B767 ATA 23 Student Book

TRAINING MANUALFOR TRAINING PURPOSES ONLY

B767-3S2F ATA 23-50 Page - 1 3/28/14 EFF - ALL

COMMUNICATIONSCH 23



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ATA 23 COMMUNICATIONS TABLE OF CONTENTS

COMMUNICATIONS TOC..................................................................... 3

AUDIO SELECTOR PANEL .................................................................. 4

AUDIO SELECTOR SCHEMATIC......................................................... 6

FLIGHT INTERPHONE SYSTEM.......................................................... 8

GROUND CREW CALL COMPONENTS ............................................ 10

FLIGHT DECK CALL AND GROUND CALL GENERAL ..................... 12

GROUND CALL FLIGHT DECK INDICATIONS.................................. 14

CREW CALL HORN ............................................................................ 16

CARGO INTERPHONE SYSTEM ....................................................... 18

SERVICE INTERPHONE .................................................................... 20

VERY HIGH FREQUENCY COMMUNICATIONS............................... 22

VHF COMM COMPONENT LOCATIONS ........................................... 24

VHF ANTENNA LOCATIONS............................................................... 26

VHF SYSTEM - BLOCK DIAGRAM..................................................... 28

VHF SELF-TESTS............................................................................... 30

HIGH FREQUENCY COMMUNICATIONS.......................................... 32

HF TYPICAL SYSTEM ........................................................................ 34

HF COMPONENT LOCATIONS.......................................................... 36

HF ANTENNA AND COUPLER LOCATIONS ..................................... 38

HF SELECTOR AND RADIO COMM PANELS ................................... 40

HF BITE............................................................................................... 42

HF FUNCTIONAL MODES.................................................................. 44

ACARS (DATALINK) INTRODUCTION............................................... 46

ACARS GENERAL DESCRIPTION..................................................... 48

ACARS COMPONENTS...................................................................... 50

ACARS INTERFACES......................................................................... 52

ACARS PRINTER................................................................................ 54

ACARS OOOI EVENTS....................................................................... 56

SELECTIVE CALLING (SELCAL)........................................................ 58

SELCAL COMPONENT LOCATIONS ................................................. 60

SELCAL BLOCK DIAGRAM ................................................................ 62

SELCAL SYSTEM ALERT................................................................... 64

VOICE RECORDER INTRODUCTION................................................ 66

VOICE RECORDER GENERAL .......................................................... 68

VOICE RECORDER FLIGHT DECK COMPONENTS.......................... 70

VOICE RECORDER LOCATION.......................................................... 72

VOICE RECORDER SCHEMATIC ....................................................... 74

VOICE RECORDER TEST ................................................................... 76



AUDIO SELECTOR PANEL

Purpose

The audio selector panel permits the flight crew to select an audio system for transmission or reception.

Features

The microphone select switches connect the microphone to a radio transceiver, the flight or service interphone system, or the passenger address system. These switches are push-on/push-off, and are mechanically interlocked so that only one can be selected at a time. The switch when depressed illuminates white if the panel lighting is on.

The listen switches select the source and control the volume of audio connected to a cockpit speaker and headset. They are push-on/push-off switches which are rotated clockwise for maximum volume.

The "BOOM/OXY" toggle switch selects the microphone input as either the oxygen mask microphone or the boom headset microphone.

The "FLT/cabin" toggle switch selects either flight interphone or cabin interphone to be used in conjunction with the "INT" microphone switch and its associated listen switch and volume control.

The "voice/both/range" toggle switch selects portions of a filter which attenuates either the range audio or the voice audio of radio navigation signals (ADF, VOR, DME or ILS). In the "both" position, the filter is bypassed.



AUDIO SELECTOR PANEL



AUDIO SELECTOR SCHEMATIC

General

The Audio Selector Panel (ASP) controls the audio in the flight interphone system. The ASP sends flight interphone audio to the Audio Accessory Unit (AAU). The AAU combines and amplifies the audio. The amplified audio goes back to the ASP. The audio then goes to the flight compartment speaker and headset.

Nose Landing Gear

The ground crew uses the flight interphone jack and a crew call switch at the nose landing gear (NLG) to speak with the flight compartment.

Communication Systems

The communication system sends received audio and sidetone to the ASP. The transceivers get microphone audio and PTT discretes from the ASP.

Navigation Receivers

The ASP gets navigation system audio from the selected navigation system.

SELCAL Decoder

The selective calling system (SELCAL) decoder sends call set discretes to the ASP. The ASP uses the discretes to control the call lights. The ASP sendscall reset discretes to the SELCAL decoder to cancel the call discrete and put off the call lights.

Cockpit Voice Recorder

The ASPs send all received and transmitted audio from these stations to the cockpit voice recorder:

• Captain • First officer • First observer



AUDIO SELECTOR SCHEMATIC



FLIGHT INTERPHONE SYSTEM

General

The Flight Interphone System provides communications between flight crew members, communications between the flight crew and ground crew, and an interface with the voice recorder, cabin and service interphone system, communication transceivers, navigation receivers, and the passenger address system.

The flight interphone system consist of amplifiers and mixing circuits in the audio accessory unit, audio selector panels, interphone speakers, mic/headphone jacks, and push to talk (PTT) switches.

System Description

During flight, a flight crew member may establish communications by using microphones and/or listening devices, in the following manner:

• With a ground control/navigation station or another airplane through the audio selector panel and a selected radio system.

• With other flight crew members, through the audio accessory unit and audio selector panels.

• Monitoring navigation systems through the audio accessory unit and audio selector panel.

On the ground, the Flight Interphone System may be used for communications between the flight crew and the ground service personnel at the nose landing gear through the APU remote control panel.

The Flight Interphone System also interfaces with the voice recorder to provide voice inputs from the captain, first officer and first observer through the audio selector panel.

Audio Selector Panels

The audio select panel contains mic selector switches which connect mic circuits to the interphone systems, to the comm radio's, or to the PA system.

• Captain -left side of the control stand, P8 • First officer - right side of the control stand, P8 • First observer - P61

Cockpit Speakers

Located on the captain's auxiliary instrument (forward) panel, P13 and on the first officer's auxiliary instrument (forward) panel, P14.

Interphone Jack Panels

• Captain - captain's auxiliary instrument panel, p15 • First officer - first officer's auxiliary instrument panel, p16 • First observer - P61



FLIGHT INTERPHONE SYSTEM



GROUND CREW CALL COMPONENTS

Audio Control Panel

The Captains and First Officers Audio Control Panels are located in the flight station on the center pedestal. The First Observers ACP is on the P61 panel.

P40 APU Remote Control Panel

The P40 APU Remote Control Panel has both the Flight Deck Call Switch and Flight Interphone Jack installed.

Pilots Call Panel

The Pilots Call Panel is located on the P5 Overhead Panel.



GROUND CREW CALL COMPONENTS



FLIGHT DECK CALL / GRND CALL GENERAL

General

The flight deck and the ground crew use the ground crew call system.

You push the GND CALL switch on the Pilots Call Panel (PCP) to make a call to the ground crew. This causes a loud horn to operate in the nose wheel well area.

You push the flight deck call switch on the Auxiliary Power Unit (APU) remote control panel to call the flight compartment. This causes these flight compartment indications:

• Blue light in the GND CALL switch on the PCP comes on. • One high chime from the aural warning speakers. • On the Audio Selector Panels (ASP), the call light in the flight interphone

system microphone select switch comes on. • Message GROUND CALL shows on the Engine Indicating and Crew

Alerting System (EICAS) primary display.

The ground crew call horn in the nose wheel well area gives a warning for these on-ground conditions:

• Forward or aft equipment cooling system has low air flow or overheat sensors operate.

• Loss of 28 VDC to the aft and forward equipment cooling low air flow sensors and overheat relays.

• An Inertial Reference Unit (IRU) is on when the left and right AC buses are off.



FLIGHT DECK CALL / GROUND CALL GENERAL



FLIGHT DECK / GROUND CALL INDICATIONS

General

Ground call indications will be displayed on the EICAS Indicator as a Comm Medium Message (White with Bullet and “GROUND CALL”). Also, it will be displayed on the Audio Control Panel at the Flight Interphone Mic selector in green letters, “CALL”, and on the Pilots Call panel the GND CALL button will light up in blue. There will also be a high chime that sounds over the aural warning speakers.



FLIGHT DECK / GROUND CALL INDICATIONS



CREW CALL HORN

General

The Crew Call horn is located in the nose wheel well on the right side. The horn sounds when the ground call button is pushed on the Pilots Call Panel. This is the same horn for low flow of the equipment cooling fans and the IRU Warning horn for IRU’s on Battery.



CREW CALL HORN



CARGO INTERPHONE GENERAL COMPONENTS

General

The cargo interphone system lets the personnel in the cargo area talk with these stations:

• Flight deck • Ground • Main deck

Use the Master Cargo Control Panels (MCCP) to control the cargo interphone system.

Calls can be sent and received from these locations:

• Flight deck • Main cargo deck

Calls using the cargo interphone system will cause the Warning Electronics Unit (WEU) to sound a chime to alert flight crew or cargo handlers.

Interphone Function

Interphone function requires the selection of CARGO INT switch on the Pilots Call Panel (PCP) on P5. The CARGO INT switch connects the cargo interphone system to the flight interphone system.

The flight interphone system allows communication between the main deck and the flight deck from these panels:

• MCCPs • Cargo handling accessory panels • Cargo interphone jack panels

The flight interphone system allows communication between the flight deck, the main deck, and the Auxiliary Power Unit (APU) control panel flightinterphone jacks. Proper switch selection to connect the systems is required.

Intercom Function

The active MCCP can call and communicate with the Speaker/Microphone Units (SMU) in the main cargo compartment.

The SMUs can call the active MCCP. The MCCP main deck switch or Push-To-Talk (PTT) switch is selected to establish communications with the SMU.

Note: All headphones used with the flight interphone jacks located on the main deck or the APU control panel require a PTT adapter.

The MCCP has a MIC switch for PTT selection.



CARGO INTERPHONE GENERAL COMPONENTS



SERVICE INTERPHONE

General

The service interphone system is used by:

• Flight crew • Ground crew

Jacks connect through mixing circuits and amplifiers in the Audio Accessory Unit (AAU). Microphone audio from the service interphone jacks connect to the AAU if the service interphone switch is in the ON position. The flight interphone system connects to the service interphone system in the AAU if the service interphone switch is in the ON position. Flight interphone microphones send audio to the AAU. Flight interphone headsets get audio from the AAU.

The audio accessory unit does these functions:

• Puts audio together from the microphones • Does an amplification of the audio signal • Sends the audio to the handsets, headsets, and speakers



SERVICE INTERPHONE



VERY HIGH FREQUENCY COMMUNICATIONS

Purpose

The purposes of the system are to provide short range, line of sight, omnidirectional air-to-air and air-ground voice communications, and air-ground data communications when used with ACARS. The primary use is for air traffic control with some alternate uses such as company operational communications.

System Description

The system operates in the VHF aeronautical communications band (118 to 136 MHz) using keying and microphone inputs from the flight interphone system and providing audio outputs to the interphone and SELCAL.

When used with ACARS, the VHF communication system provides the transmission medium, receiving data and keying from ACARS for downlink and providing received uplink data to ACARS. The effective range is extended by the use of ground repeater networks. BITE provides self-test and monitoring for the transceiver.



VERY HIGH FREQUENCY COMMUNICATIONS



VHF COMPONENT LOCATIONS

VHF Comm Transceiver

The comm transceiver modulates audio inputs for RF transmission and demodulates RF signals for audio reception. The front panel contains two jacks, two test switches, a three position switch, two light, and a digital readout display.

• The two jacks (MIC and PHONE) allow to test the transceiver without the interphone circuits.

• The SQL/LAMP TEST switch disables the squelch and test all face panel lights.

• The TEST switch starts a self test of circuits in the transceiver.

• The two status lights indicate LRU PASS and frequency CONTROL INPUT FAIL.

• The three position RFL (reflected), FWD (forward), and OFF (normal) switch checks RF power to the antennas and show the results in watts on the two digit display.

Control Panels

There is one control panel for left and right systems on the p8 aft pilot control stand. Each control panel contains two frequency controls, two frequency in-use lights and a transfer switch.

Antennas

The antennas are mounted to the center line of the aircraft fuselage. The left system antenna is mounted on the top with the right and center mounted on the bottom.



VHF COMPONENT LOCATIONS



VHF ANTENNA LOCATIONS

Antennas

The antennas are mounted to the center line of the aircraft fuselage. The left and right system antennas are mounted on the top with the center mounted on the bottom.



VHF ANTENNA LOCATIONS



VHF SYSTEM - BLOCK DIAGRAM

Power

The left transceiver and control panel get 28v dc from the 28v dc standby bus. The right transceiver and control panel get 28v dc from the right bus. The center transceiver receives 28v dc from the left bus.

Control

Frequency selection is made from the control panels for all three systems using digital data on an ARINC 429 data bus to the transceiver. When ACARS is installed, the center system is tuned by the ACARS management unit over an ARINC 429 bus when operating in the data mode.

Transceiver keying for all three systems is by the flight interphone system PTT line. Also, the center system is keyed by ACARS when operating in the data mode.

The center system also receives a voice/data mode select discrete and a frequency data port select discrete from ACARS.

Signal Flow

For transmission, the transceivers generate the carrier, amplitude modulate it with audio from the flight interphone system and transmit it out over the antenna. The center system also receives modulation audio as a data tone from ACARS when operating in data mode. System keying is recorded by the flight data recorder, provides resets to the SELCAL decoder, and is sent to the FMC for use by software options.

When receiving, the receiver amplifies the input RF signal, converts it to a lower frequency and detects the audio modulation. If the signal is strong enough, the squelch opens and the audio is routed out to the flight interphone system.

The detected audio is routed from the detector output (before the squelch) to the SELCAL system (from all systems) and to the ACARS system (from the center system). SELCAL signals activate the SELCAL (alert) lamps on the pilot call panel and sound the chime.



VHF SYSTEM - BLOCK DIAGRAM



VERY HIGH FREQUENCY SELF-TESTS

Squelch/Lamp Test

Pressing the SQL/LAMP TEST switch breaks the receiver squelch (enabling the operator to hear receiver background noise) and illuminates the CONTROL INPUT FAIL and LRU PASS LEDs as long as the switch is held pressed.

LRU Test

Momentarily pressing the TEST switch causes the microprocessor to conduct a transmitter and receiver end-to-end test, consisting of a 100 msec transmission on a test frequency, modulated at 2 KHz. Forward and reflected power is monitored and VSWR computed and displayed (VSWR value is normally less than 3.0). The transmitted RF is attenuated and injected into the receiver which is tuned to the test frequency by a special local oscillator. If the transmit frequency is correct, modulation adequate, and the receiver is operating properly, the audio is heard at the receiver output. If all monitored parameters indicate proper operation of the transceiver, the LRU PASS indicator illuminates for approximately one second. Frequency selection data on the active port is also monitored. Improper data words will result in the CONTROL INPUT FAIL indicator illuminating for about one second. If the TEST switch is held in, the test is repeated until the switch is released.

Forward and Reflected Power Measurements

Forward and reflected power can be measured by turning the RFL-OFF-FWD switch momentarily to the desired position. The 100 msec test transmission is executed and the selected parameter is measured and displayed on the segmented display on the front panel. Forward power should be 30 watts normally, 25 watts minimum, and reflected power should be no greater than 25% of the forward power value.

Operational Checkout

A test transmission can also be made from the flight compartment or from the transceiver front panel if another station is within range and available for test purposes.



SELF - TESTS

TRAINING MANUAL FOR TRAINING PURPOSES ONLY


HIGH FREQUENCY COMMUNICATIONS (HF)

General

The system is used for long range air-to-ground and air-to-air voice communications in the high frequency band, primarily for air traffic control.

The system uses direct (ground) wave for short distances, but relies on refraction in an ionized layer and the earth's surface to achieve long range "sky wave" transmission by single or multiple "bounces". Sky wave propagation distances are dependent on:

• Frequency: controls possible refraction angles • Time of day: varies height of effective ionized layer • Aircraft altitude: controls atmospheric and ground interactions

Areas between ground bounces are "skips" in the communication coverage. Therefore, successful operation may depend upon correct frequency selection for the time of day.


B767-3S2F CH 23-10 Page - 33 3/28/14 EFF - ALL

HIGH FREQUENCY COMMUNICATIONS



HF TYPICAL SYSTEM

General

A typical HF communications system consists of a control panel, a transceiver, an antenna coupler and an antenna.

Functional Interfaces

Power on-off, frequency, mode selection, and RF sensitivity are controlled from the control panel. The system receives microphone audio and key signals from the interphone system.

The transceiver generates the RF signal to be transmitted or demodulates the received RF signals.

The coupler automatically matches the antenna to the transceiver. Received audio (SSB or AM) is routed to the interphone system. Unsquelched AM audio is routed to the SELCAL system. Keying for transmission is recorded by the flight data recorder, sent to the FMC for crew alertness monitoring, and used to reset the SELCAL system.

The H/F SATCOM Control Select Panel provides L and R HF microphone and audio selections to be used by either the HF system or SATCOM system. The HF/SATCOM relay is where the PTT, MIC, and Audio are switched.



HF TYPICAL SYSTEM



HF COMPONENT LOCATIONS

Component Location

The left and right HF control panels are located on their respective sides of the overhead P5 panel. Each control panel is dedicated to providing mode control, frequency selection, and RF sensitivity adjustment for its respective HF transceiver. The control panels contain circuits inside which convert the mode and frequency selections into digital form. The control panel provides a 32-bit word to the HF transceiver in the ARINC 429 format.

HF Comm Transceiver

The left and right HF transceivers are located in the main equipment center on the E2-6 rack. The transceivers weigh 26.5 lbs. Each contains an internal blower motor.

Each HF transceiver contains a transmitter and a receiver. The transmitter output is 125w in the AM mode and 400w pep in the USB mode. The transceiver front panel contains the following:

• LRU FAIL light illuminates as a result of a transceiver fault. • KEY INTERLOCK light illuminates as a result of HF antenna coupler fault. • CONTROL INPUT FAIL light illuminates as a result of control panel fault. • SQL/LAMP TEST pushbutton, when pressed provides a test condition and

the following occurs:

1. LRU FAIL Light illuminates2. KEY INTERLOCK light illuminates 3. CONTROL INPUT FAIL light illuminates 4. Receiver audio squelch is disabled5. RF sensitivity line is grounded6. Phone jack provides a receptacle for utilizing a headphone7. MIC jack provides a receptacle for utilizing a microphone

System Test

WARNING: DO NOT OPERATE HF SYSTEM DURING REFUELING. HAZARDS TO PERSONNEL AND EQUIPMENT EXIST DURING HF TRANSMISSIONS.

This test provides a quick check of the HF communications systems utilizing the status lights on the transceiver front panels.

1. Provide electrical power.2. Check that L HF comm (11G8) and R HF comm (11G35) circuit breakers are closed on the P-11 circuit breaker panel.3. Connect headset/boom microphone to captain's (first-officer's) jack panel.4. Press L (R) HF mic selector switch on captain's asp on P-8.5. Set boom/oxy switch to boom.6. Adjust HF listen switch.7. Set mode selector to either AM or USB on the L (R) HF control panel.8. Check that the L (R) HF transceiver internal blower fan is running. (E2-6)9. Press and hold SQL/LAMP test switch on L (R) HF transceiver front panel.10. Check that the three status lights come on and remain on. Check that squelch is disabled.11. Release SQL/LAMP test switch and check that the status lights go out.12. Set frequency selector to desired AM/USB frequency between 2.8 MHz and 23.999 MHz.13. Rotate RF sense control fully clockwise.14. Press and release PTT switch. Listen for 1 KHz tune in progress tone for 2 to 7 seconds. Verify none of the status lights on the L (R) transceiver front panel illuminate.15. Press and hold the PTT switch. Verify none of the status lights illuminate. Release the PTT switch.

Note: A 1 KHz tone will be heard while the PTT switch is depressed if an out of band frequency has been selected (below 2.8 Mhz or above 23.999 MHz).



HF COMPONENT LOCATIONS



HF ANTENNA AND COUPLER LOCATIONS

General

The left and right HF antenna couplers are located in the HF coupler bay of the vertical stabilizer. The HF couplers are rack-mounted, pressurized units weighing 17 lbs. each. Both couplers are pressurized with dry air at 5-7 psig.

The coupler consists of RF tuning elements and control circuits which comprise a closed tuning loop. The coupler is tunable over the frequency range from 2 to 30 MHz. Typical tuning time required is 2 to 7 seconds. The coupler constantly monitors the RF transmissions to automatically adjust the tuning elements. In dual HF installations, the couplers are electrically interlocked so that only one HF system transmits at a time. Faults within the antenna coupler cause the key interlock light on the HF transceiver to come on.

Access to the coupler is via the left side of the vertical stabilizer.

HF Antenna

The single HF antenna functions as the transmit and receive antennas for both HF systems and is located along the leading edge of the vertical stabilizer.



HF ANTENNA AND COUPLER LOCATIONS



HF SELECTOR AND RADIO COMMUNICATION PANELS

Purpose

The HF/SAT audio transfer and SAT call/reset panel permits the flight crew to transfer the connecting interface between the flight interphone system and the desired communication system.

HF/SAT XFER Switch (L and R)

These push on/push off switches control the HF/SAT relays which transfer the connecting interface between the flight interphone system and the desired communication system. The light illuminates white to indicate the active system.

SAT Switches

These light/switches are used to indicate incoming SAT COMM calls and to reset the indication.



HF AUDIO SELECTOR AND RADIO COMMUNICATION PANELS



HF BITE

General

Set the mode selector switch to the AM position on the HF communication control panel (P5). Make sure the internal blower fan on the transceiver operates.

Do these steps to do the transceiver test:

• Push and hold the SQL/LAMP TEST switch on the transceiver front panel. • Make sure the LRU FAIL (Status), KEY INTERLOCK, and CONTROL

INPUT FAIL lights come on and stay on. • Release the SQL/LAMP TEST switch. • Make sure the LRU FAIL (Status), KEY INTERLOCK, and CONTROL

INPUT FAIL lights go out.

Key Interlock Fault

The red KEY INTERLOCK light illuminates if:

• The tuning elements fail to reach home position within 15 seconds

• The coupler fails to reach the required VSWR within 15 seconds

• Arcing in the coupler is detected

This fault-light indicates a coupler fault only while the transceiver is keyed.

LRU Failure

The red LRU FAIL light illuminates when:

• There is insufficient RF power out from the transmitter

• Low power supply voltage; loss of synthesizer lock • Micro processor fault

This fault-light indicates a transceiver fault whether or not the transceiver is keyed.

Control Input Fail

The red CONTROL INPUT FAIL light illuminates if the digital data from the control panel:

• does not contain the HF label.

• has insufficient repetition rate.

• has invalid format contents.

WARNING: DO NOT OPERATE THE HF SYSTEM WHILE FUEL IS PUT INTO THE AIRPLANE. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE EQUIPMENT.

WARNING: MAKE SURE PERSONNEL STAY A MINIMUM OF 6 FEET AWAY FROM THE VERTICAL STABILIZER WHEN THE HF SYSTEM TRANSMITS. RF ENERGY FROM THE HF COMMUNICATION ANTENNA CAN CAUSE INJURIES TO PERSONNEL.



HF BITE



HF FUNCTIONAL MODES

Major Sequence

The graphic illustrates the various modes of operation and how cycling can take place between them. Transceiver and coupler tuning is initiated by changing frequency or initially applying power, which results in a logical progression through various modes.

The first step, called the HOMING MODE, drives the tuner in the antenna coupler to the HOME position. This is the low frequency (2 MHz) position of the tuning elements. The system then advances and remains in the receive/standby (REC/STBY) mode until a key signal is introduced. Keying the transceiver starts the tuning process (TUNING MODE) which continues until a satisfactory VSWR is measured. At that time the OPERATE mode has been reached. The HF system is then ready for transmission.

Rechanneling is normally complete in 2 to 7 seconds. If the final operate mode is not reached in 15 seconds, a fault results and the transmitter is disabled.

Normal Sequence

OFF: No system functions or indications available.

HOMING: the homing mode is initiated when transceiver power is turned on or whenever a new frequency is selected. While in this mode, the antenna tuning elements are driven to the HOME position regardless of selected frequency. Keying is disabled while the coupler is in the homing mode.

REC/STBY

The system automatically cycles to the receive/standby mode as soon as the tuning elements reach their HOME position. The system is then capable of reception on the selected frequency.

In dual systems, reception is possible only when the opposite system is not transmitting

In REC/STBY mode, the system is ready to be keyed for tuning at any time.

TUNE

Coupler tuning is initiated by keying the transmitter. The key line is latched in, the transmitter section is energized and low power RF is delivered to antenna coupler, and an audio tone (1 kHz) indicates that tuning is in progress.

Tuning takes place in three steps:

• TUNE A (resonance). • TUNE B (load tuning). • TUNE C (VSWR).

TUNE A (Resonance)

The coupler's discriminator responds to phase differences between the RF voltage and current. Tuning elements are positioned for zero phase difference (load resistive and resonant).

TUNE B (Load Tuning)

During TUNE B mode, the tuning elements are adjusted to present a total impedance which is approximately 50 ohms, and resonance. The 1 kHz tune-in-progress tone is still present.

TUNE C (VSWR)

During TUNE C mode the tuning elements are further adjusted so that RF power loading generates a VSWR 1.3:1. The 1 kHz tone is still present.

OPERATE

The coupler transitions to the OPERATE mode after completion of TUNE C. The key latch is broken, tuning RF power goes off and the tune-in-progress 1 kHz tone ceases. The system is now capable of reception or transmission. During full power modulated transmission, the coupler maintains the VSWR 1.3:1 by adjustment of the tuning elements. No audio tone is heard while tuning occurs during transmission.



NO

NO

NO

NO

RECEIVE/STANDBY

YES

YES

COUPLERFAULT

YES

?COUPLERARCING

NO

TONE

YES?

TO-TALKPRESS-

AUDIO

DURINGTUNE

RESONANCETUNE A

TUNE BLOAD

TUNE CVSWR <1.3:1

OPERATE/RECEIVE

TRANSMIT COMPLETE

TRANSMIT?

TO-TALKPRESS-

?FREQUENCYCHANGED

YES

RETUNE

HOMESEQUENCE

POWER ON

COUPLERFAULT

15 SECWITHIN

NO

?HOME YES

TUNED

15 SEC

?

WITHIN

HF SYSTEM FUNCTIONAL MODES



ACARS (DATALINK) INTRODUCTION

Aircraft Communications Addressing and Reporting System (ACARS)

Purpose

The Aircraft Communications Addressing and Reporting System (ACARS) is an addressable digital Data Link system. ACARS permits the exchange of data and messages between an aircraft and a ground-based operations center over a radio network.

System Description

ACARS relieves the flight crew of sending many of the routine voice radio messages by transmitting pre-formatted messages at specific times during the flight. These messages may include the following: time the airplane left the gate, lift off time, touchdown time, and time of arrival at the gate. These ACARS functions are known as the OUT OFF ON IN or OOOI times. In addition, ACARS can collect data from the various airplane systems and send the information to the ground.

The accurate reporting of event times, engine information, crew identification, and passenger requirements provides for a close monitoring of any particular flight. Airplane system data, such as engine performance reports, can be sent to the ground on a pre-programmed schedule, or manually by the flight crew. Personnel on the ground may request data at any time during the flight. Specific ACARS functions are accomplished in accordance with an airline's specific ACARS software program.

The ACARS system can be used for verbal communications through selection of the voice mode.

Down link messages from the airplane are transmitted in digital form to ground stations along most routes. The data is relayed to a central computer which is connected via land lines to the company communications control center.

If a messages is not acknowledged because of lack of radio coverage, the system will automatically repeat the message for a maximum of six times until acknowledged by the ground.



ACARS (DATA LINK) INTRODUCTION



ACARS - GENERAL DESCRIPTION

General

The system consists of an interactive display unit (IDU), management unit, and printer. The ACARS system utilizes the center VHF radio to transmit and receive data.

Functional Interfaces

The ACARS management unit has the following attributes:

Inputs:

• The control panel provides control and downlink data inputs to the management unit.

• Uplink data comes from the center VHF communications transceiver to the management unit.

• Voice/data select switch allows operator to manually select voice mode on center VHF.

• Specified data can be supplied from the digital flight data acquisition unit (DFDAU) when requested by the operator or the management unit.

• The program pins provide logic tailoring and OOOI (out, off, on, in) inputs, airline identification code and airplane registration number code.

• Out/off/on/in events. EICAS provides a digital input when those events occur.

Outputs:

• The management unit supplies timing, status data, and uplinked data to the control panel. It also supplies uplinked data to the printer (if installed).

• The management unit also issues the request for flight recorder data, and the data tones to the VHF communications transceiver for downlink.



ACARS GENERAL DESCRIPTION



ACARS COMPONENTS

ACARS Interactive DIsplay Unit

The ACARS Interactive Display Unit (referred to as the IDU) is used to operate ACARS and interact with the SATCOM system. The IDU is installed on the aft pilots control stand, P8. Different automatic prompts and menus are shown on the IDU which are used to operate ACARS.

ACARS Main Menu Page

The ACARS MAIN MENU page lets you display each function shown on this page. Touch the line select key on the IDU that shows the function you want. The display will then show the applicable menu page.

ACARS MU - Transceiver

Selection of the source of transceiver tuning data is made by use of a port-select discrete from the ACARS management unit, which selects the tuning data input port. Tuning is accomplished through an ARINC 429 (label 030) bus to the transceiver frequency select port A.

Keying of the transceiver in the data mode is done by grounding a data key line.

Data is supplied to the transceiver, from an encoder/modulator, in form of the differentially-encoded 1200 Hz/2400 Hz tone. The data tone is applied directly to transceiver modulator for transmission.

Data from the transceiver is in the same form as outgoing data; it is demodulated and transferred to the microprocessor.



ACARS COMPONENTS



ACARS INTERFACES

System Power

The Airplane Communications Addressing and Reporting System (ACARS) Management Unit (MU) receives 115 VAC from the left AC bus. The Airplane Communications Addressing and Reporting System (ACARS) Management Unit (MU) receives 28 VDC from the hot battery bus.

Airplane Personality Module

The airplane personality module gives a unique airplane and airline code. This code identifies the correct incoming messages for the MU and sets the address for data that goes to the ground.

The airplane personality module gets 12 VDC from the MU.

Radio Control Panel (RCP)

The MU sends a discrete to the Radio Control Panels (RCP) to identify which Very High Frequency (VHF) radios are enabled for data.

Data Loader Control Panel

The data loader control panel sends a data loader enable discrete to the MU.

ACARS IDU

The ACARS IDU sends and receives inputs to the ACARS MU



ACARS INTERFACES



ACARS PRINTER

Printer - Power

The printer (when installed) receives 115 volts ac from the left bus through a circuit breaker on the P11 circuit breaker on the P11 circuit breaker panel. This is converted to dc voltages for internal uses.

Printer - Operational Controls and Indicators

The PPR ADV switch provides the means for the operator to cause paper flow through the printer.

The SELF-TEST switch provides the means for the operator to initiate an LRU self-test.

The ALERT RESET switch provides the means for the operator to reset the Aural/visual alert functions (chime control and the PTR BUSY indicator).

The remote reset control line is not used.

Normal printer operation is controlled by the ACARS management unit.

The green PWR ON lamp illuminates while power is applied to the printer.

The yellow PTR BUSY lamp flashes while the printer is receiving text to be printed, and continues to flash until reset by the operator.



ACARS PRINTER



ACARS - OUT, OFF, ON IN, (OOOI) EVENTS

General

The ACARS Management Unit (MU) will process and format the information it receives based on specific airplane conditions. OOOI inputs are responsible for defining the various conditions.

The OOOI logic is responsible for interpretation of the OOOI inputs, and the triggering of automatic events based on the captured times. These events include automatic downlinks as well as prompts to the pilot for manual data input.

Sensors

OOOI sensor data is input in digital format from EICAS.

The EICAS inputs provide the following conditions:

• Air or ground condition

• All doors closed or any doors opened condition

• Parking brake set or released condition

States

There are four OOOI states defined for the system, which are:

• OUT - The period between leaving the gate and the end of the takeoff roll

• OFF - Airborne

• ON - The period from touchdown to arrival at the gate

• IN - Defined as the plane at the gate

For the purpose of defining OOOI state transitions, the OOOI inputs are defined as:

• Brake on - parking brake set

• Brake off - parking brake released

• Doors open - any door open

• Doors closed: all doors closed - Strut ext - (strut extended) strut switch indicates an airborne condition

• Strut comp - (strut compressed)

• Strut switch indicates an on-ground condition

OOOI Times

The OOOI times are derived from the Universal Time Clock (UTC) with seconds shortened.

Departure Ground Delay

If an OFF or IN event has not occurred within 15 minutes of an OUT event, the DELAY advisory is triggered to the crew. Selecting the advisory will display the DEPT GND DELAY page.



OOOI REPORTING______________

OUT

CLOSEDDOORS

BRAKE OFF

STRUT EXT

OFF

STRUTCOMP

ON

BRAKE OFF

IN

DOORSCLOSED

DOOR OPEN BRAKE ON

DOOR OPENBRAKE ON

1

2

3

1

2

3

4

4

OUT REPORT

OFF REPORT

ON REPORT

IN REPORT

ACARS - OUT, OFF, ON, IN (OOOl) events



SELECTIVE CALLING (SELCAL)

Purpose

The purpose of the SELCAL system is to tell the flight crew when a ground station wants to contact them on a radio. The system helps reduce pilot workload and distractions by making continuous monitoring of a radio unnecessary.

Operation

The ground station calls a certain airplane by transmitting, on a assigned frequency, an amplitude-modulated set of four audio tones that agree with the airplane's assigned SELCAL code. The airplane's radio transceiver (VHF or HF) tuned to the assigned frequency will receive and demodulate the SELCAL signal. The demodulated signal is sent to the SELCAL decoder which only reacts to its assigned tone combination. When the assigned code is recognized, the decoder sounds the warning electronics unit chime and illuminates the pilot's call panel lamp associated with the radio receiving the signals. The decoder and pilot's call panel lamp are manually reset. The flight crew then selects the indicated radio to contact the ground station.

A ground station is able to call a particular aircraft by transmitting a set of four tones. The SELCAL decoder receives the audio from the comm radio which it’s tuned and compares the tones to the assigned code. When the tones and codes are the same, a chime sounds and a call light illuminates on the pilot's call panel. The decoder reset comes from the pilot call panels or microphones. The reset is initiated either from the alert lamp/switch, from the flight interphone PTT, or from the key event contacts, for the associated transceiver.

The system consists of a SELCAL decoder, a coding receptacle, HF, and VHF pilot call switches.

The decoder monitors audio from the VHF and HF communication transceivers, recognizes receipt of the SELCAL code assigned to the airplane, and provides flight compartment call alert signals.

When the SELCAL code assigned to the airplane is received by one of the communication transceivers, the SELCAL decoder recognizes the code and provides the appropriate call signals to the flight compartment.

Power and audio inputs are wired directly to the decoder. Thus, the only operational control is for the reset function. The system is reset by pushing the associated indicator or by keying the PTT line for the associated transceiver.

When one of the transceivers receives a SELCAL code matching the code programmed by the shorting receptacle, the decoder recognizes it as a call to that airplane. The decoder turns on the indicator associated with the transceiver which received the call, and also sounds a chime in the flight compartment. The indicator and SELCAL decoder are then manually reset to wait for the next call. The decoder monitors audio from the VHF and HF communication transceivers, recognizes receipt of the SELCAL code assigned to the airplane, and provides flight compartment call alert signals.



SELECTIVE CALLING (SELCAL)



SELCAL COMPONENT LOCATIONS

General

The decoder has no front panel features, and is located on shelf 3 of the main equipment center rack E4 (E4-3).

The SELCAL shorting receptacle or DIP switch module provides a 4-bit binary code to the decoder for each of the four tones that make up the SELCAL code.

The SELCAL alert indicators are located on the pilots' call panel, on the pilots' overhead panel P5.



SELCAL SYSTEM COMPONENT LOCATIONS



SELCAL BLOCK DIAGRAM

Power

The decoder receives 28v dc from a left bus circuit breaker on the P11 circuit breaker panel.

Control

Power and audio inputs are wired directly to the decoder. Therefore, the only operator control required is for the reset function. The system is reset by either depressing the SELCAL lamp corresponding to the transceiver that received the call signal or by keying that transceiver.

Signal Flow

The decoder receives audio directly from the communication transceivers. When the received code matches the code set by the shorting receptacle, the decoder recognizes it as a call to that airplane. The decoder generates a call alert signal to the pilot call panel SELCAL lamp corresponding to the transceiver that received the call signal. The decoder also issues a call signal to the warning electronics unit to actuate the pilot's chime. An activated channel can be reset by a reset signal from the pilot call panel. This reset signal is initiated either by the corresponding call lamp/switch or by the corresponding transceiver key event signal.

ACARS Interface

ACARS interfaces with SELCAL, and operates as follows:

• ACARS voice go-ahead discrete is a parallel input to the WEU chime input.

• Center VHF SELCAL reset is a parallel output to the ACARS management unit.

SELCAL Decoder

The decoder monitors audio from the comm radio's and recognizes the receipt of the tone set assigned to the aircraft and provides flight deck call light illumination.

The decoder monitors audio from the VHF and HF communication transceivers, recognizes receipt of the SELCAL code assigned to the airplane, and provides flight compartment call alert signals.

Coding Receptacle

The Selcal code shorting receptacle provides a 4-bit code to the decoder for each letter of the assigned code. It is located on the E2-5 rack.

SELCAL Call Switches

There is one blue call switch on the pilot's call panel for each transceiver connected to the SELCAL decoder. Each call switch alerts the flight crew of a ground to air call received by the comm radio tuned.

When the SELCAL code assigned to the airplane is received by one of the communication transceivers, the SELCAL decoder recognizes the code and provides the appropriate call signals to the flight compartment.

Power and audio inputs are wired directly to the decoder. Thus, the only operational control is for the reset function. The system is reset by pushing the associated indicator or by keying the PTT line for the associated transceiver.

When one of the transceivers receives a SELCAL code matching the code pro-grammed by the shorting receptacle, the decoder recognizes it as a call to that airplane. The decoder turns on the indicator associated with the transceiver which received the call, and also sounds a chime in the flight compartment. The indicator and SELCAL decoder are then manually reset to wait for the next call.



SELCAL SYSTEM - BLOCK DIAGRAM



VOICE RECORDER INTRODUCTION

General

The voice recorder system preserves a continuing record of the latest 120 minutes of flight crew communications and conversations. The solid state memory receives inputs from the captain's, the first officer's, and the first observer's audio selector panels and from an area microphone in the flight compartment. The voice recorder system consists of a recorder located in the aft passenger cabin ceiling and a control panel with an area microphone located on overhead panel P5. 115 VAC power is supplied to the system from the right AC bus. The VOICE RECORDER circuit breaker, located on overhead panel P11, controls power to the system.

Operation

The latest 120 minutes of flight compartment communications are recorded by the voice recorder. Channels 1 thru 3 record audio from the first observer's, the first officer's, and the captain's audio selector panels, respectively. Channel 4 records audio picked up by the area microphone on the voice recorder control panel (P5). The flash crash survivable store unit contains a flash memory array which allows the 120 minute continuous recording of the standard audio data which is a summation of the three audio channels and the area microphone.



FIRSTOFFICER

AREA

CAPTAIN

VOICE RECORDER

MICROPHONE

OBSERVER

VOICE RECORDER

VOICE RECORDER INTRODUCTION



VOICE RECORDER GENERAL

General

The voice recorder unit makes a continuous record of flight crew communication and flight compartment sounds. It erases the communication data so that the memory stores only the most recent audio.

The voice recorder unit keeps the last 120 minutes of communication data in memory.

Components

The voice recorder system has these components:

• Voice recorder control panel • Voice recorder switch • Voice recorder unit

Functional Description

The voice recorder unit collects these inputs at the same time:

• Captain microphone audio • First officer (F/O) microphone audio • First observer (F/OBS) microphone audio • Area microphone audio on the cockpit voice recorder panel.

The audio inputs from the captain, first officer, and first observer microphones go to the voice recorder through the flight interphone system Audio Selector Panels (ASP).

The area microphone collects flight compartment sounds, such as voices and aural warnings. The cockpit voice recorder control panel does an amplification of the audio signal and sends it to the voice recorder unit.

You can monitor this audio with a headphone connected to the phone jack at the cockpit voice recorder panel.

An erase switch on the voice recorder control panel removes all the audio that is stored on the voice recorder. You can only erase data when the airplane is on the ground and the parking brake is set.

An underwater locator beacon is on the front panel of the voice recorder unit.



VOICE RECORDER GENERAL



VOICE RECORDER FLIGHT DECK COMPONENT LOCATIONS

General

The Voice Recorder Control Panel is located on the P5 Overhead Panel in the Flight Deck.

Voice Control Panel

The voice recorder control panel is located on the overhead panel P5. The control panel contains an area microphone, TEST switch, ERASE switch, TEST light, and monitor HEADSET jack. The microphone and the preamplifier pick up flight compartment conversations which are recorded by the voice recorder.

Erase Switch

Under certain conditions, pushing the ERASE switch on the control panel will cause the solid state memory to be erased. Bulk erasure requires that the ERASE switch be pushed a minimum of two seconds when the airplane is on the ground with the parking brake set. When the ERASE switch is released after being pushed for a minimum of two seconds, the entire flash memory is erased. A modulated tone can be heard for 5 to 14 seconds through the HEADSET jack.

Test Switch

When the TEST switch on the control panel is pushed, a 600 Hz test tone is generated in the voice recorder unit. A ring counter sequentially switches the 600 Hz test tone for 0.8 seconds to each of the four record amplifiers. A good test will cause the TEST light to come on momentarily and you hear a tone from the headset jack.



VOICE RECORDER FLIGHT DECK COMPONENT LOCATIONS



VOICE RECORDER LOCATION

Voice Recorder General

The Voice Recorder is located next to the Flight Recorder in a panel at the entry of the aft Bulk Cargo door.

The voice recorder is installed in the E7 equipment rack in the aft bulk entry way. The recorder is a thermally insulated, impact resistant, 4 MCU unit, and international orange in color. The voice recorder consists of a chassis and front panel, four replaceable assemblies: the Aircraft Interface Unit, the Audio Compressor Unit, the Acquisition Processor Unit and the Crash Survivable Memory Unit. The store processor contains sufficient solid state memory to provide 120 minutes of continuous recording. An underwater locator beacon (ULB) is attached to the voice recorder front panel and is a self-contained device. The ULB will emit a 37.5-KHz signal when the water activated switch is closed. The ULB contains a dated label to indicate when the battery requires periodic replacement.



VOICE RECORDER LOCATION



VOICE RECORER SYSTEM - SCHEMATIC

Recorder Power

The recorder receives 115 volts 400 Hz directly (un-switched) from the P11 circuit breaker and the right bus. The power supply in the voice recorder supplies 5 and 24 VDC used within the recorder and 18 VDC used in the voice recorder control panel.

Control Panel Power

The control panel receives +18 volts dc, un-switched, from the recorder for use by the microphone preamplifier.

Input

The area microphone input is routed through the preamplifier in the control panel and out to the voice recorder. The audio selector panel inputs are routed directly from the ASPs to the recorder.

Output

The recorder audio signals can be monitored, with a slight delay, by plugging a headset into the front panel jack or the control panel jack.

Recording

The four channels of HI, LO audio inputs to the voice recorder are routed through the aircraft interface to the audio processor where it is digitally linked through the store processor to the flash store.

Auto Erase

The voice recorder continuously overwrites the information saved in the flash store retaining only the latest 120 minutes of flight compartment communications.



VOICE RECORER SYSTEM - SCHEMATIC



VOICE RECORDER TEST

General

The cockpit voice recorder system has an internal Built-In Test Equipment (BITE) circuit that lets you monitor system operation and do system tests.A TEST switch on the control panel lets you manually start the system test.

Automatic BITE Operation

The recorder does a test at power-up. It also does a continuous monitor during normal operation.

Manual BITE Operation

You use the control panel TEST switch to start the BITE test. You can do the test on the ground or in the air. When you push the TEST switch, the BITE circuits make an analog test tone. The recorder changes and stores this test tone on each channel. BITE then does checks of the stored tone to make sure it is the correct frequency and amplitude.

BITE Test

You use the Cockpit Voice Recorder (CVR) AUTO/ON switch to manually apply power to the voice recorder system. To start the system test, you push and hold the control panel TEST switch for a minimum of five seconds.

These are the control panel indications of a passed test::

• 800 Hz tone on the headphone jack

• Green status indicator comes on one time

These are the results if the test fails:

• Control panel status indicator stays off

• There is no tone in the headphone jack

System Test

The BITE test only monitors for the recorder to record. It does not examine the recording quality. To examine the recording quality, you must do thesystem test. You must listen through a headset and use the airplane microphones for input.

Put the headset plug into the control panel HEADSET jack. The voice recorder has an active microphone input when a microphone connects to a flight crew position.

Do these steps to do a test of the captain, first officer, and first observer input channels:

• Disconnect all microphones but the one for the test channel

• Put a cover on the area microphone



VOICE RECORER TEST

Documents

B767 ATA 23 Student Book