Gulfstream Aerospace G550 Page 20 Operating Manual Download | Manualshive

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Summary of Contents for G550

Page 1: ...th a Data Management Unit DMU and Personal Computer PC interface for loading software data and performing maintenance analysis and testing All data flow within the PlaneView system is governed by a Digital Engine Operating System DEOS that provides space partitioning to ensure the memory integrity within all avionics functions and additionally provides the timing separation that allows multiple so...

Page 2: ...Flight Displays PFDs Navigation displays Crew Alerting System CAS messages Synoptic and System Window displays uploaded weather overlays and real time video from aircraft cameras EGPWS module provides all of the functionality of the Enhanced Ground Proximity Warning System and stores the terrain database Global Positioning System GPS modules interpret data received by the GPS antenna to compute ai...

Page 3: ...ng System CAS Messages The following CAS messages are associated with the MAUs Area Monitored CAS Message Message Color AGMs AGM 1 2 3 4 Fail Amber APMs APM 1 2 3 4 Fail Amber APMs APM Miscompare Amber MAU Fans MAU 1 2 3 Fan Fail Amber MAU MAU 1A 1B 2A 2B 3A 3B OVRHT Amber MAU MAU 1A 1B 2A 2B 3A 3B Fail Amber AGMs AGM 1 2 3 4 Fail Blue APMs APM 1 2 3 4 Fail Blue NOTE The listed caution messages ma...

Page 4: ...MAU 1 Figure 1 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 4 July 15 04 Title Page Prev Page Next Page TOC ...

Page 5: ...MAU 2 Figure 2 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 5 July 15 04 Title Page Prev Page Next Page TOC ...

Page 6: ...MAU 3 Figure 3 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 6 July 15 04 Title Page Prev Page Next Page TOC ...

Page 7: ... since the weight on wheels switch transitions from ground to flight mode Each chronometer receives power from the essential flight instrument bus and has replaceable batteries to ensure operation if aircraft power is interrupted Each installation has a two inch digital display containing the microprocessor controlled chronometer and incandescent lighting See Figure 4 3 Controls and Indications Se...

Page 8: ...Cockpit Clocks Figure 4 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 8 July 15 04 Title Page Prev Page Next Page TOC ...

Page 9: ...ct switch may be reset on the ground See the illustration in Figure 7 An underwater locator device see Figure 6 is attached to the DFDR to facilitate recovering the recorder if the aircraft is lost over water 2 Description of Subsystems Units and Components A Digital Flight Data Recorder FDR The DFDR records and stores digitized MAU data The data can be retrieved to assist in reconstruction of eve...

Page 10: ...ced on the FDR tape When the event switch is depressed the Central Maintenance Computer CMC saves a data block of information that spans from 30 seconds prior to switch activation and continues for one minute following release of the switch A blue Event Record advisory message is also displayed on the Crew Alerting System CAS 3 Controls and Indications See Figure 5 and Figure 8 A Circuit Breakers ...

Page 11: ...FDR Maintenance Ground Override Switch Figure 5 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 11 July 15 04 Title Page Prev Page Next Page TOC ...

Page 12: ...Flight Data Recorder FDR Underwater Locating Beacon ULB Figure 6 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 12 July 15 04 Title Page Prev Page Next Page TOC ...

Page 13: ...FDR Impact Switch Figure 7 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 13 July 15 04 Title Page Prev Page Next Page TOC ...

Page 14: ...FDR CMC EVENT Switch Figure 8 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 14 July 15 04 Title Page Prev Page Next Page TOC ...

Page 15: ...ion Control and Display Units MCDUs or through a Personal Computer PC connected to a sub D outlet on the Test and Monitor Panel The database transfer operations are described in Section 2B 23 00 If a fault is detected within the DMU DVD or PCMCIA card during the transfer operation the MCDU s will display a message associated with the fault A list of DMU fault messages is contained in Section 2B 34...

Page 16: ...Data Management Unit Figure 9 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 16 July 15 04 Title Page Prev Page Next Page TOC ...

Page 17: ...eplate with two push latches on either side of the printer 2 Controls and Indications A Printer Indications A horizontal row of indicators pushbuttons is installed on the upper face of the printer The legends within the indicators pushbuttons are arranged vertically and may require the operating crew member to view the text sideways The indicators and associated actions are OFF selects the printer...

Page 18: ... CAS messages associated with the cockpit printer D Limitations There are no limitations applicable to the cockpit printer as of this writing OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 18 July 15 04 Title Page Prev Page Next Page TOC ...

Page 19: ...Cockpit Printer Figure 10 OPERATING MANUAL 2A 31 00 Page 19 20 July 15 04 Title Page Prev Page Next Page TOC ...

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Page 21: ... flight report summarizing activity for each flight segment The CMC system is composed of the following subsystems Central Maintenance Computer module Digital Engine Operating System DEOS software helper application Remote terminal Loadable Diagnostic Information LDI database 2 Description of Subsystems Units and Components A Central Maintenance Computer module The CMC module is installed in slot ...

Page 22: ...r 1 FLAPSTAB 1 Flap Stab Controller 2 FLAPSTAB 2 Fuel Quantity Measuring System FQMS Nosewheel Steering NWS ASCB D Interface Protocol MEMBER SYSTEM NAME PNEUMONIC Actuator I O Command Function 1 AIOC 1 Actuator I O Command Function 2 AIOC 2 Actuator I O Monitor Function 1 AIOM 1 Actuator I O Monitor Function 2 AIOM 2 Advanced Graphics Module 1 AGM 1 Advanced Graphics Module 2 AGM 2 Advanced Graphi...

Page 23: ...re GIOM S6 Global Positioning System Function 1 GPS 1 Global Positioning System Function 2 GPS 2 Internal Reference Unit 1 IRU 1 Internal Reference Unit 2 IRU 2 Internal Reference Unit 3 IRU 3 MAU 1 NIC Module 1 Core MAU1 NIC1 MAU 1 NIC Module 2 Core MAU1 NIC2 MAU 2 NIC Module 1 Core MAU2 NIC1 MAU 2 NIC Module 2 Core MAU2 NIC2 MAU 3 NIC Module 1 Core MAU3 NIC1 MAU 3 NIC Module 2 Core MAU3 NIC2 Mod...

Page 24: ...oubleshooting data downloads software updates and component system member configuration The dual connectors on the module face enable both a laptop and a printer to interface with the CMC module The remote terminal also allows access via the CMC to maintenance information stored in the database module on MAU 1 The database can be loaded with a complete aircraft maintenance manual diagnostic softwa...

Page 25: ...is possible on the DC menu All monitored components systems and subsystems are directly linked to the processor modules through the ASCB D bus or indirectly through Input Output I O modules communicating over ARINC 429 busses Thresholds for initiation of Warning Caution and Advisory notifications over the crew alerting system CAS are software programmable and are set as part of the aircraft config...

Page 26: ...requiring illumination The flashing text and single chime accompanying advisories are active for only five seconds The cockpit glareshield warning caution inhibit panel contains additional functions related to the MWS and is discussed below In most cases system or equipment malfunctions that prompt CAS messages and illuminate glareshield indicator lights also cause the annunciator in the control s...

Page 27: ... the top half of the switch and G S INHIBIT on the bottom half top portion will illuminate BELOW G S with an accompanying aural annunciation during an Instrument Landing System ILS approach if the aircraft is flown below the lower margin of the glide slope signal If the flight condition is intentional depressing the annunciator will inhibit subsequent annunciations and the lower portion of the swi...

Page 28: ...tors in the engine fire handles fuel control switches and the thrust reverser manual stow switches are not dimmable and illuminate at full brightness regardless of cockpit lighting control settings Six 6 warning lights power WARN LTS PWR circuit breakers are incorporated to control L and R ESS 28v DC bus power distribution to numerous system signals and or indications The circuit breaker names loc...

Page 29: ...ve IRS 1 relay and select switch WRN LTS PWR 3 Circuit Breaker REER A 24 Signals Indications Right engine fire extinguisher switch Right wing anti ice thermal switches inboard mid and outboard Copilot WARN INHIBIT switch WRN LTS PWR 4 Circuit Breaker LEER A 8 Signals Indications APU fire annunciator light Left engine fire detector test switch L T REV MAN STOW switch WRN LTS PWR 5 Circuit Breaker R...

Page 30: ...R 6 LEER A 7 L ESS DC Bus WARN LTS PWR 4 LEER A 8 L ESS DC Bus WARN LTS PWR 2 LEER A 9 L ESS DC Bus WARN LTS PWR 5 REER A 25 R ESS DC Bus WARN LTS PWR 3 REER A 24 R ESS DC Bus WARN LTS PWR 1 REER A 23 R ESS DC Bus B Crew Alerting System CAS Messages CAS messages associated with the monitor and warning system are Area Monitored CAS Message Message Color Fault Warning Computer MWS FWC 1 2 Fail Amber...

Page 31: ...Warning Caution Inhibit Panels Figure 11 OPERATING MANUAL 2A 31 00 Page 31 32 July 15 04 Title Page Prev Page Next Page TOC ...

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Page 33: ...Warning Lights Power Simplified Schematic Figure 12 OPERATING MANUAL 2A 31 00 Page 33 34 July 15 04 Title Page Prev Page Next Page TOC ...

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Page 35: ...Maintenance Test Switch Figure 13 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 35 July 15 04 Title Page Prev Page Next Page TOC ...

Page 36: ... DUs Four DU 1310 active matrix liquid display units numbered 1 2 3 and 4 are installed in the cockpit instrument panel The DUs are identical and interchangeable and each has an internal cooling fan The pilot normally uses 1 and 2 the copilot 3 and 4 The displays have wide viewing angles so that the information on every display may be viewed by either pilot The DUs have no installed software but i...

Page 37: ...ssential information For a full description of the display window formats during various failure scenarios see Section 2B 04 00 of this manual The following formats are included for user convenience Power up default settings are DU 1 to 2 3 PFD with two blank selectable 1 6 windows DU 2 to 2 3 MAP with upper 1 6 window to primary engine instruments and lower 1 6 window to secondary engine instrume...

Page 38: ... can control DUs 2 3 and 4 A movable cursor pointing device A rotary dial to adjust ranges or values An enter button to select the option designated with the cursor A push to talk button for communications The crew first selects the display on which the cursor will be active using the selection buttons The cursor then appears on the active display formatted as a green plus type symbol for the pilo...

Page 39: ...t be displayed in steady mode in order for the scroll switch or CCD to move the messages on the display When messages are scrolled from the CAS display a status bar on the lowest line of the display will contain a numerical indication of the number of messages hidden from view with an arrow corresponding to direction that the messages have been scrolled Caution message status is shown in amber on ...

Page 40: ... inner outer knob controls the brightness of DU 1 and 2 the right inner outer controls the brightness of DU 3 and 4 Once set an automatic sensor on each DU adjusts brightness to maintain the selected contrast level in changing light conditions G DISPLAY SWITCHING DISPLAY CONTROL Panel The DISPLAY SWITCHING DISPLAY CONTROL panel is located on the cockpit overhead panel COP The switches on the panel...

Page 41: ...Bus DISPLAY UNIT 3 PRI CPOP B 6 R MAIN DC Bus DISPLAY UNIT 3 SEC CPOP B 7 R ESS DC Bus DISPLAY UNIT 4 CPOP B 5 R ESS DC Bus L CCD POP B 10 L ESS DC Bus R CCD CPOP B 10 R ESS DC Bus DISPLAY CONT 1 LEER G 9 L ESS DC Bus DISPLAY CONT 2 REER C 2 R ESS DC Bus DU REV POP E 10 L ESS DC Bus B Crew Alerting Systems CAS Messages CAS messages associated with the electronic display system are Area Monitored C...

Page 42: ...c Fuel Flow FF No limitation markings Oil Temperature OIL TEMP 160 C and above Red Digits 20 C to 160 C White Digits 30 C to 19 C Amber Digits 31 C and below Red Digits Oil Pressure OIL PRESS 35 psi and above White Digits 26 to 34 psi Amber Digits 0 to 25 psi Red Digits Engine Anti ice Pressure 33 psi and above Amber Digits Fuel Indications Fuel Tank Temperature Indications 54 C and above Red Digi...

Page 43: ...per minute as the aircraft either climbs or descends to the new altitude The arc is tied to the altitude preselect value and predicts where on the lateral map the new altitude will be achieved During VNAV operations the arc will not be displayed if the aircraft is operated in a vertical mode that does not involve the Altitude Preselect target on the Guidance Panel such as vertical speed The altitu...

Page 44: ...OPERATING MANUAL THIS PAGE IS INTENTIONALLY LEFT BLANK PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 44 July 15 04 Title Page Prev Page Next Page TOC ...

Page 45: ...Cockpit Display Formats Default Settings Figure 14 OPERATING MANUAL 2A 31 00 Page 45 46 July 15 04 Title Page Prev Page Next Page TOC ...

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Page 47: ...Cursor Control Device Figure 15 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 47 July 15 04 Title Page Prev Page Next Page TOC ...

Page 48: ...CAS Scroll Switch Figure 16 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 48 July 15 04 Title Page Prev Page Next Page TOC ...

Page 49: ...DISPLAY BRIGHTNESS Panel Figure 17 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 49 July 15 04 Title Page Prev Page Next Page TOC ...

Page 50: ...Display Switching Panel Figure 18 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 50 July 15 04 Title Page Prev Page Next Page TOC ...

Page 51: ...he operating panel The inactive panel will indicate the slave status by illumination of the SLV light located on the bottom center of the panel as shown in Figure 20 Radar return data is presented graphically in color on the MAP display with pull down menu choices using the Cursor Control Device CCD and or on the Horizontal Situation Indicator HSI section on the lower half of the Primary Flight Di...

Page 52: ...splay The box provides an indication of the current radar operating mode and or antenna tilt setting 1 MODE rotary knob with the following settings OFF prevents power to the RTA STBY selects standby mode to power the RTA assembly without antenna movement or signal transmission TEST to perform a system test with the antenna transmitting and a test pattern shown at a one hundred 100 mile range Fault...

Page 53: ...fined up or down two degrees 2 by rotating the extended TILT knob 4 GAIN rotary knob adjusts the RTA receiver gain The knob is normally pushed in to select the normal calibrated gain setting Pulling the knob out allows manual gain adjustment by turning the knob in order to increase or decrease receiver sensitivity 5 BRT knob adjusts the brightness of the radar presentation on the selected displays...

Page 54: ...R SYSTEM CAN ONLY INDICATE LIKELY BUT NOT ALL AREAS OF TURBULENCE ASSOCIATED WITH PRECIPITATION RADAR CANNOT DETECT CLEAR AIR TURBULENCE An additional automatic control mode is incorporated into the RTA termed Forced Standby FSBY mode This mode employs an input from the Weight On Wheels WOW system to place the radar system in standby whenever the aircraft is on the ground in order to preclude inju...

Page 55: ...at Whenever lightning is detected by the system an alert symbol is shown at the range perimeter of the active display window The alert symbol is a single strike icon shown in magenta The purpose of the alert icon is to identify for the flight crew the relative bearing from the aircraft of any lightning activity since the crew may have selected a display range that does not encompass the strike occ...

Page 56: ...ssociated with the weather radar system weather radar failure is annunciated on the PFD MAP display windows NOTE Circuit breakers and CAS messages associated with the Lightning Sensor System are defined upon system installation 4 Limitations A Flight Manual Limitations 1 Do NOT operate radar during refueling of the airplane nor when within 300 ft 92 meters of other refueling operations 2 Do NOT op...

Page 57: ...Weather Radar Antenna Installation Figure 19 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 57 July 15 04 Title Page Prev Page Next Page TOC ...

Page 58: ...Radar Controller Panel Figure 20 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 58 July 15 04 Title Page Prev Page Next Page TOC ...

Page 59: ...Lightning Sensor Display Figure 21 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 59 July 15 04 Title Page Prev Page Next Page TOC ...

Page 60: ...Lightning Sensor Control Panel Figure 22 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 60 July 15 04 Title Page Prev Page Next Page TOC ...

Page 61: ...om 2 0 G to 2 15 G at the G550 maximum landing weight of 75 300 lb Conversely the established maximum acceleration limit which determines whether an overweight landing inspection is required decreases with airplane gross weight from 2 15 G at the maximum landing weight of 75 300 lb 1 60 G at the maximum takeoff weight of 90 000 lb In addition to depending on actual airplane weight the maximum vert...

Page 62: ...Acceleration Limits Figure 23 OPERATING MANUAL PRODUCTION AIRCRAFT SYSTEMS 2A 31 00 Page 62 July 15 04 Title Page Prev Page Next Page TOC ...

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