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Cobham plc Cobham plc 10/6/2016 5

ADS-B Out

ADS-B Extended Squitter Types

Cobham plc Cobham plc

Testing a 1090 ADS-B Out Installation

General guidance only Installers must satisfy themselves that the installation is compliant

with all appropriate standards, regulations etc

Testing 1090 ADS-B Out


SETUP XPDR Screen

B AT 2 . 5 H r

P R E V P A R A M

S E T U P - X P D R

D I A G

A N T E N N A : B O T T O M R F P O R T : A N T E N N A A N T R A N G E A N T H E I G H T T O P : 5 0 . 0 F T 1 0 . 0 F T B O T T O M : 5 0 . 0 F T 0 . 0 F T A N T C A B L E L E N : 6 F T A N T G A I N ( d B i ) A N T C A B L E L O S S : 1 . 8 d B 0 . 9 6 G H z : 7 . 5 C O U P L E R L O S S : 0 . 8 d B 1 . 0 3 G H z : 7 . 1 U U T A D D R E S S : A U T O 1 . 0 9 G H z : 6 . 1 M A N U A L A A : 1 2 3 4 5 6 P W R L I M : F A R 4 3 D I V T E S T : O N R A D 4 7 : O F F C H E C K C A P : Y E S

T E S T D A T A

N E X T P A R A M

A D S B S E T U P


SETUP ADS-B Screen

B AT 2 . 5 H r

T E S T D A T A

P R E V P A R A M

N E X T P A R A M

S E T U P - A D S - B

R E T U R N

P O S D E C O D E : G L O B A L L AT : 8 9 2 5 3 5 N L O N G : 1 2 6 3 5 3 5 E B AR O P R E S AL T : 0 f t A D S - B G E N : D F 1 7 A D S - B M O N : D F 1 7 G I C B : D F 2 0


BDS Registers Tested with 6000

10/6/2016 9

DF17/18/19

ADS-B Mon

BDS 0,5 BDS 0,6 BDS 0,8 BDS 0,9 BDS 0,A BDS 6,1 BDS 6,2 BDS 6,5

DF17/18/19

ADS-B Gen

BDS 0,5 BDS 0,6 BDS 0,8 BDS 0,9 BDS 0,A BDS 6,1 BDS 6,2 BDS 6,5

BDS 0,5 BDS 0,6 BDS 0,7 BDS 0,8 BDS 0,9 BDS 6,0 BDS 6,1 BDS 6,2 BDS 6,5 BDS 1,0 BDS 1,7 BDS 1,8 BDS 1,9 BDS 1,A BDS 1,B BDS 1,C BDS 2,0 BDS 2,1 BDS 3,0 BDS 4,0 BDS 4,1 BDS 4,2 BDS 4,3 BDS 5,0

UF20/21

GICB


ADS-B/GICB/UAT Screen

B AT 2 . 5 H r

A D S B M O N G I C B

A D S - B / G I C B / U AT M A I N

A D S B

G E N A D V

C I R C U A T


ADS-B MON List Screen

B AT 2 . 5 H r

1 0 , 5 A I R B O R N E P O S - A V A I L 2 0 , 6 S U R F A C E P O S - N O S Q T R 3 0 , 8 I D E N T & C AT - A V A I L 4 0 , 9 A I R B O R N E V E L - A V A I L 5 6 , 1 A / C S T AT U S S T 1 - A V A I L 6 6 , 1 A / C S T AT U S S T 2 - A V A I L 7 6 , 2 T S S S U B T Y P E 0 - N O S Q T R 8 6 , 2 T S S S U B T Y P E 1 - N O S Q T R 9 6 , 5 A / C O P S T AT U S A I R - A V A I L 1 0 6 , 5 A / C O P S T AT U S S U R - N O S Q T R 1 1 0 , A T E S T M S G - N O T C A P

R U N T E S T

B D S D A T A

A D S - B M O N D F 1 7

R E T U R N

If squitter status does not automatically populate the ADS-B monitor screen, then check notes page for setup screen, regarding transponders that do not have automatic ‘on ground’ determination, to advise manual setting of aircraft address.


Preliminary Actions Check BDS 6,5

Prior to carrying out testing, it is important when validating an ADS-B installation to know what standard the transponder is: • RTCA/DO-260 (TSO-166) • RTCA/DO-260A (TSO-166A) • RTCA/DO-260B (TSO-166B) If the Aircraft is in the airborne state, then running the MON BDS 6,5 AIR test will provide the ADS-B Version Number. If the aircraft is in the ground state, then the MON BDS 6,5 SUR test may be run to display the same version information.

B AT 2 . 5 H r

B D S = 6 , 5 A / C O P S T AT U S T Y P E = 3 1 D F 1 7 A A = 1 2 3 4 5 6 C O U N T = 1 1 M E = F 8 2 A A A 2 A A A 4 A A F P E R I O D = 1 . 5 7 s S U B T Y P E = 0 - A I R V E R S I O N = 2 - D O - 2 6 0 B C C F M T = 2 A A A A R V = 1 T S = 0 1 0 9 0 = 0 U AT = 1 T C = 2 A D S R = 0 T C A S O P = 1 O M F M T = 0 S D A = 0 S A F = 0 AT C = 1 R A = 1 I D = N O N I C B A R O = 1 H R Z R E F = M A G N O R T H N I C - A = 0 G V A = 2 N I C - B A R O = 1 S I L S U P = 1 S I L = 2 N A C P = 1 0 - E P U < 0 . 0 0 5 4 A D S R ( 5 6 ) = 1

R U N T E S T

P R E V T E S T

M O N B D S 6 , 5 A I R A V A I L

N E X T T E S T

R E T U R N

Some important points to observe, when carrying out validation checks on ADS-B equipment: The aircraft GPS needs a clear view of the sky/GPS constellation to generate a good Horizontal Protection Limits (HPL)/NUC/NIC value. Normally the testing results inside a hangar are not acceptable due to satellite blocking and multipath. A GNSS simulator such as the GPSG-1000 is a cost effective alternative to using the live constellation.


Verify Aircraft Parameters BDS 0,8

B AT 2 . 5 H r

B D S = 0 , 8 I D E N T & C AT T Y P E = 4 D F 1 7 A A = 3 AC 4 2 1 C O U N T = 1 0 0 0 M E = 2 3 6 1 0 3 B 3 D 3 5 C 7 1 P E R I O D = 1 0 . 0 0 s A I S = 6 1 0 3 B 3 D 3 5 6 7 2 F L I G H T I D = X P N 3 4 5 1 2 E M I T C AT S E T = A E M I T C AT = L AR G E

R U N T E S T

P R E V T E S T

M O N B D S 0 , 8 A V A I L

N E X T T E S T

R E T U R N

Flight ID: Normally set by the crew using an entry panel or FMS interface The crew must set the Flight ID to match EXACTLY the flight plan field 7 – “Callsign” In some installations, the Flight ID can be pre-programmed, to the registration however, always verify the flight ID is reported correctly. DO NOT enter the 24 bit aircraft address into the aircraft Flight ID field.

24 bit aircraft address : Check 24 bit aircraft address as allocated by Aviation Authority

Emitter category : Check emitter category set and type are appropriate for the aircraft.


Squitter Rates DO-260B

Squitter Type DF BDS Air Status Ground Status Info

High Rate Normal Rate

High Rate

Low Rate * * (A/C not moving)

Acquisition 11 N/A 0.8 - 1.2 sec

0.8 - 1.2 sec

0.8 - 1.2 sec

TCAS Acquisition

Airborne Position 17 0,5 0.4 - 0.6 sec Not Transmitted

Not Transmitted

Surface Position 17 0,6 0.4 - 0.6 sec * Up to 60 sec

0.4 – 0.6 sec 4.8 – 5.2 sec * Requested

Aircraft Identification 17 0,8 4.8 - 5.2 sec

4.8 - 5.2 sec

9.6 - 10.4 sec

Airborne Velocity 17 0,9 0.4 - 0.6 sec Not Transmitted

Not Transmitted

Target State & Status DO-260A Only

17 6,2 1.2 - 1.3 sec Not Transmitted

Not Transmitted

Event Driven 17 0,A 2 per sec max Emergency/ TCAS RA

Mode A Code Change

NIC, NAC, SIL Change

Aircraft Status 17 6,1 0.7 - 0.9 sec 4.8 - 5.2 sec

Refer to DO-260B Tables R2-R6 for transmission durations after above parameter status changes Aircraft Operational

Status 17 6,5 0.7 - 0.9 sec

2.4- 2.6 sec


GPS Accuracy & Reported Accuracy

GPS accuracy is dependent on a number of factors such as : The User Equivalent Range Errors (UERE) including Ionospheric effects, Ephemeris errors, satellite clock errors, multipath etc; and Satellite geometry

The accuracy is a function of HDOP * UERE where HDOP is the Horizontal Dilution of Precision, a measure of the position accuracy degradation due to satellite geometry. Typical GPS errors (95%) are as follows depending on the number and geometry of satellites received :

GPS system with SA activated ± 100 Metres (no longer relevant because SA is deactivated) GPS system with SA deactivated ± 15 Metres SBAS augmented GPS ± 1 - 3 Metres

Reported Accuracy & Integrity For GPS receivers which are not SA aware, the accuracy and integrity REPORTED which are then used in ADS-B messages, is based on an ASSUMED value of UERE, corresponding to the period when SA was active. This value is grossly larger than the accuracy of the positional data delivered now that SA is inactive. For SA OFF/SA aware receivers, some report accuracy and integrity values based on the assumed UERE in the SA inactive environment and some determine the UERE from the GPS message contents. Thus SA aware systems report more realistic accuracy and integrity values.


ARINC 743A GPS Output Data DO-229D


ADS-B Accuracy & Integrity Reporting

• GPS accuracy is reported by GPS receivers in a parameter called Horizontal Figure of Merit (HFOM)

• GPS integrity is reported by GPS receivers in a parameter called Horizontal Protection Limit (HPL)

• The reported accuracy and integrity are further modified by ADS-B Transponders in the DO-260, DO-260A & DO-260B encoding process, resulting in NAC, NIC & NUC • DO260A & DO260B Accuracy: Navigation Accuracy Category (NAC)

• DO260A & DO260B Integrity: Navigation Integrity Category (NIC)

• DO260 Integrity: Navigation Uncertainty Category (NUC) • Accuracy is not reported in DO-260


The NACp - NIC Relationship

NACp EPU < NIC Rc for Same NACp & NIC Values


GPS Type - Accuracy & Integrity Reporting

GPS Type DO-260 DO-260A/B

SA aware GPS (airborne)

NUC value reports integrity based on HPL data. Accuracy values can be inferred from the HPL data, in particular that 95% accuracy is <HPL/4

NAC value reports accuracy which closely matches actual accuracy. SA aware receiver uses realistic UERE

SA aware GPS (surface)

If integrity > 182 metres, then transponder reports that integrity is unknown. This is not frequent for SA aware GPS.

If integrity > 182 metres (1,111 metres in DO260B), then transponder reports that integrity is unknown. This is not frequent for SA aware GPS.

SA ON GPS (Airborne) Same actual accuracy as SA aware GPS

NUC value reports integrity. NUC is based on HPL, which is reported unrealistically high because SA ON receiver assumes that selective availability is still ON.

NAC value reports accuracy much worse than reality, because SA ON receiver assumes that selective availability is still ON. It assumes an unrealistically large UERE

SA ON GPS (Surface) Same actual accuracy as SA aware GPS

If aircraft is “on ground” and integrity > 182 metres, then transponder reports that integrity is unknown. This is often the case with SA ON GPS avionics

If integrity > 182 metres (1,111 metres in DO260B), then transponder reports that integrity is unknown. For DO260A, this often the case with SA ON GPS avionics, but much less frequent with DO260B avionics.


Determining DO-260 NUCp – Surface Position

B AT 2 . 5 H r

B D S = 0 , 6 S U R F A C E P O S T Y P E = 5 D F 1 7 A A = 3 A C 4 2 1 C O U N T = 1 0 0 0 M E = 0 0 0 0 0 0 0 0 0 0 0 0 0 P E R I O D = 0 . 5 0 S L AT = 3 7 3 9 0 0 N L O N G = 9 7 2 5 4 8 W M O V M E N T = 0 k t s T = N / U T C H D G = 2 3 0 d e g P O S = G L O B A L N I C = - R c = -

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

If the aircraft is transmitting SURFACE squitters (i.e. WOW switch is active), then generally the type code needs to be 5, 6 or 7. Type Code may be used in the table shown below to determine NUC A NUC=6 is unusable. It is normal for NUC to change, as the received satellite geometry changes. SA ON GPS units (receivers that assume that SA is always on), sometimes generate Rc>185 metres and hence a surface squitter with NUC=6 can be transmitted even for “good” installations. Lat, Long, Hdg & Movement are directly displayed

Type Code

BDS Horizontal Containment Radius Limit (Rc)

NUCp

5

BDS 0,6 Surface Position

Rc <7.5 m NUC=9

6 Rc <25 m NUC=8

7 Rc <185.2 m (0.1 NM) NUC=7

8 Rc> 185.2 m (0.1 NM) or unknown NUC=6


Determining DO-260 NUCp – Airborne Position

B AT 2 . 5 H r

B D S = 0 , 5 A I R B O R N E P O S T Y P E = 1 1 D F 1 7 A A = 3 A C 4 2 1 C O U N T = 1 0 0 0 M E = 0 0 0 0 0 0 0 0 0 0 0 0 0 0 P E R I O D = 0 . 5 0 S L AT = 3 7 3 9 0 0 N L O N G = 9 7 2 5 4 8 W P O S = G L O B AL N I C - B = 1 T = N / U T C S U R V E I L L A N C E S T AT U S = N O I N F O B A R O P R E S A L T = 1 3 1 0 2 5 f t G N S S A L T = - N I C = - R c = -

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

Type Code may be used in the table shown on the next slide to determine NUC. Generally, Type Code needs to be 9 – 14 A “good” installation needs to transmit a NUC of at least 5, 6 or 7. A NUC=0 is unusable. If you are seeing NUC= 3-4 then something is probably wrong because real HPLs do not get this low. .


Determining DO-260 NUCp – Airborne Position

Type Code

BDS

Horizontal Protection Limit HPL

95% Containment Radius On Horizontal (u)

Position Error

NUCp

Frequency of Type

Code

Useable by ATC

9

BDS 0,5 Airborne Position

HPL < 7.5 m u <3 m NUC=9 Rare

Yes

10 HPL < 25 m 3 m ≤ u <10 m NUC=8 Common

11 25 m ≤ HPL < 185 .2 m (0.1NM)

10 m ≤ u <92.6 m (0.05 NM)

NUC=7 Common

12 185.2 m ( 0.1 NM) ≤ HPL < 370.4 m (0.2 NM)

92.6 m (0.05 NM) ≤ u <185.2 m (0.1 NM)

NUC=6 Common

13 380.4 m (0.2 NM) ≤ HPL < 926 m (0.5 NM)

185.2 m (0.1 NM) ≤ u <463 m (0.25 NM)

NUC=5 Less Common

14 926 m (0.5 NM) ≤ HPL < 1852 m (1.0 NM)

463 m (0.25 NM) ≤ u <926 m (0.5 NM)

NUC=4 Infrequent

15 1852 m (1.0 NM) ≤ HPL < 3704 m (2.0 NM)

926 m (0.5 NM) ≤ u <1.852 km (1.0 NM)

NUC=3

Unlikely

No 16 7.704 km (2.0 NM) ≤ HPL < 18.52 km (10 NM)

1.852 km (1.0 NM) ≤ u <9.26 km (5.0 NM)

NUC=2

17 18 .52 km (10 NM) ≤ HPL < 37.04 km (20 NM)

9.26 km (5.0 NM) ≤ u <18.52 km (10.0 NM)

NUC=1

18 HPL > 37.04 km(20 NM) 18.52 km (10.0 NM) ≤ u NUC=0 Not Usable


Determining DO-260A/B NIC – Surface Position

B AT 2 . 5 H r

B D S = 0 , 6 S U R F A C E P O S T Y P E = 6 D F 1 7 A A = 3 A C 4 2 1 C O U N T = 1 0 0 0 M E = 3 0 1 D 2 0 6 6 6 6 2 1 B 4 P E R I O D = 0 . 5 0 s L AT = 3 7 3 9 0 . 0 0 N L O N G = 9 7 3 2 0 . 7 0 W M O V M E N T = S T O P P E D T = N / U T C H D G = 2 3 0 d e g P O S = G L O B A L N I C = 1 0 R c = < 2 5 m

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

If the aircraft is transmitting SURFACE squitters (i.e. WOW switch is active), then generally the type code needs to be 5, 6 or 7. Type Code may be used in the tables shown on the next slide to show full details i.e. NIC Supplement. Note: The tables shown are for where a Barometric Altitude Source is used. NIC and Rc are directly displayed. NIC should be 11 - 8 for DO-260A Transponders and 11- 6 for DO-260B transponders In both DO-260A and DO-260B, NIC=0 is unusable. It is normal for NIC to change, as the received satellite geometry changes. Lat, Long, Hdg & Movement are directly displayed


Determining DO-260A/B NIC – Surface Position

Type Code

BDS DO-260B Horizontal Containment Radius Limit (Rc)

NIC Supplement A B C

NIC

5


Rc <7.5 m 0 - 0 NIC=11

6 Rc <25 m 0 - 0 NIC=10

7

Rc <75 m 1 - 0 NIC=9

Rc <0.1 NM (185.25 m) 0 - 0 NIC=8

8

Rc <0.2 NM (370.4 m) 1 - 1 NIC=7

Rc <0.3 NM (555.6 m) 1 - 0 NIC=6

Rc <0.6 NM (1111.2 m) 0 - 1

Rc >0.6 NM (1111.2 m) or unknown 0 - 0 NIC=0

Type Code

BDS DO-260A Horizontal Containment Radius Limit (Rc)

NIC Supplement

NIC

5


Rc <7.5 m 0 NIC=11

6 Rc <25 m 0 NIC=10

7

Rc <75 m 1 NIC=9

Rc <0.1 NM (185.25 m) 0 NIC=8

8 Rc >0.1 NM (185.25 m) or unknown 0 NIC=0


Determining DO-260A/B NIC – Airborne Position

B AT 2 . 5 H r

B D S = 0 , 5 A I R B O R N E P O S T Y P E = 1 1 D F 1 7 A A = 3 A C 4 2 1 C O U N T = 1 0 0 0 M E = 5 8 3 7 8 4 A E 8 2 E 8 2 E C D C P E R I O D = 0 . 5 0 S L AT : 3 7 3 9 0 . 0 0 N L O N G : 9 7 3 2 0 . 7 0 W P O S = G L O B AL N I C - B = 1 T = N / U T C S U R V E I L L A N C E S T AT U S = N O I N F O B A R O P R E S A L T = 1 3 1 0 2 5 f t G N S S A L T = N / A N I C = 7 R c = < 0 . 2 n m ( 3 7 0 . 4 m )

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

Type Code may be used in the table shown on the next slide to show full details i.e. NIC Supplement NIC and Rc are directly displayed. NIC should be 11 - 8 for DO-260A Transponders and 11- 6 for DO-260B Transponders In both DO-260A and DO-260B, NIC=0 is unusable. It is normal for NIC to change, as the received satellite geometry changes. Lat, Long, Hdg & Movement are directly displayed


Determining DO-260A NIC – Airborne Position

Type Code


NIC Supplement

NIC Frequency of Type Code

Useable by ATC

9


Rc <7.5 m & VPL < 11 m - 0 - NIC=11 Rare

Yes

10 Rc <25 m & VPL < 37.5 m - 0 - NIC=10 Common

11

Rc <75 m & VPL < 112 m - 1 - NIC=9 Common

Rc <0.1 NM (185.25 m) - 0 - NIC=8 Common

12 Rc <0.2 NM (370.4 m) - 0 - NIC=7 Common

13

Rc <0. 6 NM (1111.2 m) - 1 - NIC=6

Less Common Rc <0.5 NM (925.6 m) - 0 -

14 Rc <1.0 NM (1852 m) - 0 - NIC=5 Infrequent

15 Rc <2 NM (3.704 km) - 0 - NIC=4

Unlikely 16

Rc <4 NM (7.408 km) - 1 - NIC=3 No Rc <8 NM (14.816 km) - 0 - NIC=2

17 Rc <20 NM (37.04 km) - 0 - NIC=1

18 Rc>20 NM (37.04 km) or unknown - 0 - NIC=0 Unusable


Determining DO-260B NIC – Airborne Position

Type Code


NIC Supplement A B C

NIC Frequency of Type Code

Useable by ATC

9


Rc <7.5 m 0 0 - NIC=11 Rare

Yes

10 Rc <25 m 0 0 - NIC=10 Common

11

Rc <75 m 1 1 - NIC=9 Common

Rc <0.1 NM (185.25 m) 0 0 - NIC=8 Common

12 Rc <0.2 NM (370.4 m) 0 0 - NIC=7 Common

13

Rc <0.3 NM (555.6 m) 0 1 - NIC=6 Less Common Rc <0.5 NM (925.6 m) 0 0 -

Rc <0.6 NM (1111.2 m) 1 0 -

14 Rc <1.0 NM (1852 m) 0 0 - NIC=5 Infrequent

15 Rc <2 NM (3.704 km) 0 0 - NIC=4

Unlikely

16

Rc <4 NM (7.408 km) 1 1 - NIC=3

No Rc <8 NM (14.816 km) 0 0 - NIC=2

17 Rc <20 NM (37.04 km) 0 0 - NIC=1

18 Rc>20 NM (37.04 km) or unknown 0 0 - NIC=0 Unusable


Determining DO-260A/B NACp SV Quality Position

B AT 2 . 5 H r

B D S = 6 , 5 A / C O P S T AT U S T Y P E = 3 1 D F 1 7 A A = 1 2 3 4 5 6 C O U N T = 1 1 M E = F 8 2 A A A 2 A A A 4 A A F P E R I O D = 1 . 5 7 s S U B T Y P E = 0 - A I R V E R S I O N = 2 - D O - 2 6 0 B C C F M T = 2 A A A A R V = 1 T S = 0 1 0 9 0 = 0 U AT = 1 T C = 2 A D S R = 0 T C A S O P = 1 O M F M T = 0 S D A = 0 S A F = 0 AT C = 1 R A = 1 I D = N O H R Z R E F = M A G N O R T H N I C - A = 0 G V A = 2 N I C - B A R O = 1 S I L S U P = 1 S I L = 2 N A C P = 8 ( E P U < 9 2 . 6 m ) A D S R ( 5 6 ) = 1

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

NACP Displays the SV (Satellite Vehicle) quality.. EPU (Estimated Position Uncertainty). For NACP=9, A, B VEPU Vertical Estimated Position Uncertainty is also displayed The NACP should be 5 – 11 Note: There is no equivalent of NACP within DO-260 BDS 6,5 (Type 31 messages) reports NACP In DO-260A transponders, BDS 6,2 (Type 29 messages), also report NACP. Refer to the next slide for the NACP table.


Determining DO-260A/B NACp SV Quality Position

NACp 95% Horizontal Accuracy Bounds EPU

Comment Used By ATC

B EPU <3 m LAAS

Yes

A EPU <10 m WAAS

9 EPU <30 m GPS (with SA OFF)

8 EPU <92.6 m (0.05 NM) GPS (with SA ON)

7 EPU <185.2m (0.1 NM) RNP-0.1 accuracy

6 EPU <555.6 m (0.3 NM) RNP-0.3 accuracy

5 EPU <926 m (0.5 NM) RNP-0.5 accuracy

4 EPU <1852 m (1 NM) RNP-1 accuracy

No

3 EPU <3.704 km (2 NM) RNP-2 accuracy

2 EPU < 7.408 km (4 NM) RNP-4 accuracy

1 EPU <18.52 km (10 NM) RNP-10 accuracy

0 EPU≥ 18.52 km (≥10 NM) Unknown Accuracy


Determining DO-260A/B SIL SV Quality Position

B AT 2 . 5 H r

B D S = 6 , 5 A / C O P S T AT U S T Y P E = 3 1 D F 1 7 A A = 1 2 3 4 5 6 C O U N T = 1 1 M E = F 8 2 A A A 2 A A A 4 A A F P E R I O D = 1 . 5 7 s S U B T Y P E = 0 - A I R V E R S I O N = 2 - D O - 2 6 0 B C C F M T = 2 A A A A R V = 1 T S = 0 1 0 9 0 = 0 U AT = 1 T C = 2 A D S R = 0 T C A S O P = 1 O M F M T = 0 S D A = 0 S A F = 0 AT C = 1 R A = 1 I D = N O N I C B A R O = 1 H R Z R E F = M A G N O R T H N I C - A = 0 G V A = 2 N I C - B A R O = 1 S I L S U P = 1 S I L = 2 N A C P = 8 ( E P U < 9 2 . 6 m ) A D S R ( 5 6 ) = 1

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

SIL displays the Source Integrity Level. BDS 6,5 (Type 31 messages) reports SIL. In DO-260A transponders, BDS 6,2 (Type 29 messages), also report SIL It is important that SIL be value 2 or 3 if using a GPS with HPL calculation & FDE (Fault Detection and Exclusion) an advanced version of RAIM. SIL should only be set to value 2 or 3 if the GPS is an approved position source for ADS-B. The SIL Supplement reports: 0= per hour 1= per sample

SIL Probability of Exceeding the NIC Containment Radius (Rc) Comment

3 ≤1 x 10-7 per flight hour or per sample Acceptable Integrity

2 ≤1 x 10-5 per flight hour or per sample Acceptable Integrity

1 ≤10 x 10-³ per flight hour or per sample Inadequate Integrity

0 Unknown or >1 x 10-³ per flight hour or per sample No Integrity


FAA AC 20-165 Test - Air

B AT 2 . 5 H r

L AT = 3 7 2 9 3 1 . 3 3 N L O N = 9 7 2 1 3 7 . 3 5 W P O S I T I O N E R R O R = 2 . 7 6 3 m N A C P = 8 ( E P U < 9 2 . 6 m ) N I C = 9 N AC V = 2 E - W V E L = 1 1 1 k t s E N - S V E L = 2 4 6 k t s N A D S - B B AR O AL T = 2 0 0 0 0 f t X P D R B A R O A L T = 2 0 1 0 0 f t AL T I T U D E E R R O R = 1 0 0 f t G E O M E T R I C AL T = 2 0 2 2 5 f t

R U N T E S T

P R E V T E S T

AD V C I R C 2 0 - 1 6 5 A I R A V A I L

N E X T T E S T

R E T U R N

The FAA AC 20-165 Test supports the FAA Advisory Circular of the same designation, specifically chapter 4.1. Ground Test. The test provides a convenient means of bringing together many of the test elements we have seen over the last few slides. The test reduces the time for test and provides a permanent record in the data dump.

B AT 2 . 5 H r

S I L = 3 S D A = 3 T C AS O P = 0 R A A C T I V E = 0 M O D E 3 / A C O D E = 6 6 1 1 I D E N T = N O A D D R E S S = 5 5 5 5 5 5 ( 2 5 2 5 2 5 2 5 ) E M E R G / P R I O R C O D E = 0 - N O E M E R G E N C Y E M I T C AT = R E S E R V E D A D S - B I N C A P = 1 F L I G H T I D = A E R O F L E X

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

The Position Error is calculated with the Haversine formula, with the position entered in the ADS-B setup as the reference.


FAA AC 20-165 Test - Surface

B AT 2 . 5 H r

L AT = 3 7 3 7 2 6 . 1 0 N L O N = 9 7 2 7 4 0 . 8 6 W P O S I T I O N E R R O R = 4 . 4 5 1 m N A C P = B ( E P U < 3 m a n d V E P U < 4 m ) N I C = 8 N AC V = 1 R E P O R T E D M O V E M E N T = 0 k t T O < 0 . 1 2 5 k t H E A D I N G = 2 8 d e g

R U N T E S T

P R E V T E S T

AD V C I R C 2 0 - 1 6 5 S U R A V A I L

N E X T T E S T

R E T U R N

B AT 2 . 5 H r

S I L = 3 S D A = 3 L E N / W I D T H = 8 - < 5 5 m , < 4 5 m R A A C T I V E = 0 M O D E 3 / A C O D E = 7 0 0 0 I D E N T = N O A D D R E S S = 5 5 5 5 5 5 ( 2 5 2 5 2 5 2 5 ) E M E R G / P R I O R C O D E = 0 - N O E M E R G E N C Y E M I T C AT = H E A V Y A D S - B I N C A P = 1 F L I G H T I D = A E R O F L E X

R U N T E S T

P R E V T E S T


N E X T T E S T

R E T U R N

The Position Error is calculated with the Haversine formula, with the position entered in the ADS-B setup as the reference.

The FAA AC 20-165 Test supports the FAA Advisory Circular of the same designation, specifically chapter 4.1. Ground Test. The test provides a convenient means of bringing together many of the test elements we have seen over the last few slides. The test reduces the time for test and provides a permanent record in the data dump.


Testing an ADS-B In Installation

Testing ADS-B In


Target Capability of the 6000

The 6000 does not have a multiple dynamic ADS-B Target Generation capability however, it is capable of generating either an airborne or surface single static target. A DO-260B ADS-B aircraft target typically comprises of… Airborne: 5 extended squitter BDS messages BDS 0,5 Air Position BDS 0,8 Identity & Category BDS 0,9 Airborne Velocity BDS 6,1 Aircraft Status BDS 6,5 Aircraft Operational Status Surface: 4 extended squitter BDS messages BDS 0,6 Surface Position BDS 0,8 Identity & Category BDS 6,1 Aircraft Status BDS 6,5 Aircraft Operational Status


ADS-B GEN List Screen

The ADS-B GEN List screen displays the available BDS registers for transmission as extended squitter. The up down keys are used to select the desired BDS. The selected BDS may be ENABLED by pressing the BDS ON key, which also becomes the BDS OFF key if the BDS is already ENABLED.


Setting up a DO-260B Airborne Target - BDS 6,5

Ensure the VERSION is set to 2-DO-260B. Ensure the AA is different to the Aircraft under test. Also ensure the MANUAL AA in the setup menu is set to the same AA setting in all the GEN BDS screens. Ensure that NACP is set so the EPU is less than the Rc set in the NIC field in BDS 0,5 .


Setting up a DO-260B Airborne Target – BDS 0,5

B AT 2 . 5 H r

B D S = 0 , 5 A I R B O R N E P O S T Y P E : 1 1 D F 1 7 A A : 3 A C 4 2 1 C O U N T = 0 M E = 5 8 3 7 8 4 A E 8 2 E 8 2 E C D C P E R I O D : 0 . 5 0 s L AT : 3 7 3 9 0 . 0 0 N L O N G : 9 7 3 2 0 . 7 0 W P O S : G L O B AL N I C - B : 0 T : N / U T C S U R V E I L L A N C E S T AT U S : N O I N F O B A R O P R E S A L T : 1 0 0 0 0 f t G N S S A L T : - N I C = 8 R c = < 0 . 1 N M ( 1 8 5 . 2 5 m )

R U N T E S T

P R E V P A R A M

G E N B D S 0 , 5 A I R

N E X T P A R A M

R E T U R N B D S O F F

For an Aircraft Under Test position of .. LAT : 37.39.00 N LONG: 97.25.48 W To generate a target at 90 deg 5nm Enter: LAT: 37.38.0.00 N LONG: 97.32.0.70 W This website has useful online calculator for determining the Lat/Long offsets required for specific target positions relative to the UUT position. http://www.movable-type.co.uk/scripts/latlong.html Set BARO PRES ALT to same altitude as Aircraft Under Test COUNT displays the total number of squitters transmitted since the test was run. Note: ME field will toggle between two sets of values as each odd & even position squitter is sent. Set BARO PRES ALT the same as the Aircraft altitude.

Note: Use UC584 antenna coupler, or apply antenna shields when running the aircraft at altitude, to prevent either ADS-B In systems or Hybrid TCAS seeing the aircraft under test.



B AT 2 . 5 H r

B D S = 0 , 8 I D E N T & C AT T Y P E : 4 D F 1 7 A A = 3 A C 4 2 1 C O U N T = 0 M E = 2 3 6 1 0 3 B 3 D 3 5 C 7 2 P E R I O D : 5 . 0 0 s A I S = 6 1 0 3 B 3 D 3 5 C 7 2 F L I G H T I D : X P N 3 4 5 1 2 E M I T C AT S E T : A E M I T C AT : L AR G E

R U N T E S T

P R E V P A R A M

G E N B D S 0 , 8

N E X T P A R A M


.

Type in the flight ID and emitter category for the simulated target.



B AT 2 . 5 H r

B D S = 0 , 9 A I R B O R N E V E L T Y P E : 1 9 D F 1 7 A A : 3 A C 4 2 1 C O U N T = 0 M E = 9 9 2 0 0 1 0 0 3 8 0 4 8 1 P E R I O D : 0 . 5 0 s E - W V E L : 0 k t s E N A C V : 4 N - S V E L : 0 k t s N H D G : 0 . 0 0 d e g s S U B T Y P E : 1 - V E L O V R G N D N O R M V E R T R AT E = 0 f t / m i n G E O A L T D I F F F R O M B AR O : 0 f t S O U R C E : B A R O I N T E N T C H A N G E : N O A I R S P E E D : - A I R S P E E D T Y P E : - R E S E R V E D : N O

R U N T E S T

P R E V P A R A M

G E N B D S 0 , 9

N E X T P A R A M


.

E-W & N-S: Important to set these parameters to 0, to agree with the Latitude and Longitude not changing over time. VERT RATE: Set this parameter to 0 , to agree with BARO PRES ALT not changing over time.


Setting up a DO-260B Airborne Target – BDS 6,1 ST1

B AT 2 . 5 H r

B D S = 6 , 1 A / C S T AT U S S T 1 T Y P E : 2 8 D F 1 7 A A : 3 A C 4 2 1 C O U N T = 0 M E = E 1 1 C 0 9 0 0 0 0 0 0 0 0 P E R I O D = 5 . 0 0 s S U B T Y P E : 1 - E M E R G E N C Y / P R I O R S T AT U S E M E R G E N C Y / P R I O R C O D E : 0 - N O E M E R G E N C Y M O D E A ( 4 0 9 6 ) C O D E : 1 2 3 4 R E S E R V E D : 0 0 0 0 0 0 0 0 0

R U N T E S T

P R E V P A R A M

G E N B D S 6 , 1 S T 1

N E X T P A R A M


.

Set Mode A code to be different to that of the Aircraft under test. Note on 6,5 ensure the VERSION is set to 2-DO-260B.


Setting up a DO-260B Airborne Target – BDS 6,1 ST2

B AT 2 . 5 H r

B D S = 6 , 1 A / C S T AT U S S T 2 T Y P E : 2 8 D F 1 7 A A : 3 A C 4 2 1 C O U N T = 0 M E = E 2 0 0 0 0 0 0 0 0 0 0 0 0 P E R I O D : 5 . 0 0 s S U B T Y P E = 2 - T C A S R A B R O A D C A S T T T I : 0 - N O T I D D AT A T I D A : T I D R : T I D B : R AT : A R A: M T E : R A C : T H R E AT A D D R :

R U N T E S T

P R E V P A R A M

G E N B D S 6 , 1 S T 2

N E X T P A R A M


No changes needed


GICB List Screen, 1-12

B AT 2 . 5 H r

1 0 , 5 A I R B O R N E P O S - A V A I L 2 0 , 6 S U R F A C E P O S - N O T C A P 3 0 , 7 S Q T R S T AT U S - AV A I L 4 0 , 8 I D E N T & C AT - A V A I L 5 0 , 9 A I R B O R N E V E L - A V A I L 6 1 , 0 D AT A L N K C A P - A V A I L 7 1 , 7 C O M G I C B C A P - A V A I L 8 1 , 8 S P E C S E R V C A P # 1 - A V A I L 9 1 , 9 S P E C S E R V C A P # 2 - A V A I L 1 0 1 , A S P E C S E R V C A P # 3 - A V A I L 1 1 1 , B S P E C S E R V C A P # 4 - A V A I L 1 2 1 , C S P E C S E R V C A P # 5 - A V A I L

R U N T E S T

B D S D A T A

G I C B D F 2 0

R E T U R N

The GICB Tests may be used to extract the ADS-B BDS registers from the transponder for examination. This is useful when a particular BDS is not squittering, and will confirm that the BDS register is being populated or partially populated. If the BDS register is populated with data, then the problem is likely to be a condition not being met in the transponder, preventing squitter transmission.



B AT 2 . 5 H r

1 3 1 , D M S P C A P R P T 1 - 2 8 - AV A I L 1 4 1 , E M S P C A P R P T 2 9 - 5 6 - AV A I L 1 5 1 , F M S P C A P R P T 5 7 - 6 3 - AV A I L 1 6 2 , 0 F L I G H T I D AT - AV A I L 1 7 2 , 1 A I R C R A F T R E G # - AV A I L 1 8 3 , 0 A C A S A R A - AV A I L 1 9 4 , 0 V E R T I N T E N T - AV A I L 2 0 4 , 1 W A Y P O I N T N A M E - AV A I L 2 1 4 , 2 W A Y P O I N T P O S - AV A I L 2 2 4 , 3 W A Y P O I N T D E T A I L S - AV A I L 2 3 5 , 0 T R A C K & T U R N - N O T R U N 2 4 6 , 0 H E A D I N G & S P E E D - N O T R U N

R U N T E S T

B D S D A T A

G I C B D F 2 0

R E T U R N



B AT 2 . 5 H r

1 7 2 , 1 A I R C R A F T R E G # - A V A I L 1 8 3 , 0 A C A S A R A - A V A I L 1 9 4 , 0 V E R T I N T E N T - A V A I L 2 0 4 , 1 W A Y P O I N T N A M E - AV A I L 2 1 4 , 2 W A Y P O I N T N A M E - AV A I L 2 2 4 , 3 W A Y P O I N T N A M E - AV A I L 2 3 5 , 0 T R A C K & T U R N - AV A I L 2 4 6 , 0 H E A D I N G & S P E E D - AV A I L 2 5 6 , 1 A / C S T AT U S S T 1 - AV A I L 2 6 6 , 1 A / C S T AT U S S T 2 - AV A I L 2 7 6 , 2 T S S S U B T Y P E 0 - AV A I L 2 8 6 , 2 T S S S U B T Y P E 1 - N O T R U N 2 9 6 , 5 A / C O P S T AT U S A I R - AV A I L 3 0 6 , 5 A / C O P S T AT U S S U R - AV A I L

R U N T E S T

B D S D A T A

G I C B D F 2 0

R E T U R N


GICB Data Screen

B AT 2 . 5 H r

B D S = 0 , 5 A I R B O R N E P O S T Y P E = 1 4 D F 2 0 A A = 3 A C 4 2 1 ( 1 6 5 4 2 0 4 1 ) M B = 0 0 0 0 0 0 0 0 0 0 0 0 0 0 L AT = 3 7 3 9 0 0 N L O N G = 9 7 2 5 4 8 W P O S = G L O B AL N I C - B = 1 T = N / U T C S U R V E I L L A N C E S T AT U S = N O I N F O B A R O P R E S A L T = 1 3 1 0 2 5 f t G N S S A L T = N / A N I C = 6 R c = < 1 n m ( 1 8 5 2 m )

R U N T E S T

P R E V T E S T

G I C B B D S 0 , 5 A V A I L

N E X T T E S T

R E T U R N

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