Becker BXP6401-1-(01), BXP6401-2-(01) Installation And Operational Manual

NSCM: D2356

AIR TRAFFIC CONTROL RADAR BEACON SYSTEM / MODE SELECT

(ATCRBS / MODES) AIRBORNE EQUIPMENT

TransponderLevel2es

BXP6401-1-(XX) Class1

BXP6401-2-(XX) Class2

INSTALLATIONANDOPERATION

ManualDV69801.03PN0584.053-071

Issue 3 September 2011

Becker Flugfunkwerk GmbH · Baden-Airpark B 108 · 77836 Rheinmünster · Germany

Telephone [phone] / 305-0 · Fax [phone] / 305-217

http://www.becker-avionics.de · e-mail: [e-mail] or [e-mail]

Issue 3

September 2011 34-50-08

© Copyright by Becker Flugfunkwerk GmbH 77836 Rheinmünster / Germany

All rights reserved. Subject to technical changes.

34-50-08 Issue 3

September 2011

RECORD OF REVISIONS

REV.

NO.

ISSUE

DATE

INSERTED REV.

NO.

ISSUE

DATE

INSERTED

DATE BY DATE BY

1
2
3

February 2007

April 2007

September 2011

02/07
04/08
09/11

Becker
Becker
Becker

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LIST O F EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

Title Page TP-1 Sept. 2 0 1 1 Operation 3-1 Sept. 2011

TP-2 3-2 Se p t . 2011

3-3 Se p t . 2011

Record of R e v i s i o n s R O R - 1 Sept. 2011 3-4 Se p t . 2011

ROR-2 Se p t . 2 0 1 1 3 - 5 Sept. 2 0 1 1

3-6 Se p t . 2011
3-7 Se p t . 2011

List of E f f e c t i v e Pages LEP-1 Sept. 2 0 1 1 3-8 Sept. 2 0 1 1

LEP-2 S e p t . 20 1 1 3 - 9 Sept. 2 0 1 1

3-10 Sept. 2011

Introduction Intro-1 Sept. 2 0 1 1

Intro-2 Sept. 2 0 1 1
Intro-3 Sept. 2 0 1 1
Intro-4 Sept. 2 0 1 1

Table of C o n t e n t s I-I Sept. 2011

I-II Sept. 2011

General Description 1 - 1 Se p t . 2011

1-2 Sept. 2011
1-3 Sept. 2011
1-4 Sept. 2011
1-5 Sept. 2011
1-6 Sept. 2011
1-7 Sept. 2011
1-8 Sept. 2011

Table of C o n t e n t s II-I Sept. 2011

II-II Sept. 2011

Installation 2-1 Sept. 2011

2-2 Sept. 2011
2-3 Sept. 2011
2-4 Sept. 2011
2-5 Sept. 2011
2-6 Sept. 2011
2-7 Sept. 2011
2-8 Sept. 2011
2-9 Sept. 2011
2-10 Sept. 2 0 1 1
2-11 Sept. 2 0 1 1
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Table of C o n t e n t s III-I Sept. 2011

III-II S e p t . 2011

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INTRODUCTION

1. General

The single b l o c k Mode S t r a n s p o n d e r BXP6401-X-(XX) is d e s c r i b e d in this m a n u a l
“Installation and O p e r a t i o n ” .

2. Manufacturer

The Mode S transponder was d e v e l o p e d and is m a n u f a c t u r e d by :

Becker Flugfunkwerk G m b H
Baden-Airpark B 1 0 8
77836 Rheinmünster / Germany

Telephone: +49 ( 0 ) 7229 / 3 0 5 - 0
Telefax: +49 (0) 7 2 2 9 / 305-217
http://www.becker-avionics.de
e-mail: [e-mail] o r [e-mail]

CERTIFIED QUALITY S Y S T E M

The Becker q u a l i t y management system i s certified according t o :

DIN EN I S O 9001:2008
and EN9100:2003/AS9100B Ce r t i f i c a t e Registration No. 1 2 210 20985 T M S

LICENSES AND A P P R O V A L S

DE.21G.0075 Approval as m a n u f a c t u r e r to EASA P A R T 21

DE.145.0166 Approval as m a i n t e n a n c e organization to

EASA PART 1 4 5

3. Safety i n f o r m a t i o n

n

The installation o f the Mode S transponder into a n aircraft may b e carried
out only b y an authorized i n s t a l l a t i o n company. The c o u n t r y regulations
always have t o be observed.

n

Do not c o n n e c t the unit t o AC sources.

n

Make sure t h a t the unit i s connected to a DC source £ 33 V D C .

n

If no l o a d is connected t o pin 6 o f P9, the u n i t should be p r o t e c t e d from the
aircraft power s u p p l y by a d e d i c a t e d 3 A c i r c u i t breaker.

n

If an e x t e r n a l load is c o n n e c t e d to pin 6 of P9, t h e circuit breaker s h o u l d
be a 5 A type.

n

Do not c o n n e c t the unit w i t h reversed polarity t o the DC s o u r c e .

n

Do not s w i t c h on the u n i t before the a i r c r a f t engines are s t a r t e d . Switch off
the unit b e f o r e the engines a r e shut down.

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

n

Do not o p e r a t e the unit u n d e r ambient temperatures b e l o w -20 °C a n d abo

-

ve +70 ° C .

n

Voltages > 4 2 V are p o s s i b l e within the t r a n s p o n d e r .

n

The programming o f the address m o d u l e AM6400-1 with t h e ICAO 24-bit
address of t h e aircraft must b e carried out b y an authorized i n s t a l l a t i o n
company or t h e manfacturer.

4.

Layout o f manual

The manual i s divided into t h r e e chapters:

- GENERAL D E S C R I P T I O N

- INSTALLATION

- OPERATION

5.

Revisions o f the manual

All changes t o the manual a r e recorded consecutively o n the pre-page “ R e c o r d of
Revisions”.

6.

List o f abbreviations

AA Ai c r a f t A d d r e s s (24-bit I C A O )
ADLP Avionics Data L i n k Processor
ADS-B Automatic D e p e n d e n t Surveillance-Broadcast
AI Aircraft Identifier
ALT Altitude or t r a n s p o n d e r ALT mode
ATC Air Traffic C o n t r o l
BIT Built-In Test
CBIT Continuous B u i l t - I n Test
CCS Co m p a n y Call Sign
CS Call Sign
DV Manual identification n u m b e r
EASA European A v i a t i o n Safety Agency
ELS Elementary S u r v e i l l a n c e
EHS Enhanced Su r v e i l l a n c e
es e = E x t e n d e d squitter and s = SI c a p a b i l i t y
FAA F e d e r a l Av i a t i o n Administration
FL Flight Level
FMS Fl i g h t Management System
FN F l i g h t Number
GICB G r o u n d Initiated Comm-B
GND Ground
ICAO I n t e r n a t i o n a l Civil Aviation O r g a n i z a t i o n
IBIT Initiated Built-In T e s t
ID I d e n t i f i e r
IDT Ident ( I d e n t i f i c a t i o n )
IFR Instrument F l i g h t Rules

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

MTL Minimum Triggering L e v e l
ON Transponder O N mode (without a l t i t u d e transmission)
NSCM Nato Supply C o d e of Manufacturers
PBIT Power-on Built-In T e s t
PN Part Number
R Reply
RX Receiver
SBY St a n d b y mode
SEL Selection
SI Surveillance Identifier
SPI Special P o s i t i o n Identification Pulse
STO Store
SUPP S u p p l y voltage D C
TCAS Traffic C o l l i s i o n and Alert A v o i d a n c e System (US)
TIS Traffic Information S e r v i c e
TN T a i l Number
TX Transmitter
VFR Visual Flight R u l e s
XPDR Transponder

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TABLE OF CONTENTS

GENERAL DESCRIPTION Page

1. Application 1-1

2. General description 1-1

3. Technical data 1-2

4. Software 1-7

5. System approvals 1-7

6. Equipment 1-7

7. Accessories 1-7

INSTALLATION AND OPERATION BXP 6401-X-(XX)

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GENERAL D E S C R I P T I O N

1. Application

The single block Mode S transponder BXP6401-X-(XX) is the airborne component of the
Air Traffic Control (ATC) Mode S Secondary Surveillance Radar system with added
ADS-B Transmitting Subsystem functionality. It acts as a part of the surveillance system
in two ways:

l

as a M o d e S Transponder w h i c h provides responses t o ground station i n t e rroga

-

tions and allows air traffic control to locate, identify and track aircraft

l

as an ADS-B Broadcast-Only System which spontaneously broadcasts aircraft in

-

formation

2.

General d e s c r i p t i o n

A. The B X P 6 4 0 1 - X - ( X X ) t r a n s p o n d e r is d e s i g n e d a s a s i n g l e block unit a n d is in-

tended f o r installation in t h e instrument panel o f aircraft. T h e d i m e n s i o n s cor­respond t o the standard i n s t r u m e n t size with a 58 m m ( 2 ¼ inch) d i a m e t e r .

B. All c o n t r o l e l e m e n t s are l o c a t e d o n the f r o n t panel of t h e unit. The t w o 25-pin

unit c o n n e c t o r s for connection t o the aircraft i n t e r w i r i n g , the 5 - p i n s u b m i n i a t u ­re c o n n e c t o r for the A d d r e s s Module AM6400-1-(XX) a n d the T N C a n t e n n a
socket a r e located at t h e rear side o f the u n i t .

C. Se r i a l interfaces R S - 4 2 2 a r e available a t t h e unit c o n n e c t o r s .

D. Th e Mode S t r a n s p o n d e r provides t h e f o l l o w i n g features:

(1) In t h e selective mode ( M o d e S), the G r o u n d Control can i n t e r r o g a t e the

transponder individually u s i n g an ICAO-24-bit a d d r e s s , which is u n i q u e
to the p a r t i c u l a r aircraft.

(2) Support o f the SI c o d e (Surveillance Identifier)

(3) Register c a p a b i l i t y for elementary s u r v e i l l a n c e (ELS) and e n h a n c e d sur-

veillance (EHS)

(4) Extended s q u i t t e r s transmission

(5) Data l i n k capability

(6) GPS receiver connection capability
(7) ADS-B Broadcast-Only System Class B0 i.e. broadcasts following data:

- Airborne Position Message

- Surface Position Message

- Airborne Velocity Message

- Extended Squitter Aircraft Status Message

NOTE:

Actual generation o f each ADS-B m e s s a g e type and d a t a within each

message depends o n availability of navigation data and GPS engine ca

-

pabilities.

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

E. Inherent f e a t u r e s :

(1) Mode A - in t h i s mode, the 4 0 9 6 character code s e t on the c o n t r o l head

is sent a s a reply t o interrogation from a ground station.

(2) Mode C - in t h i s mode, the e n c o d e d altitude is s e n t in addition t o the

mode A r e p l y . The altitude i n f o r m a t i o n must be d e l i v e r e d from an e x t e r ­nal device ( e . g . Becker Blind E n c o d e r BE6400).

(3) A s p e c i a l identifier pulse ( S P I ) can be a c t i v a t e d by pressing t h e IDT

button in M o d e A/C and M o d e S.

(4) Selftests ( B I T s ) . An Initiated B u i l t - I n Test (IBIT), a Continuous Built-

In Test ( C B I T ) and a P o w e r - o n Built-In Test ( P B I T ) are integrated i n
the transponder.

3. Technical d a t a

A. General d a t a

Supply voltage 10.0 V t o 33.0 V D C

Typical consumption 50 mode S replies/sec. + S q u i t t e r

0.37 A a t 14 V ( i l l u m i n a t i o n off)

0.22 A a t 28 V ( i l l u m i n a t i o n off)

0.43 A a t 14 V ( i l l u m i n a t i o n max.)

0.25 A a t 28 V ( i l l u m i n a t i o n max.)
in standby m o d e :

0.22 A a t 14 V ( i l l u m i n a t i o n off)

0.14 A a t 28 V ( i l l u m i n a t i o n off)

0.28 A a t 14 V ( i l l u m i n a t i o n max.)

0.16 A a t 28 V ( i l l u m i n a t i o n max.)

Panel illumination control input

Illumination control c u r r e n t max. 1 m A at 28 V

Illumination color ( d i s p l a y and buttons) white

Serial interfaces RS-422

Data link c a p a b i l i t y 255 GICB r e g i s t e r s

DME suppression:

- input v o l t a g e < 2 V (no suppression)
> 8 V (suppression)

- output v o l t a g e < 0.5 V (not active)
> 18 V (active)

External Ident i n p u t :
“0” (active) £ 3.5 V
“1” (passive) ³ 4.0 V
source (shorted t o GND) £ 10 m A

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Ground detection i n p u t :
“ground” £ 0.5 V
“airborne” ³ 2 V
source (shorted t o GND) £ 10 m A

Power-up time 2 s (including internal s e l f - t e s t PBIT)

Internal fuse p r o t e c t i o n F 5 A

External fuse p r o t e c t i o n T 3 A (circuit breaker) *

* NOTE:

5 A c i r c u i t breaker if a n external load i s connected to p i n 6 at P 9 .

Operating temperature r a n g e -20 °C t o +55 °C

(short-time +70 ° C )

Storage temperature r a n g e -5 5 °C to + 8 5 ° C

Operating altitude 50000 f t . max. (class 1 )

15000 ft. m a x . (class 2)

Mode S Class 1 o r 2, Level 2 e s

- extended s q u i t t e r capability

- surveillance i d e n t i f i e r (SI code)

Conformity RTCA DO-181C,

FAA TSO-C112, c l a s s 2A or 2 B ,
EUROCAE ED-73B, L e v e l 2es,
EASA ETSO-2C112a, c l a s s 1or 2

Environmental conditions in accordance w i t h EUROCAE/
(see also p a r a g r a p h D) RTCA ED-14D/DO-160D

Mechanical dimensions :

- Front p a n e l 61.3 x 6 1 . 3 mm (H x W)
(2.413 x 2 . 4 1 3 inch)

- Instrument s i z e diameter 58 mm ( 2 ¼ inch)

- Case d e p t h

without antenna s o c k e t 192 mm ( 7 . 5 9 9 inch)
with antenna s o c k e t 206 mm ( 8 . 1 1 0 inch)
with address m o d u l e 239 mm ( 9 . 4 0 9 inch)

Weight approx. 0.8 k g (1.764 lb)

B. Receiver d a t a

Operating modes Mode A/C/S,

depending on i n t e r r o g a t i o n

Receive frequency 1030 MHz ± 0.1 MHz ( m o d e A/C)

1030 MHz ± 0.01 MHz ( m o d e S)

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Sensitivity (MTL) - 74 dBm ± 3 dB ( f o r 90 % r e p l y rate

in mode A / C and 99 % in mode S )

Selectivity ± 15 M H z > 40 d B

± 25 M H z > 60 d B

Dynamic range ³ 60 d B

Bandwidth ± 3 M H z < 3 d B

Modulation (Mode A / C ) PAM (Pulse A m p l i t u d e Modulation)

Modulation (Mode S ) D P S K (Differential P h a s e S h i f t

Keying)

Side Lobe S u p p r e s s i o n 3-pulse m e t h o d (Mode A/C)

P5 (Mode S )

Nominal impedance 50 W

C. Tr a n s m i t t e r data

Transmit frequency 10 9 0 MH z ± 1 M H z

Transmit modulation 1 2 M O M 1 D PAM (Pulse A m p l i t u d e

Modulation)

Transmitter type Solid s t a t e

Transmit power ( c l a s s 1) ³ 125 W (+ 21 d B W ) at antenna e n d

terminal and ³ 250 W a t unit output

Transmit power ( c l a s s 2) ³ 70 W (+ 18.5 d B W ) at antenna e n d

terminal and ³ 140 W a t unit output

Reply rate c a p a b i l i t y (mode A/C) at least 1 2 0 0 mode A/C r e p l i e s

per second f o r a 15 p u l s e coded
reply, can b e limited to 5 0 0 . . . 1 2 0 0

Reply rate c a p a b i l i t y (mode S) at least 5 0 mode S r e p l i e s in

one-second interval ( t h e r e o f at
least 16 l o n g formats)

Mode S s q u i t t e r rate (approx.) Acquisition squitter 4 / s e c .

Extended squitter 1 / s e c .

Reply code ( m o d e A) ICAO coding s y s t e m with 4096

pulse reply p o s s i b i l i t i e s (octal
code)

Altitude code ( m o d e C) ICAO coding s y s t e m 100 ft. s t e p s

from -1000 t o 62700 ft.

Altitude code ( m o d e S) 2 5 ft. or 1 0 0 ft. steps

(depending on s o u r c e )

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

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34-50-08 S e p t e m b e r 2011

Transmit pulse s h a p e pulse width 0 . 4 5 m s ± 0.1ms ( m o d e A/C)

pulse width 0 . 5 m s ± 0.05ms ( m o d e S)
rise time 0 . 0 5 to 0.1ms
fall time 0 . 0 5 to 0.2ms

Nominal output i m p e d a n c e 50 W

D. En v i r o n m e n t a l conditions i n a c c o r d a n c e

with E U R O C A E / R T C A ED-14D/DO-160D

Input v o l t a g e range 10.0 t o 3 3 . 0 V D C

Low o p e r a t i n g temperature -20 ° C

High o p e r a t i n g temperature +55 ° C

High s h o r t - t i m e operating temperature +70 °C

Storage t e m p e r a t u r e range - 5 5 °C t o + 8 5 °C

In-flight l o s s of cooling Cat. Z , no auxiliary c o o l i n g required

Altitude 50 , 0 0 0 ft. max. ( c l a s s 1)

15,000 f t . max. (class 2 )

Humidity Cat. A / +50° C ; 95%, 48 h

Vibration r e s i s t a n c e Cat. S , test curve M

Cat, U , test curve G

Operational s h o c k s 6 g i n a n y direction

Crash s a f e t y 20 g shocks

20 g acceleration

Magnetic effect Category Z

Environmental c a t e g o r i e s :

Env.Cat. [ D 1 Z ] B A B [ ( S M ) ( U G ) ] X X X X X X Z B A B A [ W W ] B [ A 3 E 3 X ] X X A

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

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E. Environmental q u a l i f i c a t i o n

EUROCAE/RTCA ED-14D/DO-160D

Con d i t ion Sec t i o n Cat . Des c r i p tion

Tem p e r ature a n d Altit u d e 4.0 D1 Equi p m e n t test e d to Cat e g o ry D1
Low G r ound S u r v ival T e m p eratur e 4. 5 . 1 D1 - 55 °C
Low O p eratin g T emperat u r e 4.5.1 D1 BXP6 4 0 1 -X-(XX) : - 20 °C ,
Hig h G round S u r vival T e m p 4 .5.2 D1 +85 ° C
Hig h S hort-T i m e Operat i n g Temp. 4.5.2 D1 +70 ° C
Hig h O perati n g Temp. 4.5 . 2 D1 + 5 5 °C
In- f l i ght Lo s s of Coo l i n g 4. 5 . 4 Z No forced c o oling r e q uired – N o test

req u i r ed

Alt i t u de 4 . 6 .1 D1

A1

BXP 6 4 0 1-1-(XX ) : 50,000 f t (clas s 1 )

BXP 6 4 0 1-2-(XX ) : 15,000 f t (clas s 2 )
Dec o m p ression 4.6 . 2 N o t app l i c a ble
Ove r p r essure 4. 6 . 3 N ot app l i c a ble
Tem p e r ature V a r iation 5.0 B Eq u ipment t e sted t o C ategor y B
Hum i d i ty 6.0 A Eq u ipment t e sted t o C ategor y A
Sho c k and C r a s h Safet y 7 . 0 B Eq uipmen t t ested t o Catego r y B
Vib r a t ion 8.0 S

U

Cat . S , vibr a t i on tes t c urve M

Cat . U , vibr a t i on tes t c urve G
Exp l o s ion Pr o o f n ess 9.0 X No test r e q u ired, E q u ipment i d entifi e d

as C a tegory X
Wat e r p roofnes s 1 0.0 X No t e s t requi r e d , Equi p m e n t ide n t i f ied

as C a tegory X
Flu i d s Susce p t i b ility 11.0 X No t e st req u i r e d, Equ i p m ent id e n t i fied

as C a tegory X
San d a nd Dus t 12. 0 X N o test r e q u ired, E q u ipment i d entifie d

as C a tegory X
Fun g u s Resis t a n c e 13. 0 X N o test r e q u ired, E q u ipment i d entifie d

as C a tegory X
Sal t S pray 1 4 .0 X No te s t requir e d , Equipm e n t ident i f i e d

as C a tegory X
Mag n e t ic Eff e c t 1 5 .0 Z Eq u i p m ent i s C lass Z
Pow e r Input 16. 0 B E q u i pment t e s ted t o C ategor y B
Vol t a g e Spik e 17 . 0 A Equipme n t tested t o Categ o r y A
Aud i o Freq. C o n ducted S u scepti

-

bil i t y

18. 0 B E q u i pment t e s ted t o C ategor y B

Ind u c e d Sign a l Suscept i b i lity

19. 0 A E q u i pment t e s ted t o C ategor y A
Rad i o Freque n c y Suscep t i b ility 2 0 .0 WW Eq u i pment t e s ted t o C a tegory W W
Spu r i o us RF E m i ssion 21.0 B Equi p m e n t tes t e d to Ca t e g o ry B
Lig h t n ing In d u c e d Tran s i e nts Su s

-

cep t i b ility

22. 0 A3E3X Eq u i pment t e s ted t o C ategor y A 3 E3X

Lig h t n ing Di r e c t Effec t s

23. 0 X N o test r e q u ired, E q u ipment i d entifie d

as C a tegory X

Ici n g 24. 0 X N o test r e q u ired, E q u ipment i d entifie d

as C a tegory X

Ele c t r ostatic D i scharg e 25 . 0 A E q u ipment t e sted t o Categor y A

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

4. Software

l

The transponder B P X 6 4 0 1 - X - ( X X ) is controlled b y a microcontroller i n the control
head and t h e core unit. T h e software criticality i s determined to b e Level C i n
accordance with E U R O C A E / R T C A document ED12B/DO-178B.

5. System a p p r o v a l s

EASA.21O.322 ETSO-2C112a

FAA TSO-C112

6.

Equipment

Des t i n ation D e scripti o n Artic l e - No.:
BXP 6 4 0 1-1-(01 ) Tra n s p onder,

Lev e l 2, cla s s 1

Art i c l e-No. 0 5 8 8.687-9 1 5

BXP 6 4 0 1-2-(01 ) Tra n s p onder,

Lev e l 2, cla s s 2

Art i c l e-No. 0 5 8 8.709-9 1 5

AM6 4 0 0 -1-(01) Add r e s s Modu l e A r ticle- N o . 0572.9 4 2 - 915
BE6 4 0 0 -01-(01 ) Bli n d Encode r Artic l e - N o. 05 9 2 . 1 37-915

7. Accessories

AMP6400-1 Address Module p r o g r a m m e r A r t i c l e - N o . 0584.843-954

kit (software a n d cable),
parallel interface

AMP6400-2 Address Module p r o g r a m m e r A r t i c l e - N o . 0604.054-954

kit (software, a d a p t e r and cable),
USB interface

CK4401-C S t a n d a r d co n n e c t o r kit Article-No. 0552.798-954

1 D-Sub p l u g , 25-pin
(crimp version)

CK4401-S Standard c o n n e c t o r kit A r t i c l e - N o . 0552.801-954

1 D-Sub p l u g , 25-pin
(soldering version)

CK6400-C E x t e n d e d co n n e c t o r kit Article-No. 0586.064-954

1 D-Sub p l u g , 25-pin
1 D-Sub j a c k , 25-pin
(crimp version)

CK6400-S Extended c o n n e c t o r kit Ar t i c l e - N o . 0586.072-954

1 D-Sub p l u g , 25-pin
1 D-Sub j a c k , 25-pin
(soldering version)

TNC coaxial c o n n e c t o r for RG-58C/U Article-No. 0 5 5 1 . 6 9 4 - 2 7 7
(crimp version)

TNC coaxial c o n n e c t o r for RG-223/U Ar t i c l e - N o . 05 5 1 . 7 3 2 - 2 7 7
(crimp version)

Page 1-7

34-50-08 September 2011

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

TNC coaxial c o n n e c t o r for RG-58C/U Article-No. 0 5 5 2 . 7 8 1 - 2 7 7
and RG-223/U ( s o l d e r i n g version)

or spare c o n n e c t o r Article-No. 0725.900-277

1A032 T r a n s p o n d e r antenna A r t i c l e - N o . 0707.007-952

Coaxial connectors f o r antenna 1A032:

BNC antenna c o n n e c t o r for RG-58C/U ( c r i m p ) Article-No. 0 5 5 1 . 7 0 8 - 2 7 7

BNC antenna c o n n e c t o r for RG-223/U ( c r i m p ) Article-No. 0551.740-277

BNC antenna c o n n e c t o r for RG-58C/U
and RG-223/U ( s o l d e r i n g ) Article-No. 0552.771-277

Manuals:

Installation and O p e r a t i o n BXP6401-X-(XX) Article-No. 0584.053-071

Maintenance and R e p a i r BXP6401-X-(XX) Article-No. 0584.061-071

Data Transfer I n t e r f a c e Protocol Article-No. 0590.258-071
BXP640X-XX-(XX)

Installation and O p e r a t i o n BE6400-01-(XX) A r t i c l e - N o . 0594.547-071

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 1-8

34-50-08 S e p t e m b e r 2011

TABLE OF CONTENTS

INSTALLATION Page

1. General 2-1

2. Inspection before installation 2-1

3. Mechanical installation 2-1

4. Aircraft wiring 2-1

5. Installing the transponder antenna 1A032 2-4

6. Programming of the Address Module 2-6

7. Avionics data transfer 2-6

8. GPS Configuration 2-7

9. Settings after installation 2-7

10. Checking after installation 2-9

Fig. 2-1 Installation dimensions BXP6401-X-(XX) 2-11
Fig. 2-2 Installation dimensions 1A032 2-12
Fig. 2-3 Proposal for aircraft wiring BXP6401-X-(XX) with serial 2-13

encoding altimeter

Fig. 2-4 Proposal for aircraft wiring BXP6401-X-(XX) with paralle 2-14

encoding altimeter
Fig. 2-5 RS-232 serial encoding altimeter connection 2-15
Fig. 2.6 RS-232 GPS receiver connection P9 2-15

INSTALLATION AND OPERATION BXP6401-X-(XX)

Page II-I

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BLANK

INSTALLATION AND OPERATION BXP6401-X-(XX)

Page II-II

34-50-08 September 2011

INSTALLATION

1. General

Installation of t h e transponder BXP6401-X-(XX) i s depending on t h e aircraft type
and its c l a s s i f i c a t i o n as well a s indivitual requirements. T h e r e f o r e , only general i n

-

formation can b e provided in t h i s section.

2.

Inspection b e f o r e installation

Before the t r a n s p o n d e r is installed o n an aircraft, a visual inspection f o r possible
transport damages s h a l l be done.

Please l o o k for the f o l l o w i n g defects:

(1) Dirt, dents, s c r a t c h e s , corrosion, broken f a s t e n i n g elements on h o u s i n g

and h o u s i n g parts.

(2) Dirt and s c r a t c h e s on nameplate, f r o n t plate and i n s c r i p t i o n s .

(3) Dirt, bent o r broken pins, c r a c k e d insert of u n i t connector and a n t e n n a socket.

(4) Dirt, stiffness a n d mechanical damage t o the pushbuttons, r o t a r y switches and

LC d i s p l a y .

(5) Missing screws.

3. Mechanical i n s t a l l a t i o n

The t r a n s p o n d e r is designed f o r installation in t h e instrument p a n e l o f an a i r c r a f t . I t
is c o n s t r u c t e d for mounting b e h i n d the panel. T h e circular c u t o u t and t h e m o u n t i n g
holes a r e to be d r i l l e d in accordance w i t h the s m a l l i n s t r u m e n t size. T h e m o u n t i n g
shall b e at least 3 0 cm away f r o m the a i r c r a f t m a g n e t i c compass, t o a v o i d any i n t e r

-

ference f r o m transponder.

The n e c e s s a r y dimensions are g i v e n in Fig. 2 - 1 . Attachment i s b y means o f f o u r
screws M 3 x 1 2 , which are i n c l u d e d in the d e l i v e r y .

Blind E n c o d e r installation:

For i n s t a l l a t i o n of the B e c k e r Blind Encoder B E 6 4 0 0 the c o r r e s p o n d i n g m a n u a l (Arti

­cle-No. 0 5 9 4 . 5 4 7 - 0 7 1 ) has to b e noticed. The B l i n d Encoder B E 6 4 0 0 i s intended t o
be c o n n e c t e d to the J 8 connector of t h e transponder a n d c a n be u s e d o n l y on i n s t a l

­lations t h a t do not u t i l i z e this connector f o r other e q u i p m e n t . T h e Blind E n c o d e r i s
directly c o n n e c t e d to the t r a n s p o n d e r , without any i n t e r w i r i n g .

4.

Aircraft w i r i n g

A. The a i r c r a f t w i r i n g of t h e t r a n s p o n d e r is s h o w n on Fig. 2 - 3 and Fig. 2 - 4 .

CAUTION :

For i n s t a l l a t i o n s in a m o r e severe electromagnetical e n v i r o n m e n t use s h i e l d e d
cable c o n n e c t o r s and a c o m m o n shielding for t h e transponder i n t e r w i r i n g .

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34-50-08 September 2 0 1 1

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

B. RF c o n n e c t o r

The u n i t RF connector i s of the T N C female t y p e . T h e antenna c a b l e s h a l l be
of l o w - l o s s 50 W c a b l e , at least R G 58C/U o r b e t t e r RG 2 2 3 / U t y p e .

Pin N a me Pin D e script i o n So u r ce Destin a t i o n Recom m e n d ed

cab l e type

Ant e n n a

50 W TNC a n t e n na con

-

nec t o r , fema l e

bi- d i r ectiona l t o the
ant e n n a

bi- d i r ectiona l t o the
ant e n n a

RG5 8 C / U or
RG2 2 3 / U

C. Pi n connections o f t h e unit c o n n e c t o r P 9

The u n i t connector type i s D-SUB 25-pins m a l e .

Pin Pin N a me P i n Descri p t i o n S o u r ce Des t i n ation Recomme n

­ded c a ble
typ e

1 A1 Altitud e A 1 En c oding a l t imeter

(pa r a l lel in t e r f ace)

BXP 6 4 0 1-X-(XX ) AWG24

2 A2 Altitud e A 2

or

Enc o d i ng alt i m e t er
(pa r a l lel in t e r f ace)

BXP 6 4 0 1-X-(XX ) AWG24

GPS / E nable* Aircra f t DC su p p l y

gro u n d *

AWG 2 6

3 A4 Altitud e A 4

Enc o d ing altime­ter (p a r allel inter ­fac e

)

BXP 6 4 0 1-X-(XX ) AWG24

4 IDENT _ N IDE N T switch E x t ernal I D E NT but -

ton

BXP 6 4 0 1-X-(XX ) AWG26

5 EXT. S U P PRES

-

SIO N

Air c r a ft sup p r e s sion s y

-

ste m

Bi- d i r ectiona l B i -direc t i o n al C o a xial c a

-

ble

6 SWITC H E D PO

-

WER O U T

Swi t c h ed sup p l y volta

-

ge, I m ax = 1 A

BXP 6 4 0 1-X-(XX ) E n c oding a l t ime

-

ter

AWG 2 0

7 REPLY O U T Outp u t for ex t e r n al re

-

ply l a mp, a c t i v e LOW

BXP 6 4 0 1-X-(XX ) R e p ly lam p AW G 2 6

8 RX+ RS - 4 2 2 GPS r e c eiver* * GP S rece i v e r B X P 6401-X- ( X X ) 2 x A W G 26

9 RX- shi e l d ed

10 Illumin a t i o n A Il l uminat i o n contro l Ai r craft i l l uminati o n

vol t a g e

BXP 6 4 0 1-X-(XX ) AWG24

11 SUPP Sup p l y Aircra f t D C sup p l y BXP 6 4 0 1 -X-(XX ) AWG20

12 10 V to 33 V

13 GND D C suppl y g round, a d di

­tio n a l ly con n e c t ed to
pin 2 5

Air c r a ft DC s u p ply
gro u n d

BXP 6 4 0 1-X-(XX ) AWG20

14 B1 Al t i tude B 1 En c o d i ng al t i m e ter BXP6401 - X - (XX) 7 xAWG24

15 B2 Al t i tude B 2 (p a r a l lel i n t e r face)

16 B4 Al t i tude B 4

17 C1 Alt i t u de C1

18 C2 Alt i t u de C2

19 C4 Alt i t u de C4

20 D4 Alt i t u de D4

21 Not con n e c t ed — — — —

22

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34-50-08 S e p t e m b e r 2011

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Pin Pin N a me P i n Descri p t i o n S o u r ce Des t i n ation Recomme n

­ded c a ble
typ e

23 Illumin a t i o n B Il l uminat i o n contro l Ai r craft i l l uminati o n

vol t a g e

AWG 2 4

24 Not con n e c t ed — — — —

25 GND G r ound, a d d itiona l l y

con n e c ted to p i n 13

Air c r a ft DC s u p ply
gro u n d

BXP 6 4 0 1-X-(XX ) AWG20

*NOTE:

If parallel a l t i m e t e r and GPS r e c e i v e r is not u s e d then pin 2 serves as G P S Enable/Dis

-

able input ( a c t i v e LOW) should b e left not c o n n e c t e d .

**NOTE:

See F i g . 2.6 for R S - 2 3 2 GPS receiver c o n n e c t i o n details.

D. Pi n connections o f t h e unit c o n n e c t o r J 8

The u n i t connector type i s D-SUB 25-pins f e m a l e .

Pin

Pin N a me Pi n Desc r i p tion S o u r ce Des t i n ation R e c o mmende d

cab l e type

1 Not c o n n ected Reserve d f or pro t o c ol

sel e c t ion

— — —

2 GPS_E N GPS / E n a ble A i rcraft D C supp-

ly g r ound*

BXP 6 4 0 1-X-(XX ) AWG 2 6

3 GND Gr ound c o n n ection A ircraf t D C supp -

ly g r ound

BXP 6 4 0 1-X-(XX ) AWG 2 4

4 BSUPP BE6400 b l i nd enc o d e r

sup p l y **

BXP 6 4 01-X-( X X ) B E6400 —

5 Not c o n n ected — — — —

6 Not c o n n ected — — — —

7 Not c o n n ected — — — —

8 Not c o n n ected — — — —

9 Not c o n n ected — — — —

10 Not con n e c t ed Re s erved f o r SQ — — —

11 GND SWI T C H “W e ight-o n - w h eels”

sen s o r , acti v e LOW

Air c r a ft B X P 6 401-X- ( X X ) A W G 26

1213ALT S -

ALT S +

RS- 4 2 2 data i n t erfa

-

ce* * *

Ser i a l encod i n g
alt i m e ter

BXP 6 4 0 1-X-(XX ) 2 x A WG26 t w i

-

ste d p air, s h i e l

-

ded

14
15

TIS R X ­TIS R X +

RS- 4 2 2 data i n t erface A D L P BXP64 0 1 - X -(XX) 2 x A W G 2 6 twi

-

ste d p air, s h i e l

-

ded

16 Not con n e c t ed — — — —

1718TIS T X -

TIS T X +

RS- 4 2 2 data i n t erface B X P 6 401-X- ( X X ) A D L P 2 x A W G 2 6 twi

-

ste d p air, s h i e l

-

ded

19 Not con n e c t ed — — — —

20 Not con n e c t ed — — — —

21 GND Gr o u n d con n e c t ion Ai r c raft D C supp

-

ly g r ound

BXP 6 4 0 1-X-(XX ) AWG 2 4

22 Not con n e c t ed — — — —

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Pin

Pin N a me Pi n Desc r i p tion S o u r ce Des t i n ation R e c o mmende d

cab l e type

23 Not con n e c t ed — — — —

24 Not con n e c t ed — — — —

25 Not con n e c t ed — — — —

* N O T E :

If G P S receiver is n o t used pin 2 should b e l e f t not c o n n e c t e d .

** N O T E :

Do n o t connect if B E 6 4 0 0 is not u s e d .

*** N O T E :

See F i g . 2-3 for R S - 2 3 2 serial encoding a l t i m e t e r connection d e t a i l s .

E. Pin c o n n e c t i o n s o f the u n i t c o n n e c t o r J7

The unit c o n n e c t o r type is s u b m i n a t u r e 5-pins female.

Pin

Pin N a me Pi n Descr i p t i on So u r c e Des t i n a tion

1 VCC Power supply BXP6401-X-(XX) AM6400-1-(01)
2 I2C_CLK Bus clock AM6400-1-(01) BXP6401-X-(XX)
3 Not connected Reserved — —
4 I2C_DAT Bus data AM6400-1-(01) BXP6401-X-(XX)

05 GND Supply GND BXP6401-X-(XX) AM6400-1-(01)

F. DME s u p p r e s s i o n

If required, c o n n e c t the suppression i n / o u t of transponder t o the correspon

-

ding pin o f the DME u n i t or any r e l e v a n t device.

G. External IDENT p u s h - b u t t o n

If this i n p u t (Pin 4 o f unit connector P 9 ) is briefly c o n n e c t e d to GND ( e . g . by
an external p u s h - b u t t o n ) , the IDENT f u n c t i o n (SPI) is s t a r t e d in the s a m e way
as when u s i n g the IDENT p u s h - b u t t o n on the f r o n t panel.

H. Gr o u n d switch

If required, c o n n e c t an automatic g r o u n d switch (weight o n wheel sensor) a t
Pin 11 o f unit connector J 8 .

I. I l l u m i n a t i o n

For external i l l u m i n a t i o n control connect t h e illumination voltage t o pin 10 o f
P 9 a n d attach pin 2 3 to the i l l u m i n a t i o n ground. Set t h e max. illumination
voltage in t h e installation menu. F o r manual illumination c o n t r o l set dimming
input to “ n o n e ” in the i n s t a l l a t i o n menu. Set i l l u m i n a t i o n intensity manually i n
the configuration m e n u .

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-4

34-50-08 S e p t e m b e r 2011

5. I n s t a l l i n g the t r a n s p o n d e r a n t e n n a 1A032

A. The t r a n s p o n d e r a n t e n n a has t o b e fitted ( o u t s i d e ) to the b o t t o m of the a i r c r a f t

at a horizontal, flat l o c a t i o n . This location s h o u l d not b e i n the “ s h a d o w ” o f air­craftstructure i t e m s . The highest r a n g e is achievied w h e n the a n t e n n a i s
located a t the lowest p o i n t of the a i r c r a f t fuselage.

B. The i n s t a l l a t i o n d i m e n s i o n s of t h e t r a n s p o n d e r antenna 1 A 0 3 2 is shown i n

Fig. 2 - 2 .

CAUTION :

n

The transponder a n t e n n a 1A032 is p r o v i d e d with a s i l i c o n e rubber
gasket which m u s t also be i n t e r p o s e d between the s k i n of the a i r c r a f t
and the a n t e n n a .

n

In aircraft h a v i n g a wooden o r plastic airframe a n electric counter­weight plate o r panel must b e located within t h e fuselage at t h e an­tenna location w i t h minimum dimensions o f 40x40 cm ( 1 5 . 7 x 1 5 . 7 inch).

C. An t e n n a cable

RG-58C/U (0.9 d B / m ) or RG-223/U ( 0 . 6 dB/m) can b e used for t h e transpon

­der. If t h e cable length i s longer than 2 m between t h e unit and t h e antenna,
the cable t y p e RG- 223/U i s recommended. The m a x i m u m cable length
shouldn’t be m o r e than 5 m . The attenuation l o s s of the a n t e n n a cable must
n’t be h i g h e r than 3 d B in complete.

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INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

6. Programming o f t h e Address M o d u l e

The 2 4 - b i t ICAO address o n c e allocated by t h e local a u t h o r i t y i s stored f o r t h e as

-

signed t r a n s p o n d e r in the A d d r e s s Module AM6400-1-(01).

The a d d r e s s module programmer k i t s AMP6400-1 (parallel i n t e r f a c e ) and
AMP6400-2 ( U S B interface) are t o o l s for reading a n d storing f i x e d a i r c r a f t data i n t o
the A d d r e s s Module. This t o o l s are for s e r v i c e and m a i n t e n a n c e o n l y .

The C D - R O M , which is p a r t of the a d d r e s s module p r o g r a m m e r k i t , includes a d e s

­cription o f the programming p r o c e d u r e . Insert the C D - R O M into a P C and f o l l o w t h e
instructions. I f autostart is d i s a b l e d on your P C , you h a v e t o start “ s e t u p . e x e ” m a n u

-

ally.

7.

Avionics d a t a transfer

A. The B X P 6 4 0 1 - X - ( X X ) is a “ d a t a link t r a n s p o n d e r ” according to R T C A

DO-181C, r e s p e c t i v e l y a “level 2 e s ” transponder according t o EUROCAE
ED-73B.This s t a n d s for the c a p a b i l i t y to transfer d a t a from t h e g r o u n d to a

connected A D L P or a s i m i l a r device and v i c e versa.

B. The t r a n s p o n d e r t r a n s m i t s information as r e p l y on a G r o u n d Initiated Comm-B

(GICB) r e q u e s t or by m e a n s of the e x t e n d e d squitter f u n c t i o n . I n both c a s e s
the v a l i d information must b e available in t h e GICB r e g i s t e r s i n the t r a n s p o n ­der.

C. Th e transponder a l s o t r a n s m i t s information b y m e a n s of t h e Air Initiated

Comm-B ( A I C B ) function. In t h i s case the i n f o r m a t i o n must b e a v a i l a b l e in a
special r e g i s t e r in the t r a n s p o n d e r . The transponder a n n o u n c e s the m e s s a g e
and t r a n s m i t s it after a u t h o r i s a t i o n from the g r o u n d station.

D. In the o t h e r d i r e c t i o n , the t r a n s p o n d e r i s able t o receive information w i t h i n a

Comm-A f o r m a t from the g r o u n d station, which i s then b u f f e r e d a n d transferred
to t h e connected device.

E. In t h e B X P 6 4 0 1 - X - ( X X ) a “ s t o r a g e d e s i g n ” is i m p l e m e n t e d for uplink- a s well

as f o r downlink messages. T h i s means that a l l information t h a t m i g h t be t r a n s ­ferred f r o m the transponder i s buffered inside t h e transponder f i r s t .

F. The b u f f e r s can be a c c e s s e d from an A D L P or a s i m i l a r device v i a t h e interfa-

ce o n the rear c o n n e c t o r J8. The i n t e r f a c e is m a r k e d w i t h “TISRX” a n d “ T I S T X ”

in t h e aircraft wiring d i a g r a m (see Fig. 2 - 3 and Fig. 2-4).

G. The related p r o t o c o l is specified i n the attachment d o c u m e n t “Data Transfer

Interface P r o t o c o l BXP 640X-XX-(XX)”. T h i s manual is a v a i l a b l e at t h e B e c k e r
Product S u p p o r t under the A r t i c l e - N o . 0590.258-071.

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34-50-08 S e p t e m b e r 2011

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

8. GPS C o n f i g u r a t i o n

A. If G P S r e c e i v e r is u s e d p i n GPS / E n a b l e should be c o n n e c t e d to aircraft D C

supply g r o u n d ( if p a r a l l e l altimeter is u s e d GPS/Enable i s s e r v e d on p i n 2 J8
connector, i f serial altimeter i s used PS/Enable i n p u t is s e r v e d o n pin 2 P 9
connector– f o r details see F i g . 2-3 or 2 - 4 ) . GPS r e c e i v e r d a t a lines s h o u l d b e
connected t o pins P9-8 R X + and P9-9 R X - . GPS r e c e i v e r s u p p l y may b e c o n ­nected t o pin P9-6* i f its current c o n s u m p t i o n does n o t e x c e e d 1A.
Otherwise i t should be c o n n e c t e d directly to a i r c r a f t supply.

Note*

P9-6 S w i t c h a b l e power supply o u t p u t , when the u n i t is s w i t c h e d O N the o u t p u t p r o v i

-

de t h e supply voltage f r o m the supply i n p u t . ” .

B. The equipment is capable to operate with following certified GPS receivers:

- FreeFlight System GPS/WAAS 1201 Sensor, part number 84100-02-XXXX

- NexNav miniGNSS/ GPS-SBAS Sensor/ Receiver.
The equipment is capable to operate with following non-certified GPS recei-

vers:

- Garmin GNS 430

- Garmin GNS 530
The equipment is also capable to operate with GPS receivers which provide

EIA-232C or EIA-422 interface with serial asynchronous transmission parame­ters: 4800, n, 8, 1 and transmit data with NMEA-0183 protocol GGA and VTG
sentences.

C. Complete specification of GPS protocols describes supplementary document

“BXP6400 GPS Protocols”.

9.

Settings a f t e r installation

Installation m o d e is available f r o m SBY mode o n l y . To g e t i n t o installation m o d e
press b u t t o n SEL (G, s e e Fig. 3-1), t u r n with r o t a r y e n c o d e r (B) u n t i l “ I N S ” appears
in t h e bottom line o f the display. S e l e c t by p r e s s i n g p u s h - b u t t o n (C). T h e i n s t a l l a t i o n
setup i s protected by p a s s w o r d “6435”. Enter p a s s w o r d and p r e s s s t o r e button ( F ) .
See t a b l e on the n e x t page.

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-7

34-50-08 September 2 0 1 1

Sel e c t with b u t ton ( C ) Sel e c t with r o t a ry en c o d e r (B) Stor e b utton ( F )

ALT M S ELECT G A R M I N / T R I M BLE

NOR T H S TAR
UPS A T (BECK E R BE6400 )
LOR A N
MAG E L L AN
SHA D I N
ARN A V
GIL H A M / PAR A L L EL defaul t

sto r e
sto r e
sto r e
sto r e
sto r e
sto r e
sto r e
sto r e

DIM M I N G INPU T Non e

(se t i llumin a t i o n inte n s i ty ma

­nua l l y in t h e configu r a t ion
men u )

+5V D C
+14 V D C
+28 V D C

def a u l t st o r e

sto r e
sto r e
sto r e

SQU I T T ER

Sho r t ACQ S Q U

*

def a u l t on of f / on

REP L Y RATE L I M I T RP L RATE L M T

500 - 1 2 00 rep l i e s /sec.
in M o de A/C
(se t t i ng in s t e ps of 5 0 )

sto r e

SPE C I A LS

DAT A L INK

**

DEF A U L T CONF I G ***
ALT H I GH RES O L

sto r e
exe c u t e
sto r e

Err o r Latch L OW VOL T

HIG H T EMP
ANT E N N A
RF P O WER
DME E R R
SQR T E RR
COR E E E
REC E I V ER
FIX D A TA
ALT I M E TER
DAT A L INK / G P S****
Cle a r latch

vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
vie w o nly
exe c u t e

* Transponders e q u i p p e d f o r extended s q u i t t e r o p e r a t i o n should h a v e a me

­ans to d i s a b l e acquisition squitters t o facilitate the s u p p r e s s i o n of acquisition
squitters when a l l TCAS units h a v e been converted t o receive extended
squitter.

** Shall b e disabled if A D L P or similar d e v i c e is not c o n n e c t e d . The same i s
also recommended i f GPS receiver i s used.

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-8

34-50-08 S e p t e m b e r 2011

*** Default config: D i m m i n g input ® n o n e

Brightness ® 5 0 %
Altitude d i s p l a y e d in ALT m o d e
AI i n SBY
AI i n ON
IIlumin. c h a r a c t e r i s t i c s ® max. r a n g e
Code ® 0000
VFR ® 0 0 0 0
Flight n u m b e r ® eight b l a n k s
Flight n u m b e r ® not a c t i v e

NOTE:

If n o type is a v a i l a b l e , this field i n d i c a t e s nothing.

**** T h i s latch serves b o t h as DATA L I N K or G P S i n d i c a t o r . If D A T A L I N K switch i n
section S P E C I A L S is selected t h e n this latch i n d i c a t e s either D A T A L I N K or G P S e r

-

ror. O t h e r w i s e GPS error i s indicated if G P S receiver i s c o n n e c t e d .

10.

Checking a f t e r installation

A. General

After the i n s t a l l a t i o n , check the t r a n s p o n d e r to ensure s a t i s f a c t o r y operation
of the u n i t .

B. Pre-flight c h e c k u s i n g selftest

Power-on t e s t :

Switch the t r a n s p o n d e r operating mode s w i t c h from OFF t o SBY. A p o w e r - o n
built-in test ( P B I T ) is automatically a c t i v a t e d for 1 s e c o n d . During the t e s t
“WAIT is i n d i c a t e d . If the t e s t was successful, t h e transponder automatically
switches to t h e SBY mode.

Initiatet test (IBIT):
Press the SEL and STO b u t t o n at the s a m e time in m o d e ON or A L T . A IBIT

test is a c t i v a t e d . During the t e s t , “IBIT” is i n d i c a t e d on the d i s p l a y . If the I B I T
was successful, t h e transponder switches i m m e d i a t e l y into the n o r m a l opera

-

ting mode.

In case of a fault “FAILURE” report appears in the display. In this case acti

­vate the procedur “9. Settings after intsallation” page 2-7 in this manual. In
the table “error latches” the failure is displayed.

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

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34-50-08 September 2 0 1 1

C. Ch e c k of t h e a d d r e s s module

The i n s t a l l a t i o n company has t o ensure that t h e corresponding a d d r e s s
module A M 6 4 0 0 - 1 is installed w i t h the transponder a n d that t h e a d d r e s s
module i s programmed correctly. I t is recommended t o connect t h e a d d r e s s
module w i t h the aircraft t i g h t l y .

D. Te s t of t r a n s m i t f r e q u e n c y

Set c o d e 0000 on t h e transponder and m o d e A i n t e r r o g a t i o n o n the r a m p t e s t
set. C h e c k transmit frequency b y means of t h e ramp t e s t s e t . Transmit f r e -

quency m u s t be 1090 ± 1 MHz. If this is not the case send the transponder to

authorised service.

E. Check o f t h e transmit p o w e r

After installation o f equipment and a n t e n n a the transmit p o w e r has to b e che

-

cked at t h e antenna end o f the feeder l i n e . It should fulfill the following requi

-

rements:

Requirement: ³ 1 2 5 W (21 d B W ) at class 1 transponder

³ 70 W (18.5 dBW) a t class 2 t r a n s p o n d e r

WARNING:

Radiation risk: A safe distance t o the installed a n t e n n a must be e n s u r e d by
corresponding installation m e a s u r e s around human b o d y damage (e.g. a t the
eyes) and / or avoid t h e inflammation of c o m b u s t i b l e materials by r a d i a t e d
energy.

Page 2-10

34-50-08 S e p t e m b e r 2011

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Fig. 2 - 1 In s t a l l a t i o n d i m e n s i o n s BXP6401-X-(XX)

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-11

34-50-08 September 2 0 1 1

Fig. 2 - 2 In s t a l l a t i o n d i m e n s i o n s Transponder A n t e n n a

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-12

34-50-08 S e p t e m b e r 2011

Fig. 2 - 3 P r o p o s a l for a i r c r a f t wiring BXP6401-X-(XX) w i t h serial encoding a l t i m e t e r

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-13

34-50-08 September 2 0 1 1

Fig. 2 - 4 Proposal for aircraft wiring BXP6401-X-(XX) with parallel encoding altimeter

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

Page 2-14

34-50-08 S e p t e m b e r 2011

Fig. 2-5 RS-232 se ri al en co ding al ti me ter con nec tion

Fig. 2.6 RS-232 GPS re cei ver con nec tion P9

IN STAL LA TI ON AND OPE RA TION BXP6401-X-(XX)

Page 2-15

34-50-08 Sep tem ber 2011

Core Unit

9
8

2

13

GPS

TX

GND

P 9

Core Unit

12
13

21

Altimeter

TX

GN D

J8

P9

Blanc

INSTALLATION AND O P E R A T I O N BXP6401-X-(XX)

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34-50-08 S e p t e m b e r 2011

TABLE OF CONTENTS

OPERATION Page

1. Controls and indicators 3-1

2. Function of controls and indicators 3-1

3. Operating instructions 3-2
A. Switching on the unit (pre-flight check) 3-2
B. Start-up 3-3
C. CODE display 3-3
D. Aircraft identification / Flight number 3-3
E. Flight level 3-4
F. Selftests of the unit (BITs) 3-4
G. Selection mode 3-5
G.1 Aircraft Identification (AI or FN) 3-6
G.2 VFR code setting 3-7
H. Flight operation in Mode A/C/S (reply and altitude code) 3-8
I. VFR code activation 3-9
J. Internal and external Ident 3-9
K. Special condings for air emergencies 3-9
L. Configuration mode 3-10

Fig. 3-1 Front view of BXP6401-X-(XX) 3-1
Fig. 3-2 Start-up indication 3-3
Fig. 3-3 AID indication 3-3
Fig. 3-4 FN indication 3-3
Fig. 3-5 Flight level indication 3-4
Fig. 3-6 Error indication and Warning indication 3-5

INSTALLATION AND OPERATION BXP6401-X-(XX)

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BLANK

INSTALLATION AND OPERATION BXP6401-X-(XX)

Page III-II

34-50-08 September 2011

OPERATION

1. Controls a n d i n d i c a t o r s

Fig. 3 - 1 F r o n t view o f BXP6401-X-(XX)

2.

Function o f controls and i n d i c a t o r s

Ref. to
Fig. 3-1

Controls and
Indicators

Description F u n c t i o n

A Mode selector Rotary switch w i t h 4

positions

OFF position: T r a n s p o n d e r i s s w i t c h e d o f f

SBY position: S t a n d b y m o d e i s a c t i v a t e d

ON position: M o d e A / S i s s w i t c h e d o n .
Transmission of a l t i t u d e i n f o r m a t i o n i s
suppressed.

ALT position: M o d e A / C / S i s s w i t c h e d o n a n d
the altitude i n f o r m a t i o n i s t r a n s m i t t e d .

B Rotary Encoder Rotary optical encoder R o t a r y e n c o d e r t o c h a n g e s e t t i n g s

(16 steps p e r t u r n )

INSTALLATION AND OPERATION BXP6401-X-(XX)

Page 3-1

34-50-08 September 2011

Ref. to
Fig. 3-1

Controls and
indicators

Description F u n c t i o n

C B u t t o n Push-button P u s h t o j u m p f r o m d i g i t t o digit for settings

or from o n e menu to t h e next;
generally used a s an enter k e y

D I D T P u s h - b u t t o n Activates the S p e c i a l I d e n t i f i e r ( S P I ) i n a d -

dition to t h e r e p l y c o d e f o r a p p r o x . 1 8 s e

­conds; during t h i s t i m e “ I D ” a p p e a r s i n t h e
LC display

E Display, part 1 2 - l i n e L C D d i s p l a y Displays the following informations:

- code i n d i c a t i o n i n t h e t o p r o w

- flight l e v e l i n t h e b o t t o m r o w

- various i n f o r m a t i o n s i n t h e b o t t o m r o w

- additional i n d i c a t o r s o n t h e l e f t s i d e ( s e e

Ref. H)

F S T O Pu s h - b u t t o n Stores the s e l e c t e d v a l u e s t o t h e s e t t i n g s

G SEL P u s h - b u t t o n Opens and s e l e c t s t h e m e n u

H D i s p l a y

, part 2 L C D i n d i c a t o r s Displays additional indicators, ( R f o r r e p l y ,

ID for I d e n t , A L T f o r X P D R A L T m o d e o r O N
for XPDR O N m o d e , F L f o r f l i g h t l e v e l )

J V F R Push-button A c t i v a t e s V F R c o d e in the upper row of the

display

3. O p e r a t i n g instructions

A. Switching o n t h e unit ( p r e - f l i g h t c h e c k )

(1) Check t h a t the circuit b r e a k e r is set a n d switch on t h e aircraft power

supply.

CAUTION: Do n o t switch on t h e transponder when e n g i n e s are being

started or shutdown.

(2) Using m o d e switch (A), s w i t c h the transponder f r o m OFF to S B Y . A Po-

wer-on Built-In T e s t (PBIT) then f o l l o w s automatically for 1 second.
Start-up see a l s o section B.

INSTALLATION AND OPERATION BXP6401-X-(XX)

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34-50-08 September 2011

B. Start-up

On power-up, the device starts. The software initiates circuits and performs
PBIT. During that time the display looks as follows.

Fig. 3-2 Start-up indication

After the PBIT has elapsed and no error-message is shown in the display, the
transponder switches to the mode set by the mode switch (A).

C. CODE display

Transponder’s code is displayed in the top line using high readability font, at
all times in modes SBY, ON, ALT.

D. Aircraft identification / Flight number

Depending on the configuration settings, the Aircraft Identification (AI) or
Flight Number (FN) is displayed in the bottom line as follows:

Fig. 3-3 AI indication

Fig. 3-4 FN indication

INSTALLATION AND OPERATION BXP6401-X-(XX)

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E. Flight le vel

Flight le vel is dis play ed in ALT mode in the bot tom line of the dis play (al ti tu de
= FL x 100 in ft):

Fig. 3-5 Flight le vel in di ca ti on

F. Self tests of the unit (BITs)

The fol lo wing dif fe rent tests are in te gra ted in the trans pon der or can be trig ge red at
the trans pon der:

(1) The IBIT (Ini tia ted Built-in Test) can be ac ti vat ed in any mode (ex clu ding the

con figu ra ti on mode) with the push of (F) and (G) at the same time. The ac ti on
starts with the lea ding edge of the se cond pus hed but ton.

The IBIT works as fol lows in all modes:

The test starts with all avai la ble test rou ti nes inclu ding the trans mit ter test rou­tine. Du ring the test, “IBIT” is in di ca ted on the dis play.The test takes not lon­ger than 1 se cond. If the IBIT was suc cess ful, the XPDR swit ches immediately
into the nor mal ope ra ting mode. Du ring the IBIT any ac ti on from ot her switches
is not re cognized.

Negative results of the IBIT are indicated on the display with “FAILURE”. The
transponder may be not switched into ON or ALT mode if any failure was
found.

(2) The CBIT (Continuous Built-in Test) works as follows:

The continuous BIT acts as a kind of watchdog during operation. Negative
results of the CBIT are indicated on the display with “FAILURE”. In this case
the transponder may be not switched into ON or ALT mode (display indication
of operating mode set to SBY) if any failure was found.

(3) The PBIT (Power-on Built-in Test) works as follows:

The XPDR has a power-on BIT after switching on. During the PBIT any actions
from other switches are not accepted.

During the PBIT the XPDR is in the SBY mode but this is not indicated on the
display. The operating mode indication on the display starts immediately after
finalisation of the PBIT.

INSTALLATION AND OPE RA TION BXP6401-X-(XX)

Page 3-4

34-50-08 Sep tem ber 2011

4121

R
ID

A L T

F L

050

Negative results are indicated on the display with “FAILURE”. The transponder
may be not switched into ON or ALT mode if any failure was found.

The PBIT takes not longer than 1 second. If the test was successful, the XPDR
switches immediately into the normal operating mode.

Fig. 3-6 Error indication and Warning indication

G. Selection mode

Press SEL button (G) and rotate encoder (B) for selection. In selection mode
additional information is displayed in the bottom line of the display. Some of
the data are editable, some are read only:

VFR 4096 code presetting editable; see section G.2
AI Aircraft Identifier fixed; read only from address mo-

(Tail Number) dule (can be replaced by FN)

If no valid AI is stored, “--------”
is displayed.

FN Flight Number or editable; see section G.1,

Company Call Sign can be replaced by AI (fixed) by

selecting “AI DEF”

AA Aircraft Address fixed; read only from address

(24-bit ICAO) module (unique number for each

aircraft)

MA Maximum Airspeed fixed; read only from address

module

AT Aircraft Type fixed; read only from address

module

CFG Configuration available in SBY mode only,

see section L

INS Installation setup available in SBY mode only;

protected by password,
see chapter 2, section 8

INSTALLATION AND OPERATION BXP6401-X-(XX)

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G.1 Aircraft Identification (AI or FN)

With flight plan: The definition out of the flight plan:

e.g. Flight Number or Company Call Sign

Without flight plan (VFR): Tail Number (Call Sign)

The i n d i c a t i o n of AI i n the bottom l i n e of t h e d i s p l a y is i n m o d e SBY a n d ON
only i f selected in c o n f i g u r a t i o n menu. The A i r c r a f t Identifier ( f i x e d ) i s availa­ble i n any mode a f t e r pressing SEL b u t t o n (G) a n d t u r n i n g the r o t a r y e n c o d e r
(B). T h e default value f o r AI is t h e Tail N u m b e r o f the a i r c r a f t a n d is s t o r e d in
the A d d r e s s Module.

If a flight plan e x i s t s , it has t o be c h e c k e d , w h i c h AI h a s t o be u s e d . If a F l i g h t
Number i s assigned it h a s to be e n t e r e d . If a C o m p a n y Call S i g n i s mentioned,
this h a s to be e n t e r e d . To enter i t see b e l o w . I t will b e s t o r e d in t h e EEPROM
of t h e control head. I n this case t h e indication o n t h e display c h a n g e s t o FN
(Flight N u m b e r ) . If the C a l l Sign (Tail N u m b e r ) is m e n t i o n e d , n o change, a s i t
is t h e default setting f r o m the Address M o d u l e .

Setting t h e flight number:

(1) Press S E L button (G) t o enter the s e l e c t mode.

(2) Rotate ( B ) until AI i s displayed.

(3) Push ( C ) to switch t o FN. The c u r s o r is set o n the first c h a r a c t e r .

(4) Rotate ( B ) to change t h i s character.

(5) Push ( C ) to set t h e cursor to t h e next character.

(6) Repeat s t e p s 4 and 5 until the f l i g h t number is e n t e r e d .

(7) If t h e flight number c o n s i s t s of less t h a n 7 characters, p u t a space a t

the end t o fill the r e m a i n i n g characters with s p a c e s .

(8) Store t h e changes with S T O button (F). F o r leaving the s e t t i n g proce-

dure without s t o r i n g , push the S E L button (G).

NOTE:

Aircraft Identifier / Flight Number consists of max. 7 characters (on the left­hand side oriented). No dashes or spaces shall be included. If the FN con­sists of less than 7 characters, the remaining characters on the right side
shall be filled with spaces.

Switching back to default AI:
(1) Press SEL button (G) to enter the select mode.
(2) Rotate (B) to the indication FN=XXXXXXXX.
(3) First push on (C) indicates”FN=AI DEF” (inverted).
(4) Can be set to AI=DEF with STO button (F).

INSTALLATION AND OPERATION BXP6401-X-(XX)

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34-50-08 September 2011

Changing the flight number:
(1) Press SEL button (G).
(2) Rotate (B) until FN is displayed.
(3) Push (C) twice to enter the FN editing mode.
(4) Change the FN as described above.

G.2 VFR code presetting

Press the S E L button (G) t o get into c o n f i g u r a t i o n mode (selection i s indica­ted in t h e left bottom c o r n e r of the d i s p l a y under the o p e r a t i n g mode indica­tion).

(1) Rotate ( B ) to the i n d i c a t i o n VFR=XXXX.

(2) First p u s h to button ( C ) Þ left d i g i t of the c o d e is inverted.

(3) Now t h e digit can b e changed with ( B ) .

(4) Second p u s h to button ( C ) Þ next l e f t digit of t h e code is i n v e r t e d .

(5) The n e x t digit can b e changed with ( B )

(6) and t h e same for n e x t digits.

(7) Fifth p u s h to button ( C ) Þ again f i r s t digit is i n v e r t e d .

(8) Changes c a n be stored w i t h STO button ( F ) at any t i m e , inversion stops

in this c a s e .

(9) A V F R code that w a s preset in t h i s way can b e activated as d e s c r i b e d

in chapter I .

(10) A timeout f o r inversion (10 s e c ) is introduced i f no action h a p p e n s .

Nothing stored, a s long as ( F ) is not p r e s s e d .

NOTE:

It is p o s s i b l e to leave t h e setting procedure w i t h SEL button ( G ) at any t i m e
and normal m o d e is available t h e n . Indication SEL o n the display c h a n g e s
back to m o d e indication. If S T O button (F) w a s not used, n o change has b e e n
stored.

INSTALLATION AND OPERATION BXP6401-X-(XX)

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H. Flight operation in Mode A/C/S (reply code and altitude code)

(1) When A T C requests the t r a n s m i s s i o n “squawk”, switch t h e transponder

to ALT u s i n g mode switch ( A ) .

NOTES: Th i s o n l y makes s e n s e i f the t r a n s p o n d e r is connected to a

coding altimeter. If not, tell ATC that you do not have mode C
(“mode charlie not available”).

In exceptions the altitude has to be turned off, i.e. switch the
transponder to ON using mode switch (A).

(2) The t r a n s p o n d e r replies using t h e selected Code a n d in response t o

mode C i n t e r r o g a t i o n it transmits t h e altitude of t h e aircraft to A T C . A
“R” on t h e left next t o the Code o n the display s i g n a l s the transponder
replies.

NOTE : Switch t h e transponder to S t a n d - b y (SBY), if t h e Code has t o

be changed. O t h e r w i s e if could h a p p e n that a C o d e with a
special meaning ( s e e chapter K, e . g . highjack) will b e trans­mitted and u n w a n t e d actions could t a k e place.

(3) After a “squawk ident” request from ATC, press Ident button IDT (D)

briefly. This transmits an additional special pulse (SPI) for approx. 18
seconds, which enables the aircraft to be clearly identified on the radar
screen of the controller. “ID” appears on the left side in the LC dis­play during this time.

(4) In a normal installation the blind encoder is only powered if the trans-

ponder is not switched OFF (at least SBY).
A blind encoder needs a warm-up time (sometimes several minutes).
Therefore, although the solid state transponder needs no warm-up time,

turn the transponder to SBY immediately after starting the engine.

INSTALLATION AND OPERATION BXP6401-X-(XX)

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I. VFR code activation

(1) Press t h e VFR push-button ( J ) . The preselected c o d e is then d i s p l a y e d .

After 3 s e c o n d s , the displayed c o d e gets active a n d overwrites the p r e ­viously-set reply c o d e .

(2) Pressing p u s h - b u t t o n (J) again w i t h i n 3 seconds r e a c t i v a t e s the previ-

ously-set reply c o d e .

NOTE :

When the u n i t is delivered, t h e VFR button i s not assigned a code. This
means that i f this button i s pressed for 0 . 5 seconds, “----” i s shown in t h e
code display a n d the transponder t h e n switches back t o the previously-active
code.

J. Internal and external Ident

The special identifier pulse (SPI) can be triggered by pressing “IDT” button on
the control panel or from external input located on the transponder.

If special identifier pulse has been triggered, then “IDT is displayed on the
display as long as SPI is active.

K. Special codings for air emergencies

(1) Special c o d i n g s , which depend o n the type o f incident, are s t i p u l a t e d for

certain air e m e r g e n c i e s :

n 7500 H i j a c k i n g

n

7600 Loss o f communications

n

7700 Emergency o n board which c o n s t i t u t e s an immediate

danger to t h e aircraft

(2) The code evaluation devices of the radar systems automatically alarm

the controllers at the radar screens immediately if one of these special
codes is received.

INSTALLATION AND OPERATION BXP6401-X-(XX)

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L. Configuration mode

The configuration mode is available from SBY mode only. To get into configu

-

ration mode press button SEL (G), turn rotary encoder (B) until “CFG” appe

-

ars in the bottom row of the display. Available options are defined in the fol

-

lowing table.

Select with p u s h ­button (C)

Select with r o t a r y
switch (B)

Store button ( F )

BRIGHTNESS

(only if d i m m i n g i n p u t
is set t o “ n o n e ” i n
installation menu)

0 %

…

50%

…

100 %

default

store

store

store

store

store

ILLUM CURVE

(only if e x t e r n a l
illumination control i s
set in t h e i n s t a l ­lation menu)

Characteristics s t o r e t o c h a n g e

VIEW CONFIG A I IN SBY

AI IN O N

FL IN A L T

default

default

default

ON

OFF

ON

OFF

ON

OFF

DEVICE INFO C U V E R

CORE VER

FPGA VER

DEV TYPE

SERIAL NB

view only

view only

view only

view only

not supported

NOTE: The field “DEV TYPE” and “SERIAL NB” is not available.

INSTALLATION AND OPERATION BXP6401-X-(XX)

Page 3-10

34-50-08 September 2011