Becker | RA3502 | manual | Becker ADF3502 Automatic Direction Finder System Manual

Becker ADF3502 Automatic Direction Finder System Manual
Control Unit
CU 5502 - ( )
Installation and Operation
Manual
Issue 1
DV 60531.03
July 1997
Becker Flugfunkwerk GmbH • Baden Airpark • 77836 Rheinmünster • Germany
Telephone +49 (0) 7229 / 305-0 • Fax +49 (0) 7229 / 305-217
http://www.becker-avionics.com • Email : info@becker-avionics.de
Becker Avionics Inc. • 10830 N.W. 27 Street Miami FL 33172 • USA
Telephone +1 (305) 597 0069 · • Fax +1 (305) 597 8737
http://www.beckerusa.com· • Email : info@beckerusa.com
FIRST ISSUE AND CHANGES
Issue . . . . . 1 . . . . . July 1997
LIST OF EFFECTIVE PAGES
Page No.:
Date :
Title
07/97
1 -I - 1-II
1-1 - 1-6
07/97
07/97
2-I - 2-II
2-1 - 2-6
07/97
07/97
3-I - 3-II
3-1 - 3-8
07/97
07/97
Page No.:
© 1997 by Becker Flugfunkwerk
All rights reserved
Date :
CU 5502 - ( )
Table of contents
Section
1
1.1
1.2
1.3
1.3.1
1.3.2
1.4
1.5
1.6
1.7
1.8
1.9
1.10
Introduction
Purpose
General description
Mechanical description
Electrical
Technical data
Software
Overview of variants
Specification
Environmental influences
Scope of delivery
Accessories (not included in scope of delivery)
DV 60531.03/.04 Issue 07/97
General Information
Page
1-1
1-1
1-2
1-2
1-2
1-3
1-3
1-4
1-4
1-5
1-6
1-6
Page 1-I
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Blank
Page 1-II
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CU 5502 - ( )
Section
1.1
1
General Information
Introduction
The CU 5502 - ( ) control unit is described in the “Installation and Operation” DV 60531.03 and “Maintenance and Repair” DV 60531.04 manuals.
The manuals DV 60531.03 “Installation and Operation” and DV 60531.04 “Maintenance and Repair”
contain the following sections:
Section
1.2
DV 60531.03
DV 60531.04
1
General Information
X
X
2
Installation
X
X
3
Operation
X
X
4
Theory of Operation
X
5
Maintenance and Repair
X
6
Illustrated Parts List
X
7
Modification and Changes
X
8
Circuit Diagrams
X
Purpose
The control unit is used to control and operate the RA 3502 - ( ) ADF receiver and is part of the ADF
3500 system. Both together form the automatic direction finding system which operates in the 190 kHz
to 1799.5 kHz and 2182 kHz ± 5 kHz frequency range and was developed for use in aircraft.
The control unit was designed in accordance with RTCA Air Worthiness Requirements. RTCA
DO-160C was used for the requirements under environmental influences. There is no restriction with
regard to installation by rigid attachment to the fuselage of the aircraft or installation in the instrument
panel, including in rotary wing aircraft, in the verified environmental categories.
A maximum operating ceiling of 50.000 ft. was verified for all system functions in the suitability test.
DV 60531.03/.04 Issue 07/97
Page 1-1
CU 5502 - ( )
1.3
General description
1.3.1
Mechanical description
The control unit is designed for installation in the instrument panel of aircraft. The dimensions correspond to the ARINC standard for standard instruments of 60 mm (2 1/4") diameter. Installation is by
means of four bolts (back panel mounting).
All the controls and indicators are located on the front panel. The equipment connectors are fitted on
the back.
The control unit consists of the following circuit boards:
Display Board,
Switch Board,
Processor Board,
Power Supply Board.
Mechanically the control unit consists of a front section and rear section. The front section contains the
display board and the switch board and these boards are connected to each other by a connector and
held in place within the unit by four bolts. The processor board, which is also secured to the front section by two bolts, is mounted on a switch board. The power supply board is inserted into the rear section
and secured from outside (back of rear section) by three bolts. After all the boards are assembled, the
front and rear sections are joined together and secured to each other by four bolts inserted from the
front section.
1.3.2
Electrical
After switch on, an initialization phase takes place between the control unit and the ADF receiver. During this period data transmission takes place from the remote ADF receiver to the control unit. This is
necessary because data backup takes place in the remote ADF receiver. On completion of this phase,
the mode which was set before switch off is automatically displayed on the control unit.
The frequencies are indicated by means of an LC display. The required active working frequency can
be set using the frequency selector switches. The outer rotary switch engages at steps of 100 kHz/
10 kHz and the inner rotary switch at steps of 2 kHz/500 kHz. In the frequency preselection mode, a faster frequency change between the set active frequency and the preset frequency is achieved by pressing the (<->) exchange key.
The control unit and ADF receiver are switched on using the mode switch with four detent positions,
OFF, REC, ADF, BFO. In the REC position the ADF receiver operates as a receiver in the A2/A3 mode,
in the ADF position as a radio direction finder and in the BFO position it operates in reception mode as
an A1 beat frequency operator and radio direction finder.
The volume is set using the + and - keys. The TMR key operates a stopwatch.
Data transmission between the control unit and ADF receiver is via a bi-directional, serial RS 422 interface.
Page 1-2
DV 60531.03/.04 Issue 07/97
CU 5502 - ( )
1.4
Technical data
Power supply
Emergency power supply
+ 27.5 V d.c. (22.0 V - 32.0 V)
+ 20 V d.c.
Power consumption (without panel lighting)
≤ 0.06 A at 27.5 V
Panel lighting
≤ 0.160 A at 13.75 V
≤ 0.080 A at 27.5 V
Operating temperature
- 20° C . . . + 55° C
Storage temperature
- 55° C . . . + 85° C
Operating ceiling
50.000 ft
Interface
RS 422
Vibration resistance in accordance with
EUROCAE/RTCA ED-14C/DO-160C
Cat. NM
Humidity resistance in accordance with
EUROCAE/RTCA ED-14C/DO-160C
Cat. A / + 50° C; 95%, 48 h
Environmental performance class
Env. Cat.
ED-14C/DO-160C
A1D1-BA(MN)XXXXXXZBABATAXXX
Dimensions
61.3 x 61.3 x 62 mm
H x W x D
Weight
0.26 kg
1.5
Software
All data such as the set frequencies, selected mode etc. are stored in the remote ADF receiver. Any
changes at the control elements result in an immediate data transmission to the remote ADF receiver.
The frequency display is controlled by a microprocessor. The software was classified as level C in
agreement with the EUROCAE/RTCA document ED12B/DO-178B.
DV 60531.03/.04 Issue 07/97
Page 1-3
CU 5502 - ( )
1.6
Overview of variants
Table 1-1 shows the variants of the CU 5502 - ( ) control unit. There is no external difference between
the different variants, i.e. dimensions, installation depth etc. are the same for all the series.
Article-No.
Part designation
Background lighting
red-orange
blue-white
Panel surface
Powder
Painted
coated
0503.800-911
CU 5502 - (1) - X01
0508.500-911
CU 5502 - (1) - X11
1.7
X
X
X
X
Specification
LBA-No.:
10.921/53 JTSO
BAPT
A132 880 J
Specifications
RTCA DO-179
JTSO - 2C41d
FTZ
17 TR 2010
Software
ED-12B/DO-178B Level C
Environmental categories
D1-BA(MN)XXXXXXZBABATAXXX
EUROCAE/RTCA ED-14C/DO-160C
Page 1-4
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CU 5502 - ( )
1.8
Environmental influences
The following resistances to environmental influences were verified in accordance with
EUROCAE/RTCA ED-14C/DO-160C.
Environmental influence
ED-14C
DO-160C
Environmental
class
Temperature and altiude
4.0
A1 D1
Low operating temperature
4.5.1
Influence variable
- 20° C
Low storage temperature
- 55° C
High short-duration
temperature
4.5.2
+ 70° C
High operating temperature
4.5.3
+ 55° C
High storage temperature
+ 85° C
Negative pressure (altitude)
4.6.1
50,000 ft.
Pressure drop
4.6.2
from 5.000 ft. altitude to 50,000 ft.
Positive pressure
4.6.3
- 15.000 ft.
Temperature change
5.0
B
Humidity
6.0
A
Impact under:
7.0
Operating conditions
7.2
6 G/11 ms for the 3 axes
Crash landing conditions
7.3
Impact:
15 G/11 ms for the 3 axes
Vibration
8.0
MN
Magnetic influence
15.0
Z
Deflection of a compass by 1° at a
distance of ≥ 30 cm
Altered power supply
16.0
B
The functioning of the equipment
on 20 V emergency power was verified
Voltage impulse on power
supply
17.0
A
Low frequency disturbing
voltages
18.0
B
Induced magnetic and
electrical fields
19.0
A
High frquency disturbing
voltages and disturbing fields
20.0
T
Unwanted radiation
21.0
A
DV 60531.03/.04 Issue 07/97
48 hrs at 50° C and ≥ 95% humidity
Page 1-5
CU 5502 - ( )
1.9
Scope of delivery
Control unit
Article-No.: refer to overview of variants
4 Phillips head screw
or
4 countersunk screw
Article-No.: 0868.590-203
Operating instructions
Article-No.: 0511.757-071
1.10
Article-No.: 0889.350-204
Accessories (not included in scope of delivery)
Equipment cable socket 15-pole (crimped version)
Article-No.: 0774.030-277
Equipment cable socket 15-pole (soldered version)
Article-No.: 0344.801-277
Housing with push-in locking
Article-No.: 0774.049-277
Manuals
Installation and Operation DV 60531.03
Article-No.: 0511.481-071
Maintenance and Repair DV 60531.04
Article-No.: 0511.498-071
Page 1-6
DV 60531.03/.04 Issue 07/97
CU 5502 - ( )
Table of contents
Section
2
2.1
2.2
2.3
2.4
2.4.1
2.4.2
2.4.3
2.5
General
Inspection before installation
Mechanical installation
Aircraft wiring
General
Panel and display lighting
Connector contact assignment for 15-pole P 31 connector
List of Abbreviations
2-1
2-1
2-1
2-1
2-1
2-2
2-2
2-3
Fig. 2-1
Installation dimensions for the Control unit CU 5502 - ( )
2-6
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Installation
Page
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CU 5502 - ( )
Section
2.1
2
Installation
General
The installation of the control unit depends on the type of aircraft and its equipment and therefore only
general information can be given in this section.
2.2
Inspection before installation
Before installing the control unit in an aircraft, carry out a visual inspection for any transport damage,
paying particular attention to the following.
1. Dirt, dents, scratches, corrosion, broken attaching parts on the housing and housing parts.
2. Dirt and scratches on the identification plate, front panel, LC display and marking.
3. Dirt, bent or broken pins, cracked connector inserts.
4. Dirt and mechanical damage to switches, keys and knobs.
5. Missing screws and bolts.
2.3
Mechanical installation
The control unit is designed for installation in the instrument panel of an aircraft. It is constructed for
rear panel mounting. The circular cutout and the attaching holes are to be drilled to suit a small instrument size. The necessary dimensional details are given in Fig. 2-1. The unit is attached using four bolts
which are included in the scope of delivery.
2.4
Aircraft wiring
2.4.1
General
The following points are to be observed for the wiring.
a.) Only cable fit for aviation (self-extinguishing) may be used. AWG 24 for power supply and AWG 24
for other cables.
b.) The interface lines TX-A/TX-B and RX-A/RX-B are each to be laid as 2-core twisted and screened
(AWG 24) cables.
c.) Rubber sleeves are to be fitted over the soldering points on the equipment connector.
d.) A 1 A fuse or circuit breaker should be fitted in the power supply.
DV 60531.03/.04 Issue 07/97
Page 2-1
CU 5502 - ( )
e.) No HF cable should be included in the cable harnesses. Laying connecting cables together with cables which carry AF power or impulses is also to be avoided.
f.) Check the wiring carefully before switching on the unit, particularly that (+ UB) and (GND) have not
been mixed up.
2.4.2
Panel and display lighting
The control unit is fitted with panel and display lighting. It can also be connected via a dimmer system.
Connection panel and display
13,75 V Power supply
27,5 V Power supply
P 31 - Pin 6 ILL.A
+ 13,75 V
Ground
P 31 - Pin 8 ILL.B
Ground
+ 27,5 V
lighting
NOTE
The panel and display lighting is not switched off when the unit is switched off ON/OFF
switch).
2.4.3
Connector contact assignment for 15-pole P 31 connector
Pin
Connection
1
TX-A
RS 422 interface
2
TX-B
RS 422 interface
3
Shield
Screen of RS 422 interface ground
4
RX-A
RS 422 interface
5
RX-B
RS 422 interface
6
ILL.A
Panel and display lighting A
7
Spare
Not wired
8
ILL.B
Panel and display lighting B
9
GND
Ground
10
GND
Ground
11
+UB
+ UB operating voltage
12
+UB
+ UB operating voltage
13
/ON
ON/OFF function
14
UBSW
15
/X
Page 2-2
Description
Switched operating voltage
Input special function low active
DV 60531.03/.04 Issue 07/97
CU 5502 - ( )
2.5
List of Abbreviations
The following abbreviations are used in this manual:
Abbreviations
Fig.
Figure
AC
Alternating current
AM
Amplituden modulation
ARINC
Aeronautical radio incorporation
ARINC 429 Line
ARINC 429 serial bus
ARINC 410 Line
ARINC 410 parallel bus
ATR
Avionics transport rack
Bite
Built in test equipment (Self test)
COM
Communication (Transceiver)
CU
Control Unit
dB
Dezibel
dBm
Dezibel refer to 1mW
DC
Direct current
D-GPS
Differential global positioning system
DME
Distance measuring equipment
EMK (EMF)
Electromotive force
EMV
Electrical magnetic interference
EEPROM
Electrical erasable programable read only memory
EXT
External
FTZ
Fernmelde-Technisches Zentralamt
ft
Feet
ICAO
Internationale civil aviation organization
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CU 5502 - ( )
ILL.A
Illumination.A
ILL.B
Illumination.B
I/O ports
Input/Output ports
GND
Ground
HSI
Horizontal situation indicator
Kbit/s
Data transfer rate
LBA
Luftfahrt-Bundesamt
LCD
Liquid crystal display
MAX
Maximum
MTBF
Mean time between failure
NAV
Navigation
N.C.
Not connected
NF-Signal
Audio signal
NOVRAM
Non volatile random acces memory
NVG
Night vision goggle
OUT
Output
/ON
ON/OFF function
PTT
Push-To-Talk
PRG
Program mode
PWR
Power
RAM
Random acces memory
RD
Read
RMI
Radio magnetic indicator
RX-A
RS 422 interface
RX-B
RS 422 interface
/SCK
Seriell clock display
SDA
Seriell data I2c-bus
Page 2-4
DV 60531.03/.04 Issue 07/97
CU 5502 - ( )
SCL
Seriell clock I2c-bus
SPARE
Spare
SQL
Squelch
TR
Transceiver
TX-A
RS 422 interface
TX-B
RS 422 interface
UBSW
Operating voltage switched
V5
Internal operating voltage + 5 V
VOR
Very high frequency omnidirectional range
VOL
Volume
/X
Input special function, low activ
ZF
Intermediate frequency
DV 60531.03/.04 Issue 07/97
Page 2-5
CU 5502 - ( )
Fig. 2-1 Installation dimensions for the Control unit CU 5502 - ( )
Page 2-6
DV 60531.03/.04 Issue 07/97
CU 5502 - ( )
Table of contents
Section
3
3.1
3.2
3.2.1
3.2.2
3.2.3
3.2.4
3.3
3.3.1
3.3.2
3.3.3
3.3.4
3.4
Controls and indicators
Operating instructions
Preparation
Switching on the control unit
REC/ADF/BFO mode
Adjusting the volume
Operation of the various modes
Frequency setting mode
Frequency preselection mode
Switching on the stopwatch
Display the Software-Version
Safety precautions
3-1
3-3
3-3
3-3
3-3
3-4
3-4
3-5
3-5
3-6
3-6
3-7
Fig. 3-1
Front panel of control unit
3-1
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Operation
Page
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Section
3.1
3
Operation
Controls and indicators
Fig. 3-1 Front panel of control unit
Meaning of symbols on the controls
Symbol
1
TMR
3
4
6
Description
Function
Function key
Switching the stopwatch on and off
-
Minus key
Reducing the volume
+
Plus key
Increasing the volume
Exchange key
Press key and hold for more than 2 seconds
Changeover between the frequency setting mode and
frequency presetting mode
Press key for less than 2 seconds
Exchange of preset frequency and active frequency
DV 60531.03/.04 Issue 07/97
Page 3-1
CU 5502 - ( )
Symbol
Description
Function
Pressing the - and + keys simultaneously activates the
test function. The needle of the display unit moves to approximately 90° and all digits flash.
TEST
7
Frequency selector
switch (outer rotary
switch)
Switches the displayed frequency in steps of 10 kHz upwards or downwards. If rotated quickly the change takes
place in steps of 100 kHz.
8
Frequency selector
switch (inner rotary
switch)
Switches the display frequency in steps of 500 Hz steps
upwards or downwards. If rotated quickly the change takes place in steps of 2 kHz
9
Mode switch with four
detent positions
OFF position
Control unit and ADF receiver switched off
REC position
The system operates in reception mode
ADF position
The system operates in the ADF mode. the arrow is visible in the top line of the LC display.
BFO position
The system operates in the ADF/BFO mode
Liquid crystal display
Symbol
Description
Function
5
(Top line)
(active frequency)
Display of the active reception frequency
5
(Bottom line)
(preset frequency)
Display of preset rececption frequency)
2
(Top line)
Arrow visible: ADF mode switched on
Arrow not visible: ADF mode switched off
(Bottom line)
Display of the stopwatch
T
Connector on back of unit
15-pole subminiature, male
Push-in locking
Page 3-2
Equipment connector for connecting the aircraft cabling
DV 60531.03/.04 Issue 07/97
CU 5502 - ( )
3.2
Operating instructions
3.2.1
Preparation
Switch on the aircraft power supply (check that the circuit breaker for the ADF system is set).
WARNING
Do not switch on the control unit if engines or motors are being started up or shut down.
3.2.2
Switching on the control unit
a. Set the mode switch to REC.
NOTE
System initialization takes place, i.e. data is transmitted between the control unit and the
ADF receiver, for the first 5 to 10 seconds after power on. After completion of the initialization, the mode which was set before power off appears.
In all modes, disturbances of the ADF system are displayed in the form of fault messages.
r E2 synthesizer failed, lock detect error
r E5 interface fault
A comprehensive description of the various modes follows the general operating instructions.
3.2.3
REC/ADF/BFO mode
a. Press both - and + keys simultaneously (test modes). All the segments in the LC display shall flash
and the needle of the connected display unit shall simultaneously deflect by approximately 90°.
b. Set the HDG setting on the display unit so that the 0° / 360° scale appears.
c. Using the frequency selector switches, set the required NDB station and monitor the identification
signal. For A1 identification the BFO mode must be selected (set the mode switch to BFO).
d. After checking the identification signal, select the ADF mode (set the mode switch to ADF). The
needle moves in the direction of the set NDB station.
e. Depending on the flight procedure, set the compass heading using the HDG setting.
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3.2.4
Adjusting the volume
The volume is adjusted for monitoring received signals by using the “+” and “-” keys. The volume is
shown in the bottom line by means of a numerical value between "0" (quiet) and “63" (loud). The symbol ”V" is placed before the numerical value. The indicated value remains visible for approximately
1 second after the key is released.
3.3
Operation of the various modes
The ADF system contains various functions which are performed under two modes. The modes are selected by pressing and holding the exchange key on the control unit for more than 2 seconds.
Frequency setting mode
Display of the active frequency in the top line. The bottom line is switched off. The active frequency can
be directly changed using the frequency selector switches.
Frequency preselection mode
Display of the active and preset frequency. A new frequency can be preset using the frequency selector
switches. Pressing the exchange key changes over between the active and preset frequencies.
NOTE
All mode or frequency changes are automatically stored after 2 seconds. This means that
changes which are made immediately before switching off are not stored.
Page 3-4
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3.3.1
Frequency setting mode
The active frequency is shown in the top line and the bottom line is switched off.
The active frequency can be changed using the frequency selector switches.
The set frequency remains stored even with the unit switched off.
Change of mode
To change the mode, press the exchange key and hold for at least 2 seconds.
3.3.2
Frequency preselection mode
The last active and preset frequencies appear in the top and bottom lines respectively.
The preset frequency (bottom line) is set using the frequency change switches.
Pressing the exchange key changes over between the active and preset frequencies.
NOTE
The ADF receiver is always ready to receive on the frequency shown in the top line.
Change of mode
To change the mode, press the exchange key and hold for at least 2 seconds.
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3.3.3
Switching on the stopwatch
a. Pressing the TMR key starts the stopwatch. The frequency setting mode is immediately selected
and the previously set mode is stored. The time is counted up 1 second at a time starting at 0 and
displayed in the bottom line. The symbol “T” appears before the time.
b. Pressing the TMR key a second time stops the stopwatch. The elapsed time is shown in the bottom
line and the “T” is shown flashing to the left of the time.
c. Pressing the TMR key a third time resets the stopwatch to 0. The symbol “T” is deleted from the bottom line. If the stopwatch is not re-started within 2 seconds, a changeover to the previously stored
mode takes place.
3.3.4
Display the Software-Version
Press and hold the + key whilst the unit is being switched on and wait until the version number is displayed. As long as the + key is held pressed, the following is shown in the top line.
On the left, two positions of the version number of the ADF-Receiver.
Right two positions of the version number of the Control Unit.
Release the + key. The ADF receiver is always ready to receive on the frequency shown in the top line.
Page 3-6
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3.4
Safety precautions
r Switch off the unit when starting engines.
r The unit must be protected from the aircraft supply system by a separate circuit breaker.
r ADF equipment is sensitive to radio interference. Such interference includes the following:
Atmospheric disturbances caused by weather conditions (thunderstorms, thundery
atmosphere).
Static charging of the aircraft airframe when flying through damp layers with ice particles.
In both cases this can cause uncontrolled deflection of the display unit. In the case of static
charging, reception of an NDB station can fail completely for several minutes.
Disturbances caused by the aircraft supply system due to generators or ignition systems can
substantially reduce the range to NDB stations. This can be checked as follows during the
flight:
When receiving a disturbed NDB station
a.briefly switch off the generator and observe the effect,
b.set the ignition switch for piston engines to a magneto 1, magneto 2 and 0 in turn
and observe the effect. If disturbance is detected, consult a repair facility!
r Dawn/dusk and night effect. Particularly during dawn/dusk, unusable bearings can
arise if changes in the ionization layer influence the phases of ground and ionospheric waves. These influences are also possible at night.
r Shore errors. When flying over the sea, bearing errors can occur due to the reflection
of electromagnetic waves on the coast. For this reason bearings are only correct
which are taken at 90° to the coast.
r When overflying an NDB station the needle of the display unit should ideally move either through 90° (station to the right) or over 270° (station to the left) relative bearing
until after overflying it stabilizes in the 180° direction.
Because of a cone of uncertainty of æ 45° which is unavoidable for physical reasons, it must
be taken into account that an unstable indication is obtained when flying through this cone of
uncertainty and a multiple needle deflections are possible. After departure from the cone, the
indication then stabilizes at a value of about 180°. This can vary from NDB to NDB.
r Approaches to radio transmitters can then only be correctly made if these are expressly listed in the AIP as navigational aids.
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