 60: ...he cockpit The correct GND SPOILER message and NO GND SPOILERS light indications are sufficient for satisfactory preflight functional verification D Flight Power Shutoff System The flight power shutoff valve is a mechanically operated shutoff valve located between the Combined and Flight hydraulic system pressure sources and the flight and ground spoiler actuator pressure lines The valve consists ...

Страница 61: ...andle SPEED BRAKE Handle Landing Gear Control Handle GND SPOILER GND SPOILER Failure of ground spoiler component or deployed ground spoiler panel Annunciation Cause or Meaning Red NO GND SPOILERS light on windshield center post Failure of ground spoiler component or deployed ground spoiler panel C Advisory Blue Messages and Annunciations CAS Message Cause or Meaning GND SPOILER UNARM Ground spoile...

Страница 62: ...rsers are not used for landing See Section 05 17 50 Landing With Standby Electrical Power System Operating B Other Operational Information 1 Speed Brake Operating Envelope Speed brake operation is permitted within the flight envelope up to and including VMO MMO 2 Speed Brake Operating Altitude The use of speed brakes at altitudes below 2 000 feet AGL is not recommended 3 Effects of Speed Brake Ope...

Страница 63: ...OPERATING MANUAL THIS PAGE IS INTENTIONALLY LEFT BLANK PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 76 January 31 02 ...

Страница 64: ...Spoiler Control System Simplified Electrical Diagram Figure 22 OPERATING MANUAL 2A 27 00 Page 77 78 January 31 02 ...

Страница 65: ...Spoiler Speed Brake Controls and Indications Figure 23 OPERATING MANUAL 2A 27 00 Page 79 80 January 31 02 ...

Страница 66: ...Ground Spoiler Controls and Indications Figure 24 OPERATING MANUAL 2A 27 00 Page 81 82 January 31 02 ...

Страница 67: ...Spoiler Speed Brake Control System Simplified Block Diagram Figure 25 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 83 January 31 02 Revision 6 ...

Страница 68: ...sition and the elevator to the trailing edge down position allows the gust lock to engage and lock the flight controls as their linkages reach the locking position Releasing the trigger and then lowering the GUST LOCK handle releases the gust lock Safety features prevent the gust lock from inadvertently engaging or a failure of the system preventing gust lock release With the gust lock released th...

Страница 69: ...n wind gusts up to 60 knots CAUTION ENSURE HYDRAULIC PRESSURE IS DEPLETED PRIOR TO ENGAGING GUST LOCK CYCLE THE CONTROLS WITH THE CONTROL COLUMN CONTROL WHEEL AND RUDDER PEDALS TO DEPLETE ANY RESIDUAL PRESSURE OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 85 January 31 02 Revision 6 ...

Страница 70: ...GUST LOCK Handle Figure 26 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 86 January 31 02 Revision 6 ...

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