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Get Step by step directions on using your IFR6000 with ADS ... Integrity_IFR6000...Get Step by step...
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ADVANCED ELECTRONIC SOLUTIONS AVIATION SERVICES COMMUNICATIONS AND CONNECTIVITY MISSION SYSTEMS
Get Step by step directions on using your IFR6000 with ADS-B Integrity Software
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ADS-B Out
ADS-B Extended Squitter Types
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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
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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
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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
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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
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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
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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.
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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.
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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.
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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
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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.
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ARINC 743A GPS Output Data DO-229D
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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
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The NACp - NIC Relationship
NACp EPU < NIC Rc for Same NACp & NIC Values
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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.
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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
M O N B D S 0 , 6 A V A I L
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
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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
M O N B D S 0 , 5 A V A I L
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. .
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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
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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
M O N B D S 0 , 6 A V A I L
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
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Determining DO-260A/B NIC – Surface Position
Type Code
BDS DO-260B Horizontal Containment Radius Limit (Rc)
NIC Supplement A B C
NIC
5
BDS 0,6 Surface Position
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
BDS 0,6 Surface Position
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
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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
M O N B D S 0 , 5 A V A I L
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
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Determining DO-260A NIC – Airborne Position
Type Code
BDS Horizontal Containment Radius Limit (Rc)
NIC Supplement
NIC Frequency of Type Code
Useable by ATC
9
BDS 0,5 Airborne Position
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
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Determining DO-260B NIC – Airborne Position
Type Code
BDS Horizontal Containment Radius Limit (Rc)
NIC Supplement A B C
NIC Frequency of Type Code
Useable by ATC
9
BDS 0,5 Airborne Position
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
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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
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
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.
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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
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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
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
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
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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
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 Position Error is calculated with the Haversine formula, with the position entered in the ADS-B setup as the reference.
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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
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 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.
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Testing an ADS-B In Installation
Testing ADS-B In
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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
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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.
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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 .
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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.
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Setting up a DO-260B Airborne Target – 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 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
R E T U R N B D S O F F
.
Type in the flight ID and emitter category for the simulated target.
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Setting up a DO-260B Airborne Target – BDS 0,9
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
R E T U R N B D S O F F
.
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.
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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
R E T U R N B D S O F F
.
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.
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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
R E T U R N B D S O F F
No changes needed
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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.
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GICB List Screen, 13-24
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
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GICB List Screen, 13-24
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
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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