B737-3 Comunications

ATA 23Communications

B737−3 23 B1 E

EASA Part-66 B1

737−300/400/500Boeing

For training purposes only.� Copyright by Lufthansa Technical Training.LTT is the owner of all rights to training documents and trainingsoftware.Any use outside the training measures, especially reproductionand/or copying of training documents and software − also extractsthereof −in any format all (photocopying, using electronic systemsor with the aid of other methods) is prohibited.Passing on training material and training software to third partiesfor the purpose of reproduction and/or copying is prohibited withoutthe express written consent of LTT.Copyright endorsements, trademarks or brands may not be re-moved.A tape or video recording of training courses or similar services isonly permissible with the written consent of LTT.In other respects, legal requirements, especially under copyrightand criminal law, apply.

Lufthansa Technical TrainingDept HAM USLufthansa Base HamburgWeg beim Jäger 19322335 HamburgGermany

Tel: +49 (0)40 5070 2520Fax: +49 (0)40 5070 4746E-Mail: [email protected]

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COMMUNICATIONGENERAL

B737−300/400/500

23−00

Page: 1FRA US/E nm 9.4.96

ATA 23 COMMUNICATION

23-00 GENERAL

Page: 1Figure 1 ANTENNA-LOCATION

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737330−430−530

23-00

Page: 2HAM TS 32 Kn 14.06.94

THIS PAGE INTENTIONALLY LEFT BLANK

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737330−430−530

23-00

Page: 3HAM TS 32 Kn 14.06.94 Page: 3Figure 2 ELECTRONIC-EQUIPMENT-COMPARTMENT

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COMMUNICATIONAUDIO INTEGRATING

737−300/400/500

23-50

Page: 4HAM TS 32 Kn 14.06.94

23-50 AUDIO INTEGRATING

GENERAL

The audio integrating system provides a communication link between the flightcompartment crew members, cabin crew members, ground crew members,airplane radio systems and recorders.The audio control panels (ACP’s) permit selection of the function desired. Theposition of switches and potentiometers are transmitted digitally from the ACP’sto the Remote Electronics Unit (REU). Audio from communication and naviga-tion systems and from the audio selector panels are integrated at the REU. Au-dio from the ACP’s is also sent to the voice recorder system via the REU.The REU contains amplifiers for the flight interphone system, the service inter-phone system with the capability of controlling the gain of each system. It alsocontains a tongenerator for the altitude alert warning and discrete grounds forthe flight recorder.In case of a failure in the Captains or F/O’s ACP or in the associated REU-cir-cuit audio switching relays allow the connenction to the observer interphonesystem.

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737−300/400/500

23-50

Page: 5HAM TS 32 Kn 14.06.94

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Page: 5Figure 3 DIGITAL AUDIO CONTROL SYSTEM / Schematic

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23-50

Page: 6HAM TS 32 Kn 14.06.94

LOCATION

Page: 6Figure 4 AUDIO INTEGRATING / Locations - Forward View

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Page: 7HAM TS 32 Kn 14.06.94 Page: 7Figure 5 AUDIO INTEGRATING / Locations - AFT View

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AUDIO SWITCHINGThe observer’s audio selector panel can be substituted for either the captain’sor the first officer’s ACP using a transfer switch on the P5 panel. This will allowthe captain or first officer to use the observer’s ACP to accomplish all commu-nication functions in the event his primary panel has failed. All analog signals ( mike, audio, PTT) are switched parallel to the observer’s ACP. In the processof the switching over, power is also removed from the primary panel.

AUDIO CONTROL PANEL

GENERALThe ACP enables the flight crewmembers to transmit and receive on the radiocommunication systems, communicate using the flight and service interphonesystems and make announcements over the PA system. Airplane navigationsystems can also be monitered.Three ACP’s are located in the flight compartment.

ACP ( XA - XU )This ACP has a BOOM/OXY select switch. The BOOM/OXY select switch is atwo-position locking toggle. The switch connects the boom mic (headset) or theoxygen mic (oxygen mask) to the input.

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Page: 9HAM TS 32 Kn 14.06.94

RADIO

PACABININTVHF−1

ONLYVOICE

VHF−2 HF

BOOM

OXY

SPKR MKR ADF 1−NAV−2 INT

MICROPHONE SELECTPUSHBUTTON

LISTEN LEDGREEN

BOOM/OXYGEN SELECT SWITCH

LISTEN ON/OFF UND−CONTROL SWITCHES

RAD/INT PTTSWITCH

VOICE FILTERSWITCH

Page: 9Figure 6 AUDIO CONTROL PANEL ( config. 1 )

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CONFIG. 2

The front panel of the audio selector panel has the following switches: (1) Microphone Selector Switches The microphone selector switches are used to connect the boom,oxygen mask, or hand microphone to the interphone, passenger address (PA),or any of the selectable transmitters.The microphone selector switches are momentary contact switches. Theswitches are mechanically and electronically interlocked to permit only oneswitch to be selected at a time. A light in each switch comes on when theswitch is selected, and the related receive audio channel will become active.The microphone selector switches are split legend switches used for both mi-crophone selection and call indication. The upper half of the switch, whenturned on, indicates the microphone selection made. The lower half of theswitch, when ”C” is showing, indicates an incoming call for that system. (2) Volume Control SwitchesThe switches are turned ON/OFF by pushing the switch knob. The switchescontrol the selection and volume level of the received audio. The controlswitches turn clockwise for increasing volume and counterclockwise fordecreasing volume. (3) Listen ON - green LED

(4) RADIO − INT PTT SwitchThe RADIO − INT PTT Switch is a system keying switch. When inthe RADIO position the switch will key the communications system selected bythe microphone selector into transmit. When in the INT position the switch willkey the flight interphone system into transmit regardless of the microphoneselection.This switch is spring loaded to center off. The PTT switch on the ASPis connected in parallel to the PTT switch on the control wheel which serves asimiliar function.The flight deck speakers are muted when the microphone withthe exception of the oxygen mask microphone is keyed at the audioselector panel, at the control wheels, or at the hand microphone.(5) VOICE ONLY Select SwitchThe VOICE ONLY select switch is a momentary contact switch.When active (the switch is lighted), the voice filter attenuates 1020 Hz, switch-ing out DME ident.(6) SPKR/ NAV Selector SwitchThe SPKR switch is the off−on/volume control for the interphonespeaker. This control is not used on the observer audio selector panel.The NAV switches are used to select the navigation system for monitoring.Any number of the switch may be selected at the same time permitting themonitoring of more than one system.

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Page: 11HAM TS 32 Kn 14.06.94 Page: 11Figure 7 AUDIO CONTROL PANEL ( config. 2)

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COMMUNICATIONFLIGHT INTERPHONE SYSTEM

737−300/400/500

23-51

Page: 12HAM TS 32 Kn 30.06.94

23-51 FLIGHT INTERPHONE SYSTEM

GENERALThe flight interphone system provides the flight crew with capabilities to com-municate with each other and provides the means for them to transmit and re-ceive on airplane communication radio systems and receive on airplane navi-gation radio systems.The flight interphone system consists of audio selector panels, a remoteelectronic unit, jack panels, push−to−talk (PTT) switches on the controlwheel, handheld microphones, headsets, boom microphone/headsets oxygenmask microphones, and loudspeakers.The captain and first officer each have an audio selector panel, a cockpitspeaker, a control wheel PTT switch, a boom microphone headset and oxygenmask microphone, plus jacks for a headset and a handheld microphone.The first observer has an audio selector panel, an oxygen mask microphone, ahandheld microphone and a headphone. The second observer has a head-phone jack. The audio selected by the first observer is heard at both observerstations.Ground crew personnel access the flight interphone system by plugging ahandset into the flight interphone jack on external power receptacle panel. Thisallow the ground crew to communicate with the flight crew.The flight interphone system receives power from the dual power source of28v dc battery bus and 28v dc bus No. 2, through circuit breakers anddiodes to allow either bus to power all circuits on load control center P6.

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23-51

Page: 13HAM TS 32 Kn 30.06.94 Page: 13Figure 8 AUDIO INTEGRATING / System Schematic

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OPERATIONSelection of which system will receive the microphone input from each flightcrew station is made at the audio selector panel. The last MIC SELECTORpushbutton which is pushed will determine the communication system to bekeyed by a PTT switch at that flight crew station.Flight crewmembers access the flight interphone system to communicate witheach other by setting the PTT switch on the ASP toINT or I/C position. The PTT function can also be performed ateither pilot’s station by setting the control wheel PTT switch to the INT position. Flight crewmembers key a selected airplane radio system from an audio selec-tor panel by pushing and rotating the system audio control and pushing thesystem MIC SELECTOR switch and then holding the R/T−I/C or RADIO − INTswitch to the R/T or RADIO position. This connects the boom or oxygen maskmicrophone and a control line to the selected radio system. The PTT functioncan also be completed at either pilot’s station by holding the control wheel PTTswitch to the MIC position.All flight compartment PTT switches are connected to a speaker mute line soboth cockpit speakers will be muted when a PTT switch is actuated exceptwhen the MASK/BOOM switch is in the MASK position or oxygen mask is inuse. This prevents audio feedback from the speakers to the microphones.All audio warning messages from ground proximity and altitude alert are heardby all flight crewmembers without being selected on the audio selector panel.

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Page: 15HAM TS 32 Kn 30.06.94

3

RADIO

PACABININTVHF−1

ONLYVOICE

VHF−2 HF

BOOM

OXY


3

2

PANELS WITH HF RADIO

PANELS WITH CALL (C) INDICATORS

1

1 PANELS WITHOUT CALL (C) INDICATORS

2

Page: 15Figure 9 FLIGHT INTERPHONE ACTIVATION ON ACP

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OXYGEN MASK MICROPHONES

DLH audio selector panels without a BOOM/OXY switch.The switch for selecting the oxygen mask microphone is in the oxygen maskstowage box. When the mask is packed the switch is positioned to the boomposition. Removing the mask from the stowage box will automatically positionthe switch to the OXY position to select the oxygen mask microphone as theoperating microphone at that crewmember’s station.The boom microphone can be returned to operational status by repacking themask in the stowage box, closing the compartment doors, and activating thecompartment ”PUSH TO TEST AND RESET” button or by closing the maskstowage compartment left door and activating the compartment ”PUSH TOTEST AND RESET” button.

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Page: 17HAM TS 32 Kn 30.06.94

PUSH

RESETTEST

100%

OXYGEN

MASK

RADIO

PACABININTVHF−1

ONLYVOICE

VHF−2 HF

BOOM

OXY


Audio Selector Panel ( XA − XU )

Audio Selector Panel ( XW and on )

INT

Mask Stowage Box

Page: 17Figure 10 OXYGEN MASK MIKE OPERATION

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COMPONENTS AND LOCATION

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Page: 18Figure 11 FLIGHT INTERPHONE / Components

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Page: 19HAM TS 32 Kn 30.06.94

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Page: 19Figure 12 FLIGHT INTERPHONE SYSTEM / Location

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COMMUNICATIONSERVICE INTERPHONE

737−300/400/500

23-41

Page: 20HAM TS 32 Kn 29.06.94

23-41 SERVICE INTERPHONEGENERALThe service interphone system provides interphone communications betweenthe flight crew, the attendants, and ground crew personnel. The system in-cludes: the remote electronics unit, the service interphone switch, the atten-dants handsets, and the service interphone jacks. Also, there is a provision fora control stand handset. Handsets are installed in the forward and aft attendantpanels for communication between attendants. Switched service interphonejacks located throughout the airplane are for use by ground crew personnelduring servicing and maintenance. Personnel in the control cabin can commu-nicate with the attendants or ground crew personnel through the audio selectorpanels and the headphones and microphones of the flight interphone system.The service interphone system gets power from the 28v dc battery bus andalso the unswitched electronics bus No. 2, through the INTPH AND WARNINGcircuit breaker located on the load control center−right panel, P6.The remote electronic unit (REU) is installed on the E2−1 shelf of the electronicequipment rack.There is an audio accessory unit (AAU) card inside theREU. The AAU provides the necessary dc voltage to the system microphonesand amplifies the audio signal. Automatic level control ensures a constant out-put regardless of the number of microphones connected to the system. Sincethe system has no on−off switch, it will operate whenever the battery bus or dcbus No. 2 has power. Gain controls for the service interphone system are onthe audio control panel.The service interphone switch is located on the aft overhead panel P5. In theON position, the switch connects the microphone lines from the external ser-vice interphone jacks to the input of the interphone amplifiers.The OFF positiondisconnects the microphone lines to isolate the external service interphonejacks during flight.The handset may be of the press−to−use or press−to−talk type. The button ona press−to−use type handset completes both microphone and receiver audiocircuits when the handset button is pressed. The button on a press−to−talktype handset completes only the microphone circuits when it is pressed; receiv-er circuits are connected directly to the system.

OPERATIONPush the CABIN switch and the respective LISTEN switch on the ACP.Setting the service interphone switch (on the aft overhead panel P5) to ONconnects the microphone circuits from the external service interphone jacks tothe interphone amplifier. This allows ground crew at the various maintenancelocations to talk with each other. Attendants may communicate with each other,with the flight crew, and with the ground crew, by using the handsets installedat their stations.

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23-41

Page: 21HAM TS 32 Kn 29.06.94

P8 CONTROL STAND − AFT FACE

P14 AFT ATTENDANT’S PANEL

D6019

D6023

D6021

JACK

HANDSET

HANDSET

JACK

TYPE

JACK

JACK

JACK

JACK

JACK

ELECTRONIC EQUIPMENT RACK

ATTENDANT’SINTERPHONESERVICE

AUDIOEXTERNALINTERPHONESERVICE

AUDIO

LEVEL CONTROLINTERPHONETO SERVICE

(P5 AFT)INTERPHONE SWITCHS50 SERVICE

FLIGHT CREW

D2501B

AAU CARD

M1353 REMOTE ELECTRONICS UNIT (E2−1)

D2501B

D6

G9

G8

F7

D7

ON

SERVICE

21

E7

AUDIO

H2

H1SUPPLYPOWER

OFF

LEFT WHEEL WELL

RIGHT WHEEL WELL

RIGHT WING REFUELING

(STA 1004)AFT CABIND6015

(STA 1040)APUD6017

(STA 655)

D6011

(STA 655)

D6057

STATION (STA 78)

D6013

RS

T

RS

T

RS

T

RS

T

RS

T

RS

T

FORWARD ATTENDANT’S PANEL

FORWARD OF LEFT WHEEL WELL

FORWARD OF RIGHT WHEEL WELL

AFT ATTENDANT’S PANEL

ATTENDANT/SERVICE

CONTROL STAND

APU ACCESS PANEL

INTERPHONE STATIONS

WING REFUELING STATION

AFT CABIN CEILING

K

J

H

CODE

B

C

D

E

F

G

INPH PWR

INPH PWRF/O BAT. AND WARNING

INPH AMPL

M545

P6−2 CIRCUIT BREAKER PANEL

M544F/O NO. 2 BUS

C84

C560

24−00−01BAT. BUS28V DC

24−00−01BUS 228V DC

C561

(STA 350)

D6025ELECTRONICEQUIPMENT RACK

K

K

H

G

G

D,E

B

J

F

H

B

J

F

E

D

C

P13 FORWARD ATTENDANT’S PANEL

PHONE LOPHONE HI

PHONE LOPHONE HI

PHONE LOPHONE HI

21

43

MIC LOMIC HI

21

43

MIC LOMIC HI

21

43

MIC LOMIC HI

INTERPHONE

Page: 21Figure 13 SERVICE INTERPHONE SCHEMATIC

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LOCATION

ATTENDANT’S PANELCENTER, P6−2LOAD CONTROL

ATTENDANT’S PANEL

AFT OVERHEAD PANEL, P5

ON

OFFINTERPHONE

SERVICE

A

SEEA

SERVICE

SWITCHINTERPHONE

SEE B

RECEPTACLE PANELEXTERNAL POWER

CONTROL STAND −HANDSET JACK ON

AFT FACE

ELECTRONICSREMOTE

UNIT

HANDSET AT AFT

HANDSET AT FORWARD

SERVICE INTERPHONE SWITCH

REMOTE ELECTRONICS UNIT

B

ATTENDANT’S HANDSET

Page: 22Figure 14 SERVICE INTERPHONE / Component Location

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CODE

ABCD AFT CABIN CEILING

STA

STA1043

664

A

B

C

D

E

B,C

DE

F

F

STA350

EF

APU ACCESS PANELELECTRONICS RACK

WING REFUELING STATIONFORWARD OF RIGHT WHEEL WELLFORWARD OF LEFT WHEEL WELL

EXTERNALEXTERNALINTERNALEXTERNALINTERNAL

EXTERNAL

AREALOCATION

STA1004

STA130

Page: 23Figure 15 SERVICE INTERPHONE / Jacks Location

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COMMUNICATIONCALL SYSTEM

737−300/400/500

23-43

Page: 24HAM TS 32 Kn 08. 05.96

23-43 FLT/GRD CREW CALLGENERALThe flight and ground crew call system provides for call signals betweenthe flight compartment and cabin attendant stations, between the flightcompartment and ground personnel, and between cabin attendant stations.The system is used to signal personnel that they are wanted on the serviceinterphone.The system includes the ATTEND CALL and GRD CALL switchesand the captain’s call light on the forward pilots’ overhead panel, the AT-TENDANT, CAPTAIN and RESET switches on the attendant panels, and the PILOT CALL switch on the external power receptacle panel. It also in-cludes the ground crew call horn, and the attendant call lights on the exit loca-tor signs.The call system gets power from the 28v dc bus No. 1 through thecircuit breaker on the P18 load control center labeled PASS AND CREWCALL/LAV SMK DET (or PASS AND CREW CALL on airplanes without lava-tory smoke detectors)

OPERATION

CAPTAIN CALLXA bis XU: High Chime and Capts Call Light (blue) comes on, when a callfrom ground personnel or from the attendants are initiated. The Call Light goesout automatically after 40 seconds.XW and on: High Chime and INT Call Lights on all ACPs come on, when acall from ground personnel on the external power panel is initiated. High Chime and CAB Lights on all ACP’s come on, when a call from the atten-dants is initiated. All lights go out automatically after about 40 s.

ATTENDANT CALL Pressing the ATTEND call switch on the forward overhead panel P5applies 28v dc power to the pink attendant call lights, to the R380 attendant callrelay, and to the chime in PA amplifier. The PA amplifier sounds a doublechime through the PA system. Also, the attendant call relay holds the call lighton until reset with the RESET switch on either attendant panel. Pressing theATTENDANT call switch on either attendant panel applies 28v dc power to thegreen attendant call lights, to the attendant call relay, and to the chime in thePA amplifier. The PA amplifier sounds a double chime over the PA system.Also, the attendant call relay holds the call lights on until reset with the RESETswitch on either attendant panel.The RESET switches on the attendant panelsare connected in series.Thus, pressing one removes power from the attendantrelay and makes the call lights go off.

GROUND CREW CALL Pressing the GRD CALL switch on the forward overhead panel P5 applies 28vdc power to the ground crew call horn. The horn will sound as long as theswitch is pressed. The ground crew call horn also serves as an audible warningdevice for the IRS (inertial reference system). The IRS warning system relaycomes on in the flight instrument accessory unit or integrated flight instrumentaccessory unit, and applies 28v dc power to the ground crew call horn, when-ever the IRS is powered by its battery or the IRS is turned on and the equip-ment cooling fan is not operating. The air−ground relay must be in the groundposition before the IRS warning system relay can energize.

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TD

1

1

CHIME

OVERHEAD PANELP5 PILOTS’ FORWARD


GRD CALL

OR IRS IS ON AND EQUIPMENTPOWERED BY ITS BATTERY,COMES ON WHEN IRS IS

COOLING FAN IS NOT OPERATING.(AIR−GROUND RELAY IS GROUNDED)

CAPTAIN

(STA 304)

M63 PA AMPLIFIER(E2−1)

TWO TONE CHIME

BUS NO. 128V DC

R380

DELAY RELAYR392 TIME

CALL RELAY

(STA 995)

(STA 304)LOCATOR SIGNL1086 EXIT

(STA 993)

L1088 EXITLOCATOR SIGN

P

G

P

G

DIM ANDTEST

MASTER

B

B

ATTEND

ATTENDANT

CALL RELAY

R22ATTENDANT’S

RESET

ATTENDANT

CAPTAIN

RESET


CALL

TEST

M315 AURAL WARNINGMODULE

HI TONE

L19 CALL LIGHT

PILOT CALL

P19 EXTERNAL POWERRECEPTACLE

PASS CALL

CALL/LAVSMK DET

PASS AND CREW

CREW CALL HORN

LOAD CB PANELP6−1 ELECTRONIC

(E1−2)ACCESSORY UNITINSTRUMENTM160 FLIGHT

28V DC

(STA 230)

M53 GROUNDCREW HORN

Page: 25Figure 16 CALL SYSTEMS / Config. 1

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TD

TD

1

1

CHIME

OVERHEAD PANELP5 PILOTS’ FORWARD


GRD CALL

OR IRS IS ON AND EQUIPMENTPOWERED BY ITS BATTERY,COMES ON WHEN IRS IS

COOLING FAN IS NOT OPERATING.(AIR−GROUND RELAY IS GROUNDED)

CAPTAIN

(STA 304)

M63 PA AMPLIFIER(E2−1)

TWO TONE CHIME

BUS NO. 128V DC

R380

DELAY RELAYR392 TIME

CALL RELAY

(STA 995)

(STA 304)LOCATOR SIGNL1086 EXIT

(STA 993)

L1088 EXITLOCATOR SIGN

P

G

P

G

ATTEND

ATTENDANT

CALL RELAY

R22ATTENDANT’S

RESET

ATTENDANT

CAPTAIN

RESET


TIME DELAYRELAYR455 (J5 STAB. SHIELD)

M315 AURAL WARNINGMODULE

HI TONE

PILOT CALL

P19 EXTERNAL POWERRECEPTACLE

PASS CALL

CALL/LAVSMK DET

PASS AND CREW

CREW CALL HORN

LOAD CB PANELP6−1 ELECTRONIC

(E1−2)ACCESSORY UNITINSTRUMENTM160 FLIGHT

28V DC

(STA 230)

M53 GROUNDCREW HORN

TO CABIN CALLLIGHTS ON ALL ACPs

TO INT CALLLIGHTS ONALL ACPs

Page: 27Figure 17 CALL SYSTEMS / Config. 2

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LOCATION

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Page: 29HAM TS 32 Kn 30.06.94

ATTENDANT’SATTENDANT’S

SWITCHES

AURAL WARNINGLOAD CONTROL

PA AMPLIFIER(ELECTRONIC

LOCATOR SIGN

UNIT (CHIME)

LOCATOR SIGN

PANEL

AFT

PANEL

EXTERNALPOWERRECEPTACLE ATTENDANT’S

EXIT

PANEL, P19

ATTENDANT’S

OVERHEADPANEL, P5

PILOTS’ CALL

FORWARD

EXIT

CENTER, P18

CHIME)

CALLB

ATTEND CALLGRD

ON

AUTO

SMOKINGOFF

BELTSFASTENNO

PILOTS’ CALL SWITCHES

(REF)

CALL LIGHT(PINK)

CEILING

EXIT LOCATOR SIGN

CALL LIGHT(GREEN)

EXTERNAL POWER RECEPTACLE PANEL

FORWARD ATTENDANT’S PANEL AFT ATTENDANT’S PANEL

POWERINTERPHONE

PILOTNOSE

WHEELWELL

ON

NORMLIGHTCALL

NOTIN USE

EXTERNAL

SERVICEPARKINGBRAKES

CONN FLIGHT

BSEE

SEE A

DSEE

CSEE

DSEE

SEE

E

D

C

A

WORK GROUND

SERVICE

FIRST

CEILING

FIRST

WINDOW

CALL SYSTEM

RESET

ON ON

DIM

OFF OFF OFF

OFF DIM

BRTBRT

OFF

NIGHT

OFF DIM

BRT

OFF

BRT

CEILING

NIGHT

CAPTAIN

TOURIST

BRT

WINDOW

DIM

ENTRY

LIGHTS

DIM

TOURIST

ATTENDANT

CALL SYSTEM

CAPTAIN ATTENDANT RESET

LIGHTS

BRT

DIM

ENTRYOFF

CALL SWITCHES

CALL SWITCHESCALL SWITCH

B

PAX CALLLIGHT(BLUE)

ATTENDANTS LAVATORYCALLLIGHT(AMBER)

E

Page: 29Figure 18 CALL SYSTEMS / Component Location

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COMMUNICATIONPASSENGER ADDRESS

737−300/400/500

23-31

Page: 30HAM TS 32 Kn 24.06.94

23-31 PASSENGER ADDRESS (PA)

GENERALThe PA system supplies voice messages, and chime signals via speakers toall passengers and attendants in the passenger cabin.The PA system also sup-plies boarding music via the speakers to the passenger cabin. PA sidetone isprovided to the flight deck crewmembers via their audio selector panels. PAinputs have an order of priority, when the PA receives an input it will can-cel any input with a lower priority.The PA input priority is as follows: (1) Announcements from the flight compartment have the highest priority. (2) Announcements made from an attendants panel have the second highest priority. (3) Emergency prerecorded announcements have the third highest priority. (4) Prerecorded announcements have the next highest priority. (5) Boarding music has the lowest priority input. Keying the forward attendant PA microphone mutes the forward attendant speaker(s) and keying the aft attendant PA microphone(s) mutes the aftattendant speakers. This prevents feed back during attendant announce-ments.Keying the pilot’s PA microphone will disable the muting of both forwardand aft attendant speakers.Discrete signals from the passenger signs system cause a low tone chimesignal to be sounded. A single low chime occurs whenever the NO SMOKINGor the FASTEN SEAT BELT signs are switched on or off.Discrete signals from the attendant call system cause high tone chimesignals to be sounded. A single high chime occurs when an attendant callswitch is pressed at a passenger service unit (PSU) or from a lavatory.Discrete signals from the cabin interphone system cause high−low chimesto be sounded. A single high−low chime occurs for a crew to attendantcall.

Voice announcements from the pilots are made through the flight interphonesystem. The announcements amplified by the PA amplifier are returned to thepilots via the flight interphone system. Amplification by the PA amplifier is en-abled by PTT (push−to−talk) inputs.The PA amplifier has circuitry to provide system testing. All PA speakers canbe checked. Output level of the amplifier can be determined to allow for adjust-ments.The system amplifier gain is increased by 6 db to compensate for increasednoise levels when either engine is operating.Each audio input into the PA amplifier has a PTT control signal. Priorities withinthe PA amplifier are in numerical order with No. 1 as the highest priority input.The self−test switch on the PA amplifier front panel provides tests of the op-erational status of the PA system. The spring loaded CAL position applies thePA amplifier main output to an internal load. The power applied across the loadis displayed on the LED indicators. The TEST position causes a calibrated highchime tone from the main and auxiliary outputs to all speakers. The NORMposition is used for system operation.After performing any tests, the switch should always be returned to theNORM position.

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Page: 31HAM TS 32 Kn 24.06.94

12

HI

(EXAMPLE)PSU SPEAKER

AFT RIGHTLAV SPKR

PA MIC

PTT

MIC HI

PTT

MIC HI

1

2T251C

1

2T251B

1

2T251A

2143

MIC LO

DC COMM 2143

MIC LO

DC COMM

CIRCUIT BREAKER PANELP6−1

C82

PASS ADDRESS

28V DCBAT. BUS

C

PA MIC

3412

PTT

MIC HIMIC LO

DC COMM

B

13

NC

FILT

3 BD GAIN ON DECOMPN

SIDE TONEVOLTAGE

REGULATOR

OUTPUT CONT

28V DC

SENS CONTROL

23−51−00

22

14

20

2

1

15

23−42−00

23+1DB−1DB

OUTPUTOF 60WATTS

6DB INCREASEWHEN GROUNDREMOVED

AUXAMP

CAL33−27−00

DC

LO

LO

INPUTNO. 4

32

LO

TEST

HI

NORM

HI

CHIMEGEN

HI/LOATT CALL

PASS/LAV CALL

SEAT BELTS

NO SMOKING

MASTERLEVELDC

E

D

33−25−00P14 AFT ATTENDANT

PANEL

P13 FORWARD ATTD PANEL

P8 PILOTS CONTROL STAND − AFT

TO REMOTEELECTRONICS

UNIT

M67 AFT LEFT LAV SPKR

M73 FWD LEFT LAV SPKR

ELECTRONICS

PA MIC(PROVISIONS)

24−58−21

INPUT NO. 1

INPUT NO. 2

M1353 REMOTE

UNIT (E2−1)

ODB=

NC

NC

F GAMP BAT

1

79−30−00

G

23

OIL PRESSURE SWS124 ENGINE 1 LOW

P79−32−00

78−00−00

M63 PASSENGER ADDRESS AMPLIFIER (E2−1) (346D−2B AMP)

LOW OIL PRESSURE SWS124 ENGINE 2

S124 ABOVESAME ASINTERNALS

(SHT 2)2 78−00−003

1

F2G2J5

K5F5 H5

K2K3

M1353 REMOTE ELECTRONICS UNIT (E2−1)

MUSIK/EMERGENCYANNOUNC-MENT

NEXT PAGE

PA LISTEN

(TO REU FORATT SPKR )

NEXTPAGE

NEXTPAGE

NEXTPAGE

NEXTPAGE

A

(POWER)

Page: 31Figure 19 PA SYSTEM SCHEMATIC 1

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Page: 32HAM TS 32 Kn 24.06.94


Page: 32

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Page: 33HAM TS 32 Kn 24.06.94

4CH HEAD

14

26

28

25

4

3

6

M1276 TAPE REPRODUCER PRERECORDED ANNOUNCEMENT (EXAMPLE)

FWD ATTENDANT STATION

ROM

AUDIOMUSICINPUT NO. 4

AUDIOANNOUNCEMENTPRERECORDEDINPUT NO. 3

ATT MUTE (K1)

AFT MUTE (K3)

FWD MUTE (K2)

SPEAKERR AFT ATTNDM1213

SPEAKERL AFT ATTNDM1212

SPEAKERFWD ATTNDM157

14

TAPE

BLANK &ADDR DET

AMPLIFIER (E2−1)ADDRESSM63 PASSENGER

T337

T338

T339

OUTPUT LOWMAIN AUDIO

CONTROL 4

LOW

HIGH

CONTROL 3

LOW

HIGH

3

1

18

17

6MUTE

MUSIC

ANNC

SWITCH

RLYR324 OXY IND

D1D2

E3−1 ELEX SHELFDRIVER

LED

VOICESTOREDSTATESOLID

DECK

KEY SWITCH & DISPLAY

SWITCH

#4

#3

#2

#1

SWITCH

SWITCH

SWITCH

SWITCH

LOCKELECTRONIC

CYCLE SETANNUNCIATOREMERGENCY

ON−OFFPEEPER

ASSIGNMENTMESSAGESSSV

S1−2

S1−3

S1−4

S1−5

S1−6

S2−1

S2−2

S2−3

S2−4

S2−5

S2−6

S1−1

MICROPROCES-SOR

(5 MBIT MAX)

CONTROL

21

20

+19V+5V+5V−5V+5V

SUPPLYPOWER

C

E

B

F

A

D

M1353 REMOTE ELECTRONIC UNIT (E2−1)

TAPE RPDR ACPASS ADDRESS

BREAKER PANELP6−1 CIRCUIT

C80PWR 2ELEX115V AC

1

21STOPSTART

READY

MUSIC

9

6

32

5

8

0

7

4

1

21

STOPSTART

READY

MUSIC

9

6

32

5

8

0

7

4

PREVIOUSPAGE FWD PA PTT

POWER

COCKPIT PAPTT

AFT PA PTT

PRE REC ANN PTT

PA AMPLIFIEROUTPUT

A

Page: 33Figure 20 PA SYSTEM SCHEMATIC 2

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23-31

Page: 34HAM TS 32 Kn 24.06.94

LOCATION

(EXAMPLE)

CALNORM

TEST

+10 db−1

PA AMPLIFIER

A

PSU SPEAKER

ELECTRONICEQUIPMENT

REMOTEELECTRONIC

PILOT’S PA MICROPHONE(PROVISIONS)PANELS

AUDIO SELECTOR

PA AMPLIFIER(E2−1)

RACK, E2

UNIT (E2−1)

LOAD CONTROLCENTER, P6

SEE E

SEE D

ASEE

FORWARD

ATTENDANT

STATION

FORWARD

ATTENDANT’S

SPEAKER

(LOWERED CEILING)

(LOWERED CEILING)

SPEAKERS

AFT ATTENDANT’S

MICROPHONE ON AFT

CSEE

ATTENDANT’S PANEL

SEE B SEE B

TAPE REPRODUCER −

LEFT GALLEY WALL

Page: 34Figure 21 PA / Component Location 1

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23-31

Page: 35HAM TS 32 Kn 24.06.94

FORWARD ATTENDANT’S PANEL(EXAMPLE)

(EXAMPLE)AFT ATTENDANT’S PANEL

AUDIO CONTROL PANEL

D

PA

ATTENDANT

MICROPHONE

CALL SYSTEM

CAPT ATTD RESET

E

PAPA

INT

PA MIC

SELECTOR

HF − 2− 2

SELECTOR

CREW

FLIGHT

REMOTE ELECTRONICS UNIT

(EXAMPLE)TAPE REPRODUCER

C

B

1 2

START STOP

READY

MUSIC

1

5

3

6

8 9

0

7

2

4

B

Page: 35Figure 22 PA / Component Location 2

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23-31

Page: 36HAM TS 32 Kn 24.06.94

TAPE REPRODUCER

GENERALThe tape reproducer is operated from the controls on the face of the unit.There are controls for selection and play of both boarding music and prere-corded announcements.To open the door holding the tape magazine, display 90 in the windowand press music channel switches 1 and 2 simultaneously.

MUSICThe front face of the tape reproducer has MUSIC controls for off/on/volumeand selection of music channel 1 or 2.To playback boarding music program 1 or 2, press MUSIC channelbutton 1 or 2 and press the START button. Adjust music volume by rotatingMUSIC control. Either music program may be stopped at any time by press-ing the STOP button. The boarding music program being played may also beswitched at any time by pressing the other MUSIC channel button.

PRERECORDED ANNOUNCEMENTThe front face of the reproducer has the controls for selecting and playing pre-recorded announcements. The selection is made with a numerical keyboardwhich selects the desired announcement by number and displays the selectionin the window. Upon selecting an announcement, boarding music willcease and the reproducer will search for and key at the start of the selectedannouncement. The READY light indicates the completion of the searchmode.Pushing the START button will initiate playing of the announcement. If STARTis pressed before the search is complete the search will continue and an-nouncement playback will start immediately upon completion of search. The announcement will play to completion or until STOP is pressed, after whichtime the reproducer will return to the boarding music mode of operation beforeannouncement selection.An oxygen emergency announcement has priority over any other announce-ment or boarding music. This announcement is not manually selected. It willplay automatically and repeat upon closing of the OXY IND relay, R324. Thisrelay closes as part of the sequence during activation of passenger oxygen.All keyboard, START, STOP, and channel 1 or 2 buttons backlightwhen pushed. The channel selection 1 and 2 buttons are push−on/push−off.All other buttons are momentary.

All the programs are on one C−60/90 Phillips four channel cassette tape. Twoof the channels are for boarding music; one for selected announcements andthe remaining channel for the emergency oxygen announcement.

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Page: 37HAM TS 32 Kn 24.06.94 Page: 37Figure 23 PA / Tape Reproducer

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Page: 38HAM TS 32 Kn 24.06.94

PA - AMPLIFIER / TEST

AMPLIFIER 346D - 2BThe self−test switch on the PA amplifier front panel provides tests of the opera-tion status of the PA system. The spring loaded CAL position applies the am-plifier output to an internal load. The power applied is displayed on the LEDindicators.Make sure that the -1 and the 0 dB LED’s on the PA amplifier come on. If the-1 and the 0 dB LED’s do not come on, adjust the MASTER GAIN potntiometeruntil this both LED’s come on. the MASTER GAIN potentiometer is on the low-er part of the front panel on the PA amplifier.The TEST position supplies a high chime sound to all speakers. Make sureyou hear a high chime sound on all the PA speakers.

AMPLIFIER 346D - 1BCAL position: indication 0 dB on the testmeter.TEST TONE position: a calibrated tone is applied to the input of the amplifierand applied to all speakers.

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Page: 39HAM TS 32 Kn 24.06.94

21

PA AMPLIFIERAIRPLANES WITH 346D -1B AMPLIFIER

AIRPLANES WITH 346D−2B AMPLIFIER

1

2

OUTPUT LEVEL

INDICATORS (db)

SPRING−LOADED)

TEST SWITCH

(CAL, POSITION

Page: 39Figure 24 PA AMPLIFIER

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COMMUNICATIONRADIO COMMUNICATION PANEL (RCP)

737−300/400/500

23-21

Page: 40HAM TS 32 Kn 15.06.94

23 - 21 RADIO COMMUNICATION PANELGENERALThe radio communication panels RCP-1, RCP-2 and RCP-3 are installed onthe aft electronics panel, P8.Each RCP can make a radio selection and a frequency selection for each ofavailable radio systems. To set the RCP for a VHF system, push the applica-ble radio selector switch on the RCP (VHF-1, VHF-2 or VHF-3). The switchlight will come on to show the selection was made at that RCP.Use the frequency selector knobs, frequency displays and an ACTIVE/STAND-BY transfer switch to set the RCP for a frequency selection. Each RCP has anACTIVE frequency display and a STANDBY frequency display. The ACTIVEfrequency display shows the frequency to which the selected radio is tuned.The OFF switch disables the RCP. This is only intended to used in the event ofRCP failure. All radios can still be controlled from other RCP’s in the event of asingle RCP failure.The OFF SIDE CONTROL light illuminates whenever an RCP is used to selecta frequency for an OFF-SIDE radio (refer to the operation paragraphs for a def-inition of OFF-SIDE). Radio normally associated with this VHF panel is beingtuned by another VHF panel. Onside transceiver:Left RCP is normally associated with VHF-1.Right RCP is normally associated with VHF-2.Center RCP is normally associated with VHF-3 (ACARS - MU).

OPERATIONThe frequency selected will show in the STANDBY frequency display and canbe transferred to the ACTIVE frequency display by action of the transfer switch.Then another STANDBY frequency selection can be made.This pair of frequencies is monitored by all RCP’s. All RCP’s are connected viaa cross-bus and to the associated transceiver. Whenever this radio is called upon another RCP, the frequency pair originally selected with the on-side RCP willthen show on the off-side RCP. The OFF SIDE CONTROL light will illuminateon both RCP’s.When a failure occurs the indication FAIL appears in the ACTIVE display win-dow. In this case the onside transceiver can not be tuned from the associatedRCP. With the OFF switch you must disable this RCP. Than the transceivercan be tuned from other RCP’s.The third VHF transceiver is originally connected with the ACARS managementunit. The VHF-3 is used by the ACARS to transmit and receive messages.When you select the VHF-3 transceiver on a RCP, the message ACARS ap-pears in the ACTIVE frequency window on this RCP.

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COMMUNICATIONRADIO COMMUNICATION PANEL (RCP)

737−300/400/500

23-21

Page: 41HAM TS 32 Kn 15.06.94 Page: 41Figure 25 RADIO COMMUNICATION PANEL

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COMMUNICATIONVHF - COMMUNICATION

737−330/430/530

23-21

Page: 42HAM TS 32 Kn 15.06.94

23 - 21 VHF - COMMUNICATION

GENERALThe very high frequency (VHF) communication system provides short-rangetwo-way voice and data communication in the frequency range of 118.000through 136.975 MHz with a RF power of about 25 W ( AM ).Three VHF systems are installed in the airplane.The communication equipment for each VHF system includes a VHF transceiv-er, a RCP and a blade antenna.Each VHF system interfaces with the audio integration system and the SEL-CAL system.VHF-1 system power is obtained from the hot battery bus, VHF-2 system pow-er is obtained from switched electronics bus No. 2 and VHF-3 system power isobtained from DC bus No. 1.

OPERATION (VHF - 700 COLLINS)

DESCRIPTIONThe VHF system consists of:� transceiver Collins VHF-700 (E2-1)� radio control panel (P8)� blade antenna

The frequency selection data originates in the RCP is transmitted to the trans-ceiver over an ARINC 429 data bus.Each VHF transceiver has two ports (A and B) for receiving tuning data. TheVHF No.1 transceiver receives the tuning data from the ACTIVE frequency onRCP-1 through port A when VHF-1 is selected on RCP-1. Similarly the VHFNo.2 transceiver receives the tuning data of the ACTIVE frequency on RCP-2through port B when VHF-2 is selected on RCP-2. This operation is on-sideoperation.The VHF transceiver A tuning ports are active and the cross-tunig annunciatorsare off.The selection of any VHF except No.1 by RCP-1, or the selection of any VHFradio except No.2 by RCP-2, constitutes an off-side condition.

An off-side condition will turn on the cross-tuning annunciator on the RCP-1and RCP-2 and will activate tuning port B of the selected off-side radio. Theoff-side RCP will acquire the tuning selections from the on-side radio and willtune the off-side radio with the ACTIVE frequency acquired from the on-sideRCP through tuning port B of the off-side transceiver.Tuning port A for VHF−3 is reserved for future ACARS input. VHF−3 is tunedonly through tuning port B. Selecting VHF−3 from any RCP, other than RCP−3will result in off−side operation. Thus, the radio controlled from the off-side RCPwill keep the same frequency but will be tuned through port B.Tuning port A for VHF-3 is reserved for the ACARS input, VHF-3 is tuned onlythrough tuning port B.

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23-21

Page: 43HAM TS 32 Kn 15.06.94 Page: 43Figure 26 VHF- 700 / Schematic

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23-21

Page: 44HAM TS 32 Kn 15.06.94

LOCATION

Page: 44

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23-21

Page: 45HAM TS 32 Kn 15.06.94

PANELS NO. 1,2,3,

OFF

VHF1 VHF3 VHF2

ACTIVE STANDBY

VHF−2 POWER, LOAD

ELECTRONIC

EQUIPMENT

TRANSCEIVERS

SEE B

VHF−1 AND VHF−3 POWER,

B

VHF TRANSCEIVER

VHF−1,−2,−3

CONTROL CENTER, P6

RACK, E2

LOAD CONTROL CENTER, P18

SEE A

PANEL, P8

AFT ELECTRONIC

RADIO COMMUNICATION

RADIO COMMUNICATION PANEL

A

SWITCHES (3 LOCATIONS)OFF SWITCH

DISPLAY

FREQUENCYACTIVE

TRANSFER SWITCH

ACTIVE/STANDBY

DISPLAY

FREQUENCY

STANDBY

KNOBS

SELECTOR

FREQUENCY

(WHITE)

CROSS−TUNING

ANNUNCIATOR

RADIO SELECTOR

PHONE MIC

TEST

CONTROL

INPUT

FAIL

LRU

PASS

OFF

RFL FWD

TEST

VHF−700

VSWR/POWER

DISPLAY

TEST RESULT

SWITCH

SQL/LAMP

HEADPHONE

JACK

(PHONE)

SWITCH

(POWER TEST)

RFL/OFF/FWD

LEDs

MICROPHONE

(MIC) JACK

TEST

SQL/LAMPTEST SWITCH

Page: 45Figure 27 VHF - 700 / Locations

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23-21

Page: 46HAM TS 32 Kn 15.06.94

FRONTPANELTEST (VHF−700)

SQUELCH/LAMP−TEST−SWITCHThis test switch is used to disable the squelch ( you can hear a noise sound)and to check the front panel lights prior to system self-testing. The red CON-TROL INPUT FAIL and the green LRU PASS lights come on when this testswitch is pushed.

TEST−SWITCHThe CONTROL INPUT FAIL test checks that the VHF transceiver is receivingvalid frequency tuning data from the VHF control panel RCP. If the tuning datais not valid, the red CONTROL INPUT FAIL light comes on indicating a VHFcontrol panel failure. This light remains on for about four seconds after TESTswitch is pressed.The LRU PASS test identifies a failure on the VHF transceiver. After pressingthe TEST switch, the green LRU PASS should light for approximately one tofour seconds. At the same time, the digital display should show a value of lessthan 3.0. This value is the voltage standing wave ratio (VSWR).

RFL − OFF − FWD SWITCHAfter the CONTROL INPUT FAIL / LRU PASS tests are completed, turning thepower test switch to FWD or RFL displays the forward or reflected power val-ues on the digital display.The FWD position should display a minimum value of 25 ( that means 25 W).The RFL position should display about 25 percent or less of the forward powervalue.

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Page: 47HAM TS 32 Kn 15.06.94

PHONE MIC

TEST

CONTROL

INPUT

FAIL

LRU

PASS

OFF

RFL FWD

TEST

VHF−700

VSWR/POWER

DISPLAY

TEST RESULT

SWITCH

SQL/LAMP

HEADPHONE

JACK

(PHONE)

SWITCH

(POWER TEST)

RFL/OFF/FWD

LEDs

MICROPHONE

(MIC) JACK

TEST

SQL/LAMP

TEST SWITCH

VHF TRANSCEIVER

Page: 47Figure 28 VHF - 700 / Locations

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23-21

Page: 48HAM TS 32 Kn 15.06.94

OPERATION (RTA-43A BENDIX)

TRANSCEIVERThe RTA-43A VHF transceiver is a solid state transceiver. The VHF transceiv-er provides two-way voice and data communications in the 118.000 through135.975 MHz requency range.The front panel of the transceiver has a XMTR light, a SQUELCH switch, aPHONE jack and a MIC jack. The XMTR light comes on when the transmitteroutput is greater than 12 watts. The SQUELCH switch disables the transceiversquelch circuits and tests the receiver section. The PHONE and MIC jacks areprovided to connect a headset and microphone directly to the VHF transceiver.

CONTROL PANELOn the front of the VHF control panel are two sets of concentric frequency se-lect knobs, two frequency displays, a transfer switch and a SELCAL indicationlight (with push- to- reset function).The TFR switch allows one frequency to be preselected while operating on adifferent frequency. A bar will appear across the inactive frequency.

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Page: 49HAM TS 32 Kn 15.06.94

VHF−1, −2

VHF−1, −2

VHF−1 POWER, LOAD

XMTR

2010945

VHF TRANSCEIVER

MIC PHONE

SQUELCH

RTA−43A

PANEL P8

AFT ELECTRONICCONTROL PANELS,

ASEE

VHF CONTROL PANEL

BSEE

TRANSCEIVERS

B

A

CONTROL CENTER P18

RACK E2

EQUIPMENT

ELECTRONIC

CONTROL CENTER P6

VHF−2 POWER, LOAD

VHF TRANSCEIVER

CALSELCOMM COMM

TFR

NAV

118,00 136,975

114,20

Page: 49Figure 29 VHF RTA-43A Locations

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COMMUNICATIONSELCAL

737−300/400/500

23-22

Page: 50HAM TS 32 Kn 24.06.94

23-22 SELCALGENERAL

The SELCAL (selective calling) system allows a ground station, with tonetransmitting equipment, to call a specific airplane. When the correct tone com-bination is received, the airplane SELCAL decoder unit signals the flight crewby a SELCAL light and an electronic chime. The SELCAL system eliminatesthe necessity of continuous monitoring of the communication system by theflight crew.The SELCAL system consists of the SELCAL decoder unit. Visual indicationis provided by CALL indicators on the audio selector panels or by a SELCALlight on the VHF COMM/NAV control panel.The electronic chime is part of theaural warning system.When the ground station operator wants to call a specific airplane usingthe SELCAL system, the four−tone code which has been assigned to theairplane is added to the audio transmitted from the ground station. Thiscode is received by a communication system and sent to the SELCAL decoderunit. If the four−tone code received is identical to the code entered onthe SELCAL decoder, the flight crew will be alerted by the SELCAL lightand electronic chime.On airplanes with call indications on the audio selector panels, the call is resetby pushing the call indication for the system with the call on any audio selectorpanel. For airplanes without call indications on the audio selector panels, theSELCAL reset button is on the VHF COMM/NAV control panel.

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COMMUNICATIONSELCAL

737−300/400/500

23-22

Page: 51HAM TS 32 Kn 24.06.94 Page: 51Figure 30 SELCAL / BLOCK DIAGRAM

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COMMUNICATIONSELCAL

737−300/400/500

23-22

Page: 52HAM TS 32 Kn 24.06.94

SELCAL DECODER

TEAM Selcal Decoder The SELCAL decoder is a five channel multiplexed unit. Four of the decoderchannels are connected to the VHF−1, VHF−2, VHF−3, and HF−1 transceivers,respectively. The other channel is not used. The decoder consists of com-pressor amplifiers, filters, an analog to digital converter, a microprocessor andcontrol relays.Every channel will recognize the unique four tone code assigned to the air-plane. The assigned code is pin programmable and determined by airplanewiring to SELCAL decoder connector D2555B or connector D849.The four tone code is resolved with a 16−bit binary word. Four bits of the worddetermine each tone. A coding receptacle is wired to implement the unique 16bits of this code for the airplane. This receptacle is mounted external to theSELCAL decoder and connected to it with a short cable. Thus the SELCALdecoder can be replaced without affecting the code.The coding receptacle isplaced on the rack behind the decoder.A green and a red and five yellow LED’s are located at the front panel of thisdecoder. Push the test knob on the front panel and check the indication:� all LED’s come on for about 3s (lamp test)� subsequentily all LED’s come on step by step (testsequence)� at the end of the test the green GO LED comes on for about 3 s (no failure)� in case of existing failure the red NO GO LED comes on.

MOTOROLA Selcal DecoderTwo separate decoders, in a common case, make up the dual SELCAL decod-er unit. One decoder receives the audio input from the VHF−1 transceiver,the other decoder from the VHF−2 and VHF−3 transceivers. Each decoderconsists of an audio amplifier, a resonant reed circuit, a dc amplifier and controlrelays.

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COMMUNICATIONSELCAL

737−300/400/500

23-22

Page: 53HAM TS 32 Kn 24.06.94

(A−H, J−M)

SELECT

CODEA

WINDOW

DISPLAY

CODE

(EXAMPLE)

CODE SELECTOR KNOB

SELECTOR KNOBS

NO. 1 DECODERNO. 2 DECODER

SELECTOR KNOBS

DUAL SELCAL DECODER − MOTOROLA NA−135SELCAL DECODER − TEAM SC2253AD01

Page: 53Figure 31 SELCAL DECODER

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COMMUNICATIONSELCAL

737−300/400/500

23-22

Page: 54HAM TS 32 Kn 24.06.94

LOCATION

Page: 54

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COMMUNICATIONSELCAL

737−300/400/500

23-22

Page: 55HAM TS 32 Kn 24.06.94

(E2−1),(E2−2)

CENTER, P18

CENTER, P6

SELCAL−2 POWERLOAD CONTROL

AURALWARNING

PANEL, P8

SELCAL DECODERRACK, E2

FORWARDELECTRONICSSECTION

STANDCONTROL

A

CONTROL PANEL

LOAD CONTROLSELCAL−1 POWER

SEE A

SEE B

MODULE

CONTROL

FWD

B

AURAL WARNING MODULE

ELECTRONICEQUIPMENT

SELCALCHIME

CSEE

NAV

TFR

COMMCOMM SEL

CAL

120 60 118 30

1

2

321 DLH PQ051−PQ068,PQ086−PQ099

DLH PQ069−PQ073,PV231−PV270DLH PQ051−PQ068

3

114,20

C

SELCAL DE-CODER − TEAMSC2253AD01

1

C

DUAL SELCAL DECODER − MOTOROLA NA−135

3 2

Page: 55Figure 32 SELCAL / Component Location

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COMMUNICATIONAIRCRAFT COMMUNICATION ADDRES-SING AND REPORTING SYSTEM (ACARS)

737−300/400/500

23-27

Page: 56FRA USE NM 29.02.1996

23-27 ACARS

GENERALThe Aircraft Communications Addressing and Reporting System (ACARS) is adigital data−link system that operates between an airplane and a ground−basednetwork of receiver−transmitter stations and central processing stations. Thetransmission medium is generally a single frequency in the VHF frequencyrange. The VHF−3 is used by the ACARS to transmit and receive messages.By automatically transmitting routine messages, the ACARS reduces crewworkload. Also, lengthy voice transmissions to communicate with theground are reduced with the ACARS.The airborne ACARS system is used to transmit and receive data or mes-sages. Messages for transmission can be generated automatically or can beinput manually by crewmembers.The ACARS will then properly tune and keythe VHF−3 transceiver for the data transmission.The VHF−3 can also be used for voice transmission in the ACARS voice mode of operation. Voice communications can be simplified by use of theACARS. The crew can send a downlink message to request to talk to aparty on the ground. The message can even contain the telephone numberof the party. The ground can then make the arrangements, uplink thefrequency the crew needs to tune in, and command the ACARS to switch auto-matically to voice mode.The ACARS Management Unit (MU) controls all functions of the airborneACARS system. The MU interfaces with many other systems on the airplane.Crew interface to the unit is via the FMC Multi−purpose Control Display Units(MCDU).The MU is installed on the E2−3 electronics shelf. It is fastened to the equip-ment rack by two hooks at the front and a rack and panel connector on therear.A TEST switch and a PASS and FAULT light are located on the front ofthe MU. When the TEST switch is pushed, the unit stops all ACARSfunctions and starts a self−test. The result of the test is reported by lights onthe front of the MU and are also sent to the MCDUs for display.The left and right Multi−purpose Control Display Units (MCDUs) provide theuser interface with the ACARS. When the MENU key on an MCDU is pushed,the <ACARS prompt will be available on that MCDU unless ACARS is beingused on the other MCDU. ACARS can be used on only one MCDU at a time.

Selecting the line select key adjacent to the <ACARS prompt will call up theACARS main menu page. From here, all ACARS functions can be accessed,such as pre−flight initialization, weather requests, system status checks, or linktests.The airplane registration number and the airline ID are hardwire coded at theback of the MU by the shorting receptacle. The registration number is a sevencharacter number and the airline ID a two character code.

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DOOR WARN 28V DC(52−71−00)

M1175 FMC

RSV

CLOSED

CARGODOOR

FWD

DOORSERVICE

DOOR

FWDSERVICE

AFT

AFTCARGODOOR

ENTRYFWD

AFT

DOORENTRY

DOOROPEN

M278 MISC SOLID STATE

SHORTING RCPT (E2−3)

P18−2 LOAD CONTROL CENTER

P8−54 ACMS PRINTER

545352

12

GND

SWITCHING MODULE (E3−2)

GND

AIR

OFF

SET

C3

C1

A3

C2

A2GROUND

A1

(R279)SQUATSENSING

P9−65 MCDU−L

DOOR RELAYR319 EQUIP

ACARS DATA

ACARS DATA

SHELFWIRING

ACARS DATA

LOGIC ZERO SOURCE

AIRLINE I.D. ALPHAAIRPLANE TYPE /

PRINTER STATUS

FMC DATA

CDU−L INPUT

OUTPUT BUS 1

SUPPLYPOWER

TX/RX DATA

(E11)LANDING GEAR LOGIC SHELF

(R274)BRAKEPARKING

OPEN OPEN

ACCESS DOORSW (STA 240)ACCESS DOORS196 FWD

SW (STA 338L)

S197 ELEX

VOICE GO−AHEAD ANNUNCIATOR LIGHT

ACARS MODE INPUT COMMAND

FMC−02 DATA

P8 CAPT (F/O,OBS) AUDIO SELECTORPANEL

FMC−02

M411 VHF−3 XCVR

ACARS DATA

VHF−3 PTTVOICE GO−AHEAD ALERT RESET

ACMS DATA

CDU−R INPUT

OUTPUT BUS 2

M675 DFDAU

ACARS DATA

ACARS DATA

ENABLE DISCRETE

P23−13 AIRBORNE DATA LOADER

DATA LOADER ENABLE

M1109 ACARS MANAGEMENT UNIT (E2−3)

FREQ PORT SELECT

DATA IN

VHF−3 INDICATOR LIGHT

+28V VOICE GO−AHEAD CONTACT HI−LOCHIME

M315 AURAL WARN MODULE

AUTO/MANUAL CHANGEOVER

REMOTE VOICE/DATA SWITCHPROGRAM PIN COMMON DEDICATED ACARS INPUT

VOICE/DATA OUTPUT COMMAND

P8 VHF−1 (−2,−3) CONTROL PANEL

VHF−3 CONTROL DISCRETES

DATA KEYLINE

VOICE/DATA SELECT

DATA KEYLINE RETURN

28V DCHOT BAT BUS ACARS DC

115V ACBUS 1

FREQUENCY SELECT PORT A

DATA OUT

ACARS AC

ON/OFF SENSOR

TUNING DATA

M1353 REMOTE ELECTRONICS UNIT

P9−66 MCDU−R

IN/OUTSENSORS

ACARS DATA DATADATA LOADER

(PRESENTLY NOT USED)

(not used)

(not used)

AIRPLANE REGISTRATION

(DFDAMRU)UTC (TIME)

Page: 57Figure 33 ACARS INTERFACE DIAGRAM

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OPERATIONAL DESCRIPTION

When the ACARS is not transmitting a message, it monitors the data frequencythrough the VHF−3 transceiver for messages from the ground. The systemrecognizes messages intended for the airplane in which it is installed by theaddress of the message. Each message has a 7 character address, which canbe either the registration number or the flight number. The airplane’s registra-tion number is provided by the ACMS system (DFDAMRU). The flight numberis entered into the FMS system by the crew before each flight. The ACARSwill only process messages that have the correct registration or flight number.Confirmation of messages Every message will contain an ”ACK” (acknowledge) character or a ”NAK”(no acknowledge) character. which notifies the transmitting station of the suc-cess of the previous message reception. The ”ACK” is generated when a valid address for the receiving terminal is re-ceived and a good block check sequence was performed. The ”NAK” is generated when a valid address was received and a bad blockcheck sequence was performed. The exception to this is when the receivingterminal is the ground−processor and the operating mode is the demandmode. In this case the ground−processor will have no response to a bad blockcheck sequence.

Operational ModesThe airborne ACARS system operates in conjunction with the ground−baseddata processors. The two primary modes of operation are the demand modeand the polled mode. Two additional modes of operation are the off modeand the failed mode.(1) Off Mode

− ACARS is in the off mode when 115v ac is removed from AC Bus 1 orwhen the ACARS AC circuit breaker is opened.

− As long as 28v dc Hot Bat Bus power is available to the MU through theACARS DC circuit breaker, essential RAM memory will be retained andthe UTC (GMT) clock will continue to operate.

(2) Demand Mode − The MU adopts the demand mode of operation from the off mode upon

application of 115v ac power. − In the demand mode, the MU will initiate a downlink for each of the fol-

lowing conditions:

(3) Polled Mode − The MU enters the polled mode of operation when commanded to do so

by the ground station. − In the polled mode, the MU will downlink data only when requested

(polled) by an uplink from the ground station. The ground station pollsan aircraft periodically (at most once every 2 seconds). If the MU has amessage in memory for downlink, it will initiate a transmission.

− The polled mode is used in areas of heavy ACARS traffic so that theground station will be available equally to all aircraft that use the service.

− The MU will exit the polled mode and return to the demand mode underone of the following conditions: � When commanded to do so by an uplink. � When the ON event occurs. � When 1.5 minutes has passed without a poll from the ground station.

(4) Failed Mode The MU continually runs tests to using Built−In Tests (BIT). The tests are de-signed to most failures. When a failure is detected an MCDU indication is acti-vated. Message Format

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VHF−3 Transceiver; � The MU encodes the digital data for transmission as a series of 1200 Hz

and 2400 Hz tones at 2400 baud (future ACARS systems may operate with2400/4800 Hz at 4800 baud). A 1200 Hz tone indicates a bit change fromthe previous bit (0 to 1 or 1 to 0) while a 2400 Hz tone indicates no bitchange (0 to 0 or 1 to 1).

� The MU supplies the tuning word to the VHF transceiver on port A of thetransceiver. The tuning word is in the 32 bit ARINC 429 format.

� The MU grounds the voice/data select line of the VHF transceiver.� The port select discrete between the MU and the transceiver is grounded by

the MU when it is in data mode. This selects port A of the transceiver asthe source for the tuning word, thereby allowing the MU to control the datafrequency tuning. In VHF 3−voice mode, the MU will open the port selectdiscrete to allow tuning by port B only as the VHF control panel has to tunethe transceiver to the voice frequecncy.

Radio Communication Panels;� The port select discrete to the VHF−3 transceiver is also connected to the

Radio Communication Panels . When grounded, the ACARS indication willshow in the active display of the control panel that is selected to the VHF−3transceiver, indicating that the MU has control of the tuning.

� A discrete from the VHF control panel allows for remote voice/data switch-ing. When VHF 3 is in voice mode and the display transfer button on theactive ACARS control panel is pushed, ACARS will change to data modeand the ACARS indication will move to the active display.

Aural Warning Module;� A voice−go−ahead discrete from the MU to the aural warning module pro-

vides the pilot with a chime to notify the pilot when a VOICE CONTACT−message is received .

� Automatically with the occurance of pre−defined events. These in-clude OOOI times and certain Aircraft Condition Monitoring System(ACMS) reports. The pre−defined events can be changed by soft-ware.

� Manually by crew request. � In response to uplink messages which require a response.

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23-27


LOCATION

OFF SWITCH

OFF SIDE

CONTROL LIGHT

(WHITE)

FREQUENCY

SELECTOR

KNOBS

CENTER VHF RADIO

SELECTOR SWITCH

TRANSFER SWITCH

ACTIVE/STANDBY

RADIO CONTROL PANEL

ACARS

FREQUENCY

ACTIVE

DISPLAY

FREQUENCY

STANDBY

DISPLAY

LEFT, RIGHT, OR CENTER CONTROL

DISPLAY UNIT

ACARS MANAGEMENT UNIT, B7062

MENU

<ACMS

<ACARS

<FMC

3 K

INIT

7

. DELZ

XWVU

SRQP

NML

IHGF

DC

+/−0 /

LIAF

LPSD PAGE

NEXTPAGEPREV

MENU PROGHOLDLEGS

FIX

EXECARRDEP

RTEREF

5

98

64

21

SP

BA

O

T

Y

O

J

E

CLR

TSF

GSM

BRT

MENUKEY

LINESELECT

KEY

CRZCLB DES

N1LIMIT

Page: 60Figure 34 ACARS COMPONENTS

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LEFT, RIGHT, OR CENTER CONTROL

DISPLAY UNIT

MENU

<ACMS

<ACARS

<FMC

3 K

INIT

7

. DELZ

XWVU

SRQP

NML

IHGF

DC

+/−0 /

LIAF

LPSD PAGE

NEXTPAGEPREV

MENU PROGHOLDLEGS

FIX

EXECARRDEP

RTEREF

5

98

64

21

SP

BA

O

T

Y

O

J

E

CLR

TSF

GSM

BRTCRZCLB DES

N1LIMIT

SEE A

SEE A

RIGHT CONTROL

LEFT CONTROL

B

A

LEFT, RIGHT, OR CENTER RADIO CONTROL PANEL

P8 PANEL

FLIGHT COMPARTMENT

LEFT, RIGHT, AND

P9 PANELCENTER RADIOCONTROL PANEL

BSEE

DISPLAY UNIT, M7440

DISPLAY UNIT,M7439

ACARS MANAGEMENT UNIT, B7062

C

EQUIPMENT RACK E2−3ELECTRONICMANAGEMENT UNIT,

SEEC

DATA LOADER(MULTI PURPOSEDISK DRIVE UNIT)

DATA LOADERSELECTPANEL:ONLY737−300THRU EA

Page: 61Figure 35 ACARS COMPONENT LOCATION

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DATA LOADING

The task is this procedure is the installation of the ACARS software into themanagement unit.� 1. Select ACARS position on the ADL selection panel.� 2. Insert the diskette with the ACARS customer database into the ADL.� 3. Make sure the RDY light comes on approximately five seconds.� 4. Make sure the PROG light comes on approximately three seconds after

the RDY light goes on.� 5. Make sure the COMP light comes on. This is an indication that the soft-

ware is installed.Set the selector switch to NORMAL position on the ADL selection panel. Pushthe EJECT button on the data loader. Remove the diskette.Make sure the software part-number on the ACARS maintenance page is cor-rect, that means this P/N agree with the P/N at the diskette.

DISKETTEN - LABEL

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ACARS

DATA LOADERSELCTOR PANEL FOR PORTABLE

ALTERNATE WAY OF DATALOADING IF AIRBORNE DATA LOADER, DATA-LOADER SELECTPANEL IS NOT IN-STALLED OR INOP.

ADL DOOR OPENADL DOOR CLOSED

ACARS MU

PORTABLE DATALOADERRECEPTACLE (COCKPITLH ABOVE OBS. SEAT)

AIRPLANES WITHOUTAIRBORNE DATA LOADER

AIRPLANES WITHINSTALLED AIRBORNE DATALOADER

PORTABLE DATA LOADER

AIRBORNE DATA LOADER (ADL)

Page: 63Figure 36 ACARS DATA LOADING

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MCDU OPERATION MENU

You obtain the ACARS ERROR LOG page on this way:ACARS PRFLIGHT MENU, −−> MISC, −−> MAINT, −−> STATUS, −−> ER-ROR LOG.

ACARS ERROR LOGCLASS 1,2, und 3 FAULTS:The failure with the highest priority occurs at first.

LSK2 L −Zeile: Failure description (LEG, DATE,UTC)LSK3 L −Zeile: Fault Message TextLSK5 L−Zeile: Troubleshooting Message TextLSK5 R−Zeile: Failure-Count

GROUND FAULTSFailure, oocurs on ground. Failures excist after the landing.

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< ACARS MENURETURN TO

ACARS MAINTENANCE

<PARTNUMBERS

<STATUS<TEST<COMM

ACARS STATUS

<ERROR LOG

<RCV 429 DATA<TX 429 DATA

<LRU

<DISCRETES


MENU

<ACMS

<ACARS

<FMC (ACT)

INIT

MENU PROGHOLDLEGS EXECARRDEP

RTEREFBRTCRZCLB DES

ACARS PREFLT MENU 1/2

<REPORT

<REPORT

<TELEXVOICE

CONTACT>RECEIVEDMESSAGES>

<REPORT

FPL DATA

REFUELING

LOAD DATA

<MISC

REQUEST>

REQUEST>

ATIS

WEATHER

ACARS MISC

< FREQUENCY

< STATUS

MAINT>

DISPLAY >

STATISTICS >

STATISTICS >

< ACARS MENU

DATA

OOOI

RETURN TO

VHF

SATELLITE

PARAMETER

ACARS ERROR LOG 1/3CLASS 1 AND 2 FAULTS

AC REG=. D−ABIBLEG DATE UTC ATA CLS008 FEB 03 1424 24000 1

POWER SUPPLY INTERRUPTACARS PWR IN FLTADDR COUNTGECE: 007E*

RETURN TO<ERROR MENU

1

PRINT>

ACARS ERROR LOGCLASS 1 AND 2 FAULTS

<FAULTSCLASS 3

GROUND

3

0

0

<FAULTS

<FAULTS

<STATUS MENU PRINT>RETURN TO

Page: 65Figure 37 MCDU PAGES: ERROR LOG, FAULTS

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ACARS FREQUENCYThis page shows the active ACARS frequency - default is Europe with the fre-quency of 131.725 MHz. Any other ACARS frequency is selectable by LSK.The character before the frequency value means:− A: −automatic selection− M: −manually selected− S: −selected by acars ground station− D: −selected by acars ground station

The message AUTO/MAN FREQ MISMATCH appears in the Scratch Pad ,when the manually selected artea doesn’t agree with the FMC PPOS.Is a PPOS not available, the message NO LAT/LON, USE MAN FREQ ap-pears.

TESTOn Maintenance Page you get access to the TEST page. On the associatedRCP you can see the message ACARS in the active frequency window. Thatmeans the ACARS MU is connected to the VHF-3 transceiver.� LINK TEST: This function activates a Downlink (DL) to test the link to a

ground station. Push LSK 1L to activate the test. During the testprocedure,TEST is indicated. If the link is possible, PASS is shown. If there is no con-nection to a ground station, FAIL is shown. The message INITIATE appearsabout 5 s after the end of the test.

� PRINTER TEST: This function activates a test printout on the printer.� COM AUDIT: this function can be switched ON and OFF. If the function is

ON, a status report is printed, when a DL or a Uplink (UL) is activated.� MCDU TEST: This function shows a test indication on the MCDU screen.� RAM TEST: This function activates internal RAM testing. Indication is PASS

or FAIL.

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MENU

<ACMS

<ACARS

<FMC (ACT)

INIT

MENU PROGHOLDLEGS EXECARRDEP

RTEREFBRTCRZCLB DES


<REPORT

<REPORT

<TELEXVOICE


ACARS DATA FREQA131.725

< EUR/OTHERS

<ASIA/AUS

<JAPANN−AMERICA>

AUTOMATIC

<REPORT

FPL DATA

REFUELING

LOAD DATA

<MISC

REQUEST>

REQUEST>

ATIS

WEATHER


<TELEXVOICE

CONTACT>RECEIVEDMESSAGES><MISC

<REQUESTPILACARS MISC

< FREQUENCY

< STATUS

MAINT>

DISPLAY >

STATISTICS >

STATISTICS >

< ACARS MENU

DATA

OOOI

RETURN TO

VHF

SATELLITE

PARAMETER



ACARS MAINTENANCE

<PARTNUMBERS

<STATUS<TEST<COMM



ACARS TEST 1/2

ACARS TEST 2/2

< INITIATE

< INITIATE

< INITIATE

< COM AUDIT

NO SDU

NO SDU

MCDU TEST>

INITIATE>

VHF LINK

PRINTER

SAT LINK

SDU

RAM TEST

NO TEST

NO LRU

NO LRU

NO LRU

ACMS

CABIN 1

SPARE 5

CABIN 21

1

<− FMC

Page: 67Figure 38 MCDU PAGES: FREQ., TEST

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23-27


ACARS MAINTENANCEOn Maintenance Page you get access to the following functions: PARTNUM-BERS−, STATUS−, COMM Status−and TEST−Pages.

ACARS PARTNUMBERThis page shows all part numbers of the system (hardware and software). Thesoftware partnumbers actually in the system and the information on the dis-kettes must be the same.

ACARS LRU STATUSShows all systems connected to the ACARS MU. Active systems are labeledACTIVE, inactive systems are labeled INACTIVE.

ACARS COMM STATUSShows ACARS COMM status via VHF or SAT ( LSK 1L/ LSK 1R)� LSK 2L: COMM or NO COMM� LSK 3L: DATA or VOICE mode� LSK 4L: count of unsent DL‘s

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ACARS MAINTENANCE

<PARTNUMBERS

<STATUS<TEST<COMM


ACARS PARTNUMBERS

965−0728−001

963−0001−02

998−1385−501

998−2006−503

0316MU HW P/N

DISK PN

CORE SW P/N

APP SW P/N

DB P/N998−1375−501

PRINT >

MU S/N

REVA

REVA

REVA

ACARS STATUS

<ERROR LOG

<RCV 429 DATA<TX 429 DATA

<LRU

<DISCRETES


RETURN TO

ACARS LRU STATUS 1/3FMC ACTIVEPRINTER ACTIVEACMS ACTIVESPARE 1 NOT INSTALLEDSPARE 2 NOT INSTALLEDMCDU L ACTIVESPARE 3 NOT INSTALLEDFMC 2 ACTIVE

PRINT>

RETURN TOPRINT>

RETURN TOPRINT>

ACARS LRU STATUS 2/3 ACARS LRU STATUS 3/3SPARE 4 NOT INSTALLEDMCDU R ACTIVECABIN 1 NOT INSTALLEDSPARE 5 NOT INSTALLEDSDU 1 NOT INSTALLEDMCDU C NOT INSTALLEDCABIN 2 NOT INSTALLEDSPARE 6 NOT INSTALLED

RCP INACTIVESPARE 8 NOT INSTALLEDADL NO 429 DATASPARE 9 NOT INSTALLED

< STATUS MENU

< STATUS MENU < STATUS MENU

< MAINT MENURETURN TO

PRINT>

ACARS COM STATUS

VHF (OP)

COMMDATA

(OP) SAT

NO COMM

UNSENT DOWNLINKSVHF ROUTER SAT000 000 000

Page: 69Figure 39 MCDU PAGES: ACARS MAINTENANCE

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737−300/400/500

23-27


MU RESETOn the ACARS MAINTENANCE PAGE, you have to insert a special passwordand press LSK 6R. This will show the ACARS DEBUG page 1. On page 2, youwill find the box-prompts MU RESET.If the word RESET MU is entered in SP and LSK 6R is pressed, a COLDSTART is activated - system reinitialisation !WARNINGPressing the test knob at the MU initiates also a MU-coldstart. This resets alldata the MU is presently working with, including datas entered via the MCDU.Before you carry out the MU RESET, note the QTY BEFORE fuel data on theACARS REFUELING REPORT PAGE. After MU RESET, enter this value intothe SP (without point) and press the LSK 1R on the MCDU.Nach Aufruf der REFUELING REPORT Seite wird mittels der MCDU Tastender alte QTY BEFORE Wert, (abgelesen vor dem Reset der MU), ohne Kom-mastelle in das Scratch Pad eingegeben und mittels LSK 6R auf das entspre-chende Feld gesetzt.

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ACARS MAINTENANCE

<PARTNUMBERS

<STATUS<TEST<COMM


PRINT>


PRINT>

ACARS DEBUG 1/2

ACARS DEBUG 2/2

<VHF<MEMORY DUMP

<PRINTER<MCDU<SDU

FMC>

SPARE 2>

ACMS>SPARE 5>CABIN 1>

<SAT

<BIT<VERSION

M U R E S E T

PRINT >< ACARS MENURETURN TO

ACARS REFUELING REPORTSUPPLY VOL( )UNITSLTDENSITY0.800SUPPLIER( )

BEFORE( )

SUPPLIED−−−− −

FOB3.9

FUEL DIFF−−−− −

SAM

TYPE ’SAM’ INTO THE SCRATCHPADAND PRESS LSK 6R

RESET MU

TYPE ’RESET MU’ INTOTHE SCRATCHPAD ANDPRESS LSK 6R


<REPORT

<REPORT

<TELEXVOICE


<REPORT

FPL DATA

REFUELING

LOAD DATA

<MISC

REQUEST>

REQUEST>

ATIS

WEATHER

Page: 71Figure 40 MCDU PAGES: MU RESET, REFUELING REPORT

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23-27


ACARS MU FRONTPANEL TEST

After installation, correct operation of the ACARS MU can be checked by usingthe following controls located on the MU frontface:PASS/FAULT indicator lightsIn normal operation, the lights indicate the actual status of the ACARS MU. Intest mode, after a 3s indicator light test, the lights indicate the test result.7 SEGMENT LEDIf a test is activated and a failure is detected, the LED shows a fault code. Ex-amples:� 3: A/C registration missed (the MU did not receive the A/C registration)� 2: A/C type mismatch (the A/C type defined in software is different to the pin

program information)� 1: bad H/W part number (the MU partnumber and the pin program informa-

tion is different)TEST pushbuttonWhe pressing the test pushbutton switch:� a ACARS MU ”Cold Start” is initiated.� the LRU PASS and FAULT lights come on for 3s approximately to indicate

correct operation.� the red FAULT light goes off to indicate, that no fault is present. If the red

FAULT light remains on and the green light goes off, the system is faultyand shows a fault code on the LED.

WARNINGPressing the test knob at the MU initiates a MU-coldstart! This resets all datasthe MU is presently working with, including datas entered via the MCDU!!!/Additional programming is lost!). See also ACARS MU RESET!!! ACARS

MU

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MAINTENANCE TIPS / TROUBLESHOOTING

MCDU Message: NO COMM� Description: The message NO COMM appears at the scratchpad on the

MCDU.� Status: A display of NO COMM does not necessarily indicate an aircraft

failure. It does indicate that the data-link air/ground network was not com-pleted. This can be the result of ground station problems or aircraft failures.The ACARS transmits over the VHF-3 system. If this system is inoperative,or the VHF path betweeen the airplane and the ground station is blocked,the system will go NO COMM.

� Att. Maint.:− Perform a CB-reset.− Perform a LINK test at the ACARS test page.− Check the frequency at the ACARS frequency page. Make sure that

ACARS is set to the correct data link frequency ( Europe: 131,725 Mc).− Set ACARS in the VOICE mode. At the standby window of the RCP ap-

pears ACARS and at the scratchpad of the MCDU appears ACARSVOICE. Check the quality of the voice-connection with the ground opera-tor.

− Perform a ACARS MU RESET at the DEBUG Page 2/2.

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COMMUNICATIONCOCKPIT VOICE RECORDER

737−300/400/500

23-71

Page: 74HAM TS 32 Kn 30.06.94

23-71 VOICE RECORDERGENERAL The voice recorder system records and preserves a continuing record ofthe latest 30 minutes of flight crew communications and conversation.The voice recorder system has four inputs for simultaneous recording ofall communications in the flight compartment on four track tape. Channelone receives audio from the first observer’s audio selector panel, channel tworeceives audio from the first officer’s audio selector panel and channel threereceives audio from the captain’s audio selector panel. Channel four audio istaken from a microphone in the voice recorder control panel.The voice recorder system consists of a recorder unit installed on theright side of the airplane in the aft cargo compartment; a control panelinstalled in the pilots’ overhead panel P5; interconnecting wiring; and relay con-tacts in the landing gear accessory unit Module M338.An erase head in the recorder automatically erases previously recordedinformation prior to recording. A 30−minute length of closed loop magnetictape provides a record of the previous 30 minutes of conversation. An internalmonitoring circuit ensures proper operation of the recording mechanism andcircuits. Audible and visible indications derived from the monitoring circuits arepresented at a meter and a jack on the control panel when the test switch onthe control panel is operated. The entire tape may be erased after the airplanehas landed and the parking brake has been set.An Underwater Locating Beacon (ULB) that is not part of the underwaterlocating system is installed on the front panel of the voice recorder.The ULB is an acoustic beacon that energizes when it is immersed inwater, thereby assisting to locate the recorder in case of an accident over theocean or other body of water. Three types of ULB are in service. One type (theN15F210B) is powered by a replaceable battery.The second type (DK100) ispowered by a replaceable battery, but must be returned to the vendor for bat-tery replacement or for disposal. The third type (Datasonics ELP−362) is pow-ered by a replaceable battery.Operating power for the voice recorder system is 115 volts, 400 Hz ACobtained from the unswitched electronics bus through the VOICE RECORDERcircuit breaker on the P18 panel.

OPERATIONThe voice recorder system automatically records the latest 30 minutes ofcommunications and conversation in the flight compartment. The system isin operation whenever 115−volt AC power is applied to AC bus No. 1.Communications and interphone audio from the first observer’s, the firstofficer’s and the captain’s audio selector panels is applied to channel1 through 3 respectively of the voice recorder. Conversation in the flightcompartment is picked up and amplified by the microphone and preamplifier inthe voice recorder control panel and applied to channel 4.The playback head and monitor amplifier are used to monitor informationrecorded on all tracks of the tape. The audio output of the monitor amplifier isavailable at the MONITOR jack on the front panel of the voice recorder and atthe HEADSET jack on the voice recorder control panel. This audio is suppliedto the test meter on the voice recorder control panel. On the Fairchild VoiceRecorder Model A100, the audio also supplies input to the meters on the frontof the voice recorder.Self test for Fairchild Voice Recorder Model A100Pushing the TEST pushbutton on the voice recorder control panel causes thetest module to apply a 600−Hz signal to each channel in sequence, therebytesting all channels. If they are functioning properly, the control panel meterreads in the green area and a modulated sound is present at both jacks.The ALL TEST switch on the front panel of the cockpit voice recorderoperates the same test as the TEST pushbutton on the voice recordercontrol panel.On the front panel of the cockpit voice recorder are test switches for testingrecording channels 1 through 4 individually.To initiate a test for an individualchannel, push the test switch on the face of the cockpit voice recorder for theparticular channel number.This individual channel test causes the test moduleto apply a 600 Hz signal to the channel being tested.The bulk erase module contains timing, relays, and erase circuits whichapply 115 volts, 400 Hz AC to the erase coil in the tape transport. Thebulk erase circuits erase all audio on the recorder tape within ten seconds afterthe ERASE switch on the control panel is released. The bulk erase circuits willfunction only when the airplane is on the ground and the parking brake is setbecause the control circuit must be completed through relay K4 in the landinggear accessory unit module

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Page: 75HAM TS 32 Kn 30.06.94

TEST

PARKING BRAKE SET

FLIGHT

SYSTEM

CHANNEL 1

CHANNEL 2

CHANNEL 3CAPTAIN

RECORDINGAMPLIFIERS

RECORDING HEADS

ERASE

BULKERASE

POWERSUPPLY

PREAMP

TESTMETER

TEST

MONITORAMPLIFIER

VOICERECORDER

VOICE RECORDER UNIT

OBSERVER

PLAYBACK

TAPE TRANSPORT(PROTECTED)

MODULE(600 Hz)

CHANNEL 4AREA MIC

INTERPHONEFIRST OFF

MIC

P5 OVERHEAD PANEL

ERASE

TEST

TOINTERNALCIRCUITS

BULKERASE

P18−2

115V ACUNSWITCHEDELECTRONICSBUS

MONITORJACK

LANDING GEAR LOGIC SHELF E11

TESTMETER

ALL1

2

3

4

1

VOICE RECORDER UNIT MODEL A100 ONLYTEST SWITCHES FOR FAIRCHILD1

~

PLANE ON GROUND

MONITORJACK

Page: 75Figure 41 VOICE RECORDER BLOCK DIAGRAM

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Page: 76HAM TS 32 Kn 30.06.94

LOCATION

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23-71

Page: 77HAM TS 32 Kn 30.06.94

DOOR

AFT CARGO

SEEA

VOICE RECORDERLOAD CONTROLCENTER P6

OVERHEADPANEL P5

SEE B

UNDERWATER

LOCATING

DEVICE (ULD)

HEADSET

JACK

4

ALL

MONITOR600 OHMS

3

2

1

TEST

MODIFICATIONS

UNDERWATER

LOCATOR

BEACON (ULB)

TEST

SWITCHES

CONTROL UNIT

B

COCKPIT VOICE RECORDER

TEST ERASE

HEADSET600 OHMS

AA

FAIRCHILD VOICERECORDER MODEL A100A

FAIRCHILD VOICERECORDER MODEL A100

Page: 77Figure 42 VOICE RECORDER / Component Location

TABLE OF CONTENTS

B737−3 23 B1 E

Page iFRA US/T-4 Kotzan Jun 2005

ATA 23 COMMUNICATION 1. . . . . . . . . . . . . . . . . . . .

23-00 GENERAL 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-50 AUDIO INTEGRATING 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUDIO SWITCHING 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUDIO CONTROL PANEL 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIG. 2 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-51 FLIGHT INTERPHONE SYSTEM 12. . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OXYGEN MASK MICROPHONES 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPONENTS AND LOCATION 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-41 SERVICE INTERPHONE 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-43 FLT/GRD CREW CALL 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-31 PASSENGER ADDRESS (PA) 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAPE REPRODUCER 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PA - AMPLIFIER / TEST 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23 - 21 RADIO COMMUNICATION PANEL 40. . . . . . . . . . . . . . . . . . . . . . . . GENERAL 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23 - 21 VHF - COMMUNICATION 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION (VHF - 700 COLLINS) 42. . . . . . . . . . . . . . . . . . . . . . . . . . . .

LOCATION 44. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FRONTPANELTEST (VHF−700) 46. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION (RTA-43A BENDIX) 48. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-22 SELCAL 50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELCAL DECODER 52. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 54. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

23-27 ACARS 56. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 56. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATIONAL DESCRIPTION 58. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 60. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DATA LOADING 62. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCDU OPERATION MENU 64. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACARS MU FRONTPANEL TEST 72. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTENANCE TIPS / TROUBLESHOOTING 73. . . . . . . . . . . . . . . . . . .

23-71 VOICE RECORDER 74. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GENERAL 74. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPERATION 74. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCATION 76. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TABLE OF FIGURES

B737−3 23 B1 E

Page iiFRA US/T-4 Kotzan Jun 2005

Figure 1 ANTENNA-LOCATION 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 2 ELECTRONIC-EQUIPMENT-COMPARTMENT 3. . . . . . . Figure 3 DIGITAL AUDIO CONTROL SYSTEM / Schematic 5. . . . Figure 4 AUDIO INTEGRATING / Locations - Forward View 6. . . . Figure 5 AUDIO INTEGRATING / Locations - AFT View 7. . . . . . . . Figure 6 AUDIO CONTROL PANEL ( config. 1 ) 9. . . . . . . . . . . . . . . Figure 7 AUDIO CONTROL PANEL ( config. 2) 11. . . . . . . . . . . . . . . Figure 8 AUDIO INTEGRATING / System Schematic 13. . . . . . . . . . Figure 9 FLIGHT INTERPHONE ACTIVATION ON ACP 15. . . . . . . Figure 10 OXYGEN MASK MIKE OPERATION 17. . . . . . . . . . . . . . . Figure 11 FLIGHT INTERPHONE / Components 18. . . . . . . . . . . . . . Figure 12 FLIGHT INTERPHONE SYSTEM / Location 19. . . . . . . . . Figure 13 SERVICE INTERPHONE SCHEMATIC 21. . . . . . . . . . . . . Figure 14 SERVICE INTERPHONE / Component Location 22. . . . . Figure 15 SERVICE INTERPHONE / Jacks Location 23. . . . . . . . . . . Figure 16 CALL SYSTEMS / Config. 1 25. . . . . . . . . . . . . . . . . . . . . . . Figure 17 CALL SYSTEMS / Config. 2 27. . . . . . . . . . . . . . . . . . . . . . . Figure 18 CALL SYSTEMS / Component Location 29. . . . . . . . . . . . . Figure 19 PA SYSTEM SCHEMATIC 1 31. . . . . . . . . . . . . . . . . . . . . Figure 20 PA SYSTEM SCHEMATIC 2 33. . . . . . . . . . . . . . . . . . . . . . Figure 21 PA / Component Location 1 34. . . . . . . . . . . . . . . . . . . . . . . . Figure 22 PA / Component Location 2 35. . . . . . . . . . . . . . . . . . . . . . . . Figure 23 PA / Tape Reproducer 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 24 PA AMPLIFIER 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 25 RADIO COMMUNICATION PANEL 41. . . . . . . . . . . . . . . . . Figure 26 VHF- 700 / Schematic 43. . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 27 VHF - 700 / Locations 45. . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 28 VHF - 700 / Locations 47. . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 29 VHF RTA-43A Locations 49. . . . . . . . . . . . . . . . . . . . . . . . . . Figure 30 SELCAL / BLOCK DIAGRAM 51. . . . . . . . . . . . . . . . . . . . . . Figure 31 SELCAL DECODER 53. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 32 SELCAL / Component Location 55. . . . . . . . . . . . . . . . . . . . Figure 33 ACARS INTERFACE DIAGRAM 57. . . . . . . . . . . . . . . . . . . Figure 34 ACARS COMPONENTS 60. . . . . . . . . . . . . . . . . . . . . . . . . . Figure 35 ACARS COMPONENT LOCATION 61. . . . . . . . . . . . . . . . .

Figure 36 ACARS DATA LOADING 63. . . . . . . . . . . . . . . . . . . . . . . . . . Figure 37 MCDU PAGES: ERROR LOG, FAULTS 65. . . . . . . . . . . . . Figure 38 MCDU PAGES: FREQ., TEST 67. . . . . . . . . . . . . . . . . . . . . Figure 39 MCDU PAGES: ACARS MAINTENANCE 69. . . . . . . . . . . Figure 40 MCDU PAGES: MU RESET, REFUELING REPORT 71. . Figure 41 VOICE RECORDER BLOCK DIAGRAM 75. . . . . . . . . . . . Figure 42 VOICE RECORDER / Component Location 77. . . . . . . . . .

For:batch

Printed on:Tue, Aug 2, 2005 17:09:04

From book:B737-3 23 B1 E

Document:Deckblatt B737-3 J

Last saved on:Tue, Aug 2, 2005 17:07:27

Document:01/ATA_DOC


Document:02/Gen/L1/B1/B2


Document:03/A/I Sys/L1/B1/B2


Document:05/A/I Loc/L1/B1/B2


Document:06/Ctrl/L1/B1/B2


Document:08/Flt.Int./L1/B1/B2


Document:09/Flt.Int Mask/L2/B1/B2


Document:10/Flt.Int Loc/L1/B1/B2


Document:11/Serv. Int./L2/B1/B2


Document:12/Serv.Int Loc/L1/B1/B2


Document:13/Call System/L1/B1/B2


Document:14/Call Sys Loc/L1/B1/B2


Document:15/PA Sys/L1/B1/B2


Document:16/PA Loc/L1/B1/B2


Document:17/PA Tape/L2/B1/B2


Document:18/PA Test/L2/B1/B2


Document:19/RCP/L1/B1/B2


Document:20/VHF SYS/L1/B1/B2


Document:02/VHF Loc/L1/B1/B2


Document:03/VHF Test/L2/B1/B2


Document:04/VHF/L1/B1/B2


pl2ps 7.6.0 Copyright 1993 Interleaf, Inc.

Documents

B737-3 Comunications