Training Manual
B 737-330/430/530
ATA 23
Communication
ATA Specification 104
Level 3
Book No:
B737-3 23
TABLE OF CONTENTS
ATA 23 COMMUNICATION . . . . . . . . . . . . . . . . . . . .
1
23-00 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1
23-50 AUDIO INTEGRATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AUDIO SWITCHING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AUDIO CONTROL PANEL . . . . . . . . . . . . . . . . . . . . . . . . . .
CONFIG. 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ACP DATA WORD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4
4
6
6
10
12
12
14
16
23-51 FLIGHT INTERPHONE SYSTEM . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OXYGEN MASK MICROPHONES . . . . . . . . . . . . . . . . . . .
COMPONENTS AND LOCATION . . . . . . . . . . . . . . . . . . . .
18
18
20
22
24
23-41 SERVICE INTERPHONE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
26
26
26
28
23-43 FLT/GRD CREW CALL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
30
30
30
34
23-31 PASSENGER ADDRESS (PA) . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TAPE REPRODUCER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PA - AMPLIFIER / TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . .
36
36
40
42
44
23 - 21 RADIO COMMUNICATION PANEL . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
46
46
46
23 - 21 VHF - COMMUNICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION (VHF - 700 COLLINS) . . . . . . . . . . . . . . . . . .
DESCRIPTION (VHF-700) . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FRONTPANELTEST (VHF-700) . . . . . . . . . . . . . . . . . . . . .
OPERATION (RTA-43A BENDIX) . . . . . . . . . . . . . . . . . . . .
DESCRIPTION (RTA-43A) . . . . . . . . . . . . . . . . . . . . . . . . . .
48
48
48
50
52
54
56
58
23-11 HF - COMMUNICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION (CONT.) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CALSEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
60
60
62
63
66
68
23-22 SELCAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SELCAL DECODER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
70
70
72
74
23-27 ACARS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATIONAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
REPORTS / REQUESTS . . . . . . . . . . . . . . . . . . . . . . . . . . .
MESSAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
DATA LOADING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
MCDU OPERATION MENU . . . . . . . . . . . . . . . . . . . . . . . . .
ACARS MU FRONTPANEL TEST . . . . . . . . . . . . . . . . . . .
MAINTENANCE TIPS / TROUBLESHOOTING . . . . . . . .
76
76
78
80
83
84
86
88
100
101
23-71 VOICE RECORDER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
102
102
102
104
Page: i
TABLE OF FIGURES
Figure 1
Figure 2
Figure 3
Figure 4
Figure 5
Figure 6
Figure 7
Figure 8
Figure 9
Figure 10
Figure 11
Figure 12
Figure 13
Figure 14
Figure 15
Figure 16
Figure 17
Figure 18
Figure 19
Figure 20
Figure 21
Figure 22
Figure 23
Figure 24
Figure 25
Figure 26
Figure 27
Figure 28
Figure 29
Figure 30
Figure 31
Figure 32
Figure 33
Figure 34
Figure 35
ANTENNA-LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ELECTRONIC-EQUIPMENT-COMPARTMENT . . . . . . .
DIGITAL AUDIO CONTROL SYSTEM / Schematic . . . .
REU SCHEMATIC 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
REU SCHEMATIC 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AUDIO INTEGRATING / Locations - Forward View . . . .
AUDIO INTEGRATING / Locations - AFT View . . . . . . . .
AUDIO CONTROL PANEL ( config. 1 ) . . . . . . . . . . . . . . .
AUDIO CONTROL PANEL ( config. 2) . . . . . . . . . . . . . . .
ACP DATA - WORD . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AUDIO INTEGRATING / System Schematic . . . . . . . . .
FLIGHT INTERPHONE ACTIVATION ON ACP . . . . . .
OXYGEN MASK MIKE OPERATION . . . . . . . . . . . . . . .
FLIGHT INTERPHONE / Components . . . . . . . . . . . . . .
FLIGHT INTERPHONE SYSTEM / Location . . . . . . . . .
SERVICE INTERPHONE SCHEMATIC . . . . . . . . . . . . .
SERVICE INTERPHONE / Component Location . . . . .
SERVICE INTERPHONE / Jacks Location . . . . . . . . . . .
CALL SYSTEMS / Config. 1 . . . . . . . . . . . . . . . . . . . . . . .
CALL SYSTEMS / Config. 2 . . . . . . . . . . . . . . . . . . . . . . .
CALL SYSTEMS / Component Location . . . . . . . . . . . . .
PA SYSTEM SCHEMATIC 1 . . . . . . . . . . . . . . . . . . . . .
PA SYSTEM SCHEMATIC 2 . . . . . . . . . . . . . . . . . . . . . .
PA / Component Location 1 . . . . . . . . . . . . . . . . . . . . . . . .
PA / Component Location 2 . . . . . . . . . . . . . . . . . . . . . . . .
PA / Tape Reproducer . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PA AMPLIFIER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
RADIO COMMUNICATION PANEL . . . . . . . . . . . . . . . . .
VHF- 700 / Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VHF 700 Detailed Schematic . . . . . . . . . . . . . . . . . . . . . .
VHF - 700 / Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VHF - 700 / Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VHF RTA-43A Locations . . . . . . . . . . . . . . . . . . . . . . . . . .
VHF RTA-43A Schematic . . . . . . . . . . . . . . . . . . . . . . . . .
HF - System / Block diagram . . . . . . . . . . . . . . . . . . . . . .
1
3
5
7
9
10
11
13
15
17
19
21
23
24
25
27
28
29
31
33
35
37
39
40
41
43
45
47
49
51
53
55
57
59
61
Figure 36
Figure 37
Figure 38
Figure 39
Figure 40
Figure 41
Figure 42
Figure 43
Figure 44
Figure 45
Figure 46
Figure 47
Figure 48
Figure 49
Figure 50
Figure 51
Figure 52
Figure 53
Figure 54
Figure 55
HFS - 700 Schematic / Transceiver . . . . . . . . . . . . . . . .
HFS - 700 Schematic / Coupler . . . . . . . . . . . . . . . . . . . .
CALSEL - Block diagram . . . . . . . . . . . . . . . . . . . . . . . . . .
HF - System / Location . . . . . . . . . . . . . . . . . . . . . . . . . . .
SELCAL / BLOCK DIAGRAM . . . . . . . . . . . . . . . . . . . . . .
SELCAL DECODER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SELCAL / Component Location . . . . . . . . . . . . . . . . . . . .
ACARS INTERFACE DIAGRAM . . . . . . . . . . . . . . . . . . .
ACARS COMPONENTS . . . . . . . . . . . . . . . . . . . . . . . . . .
ACARS COMPONENT LOCATION . . . . . . . . . . . . . . . . .
ACARS Flight Profile . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ACARS DATA LOADING . . . . . . . . . . . . . . . . . . . . . . . . . .
MCDU PAGES: ERROR LOG, FAULTS . . . . . . . . . . . . .
MCDU PAGES: FREQ., TEST . . . . . . . . . . . . . . . . . . . . .
MCDU PAGES: ACARS MAINTENANCE . . . . . . . . . . .
MCDU PAGES: MU RESET, REFUELING REPORT . .
MCDU PAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
ACARS MCDU-PAGES . . . . . . . . . . . . . . . . . . . . . . . . . . .
VOICE RECORDER BLOCK DIAGRAM . . . . . . . . . . . .
VOICE RECORDER / Component Location . . . . . . . . . .
64
65
67
69
71
73
75
77
80
81
82
87
89
91
93
95
97
99
103
105
Page: ii
Index
COMMUNICATION
GENERAL
B737-300/400/500
23-00
ATA 23
COMMUNICATION
For Training Purposes Only
23-00 GENERAL
Figure 1
FRA US/E nm 9.4.96
ANTENNA-LOCATION
Page: 1
COMMUNICATION
GENERAL
737330-430-530
23-00
For Training Purposes Only
THIS PAGE INTENTIONALLY LEFT BLANK
HAM TS 32 Kn 14.06.94
Page: 2
Index
COMMUNICATION
GENERAL
737330-430-530
For Training Purposes Only
23-00
Figure 2
HAM TS 32 Kn 14.06.94
ELECTRONIC-EQUIPMENT-COMPARTMENT
Page: 3
Index
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
23-50 AUDIO INTEGRATING
GENERAL
For Training Purposes Only
The audio integrating system provides a communication link between the flight
compartment 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. The
position of switches and potentiometers are transmitted digitally from the ACP’s
to the Remote Electronics Unit (REU). Audio from communication and navigation systems and from the audio selector panels are integrated at the REU. Audio 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 interphone system with the capability of controlling the gain of each system. It also
contains a tongenerator for the altitude alert warning and discrete grounds for
the flight recorder.
In case of a failure in the Captains or F/O’s ACP or in the associated REU-circuit audio switching relays allow the connenction to the observer interphone
system.
HAM TS 32 Kn 14.06.94
Page: 4
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
PA AMPL
SERV/ATT
INPH & WARN
AUDIO
SWITCHING
CAPT
FLT INPH
AMPL
F/O
CAPT
SPEAKER
CAPT R/T/INT PTT
ON CONTROL WHL
CABIN/SERVICE
AMPL
DATA BUS & POWER
P6
REMOTE
ELECTRONICS
UNIT
AUDIO
SWITCHING
JACKS
AUDIO
SWITCHING
F/O
SPEAKER
F/O R/T/INT PTT
ON CONTROL WHL
DATA BUS & POWER
RADIO XCVRS &
NAV RADIOS
F/O
ASP
OXY MASK
AUDIO
SWITCHING
JACKS
DATA BUS & POWER
COCKPIT VOICE
RECORDER
For Training Purposes Only
CAPT’S
ASP
OXY MASK
OBS
(E2−1 ELECTRONIC SHELF)
ATTENDANT
HANDSETS
FLT INPH NOSE
WHEEL JACK
Figure 3
OBS
ASP
OXY MASK
AUDIO
SWITCHING
ALT ALERT
SERVICE
JACKS
HAM TS 32 Kn 14.06.94
PA SPEAKERS
JACKS
NOTE:
DETAILS FOR AUDIO SWITCHING
SEE SEPERATE DRAWING
AUX INPUTS
GND PROX
RADIO ALT
DIGITAL AUDIO CONTROL SYSTEM / Schematic
Page: 5
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
DESCRIPTION
OPERATION
Remote Electronics Unit
The remote electronic unit (REU) is a digitally controlled, multiplexed audio
management unit. The REU manages the communication between the flight
deck stations, service and flight interphone, and all related communication, radio, navigation, and recorder system. The REU determines which selections
have been made on the ASP, and then sends appropriate signals to the selected systems.
General
All audio inputs from the flight interphone system, service interphone system,
radio communication systems, and radio navigation systems are connected
directly to the remote electronics unit where they are processed into multiplex
channels. The flight crew can then use their audio selector panels to select the
multiplex channel they wish to hear on their headphones or headsets. They can
also connect the PA channel to the passenger address amplifier.
The flight interphone system hand held, boom, and oxygen mask microphones
provide the microphone audio inputs from the flight crew to the remote electronics unit. The MIC SELECTOR switches on each audio selector panel determine which one of the communication or interphone systems will receive the
microphone input for transmission. All audio selector panels functions are connected in parallel to the REU. The same communications are monitored by all
flight crewmembers.
The REU accepts boom microphone, oxygen mask microphone, and handheld microphone inputs, and provides output to the flight compartment headphones and speakers. The REU contains service interphone, flight interphone
and speaker amplifiers to provide the necessary audio amplification between
stations. The REU routes ground proximity warnings and internally generated
altitude alert tones to the speakers.
Any audio, selected on the ASP, will be recorded on the voice recorder for each
crew member.
The REU contains:
S Three identical station cards for captain, first officer and observer. The station cards provide response to inputs from three audio selector panels.
S One audio accessory unit (AAU) card which contains circuitry for an altitude
alert warning tone, flight and service interphone, and various audio accessory functions.
S One mother board which contains and provides interconnection for the
captain’s, first officer’s and observer’s station cards and AAU card.
S One connector card which provides an interconnection between the external
connector and the mother board. The outside of the REU case contains
several screw adjustments. These are designed for in-shop test station adjustment only and should not be adjusted on the airplane. Power to the REU
is 28V dc dual power sources (battery bus and Bus No. 2). The REU provides dc power to the ASPs.
For Training Purposes Only
Radio Inputs
Audio inputs are provided from each of the communication radio receivers and
from each of the navigation radio receivers.
FRA USE NM
25.01.1996
Page: 6
Index
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
A
D
E
H
J
K
C
For Training Purposes Only
L
M
N
O
P
Q
Figure 4
FRA USE NM
25.01.1996
REU SCHEMATIC 1
Page: 7
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
Audio Outputs
Audio outputs from the remote electronics unit are provided to each flight crew
station and to the external power panel. One output is for the boom microphone/headsets and one output is for the headphone jacks.
Two audio outputs are used to drive the pilot’s overhead speakers.
Amplifiers in the remote electronics unit provide the drive for the audio outputs.
There are two audio amplifiers in the remote electronics unit;
S one used with the flight interphone and
S one used with the service interphone.
External volume control adjustments are installed for each of the amplifiers.
DLH airplanes with a BOOM/OXY switch;
the pilot overhead speaker is muted whenever a microphone is keyed from the
same pilot position (left or right) except when the pilot audio selector panel
BOOM/OXY switch is in the OXY position.
DLH airplanes without a BOOM/OXY switch;
the boom and the oxygen mask microphones are paralleled. If the boom microphone is in use the pilot’s speakers are automatically muted. When the oxygen
mask is in use, the pilot’s speakers are not muted. This action is controlled
from the PUSH TO TEST AND RESET switch on the oxygen mask stowage box.
Cockpit Speaker Volume Control
The captain’s and the first officer’s interphone speaker is turned on or off by a
switch on the flight crewmember’s audio selector panel. The audio output from
the speaker is adjusted to a comfortable listening level with this volume control
on-of f switch.
Communication between Flight Deck and Ground Service Crew
Ground crew personnel access the flight interphone system by plugging a
handset into the FLIGHT INTERPHONE jack on external power receptacle
panel P19. This allows the ground crew to communicate with the flight crew.
For Training Purposes Only
Synthesized Audio
A voice synthesizer will provide the altitude alert audio messages when triggert
by the altitude alert system.
A two wire input is provided to receive the audio warning tone from the ground
proximity warning system.
Radio Navigation Identification
A filter in the REU is installed to remove the NAV and ADF audio code identification signal from the voice messages. When the VOICE ONLY switch on a
flight crewmember’s audio selector panel is engaged, the filter is connected
and will remove the 1020 Hz coded identification signals, leaving the broader
voice spectrum essentially unchanged for that crewmember’s NAV and ADF
audio input.
FRA USE NM
25.01.1996
Page: 8
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
For Training Purposes Only
23-50
OUTPUTS
Figure 5
FRA USE NM
25.01.1996
REU SCHEMATIC 2
Page: 9
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
For Training Purposes Only
LOCATION
Figure 6
HAM TS 32 Kn 14.06.94
AUDIO INTEGRATING / Locations - Forward View
Page: 10
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
For Training Purposes Only
23-50
Figure 7
HAM TS 32 Kn 14.06.94
AUDIO INTEGRATING / Locations - AFT View
Page: 11
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
AUDIO SWITCHING
The observer’s audio selector panel can be substituted for either the captain’s
or the first officer’s ACP using a transfer switch on the P5 panel. This will allow
the captain or first officer to use the observer’s ACP to accomplish all communication 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 process
of the switching over, power is also removed from the primary panel.
AUDIO CONTROL PANEL
GENERAL
The ACP enables the flight crewmembers to transmit and receive on the radio
communication systems, communicate using the flight and service interphone
systems and make announcements over the PA system. Airplane navigation
systems can also be monitered.
Three ACP’s are located in the flight compartment.
For Training Purposes Only
ACP ( XA - XU )
This ACP has a BOOM/OXY select switch. The BOOM/OXY select switch is a
two-position locking toggle. The switch connects the boom mic (headset) or the
oxygen mic (oxygen mask) to the input.
HAM TS 32 Kn 14.06.94
Page: 12
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
MICROPHONE SELECT
PUSHBUTTON
VHF-1
VHF-2
HF
INT
CABIN
PA
LISTEN LED
GREEN
BOOM/OXYGEN SELECT
SWITCH
BOOM
OXY
RADIO
For Training Purposes Only
VOICE
ONLY
SPKR
MKR
ADF
LISTEN ON/OFF UND
-CONTROL SWITCHES
Figure 8
HAM TS 32 Kn 14.06.94
1-NA V-2
RAD/INT PTT
SWITCH
INT
VOICE FILTER
SWITCH
AUDIO CONTROL PANEL ( config. 1 )
Page: 13
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
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. The
switches are mechanically and electronically interlocked to permit only one
switch to be selected at a time. A light in each switch comes on when the
switch is selected, and the related receive audio channel will become active.
The microphone selector switches are split legend switches used for both microphone selection and call indication. The upper half of the switch, when
turned on, indicates the microphone selection made. The lower half of the
switch, when ”C” is showing, indicates an incoming call for that system.
(2) Volume Control Switches
The switches are turned ON/OFF by pushing the switch knob. The switches
control the selection and volume level of the received audio. The control
switches turn clockwise for increasing volume and counterclockwise for
decreasing volume.
(4) RADIO - INT PTT Switch
The RADIO - INT PTT Switch is a system keying switch. When in
the RADIO position the switch will key the communications system selected by
the microphone selector into transmit. When in the INT position the switch will
key the flight interphone system into transmit regardless of the microphone
selection.This switch is spring loaded to center off. The PTT switch on the ASP
is connected in parallel to the PTT switch on the control wheel which serves a
similiar function.The flight deck speakers are muted when the microphone with
the exception of the oxygen mask microphone is keyed at the audio
selector panel, at the control wheels, or at the hand microphone.
(5) VOICE ONLY Select Switch
The VOICE ONLY select switch is a momentary contact switch.
When active (the switch is lighted), the voice filter attenuates 1020 Hz, switching out DME ident.
(6) SPKR/ NAV Selector Switch
The SPKR switch is the off-on/volume control for the interphone
speaker. 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 the
monitoring of more than one system.
For Training Purposes Only
(3) Listen ON - green LED
HAM TS 32 Kn 14.06.94
Page: 14
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
For Training Purposes Only
23-50
Figure 9
HAM TS 32 Kn 14.06.94
AUDIO CONTROL PANEL ( config. 2)
Page: 15
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
23-50
ACP DATA WORD
General
The REU provides a DC voltage and a clock data line to each ACP. The ACP
switches ground completely (on/off control) or via a variable resistor (volumne
control potentiometer) the voltage line. The voltage level at a specific time represents the ACP switch position.
For Training Purposes Only
Data word
The data word consists of 64 bits. The word is refreshed every 10 seconds.
S Bit 0 is allways 0 volts. Its a synchronous- and startbit.
S Bit 1-18 represents the status of the listenswitches. 12 volts equal OFF,
less than 12 volts is ON and a specefic volume level, 0 volt is maximum volume.
S Bits 19-23 are not used in this configuration. They allways have 12 volts.
S Bit 24-27: 0 volts means active mask mike, INT PTT for the mask- or
Boom mike and voice only or voice and range.
S Bit 28-31 represent BCD-coded the status of mikeselector pushbuttons.
S Bit 32-63 are not used. Their voltage level is allways 12 volts.
FRA USE NM
25.01.1996
Page: 16
COMMUNICATION
AUDIO INTEGRATING
737-300/400/500
For Training Purposes Only
23-50
Figure 10
FRA USE NM
25.01.1996
ACP DATA - WORD
Page: 17
Index
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
23-51 FLIGHT INTERPHONE SYSTEM
GENERAL
For Training Purposes Only
The flight interphone system provides the flight crew with capabilities to communicate with each other and provides the means for them to transmit and receive on airplane communication radio systems and receive on airplane navigation radio systems.
The flight interphone system consists of audio selector panels, a remote
electronic unit, jack panels, push-to-talk (PTT) switches on the control
wheel, handheld microphones, headsets, boom microphone/headsets oxygen
mask microphones, and loudspeakers.
The captain and first officer each have an audio selector panel, a cockpit
speaker, a control wheel PTT switch, a boom microphone headset and oxygen
mask microphone, plus jacks for a headset and a handheld microphone.
The first observer has an audio selector panel, an oxygen mask microphone, a
handheld microphone and a headphone. The second observer has a headphone jack. The audio selected by the first observer is heard at both observer
stations.
Ground crew personnel access the flight interphone system by plugging a
handset into the flight interphone jack on external power receptacle panel. This
allow the ground crew to communicate with the flight crew.
The flight interphone system receives power from the dual power source of
28v dc battery bus and 28v dc bus No. 2, through circuit breakers and
diodes to allow either bus to power all circuits on load control center P6.
HAM TS 32 Kn 30.06.94
Page: 18
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
For Training Purposes Only
23-51
Figure 11
HAM TS 32 Kn 30.06.94
AUDIO INTEGRATING / System Schematic
Page: 19
Index
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
OPERATION
For Training Purposes Only
Selection of which system will receive the microphone input from each flight
crew station is made at the audio selector panel. The last MIC SELECTOR
pushbutton which is pushed will determine the communication system to be
keyed by a PTT switch at that flight crew station.
Flight crewmembers access the flight interphone system to communicate with
each other by setting the PTT switch on the ASP to
INT or I/C position. The PTT function can also be performed at
either 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 selector panel by pushing and rotating the system audio control and pushing the
system MIC SELECTOR switch and then holding the R/T-I/C or RADIO - INT
switch to the R/T or RADIO position. This connects the boom or oxygen mask
microphone and a control line to the selected radio system. The PTT function
can also be completed at either pilot’s station by holding the control wheel PTT
switch to the MIC position.
All flight compartment PTT switches are connected to a speaker mute line so
both cockpit speakers will be muted when a PTT switch is actuated except
when the MASK/BOOM switch is in the MASK position or oxygen mask is in
use. This prevents audio feedback from the speakers to the microphones.
All audio warning messages from ground proximity and altitude alert are heard
by all flight crewmembers without being selected on the audio selector panel.
HAM TS 32 Kn 30.06.94
Page: 20
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
VHF-1
VHF-2
HF
INT
CABIN
PA
3
BOOM
OXY
RADIO
VOICE
ONLY
SPKR
MKR
ADF
1-NAV-2
INT
For Training Purposes Only
1
2
1
PANELS WITHOUT CALL (C) INDICATORS
2
PANELS WITH CALL (C) INDICATORS
3
PANELS WITH HF RADIO
Figure 12
HAM TS 32 Kn 30.06.94
FLIGHT INTERPHONE ACTIVATION ON ACP
Page: 21
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
OXYGEN MASK MICROPHONES
For Training Purposes Only
DLH audio selector panels without a BOOM/OXY switch.
The switch for selecting the oxygen mask microphone is in the oxygen mask
stowage box. When the mask is packed the switch is positioned to the boom
position. Removing the mask from the stowage box will automatically position
the switch to the OXY position to select the oxygen mask microphone as the
operating microphone at that crewmember’s station.
The boom microphone can be returned to operational status by repacking the
mask in the stowage box, closing the compartment doors, and activating the
compartment ”PUSH TO TEST AND RESET” button or by closing the mask
stowage compartment left door and activating the compartment ”PUSH TO
TEST AND RESET” button.
HAM TS 32 Kn 30.06.94
Page: 22
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
VHF-1
VHF-2
HF
INT
CABIN
PA
BOOM
OXY
RADIO
VOICE
ONLY
SPKR
MKR
ADF
1-NA V-2
INT
OXYGEN
RESET
TEST
MASK
Audio Selector Panel ( XA - XU )
100%
PUSH
For Training Purposes Only
INT
Mask Stowage Box
Audio Selector Panel ( XW and on )
Figure 13
HAM TS 32 Kn 30.06.94
OXYGEN MASK MIKE OPERATION
Page: 23
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
COMPONENTS AND LOCATION
HEADBAND
PRESS−TO−
TALK
SWITCH
EARPIECE
TRANSDUCERS
AMPLIFIER
For Training Purposes Only
ACOUSTIC
TUBE
HANDHELD MIKROPHONE
OXYGEN MASK
Figure 14
HAM TS 32 Kn 30.06.94
HEADSET WITH BOOM MICROPHONE
HEADSET
FLIGHT INTERPHONE / Components
Page: 24
COMMUNICATION
FLIGHT INTERPHONE SYSTEM
737-300/400/500
23-51
LOAD CONTROL
CENTER, P6
SPEA
KERS
EXTERNAL POWER
PANEL
SEE A
AUDIO
SELECTOR PANEL
SEE C
REMOTE
ELECTRONICS
UNIT
SEE B
EXTERNAL
POWER
INTERPHONE
REMOTE ELECTRONICS UNIT
B
CONN
FLIGHT
SERVICE
For Training Purposes Only
PILOT
PARKING
BRAKE
NOSE
WHEELWELL
ON
NOT
IN USE
CALL
NORM
LIGHT
EXTERNAL POWER PANEL
A
Figure 15
HAM TS 32 Kn 30.06.94
FLIGHT INTERPHONE SYSTEM / Location
Page: 25
Index
COMMUNICATION
SERVICE INTERPHONE
737-300/400/500
23-41
For Training Purposes Only
23-41 SERVICE INTERPHONE
GENERAL
OPERATION
The service interphone system provides interphone communications between
the flight crew, the attendants, and ground crew personnel. The system includes: the remote electronics unit, the service interphone switch, the attendants handsets, and the service interphone jacks. Also, there is a provision for
a control stand handset. Handsets are installed in the forward and aft attendant
panels for communication between attendants. Switched service interphone
jacks located throughout the airplane are for use by ground crew personnel
during servicing and maintenance. Personnel in the control cabin can communicate with the attendants or ground crew personnel through the audio selector
panels and the headphones and microphones of the flight interphone system.
The service interphone system gets power from the 28v dc battery bus and
also the unswitched electronics bus No. 2, through the INTPH AND WARNING
circuit breaker located on the load control center-right panel, P6.
The remote electronic unit (REU) is installed on the E2-1 shelf of the electronic
equipment rack.There is an audio accessory unit (AAU) card inside the
REU. The AAU provides the necessary dc voltage to the system microphones
and amplifies the audio signal. Automatic level control ensures a constant output regardless of the number of microphones connected to the system. Since
the system has no on-off switch, it will operate whenever the battery bus or dc
bus No. 2 has power. Gain controls for the service interphone system are on
the audio control panel.
The service interphone switch is located on the aft overhead panel P5. In the
ON position, the switch connects the microphone lines from the external service interphone jacks to the input of the interphone amplifiers.The OFF position
disconnects the microphone lines to isolate the external service interphone
jacks during flight.
The handset may be of the press-to-use or press-to-talk type. The button on
a press-to-use type handset completes both microphone and receiver audio
circuits when the handset button is pressed. The button on a press-to-talk
type handset completes only the microphone circuits when it is pressed; receiver circuits are connected directly to the system.
Push the CABIN switch and the respective LISTEN switch on the ACP.
Setting the service interphone switch (on the aft overhead panel P5) to ON
connects the microphone circuits from the external service interphone jacks to
the interphone amplifier. This allows ground crew at the various maintenance
locations to talk with each other. Attendants may communicate with each other,
with the flight crew, and with the ground crew, by using the handsets installed
at their stations.
HAM TS 32 Kn 29.06.94
Page: 26
COMMUNICATION
SERVICE INTERPHONE
737-300/400/500
23-41
M545
28V DC
BAT. BUS
24-00-01
28V DC
BUS 2
24-00-01
D2501B
H1
C561
INPH PWR
F/O BAT.
C84
INPH AMPL
AND WARNING
C560
INPH PWR
F/O NO. 2 BUS
H2
POWER
SUPPLY
FLIGHT CREW
AUDIO
M544
P6-2 CIRCUIT BREAKER PANEL
ATTENDANT/SERVICE
INTERPHONE STATIONS
CODE
SERVICE
INTERPHONE
EXTERNAL
AUDIO
TYPE
B
ELECTRONIC EQUIPMENT RACK
JACK
C
WING REFUELING STATION
JACK
D2501B
E7
D7
D
FORWARD OF RIGHT WHEEL WELL
JACK
E
FORWARD OF LEFT WHEEL WELL
JACK
F
AFT CABIN CEILING
JACK
G
APU ACCESS PANEL
JACK
H
FORWARD ATTENDANT’S PANEL
HANDSET
J
AFT ATTENDANT’S PANEL
HANDSET
K
CONTROL STAND
JACK
T
R
S
D6013
RIGHT WING REFUELING
STATION (STA 78)
T
R
S
D6057
RIGHT WHEEL WELL
(STA 655)
T
R
S
D6011
LEFT WHEEL WELL
(STA 655)
T
R
S
D6017
APU
(STA 1040)
T
R
S
D6015
AFT CABIN
(STA 1004)
T
R
S
D6025
ELECTRONIC
EQUIPMENT RACK
(STA 350)
SERVICE
INTERPHONE
ATTENDANT’S
AUDIO
G8
F7
G9
D6
TO SERVICE
INTERPHONE
LEVEL CONTROL
C
PHONE HI
1
PHONE LO
2
MIC HI
3
MIC LO
4
D6021
AAU CARD
P13 FORWARD ATTENDANT’S PANEL
M1353 REMOTE ELECTRONICS UNIT (E2-1)
D
K
B
SERVICE
INTERPHONE
J G
H
For Training Purposes Only
F
E
PHONE HI
1
PHONE LO
2
MIC HI
3
MIC LO
4
OFF
ON
2
P14 AFT ATTENDANT’S PANEL
1
S50 SERVICE
INTERPHONE SWITCH
(P5 AFT)
F
J
K H
G
B
D6023
PHONE HI
1
PHONE LO
2
MIC HI
3
MIC LO
4
D6019
P8 CONTROL STAND - AFT FACE
D,E
Figure 16
HAM TS 32 Kn 29.06.94
SERVICE INTERPHONE SCHEMATIC
Page: 27
Index
COMMUNICATION
SERVICE INTERPHONE
737-300/400/500
23-41
LOCATION
SERVICE
INTERPHONE
SWITCH
SEE
REMOTE
ELECTRONICS
UNIT
A
AFT OVERHEAD PANEL, P5
LOAD CONTROL
CENTER, P6-2
HANDSET AT AFT
ATTENDANT’S PANEL
EXTERNAL POWER
RECEPTACLE PANEL
SEE
B
HANDSET AT FORWARD
ATTENDANT’S PANEL
HANDSET JACK ON
CONTROL STAND AFT FACE
SERVICE
INTERPHONE
OFF
For Training Purposes Only
ON
SERVICE INTERPHONE SWITCH
A
ATTENDANT’S HANDSET
REMOTE ELECTRONICS UNIT
B
Figure 17
HAM TS 32 Kn 29.06.94
SERVICE INTERPHONE / Component Location
Page: 28
COMMUNICATION
SERVICE INTERPHONE
737-300/400/500
23-41
CODE
A
B
C
D
E
F
LOCATION
AREA
WING REFUELING STATION
FORWARD OF RIGHT WHEEL WELL
FORWARD OF LEFT WHEEL WELL
AFT CABIN CEILING
APU ACCESS PANEL
ELECTRONICS RACK
EXTERNAL
EXTERNAL
EXTERNAL
INTERNAL
EXTERNAL
INTERNAL
A
B
F
STA
130
D
E
C
STA
350
STA
1004
STA
1043
For Training Purposes Only
STA
664
D
E
F
B,C
Figure 18
HAM TS 32 Kn 29.06.94
SERVICE INTERPHONE / Jacks Location
Page: 29
Index
COMMUNICATION
CALL SYSTEM
737-300/400/500
23-43
23-43 FLT/GRD CREW CALL
GENERAL
The flight and ground crew call system provides for call signals between
the flight compartment and cabin attendant stations, between the flight
compartment and ground personnel, and between cabin attendant stations.
The system is used to signal personnel that they are wanted on the service
interphone.The system includes the ATTEND CALL and GRD CALL switches
and the captain’s call light on the forward pilots’ overhead panel, the ATTENDANT, CAPTAIN and RESET switches on the attendant panels, and the
PILOT CALL switch on the external power receptacle panel. It also includes the ground crew call horn, and the attendant call lights on the exit locator signs.The call system gets power from the 28v dc bus No. 1 through the
circuit breaker on the P18 load control center labeled PASS AND CREW
CALL/LAV SMK DET (or PASS AND CREW CALL on airplanes without lavatory smoke detectors)
OPERATION
CAPTAIN CALL
XA bis XU: High Chime and Capts Call Light (blue) comes on, when a call
from ground personnel or from the attendants are initiated. The Call Light goes
out automatically after 40 seconds.
XW and on: High Chime and INT Call Lights on all ACPs come on, when a
call 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 attendants is initiated. All lights go out automatically after about 40 s.
ATTENDANT CALL
Pressing the ATTEND call switch on the forward overhead panel P5
applies 28v dc power to the pink attendant call lights, to the R380 attendant call
relay, and to the chime in PA amplifier. The PA amplifier sounds a double
chime through the PA system. Also, the attendant call relay holds the call light
on until reset with the RESET switch on either attendant panel. Pressing the
ATTENDANT call switch on either attendant panel applies 28v dc power to the
green attendant call lights, to the attendant call relay, and to the chime in the
PA 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 RESET
switch on either attendant panel.The RESET switches on the attendant panels
are connected in series.Thus, pressing one removes power from the attendant
relay and makes the call lights go off.
For Training Purposes Only
GROUND CREW CALL
Pressing the GRD CALL switch on the forward overhead panel P5 applies 28v
dc power to the ground crew call horn. The horn will sound as long as the
switch is pressed. The ground crew call horn also serves as an audible warning
device for the IRS (inertial reference system). The IRS warning system relay
comes on in the flight instrument accessory unit or integrated flight instrument
accessory unit, and applies 28v dc power to the ground crew call horn, whenever the IRS is powered by its battery or the IRS is turned on and the equipment cooling fan is not operating. The air-ground relay must be in the ground
position before the IRS warning system relay can energize.
HAM TS 32 Kn 08. 05.96
Page: 30
COMMUNICATION
CALL SYSTEM
737-300/400/500
23-43
28V DC
BUS NO. 1
CAPTAIN
PASS CALL
PASS AND CREW
CALL/LAV
SMK DET
R380
CALL RELAY
ATTENDANT
TD
HI TONE
RESET
CHIME
M315 AURAL WARNING
MODULE
ATTEND
R392 TIME
DELAY RELAY
P14 AFT ATTENDANT’S PANEL
(STA 995)
PILOT CALL
P19 EXTERNAL POWER
RECEPTACLE
CALL
P
P
G
G
B
L1086 EXIT
LOCATOR SIGN
(STA 304)
B
M53 GROUND
CREW HORN
(STA 230)
MASTER
DIM AND
TEST
TEST
L1088 EXIT
LOCATOR SIGN
(STA 993)
For Training Purposes Only
L19 CALL LIGHT
RESET
GRD CALL
28V DC
P5 PILOTS’ FORWARD
OVERHEAD PANEL
CREW CALL HORN
P6-1 ELECTRONIC
LOAD CB PANEL
1
M160 FLIGHT
INSTRUMENT
ACCESSORY UNIT
(E1-2)
1
M63 PA AMPLIFIER
(E2-1)
Figure 19
HAM TS 32 Kn 08. 05.96
ATTENDANT
TWO TONE
CHIME
COMES ON WHEN IRS IS
POWERED BY ITS BATTERY,
OR IRS IS ON AND EQUIPMENT
COOLING FAN IS NOT OPERATING.
(AIR-GROUND RELAY IS GROUNDED)
R22
ATTENDANT’S
CALL RELAY
CAPTAIN
P13 FORWARD ATTENDANT’S PANEL
(STA 304)
CALL SYSTEMS / Config. 1
Page: 31
COMMUNICATION
CALL SYSTEM
737-300/400/500
23-43
For Training Purposes Only
THIS PAGE INTENTIONALLY LEFT BLANK
HAM TS 32 Kn 08. 05.96
Page: 32
COMMUNICATION
CALL SYSTEM
737-300/400/500
23-43
28V DC
BUS NO. 1
TO INT CALL
LIGHTS ON
ALL ACPs
PASS CALL
CAPTAIN
TD
PASS AND CREW
CALL/LAV
SMK DET
R380
CALL RELAY
TIME DELAY
RELAY
R455 (J5 STAB. SHIELD)
ATTENDANT
TO CABIN CALL
LIGHTS ON ALL ACPs
TD
HI TONE
RESET
R392 TIME
DELAY RELAY
CHIME
M315 AURAL WARNING
MODULE
P14 AFT ATTENDANT’S PANEL
(STA 995)
ATTEND
PILOT CALL
P19 EXTERNAL POWER
RECEPTACLE
P
P
G
G
L1086 EXIT
LOCATOR SIGN
(STA 304)
L1088 EXIT
LOCATOR SIGN
(STA 993)
For Training Purposes Only
M53 GROUND
CREW HORN
(STA 230)
RESET
GRD CALL
28V DC
P5 PILOTS’ FORWARD
OVERHEAD PANEL
CREW CALL HORN
P6-1 ELECTRONIC
LOAD CB PANEL
1
M160 FLIGHT
INSTRUMENT
ACCESSORY UNIT
(E1-2)
1
COMES ON WHEN IRS IS
POWERED BY ITS BATTERY,
OR IRS IS ON AND EQUIPMENT
COOLING FAN IS NOT OPERATING.
(AIR-GROUND RELAY IS GROUNDED)
HAM TS 32 Kn 08. 05.96
ATTENDANT
TWO TONE
CHIME
M63 PA AMPLIFIER
(E2-1)
Figure 20
R22
ATTENDANT’S
CALL RELAY
CAPTAIN
P13 FORWARD ATTENDANT’S PANEL
(STA 304)
CALL SYSTEMS / Config. 2
Page: 33
COMMUNICATION
CALL SYSTEM
737-300/400/500
23-43
For Training Purposes Only
LOCATION
HAM TS 32 Kn 30.06.94
Page: 34
COMMUNICATION
CALL SYSTEM
737-300/400/500
23-43
EXIT
LOCATOR SIGN
SEE
NO
SMOKING
D
SEE
AUTO
AFT
ATTENDANT’S
PANEL
SEE
SEE
C
SEE
E
ON
A
GRD
CALL
ATTEND
AURAL WARNING
UNIT (CHIME)
FORWARD
ATTENDANT’S
PANEL
D
PILOTS’ CALL
SWITCHES
SEE
OFF
EXTERNAL
POWER
RECEPTACLE
PANEL, P19
EXIT
LOCATOR SIGN
OVERHEAD
PANEL, P5
FASTEN
BELTS
CALL
B
LOAD CONTROL
CENTER, P18
PA AMPLIFIER
(ELECTRONIC
CHIME)
CEILING
(REF)
B
PILOTS’ CALL SWITCHES
LIGHTS
E
BRT
ON
ON
ATTENDANT’S
CALL LIGHT
(PINK)
DIM
OFF
ENTRY
EXTERNAL
POWER
OFF
INTERPHONE
OFF
WORK
OFF
GROUND
SERVICE
DIM
PAX CALL
LIGHT
(BLUE)
ATTENDANTS
LAVATORYCALL
LIGHT
(AMBER)
EXIT LOCATOR SIGN
BRT
BRT
NIGHT
ATTENDANT’S
CALL LIGHT
(GREEN)
D
DIM
CONN
FLIGHT
SERVICE
CALL SWITCHES
PARKING
BRAKES
NOSE
WHEELWELL
PILOT
OFF
FIRST
FIRST
CEILING
CALL SYSTEM
WINDOW
For Training Purposes Only
ON
NOT
IN USE
OFF
NORM
CALL
LIGHT
DIM
BRT
BRT
NIGHT
CAPTAIN
ATTENDANT
RESET
LIGHTS
DIM
CALL SWITCH
CALL SWITCHES
EXTERNAL POWER RECEPTACLE PANEL
TOURIST
CEILING
BRT
OFF
TOURIST
WINDOW
DIM
OFF
ENTRY
CALL SYSTEM
C
B
Figure 21
HAM TS 32 Kn 30.06.94
AFT ATTENDANT’S PANEL
FORWARD ATTENDANT’S PANEL
CAPTAIN
ATTENDANT
RESET
A
CALL SYSTEMS / Component Location
Page: 35
Index
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
23-31 PASSENGER ADDRESS (PA)
For Training Purposes Only
GENERAL
The PA system supplies voice messages, and chime signals via speakers to
all passengers and attendants in the passenger cabin.The PA system also supplies boarding music via the speakers to the passenger cabin. PA sidetone is
provided to the flight deck crewmembers via their audio selector panels.
PA
inputs have an order of priority, when the PA receives an input it
will cancel 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 aft
attendant speakers. This prevents feed back during attendant announcements.
Keying the pilot’s PA microphone will disable the muting of both forward
and aft attendant speakers.
Discrete signals from the passenger signs system cause a low tone chime
signal to be sounded. A single low chime occurs whenever the NO SMOKING
or the FASTEN SEAT BELT signs are switched on or off.
Discrete signals from the attendant call system cause high tone chime
signals to be sounded. A single high chime occurs when an attendant call
switch is pressed at a passenger service unit (PSU) or from a lavatory.
Discrete signals from the cabin interphone system cause high-low chimes
to be sounded. A single high-low chime occurs for a crew to attendant
call.
HAM TS 32 Kn 24.06.94
Voice announcements from the pilots are made through the flight interphone
system. The announcements amplified by the PA amplifier are returned to the
pilots via the flight interphone system. Amplification by the PA amplifier is enabled by PTT (push-to-talk) inputs.
The PA amplifier has circuitry to provide system testing. All PA speakers can
be checked. Output level of the amplifier can be determined to allow for adjustments.
The system amplifier gain is increased by 6 db to compensate for increased
noise levels when either engine is operating.
Each audio input into the PA amplifier has a PTT control signal. Priorities within
the 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 operational status of the PA system. The spring loaded CAL position applies the
PA amplifier main output to an internal load. The power applied across the load
is displayed on the LED indicators. The TEST position causes a calibrated high
chime tone from the main and auxiliary outputs to all speakers. The NORM
position is used for system operation.
After performing any tests, the switch should always be returned to the
NORM position.
Page: 36
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
28V DC
BAT. BUS
C82
24-58-21
PASS ADDRESS
AMP BAT
NEXT
PAGE
F
G
SENS CONTROL
P6-1 CIRCUIT BREAKER PANEL
15
3 BD GAIN ON DECOMPN
MIC HI
MIC LO
PTT
DC COMM
PA MIC
(PROVISIONS)
3
4
1
2
VOLTAGE
REGULATOR
FILT
P8 PILOTS CONTROL
STAND - AFT
DC
MASTER
LEVEL
SIDE TONE
23-51-00
PA LISTEN
M1353 REMOTE
ELECTRONICS
UNIT (E2-1)
20
INPUT NO. 1
OUTPUT CONT
28V DC
1
23 NC
MUSIK/
EMERGENCY
ANNOUNCMENT
A
TO REMOTE
ELECTRONICS
UNIT
T251C
2
14
INPUT
NO. 4
PA MIC
NC
2
12
E
NEXT
PAGE
MIC HI
MIC LO
PTT
DC COMM
32
1
M73 FWD LEFT
LAV SPKR
-1DB +1DB
ODB=
OUTPUT
OF 60
WATTS
3
4
1
2
22
T251A
2
1
DC
M67 AFT LEFT
LAV SPKR
B
P13 FORWARD ATTD
PANEL
NEXT
PAGE
T251B
2
INPUT NO. 2
1
MIC HI
MIC LO
PTT
DC COMM
PA MIC
3
4
1
2
C
NEXT
PAGE
LO
NO SMOKING
33-25-00
For Training Purposes Only
P14 AFT ATTENDANT
PANEL
LO
SEAT BELTS
33-27-00
23-42-00
79-30-00
1
P
78-00-00
AFT RIGHT
LAV SPKR
HI
HI
PASS/LAV CALL
ATT CALL
HI/LO
13 NC
CHIME LO
GEN HI
AUX
AMP
NORM
CAL
TEST
PSU SPEAKER
(EXAMPLE)
6DB INCREASE
WHEN GROUND
REMOVED
79-32-00
2
3
INTERNALS
SAME AS
S124 ABOVE
1
3
2
S124 ENGINE 1 LOW
OIL PRESSURE SW
78-00-00
(SHT 2)
S124 ENGINE 2
LOW OIL PRESSURE SW
F5
K5
K3
K2
H5
M63 PASSENGER ADDRESS AMPLIFIER (E2-1) (346D-2B AMP)
J5
G2
F2 G (POWER)
M1353 REMOTE ELECTRONICS UNIT (E2-1)
Figure 22
HAM TS 32 Kn 24.06.94
D
NEXT PAGE
(TO REU FOR
ATT SPKR )
PA SYSTEM SCHEMATIC 1
Page: 37
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
For Training Purposes Only
THIS PAGE INTENTIONALLY LEFT BLANK
HAM TS 32 Kn 24.06.94
Page: 38
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
ANNC
4CH HEAD
SWITCH
#1
#2
SWITCH
#3
SWITCH
SWITCH
20
P6-1 CIRCUIT
BREAKER PANEL
D1
MUSIC
BLANK &
ADDR DET
R324 OXY IND
RLY
MUSIC
1
2
3
4
5
6
7
8
9
1
6
LOW
CONTROL 3 A
3
HIGH
LOW
25
28
CONTROL 4
MICRO
PROCESSOR
LED
DRIVER
S1-1
S1-2
S1-3
S1-4
S1-5
S1-6
S2-1
S2-2
S2-3
S2-4
S2-5
STARTSTOP
1
4
26
INPUT NO. 3
PRERECORDED
ANNOUNCEMENT
AUDIO
INPUT NO. 4
MUSIC
AUDIO
14
M63 PASSENGER
ADDRESS
AMPLIFIER (E2-1)
READY
0
HIGH
TAPE
DECK
CONTROL
14
E3-1 ELEX SHELF
3
18
SOLID
STATE
STORED
VOICE
ROM
(5 MBIT MAX)
D2
6
17
MAIN AUDIO
OUTPUT LOW
+5V
-5V
+5V
+5V
+19V
POWER
SUPPLY
21
MUTE
SWITCH
#4
115V AC
ELEX
PWR 2 C80
PASS ADDRESS
TAPE RPDR AC
SWITCH
2
S2-6
KEY SWITCH & DISPLAY
SSSV
MESSAGE
ASSIGNMENT
MUSIC
PEEPER
ON-OFF
1
2
3
4
5
6
READY
7
8
9
START STOP
EMERGENCY
ANNUNCIATOR
CYCLE SET
0
1
2
ELECTRONIC
LOCK
M1276 TAPE REPRODUCER PRERECORDED ANNOUNCEMENT (EXAMPLE)
FWD ATTENDANT STATION
For Training Purposes Only
D
PREVIOUS
PAGE
B
PA AMPLIFIER
OUTPUT
T337
M157
FWD ATTND
SPEAKER
T338
M1212
L AFT ATTND
SPEAKER
T339
M1213
R AFT ATTND
SPEAKER
FWD PA PTT
FWD MUTE (K2)
PRE REC ANN PTT
A
C
AFT PA PTT
F POWER
E
COCKPIT PA
PTT
M1353 REMOTE ELECTRONIC UNIT (E2-1)
AFT MUTE (K3)
ATT MUTE (K1)
Figure 23
HAM TS 32 Kn 24.06.94
PA SYSTEM SCHEMATIC 2
Page: 39
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
LOCATION
-1
0 db
+1
PSU SPEAKER
(EXAMPLE)
TEST
PA AMPLIFIER
(E2-1)
SEE
LOAD CONTROL
CENTER, P6
REMOTE
ELECTRONIC
UNIT (E2-1)
CAL
A
ELECTRONIC
EQUIPMENT
RACK, E2
AFT ATTENDANT’S
SPEAKERS
(LOWERED CEILING)
SEE E
AUDIO SELECTOR
PANELS
NORM
PILOT’S PA MICROPHONE
(PROVISIONS)
SEE D
MICROPHONE ON AFT
ATTENDANT’S PANEL
FORWARD
ATTENDANT’S
SPEAKER
(LOWERED CEILING)
SEE
C
For Training Purposes Only
PA AMPLIFIER
A
FORWARD
ATTENDANT
STATION
SEE
B
Figure 24
HAM TS 32 Kn 24.06.94
TAPE REPRODUCER LEFT GALLEY WALL
SEE
B
PA / Component Location 1
Page: 40
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
CALL SYSTEM
CAPT
ATTD
RESET
MUSIC
ATTENDANT
1
2
3
4
5
6
7
8
9
READY
PA
MICROPHONE
START
STOP
0
1
2
TAPE REPRODUCER
(EXAMPLE)
For Training Purposes Only
B
AFT ATTENDANT’S PANEL
(EXAMPLE)
C
SELECTOR
FORWARD ATTENDANT’S PANEL
(EXAMPLE)
B
FLIGHT
- 2
INT
HF - 2
PA
PA
CREW
PA MIC
SELECTOR
REMOTE ELECTRONICS UNIT
AUDIO CONTROL PANEL
E
D
Figure 25
HAM TS 32 Kn 24.06.94
PA / Component Location 2
Page: 41
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
TAPE REPRODUCER
GENERAL
The 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 prerecorded announcements.
To open the door holding the tape magazine, display 90 in the window
and press music channel switches 1 and 2 simultaneously.
All the programs are on one C-60/90 Phillips four channel cassette tape. Two
of the channels are for boarding music; one for selected announcements and
the remaining channel for the emergency oxygen announcement.
For Training Purposes Only
MUSIC
The front face of the tape reproducer has MUSIC controls for off/on/volume
and selection of music channel 1 or 2.
To playback boarding music program 1 or 2, press MUSIC channel
button 1 or 2 and press the START button. Adjust music volume by rotating
MUSIC control. Either music program may be stopped at any time by pressing the STOP button. The boarding music program being played may also be
switched at any time by pressing the other MUSIC channel button.
PRERECORDED ANNOUNCEMENT
The front face of the reproducer has the controls for selecting and playing prerecorded announcements. The selection is made with a numerical keyboard
which selects the desired announcement by number and displays the selection
in the window. Upon selecting an announcement, boarding music will
cease and the reproducer will search for and key at the start of the selected
announcement. The READY light indicates the completion of the search
mode.
Pushing the START button will initiate playing of the announcement. If START
is pressed before the search is complete the search will continue and announcement playback will start immediately upon completion of search. The
announcement will play to completion or until STOP is pressed, after which
time the reproducer will return to the boarding music mode of operation before
announcement selection.
An oxygen emergency announcement has priority over any other announcement or boarding music. This announcement is not manually selected. It will
play automatically and repeat upon closing of the OXY IND relay, R324. This
relay closes as part of the sequence during activation of passenger oxygen.
All keyboard, START, STOP, and channel 1 or 2 buttons backlight
when pushed. The channel selection 1 and 2 buttons are push-on/push-off.
All other buttons are momentary.
HAM TS 32 Kn 24.06.94
Page: 42
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
For Training Purposes Only
23-31
Figure 26
HAM TS 32 Kn 24.06.94
PA / Tape Reproducer
Page: 43
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
PA - AMPLIFIER / TEST
AMPLIFIER 346D - 1B
CAL position: indication 0 dB on the testmeter.
TEST TONE position: a calibrated tone is applied to the input of the amplifier
and applied to all speakers.
For Training Purposes Only
AMPLIFIER 346D - 2B
The self-test switch on the PA amplifier front panel provides tests of the operation status of the PA system. The spring loaded CAL position applies the amplifier output to an internal load. The power applied is displayed on the LED
indicators.
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 potntiometer
until this both LED’s come on. the MASTER GAIN potentiometer is on the
lower part of the front panel on the PA amplifier.
The TEST position supplies a high chime sound to all speakers. Make sure
you hear a high chime sound on all the PA speakers.
HAM TS 32 Kn 24.06.94
Page: 44
COMMUNICATION
PASSENGER ADDRESS
737-300/400/500
23-31
OUTPUT LEVEL
INDICATORS (db)
TEST SWITCH
(CAL, POSITION
For Training Purposes Only
SPRING-LOADED)
2
1
AIRPLANES WITH 346D -1B AMPLIFIER
2
AIRPLANES WITH 346D-2B AMPLIFIER
PA AMPLIFIER
Figure 27
HAM TS 32 Kn 24.06.94
1
PA AMPLIFIER
Page: 45
Index
COMMUNICATION
RADIO COMMUNICATION PANEL (RCP)
737-300/400/500
23-21
23 - 21 RADIO COMMUNICATION PANEL
OPERATION
The radio communication panels RCP-1, RCP-2 and RCP-3 are installed on
the aft electronics panel, P8.
Each RCP can make a radio selection and a frequency selection for each of
available radio systems. To set the RCP for a VHF system, push the applicable radio selector switch on the RCP (VHF-1, VHF-2 or VHF-3). The switch
light will come on to show the selection was made at that RCP.
Use the frequency selector knobs, frequency displays and an ACTIVE/
STANDBY transfer switch to set the RCP for a frequency selection. Each RCP
has an ACTIVE frequency display and a STANDBY frequency display. The ACTIVE frequency 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 of
RCP failure. All radios can still be controlled from other RCP’s in the event of a
single RCP failure.
The OFF SIDE CONTROL light illuminates whenever an RCP is used to select
a frequency for an OFF-SIDE radio (refer to the operation paragraphs for a definition of OFF-SIDE). Radio normally associated with this VHF panel is being
tuned 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).
The frequency selected will show in the STANDBY frequency display and can
be 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 via
a cross-bus and to the associated transceiver. Whenever this radio is called up
on another RCP, the frequency pair originally selected with the on-side RCP will
then show on the off-side RCP. The OFF SIDE CONTROL light will illuminate
on both RCP’s.
When a failure occurs the indication FAIL appears in the ACTIVE display window. In this case the onside transceiver can not be tuned from the associated
RCP. With the OFF switch you must disable this RCP. Than the transceiver
can be tuned from other RCP’s.
The third VHF transceiver is originally connected with the ACARS management
unit. 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 appears in the ACTIVE frequency window on this RCP.
For Training Purposes Only
GENERAL
HAM TS 32 Kn 15.06.94
Page: 46
COMMUNICATION
RADIO COMMUNICATION PANEL (RCP)
737-300/400/500
For Training Purposes Only
23-21
Figure 28
HAM TS 32 Kn 15.06.94
RADIO COMMUNICATION PANEL
Page: 47
Index
COMMUNICATION
VHF - COMMUNICATION
737-330/430/530
23-21
23 - 21 VHF - COMMUNICATION
GENERAL
The very high frequency (VHF) communication system provides short-range
two-way voice and data communication in the frequency range of 118.000
through 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 transceiver, a RCP and a blade antenna.
Each VHF system interfaces with the audio integration system and the SELCAL system.
VHF-1 system power is obtained from the hot battery bus, VHF-2 system
power is obtained from switched electronics bus No. 2 and VHF-3 system
power is obtained from DC bus No. 1.
An off-side condition will turn on the cross-tuning annunciator on the RCP-1
and RCP-2 and will activate tuning port B of the selected off-side radio. The
off-side RCP will acquire the tuning selections from the on-side radio and will
tune the off-side radio with the ACTIVE frequency acquired from the on-side
RCP through tuning port B of the off-side transceiver.
Tuning port A for VHF-3 is reserved for future ACARS input. VHF-3 is tuned
only through tuning port B. Selecting VHF-3 from any RCP, other than RCP-3
will result in off-side operation. Thus, the radio controlled from the off-side RCP
will 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 only
through tuning port B.
For Training Purposes Only
OPERATION (VHF - 700 COLLINS)
DESCRIPTION
The VHF system consists of:
S transceiver Collins VHF-700 (E2-1)
S radio control panel (P8)
S blade antenna
The frequency selection data originates in the RCP is transmitted to the transceiver over an ARINC 429 data bus.
Each VHF transceiver has two ports (A and B) for receiving tuning data. The
VHF No.1 transceiver receives the tuning data from the ACTIVE frequency on
RCP-1 through port A when VHF-1 is selected on RCP-1. Similarly the VHF
No.2 transceiver receives the tuning data of the ACTIVE frequency on RCP-2
through port B when VHF-2 is selected on RCP-2. This operation is on-side
operation.
The VHF transceiver A tuning ports are active and the cross-tunig annunciators
are off.
The selection of any VHF except No.1 by RCP-1, or the selection of any VHF
radio except No.2 by RCP-2, constitutes an off-side condition.
HAM TS 32 Kn 15.06.94
Page: 48
COMMUNICATION
VHF - COMMUNICATION
737-330/430/530
For Training Purposes Only
23-21
Figure 29
HAM TS 32 Kn 15.06.94
VHF- 700 / Schematic
Page: 49
COMMUNICATION
VHF-SYSTEM
737-300/400/500
23-21
DESCRIPTION (VHF-700)
For Training Purposes Only
A crewman may transmit or receive over a VHF system after the desired channel is selected on a radio communication panel. Receiving and transmitting are
completed on the same frequency.
To receive, a crewman must activate VHF audio on the audio selector panel
(AMM 23-51-00) and adjust the volume control on the audio selector panel to
obtain a comfortable listening level. The crewman will then hear any messages
that may be received on the selected frequency.
To transmit over the VHF systems, the mic selector switch on the audio selector panel must be pressed in for the desired VHF system. Pressing the microphone PTT (push-to-talk) button of the flight interphone system will operate
control circuits in the VHF transceiver which disconnect the receiver circuits
and connect the transmitter circuits to the VHF antenna. Amplitude modulated
transmission will begin when audio signals are present on the microphone circuits. Sidetone is rectified from the modulated rf to the VHF antenna and returned to the headphones of the flight interphone system to indicate proper
operation of the transmitter. The audio selector panel volume control may be
used to adjust the sidetone audio to a comfortable listening level. When the
PTT button is released, the system will return to the receive condition.
Receive
When the VHF transceiver is not keyed, the output from the frequency synthesizer is connected to the receiver mixer and the VHF antenna is connected to
the receiver input.
With no signal input, the receiver noise output from the detector is filtered and
compared to a squelch threshold voltage in the squelch comparator. The
comparator output turns off the voice audio output to the flight interphone system.
Transmit
Transmission is initiated by grounding the PTT line in the voice mode. This activates the antenna switch and switches the frequency synthesizer output to the
transmitter section.The frequency synthesizer output is low level amplitude
modulated by audio from the interphone system and amplified for transmission.
The forward power output is sampled and fed back to the modulator where it is
used to linearize the modulated drive signal, ensuring that the modulated drive
signal accurately follows the modulation. Forward power is also sampled to
generate sidetone audio to the voice audio output. The rf output is then routed
through the antenna switch to the VHF antenna.
The PTT signal is also routed out of the VHF transceiver as a key event signal.
This is used by the digital flight recorder system to record the times during
which the VHF transceiver is keyed.
FRA USE NM
25.01.1996
Page: 50
COMMUNICATION
VHF-SYSTEM
737-300/400/500
23-21
VHF-1
28V DC
PWR
SPLY
HOT BATTERY
BUS
+20V
+12V
+5V
-12V
RF SENSOR
CIRCUIT
P18 LOAD CONTROL CENTER-LEFT
VHF-1
AUDIO
RF
ATTEN
ACTIVE
SIDETONE
RF (FRCV)
RF
AF AMP
AGC
SQUELCH
IF
STANDBY
SELCAL
M1353 REMOTE ELECTRONICS
UNIT (E2-1)
M57 VHF COMM-1
ANTENNA
(STA 627.5 TOP)
VHF 1VHF 3VHF 2
O OFF
F
F
PHONE
CH. 1
AUDIO
M25 SELCAL DECODER
POWER
SUPPLY
SQL/LAMP
TEST
ARINC PNL 37
RX
LT
38
SQL/LAMP
TEST
SQ DISABLE
OFF
REF
R
SELF- CONTROL
+5V
INPUT
TEST
CIRCUIT FAIL
DISCRETE
INPUTS
l PROCESSOR
& MEMORY
DATA SEL
DISCRETE
OUTPUTS
CONTROL
INPUT
FAIL
NO. 1 COMM CONTROL PNL (P8)
ARINC
RX
l PROCESSOR
For Training Purposes Only
429
RCVR
I/P PORT B
429
RCVR
KEY
DATA KEY RET
VOX/DATA SEL
TO I/P PORT A
VHF-2 XCVR
NO. 2 COMM CONTROL PNL (P8)
TO I/P PORT B
VHF-3 XCVR
ARINC
RX
1
TO I/P PORT B
VHF-2 XCVR
FREQUENCY
SYNTHESIZER
+28V
DATA KEY
KEY
SELECT
LOGIC
HI DATA IN
MIC
HI
REF
OFF
TEST
AF
LO
PTT
PTT H6
AGC
MODULA
TOR
KEY EVENT
RF
TEST
GND
R276 AIR/GND RELAY
(E11 LANDING GEAR
LOGIC SHELF)
RF DIRECTIONAL RF
COUPLER &
(FXMT)
LPF
SIDETONE XMT AF
DETECTOR
KEY EVENT
HI MIC IN
A3
LO
LO B3
+16V DC
M1353 REMOTE ELECTRONICS
UNIT M1353 (E2-1)
1
25.01.1996
M675 FLIGHT DATA
ACQUISITION UNIT
TO ACARS
M149 VHF-1 TRANSCEIVER (E2-1)
Figure 30
FRA USE NM
VHF-700
AIR
FWD
NO. 3 COMM CONTROL PNL (P8)
VHF-1
INDICATES
VSWR FOR
1 SEC
DURING
SELF-TEST
AF
MIC
ARINC
TX
l PROCESSOR
I/P PORT A
LRU
PASS
MIC
PHONE
G
LRU PASS
ARINC
TX
FWD
VHF 700 Detailed Schematic
Page: 51
COMMUNICATION
VHF - COMMUNICATION
737-300/400/500
23-21
For Training Purposes Only
LOCATION
HAM TS 32 Kn 15.06.94
Page: 52
COMMUNICATION
VHF - COMMUNICATION
737-300/400/500
23-21
VHF-2 POWER, LOAD
CONTROL CENTER, P6
RADIO COMMUNICATION
PANELS NO. 1,2,3,
AFT ELECTRONIC
PANEL, P8
SEE
A
ELECTRONIC
EQUIPMENT
RACK, E2
VSWR/POWER
DISPLAY
VHF-1,-2,-3
TRANSCEIVERS
SEE
VHF-1 AND VHF-3 POWER,
LOAD CONTROL CENTER, P18
B
SQL/LAMP
TEST SWITCH
SQL/LAMP
OFF
TEST
RFL
CROSS-TUNING
ACTIVE
FREQUENCY
DISPLAY
ANNUNCIATOR
(WHITE)
ACTIVE/STANDBY
TRANSFER SWITCH
FWD
HEADPHONE
CONTROL
LRU
(PHONE)
INPUT
PASS
JACK
FAIL
RFL/OFF/FWD
(POWER TEST)
SWITCH
PHONE
STANDBY
MIC
FREQUENCY
TEST RESULT
DISPLAY
LEDs
VHF-700
TEST
For Training Purposes Only
MICROPHONE
ACTIVE
STANDBY
(MIC) JACK
FREQUENCY
VHF1
VHF3 VHF2
SELECTOR
TEST
KNOBS
SWITCH
OFF
OFF SWITCH
RADIO SELECTOR
SWITCHES (3 LOCATIONS)
VHF TRANSCEIVER
RADIO COMMUNICATION PANEL
B
A
Figure 31
HAM TS 32 Kn 15.06.94
VHF - 700 / Locations
Page: 53
COMMUNICATION
VHF - COMMUNICATION
737-300/400/500
23-21
FRONTPANELTEST (VHF-700)
SQUELCH/LAMP-TEST-SWITCH
This 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 CONTROL INPUT FAIL and the green LRU PASS lights come on when this test
switch is pushed.
TEST-SWITCH
The CONTROL INPUT FAIL test checks that the VHF transceiver is receiving
valid frequency tuning data from the VHF control panel RCP. If the tuning data
is not valid, the red CONTROL INPUT FAIL light comes on indicating a VHF
control panel failure. This light remains on for about four seconds after TEST
switch is pressed.
The LRU PASS test identifies a failure on the VHF transceiver. After pressing
the TEST switch, the green LRU PASS should light for approximately one to
four seconds. At the same time, the digital display should show a value of less
than 3.0. This value is the voltage standing wave ratio (VSWR).
For Training Purposes Only
RFL - OFF - FWD SWITCH
After the CONTROL INPUT FAIL / LRU PASS tests are completed, turning the
power test switch to FWD or RFL displays the forward or reflected power values 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 power
value.
HAM TS 32 Kn 15.06.94
Page: 54
COMMUNICATION
VHF - COMMUNICATION
737-300/400/500
23-21
VSWR/POWER
DISPLAY
SQL/LAMP
TEST SWITCH
SQL/LAMP
TEST
OFF
RFL
HEADPHONE
(PHONE)
JACK
CONTROL
INPUT
FWD
LRU
PASS
FAIL
RFL/OFF/FWD
(POWER TEST)
SWITCH
PHONE
MIC
TEST RESULT
LEDs
VHF-700
TEST
MICROPHONE
For Training Purposes Only
(MIC) JACK
TEST
SWITCH
VHF TRANSCEIVER
Figure 32
HAM TS 32 Kn 15.06.94
VHF - 700 / Locations
Page: 55
COMMUNICATION
VHF - COMMUNICATION
737-300/400/500
23-21
OPERATION (RTA-43A BENDIX)
TRANSCEIVER
The RTA-43A VHF transceiver is a solid state transceiver. The VHF transceiver provides two-way voice and data communications in the 118.000 through
135.975 MHz requency range.
The front panel of the transceiver has a XMTR light, a SQUELCH switch, a
PHONE jack and a MIC jack. The XMTR light comes on when the transmitter
output is greater than 12 watts. The SQUELCH switch disables the transceiver
squelch circuits and tests the receiver section. The PHONE and MIC jacks are
provided to connect a headset and microphone directly to the VHF transceiver.
For Training Purposes Only
CONTROL PANEL
On the front of the VHF control panel are two sets of concentric frequency select knobs, two frequency displays, a transfer switch and a SELCAL indication
light (with push- to- reset function).
The TFR switch allows one frequency to be preselected while operating on a
different frequency. A bar will appear across the inactive frequency.
HAM TS 32 Kn 15.06.94
Page: 56
COMMUNICATION
VHF - COMMUNICATION
737-300/400/500
23-21
VHF-2 POWER, LOAD
CONTROL CENTER P6
VHF-1, -2
CONTROL PANELS,
AFT ELECTRONIC
PANEL P8
SEE
A
ELECTRONIC
EQUIPMENT
RACK E2
VHF-1, -2
TRANSCEIVERS
SEE
RTA-43A
XMTR
B
VHF-1 POWER, LOAD
CONTROL CENTER P18
SQUELCH
MIC
118,00
COMM
TFR
SEL
CAL
PHONE
136,975
COMM
For Training Purposes Only
NAV
VHF TRANSCEIVER
114,20
2010945
VHF TRANSCEIVER
B
VHF CONTROL PANEL
A
Figure 33
HAM TS 32 Kn 15.06.94
VHF RTA-43A Locations
Page: 57
COMMUNICATION
VHF-SYSTEM
737-300/400/500
23-21
DESCRIPTION (RTA-43A)
For Training Purposes Only
Bendix RTA-43 VHF Transceiver
The RTA-43A VHF transceiver is a solid state transceiver. The VHF transceiver provides two-way voice and data communications in the 118.000through 135.975-MHz frequency range.
The front panel of the VHF transceiver has a XMTR light, a SQUELCH switch,
a PHONE jack, and a MIC jack. The XMTR light comes on when the transmitter output is greater than 12 watts. The SQUELCH switch disables the transceiver squelch circuits and tests the receiver section. The PHONE and MIC
jacks are provided to connect a headset and microphone directly to the VHF
transceiver.
FRA USE NM
25.01.1996
Operation
Frequency select signals from the VHF control panel are decoded by the frequency translator in the VHF transceiver. The translator develops control signals used in the transmitter and receiver.
The receive occurs anytime the PTT (press-to-talk) switch is not pressed. Audio modulated rf is received by the VHF transceiver via a coaxial cable from the
VHF antenna. It enters the receiver through the transmit/receive switch. The
audio signal is detected and sent to the squelch circuit and SELCAL audio
transformer. The output of the SELCAL audio transformer goes to the SELCAL
decoder. The squelch circuit suppresses receiver noises and sends the signal
to the audio compressor amplifier which maintains proper audio level. The audio then passes through the audio transformer and volume control on the control panel, then to the flight interphone system.
The transmit mode occurs by selecting VHF on the audio selector panel and
pressing a PTT switch. The PTT ground input makes the VHF transceiver into
a transmitter. It provides a ground from the MIC input to enable the transmitter
modulator, which provides the selected rf to the transmitter. With PTT depressed, the MIC input passes to an audio transformer in the VHF transceiver. The rf from the synthesizer is modulated with the audio and amplified.
The level detector detects forward power and if it is greater than 12 watts, the
light comes on.
Audio is detected as sidetone and returned to the flight interphone system via
the volume control. The modulated rf signal then passes through the transmit/
receive switch and coaxial cable to the VHF antenna.
The power amplifier supplies the modulated carrier signal to the VHF antenna
and the monitor circuits.
Transmitter output is indicated by means of a light. A portion of the modulated
transmitter power output is returned through the audio amplifier of the receiver
as sidetone to the flight interphone system.
Page: 58
COMMUNICATION
VHF-SYSTEM
737-300/400/500
23-21
VHF-1
28V DC
D199
A6
STANDBY BUS
UNSWITCHED
P18 LOAD CONTROL CENTER - LEFT
POWER
SUPPLY
AUDIO
COMPRESSOR
AMPLIFIER
A5
28V 16V
A3
NC A4
A9
D2501A
VHF-1 PTT H6
AUDIO COMP
REGULATOR
MODULATOR
RF
XMTR
LIGHT
MIC
JACK
A16
TRANSMIT
DC
RF
RECEIVER
RF
RF
RF POWER
AMPLIFIER
TO SELCAL SYSTEM
(23-28-00)
SELCAL
AUDIO AMPL
SIDETONE
DETECTOR
16V
A31
D2501B
VHF-1 MIC A3
LO
TUNING CONTROL
A4-K1
D199
A15
HI
AUDIO
SQUELCH
AUDIO
COMPRESSOR
Y
RF 1
POWER
DETECTOR
A30
D115
B11
DIRECTIONAL
COUPLER
A2
M57 VHF-1
ANTENNA
(STA 627.5
TOP)
A1
D2501A
HI F6
28V
RF
B28
VHF-1 AUDIO
TUNING LOGIC RANGE
118.000 TO 135.975
MHZ SYNTHESIZER
B35
B29
LO G6
1 T U
FREQUENCY TRANSLATOR/
VHF SYNTHESIZER
X Y Z
B36
0
A10
M1353 REMOTE ELECTRONIC
UNIT (E2-1)
1
A12
A5-K1
NC
2
3
A X X
A11
B
B34
B
X
1
X
X X
3
E
5
6
7
8
9
00 25 50 75
X X
A
X X
B
X X
X X
X X
D
HEADSET
4
X X
C
SQUELCH
2
X X
A
X X
X X
X
C
X X D
X
E
2 OUT OF 5 BCD CONVERTER
NOTE: VHF-2 SCHEMATIC SIMILAR
1
RF=TRANSMIT/RECEIVE
FREQUENCY 118.00-135.975 MHz
RSV
D199
M149 VHF-1 TRANSCEIVER (E2-1)
D203
For Training Purposes Only
RSV
RSV
BENDIX RTA-43A TRANCEIVER
118.00
COMM
118.00
B27
21
B1
B3
B2
B6
B4
B9
B7
1 2 3 4 5 6 7
A B C D A B C
COMM
TFR
WHOLE MHz
TEN WIRES
B11
B10
8
D
B13
B12
9
E
WHOLE MHz
UNITS WIRES
B16
B15
B18
B17
B21
B19
B23
B22
10 11 12 13 14 15 16 17 18 19
A
B
C
D
FRACTION MHz
TENTHS WIRES
E
A
B
C
D
E
FRACTION MHz
HUNDREDTH WIRES
FREQUENCY SELECTOR SWITCHES 1
FREQUENCY SELECTOR SWITCHES 1
G-5905-04
(P8-2) VHF 1 CONTROL PANEL
Figure 34
FRA USE NM
25.01.1996
VHF RTA-43A Schematic
Page: 59
Index
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
23-11 HF - COMMUNICATION
GENERAL
For Training Purposes Only
A single high frequency (HF) communication system is installed in the airplane.
The HF communication system (referred to as the HF system) provides amplitude modulated and single sideband voice communication between airplane
and ground or other airplane. Communication is in the 2.000 to 29.999 MHz
frequency range on any of 28,000 channels at 1 kHz spacing. Propagation
characteristics of the HF band are most suitable for long distance communications. The HF system is composed of an HF control panel, HF transceiver,
HF antenna coupler and an HF antenna. The HF control panel is installed
on the aft electronics control stand. The HF transceiver and adapter
is installed on electronic equipment rack E6. The flush-mounted HF antenna is
part of the vertical fin leading edge. The HF antenna coupler is installed inside
the vertical fin leading edge approximately under the HF antenna. The component locations are shown in figure 1. The HF control panel enables the desired
communication channel to be selected. Sidetone is connected to the HF system audio switch in the flight interphone system. The HF antenna coupler
matches the characteristic antenna impedance to the impedance of the HF
transceiver at the particular frequency on which the system is operating. The
tuner control unit and tuner will automatically keep the voltage standing
wave ratio (VSWR) to a level between 1.3 and 1.0 thus assuring good
power transfer. Communications are completed through the flight interphone system (AMM 23-51-00/001). The HF system uses 3-phase, 115-volt,
400-Hz ac power obtained from load control center P18.
Control Panel
The HF control panel can select any one of 28,000 channels, spaced 1
kHz apart in the 2.000 to 29.999 MHz range. The HF control panel contains four frequency select knobs, a frequency display, SQ knob and a
mode select switch. The SQ (squelch) knob controls audio gain in the receiving section of the HF transceiver. The mode select switch (referred to as the
mode switch) turns the system off (OFF), selects upper sideband (USB), and
amplitude modulation (AM). A ten position rotary switch controls the calsel
system (Ref 23-29-00). The HF control panel is located on the pilot’s overhead panel.
HAM US/E KN
17.10.97
HF Transceiver
Each HF transceiver is a tray-type unit located in the electronic equipment
rack, shelf No. E6-2. Electrical connection is made through a multipin connector located at the rear of the HF transceiver. Antenna line connection is made
at the back of the HF transceiver.
An internal blower provides forced air cooling for the HF transceiver components. The blower is located towards the rear of the HF transceiver. The
blower operates during transmission cycles.
Each HF transceiver panel contains:
(1) LRU FAIL light that comes on as a result of HF transceiver faults.
(2) KEY INTERLOCK light that is activated as a result of HF antenna coupler
faults.
(3) CONTROL INPUT FAIL light that is activated as a result of control faults.
(4) SQL/LAMP TEST switch which tests the above indicator lights and disables squelch of receiver audio.
(5) PHONE jack, a 600-ohm headset plug-in to monitor test audio.
(6) MIC jack, a carbon microphone plug-in to enable voice modulation tests
at the HF transceiver.
HF Antenna
The HF system transmits and receives thru a flush-mounted shunt-fed
slot type of HF antenna. The HF antenna is located in the vertical fin leading
edge. The antenna dielectric portion is constructed of fiberglass. The HF antenna is the metal leading edge of the vertical fin.
HF Antenna Coupler
An HF antenna coupler is located just below the HF antenna in the vertical fin
leading edge. The HF antenna coupler has miniaturized transistor circuits contained in a rack-mounted pressurized ATR case. Electrical connection is provided through a multipin connector located on the unit front. The RF connection is through a coaxial plug designated RF INPUT also located on the front
panel. The antenna connection is on the unit rear panel. The pressurized case
has two sections divided by an RF shield which provides thermal protection
and RF isolation. The forward compartment contains tuning control modules, a
dual servo-amplifier, and the power supplies. Integrated circuit construction is
used in the servo-amplifier and tuning control modules. The rear section of the
HF antenna coupler (the RF compartment) contains the tuning element, a discriminator module, and an isolation amplifier. The tuning elements consist of
two variable vacuum capacitors and a variable inductor, associated motors,
gear trains, switches, and RF relays.
Page: 60
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
D345B
71
D337
M889 RF
FEEDLINE
M228 HF
LEADING EDGE
SLOT ANTENNA
D345B
C3
TO SELCAL
SYSTEM
23-28-00
F5
D3
A
COLLINS
E5
SQL/LAMP TEST
PUSHBUTTON
PTT FROM AUDIO
INTEGRATION
LRU FAIL
HEADPHONE JACK
KEY INTERLOCK
E1
RECHNNELD341
F
LINE
CONTROL INPUT FAIL
D1
AUDIO/
SIDETONE
MIC AUDIO
D4287
LO 2
HI 1
C1
A1
LO 8
B1
ELECTRONIC SHELF
(E2-1)
C5
TUNE
PWR
K
H
B5
D345C
2
D345C
9
115V AC
28V DC
11
öB
115V AC
ESS ELEX
BUS-1
TO FLIGHT
RECORDER
(31-24-00)
PHONE MIC
MIC
JACK
HF-1 AC
öA
PTT LINE
E2
HFS-700
7
HI
KEY
S
INTLK
H5
SQL/LAMP TEST
A
L
3
öC
PRESSURIZING
CONNECTOR
7
öA
M227 HF-1 ANTENNA COUPLER (VERTICAL FIN)
CALSEL
M226 HF-1 TRANSCEIVER (E6-2)
P18 LOAD CONTROL
CENTER
For Training Purposes Only
A
13
D419
3
HF
SQ
SSB
2
4
FROM CONTROL
STAND PANEL
LIGHT CONTROL
(P8)
6
1
6
14
CALSEL
4
3
5
AM
7
0
5V AC
9
8
2
15
P9-18 HF-1 CONTROL PANEL
Figure 35
HAM US/E KN
17.10.97
HF - System / Block diagram
Page: 61
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
For Training Purposes Only
OPERATION
A 3-phase, 115-volt ac circuit breaker, on the P18 load control center, supplies
power to the HF transceiver. To receive; the mode switch, on the HF control
panel, is switched to SSB or AM mode and the desired frequency is selected.
The HF system must be selected on the audio selector panel. The VOL (volume) knob on the audio select panels, may be adjusted to obtain a comfortable
listening level. To transmit; the HF system microphone selector switch, on the
audio selector panel, must be pressed. Pressing the microphone PTT (pushto-talk) switch operates control circuits in the HF transceiver which disconnects
the receiver circuits and connects the transmitter circuits to the antenna.
Transmission begins when audio signals are present on the microphone circuits. Sidetone is returned to the interphone system so that audio being used
to modulate the transmitter can be heard.
(1) Data
The transmitter output is nominally 400 watts PEP (peak effective power) with
a maximum average power of 125 watts. The HF transceiver has a dual-conversion receiver that produces 100 mw received voice audio output, 100 mw
of sidetone output and 500 mw of SELCAL audio. Operating voltages are
produced by internal power supplies that operate from a 3-phase, 115-volt,
400 Hz primary source.
(2) Power Control
(a) Turning the HF control panel’s mode switch from OFF energizes the ON/
OFF relay; which provides 3-phase 115v ac to the power supply. Phase C operates the relay driver and the blower which provides cooling air during transmit
operations.
(3) Frequency and Mode Selection
(a) The operating mode and frequency are selected on the HF control panel
and supplied to the HF transceiver. This parallel data is serialized then sent to
the tuning control circuits where it is converted into bcd (binary coded decimal)
data. The bcd data is used to tune the frequency synthesizer.
(b) When a change of operating frequency is selected on the HF control panel
a rechannel signal is sent to the HF antenna coupler. This signal causes the
HF antenna coupler to return to its home position. Before the HF transceiver
can operate on this new frequency, the HF antenna must be tuned.
HAM US/E KN
17.10.97
(4) Transmit Mode
(a) In transmit mode, the HF transceiver will produce nominally 400 watts PEP
RF output in SSB operations and a nominal 125 watts average RF output in
AM operation.
(b) Pressing the microphone key or PTT switch initiates tuning of the HF antenna coupler and activates the transmitter circuits in the HF transceiver.
(c) During tuning, the HF antenna coupler supplies a TIP (tune-in-progress)
signal to the HF transceiver and holds the key line down until tuning is complete ( this signal is also called ”Key Interlock” ). Within the HF transceiver the
TIP signal produces the following results: the transmitter is placed in the AM
mode with low-power output (72 watts), and the tune tone oscillator produces a
1000-Hz modulating audio tone. When tuning is complete (VSWR signal is
less than 1:1,3), the TIP signal is removed from the HF transceiver, the HF antenna coupler unkeys the transmitter, and HF transceiver returns to the receive
mode. With the HF antenna coupler tuned to the selected operating frequency,
the HF transceiver is then ready for transmission.
(d) If the HF antenna coupler fails to tune properly, transmission will be inhibited. In this situation, when the key or PTT switch is activated, the KEY INTERLOCK lamp on the HF transceiver front panel will light to indicate an HF
antenna coupler fault.
(e) In the HF transceiver, mike audio is applied to the balanced modulator.
Part of the audio that’s being used to modulate the transmitter is routed to the
audio/sidetone output system.
(f) The output from the receiver/exciter is applied to a power amplifier through
an ALC (automatic load control) attenuator. The power amplifier raises the
100-milliwatt PEP input to a nominally 400-watt PEP output. The power amplifier has protective circuits that provide almost instantaneous shutdown of the
power amplifiers in the event of excessive power amplifier internal power dissipation.
(g) The 400-watt PEP RF output is routed through a directional wattmeter and
a transmit-receive relay to the external HF antenna coupler. Forward and reflected power detectors, within the directional wattmeter, provide voltages that
are used to generate the ALC signal and to drive the power amplifier protection
control circuit. The relay disconnects the receiver from the HF antenna coupler
and connects the transmitter to the HF antenna coupler. Whenever the HF
transceiver is in the transmit mode, an internal blower provides forced-air cooling to the transmitter circuits to prevent overheating.
Page: 62
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
OPERATION (CONT.)
For Training Purposes Only
(5) Receive Mode
(a) In the receive mode, the HF transceiver receives 2.000 to 29.999 MHz
SSB or AM signals from the external HF antenna coupler. The receiver uses
dual conversion to provide 100-mW received voice audio output.
(b) The 2.000 to 29.999 MHz signal from the HF antenna coupler is routed
through the transmit-receive relay to an RF attenuator. The RF attenuator output is applied to an RF amplifier. The output from the RF amplifier is then
routed to the receiver.
(6) Fault Lights
(a) The LRU fail light is activated by faults such as frequency synthesizer out
of lock, low transmitter power output, low power supply voltages, or failure of
the frequency control board microcomputer.
(b) The KEY INTERLOCK FAIL light is activated by HF antenna coupler faults
such as excessive tuning time (more than 15 seconds), HF antenna coupler
power failure, or excessive tuning reactance.
(c) The CONTROL INPUT FAIL light is activated by such problems with frequency selection as absence of parallel data with HF label, or invalid format or
faulty content of input from the HF control panel.
Antenna Tuning
A complete tuning sequence consists of four basic steps. These steps are:
Home, Standby, Tune, and Operate.
The four steps are controlled by a sequence counter which can only advance
to a new position if the conditions of the existing step are satisfied. When a
fault sensor (fifth step) is activated, the circuit overrides all other steps.
A brief description of each sequence follows:
(1) Home
When primary power is first applied, or when a new frequency is selected on
the HF control panel, a ground is switched to the HF antenna coupler. The HF
antenna coupler, in turn, sets a sequence counter to run the elements to the
home position. In this position (home), the series capacitor, shunt capacitor, and shunt coil are effectively set to provide minimum attenuation. When all
tuning elements reach their home position, a pulse is sent to the sequence
counter to advance it to the standby position.
HAM US/E KN
17.10.97
(2) Standby
In the standby position, the HF antenna coupler is set up to receive and the HF
antenna coupler is ready to start a tune cycle upon receipt of a key line ground.
The receive path is from the HF antenna through a relay switch, the isolation amplifier, and from the descriminator to the receiver. If the other HF antenna coupler is keyed, the relay switch de-energizes and shorts the receive
signal to ground. When the HF antenna coupler receives the key line ground
return, the sequence counter advances the system to the tune position.
(3) Tune
(a) Tuning is performed in three steps.
(b) In step A, the series capacitor is servo-tuned to a zero-phasing error position. At some frequencies, the series capacitor or the shunt coil will be inserted
and positioned due to band information commands so the series capacitor
can produce a zero phasing error. The sequence counter then advances to
step B.
(c) Step B determines whether or not the shunt coil is needed for tuning.
(d) During step C, either the shunt capacitor or the shunt coil (as selected in
steps A and B) is servo-tuned to produce zero loading error. The series capacitor is fine-tuned to retain a zero phasing error. At this point, the sequence
counter advances to the operate position.
(4) Operate
Upon reaching the operate sequence, the tune power and key lines have unlatched and the HF antenna coupler is ready to transmit and receive. When
the operator selects a new frequency, the sequence counter advances to the
home step and the complete tuning sequence is repeated.
Page: 63
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
AMP
D345B
C3
TO SELCAL
SYSTEM
23-28-00
D3
A
E5
AM IF
AND DET
SELCAL OUTPUT
SQUELCH
AM AGC
IF AGC
AUDIO
SWITCH
ALC
CONTROL INPUT FAIL IND
LRU FAIL IND
REG
D4287
LO 2
HI 1
7
A1
LO 8
B1
KEY INTERLOCK IND
SSB MECH
FILTER
AUDIO/SIDETONE OUTPUT
AMP
20V
DC
AMP
FREQ
SYNTHESIZER
BAL
MOD
INTERNAL KEY LINE
AVC
MIC INPUT
115V AC
ESS ELEX
BUS-1
vB
TUNING
CONTROL
CIRCUITS
vC
P18 LOAD CONTROL
CENTER
7
D345B
115V AC vB
+28V DC
POWER
SUPPLY
115V AC vC
RELAY
DRIVER
For Training Purposes Only
C
TO FLIGHT
RECORDER
(31-24-00)
C5
D
RECHANNEL
B5
PULSE
E
115V AC OUT D345C
9
28V DC OUT
11
F
G
+20V DC
COLLINS HFS-700 TRANSCEIVER
INTERNAL KEY LINE
BLOWER
D345C
AC COLD
8
B
E2
TUNE POWER
D345C
115V AC vA
2
3
PTT FROM AUDIO
INTEGRATION
KEY
H5
INTERLOCK
KEY LINE
C1
ELECTRONIC SHELF MIC
(E2-1)
JACK
HF-1 AC
vA
F5
DIR.
WATTMETER 20V DC
TEST
AUDIO
MUX
A
PA
AGC
D1
HI
ALC
ATTENUATOR
RECEIVER/
EXCITER
SSB IF
AND DET
D345B
71
RF
AGC
SQ
E1
MIC AUDIO
COAX
RF SENS
HEADPHONE JACK
AUDIO/
SIDETONE
RF
ATTENUATOR
INTERNAL
KEY LINE
AM MECH
FILTER
AGC
SQL/LAMP TEST
PUSHBUTTON
T/R RELAY
AMP
AGC
ON/OFF RELAY
A
D345B G3
M226 HF-1 TRANSCEIVER (E6-2)
D419
D419
3
FROM CONTROL
STAND PANEL
LIGHT CONTROL
(P8)
RECTIFIER/
FILTER
DC/DC
CONVERTER
1
2
1V
DISPLAY TEST
6
5V AC
AM
HI
LO
PANEL
LIGHTS
SSB
25.300
9
H3
10
13
14
SEGMENT
DRIVERS
OPTICAL
ISOLATORS
SQ
FREQUENCY
SELECT ENCODER
ARINC 429
ENCODER
SQUELCH
15
P9-18 HF-1 CONTROL PANEL
Figure 36
HAM US/E KN
17.10.97
HFS - 700 Schematic / Transceiver
Page: 64
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
M889 RF
D337 RF INPUT
A
REFLECTED
DISCRIMINATOR
MODULE
FWD PWR
ISO AMP
28V DC
TO
TUNE
LOGIC
PWR
28V DC
D
K4
FEEDLINE
M228 HF
LEADING EDGE
SLOT ANTENNA
K6
F
E
28V DC
ARC
GAP
INSUFFICIENT
K5
D341
RF = 1
28V DC
HOME COMPLETE
OPERATE
RECHNNEL D341
F
LINE
G
28V DC
POWER
SUPPLY
FILTER
+28V DC
HOME
LOGIC
REC/STBY
LOGIC
D
INHIBIT
CPLR = 0
For Training Purposes Only
HOME
HOME
TUNE C
LOGIC
FWD PWR
REEL PWR
START
COMPLETE
FWD PWR
REEL PWR
START
FWD PWR
TUNE B
LOGIC
OPERATE
LOGIC
CPLR FAULT
OPERATE
PTT LINE
HOME
TUNE IN
PROGRESS
LOADING ERROR
HOME
PRESS > 15.5 PSIA = 1
D
PHASING AMP
PHASING
ERROR
CPLR FAULT
PRESSURIZING
CONNECTOR
NC
PHASE AND LOADING
AMP ENABLE
KEY LATCH
SWITCH
C FROM PRESS
FAULT LT
TUNE A
LOGIC
COMPLETE
A
L
REEL PWR
28V DC
V
C
START
115V AC
C
SEQUENCE COUNTER MODULE
(HOLD
UNTIL
KEYED)
FWD PWR
INHIBIT
CPLR 1
RECHANNEL
(HOME
INITIATE)
CPLR
FAULT
OVERRIDE
COMPLETE
F
CPLR
FAULT
J
START
E
INHIBIT
CPLR 2
IF SYSTEM 2
IS INSTALLED
TO OPEN
20 MS
MOTORS ENABLE
H
B
TIME > 15 SEC = 1
TUNE A (INITIATE)
K
COMPLETE
TUNE
PWR
CPLR
FAULT
START
D
PTT LINE
c
_
ARC DETECTED = 1
HOME
35 MS
COMPLETE
C
KEY
S
INTLK
START
B
FILTER
OFF FAULT
TIMER
ON (15 SEC)
R
DC CPLR FAULT
OVERRIDE
SIGNAL
CPLR FAULT
DRIVE MOTOR
E
LOADING AMP
CPLR FAULT
DC CPLR FAULT
OVERRIDE
SIGNAL
DRIVE MOTOR
F
DRIVE MOTOR
M227 HF-1 ANTENNA COUPLER (VERTICAL FIN)
Figure 37
HAM US/E KN
17.10.97
HFS - 700 Schematic / Coupler
Page: 65
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
CALSEL
The CALSEL system allows the flight crew to alert an appropriately equipped
ground station via the HF system using the CALSEL encoder control.
the registration number of the calling airplane will be displayed to the operator
on ground. The call signal can be selected on the CALSEL control panel
Activation of the CALSEL encoder control will automatically key the HF radio
system and transmit the airplane CALSEL code on the HF frequency determined by the HF radio frequency selector.
The transmitted signal contains the registration number of the calling airplane.
It is coded by wire links on the panel connector.
The coded signal consists of a 32 bit word. The bit states are represented by
two audio frequencies: 1285 and 1715 Hz.
For Training Purposes Only
CALSEL / CODE SELECTOR
0 - SELCAL received, unable to read, changing to next lower frequency
1 - SELCAL received, unable to read, changing to next higher frequency
2 - WILCO (selected if transmission unreadable at FRA ground station)
3 - Message received but unable to comply with
4 - Airplane on ground, assistance required (e.g. maintenance, flight plan)
5 - Routine calls (e.g. arrivals, departure)
6 - Request crew planning
7 - Request flight plan, MET- report or maintenance assistance
8 - Diversion
9 - Any urgent message
Note: Code numbers 5 to 9 are related to airplanes in flight.
HAM US/E KN
17.10.97
Page: 66
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
CALSEL
4 5
3
HF
SQ SSB
2
1
AM
6
7
0
9
8
D2525
MIC HI
7
CALSEL ENCODER CONTROL PANEL
A
MIC LO
PTT
9
FLT
INTPH
SYS
5
28V DC
CALSEL
SWITCH
ENCODING
MODULE
CALSEL ENCODER
AFT
ELECCONTROL
TRONIC
PANEL
SEE
A
PANEL
(P8)
D2525
NC 11
K1
30
29
28
27
START
26
25
24
23
A/C CODE
For Training Purposes Only
28V DC
BUS NO. 1
10
28V DC
CALSEL
P18-2
P18 LOAD CONTROL PANEL
1
DC GROUND
2
1
LOGIC HI
LOGIC LO
1
17
16
15
14
13
12
CDF D-ABWA SHOWN
P8-56 HF/CALSEL CONTROL PANEL
Figure 38
HAM US/E KN
17.10.97
CALSEL - Block diagram
Page: 67
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
For Training Purposes Only
LOCATION
HAM US/E KN
17.10.97
Page: 68
COMMUNICATION
HF- SYSTEM
737-300/4007500
23-11
HF-1 CONTROL PANEL,
AFT ELECTRONICS PANEL
SEE
A
HF ANTENNA
COUPLER
AFT EQPMT
DOOR
AFT ELECTRONIC
EQPMT RACK, E6
SEE
HF ANTENNA
SEE C
B
FWD
HF-1 POWER,
LOAD CONTROL
CENTER P18
COLLINS
LRU FAIL
KEY INTERLOCK
CONTROL INPUT FAIL
SQ
SSB
For Training Purposes Only
AM
SQL/LAMP TEST
CALSEL
4
3
5
HF
2
6
1
7
0
9
HFS-700
PHONE MIC
8
HF TRANSCEIVER
HF CONTROL PANEL
B
A
Figure 39
HAM US/E KN
17.10.97
HF ANTENNA COUPLER
C
HF - System / Location
Page: 69
Index
COMMUNICATION
SELCAL
737-300/400/500
23-22
23-22 SELCAL
GENERAL
For Training Purposes Only
The SELCAL (selective calling) system allows a ground station, with tone
transmitting equipment, to call a specific airplane. When the correct tone combination is received, the airplane SELCAL decoder unit signals the flight crew
by a SELCAL light and an electronic chime. The SELCAL system eliminates
the necessity of continuous monitoring of the communication system by the
flight crew.
The SELCAL system consists of the SELCAL decoder unit. Visual indication
is provided by CALL indicators on the audio selector panels or by a SELCAL
light on the VHF COMM/NAV control panel.The electronic chime is part of the
aural warning system.
When the ground station operator wants to call a specific airplane using
the SELCAL system, the four-tone code which has been assigned to the
airplane is added to the audio transmitted from the ground station. This
code is received by a communication system and sent to the SELCAL decoder
unit. If the four-tone code received is identical to the code entered on
the SELCAL decoder, the flight crew will be alerted by the SELCAL light
and electronic chime.
On airplanes with call indications on the audio selector panels, the call is reset
by pushing the call indication for the system with the call on any audio selector
panel. For airplanes without call indications on the audio selector panels, the
SELCAL reset button is on the VHF COMM/NAV control panel.
HAM TS 32 Kn 24.06.94
Page: 70
COMMUNICATION
SELCAL
737-300/400/500
For Training Purposes Only
23-22
Figure 40
HAM TS 32 Kn 24.06.94
SELCAL / BLOCK DIAGRAM
Page: 71
COMMUNICATION
SELCAL
737-300/400/500
23-22
SELCAL DECODER
MOTOROLA Selcal Decoder
Two separate decoders, in a common case, make up the dual SELCAL decoder unit. One decoder receives the audio input from the VHF-1 transceiver,
the other decoder from the VHF-2 and VHF-3 transceivers. Each decoder
consists of an audio amplifier, a resonant reed circuit, a dc amplifier and control
relays.
For Training Purposes Only
TEAM Selcal Decoder
The SELCAL decoder is a five channel multiplexed unit. Four of the decoder
channels 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 compressor amplifiers, filters, an analog to digital converter, a microprocessor and
control relays.
Every channel will recognize the unique four tone code assigned to the airplane. The assigned code is pin programmable and determined by airplane
wiring to SELCAL decoder connector D2555B or connector D849.
The four tone code is resolved with a 16-bit binary word. Four bits of the word
determine each tone. A coding receptacle is wired to implement the unique 16
bits of this code for the airplane. This receptacle is mounted external to the
SELCAL decoder and connected to it with a short cable. Thus the SELCAL
decoder can be replaced without affecting the code.The coding receptacle is
placed on the rack behind the decoder.
A green and a red and five yellow LED’s are located at the front panel of this
decoder. Push the test knob on the front panel and check the indication:
S all LED’s come on for about 3s (lamp test)
S subsequentily all LED’s come on step by step (testsequence)
S at the end of the test the green GO LED comes on for about 3 s (no failure)
S in case of existing failure the red NO GO LED comes on.
HAM TS 32 Kn 24.06.94
Page: 72
COMMUNICATION
SELCAL
737-300/400/500
23-22
CODE
DISPLAY
WINDOW
A
CODE
SELECT
(A-H, J-M)
CODE SELECTOR KNOB
(EXAMPLE)
NO. 2 DECODER
NO. 1 DECODER
SELECTOR KNOBS
For Training Purposes Only
SELECTOR KNOBS
SELCAL DECODER - TEAM SC2253AD01
DUAL SELCAL DECODER - MOTOROLA NA-135
Figure 41
HAM TS 32 Kn 24.06.94
SELCAL DECODER
Page: 73
COMMUNICATION
SELCAL
737-300/400/500
23-22
For Training Purposes Only
LOCATION
HAM TS 32 Kn 24.06.94
Page: 74
COMMUNICATION
SELCAL
737-300/400/500
23-22
SELCAL-2 POWER
LOAD CONTROL
CENTER, P6
3
120 60
COMM
CONTROL
PANEL, P8
SEE A
AURAL
WARNING
MODULE
SEE B
ELECTRONIC
EQUIPMENT
RACK, E2
SELCAL DECODER
(E2-1),(E2-2)
TFR
SEL
CAL
118 30
COMM
NAV
114,20
SEE C
SELCAL-1 POWER
LOAD CONTROL
CENTER, P18
1
FORWARD
ELECTRONICS
SECTION
CONTROL
STAND
DUAL SELCAL DECODER - MOTOROLA NA-135
C
3
2
For Training Purposes Only
SELCAL
CHIME
FWD
AURAL WARNING MODULE
B
2
SELCAL DECODER C 1
TEAM
SC2253AD01
Figure 42
HAM TS 32 Kn 24.06.94
1
2
3
DLH PQ051-PQ068,PQ086-PQ099
DLH PQ069-PQ073,PV231-PV270
DLH PQ051-PQ068
CONTROL PANEL
A
SELCAL / Component Location
Page: 75
Index
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
23-27 ACARS
For Training Purposes Only
GENERAL
The Aircraft Communications Addressing and Reporting System (ACARS) is a
digital data-link system that operates between an airplane and a ground-based
network of receiver-transmitter stations and central processing stations. The
transmission medium is generally a single frequency in the VHF frequency
range. The VHF-3 is used by the ACARS to transmit and receive messages.
By automatically transmitting routine messages, the ACARS reduces crew
workload. Also, lengthy voice transmissions to communicate with the
ground are reduced with the ACARS.
The airborne ACARS system is used to transmit and receive data or messages. Messages for transmission can be generated automatically or can be
input manually by crewmembers.The ACARS will then properly tune and key
the 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 the
ACARS. The crew can send a downlink message to request to talk to a
party on the ground. The message can even contain the telephone number
of the party. The ground can then make the arrangements, uplink the
frequency the crew needs to tune in, and command the ACARS to switch automatically to voice mode.
The ACARS Management Unit (MU) controls all functions of the airborne
ACARS 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 equipment rack by two hooks at the front and a rack and panel connector on the
rear.
A TEST switch and a PASS and FAULT light are located on the front of
the MU. When the TEST switch is pushed, the unit stops all ACARS
functions and starts a self-test. The result of the test is reported by lights on
the front of the MU and are also sent to the MCDUs for display.
The left and right Multi-purpose Control Display Units (MCDUs) provide the
user 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 being
used on the other MCDU. ACARS can be used on only one MCDU at a time.
FRA USE NM
29.02.1996
Selecting the line select key adjacent to the <ACARS prompt will call up the
ACARS main menu page. From here, all ACARS functions can be accessed,
such as pre-flight initialization, weather requests, system status checks, or link
tests.
The airplane registration number and the airline ID are hardwire coded at the
back of the MU by the shorting receptacle. The registration number is a seven
character number and the airline ID a two character code.
Page: 76
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
115V AC
BUS 1
ACARS AC
737-300/400/500
23-27
POWER
SUPPLY
DATA IN
28V DC
ACARS DC
HOT BAT BUS
P18-2 LOAD CONTROL CENTER
TX/RX DATA
DATA OUT
OUTPUT BUS 1
TUNING DATA
ACARS DATA
CDU-L INPUT
FREQUENCY SELECT PORT A
DATA KEYLINE
DATA KEYLINE RETURN
P9-65 MCDU-L
VHF-3 CONTROL DISCRETES
VOICE/DATA SELECT
ACARS DATA
FREQ PORT SELECT
FMC DATA
M411 VHF-3 XCVR
M1175 FMC
ACARS DATA
PRINTER STATUS
REMOTE VOICE/DATA SWITCH
PROGRAM PIN COMMON
AUTO/MANUAL CHANGEOVER
P8-54 ACMS PRINTER
SHELF
WIRING
54
53
52
AIRPLANE TYPE /
AIRLINE I.D. ALPHA
2
1
GND
LOGIC ZERO SOURCE
SHORTING RCPT (E2-3)
AFT
CLOSED
CARGO
DOOR
PARKING
BRAKE
(R274)
FWD
CARGO
DOOR
For Training Purposes Only
FWD
SERVICE
DOOR
GROUND
GND
A1
SENSING A2
SQUAT
(R279)
AIR A3
RSV
ON/OFF SENSOR
P8 VHF-1 (-2,-3) CONTROL PANEL
HI-LO
CHIME
+28V VOICE GO-AHEAD CONTACT
(not used)
M315 AURAL WARN MODULE
VOICE GO-AHEAD ANNUNCIATOR LIGHT
(PRESENTLY NOT USED)
SET C1
C2
VOICE GO-AHEAD ALERT RESET
OFF C3
ACARS MODE INPUT COMMAND
VOICE/DATA OUTPUT COMMAND
DEDICATED ACARS INPUT
(not used)
VHF-3 PTT
M1353 REMOTE ELECTRONICS UNIT
FMC-02 DATA
LANDING GEAR LOGIC SHELF
(E11)
VHF-3 INDICATOR LIGHT
P8 CAPT (F/O,OBS) AUDIO SELECTOR
PANEL
ACARS DATA
FMC-02
OUTPUT BUS 2
AFT
SERVICE
DOOR
IN/OUT
SENSORS
CDU-R INPUT
R319 EQUIP DOOR RELAY
P9-66 MCDU-R
AFT
ENTRY
DOOR
ACMS DATA
AIRPLANE REGISTRATION
UTC (TIME)
FWD
ENTRY
DOOR
OPEN
OPEN
OPEN
DATA LOADER
DATA
DOOR WARN 28V DC
(52-71-00)
M278 MISC SOLID STATE
SWITCHING MODULE (E3-2)
S196 FWD
S197 ELEX
ACCESS DOOR ACCESS DOOR
SW (STA 240) SW (STA 338L)
ENABLE DISCRETE
M1109 ACARS MANAGEMENT UNIT (E2-3)
Figure 43
FRA USE NM
29.02.1996
ACARS DATA
ACARS DATA
M675 DFDAU (DFDAMRU)
ACARS DATA
DATA LOADER ENABLE
P23-13 AIRBORNE DATA LOADER
ACARS INTERFACE DIAGRAM
Page: 77
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
OPERATIONAL DESCRIPTION
For Training Purposes Only
When the ACARS is not transmitting a message, it monitors the data frequency
through the VHF-3 transceiver for messages from the ground. The system
recognizes messages intended for the airplane in which it is installed by the
address of the message. Each message has a 7 character address, which can
be either the registration number or the flight number. The airplane’s registration number is provided by the ACMS system (DFDAMRU). The flight number
is entered into the FMS system by the crew before each flight. The ACARS
will 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 success of the previous message reception.
The ”ACK” is generated when a valid address for the receiving terminal is received and a good block check sequence was performed.
The ”NAK” is generated when a valid address was received and a bad block
check sequence was performed. The exception to this is when the receiving
terminal is the ground-processor and the operating mode is the demand
mode. In this case the ground-processor will have no response to a bad block
check sequence.
Operational Modes
The airborne ACARS system operates in conjunction with the ground-based
data processors. The two primary modes of operation are the demand mode
and the polled mode. Two additional modes of operation are the off mode
and the failed mode.
(1) Off Mode
- ACARS is in the off mode when 115v ac is removed from AC Bus 1 or
when the ACARS AC circuit breaker is opened.
- As long as 28v dc Hot Bat Bus power is available to the MU through the
ACARS DC circuit breaker, essential RAM memory will be retained and
the 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 following conditions:
FRA USE NM
29.02.1996
(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 polls
an aircraft periodically (at most once every 2 seconds). If the MU has a
message in memory for downlink, it will initiate a transmission.
- The polled mode is used in areas of heavy ACARS traffic so that the
ground 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 under
one of the following conditions:
S When commanded to do so by an uplink.
S When the ON event occurs.
S 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 designed to most failures. When a failure is detected an MCDU indication is activated. Message Format
Page: 78
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
VHF-3 Transceiver;
S 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 with
2400/4800 Hz at 4800 baud). A 1200 Hz tone indicates a bit change from
the previous bit (0 to 1 or 1 to 0) while a 2400 Hz tone indicates no bit
change (0 to 0 or 1 to 1).
S The MU supplies the tuning word to the VHF transceiver on port A of the
transceiver. The tuning word is in the 32 bit ARINC 429 format.
S The MU grounds the voice/data select line of the VHF transceiver.
S 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 as
the source for the tuning word, thereby allowing the MU to control the data
frequency tuning. In VHF 3-voice mode, the MU will open the port select
discrete to allow tuning by port B only as the VHF control panel has to tune
the transceiver to the voice frequecncy.
For Training Purposes Only
Radio Communication Panels;
S The port select discrete to the VHF-3 transceiver is also connected to the
Radio Communication Panels . When grounded, the ACARS indication will
show in the active display of the control panel that is selected to the VHF-3
transceiver, indicating that the MU has control of the tuning.
S A discrete from the VHF control panel allows for remote voice/data switching. When VHF 3 is in voice mode and the display transfer button on the
active ACARS control panel is pushed, ACARS will change to data mode
and the ACARS indication will move to the active display.
Aural Warning Module;
S A voice-go-ahead discrete from the MU to the aural warning module provides the pilot with a chime to notify the pilot when a VOICE CONTACTmessage is received .
S Automatically with the occurance of pre-defined events. These include OOOI times and certain Aircraft Condition Monitoring System
(ACMS) reports. The pre-defined events can be changed by software.
S Manually by crew request.
S In response to uplink messages which require a response.
FRA USE NM
29.02.1996
Page: 79
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
LOCATION
ACTIVE
ACTIVE/STANDBY
FREQUENCY
TRANSFER SWITCH
OFF SIDE
STANDBY
CONTROL LIGHT
FREQUENCY
(WHITE)
DISPLAY
DISPLAY
ACARS
MENU
<FMC
<ACARS
LINE
SELECT
KEY
OFF SWITCH
CENTER VHF RADIO
FREQUENCY
SELECTOR SWITCH
SELECTOR
KNOBS
<ACMS
MENU
KEY
RADIO CONTROL PANEL
For Training Purposes Only
D
S
P
L
F
A
I
L
INIT
REF
RTE
CLB
CRZ
DES
MENU
LEGS
DEP
ARR
HOLD
PROG
BRT
EXEC
N1
LIMIT
FIX
A
B
C
D
E
PREV
PAGE
NEXT
PAGE
F
G
H
I
J
1
2
3
K
L
M
N
O
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
.
0
+/-
Z
SP
DEL
/
CLR
LEFT, RIGHT, OR CENTER CONTROL
M
S
G
O
F
S
T
ACARS MANAGEMENT UNIT, B7062
DISPLAY UNIT
Figure 44
FRA USE NM
29.02.1996
ACARS COMPONENTS
Page: 80
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
RIGHT CONTROL
DISPLAY UNIT, M7440
SEE
LEFT CONTROL
DISPLAY UNIT,
M7439
SEE
A
A
LEFT, RIGHT, OR CENTER RADIO CONTROL PANEL
DATA LOADER
SELECT
PANEL:ONLY
737-300
THRU EA
B
MENU
P8 PANEL
LEFT, RIGHT, AND
CENTER RADIO
CONTROL PANEL
B
SEE
P9 PANEL
For Training Purposes Only
FLIGHT COMPARTMENT
<FMC
<ACARS
<ACMS
DATA LOADER
(MULTI PURPOSE
DISK DRIVE UNIT)
D
S
P
L
F
A
I
L
MANAGEMENT UNIT,
ELECTRONIC
EQUIPMENT RACK E2-3
SEE
C
RTE
CLB
CRZ
DES
MENU
LEGS
DEP
ARR
HOLD
PROG
BRT
EXEC
N1
LIMIT
FIX
A
B
C
D
E
PREV
PAGE
NEXT
PAGE
F
G
H
I
J
1
2
3
K
L
M
N
O
4
5
6
P
Q
R
S
T
7
8
9
U
V
W
X
Y
.
0
+/-
Z
SP
DEL
/
CLR
M
S
G
O
F
S
T
ACARS MANAGEMENT UNIT, B7062
A
LEFT, RIGHT, OR CENTER CONTROL
DISPLAY UNIT
Figure 45
FRA USE NM
INIT
REF
29.02.1996
C
ACARS COMPONENT LOCATION
Page: 81
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
MANUAL
action required
Profile Independent DL Reports:
Profile Independent UL Reports:
Conn Gate Reqest
A/C Crew Rotation Request
Telex Report
Voice Request
ATIS Request
Weather Request
PDC Request
Telex Report
ACARS CALL
For Training Purposes Only
OUT
OFF
ON
Trigger
AUTOMATIC
IN
Time
First A/C movement
OUT : and all doors closed
now
OFF
: Ldg gear decrompressed
now
ON
: Ldg gear compressed
now
IN
: Min one door open
Last time park
brake set
Profile Independent DL Reports:
ETA Change Report
Destination Airport Change Report
Destination Runway Change Report
Frequency Change Report
Figure 46
FRA USE NM
29.02.1996
ACARS Flight Profile
Page: 82
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
REPORTS / REQUESTS
Typ
Name
Dir
1.Movement
Reports(OOOI)
O
P
E
R
Out
DL
RET IN : DL of flight number, return in time and station
Automatic
OFF
: DL of flight number, off time ( takeoff time ), destination and ETA
Automatic
ON
: DL of flight number, on time ( touch down time ), destination, destination runway Automatic
IN
: DL of flight number, touch down time, in time ( on block time ) and destination
Movement
Message
Automatic
DL of estimated time of arrival, destination and runway
Automatic
Voice
3a.Voice Cont. Req.
DL
Voice contact requests to various addresses
Manual
Voice
3b.ACARS CALL
UL
Call request from ground
Manual
Voice
DL
Free text ( telex ) to various addresses
Manual
Voice
UL
Free text ( telex ) to pilots from ground
Manual
Voice
DL
Crew ready for ACARS messages ( e.g. release for WX, ATIS, PDC, Loadsheet uplink )
Manual
Voice
DL
Request for forecast and actual weather
Manual
Voice
UL
UL of forecast and actual weather
after req.
Voice
DL
Request for ATIS
Manual
Voice
UL
UL of ATIS
after req.
Voice
DL
Request of Pre Departure Clearance
Manual
Voice
UL
UL of Pre departure Clearance
after req.
Voice
3h.Loadsheet
UL
Ul of loadsheet
after req.
Manual Ramp
4.Refueling Report
DL
DL of supplied fuel, remaining fuel and APU fuel
Automatic
Fuel Message
DL
Request for A/C crew rotation
Manual
Voice
UL
Info about arrival position and next leg for PIC and A/C
Auto or req Voice
DL
Request for PIL
Manual
UL
UL of PIL
Auto or req Manual Ramp
DL
Request for connecting gates
Manual
UL
Departure infos for connecting flights ( Gate and time within the next 30 minutes )
Auto or req Voice
DL
Engine condition monitoring reports
Automatic
3c Free Text
3c.Free
Te t
N
3f ATIS
3f.ATIS
3e Airport Weather
3e.Airport
3g PDC
3g.PDC
For Training Purposes Only
Automatic
Back- Up
DL
3d.Initial Req.
5 A/C Crew
5.A/C
Cre Rotation
S
6 Pa Info List
6.Pax
R
V
: DL of flight number, out time (off blocks) and depature airport
Trigger
2.Progress Report
A
T
I
O
E
Function
7 Connecting Gates
7.Connecting
8.ACMS/AIDS
FRA USE NM
29.02.1996
Voice
Voice
Print out
Page: 83
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
MESSAGES
The MCDU Scratch Pad (SP) display shows messages in the following priority:
4. user entries
5. ERROR / ADVISORY messages
6. Label 270 messages
The ACARS ERROR / ADVISORY messages (priority 2) are shown, when the
ACARS system is selected on the MCDU. Most of them can be cleared by
pressing the CLR-key on the MCDU ( see chart).
ACARS Error / Advisory Messages Chart
Message Text
Reset Condition
NO COMM,
MSG NOT GEN
LSK that initiates a downlink is pressed while MU is in a
NO COMM condition.
5 seconds or ” CLR ” key pressed or data entry
VOICE MODE,
MSG NOT GEN
LSK that initiates a downlink is pressed while MU is in
VOICE Mode.
5 seconds or ” CLR ” key pressed or data entry
PRINTER FAIL
LSK that initiates a print is pressed, and the printer cannot
accept a message.
5 seconds or ” CLR ” key pressed or data entry
Invalid data entry
CLR key pressed or valid data entry
NO A / C REG,
MU IN STBY
MU has not received the A / C Registration Number from the
DFDAMRU (ACMS-system)
A / C Registration Number from DFDAMRU ( Cold Start )
BUFFER FULL,
MSG NOT GEN
LSK that initiates a downlink is pressed, and the downlink
buffer is full.
5 seconds or ” CLR ” key pressed or data entry
Manually selected VHF data frequency differs from frequency indicated by automatic frequency select logic.
Select correct frequency or ” CLR ” key or data entry
MU is not receiving latitude and longitude data from aircraft
IRS and FMC
VHF data frequency manually selected or aircraft starts broadcast data or ” CLR ” key pressed or data entry
Hardware part number is invalid
Hardware part number
AIRCRAFT TYPE
MISMATCH
Aircraft type pins are not set for 737-330/430/530 aircraft
Reconfigure pins and
reset MU
ACRFT REGNUM
DBASE FAIL
Aircraft registration number initially received from broadcast
does not match database
Install MU on proper aircraft or modify database
INVALID ENTRY
AUTO / MAN
FREQ MISMATCH
NO LAT / LON,
USE MAN FREQ
BAD H / W PART NUM
For Training Purposes Only
Trigger Condition
FRA USE NM
29.02.1996
Page: 84
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
The Label 270 messages are shown on the MCDU display.
Label 270 Chart
Message Text MCDU
ACARS CALL
ACARS MESSAGE
VHF3 VOICE
ACARS NO COM
Trigger Condition
Reset Condition
An ACARS CALL uplink has been received
Activate the ACARS MCDU Operation and select
” ACARS REC MSG ” Pg.
An ACARS UPLINK has been received
Activate the ACARS MCDU Operation and select
” ACARS REC MSG ” Pg.
VHF 3 set in VOICE mode
Use TFR switch on RCP to select ACARS mode
ACARS link not possible. Out of ground station range
Check VHF 3
Indications in the cockpit
Situation
Indication on MCDU
Indication on the MCDU display
Indication on RCP
No link to ground station
NO COMM, MSG NOT GEN
ACARS NO COM
ACARS in the ”ACTIVE” WINDOW
ACARS not controling VHF 3
VOICE MODE, MSG NOT GEN
VHF3 VOICE
ACARS in the ”STANDBY” WINDOW
ACARS MU fault
ACARS not visable on MENU page
COM - ACARS FAULT
For Training Purposes Only
----- in the ”ACTIVE” WINDOW
FRA USE NM
29.02.1996
Page: 85
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
DATA LOADING
For Training Purposes Only
The task is this procedure is the installation of the ACARS software into the
management unit.
S 1. Select ACARS position on the ADL selection panel.
S 2. Insert the diskette with the ACARS customer database into the ADL.
S 3. Make sure the RDY light comes on approximately five seconds.
S 4. Make sure the PROG light comes on approximately three seconds after
the RDY light goes on.
S 5. Make sure the COMP light comes on. This is an indication that the software is installed.
Set the selector switch to NORMAL position on the ADL selection panel. Push
the EJECT button on the data loader. Remove the diskette.
Make sure the software part-number on the ACARS maintenance page is correct, that means this P/N agree with the P/N at the diskette.
DISKETTEN - LABEL
FRA USE NM
29.02.1996
Page: 86
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ALTERNATE WAY OF DATALOADING
IF AIRBORNE DATA LOADER, DATALOADER SELECTPANEL IS NOT INSTALLED OR INOP.
PORTABLE DATA LOADER
AIRPLANES WITHOUT
AIRBORNE
DATA LOADER
PORTABLE DATA
LOADER
RECEPTACLE (COCKPIT
LH ABOVE OBS. SEAT)
SELCTOR PANEL FOR PORTABLE
DATA LOADER
For Training Purposes Only
AIRPLANES WITH
INSTALLED
AIRBORNE DATA
LOADER
ACARS
ACARS MU
ADL DOOR CLOSED
ADL DOOR OPEN
AIRBORNE DATA LOADER (ADL)
Figure 47
FRA USE NM
29.02.1996
ACARS DATA LOADING
Page: 87
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
MCDU OPERATION MENU
You obtain the ACARS ERROR LOG page on this way:
ACARS PRFLIGHT MENU, --> MISC, --> MAINT, --> STATUS, --> ERROR LOG.
For Training Purposes Only
ACARS ERROR LOG
CLASS 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 Text
LSK5 L-Zeile: Troubleshooting Message Text
LSK5 R-Zeile: Failure-Count
GROUND FAULTS
Failure, oocurs on ground. Failures excist after the landing.
FRA USE NM
29.02.1996
Page: 88
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ACARS PREFLT MENU 1/2
FPL DATA
<REPORT
REFUELING
<REPORT
LOAD DATA
ATIS
WEATHER
REQUEST>
<MISC
<FMC (ACT)
<ACARS
<REPORT
<TELEX
MENU
REQUEST>
VOICE
CONTACT>
RECEIVED
MESSAGES>
<ACMS
ACARS MISC
DATA
< FREQUENCY
VHF
ACARS MAINTENANCE
STATISTICS >
OOOI
< STATUS
SATELLITE
STATISTICS >
<PARTNUMBERS
RETURN TO
RTE
CLB
CRZ
DES
MENU
LEGS
DEP
ARR
HOLD
PROG
BRT
EXEC
<STATUS
<TEST
<COMM
PARAMETER
< ACARS MENU
INIT
REF
DISPLAY >
MAINT>
RETURN TO
< ACARS MENU
ACARS STATUS
<ERROR LOG
For Training Purposes Only
ACARS ERROR LOG
CLASS 1 AND 2 FAULTS
<FAULTS
CLASS 3
<FAULTS
GROUND
<FAULTS
ACARS ERROR LOG 1/3
CLASS 1 AND 2 FAULTS
AC REG=. D-ABIB
LEG
DATE UTC
ATA CLS
008 FEB 03 1424 24000
1
POWER SUPPLY INTERRUPT
ACARS PWR IN FLT
ADDR
COUNT
GECE: 007E*
1
RETURN TO
<ERROR MENU
<RCV 429 DATA
<TX 429 DATA
0
<LRU
0
<DISCRETES
RETURN TO
< ACARS MENU
RETURN TO
<STATUS MENU
PRINT>
PRINT>
Figure 48
FRA USE NM
3
29.02.1996
MCDU PAGES: ERROR LOG, FAULTS
Page: 89
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
ACARS FREQUENCY
This page shows the active ACARS frequency - default is Europe with the frequency 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
23-27
TEST
On Maintenance Page you get access to the TEST page. On the associated
RCP you can see the message ACARS in the active frequency window. That
means the ACARS MU is connected to the VHF-3 transceiver.
S 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 connection to a ground station, FAIL is shown. The message INITIATE appears
about 5 s after the end of the test.
S PRINTER TEST: This function activates a test printout on the printer.
S 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.
S MCDU TEST: This function shows a test indication on the MCDU screen.
S RAM TEST: This function activates internal RAM testing. Indication is PASS
or FAIL.
For Training Purposes Only
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 appears.
737-300/400/500
FRA USE NM
29.02.1996
Page: 90
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
MENU
<FMC (ACT)
<ACARS
<ACMS
ACARS PREFLT MENU 1/2
FPL DATA
ATIS
<REPORT
REQUEST>
<REPORT
REQUEST>
REFUELING
LOAD DATA
WEATHER
<REPORT
<TELEX
<MISC
VOICE
CONTACT>
RECEIVED
MESSAGES>
INIT
REF
RTE
CLB
CRZ
DES
MENU
LEGS
DEP
ARR
HOLD
PROG
ACARS PREFLT MENU 2/2
ACARS MISC
ACARS TEST
VHF
STATISTICS >
VHF LINK
< INITIATE
SATELLITE
STATISTICS >
<TELEX
PARAMETER
RETURN TO
< ACARS MENU
1
<REQUEST
< FREQUENCY
OOOI
EXEC
PIL
DATA
< STATUS
BRT
<MISC
DISPLAY >
VOICE
CONTACT>
RECEIVED
MESSAGES>
PRINTER
< INITIATE
< COM AUDIT
1/2
SAT LINK
NO SDU
SDU
NO SDU
MCDU TEST>
RAM TEST
MAINT>
INITIATE>
RETURN TO
For Training Purposes Only
< ACARS MENU
ACARS DATA FREQ
<ASIA/AUS
<PARTNUMBERS
N-AMERICA>
1
<STATUS
<TEST
<COMM
RETURN TO
RETURN TO
AUTOMATIC
< ACARS MENU
Figure 49
FRA USE NM
2/2
FMC
<JAPAN
< ACARS MENU
ACARS TEST
ACARS MAINTENANCE
A131.725
< EUR/OTHERS <-
29.02.1996
< INITIATE
ACMS
NO TEST
CABIN 1
NO LRU
SPARE 5
NO LRU
CABIN 2
NO LRU
RETURN TO
< ACARS MENU
MCDU PAGES: FREQ., TEST
Page: 91
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ACARS MAINTENANCE
On Maintenance Page you get access to the following functions: PARTNUMBERS-, STATUS-, COMM Status-and TEST-Pages.
ACARS PARTNUMBER
This page shows all part numbers of the system (hardware and software). The
software partnumbers actually in the system and the information on the diskettes must be the same.
ACARS LRU STATUS
Shows all systems connected to the ACARS MU. Active systems are labeled
ACTIVE, inactive systems are labeled INACTIVE.
For Training Purposes Only
ACARS COMM STATUS
Shows ACARS COMM status via VHF or SAT ( LSK 1L/ LSK 1R)
S LSK 2L: COMM or NO COMM
S LSK 3L: DATA or VOICE mode
S LSK 4L: count of unsent DL‘s
FRA USE NM
29.02.1996
Page: 92
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ACARS MAINTENANCE
ACARS PARTNUMBERS
MU HW P/N
965-0728-001
DISK PN
963-0001-02
CORE SW P/N
998-1385-501
APP SW P/N
998-1375-501
REV
A
REV
A
REV
A
<PARTNUMBERS
MU S/N
0316
<STATUS
<TEST
<COMM
ACARS STATUS
RETURN TO
< ACARS MENU
<ERROR LOG
DB P/N
998-2006-503
<RCV 429 DATA
<TX 429 DATA
RETURN TO
< ACARS MENU
PRINT >
<LRU
<DISCRETES
RETURN TO
< ACARS MENU
ACARS LRU STATUS
FMC
PRINTER
ACMS
SPARE 1
SPARE 2
MCDU L
SPARE 3
FMC 2
RETURN TO
For Training Purposes Only
ACARS LRU STATUS
RETURN TO
< STATUS MENU
ACARS COM STATUS
(OP) SAT
VHF (OP)
NO COMM
COMM
DATA UNSENT DOWNLINKS
VHF
ROUTER
SAT
000
000
000
RETURN TO
PRINT>
< STATUS MENU
SPARE 4
MCDU R
CABIN 1
SPARE 5
SDU 1
MCDU C
CABIN 2
SPARE 6
1/3
ACTIVE
ACTIVE
ACTIVE
NOT INSTALLED
NOT INSTALLED
ACTIVE
NOT INSTALLED
ACTIVE
2/3
NOT INSTALLED
ACTIVE
NOT INSTALLED
NOT INSTALLED
NOT INSTALLED
NOT INSTALLED
NOT INSTALLED
NOT INSTALLED
PRINT>
< MAINT MENU
ACARS LRU STATUS
RCP
SPARE 8
ADL
SPARE 9
RETURN TO
< STATUS MENU
Figure 50
FRA USE NM
29.02.1996
PRINT>
3/3
INACTIVE
NOT INSTALLED
NO 429 DATA
NOT INSTALLED
PRINT>
MCDU PAGES: ACARS MAINTENANCE
Page: 93
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
For Training Purposes Only
MU RESET
On the ACARS MAINTENANCE PAGE, you have to insert a special password
and press LSK 6R. This will show the ACARS DEBUG page 1. On page 2, you
will find the box-prompts MU RESET.
If the word RESET MU is entered in SP and LSK 6R is pressed, a COLD
START is activated - system reinitialisation !
WARNING
Pressing the test knob at the MU initiates also a MU-coldstart. This resets all
data 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 the
ACARS REFUELING REPORT PAGE. After MU RESET, enter this value into
the SP (without point) and press the LSK 1R on the MCDU.
Nach Aufruf der REFUELING REPORT Seite wird mittels der MCDU Tasten
der alte QTY BEFORE Wert, (abgelesen vor dem Reset der MU), ohne Kommastelle in das Scratch Pad eingegeben und mittels LSK 6R auf das entsprechende Feld gesetzt.
FRA USE NM
29.02.1996
Page: 94
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ACARS MAINTENANCE
ACARS PREFLT MENU 1/2
FPL DATA
ATIS
<PARTNUMBERS
<REPORT
REQUEST>
<STATUS
<TEST
<COMM
<REPORT
REQUEST>
REFUELING
LOAD DATA
WEATHER
<REPORT
<TELEX
RETURN TO
<MISC
< ACARS MENU
VOICE
CONTACT>
RECEIVED
MESSAGES>
SAM
TYPE ’SAM’ INTO
THE SCRATCHPAD
AND PRESS LSK 6R
ACARS DEBUG
FMC>
<VHF
<MEMORY DUMP
SPARE 2>
<PRINTER
<MCDU
<SDU
ACMS>
SPARE 5>
CABIN 1>
SUPPLY VOL
(
)
UNITS
LT
DENSITY
0.800
SUPPLIER
( )
BEFORE
(
)
SUPPLIED
---- FOB
3.9
FUEL DIFF
---- -
RETURN TO
RETURN TO
PRINT>
< MAINT MENU
For Training Purposes Only
ACARS REFUELING REPORT
1/2
ACARS DEBUG
< ACARS MENU
PRINT >
2/2
<SAT
<BIT
<VERSION
MU RESET
TYPE ’RESET MU’ INTO
THE SCRATCHPAD AND
PRESS LSK 6R
RETURN TO
PRINT>
< MAINT MENU
RESET MU
Figure 51
FRA USE NM
29.02.1996
MCDU PAGES: MU RESET, REFUELING REPORT
Page: 95
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ACARS TELEX
Sends a TELEX to a predefined or self entered (free telex) address. Enter text
and press the SEND pushbutton.
ACARS Voice Contact Request
Sends a voice contact request to a predefined address ( the manual selected
VHF-2 frequency is part of the transmission data).
For Training Purposes Only
ACARS Received Messages
Shows all messages received by the ACARS MU, the latest received on top.
Large letter are shown if the message has not been red nor printed, small letters if so.
FRA USE NM
29.02.1996
Page: 96
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
ACARS PREFLT MENU 1/2
FPL DATA
ATIS
<REPORT
REQUEST>
<REPORT
REQUEST>
REFUELING
WEATHER
LOAD DATA
<REPORT
VOICE
CONTACT>
RECEIVED
MESSAGES>
<TELEX
<MISC
ACARS TELEX ADDRESS
OPS
<CONTROL
CREW
<SCHEDULE
TROUBLE
<SHOOTING
RETURN TO
For Training Purposes Only
< ACARS MENU
SITA ADDR >
ACARS TELEX
1/2
SEND>
)
)
)
)
RETURN TO
< ACARS MENU
ACARS VOICE CONTACT
OPS
<CONTROL
CREW
<SCHEDULE
TROUBLE
<SHOOTING
<STATION
<DISPATCH
RETURN TO
<ACARS MENU
PRINT >
29.02.1996
ACARS MAINTENANCE
<PARTNUMBERS
<STATUS
<TEST
<COMM
RETURN TO
< ACARS MENU
TROUBLE SHOOTING
EDDF
ACARS TEST
VHF LINK
< INITIATE
PRINTER
ON VHF 2
131.750
ON HF
--. ---
< INITIATE
< COM AUDIT
1/2
SAT LINK
NO SDU
SDU
NO SDU
MCDU TEST>
RAM TEST
RETURN TO
<ACARS MENU
SEND>
PRINTER MSG
ACARS CALL
RETURN TO
ACARS COM AUDIT
VHF AUDIT
<ON
UPLINKS
DOWNLINKS
ON
-RETURN-T O
<ACARS MENU
INITIATE>
< ACARS MENU
ON
Figure 52
FRA USE NM
STATION
DEST>
STATION
ORIGIN>
MAINT
DEST>
MAINT
ORIGIN>
ACARS REC MSGS
TROUBLE SHOOTING
EDDF
(
(
(
(
23-27
ACARS VOICE CONTACT REQ
STATION
DEST >
STATION
ORIGIN >
MAINT
DEST >
MAINT
ORIGIN >
<STATION
737-300/400/500
RETURN TO
< ACARS TEST
SAT AUDIT
OFF
LABEL FILTER
OFF
LABEL
( )
PRINT>
MCDU PAGES
Page: 97
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
23-27
PARAMETER DISPLAY
Shows special internal datas. Examples:
S 002
MU Partnummer
S 013
VHF frequency transmitted on a voice contact request
S 008
Aircraft Tailsign
S 220
FMGC active Data Base
VHF /SAT STATISTICS Pages
RX/TX Lines: Indication how many messages are received or transmitted in the
respective OOOI phases.
NAKS (not acknowledged) TX/RX: Indication how many messages transmitted
from the aircraft (TX) or transmitted from the ground station (RX) are not acknowledged by the opposite side.
DUP TX: Duplex mode
INC RX: no info, sorry.
NUMBER OF RETRIES :Number of messages transmitted by the airplane with
no succes.
For Training Purposes Only
OUT, OFF, ON, IN (OOOI) STATUS Pages
The OOOI reports are generated automatically by the associated sensors.
S OUT: Generation of the ”off-block time” - time between OUT ( first aircraft
movement) and OFF (Air Ground Switch to Flight).
S OFF: Generation of the ”airborne time” - Take Off.
S ON: Aircraft lnding
S IN: A/C no movement and one door open.
737-300/400/500
FRA USE NM
29.02.1996
Page: 98
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
ACARS MISC
DATA
< FREQUENCY
VHF
STATISTICS >
OOOI
SATELLITE
STATISTICS >
< STATUS
PARAMETER
RETURN TO
< ACARS MENU
DISPLAY >
MAINT>
ACARS VHF STATISTICS
ACARS OOOI STATUS 1/3
FLIGHT NO
----------
DEPT/DEST
UTC
RX
----/----
RETURN
----Z
OUT
----Z
IN
----Z
BLOCK
---RETURN TO
DATE
10 OCT 95
OFF
----Z
ON
----Z
FLIGHT
---PRINT >
< ACARS MENU
ACARS OOOI STATUS 2/3
DOOR INPUTS
LH FWD CABIN OPEN
------
LH CABIN OPEN
------
CARGO / AV OPEN
------
RH SERVICE OPEN
------
TX
0
NAKS RX
DUP TX
ACARS PARAMETER DISPLAY
PARAMETER NO.
For Training Purposes Only
090748
090748
------
STRUT
GND
090748
ENG PWR
LOW
OOOI ST
RETURN TO
< ACARS MENU
IN
RETURN TO
< ACARS MENU
0
0
NAKS TX
INC RX
NUMBER OF RETRIES
0
1
2
4
0
0
0
0
PRINT >
ACARS SAT STATISICS
PRINT >
RX
OUT
0
TX
0
NAKS RX
DUP TX
OFF
27
5
0
0
ON
0
RETURN TO
IN
0
0
0
NAKS TX
INC RX
NUMBER OF RETRIES
0
1
2
4
0
0
0
0
PRINT >
< ACARS MENU
------
PRINT >
Figure 53
FRA USE NM
IN
0
PARM DATA = --
PRINT >
OPEN
SET
------
5
0
0
ON
0
RETURN TO
ACARS OOOI STATUS 2/3
DOORS
PARK BRAKE
A/C MOVE
OFF
27
< ACARS MENU
RETURN TO
< ACARS MENU
OUT
0
29.02.1996
ACARS MCDU-PAGES
Page: 99
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
For Training Purposes Only
ACARS MU FRONTPANEL TEST
After installation, correct operation of the ACARS MU can be checked by using
the following controls located on the MU frontface:
PASS/FAULT indicator lights
In normal operation, the lights indicate the actual status of the ACARS MU. In
test mode, after a 3s indicator light test, the lights indicate the test result.
7 SEGMENT LED
If a test is activated and a failure is detected, the LED shows a fault code. Examples:
S 3: A/C registration missed (the MU did not receive the A/C registration)
S 2: A/C type mismatch (the A/C type defined in software is different to the pin
program information)
S 1: bad H/W part number (the MU partnumber and the pin program information is different)
TEST pushbutton
Whe pressing the test pushbutton switch:
S a ACARS MU ”Cold Start” is initiated.
S the LRU PASS and FAULT lights come on for 3s approximately to indicate
correct operation.
S 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 faulty
and shows a fault code on the LED.
WARNING
Pressing the test knob at the MU initiates a MU-coldstart! This resets all datas
the MU is presently working with, including datas entered via the MCDU!!!
/Additional programming is lost!). See also ACARS MU RESET!!!
FRA USE NM
29.02.1996
ACARS
MU
Page: 100
COMMUNICATION
AIRCRAFT COMMUNICATION ADDRESSING AND REPORTING SYSTEM (ACARS)
737-300/400/500
23-27
MAINTENANCE TIPS / TROUBLESHOOTING
For Training Purposes Only
MCDU Message: NO COMM
S Description: The message NO COMM appears at the scratchpad on the
MCDU.
S 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 completed. 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.
S 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 appears ACARS and at the scratchpad of the MCDU appears ACARS
VOICE. Check the quality of the voice-connection with the ground operator.
- Perform a ACARS MU RESET at the DEBUG Page 2/2.
FRA USE NM
29.02.1996
Page: 101
Index
COMMUNICATION
COCKPIT VOICE RECORDER
737-300/400/500
23-71
For Training Purposes Only
23-71 VOICE RECORDER
GENERAL
OPERATION
The voice recorder system records and preserves a continuing record of
the latest 30 minutes of flight crew communications and conversation.
The voice recorder system has four inputs for simultaneous recording of
all communications in the flight compartment on four track tape. Channel
one receives audio from the first observer’s audio selector panel, channel two
receives audio from the first officer’s audio selector panel and channel three
receives audio from the captain’s audio selector panel. Channel four audio is
taken from a microphone in the voice recorder control panel.
The voice recorder system consists of a recorder unit installed on the
right side of the airplane in the aft cargo compartment; a control panel
installed in the pilots’ overhead panel P5; interconnecting wiring; and relay contacts in the landing gear accessory unit Module M338.
An erase head in the recorder automatically erases previously recorded
information prior to recording. A 30-minute length of closed loop magnetic
tape provides a record of the previous 30 minutes of conversation. An internal
monitoring circuit ensures proper operation of the recording mechanism and
circuits. Audible and visible indications derived from the monitoring circuits are
presented at a meter and a jack on the control panel when the test switch on
the control panel is operated. The entire tape may be erased after the airplane
has landed and the parking brake has been set.
An Underwater Locating Beacon (ULB) that is not part of the underwater
locating system is installed on the front panel of the voice recorder.
The ULB is an acoustic beacon that energizes when it is immersed in
water, thereby assisting to locate the recorder in case of an accident over the
ocean or other body of water. Three types of ULB are in service. One type (the
N15F210B) is powered by a replaceable battery.The second type (DK100) is
powered by a replaceable battery, but must be returned to the vendor for battery replacement or for disposal. The third type (Datasonics ELP-362) is powered by a replaceable battery.
Operating power for the voice recorder system is 115 volts, 400 Hz AC
obtained from the unswitched electronics bus through the VOICE RECORDER
circuit breaker on the P18 panel.
The voice recorder system automatically records the latest 30 minutes of
communications and conversation in the flight compartment. The system is
in operation whenever 115-volt AC power is applied to AC bus No. 1.
Communications and interphone audio from the first observer’s, the first
officer’s and the captain’s audio selector panels is applied to channel
1 through 3 respectively of the voice recorder. Conversation in the flight
compartment is picked up and amplified by the microphone and preamplifier in
the voice recorder control panel and applied to channel 4.
The playback head and monitor amplifier are used to monitor information
recorded on all tracks of the tape. The audio output of the monitor amplifier is
available at the MONITOR jack on the front panel of the voice recorder and at
the HEADSET jack on the voice recorder control panel. This audio is supplied
to the test meter on the voice recorder control panel. On the Fairchild Voice
Recorder Model A100, the audio also supplies input to the meters on the front
of the voice recorder.
Self test for Fairchild Voice Recorder Model A100
Pushing the TEST pushbutton on the voice recorder control panel causes the
test module to apply a 600-Hz signal to each channel in sequence, thereby
testing all channels. If they are functioning properly, the control panel meter
reads 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 recorder
operates the same test as the TEST pushbutton on the voice recorder
control panel.
On the front panel of the cockpit voice recorder are test switches for testing
recording channels 1 through 4 individually.To initiate a test for an individual
channel, push the test switch on the face of the cockpit voice recorder for the
particular channel number.This individual channel test causes the test module
to apply a 600 Hz signal to the channel being tested.
The bulk erase module contains timing, relays, and erase circuits which
apply 115 volts, 400 Hz AC to the erase coil in the tape transport. The
bulk erase circuits erase all audio on the recorder tape within ten seconds after
the ERASE switch on the control panel is released. The bulk erase circuits will
function only when the airplane is on the ground and the parking brake is set
because the control circuit must be completed through relay K4 in the landing
gear accessory unit module
HAM TS 32 Kn 30.06.94
Page: 102
COMMUNICATION
COCKPIT VOICE RECORDER
737-300/400/500
23-71
VOICE
RECORDER
115V AC
UNSWITCHED
ELECTRONICS
BUS
P18-2
CHANNEL 1
OBSERVER
RECORDING
AMPLIFIERS
ERASE
CHANNEL 2
FIRST OFF
FLIGHT
INTERPHONE
SYSTEM
CHANNEL 3
CAPTAIN
P5 OVERHEAD PANEL
RECORDING HEADS
CHANNEL 4
AREA MIC
PREAMP
PLAYBACK
MIC
TEST
TEST
METER
TEST
METER
ALL
1
MONITOR
JACK
TEST
1
ERASE
2
3
4
MONITOR
AMPLIFIER
BULK
ERASE
TAPE TRANSPORT
(PROTECTED)
TEST
MODULE
(600 Hz)
MONITOR
JACK
POWER
SUPPLY
BULK
ERASE
TO
INTERNAL
CIRCUITS
For Training Purposes Only
VOICE RECORDER UNIT
1
TEST SWITCHES FOR FAIRCHILD
VOICE RECORDER UNIT MODEL A100 ONLY
Figure 54
HAM TS 32 Kn 30.06.94
PARKING BRAKE SET
PLANE ON GROUND
LANDING GEAR LOGIC SHELF E11
VOICE RECORDER BLOCK DIAGRAM
Page: 103
COMMUNICATION
COCKPIT VOICE RECORDER
737-300/400/500
23-71
For Training Purposes Only
LOCATION
HAM TS 32 Kn 30.06.94
Page: 104
COMMUNICATION
COCKPIT VOICE RECORDER
737-300/400/500
23-71
OVERHEAD
PANEL P5
AFT CARGO
DOOR
SEE B
LOAD CONTROL
CENTER P6
VOICE RECORDER
SEE
A
HEADSET
JACK
TEST
1
MONITOR
600 OHMS
2
TEST
SWITCHES
3
TEST
4
ERASE
ALL
For Training Purposes Only
HEADSET
600 OHMS
COCKPIT VOICE RECORDER
CONTROL UNIT
UNDERWATER
B
LOCATING
DEVICE (ULD)
MODIFICATIONS
FAIRCHILD VOICE
RECORDER MODEL A100
UNDERWATER
LOCATOR
BEACON (ULB)
A
Figure 55
HAM TS 32 Kn 30.06.94
FAIRCHILD VOICE
RECORDER MODEL A100A
A
VOICE RECORDER / Component Location
Page: 105