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Boeing ALTEON 777 Training Manual

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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

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ECIPIENT

BY ACCEPTING THIS DOCUMENT

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THAT NEITHER THIS DOCUMENT NOR THE INFORMATION DISCLOSED HEREIN NOR ANY PART THEREOF SHALL BE REPRODUCED OR TRANSFERRED TO OTHER DOCUMENTS

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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UNPUBLISHED, ALL RIGHTS RESERVED UNDER COPYRIGHT LAWS (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OR DISCLOSED TO OTHERS FOR MANUFACTURING OR FOR ANY OTHER PURPOSE EXCEPT AS SPECIFICALLY AUTHORIZED IN WRITING BY LTEON UNPUBLISHED, ALL RIGHTS RESERVED UNDER COPYRIGHT LAWS ( ) 2003 A L.L.C LTEON RAINING This manual has been prepared by Alteon Seattle, Washington for the Boeing Commercial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 AUTOPILOT FLIGHT DIRECTOR SYSTEM -- INTRODUCTION ..... . . 22-11-00 . . 1 GENERAL DESCRIPTION .
Page 4 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page OPERATION - LNAV ......... . .
Page 5 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page SYSTEM TESTS ..........
Page 6 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page TIP - BITE - DISPLAY TEST ........
Page 7 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page SAARU AIR DATA FUNCTION - 2 ........
Page 8 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page OPERATION - 1 ..........
Page 9 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page TUNE INPUTS ..........
Page 10 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page AUDIO CONTROL PANEL ILS AUDIO CONTROLS ....... .
Page 11 777 TRAINING MANUAL Alteon FS733 Chapter TABLE OF CONTENTS Section Subject Subject Page GROUND TEST ..........
Page 13 777 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 14: Training Manual
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 15: 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 16 777 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 17 777 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 18 777 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 - 6 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 19 777 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 - 7 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 20 777 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 - 8 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 21 777 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 - 9 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 22 777 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 - 10 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 23 777 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 - 11 - ALTEON PROPRIETARY.
Page 24 777 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 25 777 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 26 777 TRAINING MANUAL AFDS -- SYSTEMS ARINC 629 BUS INTERFACE General Overhead Panel ARINC 629 System (OPAS) Each AFDC uses the onside systems bus to transmit and The left OPAS controller transmits heading reference receive data. switch data on the left and right buses. The right OPAS controller transmits on the left and right buses.
Page 27 777 TRAINING MANUAL L AIMS CABINET R AIMS CABINET L CDU R CDU C CDU L FSEU L AFDC R FSEU L PSEU R PSEU L WOW CARD FILE R WOW CARD FILE OPAS C AFDC ELMS BACKUP GENERATOR CONVERTER L GCU R GCU L ASCPC...
Page 28 777 TRAINING MANUAL AFDC -- FLIGHT CONTROLS ARINC 629 BUSES INTERFACE AFDC Each AFDC uses the on-side flight controls bus to transmit data. Each AFDC receives data from all three buses. Primary Flight Control Computers Each PFC uses the on-side flight controls bus to transmit data.
Page 29 777 TRAINING MANUAL L AFDC L PFC R PFC C PFC L PITOT ADM C PITOT ADM R PITOT ADM C AFDC ADIRU SAARU R AFDC FLIGHT CONTROLS ARINC 629 BUSES AFDC - FLIGHT CONTROLS ARINC 629 BUSES INTERFACE 22-11-00 - 17 - ALTEON PROPRIETARY.
Page 30 777 TRAINING MANUAL AFDS -- ARINC 429 DATA BUS INTERFACE Mode Control Panel The mode control panel (MCP) has three 429 input data buses and two 429 output data buses. The MCP receives mode requests and target values from the three AFDCs on separate data buses. The MCP sends this information to the three AFDCs: Autopilot engage requests Mode requests...
Page 31 777 TRAINING MANUAL A/P ENGAGE REQUESTS/ A/P ENGAGE REQUESTS/ MODE REQUESTS/ MODE REQUESTS/ TARGET VALUES/ TARGET VALUES/ MAINT DATA MAINT DATA MODE MODE MODE REQUESTS/ REQUESTS/ REQUESTS/ TGT VALUES TGT VALUES TGT VALUES RNWY CRS RNWY CRS RNWY CRS ILS DEV ILS DEV ILS DEV L MMR...
Page 32 777 TRAINING MANUAL AFDS -- CROSS-CHANNEL DATA INTERFACE Cross Channel Bus and Discrete Information Each AFDC receives digital data on cross-channel (X-CH) buses for monitor, signal selection, and synchronization functions. Each AFDC continuously sends an AFDC ALIVE discrete to the other AFDCs if it does not detect any internal faults.
Page 33 777 TRAINING MANUAL X-CH OUT AFDC ALIVE OUT X-CH OUT LEFT AFDC X-CH OUT AFDC ALIVE OUT X-CH OUT CENTER AFDC X-CH OUT AFDC ALIVE OUT X-CH OUT RIGHT AFDC AFDS - CROSS-CHANNEL DATA INTERFACE 22-11-00 - 21 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 34 777 TRAINING MANUAL AFDS -- MISCELLANEOUS ANALOG DISCRETES INTERFACE General Th discrete inputs to the AFDC are from these switches: Autopilot disconnect switches Takeoff/go-around (TO/GA) switches Autopilot disengage bar. Interface Each control wheel has an autopilot disconnect switch. These switches supply the A/P disengage and A/P warning reset discretes to each AFDC.
Page 35 777 TRAINING MANUAL CENTER AFDC RIGHT AFDC A/P DISCONNECT A/P WARNING RESET F/O A/P DISCONNECT DISENGAGE BAR SWITCH CENTER AFDC (CONTROL A/P ENGAGE RELAY WHEEL) ENGAGE POWER RIGHT AFDC CAPT A/P DISCONNECT L AIMS SWITCH (CONTROL WHEEL) CENTER CABINET AFDC R AIMS CABINET TO/GA...
Page 36 777 TRAINING MANUAL AFDS -- WARNING ANALOG DISCRETES INTERFACE Warning Electronic System These signals go to the warning electronic units (WEUs) when there is an autopilot disconnect: Autopilot disconnect warning normal (A/P DISC WARN NORM) Autopilot disconnect warning battery 1 (A/P DISC WARN BAT 1) Autopilot disconnect warning battery 2 (A/P DISC WARN BAT 2).
Page 37 777 TRAINING MANUAL A/P DISC WARN NORM A/P DISC WARN NORM A/P DISC WARN BAT 1 A/P DISC WARN BAT 1 A/P DISC WARN BAT 2 A/P DISC WARN BAT 2 L WARNING ELECTRONIC UNIT LEFT AFDC A/P DISC WARN NORM A/P DISC WARN NORM A/P DISC WARN BAT 1 A/P DISC WARN BAT 1...
Page 38 777 TRAINING MANUAL AFDS -- ILS ANALOG DISCRETES INTERFACE Tune Inhibit Discrete During an approach with the flight director or autopilot engaged, the AFDCs send a tune inhibit discrete to the multi-mode receivers (MMRs). The tune inhibit discrete inhibits flight crew from tuning the MMRs.
Page 39 777 TRAINING MANUAL LOC ANTENNA ACKNOWLEDGE L LOC ANT IN VOR ANT IN LOC ANTENNA REQUEST 28V DC ILS TUNE INHIBIT L LOC ANT SW L MMR G/S ANTENNA ACKNOWLEDGE L G/S TRACK ANT INPUT L G/S CAPTURE ANT INPUT G/S TRACK ANTENNA REQUEST 28V DC...
Page 40 777 TRAINING MANUAL AFDS -- BACKDRIVE INTERFACE AFDC Backdrive The left and right autopilot flight director computers (AFDCs) each connect to three backdrive actuators. These are the actuators: Column backdrive actuator Wheel backdrive actuator Rudder backdrive actuator. Each actuator has these components: Two tachometers One motor One clutch.
Page 41 777 TRAINING MANUAL TACH A-COLUMN BACKDRIVE-HI TACH A-COLUMN BACKDRIVE-LO TACH B-COLUMN BACKDRIVE-HI TACH B-COLUMN BACKDRIVE-LO COLUMN BACKDRIVE MOTOR CMD-A MOTOR COLUMN BACKDRIVE MOTOR CMD-B MOTOR COLUMN BACKDRIVE CLUTCH ENGAGE L COLUMN BACKDRIVE ACTUATOR TACH A-WHEEL BACKDRIVE-HI TACH A-WHEEL BACKDRIVE-LO TACH B-WHEEL BACKDRIVE-HI TACH B-WHEEL BACKDRIVE-LO WHEEL BACKDRIVE MOTOR CMD-A MOTOR...
Page 42 777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - PHYSICAL DESCRIPTION Purpose To replace the incandescent bulbs, remove the switch assembly from the MCP. The mode control panel (MCP) supplies the interface between the pilot and the autopilot flight director Each mode select switch, except the CLB/CON switch, system (AFDS).
Page 43: Air Inlet
777 TRAINING MANUAL A/T ARM MACH ALTITUDE LNAV AUTO 1000 VNAV BANK DOWN AUTO F/D ON LIMIT F/D ON FLCH HOLD A/P DISENGAGE VS/FPA HOLD REAR CONNECTORS FLUORESCENT TUBE AIR INLET (TYP) (REAR VIEW) AFDS - MODE CONTROL PANEL - PHYSICAL DESCRIPTION 22-11-00 - 31 - ALTEON PROPRIETARY.
Page 44 777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 32 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 45: Training Manual
777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - FUNCTIONAL DESCRIPTION General To make sure all three AFDCs use data from one MCP processor, all AFDCs use the microprocessor data sent The major components of the MCP are: to the master AFDC. Power supplies, A and B When the left AFDC is master, microprocessor A writes Microprocessors, A and B...
Page 46 777 TRAINING MANUAL AFDS -- MODE CONTROL PANEL - FUNCTIONAL DESCRIPTION Liquid Crystal Displays (LCDs) And Control Knob Encoders There are four LCDs. They show mode reference values. The values change when you turn the selector or when the AFDCs command a new reference value. Microprocessor A and B drive each LCD.
Page 47 777 TRAINING MANUAL ARINC L AFDC RCVR I/O SIGNAL PROCESSING L AND C ARINC POWER SUPPLY A AFDC AND AIMS PWR SPLY A VALID SELECT XMTR PROCESSOR A VALID PROCESSOR A MICROPROCESSOR A A/T ARM ARINC C AFDC BANK AUTO FLUORESCENT RCVR LIMIT...
Page 48 777 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 49 777 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 50 777 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 51 777 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 52 777 TRAINING MANUAL AFDS -- AUTOPILOT FLIGHT DIRECTOR COMPUTER Purpose A/P interlock pins A/P options list. The autopilot flight director computer (AFDC) calculates: This information shows for each AFDC. Flight director (F/D) commands Autopilot commands Backdrive actuator commands. Physical Description The AFDC has modules, sub-assemblies, and a chassis assembly in an ARINC 600, 8 MCU box.
Page 53 777 TRAINING MANUAL AFDS - AUTOPILOT FLIGHT DIRECTOR COMPUTER 22-11-00 - 41 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 54 777 TRAINING MANUAL AFDS -- AUTOPILOT FLIGHT DIRECTOR COMPUTER - FUNCTIONAL BLOCK DIAGRAM General the autopilot and flight director control laws. Processor C also does these functions: This is a block diagram of the autopilot flight director computer (AFDC). Test and data load. Engage/disengage logic Input Signal Selection Failure detection/fault response monitor...
Page 55 777 TRAINING MANUAL LOGIC POWER SUPPLY BAT WARN POWER SUPPLY LOGIC POWER LOGIC POWER ARINC 629 BACKDRIVE OUTPUTS TRANSFER BUS BACKDRIVE COMMANDS MOTOR DRIVE (HI) FOR WHEEL, COLUMN, AND SECTION A RUDDER PEDAL ACTUATORS PROCESSOR A BACKDRIVE COMMANDS ARINC 429 MOTOR DRIVE (LO) SECTION B BACKDRIVE PWR SUPPLY (3)
Page 56 777 TRAINING MANUAL AFDS -- AUTOPILOT DISCONNECT SWITCH Purpose The autopilot disconnect switches are on the outboard side of each control wheel. The example shows the captain's control wheel. The first officer has the switch on the right side of the wheel. Each switch has a push-button and multiple contacts.
Page 57 777 TRAINING MANUAL PLATE AUTOPILOT DISCONNECT SWITCH APPROACH PLATE WIRE GUARD STABILIZER TRIM ASSEMBLY AND AUTOPILOT WIRE MEDALLION CONNECTORS CAPT CONTROL WHEEL AFDS - AUTOPILOT DISCONNECT SWITCH 22-11-00 - 45 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 58 777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR INSTALLATION - 1 Purpose The backdrive actuators are variable torque motors. They move the control columns, control wheels, and rudder pedals during autopilot operation. This movement gives the flight crew an indication of the autopilot commands that go to the primary flight computers (PFCs).
Page 59 777 TRAINING MANUAL LEFT CONTROL COLUMN BACKDRIVE ACTUATOR FORWARD BULKHEAD FORWARD EQUIPMENT CENTER BELOW FLIGHT DECK FLOOR AFDS - BACKDRIVE ACTUATOR INSTALLATION - 1 22-11-00 - 47 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 60 777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR INSTALLATION - 2 General The right control column backdrive actuator is below the flight deck floor. Access is through the forward equipment center. 22-11-00 - 48 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 61 777 TRAINING MANUAL RIGHT CONTROL COLUMN BACKDRIVE ACTUATOR FORWARD BULKHEAD FORWARD EQUIPMENT CENTER AFDS - BACKDRIVE ACTUATOR INSTALLATION - 2 22-11-00 - 49 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 62 777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR INSTALLATION - 3 General The left control wheel backdrive actuator and the left rudder pedal backdrive actuator are below the flight deck floor. Access is through the left side of the main equipment center.
Page 63 777 TRAINING MANUAL LEFT RUDDER PEDAL BACKDRIVE LEFT CONTROL ACTUATOR WHEEL BACKDRIVE ACTUATOR NOSE WHEEL WELL BULKHEAD BETWEEN FORWARD EQUIPMENT CENTER AND MAIN EQUIPMENT CENTER BELOW FLIGHT DECK FLOOR AFDS - BACKDRIVE ACTUATOR INSTALLATION - 3 22-11-00 - 51 - ALTEON PROPRIETARY.
Page 64 777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR INSTALLATION - 4 General The right control wheel backdrive actuator and the right rudder pedal backdrive actuator are below the flight deck floor. Access is through the right side of the main equipment center.
Page 65 777 TRAINING MANUAL RIGHT RUDDER RIGHT CONTROL PEDAL BACKDRIVE WHEEL BACKDRIVE ACTUATOR ACTUATOR NOSE WHEEL WELL BULKHEAD BETWEEN FORWARD EQUIPMENT CENTER AND MAIN EQUIPMENT CENTER BELOW FLIGHT DECK FLOOR AFDS - BACKDRIVE ACTUATOR INSTALLATION - 4 22-11-00 - 53 - ALTEON PROPRIETARY.
Page 66 777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR - FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 54 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 67: Training Manual
777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR - FUNCTIONAL DESCRIPTION General Actuator Authority Each backdrive actuator contains: The AFDC controls the motor current to each backdrive actuator. This limits the force that a backdrive Two tachometers actuator applies to the control columns, control A DC motor wheels, and rudder pedals.
Page 68 777 TRAINING MANUAL AFDS -- BACKDRIVE ACTUATOR - FUNCTIONAL DESCRIPTION If one control column actuator fails during autoland, the force limit of the remaining column actuator is two times as high. This makes sure there is enough force to prevent accidental column movement by the pilot during autoland.
Page 69 777 TRAINING MANUAL OUTPUT CRANK ENGAGE CLUTCH ENGAGE ENGAGE CLUTCH LOGIC MOTOR DRIVE POWER OVERRIDE SLIP SUPPLY A CLUTCH TACH A MICRO- MICRO- PROCESSOR PROCESSOR TACH B MOTOR DRIVE POWER SUPPLY B AFDC (TYPICAL) BACKDRIVE ACTUATOR (TYPICAL) AFDS - BACKDRIVE ACTUATOR - FUNCTIONAL DESCRIPTION 22-11-00 - 57 - ALTEON PROPRIETARY.
Page 70 777 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 - 58 - ALTEON PROPRIETARY.
Page 71 777 TRAINING MANUAL CRUISE DESCENT CLIMB GO-AROUND APPROACH AUTOLAND TAKEOFF ROLLOUT AFDS - OPERATION - OVERVIEW 22-11-00 - 59 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 72 777 TRAINING MANUAL AFDS -- OPERATION - TAKEOFF THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 60 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 73 777 TRAINING MANUAL AFDS -- OPERATION - TAKEOFF General The F/D roll bar shows wings level. The F/D display supplies the pilot with roll and pitch The pilot sets an engine-out climb speed (V2) and a commands during takeoff. After the airplane is off the clearance altitude on the MCP.
Page 74 777 TRAINING MANUAL AFDS -- OPERATION - TAKEOFF Pitch attitude. At five feet radio altitude, the roll command changes to track hold. If the climb rate is less than 600 feet per minute, the pitch command is to hold attitude. For a climb rate The autothrottle stays in HOLD.
Page 75 777 TRAINING MANUAL THR REF TO/GA TO/GA HOLD TO/GA TO/GA THR REF TO/GA TO/GA FLT DIR FLT DIR FLT DIR TAKEOFF START LIFT-OFF/IN AIR CLIMB OUT A/T ARM ALTITUDE MACH LNAV AUTO 1000 VNAV BANK DOWN AUTO F/D ON LIMIT F/D ON FLCH HOLD...
Page 76 777 TRAINING MANUAL AFDS -- OPERATION - AUTOPILOT ENGAGE General Engage Autopilot With Flight Director Off Autopilot engagement occurs when the pilot pushes an The active pitch mode is vertical speed or flight path autopilot (A/P) switch on the MCP. At that time, this angle.
Page 77 777 TRAINING MANUAL THR REF LNAV VNAV SPD HDG HOLD (F/D ON) (F/D OFF) A/P MODE IS SAME AS A/P MODE IS HDG HOLD F/D MODE OR: (OR TRK HOLD) AND V/S (OR FPA) IF THE BANK ANGLE - HDG HOLD (OR TRK HOLD) IS 5 DEGREES OR LESS: IF F/D IN LOC - V/S (OR FPA)
Page 78 777 TRAINING MANUAL AFDS -- ROLL ATTITUDE HOLD General In this mode, the airplane holds a roll attitude until the pilot selects another roll mode. Bank Angle More Than Five Degrees If the pilot engages the autopilot when the bank angle is more than five degrees and the flight director is off, the airplane holds the roll attitude present at that time.
Page 79 777 TRAINING MANUAL HDG HOLD PILOT ENGAGES AUTOPILOT PILOT ENGAGES AUTOPILOT WITH AIRPLANE IN A BANK WITH AIRPLANE IN A BANK OF MORE THAN FIVE DEGREES AND F/D OFF OF FIVE DEGREES OR LESS AND F/D OFF - AIRPLANE STAYS ON ROLL - HEADING/TRACK HOLD LIGHT ON ATTITUDE PRESENT - AIRPLANE HOLDS HEADING...
Page 80 777 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 81 777 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 - 69 -...
Page 82 777 TRAINING MANUAL AFDS -- OPERATION - LNAV General LNAV has these two sub-modes: LNAV arm LNAV active. LNAV Arm Push the LNAV switch on the MCP to arm LNAV. To remove the LNAV arm status, push the LNAV switch again before LNAV captures or select another roll mode.
Page 83 777 TRAINING MANUAL LNAV ARM LNAV ACTIVE HDG HOLD LNAV LNAV FLIGHT PATH A/T ARM MACH LNAV VNAV F/D ON FLCH AFDS - OPERATION - LNAV 22-11-00 - 71 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 84 777 TRAINING MANUAL AFDS -- OPERATION - HEADING/TRACK SELECT General HDG SEL shows on the PFD When the pilot turns the heading knob clockwise, The pilot uses the HDG/TRK select mode to change the the airplane banks to the right airplane heading.
Page 85 777 TRAINING MANUAL HDG SEL BANK ANGLE BANK ANGLE LIMIT IN AUTO AFDS - OPERATION - HEADING/TRACK SELECT 22-11-00 - 73 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 86 777 TRAINING MANUAL AFDS -- OPERATION - HEADING/TRACK HOLD General In this mode, the airplane holds a heading or a track angle. The pilot can set a heading or a track in the MCP displays before the mode is set. This example shows operation with HDG selected.
Page 87 777 TRAINING MANUAL HDG HOLD HDG HOLD HEADING HOLD SELECTED WITH HEADING HOLD SELECTED WITH WINGS LEVEL AIRPLANE IN BANK - HEADING/TRACK HOLD - HEADING/TRACK HOLD LIGHT ON LIGHT ON - PFD SHOWS HDG HOLD - AIRPLANE ROLLS TO - AIRPLANE HOLDS HEADING WINGS LEVEL - PFD SHOWS HDG HOLD - AIRPLANE HOLDS HEADING...
Page 88 777 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 89 777 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 - 77 - ALTEON PROPRIETARY.
Page 90 777 TRAINING MANUAL AFDS -- OPERATION - VNAV General VNAV PTH Push the VNAV mode select switch to arm VNAV. The PFD In climb, VNAV SPD changes to VNAV PTH to capture the shows VNAV in white and the switch LED is on. Push the FMCF target altitude.
Page 91 777 TRAINING MANUAL THR REF LNAV VNAV SPD LNAV VNAV PTH VNAV PTH IDLE LNAV VNAV PTH TOP OF DESCENT VNAV PTH VNAV ALT VNAV ALT VNAV SPD MCP ALT MCP ALT VNAV PTH AFDS - OPERATION - VNAV 22-11-00 - 79 - ALTEON PROPRIETARY.
Page 92 777 TRAINING MANUAL AFDS -- OPERATION - VERTICAL SPEED/FLIGHT PATH ANGLE General The pilot uses the VS/FPA mode to climb or descend to the altitude set in the MCP. This example shows FPA operation. VS mode operation is the same except for the display on the PFDs. Climb These occur when the pilot sets a positive FPA on the MCP and pushes the VS/FPA mode select switch:...
Page 93 777 TRAINING MANUAL CLIMB PATH FLIGHT PATH ANGLE LEVEL FLIGHT PATH LEVEL FLIGHT PATH AIRPLANE CLIMBS AIRPLANE DESCENDS DESCENT PATH FLIGHT PATH ANGLE CLIMB DESCEND HDG SEL AFDS - OPERATION - VERTICAL SPEED/FLIGHT PATH ANGLE 22-11-00 - 81 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 94 777 TRAINING MANUAL AFDS -- OPERATION - ALTITUDE HOLD General Capture Altitude Altitude hold is active in any of these conditions: Altitude capture starts as the airplane approaches the MCP selected altitude: Push the altitude hold switch on the MCP Select a vertical speed (V/S) of 0000 feet per The pitch flight mode annunciator on PFD shows ALT minute (FPM) in the V/S mode...
Page 95 777 TRAINING MANUAL HDG SEL HDG SEL HDG SEL CAPTURE ALTITUDE V/S MODE +1000 FPM SET V/S TO 0000 FPM SELECT ALT HOLD V/S MODE +1000 FPM V/S MODE +1000 FPM AFDS - OPERATION - ALTITUDE HOLD 22-11-00 - 83 - ALTEON PROPRIETARY.
Page 96 777 TRAINING MANUAL AFDS -- OPERATION - FLIGHT LEVEL CHANGE General In all cases, the AFDS controls to the speed on the MCP IAS/mach window until the pilot sets a new speed in the The FLCH mode permits the pilot to change flight levels window.
Page 97 777 TRAINING MANUAL SELECTED IAS/MACH WINDOW ALTITUDE - SYNC TO FMC TARGET OR CURRENT AIRSPEED FLCH SELECTED ALTITUDE CAPTURE HDG SEL FLCH SPD HDG SEL MCP ALTITUDE AFDS - OPERATION - FLIGHT LEVEL CHANGE 22-11-00 - 85 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 98 777 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 99 777 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 - 87 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 100 777 TRAINING MANUAL AFDS -- OPERATION - LOCALIZER General Localizer Active The flight crew uses the localizer switch on the MCP, At LOC capture, the active roll mode changes to LOC. to select a localizer only approach. The MCP heading/track window changes to the ILS course. The flight crew uses the localizer only approach when The localizer capture point is not fixed.
Page 101 777 TRAINING MANUAL HDG SEL LOC ARM LOC ACTIVE INTERCEPT ANGLE LOCALIZER TRANSMITTER ILS COURSE (DEG MAG) = CAPTURE POINT AFDS - OPERATION - LOCALIZER 22-11-00 - 89 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 102 777 TRAINING MANUAL AFDS -- OPERATION - APPROACH General conditions that change the autoland status to LAND 2 or NO AUTOLAND. In approach (APP), the airplane automatically captures and tracks the localizer and glideslope beams. If an These are some failures that cause a change from LAND 3 autopilot approach continues, the airplane lands to LAND 2: automatically.
Page 103: Training Manual
777 TRAINING MANUAL AFDS -- OPERATION - APPROACH Bus isolation stays active during an autoland until the At G/S capture, the active pitch mode changes to G/S. autopilot disengages or the airplane climbs above 400 feet radio altitude after a go-around starts. The AFDS supplies an ILS tune inhibit signal when G/S and LOC are active with the autopilot system engaged.
Page 104 777 TRAINING MANUAL AFDS -- OPERATION - APPROACH frequency and ILS course and pushes the APP switch to arm LOC and G/S again. 22-11-00 - 92 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 105 777 TRAINING MANUAL HDG SEL A/T ARM APPROACH ARM LOC AND G/S CAPTURE APPROACH LOC ARM G/S ARM G/S CAPTURE = CAPTURE POINT LOC CAPTURE AFDS - OPERATION - APPROACH 22-11-00 - 93 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 106 777 TRAINING MANUAL AFDS -- OPERATION - AUTOLAND PITCH General Flare/Touchdown In autoland, the AFDS controls the elevator for these FLARE replaces G/S as the active mode on the PFD. functions: During flare, airplane touchdown occurs 450 feet past Glideslope (G/S) the glideslope transmitter at a descent rate of 1.5 Flare feet/second.
Page 107 777 TRAINING MANUAL FLARE IDLE ROLLOUT ROLLOUT FLARE ROLLOUT LAND 3 LAND 3 LAND 3 TOUCHDOWN GLIDESLOPE FLARE RADIO ALTITUDE (FEET) -30.0 -22.0 -12.4 -4.0 -1.5 DESCENT RATE (FEET PER SECOND) FLARE HEIGHT GLIDESLOPE BEAM CENTER LINE 1500' GLIDESLOPE TRANSMITTER TOUCHDOWN FLARE AND NOSE...
Page 108 777 TRAINING MANUAL AFDS -- OPERATION - AUTOLAND ROLL AND YAW General Engine Out Runway Alignment The runway alignment function corrects for engine out Engine out runway alignment occurs at 1300 feet. The and crosswind conditions during an autoland. This is to speed and the direction of the crosswind sets the make sure the wings are level or the upwind wing is low amount of sideslip.
Page 109 777 TRAINING MANUAL RUNWAY ALIGNMENT ROLLOUT IDLE ROLLOUT ROLLOUT FLARE LAND 3 LAND 3 CROSS WIND CROSS WIND AFDS - OPERATION - AUTOLAND ROLL AND YAW 22-11-00 - 97 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 110 777 TRAINING MANUAL AFDS -- OPERATION - GO-AROUND THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 98 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 111 777 TRAINING MANUAL AFDS -- OPERATION - GO-AROUND General The PFD and MCP continue to show the approach modes. Go-around is a combined AFDS and TMCF mode. The pilot Go-Around Active uses the mode in these conditions: The go-around mode starts when the pilot pushes either An aborted approach TO/GA switch.
Page 112 777 TRAINING MANUAL AFDS -- OPERATION - GO-AROUND This mix of speed and attitude command gives windshear protection during go-around. Go-Around Off Below 400 feet, the AFDS stays in go-around unless the pilot disengages the autopilot and sets the flight director switches to off.
Page 113 777 TRAINING MANUAL ALTITUDE AUTO 1000 HOLD TO/GA SWITCHES TO/GA TO/GA TO/GA ROLLOUT FLARE LAND 3 GO-AROUND ARM GO-AROUND ACTIVE GO-AROUND OFF AFDS - OPERATION - GO-AROUND 22-11-00 - 101 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 114 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - AUTOPILOT CONTROLS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 102 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 115 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - AUTOPILOT CONTROLS General Roll/Yaw Control Laws The AFDC program has the: The roll/yaw control laws calculate the roll and yaw commands and sends them to the PFCs. The PFCs accept Pitch control laws the roll and yaw commands only when the PFCS mode is Roll/Yaw control laws NORMAL.
Page 116 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - AUTOPILOT CONTROLS backdrive commands. The backdrive commands go to the AFDCs. The AFDCs change the commands to actuator drive signals and send them to the backdrive actuators. For bank angle protection (BAP), the PFCs monitor manual bank angle commands.
Page 117 777 TRAINING MANUAL PITCH CMD CONTROL CONTROL LAWS AND SURFACE LIMITS ROLL/YAW CMD LIMITS PCU (15) BACKDRIVE PITCH COMMANDS CONTROL LAWS SURFACE COMMAND LOGIC SURFACE POSITION FEEDBACK MANUAL PILOT ROLL/YAW TRANSDUCER COMMAND CONTROL (15) BANK ANGLE CALCULATION LAWS PROTECTION ACE (4) FLIGHT FLIGHT POSITION...
Page 118 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - FLIGHT DIRECTOR CONTROL General The AFDC sends pitch and roll control law data to the flight director program. The program calculates this display data: Pitch flight director bar Roll flight director bar. The AFDC sends the display data to the AIMS cabinets.
Page 119 777 TRAINING MANUAL PITCH PITCH FLIGHT CONTROL DIRECTOR LAWS FLIGHT DIRECTOR BAR DISPLAY DATA L AND R AIMS ROLL/YAW CABINETS ROLL FLIGHT CONTROL DIRECTOR LAWS SYSTEMS ARINC 629 BUS (3) AFDC (3) AFDS - FUNCTIONAL DESCRIPTION - FLIGHT DIRECTOR CONTROL 22-11-00 - 107 - ALTEON PROPRIETARY.
Page 120 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - PITCH CONTROL THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 108 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 121 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - PITCH CONTROL General The AFDC uses these signals to calculate the vertical speed command: The AFDC pitch control laws calculate part of the pitch command signal that goes to the PFC. They also MCP selected vertical speed or flight path angle calculate the F/D data.
Page 122 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - PITCH CONTROL The AFDC uses the speed signal with true airspeed to Pitch CMD Limit calculate the speed command. The AFDC also makes sure the speed error stays in the protection limits. The AFDC limits the rate and angle of the pitch command signal that goes to the PFCs.
Page 123 777 TRAINING MANUAL - MCP SELECTED PITCH VERTICAL CHANGE FPA - GROUND SPEED ATTITUDE SPEED TO V/S - MCP SELECTED CALCULATIONS TO SYSTEMS PITCH F/D - VERTICAL SPEED ARINC 629 VERTICAL SPEED/ CMD TO THE PITCH BUSES AIMS CABINETS FLIGHT PATH ANGLE FLIGHT (PITCH DIRECTOR...
Page 124 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ROLL AND YAW CONTROL THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 112 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 125 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ROLL AND YAW CONTROL General MCP selected heading Airplane heading The AFDC roll/yaw control laws calculate the roll and MCP selected track yaw signals that go to the PFC. They also calculate the Ground track.
Page 126 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ROLL AND YAW CONTROL Localizer deviation Yaw Command Calculations and Limiting Localizer deviation rate Rudder position. The AFDC uses these inputs to calculate the rudder command: It also calculates a roll command for flight director (F/D) display during ground rollout.
Page 127 777 TRAINING MANUAL LNAV STEERING ROLL COMMANDS COMMAND ROLL F/D ROLL FROM ROLL CMDS TO TO SYSTEMS ATTITUDE ROLLOUT ATT HOLD THE AIMS ARINC 629 >5 DEG - MCP BANK ROLL FLIGHT CABINETS ROLL ROLL BUSES LIMIT DIRECTOR (ROLL F/D COMMAND ATTITUDE - HDG/TRK...
Page 128 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - BACKDRIVE CONTROLS General PFC engage wheel backdrive PFC wheel torque command The AFDC backdrive control laws use PFC backdrive Wheel position commands to supply these commands: Wheel TACH feedback A or B. Control column In BAP operation, the PFC sends a wheel torque limit Control wheel...
Page 129 777 TRAINING MANUAL COLUMN BACKDRIVE ENGAGE AUTOPILOT COLUMN COMMAND ENGAGE YAW BACKDRIVE COLUMN MOTOR DRIVE A ENGAGE WHEEL BACKDRIVE POWER COLUMN SUPPLY A BACKDRIVE COLUMN COLUMN TACH A ACTUATOR PRIMARY FLIGHT CONTROL COLUMN BACKDRIVE COMMAND WHEEL COLUMN POSITION BACKDRIVE WHEEL MOTOR WHEEL PROCESSOR POWER...
Page 130 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ENGAGE INTERLOCKS INTRODUCTION Purpose Autopilot disengage switches AFDC cross channel data The autopilot engage interlock circuits in the AFDCs PFCS and PFCs monitor the operation, power, and components ADIRU of the AFDS and PFCS. With normal conditions, the SAARU circuits let the autopilot engage.
Page 131 777 TRAINING MANUAL PFCS INPUT PROCESSING AND A/P ENGAGE LOGIC DISENGAGE FLIGHT 28V DC CONTROLS PFC (TYPICAL) ARINC 629 BUSES ENGAGE LOGIC AND RUDDER PEDAL AUTOPILOT DISENGAGE BACKDRIVE BACKDRIVE ACTUATOR SWITCH (2) ENGAGE (TYPICAL) RELAYS CONTROL WHEEL CROSS CHANNEL BACKDRIVE ACTUATOR INPUTS FROM (TYPICAL) OTHER AFDC(S)
Page 132 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ENGAGE INTERLOCKS BLOCK DIAGRAM THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 120 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 133 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ENGAGE INTERLOCKS BLOCK DIAGRAM General Change from pilot control to autopilot control of the pitch and roll axis. Cruise engage refers to engagement of the pitch and roll axis. Autoland engage refers to the added Each valid AFDC engages in pitch and roll.
Page 134 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ENGAGE INTERLOCKS BLOCK DIAGRAM The PFCs receive at least two valid pitch, roll and The 28v dc goes through toggle switches connected to yaw commands. the disengage bar on the MCP. There are three switches, one for each AFDC.
Page 135 777 TRAINING MANUAL DISENGAGE BAR A/P INPUT SIGNAL (L DISENG SWITCH) SELECTION AND FAULT ENGAGE DETECTION LOGIC REQUEST AND A/P F/D ON F/D ON COMMANDS COMMANDS SURFACE (P55) COMMANDS ENGAGE REQUEST POWER TO THE IS ACCEPTED 28V DC SUPPLY ACES AUTOLAND ENGAGE REQUEST PILOT COLUMN, WHEEL AND PEDAL INPUT...
Page 136 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - CRUISE ENGAGE INTERLOCK CONDITIONS General Change from autopilot control to flight crew control of the pitch, roll and yaw (if engaged) The conditions shown here apply to failures in the axis. AFDS, PFCS, and sensor components which cause the autopilot to disengage in cruise.
Page 137 777 TRAINING MANUAL ENGAGE ENGAGE CRUISE CONDITION INHIBIT REMOVAL THE PFCS IS NOT IN THE NORMAL MODE ADIRU AND SAARU FAIL THE THREE ADMS FAIL ALL PFCS FAIL (THERE ARE PROGRAM PIN FAULTS WITH THE LEFT AND RIGHT AFDC) OR (THE MASTER AFDC) ALL AFDC PROGRAM PINS ARE DIFFERENT ALL AFDC SOFTWARE IS DIFFERENT MASTER AFDC FAIL...
Page 138 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - AUTOLAND ENGAGE INTERLOCK CONDITIONS General the airplane system schematics for ATA 22-11 for a full list of all the autoland engage interlock conditions. The conditions shown have a relation to failures in the AFDS, PFCS, and sensor components that cause the autopilot to disengage during approach and autoland.
Page 139 777 TRAINING MANUAL ENGAGE ENGAGE AUTOLAND CONDITION INHIBIT REMOVAL THE PFCS ARE NOT IN THE NORMAL MODE ADIRU AND SAARU HAVE FAILURES THREE ADMS HAVE FAILURES ALL PFCS HAVE FAILURES PFCS USE AUTOPILOT COMMANDS FROM ONLY ONE AFDC IN THE FLARE MODE AT TOUCHDOWN ALL AFDC PROGRAM PINS ARE DIFFERENT ALL AFDC SOFTWARE IS DIFFERENT THERE IS A DUAL ILS FAILURE, AND THE A/P IS ENGAGED AND LOC MODE IS ACTIVE...
Page 140 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - ENGAGE INTERLOCKS MASTER/SLAVE SELECTION General Column and wheel backdrive actuator selection and control in cruise The AFDCs operate as master or slave when the autopilot Wheel backdrive actuator selection during BAP engages in cruise. Two or three AFDCs must engage Control of AFDS modes before the master/slave selection occurs.
Page 141 777 TRAINING MANUAL MICROPROCESSOR A ENGAGE LOGIC AND BACKDRIVE ENGAGE RELAYS SET THE MCP MICROPROCESSOR IN CONTROL OF WRITING BANK AUTO TO THE DISPLAYS LIMIT AFDC MASTER SELECT LOGIC LCD DISPLAYS AND ENCODERS OTHER AFDC IS MASTER CROSS CHANNEL DATA TO/FROM OTHER AFDC(S) MICROPROCESSOR B THIS AFDC...
Page 142 777 TRAINING MANUAL AFDS -- ILS ANTENNA SWITCHING LOGIC ILS Antenna Switching The autopilot flight director computers (AFDCs) select the position of their onside localizer and glideslope antenna switches. ILS Tune Inhibit The AFDCs prevent tuning of the multi-mode receivers (MMRs) when the airplane makes an autopilot engaged approach.
Page 143: Switch Position
777 TRAINING MANUAL LOC OR APP MODE SELECTED A/P ENGAGED AND G/S OR LOC CAPTURED ILS TUNE INHIBIT (TO L MMR) < 500FT AND F/D APPROACH L G/S ANTENNA RF FROM L SWITCH POSITION G/S TRACK G/S VALID ANTENNA NOSE WHEEL DOWN TO L MMR RF FROM L ON GROUND IN...
Page 144 777 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 145: 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 146 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATION - PFD AND ND DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 134 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 147 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATION - PFD AND ND DISPLAYS General AFDS Modes The primary flight displays (PFDs) show AFDS modes, The top of the PFD shows the AFDS modes of operation. status messages, and flight director (F/D) information. This is the flight mode annunciator (FMA).
Page 148 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATION - PFD AND ND DISPLAYS NO AUTOLAND A processor LAND 2 B processor. LAND 3. Barometric Reference Source MCP Selected Data The barometric reference source shows which barometric The AIMS shows this data from the MCP: (baro) correction the AFDCs use.
Page 149 777 TRAINING MANUAL SELECTED HEADING FLIGHT MODE FLIGHT MODE FLIGHT MODE ANNUNCIATIONS - ANNUNCIATIONS - ANNUNCIATIONS - ROLL MODES ACTIVE PITCH ARMED PITCH MODE MODE LNAV VNAV MODE FAIL SELECTED SELECTED ALTITUDE AIRSPEED/MACH AFDS ENGAGE/ AUTOLAND STATUS ANNUNCIATION FLIGHT DIRECTOR FAIL FLAG SELECTED VERTICAL...
Page 150 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATIONS - EICAS DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 138 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 151 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATIONS - EICAS DISPLAYS General Caution The EICAS and MFD displays show messages, warnings, and The AFDCs send these autopilot caution messages autoland capability for the autopilot system. The requests to the AIMS: warning electronic units (WEUs) make the master warning lights come on when a warning message shows on the AUTOPILOT, when an autopilot mode fail occurs...
Page 152 777 TRAINING MANUAL AFDS -- FUNCTIONAL DESCRIPTION - WARNING AND ANNUNCIATIONS - EICAS DISPLAYS AUTOPILOT BACKDRIVE L or R, when the left or right backdrive system does not operate MODE CTRL PANEL LANE, when one of the two lanes in the AFDS MCP or its interface to the AFDC fails NO AUTOLAND, when loss of all autoland capability occurs...
Page 153 777 TRAINING MANUAL OTHER MESSAGES AUTOPILOT DISC NO LAND 3 AUTOPILOT NO AUTOLAND NO LAND 3 NO AUTOLAND OTHER MESSAGES EICAS DISPLAY AFDC C AFDC R AUTOPILOT AFDC L BACKDRIVE L AUTOPILOT BACKDRIVE R WARNING MODE CTRL PANEL LANE NO AUTOLAND CAUTION NO LAND 3 MASTER WARNING AND...
Page 154 777 TRAINING MANUAL AFDS -- SPECIAL FUNCTIONS General You can select these two special functions on the MAT: Localizer antenna switching Glideslope antenna switching. The AFDS special functions make the localizer and glideslope switches change position. You use these special functions during ILS system troubleshooting. 22-11-00 - 142 - ALTEON PROPRIETARY.
Page 155 777 TRAINING MANUAL Select Function SPECIAL FUNCTIONS ILS LOCALIZER ANTENNA SWITCHING ILS GLIDESLOPE ANTENNA SWITCHING (22) Select ATA System 22 Autopilot Flight Director System 24 ELMS P110 Power Management Panel 24 ELMS P210 Power Management Panel 24 ELMS P310 Power Management Panel 27 High Lift System 29 Hydraulic System 31 AIMS - Display System...
Page 156 777 TRAINING MANUAL AFDS -- LRU TESTS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 144 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 157: 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 158 777 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 159 777 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 160 777 TRAINING MANUAL AFDS -- SYSTEM TESTS THIS PAGE INTENTIONALLY LEFT BLANK 22-11-00 - 148 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 161 777 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 162 777 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 163 777 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 164 777 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 165: 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 - 153 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 166 777 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 167: Pitot Probe
777 TRAINING MANUAL PITOT ADM (3) PITOT PROBE (3) SAARU FLIGHT CONTROLS ADIRU ARINC 629 BUS (3) ON/OFF STATIC ADM (3) SWITCH ADIRU HP/IN 29.92 STATIC STANDBY ADM AIR DATA MODULE POWER SUPPLY -200 BARO STATIC PORTS (6) INTEGRATED STANDBY CENTER PITOT PROBE PITOT STANDBY ADM FLIGHT DISPLAY...
Page 168 777 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. 34-11-00 - 156 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 169 777 TRAINING MANUAL PITOT-STATIC SYSTEM - FLIGHT DECK COMPONENT LOCATION 34-11-00 - 157 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 170 777 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 - 158 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 171 777 TRAINING MANUAL LEFT PITOT FORWARD SECTION - LEFT OF NOSE WHEEL WELL PITOT-STATIC SYSTEM - MEC COMPONENT LOCATION - 1 34-11-00 - 159 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 172 777 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 173 777 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 - 161 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 174 777 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 - 162 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 175 777 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 - 163 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 176 777 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 177 777 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 - 165 - ALTEON PROPRIETARY.
Page 178 777 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 179 777 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 180 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- INTERFACES ARINC 629 Interfaces The pitot probes and static ports send air pressure through pressure lines to the ADMs. The ADMs change the air pressures into ARINC 629 data. The data goes on the flight controls ARINC 629 buses to the ADIRU and SAARU.
Page 181 777 TRAINING MANUAL LEFT AND RIGHT CENTER PITOT RIGHT PITOT STATIC PORTS PROBE PROBE CENTER STATIC PORT RIGHT ADIRU SAARU PITOT FLIGHT CONTROLS ARINC 629 BUSES LEFT RIGHT CENTER STATIC STATIC CENTER STATIC PITOT PITOT SADM HP/IN 29.92 LEFT STATIC PITOT SADM -200...
Page 182 777 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 183 777 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 - 171 - ALTEON PROPRIETARY.
Page 184 777 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 185 777 TRAINING MANUAL PNEUMATIC CONNECTOR ELECTRICAL CONNECTOR FLANGES PITOT-STATIC SYSTEM - STANDBY AIR DATA MODULE 34-11-00 - 173 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 186 777 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 187 777 TRAINING MANUAL FASTENERS ELECTRICAL CONNECTOR FASTENERS PITOT-STATIC SYSTEM - AIR DATA MODULE POWER SUPPLY 34-11-00 - 175 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 188 777 TRAINING MANUAL PITOT-STATIC SYSTEM -- PITOT PROBE - HEAT General Air Mode The pitot air data modules (ADMs) control the heat Pitot heat goes to full power when one of these control relays in the power management panels. The heat conditions are true: control comes from data the ADMs receive from the primary flight computers (PFCs) through the flight...
Page 189 777 TRAINING MANUAL 115V AC LEFT XFR BUS PHASE B PHASE B PITOT PROBE HTR L 115V AC LEFT PITOT PROBE LEFT (STA 201, WL 156 XFR BUS LBL 53) PHASE C PHASE C PITOT GROUND PROBE HTR L PROBE HEAT GROUND SENSOR RELAY GROUND...
Page 190 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTRODUCTION THIS PAGE INTENTIONALLY LEFT BLANK 34-24-00 - 178 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 191: Training Manual
777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTRODUCTION Purpose fail warn - failure warning - forward The standby attitude reference system is a backup - grams system that shows the pilots this data: - acceleration due to gravity - glideslope Pitch attitude - heading Roll attitude...
Page 192 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTRODUCTION - power supply - reset - seconds SADM - standby air data module - software part number - airspeed - volts - wiring 34-24-00 - 180 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 193 777 TRAINING MANUAL HP/IN 29.67 3200 PITOT PRESSURE 3000 STATIC PRESSURE 2600 2,500 FT BARO 1,500 FT 500 FT STANDBY ATTITUDE REFERENCE SYSTEM - INTRODUCTION 34-24-00 - 181 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 194 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- GENERAL DESCRIPTION Standby Attitude Reference System an electrical signal and sends the data to the ISFD on an ARINC 429 data bus. The standby attitude reference system has an integrated standby flight display (ISFD) that shows: The pitot SADM gets pitot pressure from the center pitot probe.
Page 195 777 TRAINING MANUAL LEFT AIMS CABINET HP/IN MULTI-MODE RECEIVER CENTER 29.92 CENTER STATIC PORTS STATIC STANDBY ADM -200 AIR DATA MODULE POWER SUPPLY BARO PITOT STANDBY ADM INTEGRATED STANDBY FLIGHT DISPLAY LEFT POWER SUPPLY ASSEMBLY CENTER PITOT PROBE LEFT AIMS CABINET RIGHT AIMS CABINET STANDBY ATTITUDE REFERENCE SYSTEM - GENERAL DESCRIPTION 34-24-00...
Page 196 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- FLIGHT COMPARTMENT COMPONENT LOCATION Integrated Standby Flight Display The ISFD is on the P2-1 panel in the flight compartment. 34-24-00 - 184 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 197 777 TRAINING MANUAL HP/IN 29.92 -200 BARO INTEGRATED STANDBY FLIGHT DISPLAY STANDBY ATTITUDE REFERENCE SYSTEM - FLIGHT COMPARTMENT COMPONENT LOCATION 34-24-00 - 185 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 198 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- POWER Power The integrated standby flight display (ISFD) gets 28v dc from the STBY IND circuit breaker on the left power supply assembly through the ISFD circuit breaker on the P11 panel. The air data module power supply (ADM PS) gets 28v dc from the STBY IND circuit breaker on the left power supply assembly through the STBY ADM circuit breaker on...
Page 199 777 TRAINING MANUAL 28V DC LEFT FCDC 28V DC STBY IND ISFD RETURN LEFT POWER SUPPLY STBY ASSEMBLY (E1-6) INTEGRATED STANDBY 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 200 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- INTERFACES Standby Attitude Reference System Multi-Mode Receiver The standby attitude reference system has interfaces The center MMR sends localizer and glideslope deviation with: data to the ISFD on an ARINC 429 data bus. Airplane power Standby Air Data Modules Capt instrument and panel lights dimmer...
Page 201 777 TRAINING MANUAL 28V DC ISFD STBY IND LEFT POWER SUPPLY P11 CIRCUIT ASSEMBLY BREAKER PANEL 5V AC CAPT INST & MAGNETIC HEADING IR BUS L PNL LTS DIMMER GROUND SPEED CMCF LEFT AIMS CABINET AIR DATA LEFT AIMS CABINET BITE LOC DEV MMR DEV OUT 2...
Page 202 777 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 - 190 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 203 777 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 204 777 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 205 777 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 206 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- ISFD FUNCTIONAL DESCRIPTION STANDBY ATTITUDE REFERENCE SYSTEM -- ISFD FUNCTIONAL DESCRIPTION General The ISFD also gets 5v ac from the captain instrument panel lights dimmer for bezel lighting. The integrated standby flight display (ISFD) is the primary component of the standby attitude reference Program Pins system.
Page 207 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- ISFD FUNCTIONAL DESCRIPTION ARINC 429 Interfaces capacitance of the crystal. The accelerometer gives a dc voltage in proportion to the acceleration. The ISFD receives data from these components on ARINC 429 data buses: Bezel Controls Center multi-mode receiver (MMR) bus 2 - localizer The front face of the ISFD has five push-buttons and...
Page 208 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- ISFD FUNCTIONAL DESCRIPTION Controls the liquid crystal display (LCD) matrix drivers Does a refresh of the display. The display has a color active matrix LCD and a back- lighting box. The back-lighting box has these components: Three fluorescent tubes Reflector...
Page 209 777 TRAINING MANUAL POWER 28V DC GRAPHICS SUPPLY PROCESSING DISPLAY AIR- PLANE TYPE PARITY PROGRAM PINS OPTION LIGHT SENSOR DATA BEZEL CONTROL 5V DC CONTROLS LIGHTING SYSTEM BEZEL PROCESSING CONTROLS IR L MMR 2 ARINC INPUT PITOT ARINC AIMS STATIC XMTRS PITOT PNEU-...
Page 210 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - POWER-UP STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - POWER-UP Power-Up Display The ISFD uses a program pin as a parity pin to make sure the airplane model and optional functions are correct. The ISFD shows flags when it first gets power.
Page 211 777 TRAINING MANUAL HP/IN HP/IN HP/IN 30.08 INIT 90s INIT 90s -200 -200 BARO BARO BARO 0-15 SECONDS 15-90 SECONDS >90 SECONDS HP/IN HP/IN PROGRAM OUT OF ORDER PIN ERROR FAULT CODE XXXX XXXX XXXX BARO BARO FAILURE DISPLAYS STANDBY ATTITUDE REFERENCE SYSTEM - OPERATION - POWER-UP 34-24-00 - 199 - ALTEON PROPRIETARY.
Page 212 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - ATTITUDE STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - ATTITUDE THIS PAGE INTENTIONALLY LEFT BLANK 34-24-00 - 200 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 213 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - ATTITUDE Normal Display Messages The ISFD shows pitch and roll attitude. The ISFD shows these messages on the attitude display: The ISFD goes through alignment when it first receives INIT 90s - initialize for 90 seconds power.
Page 214 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - ATTITUDE The attitude reset (ATT:RST) message shows if the inertial sensors sense an angular rate or acceleration more than the maximum for more than 10 seconds. The maximum angular rate is 100 degrees per second. The maximum acceleration is 3.2g.
Page 215 777 TRAINING MANUAL ROLL ATTITUDE POINTER HP/IN ROLL ATTITUDE SCALE PITCH ATTITUDE SCALE 30.08 AIRPLANE SYMBOL -200 BARO NORMAL DISPLAY ATTITUDE RESET SWITCH HP/IN HP/IN ATTITUDE ATTITUDE MESSAGES FAILURE FLAG - WAIT ATT 30.08 IN 30.08 IN - ATT 10s - ATT:RST WAIT ATT INITIALIZATION...
Page 216 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - AIRSPEED AND ALTITUDE STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - AIRSPEED AND ALTITUDE General setting in units of hectopascals (hPa) or inches of mercury (in Hg). The ISFD shows HPA for hectopascals or The ISFD uses pneumatic inputs from alternate pitot and IN for inches of mercury.
Page 217 777 TRAINING MANUAL BAROMETRIC REFERENCE SWITCH HP/IN BAROMETRIC REFERENCE SETTING AIRSPEED 30.08 - IN (INCHES OF MERCURY) TAPE - HPA (HECTOPASCALS) - STD (STANDARD PRESSURE) ALTITUDE TAPE INDICATED ALTITUDE AIRSPEED -200 STANDARD SELECT SWITCH BAROMETRIC HP/IN CONTROL ALTITUDE 30.08 BARO FLAG NORMAL DISPLAY AIRSPEED...
Page 218 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - HEADING STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - HEADING General The integrated standby flight display (ISFD) receives magnetic heading data from the left AIMS cabinet. The ISFD shows the magnetic heading on a compass rose at the bottom of the display.
Page 219: Normal Display
777 TRAINING MANUAL HP/IN 30.08 HEADING -200 COMPASS ROSE HP/IN 30.08 BARO NORMAL DISPLAY HEADING FLAG -200 BARO FAILURE DISPLAY STANDBY ATTITUDE REFERENCE SYSTEM - OPERATION - HEADING 34-24-00 - 207 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 220 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - APPROACH STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - APPROACH THIS PAGE INTENTIONALLY LEFT BLANK 34-24-00 - 208 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 221 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - APPROACH General Not Valid Data Display There are no special ILS tests for the integrated Not valid data is the first display in the self-test standby flight display (ISFD). You do a check of the sequence.
Page 222 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- OPERATION - APPROACH Glideslope pointer shows one dot of down deviation. The approach display goes back to normal indications at the end of the self-test sequence. 34-24-00 - 210 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 223 777 TRAINING MANUAL MODE HP/IN HP/IN HP/IN GLIDE- SLOPE BCRS 29.92 29.92 29.92 POINTER -200 -200 -200 BARO DEVIATION BARO BARO SCALES APPROACH MODE LOCALIZER BACK COURSE MODE FAILURE FLAGS POINTER NOT VALID DATA DISPLAY NO COMPUTED DATA DISPLAY UP/LEFT DISPLAY DOWN/RIGHT DISPLAY 0-3 SECONDS 3-5 SECONDS...
Page 224 777 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 225 777 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 226 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - FUNCTIONAL TEST STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - FUNCTIONAL TEST General Fault Messages The functional test does checks of the operation of the At the end of the functional test the ISFD BITE shows integrated standby flight display (ISFD) and the input fault messages if there are faults.
Page 227: Fault Messages
777 TRAINING MANUAL HP/IN HP/IN TEST < TESTS TEST OK HP/IN < OTHER DATA TESTS return return BARO BARO IN PROGRESS 110s HP/IN HP/IN TESTS TESTS < FUNCTIONAL TEST (110s) BARO ISFD ALTITUDE FUNCTION ADIRU BUS IR OR IRS/ ISFD <...
Page 228 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - DISPLAY TEST STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - DISPLAY TEST General The display test does a check of the operation of the liquid crystal display (LCD) matrix in the integrated standby flight display (ISFD).
Page 229 777 TRAINING MANUAL HP/IN HP/IN TESTS < TESTS < FUNCTIONAL TEST (110s) < DISPLAY TEST < OTHER DATA return return ATT RST BARO ATT RST BARO HP/IN HP/IN < < return return ATT RST BARO ATT RST BARO STANDBY ATTITUDE REFERENCE SYSTEM - TIP - BITE - DISPLAY TEST 34-24-00 - 217 - ALTEON PROPRIETARY.
Page 230 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - LRU IDENT STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - LRU IDENT General The LRU IDENT (line-replaceable-unit identification) page lets you see identification data for the ISFD. Access Push and hold the approach mode (APP) and the barometric reference setting (HP/IN) switches for two...
Page 231 777 TRAINING MANUAL HP/IN HP/IN OTHER DATA < TESTS < LRU IDENT < OTHER DATA < ENGINEERING DATA return return ATT RST BARO BARO HP/IN LRU IDENT P/N C16221KA01 S/N C16221000388 A/C CONFIG:18DEG APP HDG BCRS FUNCT TIME: 00925h return BARO STANDBY ATTITUDE REFERENCE SYSTEM - TIP - BITE - LRU IDENT 34-24-00...
Page 232 777 TRAINING MANUAL STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - ENGINEERING DATA STANDBY ATTITUDE REFERENCE SYSTEM -- TIP - BITE - ENGINEERING DATA General These are the classes of failures: The ENGINEERING DATA page lets you see data about Class 1 - A failure with a flight deck effect that faults.
Page 233 777 TRAINING MANUAL HP/IN HP/IN OTHER DATA < TESTS < LRU IDENT < OTHER DATA < ENGINEERING DATA return return ATT RST BARO BARO HP/IN HP/IN HP/IN ENGINEERING ENGINEERING ENGINEERING DATA DATA DATA CLASS CLASS HOURS FAILURE CODE 00923h 00921h 00923 0000 0200 8020 ISFD ADIRU BUS IR OR IRS/...
Page 234 777 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 235 777 TRAINING MANUAL AIR DATA INERTIAL REFERENCE SYSTEM - INTRODUCTION 34-20-00 - 223 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 236 777 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 237 777 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 - 225 - ALTEON PROPRIETARY.
Page 238 777 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 239 777 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 240 777 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 241 777 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 242 777 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 - 230 - ALTEON PROPRIETARY.
Page 243 777 TRAINING MANUAL RIGHT AOA SENSOR LEFT AOA SENSOR TAT PROBE ADIRS - COMPONENT LOCATION - AOA SENSORS AND TAT PROBE 34-20-00 - 231 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 244 777 TRAINING MANUAL ADIRS -- COMPONENT LOCATION - LEFT PITOT ADM General The left pitot ADM is in the left forward section of the main equipment center. 34-20-00 - 232 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 245 777 TRAINING MANUAL LEFT PITOT ADM FORWARD SECTION - LEFT OF NOSE WHEEL WELL ADIRS - COMPONENT LOCATION - LEFT PITOT ADM 34-20-00 - 233 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 246 777 TRAINING MANUAL ADIRS -- COMPONENT LOCATION - CENTER AND RIGHT PITOT ADM Right and Center Pitot Air Data Modules (ADMs) The right and center pitot ADMs are in the MEC, to the right of the nose wheel well and under the flight deck. 34-20-00 - 234 - ALTEON PROPRIETARY.
Page 247 777 TRAINING MANUAL CENTER RIGHT PITOT PITOT ADM MAIN EQUIPMENT CENTER (RIGHT SIDE, LOOKING FORWARD) ADIRS - COMPONENT LOCATION - CENTER AND RIGHT PITOT ADM 34-20-00 - 235 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 248 777 TRAINING MANUAL ADIRS -- COMPONENT LOCATION - STATIC ADM AND STATIC SADM Static Air Data Modules (ADM) The static ADMs are in the forward cargo compartment ceiling above the cargo liner. 34-20-00 - 236 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 249 777 TRAINING MANUAL FWD CARGO COMPARTMENT STATIC SADM DOOR CENTER STATIC FWD CARGO COMPARTMENT (LOOKING AFT) LEFT STATIC RIGHT STATIC ADIRS - COMPONENT LOCATION - STATIC ADM AND STATIC SADM 34-20-00 - 237 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 250 777 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 251 777 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 252 777 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 253 777 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 254 777 TRAINING MANUAL ADIRS -- DIGITAL INTERFACES THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 242 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 255: 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 256 777 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 257 777 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 258 777 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 259: 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 - 247 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 260 777 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 261 777 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 262 777 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 263 777 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 264 777 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 265 777 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 266 777 TRAINING MANUAL ADIRS -- ADIRU POWERUP, ON BATTERY, POWERDOWN PFC/ADIRU Panel Battery switch is in the off position Ground service relay is in the off position The primary flight computer (PFC)/ADIRU panel has the Air/ground relay is in the ground position ADIRU switch and the ADIRU on battery (ON BAT) light.
Page 267 777 TRAINING MANUAL POWER AND I/O MONITOR GROUND CREW CALL HORN (NOSE LANDING GEAR) 28V DC POWER INPUTS FROM 28V DC FROM POWER R,L DC BUSES HOT BAT BUS SUPPLY AND HOT BAT MD&T ADIRU ADIRU SWITCH ON BAT GROUND SERVICE ADIRU ON BATTERY AIR/GROUND...
Page 268 777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 1 THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 256 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 269: Training Manual
777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 1 General Speedbrake Lever Past Arm Signal Redundancy management logic in the ADIRU selects a The primary flight computers (PFCs) supply the value from the inputs that come from more than one speedbrake lever angle signals to the ADIRU.
Page 270 777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 1 Mach from the calculate mach and airspeed logic management logic uses body accelerations from the ADIRU True airspeed (TAS) from the calculate true inertial reference section to adjust fault detection airspeed logic.
Page 271 777 TRAINING MANUAL TAT 1 (L AIMS CAB) REDUNDANCY INERTIAL TAT 2 (R AIMS CAB) DATA MANAGEMENT DATA L PITOT HTR VALID (ADM) INPUT DATA C PITOT HTR VALID (ADM) REDUNDANCY R PITOT HTR VALID (ADM) MANAGEMENT CALCULATE PITOT ADM VOTED CALCULATED REDUNDANCY...
Page 272 777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 2 THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 260 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 273 777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 2 Total Air Temperature (TAT) management logic. The calculate impact pressure function also receives pitot pressure from the pitot The TAT correction function receives TAT and calculated ADM redundancy management. The impact pressure signal mach and computed air speed (CAS).
Page 274 777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 2 Barometric altitude Total pressure. 34-20-00 - 262 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 275 777 TRAINING MANUAL TOTAL AIR TEMPERATURE CORRECTION CALCULATE STATIC AIR TEMPERATURE STATIC AIR TO CALCULATE CORR AOA TEMPERATURE CALCULATE TRUE AIRSPEED TRUE INVALID TRUE AIRSPEED AIRSPEED CAS <30 KTS (CORRECTED AOA) FROM AOA CORRECTED AOA REDUNDANCY MANAGEMENT INVALID CORRECTED AOA TO CALCULATE CORR CAS <30 KTS AOA,SSEC,AOA RED...
Page 276 777 TRAINING MANUAL ADIRS -- ADIRU AIR DATA FUNCTION - 3 Outputs The ADIRU transmits air data to the left and right flight controls ARINC 629 buses. The air data goes to these components: Left and right AIMS cabinets Left, center, and right primary flight computers (PFCs) Left, center, and right autopilot flight director computers (AFDCs).
Page 277 777 TRAINING MANUAL TOTAL AIR TEMPERATURE STATIC AIR TEMPERATURE TRUE AIRSPEED ARINC TO LEFT FLIGHT CONTROLS 629 I/O CORRECTED AOA ARINC 629 BUS: MODULE - L,R AIMS CABINETS ARINC MACH - L,C,R PFC 629 I/O - L,C,R AFDC MODULE COMPUTED AIRSPEED IMPACT PRESSURE LEFT ARINC 629 INTERFACE...
Page 278 777 TRAINING MANUAL ADIRS -- ADIRU INERTIAL REFERENCE DATA FUNCTION - 1 General Compares the entered initial position to the global position system (GPS) position or the last The ADIRU uses data from the flight management ADIRU stored position if GPS data is not computing function (FMCF) in the AIMS cabinets to do available.
Page 279 777 TRAINING MANUAL FROM LEFT INITIAL LEFT FLT ARINC POSITION CONTROLS ARINC INTFC INITIAL 629 BUS GPS LONG TO POSITION POSITION INTEGRATOR VALIDATION GPS LAT FROM L,R GPS VEL AIMS FROM CENTER CABINETS: CENTER FLT ARINC - INITIAL CONTROLS POSITION ARINC INTFC - GPS LAT...
Page 280 777 TRAINING MANUAL ADIRS -- ADIRU INERTIAL REFERENCE DATA FUNCTION - 2 THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 268 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 281 777 TRAINING MANUAL ADIRS -- ADIRU INERTIAL REFERENCE DATA FUNCTION - 2 Wind Speed and Wind Direction The accelerations in relation to the earth go to the velocities integrator. The velocities integrator True airspeed data from the ADIRU air data function calculates velocities.
Page 282 777 TRAINING MANUAL ADIRS -- ADIRU INERTIAL REFERENCE DATA FUNCTION - 2 Ground Speed, True Track, and Track Rate Body lateral. The velocities integrator calculates: Flight Path Angle Ground speed The air data function of the ADIRU supplies barometric True track altitude to the calculate flight path angle logic Track rate.
Page 283 777 TRAINING MANUAL TRUE AIRSPEED CALCULATE WIND SPEED FROM AIR DATA WIND SPEED FUNCTION INITIAL POSITION CALCULATE WIND DIRECTION VALIDATION (1 TIME) WIND DIRECTION PITCH RATE ROTATIONAL ROLL RATE RATES TO AOA HEADING RATE REDUNDANCY MANAGEMENT PITCH ANGLE ANGLES ROLL ANGLE INTEGRATOR TRUE HEADING CALCULATE...
Page 284 777 TRAINING MANUAL ADIRS -- ADIRU INERTIAL REFERENCE DATA FUNCTION - 3 Output The ADIRU transmits inertial reference data to the left and right flight control ARINC 629 buses. The inertial reference data goes to these components: Left and right AIMS cabinets Left, center, and right primary flight computers (PFCs) Left, center, and right autopilot flight director...
Page 285 777 TRAINING MANUAL WIND SPEED WIND DIRECTION PITCH RATE ROLL RATE ARINC HEADING RATE TO LEFT FLIGHT CONTROLS 629 I/O ARINC 629 BUS: PITCH ANGLE MODULE - L,R AIMS CABINETS ROLL ANGLE ARINC - L,C,R PFC 629 I/O TRUE HEADING - L,C,R AFDC MODULE MAGNETIC HEADING...
Page 286 777 TRAINING MANUAL ADIRS -- AIR DATA MODULE THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 274 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 287 777 TRAINING MANUAL ADIRS -- AIR DATA MODULE ADM General The ADM has a flange on each side. Each flange has two captive screws. The ADM mounts directly to the mounting There are six air data modules (ADMs) in the air data tray flanges.
Page 288 777 TRAINING MANUAL ADIRS -- AIR DATA MODULE Pitot Probe and AOA Sensor Heat Control The power management panels connect the ground heat and the air heat signals to current sense relays to control The left pitot ADM controls the heat for the left pitot the voltage to the pitot probes.
Page 289 777 TRAINING MANUAL MOUNTING TRAY FLANGE ARINC 629 FLANGE CONNECTOR PROGRAM PINS, POWER AND HEAT CONTROL WIRING CONNECTOR PNEUMATIC PRESSURE INPUT POWER 28V DC SUPPLY AOA SENSOR CASE INPUT/ PROGRAM HEAT IND OUTPUT PINS AOA SENSOR INPUT DECODER VANE HEAT IND BUFFER PROCESSOR TO L,R...
Page 290 777 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 291 777 TRAINING MANUAL COOLING FINS ADIRS - SECONDARY ATTITUDE AIR DATA REFERENCE UNIT 34-20-00 - 279 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 292 777 TRAINING MANUAL ADIRS -- SAARU INERTIAL REFERENCE DATA FUNCTION General Barometric Altitude Input The secondary attitude air data reference unit (SAARU) The SAARU uses barometric altitude from its air data uses gyros and accelerometers to calculate inertial section to calculate vertical speed. This barometric reference data.
Page 293 777 TRAINING MANUAL POWER 28V DC SUPPLY CALCULATE BODY BODY FRAME ACCELERATIONS ACCELERATIONS CALCULATE BUFFER BODY BODY FRAME RATES GYROS RATES CALCULATE TO CENTER ATTITUDES ATTITUDE BUFFER FLIGHT CONTROLS ARINC 629 BUS ACCEL - L,R AIMS - L,R,C PFC CALCULATE - L,R,C AFDC HORIZONTAL HORIZ AND...
Page 294 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 1 THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 282 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 295 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 1 General AOA Input Redundancy management logic in the SAARU selects or The AOA values go to the function that calculates the votes a value for the inputs that come from the corrected AOA.
Page 296 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 1 Calculate Corrected AOA The static ADM redundancy management logic calculates an average of the static pressures from the ADMs. The The calculate corrected AOA logic calculates the left static ADM redundancy management logic uses body and right corrected AOA.
Page 297 777 TRAINING MANUAL TAT 1 (L AIMS) TAT 2 (R AIMS) REDUNDANCY INERTIAL AIR MANAGEMENT DATA DATA L PITOT HTR VALID (L ADM) C PITOT HTR VALID (C ADM) CALCULATE R PITOT HTR VALID (R ADM) VOTED PITOT ADM CALCULATED PITOT DATA FROM: REDUNDANCY...
Page 298 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 2 THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 286 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 299 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 2 Total Air Temperature (TAT) management logic. The calculate impact pressure function also receives pitot pressure from the pitot The TAT signal is corrected for the small temperature ADM redundancy management. The impact pressure signal rise that occurs when the air flow through the probe goes to the output memory buffer.
Page 300 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 2 Barometric altitude Total pressure. 34-20-00 - 288 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 301 777 TRAINING MANUAL TOTAL AIR TEMPERATURE CORRECTION CALCULATE STATIC AIR TEMPERATURE STATIC AIR TO CALCULATE CORR AOA TEMPERATURE CALCULATE TRUE AIRSPEED TRUE INVALID TRUE AIRSPEED AIRSPEED CAS <50 KTS (CORRECTED AOA) FROM AOA CORRECTED AOA REDUNDANCY MANAGEMENT INVALID CORRECTED AOA TO CALCULATE CORR CAS <50 KTS AOA,SSEC,AOA RED...
Page 302 777 TRAINING MANUAL ADIRS -- SAARU AIR DATA FUNCTION - 3 Air Data Outputs The secondary attitude air data reference unit (SAARU) sends data on the center flight control ARINC 629 bus. The data goes to the: Primary flight computers (PFCs) AIMS cabinets Autopilot flight director computers (AFDCs).
Page 303 777 TRAINING MANUAL TOTAL AIR TEMPERATURE STATIC AIR TEMPERATURE TRUE AIRSPEED CORRECTED AOA MACH COMPUTED AIRSPEED IMPACT PRESSURE TO CENTER FLIGHT CONTROLS ALTITUDE ARINC 629 BUS: ARINC 629 - L,R,C PFC ALTITUDE RATE TRANSMITTER - L,R AIMS CABINETS - L,R,C AFDC PITOT PRESSURE STATIC PRESSURE SINGLE CHANNEL MACH...
Page 304 777 TRAINING MANUAL ADIRS -- SAARU BACKUP NAVIGATION General East velocity. The ADIRU supplies navigation data to the autopilot The SAARU monitors the ADIRU inputs. If one or more flight director system (AFDS) and the primary flight inputs are invalid and the true airspeed (TAS) from the control system (PFCS).
Page 305 777 TRAINING MANUAL ADIRS -- SAARU BACKUP NAVIGATION Calculate Flight Path Acceleration modes do not operate when the ADIRU fails and SAARU backup navigation is not available. These are the AFDS The calculate flight path acceleration logic uses these modes that do not operate in this condition: inputs: Approach (APP) Along track horizontal acceleration...
Page 306 777 TRAINING MANUAL ADIRS -- SAARU BACKUP NAVIGATION fails. The flight crew must select another autopilot mode or disengage the autopilot. If the ADIRU fails when the TRK HLD or TRK SEL mode is engaged, the AFDS will automatically select the SAARU backup navigation data.
Page 307 777 TRAINING MANUAL <3 MIN IN BACK-UP BACK-UP NAV ROLL ANGLE ADIRU VALIDITY BITS FOR EACH BACK-UP ADIRU WORD SAARU TAS PITCH ANGLE >80 KTS BACK-UP BACK-UP ENABLE MAG HDG SAARU ROLL ANGLE ROLL ANGLE BACK-UP MAG TRACK PITCH ANGLE ANGLE MAG HDG SAARU PITCH...
Page 308 777 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 309 777 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 310 777 TRAINING MANUAL ADIRS -- TAT PROBE FUNCTIONAL DESCRIPTION Probe Heater The TAT probe heater gets 115v ac from the P110 left power management panel. The TAT probe has heater power only when the airplane is in the air. Total Air Temperature (TAT) TAT element 1 connects to the TAT element 1 sense and return in the left AIMS cabinet.
Page 311 777 TRAINING MANUAL ELEMENT 1 TAT ELEMENT 1 SENSE TAT TO LEFT FLIGHT CONTROLS ARINC 629 BUS TAT ELEMENT 1 RETURN 115V AC HEATER LEFT AIMS CABINET FROM P110 (E3-1) LEFT POWER MGMT PANEL ELEMENT 2 TAT ELEMENT 2 SENSE TAT TO RIGHT FLIGHT CONTROLS ARINC 629 BUS TAT ELEMENT 2 RETURN...
Page 312 777 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 313 777 TRAINING MANUAL HOLE FOR ELECTRICAL MOUNTING CONNECTOR BOLTS (8) ALIGNMENT PINS SENSOR VANE ADIRS - ANGLE OF ATTACK SENSOR 34-20-00 - 301 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 314 777 TRAINING MANUAL ADIRS -- AOA SENSOR FUNCTIONAL DESCRIPTION AOA Heaters The case and the vane heaters in the angle of attack (AOA) sensors receive 115v ac from the power management panels for power. AOA Measurement and Transmission The resolvers in the left AOA sensor send the AOA to the left AIMS cabinet.
Page 315 777 TRAINING MANUAL 28V AC AOA REFERENCE AC RETURN RESOLVER 1 AOA SINE COMMON AOA COSINE CASE HEATER 115V AC IN TO LEFT FLIGHT CONTROLS 115V AC IN 28V AC ARINC 629 VANE HEATER AOA REFERENCE AC RETURN P110 LEFT POWER RESOLVER 2 MGMT PANEL AOA SINE...
Page 316 777 TRAINING MANUAL ADIRS -- ADM CONTROL OF AOA SENSOR HEAT Functional Description Training Information Point The angle of attack (AOA) sensor has two heaters, one The air AOA heat and ground AOA heat is 115v ac. for the AOA vane and one for the AOA case. Power for the heaters comes through the ground heat control relay or See the ice and rain protection chapter for information the air heat control relay.
Page 317 777 TRAINING MANUAL CASE HEATER VANE HEATER LEFT AOA SENSOR (STA 217, WL 203, LBL 74) GROUND 115V AC K30121 PROBE HEAT LEFT AC SENSOR RELAY - SEC 1 AOA CASE L AOA PROBE HTR L 28V DC LEFT MAIN PROBE/VANE GROUND HTR CTRL L...
Page 318 777 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 319 777 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 320 777 TRAINING MANUAL ADIRS -- AIR DATA/ATTITUDE SOURCE SWITCHING-NON NORMAL General SAARU center flight controls ARINC 629 bus (air data and attitude) The table shows the normal and alternate positions for ADIRU right flight controls ARINC 629 bus (single the captain and first officer air data/attitude switch channel air data) during normal and non-normal conditions.
Page 321 777 TRAINING MANUAL ADIRU NORMAL ADIRU NORMAL CONDITION ADIRU FAIL ADIRU FAIL SAARU NORMAL SAARU NORMAL AIR DATA/ATT SAARU FAIL SAARU FAIL SWITCH POSITION ADIRU L BUS SAARU C BUS SAME AS CAPT - NO DISPLAY ATTITUDE AND ATTITUDE AND ADIRU NORMAL NORMAL DATA AVAIL...
Page 322 777 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 323 777 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 - 311 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 324 777 TRAINING MANUAL ADIRS -- ALIGNMENT THIS PAGE INTENTIONALLY LEFT BLANK 34-20-00 - 312 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 325: Training Manual
777 TRAINING MANUAL ADIRS -- ALIGNMENT General available. The last stored position comes from the nonvolatile memory (NVM) of the ADIRU. To supply inertial position data, the ADIRU must be in the navigation (NAV) mode. Before the ADIRU enters the If the ADIRU fails the position compare test, the CDU NAV mode, it must go through alignment and position message ENTER INERTIAL POSITION shows.
Page 326 777 TRAINING MANUAL ADIRS -- ALIGNMENT Align Reset Mode ADIRU position and not NVM stored position if GPS data is not available. If the airplane moves during alignment, the ADIRU senses the movement and goes into the align reset mode. Two seconds after the crew enters a position, line data When airplane movement stops, the ADIRU align mode field 5R on the CDU POS INIT page goes back to dashes.
Page 327 777 TRAINING MANUAL ADIRU ALIGN MODE ADIRU SWITCH TO ON POSITION 30-SECOND CDU SHOWS BOX PROMPTS SELF-TEST STARTS INITIALIZATION MODE CDU SHOWS AUTO NAV NO AIRPLANE MOVEMENT PILOT ENTERS DASH PROMPTS NAV MODE INERTIAL POSITION REALIGN MODE FOR 6 - 15 MINUTES ENTERED? SECOND THE ENTERED...
Page 328 777 TRAINING MANUAL ADIRS -- ALIGNMENT - POS INIT CDU PAGE General INERTIAL POS message. Enter the same inertial position again and the ADIRU uses that position to complete To begin alignment, access the POS INIT page on the alignment and goes into the NAV mode. CDU.
Page 329 777 TRAINING MANUAL P O S I N I T P O S I N I T L A S T P O S L A S T P O S N 4 0 3 8 . 0 W 0 7 3 4 6 .
Page 330 777 TRAINING MANUAL ADIRS -- ND AND PFD INDICATIONS DURING ALIGNMENT General These are the indications when the ADIRU is in the align mode: The PFDs show no computed data (NCD) attitude, track and heading data The PFDs show ADIRU air data The NDs show NCD track and heading data TIME TO ALIGN display shows on the ND ADIRU ALIGN MODE memo message shows on the EICAS...
Page 331 777 TRAINING MANUAL ATTITUDE DATA DOES NOT SHOW ADIRU TIME TO HEADING AND TRACK ALIGN DISPLAY SHOWS DATA DOES NOT SHOW -200 TIME TO ALIGN 5:35 ADIRU AIR DATA SHOWS HEADING AND TRACK DATA DOES NOT SHOW ADIRU ALIGN MODE EICAS MEMO MESSAGE DURING ALIGNMENT ADIRS - ND AND PFD INDICATIONS DURING ALIGNMENT...
Page 332 777 TRAINING MANUAL ADIRS -- PFD AND ND INDICATIONS AFTER ALIGNMENT General When the ADIRU alignment completes and the ADIRU is in the NAV mode, the PFD AND ND show attitude and air data from the ADIRU. 34-20-00 - 320 - ALTEON PROPRIETARY.
Page 333 777 TRAINING MANUAL PITCH SCALE BANK POINTER HOLD LNAV VNAV AND SLIP/SKID IBFI/123` 25.3 HORIZON AND SKY-GROUND SHADING VERTICAL SPEED SCALE HEADING POINTER MAG/TRU ANNUNICATION TRACK LINE GROUND SPEED TRUE AIRSPEED TRACK OR HDG SELECTED RADIO HEADING AND BUG 29.86 TRACK/ VOR R 190` /15...
Page 334 777 TRAINING MANUAL ADIRS -- PFD AND ND INVALID IRS DATA General The PFD and ND show the invalid attitude and invalid air data indications. The PFD shows flags for these displays: Airspeed Attitude Altitude Vertical speed Heading. The ND shows a heading or track flag. 34-20-00 - 322 - ALTEON PROPRIETARY.
Page 335 777 TRAINING MANUAL AIR SPEED HEADING OR FLAG TRACK FLAG ATTITUDE FLAG ALTITUDE FLAG VERTICAL SPEED SCALE REPLACED BY VERTICAL SPEED FLAG HEADING SCALE AND NUMERICS REPLACED WITH HEADING FLAG ADIRS - PFD AND ND INVALID IRS DATA 34-20-00 - 323 - ALTEON PROPRIETARY.
Page 336 777 TRAINING MANUAL ADIRS -- INERTIAL MONITOR PAGE Purpose The inertial monitor page shows the position error rate for the ADIRU. Page Access To get access to the INERTIAL MONITOR page, select <INERTIAL MONITOR from the MAINTENANCE INDEX page. Color All text on this page is white.
Page 337 777 TRAINING MANUAL < < < < ADIRS - INERTIAL MONITOR PAGE 34-20-00 - 325 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 338 777 TRAINING MANUAL ADIRS -- FAULT REPORT AND SOFTWARE DATA LOAD General SAARU and ADM Status These components in the ADIRS report faults and system The SAARU and the ADMs continuously supply BITE status status to the central maintenance computing function data to the CMCF of the AIMS.
Page 339 777 TRAINING MANUAL STATUS, POWER-UP TEST RESULTS, DATA LOAD ADIRU (E3-3) STATUS, DATA LOAD - BITE STATUS TO CMCF (L,R AIMS CABINETS) SAARU (E2-7) - SOFTWARE DATA LOAD (FROM MAT THROUGH L OR R AIMS CABINET) STATUS, DATA LOAD LEFT PITOT AND STATIC ADM STATUS, DATA LOAD...
Page 340 777 TRAINING MANUAL STANDBY MAGNETIC COMPASS -- Purpose Use the compensation screws to correct for magnetic deviations generated by electrical currents in the The standby magnetic compass is a backup magnetic flight deck. Use only non-magnetic tools to turn the heading reference.
Page 341 777 TRAINING MANUAL TURN TO UNCOVER COMPENSATION SCREWS COMPENSATION COMPENSATION SCREW SCREW MOUNTING SCREW (4) HEADING INDICATOR CARD (INSIDE CASE) LIGHT BULB STANDBY MAGNETIC COMPASS 34-23-00 - 329 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 342 777 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 343 777 TRAINING MANUAL ALTITUDE ABOVE THE GROUND RADIO ALTIMETER SYSTEM - INTRODUCTION 34-33-00 - 331 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 344 777 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 345 777 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 - 333 - ALTEON PROPRIETARY.
Page 346 777 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 347 777 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 348 777 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 - 336 - ALTEON PROPRIETARY.
Page 349 777 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 - 337 -...
Page 350 777 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 351 777 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 352 777 TRAINING MANUAL RA SYSTEM -- DATA BUS OUTPUTS, RADIO MINIMUMS INTERFACE General Fault Summary Data The RA system supplies data to the: Fault data from each radio altimeter goes to the AIMS cabinets. The AIMS cabinets send data to the status Left, center, and right AFDCs page.
Page 353 777 TRAINING MANUAL LEFT AFDC DATA BUS 1 CDU RADIO MINIMUMS FROM SYSTEMS ARINC 629 DATA BUS 2 BUSES (L,R) RA DATA LEFT RA XCVR TCAS COMPUTER DATA BUS 2 CAPT RIGHT AFDC RADIO MINS DATA BUS 1 RA DATA LEFT EFIS CONTROL LEFT AIMS CABINET...
Page 354 777 TRAINING MANUAL RA SYSTEM -- CMCF INTERFACE CMCF Interface The central maintenance computing function (CMCF) of the airplane information management system (AIMS) does tests and monitors the status of the RA system. Maintenance technicians use the maintenance access terminal (MAT) to interface with the CMCF. The MAT data goes to the AIMS cabinets.
Page 355 777 TRAINING MANUAL RESULTS/ STATUS STATUS DATA TEST CMCF DATA LEFT RA RT RESULTS/ STATUS LEFT AIMS CABINET TEST CMCF CENTER RA RT DATA RESULTS/ STATUS STATUS DATA TEST RIGHT RA RT RIGHT AIMS CABINET RA SYSTEM - CMCF INTERFACE 34-33-00 - 343 - ALTEON PROPRIETARY.
Page 356 777 TRAINING MANUAL RA SYSTEM -- RA TRANSCEIVER Purpose A red REC ANT FAIL LED shows a receive antenna or coax cable fault. The RA transceiver calculates radio altitude. You push the test switch to start a self-test. The RA transceiver has a non-volatile memory which stores fault information from the last sixty-three Training Information Point flights.
Page 357 777 TRAINING MANUAL COLLINS CONN TEST LED STATUS STATUS INDICATORS XMIT ANT FAIL ANT FAIL TEST SWITCH TEST LRA-900 RA SYSTEM - RA TRANSCEIVER 34-33-00 - 345 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 358 777 TRAINING MANUAL RA SYSTEM -- RA ANTENNA Purpose The RA system uses six antennas that transmit and receive RF signals. Each RA xcvr has a transmit and receive antenna. The transmit and receive antenna are the same and interchangeable. Physical Description Four screws attach each antenna to the bottom of the fuselage.
Page 359 777 TRAINING MANUAL RA SYSTEM - RA ANTENNA 34-33-00 - 347 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 360 777 TRAINING MANUAL RA SYSTEM -- OPERATION - 1 THIS PAGE INTENTIONALLY LEFT BLANK 34-33-00 - 348 - ALTEON PROPRIETARY. Copyright. See title page for details...
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777 TRAINING MANUAL RA SYSTEM -- OPERATION - 1 EFIS Control Panel The barometric minimums function does not have a relation to the radio altimeter operation. The EFIS control panel controls the radio minimums and does a reset of the radio minimums alert. The radio minimums show on the captain and first officer PFDs.
Page 362 777 TRAINING MANUAL RA SYSTEM -- OPERATION - 1 Radio altitude, the letters RADIO, and the radio view. The not valid occurs when the EFIS control panel, minimums value go on and off three times at a 4 Hz the on-side CDU, and the center CDU have failures. rate.
Page 363 777 TRAINING MANUAL RA DISPLAY (YELLOW) MINS RADIO BARO RADIO/BARO MINS CONTROL RADIO RADIO MINIMUMS DISPLAY EFIS CONTROL (YELLOW) RADIO MINIMUMS ALERT PANEL RADIO ALTITUDE (WHITE) OUT OF VIEW ABOVE 2500) RADIO RADIO MINIMUMS (GREEN) (OUT OF VIEW FOR RADIO MINIMUMS >999 FEET OR <0 FEET) NCD OR RA >2500...
Page 364 777 TRAINING MANUAL RA SYSTEM -- OPERATION - 2 Purpose In addition to the EFIS control panels, the flight crew can use the CDUs to select a radio minimums value and to reset a radio minimums alert. When the flight crew uses the CDU, the onside EFIS control panel does not operate.
Page 365 777 TRAINING MANUAL LINE SELECT E F I S C O N T R O L KEYS (12) B A R O S E T M O D E 2 9 . 9 2 < S E L > A P P > M I N A L T S R C...
Page 366 777 TRAINING MANUAL RA SYSTEM -- RF PROCESSING General The aircraft installation delay (AID) program pin is grounded to 80 feet selection. This calibrates the The RA transceiver (xcvr) transmits a frequency system so that the radio altitude is zero feet at modulated/continuous wave (FM/CW) signal through the touchdown.
Page 367 777 TRAINING MANUAL TRANSMIT ANTENNA (STA 623.5) CONTROL DIFF FREQ TRANSMITTER MODULATOR RECEIVE ANTENNA (STA 665.5) LEFT AFDC LEFT SYS SELECT (E1-3) ALTITUDE PROCESSOR AID 80 FT LEFT, RIGHT AIMS CABINETS (E3-1, E3-2) CONTINUOUS DATA ARINC 429 TRANSMITTERS TCAS COMPUTER (E1-3) TRANSMIT SIGNAL RECEIVE SIGNAL...
Page 368 777 TRAINING MANUAL RA SYSTEM -- MONITOR/TEST BITE Module System status information goes to the AIMS cabinets continuously. This is for fault monitoring of the RA The built-in test equipment (BITE) module monitors the system. circuits in the RA transceiver (xcvr) for faults. The flight fault memory stores the number of faults for The primary flight computers (PFCs) supply a test each flight leg.
Page 369 777 TRAINING MANUAL TEST INHIBIT ARINC TEST COMMAND RCVR ALTITUDE AIR/GROUND PROCESSOR ARINC RELAY (K32118) STATUS (P110) CONTROL XMTR LEFT AIMS CABINET (E3-1) TEST INHIBIT TEST Ñ TEST TO STATUS Ñ COMMAND LED(S) Ñ BITE MODULE MONITORING DATA STATUS FLIGHT FAULT CONNECTOR RIGHT AIMS CABINET...
Page 370 777 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 371 777 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 372 777 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 373 777 TRAINING MANUAL GLOBAL POSITIONING SYSTEM - INTRODUCTION 34-58-00 - 361 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 374 777 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 375 777 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 376 777 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 - 364 - ALTEON PROPRIETARY.
Page 377 777 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 - 365 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 378 777 TRAINING MANUAL GPS -- ANTENNA LOCATIONS General The GPS antennas are on the top of the fuselage. 34-58-00 - 366 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 379 777 TRAINING MANUAL RIGHT GPS ANTENNA LEFT GPS ANTENNA (STA 655.64) (STA 623.64) GPS - ANTENNA LOCATIONS 34-58-00 - 367 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 380 777 TRAINING MANUAL GPS -- INTERFACES Power and Antenna Interface GPS Data Output Bus Each multi-mode receiver (MMR) has a circuit breaker. The left and right MMRs send GPS data to the two AIMS The 115v ac standby and transfer buses supply power to cabinets.
Page 381 777 TRAINING MANUAL 12V DC IRS BUS RIGHT GPS POWER ANTENNA IRS BUS 115V AC STBY MAIN MMR R CMCS BUS RIGHT 115V AC L XFER CMCS BUS LEFT POWER MMR L TIME MARK P11 OVERHEAD CIRCUIT BREAKER PANEL TIME MARK 12V DC DATA...
Page 382 777 TRAINING MANUAL GPS -- GPS ANTENNA General The GPS antennas receive L-band frequency signals and send them to the multi-mode receivers (MMRs). The GPS antenna impedance is 50 ohms. 34-58-00 - 370 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 383: Top View
777 TRAINING MANUAL HOLE FOR MOUNTING SCREW (4) TOP VIEW CONNECTOR BOTTOM VIEW GPS - GPS ANTENNA 34-58-00 - 371 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 384 777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 1 THIS PAGE INTENTIONALLY LEFT BLANK 34-58-00 - 372 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 385: Training Manual
777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 1 GPS Segments Calculate and format a satellite navigation message. This message has up-to-date descriptions The GPS has three segments: of the satellites future positions, and a collection of the latest data on all GPS Satellite satellites User...
Page 386 777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 1 Record the accuracy of the satellite clocks Military users have access to precision positioning Collect and relay to the control station service (PPS). PPS has an accuracy of 18 meters or less meteorologic data such as barometric pressure, in 95% of the fixes.
Page 387 777 TRAINING MANUAL SATELLITE SEGMENT USER SEGMENT CONTROL SEGMENT GPS - THEORY OF OPERATION - 1 34-58-00 - 375 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 388 777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 2 Ranging must calculate. The clock bias is the difference between the MMR time and GPS time. The multi-mode receivers (MMRs) use the principle of ranging to measure the distance between the MMR on the To calculate the airplane position (latitude, airplane and the satellites.
Page 389 777 TRAINING MANUAL RANGE 1 GPS TIME RANGE 2 GPS TIME RANGE 4 RANGE 3 RANGING TIME BIAS TIME BIAS GPS - THEORY OF OPERATION - 2 34-58-00 - 377 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 390 777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 3 THIS PAGE INTENTIONALLY LEFT BLANK 34-58-00 - 378 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 391 777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 3 GPS Modes of Operation The MMR takes approximately 75 seconds to acquire the satellite signals when the AIMS data is available. The The multi-mode receiver (MMR) operates in these modes: MMR takes approximately 4 minutes (maximum of 10 minutes) to acquire the satellites when the AIMS data Acquisition mode...
Page 392 777 TRAINING MANUAL GPS -- THEORY OF OPERATION - 3 There are only 3 satellites available with good Autonomous Integrity Limit geometry for position fixes The MMR stored the difference between inertial and The MMR has a receiver autonomous integrity monitor GPS altitude in memory.
Page 393 777 TRAINING MANUAL POWER-UP AIDED MODE ACQUISITION MODE RANGE 2 SATS AVAIL? RANGE 1 RANGE 3 SATS AVAIL? AIRPLANE ALTITUDE PASSED? NAVIGATION RANGE 4 MODE ALTITUDE AIDED EARTH MODE RADIUS COVERAGE? COVERAGE? THERE ONLY 3 SATS? ALTITUDE AIDED MODE SATS AVAIL? MMR MODES GPS - THEORY OF OPERATION - 3...
Page 394 777 TRAINING MANUAL GPS -- FUNCTIONAL DESCRIPTION Power (BITE) circuits do tests and give fault reports to the AIMS cabinets. The power supply makes different dc voltages from the 28v dc input to the multi-mode receiver (MMR). The MMR Outputs gives 12v dc through the antenna coax to the amplifier in the GPS antenna.
Page 395 777 TRAINING MANUAL POWER GPS DATA 28V DC - DC SUPPLY LEFT EU 12V DC NOISE RCVR CONV GPS DATA LEFT GPS ANTENNA (STA 623.64, LOCAL GPWC OSCILLATOR WL 343.14, BL 0) ARINC GPS DATA XMTRS TIME MARK LEFT AIMS CABINET IRS BUS ANALOG OUTPUT...
Page 396 777 TRAINING MANUAL GPS -- DISPLAYS - 1 General The flight management computing function (FMCF) of the AIMS shows position initialization and position reference pages on the control display unit (CDU). The multi-mode receivers (MMRs) send GPS data to the AIMS cabinets.
Page 397: Position Initialization Page
777 TRAINING MANUAL P O S I N I T L A S T P O S N 4 0 3 8 . 0 W 0 7 3 4 6 . 4 R E F A I R P O R T - - - - G A T E UNIVERSAL TIME...
Page 398 777 TRAINING MANUAL GPS -- DISPLAYS - 2 General Position reference page two shows the active flight management computing function (FMCF) airplane position. The FMCF can use GPS position data to calculate the airplane position. The FMCF also uses these other navigation aids to calculate the airplane position: Air data inertial reference unit (ADIRU) Distance measuring equipment (DME)
Page 399 777 TRAINING MANUAL ACTIVE FMCF POSITION G P S ) G P S ) D A T E D A T E A R M E D A R M E D W 0 7 3 4 6 . 4 W 0 7 3 4 6 .
Page 400 777 TRAINING MANUAL GPS -- DISPLAYS - 3 General Position reference page three shows this information: GPS position Bearing and distance to the FMCF airplane position from the GPS position. GPS Data Elimination You can remove GPS data from the FMCF position calculation: Select line select key (LSK) 5R when ON shows in larger letters to remove GPS data from the FMCF...
Page 401 777 TRAINING MANUAL BEARING AND DISTANCE FROM GPS DATA POSITION GPS POSITION TO FMC POSITION REMOVAL W 0 7 3 4 6 . 4 W 0 7 3 4 6 . 4 W 0 7 3 4 6 . 4 W 0 7 3 4 6 .
Page 402 777 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 403 777 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 404 777 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 405 777 TRAINING MANUAL VOR STATION VOR STATION VHF OMNIDIRECTIONAL RANGING (VOR) SYSTEM 34-51-00 - 393 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 406 777 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 407 777 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 408 777 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 409 777 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 410 777 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 411 777 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 412 777 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 413 777 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 414 777 TRAINING MANUAL VOR -- SYSTEM INTERFACE General right AIMS cabinet. Output bus one and two from each receiver sends VOR data, test results, and fault These are the components that interface with the VOR information to the left and right AIMS cabinets. receivers: Left and right control display units (CDUs) Left and right airplane information management...
Page 415 777 TRAINING MANUAL OUTPUT 1 L CMCS BUS ALTN TUNE R CMCS BUS L CDU OUTPUT 2 L AIMS CABINET L VOR/MB RECEIVER OUTPUT 1 L TUNE BUS ALTN TUNE R TUNE BUS R CDU OUTPUT 2 R AIMS CABINET R VOR/MB RECEIVER VOR - SYSTEM INTERFACE 34-51-00...
Page 416 777 TRAINING MANUAL VOR -- VOR/MB RECEIVER General Training Information Point The VOR/marker beacon (VOR/MB) receiver has two The maintenance manual and the fault isolation manual receivers: do not have a task for the line maintenance technician to do a test from the front panel of the VOR/MB VOR receiver receiver.
Page 417: Test Switch
777 TRAINING MANUAL COLLINS RED OR GREEN LRU STATUS STATUS LEDS CONTROL FAIL TEST SWITCH TEST VOR-900 VOR - VOR/MB RECEIVER 34-51-00 - 405 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 418 777 TRAINING MANUAL VOR -- ANTENNA General The VOR antenna is on the top of the vertical stabilizer. The VOR antenna receives RF signals in the frequency range of 108 MHz to 117.95 MHz. The antenna receives VOR and ILS frequencies. The VOR antenna sends VOR signals to both VOR/MB receivers.
Page 419 777 TRAINING MANUAL ANTENNA VOR - ANTENNA 34-51-00 - 407 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 420 777 TRAINING MANUAL VOR -- VOR/MB RECEIVER FUNCTIONAL DESCRIPTION General VOR Antenna Input The receiver has both VOR and marker beacon functions. Input signals from the VOR antenna go through the power This section only covers the VOR functions. divider then to the receiver circuits in the VOR/MB receiver.
Page 421: Receiver Circuits
777 TRAINING MANUAL POWER 28V DC 115V AC SUPPLY R34003 FAULT MEMORY LEFT CDU FREQUENCY SOURCE SELECT DISCRETE ARINC LEFT CDU ALTN TUNE RCVR TO STATUS LEDS ARINC RIGHT AIMS CABINET RCVR PROCESSOR ARINC LEFT AIMS TEST CABINET RCVR FAULT DATA GROUND AUDIO...
Page 422 777 TRAINING MANUAL VOR -- TUNE INPUTS General Alternate Tune These are the three ways to tune the VOR receivers: The CDUs monitor the AIMS cabinets tune functions. If the AIMS tune function fails, the CDUs send a frequency Manually by the left, center, or right CDU source select discrete to the VOR receivers.
Page 423 777 TRAINING MANUAL 28V DC R34003 RESISTOR ASSY - L (E1-2) FREQ SOURCE SEL DISC ALTN TUNE TUNE MANUAL L VOR RECEIVER TUNE MANUAL OR L CDU FMCF AUTO TUNE L AIMS CABINET MANUAL TUNE C CDU MANUAL TUNE MANUAL OR FMCF AUTO TUNE SYSTEMS...
Page 424 777 TRAINING MANUAL VOR -- AUDIO CONTROLS General Operation The audio control panels supply control inputs to the To hear VOR audio, do this: audio management unit. This lets the crew hear audio on the speakers and headsets in the flight deck. Set the VOR/ADF receiver selector to the left (L) or right (R) VOR position Description...
Page 425 777 TRAINING MANUAL VOR/ADF RECEIVER VOR/ADF RECEIVER NAV FILTER SELECTOR VOLUME CONTROL SELECTOR AUDIO CONTROL PANEL VOR - AUDIO CONTROLS 34-51-00 - 413 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 426 777 TRAINING MANUAL VOR -- CDU TUNING General Alternate Tune The CDUs supply manual tune inputs during normal The ALTN NAV RADIO page is available only when there is operation and alternate tune inputs if there is a a failure of the tune inputs from the AIMS cabinets. failure of the AIMS tune functions.
Page 427: Manual Tune
777 TRAINING MANUAL 1 1 6 8 0 S E A E L N 1 1 7 9 0 1 3 9 INIT ALTN VNAV MANUAL TUNE LEGS HOLD PROG EXEC COMM MENU PREV NEXT A L T N N A V R A D I O PAGE PAGE V O R...
Page 428 777 TRAINING MANUAL VOR -- EFIS CONTROLS General The left CDU is the alternate or backup control for the left EFIS control panel and the right CDU is the The EFIS control panel has controls to select the alternate or backup for the right EFIS control panel. display mode of the ND.
Page 429 777 TRAINING MANUAL MINS BARO RADIO BARO MTRS NAVIGATION DISPLAY MODE SELECTOR RIGHT VOR/ADF LEFT VOR/ADF VOR L VOR R SWITCH SWITCH ADF L ADF R ARPT DATA TERR EFIS CONTROL PANEL O P T I O N S < >...
Page 430 777 TRAINING MANUAL VOR -- ND VOR DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 34-51-00 - 418 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 431: 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 432 777 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 433 777 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 434 777 TRAINING MANUAL VOR -- ND VOR AUTOTUNE DISPLAY General In autotune, the flight management computing function (FMCF) of AIMS supplies the VOR frequencies to the VOR/MB receivers. Autotune Displays When the FMCF of AIMS autotunes the receivers, these displays change: Replace VOR selected course numbers with dashes Remove selected course arrow Remove deviation bar and scale...
Page 435 777 TRAINING MANUAL REPLACE VOR SELECTED COURSE WITH DASHES VOR R VOR R 28.5 28.5 REMOVE SELECTED COURSE ARROW REMOVE DEVIATION BAR AND SCALE REMOVE TO/FROM POINTER AND INDICATION VOR L VOR R VOR L VOR R 10.5 28.5 10.5 28.5 ND - CENTERED VOR MODE ND - EXPANDED VOR MODE...
Page 436 777 TRAINING MANUAL VOR -- ND VOR MAP MODE DISPLAYS General VOR data shows in the ND map mode when the VOR/ADF switches on the EFIS control panels are in the VOR position. Description The ND map mode shows in the centered or expanded mode. The map mode shows the tuned VOR stations if they are inside the selected range.
Page 437 777 TRAINING MANUAL SHOPEN SHOPEN 300`/15 0012.0z 300`/15 0012.0z 0002 0002 BREND TUNED VOR STATION SELECTED SHOPEN COURSE RADIAL BREND SHOPEN RADIAL DATA IDENTIFIER VOR L VOR R VOR L VOR R 28.5 10.5 28.5 10.5 DATA ND - EXPANDED MAP MODE ND - CENTERED MAP MODE DATA VOR - ND VOR MAP MODE DISPLAYS...
Page 438 777 TRAINING MANUAL VOR -- ND VOR NCD DISPLAYS General Replace the selected course numbers with dashes Remove the selected course arrow The inputs that are necessary for VOR displays are: Remove the deviation bar and scale Remove the to/from pointer and indication. Bearing from the VOR/MB receivers Frequencies from the CDUs or the AIMS cabinets Selected course from the CDUs or the AIMS...
Page 439 777 TRAINING MANUAL REMOVE DEVIATION BAR VOR R 300`/15 28.5 REMOVE TO/FROM POINTER AND INDICATION REPLACE FREQUENCY OR IDENTIFIER WITH DASHES VOR R ------ 300`/15 28.5 VOR - BEARING NCD REMOVE DEVIATION BAR REMOVE TO/FROM POINTER AND INDICATION REPLACE SELECTED VOR R 300`/15 28.5...
Page 440 777 TRAINING MANUAL VOR -- ND VOR INVALID DISPLAYS General Selected Course Invalid The inputs that are necessary for VOR displays are: When the selected course input goes invalid, these changes occur for the VOR display: Bearing from the VOR/MB receivers Frequencies from the CDU or the AIMS cabinets Remove the VOR frequency or identifier Selected course from the CDUs or the AIMS...
Page 441 777 TRAINING MANUAL VOR R SHOW AMBER VOR FLAG 300`/15 28.5 REMOVE DEVIATION BAR AND SCALE REMOVE TO/FROM POINTER VORR AND INDICATION REMOVE FREQUENCY OR IDENTIFIER VOR R 300`/15 28.5 VOR - BEARING INVALID REMOVE DEVIATION BAR REMOVE TO/FROM POINTER AND INDICATION REMOVE FREQUENCY OR IDENTIFIER...
Page 442 777 TRAINING MANUAL VOR -- ND VOR TEST DISPLAYS General VOR Test Display When you do a test of the VOR/MB receiver, the receiver After the NCD condition, the receiver shows a valid starts a test sequence that lasts approximately 15 to test display for approximately ten seconds.
Page 443 777 TRAINING MANUAL VOR R 116.10 VOR R 116.10 VOR R 116.10 DME--- DME--- DME--- VORR FROM INVALID DATA FIRST 3 SECONDS: NCD DATA FOR 2 SECONDS: TEST DISPLAY FOR APPROX. 10 SECONDS: - REMOVE SELECTED COURSE ARROW - SELECTED COURSE POINTER AT - REMOVE DEVIATION BAR - REMOVE DEVIATION BAR AND SCALE 0 DEGREES (YOU MUST SELECT A...
Page 444 777 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 445 777 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 446 777 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 447 777 TRAINING MANUAL VERTICAL DEVIATION GLIDESLOPE RUNWAY LATERAL DEVIATION RUNWAY LOCALIZER ILS - INTRODUCTION 34-31-00 - 435 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 448 777 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 449 777 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 450 777 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 451 777 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 452 777 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 453 777 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 454 777 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 - 442 - ALTEON PROPRIETARY.
Page 455 777 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 - 443 - ALTEON PROPRIETARY.
Page 456 777 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 457 777 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 - 445 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 458 777 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 459 777 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 460 777 TRAINING MANUAL ILS -- ANALOG AND DISCRETE INTERFACE General The AFDCs send a discrete to inhibit ILS tune inputs in approach (APP) mode when the airplane is at or below The LRUs that interface with the multi-mode receivers 1500 feet, and there is a localizer or glideslope (MMRs) with analog and discrete signals are: signal capture.
Page 461 777 TRAINING MANUAL 28V DC TUNE INHIBIT R34003 RESISTOR L AFDC ASSY - L AUDIO OUTPUT FREQUENCY SOURCE SELECT DISCRETE AIR/ L CDU K32118 LEFT MMR AIR/GND RELAY TUNE INHIBIT C AFDC AUDIO OUTPUT AIR/ 28V DC K32318 CENTER MMR R34004 AIR/GND RESISTOR...
Page 462 777 TRAINING MANUAL ILS -- ARINC 429 INTERFACE General Receiver Outputs These are the LRUs that have an interface with the Each receiver has two output buses. Output bus one multi-mode receivers (MMRs) on ARINC 429 data buses: supplies data to the onside AFDC. Output bus two supplies data to the two AIMS cabinets.
Page 463 777 TRAINING MANUAL OUTPUT 1 ALTN TUNE OUTPUT 2 L CDU L AFDC CMC BUS L L MMR CMC BUS C L AIMS CABINET CMC BUS R OUTPUT 2 L AIMS CABINET ISFD GPWC TUNE BUS L OUTPUT 1 TUNE BUS C C AFDC C MMR TUNE BUS R...
Page 464 777 TRAINING MANUAL ILS -- LOCALIZER ANTENNA INPUTS General The multi-mode receivers (MMRs) get localizer signal inputs from the localizer antennas in the nose radome or from the VOR antenna on the vertical stabilizer. Antenna Inputs Signal inputs from the VOR antenna on the vertical stabilizer go through the RF power dividers to the localizer antenna switches.
Page 465 777 TRAINING MANUAL LEFT MMR ANT SWITCH LEFT LOC CONTROL ANTENNA SW POS LEFT LOC ANTENNA L AFDC SWITCH CENTER MMR RIGHT AND CENTER ANT SWITCH LOC ANTENNAS CONTROL SW POS CENTER LOC ANTENNA C AFDC SWITCH TO L VOR RECEIVER L RF POWER DIVIDER...
Page 466 777 TRAINING MANUAL ILS -- GLIDESLOPE ANTENNA INPUTS General The multi-mode receivers (MMRs) get inputs from the glideslope capture antennas in the nose radome, or from the glideslope track antennas on the aft nose gear doors. The antenna inputs go through the glideslope antenna switch, then to the MMRs.
Page 467 777 TRAINING MANUAL LEFT MMR ANT SW CTRL LEFT G/S SW POS CAPTURE ANT LEFT G/S ANTENNA SW LEFT ADFC LEFT, CENTER G/S TRACK ANT CENTER MMR ANT SW CTRL SW POS CENTER G/S CENTER ADFC ANTENNA SW RIGHT, CENTER G/S CAPTURE RIGHT MMR ANT SW CTRL...
Page 468 777 TRAINING MANUAL ILS -- RECEIVER Purpose Training Information Point The multi-mode receiver (MMR) supplies localizer and The maintenance manual and the fault isolation manual glideslope deviation to the autopilot flight director do not have a task for the line maintenance technician computers (AFDCs) and to the AIMS cabinets for display.
Page 469: Status Leds
777 TRAINING MANUAL COLLINS LRU STATUS STATUS LEDS CONTROL FAIL ANT FAIL TEST SWITCH TEST GLU-920 ILS - RECEIVER 34-31-00 - 457 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 470 777 TRAINING MANUAL ILS -- LOCALIZER AND GLIDESLOPE ANTENNAS Localizer Antennas There are two localizer antennas. Each antenna has two elements. The localizer antennas receive frequencies from 108.1 MHz to 111.95 MHz at odd tenths intervals. The antennas supply signal reception within 90 degrees to the left or right of the airplane centerline.
Page 471 777 TRAINING MANUAL LEFT LOCALIZER ANTENNA RIGHT AND CENTER LOCALIZER ANTENNAS LEFT GLIDESLOPE CAPTURE ANTENNA RIGHT AND CENTER GLIDESLOPE CAPTURE ANTENNAS ILS - LOCALIZER AND GLIDESLOPE ANTENNAS 34-31-00 - 459 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 472 777 TRAINING MANUAL ILS -- GLIDESLOPE TRACK ANTENNA General The glideslope track antennas supply final approach and landing glideslope signals. The track antennas are in a position to minimize the vertical distance between the antenna flight path and the main landing gear. Description The antennas receive in the frequency range of 328.6 MHz to 335.4 MHz.
Page 473 777 TRAINING MANUAL LEFT AND CENTER GLIDESLOPE TRACK ANTENNA LEFT AFT NOSE GEAR DOOR ILS - GLIDESLOPE TRACK ANTENNA 34-31-00 - 461 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 474 777 TRAINING MANUAL ILS -- FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 34-31-00 - 462 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 475: Training Manual
777 TRAINING MANUAL ILS -- FUNCTIONAL DESCRIPTION General ILS Outputs The multi-mode receiver (MMR) gets tune inputs to tune The multi-mode receivers send the deviation on two the localizer and glideslope receivers. These receivers ARINC 429 outputs. These bus outputs go to an output in the MMR give localizer and glideslope deviations to monitor that compares the output data to the transmit other systems.
Page 476 777 TRAINING MANUAL ILS -- FUNCTIONAL DESCRIPTION A flight director is on G/S and LOC are active The airplane is below 500 feet of radio altitude. The source destination identifier (SDI) program pins identify the receiver position as the left, right, or center.
Page 477 777 TRAINING MANUAL 28V DC ARINC 429 XMTR R34003 DEV OUTPUT 1 OUTPUT FREQ DEV OUTPUT 2 SOURCE SEL DISCRETE ARINC OUTPUT ALTN TUNE PROCESSOR MONITOR RCVR L ILS TUNE INHIBIT DISC L CDU STATUS ARINC L AFDC TUNE STATUS TUNE RCVR FREQ...
Page 478 777 TRAINING MANUAL ILS -- LOCALIZER ANTENNA SWITCHING Operation The localizer antenna switch change the inputs between the VOR antenna and the localizer antennas in the nose radome. The antenna switches get 28v dc from their respective circuit breakers. The autopilot flight director computers (AFDCs) send a localizer antenna request discrete to control the position of the antenna switches.
Page 479 777 TRAINING MANUAL 28V DC LOC ANT REQUEST LOC ANT L MMR ACKNOWLEDGE USED L LOC ANT L LOC ANT SW L AFDC L VOR RCVR 28V DC L PWR R VOR RCVR DIVIDER LOC ANT VOR ANT R PWR REQUEST LOC ANT C MMR...
Page 480 777 TRAINING MANUAL ILS -- GLIDESLOPE ANTENNA SWITCHING General The glideslope (G/S) antenna switches change the receiver glideslope antenna inputs between the G/S antenna in the nose radome and the G/S track antenna on the aft nose gear doors. The antenna switches get 28v dc from their respective circuit breakers.
Page 481 777 TRAINING MANUAL 28V DC RF INPUT G/S ANT REQUEST G/S ANT L MMR ACKNOWLEDGE L G/S CAPTURE ANTENNA L G/S ANT SW L AFDC 28V DC RF INPUT G/S ANT REQUEST G/S ANT C MMR L, C G/S ACKNOWLEDGE TRACK ANT C G/S ANT SW C AFDC...
Page 482 777 TRAINING MANUAL ILS -- TUNING General CDU changes the tuning input from AIMS to the CDU. You use the right CDU to tune the right receiver. You use There are three ways to tune the multi-mode receivers the left CDU to tune the left and center receivers. (MMRs): There is no alternate tune function from the center CDU.
Page 483 777 TRAINING MANUAL 28V DC FREQ SOURCE R34003 RESISTOR ASSY - L SEL DISC ALTN TUNE TUNE MANUAL TUNE MANUAL OR LEFT MMR L CDU FMCF AUTO TUNE MANUAL L AIMS CABINET TUNE TUNE C CDU CENTER MMR TUNE L MANUAL TUNE TUNE C...
Page 484 777 TRAINING MANUAL ILS -- AUDIO CONTROL PANEL ILS AUDIO CONTROLS General Operation The audio control panels (ACPs) supply control inputs To hear ILS audio, do this: to the audio management unit. This lets the crew hear audio signals on the speakers and headsets in the Set the approach receiver selector to the left flight deck.
Page 485 777 TRAINING MANUAL AUDIO CONTROL PANEL NAV FILTER APPROACH RECEIVER VOLUME APPROACH SELECTOR CONTROL (ON/OFF AND RECEIVER VOLUME CONTROL) SELECTOR ILS - AUDIO CONTROL PANEL ILS AUDIO CONTROLS 34-31-00 - 473 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 486 777 TRAINING MANUAL ILS -- CDU ILS TUNING General When the FMCF tunes the frequency, only the frequency shows. The PARK display goes out of view when less than The CDUs supply manual tune inputs during normal 50 nm from top of descent, more than 150 nm from the operation and alternate tune inputs if there is a runway threshold, or the FMC is in the descent mode.
Page 487: Manual Tune
777 TRAINING MANUAL 1 1 6 8 0 S E A E L N 1 1 7 9 0 1 3 9 < P R K INIT ALTN VNAV MANUAL TUNE LEGS HOLD PROG EXEC COMM MENU PREV NEXT PAGE PAGE A L T N N A V R A D I O V O R...
Page 488 777 TRAINING MANUAL ILS -- EFIS ILS CONTROLS General To show ILS data on the ND, turn the mode selector to the APP position. The switch has a CTR push on, push off switch in the center. This switch changes the display format from the expanded format to the centered format.
Page 489 777 TRAINING MANUAL MINS BARO RADIO BARO MTRS VOR L VOR R ADF L ADF R ND MODE SELECTOR EFIS CONTROL PANEL ILS - EFIS ILS CONTROLS 34-31-00 - 477 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 490 777 TRAINING MANUAL ILS -- PFD DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 34-31-00 - 478 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 491: Training Manual
777 TRAINING MANUAL ILS -- PFD DISPLAYS ILS Indications ILS Course These are the ILS indications on the PFD: The ILS course shows to the right of the localizer frequency or identifier in white. It is a three digit Localizer frequency or identifier display with a range of 1 to 360 degrees.
Page 492 777 TRAINING MANUAL ILS -- PFD DISPLAYS ILS Deviation Warning These are the two types of ILS deviation warnings: Localizer deviation warnings Glideslope deviation warnings. Localizer deviation warnings occur between 0 and 500 feet RA with localizer captured. Glideslope deviation warnings occur between 100 feet and 500 feet RA with glideslope captured.
Page 493 777 TRAINING MANUAL ILS FREQUENCY AND COURSE 110.90/123 25.3 GLIDESLOPE DEVIATION POINTER AND SCALE 1000 LOCALIZER DEVIATION POINTER AND SCALE 29.86 ILS - PFD DISPLAYS 34-31-00 - 481 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 494 777 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 495 777 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 496 777 TRAINING MANUAL ILS -- ND ILS DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 34-31-00 - 484 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 497 777 TRAINING MANUAL ILS -- ND ILS DISPLAYS General Reference Receiver for ILS Deviation Select approach (APP) on the EFIS control panel to show The reference receiver for ILS deviation shows to the ILS displays on the navigation display (ND). The data left of the frequency display.
Page 498 777 TRAINING MANUAL ILS -- ND ILS DISPLAYS The glideslope deviation scale and pointer show at the right side of the ND. The fixed scale is the standard four dot scale where each dot equals 0.35 degrees of deviation. The pointer gives fly to commands to intercept the glideslope beam.
Page 499 777 TRAINING MANUAL REFERENCE ILS REFERENCE ILS REFERENCE FREQUENCY OR REFERENCE FREQUENCY OR REFERENCE REFERENCE RECEIVER IDENTIFIER IDENTIFIER ILS COURSE RECEIVER ILS COURSE ILS L 110.10 ILS L 110.00 CRS055 CRS055 DME13.5 DME13.5 EXPANDED MODE CENTERED MODE LOCALIZER LOCALIZER GLIDESLOPE GLIDESLOPE DEVIATION POINTER AND...
Page 500 777 TRAINING MANUAL ILS -- ND ILS NCD INDICATIONS ILS Course When the ILS course input is NCD, dashes replace the three digit course. These are the displays that go out of view: Course pointer Localizer deviation indication Localizer deviation scale Glideslope deviation pointer Glideslope deviation scale.
Page 501 777 TRAINING MANUAL REPLACE FREQUENCY REPLACE ILS ---- ILS R ILS R 110.00 WITH DASHES COURSE WITH 13.5 DASHES REMOVE ILS COURSE AND DME REMOVE COURSE REMOVE DEVIAITON POINTER POINTERS AND COURSE POINTER POSITION LOCALIZER REMOVE SCALE HORIZONTAL DEVIATION SCALES AND POINTERS ILS COURSE NCD FREQUENCY NCD...
Page 502 777 TRAINING MANUAL ILS -- ND ILS INVALID DISPLAY Localizer Frequency When the localizer frequency goes invalid, the frequency/identifier line goes out of view. The localizer and glideslope pointers and scales go out of view. ILS Course When the ILS course input goes invalid, these are the displays that go out of view: CRS display and ILS course Localizer deviation indication and scale...
Page 503 777 TRAINING MANUAL ILS R LOCALIZER FLAG GLIDESLOPE FLAG ILS - ND ILS INVALID DISPLAY 34-31-00 - 491 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 504 777 TRAINING MANUAL ILS -- PFD AND ND ILS TEST DISPLAYS General Use the maintenance access terminal (MAT) to do a test of the multi-mode receivers (MMRs). The MAT sends the test command to the left AIMS cabinet. The central maintenance computer function of the left AIMS cabinet sends the command to the MMR.
Page 505 777 TRAINING MANUAL FIRST 3 SECONDS OF TEST DISPLAY ILS R 110.00 13.5 110.90/123 25.3 LOCALIZER = ONE DOT LEFT GLIDESLOPE = ONE DOT 1000 29.86 NEXT 3 SECONDS OF TEST DISPLAY ILS R 110.00 13.5 110.90/123 25.3 LOCALIZER = ONE DOT RIGHT GLIDESLOPE = ONE DOT DOWN...
Page 506 777 TRAINING MANUAL ILS -- ISFD APPROACH AND ILS TEST DISPLAYS ILS -- ISFD APPROACH AND ILS TEST DISPLAYS THIS PAGE INTENTIONALLY LEFT BLANK 34-31-00 - 494 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 507 777 TRAINING MANUAL ILS -- ISFD APPROACH AND ILS TEST DISPLAYS General Invalid data causes the deviation scales and pointers to go out of view. There are no special ILS tests for the integrated standby flight display (ISFD). You do a check of the The LOC and G/S flags do not show for this test.
Page 508 777 TRAINING MANUAL ILS -- ISFD APPROACH AND ILS TEST DISPLAYS The approach display goes back to normal indications at the end of the self-test sequence. 34-31-00 - 496 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 509 777 TRAINING MANUAL MODE HP/IN HP/IN HP/IN GLIDE- SLOPE BCRS 29.92 29.92 29.92 POINTER -200 -200 -200 BARO DEVIATION BARO BARO SCALES APPROACH MODE LOCALIZER BACK COURSE MODE FAILURE FLAGS POINTER INVALID DATA DISPLAY NO COMPUTED DATA DISPLAY UP/LEFT DISPLAY DOWN/RIGHT DISPLAY 0-3 SECONDS 3-5 SECONDS...
Page 510 777 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 511 777 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 512 777 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 513 777 TRAINING MANUAL INTERROGATION REPLY DME GROUND STATION DISTANCE MEASUREMENT EQUIPMENT SYSTEM - INTRODUCTION 34-55-00 - 501 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 514 777 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 515 777 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 - 503 -...
Page 516 777 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 517 777 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 518 777 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 519 777 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 520 777 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 521 777 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 522 777 TRAINING MANUAL DME SYSTEM -- ARINC 429 INTERFACES The left and right CDUs supply alternate tune inputs directly to the DME interrogators if the AIMS tune inputs fail. The left CDU alternate tunes the left interrogator and the right CDU alternate tunes the right interrogator.
Page 523 777 TRAINING MANUAL OUTPUT BUS 1 CMC BUS LEFT ALT TUNE CMC BUS RIGHT OUTPUT BUS 2 L CDU L DME INTERROGATOR L AIMS CABINET OUTPUT BUS 2 OUTPUT BUS 1 ALT TUNE NAVAID TUNE L R CDU NAVAID TUNE R R DME INTERROGATOR R AIMS CABINET DME SYSTEM - ARINC 429 INTERFACES...
Page 524 777 TRAINING MANUAL DME SYSTEM -- INTERROGATOR General Front Panel The DME interrogator scans 252 channels and calculates The front panel of the DME interrogator has these distance information for all channels in the DME range. features: There are 200 DME channels paired with the VHF NAV frequencies.
Page 525 777 TRAINING MANUAL Collins LED STATUS LRU STATUS INDICATORS CONTROL FAIL TEST SWITCH TEST DME-900 DME SYSTEM - INTERROGATOR 34-55-00 - 513 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 526 777 TRAINING MANUAL DME SYSTEM -- ANTENNA General The DME l- band antenna transmits the interrogator output signal and receives the ground station reply signals. Physical Description The antenna has an O-ring moisture seal and attaches to the airplane by four screws. The DME and ATC antennas are the same and are interchangeable.
Page 527 777 TRAINING MANUAL COAX CABLE COAX CONNECTOR O-RING DME SYSTEM - ANTENNA 34-55-00 - 515 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 528 777 TRAINING MANUAL DME SYSTEM -- TUNING General right AIMS cabinet to the input from the left or right CDU. These are the three ways to tune the DME interrogators: In the alternate tune mode, the left CDU alternate Manually by the left, right, or center CDU tunes the left DME interrogator and the right CDU Automatically by the FMCF in the AIMS cabinets alternate tunes the right DME interrogator.
Page 529 777 TRAINING MANUAL 28V DC R34003 RESISTOR ASSY - L FREQ SOURCE SEL DISC ALTN TUNE TUNE MANUAL L DME INTERROGATOR TUNE MANUAL OR L CDU FMCF AUTO TUNE L AIMS CABINET MANUAL TUNE C CDU MANUAL TUNE MANUAL OR FMCF AUTO TUNE SYSTEMS...
Page 530 777 TRAINING MANUAL DME SYSTEM -- AUDIO CONTROL PANEL THIS PAGE INTENTIONALLY LEFT BLANK 34-55-00 - 518 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 531: Training Manual
777 TRAINING MANUAL DME SYSTEM -- AUDIO CONTROL PANEL General first officer selects the VOR, MAP, or PLAN mode, the AMU pairs the right DME interrogator audio with the The audio control panels supply control inputs to the right VOR receiver audio. audio management unit.
Page 532 777 TRAINING MANUAL DME SYSTEM -- AUDIO CONTROL PANEL Range (R) audio. Push the VOR/ADF receiver volume control to make the VOR audio come on (turn the control to adjust Approach Receiver Volume Control the volume) Set the NAV filter selector to the both (B) or The approach volume control makes the audio come on and range (R) position.
Page 533 777 TRAINING MANUAL MINS RADIO BARO VOR L ND MODE SELECTOR ADF L VOR/ADF RECEIVER NAV FILTER EFIS CONTROL PANEL VOLUME CONTROL SELECTOR VOR/ADF RECEIVER SELECTOR AUDIO CONTROL PANEL APPROACH RECEIVER APPROACH RECEIVER VOLUME CONTROL SELECTOR DME SYSTEM - AUDIO CONTROL PANEL 34-55-00 - 521 - ALTEON PROPRIETARY.
Page 534 777 TRAINING MANUAL DME SYSTEM -- MANUAL AND ALTERNATE TUNING General scratchpad. Next, line select the delete function to the applicable VOR data line. The CDUs supply manual tune inputs during normal operation and alternate tune inputs when the AIMS tune Alternate Tuning inputs fail.
Page 535 777 TRAINING MANUAL 1 1 6 8 0 S E A E L N 1 1 7 9 0 < INIT ALTN VNAV HOLD LEGS PROG EXEC COMM MENU A L T N N A V R A D I O PREV NEXT V O R...
Page 536 777 TRAINING MANUAL DME SYSTEM -- EFIS CONTROLS General The EFIS control panel has controls to select DME data to show on the navigation displays (NDs). Navigation Display Mode Selector You use the navigation display mode selector to select the display mode on the NDs. DME data shows in all modes except plan (PLN) mode.
Page 537 777 TRAINING MANUAL MINS BARO RADIO BARO MTRS NAVIGATION DISPLAY MODE SELECTOR VOR L VOR R ADF L ADF R EFIS CONTROL PANEL < > > < > MODE > SELECT < > < > < > EFIS CONTROL PAGE DME SYSTEM - EFIS CONTROLS 34-55-00 - 525 -...
Page 538 777 TRAINING MANUAL DME SYSTEM -- PRIMARY FLIGHT DISPLAY Normal Display The primary flight display (PFD) format shows the ILS/DME distance when you tune the onside DME to a paired ILS frequency and when the onside DME distance is valid. The left PFD shows left DME data.
Page 539 777 TRAINING MANUAL HOLD HOLD HOLD 110.90/123 110.90/123 110.90/123 DME ---- 25.3 DME FAIL NO COMPUTED FLAG DISTANCE DME DATA (AMBER) NORMAL DME NCD DME FAIL DISPLAY DISPLAY DISPLAY DME SYSTEM - PRIMARY FLIGHT DISPLAY 34-55-00 - 527 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 540 777 TRAINING MANUAL DME SYSTEM -- ND APPROACH MODE DISPLAY DME Normal Displays The ILS/DME data shows on the ND in the centered and expanded approach (APP) modes. DME distance shows in the upper right corner of the ILS display when the onside DME is tuned to a paired ILS frequency, and the onside DME distance is valid.
Page 541 777 TRAINING MANUAL ILS L IBFI ILS L IBFI ILS L IBFI 13.5 ---- DME L DISTANCE NO COMPUTED DME FAIL DME DATA FLAG (AMBER) NORMAL DISPLAY DME NCD DISPLAY DME FAIL DISPLAY DME SYSTEM - ND APPROACH MODE DISPLAY 34-55-00 - 529 - ALTEON PROPRIETARY.
Page 542 777 TRAINING MANUAL DME SYSTEM -- MAP MODE DISPLAY General The DME distance shows in all ND modes except PLAN. With the EFIS control panel mode selector set to the MAP mode and the VOR/ADF switches in the VOR position, the ND shows slant range distance of the paired DME stations.
Page 543 777 TRAINING MANUAL VOR ID NCD LOWER RIGHT CORNER LOWER LEFT CORNER DME STATION ID NAV DISPLAY NAV DISPLAY SHOWS IN SMALL DME FAIL FONT VOR R VOR L VOR R VOR L DME R 28.5 NORMAL DISPLAYS MAP MODE NON-NORMAL DISPLAYS VOR L VOR R...
Page 544 777 TRAINING MANUAL DME SYSTEM -- VOR MODE DISPLAY DME Normal Displays The VOR/DME data shows on the ND in center or expanded VOR modes. DME distance shows in the upper right corner of the VOR display when the onside DME is tuned to a paired VOR frequency, and the onside DME distance is valid.
Page 545 777 TRAINING MANUAL VOR R VOR R VOR R 13.5 ---- DME R REPLACE DME DISTANCE DISTANCE DME FAIL FLAG WITH DASHES VOR R VOR R VOR R DME R 13.5 ---- DME NORMAL DME NCD DME FAIL VOR L VOR R ADF L ADF R...
Page 546 777 TRAINING MANUAL DME SYSTEM -- TEST DISPLAYS General During a ground test or a self test, the onside PFD and ND show: The DME fail condition for two seconds The DME NCD condition for the next two seconds The DME normal condition to end the test. The DME normal condition is the distance that shows before the test starts.
Page 547 777 TRAINING MANUAL VOR R VOR R VOR R 13.5 ---- DME R REPLACE DISTANCE DME FAIL DISTANCE WITH DASHES FLAG VOR R VOR R VOR R 13.5 DME R ---- ND - VOR MODE ND - VOR MODE ND - VOR MODE DISPLAYS SHOW A DISPLAYS SHOW DISPLAYS SHOW A...
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Page 549: Training Manual
777 TRAINING MANUAL DME SYSTEM -- SIGNAL PROCESSING CDU and AIMS Inputs Operation The right AIMS cabinet is the normal source for tune The CPU uses tune inputs to tune the frequency inputs. It supplies both manual tune inputs from the synthesizer.
Page 550 777 TRAINING MANUAL DME SYSTEM -- SIGNAL PROCESSING transmitter sends the slant range data to the AIMS cabinets for the flight deck displays. The CPU sends the pulse pairs to the pulse pair decoder. The decoder sends the DME audio to the AMU. Test The CPU does a test of the interrogator when it receives a test command from the left AIMS cabinet or...
Page 551 777 TRAINING MANUAL PULSE PAIR DECODER FREQUENCY TRANSMITTER SYNTHESIZER ANTENNA (STA 707.5) L CDU RECEIVER CIRC FREQUENCY SOURCE SELECT DISCRETE R DME SUPPRESSION ARINC L ATC XPNDR LEFT CDU R ATC XPNDR ALTN TUNE RCVR TCAS COMPUTER ARINC OUTPUT 1 R AIMS ARINC RIGHT AIMS...
Page 552 777 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 553 777 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 554 777 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 555 777 TRAINING MANUAL AIRPLANE LONGITUDINAL AXIS BEARING TO THE STATION ADF STATION AUTOMATIC DIRECTION FINDER SYSTEM - INTRODUCTION 34-57-00 - 543 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 556 777 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 557 777 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 - 545 -...
Page 558 777 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 559 777 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 560 777 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 - 548 - ALTEON PROPRIETARY.
Page 561 777 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 - 549 - ALTEON PROPRIETARY.
Page 562 777 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 563 777 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 564 777 TRAINING MANUAL ADF SYSTEM -- DIGITAL INTERFACE General The components that interface with the ADF receivers on ARINC 429 data buses are the left and right CDUs and the left and right AIMS cabinets. CDU Interfaces The CDUs supply tune inputs directly to the ADF receivers on the NAV aid tune buses when the tune inputs from the AIMS cabinets fail.
Page 565 777 TRAINING MANUAL BEARING OUTPUT 1 BEARING OUTPUT 2 L NAV AID L CMCF BUS TUNE BUS R CMCF BUS L CDU L AIMS CABINET L ADF RECEIVER L NAV AID TUNE BUS R NAV AID R NAV AID TUNE BUS TUNE BUS BEARING OUTPUT 1 R CDU...
Page 566 777 TRAINING MANUAL ADF SYSTEM -- ADF RECEIVER Purpose The ADF receiver calculates bearing to a station that transmits in the frequency range of 190 KHz to 1750 KHz. The receiver also receives station identifiers and AM broadcasts. Description The ADF receiver operates on 115v ac power. The receiver has built-in test equipment (BITE) that monitors receiver operation and data inputs.
Page 567: Test Switch
777 TRAINING MANUAL COLLINS LED STATUS LRU STATUS INDICATORS CONTROL FAIL TEST SWITCH TEST ADF-900 ADF SYSTEM - ADF RECEIVER 34-57-00 - 555 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 568 777 TRAINING MANUAL ADF SYSTEM -- ADF ANTENNA Purpose The ADF antenna receives electromagnetic signals from ground stations. The loop antenna receives the magnetic part of the ground station signal, and the sense antenna receives the electrical part of the signal. Description The antenna assembly is a one piece molded shell.
Page 569 777 TRAINING MANUAL CONDUCTIVE MOUNTING SCREW WITH GASKET TAB/WASHER FOR RESISTANCE MEASUREMENT NAMEPLATE TOP VIEW SENSE ANTENNA LOOP ANTENNAS ELECTRONICS ASSEMBLY ELECTRICAL CONNECTOR ADF SYSTEM - ADF ANTENNA 34-57-00 - 557 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 570 777 TRAINING MANUAL ADF SYSTEM -- FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 34-57-00 - 558 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 571: Training Manual
777 TRAINING MANUAL ADF SYSTEM -- FUNCTIONAL DESCRIPTION Power audio processor. The audio goes through an audio amplifier then to the AMU. The ADF receiver power supply receives 115v ac and supplies all the voltages for the internal circuits. The audio processor sends the Morse code station identifier to the Morse decoder circuits.
Page 572 777 TRAINING MANUAL ADF SYSTEM -- FUNCTIONAL DESCRIPTION Built-in-Test Equipment The source destination indicator (SDI) discrete identifies the ADF receiver as the left or right The ADF receiver contains BITE that monitors ADF receiver. receiver operation and signal inputs. A fault memory keeps failures that occur by flight legs.
Page 573 777 TRAINING MANUAL POWER INTERNAL 115V AC SUPPLY CIRCUITS AUDIO RECEIVER PROCESSOR CIRCUITS MORSE 12V DC DECODER ANTENNA SENSE CONTROL OUTPUT 1 ARINC LEFT AND RIGHT LEFT ADF ANTENNA AIMS CABINETS (STA 1354.6) XMTR 28V DC OUTPUT 2 L CDU FREQUENCY R34003 SOURCE SELECT...
Page 574 777 TRAINING MANUAL ADF SYSTEM -- TUNING INPUTS General These are the two ways to tune the ADF receivers: Manually by the left, center, or right CDU By the CDUs as an alternate tune source. Manual Tuning You manually tune the ADF receivers from the left or right control display units (CDUs).
Page 575 777 TRAINING MANUAL 28V DC R34003 RESISTOR ASSY - L FREQ SOURCE SEL DISC ALTN TUNE TUNE MANUAL TUNE L ADF RECEIVER L CDU MANUAL TUNE MANUAL L AIMS CABINET TUNE C CDU MANUAL TUNE MANUAL TUNE SYSTEMS TUNE R AIMS CABINET ARINC 629 BUS ALTN TUNE FREQ SOURCE...
Page 576 777 TRAINING MANUAL ADF SYSTEM -- AUDIO CONTROLS General Operation The audio control panels supply control inputs to the Do this to hear ADF audio: audio management unit. This permits the crew to hear audio signals on the speakers and headsets in the Set the VOR/ADF selector to the left (L) or right flight deck.
Page 577: Audio Control Panel
777 TRAINING MANUAL VOR/ADF RECEIVER VOR/ADF RECEIVER NAV FILTER SELECTOR VOLUME CONTROL SELECTOR AUDIO CONTROL PANEL ADF SYSTEM - AUDIO CONTROLS 34-57-00 - 565 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 578 777 TRAINING MANUAL ADF SYSTEM -- CDU ADF TUNING General Antenna (ANT) Mode The CDUs supply manual tune inputs during normal In the antenna (ANT) mode the ADF receiver uses only operation and alternate tune inputs if there is a the sense antenna to receive station audio broadcasts.
Page 579 777 TRAINING MANUAL 1 1 6 8 0 S E A E L N 1 1 7 9 0 < MANUAL TUNE INIT ALTN VNAV NAVIGATION RADIO KEY LEGS HOLD PROG EXEC COMM MENU L T N N A V R A D I O PREV NEXT PAGE...
Page 580 777 TRAINING MANUAL ADF SYSTEM -- EFIS CONTROLS General The EFIS control panel has controls to select ADF data to show on the navigation displays (NDs). VOR/ADF Switch The VOR/ADF switches select the VOR or ADF receivers as the source of data for the left and right bearing pointers on the ND.
Page 581 777 TRAINING MANUAL MINS BARO RADIO BARO MTRS LEFT VOR/ADF RIGHT VOR/ADF SWITCH SWITCH VOR L VOR R ADF L ADF R EFIS CONTROL PANEL O P T I O N S < > > < > < > < >...
Page 582 777 TRAINING MANUAL ADF SYSTEM -- DISPLAYS General ADF pointers show in all EFIS modes but PLN (plan). The pointers are cyan in color. To display the ADF pointers, set the ND mode selector to APP, VOR, or MAP. Set the VOR/ADF switch on the EFIS control panel to the ADF position.
Page 583 777 TRAINING MANUAL LEFT ADF RIGHT ADF LEFT ADF RIGHT ADF POINTERS POINTERS POINTERS POINTERS (CYAN) (CYAN) (CYAN) (CYAN) VOR R ELN VOR R ELN CRS--- CRS--- DME28.5 DME28.5 VOR/ADF SELECTION (CYAN) ADF R ADF L ADF R ADF L VOR/ADF FREQUENCY OR IDENTIFIER...
Page 584 777 TRAINING MANUAL ADF SYSTEM -- ND NCD AND INVALID DISPLAYS General When the receiver output is no computed data (NCD), the ADF pointers go out of view. The source annunciation and frequency remain in view. When the receiver output is invalid, all ADF data goes out of view and the amber ADF flags show.
Page 585 777 TRAINING MANUAL VOR R ELN VOR R ELN 28.5 28.5 ADF R ADF L ADF R ADF L ADF FAIL FLAGS NCD: INVALID: REMOVE POINTERS AND SHOW SOURCE REMOVE POINTERS, SOURCE ANNUNCIATION, ANNUNCIATION AND FREQUENCY. AND FREQUENCY OR IDENTIFIER AND SHOW AMBER ADF FLAGS.
Page 586 777 TRAINING MANUAL ADF SYSTEM -- TEST DISPLAYS Test Use the maintenance access terminal (MAT) to do a test of the ADF receivers. To see the test displays, select APP, VOR, or MAP on the ND mode selector of the EFIS control panel.
Page 587 777 TRAINING MANUAL 3 TO 6 SECONDS: 1 TO 3 SECONDS: FROM 6 SECONDS TO END OF TEST: THE RECEIVER OUTPUT GOES THE RECEIVER OUTPUT GOES TO THE RECEIVER OUTPUT GOES VALID INVALID, ALL ADF DATA GOES NO COMPUTED DATA (NCD). THE AND THE POINTERS GO TO THE TEST OUT OF VIEW, AND THE AMBER FLAG GOES OUT OF VIEW, THE...
Page 588 777 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 589 777 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 590 777 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 591 777 TRAINING MANUAL AIRPORT RUNWAY INNER MIDDLE OUTER MARKER BEACONS MARKER BEACON SYSTEM - INTRODUCTION 34-32-00 - 579 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 592 777 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 593 777 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 - 581 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 594 777 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 - 582 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 595 777 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 - 583 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 596 777 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 597 777 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 598 777 TRAINING MANUAL MARKER BEACON SYSTEM -- VOR/MARKER BEACON RECEIVER General receiver. You must do all tests for the VOR/MB receiver from the MAT or a PMAT. The VOR/marker beacon (VOR/MB) receiver has two parts: Many LRUs on the 777 are compatible with other model VOR receiver airplanes that do not have a central maintenance Marker beacon receiver...
Page 599 777 TRAINING MANUAL COLLINS LRU STATUS STATUS LEDS CONTROL FAIL TEST SWITCH TEST VOR-900 MARKER BEACON SYSTEM - VOR/MARKER BEACON RECEIVER 34-32-00 - 587 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 600 777 TRAINING MANUAL MARKER BEACON SYSTEM -- MARKER BEACON ANTENNA General The marker beacon antenna receives signals from marker beacon ground stations. Six screws hold the antenna to the fuselage. 34-32-00 - 588 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 601 777 TRAINING MANUAL MARKER BEACON SYSTEM - MARKER BEACON ANTENNA 34-32-00 - 589 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 602 777 TRAINING MANUAL MARKER BEACON SYSTEM -- DISPLAYS AUDIO OUTPUTS General Audio Operation When the airplane passes over a marker beacon To listen to marker beacon audio signals: transmitter, marker beacon data shows on the primary flight display (PFD). Select marker beacon audio with the approach receiver selector If you want to listen to marker beacon audio, select Push the approach receiver volume control to make...
Page 603 777 TRAINING MANUAL CYAN AMBER LAND 3 LAND 3 WHITE MARKER BEACON DISPLAYS (PFD) APPROACH RECEIVER VOLUME CONTROL VOR R APPROACH RECEIVER SELECTOR AUDIO CONTROL PANEL 3000 HZ 400 HZ 1300 HZ 3000 HZ 3000 HZ (- - - -) (-.-.-.-.) (..) (..
Page 604 777 TRAINING MANUAL MARKER BEACON SYSTEM -- FUNCTIONAL DESCRIPTION THIS PAGE INTENTIONALLY LEFT BLANK 34-32-00 - 592 - ALTEON PROPRIETARY. Copyright. See title page for details...
Page 605 777 TRAINING MANUAL MARKER BEACON SYSTEM -- FUNCTIONAL DESCRIPTION Marker Beacon Signal Monitor and Test The marker beacon antenna receives the 75 MHz signal The test switch starts a test of the VOR/MB receiver. and sends it to a 75 MHz filter in the left VOR/marker The built-in test equipment (BITE) circuits do a test beacon (VOR/MB) receiver.
Page 606 777 TRAINING MANUAL MARKER BEACON SYSTEM -- FUNCTIONAL DESCRIPTION An internal nonvolatile fault memory (NVM) in the BITE circuits uses the air/ground discrete signal. The NVM uses this signal as an alternate method to define flight legs if the AIMS CMCF fails. 34-32-00 - 594 - ALTEON PROPRIETARY.
Page 607 777 TRAINING MANUAL TO LEFT I/O CARD AIMS POWER CABINET 115V AC DATA/ SUPPLY STATUS TO RIGHT AIMS CABINET BAND PASS FILTER FILTER DETECTOR 400 HZ MARKER 75 MHZ BEACON RF AMP ANTENNA FILTER (STA 771.2, 1300 HZ WL 99.14, MARKER BEACON MODULE BL 0) FILTER...
Page 608 777 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 609 777 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...