Boeing ALTEON 777 Training Manual
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Boeing ALTEON 777 Training Manual

Boeing ALTEON 777 Training Manual

This manual is for training purposes only.
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777
Training Manual
THIS MANUAL IS FOR TRAINING PURPOSES ONLY.
NO MAINTENANCE ACTION SHOULD BE TAKEN AS A RESULT OF INFORMATION CONTAINED IN THIS MANUAL.
ALTEON PROPRIETARY RIGHTS ARE INCLUDED IN THE INFORMATION DISCLOSED HEREIN. R
,
,
ECIPIENT
BY ACCEPTING THIS DOCUMENT
AGREES
THAT NEITHER THIS DOCUMENT NOR THE INFORMATION DISCLOSED HEREIN NOR ANY PART THEREOF SHALL BE REPRODUCED OR TRANSFERRED TO OTHER DOCUMENTS
A
.
OR USED OR DISCLOSED TO OTHERS FOR MANUFACTURING OR FOR ANY OTHER PURPOSE EXCEPT AS SPECIFICALLY AUTHORIZED IN WRITING BY
LTEON
UNPUBLISHED, ALL RIGHTS RESERVED UNDER COPYRIGHT LAWS (
) 2003 A
T
L.L.C
C
LTEON
RAINING
This manual has been prepared by Alteon Seattle, Washington for the
Boeing Commercial Airplane Group.

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  • Page 1 OR USED OR DISCLOSED TO OTHERS FOR MANUFACTURING OR FOR ANY OTHER PURPOSE EXCEPT AS SPECIFICALLY AUTHORIZED IN WRITING BY LTEON UNPUBLISHED, ALL RIGHTS RESERVED UNDER COPYRIGHT LAWS ( ) 2003 A L.L.C LTEON RAINING This manual has been prepared by Alteon Seattle, Washington for the Boeing Commercial Airplane Group.
  • Page 2 This page is intentionally left blank...
  • Page 3 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page FLIGHT MANAGEMENT COMPUTING SYSTEM -- INTRODUCTION ..... . 34-61-00 . . 1 GENERAL DESCRIPTION .
  • Page 4 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page OPERATION - PITCH INTRODUCTION ........
  • Page 5 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page ADIRU REMOVAL AND LOCK BAR OPERATION ....... . .
  • Page 6 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page ILS -- INTRODUCTION ........34-31-00 . 200 GENERAL DESCRIPTION .
  • Page 7 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page GPWS -- INTRODUCTION ........34-46-00 . 252 GENERAL DESCRIPTION .
  • Page 8 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page GROUND TESTS ..........
  • Page 9 777 TRAINING MANUAL FLIGHT MANAGEMENT COMPUTING SYSTEM -- INTRODUCTION General ARINC - Aeronautical Radio, Incorporated - arrival The FMCS supplies these functions: ASCPC - air supply cabin pressure controller - ARINC signal gateway Flight plan control data - actual time of arrival Navigation calculations - aeronautical telecommunication network Display data.

  • Page 10: Training Manual

    777 TRAINING MANUAL FLIGHT MANAGEMENT COMPUTING SYSTEM -- INTRODUCTION - derated FDCF - flight deck communication function DCMF - data communication management function - fuel flow DCGF - data conversion gateway function - flight level - drift down FLCH - flight level change DFDAF - digital flight data acquisition function - flight...
  • Page 11 777 TRAINING MANUAL FLIGHT MANAGEMENT COMPUTING SYSTEM -- INTRODUCTION inbd - inboard - no computed data info - information - navigation database INIT/REF - initialization reference - nautical miles intcp - intercept - outside air temperature - international standard atmosphere OFST - offset ISSP...
  • Page 12 777 TRAINING MANUAL FLIGHT MANAGEMENT COMPUTING SYSTEM -- INTRODUCTION QARF - quick access recorder function - top of climb - altimeter setting to indicate height - top of descent above reference airfield - target - altimeter setting to indicate altitude - thrust above mean sea level thr ref...
  • Page 13 777 TRAINING MANUAL ACMF LNAV VNAV HOLD QARF CMCF 0838.4 336`/15 5100 32.5 110.90/123 25.3 DCGF AIRPLANE INFORMATION 5000 MANAGEMENT SYSTEM FRED INIT ALTN VNAV DCMF FMCF LEGS HOLD PROG EXEC COMM MENU PREV NEXT TMCF FDCF PAGE PAGE DFDAF 1000 RADIO VOR L...
  • Page 14 777 TRAINING MANUAL FMCS -- GENERAL DESCRIPTION General Instrument source select panel (ISSP) navigation source switches (2). The flight management computing system gives data to and receives data from these systems or components: The mode control panel (MCP) also has an interface with the FMCS, but is not an FMCS component.
  • Page 15 777 TRAINING MANUAL FMCS -- GENERAL DESCRIPTION Navigation radio tuning command outputs. CDU - General The FMCFs use performance and navigation data bases and There are three CDUs in the flight compartment. The sensor inputs to calculate guidance commands. When the CDUs are the primary control and display interface unit flight crew uses the MCP to select the LNAV and VNAV for the FMCF.
  • Page 16 777 TRAINING MANUAL FMCS -- GENERAL DESCRIPTION changes these inputs and sends them to the AIMS cabinet on the systems ARINC 629 buses. The NAV ISSP switch sets the source of navigation display data. 34-61-00 - 8 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 17: Display Unit

    777 TRAINING MANUAL MASTER DIM & TEST MODULE NAVIGATION RADIOS PA/CI CONTROLLER INIT ALTN VNAV DME (2) LEGS HOLD PROG EXEC COMM MENU ILS (3) PREV NEXT PAGE PAGE VOR (2) ADF (2) AFDC SYSTEMS ARINC 629 BUS (4) OPAS FLIGHT CONTROLS AIRPLANE ARINC 629 BUS (3)
  • Page 18 777 TRAINING MANUAL FMCS -- CDU POWER INTERFACE General These power buses supply 28v dc power to a CDU through an insertion switch: Captain's flight instrument bus (L CDU) Left bus (C CDU) Right bus (R CDU). Insertion Switch When you remove the CDU from the CDU mount, the insertion switch opens and removes power from the CDU.
  • Page 19 777 TRAINING MANUAL 28V DC INSERTION SWITCH CAPT FLT INST BUS POWER SUPPLY CDU L LEFT CDU INSERTION SWITCH 28V DC LEFT BUS POWER SUPPLY CDU C CENTER CDU INSERTION SWITCH 28V DC RIGHT BUS POWER SUPPLY CDU R P11 OVERHEAD CIRCUIT RIGHT CDU BREAKER PANEL FMCS - CDU POWER INTERFACE...
  • Page 20 777 TRAINING MANUAL FMCS -- CONTROL DISPLAY UNIT THIS PAGE INTENTIONALLY LEFT BLANK 34-61-00 - 12 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 21 777 TRAINING MANUAL FMCS -- CONTROL DISPLAY UNIT Purpose page, the current page number, and the total number of pages for the page display. Lines 1L to 6L and 1R to 6R The CDU is the primary control and display interface have title fields and data fields.
  • Page 22 777 TRAINING MANUAL FMCS -- CONTROL DISPLAY UNIT Dashes - this does not include the dash as an Not all keys permit all operations. Keys can have integral part of the data field different functions on other pages. Slashes - this does not include the slash with data on its two sides.
  • Page 23 777 TRAINING MANUAL FMCS -- CONTROL DISPLAY UNIT NAV/RAD (navigation radio page). contains data. Some data fields do not permit the DEL key function. For these the INVALID DELETE message Alpha-numeric Keys shows in the CDU sratchpad. The alpha-numeric keys permit the operator to put Annunciators alpha-numeric data into the scratchpad.
  • Page 24 777 TRAINING MANUAL FMCS -- CONTROL DISPLAY UNIT The others are the light sensors from the other CDUs and the PDS light sensors. Manual Brightness Control The manual brightness control adjusts the brightness level more or less than the automatic brightness level set by the CDU.

  • Page 25: Control Display Unit

    777 TRAINING MANUAL LIGHT SENSOR PAGE 1 OF 2 ANNUNCIATION PAGE TITLE FIELD LINE TITLE FIELD LINE TITLE FIELD LINE DATA FIELD 1 / 2 LINE DATA FIELD LCD AREA BOX PROMPTS LINE SELECT DASH PROMPTS KEYS (12) ---- BRIGHTNESS CONTROL SCRATCH PAD EXECUTE LIGHT...
  • Page 26 777 TRAINING MANUAL FMCS -- INSTRUMENT SOURCE SELECT PANELS AND F/O DISPLAY SWITCHING PANEL General Left (L) AUTO The FMCS has an interface with these controls: Right (R). Captain's NAV source switch on the instrument In the left position, the left FMCF and TMCF are source select panel (ISSP) active.
  • Page 27 777 TRAINING MANUAL LEFT NAV SOURCE SWITCH (CDU SELECTED) RIGHT NAV SOURCE SWITCH (FMCF SELECTED) DSPL DSPL CTRL CTRL DATA DATA /ATT /ATT LEFT INSTRUMENT RIGHT INSTRUMENT SOURCE SELECT PANEL SOURCE SELECT PANEL FMC SELECTOR LNAV MODE A/T ARM MACH SWITCH INBOARD DSPL VNAV MODE...
  • Page 28 777 TRAINING MANUAL FMCS -- NAV RADIO PAGE Purpose The letter A shows between the frequency and the identifier for the auto-tune mode. The FMC You use the NAV RADIO page on the left and right CDUs to automatically tunes to the best available VOR station. manually tune the VOR/DME, ADF, and ILS radios.
  • Page 29 777 TRAINING MANUAL FMCS -- NAV RADIO PAGE To enter a VOR course at 2L or 2R, do this: Type the letter A (ANT) or B (BFO) into the scratchpad Type a three digit number between 000 and 360 into Enter into 3L or 3R.
  • Page 30 777 TRAINING MANUAL FMCS -- NAV RADIO PAGE A prompt, ILS frequency, ILS course, and PARK in preselect line. To use this data on the preselect line, medium font when the airplane is less than 200 nm do this: from the top of descent or more than halfway to the destination.
  • Page 31 777 TRAINING MANUAL 1 1 6 S E A E L N 1 1 7 < FMCS - NAV RADIO PAGE 34-61-00 - 23 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 32 777 TRAINING MANUAL FMCS -- ALTN NAV RADIO PAGE THIS PAGE INTENTIONALLY LEFT BLANK 34-61-00 - 24 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 33 777 TRAINING MANUAL FMCS -- ALTN NAV RADIO PAGE Purpose Line 3L shows the ADF frequency and tune mode. The tune mode shows next to the ADF frequency, ANT (A) or BFO The alternate (back-up) navigation (ALTN NAV) RADIO (B). No show of A or B means that ADF is the active tune page gives an alternate means to tune the navigation mode.
  • Page 34 777 TRAINING MANUAL FMCS -- ALTN NAV RADIO PAGE Dashes show in the VOR course data field and M shows Type a course between 000 to 360 with a leading next to the VOR frequency. An entry of 360 shows as slash 000.
  • Page 35 777 TRAINING MANUAL & - - - - - - FMCS - ALTN NAV RADIO PAGE 34-61-00 - 27 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 36 777 TRAINING MANUAL FMCS -- SYSTEM TESTS General These are the system tests for the flight management computing system: Control display unit (CDU), center Control display unit, left Control display unit, right. CDU System Test This test makes sure that the center, left, or right CDU operates correctly.
  • Page 37 777 TRAINING MANUAL Select System Test CONTROL DISPLAY UNIT (CENTER) GROUND TESTS CONTROL DISPLAY UNIT (LEFT) CONTROL DISPLAY UNIT (RIGHT) Select ATA System (55) Select Test Type 32 Left Main Landing System SYSTEM TEST 32 Nose Landing Gear OPERATIONAL TEST 32 Proximity Sensor System 32 Right Main Landing System LRU REPLACEMENT TEST...
  • Page 38 777 TRAINING MANUAL FMCS -- CDU SPECIAL FUNCTIONS General The approximate time to run a CDU special function is two to five minutes. The FMCS control display unit (CDU) special function makes sure the internal hardware and software operates There are no limitations or special requirements to run correctly.
  • Page 39 777 TRAINING MANUAL Select Function CONTROL DISPLAY UNIT (CENTER) DISPLAY CONTROL DISPLAY UNIT (LEFT) DISPLAY SPECIAL FUNCTIONS CONTROL DISPLAY UNIT (RIGHT) DISPLAY Select ATA System Select ATA System (21) 31 AIMS - Flight Data Recorder System 31 AIMS - Display System 32 Air/Ground System 32 Antiskid/Autobrake Control System 32 Brake Temperature Monitor System...
  • Page 40 777 TRAINING MANUAL THRUST MANAGEMENT COMPUTING SYSTEM (TMCS) -- INTRODUCTION THIS PAGE INTENTIONALLY LEFT BLANK 22-31-00 - 32 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 41 777 TRAINING MANUAL THRUST MANAGEMENT COMPUTING SYSTEM (TMCS) -- INTRODUCTION General - climb CMCF - central maintenance computing function The thrust management computing system (TMCS) is part - command of the airplane information management system (AIMS). - continuous The TMCS controls engine thrust in response to mode - core processor module requests from the: - cabin temperature controller...
  • Page 42 777 TRAINING MANUAL THRUST MANAGEMENT COMPUTING SYSTEM (TMCS) -- INTRODUCTION - indicated airspeed SAARU - secondary attitude air data reference unit - intercabinet - shutoff - input/output module - speed - knots (nautical miles per hour) tach - tachometer - left - true airspeed - maintenance access terminal - total air temperature...
  • Page 43 777 TRAINING MANUAL ACMF QARF CMCF DCGF UTCF AIRPLANE INFORMATION MANAGEMENT SYSTEM DCMF FMCF TMCF FDCF INIT ALTN VNAV LEGS HOLD PROG EXEC COMM DFDAF MENU PREV NEXT PAGE PAGE THRUST MANAGEMENT COMPUTING SYSTEM TAKEOFF CLIMB CRUISE DESCENT APPROACH AUTOLAND THRUST MANAGEMENT COMPUTING SYSTEM (TMCS) - INTRODUCTION 22-31-00 - 35 -...
  • Page 44 777 TRAINING MANUAL TMCS -- GENERAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 22-31-00 - 36 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 45 777 TRAINING MANUAL TMCS -- GENERAL DESCRIPTION General The ASMs receive digital commands from the TMCF and analog data from the MCP. The operator interface to the TMCS is through the control display units (CDUs) and the mode control panel The A/T disconnect and TO/GA switches on the center (MCP).
  • Page 46 777 TRAINING MANUAL TMCS -- GENERAL DESCRIPTION Overhead panel bus controller (OPBC) (2) The TMCF sends display and fault data to the primary Flap slat electronics unit (FSEU) (2) display function and the central maintenance computing ARINC signal gateway (ASG) (2) function in the AIMS cabinets.
  • Page 47 777 TRAINING MANUAL ADIRU SAARU PFC (3) INIT ALTN VNAV FLT CTRL ARINC LEGS HOLD PROG EXEC COMM 629 BUS (3) MENU AFDC (3) PREV NEXT PAGE PAGE ASCPC (2) CTC (2) PSEU (2) CDU (3) WEU (2) TO/GA EDIU (2) SWITCH (2) OPBC(2) FSEU (2)
  • Page 48 777 TRAINING MANUAL TMCS -- A/T SERVO MOTOR General There are three magnetic pick-off sensors in the DC motor stator that measure rate feedback. These sensors The integrated autothrottle servo motors (ASMs) are measure the rate between the rotor and stator as the below the throttle quadrant (P10).
  • Page 49 777 TRAINING MANUAL RIGHT AUTOTHROTTLE SERVO MOTOR LEFT AUTOTHROTTLE SERVO MOTOR (ROTATED 90 CLOCKWISE) TMCS - A/T SERVO MOTOR 22-31-00 - 41 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 50 777 TRAINING MANUAL TMCS -- EICAS DISPLAY - OPERATION THIS PAGE INTENTIONALLY LEFT BLANK 22-31-00 - 42 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 51 777 TRAINING MANUAL TMCS -- EICAS DISPLAY - OPERATION General G/A. The EICAS display shows this TMCF data that relates to These are the three ways to derate the engine thrust: engine/thrust performance: Enter an assumed temperature Thrust limit mode Select TO 1 or TO 2 Selected temperature Select CLB 1 or CLB 2.
  • Page 52 777 TRAINING MANUAL TMCS -- EICAS DISPLAY - OPERATION Thrust Limit Fault Messages The TMCF calculates the thrust limit with inputs from TMCS fault messages show on the EICAS display for these the FMCF and other sensors and components. The digital conditions: readout shows on the EICAS display.
  • Page 53 777 TRAINING MANUAL THRUST LIMIT MODES: - TO - TO 1 - TO 2 - D-TO - D-TO 1 - D-TO 2 - CLB SELECTED TMCS MESSAGES: - CLB 1 TEMPERATURE - AUTOTHROTTLE DISC - CLB 2 - AUTOTHROTTLE L - CRZ - AUTOTHROTTLE R - CON...
  • Page 54 777 TRAINING MANUAL TMCS -- SYSTEM TESTS General The third step is the forward command. This test has a TLA rate of 8 degrees/second for 5 seconds. During the These are the servo loop system tests for the left and thrust lever movement, the average tach feedback must right TMCF: be between +6 and +10 degrees/second.
  • Page 55 777 TRAINING MANUAL Select System Test LEFT CABINET SERVO LOOP TEST GROUND TESTS RIGHT CABINET SERVO LOOP TEST Select ATA System (55) Select Test Type 21 Cabin Temperature Control System SYSTEM 21 Cabin Pressure Control System TEST 21 Environmental Control System 22 AIMS - Autothrottle OPERATIONAL 22 Autopilot Flight Director System...
  • Page 56 777 TRAINING MANUAL TMCS -- LRU REPLACEMENT TESTS General The LRU Replacement tests for the TMCS are the left and right cabinet analog discrete input tests. Analog Input Discrete Test This test makes sure that the TMCF in the AIMS and the takeoff/go-around switches, the autothrottle disconnect switches, and the autothrottle arm switches operate correctly.
  • Page 57 777 TRAINING MANUAL Select LRU Replacement Test LEFT CABINET ANALOG DISCRETE INPUT TEST GROUND TESTS RIGHT CABINET ANALOG DISCRETE INPUT TEST Select ATA System (55) Select Test Type 21 Cabin Temperature Control System SYSTEM 21 Cabin Pressure Control System TEST 21 Environmental Control System 22 AIMS - Autothrottle OPERATIONAL...
  • Page 58 777 TRAINING MANUAL PRIMARY FLIGHT CONTROL SYSTEM -- INTRODUCTION Purpose Speedbrakes The primary flight control system (PFCS) controls the The PFCS also includes the speedbrakes. The spoilers airplane flight attitude in relation to the three basic not only supply roll control but also are speedbrakes axes: in the air and on the ground.
  • Page 59 777 TRAINING MANUAL ELEVATOR RUDDER RUDDER TAB AILERON ELEVATOR SPOILERS FLAPERON LATERAL HORIZONTAL AXIS STABILIZER FLAPERON SPOILERS LONGITUDINAL AILERON AXIS VERTICAL AXIS PITCH CONTROL ROLL CONTROL YAW CONTROL PRIMARY FLIGHT CONTROL SYSTEM - INTRODUCTION 27-02-00 - 51 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 60 777 TRAINING MANUAL PFCS -- GENERAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 27-02-00 - 52 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 61 777 TRAINING MANUAL PFCS -- GENERAL DESCRIPTION General The ACEs change these command signals to analog format and send them to the power control units (PCUs) and the The pilots or the autopilot commands control the PFCS. stabilizer trim control modules (STCMs). The ACEs and The pilots can override the autopilot.
  • Page 62 777 TRAINING MANUAL PFCS -- GENERAL DESCRIPTION movement of the flight deck controls supplies visual indications to the flight crew. PFCS Modes of Operation The PFCS has three modes of operation: normal, secondary, and direct. Normal mode operates when the necessary data are available for the PFCs and the ACEs.
  • Page 63 777 TRAINING MANUAL SPEEDBRAKE LEVER ANALOG ANALOG CONTROL (TYPICAL) POSITION SURFACES TRANSDUCERS FORCE ACE (4) TRANSDUCERS BACKDRIVE DIGITAL ACTUATORS PFC (3) FLIGHT CONTROLS ARINC 629 BUSES (3) AIMS ADIRU SAARU CABINETS MECHANICAL ANALOG CONNECTION AFDC (3) PFCS - GENERAL DESCRIPTION 27-02-00 - 55 - ALTEON PROPRIETARY.
  • Page 64 777 TRAINING MANUAL PFCS -- OPERATIONAL MODES - FUNCTIONAL DESCRIPTION General At least one PFC and three ACEs are in normal mode. These are the three modes of PFCS operation: All the control laws, the protection functions, and the stability augmentation of the PFCs are active in the Normal normal mode.
  • Page 65 777 TRAINING MANUAL PFCS -- OPERATIONAL MODES - FUNCTIONAL DESCRIPTION wheels, columns and pedals go directly to the ACEs The EICAS caution message PRI FLIGHT COMPUTERS shows which use them to control the PCUs. The protection when all ACEs under power are in direct mode and the functions are not available.
  • Page 66 777 TRAINING MANUAL PFCS -- OPERATIONAL MODES - FUNCTIONAL DESCRIPTION Two elevator PCUs and one stabilizer path are not operative The wheel, column, or pedal position transducers for the captain and first officer disagree by more than 15 percent of full range with the airplane on the ground The elevator force fight equalization function is defective.
  • Page 67 777 TRAINING MANUAL PRIMARY FLIGHT COMPUTERS DISC DISC AUTO NORMAL PFC DISCONNECT SWITCH (P5) AUTOMATIC OR MANUAL SWITCHING TO THE HIGHEST MODE AVAILABLE AUTOMATIC OR MANUAL SWITCHING SECONDARY AUTOMATIC SELECTION AUTOMATIC OR MANUAL DIRECT SWITCHING AUTOMATIC OR MANUAL SWITCHING PFCS - OPERATIONAL MODES - FUNCTIONAL DESCRIPTION 27-02-00 - 59 - ALTEON PROPRIETARY.
  • Page 68 777 TRAINING MANUAL AUTOPILOT FLIGHT DIRECTOR SYSTEM -- INTRODUCTION THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 60 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 69 777 TRAINING MANUAL AUTOPILOT FLIGHT DIRECTOR SYSTEM -- INTRODUCTION General director bars as guides to control the attitude of the airplane. The autopilot flight director system (AFDS) has two purposes. These purposes are: Abbreviations and Acronyms To automatically control the airplane attitude - autopilot To supply indications so the flight crew can - actuator control electronics...
  • Page 70 777 TRAINING MANUAL AUTOPILOT FLIGHT DIRECTOR SYSTEM -- INTRODUCTION - glideslope - generator control unit - heading HYDIM - hydraulic interface module - liquid crystal display - light emitting diode LNAV - lateral navigation - localizer - mode control panel - multi-function display - navigation display OPAS...

  • Page 71: Flight Director Command Bars

    777 TRAINING MANUAL CRUISE CLIMB A/T ARM ALTITUDE MACH DESCENT LNAV AUTO 1000 VNAV BANK DOWN AUTO F/D ON LIMIT F/D ON FLCH HOLD VS/FPA HOLD A/P DISENGAGE MODE CONTROL PANEL FLIGHT DIRECTOR LNAV VNAV IDLE COMMAND BARS GO-AROUND APPROACH TAKEOFF AUTOLAND PRIMARY FLIGHT DISPLAY...
  • Page 72 777 TRAINING MANUAL AFDS -- GENERAL DESCRIPTION Pilot Interface The thrust management computer function (TMCF) sends autothrottle data to the AFDCs. The mode control panel (MCP) is the primary interface between the pilot and the autopilot flight director The primary display function receives AFDS display computers (AFDCs).
  • Page 73 777 TRAINING MANUAL A/T ARM MACH ALTITUDE AIMS LNAV MACH AUTO 1000 VNAV BANK DOWN AUTO F/D ON LIMIT F/D ON AIRPLANE FLCH A/P DISENGAGE HOLD VS/FPA HOLD SENSORS SYSTEMS MODE CONTROL PANEL ARINC 629 BUS (3) COLLINS SENSORS BACKDRIVE ACTUATOR (6) TO/GA SW (2) AFDC (3)
  • Page 74 777 TRAINING MANUAL AFDS -- FLIGHT DECK COMPONENT LOCATIONS AFDS Component Location In The Flight Deck These are the AFDS components in the flight deck: Mode control panel (MCP) Takeoff/go-around (TO/GA) switches Autopilot disconnect switches. 22-11-00 - 66 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 75 777 TRAINING MANUAL MODE CONTROL PANEL THRUST LEVERS (P10) - TO/GA SWITCHES CONTROL WHEELS - A/P DISCONNECT SWITCHES AFDS - FLIGHT DECK COMPONENT LOCATIONS 22-11-00 - 67 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 76 777 TRAINING MANUAL AFDS -- MAIN EQUIPMENT CENTER COMPONENT LOCATION AFDS Component Location The AFDCs are on the E1, E2, and E4 racks in the main equipment center. 22-11-00 - 68 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 77 777 TRAINING MANUAL E1-3 - LEFT AFDC E4-1 - CENTER AFDC E2-5 - RIGHT AFDC MAIN EQUIPMENT CENTER (LOOKING AFT) MAIN EQUIPMENT CENTER (LOOKING FWD) AFDS - MAIN EQUIPMENT CENTER COMPONENT LOCATION 22-11-00 - 69 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 78 777 TRAINING MANUAL AFDS -- BELOW FLIGHT DECK COMPONENT LOCATIONS AFDS Component Locations The backdrive actuators and their mechanical connections are under the flight deck floor. 22-11-00 - 70 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 79 777 TRAINING MANUAL RIGHT CONTROL COLUMN RIGHT BACKDRIVE RUDDER ACTUATOR PEDAL BACKDRIVE LEFT ACTUATOR CONTROL COLUMN BACKDRIVE ACTUATOR RIGHT CONTROL LEFT WHEEL RUDDER BACKDRIVE PEDAL ACTUATOR BACKDRIVE ACTUATOR LEFT CONTROL WHEEL BACKDRIVE ACTUATOR AFDS - BELOW FLIGHT DECK COMPONENT LOCATIONS 22-11-00 - 71 - ALTEON PROPRIETARY.
  • Page 80 777 TRAINING MANUAL AFDS -- POWER INTERFACE AFDS - Power Distribution The left and right 28v dc buses supply AFDC and backdrive power to their onside AFDCs and the MCP. The 28v dc battery bus supplies AFDC power to the center AFDC.
  • Page 81 777 TRAINING MANUAL MCP L 28V DC AFDC L L BUS 5V AC PANEL LIGHT PWR MASTER DIM AND TEST AFDC BACK DRIVE L LEFT AFDC 28V DC AFDC C BAT BUS 28V DC AFDC HOT BAT WARN CENTER AFDC MASTER DIM AND TEST AFDC R 28V DC...
  • Page 82 777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - CONTROLS AND DISPLAYS Autopilot (A/P) Engage Switches Light Sensor Push either switch to engage all available A/P A photo diode light sensor on the MCP front panel channels. The LEDs in both switches come on. monitors ambient lighting.

  • Page 83: Training Manual

    777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - CONTROLS AND DISPLAYS The window shows four dashes when vertical speed and With the outer selector in the AUTO position, the flight path angle modes are not active. window change rate is 100 feet/detent. The altitude window also shows the barometric minimums you selected Altitude Window on both EFIS control panels.
  • Page 84 777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - CONTROLS AND DISPLAYS Vertical Speed/Flight Path Angle Selector In VNAV, the IAS/MACH window is normally blank. If you push the selector, the window unblanks to show the Rotate the selector up to decrease the value. Rotate current FMCF target airspeed.
  • Page 85 777 TRAINING MANUAL AUTOPILOT ENGAGE IAS/MACH SWITCH (2) REFERENCE SWITCH IAS/MACH AUTOTHROTTLE WINDOW ARM SWITCHES MODE LIGHT HEADING/TRACK SWITCH SENSOR REFERENCE SWITCH HEADING/TRACK WINDOW VERTICAL SPEED/FLIGHT PATH ANGLE REFERENCE SWITCH VERTICAL SPEED/FLIGHT PATH ANGLE WINDOW ALTITUDE WINDOW CLIMB/ CONTINUOUS IAS/MACH THRUST SELECTOR SWITCH...
  • Page 86 777 TRAINING MANUAL AFDS -- OPERATION - OVERVIEW General The autopilot flight director system (AFDS) operates on the ground and in flight. The AFDS calculates commands for these flight sequences: Takeoff Climb Cruise Descent Approach Autoland Rollout Go-around. 22-11-00 - 78 - ALTEON PROPRIETARY.
  • Page 87 777 TRAINING MANUAL CRUISE DESCENT CLIMB GO-AROUND APPROACH AUTOLAND TAKEOFF ROLLOUT AFDS - OPERATION - OVERVIEW 22-11-00 - 79 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 88 777 TRAINING MANUAL AFDS -- OPERATION - ROLL INTRODUCTION General Heading/Track Select These AFDS roll modes are available during climb, In this mode, the airplane turns to the heading or cruise and descent: track that shows in the heading/track window. Lateral navigation (LNAV) If the HDG/TRK display shows HDG, the airplane goes to Heading hold (HDG HOLD)
  • Page 89 777 TRAINING MANUAL A/T ARM MACH ALTITUDE LNAV AUTO 1000 VNAV BANK DOWN AUTO F/D ON LIMIT F/D ON A/P DISENGAGE FLCH HOLD HOLD VS/FPA CLIMB, CRUISE, AND DESCENT LNAV HEADING/TRACK HOLD HEADING/TRACK SELECT LNAV VNAV PTH ROLL MODE ANNUNCIATION AFDS - OPERATION - ROLL INTRODUCTION 22-11-00 - 81 -...
  • Page 90 777 TRAINING MANUAL AFDS -- OPERATION - PITCH INTRODUCTION General When the VS/FPA display shows FPA, the airplane goes to and holds the flight path angle that shows on the These AFDS pitch modes are available during climb, vertical speed/flight path angle window. cruise and descent: FLCH Vertical navigation (VNAV)
  • Page 91 777 TRAINING MANUAL A/T ARM MACH ALTITUDE LNAV AUTO 1000 VNAV BANK DOWN AUTO LIMIT F/D ON F/D ON FLCH HOLD A/P DISENGAGE HOLD VS/FPA CRUISE VNAV VS/FPA CLIMB DESCENT VNAV VNAV HDG SEL VS/FPA VS/FPA FLCH FLCH AFDS - OPERATION - PITCH INTRODUCTION 22-11-00 - 83 - ALTEON PROPRIETARY.
  • Page 92 777 TRAINING MANUAL AFDS -- OPERATION - APPROACH/AUTOLAND INTRODUCTION General Runway Alignment These AFDS functions are available for landing: In crosswind conditions, the runway alignment mode supplies roll and yaw control to decrease the airplane Localizer (LOC) crab angle for touchdown. The runway alignment mode Glideslope (G/S) also includes roll and yaw control for an engine Flare (FLARE)
  • Page 93 777 TRAINING MANUAL GO-AROUND APPROACH/AUTOLAND G/S CAPTURE FLARE LOC CAPTURE ROLLOUT GO-AROUND RUNWAY ALIGNMENT AFDS - OPERATION - APPROACH/AUTOLAND INTRODUCTION 22-11-00 - 85 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 94 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATION INTRODUCTION General The AIMS also turns on the master caution light and causes the WES to make the caution aural. The AFDCs warning and annunciation functions send normal and non-normal indications of AFDS performance The AIMS cabinets The warning electronic system (WES).

  • Page 95: Status Format

    777 TRAINING MANUAL WARNING WARNING CAUTION CAUTION LEFT AURAL LEFT MASTER WARNING/ RIGHT MASTER WARNING/ RIGHT AURAL WARNING SPEAKER MASTER CAUTION LIGHTS MASTER CAUTION LIGHTS WARNING SPEAKER AFDC (3) LNAV VNAV FLT DIR 1000 EICAS DISPLAY LNAV VNAV AUTOPILOT DISC AUTOPILOT NO LAND 3 1000...
  • Page 96 777 TRAINING MANUAL AFDS -- LRU TESTS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 88 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 97: Training Manual

    777 TRAINING MANUAL AFDS -- LRU TESTS General Backdrive Actuator LRU Replacement Tests The LRU replacement tests verify the correct All backdrive actuator LRU replacement tests make sure installation of an LRU. the backdrive electrical signal wires are good. They also make sure the flight deck controls move to the Autopilot Disconnect Switch LRU Replacement Test correct position at the correct rate.
  • Page 98 777 TRAINING MANUAL AFDS -- LRU TESTS TO/GA Switch LRU Replacement Test The TO/GA switch LRU replacement test makes sure all contacts of both TO/GA switches operate correctly. The TO/GA switches interface with all AFDCs and AIMS cabinets. During the test, the MAT tells you to operate the left and right go-around switches one at a time.
  • Page 99 777 TRAINING MANUAL (12) Select LRU Replacement Test AUTOPILOT DISCONNECT SWITCH GROUND TESTS AUTOPILOT FLIGHT DIRECTOR COMPUTER (CENTER) AUTOPILOT FLIGHT DIRECTOR COMPUTER (LEFT) Select ATA System (55) AUTOPILOT FLIGHT DIRECTOR COMPUTER (RIGHT) Select Test Type 21 Environmental Control System CONTROL COLUMN BACKDRIVE ACTUATOR (LEFT) SYSTEM 21 Cabin Pressure Control System 21 Cabin Temperature Control System...
  • Page 100 777 TRAINING MANUAL AFDS -- SYSTEM TESTS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 92 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 101 777 TRAINING MANUAL AFDS -- SYSTEM TESTS General Analog signals that are not in their normal state when the airplane is on the ground and is not The AFDS system tests verify the correct functionality moving of the AFDS. ARINC 629 input bus inactivity ARINC 429 input bus inactivity Autopilot Disconnect Warning System Test Incorrect ILS or RA to AFDC connections.
  • Page 102 777 TRAINING MANUAL AFDS -- SYSTEM TESTS During the test, the AFDCs operate these functions to MCP/AFDC discrete interface faults make sure all signal wires are correct: MCP/AIMS discrete interface faults ARINC 429 output bus faults Tune inhibit discrete Internal MCP monitor faults Localizer antenna switches Internal MCP redundant and parallel data path Glideslope antenna switches.
  • Page 103 777 TRAINING MANUAL Select System Test AUTOPILOT DISCONNECT WARNING GROUND TESTS AUTOPILOT FLIGHT DIRECTOR COMPUTERS CONTROL COLUMN BACKDRIVE Select ATA System (55) CONTROL WHEEL BACKDRIVE Select Test Type 21 Environmental Control System ILS INTERFACE 21 Cabin Pressure Control System SYSTEM 21 Cabin Temperature Control System TEST MODE CONTROL PANEL...
  • Page 104 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- INTRODUCTION Pitot-Static System The pitot-static system uses pitot probes and flush static ports to sense total and static air pressures. These pressures go to the air data inertial reference system (ADIRS) and the integrated standby flight display (ISFD) to calculate flight parameters such as air speed and altitude.

  • Page 105: Static Pressure

    777 TRAINING MANUAL TOTAL PRESSURE Ñ Ñ Ñ PITOT PROBES (2 RIGHT SIDE) STATIC PORTS (1 LEFT SIDE) (3 EACH SIDE) 20,000 FT STATIC PRESSURE 10,000 FT 5,000 FT PITOT-STATIC SYSTEM - INTRODUCTION 34-11-00 - 97 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 106 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- GENERAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 34-11-00 - 98 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 107 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- GENERAL DESCRIPTION Pitot-Static System change the air pressures to electrical signals and send them to the air data inertial reference unit (ADIRU) The pitot-static system receives air pressure inputs and secondary attitude air data reference unit (SAARU) from three pitot probes and six flush static ports on on the flight controls ARINC 629 data buses.
  • Page 108 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- GENERAL DESCRIPTION Power Inputs The ISFD gets airplane power from the left power supply assembly (PSA). The left PSA also sends power to the ADM power supply (PS). The ADM PS sends power for operation to the SADMs.
  • Page 109 777 TRAINING MANUAL SAARU PITOT ADM (3) PITOT PROBE (3) ADIRU ON/OFF SWITCH ADIRU STATIC ADM (3) FLIGHT CONTROLS RIGHT AIMS ARINC 629 BUS (3) CABINET HP/IN 29.92 LEFT AIMS CABINET STATIC STANDBY ADM AIR DATA MODULE POWER SUPPLY -200 BARO STATIC PORTS (6) INTEGRATED STANDBY...
  • Page 110 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- FLIGHT DECK COMPONENT LOCATION Air Data Module Power Supply The air data module power supply (ADM PS) is behind the P2-1 panel in the flight compartment. Integrated Standby Flight Display The ISFD is on the P2-1 panel in the flight compartment.
  • Page 111 777 TRAINING MANUAL AIR DATA MODULE POWER SUPPLY HP/IN 29.92 -200 BARO INTEGRATED STANDBY FLIGHT DISPLAY PITOT-STATIC SYSTEM - FLIGHT DECK COMPONENT LOCATION 34-11-00 - 103 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 112 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- MEC COMPONENT LOCATION - 1 General The location of the left pitot air data module (ADM) is in the left forward section of the main equipment center. 34-11-00 - 104 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 113 777 TRAINING MANUAL LEFT PITOT FORWARD SECTION - LEFT OF NOSE WHEEL WELL PITOT-STATIC SYSTEM - MEC COMPONENT LOCATION - 1 34-11-00 - 105 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 114 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- MEC COMPONENT LOCATION - 2 Right and Center Pitot ADM Locations The right and center pitot ADMs are in the MEC to the right of the nose wheel well and below the flight compartment. Pitot SADM The pitot SADM is in the MEC below the flight compartment and aft of the center pitot ADM.
  • Page 115 777 TRAINING MANUAL PITOT SADM CENTER RIGHT PITOT PITOT ADM MAIN EQUIPMENT CENTER (RIGHT SIDE, LOOKING FORWARD) PITOT-STATIC SYSTEM - MEC COMPONENT LOCATION - 2 34-11-00 - 107 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 116 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- FWD CARGO COMPARTMENT COMPONENT LOCATION Static SADM and Static ADMs The static SADM and the three static ADMs are in the forward cargo compartment ceiling above the cargo liner. 34-11-00 - 108 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 117 777 TRAINING MANUAL FWD CARGO COMPARTMENT STATIC SADM DOOR CENTER STATIC FWD CARGO COMPARTMENT (LOOKING AFT) LEFT STATIC RIGHT STATIC PITOT-STATIC SYSTEM - FWD CARGO COMPARTMENT COMPONENT LOCATION 34-11-00 - 109 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 118 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- EXTERNAL COMPONENT LOCATION Pitot Probes Location There are 3 pitot probes on the airplane. The left pitot probe is on the left side of the airplane. The right and center pitot probes are on the right side of the airplane.
  • Page 119 777 TRAINING MANUAL LEFT CENTER LEFT RIGHT PITOT STATIC STATIC STATIC PROBE PORT PORT PORT RIGHT LEFT CENTER RIGHT CENTER STATIC STATIC STATIC PITOT PITOT PORT PORT PORT PROBE PROBE PITOT-STATIC SYSTEM - EXTERNAL COMPONENT LOCATION 34-11-00 - 111 - ALTEON PROPRIETARY.
  • Page 120 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- POWER Power The STBY IND circuit breaker on the left power supply assembly gives 28v dc to the integrated standby flight display (ISFD) through the ISFD circuit breaker on the P11 panel. The STBY IND circuit breaker on the left power supply gives 28v dc to the air data module power supply (ADM PS) assembly through the STBY ADM circuit breaker on the P11 panel.
  • Page 121 777 TRAINING MANUAL 28V DC LEFT FCDC 28V DC ISFD STBY IND RETURN INTEGRATED STANDBY LEFT POWER SUPPLY STBY ASSEMBLY (E1-6) FLIGHT DISPLAY (P2-1) P11 OVERHEAD CIRCUIT BREAKER PANEL +13.5V DC POWER RETURN -13.5V DC PITOT SADM +13.5V DC POWER RETURN -13.5V DC STATIC SADM AIR DATA MODULE...
  • Page 122 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- PITOT PROBES AND STATIC PORTS Static Ports The static ports supply static pressure to the static air data modules (ADMs). Pitot Probes The pitot probes supply total pressure to the pitot ADMs. Training Information Point Before you remove a pitot probe, obey this warning.
  • Page 123 777 TRAINING MANUAL AIRPLANE SKIN ELECTRICAL CONNECTOR PITOT LINE PITOT PROBE STATIC GASKET STATIC PORTS LINES (NOT USED) STATIC (CAPPED) LINE ELECTRICAL CONNECTOR PITOT PROBE STATIC PORT STATIC PORT PITOT-STATIC SYSTEM - PITOT PROBES AND STATIC PORTS 34-11-00 - 115 - ALTEON PROPRIETARY.
  • Page 124 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- STANDBY AIR DATA MODULE General Training Information Point There are two standby air data modules (SADMs) on the The SADM is not software loadable. airplane. The SADMs and the ADMs are different in size and shape. Since they send data on different ARINC formats, they are not interchangeable.
  • Page 125 777 TRAINING MANUAL PNEUMATIC CONNECTOR ELECTRICAL CONNECTOR FLANGES PITOT-STATIC SYSTEM - STANDBY AIR DATA MODULE 34-11-00 - 117 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 126 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- AIR DATA MODULE POWER SUPPLY General The air data module power supply (ADM PS) is behind the P2-1 panel in the flight compartment. ADM PS Hardware The ADM PS is 7 in deep x 3.38 in wide x 3.38 in tall (17.78 cm x 8.58 cm x 8.58 cm).
  • Page 127 777 TRAINING MANUAL FASTENERS ELECTRICAL CONNECTOR FASTENERS PITOT-STATIC SYSTEM - AIR DATA MODULE POWER SUPPLY 34-11-00 - 119 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 128 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTEGRATED STANDBY FLIGHT DISPLAY STANDBY ATTITUDE REFERENCE SYSTEM -- INTEGRATED STANDBY FLIGHT DISPLAY THIS PAGE INTENTIONALLY LEFT BLANK 34-24-00 - 120 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 129: Training Manual

    777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTEGRATED STANDBY FLIGHT DISPLAY General Weight - 4.41 pounds (2.0 kg) Power - 20 watts dc. The integrated standby flight display (ISFD) gives the flight crew a single integrated display of these The ISFD has three connectors at the rear of the unit.
  • Page 130 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTEGRATED STANDBY FLIGHT DISPLAY Approach Mode Switch (APP) Turn the control to set the barometric correction. The barometric correction shows on the top right side of The approach mode switch controls the display of the the display in units of hectopascals (hPa) or inches of localizer and glideslope deviation.
  • Page 131 777 TRAINING MANUAL APPROACH BAROMETRIC MODE SWITCH REFERENCE SWITCH HP/IN ROLL ATTITUDE 30.08 LIGHT SENSOR ELECTRICAL PITCH CONNECTOR ATTITUDE DISPLAY ALTITUDE BRIGHTNESS SWITCHES -200 STANDARD INDICATED SELECT SWITCH AIRSPEED BARO BAROMETRIC CONTROL ATTITUDE HEADING PITOT AND STATIC AIR INPUTS NOT USED RESET SWITCH STANDBY ATTITUDE REFERENCE SYSTEM - INTEGRATED STANDBY FLIGHT DISPLAY 34-24-00...
  • Page 132 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE MENU STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE MENU General The ISFD has internal BITE that lets you monitor and do tests. To show the BITE displays, the airplane must be on the ground and the ISFD power-up complete.
  • Page 133 777 TRAINING MANUAL PRESS HP/IN HP/IN HP/IN HP/IN TESTS OTHER DATA 1200 29.92 1000 < FUNCTIONAL TEST (110s) < TESTS < LRU IDENT < DISPLAY TEST < OTHER DATA < ENGINEERING DATA return return return ATT RST BARO ATT RST BARO ATT RST BARO...
  • Page 134 777 TRAINING MANUAL AIR DATA INERTIAL REFERENCE SYSTEM -- INTRODUCTION General FCDC - flight controls direct current FMCF - flight management computing function These are the two functions of the air data inertial - flight path angle reference system (ADIRS): FSEU - flap/slat electronics unit - global positioning system...
  • Page 135 777 TRAINING MANUAL AIR DATA INERTIAL REFERENCE SYSTEM - INTRODUCTION 34-20-00 - 127 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 136 777 TRAINING MANUAL ADIRS -- GENERAL DESCRIPTION General Air Data Inertial Reference Unit The air data inertial reference system (ADIRS) has The air data inertial reference unit (ADIRU) uses these these components: inputs to calculate and supply air data to user systems: Pitot probes Static port...
  • Page 137 777 TRAINING MANUAL PITOT PROBE ADM (3) ADIRU SWITCH STATIC ADIRU PORT ADM (3) TAT PROBE FLIGHT CONTROLS SAARU ARINC 629 BUS (3) ADIRS DISPLAY DATA TO: - PFD - ND AIMS CABINET (2) - ISFD AOA SENSOR (2) ADIRS - GENERAL DESCRIPTION 34-20-00 - 129 - ALTEON PROPRIETARY.
  • Page 138 777 TRAINING MANUAL ADIRS -- COMPONENT LOCATION - FLIGHT COMPARTMENT ADIRS Component Location The ADIRS components in the flight compartment are: ADIRU switch ADIRU on battery light. Other Systems Component Location The components in the flight compartment that have an interface with the ADIRS are: Left and right control display units (CDUs) Left and right air data/attitude source switches.
  • Page 139 777 TRAINING MANUAL PRIMARY FLIGHT COMPUTERS/ADIRU PANEL (P5 OVERHEAD PANEL) - ADIRU SWITCH - ADIRU ON BATTERY LIGHT P9 FORWARD AISLE STAND PANEL - LEFT CONTROL DISPLAY UNIT - RIGHT CONTROL DISPLAY UNIT P1 LEFT FORWARD PANEL P3 RIGHT FORWARD PANEL - LEFT AIR DATA/ATTITUDE - RIGHT AIR DATA/ SOURCE SWITCH...
  • Page 140 777 TRAINING MANUAL ADIRS -- COMPONENT LOCATION - EQUIPMENT CENTERS ADIRS Component Locations The right power supply assembly has these circuit breakers: These air data inertial reference system (ADIRS) components are in the equipment centers: STATIC ADM PITOT ADM. Air data inertial reference unit (ADIRU) Secondary attitude air data reference unit (SAARU) ADIRU BAT PWR L, C, and R circuit breakers ADIRU PRI PWR L, C, and R circuit breakers.
  • Page 141 777 TRAINING MANUAL P110 LEFT POWER P210 RIGHT POWER MANAGEMENT PANEL MANAGEMENT PANEL - ADIRU PRI PWR L CB - ADIRU PRI PWR C CB - ADIRU PRI PWR R CB E3-3 - ADIRU MAIN EQUIPMENT CENTER P310 STANDBY POWER (LOOKING FORWARD) MANAGEMENT PANEL - ADIRU BAT PWR L CB...
  • Page 142 777 TRAINING MANUAL ADIRS -- COMPONENT LOCATION - AOA SENSORS AND TAT PROBE General The angle of attack (AOA) sensors are on both sides of the fuselage and the TAT probe is on the left side. 34-20-00 - 134 - ALTEON PROPRIETARY.
  • Page 143 777 TRAINING MANUAL RIGHT AOA SENSOR LEFT AOA SENSOR TAT PROBE ADIRS - COMPONENT LOCATION - AOA SENSORS AND TAT PROBE 34-20-00 - 135 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 144 777 TRAINING MANUAL ADIRS -- ADIRU, AOA AND SENSOR, SAARU POWER Air Data Inertial Reference Unit The air data inertial reference unit (ADIRU) gets power from these sources: Right 28v dc bus Left 28v dc bus Hot battery bus. The PFC (primary flight computer)/ADIRU panel supplies on/off discretes to the ADIRU.
  • Page 145 777 TRAINING MANUAL 28V DC L BUS 28V DC ADIRU FCDC-C PRI PWR L SAARU 28V AC L BUS SAARU CENTER POWER SUPPLY RESOLVER 1 ASSEMBLY P110 LEFT POWER MGMT PANEL ADIRU PRI PWR C 28V DC R BUS ADIRU PRI PWR R 28V AC R BUS...
  • Page 146 777 TRAINING MANUAL ADIRS -- AIR DATA MODULES POWER General The power supply assemblies supply power to their onside pitot and static air data modules (ADMs). The left power supply assembly supplies power to the left static and pitot ADMs. The center power supply assembly supplies power to the center static and pitot ADMs.
  • Page 147 777 TRAINING MANUAL STATIC 28V DC LEFT STATIC ADM FCDC-L PITOT ADM LEFT PITOT ADM LEFT POWER SUPPLY ASSEMBLY STATIC 28V DC CENTER STATIC ADM FCDC-C PITOT ADM CENTER PITOT ADM CENTER POWER SUPPLY ASSEMBLY STATIC 28V DC RIGHT STATIC ADM FCDC-R PITOT ADM RIGHT PITOT ADM...
  • Page 148 777 TRAINING MANUAL ADIRS -- DIGITAL INTERFACES THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 140 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 149: Training Manual

    777 TRAINING MANUAL ADIRS -- DIGITAL INTERFACES General Pitot Probes These components send data to the ADIRU and the SAARU The pitot probes send total pressure to the pitot air through the flight controls ARINC 629 buses: data modules (ADMs). The pitot ADMs change the total pressure to ARINC 629 data.
  • Page 150 777 TRAINING MANUAL ADIRS -- DIGITAL INTERFACES SAARU The SAARU receives data on all flight control ARINC 629 buses. The SAARU has one connection to each flight control ARINC 629 bus. The SAARU sends inertial reference and air data to user systems through the center flight control ARINC 629 bus.
  • Page 151 777 TRAINING MANUAL TAT PROBE TAT,AOA,PSEU, L AOA FSEU DATA SENSOR LEFT AIMS CABINET L PFC C PFC R PFC TAT,AOA,PSEU, R AOA FSEU DATA SENSOR RIGHT AIMS CABINET LEFT PITOT L AFDC C AFDC R AFDC PITOT CENTER PROBES PITOT RIGHT PITOT...
  • Page 152 777 TRAINING MANUAL ADIRS -- ADIRU General Three power supplies Three dual channel ARINC 629 input/output The air data inertial reference unit (ADIRU) has two interfaces. functions: Software Loading Air data Inertial reference data. The ADIRU can receive operational program software (OPS) from the AIMS cabinets through the flight The ADIRU has internal redundancy and automatically controls ARINC 629 buses.

  • Page 153: Installation

    777 TRAINING MANUAL FRONT HANDLE COOLING FINS LOCKING BAR INSTALLATION SCREWS ARINC 629 CONNECTORS INSTALLATION SIDE GUIDE POWER HANDLE CONNECTORS INSTALLATION SCREWS ADIRS - ADIRU 34-20-00 - 145 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 154 777 TRAINING MANUAL ADIRS -- ADIRU REMOVAL AND LOCK BAR OPERATION Locking Bar The locking bar prevents these: Removal of the ADIRU until you disconnect the ARINC 629 connections Connection of the ARINC 629 interfaces until you install and secure the ADIRU. Training Information Point You must use a 1/4 inch hex wrench to turn the ADIRU installation screws.
  • Page 155 777 TRAINING MANUAL HG2080 F-T ADIRU SCREWS (2) ADIRU WITH 6 CONNECTORS REMOVED THE ADIRU IS FULLY INSTALLED WITH LOCKING BAR SCREWS TIGHT, LOCKING BAR DOWN AND CONNECTORS IN PLACE SLIDE THE LOCKING BAR UP AND LOOSEN THE SCREWS THE LOOSENED SCREWS MOVE OUT AND HOLD THE LOCKING BAR UP THE ADIRU IS READY FOR REMOVAL ADIRS - ADIRU REMOVAL AND LOCK BAR OPERATION...
  • Page 156 777 TRAINING MANUAL ADIRS -- ADIRU INSTALLATION ADIRU Installation Put the ADIRU on the rack and align the two alignment pins in the back of the ADIRU and one pin in the front of the ADIRU. Do these steps to install the ADIRU: Install the ADIRU in the rack Tighten the screws Slide the locking bar down...
  • Page 157 777 TRAINING MANUAL NOTICE: INSTALL THE ADIRU ON THE AIRPLANE MOUNTING SHELF, THEN LOWER THE LOCKING BAR BEFORE YOU ATTACH THE CONNECTORS. LOCKING BAR NOTICE INSTALL THE ADIRU ON THE SHELF TIGHTEN THE SCREWS MOVE THE LOCK BAR DOWN MAKE SURE ALL CONNECTORS ARE IN THE FULL LOCK POSITION.
  • Page 158 777 TRAINING MANUAL ADIRS -- ADIRU RELIABILITY AND FAULT TOLERANCE General maintenance access terminal (MAT). The maintenance memo is ADIRS and it shows on the maintenance planning page. The ADIRU has fault containment areas (FCAs). The FCAs have fault containment modules (FCMs). The flight crew will not see a flight deck effect.
  • Page 159 777 TRAINING MANUAL SINGLE FCM FAULT FAILURES CONTAINMENT ADIRU MODULES GYRO ACCELEROMETER POWER SUPPLY FAULT CONTAINMENT MULTIPLE AREAS FAILURES (SAME FCA) PROCESSORS PROCESSOR PROCESSOR PROCESSOR PROCESSOR LEFT ARINC CENTER ARINC RIGHT ARINC 629 INTERFACE 629 INTERFACE 629 INTERFACE FAULT CONTAINMENT ARINC ARINC ARINC...
  • Page 160 777 TRAINING MANUAL ADIRS -- SECONDARY ATTITUDE AIR DATA REFERENCE UNIT General The secondary attitude air data reference unit (SAARU) is a backup source of attitude and air data. Physical Description The SAARU weighs 30 pounds. It uses passive cooling. Cooling fins take heat away from the SAARU.
  • Page 161 777 TRAINING MANUAL COOLING FINS ADIRS - SECONDARY ATTITUDE AIR DATA REFERENCE UNIT 34-20-00 - 153 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 162 777 TRAINING MANUAL ADIRS -- TOTAL AIR TEMPERATURE PROBE Purpose A total air temperature (TAT) probe measures temperature outside the airplane. Sensing Elements There are two sensing elements in a TAT probe. Each sensing element is a resistive element. The value of resistance changes when the temperature of the air flow across the element changes.
  • Page 163 777 TRAINING MANUAL INSTALLATION BOLT (6) AIR FLOW SENSING ELEMENTS AIR SUPPLY DISTRIBUTION SYSTEM AIR OUT HEATER AIRPLANE SKIN AIRFLOW OUT FROM SENSING ELEMENTS AIR SUPPLY DISTRIBUTION SYSTEM AIR CONNECTION ELECTRICAL CONNECTOR ELECTRICAL AIR SUPPLY CONNECTOR FROM LEFT AIR CONDITIONING PACK CROSS MANIFOLD ADIRS - TOTAL AIR TEMPERATURE PROBE...
  • Page 164 777 TRAINING MANUAL ADIRS -- ANGLE OF ATTACK SENSOR Electrical Connector The angle of attack (AOA) sensor sends AOA data to the AIMS cabinet and receives heater power through the electrical connector. Resolvers There are two resolvers in each AOA sensor. The AOA data from the two resolvers in the left AOA sensor goes to the left AIMS cabinet.
  • Page 165 777 TRAINING MANUAL HOLE FOR ELECTRICAL MOUNTING CONNECTOR BOLTS (8) ALIGNMENT PINS SENSOR VANE ADIRS - ANGLE OF ATTACK SENSOR 34-20-00 - 157 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 166 777 TRAINING MANUAL ADIRS -- AIR DATA/ATTITUDE SOURCE SWITCH General The captain and first officer air data/attitude switches on the instrument source select panels control the source of attitude and air data that shows for the onside PFD and ND. Air Data/Attitude Switch in the Normal Position When the air data/attitude switches are in the normal position, the ADIRU is the source of attitude and air...
  • Page 167 777 TRAINING MANUAL - ADIRU - ADIRU ATTITUDE ATTITUDE - VOTED - VOTED AIR DATA AIR DATA FROM ADIRU FROM ADIRU DSPL DSPL NORMAL NORMAL CTRL CTRL POSITION POSITION DATA DATA /ATT /ATT - SAARU - SAARU ATTITUDE ATTITUDE ALTN - SINGLE - SINGLE ALTN...
  • Page 168 777 TRAINING MANUAL ADIRS -- ADIRU SWITCH, ADIRU ON BATTERY LIGHT General The primary flight computers/ADIRU panel has the ADIRU switch and the ADIRU on battery light. ADIRU On Battery Light The ADIRU on battery light comes on when the airplane is on the ground and the only source of power for the ADIRU is the hot battery bus.
  • Page 169 777 TRAINING MANUAL ADIRU ON BATTERY LIGHT ADIRU SWITCH ADIRU ON BAT PRIMARY FLIGHT COMPUTERS THRUST ASYM COMP DISC AUTO DISC AUTO PRIMARY FLIGHT COMPUTERS/ADIRU PANEL (P5) ADIRS - ADIRU SWITCH, ADIRU ON BATTERY LIGHT 34-20-00 - 161 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 170 777 TRAINING MANUAL RADIO ALTIMETER SYSTEM -- INTRODUCTION General The radio altimeter (RA) system measures the distance from the airplane to the ground. The radio altitude shows in the flight deck. The system has a range of -20 to 2500 feet. The flight crew and other airplane systems use radio altitude during approach and landing.
  • Page 171 777 TRAINING MANUAL ALTITUDE ABOVE THE GROUND RADIO ALTIMETER SYSTEM - INTRODUCTION 34-33-00 - 163 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 172 777 TRAINING MANUAL RA SYSTEM -- GENERAL DESCRIPTION General The system has three transceivers (xcvr). Each xcvr has a transmit and a receive antenna. The transceivers get discrete inputs from the air ground relays and from the AIMS cabinets. Radio altitude data goes on ARINC 429 data buses to the these components: Airplane information management system (AIMS) cabinets...
  • Page 173 777 TRAINING MANUAL COLLINS RECEIVE ANTENNA TRANSMIT ANTENNA TEST CONN STATUS XMIT ANT FAIL AIMS CABINET (2) ANT FAIL AFDC (3) TEST LRA-900 TCAS COMPUTER GPWC RADIO ALTIMETER WXR RT (2) AIR/GROUND RELAYS TRANSCEIVER (3) RA SYSTEM - GENERAL DESCRIPTION 34-33-00 - 165 - ALTEON PROPRIETARY.
  • Page 174 777 TRAINING MANUAL RA SYSTEM -- COMPONENT LOCATION - 1 General These are the RA system components in the E5 rack in the forward cargo compartment: Right RA transceiver (xcvr) Center RA xcvr Left RA xcvr. These are the RA system components on the bottom of the fuselage: Left RA receive antenna Center RA receive antenna...
  • Page 175 777 TRAINING MANUAL RADIO ALTIMETER TRANSMIT ANTENNAS (LEFT, CENTER, AND RIGHT) (STA 623.5) E5 RACK (FORWARD CARGO COMPARTMENT) - RIGHT RA XCVR (E5-2) - CENTER RA XCVR (E5-3) - LEFT RA XCVR (E5-4) RADIO ALTIMETER RECEIVE ANTENNAS (LEFT, CENTER, AND RIGHT) (STA 665.5) RA SYSTEM - COMPONENT LOCATION - 1 34-33-00...
  • Page 176 777 TRAINING MANUAL RA SYSTEM -- COMPONENT LOCATION - 2 General These are the RA system components and components that interface with the RA system in the flight deck: Primary flight displays (PFD) Left and right EFIS control panels Left and right control display units (CDU). 34-33-00 - 168 - ALTEON PROPRIETARY.
  • Page 177 777 TRAINING MANUAL P55 GLARESHIELD CENTER PANEL - LEFT EFIS CONTROL PANEL - RIGHT EFIS CONTROL PANEL P1 LEFT FORWARD PANEL - PFD P3 RIGHT FORWARD PANEL - PFD P9 FORWARD AISLE STAND PANEL - LEFT CDU - RIGHT CDU RA SYSTEM - COMPONENT LOCATION - 2 34-33-00 - 169 -...
  • Page 178 777 TRAINING MANUAL RA SYSTEM -- POWER, ANTENNA, AND DISCRETE INPUTS Power Input Program Pins Power for the RA xcvrs is 115v ac from: The RA xcvr program pins are: 115v ac left transfer bus (left RA) Continuous data 115v ac standby bus (center RA) Aircraft installation delay (AID) of 80 feet 115v ac right transfer bus (right RA).
  • Page 179 777 TRAINING MANUAL LEFT RA CENTER RA RIGHT RA RECEIVE RECEIVE RECEIVE ANTENNA ANTENNA ANTENNA LEFT RA CENTER RA RIGHT RA RECEIVED RF RECEIVED RF RECEIVED RF TRANSMIT TRANSMIT TRANSMIT ANTENNA ANTENNA ANTENNA 115V AC L AC TRANSMIT RF TRANSMIT RF TRANSMIT RF TRANSFER POWER...
  • Page 180 777 TRAINING MANUAL RA SYSTEM -- GROUND TEST General There are only operational tests available for the radio altimeter system. These are the operational tests available: Center radio altimeter system Left radio altimeter system Right radio altimeter system. Operational Test The purpose of this test is to verify the operation and function of the radio altimeter transceivers.
  • Page 181 777 TRAINING MANUAL Select Operational Test CENTER RADIO ALTIMETER SYSTEM GROUND TESTS LEFT RADIO ALTIMETER SYSTEM RIGHT RADIO ALTIMETER SYSTEM Select ATA System (55) Select Test Type 32 Nose Landing Gear SYSTEM 32 Right Main Landing Gear TEST 34 Instrument Landing System 34 Radio Altimeter System OPERATIONAL 34 Paravisual Display System...
  • Page 182 777 TRAINING MANUAL GLOBAL POSITIONING SYSTEM -- INTRODUCTION General The global positioning system (GPS) uses navigation satellites to supply accurate airplane position to airplane systems and to the flight crew. Abbreviations and Acronyms ADIRU - air data inertial reference unit AIMS - airplane information management system BITE...
  • Page 183 777 TRAINING MANUAL GLOBAL POSITIONING SYSTEM - INTRODUCTION 34-58-00 - 175 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 184 777 TRAINING MANUAL GPS -- GENERAL DESCRIPTION General the flight compartment through the AIMS cabinets. The clocks can show GPS time. The global positioning system (GPS) calculates: Latitude Longitude Altitude Accurate time Ground speed. There are two GPS antennas. The MMRs send power to the antenna amplifier circuits.
  • Page 185 777 TRAINING MANUAL COLLINS LRU STATUS CONTROL FAIL ANT FAIL LEFT EFB EU TEST GLU-920 FLIGHT CONTROLS ARINC 629 BUS (3) LEFT GPS ANTENNA ADIRU LEFT MULTI- MODE RECEIVER GPWC COLLINS LRU STATUS MO/YR CONTROL FAIL DATE ANT FAIL TIME ET/CHR TEST GLU-920...
  • Page 186 777 TRAINING MANUAL GPS -- MAIN EQUIPMENT CENTER COMPONENT LOCATIONS Equipment Center The left MMR is on the E1-2 shelf. The center MMR is on the E1-3 shelf. The right MMR is on the E2-3 shelf. 34-58-00 - 178 - ALTEON PROPRIETARY.
  • Page 187 777 TRAINING MANUAL E2-3 E1-3 E1-2 - LEFT MMR - RIGHT MMR - CENTER MMR (LOOKING AFT) GPS - MAIN EQUIPMENT CENTER COMPONENT LOCATIONS 34-58-00 - 179 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 188 777 TRAINING MANUAL GPS -- ANTENNA LOCATIONS General The GPS antennas are on the top of the fuselage. 34-58-00 - 180 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 189 777 TRAINING MANUAL RIGHT GPS ANTENNA LEFT GPS ANTENNA (STA 655.64) (STA 623.64) GPS - ANTENNA LOCATIONS 34-58-00 - 181 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 190 777 TRAINING MANUAL GPS -- GROUND TEST General There are only system tests available for the GPS. These are the system tests available: Left global positioning system Right global positioning system. System Test This test lets you verify the operation of the GPS function of the multi-mode receivers (MMRs).
  • Page 191 777 TRAINING MANUAL Select System Test LEFT GLOBAL POSITIONING SYSTEM GROUND TESTS RIGHT GLOBAL POSITIONING SYSTEM Select ATA System (55) Select Test Type 34 Ground Proximity Warning System SYSTEM 34 VOR / Marker Beacon System 34 Air Traffic Control (ATC) Mode S System TEST 34 Distance Measuring Equipment 34 Automatic Direction Finder (ADF) System...
  • Page 192 777 TRAINING MANUAL VHF OMNIDIRECTIONAL RANGING (VOR) SYSTEM -- Purpose CMCS - central maintenance computing system EFIS - electronic flight instrument system The VHF omnidirectional ranging (VOR) system is a FMCF - flight management computing function navigation aid that gives magnetic bearing data from a - light emitting diode VOR ground station to the airplane.
  • Page 193 777 TRAINING MANUAL VOR STATION VOR STATION VHF OMNIDIRECTIONAL RANGING (VOR) SYSTEM 34-51-00 - 185 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 194 777 TRAINING MANUAL VOR -- GENERAL DESCRIPTION General The VOR system has two VOR/marker beacon (MB) receivers. The receivers have the VOR and marker beacon functions. This section shows only the VOR operation of the VOR/MB receiver. The VOR receivers get RF inputs from one VOR antenna on the vertical stabilizer.
  • Page 195 777 TRAINING MANUAL COLLINS SYSTEMS ARINC 629 BUS (4) INIT ALTN VNAV LRU STATUS LEGS HOLD PROG EXEC COMM MENU CONTROL FAIL PREV NEXT PAGE PAGE AIMS CABINET (2) L, R CDU TEST AIR/GND VOR-900 RELAYS POWER VOR ANTENNA DIVIDER (2) VOR/MB RECEIVER (2) VOR - GENERAL DESCRIPTION 34-51-00...
  • Page 196 777 TRAINING MANUAL VOR -- FLIGHT DECK COMPONENT LOCATION General The components on the flight deck that interface with the VOR system are: Captain and first officer navigation displays (NDs) Left and right EFIS control panels (CPs) Left and right CDUs Audio control panels (ACPs).
  • Page 197 777 TRAINING MANUAL P55 GLARESHIELD PANEL - LEFT EFIS CP - RIGHT EFIS CP P3 RIGHT FORWARD P1 LEFT FORWARD PANEL PANEL - ND - ND P9 FORWARD AISLE STAND PANEL - LEFT CDU - RIGHT CDU P8 AFT AISLE STAND PANEL - AUDIO CONTROL PANELS (3) VOR - FLIGHT DECK COMPONENT LOCATION 34-51-00...
  • Page 198 777 TRAINING MANUAL VOR -- ANTENNA AND MAIN EQUIPMENT CENTER COMPONENT LOCATION General The VOR antenna is at the top of the vertical stabilizer. These components are in the main equipment center on the E1 and E2 racks: Left and right VOR/MB receivers Left and right RF power dividers Left and right resistor assemblies.
  • Page 199 777 TRAINING MANUAL ANTENNA ANTENNA LOCATION E2-3 RACK LEFT AND RIGHT - RIGHT VOR/MB RESISTOR ASSEMBLIES RECEIVER (AT REAR OF E1-2) LEFT RF POWER DIVIDER RIGHT RF POWER DIVIDER (OUTBD SIDE OF E2) (OUTBD SIDE OF E1) E1-3 RACK - LEFT VOR/MB RECEIVER MAIN EQUIPMENT CENTER (LOOKING AFT)
  • Page 200 777 TRAINING MANUAL VOR -- POWER, ANALOG, AND DISCRETE INTERFACE General Air/Ground Relay These are the components that have interface with the The air/ground relays supply discrete inputs to the VOR system: VOR/MB receivers to do these functions: Circuit breakers Set flight legs (as alternate source, primary is VOR antenna from the CMCF of AIMS)
  • Page 201 777 TRAINING MANUAL 115V AC STBY BUS VOR MKR L 28V DC P11 OVERHEAD CIRCUIT R34003 BREAKER PANEL RESISTOR FREQUENCY ASSY - L SOURCE SELECT AUDIO DISCRETE L CDU K32115 TO L MMR AIR/GND RELAY L RF PWR DIVIDER L VOR/MB RECEIVER TO R AND C DUAL VOR ANTENNA...
  • Page 202 777 TRAINING MANUAL VOR -- ND VOR DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 34-51-00 - 194 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 203: Training Manual

    777 TRAINING MANUAL VOR -- ND VOR DISPLAYS General NAV Data Source When the navigation display mode selector on the EFIS The NAV data source display shows at the top right control panel is in the VOR position and the VOR/ADF corner of the ND.
  • Page 204 777 TRAINING MANUAL VOR -- ND VOR DISPLAYS To/From Pointer and Indicator The to/from indications show if the selected course will take the airplane to or from the VOR station. VOR/ADF Switch Data The VOR/ADF data shows the data source for the left and right bearing pointers and their frequencies.
  • Page 205 777 TRAINING MANUAL DEVIATION SELECTED BAR AND COURSE NAV DATA SCALE POINTER SOURCE VOR FREQUENCY OR IDENTIFIER VOR L VOR L 10.5 10.5 VOR SELECTED COURSE BEARING POINTERS TO/FROM POINTER AND INDICATOR VOR DATA FROM FROM VOR L VOR R VOR L VOR R 10.5...
  • Page 206 777 TRAINING MANUAL VOR -- GROUND TEST General You can test the VOR/MB system from the MAT. These are the tests that are available from the operational test selection on the MAT: Left VOR M/B System Right VOR System. Operational Test The operational test for the left VOR M/B system does a test of: Normal operation of the VOR receiver...
  • Page 207 777 TRAINING MANUAL Select Operational Test LEFT VOR M/B SYSTEM GROUND TESTS RIGHT VOR SYSTEM Select ATA System (55) Select Test Type 34 Paravisual Display System SYSTEM 34 Weather Radar System TEST 34 Traffic Alert and Collision Avoidance System 34 Ground Proximity Warning System OPERATIONAL 34 VOR / Marker Beacon System TEST...
  • Page 208 777 TRAINING MANUAL ILS -- INTRODUCTION Purpose ISFD - integrated standby flight display - multi-mode receiver The multi-mode receiver (MMR) has these functions: - navigation display - primary flight display Instrument landing system (ILS) function - VHF omnidirectional ranging Global positioning system (GPS) function. The ILS function provides lateral and vertical guidance to the runway on approach.
  • Page 209 777 TRAINING MANUAL VERTICAL DEVIATION GLIDESLOPE RUNWAY LATERAL DEVIATION RUNWAY LOCALIZER ILS - INTRODUCTION 34-31-00 - 201 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 210 777 TRAINING MANUAL ILS -- GENERAL DESCRIPTION General The center MMR sends localizer and glideslope deviation to the integrated standby flight display (ISFD). The instrument landing system (ILS) has three multi- mode receivers (MMRs). The ILS system uses inputs from The receivers also send station audio and identifier these antennas: signals to the audio management unit (AMU).
  • Page 211 777 TRAINING MANUAL COLLINS VOR ANTENNA G/S CAPTURE LRU STATUS ANTENNA (2) CONTROL FAIL ISFD ANT FAIL G/S, LOC ANTENNA SWITCH (6) LOC ANTENNA (2) AIMS CABINET (2) G/S TRACK ANTENNA (2) TEST GLU-920 AFDC (3) AIR/GND RELAYS GPWC SYSTEMS ARINC AIMS MMR (3) 629 BUS (4)
  • Page 212 777 TRAINING MANUAL ILS -- FLIGHT COMPARTMENT COMPONENT LOCATION General These components in the flight compartment have an interface with the ILS system: Left and right EFIS control panels Captain and first officer primary flight displays (PFDs) and navigation displays (NDs) Left and right CDUs Integrated standby flight display (IFSD) Audio control panels (ACP).
  • Page 213 777 TRAINING MANUAL P55 GLARESHIELD PANEL - LEFT EFIS CP - RIGHT EFIS CP P3 RIGHT FORWARD PANEL - PFD - ND P1 LEFT FORWARD PANEL - PFD - ND P9 FORWARD AISLE STAND PANEL - LEFT CDU - RIGHT CDU P8 AFT AISLE P2 CENTER FORWARD PANEL STAND PANEL...
  • Page 214 777 TRAINING MANUAL ILS -- MAIN EQUIPMENT CENTER COMPONENT LOCATIONS Equipment Center These are ILS components in the main equipment center: Left, center, and right glideslope antenna switches Left, center, and right multi-mode receivers (MMRs) Left, center, and right localizer antenna switches Left and right resistor assemblies Left and right RF power dividers.
  • Page 215 777 TRAINING MANUAL E1-3 LEFT LOC - RIGHT RF - CENTER MMR ANT SWITCH POWER - CENTER (OUTBD DIVIDER LOC ANT SWITCH SIDE OF (OUTBD SIDE (BEHIND CENTER OF E2) MMR) LEFT AND CENTER GLIDESLOPE ANT SWITCH (RIGHT GLIDESLOPE ANT SWITCH SAME LOCATION ON RIGHT SIDE) E2-3...
  • Page 216 777 TRAINING MANUAL ILS -- NOSE RADOME COMPONENT LOCATIONS General The ILS components in the nose radome are: Left localizer antenna Right and center localizer antennas Left glideslope capture antenna Right and center glideslope capture antennas. 34-31-00 - 208 - ALTEON PROPRIETARY.
  • Page 217 777 TRAINING MANUAL LEFT LOCALIZER ANTENNA (ONLY ONE ELEMENT USED) (SHOWN WITH PARTIAL VIEW OF WEATHER RADAR ANTENNA) RIGHT AND CENTER LOCALIZER ANTENNAS LEFT GLIDESLOPE CAPTURE ANTENNA (ONLY ONE ELEMENT USED) RIGHT AND CENTER GLIDESLOPE CAPTURE ANTENNAS ILS - NOSE RADOME COMPONENT LOCATIONS 34-31-00 - 209 - ALTEON PROPRIETARY.
  • Page 218 777 TRAINING MANUAL ILS -- FUSELAGE COMPONENT LOCATIONS VOR Antenna The VOR antenna is on top of the vertical stabilizer. The VOR antenna receives VOR and localizer signals. Glideslope Track Antennas The glideslope track antennas are on the leading edge of the left and right aft nose gear doors.
  • Page 219 777 TRAINING MANUAL RIGHT GLIDESLOPE TRACK ANTENNA LEFT AND CENTER GLIDESLOPE TRACK ANTENNA RIGHT AFT NOSE GEAR DOOR VOR ANTENNA LEFT AFT NOSE GEAR DOOR NOSE LANDING GEAR ILS - FUSELAGE COMPONENT LOCATIONS 34-31-00 - 211 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 220 777 TRAINING MANUAL ILS -- POWER INPUTS Power Inputs The left and right multi-mode receivers (MMRs) get 115v ac, 400 Hz power from the left and right 115v ac transfer buses. The center MMR gets 115v ac, 400 Hz power from the AC standby bus. The left and right localizer and glideslope antenna switches get 28v dc from the left and right main DC buses.
  • Page 221 777 TRAINING MANUAL 115V AC L XFER MMR L 28V DC L MAIN DC L MMR L LOC ANT SW ILS ANT SWITCH L 115V AC L G/S AC STDBY ANT SW MMR C 28V DC DC STDBY C LOC BAT BUS C MMR ANT SW...
  • Page 222 777 TRAINING MANUAL ILS -- PFD NCD AND INVALID ILS DISPLAYS Frequency or Identifier The ILS frequency or identifier does not show when the ILS input frequency goes invalid or if the selected frequency is not a valid localizer frequency. ILS course Dashes replace the ILS course display when the input goes NCD.
  • Page 223 777 TRAINING MANUAL REPLACE LOCALIZER REMOVE LOCALIZER FREQUENCY OR IDENTIFIER FREQUENCY OR IDENTIFIER AND ILS COURSE WITH DASHES AND ILS COURSE DME 25.3 DME 25.3 4600 4600 1000 1000 L 29.86 IN L 29.86 IN NO COMPUTED DATA DISPLAY INVALID DISPLAY REMOVE GLIDESLOPE REMOVE GLIDESLOPE AND LOCALIZER...
  • Page 224 777 TRAINING MANUAL ILS -- GROUND TEST General You can do a test of the ILS system from the MAT. These are the tests that are available from the operational test selection on the MAT: Center instrument landing system Left instrument landing system Right instrument landing system.
  • Page 225 777 TRAINING MANUAL Select Operational Test CENTER INSTRUMENT LANDING SYSTEM GROUND TESTS LEFT INSTRUMENT LANDING SYSTEM RIGHT INSTRUMENT LANDING SYSTEM Select ATA System (55) Select Test Type 32 Proximity Sensor System (PSS) SYSTEM 32 Left Main Landing Gear TEST 32 Nose Landing Gear 32 Right Main Landing Gear OPERATIONAL 34 Instrument Landing System...
  • Page 226 777 TRAINING MANUAL DISTANCE MEASUREMENT EQUIPMENT SYSTEM -- INTRODUCTION Purpose The distance measuring equipment (DME) system supplies slant range (line of sight) distance between the airplane and the ground station. The DME system supplies station audio and identifier signals to the flight interphone speakers and headsets. Abbreviations and Acronyms - audio control panel AIMS...
  • Page 227 777 TRAINING MANUAL INTERROGATION REPLY DME GROUND STATION DISTANCE MEASUREMENT EQUIPMENT SYSTEM - INTRODUCTION 34-55-00 - 219 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 228 777 TRAINING MANUAL DME SYSTEM -- GENERAL DESCRIPTION General to the other units to inhibit reception in the other units to prevent interference in them. The DME system has two interrogators and two antennas. The DME interrogator receives the station audio The DME interrogator transmits a signal to DME ground identifiers and sends them to the audio management unit stations.
  • Page 229 777 TRAINING MANUAL Collins LRU STATUS AIMS CABINET (2) DME ANTENNA (2) CONTROL FAIL L ATC XPNDR AIR/GND RELAYS R ATC XPNDR TEST DME-900 TCAS COMPUTER SUPPRESSION SPLITTER L, R CDU AIMS DME INTERROGATOR (2) SYSTEMS ARINC CABINET (2) 629 BUS (3) DME SYSTEM - GENERAL DESCRIPTION 34-55-00 - 221 -...
  • Page 230 777 TRAINING MANUAL DME SYSTEM -- COMPONENT LOCATIONS - FLIGHT DECK DME Component locations - Flight Deck These are the components on the flight deck that interface with DME: Left and right EFIS Control Panel (CP) Captain and first officer primary flight displays (PFDs) and navigation displays (NDs) Left and right control display units (CDUs) Audio control panels (ACPs).
  • Page 231 777 TRAINING MANUAL P55 GLARESHIELD PANEL - LEFT EFIS CP - RIGHT EFIS CP P3 RIGHT FORWARD PANEL P1 LEFT FORWARD PANEL - PFD - PFD - ND - ND P9 FORWARD AISLE STAND PANEL - LEFT CDU - RIGHT CDU P8 AFT AISLE STAND PANEL - AUDIO CONTROL PANEL (3)
  • Page 232 777 TRAINING MANUAL DME SYSTEM -- COMPONENT LOCATION - MAIN EQUIPMENT CENTER AND ANTENNAS DME Component Locations These components are in the main equipment center: Left DME interrogator Right DME interrogator DME/ATC/TCAS suppression splitter left and right resistor assemblies. These components are on the exterior of the airplane: Left DME antenna Right DME antenna.
  • Page 233 777 TRAINING MANUAL DME/ATC/TCAS SUPPRESSION SPLITTER (AT REAR, BETWEEN E1/E2) E2-3 E1-2 - RIGHT DME - LEFT DME INTERROGATOR INTERROGATOR LEFT DME ANTENNA (STA 707.5 WL 99.7 LBL 12.4) RIGHT DME ANTENNA (STA 814.5 WL 99.7 RBL 12.4) LEFT AND RIGHT RESISTOR ASSEMBLIES (BEHIND E1-2) MAIN EQUIPMENT CENTER...
  • Page 234 777 TRAINING MANUAL DME SYSTEM -- POWER, ANALOG, AND DISCRETE INTERFACE Power and Antenna Interface DME/ATC/TCAS Suppression Each DME interrogator receives 115v ac from its circuit The DME system, the air traffic control (ATC) system, breaker. and the traffic alert and collision avoidance system (TCAS) operate in the same frequency band.
  • Page 235 777 TRAINING MANUAL 115V AC L AC XFR AUDIO DME L P11 OVERHEAD CIRCUIT BREAKER PANEL K32117 AIR/GND 28V DC RELAY R34003 RESISTOR FREQUENCY ASSY - L SOURCE SELECT DISCRETE L ATC SUPPRESSION TRANSPONDER PULSE L CDU L DME ANT L DME INTERROGATOR TCAS COMPUTER...
  • Page 236 777 TRAINING MANUAL DME SYSTEM -- GROUND TEST General You can do a test of the DME system from the MAT. These tests are available from the operational test selection on the MAT: Left DME System Right DME System. Operational Test The operational test for the left and right DME systems does a check for normal operation of the DME interrogators and the control inputs to both...
  • Page 237 777 TRAINING MANUAL Select Operational Test LEFT DME SYSTEM GROUND TESTS RIGHT DME SYSTEM Select ATA System (55) Select Test Type 34 Paravisual Display System SYSTEM 34 Weather Radar System TEST 34 Traffic Alert and Collision Avoidance System 34 Ground Proximity Warning System OPERATIONAL 34 VOR / Marker Beacion System TEST...
  • Page 238 777 TRAINING MANUAL AUTOMATIC DIRECTION FINDER SYSTEM -- INTRODUCTION Purpose The automatic direction finder (ADF) system is a navigation aid. The ADF receiver uses AM signals from ground stations to calculate the bearing to the station from the airplane longitudinal axis, and to receive standard AM radio broadcasts.
  • Page 239 777 TRAINING MANUAL AIRPLANE LONGITUDINAL AXIS BEARING TO THE STATION ADF STATION AUTOMATIC DIRECTION FINDER SYSTEM - INTRODUCTION 34-57-00 - 231 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 240 777 TRAINING MANUAL ADF SYSTEM -- GENERAL DESCRIPTION General The ADF system has two receivers and two antennas. Description The loop and sense antennas are part of the ADF antenna assembly. The antenna receives signals from the ground stations and sends them to the ADF receiver. The ADF receiver calculates the bearing to the station and sends it to the AIMS cabinets to show on the navigation displays (ND).
  • Page 241 777 TRAINING MANUAL COLLINS LRU STATUS CONTROL FAIL ADF ANTENNA (2) AIMS CABINET TEST ADF-900 INIT ALTN VNAV LEGS HOLD PROG EXEC COMM MENU PREV NEXT PAGE PAGE AIMS SYSTEM ARINC L, R CDU ADF RECEIVER (2) CABINET 629 BUS (3) ADF SYSTEM - GENERAL DESCRIPTION 34-57-00 - 233 -...
  • Page 242 777 TRAINING MANUAL ADF SYSTEM -- FLIGHT DECK COMPONENT LOCATION General These are the components on the flight deck that interface with the ADF system: Left and right EFIS control panel (CP) Captain and first officer navigation display (ND) Left and right control display units (CDUs) Audio control panels (ACPs).
  • Page 243 777 TRAINING MANUAL P55 GLARESHIELD PANEL - LEFT EFIS CP - RIGHT EFIS CP P1 LEFT P3 RIGHT FORWARD PANEL FORWARD PANEL - ND - ND P8 AFT AISLE P9 FORWARD AISLE STAND PANEL STAND PANEL - AUDIO CONTROL - LEFT CDU - RIGHT CDU PANELS (3) ADF SYSTEM - FLIGHT DECK COMPONENT LOCATION...
  • Page 244 777 TRAINING MANUAL ADF SYSTEM -- MAIN EQUIPMENT CENTER AND FUSELAGE COMPONENT LOCATION General The ADF antennas are on the top of the fuselage. The left and right ADF receivers are in the main equipment center on the E1 and E2 racks. 34-57-00 - 236 - ALTEON PROPRIETARY.
  • Page 245 777 TRAINING MANUAL LEFT ADF RIGHT ADF ANTENNA ANTENNA (STA 1354.6) (STA 1291.6) FUSELAGE ANTENNA LOCATION E2-3 E1-2 - RIGHT ADF - LEFT ADF RECEIVER RECEIVER MAIN EQUIPMENT CENTER (LOOKING AFT) ADF SYSTEM - MAIN EQUIPMENT CENTER AND FUSELAGE COMPONENT LOCATION 34-57-00 - 237 - ALTEON PROPRIETARY.
  • Page 246 777 TRAINING MANUAL ADF SYSTEM -- POWER, ANALOG, AND DISCRETE INTERFACES Power The left and right ADF receivers get 115v ac from the The audio management unit (AMU) receives Morse code left and right 115v ac transfer buses. station identifier signals and audio from the receivers and sends them to the flight interphone speakers and The ADF receivers send 12v dc to their ADF antennas.
  • Page 247 777 TRAINING MANUAL 115V AC L XFER BUS ADF L 28V DC P11 OVERHEAD CIRCUIT BREAKER PANEL R34003 RESISTOR FREQUENCY ASSY - L SOURCE SELECT DISCRETE L CDU AUDIO K32117 AIR/GND RELAY 12V DC L ADF RECEIVER L ADF ANT 115V AC R XFER BUS ADF R...
  • Page 248 777 TRAINING MANUAL ADF SYSTEM -- GROUND TEST General You can do a test of the ADF system from the MAT. These are the tests that are available from the operational test selection on the MAT: Left ADF System Right ADF System. Operational Test The operational test for the ADF system makes sure the ADF receiver operates normally.
  • Page 249 777 TRAINING MANUAL Select Operational Test LEFT ADF SYSTEM GROUND TESTS RIGHT ADF SYSTEM Select ATA System (55) Select Test Type 34 Paravisual Display System SYSTEM 34 Weather Radar System TEST 34 Traffic Alert and Collision Warning System 34 Ground Proximity Warning system OPERATIONAL 34 VOR / Marker Beacon System TEST...
  • Page 250 777 TRAINING MANUAL MARKER BEACON SYSTEM -- INTRODUCTION Purpose The marker beacon system supplies visual and aural indications when the airplane flies over marker beacon transmitters. Abbreviations and Acronyms - audio control panel AIMS - airplane information management system - audio management unit BITE - built-in test equipment CMCF...
  • Page 251 777 TRAINING MANUAL AIRPORT RUNWAY INNER MIDDLE OUTER MARKER BEACONS MARKER BEACON SYSTEM - INTRODUCTION 34-32-00 - 243 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 252 777 TRAINING MANUAL MARKER BEACON SYSTEM -- GENERAL DESCRIPTION General The marker beacon system has an antenna and a VOR/marker beacon (VOR/MB) receiver. The marker beacon function only operates in the left VOR/MB receiver. Description The marker beacon antenna receives the marker beacon signals.
  • Page 253 777 TRAINING MANUAL COLLINS LRU STATUS CONTROL FAIL AIMS CABINET (2) TEST VOR-900 MARKER BEACON ANTENNA LEFT VOR/MB RECEIVER MARKER BEACON SYSTEM - GENERAL DESCRIPTION 34-32-00 - 245 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 254 777 TRAINING MANUAL MARKER BEACON SYSTEM -- COMPONENT LOCATIONS General The marker beacon antenna is on the bottom of the fuselage. The left VOR/MB receiver is in the main equipment center. 34-32-00 - 246 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 255 777 TRAINING MANUAL MARKER BEACON ANTENNA (STA 771, WL 688.67, BL 0) E1-3 SHELF - LEFT VOR/MB RECEIVER MAIN EQUIPMENT CENTER MARKER BEACON SYSTEM - COMPONENT LOCATIONS 34-32-00 - 247 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 256 777 TRAINING MANUAL MARKER BEACON SYSTEM -- INTERFACES Power Marker Beacon Output The left VOR/marker beacon (VOR/MB) receiver uses 115v The left VOR/MB receiver supplies marker beacon data to ac for power. the left and right AIMS cabinets. The AIMS cabinets: Antenna Interface Supply marker beacon display data to the PFDs Receive marker beacon fault and status data.
  • Page 257 777 TRAINING MANUAL 115V AC STBY BUS POWER AUDIO VOR MKR L P11 OVERHEAD CIRCUIT AUDIO MANAGEMENT UNIT BREAKER PANEL MARKER BEACON ANTENNA CMCS BUS L AIR/GND DISCRETE LEFT AIMS CABINET K32115 AIR/ GND RELAY (P110) OMNIBEARING MB OUTPUT RIGHT AIMS CABINET LEFT VOR/MB RECEIVER MARKER BEACON SYSTEM - INTERFACES...
  • Page 258 777 TRAINING MANUAL MARKER BEACON SYSTEM -- GROUND TEST General You can do a left VOR/MB system test from the MAT. Left VOR M/B System Test When you do a test of the left VOR system, you also do a test of the marker beacon system. This test verifies the operation of the marker beacon system.
  • Page 259 777 TRAINING MANUAL Select Operational Test LEFT VOR M/B SYSTEM GROUND TESTS RIGHT VOR SYSTEM Select ATA System (55) Select Test Type 34 Radio Altimeter System SYSTEM 34 Paravisual Display System TEST 34 Weather Radar system 34 Traffic Alert and Collision Avoidance system OPERATIONAL 34 Ground Proximity Warning System TEST...
  • Page 260 777 TRAINING MANUAL GPWS -- INTRODUCTION Purpose Abbreviations and Acronyms The purpose of the ground proximity warning system - angle of attack (GPWS) is to alert the flight crew of an unsafe BITE - built-in test equipment condition when near the terrain. It also supplies a EFIS - electronic flight instrument system warning for windshear conditions.
  • Page 261 777 TRAINING MANUAL "PULL-UP..." GPWS - INTRODUCTION 34-46-00 - 253 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 262 777 TRAINING MANUAL GPWS -- GENERAL DESCRIPTION General Description The program pins selects options available for the GPWC. The main component of the ground proximty warning system (GPWS) is the ground proximity warning computer The GPWC sends discretes to the weather radar (WXR) (GPWC).
  • Page 263 777 TRAINING MANUAL PFD (2) ND (2) EXTERNAL RADIO FAULT E N H A N C E D ALTIMETER COMPUTER AIMS TRANSCEIVER (3) COMPUTER CABINET (2) FAIL TCAS COMPUTER AURAL WARNING SPEAKERS WEATHER RADAR RT (2) WARNING WARNING CAUTION WEU (2) CAUTION MASTER WARNING LIGHTS...
  • Page 264 777 TRAINING MANUAL GPWS -- FLIGHT DECK COMPONENT LOCATION GPWS Component Locations These are the GPWS components in the flight deck: Ground proximity glideslope inhibit switch and ground proximity light Ground proximity gear override switch Terrain override switch Ground proximity flap override switch. Other Systems Component Locations These are the components in the flight deck that have an interface with the GPWS:...
  • Page 265 777 TRAINING MANUAL LEFT AND RIGHT AURAL WARNING SPEAKERS P7 GLARESHIELD PANEL - RIGHT EFIS CONTROL PANEL - RIGHT MASTER WARNING LIGHT P7 GLARESHIELD PANEL - LEFT EFIS CONTROL PANEL LANDING GEAR PANEL (P2) - LEFT MASTER WARNING LIGHT - GROUND PROXIMITY GLIDESLOPE INHIBIT SWITCH AND GROUND PROXIMITY LIGHT - GROUND PROXIMITY GEAR...
  • Page 266 777 TRAINING MANUAL GPWS -- MAIN EQUIPMENT CENTER COMPONENT LOCATIONS GPWS Component Locations These components are in the main equipment center: Terrain select relays Ground proximity warning computer (GPWC). 34-46-00 - 258 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 267 777 TRAINING MANUAL E1-4 - GROUND PROXIMITY WARNING COMPUTER (TERRAIN SELECT RELAYS ARE BEHIND E1-4 SHELF) GPWS - MAIN EQUIPMENT CENTER COMPONENT LOCATIONS 34-46-00 - 259 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 268 777 TRAINING MANUAL GPWS -- INTERFACE Power If the three radio altimeter transceivers are valid and the left, right, and center radio altitudes are The GPWC gets 115v ac power from the GND PROX circuit different by more than 500 feet between each other, the breaker on the P11 overhead circuit breaker panel.

  • Page 269: Training Manual

    777 TRAINING MANUAL GPWS -- INTERFACE Longitudinal acceleration Global Positioning System (GPS) Vertical acceleration. The GPWC receives this data from the multi-mode The general purpose (GP) data buses supply this data: receivers (MMRs): Computed airspeed Latitude True airspeed Longitude Barometric altitude Altitude Baro-corrected altitude Vertical speed...
  • Page 270 777 TRAINING MANUAL GPWS -- INTERFACE Landing Gear Panel Weather Radar (WXR) System The landing gear panel has these functions: The WXR receiver-transmitters (RTs) sends predictive windshear (PWS) data to the GPWC to inhibit lower Terrain override switch priority GPWS alerts. Ground proximity gear override switch Ground proximity flap override switch The GPWC sends a discrete to the WXR RTs to inhibit...
  • Page 271 777 TRAINING MANUAL 115V AC AUDIO L XFR RADIO ALT PROX LEFT WEU P11 OVERHEAD L RA XCVR PWS DATA CIRCUIT PWS INHIBIT BREAKER PANEL DISCRETE RIGHT WEU L WXR RT RADIO ALT C RA XCVR PWS DATA TERRAIN OVRD SW R WXR RT GND PROX GEAR OVRD SW RADIO ALT...
  • Page 272 777 TRAINING MANUAL GPWS -- GROUND PROXIMITY WARNING COMPUTER Purpose EXTERNAL FAULT - amber LED turns on for a failure external to the GPWC. The ground proximity warning computer (GPWC) compares COMPUTER OK - green LED stays on when GPWC has the airplanes flight profile, flap and gear position, power and operates normally and terrain clearance to determine if an alert...

  • Page 273: Headphone Jack

    777 TRAINING MANUAL EXTERNAL FAULT E N H A N C E D STATUS COMPUTER INDICATORS COMPUTER FAIL PUSH EJECT PRESS TO SELF TEST PROG SELF TEST HEADPHONES SWITCH CARD UPLOAD/DOWNLOAD CHNG STATUS INDICATORS XFER COMP HEADPHONE JACK XFER FAIL DOOR MEMORY CARD SLOT...
  • Page 274 777 TRAINING MANUAL GPWS -- CONTROL - EFIS CONTROL PANEL Description ND Range Selector The EFIS control panel provides these functions: The EFIS control panel has a six position range selector. The range selections are 10, 20, 40, 80, 320 Enables the navigation displays (NDs) to show and 640 NM.
  • Page 275 777 TRAINING MANUAL MINS BARO RADIO BARO MTRS ND MODE SELECTOR ND RANGE SELECTOR VOR MAP VOR L VOR R ADF R ADF L ARPT DATA TERRAIN MAP SWITCH TERR GPWS - CONTROL - EFIS CONTROL PANEL 34-46-00 - 267 - ALTEON PROPRIETARY.
  • Page 276 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVEL 1 THIS PAGE INTENTIONALLY LEFT BLANK 34-46-00 - 268 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 277 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVEL 1 General test first does a test of these configuration conditions: The ground proximity warning system (GPWS) has six levels of self-test. Each level provides different Program pin parity information about the GPWS. These are the six levels of Airplane configuration database validity self-test: Airplane type.
  • Page 278 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVEL 1 These visual and aural annunciations are for a normal Aural message TERRAIN, TERRAIN, PULL UP. level 1 test: Master warning lights, PFD message PULL UP (red), OBSTACLE alert message (red) on NDs, and aural ND system message, TERR TEST in cyan message OBSTACLE, OBSTACLE, PULL UP Ground proximity warning light and aural message,...
  • Page 279 777 TRAINING MANUAL VOR R 28.5 TERRAIN GPWS TERRAIN AWARENESS TEST PATTERN TERR TEST GPWS - SELF-TEST - LEVEL 1 34-46-00 - 271 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 280 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVELS 2-5 THIS PAGE INTENTIONALLY LEFT BLANK 34-46-00 - 272 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 281 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVELS 2-5 General Description When a test level ends, the aural message PRESS TO CONTINUE shows. Push the self-test button to go to the The ground proximity warning computer (GPWC) has six next test level. If you do not push the self-test levels of self-test: button within three seconds, self-test ends.
  • Page 282 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVELS 2-5 Selected options. the most recent alerts first. You hear the alerts in this order: Level 4 Self-Test - Fault History FLIGHT X (X is the most recent flight leg number) Level 4 self-test shows the GPWS fault history for the GPWS alerts for flight X last 10 flights.
  • Page 283 777 TRAINING MANUAL EXTERNAL FAULT E N H A N C E D COMPUTER COMPUTER FAIL PUSH EJECT PRESS TO SELF TEST SELF-TEST BUTTON PROG HEADPHONES CARD CHNG HEADPHONE JACK XFER COMP XFER FAIL GPWS - SELF-TEST - LEVELS 2-5 34-46-00 - 275 - ALTEON PROPRIETARY.
  • Page 284 777 TRAINING MANUAL GPWS -- SELF-TEST - LEVEL 6 General Description Level 6 Self-Test - Discrete Input Test The ground proximity warning computer (GPWC) has a A level 6 test shows changes in discrete inputs. level six discrete input test. The test starts with the aural message, DISCRETE TEST.
  • Page 285 777 TRAINING MANUAL DISCRETE INPUT INPUT SOURCE ANNUNCIATIONS - GEAR OVERRIDE SWITCH P2-2 PANEL LANDING GEAR DOWN LANDING GEAR UP - FLAP OVERRIDE SWITCH P2-2 PANEL LANDING FLAPS NOT LANDING FLAPS - GLIDESLOPE OVERRIDE SWITCH P2-2 PANEL GLIDESLOPE CANCELLED GLIDESLOPE ENABLED - TERRAIN OVERRIDE SWITCH P2-2 PANEL TERRAIN OFF...
  • Page 286 777 TRAINING MANUAL GPWS -- STATUS LEDS Purpose There are three status LEDs on the front panel of the ground proximity warning computer (GPWC). The LEDs come on when there is power to the GPWC. These LEDs are: External fault - yellow Computer OK - green Computer fail - red.
  • Page 287 777 TRAINING MANUAL EXTERNAL FAULT E N H A N C E D COMPUTER EXTERNAL FAULT COMPUTER OK COMPUTER FAIL CONDITION COMPUTER FAIL GPWC POWER OFF GPWC INTERNAL FAULT GREEN NORMAL OPERATION GREEN GPWC INTERNAL FAULT YELLOW GPWS EXTERNAL FAULT YELLOW BOTH GPWC INTERNAL AND GPWS EXTERNAL...
  • Page 288 777 TRAINING MANUAL GPWS -- GROUND TESTS General You do an operational test of the GPWS from the MAT. Operational Test The operational test makes sure the ground proximity warning system operates correctly. You get these indications when you do an operational test: All the GPWS aurals The master warning lights come on...

  • Page 289: Ground Proximity Warning System

    777 TRAINING MANUAL Select Operational Test GROUND PROXIMITY WARNING SYSTEM GROUND TESTS Select ATA System (55) Select Test Type 34 Weather Radar System SYSTEM 34 Traffic Alert and Collision Avoidance System TEST 34 Ground Proximity Warning System 34 VOR/Marker Beacon System OPERATIONAL 34 Air Traffic Control (ATC) Mode S System TEST...
  • Page 290 777 TRAINING MANUAL WEATHER RADAR SYSTEM -- INTRODUCTION Purpose - predictive windshear - radio altimeter The weather radar (WXR) system supplies: - radio frequency - receiver-transmitter Visual indications of weather conditions TCAS - traffic and collision avoidance system Visual indications of land contours. - warning electronics system Description - warning electronics unit...
  • Page 291 777 TRAINING MANUAL WEATHER RADAR SYSTEM - INTRODUCTION 34-43-00 - 283 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 292 777 TRAINING MANUAL WXR SYSTEM -- GENERAL DESCRIPTION Control Receives the RF returns Supplies the WXR display data. These components supply weather radar (WXR) system control: Interfaces Left, center, and right control display units The WXR system has interfaces with these systems: (CDUs) Left and right EFIS CPs Warning electronic system (WES)
  • Page 293 777 TRAINING MANUAL TO NAVIGATION DISPLAYS SYSTEMS ARINC 629 GPWS BUS (4) CDU (3) MINS BARO RADIO BARO MTRS TCAS VOR L VOR R WXR ANTENNA SYSTEM ADF L ADF R ARPT DATA TERR EFIS CP (2) LEFT OPAS WX+T AIMS LANDING GEAR CABINET...
  • Page 294 777 TRAINING MANUAL WXR SYSTEM -- COMPONENT LOCATIONS - FLIGHT DECK WXR System Components The WXR system component on the flight deck is the weather radar panel. WXR System Interface Components The components that interface with the WXR system are: Left EFIS control panel Right EFIS control panel Left control display unit (CDU)
  • Page 295 777 TRAINING MANUAL RIGHT AURAL LEFT AURAL WARNING SPEAKER WARNING SPEAKER P55 GLARESHIELD CENTER PANEL - LEFT EFIS CONTROL PANEL RIGHT MASTER WARNING LIGHT - RIGHT EFIS CONTROL PANEL P2 CENTER FORWARD PANEL - LANDING GEAR CONTROL LEFT MASTER LEVER MODULE WARNING LIGHT P1 LEFT FORWARD PANEL P3 RIGHT FORWARD PANEL...
  • Page 296 777 TRAINING MANUAL WXR SYSTEM -- COMPONENT LOCATIONS - FORWARD EQUIPMENT CENTER AND NOSE RADOME General The WXR antenna assembly is in the nose radome. The WXR system components in the forward equipment center are the: Left WXR RT Waveguide switch Right WXR RT.
  • Page 297 777 TRAINING MANUAL WAVEGUIDE WXR ANTENNA SWITCH ASSEMBLY LEFT WXR RT RIGHT WXR RT NOSE RADOME FORWARD EQUIPMENT CENTER WXR SYSTEM - COMPONENT LOCATIONS - FORWARD EQUIPMENT CENTER AND NOSE RADOME 34-43-00 - 289 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 298 777 TRAINING MANUAL WXR SYSTEM -- INTERFACE - POWER, INTERLOCKS, ENABLES AND RF TRANSMISSION System Power The RT ENABLE also causes the waveguide switch to connect the antenna to the selected RT. When the The left WXR RT gets 115v ac through the left WXR selected RT operates, it sends 28v to the WXR panel circuit breaker from the left ac transfer bus (L AC power supply to make the WXR panel operate.
  • Page 299 777 TRAINING MANUAL 115V AC 115V AC L AC WXR L 28V DC 115V AC SYSTEM R AC ON/OFF SEC 2 28V DC WXR R INTRLK P11 OVERHEAD CB PANEL ENABLE LEFT WXR RT CONNECT LEFT EFIS CP L RT ENABLE LEFT RT RIGHT EFIS CP L, C, R CDU INPUTS...
  • Page 300 777 TRAINING MANUAL WXR SYSTEM -- WEATHER RADAR PANEL Purpose Test The weather radar (WXR) panel has controls for WXR The TEST switch lets the flight crew do an operation system operation. test of the WXR system. Line maintenance personnel use the MAT to do a test of the WXR system.
  • Page 301 777 TRAINING MANUAL TILT AND GAIN CONTROL LEFT WX+T TILT LEFT AND RIGHT LR/T RR/T TEST MODE SELECT GAIN GAIN SWITCHES TILT WX+T RIGHT TEST SYSTEM SELECT SWITCH SWITCHES WXR SYSTEM - WEATHER RADAR PANEL 34-43-00 - 293 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 302 777 TRAINING MANUAL WXR SYSTEM -- CONTROL - EFIS CONTROL PANEL EFIS Control Panel If the mode selector is not in a correct mode when you push the WXR map switch, the weather display arms. When These are the functions of the EFIS control panel for armed, the weather display shows as soon as you change WXR control: the ND selector to a correct mode.
  • Page 303 777 TRAINING MANUAL MINS BARO RADIO BARO MTRS ND MODE SELECTOR ND RANGE SELECTOR VOR L VOR R ADF L ADF R WXR MAP SWITCH ARPT DATA WXR SYSTEM - CONTROL - EFIS CONTROL PANEL 34-43-00 - 295 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 304 777 TRAINING MANUAL WXR SYSTEM -- SELF-TEST THIS PAGE INTENTIONALLY LEFT BLANK 34-43-00 - 296 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 305: Training Manual

    777 TRAINING MANUAL WXR SYSTEM -- SELF-TEST General Push the WXR button to supply power to the selected The WXR self-test function does a test of the WXR system. This test gives the flight crew a way to do a Select TEST on the WXR control panel to start self- check of the WXR system.
  • Page 306 777 TRAINING MANUAL WXR SYSTEM -- SELF-TEST Training Information Point Many LRUs on the 777 are compatible with other model airplanes that do not have a central maintenance computing system (CMCS). For this reason, the WXR system shows fail messages on the ND. Maintenance personnel should use the MAT to do a test of the WXR system.
  • Page 307 777 TRAINING MANUAL WEATHER TEST PATTERN REMOVED VOR R VOR R SYMBOL 28.5 28.5 MAGENTA YELLOW GREEN TEST PASS MESSAGE TEST FAIL FAIL TEST - WXR TEST - PWS MODE AND TILT TEST LRU OR FUNCTION FAILURE FROM - RT FROM - ANT - CONT...
  • Page 308 777 TRAINING MANUAL WXR SYSTEM -- LRU REPLACEMENT TEST General Test Start The WXR system LRU replacement test does an internal Follow the instructions on the MAT to start a WXR LRU check of WXR RT operations. This test also makes sure replacement test.
  • Page 309 777 TRAINING MANUAL Select LRU Replacement Test LEFT WXR SYSTEM GROUND TESTS RIGHT WXR SYSTEM Select ATA System (55) Select Test Type 34 Weather Radar System 34 Traffic Alert and Collision Avoidance System SYSTEM TEST 34 Ground Proximity Warning System 34 VOR/Marker Beacon System OPERATIONAL 34 Air Traffic Control (ATC) Mode S System...
  • Page 310 777 TRAINING MANUAL WXR SYSTEM -- SYSTEM TEST THIS PAGE INTENTIONALLY LEFT BLANK 34-43-00 - 302 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 311 777 TRAINING MANUAL WXR SYSTEM -- SYSTEM TEST Training Information Point Aural message - GO AROUND, WINDSHEAR AHEAD, (pause) WINDSHEAR AHEAD, WINDSHEAR AHEAD The weather radar (WXR) system transmits some pulses to Red WINDSHEAR message on ND and PFD let BITE monitor for correct operation. Do not do a Master warning lights on test of the WXR system in a hangar.
  • Page 312 777 TRAINING MANUAL WXR SYSTEM -- SYSTEM TEST Training Information Point The maintenance manual and the fault isolation manual do not have tasks for the WXR FAIL messages on the ND. Many LRUs on the 777 are compatible with other model airplanes that do not have a central maintenance computing system (CMCS).
  • Page 313 777 TRAINING MANUAL Select System Test LEFT WXR SYSTEM GROUND TESTS RIGHT WXR SYSTEM Select ATA System (55) Select Test Type 34 Weather Radar System SYSTEM 34 Traffic Alert and Collision Avoidance System TEST 34 Ground Proximity Warning System 34 VOR/Marker Beacon System OPERATIONAL 34 Air Traffic Control (ATC) Mode S System TEST...
  • Page 314 777 TRAINING MANUAL AIR TRAFFIC CONTROL/MODE S TRANSPONDER SYSTEM -- THIS PAGE INTENTIONALLY LEFT BLANK 34-53-00 - 306 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 315 777 TRAINING MANUAL AIR TRAFFIC CONTROL/MODE S TRANSPONDER SYSTEM -- General - air traffic control ATCRBS - air traffic control radio beacon system The air traffic control (ATC) ground stations make BITE - built-in test equipment interrogations of the airborne ATC/mode S transponder - below system.
  • Page 316 777 TRAINING MANUAL AIR TRAFFIC CONTROL/MODE S TRANSPONDER SYSTEM -- TCAS - traffic alert and collision avoidance system - transponder - transfer xpdr - transponder xpndr - transponder 34-53-00 - 308 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 317 777 TRAINING MANUAL INTERROGATION REPLY MODE S INTERROGATION MODE S REPLY SECONDARY FOR TCAS SURVEILLANCE RADAR (SSR) ANTENNA PRIMARY SURVEILLANCE RADAR (PSR) ANTENNA SIDE LOBE SUPPRESSION (SLS) ANTENNA GROUND RADAR DISPLAY ATC RADAR TRANSMITTER/ ATC GROUND STATION RADAR ATC FACILITY RECEIVER AIR TRAFFIC CONTROL/MODE S TRANSPONDER SYSTEM 34-53-00...
  • Page 318 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- GENERAL DESCRIPTION General The ATC/mode S transponders have an interface with the TCAS computer. When a ground station or a traffic collision avoidance system (TCAS) computer from a different airplane makes an interrogation of the air traffic control (ATC)/mode S transponder system, the transponder transmits a pulse-coded reply signal.
  • Page 319 777 TRAINING MANUAL PASS AIMS CABINET (2) FAIL UPPER ANT LOWER ANT ATC COAX RELAY TCAS COMPUTER (TOP) ANTENNA (TOP) TEST TPR-900 DME/ATC/TCAS INT (2) SUPPRESSION ANTENNA ATC COAX RELAY SPLITTER (BOTTOM) (BOTTOM) ABS REL ATC/MODE S TRANSPONDER (2) PROGRAM SWITCH MODULE (2) ATC L NORM...
  • Page 320 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- COMPONENT LOCATIONS Flight Deck The transponder panel is on the P8 aft aisle stand. Main Equipment Center These are the ATC/Mode S transponder system components in the main equipment center: Left ATC/Mode S transponder Right ATC/Mode S transponder DME/ATC/TCAS suppression splitter Left program switch module...
  • Page 321 777 TRAINING MANUAL E2 RACK DME/ATC/TCAS SUPPRESION E1 RACK - BOTTOM ATC SPLITTER (AT REAR BETWEEN - TOP ATC COAX COAX RELAY E1/E2) RELAY (BEHIND LEFT AFDC) MAIN EQUIPMENT CENTER P8 AFT AISLE STAND - TRANSPONDER PANEL E2-3 E1-3 - RIGHT ATC/MODE S - LEFT ATC/MODE S TRANSPONDER TRANSPONDER...
  • Page 322 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- ANTENNA LOCATION General The top antenna is on top of the fuselage and the bottom antenna is bottom of the fuselage. 34-53-00 - 314 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 323 777 TRAINING MANUAL TOP ATC ANTENNA (STA 560.5) BOTTOM ATC ANTENNA (STA 480) ATC/MODE S TRANSPONDER SYSTEM - ANTENNA LOCATION 34-53-00 - 315 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 324 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- POWER, IDENTITY, CONTROL, AND AIR DATA INTERFACES Power air data to the AIMS cabinets. The ATC/Mode S transponders receive the air data from both AIMS The left ATC/Mode S transponder gets 115v ac power from cabinets.
  • Page 325 777 TRAINING MANUAL 115V AC AC STBY ATC L 115V AC R AC XFR GP BUS 3 ADC INPUT 1 (ADIRU) ATC R ADC INPUT 2 P11 OVERHEAD LEFT STANDBY/ON CIRCUIT BREAKER LEFT AIMS PANEL (GND = STBY) CABINET IDENTITY CODE AND CONTROL DATA LEFT ATC/MODE S TRANSPONDER...
  • Page 326 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- TRANSPONDER PANEL THIS PAGE INTENTIONALLY LEFT BLANK 34-53-00 - 318 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 327 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- TRANSPONDER PANEL General discrete to the right transponder only. Then the right transponder is in standby. The left transponder is The dual transponder panel controls the ATC/Mode S active. transponder and the TCAS computer. With the right position selected, the control panel The ATC controls and displays on the transponder panel sends an open standby/on discrete to the right...
  • Page 328 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- TRANSPONDER PANEL STBY (standby) - a ground discrete goes to both transponders; this ground discrete prevents operation of the transponder, but does not prevent built-in-test-equipment (BITE) functions. ALT RPTG OFF (altitude reporting off) - the active transponder responds to ATC interrogations with mode A replies only XPNDR (transponder) - the active transponder...
  • Page 329 777 TRAINING MANUAL FOUR DIGIT IDENTIFICATION CODE WINDOW ACTIVE SYSTEM ABOVE-NORMAL-BELOW DISPLAY SWITCH ABS REL ALTITUDE ATC L SOURCE SELECTOR NORM ALTN XPNDR TA ONLY RPTG OFF SOURCE STBY TA/RA TRANSPONDER SELECTOR IDENT TRANSPONDER XPNDR MODE SELECTOR IDENT SWITCH TRANSPONDER CODE SELECTORS ATC/MODE S TRANSPONDER SYSTEM - TRANSPONDER PANEL 34-53-00...
  • Page 330 777 TRAINING MANUAL ATC/MODE S TRANSPONDER SYSTEM -- GROUND TESTS General You can do a system test of the ATC/Mode S transponder system from the MAT. System Test There is a system test for the left ATC/Mode S transponder system and the right ATC/Mode S transponder system.
  • Page 331 777 TRAINING MANUAL Select System Test LEFT ATC SYSTEM GROUND TESTS RIGHT ATC SYSTEM Select ATA System (55) Select Test Type 34 Weather Radar System 34 Traffic Alert and Collision Avoidance System SYSTEM 34 Ground Proximity Warning System TEST 34 VOR/Marker Beacon System 34 Air Traffic Control (ATC) Mode S System OPERATIONAL 34 Distance Measuring Equipment System...
  • Page 332 777 TRAINING MANUAL TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM -- INTRODUCTION General - resolution advisory - relative The traffic alert and collision avoidance system (TCAS) TCAS - traffic alert and collision avoidance helps the flight crew and air traffic control maintain system safe air traffic separation.
  • Page 333 777 TRAINING MANUAL TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM - INTRODUCTION 34-45-00 - 325 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 334 777 TRAINING MANUAL TCAS -- GENERAL DESCRIPTION General The traffic alert and collision avoidance system (TCAS) interrogates other airplanes to get altitude, range, and bearing data. TCAS uses the replies and inputs from other onboard airplanes systems to calculate traffic avoidance data.
  • Page 335 777 TRAINING MANUAL TOP TCAS DIRECTIONAL TOP ATC ANTENNA ANTENNA WXR RT (2) Collins DISPLAYS PASS FAIL AIMS CABINET (2) BOTTOM ATC X PNDR ANTENNA UPPER ANT TO AURAL LOWER ANT WARNING RAD ALT SPEAKERS ATC/MODE S HDNG TRANSPONDER (2) WARNING ELECTRONIC UNIT (2) TEST...
  • Page 336 777 TRAINING MANUAL TCAS -- COMPONENT LOCATIONS Main Equipment Center The TCAS computer and the DME/ATC/TCAS suppression splitter are in the main equipment center. Flight Deck These are the components in the flight deck that interface with TCAS: Left EFIS control panel Captain primary flight display (PFD) Captain navigation display (ND) Right EFIS control panel...
  • Page 337 777 TRAINING MANUAL P55 GLARESHIELD CENTER PANEL - LEFT EFIS CONTROL PANEL - RIGHT EFIS CONTROL PANEL P3 RIGHT FORWARD PANEL - FIRST OFFICER PFD P1 LEFT FORWARD PANEL - FIRST OFFICER ND - CAPTAIN PFD - CAPTAIN ND P8 AFT AISLE STAND PANEL - TRANSPONDER PANEL DME/ATC/TCAS SUPPRESSION SPLITTER (AT REAR, BETWEEN...
  • Page 338 777 TRAINING MANUAL TCAS -- ANTENNA LOCATION General The top TCAS antenna is on top of the fuselage. The bottom TCAS antenna is on bottom of the fuselage. 34-45-00 - 330 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 339 777 TRAINING MANUAL TOP TCAS ANTENNA (STA 455.5) BOTTOM TCAS ANTENNA (STA 539, LBL 6.3) TCAS - ANTENNA LOCATION 34-45-00 - 331 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 340 777 TRAINING MANUAL TCAS -- POWER, ANTENNAS, ANALOG DISCRETE INTERFACES AND PROGRAM PINS THIS PAGE INTENTIONALLY LEFT BLANK 34-45-00 - 332 - ALTEON PROPRIETARY. Copyright. See title page for details...

  • Page 341: Training Manual

    777 TRAINING MANUAL TCAS -- POWER, ANTENNAS, ANALOG DISCRETE INTERFACES AND PROGRAM PINS General AIMS - Display Status The TCAS computer has interfaces with these components: An analog discrete from either AIMS cabinet goes to the TCAS computer when the display function of AIMS fails. Overhead circuit breaker panel When the TCAS computer gets this discrete, the TCAS Top and bottom TCAS directional antennas...
  • Page 342 777 TRAINING MANUAL TCAS -- POWER, ANTENNAS, ANALOG DISCRETE INTERFACES AND PROGRAM PINS WXR - TCAS Alert Inhibit The TCAS computer gets an inhibit discrete from the predictive windshear (PWS) function of WXR. When there is a PWS alert, this discrete does these functions: Changes TCAS resolution advisories (RAs) to traffic advisories (TAs) Inhibits TCAS aural alerts.
  • Page 343 777 TRAINING MANUAL 115V AC L AC SEC 2 115V AC TCAS L ATC/MODE S TRANSPONDER P11 OVERHEAD CIRCUIT BREAKER PANEL RF TRANSMIT AND RECEIVE SUPPRESSION R ATC/MODE S TOP TCAS TRANSPONDER DIRECTIONAL ANT RF TRANSMIT AND RECEIVE L DME BOTTOM TCAS INTERROGATOR DIRECTIONAL ANT...
  • Page 344 777 TRAINING MANUAL TCAS -- GROUND TESTS General You can do a TCAS system test from the MAT. TCAS System Test The TCAS system test makes sure the TCAS computer and its interfaces operate properly. You get these indications when you do a system test: Traffic symbols on the NDs Up and down preventative advisories on the PFDs TCAS TEST PASS or FAIL aural at the end of the...
  • Page 345 777 TRAINING MANUAL Select System Test TCAS GROUND TESTS Select ATA System (55) Select Test Type 34 Weather Radar System 34 Traffic Alert and Collision Avoidance System SYSTEM 34 Ground Proximity Warning System TEST 34 VOR/Marker Beacon System 34 Air Traffic Control (ATC) Mode S System OPERATIONAL 34 Distance Measuring Equipment System TEST...
  • Page 346 777 TRAINING MANUAL CLOCKS -- INTRODUCTION General The clocks give time reference to the flight crew. Abbreviations and Acronyms AIMS - airplane information management system ARINC - Aeronautical Radio, Incorporated - control display unit - chronograph - hours/days HLDY - hold/year - global positioning system GPSSU - global positioning system sensor unit...
  • Page 347 777 TRAINING MANUAL MO/YR DATE TIME ET/CHR HLDY RESET CLOCKS - INTRODUCTION 31-25-00 - 339 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 348 777 TRAINING MANUAL CLOCKS -- GENERAL DESCRIPTION General This is the data that the clocks show: Time and date set manually from the clock Universal time (controlled) (UTC) and date from the airplane information management system (AIMS) Elapsed time Chronograph time. Use the clock switches on the glareshield panel to control the chronograph function of the clocks.
  • Page 349 777 TRAINING MANUAL CLOCK TIME/DATE MO/YR DATE TIME GPS TIME CLOCK ET/CHR AIMS UTC/DATE MULTI-MODE HLDY CLOCK SWITCH (2) RECEIVER (2) RESET CLOCK (2) AIMS CABINET (2) CLOCKS - GENERAL DESCRIPTION 31-25-00 - 341 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 350 777 TRAINING MANUAL CLOCKS -- COMPONENT LOCATIONS General These are the clock system components: Captain clock First Officer clock Captain clock switch First Officer clock switch. 31-25-00 - 342 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 351 777 TRAINING MANUAL P7 GLARESHIELD PANEL - CAPTAIN CLOCK SWITCH - FIRST OFFICER CLOCK SWITCH P1 LEFT FORWARD PANEL P3 RIGHT FORWARD PANEL - LEFT CLOCK - RIGHT CLOCK CLOCKS - COMPONENT LOCATIONS 31-25-00 - 343 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 352 777 TRAINING MANUAL CLOCKS -- CLOCK Displays Time/Date Selector The clock has a time/date window and an elapsed The time/date selector is a push-button rotary two- time/chronograph window. Both are liquid crystal position switch. In the MAN (manual) position, clock displays (LCDs).

  • Page 353: Elapsed Time

    777 TRAINING MANUAL TIME/DATE WINDOW CHRONOGRAPH SWITCH TIME/DATE SELECTOR SWEEP ELAPSED TIME/ MO/YR DATE SECOND HAND CHRONOGRAPH WINDOW TIME ET/CHR HLDY RESET ELAPSED TIME CLOCK SET SELECTOR SELECTOR CLOCKS - CLOCK 31-25-00 - 345 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 354 777 TRAINING MANUAL WARNING ELECTRONIC SYSTEM -- INTRODUCTION THIS PAGE INTENTIONALLY LEFT BLANK 31-51-00 - 346 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 355 777 TRAINING MANUAL WARNING ELECTRONIC SYSTEM -- INTRODUCTION General - main landing gear - maximum operating mach number The warning electronic system (WES) supplies - master warning light indications of incorrect airplane system conditions to - no computed data the flight crew. - nose landing gear OPBC - overhead panel bus controller...
  • Page 356 777 TRAINING MANUAL WARNING ELECTRONIC SYSTEM -- INTRODUCTION - maximum flaps extended speed - maximum gear extended speed VMAX - maximum speed limit VMIN - minimum speed limit - maximum operating speed - stick shaker speed VSSNG - maneuver margin above stick shaker speed - warning electronic system - warning electronic unit - weather radar...
  • Page 357 777 TRAINING MANUAL WARNING ELECTRONIC SYSTEM - INTRODUCTION 31-51-00 - 349 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 358 777 TRAINING MANUAL WES -- GENERAL DESCRIPTION General Weather radar (WXR) system Airplane information management system (AIMS) for The warning electronic system (WES) has two warning displays, maintenance functions, and data electronic units (WEUs). Each WEU has two internal conversion. channels which do the same functions.
  • Page 359 777 TRAINING MANUAL LEFT MASTER WARNING WARNING LIGHT CAUTION LEFT AURAL WARNING SPEAKER LEFT WEU LEFT STICK SHAKER ACTUATOR DISCRETE GPWC ANALOG INPUTS AIMS TCAS COMPUTER CABINET RIGHT MASTER WARNING WARNING LIGHT CAUTION SYSTEMS ARINC RIGHT WEU RIGHT AURAL 629 BUS (3) WARNING SPEAKER RIGHT STICK SHAKER ACTUATOR...
  • Page 360 777 TRAINING MANUAL WES -- COMPONENT LOCATIONS 1 General The warning electronic units (WEUs) are in the main equipment center. The alternate gear down dispatch switch is on the right side of the lower main equipment access hatch. 31-51-00 - 352 - ALTEON PROPRIETARY.
  • Page 361 777 TRAINING MANUAL E1-5 SHELF - LEFT WARNING ELECTRONIC UNIT ALTERNATE GEAR DOWN DISPATCH SWITCH ACCESS DOOR E4-2 SHELF MAIN EQUIPMENT CENTER - RIGHT WARNING ELECTRONIC UNIT (LOOKING AFT) MAIN EQUIPMENT CENTER (LOOKING FWD) WES - COMPONENT LOCATIONS 1 31-51-00 - 353 - ALTEON PROPRIETARY.
  • Page 362 777 TRAINING MANUAL WES -- COMPONENT LOCATIONS 2 General The WES components in the flight deck, show on the graphic. 31-51-00 - 354 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 363 777 TRAINING MANUAL LEFT AURAL WARNING SPEAKER RIGHT AURAL WARNING SPEAKER LEFT MASTER WARNING LIGHT RIGHT MASTER WARNING LIGHT FLIGHT DECK FLOOR (REF) RIGHT CONTROL COLUMN (REF) STICK SHAKER ACTUATORS (BELOW FLOOR) WES - COMPONENT LOCATIONS 2 31-51-00 - 355 - ALTEON PROPRIETARY.
  • Page 364 777 TRAINING MANUAL WES -- POWER INPUTS General Each WEU receives two 28v dc inputs, one for each internal channel. Each aural warning speaker and each stick shaker actuator receives 28v dc for operation. 31-51-00 - 356 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 365 777 TRAINING MANUAL WARN WARN SPKR/ SPKR L STICK SHAKER L LEFT AURAL WARNING SPEAKER STICK 28V DC SHAKER L POWER SEC 2 WEU L1 CHANNEL L1 LEFT STICK POWER WEU L2 SHAKER ACTUATOR CHANNEL L2 P310 STANDBY POWER MANAGEMENT PANEL LEFT WEU WARN SPKR R...
  • Page 366 777 TRAINING MANUAL WES -- STICK SHAKER ACTUATOR General The stick shaker actuators are dc motors that shake the control columns when the airplane is near a stall condition. The WEUs control the stick shaker actuators. There are two stick shaker actuators, one below each control column.
  • Page 367 777 TRAINING MANUAL FLIGHT DECK FLOOR LEFT STICK SHAKER ACTUATOR RIGHT STICK SHAKER ACTUATOR RIGHT CONTROL COLUMN CONTROL COLUMN (BELOW FLOOR) WES - STICK SHAKER ACTUATOR 31-51-00 - 359 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 368 777 TRAINING MANUAL WES -- ALTERNATE GEAR DOWN DISPATCH SWITCH Description The alternate gear down dispatch switch has two positions. Operation When the alternate gear down dispatch switch is in the maximum operating speed (VMO) position, the WEU channels use the switch signals to lower the maximum speed limit to 270 knots and the maximum operating mach (MMO) to mach .73.
  • Page 369 777 TRAINING MANUAL MAIN EQUIPMENT CENTER LOWER ACCESS DOOR ALTERNATE GEAR DOWN DISPATCH SWITCH NORMAL ALTERNATE GEAR DOWN DISPATCH S33076 S33007 GND E/E BAY FWD E/E BAY S27033 LTS SWITCH LTS SWITCH GD41229 WES - ALTERNATE GEAR DOWN DISPATCH SWITCH 31-51-00 - 361 - ALTEON PROPRIETARY.
  • Page 370 777 TRAINING MANUAL WES -- STICK SHAKER ACTUATION General Each WEU channel independently calculates stick shaker actuator signals when the airplane is near a stall. Interlocks The stick shaker actuators come on only when the two channels inside a WEU produce a stick shaker actuation signal.
  • Page 371 777 TRAINING MANUAL INTLCK LEFT WEU LEFT STICK SHAKER ACTUATOR AIRPLANE DATA INTLCK RIGHT WEU RIGHT STICK SHAKER ACTUATOR WES - STICK SHAKER ACTUATION 31-51-00 - 363 - ALTEON PROPRIETARY. Copyright. See title page for details...
  • Page 372 777 TRAINING MANUAL WES -- GROUND TESTS - 1 General WES System Test These are the WES tests you can do from the MAT: The WES system test verifies the status of each one of the WES channels. The test also verifies the operation WES system test of these: Takeoff configuration warning test...
  • Page 373 777 TRAINING MANUAL Select System Test LANDING CONFIGURATION WARNING GROUND TESTS TAKEOFF CONFIGURATION WARNING WARNING ELECTRONIC SYSTEM Select ATA System (55) Select Test Type 31 AIMS - Airplane Condition Monitoring System SYSTEM 31 AIMS - Left AIMS TEST 31 AIMS - Right AIMS 31 Warning Electronic System OPERATIONAL 31 AIMS - Display System...
  • Page 374 777 TRAINING MANUAL WES -- GROUND TESTS - 2 General You do the stall warning test from the MAT. Training Information Point The WES is in ATA chapter 31. However, you must select ATA System 27 Stall Warning Management to do a stall warning test.

  • Page 375: Stall Warning

    777 TRAINING MANUAL Select System Test STALL WARNING GROUND TESTS Select ATA System (55) Select Test Type 26 Cargo Smoke Detection System SYSTEM 26 Fire Extinguishing System TEST 27 Primary Flight Control System 27 Stall Warning Management OPERATIONAL 27 High Lift System TEST 29 Hydraulic System 30 Airfoil Cowl Ice Protection System...

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