Gulfstream G550 Operating Manual Download

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OPERATING MANUAL

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PRODUCTION AIRCRAFT SYSTEMS

2A-27-00

Page 94
August 14/03

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Summary of Contents for G550

Page 1: ...sets of rudder pedals are similarly mechanically linked together but both are connected to the rudder by a single cable For this reason there is no provision for interrupting the linkage between the two sets of pedals since each set does not have an independent route to the rudder The cable connections from the yokes and rudder pedals are continuous loop installations providing feedback to the mov...

Page 2: ... trim uses the hydraulic actuator to project the rudder slightly into the windstream in the desired direction to compensate for induced yaw The secondary flight controls and functions are Wing flaps enhance wing lift characteristics Flight and Ground Spoilers reduce wing lift and add overall drag Movable horizontal stabilizer aligns the elevator with aircraft angle of attack Yaw damper uses the au...

Page 3: ... AP Inhibit ADS Blue Inertial Reference System AP Inhibit IRS Blue Control Column Force AP Inhibit Left Column Blue Control Column Force AP Inhibit Right Column Blue Control Wheel Force AP Inhibit Left Wheel Blue Control Wheel Force AP Inhibit Right Wheel Blue Manual Trim Wheel AP Inhibit Man Trim Active Blue Autopilot Quick Disconnect Switch AP Inhibit QD Blue Stall Shaker AP Inhibit Stall Blue A...

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Page 5: ...Flight Controls System Simplified Fluid Power Diagram Figure 1 OPERATING MANUAL 2A 27 00 Page 5 6 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 7: ...Flight Controls System Components Figure 2 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 7 August 14 03 Title Page Prev Page Next Page TOC ...

Page 8: ... sides of the hydraulic actuators are monitored to assure correct operation The cockpit cable input motion must result in a corresponding actuator output motion and similarly the output side of the actuator should not move without cockpit input If input and output do not correspond actuator hydraulic pressure is bypassed to prevent movement of the elevator Anytime hydraulic pressure to the actuato...

Page 9: ...arm is positioned with a defined amount of clearance between the plunger type switches Under normal conditions the bracket holding the switches moves with elevator command input and the cam arm moves with the elevator hydraulic actuator output so the clearance between the switches and the arm is maintained If a malfunction occurs and the elevator moves opposite to or further from the commanded dir...

Page 10: ... hydraulic actuator will continue to function using the remaining hydraulic system The operation of the hydraulic shut off valves by the HOPS is signaled to the MAUs left elevator to MAU 1 right elevator to MAU 2 over ARINC 429 connections The shut off condition is monitored by the MWS and a CAS message corresponding to the condition is displayed on the CAS window If either or both hydraulic syste...

Page 11: ...ioning elevator linkage the yokes may be reconnected by pushing in on the disconnect handle when the yokes are aligned provided that the power assist disconnect was not used A reset of the yoke torque tube coupling is not possible without special maintenance tools after activation of the power assist disconnect C Pitch Trim System See Figure 4 through Figure 6 Each elevator has a trim tab installe...

Page 12: ... trim The yoke trim switches are composed of split halves Both halves must be moved in the same direction to move the elevator trim The split switch design helps to prevent accidental trim input The switches are wired to an electric servomotor that is located in the tail of the aircraft and incorporated into the cable linkage to the trim tabs An electric signal from a cockpit trim switch results i...

Page 13: ...t elevator pitch control Circuit Breaker Name CB Panel Location Power Source ELEV SERVO 1 POP D 4 L ESS DC Bus ELEV SERVO 2 CPOP D 4 R ESS DC Bus PITCH TRIM SERVO 1 POP E 2 L ESS DC Bus PITCH TRIM SERVO 2 CPOP E 1 R ESS DC Bus L ELEV TRIM HEAT REER E 16 R MAIN AC Bus R ELEV TRIM HEAT REER F 16 R MAIN AC Bus LEFT ELEV HYD S O POP C 5 L ESS DC Bus RIGHT ELEV HYD S O CPOP C 5 R ESS DC Bus B Crew Aler...

Page 14: ...ch Trim Servos and MAUs Elevator Trim Up Limit Blue 4 Limitations A Mach Trim Electric Elevator Trim Functions 1 Use of Mach Trim Electric Elevator Trim Functions Mach trim electric elevator trim must be ON during all flight operations except as provided for in Section 05 02 40 Mach Trim Failure 2 With both Mach Trim Electric Elevator Trim Inoperative Mmo is reduced to 0 80MT OPERATING MANUAL PROD...

Page 15: ...Hard Over Prevention System HOPS Figure 3 Sheet 1 of 2 OPERATING MANUAL 2A 27 00 Page 15 16 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 17: ...Hard Over Prevention System HOPS Figure 3 Sheet 2 of 2 OPERATING MANUAL 2A 27 00 Page 17 18 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 19: ...Pitch Flight Controls System Controls and Indications Cockpit Center Pedestal Figure 4 OPERATING MANUAL 2A 27 00 Page 19 20 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 21: ...Electric Pitch Trim Engage Disengage Switch Controls and Indications Figure 5 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 21 August 14 03 Title Page Prev Page Next Page TOC ...

Page 22: ...Electric Pitch Trim Stall Barrier System Controls and Indications Figure 6 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 22 August 14 03 Title Page Prev Page Next Page TOC ...

Page 23: ...each to prevent structural damage to the rudder and vertical stabilizer The output end of the hydraulic actuator shaft is connected to linkages that move the rudder around the pivot point connections on the vertical stabilizer If one hydraulic system fails the regulator valve of the remaining system shifts to provide up to three thousand 3 000 psi to move the rudder Additionally in the event of du...

Page 24: ...n wheels to prolong system life If the active channel fails the standby channel will automatically assume yaw damper control The yaw damper function also provides a rudder input for aircraft turn coordination provided the flaps are not set to thirty degrees 30 or more The yaw damper will add up to five degrees 5 of rudder in the direction of turn without pilot rudder input Autopilot control of the...

Page 25: ...l switches are integrated into the rudder control linkage to provide a comparison reference for four switches mounted internally within the hydraulic actuator The external HOPS switches are noted on Figure 8 Of the four external switches two are for left hydraulic system reference and two are for right hydraulic system reference Of the two switches for each hydraulic system one provides a left rud...

Page 26: ...racket and hydraulic pressure would be shut off to the rudder actuator after a one half second delay If a hydraulic malfunction in a single system left or right side of the actuator moves the actuator shaft in a wrong direction only the hydraulic pressure of the malfunctioning system is shut off For instance in a stabilized rudder condition if the left hydraulic system piston attempts to move the ...

Page 27: ...eft system reservoir and there is no leak in the left hydraulic system lines connecting to the rudder actuator The AUX hydraulic pump located in the right main landing gear wheel well is powered by left essential DC bus and can provide three thousand 3 000 psi at a flow rate of two 2 gallons per minute Normally the AUX is used to actuate the flaps ground spoiler servos brakes and nose wheel steeri...

Page 28: ...lves Yaw Damper 1 2 Fail Amber YAW DAMP ENG DISENG Switch Yaw Damper Off Amber Autopilot YAW DAMP ENG DISENG Switch No YD Turn Coordination Blue MWS Software Aircraft Speed Rudder Position RVDT Rudder Limit Blue Rudder Hydraulic Shutoff Valves Single Rudder Blue Standby Rudder Switch AUX Pump Standby Rudder Hyd On Blue Yaw Damper Servo Valves YD 1 2 Power Fail Blue 4 Limitations A Yaw Damper Inope...

Page 29: ... VREF 147 160 29 000 VREF VREF 153 160 30 000 VREF VREF 158 160 31 000 VREF VREF 163 160 32 000 VREF VREF 168 160 33 000 VREF VREF 174 160 34 000 VREF VREF 179 160 35 000 VREF VREF 184 160 36 000 VREF VREF 189 160 37 000 VREF VREF 195 160 38 000 VREF VREF 200 160 39 000 VREF VREF 205 160 40 000 VREF VREF 211 160 41 000 VREF VREF 216 160 41 300 VREF VREF 217 160 OPERATING MANUAL PRODUCTION AIRCRAFT...

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Page 31: ...Rudder Control Cable Linkage Figure 7 OPERATING MANUAL 2A 27 00 Page 31 32 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 33: ...Control Cable Termination at Rudder Actuator Figure 8 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 33 August 14 03 Title Page Prev Page Next Page TOC ...

Page 34: ...Yaw Flight Controls System Controls and Indications Figure 9 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 34 August 14 03 Title Page Prev Page Next Page TOC ...

Page 35: ...Rudder Trim Controls Figure 10 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 35 August 14 03 Title Page Prev Page Next Page TOC ...

Page 36: ...left wing trailing edge deflects upward disrupting airflow over the wing and decreasing lift The left wing falls due to the decrease in lift on a portion of the wing A roll in the opposite direction is accomplished by reversing the direction of the aileron deflection creating the same circumstances on opposite wings The maximum aileron deflection is eleven degrees 11 up or down To increase the res...

Page 37: ...o the aileron hydraulic actuators The hydraulic actuators are located on the aft wing beam between the flaps and the ailerons The actuators boost manual or autopilot control inputs and position the ailerons in the commanded direction Each hydraulic actuator is powered by both hydraulic systems The actuators have a central shaft surrounded by a dual piston chamber Each chamber is powered by a dedic...

Page 38: ... initiates a signal to the hydraulic control valves of both left and right aileron hydraulic actuators to bypass system pressure If a resistance to control link input is present in the pull direction the spring and electrical contact at the end of the other section would operate in the same way to activate HOPS bypass of hydraulic pressure The electrical signal incorporates a one half second delay...

Page 39: ...leron down to increase lift on the right wing and move the wing up The range of travel for the aileron trim tab is 15 degrees up or down The aileron trim tab actuator has ceramic element that is heated to prevent the actuator from freezing The actuator is maintained at a constant temperature of 175 20 F The heater is controlled by the AIL TRIM HEAT circuit breaker on the Right Electronic Equipment...

Page 40: ...5 Up seven degrees 7 Up twenty eight degrees 28 Up eleven degrees 11 Up forty seven degrees 47 If the spoilers are in use as speed brakes all three spoiler panels on each wing can be extended up to thirty degrees 30 with commands from the speed brake control handle on the cockpit center pedestal If a turn is initiated with speed brakes extended the two outboard spoiler panels on the downward rolli...

Page 41: ...eron Hydraulic Actuators L R Aileron Hydraulics Off Amber Spoiler Control Switch Spoilers Hydraulic Off Amber Aileron Trim Tab RVDT and Autopilot Aileron Servos Retrim Left Wing Down Amber Aileron Trim Tab RVDT and Autopilot Aileron Servos Retrim Right Wing Down Amber 4 Limitations There are no limitations established for the aileron roll control system at the time of this writing OPERATING MANUAL...

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Page 43: ...Aileron Linkage and Actuators Figure 11 OPERATING MANUAL 2A 27 00 Page 43 44 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 45: ...Aileron and Spoiler Controls and Indications Figure 12 OPERATING MANUAL 2A 27 00 Page 45 46 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 47: ...ent is an electrically powered jackscrew that moves the leading edge of the stabilizer up and down The range of movement available for the horizontal stabilizer is 1 25 up to 4 6 down The jackscrew is driven by an electric actuator with two motor windings and incorporates a locking ratchet mechanism that prevents movement of the stabilizer if there is no electrical input to the AC drive motor The ...

Page 48: ...System FMS Actuator Input Output Processor AIOP modules in MAU 1 and 2 and the MWS processors in MAU 1 2 and 3 The MWS initiates the display of a CAS message indicating emergency stabilizer operation and provides the stabilizer position display on the Flight Controls 2 3 synoptic page and HSI on the PFD B Flap Control Unit FCU and Horizontal Stabilizer Operation The Flap and Stabilizer Controller ...

Page 49: ...owing additional airflow over the flap RVDTs are installed on the outer section of the flaps to provide position feedback information to the FCU Flap extension and retraction is controlled with the flap handle on the copilot side of the center console shown in Figure 16 Each flap extends back from the wing along four tracks with rollers attached to the flaps moving within the tracks The two middle...

Page 50: ...eration of the malfunctioning unit flaps or stabilizer is interrupted and through ARINC 429 connections to the MAUs the MWS generates the display of the appropriate CAS message s For instance if the FCU detects an asymmetry during the extension of the two wing flaps the FCU stops operation of the PDU and signals the condition to the MWS through the MAUs The MWS generates an amber Flap Asymmetry ca...

Page 51: ... Flap Control Unit Flap Command Invalid Amber Flap Control Unit Flaps Failed Amber Flap Control Unit Flap Stab Independent Op Amber Flap Control Unit Flap Stab Miscompare Amber Flap Control Unit Flap Stab Sync Fail Amber Flap Control Unit Stabilizer Failed Amber Flap Control Unit Uncommanded Flaps Amber Flap Control Unit Uncommanded Stabilizer Amber Flap Control Unit Flap Stab Maint Reqd A B Blue ...

Page 52: ...tions is restricted to takeoff approach and landing only Holding in icing conditions is limited to 0 flaps only Emergency Stabilizer Trim Maximum airspeed with the emergency stabilizer armed with the autopilot engaged and a jammed elevator is 270 KCAS M 80 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 52 August 14 03 Title Page Prev Page Next Page TOC ...

Page 53: ...Flap Horizontal Stabilizer System Block Diagram Figure 13 OPERATING MANUAL 2A 27 00 Page 53 54 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 55: ...Horizontal Stabilizer System Controls and Indications Figure 14 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 55 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 57: ...Wing Flaps System Figure 15 OPERATING MANUAL 2A 27 00 Page 57 58 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 59: ...Flap Handle Figure 16 OPERATING MANUAL 2A 27 00 Page 59 60 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 61: ... to be selected on for all flight operations unless a malfunction occurs during flight See Figure 18 3 Description of Subsystems Units and Components A Angle of Attack AOA Sensors Because an aircraft stall is an aerodynamic condition caused by separation of the boundary layer of airflow over the wing at high angles of attack AOA data is more accurate than airspeed in determining the onset of a sta...

Page 62: ...ack As airspeed slows the stick shaker threshold point is shown beside the airspeed tape as a red bar descending with airspeed from the shaker initiation point If airspeed is slowing at a rate that will soon reach the shaker initiation speed the airspeed trend vector indicator will change to amber If airspeed reaches the stick shaker threshold the digital airspeed readout and AOA display will chan...

Page 63: ...is biased out of the activation logic since large control inputs are not necessary at high airspeeds The stick pusher will deactivate the nose down input to the elevators when aircraft acceleration drops below 0 5 G or the actual wing AOA decreases 3 6 below the stick pusher activation threshold If a malfunction causes a spurious activation of the stick pusher a manual force on the control column ...

Page 64: ... CPOP E 5 Right Essential DC Bus B Crew Alerting System CAS Messages The following CAS messages are associated with the SWPS system Area Monitored CAS Message Message Color AOA Probe AOA Probe 1 2 Fail Amber SWPS function AOA Miscompare Amber SWPS function Stall Barrier 1 2 Amber SWPS function STALL BARR Switch Stall Barrier Off Amber SWPS function hydraulic actuator Stick Push 1 2 Fault Amber SWP...

Page 65: ...odified to no longer be inhibited when the autopilot disconnect switch is held in the IN position 4 Stick Pusher System Activation Logic The stick pusher system has been modified to not activate until both AOA vanes are at or above the push AOA 5 Stick Shaker Stick Pusher Threshold Ratio 00b7 The AOA stick shaker stick pusher threshold ratio has been modified to 0 9 when the Weight On Wheels WOW s...

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Page 67: ...Stall Warning Stick Pusher Block Diagram Figure 17 OPERATING MANUAL 2A 27 00 Page 67 68 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 69: ...STALL BARR Switch Figure 18 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 69 August 14 03 Title Page Prev Page Next Page TOC ...

Page 70: ...stem CAS message Diagrams of the spoiler system is included in Figure 19and Figure 20 The two hydraulic actuators are necessary to provide the multi purpose operation of the spoiler system The two outer spoiler panels on each wing operate in three 3 modes To assist the ailerons in aircraft roll control To actuate as speed brakes To actuate as ground spoilers The single inner spoiler panel on each ...

Page 71: ...spoiler hydraulic actuators are in turn mechanically linked to the flight spoiler actuators on each wing that position the middle and outboard spoiler panels The amount of spoiler panel deflection is dependent upon the position of the speed brake handle The handle may be moved to any range from the retract position to fully extended position with no detents in the handle range At the fully extende...

Page 72: ... system operation is the same as that in speed brake operation the hydraulic actuators use both left and right hydraulic system pressure reduced to fifteen hundred 1 500 psi to operate the inboard spoiler panels and the mechanical linkage to the outboard flight spoiler actuators commands operation of the two outboard panels on each wing All six wing panel spoilers extend to fifty five degrees plus...

Page 73: ...essed CAUTION A HARD LANDING THAT RESULTS IN A SIGNIFICANT BOUNCE WILL DEPLOY THE GROUND SPOILERS IF THE POWER LEVERS ARE MAINTAINED AT IDLE RESULTING IN A RAPID LOSS OF LIFT AND AIRSPEED DURING THE SUBSEQUENT TOUCHDOWN ADVANCING THE POWER LEVERS WILL RETRACT THE GROUND SPOILERS AND DECREASE THE SINK RATE IF THE AMOUNT OF RUNWAY REMAINING ALLOWS SAFE COMPLETION OF THE LANDING For automatic ground ...

Page 74: ...crease over forty seven knots 47 kts for the ground spoilers to deploy during an aborted takeoff C Malfunction Monitoring Landing and Takeoff When the automatic ground spoilers are armed for landing or for aborted takeoff protection the system is monitored by the MWS for correct performance The MWS verifies all of the control logic parameters senses uncommanded pressurization of the ground spoiler...

Page 75: ...e runway and one or both of the ground spoiler panels is not in the stowed position sensed by the contact switches the red Ground Spoiler CAS message will be displayed along with illumination of the Master Warning glareshield lights and aural warning tones The MWS will also generate a red Ground Spoiler warning if conditions are detected that could cause an uncommanded spoiler activation Areas sam...

Page 76: ...t Essential DC Bus GND SPLR CPOP E 2 Right Essential DC Bus LEFT WOW POP C 1 Left Essential DC Bus RIGHT WOW CPOP C 1 Right Essential DC Bus WHEEL SPEED POP C 3 Left Essential DC Bus THROT QUAD CPOP C 2 Right Main DC Bus B Crew Alerting System CAS Messages The following CAS messages indicate the status of the speed brake ground spoiler system Area Monitored CAS Message Message Color MAUs 1 and 2 S...

Page 77: ...th automatic ground spoilers inoperative provided the Anti Skid is operative 20 flaps are used and the cowl and wing anti ice systems are not used Dispatch with reference to MMEL If a touch and go landing is to be performed the GND SPLR must be OFF and manual spoiler landing distances must be taken into account OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 77 August 14 03 Title Page P...

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Page 79: ...Spoiler System Figure 19 Sheet 1 of 3 OPERATING MANUAL 2A 27 00 Page 79 80 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 81: ...Spoiler System Figure 19 Sheet 2 of 3 OPERATING MANUAL 2A 27 00 Page 81 82 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 83: ...Spoiler System Figure 19 Sheet 3 of 3 OPERATING MANUAL 2A 27 00 Page 83 84 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 85: ...Ground Spoiler Circuits Figure 20 OPERATING MANUAL 2A 27 00 Page 85 86 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 87: ...Spoiler System Controls Figure 21 OPERATING MANUAL 2A 27 00 Page 87 88 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 89: ...Spoiler System Indications Figure 22 OPERATING MANUAL 2A 27 00 Page 89 90 August 14 03 Title Page Prev Page Next Page TOC ...

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Page 91: ...loaded latch on the back of the handle must be depressed The spring latch prevents inadvertent engagement and also maintains engagement of the gust lock once selected The handle rotates aft from the horizontal disengaged position up to a ninety degree 90 vertical position when engaged in order provide a strong visual cue that the aircraft flight controls are locked B Flight Control Latches As the ...

Page 92: ... 3 Controls and Indications See Figure 23 There are no circuit breakers or CAS messages related to the gust lock 4 Limitations A Flight Manual Limitations There are no limitations for the gust lock system at the time of this writing OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 92 August 14 03 Title Page Prev Page Next Page TOC ...

Page 93: ...Gust Lock System Controls Figure 23 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 27 00 Page 93 August 14 03 Title Page Prev Page Next Page TOC ...

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