ACSS an L 3 Communications and Thales TT-950 TCAS II User Manual Part 2

ACSS an L-3 Communications and Thales Company TCAS II Part 2

1. User Manual Part 1
2. User Manual Part 2

User Manual Part 2

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Document ID	302828
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Document Description	User Manual Part 2
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Document Type	User Manual
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Date Submitted	2003-02-13 00:00:00
Date Available	2003-04-16 00:00:00
Creation Date	2003-02-13 14:35:41
Producing Software	Acrobat Distiller 5.0.5 (Windows)
Document Lastmod	2003-02-13 14:36:03
Document Title	User Manual Part 2

SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 2--13 (Sheet 2).
Directional Antenna Baseplate Outline and Installation Diagram
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2--53/(2--54 blank)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 2--14. Gables G130--XX Control Panel Outline and Installation Diagram
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2--55/(2--56 blank)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 2--15. VSI/TRA Outline and Installation Diagram
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2--57/(2--58 blank)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
ELECTRICAL INSTALLATION
1. General
This section gives electrical installation procedures, power distribution, and interconnect
information for each component on the T2CAS system.
2. Equipment and Materials
For new T2CAS installations, refer to Table 1--1 for RCZ--852 Transponder Installation Kit
information. For all other components, refer to the applicable Outline and Installation Diagram
in the MECHANICAL INSTALLATION section for mating connector part numbers.
3. Electrical Installation Procedure
The information necessary to provide the electrical interconnections is contained in the
following paragraphs. Refer to Section 4, LOADING/GRADIENT SPECIFICATIONS, for a list
of the signal names used in the interconnect diagrams and tables.
NOTE:
Unless otherwise specified, all wires shall be stranded #22 AWG.
NOTE:
All ARINC 429 Data Bus wires shall be stranded #22 AWG twisted shield wire. All
outer shields shall be terminated to the airframe ground. Unshielded portions of the
cable and shield ground wires should be kept to a minimum length to minimize RF
susceptibility.
NOTE:
All electrical installations must be in compliance with SFAR--88.
4. Electrical Installation
A. TT--950/951/952 T2CAS Computer Units
Figure 3--1 shows some general types of T2CAS system installations, using various
combinations of controllers (control panels) and transponders.
The various installation options require different electrical connections as described in the
paragraphs that follow.
The T2CAS Computer Unit uses programming and configuration straps to select or
deselect various TCAS functions. In addition, the T2CAS uses the APM and ASDB to
select or deselect various TAWS/RWS functions.
The T2CAS Computer Unit ARINC 600 connector layout is shown in Figure 3--2. The
contact arrangement for the various connector plugs are shown in Figure 3--3 thru
Figure 3--8. Figure 3--9 shows the connector pin layout for the DATA LOADER connector
located on the front of the computer unit.
B. APM
Figure 2--6 shows a typical APM installation. An APM can be mounted to existing aircraft
structure or can be mounted to the ACSS’ APM mounting bracket that is secured to the
aft side of the T2CAS computer tray connector, reference Figure 3--3. If the Customer
specifies the ACSS APM mounting bracket, the Contractor shall manufacture and provide
this APM bracket sub kit for this Customer’s T2CAS installations
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3--1
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
C. TCAS Antennas
The electrical installation for the TCAS antennas is specified in the LOADING AND
GRADIENT section. Figure 3--3 shows the T2CAS computer contact arrangement for the
top directional antenna and Figure 3--4 shows the T2CAS computer contact arrangement
for the bottom antenna.
3--2
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--1. Typical TCAS Installation Types
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
D. GPS Antenna and Coax
All T2CAS installations require a GPS position source (that includes GPS altitude). The
installation design will consist of an A429 interface to the GPS sensor if the signal is
available, or the T2CAS internal GPS module will be required. The installation then
consists of the installation of a GPS antenna and the coax cable to the T2CAS unit, LBP
pin 13. Figure 2--4 shows a typical T2CAS installation with an existing GPS source.
Where the internal module is required, the T2CAS GPS Installation Data Package
includes the GPS antenna mounting structures provisions and all of the coax details to
secure the coax to the airframe and connect the T2CAS GPS antenna with the T2CAS
computer’s LBP pin 13. Figure 2--4 shows a typical T2CAS installation with an internal
GPS module (installation includes GPS antenna and coax kit).
3--4
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--2. T2CAS Computer Tray Mating Connector
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3--5
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--3. Contact Arrangement for CU Left Top Plug (LTP) Insert
Figure 3--4. Contact Arrangement for CU Left Middle Plug (LMP) Insert
3--6
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--5. Contact Arrangement for Left Bottom Plug (LBP) Insert
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3--7
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--6. Contact Arrangement for Right Top Plug (RTP) Insert
3--8
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--7. Contact Arrangement for Right Middle Plug (RMP) Insert
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3--9
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--8. Contact Arrangement for Right Bottom Plug (RBP) Insert
3--10
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--9. TCAS Computer Unit Data Loader Connector (J1) Pin Layout
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3--11
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
E.
Control Panels
Table 3--1 contains the interconnect data for the Gables G7130 series control panels.
Table 3--1. Gables G7130--XX ATC/TCAS Control Panel Interconnect Data
I/O
Description
Connector
Pin
Connects To
(I)
5 V ac Pnl Lighting (H)
J1--1
(20)
Acft Lighting Source
(I)
5 V ac Pnl Lighting (L)
J1--2
(20)
Acft Lighting Source
(I)
+28 V dc Input Power (H)
J1--3
(20)
Acft 28 V dc Power
(I)
+28 V dc Return (L)
J1--4
(20)
Acft dc Ground
(O) Antenna Transfer Discrete
J1--5
(22)
Antenna Relay
(I)
J1--6
(22)
Acft dc Ground
(O) Standby/On Output Disc
J1--7
(22)
Transponder No. 1
(I)
Chassis Ground
J1--8
(22)
Airframe Ground
(I)
Functional Test
J1--9
(22)
Remote Test Switch
J1--10
(22)
Remote Warn Sys
dc Ground
(O) Warning & Caution
Reserved
J1--11
(I)
XPDR Fail Logic No.2
J1--12
(22)
Transponder No. 1
(I)
Ident Input
J1--13
(22)
Remote IDENT Switch
(I)
XPDR Fail (High Level)
J1--14
NC
(O) Air/Gnd Switched Discrete
J1--15
NC
(O) Alt Source Select Discrete
J1--16
(22)
Transponder No.1
(20)
Acft 28 V dc Power
J1--17
Monitor Lamp Power
J1--18
Reserved
J1--19
(I)
XPDR Configuration
J1--20
(I)
Lamp Test
J1--21
(22)
(O) ARINC 429 (A) Out
J1--22
(22)
(O) ARINC 429 (B) Out
J1--23
(22)
NC
GND
(I)
Air/Gnd Discrete
J1--24
Reserved
J2--1
Reserved
J2--2
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1, 2
2, 4
Reserved
(I)
Notes
Rmt Lamp Test SW
Transponder No.1
Transponder No.1
WOW Switch
(22)
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GND
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--1. Gables G7130--XX ATC/TCAS Control Panel Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
Notes
(I)
+28V dc Input Power (H)
J2--3
(20)
Acft 28 V dc Power
(I)
+28V dc Return (L)
J2--4
(20)
Acft dc Ground
(O) Antenna Transfer Discrete
J2--5
(22)
Antenna Relay
(I)
J2--6
(22)
Acft dc Ground
(O) Standby/On Discrete
J2--7
(22)
Transponder No.2
(I)
Chassis Ground
J2--8
(22)
Airframe Ground
(I)
Functional Test
J2--9
(22)
Remote Test SW
J2--10
(22)
Remote Warn Sys
dc Ground
(O) Warning & Caution
Reserved
J2--11
(I)
XPDR Fail Logic No.2
J2--12
(22)
Transponder No.2
(I)
Ident Input
J2--13
(22)
Remote Ident SW
(I)
XPDR Fail (High Level)
J2--14
1, 2
NC
2, 4
(O) Air/Gnd Switched Discrete
J2--15
(22)
(O) Alt Source Select Discrete
J2--16
(22)
Transponder No.2
(20)
Acft 28 V dc Power
Gnd/Open
Rmt Lamp Test SW
Transponder No.2
Transponder No.2
Acft WOW Switch
Reserved
J2--17
Monitor Lamp Pwr
J2--18
Reserved
J2--19
(I)
XPDR Configuration
J2--20
(I)
Lamp Test
J2--21
(22)
(O) ARINC 429 (A) Out
J2--22
(22)
(O) ARINC 429 (B) Out
J2--23
(22)
(I)
NC
NC
GND
(I)
Air/Gnd Discrete
J2--24
(22)
GND
NOTES:
1. Connect either J1--5 or J2--5 to an antenna switching relay if one set of ATC antennas is used in a
dual transponder installation.
2. Refer to Loading Gradient Specifications in Table 4--2.
3. Tie chassis ground to aircraft frame.
4. 28 V dc discrete input from Collins TDR--94D transponder.
5. Two wire shielded cable. Tie shields to aircraft dc ground.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
F.
Thales VSI/TRA Display
Table 3--2 contains interconnect data for the Thales 41--pin connector units.
Figure 3--10 shows the connector pin layouts for the 41--pin VSI/TRA configuration.
Table 3--2. 41--Pin VSI/TRA Interconnect Data
I/O
Description
Connector
Pin
Connects To
(I)
VS +dc Ref
J1--1
(22)
ARINC 575 ADC
(I)
VS dc Rate
J1--2
(22)
ARINC 575 ADC
(I)
VS --dc Ref
J1--3
(22)
ARINC 575 ADC
(I)
Primary VS (HI)
J1--4
(22)
(I)
Primary VS (LO)
J1--6
(22)
GND
(I)
VS 26 V ac Ref (HI)
J1--5
(I)
Vert. Speed Digital Port (A) J1--7
(I)
Vert. Speed Digital Port (B) J1--21
(I)
VS VALID NO.1
(I)
Notes
ARINC 565 ADC or
IRS
ARINC 565 ADC or
GND IRS
(22)
ARINC 565 ADC or
IRS
J1--8
(22)
ARINC 565/575 ADC
or IRS
5 V Lamp Dimming (LO)
J1--9
(22)
Acft Lamp Dim Ckt
(I)
5 V Lamp Dimming (HI)
J1--10
(22)
Acft Lamp Dim Ckt
(I)
TCAS TA/RA
ARINC 429 (B)
J1--11
(22)
TCAS Computer
(I)
TCAS TA/RA
ARINC 429 (A)
J1--26
(22)
TCAS Computer
(I)
VS No.1 ARINC 429 (B)
J1--12
(22)
Digital ADC No.1 or
IRS No.1
(I)
VS No.1 ARINC 429 (A)
J1--27
(22)
Digital ADC No.1 or
GND IRS No.1
GND
GND
(O) 26 VAC Bootstrap ref. Out
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J1--13
GND
Bootstrap instrument
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--2. 41--Pin VSI/TRA Interconnect Data (cont)
I/O
Description
Connector
Pin
(I)
VS No.2 ARINC 429 (B)
J1--14
(22)
(I)
VS No.2 ARINC 429 (A)
J1--30
(22)
Connects To
GND
Notes
Digital ADC No.2 or
IRS No.2
Digital ADC No.2 or
GND IRS No.2
(I)
Config Strap Common
J1--15
(22)
Config Strap Logic
Gnd
(I)
VS 26 V ac Ref (C)
J1--16
(22)
ARINC 565 ADC or
IRS
(I)
Config Strap No.3 (CS3)
J1--17
(22)
Gnd/Open
(O) Secondary VERT SPEED
Validity input (+ 28 VDC)
J1--18
(20)
(O) VERT SPEED Bootstrap
AC Out (HI)
J1--19
(O) VERT SPEED Boots strap
AC Out (LO)
(I)
ARINC 565/575 ADC
(20)
Bootstrap instrument
J1--20
(20)
Bootstrap instrument
Chassis Ground
J1--22
(22)
Airframe Ground
(I)
115 V ac Return (C)
J1--23
(20)
Acft ac Ground
(I)
Remote Light Sensor (LO)
J1--24
(22)
(I)
Remote Light Sensor (HI)
J1--25
(22)
GND
(I)
Configuration strap
J1--28
Acft Rmt Light Sensor
Acft Rmt Light Sensor
GND
V/S response time
selection
(O) RA Valid Out
J1--29
(22)
TCAS Computer
(I)
Source Sel Discrete In
(SS 1)
J1--31
(22)
Gnd/Open
(I)
Config Strap No.0 (CS0)
J1--32
(22)
Gnd/Open
(I)
Config Strap No.1 (CS1)
J1--33
(22)
Gnd/Open
(I)
Config Strap No.2 (CS2)
J1--34
(22)
Gnd/Open
(I)
Config Strap No.4 (CS4)
J1--35
(22)
Gnd/Open
(I)
Secondary Analog AC
Input (LO)
J1--36
(22)
ARINC 565 ADC
(I)
Secondary Source Select
Discrete Input (SS 2)
J1--37
(22)
Aircraft Switch
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--2. 41--Pin VSI/TRA Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
(O) VERT SPEED VALID
Discrete Output
J1--38
(22)
(I)
dc Ground
J1--39
(22)
Acft dc Ground
(I)
115 V ac Input Power (H)
J1--40
(20)
Acft 115 V ac Supply
(I)
Self--test/Display Test
J1--41
(22)
Aircraft Switch
NOTES:
1. Two wire shielded cable. Tie shields to aircraft dc ground.
2. Three wire shielded cable. Tie shields to aircraft dc ground.
3. Tie chassis ground to aircraft frame.
3--16
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Notes
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--10. VSI/TRA 41--Pin Connector Layout
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
G. TAWS Terrain Hazard Display
All T2CAS installations will require at least one TAWS terrain hazard display. ARINC 708
and ARINC 429 WXR display and EFIS interfaces are supported. Figure 3--11 shows a
typical single ARINC 708 terrain hazard display interface. T2CAS’ dual--independent
terrain hazard display I/O supports dual ARINC 708 and dual ARINC 429 terrain hazard
display systems. Figure 3--11 shows a typical single ARINC 708 terrain hazard display
and display interface with annunciator switch panels. The TERR and WXR select
switches shown are momentary but alternate action switches are also supported. The
terrain INHIBIT or OVRD switches are alternate action switches and are typically guarded.
3--18
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--11. Typical T2CAS Single Terrain Hazard Display Interface
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
H. Transponders
Table 3--3 thru Table 3--6 contain the interface information for the ACSS transponders.
The transponders use altimetry data supplied in one of the following formats: ARINC 429
(from a digital ADC), ARINC 575, Synchro, or Gillham code. Altimetry data from one of
these source types must be connected to the transponder. If a single altimetry source is
used, it should be wired to both sets of transponder inputs.
All Mode S transponders require a unique 24--bit code (Mode S address) assigned to
each aircraft. For aircraft registered in the United States, it is necessary to have a
specific address code assigned. These address codes are presently issued by:
Federal Aviation Administration
FAA Aircraft Registry
P.O. Box 25504
Oklahoma City, OK 73125
Tel: (405) 954--3116
Fax: (405) 954--3548
If the aircraft is registered in a country other than the United States, contact the aviation
authority of the country in which the aircraft is registered.
The Mode S address is usually issued as an 8--digit octal number. To strap the address
code correctly, each digit must be converted to a corresponding binary number. (For
example: 7 octal = 111 binary, 1 octal = 001 binary.)
Once the 8--digit octal code is converted to a 24--bit binary number, the straps (address
pins) must be grounded or left open according to this binary number representation.
Each binary 0 represents an open strap and each binary 1 represents a grounded strap.
An example of an octal code number being converted to a binary number is shown below:
Octal address code = 1 2 3 4 5 6 7 0
In binary this number is: (MSB) 001 010 011 100 101 110 111 000 (LSB)
(1) XS--950 Data Link Transponder
Table 3--3 contains the interconnect data for the XS--950 Data Link Transponder, Part
No. 7517800--XXYYY.
If additional XS--950 Data Link Transponder installation or operational information is
required, refer to Mode S Data Link Transponder System Description and Installation
Manual, ACSS Pub. No. A09--3839--001.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data
I/O
Description
Connector
Pin
Connects To
Notes
(I)
Mode C Pulse A1 #2
P1A--1A
(22)
Encoding Altm #2
(I)
Mode C Pulse A2 #2
P1A--1B
(22)
Encoding Altm #2
(I)
Mode C Pulse A4 #2
P1A--1C
(22)
Encoding Altm #2
(I)
Mode C Pulse B1 #2
P1A--1D
(22)
Encoding Altm #2
(I)
Mode C Pulse B2 #2
P1A--1E
(22)
Encoding Altm #2
(I)
Mode C Pulse B4 #2
P1A--1F
(22)
Encoding Altm #2
(I)
Mode C Pulse C1 #2
P1A--1G (22)
Encoding Altm #2
(I)
Mode C Pulse C2 #2
P1A--1H
(22)
Encoding Altm #2
(I)
Mode C Pulse C4 #2
P1A--1J
(22)
Encoding Altm #2
(I)
Mode C Pulse D2 #2
P1A--1K
(22)
Encoding Altm #2
(I)
ARINC 429 (A) COMM A/B P1A--2A
Input from ADLP
(22)
Airborne Data Link
Processor
(I)
ARINC 429 (B) COMM A/B P1A--2B
Input from ADLP
(22)
Airborne Data Link
GND Processor
(I)
ARINC 429 (A) COMM C/D P1A--2C
Input from ADLP
(22)
(I)
ARINC 429 (B) Comm C/D P1A--2D
Input from ADLP
(22)
(O) ARINC 429 (A) COMM C/D P1A--2E
Output to ADLP
(22)
(O) ARINC 429 (B) COMM C/D P1A--2F
Output to ADLP
(22)
(I)
Reserved
P1A--2G
Reserved
P1A--2H
Reserved
P1A--2J
Mode C Pulse D4 #2
P1A--2K
Reserved
P1A--3A
GND
GND
GND
Airborne Data Link
Processor
Airborne Data Link
GND Processor
Airborne Data Link
Processor
Airborne Data Link
GND Processor
(22)
Encoding Altm #2
(O) XPDR Fail Discrete Out #2 P1A--3B
(22)
Control Panel
(I)
Cable Delay Prog Top/Bot
P1A--3C
(22)
Gnd/Open
(I)
Cable Delay Program B
P1A--3D
(22)
Gnd/Open
(I)
Cable Delay Program A
P1A--3E
(22)
Gnd/Open
(I)
Cable Delay Prog Common P1A--3F
(22)
Program Logic Gnd
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
Notes
(I)
SDI Program A
P1A--3G (22)
Gnd/Open
(I)
SDI Program B
P1A--3H
(22)
Gnd/Open
(I)
SDI Common
P1A--3J
(22)
Program Logic Gnd
(I)
Mode C Pulse Common #2 P1A--3K
(22)
Encoding Altm #2
(I)
Syn Alt In #1: Coarse X
P1A--4A
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: Coarse Y
P1A--4B
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: Coarse Z
P1A--4C
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: 26 V Ref (H)
P1A--4D
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: 26 V Ref (C) P1A--4E
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: Fine X
P1A--4F
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: Fine Y
P1A--4G (22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: Fine Z
P1A--4H
(22)
ARINC 565 ADC #1
(I)
Syn Alt In #1: Flag
P1A--4J
(22)
ARINC 565 ADC #1
Reserved
P1A--4K
(22)
(I)
Max True Airspeed Prog A
P1A--5A
(22)
Gnd/Open
(I)
Max True Airspeed Prog B
P1A--5B
(22)
Gnd/Open
(I)
Max True Airspeed Prog C
P1A--5C
(22)
Gnd/Open
(I)
Max True AS Common
P1A--5D
(22)
Program Logic Gnd
(I)
ARINC 429 (A) TX Coord
P1A--5E
(22)
TCAS Computer
(I)
ARINC 429 (B) TX Coord
P1A--5F
(22)
TCAS Computer
GND
GND
(O) ARINC 429 (A) XT Coord
P1A--5G (22)
TCAS Computer
(O) ARINC 429 (B) XT Coord
P1A--5H
TCAS Computer
(22)
GND
GND
(I)
Air/Gnd Discrete Input #2
P1A--5J
(22)
Control Panel
(I)
Air/Gnd Discrete Input #1
P1A--5K
(22)
Control Panel
(I)
ARINC 429 (A) Flt ID Input
P1A--6A
(22)
(I)
ARINC 429 (B) Flt ID Input
P1A--6B
(22)
GND
3--22
15 Feb 2003
34-43-20
Flight ID Source
Flight ID Source
GND
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
Notes
(I)
ARINC 429 (A) ADL Input
P1A--6C
(22)
ARINC 615 Airborne
Data Loader
(I)
ARINC 429 (B) ADL Input
P1A--6D
(22)
ARINC 615 Airborne
GND Data Loader
GND
(O) ARINC 429 (A) ADL Out
P1A--6E
(22)
(O) ARINC 429 (B) ADL Out
P1A--6F
(22)
GND
ARINC 615 Airborne
Data Loader
ARINC 615 Airborne
GND Data Loader
(I)
ADL Input Link A
P1A--6G (22)
ARINC 615 Airborne
Data Loader
(I)
ARINC 575 (A) ADC In #1
P1A--6H
(22)
ARINC 575 ADC #1
(I)
ARINC 575 (B) ADC In #1
P1A--6J
(22)
ARINC 575 ADC #1
GND
GND
(I)
Single/Dual Antenna Prog
P1A--6K
(22)
Gnd/Open
(I)
ARINC 429 (A) Control
Data Input Port A
P1A--7A
(22)
Control Panel
(I)
ARINC 429 (B) Control
Data Input Port A
P1A--7B
(22)
Control Panel
Reserved
P1A--7C
GND
GND
(I)
Control Data Port Select In P1A--7D
(22)
Gnd/Open
(I)
ARINC 429 (A) Control
Data Input Port B
P1A--7E
(22)
(I)
ARINC 429 (B) Control
Data Input Port B
P1A--7F
(22)
(I)
STBY/ON Discrete Input
P1A--7G (22)
(I)
ARINC 429 (A) ADC #1 In
P1A--7H
(22)
ARINC 706 ADC #1
(I)
ARINC 429 (B) ADC #1 In
P1A--7J
(22)
ARINC 706 ADC #1
GND
(I)
P1A--7K
Top Antenna RF Input
P1A--71
Control Panel
Control Panel
GND
Control Panel
GND
Reserved
coax
34-43-20
GND
Top Antenna
3--23
15 Feb 2003
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
Connector
Pin
I/O
Description
(I)
Mode S Adrs Bit A1 (MSB)
P1B--1A
(22)
Gnd/Open
(I)
Mode S Address Bit A2
P1B--1B
(22)
Gnd/Open
(I)
Mode S Address Bit A3
P1B--1C
(22)
Gnd/Open
(I)
Mode S Address Bit A4
P1B--1D
(22)
Gnd/Open
(I)
Mode S Address Bit A5
P1B--1E
(22)
Gnd/Open
(I)
Mode S Address Bit A6
P1B--1F
(22)
Gnd/Open
(I)
Mode S Address Bit A7
P1B--1G (22)
Gnd/Open
(I)
Mode S Address Bit A8
P1B--1H
(22)
Gnd/Open
(I)
Mode S Address Bit A9
P1B--1J
(22)
Gnd/Open
(I)
Mode S Address Bit A10
P1B--1K
(22)
Gnd/Open
(I)
Mode S Address Bit A11
P1B--2A
(22)
Gnd/Open
(I)
Mode S Address Bit A12
P1B--2B
(22)
Gnd/Open
(I)
Mode S Address Bit A13
P1B--2C
(22)
Gnd/Open
(I)
Mode S Address Bit A14
P1B--2D
(22)
Gnd/Open
(I)
Mode S Address Bit A15
P1B--2E
(22)
Gnd/Open
(I)
Mode S Address Bit A16
P1B--2F
(22)
Gnd/Open
(I)
Mode S Address Bit A17
P1B--2G (22)
Gnd/Open
(I)
Mode S Address Bit A18
P1B--2H
(22)
Gnd/Open
(I)
Mode S Address Bit A19
P1B--2J
(22)
Gnd/Open
(I)
Mode S Address Bit A20
P1B--2K
(22)
Gnd/Open
(I)
Mode S Address Bit A21
P1B--3A
(22)
Gnd/Open
(I)
Mode S Address Bit A22
P1B--3B
(22)
Gnd/Open
(I)
Mode S Address Bit A23
P1B--3C
(22)
Gnd/Open
(I)
Mode S Adrs Bit A24 (LSB) P1B--3D
(22)
Gnd/Open
(I)
Mode S Adrs Bit Common
P1B--3E
(22)
Address Logic Gnd
Reserved
P1B--3F
Reserved
P1B--3G
Functional Test Discrete In
P1B--3H
(22)
Remote Test Switch
P1B--3J
(22)
Control Panel
(O) XPDR Fail Discrete Out #1 P1B--3K
(22)
(I)
(O) Alt Comparison Fail
Discrete Output
3--24
15 Feb 2003
Connects To
NC
34-43-20
Control Panel
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Notes
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
Notes
(I)
Mode C Pulse A1 #1
P1B--4A
(22)
Encoding Altm #1
(I)
Mode C Pulse A2 #1
P1B--4B
(22)
Encoding Altm #1
(I)
Mode C Pulse A4 #1
P1B--4C
(22)
Encoding Altm #1
(I)
Mode C Pulse B1 #1
P1B--4D
(22)
Encoding Altm #1
(I)
Mode C Pulse B2 #1
P1B--4E
(22)
Encoding Altm #1
(I)
Mode C Pulse B4 #1
P1B--4F
(22)
Encoding Altm #1
(I)
Mode C Pulse C1 #1
P1B--4G (22)
Encoding Altm #1
(I)
Mode C Pulse C2 #1
P1B--4H
(22)
Encoding Altm #1
(I)
Mode C Pulse C4 #1
P1B--4J
(22)
Encoding Altm #1
(I)
Mode C Pulse D2 #1
P1B--4K
(22)
Encoding Altm #1
(I)
ARINC 429 (A) ADC #2 In
P1B--5A
(22)
ARINC 706 ADC #2
(I)
ARINC 429 (B) ADC #2 In
P1B--5B
(22)
ARINC 706 ADC #2
ARINC 575 ADC #2
ARINC 575 ADC #2
GND
(I)
ARINC 575 (A) ADC #2 In
P1B--5C
(22)
(I)
ARINC 575 (B) ADC #2 In
P1B--5D
(22)
GND
GND
GND
(O) ARINC 429 (A) Comm A/B
Output to ADLP
P1B--5E
(22)
Airborne Data Link
Processor
(O) ARINC 429 (B) Comm A/B
Output to ADLP
P1B--5F
(22)
Airborne Data Link
GND Processor
(I)
Alt Comparison On/Off
Discrete Input
P1B--5G (22)
(I)
Mode S Data Link Program P1B--5H
(22)
Gnd/Open
(I)
Antenna Bite Program
P1B--5J
(22)
Gnd/Open
(I)
Mode C Pulse D4 #1
P1B--5K
(22)
Encoding Altm #1
(I)
ARINC 429 (A)
Maintenance Data Input
P1B--6A
(22)
Onboard Maint
Computer System
(I)
ARINC 429 (B)
Maintenance Data Input
P1B--6B
(22)
Onboard Maint
GND Computer System
GND
Control Panel
GND
34-43-20
3--25
15 Feb 2003
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
(O) ARINC 429 (A)
Maintenance Data Output
P1B--6C
(22)
(O) ARINC 429 (B)
Maintenance Data Output
P1B--6D
(22)
(I)
Air Data Source Select
Discrete Input
P1B--6E
(22)
Gnd/Open
(I)
Alt Type Select Prog B
P1B--6F
(22)
Gnd/Open
(I)
Alt Type Select Prog A
P1B--6G (22)
Gnd/Open
(I)
Alt Type Select Common
P1B--6H
(22)
Program Logic Gnd
Reserved
P1B--6J
GND
Onboard Maint
Computer System
Onboard Maint
GND Computer System
(I)
Mode C Pulse Common #1 P1B--6K
(22)
Encoding Altm #1
(I)
Syn Alt In #2: Coarse X
P1B--7A
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: Coarse Y
P1B--7B
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: Coarse Z
P1B--7C
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: 26 V Ref (H) P1B--7D
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: 26 V Ref (C) P1B--7E
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: Fine X
P1B--7F
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: Fine Y
P1B--7G (22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: Fine Z
P1B--7H
(22)
ARINC 565 ADC #2
(I)
Syn Alt In #2: Flag
P1B--7J
(22)
ARINC 565 ADC #2
Reserved
P1B--7K
(I)
Bottom Antenna RF Input
P1B--71
coax
Bottom Antenna
(I)
115 V ac Input Power (H)
P1C--1
(20)
Acft 115 V ac Sup
Spare
P1C--2
(I)
+28 V dc Return (L)
P1C--3
(16)
Acft dc Ground
(I)
XPDR OFF (NO)
P1C--4
Spare
P1C--5
NC
(O) Fan +28 V dc
P1C--6
(22)
Fan +
(I)
115 V ac Return (L)
P1C--7
(20)
Acft ac Ground
(I)
Signal Ground
P1C--8
(16)
Acft ac Ground
(O) Fan Return (L)
P1C--9
3--26
15 Feb 2003
Notes
Fan --
34-43-20
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
(I)
+28 V dc Input Power
P1C--10
(16)
+28V Acft Power
(I)
Chassis Ground
P1C--11
(16)
Airframe Ground
I/O Suppression Pulse
P1C--12 coax
L--Band Suppression
Bus
I/O Suppression Pulse
P1C--13 coax
L--Band Suppression
Bus
Notes
The interconnect data that follows is for the ARINC 615 Portable Data Loader (PDL) connector J1 located
on the front panel of the transponder. The transponder’s operational software can be updated (upload to
transponder) through this connector. In addition, the contents of the fault log can be extracted for analysis
and troubleshooting (download from transponder).
The 53 pin front panel PDL connector contains both an ARINC 429 high speed bus interface for connection
to an ARINC 615 PDL, and an RS--232 bus interface for connection to a personal computer (PC) through a
standard serial port. Only the pins used by the transponder are shown.
The PDL standard interface cable should be 10 feet in length (3 meters) and be terminated with a connector
type MS27473T--18A--53S at the data loader end and connector type MS27473T--18A--53P at the
transponder end.
(I)
ARINC 429 (A) PDL Input
J1--1
(22)
ARINC 615 PDL
(I)
ARINC 429 (B) PDL Input
J1--2
(22)
ARINC 615 PDL
(I)
Bus Shield
J1--5
(22)
Chassis Ground
(O) ARINC 429 (A) PDL Out
J1--8
(22)
ARINC 615 PDL
(O) ARINC 429 (B) PDL Out
J1--9
(22)
ARINC 615 PDL
(O) Bus Shield
J1--16
(22)
Chassis Ground
PDL Link A
J1--18
(22)
ARINC 615 PDL
PDL Link B
J1--19
(22)
ARINC 615 PDL
(O) 115 V ac Power Out (H)
J1--20
(22)
ARINC 615 PDL
(O) Chassis Ground
J1--21
(22)
ARINC 615 PDL
(O) 115 V ac Power Out (C)
J1--22
(22)
ARINC 615 PDL
(O) +28 V dc Power Out
J1--37
(22)
ARINC 615 PDL
(O) +28 V dc Return
J1--38
(22)
ARINC 615 PDL
(I)
J1--40
(22)
RS--232 Interface
J1--41
(22)
RS--232 Interface
Logic Common (Gnd)
J1--48
(22)
RS--232 Interface
Logic Common (Gnd)
J1--49
(22)
RS--232 Interface
(I)
PDL Function Discrete #1
J1--50
(22)
ARINC 615 PDL
(I)
PDL Function Discrete #2
J1--51
(22)
ARINC 615 PDL
RS--232 PDL Input
(O) RS--232 PDL Output
34-43-20
3--27
15 Feb 2003
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
(I)
PDL Function Discrete #3
J1--52
(22)
ARINC 615 PDL
(I)
PDL Function Discrete #4
J1--53
(22)
ARINC 615 PDL
NOTES:
1.
2.
3.
4.
5.
6.
7.
3--28
Notes
Two wire shielded cable. Tie shields to aircraft dc ground.
Tie chassis ground to aircraft frame.
Two wire shielded cable. Tie shield to pin 5.
Two wire shielded cable. Tie shield to pin 16.
The 115 V ac (H) and 115 V ac (C) should be shielded or twisted and shielded with an insulating
jacket over the shield. The shield should be connected to chassis ground (pin 21).
There is a +28 V dc output available from the transponder, however most ARINC 615 Data
Loaders do not have the capability to operate from 28 Volt power.
If the RS--232 interface is going to be used, these pins should be connected to a standard serial
port (usually a 9--pin D connector).
15 Feb 2003
34-43-20
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
(2) RCZ--852 Diversity Mode S Transponder
Table 3--4 contains the interconnect data for the RCZ--852 Diversity Mode S
Transponder, Part No. 7510700--850.
Prior to final installation of the transponder mounting tray, the strap assembly,
Figure 3--12, located on the back of each mounting tray must be programmed to
incorporate the aircraft Mode S address and the desired options. Information for
programming the strap assembly is contained in Table 3--5 and Table 3--6.
Programming of the strap assembly consists of removing or installing a string of
jumper wires that provide a 48--bit serial data word for encoding the system
configuration. In Table 3--6, the output is grounded if the corresponding W* (jumper
wire) is installed for a particular bit, and open if the jumper wire is cut out.
The strap assembly is shipped with all 48--bit jumpers installed. If a jumper is
inadvertently cut out or a parameter change requires a jumper to be reinstalled, a
suitable piece of AWG 24 bus wire should be used.
Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data
I/O
Description
Connector
Pin
Connects To
(O) XPDR +28 V FAN RTN
J1--1
NC
(O) XPDR +28 V FAN PWR
J1--2
NC
I/O MUT SUP (P)
J1--3
(24)
GND
L--Band Suppression
GND Bus
Spare
J1--4
Spare
J1--5
Spare
J1--6
(I)
XPDR +28V RTN
J1--7
(22)
Acft dc Ground
(I)
XPDR +28V PWR
J1--8
(22)
Acft 28 V Supply
(I)
XPDR +28V PWR
J1--9
(22)
Acft 28 V Supply
Spare
J1--10
PROGRAM ENA (PO)
J1--11
NC
J1--12
NC
(I)
(O) XPDR TX RS232
Reserved
J1--13
Reserved
J1--14
Reserved
J1--15
Reserved
J1--16
(I)
dc GROUND
J1--17
(22)
Acft dc Ground
(I)
dc GROUND
J1--18
(22)
Acft dc Ground
34-43-20
Notes
3--29
15 Feb 2003
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
Connects To
(I)
dc GROUND
J1--19
(22)
Acft dc Ground
(I)
XPDR +28V RTN
J1--20
(22)
Acft dc Ground
(I)
dc GROUND
J1--21
(22)
Acft dc Ground
Spare
J1--22
(O) XPDR VALID (PO)
J1--23
NC
(I)
XPDR RX RS232
J1--24
NC
(O) PROGRAM +15V
J1--25
NC
(O) XPDR to TCAS 429 (A)
J1--26
(22)
GND
(O) XPDR to TCAS 429 (B)
J1--27
(22)
GND
TCAS Computer
TCAS Computer
GND
Notes
GND
(O) XPDR to DLP A/B 429 (A)
J1--28
(22)
Airborne Data Link
Processor
(O) XPDR to DLP A/B 429 (B)
J1--29
(22)
Airborne Data Link
GND Processor
GND
(O) XPDR to DLP C/D 429 (A)
J1--30
(22)
Airborne Data Link
Processor
(O) XPDR to DLP C/D 429 (B)
J1--31
(22)
Airborne Data Link
GND Processor
GND
(I)
ADC1 to XPDR 429/575A
J1--32
(22)
(I)
ADC1 to XPDR 429/575B
J1--33
(22)
GND
ARINC 429 or 575
ADC #1
ARINC 429 or 575
GND ADC #1
(I)
CTL1 to XPDR 429 (A)
J1--34
(22)
Control Panel
(I)
CTL1 to XPDR 429 (B)
J1--35
(22)
Control Panel
GND
Reserved
J1--36
Reserved
J1--37
Reserved
J1--38
Reserved
J1--39
3--30
15 Feb 2003
34-43-20
GND
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)
I/O
Description
Connector
Pin
(I)
TCAS to XPDR 429 (A)
J1--40
(22)
(I)
TCAS to XPDR 429 (B)
J1--41
(22)
Connects To
GND
Notes
TCAS Computer
TCAS Computer
GND
(I)
DLP A/B to XPDR 429 (A)
J1--42
(22)
Airborne Data Link
Processor
(I)
DLP A/B to XPDR 429 (B)
J1--43
(22)
Airborne Data Link
GND Processor
GND
(I)
DLP C/D to XPDR 429 (A)
J1--44
(22)
Airborne Data Link
Processor
(I)
DLP C/D to XPDR 429 (B)
J1--45
(22)
Airborne Data Link
GND Processor
GND
(I)
ADC2 to XPDR 429/575A
J1--46
(22)
(I)
ADC2 to XPDR 429/575B
J1--47
(22)
GND
ARINC 429/575
Digital ADC
ARINC 429/575
GND Digital ADC
(I)
CTL2 to XPDR 429 (A)
J1--48
(22)
Control Panel
(I)
CTL2 to XPDR 429 (B)
J1--49
(22)
Control Panel
GND
GND
(O) XPDR to CTL 429 (A)
J1--50
(22)
Control Panel
2, 3
(O) XPDR to CTL 429 (B)
J1--51
(22)
Control Panel
2, 3
GND
GND
Reserved
J1--52
(I)
ENC ALT1 C1 (N)
J1--53
(24)
Encoding Altm #1
(I)
ENC ALT1 C2 (N)
J1--54
(24)
Encoding Altm #1
(I)
ENC ALT1 C4 (N)
J1--55
(24)
Encoding Altm #1
(I)
ENC ALT1 D2 (N)
J1--56
(24)
Encoding Altm #1
(I)
ENC ALT1 D4 (N)
J1--57
(24)
Encoding Altm #1
(I)
ENC ALT1 A1 (N)
J1--58
(24)
Encoding Altm #1
(I)
ALT COMP ENA (NO)
J1--59
(24)
Gnd/Open
(I)
ALT SRC SEL2 (NO)
J1--60
(24)
Gnd/Open
34-43-20
3--31
15 Feb 2003
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)
I/O
(I)
Description
Connector
Pin
Connects To
CTL SRC SEL1 (NO)
J1--61
(24)
Reserved
J1--62
Reserved
J1--63
(I)
FMS to XPDR 429 (A)
J1--64
(22)
(I)
FMS to XPDR 429 (B)
J1--65
(22)
GND
Notes
Gnd/Open
Flt Management Sys
Flt Management Sys
GND
Reserved
J1--66
(I)
ENC ALT1 A2 (N)
J1--67
(24)
Encoding Altm #1
(I)
ENC ALT1 A4 (N)
J1--68
(24)
Encoding Altm #1
(I)
ENC ALT1 B1 (N)
J1--69
(24)
Encoding Altm #1
(I)
ENC ALT1 B2 (N)
J1--70
(24)
Encoding Altm #1
(I)
ENC ALT1 B4 (N)
J1--71
(24)
Encoding Altm #1
(I)
XPDR STANDBY (NO)
J1--72
(24)
Control Panel
(I)
SQUAT SWITCH 1 (NO)
J1--73
(24)
Control Panel or Acft
Squat Switch
(I)
XPDR OFF (NO)
J1--74
(I)
SQUAT SWITCH 2 (NO)
J1--75
Control Panel or Acft
Squat Switch
XPDR TX RCB (P)
J1--76
NC
XPDR TX RCB (N)
J1--77
NC
XPDR RX RCB (P)
J1--78
NC
XPDR RX RCB (N)
J1--79
NC
(I)
ENC ALT2 C1 (N)
J1--80
(24)
Encoding Altm #2
(I)
ENC ALT2 C2 (N)
J1--81
(24)
Encoding Altm #2
(I)
ENC ALT2 C4 (N)
J1--82
(24)
Encoding Altm #2
(I)
ENC ALT2 D2 (N)
J1--83
(24)
Encoding Altm #2
(I)
ENC ALT2 D4 (N)
J1--84
(24)
Encoding Altm #2
(I)
ENC ALT2 A1 (N)
J1--85
(24)
Encoding Altm #2
Reserved
J1--86
Reserved
J1--87
Reserved
J1--88
3--32
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NC
(24)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)
I/O
Description
Reserved
Connector
Pin
Connects To
Notes
J1--89
(O) XPDR STRAP +5V
J1--90
(26)
Strap Board (Red)
(O) XPDR STRAP CLK (N)
J1--91
(26)
Strap Board (Blue)
(O) XPDR STRAP LOAD (N)
J1--92
(26)
Strap Board (Orn)
(I)
XPDR STRAP DATA (P)
J1--93
(26)
Strap Board (Wht)
(I)
ENC ALT2 A2 (N)
J1--94
(24)
Encoding Altm #2
(I)
ENC ALT2 A4 (N)
J1--95
(24)
Encoding Altm #2
(I)
ENC ALT2 B1 (N)
J1--96
(24)
Encoding Altm #2
(I)
ENC ALT2 B2 (N)
J1--97
(24)
Encoding Altm #2
(I)
ENC ALT2 B4 (N)
J1--98
(24)
Encoding Altm #2
(O) XPDR ACTIVE (NO)
J1--99
(24)
Antenna Switching
Relay
(O) XPDR VALID (NO)
J1--100 (24)
Reserved
Control Panel
J1--101
(O) ALT VALID (NO)
J1--102 (24)
Control Panel
(O) XPDR STRAP GND
J1--103 (26)
Strap Board (Blk)
(O) XPDR STRAP PGM (N)
J1--104 (26)
Strap Board (Grn)
(O) XPDR STRAP PGM (P)
J1--105 (26)
Strap Board (Yel)
--
POLARIZATION PIN
J1--106
NC
(I)
Bottom Antenna RF Input
J2
coax
Bottom Antenna
(I)
Top Antenna RF Input
J3
coax
Top Antenna
NOTES:
1. Use AWG--24 single conductor, shielded wire. Attach shield to ground loop E1 or E2 on back of
mounding tray.
2. Two wire shielded cable. Tie shields to ground loop E1 or E2 located on back of mounting tray.
3. This ARINC 429 output is required on some Collins Control Panels that require a feedback loop to
make sure the transponder is working properly.
4. Refer to interface descriptions in Table 4--5.
5. This output is connected only if the control panel has an ALT FAIL input function.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--5. Strap Assembly Strap Assignments
Strap
Number
Strap
Number
Name
NAME
W1
System Position B0
W25
Mode S Address B16
W2
System Position B1
W26
Mode S Address B17
W3
Parity
W27
Mode S Address B18
W4
Parity
W28
Mode S Address B19
W5
Squat Switch Polarity
W29
Mode S Address B20
W6
Maximum Airspeed B0
W30
Mode S Address B21
W7
Maximum Airspeed B1
W31
Mode S Address B22
W8
Maximum Airspeed B2
W32
Mode S Address B23
W9
Mode S Address B0
W33
Altitude Source B0
W10
Mode S Address B1
W34
Altitude Source B1
W11
Mode S Address B2
W35
DLP Installed
W12
Mode S Address B3
W36
TCAS II Installed
W13
Mode S Address B4
W37
Antenna Cable Installation B0
W14
Mode S Address B5
W38
Antenna Cable Installation B1
W15
Mode S Address B6
W39
TCAS TA Display Enable
W16
Mode S Address B7
W40
TCAS I Installed
W17
Mode S Address B8
W41
Altitude Resolution
W18
Mode S Address B9
W42
Reserved
W19
Mode S Address B10
W43
Reserved
W20
Mode S Address B11
W44
Reserved
W21
Mode S Address B12
W45
Reserved
W22
Mode S Address B13
W46
Reserved
W23
Mode S Address B14
W47
Reserved
W24
Mode S Address B15
W48
Reserved
NOTE:
The strap logic levels are as follows:
GND = Jumper wire installed (Uncut)
OPEN = Jumper wire not installed (Cut)
3--34
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 3--12. Strap Assembly
Table 3--6. Strap Assembly Programming Instructions
Strap
Number
W1
W2
Functional Description
SYSTEM (SIDE) POSITION: (B0, B1)
The System (Side) Position straps define which system position the transponder is
located at. Normal practice is to designate the captain’s or pilot’s system as Side 1, the
copilot’s system as Side 2, and the engineer’s, center, or backup system as Side 3. The
straps are defined as follows:
Strap Number
W1
W2
Definition
Gnd
Open
Gnd
Open
W3
W4
Gnd
Gnd
Open
Open
Side 1
Side 2
Side 3
Reserved
PARITY
The Parity straps are used to make sure the strap data is valid. Straps W3 and W4 are
parity bits and must be programmed as follows:
After all other straps have been programmed, count the number of Gnd (Uncut) straps in
positions W1, W2 and W5 thru W48. If the number of uncut straps is even, cut strap W3.
If the number of uncut straps is odd, cut strap W4.
NOTES:
1. To have correct parity, either jumper W3 or W4 has to be cut, but not both.
2. If parity is invalid, the transponder fails the Power--On Self--Test (POST) and
discontinues operation.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--6. Strap Assembly Programming Instructions (cont)
Strap
Number
Functional Description
W5
SQUAT SWITCH POLARITY
The Squat Switch Polarity strap is used to indicate the logic or signal sense of the aircraft
squat switch on ground condition. If the squat switch is closed when the aircraft is on the
ground, jumper W5 must be installed (Uncut). If the squat switch is closed when the
aircraft is airborne, jumper W5 must be Open (Cut).
W6
W7
W8
AIRCRAFT MAXIMUM TRUE AIRSPEED RANGE: (B0, B1, B2)
The Aircraft Maximum True Airspeed Range straps are used to define the aircraft’s
maximum airspeed capability. The straps are defined as follows:
Strap Number
W6
W7
W8
Definition
Gnd
Open
Gnd
Open
Gnd
Open
Gnd
Open
Gnd
Gnd
Open
Open
Gnd
Gnd
Open
Open
Gnd
Gnd
Gnd
Gnd
Open
Open
Open
Open
No Data Available
75 Knots or Less
76 to 150 Knots
151 to 300 Knots
301 to 600 Knots
601 to 1200 Knots
Over 1200 Knots
Not Assigned
W9 thru W32
(LSB -- MSB)
MODE S ADDRESS: (B0 THRU B23)
The Mode S Address is a unique 24--bit code assigned to each aircraft. Straps W9 thru
W32 are used to program this 24--bit binary number. The straps must be set according to
this binary number representation. Each binary 1 represents a Cut strap and each binary
0 represents an Uncut strap. Strap W9 represents the least significant digit of the binary
number and strap W32 represents the most significant digit of the binary number. The
initial board condition with all jumpers is a 0 address.
NOTE: An address of all 0’s or all 1’s is an illegal address, and can cause the aircraft to
be invisible to TCAS II equipped aircraft in flight. Never use an illegal address
for an installed system.
W33
W34
ALTITUDE SOURCE: (B0, B1)
The Altitude Source straps select the type of altitude information used by the transponder.
Altitude information can be generated by an encoding altimeter in the form of Gray aka
Gillham code, or by a digital Air Data Computer. The straps are defined as follows:
Strap Number
W33
W34
Definition
Gnd
Gnd
Gillham Gray Code Altitude Source
Open
Gnd
ARINC 429 Altitude Source
Gnd
Open
ARINC 575 Altitude Source
Open
Open
RSB Altitude Source
NOTE: The RSB altitude source is a valid selection only when the transponder receives
tuning information from an RCB bus.
3--36
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--6. Strap Assembly Programming Instructions (cont)
Strap
Number
Functional Description
W35
DLP INSTALLED
The DLP Installed strap specifies whether the transponder is connected to an Airborne
Data Link Processor system. The strap is selected as follows:
Gnd = DLP is not installed
Open = DLP is installed
W36
TCAS II INSTALLED
The TCAS II Installed strap specifies whether the transponder is connected to a TCAS II
system. The strap is selected as follows:
Gnd = TCAS II is not installed
Open = TCAS II is installed
NOTE: If both TCAS II and TCAS I (strap W40) are set (Grounded), the transponder
will default to TCAS II operation. Both straps should not be cut.
W37
W38
ANTENNA CABLE INSTALLATION: (B0, B1)
The Antenna Cable Install straps are used to set the system for either a single (bottom)
antenna installation, or a diversity installation. In the diversity installation, the straps
adjust for the difference in RF propagation times through the upper and lower antenna
cables which occur because of their dissimilar lengths. The antenna cable delay is
selected as follows:
Strap Number
W37
W38
Definition
Gnd
Gnd
Single (bottom) Antenna Installation
Open
Gnd
Top > Bottom Cable Length, Differential Delay >40 nanoseconds
Gnd
Open
Bottom > Top Cable Length, Differential Delay >40 nanoseconds
Open
Open
Differential Delay is <40 nanoseconds
NOTE: The differential delay is equal to two times the length (in feet) of the difference
between the top and bottom antenna cable lengths, times the characteristic
delay (nanoseconds / feet) of the cable type in use.
W39
TCAS TA DISPLAY ENABLE
The TCAS Display Enable strap allows the TCAS display to be either tunable or fixed.
The strap is not processed by the transponder, but is used by a RMU when an RSB
tuning source is selected. The strap is not used by ARINC tuning sources. The strap
definition is as follows:
Gnd = TA Display is tunable (ON / OFF / AUTO POP--UP) modes selectable
Open = TA Display is not selectable (AUTO POP--UP mode only)
W40
TCAS I INSTALLED
The TCAS I Installed strap specifies whether the transponder is connected to a TCAS I
system. The strap is selected as follows:
Gnd = TCAS I is not installed
Open = TCAS I is installed
NOTE: If both TCAS I and TCAS II (strap W36) are set (Grounded), the transponder
will default to TCAS II operation. Both straps should not be cut.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 3--6. Strap Assembly Programming Instructions (cont)
Strap
Number
W41
ALTITUDE RESOLUTION
The Altitude Resolution strap allows the transponder output to the TCAS (label 203) to be
either 100 foot resolution or 1 foot resolution. The strap definition is as follows:
Gnd = 1 Foot Resolution
Open = 100 Foot Resolution
NOTE: Most ARINC altitude inputs require 1 foot resolution.
W42 thru W48
W49
W50
3--38
Functional Description
RESERVED FUNCTION
These straps are not used. The jumpers should be installed (Uncut).
Jumpers W49 and W50 are not part of the 48--bit serial data pulse train and are not used
on RCZ--852 Transponder installations. The jumpers should be installed (Uncut).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
LOADING/GRADIENT SPECIFICATIONS
1. General
This section contains the loading and gradient specifications for the input and output signals
of each component of the T2CAS system.
2. TCAS Interface Description
Component
Table No.
TT--950/951/952 T2CAS Computer Unit Interface Description
Table 4--1
Gables Control Panel Interface Description
Table 4--2
41--Pin VSI/TRA Interface Description (Thales)
Table 4--3
XS--950 Data Link Transponder Interface Description
Table 4--4
RCZ--852 Diversity Mode S Transponder Interface Description
Table 4--5
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description
Connector Pin
Designation
Functional Description
T2CAS Computer Unit Right Middle Plug (RMP)
RMP--1A,
to
RMP--1D
Reserved Discrete Outputs (Standard Ground/Open)
RMP--1E
TA Display Enable Discrete Output (NO)
This output is a ground/open type discrete (Note 3) used by the weather radar display to
place the radar in standby mode. A ground on this pin enables the weather radar display.
RMP--1F
Corrective Aural Advisory Discrete Output (NO)
This aural advisory discrete output is a ground/open type discrete (Note 3) used to control
external equipment that generate tones to accompany TCAS advisories. The output is
active whenever a corrective advisory (RA that requires a corrective maneuver) is issued.
The output remains active for the duration of the synthesized voice unless it is cancelled
by the cancel discrete at RMP--3D. Only one aural advisory is active at a time. The
corrective discrete and preventative discrete at RMP--1K are mutually exclusive. The
active state is ground and the inactive state is open.
RMP--1G
Reserved for GPS use.
RMP--1H
Reserved for GPS use.
RMP--1J
Climb Inhibit No. 1 Discrete Input (NO)
This input is a ground/open type discrete used to provide information to the T2CAS CU
whether to assume the aircraft cannot achieve a climb rate of 1500 feet per minute
(FPM). The climb inhibit discrete inputs are designed in pairs (No. 1 and No. 2 at
RMP--13G, or No. 3 at RBP--5J and No. 4 at RBP--5K) but can be wired as a single input
or in conjunction with other aircraft operations to achieve airframe customization of the
climb inhibit feature. The 1500 FPM climb inhibit function is assumed whenever No. 1
and No. 2 are ground or No. 3 and No. 4 are ground.
See Note 1 for Ground/Open type discrete input definition.
RMP--1K
Preventive Aural Advisory Discrete Output (NO)
Same as RMP--1F, except this discrete is active whenever a preventative advisory (RA
that directs the flight crew to avoid certain maneuvers or maintain flight path) is issued.
RMP--2A
Traffic Aural Advisory Discrete Output (NO)
Same as RMP--1F, except this discrete is active during a traffic advisory when information
is being given to the flight crew regarding other aircraft in the immediate vicinity. No
suggested maneuver is issued. This output is inhibited if either the corrective or
preventative output is active.
RMP--2B
Reserved for TAWS/RWS use.
RMP--2C
Reserved for TAWS/RWS use.
RMP--2D
Advisory/Announce Common
This is the return line for the aural and visual advisory discrete outputs.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
RMP--2E
Functional Description
Spare Pin
RMP--2F, 2G
8 Ohm Audio Output: (RMP--2F [HI], RMP--2G [LO])
This is a synthesized voice output supplied by the T2CAS computer unit. Its level is
programmable up to 8 Watts into an 8 Ohm speaker. All aural traffic and resolution
advisories are announced over this output. See RBP--7A for audio level programming.
RMP--2H, 2J
Radio Altimeter No. 1 ARINC 552/Analog Input: (RMP--2H [HI], RMP--2J [LO])
Normal aircraft configurations include either two digital or two analog radio altimeter
sources. The T2CAS computer unit attempts to establish which type is present in order to
obtain data from one of the two available sources. TCAS first checks the radio altimeter
No. 1 valid flag at RMP--2K. If No. 1 is not valid then No. 2 valid is checked at RBP--3C.
If neither are valid then TCAS checks digital source No. 1 for valid data on the ARINC
429 bus at RMP--13H and RMP--13J. If none of the above are valid then the TCAS
checks the digital source No. 2 for valid data on the ARINC 429 bus at RBP--3D and
RBP--3E. This process is repeated until a valid flag or data is detected.
Until a valid source is found, the TCAS function inhibits all surveillance, CAS, and TA/RA
display functions, records failures in maintenance memory, and sets the TCAS system
status discrete output at RMP--13K to invalid. The TCAS function uses radio altitude to
inhibit advisories and aural annunciation when in close proximity to the ground. This
analog input No. 1, as well as analog input No. 2, can accept data as a dc voltage from
several types of radio altimeters. The type of radio altimeter is selected using the
program pins RMP--12B and RMP--12H thru RMP--12K.
RMP--2K
Radio Altimeter No. 1 Valid Input (PO)
See RMP--2H. A valid condition is greater than +18.5 Vdc. An invalid is open circuit.
RMP--3A
Corrective Visual Advisory Discrete Output (NO)
The visual advisory discrete outputs are ground/open type discretes (Note 3) used to
operate the annunciator lights on the displays. This output is activated whenever a
corrective aural advisory is issued. The output remains active for the duration of the
advisory unless cancelled by the cancel discrete at RMP--3D. Only one visual advisory is
active at a time. The active state is ground and the inactive state is open.
RMP--3B
Preventive Visual Advisory Discrete Output (NO)
Same as RMP--3A, except this discrete is activated whenever a preventative aural
advisory is issued.
RMP--3C
Traffic Visual Advisory Discrete Output (NO)
Same as RMP--3A, except this discrete is active during a traffic advisory.
RMP--3D
Cancel Discrete Input (NO)
This input discrete provides a means of canceling aural and visual alerts. It should be
connected to a cancel button (momentary ground type), if used. Groundprox/Windshear
has priority over the cancel button. Open is the inactive state and a momentary ground
(less than 50 Ohms) produces the active state, canceling any active aural or visual alert.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
RMP--3E
RMP--3F, 3G
Functional Description
Spare Pin
600 Ohm Audio Output: [RMP--3F (HI), RMP--3G (LO)]
This is a synthesized voice output supplied by the T2CAS computer unit. Its level is
programmable up to 80 milliwatts into a 600 Ohm audio distribution system. All aural
traffic and resolution advisories are annunciated over this output. See RBP--7A for audio
level programming.
RMP--3H
Spare Pin
RMP--3J
Reserved for TAWS/RWS use.
RMP--3K
Reserved for TAWS/RWS use.
RMP--4A
Reserved for TAWS/RWS use.
RMP--4B
Reserved for TAWS/RWS use.
RMP--4C
Reserved for TAWS/RWS use.
RMP--4D
TCAS Installed Discrete Output (Ground)
Indicates to external systems that a TCAS Computer is installed.
RMP--4E
Reserved for TAWS/RWS use.
RMP--4F
Reserved for TAWS/RWS use.
RMP--4G
Reserved for TAWS/RWS use.
RMP--4H
Reserved for TAWS/RWS use.
RMP--4J
Reserved for TAWS/RWS use.
RMP--4K
Reserved for TAWS/RWS use.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RMP--5A
Reserved for TAWS/RWS use.
RMP--5B
Reserved for TAWS/RWS use.
RMP--5C
Reserved for TAWS/RWS use.
RMP--5D
Reserved for TAWS/RWS use.
RMP--5E
ADS--B Program Input (Intruder File Enable).
RMP--5F
ADS--B Program Input (GP Bus Enable).
RMP--5G
ADS--B Program Input (Reserved)
RMP--5H
Reserved for TAWS/RWS use.
RMP--5J
Reserved for TAWS/RWS use.
RMP--5K
Air Ground Discrete Input (NO): (Weight--On--Wheels)
This ground/open type discrete input (Note 1) to the T2CAS computer unit indicates the
status of the Air/Ground or Weight--On--Wheels (WOW) switch. TCAS filters this input to
make sure it remains in a steady state a minimum of 4 seconds before an Air/Ground
transition is recorded. An open indicates the aircraft is airborne and a ground indicates
the aircraft is on the ground.
Inputs should be diode isolated from each other.
RMP--6A, 6B
ARINC 429 Performance Limit Input: [RMP--6A (A), RMP--6B (B)]
This Low Speed ARINC 429 (12.5 Kbits/s) input is provided for future applications to
receive climb rate performance limit information from an external device such as a Flight
Management Computer.
RMP--6C
Reserved for TAWS/RWS use.
RMP--6D
Performance Limit Discrete Input (NO)
This input provides the T2CAS computer unit with an input from the Flight Management
Computer (or equivalent) which indicates when the aircraft cannot achieve a 1500 FPM
climb rate. When this input is ground, the climb rate is not limited and no action is
needed by the T2CAS computer unit. When this input is open, the climb rate is limited
when the aircraft is above the value set by the altitude limit program pins (RMP--6E thru
RMP--6J).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RMP--6E
2000 FT Altitude Limit Program Pin (NO)
This pin, along with pins RMP--6F thru RMP--6J, select the “can’t climb” altitude in
2,000--foot increments up to 62,000 feet. This is the altitude the aircraft is not able to
achieve a 0.25 G vertical acceleration to a 1500 FPM climb rate for an altitude gain of 750
feet above a certain altitude under all circumstances. The “can’t climb” altitude is
selected by connecting jumper wires from altitude limit program pins to the program
common pin (RMP--6K).
RMP--6F
4000 FT Altitude Limit Program Pin (NO)
See RMP--6E.
RMP--6G
8000 FT Altitude Limit Program Pin (NO)
See RMP--6E.
RMP--6H
16000 FT Altitude Limit Program Pin (NO)
See RMP--6E.
RMP--6J
32000 FT Altitude Limit Program Pin (NO)
See RMP--6E.
RMP--6K
Program Common
See RMP--6E.
RMP--7A, 7B
ARINC 429 Magnetic Heading/Attitude Input: [RMP--7A (A), RMP--7B (B)]
Reserved for future use
RMP--7C, 7D
ARINC 429 TA/RA Display No. 1 Output: [RMP--7C (A), RMP--7D (B)]
This is one of two ARINC 429 high speed (100 kbits/s) bus outputs that supplies data to
the TA/RA display such as a VSI/TRA or EFIS. The other output (TA/RA Display No. 2) is
at RMP--7G and --7H. The TA/RA Display No. 1 outputs are also connected to the front
(PDL) connector, which is used to supply display information to maintenance displays.
See J1--33 and J1--34.
RMP--7E
TA/RA Display No. 1 Status Discrete Input (NO)
Two display status ground/open discrete inputs (Note 1) are provided by the T2CAS
computer unit at RMP--7E (TA/RA Display No. 1) and RMP--7J (TA/RA Display No. 2). A
ground on either of these inputs is interpreted by TCAS to mean the display associated
with that input is operating normally and is capable of displaying the TA/RA information,
and that its data bus is active. An open indicates the inability of the display to present
advisories or indicates its data bus is inactive.
RMP--7F
Spare Pin
RMP--7G, 7H
ARINC 429 TA/RA Display No. 2 Output: [RMP--7G (A), RMP--7H (B)]
See RMP--7C and --7D.
RMP--7J
TA/RA Display No. 2 Status Discrete Input (NO)
See RMP--7E.
RMP--7K
Spare Pin
4--6
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RMP--8A, 8B
ARINC 429 Data Loader Input: [RMP--8A (A), RMP--8B (B)]
These pins are used when the T2CAS computer unit is communicating with an ARINC
603 or 615 airborne data loader (ADL) through the rear ARINC 600 connector. The data
loader programs the program memory in the T2CAS computer unit per the data loader
function specified. The ADL and portable data loader (PDL) Low Speed ARINC 429
inputs (12.5 kbits/s) have separate receiver busses to allow for simultaneous connection
of the ADL and PDL.
These pins are also connected to the front (PDL) connector on the front of the unit. See
J1--1 and J1--2.
RMP--8C,8D
ARINC 429 ADS--B No. 1 Input: [RMP--8C (A), RMP--8D (B)]
TA/RA Display Control A429 Input #1
RMP--8E, 8F
ARINC 429 Bus Input: [RMP--8E (A), RMP--8F (B)]
General Purpose A429 Input #1
RMP--8G, 8H
ARINC 429 Bus Input: [RMP--8G (A), RMP--8H (B)]
TA/RA Display Control A429 Input #2
RMP--8J, 8K
ARINC 429 ADS--B No. 2 Input: [RMP--8J (A), RMP--8K (B)]
TAWS to TCAS A429 Output (A)
RMP--9A, 9B
ARINC 429 Data Loader Output: [RMP--9A (A), RMP--9B (B)]
These pins are used when the T2CAS computer unit is communicating with an ARINC
603 or 615 airborne data loader (ADL) through the rear ARINC 600 connector. This
connection is used to transmit data to the ADL during data loading operations.
These pins are also connected to the front (PDL) connector on the front of the unit. See
J1--8 and J1--9.
RMP--9C, 9D
Reserved for GPS use.
RMP--9E, 9F
Reserved for TAWS/GPS use.
RMP--9G, 9H
ARINC 429 Bus Output: [RMP--9G (A), RMP--9H (B)]
CD General Purpose A429 Output #1
RMP--9J, 9K
ARINC 429 ADS--B No. 2 Output: [RMP--9J (A), RMP--9K (B)]
CD General Purpose A429 Output #2
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RMP--10A
RMP--10B
RMP--10C
ADS--B Program Inputs
Reserved for future use.
RMP--10D
Single Mode S Installation Program Inputs
This pin allows the T2CAS CU to be configured for single or dual Mode S Transponder
operation. When a single Mode S installation is enabled, the T2CAS CU defaults to the
No. 1 Position Transponder without indicating Failure of the No. 2 Position Transponder.
A Ground indicates Single Mode S Transponder Installation and an Open indicates Dual
Mode S Transponder Installation.
RMP--10E
Reserved for TAWS/RWS use.
RMP--10F
Reserved for TAWS/RWS use.
RMP--10G
Thru
RMP--10K
Reserved Program Inputs
Reserved for future use.
RMP--11A
Altitude Alerter Program Input
RMP--11B
Traffic Display of Flight ID Program Input
This program pin allows traffic display of flight identification information from a
transponder to be output on the TA/TA displays. A ground on this pin enables this
function and an open disables the function.
RMP--11C
Male Voice Program Input
This program input is intended to allow audio annunciation to be selectable for either male
or female genders. A ground on this pin selects the male voice and an open selects the
female voice.
RMP--11D
Flight Data Recorder ARINC 429 and Extended Maintenance Log Program Input
This program pin is used to specify whether the ARINC 429 Flight Data Recorder (FDR)
is to be used. An open on this pin means that the FDR is not utilized. A ground indicates
that flight data is output as high--speed ARINC 429 (100 kbits/s) data on RA Display No. 1
and No. 2 buses. While the FDR is enabled, normal low--speed RA display bus operation
is not available. A ground also enables RA/TA events recording in memory.
RMP--11E
Thru
RMP--11K
RMP--12A
4--8
15 Feb 2003
Reserved for TAWS/RWS use.
Reserved Program Input
Reserved for future use.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
RMP--12B
Radio Altimeter Type Select Program Input No. 4 (NO)
The T2CAS computer unit uses radio altitude to inhibit advisories and aural annunciation
when in close proximity to the ground. This analog input No. 1, as well as analog input
No. 2 can accept data as a dc voltage from several types of radio altimeters. Program
pin RMP--12B is used, along with program pins RMP--12H, --12J, and --12K, to identify the
type of analog radio altimeter installed.
For T2CAS CU ARINC 552, Collins BCA, AHV--6, NR--AS--10A, LPIA, APN--232 CARA
and metric type radio altimeters can be selected. The program pin inputs use
ground/open logic levels. All unassigned program pin combinations are invalid and
should not be selected. Pin RMP--6K can be used to supply a ground.
Program Pin
RMP--12K RMP--12J RMP--12H RMP--12B
Altimeter Type
Open
Open
Open
Open
Open
Open
Open
Open
Ground
Ground
Ground
Ground
Ground
Ground
Ground
Ground
Open
Open
Open
Open
Ground
Ground
Ground
Ground
Open
Open
Open
Open
Ground
Ground
Ground
Ground
Open
Open
Ground
Ground
Open
Open
Ground
Ground
Open
Open
Ground
Ground
Open
Open
Ground
Ground
Open
Ground
Open
Ground
Open
Ground
Open
Ground
Open
Ground
Open
Ground
Open
Ground
Open
Ground
ARINC 552/552A
Collins BCA
Metric Altimeter No. 1
Unassigned
Metric Altimeter No. 2
Unassigned
Metric Altimeter No. 3
Unassigned
Metric Altimeter No. 4
Unassigned
Military AHV6 (Linear)
Military AHV6 (Log)
Military NR--AS--10A (Alternate)
Military APN--232 CARA
Military LPIA
Military NR--AS--10A (Curve Fit)
The Radio Altitude sources listed are defined by the following:
ARINC 552/552A
--20 < H < 480 feet: Voltage = [ 0.02 x (H + 20) ] Vdc
480 < H < 2500 feet: Voltage = [ 10 x ( 1 + ln((H + 20)/500)) ] Vdc
Were H = Radio Altitude in feet.
Maximum Voltage output is 26.2 Vdc at any height above 2500 feet.
Collins BCA
--20 < H < 500 feet: Voltage = [ 0.02 x (H + 20) ] Vdc
500 < H < 2500 feet: Voltage = [ 10.4 + 0.003 x (H -- 500) ] Vdc
Were H = Radio Altitude in feet.
Maximum Voltage output is 26.2 Vdc at any heightabove 2500 feet.
AHV 6 Linear
0.0 to 25.0 Vdc: H = 200V -- 20
Were H = Radio Altitude in feet and V = Voltage in Volts dc.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
RMP--12B
(Continued)
Functional Description
Radio Altimeter Type Select Program Input No. 4 (NO)
AHV 6 Log
0.0 to 10.4 Vdc: H = 50V -- 20
> 10.4 to 18.09 Vdc: H = EXP(0.1479V + 4.7289)
> 18.09 to 25 Vdc: H = 695 + EXP(0.2532V + 2.1111)
Were H = Radio Altitude in feet and V = Voltage in Volts dc.
APN 232
0.0 to 27.0 Vdc: H = 200V
Were H = Radio Altitude in feet and V = Voltage in Volts dc.
LPIA
1.0 to 9.0 Vdc: H = 50V -- 50
> 9.0 to 21.0 Vdc: H = 383.14V -- 3048
Were H = Radio Altitude in feet and V = Voltage in Volts dc.
NR--AS--10A Alternate
0.0 to 1.2 Vdc: H = 2105.7V
Were H = Radio Altitude in feet and V = Voltage in Volts dc.
NR--AS--10A Curve Fit
0.0 to 18.1 Vdc: H = 0.0833V4 -- 1.8887V3 + 15.5169V2 -- 21.9374V + 14.8097
Were H = Radio Altitude in feet and V = Voltage in Volts dc.
Each of the military radio altimeter types provide two outputs that are connected to the
T2CAS computer unit input pins. The two altimeter outputs are the Analog Data Output
and Analog Data Reliability Signal. The Data Reliability Signal is connected to RMP--2K
for source No. 1 and RBP--3C for source No. 2, except for altimeter type LPIA. For radio
altimeter type LPIA, the Analog Data Output must be connected to RMP--2H (HI) and
RMP--2J (LO), the Analog Data Reliability Signal must be connected to RBP--3A (HI) and
RBP--3B (LO), and the inputs RMP--2K and RMP--3C are set high (greater than 18.5 V).
The metric radio altimeters are defined as follows:
Metric
Altimeter Definition
No. 1
No. 2
No. 3
No. 4
4--10
15 Feb 2003
Metric unit-Metric unit-Metric unit-Metric unit--
1000 meter range, 25 mV/M scaling
1000 meter range, 20 mV/M scaling
1500 meter range, 20 mV/M scaling
750 meter range, 50 mV/M scaling
34-43-20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RMP--12C
RA/TA Block Transfer Program Input (NO)
This program input determines the type of block transfer that is made from the T2CAS
computer unit to the TA/RA displays. If this pin is grounded, the T2CAS computer unit
transmits in Honeywell BCA EFIS format. If the T2CAS computer unit senses an open at
this pin, it transmits in ARINC 735 format.
RMP--12D
Aircraft Type 1 Program Input
This program pin is used with pin RMP--12E to designate the aircraft manufacturer (Air
Transport customers only) for maintenance support functionality. The aircraft
manufacturer is determined as follows:
RMP--12D RMP--12E
Description
Open
Open
Ground
Ground
All other airframes including BCA aircraft
Boeing
McDonnell Douglas
Airbus
Open
Ground
Open
Ground
RMP--12E
Aircraft Type 0 Program Input
See RMP--12D.
RMP--12F
Reserved Program Input
Reserved for future use.
RMP--12G
Option Parity Program Input
The T2CAS computer unit uses nine discrete program input pins to determine which
options have been selected by the installer. Eight of these pins are used to determine
option selections. The ninth pin (RMP--12G) is used to determine parity for the eight
option selection pins (RMP--10G, --10H, --10J, --10K, --11A, --11B, --11C, and --11D). To
determine parity, count the number of option pins that are grounded. If the number of
pins that are grounded is an odd number (1, 3, 5, 7), ground pin RMP--12G. If the
number of grounded pins in the option group is an even number (0, 2, 4, 6, 8), leave pin
RMP--12G open.
RMP--12H
Analog Radio Altimeter Type Select Program Input No. 3 (NO)
See RMP--12B.
RMP--12J
Analog Radio Altimeter Type Select Program Input No. 2 (NO)
See RMP--12B.
RMP--12K
Analog Radio Altimeter Type Select Program Input No. 1 (NO)
See RMP--12B.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RMP--13A, 13B RA Display No. 1/ARINC 429 Data Recorder Output: [RMP--13A (A), RMP--13B (B)]
These ARINC 429 outputs are configured to output either RA information or for use as an
ARINC 429 data recorder function. The output is configured by program pin RMP--11D.
When RMP--11D is open (standard configuration), the bus is configured for low--speed
(12.5 kbits/s) ARINC 429 operation and RA information is output according to the format
specified for the RA display bus in ARINC 735. When RMP--11D is grounded, the bus is
configured for high--speed (100 kbits/s) ARINC 429 operation and the output supplies TA
and RA information to a 429 data recorder.
RMP--13C, 13D RA Display No. 2/ARINC 429 Data Recorder Output: [RMP--13C (A), RMP--13D (B)]
See RMP--13A.
RMP--13E
RA Display No. 2 Status Discrete Input (NO)
This ground/open discrete input (Note 1) provides the functional status of RA Display No.
2. A ground on this pin indicates a valid display. If this discrete is not used by the RA
Display, connect to aircraft ground to prevent RA DISPLAY No. 2 fail message during
self--test.
RMP--13F
Landing Gear Discrete Input (NO)
The T2CAS computer monitors this discrete that indicates the landing gear position.
Landing Gear is a Ground/Open type discrete (Note 1) were an open indicates the gear is
retracted (gear is up) and a ground indicates the gear is extended (gear is down).
RMP--13G
Climb Inhibit No. 2 Discrete Input (NO)
See RMP--1J.
RMP--13H, 13J Radio Altimeter No. 1 Input: [RMP--13H (A), RMP--13J (B)]
This input is provided for Low Speed ARINC 429 (12.5 Kbits/s) altitude inputs from an
ARINC 707 digital radio altimeter. Radio altitude data is used for computation of
sensitivity level, inhibit descend advisories, and inhibit aural annunciation when in close
proximity to the ground. Also see RMP--2H.
RMP--13K
TCAS System Valid Discrete Output (NO)
This ground/open type discrete output (Note 3) indicates the health status of the T2CAS
computer unit to other avionics systems that monitor TCAS system status. This output is
used in retrofit installations where instrumentation needs to monitor TCAS status and the
status is not available across an A429 bus. A ground at this pin indicates normal TCAS
operation. An open indicates a TCAS fault.
RMP--14A, 14B ARINC 429 TX Coordination Bus No. 2 Output: [RMP--14A (A), RMP--14B (B)]
This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal),
that transmits data from the TCAS computer unit to the No. 2 Mode S Transponder.
The labels on this bus are as follows: 273, 274, 275.
4--12
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
RMP--14C
Functional Description
RA Display No. 1 Status Discrete Input (NO)
This ground/open discrete input (Note 1) provides the functional status of RA Display No.
1. A ground on this pin indicates a valid display. If this discrete is not used by the RA
display, connect to aircraft ground to prevent RA DISPLAY No. 1 fail message during
self--test.
RMP--14D, 14E Selected Altitude701/720 ARINC 429 Bus Input
Reserved for future use.
RMP--14F, 14G ARINC 429 XT Coordination No. 1 Input: [RMP--14F (A), RMP--14G (B)]
This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal),
that receives data from the No. 1 Mode S Transponder.
The labels on this bus are as follows: 013, 015, 016, 203, 271, 272, 273, 274, 275, 276,
277, 350.
RMP--14H, 14J ARINC 429 XT Coordination No. 2 Input: [RMP--14H (A), RMP--14J (B)]
This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal),
that receives data from the No. 2 Mode S Transponder.
The labels on this bus are as follows: 013, 015, 016, 203, 271, 272, 273, 274, 275, 276,
277, 350.
RMP--14K
Reserved for TAWS/RWS use.
RMP--15A
to
RMP--15H
Reserved for TAWS/RWS use.
RMP--15J, 15K ARINC 429 TX Coordination No. 1 Output: [RMP--15J (A), RMP--15K (B)]
This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal),
that transmits data from the T2CAS computer unit to the No. 1 Mode S Transponder.
The labels on this bus are as follows: 273, 274, 275.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
T2CAS Computer Unit Right Bottom Plug (RBP)
RBP--1A
Thru
RBP--1G
Reserved for TAWS/RWS use.
RBP--1H
RA Data Word 270 Bit 18 Discrete Output
This discrete output provides RA information to the ARINC 573 flight recorder. The
output goes to the “ground” state each time its associated bit within the advisory field of
the RA output words changes from a “zero” condition to a “one” condition. The output
remains in the “ground” state for as long as the associated RA bit remains non--zero.
This output is read by the flight recorder as either a series or shunt output.
NOTE: The discrete is pulled up to +28 Vdc in the “open” state.
RBP--1J
RA Data Word 270 Bit 19 Discrete Output
See RBP--1H.
RBP--1K
RA Data Word 270 Bit 20 Discrete Output
See RBP--1H.
RBP--2A
Thru
RBP--2G
Reserved for TAWS/RWS use.
RBP--2H
RA Data Word 270 Bit 21 Discrete Output
See RBP--1H.
RBP--2J
RA Data Word 270 Bit 22 Discrete Output
See RBP--1H.
RBP--2K
RA Data Word 270 Bit 23 Discrete Output
See RBP--1H.
RBP--3A, 3B
RBP--3C
RBP--3D, 3E
Radio Altimeter No. 2 ARINC 552/Analog Input: [RBP--3A (HI), RBP--3B (LO)]
See RMP--2H and --2J.
Radio Altimeter No. 2 Valid Discrete Input (PO)
See RMP--2H. Valid condition is greater than +18.5 Vdc. Invalid is open.
Radio Altimeter No. 2 Input: [RBP--3D (A), RBP--3E (B)]
See RMP--13H. Also see RMP--2H.
RBP--3F,
RBP--3G
Reserved for TAWS/RWS use.
RBP--3H
RA Data Word 270 Bit 24 Discrete Output
See RBP--1H.
RBP--3J
RA Data Word 270 Bit 25 Discrete Output
See RBP--1H.
4--14
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RBP--3K
RA Data Word 270 Bit 26 Discrete Output
See RBP--1H.
RBP--4A
Thru
RBP--4F
Reserved Discrete Inputs (Standard Ground/Open)
Reserved for future use.
RBP--4G
RA Display Test Inhibit Program Pin
This program pin is used to determine if RA discrete monitoring will be inhibited during
self--test. If this pin is connected to program common (ground), RA discrete self--test
monitoring is inhibited. An open on this pin indicates RA discretes monitoring during
self--test.
RBP--4H
RA Data Word 270 Bit 27 Discrete Output
See RBP--1H.
RBP--4J
RA Data Word 270 Bit 28 Discrete Output
See RBP--1H.
RBP--4K
RA Data Word 270 Bit 29 Discrete Output
See RBP--1H.
RBP--5A
Advisory Inhibit Discrete Input No. 1 (NO)
Four ground/open type discrete inputs (Note 1) at RBP--5A, --5B, --5C, and --5D provide
the capability for the T2CAS computer to defer all advisory (TA), aural alert and visual
alert outputs until another, higher priority announcement or alert is completed. An open at
all four of these discrete inputs indicates normal advisory/alert operation. These discrete
inputs become active by connection to program common (ground) at RBP--7K. No new
TA information can be placed on the RA or RA/TA busses during a period of Advisory
Inhibit. If an advisory condition, which occurred during a period of Advisory Inhibit,
remains when the T2CAS computer returns to normal operation, it is annunciated. The
Advisory Inhibit inputs and their effect on the advisory/alert priority system are as follows:
Discrete No.
Pin No.
Mode
Priority
RBP--5A
Forced Standby
RBP--5B
Force TA Only (no voice/tone)
RBP--5C
Force TA Only (no voice/tone)
RBP--5D
Force TA Only (no voice/tone)
Discrete No. 1 (RBP--5A) has priority over No. 2 (RBP--5B), No. 3 (RBP--5C) and No. 4
(RBP--5D). Discrete No. 1 forces TCAS into STANDBY mode. Discretes No. 2, No. 3,
and No. 4 force TCAS into TA mode with no voice or tone annunciations.
See Note 1 for Ground/Open type discrete input definition.
RBP--5B
Advisory Inhibit Discrete Input No. 2 (NO)
See RBP--5A.
RBP--5C
Advisory Inhibit Discrete Input No. 3 (NO)
See RBP--5A.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RBP--5D
Advisory Inhibit Discrete Input No. 4 (NO)
See RBP--5A.
RBP--5E
Increase Climb Inhibit Discrete Input No. 1 (NO)
This input is a ground/open type discrete (Note 1) used to provide information to the
T2CAS CU whether to assume that the aircraft cannot achieve a climb rate of 2500 feet
per minute (FPM). The climb inhibit discrete inputs are designed in pairs (No. 1 and No.
2 at RBP--5F, or No. 3 at RBP--5G and No. 4 at RBP--5H) but can be wired as a single
input or in conjunction with other aircraft operations to achieve airframe customization of
the climb inhibit feature. The 2500 FPM climb inhibit function is assumed whenever No. 1
and No. 2 are ground or No. 3 and No. 4 are ground.
RBP--5F
Increase Climb Inhibit Discrete Input No. 2 (NO)
See RBP--5E.
RBP--5G
Increase Climb Inhibit Discrete Input No. 3 (NO)
See RBP--5E.
RBP--5H
Increase Climb Inhibit Discrete Input No. 4 (NO)
See RBP--5E.
RBP--5J
Climb Inhibit Discrete Input No. 3 (NO)
See RMP--1J.
RBP--5K
Climb Inhibit Discrete Input No. 4 (NO)
See RMP--1J.
RBP--6A
Airborne Data Loader Link A Discrete Input
This discrete input, along with Data Loader Discrete Inputs No. 2, 3, and 4 (pins RBP--6B,
RBP--6C, and RBP--6D, respectively), is a ground/open type discrete that specifies what
type of data loader (ARINC 603 or ARINC 615) is attached. The T2CAS computer has
separate receiver busses and separate data loader enable discrete inputs to support
simultaneous connections to an ADL and PDL. A ground on pin RBP--6A indicates that
an airborne data loader is connected to the rear connector of the T2CAS computer. A
ground on pin J1--18, PDL Link A Discrete Input, indicates that a portable data loader is
connected to the front connector of the T2CAS computer. The data loader discrete inputs
at RBP--6B, RBP--6C, and RBP--6D are also connected to the data loader discrete inputs
on the front connector (pins J1--51, J1--52, and J1--53, respectively). Listed below is an
active discrete (selected) indicated by a ground and an inactive discrete (not selected)
indicated by an open.
4--16
15 Feb 2003
RBP--6A J1--18
J1--51/
J1--52/
J1--53/
RBP--6B RBP--6C RBP--6D
Function
Ground
Ground
Open
Open
-- --
Ground
Open
Ground
Open
-- --
ARINC 615 ADL
ARINC 603 ADL
ARINC 615 PDL
ARINC 603 PDL
SW Part Number is output
Open
Open
Ground
Ground
-- --
Open
Ground
Open
Ground
-- --
Open
Open
Open
Open
Ground
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RBP--6B
Data Loader Discrete Input No. 2
See RBP--6A.
RBP--6C
Data Loader Discrete Input No. 3
See RBP--6A.
RBP--6D
Data Loader Discrete Input No. 4
See RBP--6A.
RBP--6E, 6F
ARINC 429 CFDS Output: [RBP--6E (A), RBP--6F (B)]
This differential pair output is a low speed ARINC 429 bus (12.5k bits/second nominal),
that transmits data to an onboard maintenance computer or a central fault display system.
RBP--6G, 6H
ARINC 429 CFDS Input: [RBP--6G (A), RBP--6H (B)]
This differential pair input is a low speed ARINC 429 bus (12.5k bits/second nominal), that
receives data from an onboard maintenance computer or a central fault display system.
RBP--6J
Spare Pin
RBP--6K
Spare Pin
RBP--7A
Audio Level Program Pin No. 1 (NO)
Two synthesized voice outputs with programmable output levels are provided by the
T2CAS computer unit. The output at RMP--2F and --2G supply high level (up to 8 Watts)
audio signals to an 8 Ohm speaker. The second output at RMP--3F and --3G supply low
level (up to 80 milliwatts) audio signals to a 600 Ohm audio distribution system. All aural
traffic and resolution advisories can be annunciated over these outputs unless cancelled
by a Cancel Discrete (RMP--3D).
Listed below are the audio level program pin configurations and the resulting output
levels:
RBP--7A
(MSB)
Open
Open
Open
Open
Ground
Ground
Ground
Ground
Program Pin
RBP--7B
RBP--7C
(LSB)
Open
Open
Ground
Ground
Open
Open
Ground
Ground
Low Level Output
dBm
mW
Open
Ground
Open
Ground
Open
Ground
Open
Ground
RBP--7B
Audio Level Program Pin No. 2 (NO)
See RBP--7A.
RBP--7C
Audio Level Program Pin No. 3 (NO)
See RBP--7A.
16
13
10
--2
19
34-43-20
40
20
10
2.5
1.25
0.625
80
High Level Output
dBm
--3
--6
--9
--12
0.5
0.25
0.125
0.0625
4--17
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RBP--7D
Audio Tone Enable Program Pin (NO)
If this programming pin is connected to program common, (RBP--7K), all voice
announcements are delayed by one second and are preceded by a tone. If pin is left
open, no delays or tones occur.
RBP--7E
Ground Display Mode Program Pin (NO)
The T2CAS computer unit monitors this programming pin to select the TCAS ground
display mode while the aircraft is on the ground. If the aircraft is on the ground and this
pin is connected to program common (RBP--7K), TCAS goes into standby mode. If this
pin is left open and the aircraft is on the ground, TCAS displays traffic only. Aural and
voice annunciations are inhibited while the aircraft is on the ground.
NOTE: TCAS does not display any traffic that it locates on the ground. TCAS aircraft
has WOW and intruder aircraft reports the same altitude or a lower altitude.
RBP--7F
Display All Traffic Program Pin (NO)
The T2CAS computer unit monitors this program pin to select either the all traffic display
mode or the TA/RA only mode. If this pin is open, all traffic is displayed. If this pin is
connected to program common (RBP--7K), the TCAS displays only TA/RA type intruders.
RBP--7G
Cable Delay Signal Program Pin (NO)
The cable delay program pins (RBP--7G, RBP--7H, and RBP--7J) convey to the T2CAS
computer unit the amount of delay differential between the top and bottom antenna
cables. Pin RBP--7G determines whether a time delay is added to the top or bottom. If
this pin is open, the time delay is added to the top. If this pin is ground (connected to
program pin RBP--7K), the time delay is added to the bottom. The cable delay logic is
given below. Program common for the cable delay program pins is RBP--7K.
RBP--7H
(MSB)
RBP--7J
(LSB)
Differential
Delay
Adjustment
Open
Open
Ground
Ground
Open
Ground
Open
Ground
0--50 nsec
51--150 nsec
151--250 nsec
251--350 nsec
No Change
Add 100 nsec delay
Add 200 nsec delay
Add 300 nsec delay
RBP--7H
Cable Delay MSB Program (NO)
See RBP--7G.
RBP--7J
Cable Delay LSB Program Pin (NO)
See RBP--7G.
RBP--7K
Program Common
This is the ground source for use with program pins.
RBP--8A
Thru
RBP--8D
Reserved Program Pins
4--18
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
RBP--8E
Self--Test Test Inhibit Program Pin (NO)
This program pin determines if self--test will be inhibited while airborne. If grounded, this
pin inhibits self--test while airborne. If open, self--test is enabled while airborne.
RBP--8F
TA/RA Display Symbol Maximum 16 Program Pin (NO)
The T2CAS computer unit establishes the number of intruder symbols to be displayed on
the TA display through the program pins RBP--8F, --8G, --8H, --8J, and --8K. This number
can vary between 0 and 31, depending on the programming that is a summation of the
selected pins (--8F = 16, --8G = 8, --8H = 4, --8J = 2 and --8K = 1). Connecting one of
these pins to program common (RBP--7K) indicates the associated pin is not selected
and that its value is not included in the summation. Leaving the pin open designates the
associated pin is selected and its value is included in the summation. The encoded
number is placed within the RTS data word (label 357) and sent to the display. The
display should then limit the intruder symbols to this number.
RBP--8G
TA/RA Display Symbol Maximum 8 Program Pin (NO)
See RBP--8F.
RBP--8H
TA/RA Display Symbol Maximum 4 Program Pin (NO)
See RBP--8F.
RBP--8J
TA/RA Display Symbol Maximum 2 Program Pin (NO)
See RBP--8F.
RBP--8K
TA/RA Display Symbol Maximum 1 Program Pin (NO)
See RBP--8F.
RBP--9A
Thru
RBP--9J
Reserved Factory Test Pins
Leave these pins unconnected for aircraft installations.
RBP--9K
Spare Pin
RBP--10A
Thru
RBP--10G
Reserved Factory Test Pins
Leave these pins unconnected for aircraft installations.
RBP--10H
Thru
RBP--10J
Spare Pins
RBP--10K
Reserved Factory Test Pin
Leave this pin unconnected for aircraft installations.
34-43-20
4--19
15 Feb 2003
Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
T2CAS Computer Unit Left Top Plug (LTP)
LTP--1
Top Antenna 0 Degree Port
J1 on the antenna is color--coded yellow. This antenna port (Note 2) is called the 0
degree port because it produces a transmission pattern in the forward quadrant of the
aircraft. J1 is physically located toward the rear of the antenna and to the rear of the
aircraft when antenna is properly installed. The T2CAS computer unit checks the built--in
dc to ground resistance of this antenna port. It must detect approximately 1000 Ohms or
TCAS fails its antenna test.
LTP--2
Top Antenna 270 Degree Port
J2 on the antenna is color--coded black. This antenna port (Note 2) is called the 270
degree port because it produces a transmission pattern in the left wing quadrant of the
aircraft. J2 is physically located toward the right wing of the aircraft when antenna is
properly installed. The TCAS function checks the built--in dc to ground resistance of this
antenna port. It must detect approximately 8000 Ohms or it reports antenna test failure.
LTP--3
Top Antenna 180 Degree Port
J3 on the antenna is color--coded blue. This antenna port (Note 2) is called the 180
degree port because it produces a transmission pattern in the rear quadrant of the
aircraft. J3 is physically located toward the front of the antenna and to the front of the
aircraft when antenna is installed properly. The T2CAS computer unit checks the built--in
dc to ground resistance of this antenna port. It must detect approximately 4000 Ohms or
it reports antenna test failure.
LTP--4
Top Antenna 90 Degree Port
J4 on the antenna is color--coded red. This antenna port (Note 2) is called the 90 degree
port because it produces a transmission pattern in the right wing quadrant of the aircraft.
J4 is physically located toward the left wing of the aircraft when antenna is properly
installed. The TCAS function checks the built--in dc to ground resistance of this antenna
port. It must detect approximately 2000 Ohms or it reports antenna test failure.
T2CAS Computer Unit Left Middle Plug (LMP)
LMP--1
Bottom Antenna 0 Degree Port
J1 on the antenna is color--coded yellow. Same as top antenna 0 degree port (LTP--1).
In addition, this port (Note 2) is used as the omnidirectional antenna connection. The
TCAS function determines that a bottom omnidirectional antenna is installed if it detects
less than 500 Ohms (50 Ohms typical) to ground on this pin and an open circuit (>13k
Ohms) at LMP-- 2, --3, and --4 or a dc short (<500 Ohms) if unused ports are terminated
at back of mounting tray.
LMP--2
Bottom Antenna 90 Degree Port
J2 on the antenna is color--coded black. This antenna port (Note 2) is called the 90
degree port because it produces a transmission pattern in the right wing quadrant of the
aircraft. J2 is physically located toward the left wing of the aircraft when antenna is
properly installed. The TCAS function checks the built in dc to ground resistance of this
antenna port. It must detect approximately 8000 Ohms or it reports antenna test failure.
4--20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
LMP--3
Bottom Antenna 180 Degree Port
J3 on the antenna is color--coded blue. Same as top antenna (Note 2) 180 degree port
(LTP--3).
LMP--4
Bottom Antenna 270 Degree Port
J4 on the antenna is color--coded red. This antenna port (Note 2) is called the 270
degree port because it produces a transmission pattern in the left wing quadrant of the
aircraft. J4 is physically located toward the right wing of the aircraft when properly
installed. The TCAS function checks the built in dc to ground resistance of this antenna
port. It must detect approximately 2000 Ohms or it reports antenna test failure.
T2CAS Computer Unit Left Bottom Plug (LBP)
LBP--1
115 Vac Power Input (H)
This pin along with the 115 Vac Power Input (C) line (pin LBP--7) provides the 115 Vac
power requirements for the TT--950/--952 T2CAS computer units.
Wiring requirement is a standard #20 AWG.
NOTE:
The T2CAS computer unit operates with either 115 Vac, 400 Hz, or +28 Vdc
input power. If 115 Vac is used, the power should be connected through a
5 Amp circuit breaker, and the pins for the +28 Vdc input should be left
unconnected.
LBP--2
Spare Pin
LBP--3
+28 Vdc Power Return (LO)
See LBP--10.
LBP--4
Spare Pin
LBP--5
Fan 115 Vac Power Output (H)
This pin along with the Fan 115 Vac Output Power (C) line (pin LBP--9) provides 115 Vac
power for an external fan.
LBP--6
Spare Pin
LBP--7
115 Vac Power Input (C)
See LBP--1.
LBP--8
Signal Ground
Connect to Aircraft Signal Ground.
LBP--9
Fan 115 Vac Power Output (C)
See LBP--5.
34-43-20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
LBP--10
Functional Description
+28 Vdc Power Input (HI)
This pin along with the T2CAS computer unit +28 Vdc Power Return line (LBP--3) provide
the +28 Vdc power requirements for the T2CAS computer unit.
Wiring requirement is a standard #18 AWG.
NOTE:
The T2CAS TT--950/--952 computer operates with either 115 V ac, 400 Hz, or
+28 Vdc input power and the TT--951 computer operates on +28 Vdc input
power only. On the TT--950/--952 computers, if +28 Vdc is used, the power
should be connected through a 10 Amp circuit breaker, and the pins for the 115
Vac input should be left unconnected.
LBP--11
Chassis Ground
Connect to aircraft frame. The T2CAS Chassis and signal ground pins should use the
same AWG as the power connections (See LBP--1 and LBP--10).
LBP--12
Mutual Suppression Pulse Bus Input
The T2CAS computer unit joins the mutual suppression bus daisy chained through TCAS
and other RF transmitting equipment on board the aircraft. The TCAS function receives
suppression pulses from other LRUs on this bus, which is used to suppress the TCAS
receivers during such transmissions. This prevents the TCAS function from interpreting
these transmissions as valid replies from an intruder aircraft. When not suppressed, the
TCAS function transmits its own suppression pulses on the same bus in order to
suppress the receivers in other L--band systems on the aircraft. The L--Band suppression
coax must be RG142, RG400, or equivalent coaxial cable which meets the operational
characteristics required by ARINC 735A.
LBP--13
GPS Antenna Port (Active on TT--952 and reserved for TT--950 and TT--951)
T2CAS unit TT--952 uses this pin for the GPS Antenna port -- RF input from the GPS
antenna and +12 Vdc output to power the active amplifier GPS antenna.
The minimum coax loss between the GPS antenna’s output and the T2CAS computer’s
GPS input port is equal to the maximum preamplifier gain minus 29 dB. The maximum
coax loss between the GPS antenna’s output and the T2CAS computer’s GPS input port
is equal to the minimum preamplifier gain minus 12.5 dB.
The Interface descriptions that follow are for the 53--pin Data Loader connector J1 mounted on the
front panel of the T2CAS computer unit. These descriptions are used to make up the cable that is
used to interface between the T2CAS computer unit and an ARINC 615 Portable Data Loader (PDL),
a RS--232 PC Serial Port, a RS--422 Flight Data Recorder, or an ARINC 429 Maintenance Display.
J1--1, 2
J1--3,
J1--4
4--22
15 Feb 2003
ARINC 429 PDL Bus Input: [J1--1 (A), J1--2 (B)]
This differential pair input is a high--speed ARINC 429 bus (100k bits/second nominal)
that is used to input data from the data loader to the TCAS computer unit. The standards
for this interface are defined in ARINC 615 Airborne Computer High Speed Data Loader.
These pins should be connected to pins 1 and 2 of the PDL cable interface.
Spare Pins
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--5
Output Bus Shields
The shields from the output bus (J1--8, 9) should be connected to this pin.
J1--6,
J1--7
A615A Data Loader Ethernet Output [J1--6 (TD+), J1--7 (TD--)]
TAWS Ethernet 10 Base--T.
J1--8, 9
ARINC 429 Data Loader/PDL Recorder Bus Output: [J1--8 (A), J1--9 (B)]
This differential pair output is a high--speed ARINC 429 bus (100K bits/second nominal)
that is used to output data from the T2CAS computer unit to the data loader. The
standards for this interface are defined in ARINC 615 Airborne Computer High Speed
Data Loader.
These pins should be connected to pins 8 and 9 of the PDL cable interface.
J1--10, 11
RS--422 Recorder External Clock Input: [J1--10 (+), J1--11 (--)]
These two pins provide external clocking from an RS--422 Flight Data Recorder for
TCAS.
J1--12, 13
RS--422 Recorder Reply Input: [J1--12 (+), J1--13 (--)]
These two pins provide communication from a RS--422 Flight Data Recorder for TCAS.
J1--14
RS--422 Recorder 125 kHz/ External Program Pin
This pin is used to designate internal or external recorder clock operation for TCAS. A
ground on this pin selects external recorder clock operation. An open selects 125k Hz
internal recorder clock operation.
J1--15
RS--422 Recorder Disable Program Pin
This program pin is used to enable or disable the RS--422 Data Recorder function for
TCAS. The program pin is activated externally by the Flight Data Recorder. Logic is as
follows:
Ground = RS--422 Recorder disabled; Open = RS--422 Recorder enabled
J1--16
Input Bus Shields
The shields from the input bus (J1--1, 2) should be connected to this pin.
J1--17
Spare Pin
J1--18
PDL Link A Discrete Input
This is a ground/open discrete (Note 1) from an portable ARINC 615 or ARINC 603 data
loader which indicates, to the T2CAS computer unit, that a data loader is connected. A
ground indicates a data loader is connected. This pin is used by the TCAS, TAWS/RWS
and GPS.
J1--19
PDL Link B Common
Connect this pin to pin 19 of the PDL cable interface.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
J1--20, 22
Functional Description
115 Vac Power Output: [J1--20 (H), J1--22 (C)]
These power output pins provide the 115 Vac operating power for the data loader.
The 115 Vac (H) and 115 Vac (C) interconnect wires should be shielded or twisted and
shielded with an insulating jacket over the shield. The shield should be connected to
chassis ground (J1--21).
J1--21
Chassis Ground
Connect 115 Vac power shields to this pin.
J1--23
A615A Dataloader Ethernet Input (RD+)
TAWS Ethernet 10--base--T read input
J1--24
Thru
J1--28
Spare Pins
J1--29, 30
RS--422 Recorder Data Output: [J1--29 (+), J1--30 (--)]
The RS--422 Flight Data Recorder data is output on these pins.
J1--31, 32
RS--422 Recorder Clock Output: [J1--31 (+), J1--32 (--)]
The RS--422 Flight Data Recorder internal 125k Hz internal clock is output on these pins.
J1--33,34
ARINC 429 TA/RA Display No. 1 Output: [J1--33 (A), J1--34 (B)]
This bus can be used to connect to a maintenance display. These pins are also
connected to the ARINC 600 connector on the rear of the unit (RMP--7C and --7D).
J1--35,
J1--36
J1--37, 38
Spare Pins
28 V dc Power Output: [J1--37 (HI), J1--38 (LO)]
These power output pins provide the +28 Vdc operating power for the data loader. These
pins are used only if the data loader operates from a +28 Vdc source.
J1--39
A615A Dataloader Ethernet Input (RD--)
TAWS Ethernet 10--base--T read input
J1--40
T2CAS RS--232 Data Input
This input is used by the TAWS, TCAS and GPS function to receive RS--232 data from a
portable maintenance terminal.
J1--41
T2CAS RS--232 Data Output
This output is used by the TAWS, TCAS and GPS function to transmit RS--232 data to a
portable maintenance terminal.
J1--42
TCAS RS--232 Data Input
This input is used by the TCAS function to receive RS--232 data from a portable
maintenance terminal.
J1--43
TCAS RS--232 Data Output
This output is used by the TCAS function to transmit RS--232 data to a portable
maintenance terminal.
4--24
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--44
GPS RS--232 Data Input
This input is used by the GPS function to receive RS--232 data from a portable
maintenance terminal.
J1--45
GPS RS--232 Data Output
This output is used by the GPS function to transmit RS--232 data to a portable
maintenance terminal.
J1--46
Thru
J1--47
Spare Pins
J1--48,
J1--49
Logic Common
Common lines for the RS--232 Data Input/Output lines. These two pins are tied together
in the T2CAS computer unit.
J1--50
Reserved Pin
J1--51
Data Loader Link No. 2 Discrete Input
Pins J1--51 and J1--52 are ground/open discretes from a portable data loader, which are
used to specify what type of data loader (ARINC 603 or ARINC 615) is connected to the
T2CAS computer unit. These two pins are also connected to the ARINC 600 connector
on the rear of the unit (RBP--6B and --6C respectively).
J1--52
Data Loader Link No. 3 Discrete Input
See J1--51.
J1--53
Data Loader Link No. 4 Discrete Input
This is a ground/open discrete from a Portable Data Loader (PDL) that is used to transmit
the software part number on the Data Loader output bus when grounded, The landing
gear indicates extended, and the air/ground indicates ground. This pin is also connected
to the ARINC 600 connector on the rear of the unit (RBP--6D).
NOTE:
1: Ground = Voltage of 0.0 Vdc to +3.5 Vdc or Resistance of less than 10 Ohms
applied to input.
Open = Voltage of +18.5 to +36 Vdc or Resistance greater than 100k Ohms
applied to input.
NOTE:
2: The Antenna Coax shall be RG225 or equivalent coaxial cable that provides a
loss of 2.5 db ± 0.5 db or less between the T2CAS computer and each TCAS
Antenna port. For Directional Antenna Coaxes, each coax cable must be within
0.5 db of the other coaxes (e.g. if one port has a 2 db loss, the other 3 ports can
not exceed 2.5 db loss).
NOTE:
3: Ground = Port capable of sinking at least 20 milli--Amps of current.
Open = Voltage of +18.5 to +36 Vdc or Resistance greater than 100k Ohms
applied to output.
34-43-20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--2. Gables Control Panel Interface Description
Connector Pin
Designation
J1--1, 2
J1/J2--3, 4
Functional Description
PANEL AND DISPLAY LIGHTING INPUT: (J1--1 HIGH, J1--2 LOW)
5 Vac, 2.3 Amp maximum lighting input for front panel and display lighting. Lighting is
provided by incandescent lamps.
+28 Vdc INPUT POWER: (J1/J2--3 HIGH, J1/J2--4 LOW)
The control panel is powered from a +28 Vdc power bus. Two identical but isolated
power supplies provide the power requirements to each individual electronic module that
independently control transponder 1 and 2. Maximum current is 2.5 Amps dc.
J1/J2--5
ANTENNA TRANSFER DISCRETE OUTPUT: (J1/J2--5)
This discrete output is used to provide the ability to switch a RF relay for dual transponder
installations that have only one set of antennas. These outputs from J1 and J2 are linked
to the XPDR 1--2 switch. The output is OPEN(+12 to +35 Vdc) when the transponder is
in standby (inactive) mode, and GROUND(< +3.5 Vdc) when the transponder is in an
active operational mode.
J1/J2--6
DC GROUND INPUT: (J1/J2--6)
Reference for all discrete inputs/outputs. Tied to aircraft dc ground.
J1/J2--7
STANDBY/ON OUTPUT: (J1/J2--7)
These discrete outputs (STANDBY/ON) will mimic the XPDR switch position placing one
transponder in Standby and the other in the ON (active) mode. Both transponders will
never be in the ON mode simultaneously. This output is GROUND(< +3.5 Vdc) when in
Standby mode and OPEN(+12 to +35 Vdc) when in the ON mode. This output can sink
100 mA maximum.
Connect pin to transponder STANDBY / ON Discrete Input.
J1/J2--8
CHASSIS GROUND INPUT: (J1/J2--8)
Tied to airframe. Also used to connect ARINC 429 cable shields to the chassis.
J1/J2--9
FUNCTIONAL TEST INPUT: (J1/J2--9)
Functional test can also be initiated using this input discrete. When J1/J2--9 is grounded,
a functional test similar to pushing the TEST button on the front panel is done.
J1/J2--10
WARNING AND CAUTION OUTPUT: (J1/J2--10)
This discrete output provides a low signal to a remote master warning system when the
control panel receives a Monitor Lamp fault indication from the active transponder.
Otherwise it provides 7 to 30 Vdc or a resistance of >100k Ohms to ground. This output
can sink 20 mA maximum.
J1/J2--12
TRANSPONDER FAIL #2 INPUT: (J1/J2--12)
The G7130--XX ATC/TCAS control panel transponder fail annunciator is controlled by this
input. When the transponder is operating normally this input remains grounded.
Otherwise, the transponder opens this input to indicate a transponder failure. The control
panel turns the annunciator ON to alert the user of a transponder malfunction. The
transponder fail annunciator turns on only when the failed transponder is selected by the
XPDR 1--2 switch.
Connect this pin to the transponder XPDR FAIL #2 Discrete Output.
4--26
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--2. Gables Control Panel Interface Description (cont)
Connector Pin
Designation
Functional Description
J1/J2--13
IDENT INPUT: (J1/J2--13)
The IDENT discrete input provides another means of activating the IDENT function. This
input allows the control panel to interface with an external IDENT switch located in the
Flight Deck. When the input is grounded, the IDENT function is activated; otherwise it
should remain open.
J1/J2--14
TRANSPONDER FAIL LOGIC DISCRETE INPUT: (TDR--94D ONLY) (J1/J2--14)
This input allows the control panel to use +28 Vdc logic from a Collins TDR--94D
transponder to control the transponder fail annunciator. This input should not be used
unless a Collins TDR--94D transponder is used with this control panel.
J1/J2--15
AIR/GROUND SW DISCRETE OUTPUT: (J1/J2--15)
This output is directly connected to the AIR/GND discrete input (J1/J2--24). This output
can be routed directly to the transponder to disable it (Standby), and terminate ATC code
replies. J1 discrete logic operates independently from J2.
J1/J2--16
AIR DATA SOURCE OUTPUT: (J1/J2--16)
Ground/Open output that is dependent on the front panel ALT RPTG and XPDR switch
positions. This discrete output is enabled when altitude reporting is selected in the ON
mode. When altitude reporting is selected OFF, the J1/J2--16 output remains in the
OPEN state.
This discrete output is connected to the transponder AIR DATA SOURCE SELECT
Discrete Input.
J1/J2--18
MONITOR LAMP POWER INPUT: (J1/J2--18)
These inputs are used as the input power source for the transponder fail annunciator on
the front panel of the control panel. The input supply voltage is a dimmable +28 Vdc at
200 mA maximum.
J1/J2--20
TRANSPONDER STRAPPING CONFIGURATION: (J1/J2--20)
This discrete input programs the control panel to operate, and be able to properly
interface to one of two types of transponder configurations. If this input is left OPEN then
the control panel operates in accordance with ACSS transponder specifications. If the
input is GROUNDED, it is programmed to operate in accordance with Collins transponder
specifications.
J1/J2--21
LAMP TEST INPUT: (J1/J2--21)
To initiate a lamp test, J1 or J2 pin 21 must be grounded through an external switch. All
segments and annunciators in the control panel LCD (except RPLY and decimal points)
are ON for as long as this input is grounded. ARINC 429 labels are not affected by the
activation of a lamp test mode.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--2. Gables Control Panel Interface Description (cont)
Connector Pin
Designation
Functional Description
J1/J2--22, 23
ARINC 429 OUTPUTS: (J1/J2--22,23)
Communication between the control panel and the transponder is done over a two wire
low speed, odd parity, ARINC 429 compatible bus. Selected ATC code, operating mode,
and system parameters are communicated to the transponder over these lines.
Transmission of labels 013, 015, 016, and 031 is done every 150 milliseconds.
Connect these pins to one of the two transponder ARINC 429 CONTROL DATA Input
Ports.
J1/J2--24
AIR/GROUND INPUT DISCRETE: (J1/J2--24)
The control panel accepts input from two independent Air/Ground (WOW) switches for
applications that require automatic disabling of the transponder upon landing. This input
is wired directly to the AIR/GROUND SW Discrete Output (J1/J2--15).
4--28
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--3. 41--Pin VSI/TRA Interface Description
Connector Pin
Designation
Functional Description
J1--1
VERTICAL SPEED +DC REFERENCE INPUT:
Pins 1, 2, and 3 are inputs to the VSI/TRA from an ARINC 575 air data computer
indicating vertical speed. Pin 1 is a +12 Vdc regulated reference voltage from the ADC.
Pin 3 is a --12 Vdc regulated reference voltage from the ADC. Pin 2 receives a +10 to
--10 Vdc rate signal from the ADC. Also see pins 31, 32, and 33.
J1--2
VERTICAL SPEED DC RATE INPUT:
See pin 1.
J1--3
VERTICAL SPEED --DC REFERENCE INPUT:
See pin 1.
J1--4, 6
ARINC 565 VERTICAL SPEED AC INPUT: (J1--4 HIGH, J1--6 LOW)
Pins 4, 5, 6, and 16 are inputs to the VSI/TRA from an ARINC 565 air data computer or
IRS. A 26 Vac, 400 Hz reference signal is received on pin 5, (HI) and pin 16, (LO). Pin 4,
(HI) and pin 6, (LO) provides an amplitude modulated 400 Hz signal with a maximum
voltage of  6.25 volts. The RMS value of this signal is used by the VSI/TRA to compute
and display the vertical rate. The phase of this signal is compared with the reference
signal to determine if the rate is positive or negative. An in--phase signal equals a
positive rate, an out--of-- phase signal indicates a negative rate. Also see pins 8 and 31.
J1--5
VERTICAL SPEED 26 Vac, 400 Hz REFERENCE INPUT (HI):
See pins 4 and 16.
J1--8
VERTICAL SPEED VALID DISCRETE INPUT:
The VSI/TRA receives a +28 Vdc signal from an ARINC 575 or 565 air data computer
indicating its valid operation. An “open” at this pin indicates an invalid vertical speed
signal from the ADC. This pin is only used when pins (1, 2, 3) or (4, 5, 6, and 16) are
used. Also see pins 1 and 4.
J1--9, 10
5 VOLT LAMP DIMMING INPUT: (J1--9 C, J1--10 H)
The VSI/TRA monitors the Flight Deck lamp voltage bus at pins 9 and 10. This voltage
may be either ac or dc. The back lighting in the VSI/TRA is adjusted by and tracks this
voltage from 0.5 Volts to 5 Volts. If this input falls below 0.5 Volts or is absent, the
VSI/TRA sets itself to a nominal level to prevent the display from going dark due to loss
or failure of the lamp dimming bus.
J1--11
ARINC 429 (B) TCAS TA/RA DATA BUS INPUT:
Paired with pin 26. These pins connect to a T2CAS computer unit.
J1--12
ARINC 429 (B) VERTICAL SPEED NO. 1 INPUT BUS:
Paired with pin 27. These pins connect to Digital ADC No. 1 or IRS No 1.
J1--14
ARINC 429 (B) VERTICAL SPEED NO. 2 INPUT:
Paired with pin 30. These pins connect to Digital ADC No. 2 or IRS No. 2.
J1--15
CONFIGURATION STRAP COMMON INPUT:
This pin is the return line for the configuration strapping pins J1--17, and J1--32 thru 35.
J1--16
VERTICAL SPEED 26 Vac, 400 Hz REFERENCE INPUT (C):
See pins 4 and 5.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--3. 41--Pin VSI/TRA Interface Description (cont)
Connector Pin
Designation
J1--17
Functional Description
CONFIGURATION STRAP #3 INPUT (NO):
Pin 17 is used in conjunction with pin 35 to select the indicator operating mode as follows:
The following applies: O = Open, G = Ground.
Pin
J1--18
35
17
Indicator Operating Mode
Test (shop level)
VSI only
RA VSI only
TA/RA VSI
SECONDARY VERT SPEED VALIDITY INPUT (+28 Vdc):
The VSI/TRA receives a +28 Vdc signal from an ARINC 575 or 565 air data computer
indicating its valid operation. An “open” at this pin indicates an invalid vertical speed
signal from the ADC. This pin is only used when pins (1, 2, 3) or (4, 5, 6, and 16) are
used.
J1--19, 20
VERT SPEED BOOTSTRAP AC OUT: (J1--19 [HIGH], J1--20 [LO])
This output repeats the ARINC 565 input signals (26 V 400 Hz reference and signal)
available on the primary input when this input has been selected :
-- 26 V 400 Hz reference
The voltage available on the output (26 Vac Bootstrap ref. output) is the same as that
available on the 26 Vac 400 Hz reference (hot) of the ARINC 565 primary input, the
common reference being the cold of the 26 Vac primary ref. input.
-- Output signal (vertical speed bootstrap AC output) available on two wires (HI and LO).
J1--22
CHASSIS GROUND INPUT:
Connected to aircraft frame. Also used to connect ARINC cable shields to the chassis.
J1--23
115 Vac, 400 HZ POWER INPUT (COMMON):
See pin 40. Connect to aircraft AC ground.
J1--24, 25
J1--26
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15 Feb 2003
REMOTE LIGHT SENSOR INPUT: (J1--24 LOW, J1--25 HIGH)
This input at pins 24 and 25 provides a means of controlling the VSI/TRA back lighting via
a remote light sensor already present in some aircraft (Douglas and Boeing). The
VSI/TRA has its own built--in sensor and therefore a remote light sensor need not be
used in all installations. Program the VSI/TRA for a remote light sensor, as described
under pin 34.
ARINC 429 (A) TCAS TA/RA DATA INPUT:
Traffic and Resolution Advisory data is supplied to the VSI/TRA from the T2CAS
computer unit via this high speed ARINC 429 data bus. Paired with pin 11.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--3. 41--Pin VSI/TRA Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--27
ARINC 429 (A) VERTICAL SPEED NO. 1 INPUT:
This is the primary ARINC 429 input bus to the VSI/TRA. This pin accepts high or low
speed ARINC 429 vertical speed data (Label 212). Its use is determined by the source
select discrete and configuration straps CS0 and CS1 (pins 31, 32, and 33 respectively).
Paired with pin 12.
J1--28
CONFIGURATION STRAP #2 INPUT (NO):
This is the V/S response time selection. A time constant of 3.8 sec with pin 28 open and
of 7.6 sec with pin 28 grounded.
J1--29
TA/RA VALID DISCRETE OUTPUT (NO):
This output discrete indicates the ability of the VSI/TRA to perform as a resolution
advisory and/or a traffic advisory display. If the VSI/TRA fails, this discrete presents an
open. Normal operation causes a ground. This discrete is monitored by the T2CAS
computer unit.
J1--30
ARINC 429 (A) VERTICAL SPEED NO. 2 INPUT:
This is the secondary ARINC 429 input bus to the VSI/TRA. This pin accepts high or low
speed ARINC 429 vertical speed data (Label 212). Its use is determined by the source
select discrete and configuration straps CS0 and CS1 (pins 31, 32 and 33 respectively).
Paired with pin 14.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--3. 41--Pin VSI/TRA Interface Description (cont)
Connector Pin
Designation
J1--31
Functional Description
SOURCE SELECT DISCRETE INPUT (NO):
This discrete input is used in conjunction with configuration straps CS0, CS1 and CS2 to
program the VSI/TRA to accept and use the vertical speed data being supplied. In some
installations, this discrete is connected to a switch in the Flight Deck and is used to select
between primary and secondary ARINC 429 vertical speed inputs. It is hard wired to
configuration strap common if ac or dc analog vertical speed inputs are used. Cycle
power to update to the new configuration.
The following applies: O = Open, G = Ground.
Pin
SS
CS0 CS1
32 33
CS2
34
Note: SS is Source Select Pins 31 or 37.
Definition
ARINC 429 LS (label 212)
ARINC 565 analog AC
ARINC 575 analog DC
PNEUMATIC
ARINC 429 HS (label 365)
ARINC 429 LS (Port # 3)
Reserved (ARNICA 575 dig)
User defined
User defined
”Traffic display only” mode
In those configurations where digital or analog primary or secondary inputs can be
selected, the two source select pins, 31 and 37, are used to select one or other of these
inputs.
• pin 31 for the logic OPEN (primary)/GROUND (secondary)
• pin 37 for the logic OPEN (primary)/+28 Vdc (secondary) in relation to the dc common
reference pin.
Pin
31
37
Input Selected
28V
28V
Primary
Secondary
Secondary
Not Used
J1--32
CONFIGURATION STRAP #0 INPUT (NO):
See pin 31.
J1--33
CONFIGURATION STRAP #1 INPUT (NO):
See pin 31.
4--32
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--3. 41--Pin VSI/TRA Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--34
CONFIGURATION STRAP #2 INPUT (NO):
See pin 31.
J1--35
CONFIGURATION STRAP #4 INPUT (NO):
See pin 17.
J1--36
SECONDARY ANALOG AC INPUT (LO):
ARINC 565 ADC
J1--37
SECONDARY SOURCE SELECT DISCRETE INPUT (NO):
See pin 31.
J1--38
VERTICAL SPEED VALID DISCRETE OUTPUT (NO):
This validity discrete is representative of the operation of the vertical speed channel.
The state of this discrete corresponds to an invalid state (OPEN) if :
· the indicator is not energized
· the indicator is in the initialization phase on power up
· the vertical speed failure warning flag is in view (case of internal or external failures)
· the self test/display test pin is activated.
Definition of the OPEN state : impedance in relation to the dc common greater than 100k
Ohms (open collector with an applicable voltage of +14 Vdc to +32 Vdc).
A valid state is indicated by either:
1) a GROUND state characterized by a voltage of less than 3.5 Vdc in relation to dc
commons with a maximum current of 20 mA, when the following types of vertical
speed are selected :
-- pneumatic input
-- digital inputs (per ARINC 429 HS or LS and digital ARINC 575).
or
2) a dc output voltage (+ 28 Vdc nominal), the minimum value of which is equal to VIN -(2 + 200 x I), where VIN is the greater of the primary vertical speed and secondary
vertical speed voltages available and I the output current expressed in amps (0.02 A
max.). This type of signal is present on the output when the following types of vertical
speed are selected :
-- AC analogue input (ARINC 565)
-- DC analogue input (ARINC 575).
J1--39
DC GROUND INPUT:
To be connected to aircraft dc Ground.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--3. 41--Pin VSI/TRA Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--40
115 Vac, 400 Hz POWER INPUT (HI):
This pin, along with its return line (pin 23) supplies power to the VSI/TRA. Connect power
through a 1 Amp circuit breaker.
J1--41
SELF--TEST/DISPLAY TEST:
This input functions on an OPEN/GROUND logic (in relation to dc common) and in
parallel with the TEST Push button located on the front face of the indicator (for
maintenance purposes only).
When this input is activated and maintained in the GROUND state, the indicator performs
a self test procedure which results in:
-- The display of a representative test pattern within 3 seconds.
-- The transmission of an OPEN (invalid) state on the TCAS Display Status Discrete
Output for the duration of the test.
4--34
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description
Connector Pin
Designation
Functional Description
P1A--1A THRU ENCODING ALTIMETER #2 INPUTS:
P1A--1K, AND These Mode C pulse discrete inputs allow for altitude inputs from an encoding altimeter
P1A--2K
that contains a discrete 11 wire interface. The standards for this interface are defined in
ARINC Characteristic 572, “Air Traffic Control Transponder”. The inputs use ground/open
logic levels.
NOTE: Two encoding altimeters are required if the transponder is used with TCAS.
P1A--2A, 2B
ARINC 429 ADLP TO COMM A/B BUS INPUT: [P1A--2A (A), P1A--2B (B)]
Four high speed ARINC 429 busses (100k bits/second nominal) are provided for
interfacing to a Mode S Airborne Data Link Processor (ADLP). The COMM A/B input and
output busses are used for the transfer of standard length messages to and from the
ADLP. The COMM C/D input and output busses are used for the transfer of extended
length messages (ELM) to and from the ADLP. The standard for this interface is defined
in ARINC Characteristic 718, “Air Control Transponder (ATCRBS/Mode S)”.
P1A--2C, 2D
ARINC 429 ADLP TO COMM C/D BUS INPUT: [P1A--2C (A), P1A--2D (B)]
See pins P1A--2A, 2B
P1A--2E, 2F
ARINC 429 COMM C/D TO ADLP BUS OUTPUT: [P1A--2E (A), P1A--2F (B)]
See pins P1A--2A, 2B
P1A--3B
XPDR FAIL DISCRETE OUTPUT #2:
This discrete output is set to annunciate an internal transponder failure or the Mode S
address is illegal (All 0’s or 1’s). A ground logic threshold (< +3.0 Vdc) is output when the
transponder is operating normally, and an open logic threshold (resistance >100k Ohms
to unit ground) when a failure has occurred. The output is capable of sinking 200 mA of
current. Connect this pin to the Control Panel XPDR FAIL #2 input.
P1A--3C,
P1A--3D,
P1A--3E,
P1A--3F
CABLE DELAY PROGRAM INPUTS:
The Cable Delay Program Inputs are used to compensate for the difference in
propagation delays in the transponder due to antenna transmission line length differences
between the top and bottom antennas. The inputs use ground/open logic levels. The
Cable Delay Program Common (pin P1A--3F) can be used to supply a ground.
Program Pin
Differential
Transponder
P1A--3C P1A--3D
P1A--3E Delay
Adjustment
Open
Open
Open
Open
Open
Open
Ground
Ground
Open
Ground
Open
Ground
0--50 nsec
51--150 nsec
151--250 nsec
251--350 nsec
No Change
Add Delay to Top Channel
Add Delay to Top Channel
Add Delay to Top Channel
Ground
Open
Open
0--50 nsec
No Change
Ground
Open
Ground
51--150 nsec
Add Delay to Bottom Channel
Ground
Ground
Open
151--250 nsec
Add Delay to Bottom Channel
Ground
Ground
Ground
251--350 nsec
Add Delay to Bottom Channel
The differential delay column is the difference in the round trip cable delay between the
top and bottom antenna cables. The differential delay can be calculated as follows:
[Top length in feet -- Bottom length in feet] X [Characteristic Delay (nsec/foot)] X 2.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
P1A--3G,
P1A--3H,
P1A--3J
Functional Description
SDI PROGRAM INPUTS:
The SDI program inputs are used to identify the system number in the installation. The
inputs use ground/open logic levels. The SDI Common (pin P1A--3J) can be used to
supply a ground.
Program Pin
P1A--3G
P1A--3H
Definition
Open
Open
Ground
Ground
Open
Ground
Open
Ground
Not Applicable (SDI = 00)
LRU System #1 (SDI = 01)
LRU System #2 (SDI = 10)
LRU System #3 (SDI = 11)
P1A--4A
THRU
P1A--4J
ARINC 565 ANALOG AIR DATA COMPUTER #1 INPUTS:
These input pins allow for altitude information from an Analog Synchro Altitude Interface
to be connected to the transponder. The standards for this interface are defined in
ARINC 565, “Subsonic Air Data System”.
P1A--5A,
P1A--5B,
P1A--5C,
P1A--5D
MAXIMUM TRUE AIRSPEED PROGRAM INPUTS:
The Maximum True Airspeed inputs are used for strapping the maximum cruise airspeed
capability of the aircraft. The inputs use ground/open logic levels. The Max True
Airspeed Common (pin P1A--5D) can be used to supply a ground.
Program Pin
P1A--5A P1A--5B P1A--5C
Definition
Open
Ground
Open
Ground
Open
Ground
Open
Ground
Open
Open
Ground
Ground
Open
Open
Ground
Ground
Open
Open
Open
Open
Ground
Ground
Ground
Ground
No Maximum Airspeed Available
Maximum Airspeed ≤75 Knots
Maximum Airspeed >75 and ≤150 Knots
Maximum Airspeed >150 and ≤300 Knots
Maximum Airspeed >300 and ≤600 Knots
Maximum Airspeed >600 and ≤1200 Knots
Maximum Airspeed >1200 Knots
Not Assigned
P1A--5E, 5F
ARINC 429 TX COORDINATION BUS INPUT: (P1A--5E [A], P1A--5F [B])
Two high speed ARINC 429 busses (100k bits/second nominal) are provided to interface
between the transponder and a TCAS computer unit. The standards for this interface are
defined in ARINC Characteristic 735A, “Traffic Alert and Collision Avoidance System”.
P1A--5G, 5H
ARINC 429 XT COORDINATION BUS OUTPUT: (P1A--5G [A], P1A--5H [B])
See pins P1A--5E, 5F.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
P1A--5J
AIR / GROUND #2 DISCRETE INPUT:
This pin and AIR / GROUND #1 Discrete Input (pin P1A--5K) provide a method for the
transponder to automatically determine the Air/Ground status of the aircraft. The status is
used in replies to Mode S interrogations and to inhibit replies to certain types of
interrogations. Both inputs use ground/open logic, where a Ground specifies an “On the
Ground” condition and an Open specifies an “In the Air” condition.
When this pin is connected to the Air/Ground Relay (Squat Switch), the transponder will
not reply to ATCRBS, ATCRBS/Mode S All Call, or Mode S All Call when the input is set
for “On the Ground”. This input should be connected to the Air/Ground Relay for normal
operation.
P1A--5K
AIR / GROUND #1 DISCRETE INPUT:
See pin P1A--5J.
When this pin is connected to the Air/Ground Relay (Squat Switch), the transponder
replies to all types of interrogations irregardless of the state of the input. This input allows
the transponder to reply during a ramp test.
P1A--6A, 6B
ARINC 429 FLIGHT IDENTIFICATION BUS INPUT: (P1A--6A [A], P1A--6B [B])
This differential pair input is a low speed ARINC 429 bus (12.5k bits/second nominal) that
accepts a flight identification that is contained within four ARINC 429 data words (labels
233, 234, 235 and 236).
P1A--6C, 6D
ARINC 615 AIRBORNE DATA LOADER BUS INPUT: (P1A--6C [A], P1A--6D [B])
The Airborne Data Loader interface consists of two high speed ARINC 429 busses (100k
bits/second nominal) and a ground/open logic discrete (pin P1A--6G). The interface
allows for operational transponder software to be loaded into the unit through an onboard
data loader. The standards for this interface are defined in ARINC 615 “Airborne
Computer High Speed Data Loader”.
P1A--6E, 6F
ARINC 615 AIRBORNE DATA LOADER BUS OUTPUT: (P1A--6E [A], P1A--6F [B])
See pins P1A--6C, 6D
P1A--6G
P1A--6H, 6J
P1A--6K
ADL INPUT LINK A DISCRETE INPUT:
See pins P1A--6C, 6D
ARINC 575 AIR DATA COMPUTER #1 INPUT: (P1A--6H [A], P1A--6J [B])
This differential pair input is a low speed ARINC 575 bus (12.5k bits/second nominal) that
can be used to input altitude information from an ARINC 575 Air Data System. The
standards for this interface are defined in ARINC Characteristic 575, “Subsonic Air Data
System (Digital) DADS”.
SINGLE / DUAL ANTENNA PROGRAM INPUT:
This pin allows for installation of the transponder in a system with a single bottom
mounted antenna or dual top and bottom mounted antennas. The input uses
ground/open logic as follows:
Ground = Single Bottom Mounted Antenna Configuration
Open = Diversity Antenna Configuration
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
P1A--7A, 7B
Functional Description
ARINC 429 CONTROL DATA PORT A BUS INPUT: (P1A--7A [A], P1A--7B [B])
The control panel data can be input into the transponder on either of two low speed
ARINC 429 busses. (Ports A and B). The control data is contained in labels 013, 015,
and 016. The port is selected by the CONTROL DATA PORT SELECT Discrete Input
(pin PIA--7D).
P1A--7D
CONTROL DATA PORT SELECT INPUT:
See pins P1A--7A, 7B.
This discrete input is used to select which port is used to input control data to the
transponder. This input uses a ground/open logic as follows:
Ground Specifies Port A
Open
Specifies Port B
P1A--7E, 7F
ARINC 429 CONTROL DATA PORT B BUS INPUT: (P1A--7E [A], P1A--7F [B])
See pins P1A--7A, 7B.
P1A--7G
STANDBY / ON DISCRETE INPUT:
This discrete input is connected to the Control Panel STANDBY/ON output. The input
selects the active or standby status of the transponder. A ground causes the transponder
to be in standby, and an open causes the transponder to be active.
P1A--7H, 7J
ARINC 429 ADC #1 BUS INPUT: (P1A--7H [A], P1A--7J [B])
The altitude information for the transponder can be obtained from an ARINC 706 Air Data
System through two low speed ARINC 429 data busses. The standards for this interface
are defined in ARINC Characteristic 706, “Mark 5 Subsonic Air Data System”.
This differential pair input is a low speed ARINC 429 bus that inputs uncorrected pressure
altitude (ARINC label 203) from an altitude source. Also see pins P1B--5A, 5B.
P1A--71
TOP ANTENNA RF INPUT:
RF input from top antenna.
P1B--1A
THRU
P1B--3E
MODE S ADDRESS INPUTS:
The Mode S Address is a unique 24--bit code assigned to each aircraft. Pins P1B--1A
thru P1B--3E are used to program this 24--bit binary number. The inputs must be set
according to this binary number representation. Each binary 1 represents a Grounded pin
and each binary 0 represents an Open pin. Pin P1B--1A represents the most significant
bit (MSB) of the binary number and pin P1B--3D represents the least significant bit (LSB)
of the binary number.
NOTE: An address of all 0’s or all 1’s is an illegal address, and can cause the aircraft to
be invisible to TCAS II equipped aircraft in flight. Never use an illegal address
for an installed system.
P1B--3H
FUNCTIONAL TEST DISCRETE INPUT:
This discrete input is used to put the transponder in a functional test mode. The
functional test that is performed by the transponder is equivalent to a test that is initiated
from the control panel. The input uses ground/open logic as follows:
Ground = Initiate Functional Test
Open = Normal Operation
4--38
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
P1B--3J
ALTITUDE COMPARISON FAIL DISCRETE OUTPUT:
This discrete output annunciates a comparison failure in the altitude data for the
transponder if Gillham altitude data is selected. The output annunciates a failure if the
two altitude sources are not within 500 feet.
The output drives a ground logic threshold (voltage of less than +3.0 Vdc) when the
altitude is valid, and an open logic threshold (resistance is greater than 100k Ohms to unit
ground) when a failure has occurred. The output is capable of sinking 200 mA of current.
P1B--3K
XPDR FAIL DISCRETE OUTPUT #1:
This discrete output is set to annunciate an internal transponder failure or that the Mode S
address is illegal (All 0’s or 1’s). The output will source a voltage of greater than +5.0 Vdc
at 100 mA of current when a failure has occurred, and an open circuit (resistance of
greater than 100k Ohms to unit ground) when the transponder is operating normally. The
output contains diode isolation. Connect this pin to the Control Panel XPDR FAIL #1
input.
P1B--4A THRU ENCODING ALTIMETER #1 INPUTS:
P1B--4K, AND First of two Encoding Altimeter interfaces. See pins P1A--1A thru 4K and P1A--2K.
P1B--5K
P1B--5A, 5B
ARINC 429 AIR DATA COMPUTER #2 BUS INPUT: (P1B--5A [A], P1B--5B [B])
Second ARINC 429 Air Data Computer bus input. See pins P1A--7H, 7J.
P1B--5C, 5D
ARINC 575 AIR DATA COMPUTER #2 BUS INPUT: (P1B--5C [A], P1B--5D [B])
Second ARINC 575 Air Data Computer bus input. See pins P1A--6H, 6J.
P1B--5E, 5F
ARINC 429 COMM A/B TO ADLP BUS OUTPUT: (P1B--5E [A], P1B--5F [B])
See pins P1A--2A, 2B.
P1B--5G
ALTITUDE COMPARISON ON / OFF DISCRETE INPUT:
This discrete input is used to enable/disable the Altitude Comparison function. The
Altitude Comparison function is used only if a Gillham altitude source is selected. This pin
uses a ground/open logic as follows:
Ground = Altitude Comparison Enabled
Open = Altitude Comparison Disabled
NOTE: If an altitude source other than Gillham is selected, the input has no function.
P1B--5H
MODE S DATA LINK PROGRAM INPUT:
This program input specifies if the transponder is connected to an Airborne Data Link
Processor (ADLP) Unit. The input uses ground/open logic as follows:
Ground = ADLP is Installed
Open = ADLP is not installed
P1B--5J
ANTENNA BITE PROGRAM INPUT:
This program input specifies if the transponder is to perform a built--in test to the antenna
subsystem. The transponder performs a continuity check of the antenna to make sure it
is not an open circuit. The input uses ground/open logic as follows:
Ground = Enables Antenna Subsystem Test
Open = Disables Antenna Subsystem Test
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
P1B--6A, 6B
ARINC 429 MAINTENANCE DATA BUS INPUT: (P1B--6A [A], P1B--6B [B])
Two low speed ARINC 429 busses (12.5k bits/second nominal) are provided to interface
between the transponder and an onboard maintenance system. The maintenance
computer interface is designed to work with all airframe models and types.
P1B--6C, 6D
ARINC 429 MAINTENANCE DATA BUS OUTPUT: (P1B--6C [A], P1B--6D [B])
See pins P1B--6A, 6B.
P1B--6E
AIR DATA SOURCE SOURCE SELECT DISCRETE INPUT:
The transponder contains dual inputs for all types of altitude sources. This discrete input
specifies which of the two inputs are used to obtain altitude information.
Ground = Altitude Source No. 2
Open = Altitude Source No. 1
P1B--6F,
P1B--6G,
P1B--6H
ALTITUDE TYPE SELECT PROGRAM INPUT:
The Altitude Type Select program pins are used to configure the transponder for the type
of altitude source that is connected to it. The inputs use ground/open logic. The Altitude
Type Select Common (pin P1B--6H) can be used to supply a ground.
Program Pin
P1B--6F
P1B--6G
Definition
Ground
Ground
Open
Open
Ground
Open
Ground
Open
Selects Gillham Altitude Source
Selects ARINC 575 Altitude Source
Selects ARINC 407 Synchro Altitude Source
Selects ARINC 429 Altitude Source
P1B--7A
THRU
P1B--7J
ARINC 565 ANALOG AC AIR DATA COMPUTER #2 INPUTS:
Second ARINC 565 Analog AC Air Data Computer Input. See pins P1A--4A Thru 4J.
P1B--71
BOTTOM ANTENNA RF INPUT:
RF input from bottom antenna.
P1C--1
XPDR 115 Vac INPUT POWER: (H)
This pin along with the XPDR 115 Vac RETURN line (pin P1C--7) provides the 115 Vac
power requirements for the transponder.
NOTE: Only --10XXX thru --54XXX transponders accept 115 Vac, 400 Hz input power.
If the 115 Vac version is used, the power should be connected through a 5 amp
circuit breaker, and the pins for the 28 Vdc input (P1C--10 and P1C--3) should
be left unconnected.
P1C--3
XPDR +28 Vdc RETURN: (L)
See pin P1C--10.
P1C--4
XPDR OFF (NO) INPUT:
This discrete input is used to turn the transponder power supply OFF. It should not be
connected in aircraft installations.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
P1C--6
FAN +28 Vdc OUTPUT: (+)
The 28 Vdc version of the transponder can control an externally mounted +28 Vdc fan to
provide cooling air for the transponder. The Fan +28 Vdc output (P1C--6) should be
connected to the positive input of the fan, and the Fan Return (NO) Output (P1C--9)
should be connected to the negative input of the fan. The output has the capability to
drive a fan that draws up to 200 mA of current. The fan is turned on when the internal
transponder temperature rises above 30 degrees centigrade. In the 115 Vac version of
the transponder, the outputs are not used.
P1C--7
XPDR 115 Vac RETURN: (C)
See pin P1C--1.
P1C--8
SIGNAL GROUND INPUT:
Connect to Aircraft Signal Ground.
P1C--9
FAN RETURN (NO): (--)
See pin P1C--6.
P1C--10
XPDR +28 Vdc INPUT POWER: (H)
This pin along with the +28 Vdc RETURN line (P1C--3) provide the 28 Vdc power
requirements for the transponder.
NOTE: Only --55XXX thru --99XXX transponders accept +28 Vdc input power. If the
+28 Vdc version is used, the power should be connected through an 8 amp
circuit breaker, and the pins for the 115 Vac input (P1C--1 and P1C--7) should
be left unconnected.
P1C--11
CHASSIS GROUND INPUT:
Connect to aircraft frame.
P1C--12,
P1C--13
MUTUAL SUPPRESSION BUS INPUT/OUTPUT:
L--Band suppression coax must be RG--142 or equivalent coaxial cable. P1C--12 and
P1C--13 are connected internally. Connection to only one pin is required.
The Interface descriptions that follow are for the 53--pin ARINC 615 Portable Data Loader connector
J1 mounted on the front panel of the transponder. These descriptions are used to make up the
cable that is used to interface between the transponder and the ARINC 615 Data Loader or a
RS--232 PC Serial Port.
J1--1, 2
J1--5
XPDR ARINC 429 PDL BUS INPUT: (J1--1 [A], J1--2 [B])
This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal) is
used to input data from the data loader to the transponder. The standards for this
interface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”.
These pins should be connected to pins 1 and 2 of the PDL cable interface.
INPUT BUS SHIELD:
The shields from the input bus (J1--1, 2) should be connected to this pin.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--8, 9
XPDR ARINC 429 PDL BUS OUTPUT: (J1--8 [A], J1--9 [B])
This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)
used to output data from the transponder to the data loader. The standards for this
interface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”.
These pins should be connected to pins 8 and 9 of the PDL cable interface.
J1--16
OUTPUT BUS SHIELD:
The shields from the output bus (J1--8, 9) should be connected to this pin.
J1--18
PDL LINK A:
Connect this pin to pin 18 of the PDL cable interface.
J1--19
PDL LINK B:
Connect this pin to pin 19 of the PDL cable interface.
J1--20, 22
115 Vac POWER OUTPUT: (J1--20 [H], J1--22 [C])
These power output pins provide the 115 Vac operating power for the data loader.
NOTE: Only the 115 Vac version transponders provide this output. If a +28 Vdc version
transponder is installed, either the data loader must be able to operate from +28
Vdc or the data loader 115 Vac input power must be connected to a source
external to the transponder.
The 115 Vac (H) and 115 Vac (C) should be shielded or twisted and shielded with an
insulating jacket over the shield. The shield should be connected to chassis ground (pin
21).
J1--21
J1--37, 38
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15 Feb 2003
CHASSIS GROUND:
Connect 115 Vac power shields to this pin.
+28 Vdc POWER OUTPUT: (J1--37 [HI], J1--38 [LO])
These power output pins provide the +28 Vdc operating power for the data loader. These
pins are used only if the data loader operates from +28 Vdc.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--4. XS--950 Data Link Transponder Interface Description (cont)
Connector Pin
Designation
J1--40
J1--41
J1--48, 49
Functional Description
RS--232 PDL INPUT:
RS--232 PDL OUTPUT
LOGIC COMMON (Gnd)
These pins would be connected to an RS--232 Serial Port as follows. Most RS--232
Serial Ports use either a 9 pin RS--232 (COM) connector or a 25 pin RS--232 (COM)
connector.
ARINC 615
PC COM1 OR COM2
PC COM1 OR COM2
CONNECTOR PIN
9 PIN CONNECTOR
25 PIN CONNECTOR
40
41
48 or 49
NOTE:
J1--50
J1--51
J1--52
J1--53
PC TX (pin 3)
PC RX (pin 2)
Ground (pin 5)
PC TX (pin 2)
PC RX (pin 3)
Ground (pin 7)
When using a RS--232 interface, transponder pin J1--18 (Link A) and pin J1--19
(Link B) must be connected (tied together) to do a software upload. The pins
should be open to verify the software status.
PDL FUNCTION DISCRETE #1 INPUT:
PDL FUNCTION DISCRETE #2 INPUT:
PDL FUNCTION DISCRETE #3 INPUT:
PDL FUNCTION DISCRETE #4 INPUT:
These pins are used to receive discrete functional information from the data loader.
These pins should be connected to the PDL cable interface.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description
Connector Pin
Designation
J1--1, 2
Functional Description
XPDR +28 Vdc FAN PWR and +28Vdc FAN RTN: (J1--1 LOW, J1--2 HIGH)
The fan discrete outputs supply a switched, filtered +28 Vdc for a dc fan. The RCZ--852
Transponder has an internal fan built into the unit, so external cooling is not required.
Pins J1--1 and J1--2 should not be connected.
J1--3
MUTUAL SUPPRESSION BUS I/O:
This bus is a single conductor, shielded bidirectional line that connects to all aircraft
L--Band equipment. It is used to desensitize the associated receiver inputs while
transmitting.
J1--7
XPDR +28 Vdc RTN:
See pins 8, 9.
J1--8
J1--9
XPDR +28 Vdc PWR:
These pins along with there return lines (J1--7 and J1--20) provide the +28 Volt power
requirements for the transponder.
J1--11
PROGRAM ENABLE INPUT:
Bench test function. Do not connect this pin in aircraft installations.
J1--12
XPDR RS232 TX OUTPUT:
Bench test function. Do not connect this pin in aircraft installations.
J1--17, J1--18
J1--19, J1--21
DC GROUND INPUT:
To be connected to aircraft dc ground.
J1--23
XPDR VALID (PO) OUTPUT:
This discrete outputs the status of the transponder continuous monitor tests. It is the
same as the XPDR VALID (NO) output (J1--100) except the discrete is a positive/open
logic. A +28 Vdc (200 mA maximum) is provided when the transponder is operational
and an active transponder mode is selected. An Open (>100k Ohms resistance to
ground) output is provided when the transponder has failed or the standby mode is
selected.
J1--24
XPDR RS232 RX INPUT:
Bench test function. Do not connect this pin in aircraft installations.
J1--25
PROGRAM +15 Vdc OUTPUT:
Bench test function. Do not connect this pin in aircraft installations.
J1--26, 27
XPDR TO TCAS ARINC 429 BUS OUTPUT: (J1--26 [A], J1--27 [B])
This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)
that sends data to the TCAS computer unit. The data bus conforms to the ARINC 718
and ARINC 735A standards for TCAS to transponder interface.
J1--28, 29
XPDR TO DLP A/B ARINC 429 BUS OUTPUT: (J1--28 [A], J1--29[B])
This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)
that sends data to an airborne data link processor (ADLP) system. The data bus is used
to transfer COMM--A and COMM--B messages between the two systems and conforms to
the ARINC 718 standard for ADLP to transponder interface.
4--44
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--30, 31
XPDR TO DLP C/D ARINC 429 BUS OUTPUT: (J1--30 [A], J1--31 [B])
This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)
that sends data to an airborne data link processor (ADLP) system. The data bus is used
to transfer COMM--C and COMM--D messages between the two systems and conforms
to the ARINC 718 standard for ADLP to transponder interface.
J1--32, 33
ADC1 TO XPDR ARINC 429/575 BUS INPUT: (J1--32 [A], J1--33 [B])
This differential pair input is a low speed ARINC 429 or 575 bus that inputs uncorrected
pressure altitude (ARINC label 203) from an altitude source. The input accepts either
ARINC 429 or 575 data format, which is selected by the altitude source straps (W33,
W34) on the Strap Assembly. The ALT SRC SEL2 (NO) discrete, pin 60, selects either
ADC1 or ADC2.
J1--34, 35
CTL1 TO XPDR ARINC 429 BUS INPUT: (J1--34 [A], J1--35 [B])
The transponder can receive data from the control panel(s) on the CTL1 TO XPDR and
CTL2 TO XPDR data busses. The bus used, is selected by the CTL SRC SEL1 (NO)
DISCRETE. See pin 61. The data bus not selected will not be processed. These
differential pair inputs are low speed ARINC 429 busses (12.5k bits/second nominal) that
transmits tuning information from the control panel to the transponder. The transponder
expects to receive ARINC labels 016 and 031 at an update rate of 100 to 200
milliseconds. Also see CTL2 TO XPDR ARINC 429 bus input (pins 48 and 49).
J1--40, 41
TCAS TO XPDR ARINC 429 BUS INPUT: (J1--40 [A], J1--41 [B])
This differential pair input is a high speed ARINC 429 bus (100k bit/second nominal) that
receives data from a T2CAS computer unit. The data bus conforms to the ARINC 718
and ARINC 735A standards for TCAS to transponder interface.
J1--42, 43
DLP A/B TO XPDR ARINC 429 BUS INPUT: (J1--42 [A], J1--43 [B])
This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal) that
receives data from an airborne data link processor (ADLP) system. The data bus is used
to transfer COMM--A and COMM--B messages between the two systems and conforms to
the ARINC 718 standard for ADLP to transponder interface.
J1--44, 45
DLP C/D TO XPDR ARINC 429 BUS INPUT: (J1--44 [A], J1--45 [B])
This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal) that
receives data from an airborne data link processor (ADLP) system. The data bus is used
to transfer COMM--C and COMM--D messages between the two systems and conforms
to the ARINC 718 standard for ADLP to transponder interface.
J1--46, 47
ADC2 TO XPDR ARINC 429/575 BUS INPUT: (J1--46 [A], J1--47 [B])
See pins J1--32, 33
J1--48, 49
CTL2 TO XPDR ARINC 429 BUS INPUT: (J1--48 [A], J1--49 [B])
See pins J1--34, 35
J1--50, 51
XPDR TO CTL ARINC 429 BUS OUTPUT: (J1--50 [A], J1--51 [B])
This differential pair output is a low speed ARINC 429 bus (12.5k bits/second) that
transmits control panel input data back to the control panel for verification purposes.
These output pins are connected only on some Collins control panels that require
feedback from the transponder to make sure it is operating properly.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)
Connector Pin
Designation
J1--53 thru 58,
J1--67 thru 71
Functional Description
ENCODING ALTIMETER NO.1 ELEVEN BIT INPUT:
Transponder input from Encoding Altimeter No. 1. These eleven lines from the altitude
encoder comprise an 11--bit word representative of the aircraft’s uncorrected pressure
altitude.
J1--59
ALT COMP ENA (NO) DISCRETE INPUT:
This discrete input enables or disables altitude comparison when dual Gillham altitude
sources are selected via the ALTITUDE SOURCE strap. If comparison is enabled (J1--59
Grounded), the two altitude sources (ENC ALT1 and ENC ALT2) are compared, and are
considered valid if they are within 500 feet. If the altitude comparison is enabled and it
fails, the altitude data is considered invalid in Mode S replies and altitude data sent to
TCAS. If comparison is disabled (J1--59 Open), only the selected altitude source is used.
This discrete has no effect if ARINC 429 or 575 altitude sources are used.
NOTE: For installations with TCAS that use Gillham encoding altimeter sources, two
encoding altimeter sources must be used, and pin J1--59 must be enabled
(Grounded).
J1--60
ALT SRC SEL2 (NO) DISCRETE INPUT:
This discrete input allows selection of one of two altitude sources. An Open causes the
transponder to use altitude source No.1, and a Ground causes the transponder to use
altitude source No.2. The altitude data sent to TCAS and used for transponder replies is
derived from the selected source.
J1--61
CTL SRC SEL1 (NO) DISCRETE INPUT:
This discrete input is used to select one of two ARINC 429 control tuning ports. A
Ground on this pin causes the transponder to use CTL1 TO XPDR bus for tuning data,
and an Open causes the transponder to use CTL2 TO XPDR bus for tuning data. The
input is used only when the transponder tuning source is an ARINC 429 source in a
stand--alone transponder system. When an RSB tuning source is used, the input is
ignored.
J1--64, 65
FMS TO XPDR ARINC 429 BUS INPUT: (J1--64 [A], J1--65 [B])
This differential pair input is a low speed ARINC 429 bus (12.5k bits/second nominal) that
receives basic transponder control data (label 031) and AIS flight ID (labels 233, 234,
235, and 236) from a Flight Management System (FMS).
J1--72
XPDR STANDBY (NO) INPUT:
This discrete input is connected to the Control Panel STANDBY/ON output. The input
selects the active or standby status of the transponder. A ground causes the transponder
to be in Standby, and an Open causes the transponder to be active. The input is used
only when the transponder tuning source is an ARINC 429 source in a stand--alone
transponder system. When an RCB tuning source is used, the input is ignored.
NOTE: If using a Collins CTL--92 Controller, this pin is not used.
4--46
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)
Connector Pin
Designation
J1--73
Functional Description
SQUAT SWITCH 1 (NO) DISCRETE INPUT:
This discrete input is used in conjunction with SQUAT SWITCH 2 discrete input (pin 75).
The squat switch inputs tell the transponder if the aircraft is on the ground or in the air.
The two inputs have different affects on transponder operation, and the status of the two
are combined. SQUAT SWITCH 1 (NO) causes the transponder to indicate the in the air/
on the ground condition in replies to interrogations. SQUAT SWITCH 2 (NO) in addition
to performing the function of SQUAT SWITCH 1 (NO), also inhibits replies to ATCRBS,
ATCRBS/Mode S All--Call, and Mode S All--Call interrogations when the aircraft is “on the
ground”. The air/ground polarity is set by the SQUAT SWITCH POLARITY strap. The
matrix that follows, shows how the discretes affect the transponder operation:
Squat Sw
Polarity
Strap
Squat Switch Inputs
1 (NO)
2 (NO)
Transponder Operation
Air/Ground
ATCRBS/All--Call
Status
Replies
Gnd
Gnd
Gnd
Gnd
Open
Open
Open
Open
Gnd
Gnd
Open
Open
Gnd
Gnd
Open
Open
On Ground
On Ground
On Ground
In Air
In Air
On Ground
On Ground
On Ground
Gnd
Open
Gnd
Open
Gnd
Open
Gnd
Open
Disabled
Enabled
Disabled
Enabled
Enabled
Disabled
Enabled
Disabled
J1--74
XPDR OFF (NO) INPUT:
This discrete input is used to turn the transponder power supply OFF. It should not be
connected in aircraft installations.
J1--75
SQUAT SWITCH 2 (NO) DISCRETE INPUT:
See pin 73.
J1--80 thru 85
J1--94 thru 98
ENCODING ALTIMETER NO. 2 ELEVEN BIT INPUT:
Transponder input from Encoding Altimeter No. 2. These eleven (11) lines from the
altitude encoder comprise an 11--bit word representative of the aircraft altitude.
J1--90
XPDR STRAP +5 Vdc OUTPUT:
Connect Strap Board connector pin W1P1--3 (red wire) to J1--90. This output pin
provides the +5 Vdc input power required by the Strap Assembly.
J1--91
XPDR STRAP CLOCK (N) OUTPUT:
Connect Strap Board connector pin W1P1--6 (blue wire) to J1--91. This output consists of
48 clock pulses that serially shift the system options data out of the Strap Assembly shift
registers.
J1--92
XPDR STRAP LOAD (N) OUTPUT:
Connect Strap Board connector pin W1P1--2 (orange wire) to J1--92. This output is used
to load the system options status into the Strap Assembly shift registers during initial
system power--up.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)
Connector Pin
Designation
Functional Description
J1--93
XPDR STRAP DATA (P) INPUT:
Connect Strap Board connector pin W1P1--7 (white wire) to J1--93. This input receives
the serial data from the Strap Assembly that is used to program the desired system
options and Mode S address.
J1--99
XPDR ACTIVE (NO) OUTPUT:
This discrete output can be connected to an RF relay for systems that use a single
antenna connected to two transponders for the purpose of switching the antenna to the
active transponder. A Ground (200 mA maximum) output is provided when an Active
transponder mode is selected. An Open (>100k Ohms to ground) output is provided
when Standby mode is selected.
J1--100
XPDR VALID (NO) OUTPUT:
This discrete outputs the status of the transponder continuous monitor tests. A Ground
(200 mA maximum) output is provided when the transponder is operational and an active
transponder mode is selected. An Open (>100k Ohms resistance to ground) output is
provided when the transponder has failed or the Standby mode is selected.
This pin should be connected to the Control Panel XPDR FAIL input.
J1--102
ALT VALID (NO) OUTPUT:
This discrete outputs the status of the altitude source when the transponder is in an active
mode and altitude reporting is enabled. A Ground (200 mA maximum) is output when the
selected altitude source is valid and the transponder is in an altitude reporting mode. An
Open (>100k Ohms resistance to ground) output is provided when the selected altitude
source is invalid or the transponder is in Standby or not in an altitude reporting mode.
This pin should be connected to the Control Panel ALT FAIL input if applicable.
J1--103
XPDR STRAP GROUND OUTPUT:
Connect Strap Board connector pin W1P1--4 (black wire) to J1--103. This output is the
return line for the +5 Vdc output. See pin 90.
J1--104
RESERVED FUNCTION:
Connect Strap Board connector pin W1P1--1 (green wire) to J1--104.
J1--105
RESERVED FUNCTION:
Connect Strap Board connector pin W1P1--8 (yellow wire) to J1--105.
4--48
J2
BOTTOM ANTENNA RF INPUT:
RF input signal from bottom antenna.
J3
TOP ANTENNA RF INPUT:
RF input signal from top antenna.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
TAWS/RWS PINOUTS AND PIN DEFINITIONS
3. TAWS/RWS Specifications
The Ground Collision Avoidance Module (GCAM) function performs the core TAWS and
reactive windshear detection processing. Inputs to the GCAM are aircraft state variables,
aircraft performance models, the combined terrain and airport database, aircraft discretes, and
ARINC label busses. The outputs from the GCAM are the TAWS alerts, reactive windshear
(RWS) alerts, and the terrain display buffers.
The TAWS/RWS input data is attained from a variety of aircraft LRUs depending on the
configuration of the specific aircraft. Since the source of the TAWS/RWS input data is
primarily unknown until a Customer Worksheet (Appendix A) and aircraft survey has been
completed, most of the ARINC 600 connector pins are configurable. Once the origin of the
TAWS/RWS input data has been determined an Aircraft Specific Data Base (ASDB) is
generated by ACSS that defines the pin assignments for that specific aircraft. At installation
time, the ASDB is loaded into the aircraft’s Aircraft Personality Module (APM) which then
remains with the aircraft throughout any T2CAS LRU removal/replacements to retain the
aircraft configuration data.
In addition to the configurable pins, the TAWS/RWS also contains some permanent or
non--configurable pin assignments as well as some pin assignments that are shared with the
TCAS functionality.
This section is organized in a generic format to accommodate the dynamic, aircraft dependant
pin assignments. The flow for configurable pin assignments is as follows:
• An aircraft configuration type is determined based on the equipment installed.
• Using the aircraft configuration data, the pin assignments are engineered, assigned and
documented in the ASDB system requirements.
• An Aircraft Configuration Table is then generated in Appendix B of this document that
details the specifics of the equipment installed on the new aircraft (columns) and assigns
an Aircraft Installation Number to the newly identified aircraft installation type (rows).
• The Aircraft Installation Number then references a Table that assigns the TAWS/RWS
signals to an Analog, Discrete or Digital Input/Output number. For example, FMS #1 (Left)
could be assigned Digital Input #2. Table 4--13 of this section would then be referenced to
obtain the specifics (pin numbers, usage, tolerances, etc.) of Digital Input #2.
• If any new aircraft installation data and pinouts match a previously identified aircraft
installation type, then that specific aircraft (identified at a minimum by Customer and aircraft
type) is added to the existing Aircraft Configuration Table.
In addition to providing configurable and non--configurable pinouts, this section also provides
the following:
• Characteristics and tolerances for the generic analog, discrete and digital inputs/outputs.
For example, analog Input #1 must be a 3W or 2W Synchro, be within the
voltage/impedance tolerances defined in Table 4--10 and Table 4--11, and have the signal
characteristics defined in the applicable subsection of the “Programmable Analog Input
Pins” section.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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• A listing of the TAWS/RWS Input Data Signals, LRUs providing those signals, their data
definitions (i.e. Analog signal type, A429 Label, etc.) and the minimum requirements that
must be met by that specific input signal in order for TAWS/RWS to function within
specification.
A. TAWS/RWS Pinout and Pin Descriptions (Non--Configurable)
This section contains the non--configurable pin assignments for the GCAM functionality
(Table 4--6).
Table 4--6. TAWS/RWS Non--Configurable Pinout
Pin
Designation
Signal
Functional Description
Right Top Plug (RTP)
RTP--1A, --1B ARINC 453 Terrain Display Output No. 1:
(RTP--1A [A], RTP--1B [B])
A453 Output
RTP--1E, --1F ARINC 453 Terrain Display Output No. 2:
(RTP--1E [A], RTP--1F [B])
A453 Output
RTP--8G, --8H Glide Slope Low Level Deviation No. 1:
(RTP--8G [+], RTP--8H [--])
Analog ILS Input
RTP--8J, --8K Localizer Low Level Deviation No. 1:
(RTP--8J [+], RTP--8K [--])
Analog ILS Input
RTP--9C, --9D Glide Slope Low Level Deviation No. 2:
(RTP--9C [+], RTP--9D [--])
Analog ILS Input
RTP--9E, --9F Localizer Low Level Deviation No. 2:
(RTP--9E [+], RTP--9F [--])
Analog ILS Input
RTP--14E
RTP--14F,
--14G, --14H
RTP--14J
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dc Total Air Temperature Return
Analog dc TAT Return
dc Altitude Rate A575/595:
(RTP--14F [Signal], --14G [Ref+], --14H [Ref--])
Analog dc A575/595
dc Output Reference +5 Vdc:
The T2CAS provides a +5 Vdc
precision reference output as a
reference voltage for analog
sensors which provide a
ratio--metric output. In most
installations the reference
voltage and the signal voltage
are monitored so that the
tolerance of the reference output
is not critical. This is the
preferred method and eliminates
issues such as ground
differentials in aircraft
installations.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)
Pin
Designation
Signal
Functional Description
RTP--14K
dc Output Reference Return:
This is the Analog Reference
Return for the +5 Vdc Output
Reference voltage on pin
RTP--14J. Hence, the output
voltage is measured between the
Analog Reference +5 Vdc output
and Analog Reference Return
output.
RTP--15A
Audio Output -- 8Ω (H)
The 8Ω analog outputs are used
to drive a speaker in the aircraft
for the annunciation of aural
alerts. The TCAS has it’s own
audio output, and TAWS and
RWS functions share an audio
output. The TCAS and
TAWS/RWS outputs are
independent and separately
controlled.
RTP--15B
Audio Output -- 600Ω (H)
The 600Ω analog outputs are
used to drive an intercom or
headset in the aircraft for the
annunciation of aural alerts. The
TCAS has it’s own audio output,
and TAWS and RWS functions
share an audio output. The
TCAS and TAWS/RWS outputs
are independent and separately
controlled.
RTP--15C
Audio Output -- 8Ω (L) / 600Ω (L)
This is the Ground return for
both the 8Ω and 600Ω Audio
outputs (RTP--15A and --15B
respectfully).
RTP--15D
APM Power
This is the +12 Vdc power
source for the Airplane
Personality Module.
RTP--15E
APM Return
This is the Ground return for
+12 Vdc APM power source.
See pin RTP--15D
RTP--15F
APM Clock
This the APM Clock Output
which is used to synchronize
serial output to the APM. The
Clock output frequency is 2.0
MHz + 1% when the APM is
being accessed and is set to a
logic 0 (not toggling) when the
APM is not being accessed.
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Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)
Pin
Designation
Signal
Functional Description
RTP--15G
APM Serial Data Input:
This is the Serial Data Output
from T2CAS to the APM Serial
Data Input. APM Enable
(RTP--15J) and APM Write
Enable (RTP--15K) must be
enabled before data can be
written to the APM.
RTP--15H
APM Serial Data Output
This is the Serial Data Input to
T2CAS from the APM Serial
Data Output. APM Enable
(RTP--15J) must be enabled
before data can be read from the
APM.
RTP--15J
APM Enable No. 1
This pin is used to Enable
Read/Write access to the APM.
An APM Enable Output logic of 1
disables Read/Write access to
the APM and a logic 0 enables
APM Read/Write access. This
pin is used in conjunction with
pins RTP--15G (APM serial
output) and RTP--15H (APM
serial input).
RTP--15K
APM Write Enable No. 1
This pin is used to Enable Write
access to the APM. An APM
Write Enable Output logic of 1
disables Write access to the
APM and a logic 0 enables APM
Write access. This pin is used in
conjunction with pin RTP--15G
(APM serial output).
Right Middle Plug (RMP)
RMP--2H, --2J Radio Altitude ARINC 552/552A #1
(RMP--2H [+], RMP--2J [--])
RMP--2K
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Radio Altitude Valid Discrete Input #1
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Analog Rad Alt Input
+28 Vdc Disc Input. Used with
Analog Rad Alt Input #1
(RMP--2H, --2J).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)
Pin
Designation
Signal
Functional Description
RMP--5K
Air Ground Discrete Input
(Weight--On--Wheels)
This discrete input to the T2CAS
computer unit indicates the
status of the Air/Ground or
Weight--On--Wheels (WOW)
switch. TCAS filters this input to
make sure it remains in a steady
state a minimum of 4 seconds
before an Air/Ground transition
is recorded. An open indicates
the aircraft is airborne and a
ground indicates the aircraft is
on the ground.
Inputs should be diode isolated
from each other.
RMP--9C,
RMP--9D
GPS Data A429 Output
(RMP--9C [A], RMP--9D [B])
A429 Output H/L. Signal is
reserved on TT--950 and
TT--951 models (units without
GPS).
RMP--9E, --9F GPS Time Mark RS--422 Input/Output
(RMP--9E [A], RMP--9F [B])
Signals are GPS Time Mark
Inputs on TT--950 and TT--951
models (units without GPS).
Signals are GPS Time Mark
Outputs on TT--952 (unit with
GPS).
CD General Purpose A429 Output #1
(RMP--9G [A], RMP--9H [B])
A429 Output H/L. Signals are
reserved for TCAS functions,
however the ARINC 429 output
busses are internally connected
and generated by the A6 TAWS
CCA.
RMP--9J, --9K CD General Purpose A429 Output #2
(RMP--9J [A], RMP--9K [B])
A429 Output H/L. Signals are
reserved for TCAS functions,
however the ARINC 429 output
busses are internally connected
and generated by the A6 TAWS
CCA.
RMP--9G,
--9H
RMP--13F
Landing Gear Discrete Input
GND Disc Input
RMP--13H,
RMP--13J
Radio Altitude A429 Input #1
(RMP--13H [A], RMP--13J [B])
A429 Input H/L. Signals are
used by TCAS and TAWS/RWS
functions
RMP--14K
Accelerometer Self Test Output
Accelerometer Test Output
RMP--15G
Pitch Limit Indicator Output #1 (Reserved)
Pitch Limit Output
RMP--15H
Pitch Limit Indicator Output #2 (Reserved)
Pitch Limit Output
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)
Pin
Designation
Signal
Functional Description
Right Bottom Plug (RBP)
RBP--1E, --1F Computer Power Output
(RMP--1E [+], RMP--1F [--])
RBP--1G
Radio Altitude Valid Discrete Input #3
RBP--3A, --3B Radio Altitude ARINC 552/552A #2
(RBP--3A [+], RBP--3B [--])
RBP--3C
Radio Altitude Valid Discrete Input #2
RBP--3D, --3E Radio Altitude A429 Input #2
(RBP--3D [A], RBP--3E [B])
Power Output (+24V)
+ 28 Vdc Disc Input. Used with
Analog Rad Alt Input #3
(RBP--3F, --3G).
Analog Rad Alt Input.
+28 Vdc Disc Input. Used with
Analog Rad Alt Input #2
(RBP--3A, --3B).
A429 Input H/L. Signals are
used by TCAS and TAWS
functions.
Radio Altitude ARINC 552/552A #3
(RBP--3F [+], RBP--3G [--])
Analog Rad Alt Input.
RBP--10A
JTAG Test Bus -- TCK Input
Test JTAG Bus.
RBP--10D
JTAG Test Bus -- TDI Input
Test JTAG Bus.
RBP--10E
JTAG Test Bus -- TDO Output
Test JTAG Bus.
RBP--10F
JTAG Test Bus -- TMS Output
Test JTAG Bus.
RBP--10G
Reserved JTAG Test Bus -- TRST Output
Test JTAG Bus.
RBP--3F, 3G
B. TAWS/RWS Data Configuration
(1) ASDB
The ASDB is a field loadable database that customizes the T2CAS operation for a
specific aircraft. The ASDB defines the Input/Output definition for the specific aircraft
type, the aircraft climb performance data to support of the TAWS functionality, and
the windshear algorithm coefficient data. The ASDB file is produced with a unique
part number and can be uploaded to the APM via the RS--232 port or from a
Compact Flash card.
The ASDB I/O Database contains specific information needed to perform the I/O
functionality for the specific aircraft type. The I/O tables define the following types of
information for processing system inputs and outputs:
• Physical mapping between external systems and T2CAS inputs and outputs.
Example, GPS #1 is connected to ARINC 429 Input Bus #5.
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• Types of data or information which is processed by the input or generated by the
output. Example: GPS#1 has the following ARINC 429 labels: 100, 101, etc..
• Input or output timing characteristics such as time--out periods or output rates.
Example: Label 100 must be received every 2 seconds for it to be valid.
• Data processing characteristics which define specific types of processing which
may be performed on each input or output. This includes an example of the
following types of options:
-- Method of storage (single or ping--pong buffer)
-- Digital filter option (low--pass filter received data with a specified cut--off
frequency based on parameters in the tables)
-- Extrapolation option (extrapolate data at a given interval based on previous
samples received)
-- Sequence number option (example, process 310 Latitude and 311 Longitude
as a pair)
-- Push--button option (look for a transition from 0 to 1 in the data)
• Conversion code and parameters which specify how to process the data.
Examples: 1) Decode Label 310 as a BNR (binary) number with a MSB of 90
degrees. 2) Multiply analog radio altitude voltage by a parameter (scale factor) to
get feet.
• Non--standard conversion parameters. The conversion code in 5) provides a
standard set of conversion operations which can handle many types of inputs and
outputs. However for more complex types of conversions, the non--standard
conversion allows for a number of operations to be performed on the data.
Operations which may be performed include mathematical, comparison and
branching.
• A parameter which is used to determine the location in RAM where the input data
is stored after processing, or data is read prior to output. This allows I/O data to
be mapped into the correct memory locations where GCAM can access it.
(2) APM
The T2CAS uses an Airplane Personality Module (APM) to hold aircraft specific
configuration data for TAWS and RWS functions. The APM is used in place of
program pin inputs to provide system configuration. The APM is in an ARINC 607
Type II form factor, and is mounted to the aircraft as part of the installation. It retains
configuration data if a T2CAS LRU is removed and replaced with a new LRU serial
number.
The APM contains two types of data:
• Aircraft Type Data
• Installation Option Data
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The aircraft type data is produced by ACSS, and contains data that is specific to
each particular aircraft type. It contains performance data for that aircraft which is
used by TAWS and Windshear functions. It also contains I/O configuration data for
the aircraft that defines and configures the interfaces to the aircraft system. For each
aircraft type, a unique Aircraft Type Data file is produced by ACSS that has a unique
part number.
The Installation Option data replaces the function of program pin (strap) inputs, and
allows the installer to customize the operation of the unit at the time of installation.
Types of functions that can be configured include display options, discrete output
options, altitude callout options, aural annunciation volume control, and other options.
A complete list of Operator Selectable Options is contained in Table 4--7 and
Table 4--8.
The programming of the APM includes the Aircraft Type Data and Installation Option
Data, and is accomplished through the RS--232 port on the PDL connector through a
Laptop PC, or a Compact Flash Card. The APM data file that contains both types of
data is generated on a PC with the EDDIT software tool and allows the selection of
the aircraft type and installation options for that aircraft type. The EDDIT tool builds a
file that contains a cyclical redundancy check (CRC) field around the APM data. With
a blank APM installed in the aircraft, the file can be uploaded to the T2CAS unit over
the RS--232 port or through a Compact Flash card. The T2CAS will then program the
APM.
Verification of the correct APM contents may be accomplished by the RS--232 port or
on the TAWS display. After the APM is programmed, the T2CAS, will output the
Aircraft Type Data part number and the installation option settings to the RS--232
port. Additionally, it will display the APM configuration information on the TAWS
display. The data contained in the APM is recorded as part of the aircraft
configuration data. The software in the T2CAS unit checks the CRC of the data to
insure the file is not corrupted.
Table 4--7. Callout Configuration Items
Configuration Option
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ACD Setting Option
Callout Enable Flag [1]
Enable/Disable Callouts
Bank Angle Callout Enable Flag
Enable/Disable Bank Angle
Callout
DH/MDA Switch Available Flag
Enable/Disable
Decision Height Callout Enable Flag
Enable/Disable DH Callout
Minimums Callout Enable Flag
Enable/Disable Minimums Callout
Minimums--Minimums Callout Enable Flag
Enable/Disable Callout
Approaching Decision Height Callout Enable Flag
Enable/Disable Approaching DH
Callout
Approaching Minimums Callout Enable Flag
Enable/Disable Approaching
Minimums Callout
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--7. Callout Configuration Items(cont)
Configuration Option
ACD Setting Option
1000 ft. Callout Enable Flag
Enable/Disable Callout
500 ft. Callout Enable Flag
Enable/Disable Callout
500 ft. (Tone) Callout Enable Flag
Enable/Disable Callout Tone
400 ft. Callout Enable Flag
Enable/Disable Callout
300 ft. Callout Enable Flag
Enable/Disable Callout
200 ft. Callout Enable Flag
Enable/Disable Callout
100 ft. Callout Enable Flag
Enable/Disable Callout
100 ft. (Tone) Callout Enable Flag
Enable/Disable Callout Tone
80 ft. Callout Enable Flag
Enable/Disable Callout
60 ft. Callout Enable Flag
Enable/Disable Callout
50 ft. Callout Enable Flag
Enable/Disable Callout
40 ft. Callout Enable Flag
Enable/Disable Callout
35 ft. Callout Enable Flag
Enable/Disable Callout
35 ft. (Tone) Callout Enable Flag
Enable/Disable Callout Tone
30 ft. Callout Enable Flag
Enable/Disable Callout
20 ft. Callout Enable Flag
Enable/Disable Callout
20 ft. (Tone) Callout Enable Flag
Enable/Disable Callout Tone
10 ft. Callout Enable Flag
Enable/Disable Callout
Table 4--8. Operator Selectable Options -- Default Settings
Operator Selectable
Options
Data Parameter
Selectable Option
Aircraft Configuration Data
Part Number
ACD_PART_NUMBER
up to 23 ASCII characters
Aircraft Registration Number
(Tail Number)
AIRCRAFT_REGISTRATION_
NUMBER
up to 23 ASCII characters
Alert High Impedance
Volume Level
HIGH_IMPEDANCE_VOLUME
_LEVEL
integer in the range 0 .. 255
( min = 0, max = 255)
Alert Low Impedance
Volume Level
LOW_IMPEDANCE_VOLUME_ integer in the range 0 .. 255
LEVEL
( min = 0, max = 255)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--8. Operator Selectable Options -- Default Settings(cont)
Operator Selectable
Options
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Data Parameter
Selectable Option
Bank Angle Repetition
BANK_ANGLE_REPETITION
1, 2, 3, 4, Infinity -- T2CAS
will repeat the Bank Angle
Warning based on the Bank
Angle Repetition input.
CPA Caution Alert
CPA_MODE_CAUTION
1 = “TERRAIN AHEAD”,
2 = “TERRAIN CAUTION“
CPA Mode A Warning Alert
CPA_MODE_A_WARNING
1 = “TERRAIN AHEAD
PULL--UP”,
2 = “TERRAIN TERRAIN
PULL--UP PULL--UP” or
3 = “Whoop, Whoop--PULL
UP”
CPA Mode B Warning Alert
CPA_MODE_B_WARNING
1 = “AVOID TERRAIN”
GPWS Caution Flash
Enable
GPWS_CAUTION_FLASH_
ENABLE
Enable -- Caution lamp
flashing for the duration of
the GPWS Caution Event.
Disable -- Caution lamp
solid for the duration of the
GPWS Caution Event.
GPWS Warning Flash
Enable
GPWS_WARNING_FLASH_
ENABLE
Enable -- Warning lamp
flashing for the duration of
the GPWS Warning Event.
Disable -- Warning lamp
solid for the duration of the
GPWS Warning Event.
Male Voice Enable
MALE_VOICE_ENABLE
Enable -- enables the male
alerting voice
Disable -- alerting voice is a
female voice.
Mode 1 Caution Alert
MODE_1_CAUTION
1 = “Whoop, Whoop, PULL
UP” or
2 = “PULL UP, PULL UP”
Mode 1 Warning Alert
MODE_1_WARNING
1 = “Whoop, Whoop, PULL
UP” or
2 = “PULL UP, PULL UP”
Mode 2 Caution Alert
MODE_2_CAUTION
1 = “TERRAIN, TERRAIN”
Mode 2 Warning Alert
MODE_2_WARNING
1 = “Whoop, Whoop, PULL
UP” or
2 = “PULL UP, PULL UP”
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Table 4--8. Operator Selectable Options -- Default Settings(cont)
Operator Selectable
Options
Data Parameter
Selectable Option
Mode 3 Caution Alert
MODE_3_CAUTION
1 = “DON’T SINK, DON’T
SINK”
Mode 4A Caution Alert
MODE_4A_CAUTION
1 = “TOO LOW TERRAIN”
or
2 = “TOO LOW FLAPS”
Mode 4B Caution Alert
MODE_4B_CAUTION
1 = “TOO LOW TERRAIN”
or
2 = “TOO LOW GEAR”
Mode 5 Caution Alert
MODE_5_CAUTION
1 = “GLIDESLOPE”
Mode 6 High Impedance
Volume Level
MODE_6_HIGH_IMPEDANCE_ integer in the range 0 .. 255
VOLUME_LEVEL
( min = 0, max = 255)
Mode 6 Low Impedance
Volume Level
MODE_6_LOW_IMPEDANCE_
VOLUME_LEVEL
integer in the range 0 .. 255
( min = 0, max = 255)
Mode 6 Volume Level
Enable -- Altitude Callouts
MODE_6_VOLUME_LEVEL_
ENABLE_ALTITUDE_
CALLOUTS
Enable -- Altitude Callouts
annunciated at the Mode 6
Volume Level.
Disable -- Altitude Callouts
annunciated at the High
Impedance or Low
Impedance Normal Volume
Levels.
Mode 6 Volume Level
Enable -- Bank Angle
Callouts
MODE_6_VOLUME_LEVEL_
ENABLE_BANK_ANGLE_
CALLOUTS
Enable -- Bank Angle
Callouts annunciated at the
Mode 6 Volume Level.
Disable -- Bank Angle
Callouts annunciated at the
High Impedance or Low
Impedance Normal Volume
Levels.
Mode 6 Volume Level
Enable -- Minimum Callouts
MODE_6_VOLUME_LEVEL_
ENABLE_MINIMUM_
CALLOUTS
Enable -- Minimums
Callouts annunciated at the
Mode 6 Volume Level.
Disable -- Minimums
Callouts annunciated at the
High Impedance or Low
Impedance Normal Volume
Levels.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--8. Operator Selectable Options -- Default Settings(cont)
Operator Selectable
Options
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Data Parameter
Selectable Option
Mode 6 Volume Level
Enable -- Mode 5 Callout
MODE_6_VOLUME_LEVEL_
ENABLE_MODE_5_CALLOUT
Enable -- Mode 5 Callouts
annunciated at the Mode 6
Volume Level.
Disable -- Mode 5 Callouts
annunciated at the High
Impedance or Low
Impedance Normal Volume
Levels.
QFE Enable
QFE_ENABLE
Enable -- Indicates QFE
altitude correction is
enabled.
Disable -- QNH altitude
correction is used.
Store GCAM Parameters
Enable
STORE_GCAM_
PARAMETERS
Enable -- Records additional
GCAM parameters when an
Event occurs, for added
diagnostic ability of GCAM
parameters.
Disable -- Records standard
set of GCAM Data.
GCAM Event data is stored
for every event,
independent of this setting.
Store GFM Parameters
Enable
STORE_GFM_PARAMETERS
Enable -- Records additional
GFM parameters when an
Event occurs, for added
diagnostic ability of Platform
parameters.
Disable -- Records standard
set of GFM Data.
TAWS Caution Flash Enable
TAWS_CAUTION_FLASH_
ENABLE
Enable -- Caution lamp
flashing for the duration of
the TAWS Caution Event.
Disable -- Caution lamp
solid for the duration of the
TAWS Caution Event.
TAWS Warning Flash
Enable
TAWS_WARNING_FLASH_
ENABLE
Enable -- Warning lamp
flashing for the duration of
the TAWS Warning Event.
Disable -- Warning lamp
solid for the duration of the
TAWS Warning Event
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Table 4--8. Operator Selectable Options -- Default Settings(cont)
Operator Selectable
Options
Data Parameter
Selectable Option
Terrain Alert Audio
Suppression Enable
TERRAIN_ALERT_AUDIO_
SUPPRESSION_ENABLE
Enable -- Allows Terrain
Alert (CPA or GPWS) audio
alerts to be suppressed by
the flight crew after one
cycle.
Disable -- Prohibits flight
crew from suppressing
Terrain audio alerts.
Windshear Caution Flash
Enable
WINDSHEAR_CAUTION_
FLASH_ENABLE
Enable -- Caution lamp
flashing for the duration of
the Windshear Caution
Event.
Disable -- Caution lamp
solid for the duration of the
Windshear Caution Event
Windshear Warning Alert
WINDSHEAR_WARNING_
AURAL
1 = “WINDSHEAR,
WINDSHEAR,
WINDSHEAR”
2 = “Siren, WINDSHEAR,
WINDSHEAR,
WINDSHEAR”
Windshear Warning Audio
Suppression Enable
WINDSHEAR_WARNING_
AUDIO_SUPPRESSION_
ENABLE
Enable -- Allows Windshear
Alert audio alerts to be
suppressed by the flight
crew after one cycle.
Disable -- Prohibits flight
crew from suppressing
Windshear audio alerts.
Windshear Warning Flash
Enable
WINDSHEAR_WARNING_
FLASH_ENABLE
Enable -- Warning lamp
flashing for the duration of
the Windshear Warning
Event.
Disable -- Warning lamp
solid for the duration of the
Windshear Warning Event
Aural Alert Prioritization
Input 1 Enable
AURAL_ALERT_
PRIORITIZATION_INPUT_1_
ENABLE
Enable -- Inhibits Aural
alerts that are of lesser
priority than Aural Alert
Priority 1.
Disable -- Lesser priority
aural alerts Not inhibited.
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Table 4--8. Operator Selectable Options -- Default Settings(cont)
Operator Selectable
Options
Data Parameter
Selectable Option
Visual Alert Prioritization
Input 1 Enable
VISUAL_ALERT_
PRIORITIZATION_INPUT_1_
ENABLE
Enable -- Inhibits Visual
alerts that are of lesser
priority than Visual Alert
Priority 1.
Disable -- Lesser priority
Visual alerts Not inhibited.
Aural Alert Prioritization
Input 2 Enable
AURAL_ALERT_
PRIORITIZATION_INPUT_2_
ENABLE
Enable -- Inhibits Aural
alerts that are of lesser
priority than Aural Alert
Priority 2.
Disable -- Lesser priority
aural alerts Not inhibited.
Visual Alert Prioritization
Input 2 Enable
VISUAL_ALERT_
PRIORITIZATION_INPUT_2_
ENABLE
Enable -- Inhibits Visual
alerts that are of lesser
priority than Visual Alert
Priority 2.
Disable -- Lesser priority
Visual alerts Not inhibited.
Aural Alert Prioritization
Input 3 Enable
AURAL_ALERT_
PRIORITIZATION_INPUT_3_
ENABLE
Enable -- Inhibits Aural
alerts that are of lesser
priority than Aural Alert
Priority 3.
Disable -- Lesser priority
aural alerts Not inhibited.
Visual Alert Prioritization
Input 3 Enable
VISUAL_ALERT_
PRIORITIZATION_INPUT_3_
ENABLE
Enable -- Inhibits Visual
alerts that are of lesser
priority than Visual Alert
Priority 3.
Disable -- Lesser priority
Visual alerts Not inhibited.
4--62
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Aural Alert Prioritization
Input 4 Enable
AURAL_ALERT_
PRIORITIZATION_INPUT_4_
ENABLE
Enable -- Inhibits Aural
alerts that are of lesser
priority than Aural Alert
Priority 4.
Disable -- Lesser priority
aural alerts Not inhibited.
Visual Alert Prioritization
Input 4 Enable
VISUAL_ALERT_
PRIORITIZATION_INPUT_4_
ENABLE
Enable -- Inhibits Visual
alerts that are of lesser
priority than Visual Alert
Priority 4.
Disable -- Lesser priority
Visual alerts Not inhibited.
34-43-20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
C. APM/ASDB Configurable Pinout and Pin Description
(1) Programmable Analog Input Pins
T2CAS contains generic analog inputs which are used to input a variety of
dynamically assigned analog signals. Most inputs channels can accept a number of
different signal types and are individually selectable by the APM through the ASDB
database.
The analog signals addressed in this section are APM/ASDB programmable inputs
as shown in Table 4--9. As new Aircraft configurations/ASDBs are defined, the
analog signals will be assigned to a particular input per Appendix n (’n’ denotes an
Appendix assigned as new Aircraft Configurations are defined).
The statically assigned analog signal definitions are addressed in the “TAWS/RWS
Pinout and Pin Descriptions (Non--Configurable)” Section.
Table 4--9. APM/ASDB Programmable Analog Inputs
Analog Signal Definition
Pin #
Notes
3W Synchro(X) #1
RTP--3J
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #1
RTP--4K
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Z) or 2W(--) #1
RTP--3K
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #2
RTP--4A
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #2
RTP--4C
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #2
RTP--4B
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #3
RTP--4D
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #3
RTP--4F
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #3
RTP--4E
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #4
RTP--4G
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #4
RTP--4J
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #4
RTP--4H
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #5
RTP--5A
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #5
RTP--5C
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #5
RTP--5B
2/3W Syncro Input, multiplexed with
A429 receivers
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--9. APM/ASDB Programmable Analog Inputs(cont)
Analog Signal Definition
4--64
15 Feb 2003
Pin #
Notes
3W Synchro(X) #6
RTP--5D
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #6
RTP--5F
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #6
RTP--5E
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #7
RTP--5G
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #7
RTP--5J
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #7
RTP--5H
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #8
RTP--6A
3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(Y) or 2W(+) #8
RTP--6C
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #8
RTP--6B
2/3W Syncro Input, multiplexed with
A429 receivers
3W Synchro(X) #9
RTP--6D
3W Syncro Input
3W Synchro(Y) or 2W(+) #9
RTP--6F
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #9
RTP--6E
2/3W Syncro Input
3W Synchro(X) #10
RTP--6G
3W Syncro Input
3W Synchro(Y) or 2W(+) #10
RTP--6J
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #10
RTP--6H
2/3W Syncro Input
3W Synchro(X) #11
RTP--7A
3W Syncro Input
3W Synchro(Y) or 2W(+) #11
RTP--7C
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #11
RTP--7B
2/3W Syncro Input
3W Synchro(X) #12
RTP--7D
3W Syncro Input
3W Synchro(Y) or 2W(+) #12
RTP--7F
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #12
RTP--7E
2/3W Syncro Input
3W Synchro(X) #13
RTP--7G
2W Syncro Input
3W Synchro(Y) or 2W(+) #13
RTP--7J
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #13
RTP--7H
2/3W Syncro Input
3W Synchro(X) #14
RTP--5K
3W Syncro Input
3W Synchro(Y) or 2W(+) #14
RTP--7K
2/3W Syncro Input
3W Synchro(Z) or 2W(--) #14
RTP--6K
2/3W Syncro Input
34-43-20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--9. APM/ASDB Programmable Analog Inputs(cont)
Analog Signal Definition
Pin #
Notes
2W dc Input #1 (+)
RTP--9A
2W dc Input
2W dc Input #1 (--)
RTP--9B
2W dc Input
2W dc Input #2 (+)
RTP--9G
2W dc Input
2W dc Input #2 (--)
RTP--9H
2W dc Input
2W dc Input #3 (+)
RMP--2B
2W dc Input
2W dc Input #3 (--)
RMP--2C
2W dc Input
2W dc Input #4 (+)
RMP--3J
2W dc Input
2W dc Input #4 (--)
RMP--3K
2W dc Input
2W dc Input #5 (+)
RMP--4A
2W dc Input
2W dc Input #5 (--)
RMP--4B
2W dc Input
2W dc Input #6 (+)
RMP--4C
2W dc Input
2W dc Input #6 (--)
RMP--4E
2W dc Input
2W dc Input #7 (+)
RMP--4F
2W dc Input
2W dc Input #7 (--)
RMP--4G
2W dc Input
2W ac/dc Input #8 (+)
RMP--5A
2W ac/dc Input
2W ac/dc Input #8 (--)
RMP--5B
2W ac/dc Input
2W ac/dc Input #9 (+)
RMP--5C
2W ac/dc Input
2W ac/dc Input #9 (--)
RMP--5D
2W ac/dc Input
2W dc Input #10 (+)
RMP--10E
2W dc Input
2W dc Input #10 (--)
RMP--10F
2W dc Input
2W dc Input #11 (+)
RMP--11E
2W dc Input
2W dc Input #11 (--)
RMP--11F
2W dc Input
2W dc Input #12 (+)
RMP--11G
2W dc Input
2W dc Input #12 (--)
RMP--11H
2W dc Input
2W dc / ac Reference Input #13 (+)
RMP--11J
2W dc / ac reference Input
2W dc / ac Reference Input #13 (--)
RMP--11K
2W dc / ac reference Input
2W dc / ac Reference Input #14 (+)
RMP--15A
2W dc / ac reference Input
2W dc / ac Reference Input #14 (--)
RMP--15B
2W dc / ac reference Input
2W dc / ac Reference Input #15 (+)
RMP--15C
2W dc / ac reference Input
2W dc / ac Reference Input #15 (--)
RMP--15D
2W dc / ac reference Input
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15 Feb 2003
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--9. APM/ASDB Programmable Analog Inputs(cont)
Analog Signal Definition
Pin #
Notes
2W dc / ac Reference Input #16 (+)
RMP--15E
2W dc / ac reference Input
2W dc / ac Reference Input #16 (--)
RMP--15F
2W dc / ac reference Input
2W ac / dc / ac Ref Input #17 (+)
RBP--1A
2W ac/dc / ac reference Input
2W ac / dc / ac Ref Input #17 (--)
RBP--1B
2W ac/dc / ac reference Input
2W ac / dc / ac Ref Input #18 (+)
RBP--1C
2W ac/dc / ac reference Input
2W ac / dc / ac Ref Input #18 (--)
RBP--1D
2W ac/dc / ac reference Input
ac 400Hz Reference #1 (H)
RMP--4H
2W ac reference Input
ac 400Hz Reference #1 (C)
RMP--4J
2W ac reference Input
ac 400Hz Reference #2 (H)
RMP--5H
2W ac reference Input
ac 400Hz Reference #2 (C)
RMP--5J
2W ac reference Input
(a) Analog Input Type Definitions/Tolerances
The analog input types accept signals with input voltage ranges as defined in
Table 4--10. Table 4--11 list the input impedance ranges for the accepted analog
input types.
Table 4--10. Analog Input Voltage Ranges
Common mode
voltage on each pin
(Volts, peak)
Differential voltage
between 2 pins
(Volts, peak) (NOTE)
Analog 3W/2W multiplexed with A429
receivers
--22.0V to +22.0 V
--22.0V to +22.0 V
Analog 3W/2W non--multiplexed
--50.0V to +50.0 V
--50.0V to +50.0 V
Analog 2W ac/dc
--50.0V to +50.0 V
--50.0V to +50.0 V
Analog 2W dc
--50.0V to +50.0 V
--50.0V to +50.0 V
Analog 2W dc/Ref
--50.0V to +50.0 V
--50.0V to +50.0 V
Analog 2W ac/dc/Ref
--50.0V to +50.0 V
--50.0V to +50.0 V
Analog Input Type
NOTE:
4--66
15 Feb 2003
For 3 Wire inputs, the differential voltage requirement applies to the
voltage between the XZ and YZ legs.
34-43-20
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--11. Analog Input Impedance
Impedance relative
to ground
Impedance between
2 pins (NOTE)
> 9k Ohms
> 9k Ohms
> 95k Ohms (X, Y)
> 47k Ohms (Z)
> 500k Ohms
Analog 2W ac/dc
> 95k Ohms
> 500k Ohms
Analog 2W dc
> 95k Ohms
> 500k Ohms
Analog 2W dc/Ref
> 95K Ohms
> 500K Ohms
Analog 2W ac/dc/Ref
> 95K Ohms
> 500K Ohms
Analog Input Type
Analog 3W/2W multiplexed with A429
receivers
Analog 3W/2W non--multiplexed
NOTE:
For 3 Wire inputs, the differential impedance requirement applies to the
impedance between the XZ and YZ legs.
(b) 3W AC Synchro Signal Type Processing
The 3W ac synchro input signal consists of a 3 wire synchro which is excited by
a 400 Hz (nominal) AC reference input. The amplitude of the X, Y and Z inputs
and the phase relative to the AC reference determines the angle. The 3W ac
synchro inputs accept ARINC 407 syncro signals.
T2CAS accepts the 400 Hz ac reference signals on the specified programmable
pins as defined in Table 4--12.
NOTE:
The reference is used to synchronously detect 400 Hz ac signals.
Table 4--12. 3W Synchro AC References
400Hz AC Reference Signal Type
Pin Assignment
a.
Internal self--generated ac reference
N/A
b.
ac synchro Reference #1
RMP--4H (H), RMP--4J (C)
c.
ac synchro Reference #2
RMP--5H (H), RMP--5J (C)
d.
Analog 2W dc / ac Reference Input #13
RMP--11J (+), RMP--11K (--)
e.
Analog 2W dc / ac Reference Input #14
RMP--15A (+), RMP--15B (--)
f.
Analog 2W dc / ac Reference Input #15
RMP--15C (+), RMP--15D (--)
g.
Analog 2W dc / ac Reference Input #16
RMP--15E (+), RMP--15F (--)
h.
Analog 2W ac / dc / ac Reference Input #17
RBP--1A (+), RBP--1B (--)
j.
Analog 2W ac / dc / ac Reference Input #18
RBP--1C (+), RBP--1D (--)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
(c) 2W DC Signal Processing
The 2W dc Inputs input signal consists of a 2 Wire dc input signal that is
connected to the Y and Z leg of the input circuit. The X leg is not connected to
external circuitry in this configuration.
(2) Programmable Digital Input/Output Pins
This section defines the physical characteristics of each Digital signal type supported
by the T2CAS TAWS/RWS function. The T2CAS supports the following Digital
signals: ARINC 429, ARINC 453, Ethernet 10 Base--T and RS--422.
The Digital signals addressed in this section are APM/ASDB programmable input and
output signals as shown in Table 4--13 and Table 4--14 respectfully. As new Aircraft
configurations/ASDBs are defined, the Digital signals will be assigned to a particular
input/output per Appendix n (’n’ denotes Appendix’ that are created as new Aircraft
Configurations are defined).
The statically assigned Digital signal definitions are addressed in the “TAWS/RWS
Pinout and Pin Descriptions (Non--Configurable)” Section.
Table 4--13. APM/ASDB Programmable Digital Inputs
Digital Signal Definition
4--68
15 Feb 2003
Pin #
Notes
ARINC 429 Input #1 (A)
RTP--1C
A429 Input H/L
ARINC 429 Input #1 (B)
RTP--1D
A429 Input H/L
ARINC 429 Input #2 (A)
RTP--1G
A429 Input H/L
ARINC 429 Input #2 (B)
RTP--1H
A429 Input H/L
ARINC 429 Input #3 (A)
RTP--1J
A429 Input H/L
ARINC 429 Input #3 (B)
RTP--1K
A429 Input H/L
ARINC 429 Input #4 (A)
RTP--2E
A429 Input H/L
ARINC 429 Input #4 (B)
RTP--2F
A429 Input H/L
ARINC 429 Input #5 (A)
RTP--3A
A429 Input H/L
ARINC 429 Input #5 (B)
RTP--3B
A429 Input H/L
ARINC 429 Input #6 (A)
RTP--3C
A429 Input H/L
ARINC 429 Input #6 (B)
RTP--3D
A429 Input H/L
ARINC 429 Input #7 (A)
RTP--3E
A429 Input H/L
ARINC 429 Input #7 (B)
RTP--3F
A429 Input H/L
ARINC 429 Input #8 (A)
RTP--3G
multiplexed with RS--422 and GPS Time Mark
Inputs
ARINC 429 Input #8 (B)
RTP--3H
multiplexed with RS--422 and GPS Time Mark
Inputs
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--13. APM/ASDB Programmable Digital Inputs(cont)
Digital Signal Definition
Pin #
Notes
ARINC 429 Input #9 (A)
RTP--3J
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #9 (B)
RTP--3K
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #10 (A)
RTP--4A
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #10 (B)
RTP--4B
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #11 (A)
RTP--4D
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #11 (B)
RTP--4E
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #12 (A)
RTP--4G
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #12 (B)
RTP--4H
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #13 (A)
RTP--5A
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #13 (B)
RTP--5B
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #14 (A)
RTP--5D
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #14 (B)
RTP--5E
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #15 (A)
RTP--5G
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #15 (B)
RTP--5H
multiplexed with Analog 3W Synchro(Z) or 2W(--)
ARINC 429 Input #16 (A)
RTP--6A
multiplexed with Analog 3W Synchro(X)
ARINC 429 Input #16 (B)
RTP--6B
multiplexed with Analog 3W Synchro(Z) or 2W(--)
RS--422 Input (H)
RTP--3G
multiplexed with A429 and GPS Time Mark Inputs
RS--422 Input (L)
RTP--3H
multiplexed with A429 and GPS Time Mark Inputs
Ethernet LAN #1 RX (+)
RTP--2C
Ethernet 10 Base--T
Ethernet LAN #1 RX (--)
RTP--2D
Ethernet 10 Base--T
Ethernet LAN #2 RX (+)
RTP--2J
Ethernet 10 Base--T
Ethernet LAN #2 RX (--)
RTP--2K
Ethernet 10 Base--T
Table 4--14. APM/ASDB Programmable Digital Outputs
Digital Signal Definition
Pin #
Notes
ARINC 429 Output #1 (A)
RTP--8A
A429 Output H/L
ARINC 429 Output #1 (B)
RTP--8B
A429 Output H/L
ARINC 429 Output #2 (A)
RTP--8E
A429 Output H/L
ARINC 429 Output #2 (B)
RTP--8F
A429 Output H/L
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--14. APM/ASDB Programmable Digital Outputs(cont)
Digital Signal Definition
Pin #
Notes
RS--422 Output (H)
RTP--8C
RS--422 Output
RS--422 Output (L)
RTP--8D
RS--422 Output
Ethernet LAN #1 TX (+)
RTP--2A
Ethernet 10 Base--T
Ethernet LAN #1 TX (--)
RTP--2B
Ethernet 10 Base--T
Ethernet LAN #2 TX (+)
RTP--2G
Ethernet 10 Base--T
Ethernet LAN #2 TX (--)
RTP--2H
Ethernet 10 Base--T
(a) ARINC 429 Signals
The T2CAS TAWS/RWS Circuit Card supports up to 18 ARINC 429 receivers, 16
of which are APM/ASDB programmable (as shown in Table 4--13). Additionally,
4 ARINC 429 transmitters are supported, 2 of which are APM/ASDB
programmable (as shown in Table 4--14).
The ARINC 429 definition for the Source Destination Identifier Bits are shown in
Table 4--15.
Table 4--15. Source Destination Identifier (SDI)
BITS
Meaning
10
All--Call
Installation #1
Installation #2
Installation #3
The ARINC 429 Sign Status Matrix Bit definitions for Binary data and Binary
Coded Decimal data are shown in Table 4--16 and Table 4--17 respectfully.
Table 4--16. Sign Status Matrix (SSM) [BNR]
BITS
4--70
15 Feb 2003
Meaning
30
31
Failure Warning
No Computed Data
Functional Test
Normal Operation
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--17. Sign Status Matrix (SSM) [BCD]
BITS
Meaning
30
31
North/Plus
No Computed Data
Functional Test
Undefined
ARINC 429 inputs are classified as one of the following: high speed (H), low
speed (L) or either (H/L). The A429 receivers are capable of receiving high or
low speed data through APM configuration. The ports are designated H or L if
they are designated for a function with a known bus speed, otherwise H/L is
assigned (there is no hardware difference between the H, L or H/L ports).
ARINC 429 outputs are also classified as either high speed (H), low speed (L) or
selectable (H/L). A429 outputs designated as H/L speed are capable of
operating in either high or low speed modes, selectable by the APM through the
ASDB database.
(b) Ethernet 10 Base--T Signals
Ethernet 10 Base--T is specified in IEEE Standard 802.3 Ethernet 10 Base--T
provides communication at a data rate of 10 MBPS over two pairs of wires,
where one twisted pair is used to receive data and the other twisted pair is used
to transmit data. Segments of approximately 100 meters in length can be
constructed when twisted pair wire that meets the EIA/TIA Category 3 wire
specifications is used.
(c) RS--422 Signals
The TAWS/RWS card has an RS--422 Input bus which is multiplexed on the
same pins as an ARINC 429 Input bus. The RS--422 Input Bus meets the
electrical requirements in EIA/TIA--422--B.
The RS--422 Input Bus has an input impedance on each pin relative to ground of
≥ 9k Ohms and a differential input impedance between + and -- pins of ≥ 9k
Ohms.
NOTE:
This is due to the fact the input is multiplexed with an ARINC 429
Receiver.
The RS--422 Output Bus has an output impedance of 75 ± 5 Ohms distributed
equally between the + and -- outputs.
(d) GPS Time Mark
The GPS Time Mark Input accepts RS--422 GPS Time Mark signals from an
ARINC--743A GPS.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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The GPS Time Mark Output is used to provide an accurate timing reference for
GPS signals. The output has a differential RS--422 signal format.
(3) Programmable Discrete Input/Output Pins
The Discrete signals addressed in this section are APM/ASDB programmable input
and output signals as shown in Table 4--18 and Table 4--19 respectfully. As new
Aircraft configurations/ASDBs are defined, the Discrete signals will be assigned to a
particular input/output per Appendix n (’n’ denotes Appendix’ that are created as new
Aircraft Configurations are defined).
Table 4--18. APM/ASDB Programmable Discrete Inputs
Digital Signal Definition
4--72
15 Feb 2003
Pin #
Notes
Ground Discrete Input #1
RTP--9J
GND Disc Input
Ground Discrete Input #2
RTP--9K
GND Disc Input
Ground Discrete Input #3
RTP--10A
GND Disc Input
Ground Discrete Input #4
RTP--10B
GND Disc Input
Ground Discrete Input #5
RTP--10C
GND Disc Input
Ground Discrete Input #6
RTP--10D
GND Disc Input
Ground Discrete Input #7
RTP--10E
GND Disc Input
Ground Discrete Input #8
RTP--10F
GND Disc Input
Ground Discrete Input #9
RTP--10G
GND Disc Input
Ground Discrete Input #10
RTP--10H
GND Disc Input
Ground Discrete Input #11
RTP--10J
GND Disc Input
Ground Discrete Input #12
RTP--10K
GND Disc Input
Ground Discrete Input #13
RTP--11A
GND Disc Input
Ground Discrete Input #14
RTP--11B
GND Disc Input
Ground Discrete Input #15
RTP--11C
GND Disc Input
Ground Discrete Input #16
RTP--11D
GND Disc Input
Ground Discrete Input #17
RTP--11E
GND Disc Input
Ground Discrete Input #18
RTP--11F
GND Disc Input
Ground Discrete Input #19
RTP--11G
GND Disc Input
Ground Discrete Input #20
RTP--11H
GND Disc Input
Ground Discrete Input #21
RTP--11J
GND Disc Input
Ground Discrete Input #22
RTP--11K
GND Disc Input
+28 Vdc Discrete Input #1
RTP--12A
+28 Vdc Disc Input
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--18. APM/ASDB Programmable Discrete Inputs(cont)
Digital Signal Definition
Pin #
Notes
+28 Vdc Discrete Input #2
RTP--12B
+28 Vdc Disc Input
+28 Vdc Discrete Input #3
RTP--12C
+28 Vdc Disc Input
+28 Vdc Discrete Input #4
RTP--12D
+28 Vdc Disc Input
+28 Vdc Discrete Input #5
RTP--12E
+28 Vdc Disc Input
+28 Vdc Discrete Input #6
RTP--12F
+28 Vdc Disc Input
+28 Vdc Discrete Input #7
RTP--12G
+28 Vdc Disc Input
+28 Vdc Discrete Input #8
RTP--12H
+28 Vdc Disc Input
+28 Vdc Discrete Input #9
RTP--12J
+28 Vdc Disc Input
+28 Vdc Discrete Input #10
RTP--12K
+28 Vdc Disc Input
+28 Vdc Discrete Input #11
RTP--13A
+28 Vdc Disc Input
+28 Vdc Discrete Input #12
RMP--4K
+28 Vdc Disc Input
+28 Vdc Discrete Input #13
RMP--6C
+28 Vdc Disc Input
+28 Vdc Discrete Input #14
RBP--2A
+28 Vdc Disc Input
+28 Vdc Discrete Input #15
RBP--2B
+28 Vdc Disc Input
+28 Vdc Discrete Input #16
RBP--2C
+28 Vdc Disc Input
+28 Vdc Discrete Input #17
RBP--2D
+28 Vdc Disc Input
+28 Vdc Discrete Input #18
RBP--2E
+28 Vdc Disc Input
+28 Vdc Discrete Input #19
RBP--2F
+28 Vdc Disc Input
+28 Vdc Discrete Input #20
RBP--2G
+28 Vdc Disc Input
Table 4--19. APM/ASDB Programmable Discrete Outputs
Digital Signal Definition
Pin #
Notes
Ground Discrete Output #1
RTP--13B
GND Disc Output 500mA
Ground Discrete Output #2
RTP--13C
GND Disc Output 500mA
Ground Discrete Output #3
RTP--13D
GND Disc Output 500mA
Ground Discrete Output #4
RTP--13E
GND Disc Output 500mA
Ground Discrete Output #5
RTP--13F
GND Disc Output 500mA
Ground Discrete Output #6
RTP--13G
GND Disc Output 500mA
Ground Discrete Output #7
RTP--13H
GND Disc Output 500mA
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--19. APM/ASDB Programmable Discrete Outputs(cont)
Digital Signal Definition
Pin #
Notes
Ground Discrete Output #8
RTP--13J
GND Disc Output 500mA
Ground Discrete Output #9
RTP--13K
GND Disc Output 500mA
Ground Discrete Output #10
RTP--14A
GND Disc Output 500mA
Ground Discrete Monitor Output #1
RTP--14B
GND Disc Monitor 500mA
Ground Discrete Monitor Output #2
RTP--14C
GND Disc Monitor 250mA
Ground Discrete Monitor Output #3
RTP--14D
GND Disc Monitor 250mA
(a) Discrete Input Ground/Open
T2CAS provides ground/open discrete inputs for aircraft level discrete interfaces.
The GROUND and OPEN logic states are determined as follows:
GROUND ≤ 3.5 Vdc at the input OR a resistance of less than 10 Ohms to
ground.
OPEN ≥ 14.0 Vdc at the input OR a resistance of greater than 100k Ohms to
ground.
The discrete inputs source 1.0 ± 0.25 ma of current when the input is grounded
and has diode isolation circuitry to prevent the inputs from being loaded to
ground when power is removed from the T2CAS.
NOTE:
When an input goes to a discrete on both TCAS and TAWS/RWS, the
input current is twice the specification for a single discrete.
(b) Discrete Input +28 Vdc/Open
T2CAS provides +28 Vdc/open discrete inputs for aircraft level discrete
interfaces. The +28 Vdc and OPEN logic states are determined per the
following:
+28 Vdc ≥14.0 Vdc at the input.
OPEN ≤ 3.5 Vdc at the input OR a resistance of greater than 100k Ohms to
the positive voltage source.
The discrete inputs sink 1.0 ± 0.25 mA of current when a +27.5 Vdc input and
has diode isolation circuitry is applied to prevent the inputs from being loaded to
ground when power is removed from the T2CAS.
NOTE:
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When an input goes to a discrete on both TCAS and TAWS/RWS, the
input current is twice the specification for a single discrete.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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(c) Discrete Output Ground/Open 500 mA
The discrete outputs listed in this section pertain to ground/open discrete outputs
for the TAWS/RWS function.
The discrete output in the GROUND logic state has an output voltage of ≤3.0
Vdc when sinking 500 mA of current and an output voltage of ≤ 1.5 Vdc when
sinking 100 mA of current.
The discrete output in the OPEN logic state has an output impedance of ≥ 2.4M
Ohms to ground for voltages applied to the output of 0.0 to +33.0 Vdc and ≥100k
Ohms to ground for voltages applied to the output of +33.0 to +36.0 Vdc.
The discrete output circuitry contains a monitor which detects if an over--current
condition has occurred and is able to withstand a direct short to +28 Vdc for an
indefinite period of time.
Additionally, the discrete output circuitry contains a monitor which detects if the
output voltage is incorrect for the driven state of the discrete output.
D. TAWS/RWS Input Data Signals
The T2CAS TAWS/RWS functions requires a minimum set of data that is needed to
perform within the standard specifications (detailed in RTCA DO--161A [GPWS],
TSO--C151a [TAWS] and TSO--C117a [RWS] ). This section contains the minimum set of
TAWS/RWS data signals and the information/guidelines that is needed by the installer to
obtain the correct analog or digital signal on a specific aircraft. Since the TAWS/RWS I/O
function is very flexible, the installer must keep in mind that the data signal sources listed
in this section are typical for the specified signal and that the I/O function can be modified
via the ASDB to accommodate other non--typical signal sources.
The information in this section will include External Sensor Input accuracies for specific
inputs to T2CAS GCAM function. These External Sensor accuracies must be met for the
specified inputs in order for the T2CAS to perform the TAWS/RWS functions. Inputs to
T2CAS GCAM function consists of errors due to the external system sensor plus
measurement errors within the T2CAS LRU. In addition, for analog inputs the internal
T2CAS errors due to the hardware circuit are also considered.
(1) Vertical Speed (Digital/Analog)
The TAWS/RWS Vertical Speed parameter is updated from an Inertial, GPS or Air
Data Computer source. The IRS/GPS source can be any one of the following :
ADIRS, GPIRS, IRS, AHRS, GPS and ADC.
NOTE:
When Vertical Speed is unavailable from an IRS or GPS source, the
alternate variable Baro Altitude Rate will be used from an ADC source.
The minimum External Sensor input accuracy accepted is 68 ft/min when GPS is the
source or 30 ft/min when IRS, ADIRS, AHRS or ADC (alternate Baro Altitude Rate
variable) is the source.
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(a) Digital Input
T2CAS accepts ARINC 429 Vertical Speed inputs from Inertial Systems, GPS
Systems and Digital Air Data Systems (DADC).
IRS systems supported: ARINC 705 Attitude Reference and Heading System
(AHRS), ARINC 738 Air Data Inertial Reference System (ADIRS), and other
non--ARINC standard interfaces.
GPS systems supported: ARINC 743 or ARINC 743A.
DADC systems supported: ARINC 706 Air Data Computer (ADC), ARINC 738 Air
Data Inertial Reference System (ADIRS) and other non--ARINC standard
interfaces.
(b) Analog Input
The electrical pin connection for the analog Altitude Rate is listed under
Table 4--6 of the TAWS/RWS Non--Conigurable Pinout and Pin Description
section.
T2CAS can also process ARINC 575/595 analog DC Altitude Rate inputs. The
DC altitude rate input consists of a positive and negative reference voltage
(nominally +12.0 Vdc) and a signal input which can range between the positive
and negative reference input.
(2) Ground Speed
The T2CAS Digital Ground Speed input parameter is updated from a GPS, Flight
Management Systems or Inertial source. GPS/FMS would be the primary source, an
Inertial source would only be used in the short--term during GPS drop--outs.
GPS system supported: ARINC 743/743A.
FMC system supported: ARINC 702 Flight Management System and other
non--ARINC standard interface.
Inertial systems supported: ARINC 704 Inertial Reference System (IRS), ARINC 705
Attitude Reference and Heading System (AHRS), ARINC 738 Air Data Inertial
Reference System (ADIRS), ARINC 743A GPS and other non--ARINC standard
interfaces.
The minimum External Sensor input accuracy accepted for Ground Speed is 2 Kts
from a primary source (GPS/FMS) and 12 Kts from a secondary (Inertial) source.
(3) True Track Angle
The T2CAS Digital True Track Angle input parameter is updated from a GPS, Flight
Management Systems or Inertial source. GPS/FMS would be the primary source, an
Inertial source would only be used in the short--term during GPS drop--outs.
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Inertial systems supported: ARINC 704 IRS, ARINC 705 AHRS, ARINC 738 ADIRS,
and other non--ARINC standard interface.
GPS system supported: ARINC 743/743A.
FMC system supported: ARINC 702 Flight Management System and other
non--ARINC standard interface.
The minimum External Sensor input accuracy accepted for True Track Angle is 1
Degree from a primary source (GPS/FMS) and 5 Degrees from a secondary (Inertial)
source.
(4) Radio Altitude (Digital/Analog)
T2CAS accepts up to 3 analog Radio Altitude inputs or 3 Digital ARINC 429 Radio
Altitude inputs. Digital Radio Altitude Inputs 1 and 2 are shared with the TCAS
function.
The external LRUs/External Sensors providing the data parameters must provide an
input to the T2CAS that is within the range of ±3 ft. or 4% from 0 to 500 ft. and 5%
when above 500 ft.
The electrical pin connections for the Digital/Analog Radio Altitude is listed under
Table 4--6 of the TAWS/RWS Non--Configurable Pinout and Pin Description section.
(a) Digital Input
The Table below shows the ARINC 429 digital interface characteristics for the
ARINC 707 radio altimeter system. Two of the ARINC 429 input busses
(RADIO_ALTITUDE_1 and RADIO_ALTITUDE_2) are shared with the TCAS
ARINC 429 Radio Altitude Inputs. The TAWS input circuitry is independent from
TCAS.
Radio Altitude
429 Label: 164 (Octal)
Units: Feet
Max Range: ±8,192 Feet
Appox. LSB: 0.125
Data Bits: 16
13(lsb) -- 28(msb)
Sign Bit: 29
Transmit Interval:
25--50ms
Data Type: Two’s Complement
Binary
Pad Bits: 11, 12
0 = Up, 1 = Down
(b) Analog Input
The Analog Radio Altitude inputs are compatible with an ARINC 552 Radio
Altimeter system and may have a number of different input formats as defined for
specific aircraft requirements. The external connector pins for Analog Radio
Altitude Inputs #1 and #2 are shared by TCAS and TAWS/RWS, both have
independent circuitry.
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The following common mode and differential mode inputs signals are accepted
by the T2CAS with the voltage ranges defined:
• (+) input common mode range --5.0 to +40.0 Vdc
• (--) input common mode range --2.5 to +2.5 Vdc
• Differential (+ to --) range --2.5 to +37.5 Vdc
NOTE:
The maximum radio altitude input currently used in TCAS is +37.5 Vdc
for a metric system. The common mode ranges allow for a ±2.5 Vdc
ground voltage differential.
The minimum input impedance on each pin is 95k Ohms relative to ground. The
minimum input impedance for inputs which are connected to both TCAS and
TAWS/RWS will be one half the minimum number listed.
(5) Flight Path Angle
The T2CAS Digital Flight Path Angle input parameter is updated from an Inertial,
Flight Management or GPS source.
Inertial systems supported: ARINC 704 IRS, ARINC 705 AHRS, ARINC 738 ADIRS,
and other non--ARINC standard interface.
FMC system supported: ARINC 702 Flight Management System and other
non--ARINC standard interface.
GPS system supported: ARINC 743/743A.
The minimum External Sensor input accuracy accepted for Flight Path Angle is 0.3
Degrees.
(6) Current Aircraft Weight
The T2CAS updates the Current Aircraft Weight from either an FMS or a Weight and
Balance System source.
FMC system supported: ARINC 702 Flight Management System and other
non--ARINC standard interface.
The minimum External Sensor input accuracy accepted for Current Aircraft Weight is
220 lbs. with 95% confidence.
(7) Aircraft Position Latitude/Longitude
The T2CAS Aircraft Position input parameter is updated from a GPS or FMS source.
The GPS source can be any one of the following: GPIRS or GPS. In addition, an IRS
source can be used, but only for short periods of time during GPS or FMS drop--outs
GPS system supported: ARINC 743/743A.
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FMC system supported: ARINC 702 Flight Management System and other
non--ARINC standard interface.
The minimum External Sensor input accuracies accepted for Aircraft Position are:
• Phase I (Take Off)
1 nmi
• Phase II (Outside Terminal or final area)
2 nmi
• Phase III (Terminal area)
1 nmi
• Phase IV (Final area)
0.5 nmi
(8) Aircraft Altitude
The T2CAS Aircraft Altitude input parameter is updated from an ADC or GPS source.
The T2CAS uses (but is not limited to) the following altitude types: Corrected
Barometric Altitude, GPS Altitude -- MSL and Uncorrected Barometric Altitude.
The minimum External Sensor input accuracy accepted for Aircraft Altitude is 95 feet
with 95% confidence.
(9) Navigation Accuracy
When using GPS or FMS data for aircraft position determination, the T2CAS uses
the available GPS or FMS signals to determine accuracy of the Position information..
(a) GPS
For a GPS source, the minimum External Sensor input accuracy accepted is
100m (333 feet) for an HDOP (Horizontal Dilution of Position) of 1.5 with S/A on.
(b) FMS
The T2CAS determines the Navigation Accuracy parameter by using the RNP
data value if a valid RNP data is received AND a valid FMS Discrete Word is
received with the Nav Mode set to ”High Accuracy”.
For FMS Discrete Word -- Type 2, bit 15 indicates high or low navigation
accuracy and is set independently of the navigation mode, bits 16 -- 18. The
FMS sets bit 15 (high accuracy) if the estimated error of the FMS position is less
than the phase of flight position accuracy tolerance listed in Table 4--20.
Otherwise the FMS resets bit 15 (low accuracy).
Table 4--20. Navigation Accuracy
Phase of Flight
Accuracy Tolerance
Approach
0.5 nm
Terminal
0.5 nm
Enroute
FMS not in Degrade
Oceanic
FMS not in Degrade
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(10) Static Air Temperature
The T2CAS Static Air Temperature parameter is updated from a Digital ADC or FMS
source.
The minimum External Sensor input accuracy accepted for Static Air Temperature is
4.5 Degrees C, with 95% confidence.
(11) Roll Angle
The T2CAS Roll Angle parameter is updated from an Inertial Reference source
(GPIRS, ADIRS, IRS and AHRS).
For a T2CAS TAWS only system, the minimum External Sensor input accuracy for
Roll Angle is 2 Degrees with 95% confidence.
For T2CAS equipped with Windshear, the minimum External Sensor input accuracy
Roll Angle is 0.5 Degrees with 95% confidence.
(12) Computed Airspeed
The T2CAS Computed Airspeed input parameter is updated from an Air Data
Computer source.
The minimum External Sensor input accuracy accepted for Computed Airspeed is as
follows (with 95% confidence):
• 5 kts @ 60 kts
• 2 kts @ 100 kts
• 2 kts @ 200 kts
• 4 kts @ 450 kts
(13) Selected Runway Heading
The T2CAS Selected Runway Heading input parameter is updated using either
Selected Runway Heading data OR Selected Course from one of the following LRU
data sources: ILS, MCP or FMS.
The minimum External Sensor input accuracy accepted for Selected Runway
Heading is 2 Degrees.
(14) Glideslope Deviation (Digital/Analog)
The T2CAS Glideslope Deviation input parameter is updated using either Glideslope
Deviation data or MLS Elevation Deviation from one of the following LRU data
sources: ILS, FMS, DFS, MLS or GPS.
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The minimum External Sensor input accuracies accepted for Glideslope Deviation
are as follows:
• 0.00455 for ddm < 0.0455
• 10% for ddm < 0.175
• non--decreasing for ddm < 0.800
(a) Analog ILS Input
The glideslope deviation input signal is defined in ARINC 547 and ARINC 578--4.
This input accepts signals which have a common mode voltages of --5.0 V to
+5.0 V, a differential voltages between pins of --2.5 V to +2.5 V and an input
impedance relative to ground of greater than 1M Ohm on each pin.
NOTE:
The common mode ranges allow for a ±2.5 V ground voltage differential.
NOTE:
ARINC 547 ILS receivers have current mode outputs which drive 5
meter movements in parallel, each with 1k Ohm impedance. The ILS is
calibrated to output the correct current into 5 -- 1k Ohm loads in parallel.
Any additional impedance added to the circuit will cause an error in the
output. A 1M Ohm input impedance will induce a 0.02% error. Newer
ARINC 578 ILS receivers have voltage mode outputs which are immune
to load variations.
(15) Localizer Deviation (Digital/Analog)
The T2CAS Localizer Deviation input parameter is updated using either Localizer
Deviation data OR MLS Azimuth Deviation from the following LRU data sources: ILS,
FMS, DFS and MLS.
The minimum External Sensor input accuracies accepted for Localizer Deviation are
as follows:
• 0.00465 for ddm < 0.0465
• 10% for ddm < 0.155
• 20% for ddm < 0.310
• non--decreasing for ddm < 0.400
(a) Analog ILS Input
See Glideslope Deviation Analog ILS Input
(16) Selected Decision Height
The T2CAS Selected Decision Height input parameter is updated using one of the
following LRU data sources: EFIS, MCP or FMS.
If the Decision Height is not available from one of the above LRU sources, the
Decision Height will not be annunciated.
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The minimum External Sensor input accuracy accepted for Selected Decision Height
is 1 foot.
(17) Minimum Descent Altitude
The T2CAS Minimum Descent Altitude input parameter is updated using one of the
following LRU data sources: EFIS, MCP or FMS.
The minimum External Sensor input accuracy accepted for Minimum Descent Altitude
is 1 foot.
(18) Body Longitudinal Acceleration (Digital/Analog)
The Body Longitudinal Acceleration input parameter is only used on installations
where T2CAS is performing the RWS function.
The T2CAS Body Longitudinal Acceleration input parameter is updated from one of
the following Inertial Reference sources: ADIRS, IRS or AHRS.
The minimum External Sensor input accuracy accepted for Body Longitudinal
Acceleration is 0.01 G with 95% confidence.
(19) Body Normal Acceleration (Digital/Analog)
The Body Normal Acceleration input parameter is only used on installations where
T2CAS is performing the RWS function.
The T2CAS Body Normal Acceleration input parameter is updated from one of the
following Inertial Reference sources: ADIRS, IRS or AHRS.
The minimum External Sensor input accuracy accepted is 0.01 G with 95%
confidence.
(20) Pitch Angle
The T2CAS Pitch Angle input parameter is updated from one of the following Inertial
Reference sources: GPIRS, ADIRS, IRS or AHRS.
For T2CAS equipped with Windshear, the minimum External Sensor input accuracy
accepted for Pitch Angle is 0.5 Degrees with 95% confidence.
(21) Flap Angle
The T2CAS Flap Angle input parameter is updated with valid Flap Angle data from
one of the following LRUs: Flap Slat Electronic/Control Unit, Digital Stall Warning
Computer (DSWC), Analog or Discrete.
The minimum External Sensor input accuracy accepted for Flap Angle is 2.0 Degrees
with 95% confidence or the Discrete value setting.
NOTE:
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Most aircraft types have discrete flap settings, where a range of angles or
voltages map into discrete flap settings. For example, 747--1/2/3 has 7 flap
settings with 40--50 degrees range per setting.
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(22) Slat Angle
The Slat Angle input parameter is only used on installations where T2CAS is
performing the RWS function. Slat Angle data is updated from one of following LRU
sources: Flap Slat Electronic/Control Unit, Digital Stall Warning Computer (DSWC),
Analog or Discrete.
The minimum External Sensor input accuracy accepted for Slat Angle is 2.0 Degrees
with 95% confidence or the Discrete value setting.
NOTE:
Most aircraft types have discrete Slat settings, where a range of angles or
voltages map into discrete Slat settings. For example, 747--1/2/3 has 7 slat
settings with 40--50 degrees range per setting.
(23) True Airspeed
The True Airspeed input parameter is only used on installations where T2CAS is
performing the RWS function.
The T2CAS True Air Speed input parameter is updated from one of the following Air
Data sources: ADIRS or ADC.
The minimum External Sensor input accuracy accepted for True Airspeed is 4.0 kts
with 95% confidence.
(24) Angle of Attack (AOA) Left/Right
The AOA input parameter is only used on installations where T2CAS is performing
the RWS function.
The T2CAS AOA input parameter is updated from a Digital Stall Warning Computer or
a Analog Left/Right Angle of Attack Vane source.
The minimum External Sensor input accuracy accepted for AOA is 0.6 degrees with
95% confidence.
(25) Magnetic Heading
The T2CAS Magnetic Heading input parameter is updated from one of the following
Inertial Reference sources: ADIRS or IRS.
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(26) True Display Orientation Left
The T2CAS updates the True Display Orientation Left data based on Table 4--21.
The minimum External Sensor input accuracy accepted for True Display Orientation
Left is the same as what is accepted for True Track Angle, True Heading or Magnetic
Heading.
Table 4--21. True Display Orientation Left
If Map Mode Orientation Left indicates:
Then True Display Orientation Left =
Track Up
True Track Angle
Heading Up
True Heading OR (Magnetic Heading -Magnetic Variation)
North Up OR Other
INVALID
(27) True Display Orientation Right
The T2CAS updates the True Display Orientation Right data based on Table 4--22.
The minimum External Sensor input accuracy accepted for True Display Orientation
Left is the same as what is accepted for True Track Angle, True Heading or Magnetic
Heading.
Table 4--22. True Display Orientation Right
If Map Mode Orientation Right indicates:
Then True Display Orientation Right =
Track Up
True Track Angle
Heading Up
True Heading OR (Magnetic Heading -Magnetic Variation)
North Up OR Other
INVALID
(28) Display Range Left/Right
The T2CAS Display Range input parameter is updated from the EFIS Control Panel.
The range selections are dependant on the type of Display installed.
The minimum External Sensor input accuracy accepted is 1.0 nmi.
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E.
TAWS/RWS Discrete Inputs
The specifics of the following discrete (e.g. ground/open, +28 Vdc/open, definition of
open/ground states, etc.) are aircraft dependant and will be defined in the ASDB.
(1) Landing Gear Down
The Landing Gear Down input Discrete is used on installations where T2CAS is
performing both the TAWS and RWS functions.
This Discrete input is shared between the TCAS and TAWS functions with separate
internal wiring. The T2CAS computer unit monitors this discrete to update the landing
gear position.
(2) Landing Flap
The Landing Flap Discrete input is used for GPWS Mode 2, GPWS Mode 4 and
Windshear Caution/Warning Calculations.
This discrete indicates whether or not the Flaps are in the correct position for aircraft
landing.
(3) Terrain Inhibit
When the Terrain Inhibit switch is engaged, all TAWS aural and visual alerts are
inhibited. The Auto Pop--up feature, being based on these alerts, is suppressed as
well. The terrain image, if selected for display, is removed and a ”TERRAIN
INHIBITED” message is displayed. This inhibit feature is typically used to avoid
nuisance alerts during operation around airports that are not in the terrain database,
or during approach under VFR conditions at airports in close proximity to terrain
features. The Terrain Inhibit must be manually de--selected.
(4) Steep Approach
The Steep Approach Discrete input enables Mode 1 Steep Approach alert biasing.
This discrete is typically enabled by an Autopilot Flight Deck switch and is used to
reduce nuisance alerts during aircraft steep approach landings.
(5) Glideslope Inhibit
The Glideslope Inhibit Discrete input is used to inhibit Mode 5 Glideslope alerting.
This discrete would typically be enabled by a Flight Deck switch during back--course
approaches (see ILS Back--Course).
(6) Glideslope Cancel
The Glideslope Cancel Discrete input is typically a Flight Deck switch that is used to
cancel Glideslope alerting when an unreliable Glideslope is expected or when
maneuvering is required during ILS final approach.
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(7) Decision Height /Minimum Descent Altitude Selection (DH/MDA)
The DH/MDA Discrete input is used select either the Decision Height or Minimum
Descent Altitude input. The selected DH or MDA is used to determine Altitude
Call--Outs.
(8) Below Decision Height
The Below Decision Height Discrete input is to trigger Altitude Call--Outs.
(9) Aircraft On Ground
The Aircraft On Ground Discrete input is shared between the TCAS and TAWS
functions with separate internal wiring.
(10) ILS Back Course
The ILS Back Course Discrete input is used to indicate that a back--course landing
approach has been selected/detected.
A back--course approach is a landing approach in which the localizer signal lobes
have been reversed. Typically the back--course switch is selected on the Auto--Pilot
control panel and will compensate for the reversal of the localizer radio beams.
Additionally, when Back--Course is selected, the Glideslope radio beams become
invalid )resulting in the Glideslope Inhibit discrete being set).
(11) Altitude Callout Disable
The Altitude Callout Disable Discrete input is used to disable all altitude call--outs.
(12) Engine Out
When set, the Engine Out discrete indicates that one or more aircraft engines is
inoperative. The Engine Out data is used as part of the aircraft performance
calculations during a TAWS or Windshear event.
F.
TAWS/RWS Digital Output Data
(1) GCAM Event Data
The T2CAS TAWS/Windshear events are caused by terrain and weather conditions.
An event begins when a terrain or weather condition causes the T2CAS to declare a
TAWS/Windshear caution or warning alert or when the aircraft telemetry causes a
Bank Angle Callout. This data is set at each apparition of alert (caution or warning)
and contains information about the triggering event. The T2CAS then transmits the
GCAM Event Data over one of the programmable ARINC 429 output Buses in
Table 4--14.
Table 4--23 shows the GCAM Event Data Labels transmitted on the A429 output Bus.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--23. A429 Output Bus GCAM Event Data Labels
Label Number
Data Name
100
Vertical speed
101
Ground speed
102
True Track Angle
103
Radio Altitude
104
Flight Path Angle
105
Current aircraft weight
106
Latitude
107
Longitude
110
Altitude
111
Navigation accuracy
112
Static Air temperature
113
Roll Angle
114
Computed Air Speed
115
Selected Runway Heading
116
Glide slope deviation
117
Localizer deviation
120
Body axis longitudinal acceleration
121
Body axis normal acceleration
122
Pitch angle
123
Flap angle
124
Slat angle
125
Baro Altitude Rate
126
True airspeed
127
Body Angle of attack left
130
Body Angle of attack right
131
True Display Orientation #1
132
True Display Orientation #2
133
Display Range #1
134
Display Range #2
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Table 4--23. A429 Output Bus GCAM Event Data Labels(cont)
Label Number
270
(Discrete Data)
Data Name
Gear in Landing
Flaps in Landing
Terrain Inhibit
GPWS Inhibit
Steep approach
Glideslope Inhibit
Glideslope cancel
DH/MDA Selection
Below Decision Height
ILS Backcourse
Engine out
Callout disable
Aircraft on ground
Warm Start
Flight Phase read at warm start
GCAM flight Phase
(2) GCAM Data
The GCAM Data output relays information about the GCAM, which is set at each
computation cycle.
(3) GCAM General Purpose
The GCAM General Purpose output relays information about the GCAM as set in the
APM.
(4) Terrain Awareness Display Output
Terrain Awareness Display Images are transmitted to the display using the ARINC
708A format.
NOTE:
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Although Draft characteristic ARINC 453 is engrained in industry
terminology, ARINC 453 was never adopted as a characteristic. ARINC 453
has been superceded and included into the ARINC 708A characteristic.
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The ARINC 708A formatted terrain display is transmitted as a series of 1600--bit
words, each word containing color information along a specific angle radial. The
refresh rate of the entire image is based on the number of radials transmitted. A
transmission interval of 5.00 milliseconds per radial with a total of 513 radials per
image results in an image refresh interval of 2.565 seconds with an acceptable level
of image clarity.
(5) OMS Fault Summary Word
The T2CAS transmits the OMS information (overall fault bit, status of all ARINC 429
digital input buses, and status of all BITE tests) listed in Table 4--24, Table 4--25 and
Table 4--26, OMS Fault Summary Words.
OMS Fault Summary Discrete Word
429 Label: 350, 351, and
352 (Octal)
Units: N/A
Max Range: N/A
Appox. LSB: N/A
Data Bits: 19
11 -- 29
Sign Bit: None
Pad Bits: None
Transmit Interval: 100ms
Data Type: Discrete
Table 4--24. OMS Label 350 Discretes
Bit
FUNCTION
DESCRIPTION
11
TAWS Fail (overall fault bit)
0 = Normal, 1 = Fail
12
ARINC 429 Input #1 Fail
0 = Normal, 1 = Fail
13
ARINC 429 Input #2 Fail
0 = Normal, 1 = Fail
14
ARINC 429 Input #3 Fail
0 = Normal, 1 = Fail
15
ARINC 429 Input #4 Fail
0 = Normal, 1 = Fail
16
ARINC 429 Input #5 Fail
0 = Normal, 1 = Fail
17
ARINC 429 Input #6 Fail
0 = Normal, 1 = Fail
18
ARINC 429 Input #7 Fail
0 = Normal, 1 = Fail
19
ARINC 429 Input #8 Fail
0 = Normal, 1 = Fail
20
ARINC 429 Input #9 Fail
0 = Normal, 1 = Fail
21
ARINC 429 Input #10 Fail
0 = Normal, 1 = Fail
22
ARINC 429 Input #11 Fail
0 = Normal, 1 = Fail
23
ARINC 429 Input #12 Fail
0 = Normal, 1 = Fail
24
ARINC 429 Input #13 Fail
0 = Normal, 1 = Fail
25
ARINC 429 Input #14 Fail
0 = Normal, 1 = Fail
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 4--24. OMS Label 350 Discretes(cont)
Bit
FUNCTION
DESCRIPTION
26
ARINC 429 Input #15 Fail
0 = Normal, 1 = Fail
27
ARINC 429 Input #16 Fail
0 = Normal, 1 = Fail
28
ARINC 429 Input #17 Fail
0 = Normal, 1 = Fail
29
ARINC 429 Input #18 Fail
0 = Normal, 1 = Fail
Table 4--25. OMS Label 351 Discretes
Bit
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FUNCTION
DESCRIPTION
11
A/D Converter and Analog
Multiplexer Monitor
0 = Normal, 1 = Fail
12
Analog LRU Input Monitor
0 = Normal, 1 = Fail
13
APM Test
0 = Normal, 1 = Fail
14
APM Monitor
0 = Normal, 1 = Fail
15
ARINC 429 Input Bus Monitor
0 = Normal, 1 = Fail
16
ARINC 429 Receiver Loop Back Test
0 = Normal, 1 = Fail
17
ARINC 429 Transmitter Monitor
0 = Normal, 1 = Fail
18
ARINC 453 Transmitter Monitor
0 = Normal, 1 = Fail
19
Compact Flash Data Loader Test
0 = Normal, 1 = Fail
20
CPLD Register Test
0 = Normal, 1 = Fail
21
Discrete Outputs Monitor
0 = Normal, 1 = Fail
22
EDC Monitor
0 = Normal, 1 = Fail
23
EEPROM Monitor
0 = Normal, 1 = Fail
24
Exception Interrupt Monitor
0 = Normal, 1 = Fail
25
External Interrupt Controller Test
0 = Normal, 1 = Fail
26
Flash EPROM Test/Monitor
0 = Normal, 1 = Fail
27
FPGA Program Test
0 = Normal, 1 = Fail
28
HBM Test
0 = Normal, 1 = Fail
29
HBM Monitor
0 = Normal, 1 = Fail
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 4--26. OMS Label 352 Discretes
Bit
FUNCTION
DESCRIPTION
11
MMU Partition Test
0 = Normal, 1 = Fail
12
Over--Temperature Monitor
0 = Normal, 1 = Fail
13
PCI Bus Monitor
0 = Normal, 1 = Fail
14
PCI Bus Configuration Test
0 = Normal, 1 = Fail
15
Power Fail Monitor
0 = Normal, 1 = Fail
16
Power Supply Monitor
0 = Normal, 1 = Fail
17
SDRAM Flash Copy Monitor
0 = Normal, 1 = Fail
18
SDRAM/EDC Test
0 = Normal, 1 = Fail
19
Software Event Log
0 = Normal, 1 = Fail
20
Software Heartbeat Monitor
0 = Normal, 1 = Fail
Spare
0 = Normal, 1 = Fail
21--29
G. TAWS/RWS Discrete Output Data
(1) Ground Discrete Parameters
This section describes the T2CAS TAWS/RWS ground discrete outputs. The ground
discrete outputs are used to drive alert lamps and are not activated when power is
removed from the LRU. All Ground discretes in this section are dependant on the
aircraft Flight Deck configuration and subsequent ASDB settings.
(a) Alert Prioritization Output 1 -- 4
These discretes exist to inform external LRUs that T2CAS has a higher priority
alert. For example, on the input side, if the Alert Prioritization Input 2 Value was
’5’ and the Alert Prioritization Input 2 Discrete became active because an
engine--out condition was detected, the T2CAS would suppress all of its alerts of
lower priority but still allow output alerts of priority 1 through 4. On the output
side, the T2CAS would set only the Alert Prioritization Output # discretes to
active whose corresponding values are of lower priority than the alert. Other
LRUs capable of sensing the states of these discretes would suppress their own
alerts of lower priority.
(b) Audio On
The Audio On output discrete is used to inhibit other audio systems (e.g., TCAS)
during GPWS warnings. In addition, it can be used to drive the audio key line
input provided on some aircraft audio systems.
The Audio On discrete is activated whenever any aural message is being
annunciated and it remains activated until the aural message is completed.
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(c) Glideslope Cancel Indicator
The Glideslope Cancel Indicator output discrete is activated when the T2CAS
detects the Glideslope Cancel input discrete is active AND the aircraft is at a low
altitude (below 2000 ft. radio altitude).
(d) Ground Proximity Caution Alert
Used to activate the GPWS Caution Alert lamp.
(e) Ground Proximity Warning Alert
Used to activate the GPWS Warning Alert lamp.
(f)
TAWS Caution Alert
Used to activate the TAWS Caution Alert lamp.
(g) TAWS Warning Alert
Used to activate the TAWS Warning Alert lamp.
(h) Terrain Mode Display #1/Terrain Mode Display #2
The Terrain Display Switch output discretes are used to activate external relays
that make the switch between Weather and Terrain. When the relay is activated
(IO_TERRAIN_DISPLAY_SWITCH_# is Active), Terrain is displayed. When the
relay is de--activated (IO_TERRAIN_DISPLAY_SWITCH_# is Not Active),
Weather is displayed.
This output discrete can be activated/de--activated by one of two methods: Pilot
selection via a control panel pushbutton, or as a result of the auto pop--up
feature. In the event that the TAWS function generates an alert, terrain is
automatically selected for display.
(i)
Windshear Caution Alert
Used to activate the Windshear Caution Alert lamp.
(j)
Windshear Warning Alert
Used to activate the Windshear Warning Alert lamp.
(2) Ground Discrete Monitor Parameters
This section describes the T2CAS TAWS/RWS ground discrete monitor outputs. The
ground discrete monitor outputs are used to signal failure conditions and are
activated (grounded) when power is removed from the LRU.
(a) GCAM Fail Indicator
Used to activate the GCAM Fail lamp.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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(b) GCAM Inop Indicator
Used to activate the GCAM Inop lamp.
(c) GPWS Fail Indicator
Used to activate the GPWS Fail lamp.
(d) GPWS Inop Indicator
Used to activate the GPWS Inop lamp.
(e) Terrain Fail Indicator
Used to activate the Terrain Fail lamp.
(f)
Terrain Inop Indicator
Used to activate the Terrain Inop lamp.
(g) Windshear Fail Indicator
Used to activate the Windshear Fail lamp.
(h) Windshear Inop Indicator
Used to activate the Windshear Inop lamp.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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ADJUSTMENT/TEST
1. General
The procedures that follow are designed to check for proper operation and satisfactory
installation of the T2CAS Traffic and Terrain Collision Avoidance System components.
Should any failures occur while performing the check out procedures, refer to FAULT
ISOLATION as required.
2. Equipment
See Table 5--1 for equipment required to test the unit.
Table 5--1. Equipment
Name
Description
Source
Digital Multimeter
Fluke Model 29 Digital
Multimeter
John Fluke Mfg Co Inc.,
Everett, WA
TCAS Ramp Tester
TCAS--201 Reply Generator
Traffic Alert and Collision
Avoidance System Test Set
IFR Systems, Inc.
Wichita, KS
NOTE:
Equivalent alternatives are permitted for equipment in this list.
3. Initial Harness Checkout (New Installations Only)
A. T2CAS Computer Unit Harness Checkout
Check the T2CAS computer unit’s mounting tray connector pins referenced in Table 5--2,
to make sure they are not connected or shorted to ground. A ground on these pins can
cause damage or degrade system performance.
Table 5--2. Computer Unit Harness Checkout
Connector Pin No.
Pin Function
P1C--1 (LBP)
115 V AC (H) T2CAS
P1C--5 (LBP)
115 V AC (H) External Fan
P1C--10 (LBP)
28 V AC T2CAS Power
B. T2CAS Controller and Display Unit Harness Checkout
Refer to the applicable controller and display unit interconnect diagrams to do continuity
measurements and to ensure confidence in wiring for these units.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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C. LRU Preinstallation Power Checkout
Before you do any operational tests, a power--on check is recommended to reduce the
possibility of damage to newly installed system components due to miswired power leads.
(1) Make sure all T2CAS system components are removed from their mounting trays or
that their aircraft mating connector(s) are disconnected.
(2) Connect external power to aircraft.
(3) Close all T2CAS system 115 V, 400 Hz circuit breakers, if applicable, and check for
115 V ac at the appropriate LRU mating connector pins. Refer to the applicable
interconnect diagrams for LRU pin numbers.
(4) Close all T2CAS system 28 V dc circuit breakers, if applicable, and check for 28 V dc
at the appropriate LRU mating connector pins. Refer to the applicable interconnect
diagrams for LRU pin numbers.
(5) If power is misapplied on any connector pin, open the circuit breaker and rework
miswired harness.
(6) Remove aircraft power.
D. Initial System Installation Operational Test
The initial checkout of a newly installed system should start with a system self--test and
then be followed by a ramp test. The system self--test procedures are referenced in
paragraph 4.A. The ramp tests should include a Scenario Test and a Power and
Frequency Test. Refer to the applicable TCAS Ramp Tester Operation Manual for
procedures to do these tests.
If an ACSS VSI/TRA is used as the display instrument, it contains a feature that displays
some typical installation errors. See Figure 5--1. If an error is detected during initial
installation checkout, the VSI/TRA displays the error as follows:
(1) Removes all symbology from the display.
(2) Displays a red X that covers the entire screen.
(3) Displays a two digit error code as follows:
• 00 = Invalid discrete setting at power--up
• 01 = Invalid light curve setting specified at power--up
• 03 = Bad checksum detected at power--up
• 04 = Illegal op--code test failed
• 05 = Unsupported test failed.
(4) Strobes the watchdog timer to keep the red X and status displayed.
NOTE:
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If the VSI/TRA displays error code 10, 11, 12, 29, 30, 31, or 40, an internal
VSI/TRA failure has been detected.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Figure 5--1. VSI/TRA Fault Warning Display
4. System Self--Tests
A. TCAS Flight Deck Display Test Modes
The T2CAS TCAS System provides two types of test modes; a short functional test mode
and an extended maintenance test. Both test modes can be activated by the TEST
button or switch on the ATC/TCAS Control Panel. The short test mode can also be
activated by a central maintenance computer (CMC) or a central fault display interface
unit (CFDIU). The extended test mode can only be initiated at the end of the short test.
The short test mode is inhibited in the air if the Self--Test Inhibit programming pin
(RBP--8E) is grounded.
(1) Short Test Mode
The short test mode provides a flight deck initiated functional test of the TCAS RA
and TA displays and associated TCAS interfaces. It also provides an aural
annunciation of the TCAS system status.
The short test mode is available in all TCAS operational modes (Standby, TA Only, or
TA/RA) when on the ground. If a TA or RA occurs while airborne, the test is
terminated and normal operating status is resumed. The test mode is also
terminated if any of the Advisory Inhibit discrete inputs (grounds) are received on pins
RBP--5A, RBP--5B, RBP--5C, or RBP--5D.
Push and hold the TEST button/switch on the ATC/TCAS controller for a few seconds
to start the test. When the test mode becomes active, the words “TCAS Test” are
transmitted once aurally. In addition to the TCAS test pattern, RA indications and a
red TCAS TEST annunciation are displayed on the applicable display(s). Refer to
Figure 1--18 for a typical test pattern display on the VSI/TRA.
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At the completion of the test (8--seconds), the words “TCAS Test Pass” should be
transmitted once aurally. In addition, the test pattern is removed from the display(s)
and a TCAS PASS annunciation is displayed. If the test fails, the words “TCAS Test
Fail” are transmitted once aurally and a TCAS FAIL annunciation is displayed on the
applicable display(s).
If the TCAS short test fails, do the TCAS Computer Unit Self--Test procedures
referenced in paragraph 4.C. to determine which LRU or subsystem is not functioning
properly. To troubleshoot the system, refer to the procedures in the FAULT
ISOLATION section.
(2) Extended Test Mode
The extended test mode provides a flight deck initiated test that displays various
pages of text information that is selected by the ATC Mode S control panel 4096
code switches. This test mode is accessible only when on the ground and cannot be
initiated while airborne.
The extended test mode is used for maintenance purposes only. It displays various
pages of text information containing the TCAS software part number, fault messages,
status of program pins, analog and digital inputs, and other aircraft parameters.
To start the test, push and hold the TEST button/switch on the ATC/TCAS controller
for a minimum of 9 seconds. In addition the conditions that follow must occur:
• TCAS is in Standby
• The selected transponder is in Standby
• Aircraft is on the ground (The AIR/GND discrete [RMP--5K] is grounded)
• Landing gear is extended (Landing Gear discrete [RMP--13F] is grounded).
Once the extended test mode is established, the 4096 code switches on the
ATC/TCAS controller are used to select the desired maintenance page for display.
Table 5--3 lists the extended mode page names and numbers and the corresponding
4096 Ident Code number.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 5--3. Extended Test Menu Selections
4096 Ident Code Number
Page
Page Name
0000
System Status
0001
Display Status
0002
Rad/Alt Status
0003
Xpdr Status
0004
Program Pins 1/3
0005
Program Pins 2/3
0006
Program Pins 3/3
0007
Help Reference
0011
11
Antenna Port Status
0012
12
Option Pins Status
All Other Codes
Blank
TCAS Test Menu
To view the TCAS test menu and system status pages along with the troubleshooting
messages, refer to the FAULT ISOLATION section.
To exit the extended test mode, set the ATC/TCAS mode selector switch to Mode S
ON.
B. TAWS/RWS Flight Deck Display Test Modes
The T2CAS TAWS/RWS System provides two types of test modes; a standard functional
test mode and an extended maintenance test. Both test modes can be activated by the
TAWS/RWS/GPS TEST button or switch on the Flight Deck. The short test mode can
also be activated by a central maintenance computer (CMC) or a central fault display
interface unit (CFDIU). The extended test mode can only be initiated at the end of the
short test.
(1) Standard Test Mode
The standard test mode provides a flight deck initiated functional test of the aural
annunciations, lamp tests, and display activity.
The Standard Self--Test is performed by activating either the CMC self--test or the
self--test discrete input (RTP--10E = GND). The Standard Self--Test can occur while
on the ground or while in the airborne state.
Upon activating the Standard Self--Test the following will occur:
The Standard Self--Test will not be initiated if a TAWS alert is present when either
the CMC self test or the self test discrete input is activated.
If the T2CAS unit has the windshear function enabled, the following aural
annunciation will occur:
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
”TERRAIN AWARENESS AND WINDSHEAR TEST START”
If the T2CAS unit does not have the windshear function enabled, the following
aural annunciation will occur:
”TERRAIN AWARENESS TEST START”
During the Standard Self--Test the following will occur:
All discrete outputs implemented within a specific aircraft installation will be
tested for over current and output voltage levels by activating the output for 1.5
seconds (±100 milliseconds), then deactivating the output for 1.5 seconds (±100
milliseconds), and then reactivating the output for 1.5 seconds (±100
milliseconds). Any faults found will be recorded in the T2CAS unit’s nonvolatile
memory.
The T2CAS unit will verify the following functional areas in accordance with
Figure 1--32.
• Aircraft Personality Module (APM)
• Terrain Database CRC
• External System Inputs
• Internal TAWS Parameters
• Internal GPS Parameters (if installed)
The T2CAS unit will display a multicolor test pattern on both the captain’s and first
officer’s TAWS displays. Figure 1--33 shows a typical multicolor test pattern.
The T2CAS unit will interrupt the Standard Self--Test when any of the following alerts
occur:
• “WINDSHEAR, WINDSHEAR, WINDSHEAR”
• “TERRAIN AHEAD, PULL UP”
• “TERRAIN TERRAIN, PULL UP PULL UP”
• “≈≈ PULL UP”
• “TERRAIN AHEAD”
• “TERRAIN CAUTION”
• “AVOID TERRAIN”
• “PULL UP, PULL UP”
• “TERRAIN, TERRAIN”
• “SINK RATE, SINK RATE”
• “DON’T SINK, DON’T SINK”
• “TOO LOW, TERRAIN”
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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• “TOO LOW, GEAR”
• “TOO LOW, FLAPS”
• “GLIDESLOPE”
NOTE:
“≈≈” designates a pair of varying tones from 400 to 800 Hz; where each
tone is 0.3 seconds in duration, separated by 0.1 seconds, and at the end of
the pair there is 0.1 seconds of silence.
NOTE:
The aural annunciations listed above will depend on the Operator Selectable
Options chosen during installation of the T2CAS unit.
Upon completion of the Standard Self--Test the following will occur:
If the T2CAS unit has the windshear function enabled and the APM and Terrain
Database and Internal system and Internal GPS self--tests have passed, the
following aural annunciation will occur:
”TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”
If the T2CAS unit does not have the windshear function enabled and the APM
and Terrain Database and Internal system and Internal GPS self--tests have
passed, the following aural annunciation will occur:
”TERRAIN AWARENESS TEST PASSED”
If the T2CAS unit does not have the windshear function enabled and the APM or
Terrain Database or Internal system or Internal GPS self--tests have failed, the
following aural annunciation will occur:
”TERRAIN AWARENESS AND WINDSHEAR TEST COMPLETE”
If the T2CAS unit does not have the windshear function enabled and the APM or
Terrain Database or Internal system or Internal GPS self--tests have failed, the
following aural annunciation will occur:
”TERRAIN AWARENESS TEST COMPLETE”
If the TAWS/RWS standard test fails, do the T2CAS Computer Unit Self--Test
procedures referenced in paragraph 4.C. to determine which LRU or subsystem is
not functioning properly. To troubleshoot the system, refer to the procedures in the
FAULT ISOLATION section.
(2) Extended Test Mode
The Extended Self--Test can only be entered at the completion of the Standard
Self--Test. The Extended Self--Test can only be entered while on the ground
(RMP--5K = GND). The Extended Self--Test is activated at the end of the Standard
Self--Test by activating the self--test discrete input (RTP--10E = GND) for a minimum
of 3 seconds within 3 seconds after the initial aural annunciation (”TERRAIN
AWARENESS AND WINDSHEAR TEST COMPLETE” or ”TERRAIN AWARENESS
TEST COMPLETE ” or ”TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”
or ”TERRAIN AWARENESS TEST PASSED”) occurs. This activation sequence is
summarized in Figure 5--2.
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Figure 5--2. Extended Self--Test of TAWS/Windshear Functional Areas
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Upon activating the Extended Self--Test the T2CAS unit will display the Extended
Self--Test Introduction page on both the captain’s and first officer’s TAWS displays.
While in the Extended Self--Test:
(a) The T2CAS unit will display the next Extended Self--Test page when the self--test
discrete input (RTP--10E) is active for less than or equal to three seconds.
(b) Each subsequent activation of the self--test discrete input will result in the T2CAS
unit displaying the next Extended Self--Test page.
(c) The following is a listing of Extended Self--Test information pages available for
display:
Information Displayed
Pages
Introduction
0, 1
Part Numbers
2, 3, 4, 5, 6
The T2CAS unit will exit the Extended Self--Test when the self--test discrete input
(RTP--10E) is active for greater than three seconds or the aircraft transitions from
ground to air (RMP--5K = OPEN).
C. T2CAS Computer Unit Self--Test
The Front Panel has a test switch to initiate testing of T2CAS as well as LED indicators
which are used for the annunciation of internal LRU or external system faults for T2CAS.
There are two sets of LED indicators, one set pertains to the TCAS function and TCAS
external I/O; the other set pertains to the TAWS/RWS and internal GPS functions.
The testing for T2CAS is initiated through the test switch on the front of the LRU. TCAS
and TAWS/RWS functions both monitor the switch and initiate a test sequence when the
switch is pressed. The test results for both functions are annunciated on their respective
LED displays.
(1) With all power off, reinstall the T2CAS computer unit in its mounting tray. Make sure
the TCAS control panel and display(s) are also installed.
(2) Apply aircraft power and close all applicable T2CAS system circuit breakers.
(3) On the TCAS control panel, set the ATC/TCAS controller mode switch to Mode S ON.
(4) Push the PUSH TO TEST button on the T2CAS computer unit front panel. The
TCAS and TAWS/RWS test sequence that follows should occur:
• All TCAS computer unit front panel annunciators come on for a 3--second lamp
test.
• If the TCAS is operational, the TCAS PASS green annunciator comes on for a
10--second display period and then goes off.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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• If the TCAS is not operational, one or more of the red fault annunciators comes on
for a 10--second display period.
• For TAWS/RWS, an LED test will occur where all LEDs, on the T2CAS unit, will be
lit for a minimum of 1.5 seconds in the following colors:
-- TAWS P/F STATUS: Red
-- TAWS I/O FAIL: Amber
-- TAWS APM FAIL: Amber
-- XFER IN PROCESS: Green
-- C/F LOAD STATUS: Red
• For TAWS/RWS, an LED test will occur where all LEDs, on the T2CAS unit, will
then be lit for a minimum of 1.5 seconds in the following colors:
-- TAWS P/F STATUS: Green
-- TAWS I/O FAIL: Amber
-- TAWS APM FAIL: Amber
-- XFER IN PROCESS: Green
-- C/F LOAD STATUS: Green
• During the TAWS/RWS LED test, the last 10 flight legs will be reviewed for faults.
After the LEDs are illuminated, as described above, if a fault has occurred during
the last 10 flight legs then the LED associated with that fault will be lit for 11
seconds ±1 second in the following colors:
-- TAWS P/F STATUS: Red
-- TAWS I/O FAIL: Amber
-- TAWS APM FAIL: Amber
-- XFER IN PROCESS: --- C/F LOAD STATUS: Red
• During the TAWS/RWS LED test, all discrete outputs implemented within a specific
aircraft installation will be tested for over current and output voltage levels by
activating the output for 1.5 seconds (±100 milliseconds), then deactivating the
output for 1.5 seconds (±100 milliseconds), and then reactivating the output for 1.5
seconds (±100 milliseconds). Any faults found will be recorded in the T2CAS
unit’s nonvolatile memory. At the end of this test the XFER IN PROCESS LED will
be extinguished.
During the TAWS/RWS LED test, each time the push to test button (on the T2CAS
unit) is reactivated, the following will occur in the order presented:
(a) All front TAWS/Windshear LEDs will be lit for 1 second (± 0.5 seconds) in the
following colors:
• TAWS P/F STATUS: Red
• TAWS I/O FAIL: Amber
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
• TAWS APM FAIL: Amber
• XFER IN PROCESS: Green
• C/F LOAD STATUS: Red
(b) The XFER IN PROCESS LED and C/F LOAD STATUS LED will be extinguished.
(c) The TAWS P/F STATUS, TAWS IO FAIL, TAWS APM FAIL and C/F LOAD
STATUS LEDs will be set for the fault information of the current and previous
flight legs for a period of 11 seconds ( ±1 second). The first time the push to test
button, on the T2CAS unit, is depressed the current flight leg information is
displayed. Subsequent activations of the push to test button, on the T2CAS unit,
will display faults from previous flight legs in order from most recent to least
recent.
(d) If the push to test button, on the T2CAS unit, is reactivated during the display of
the tenth previous flight leg fault information (or during the display of the oldest
flight leg stored in the BITE log), then the LEDs, on the T2CAS unit, will flash at 2
Hz for 3 seconds and then extinguish, terminating the display mode.
(5) If a TCAS or TAWS/RWS fault is detected, refer to the Fault Isolation section for
troubleshooting information.
5. Return to Service Test
Any time a T2CAS LRU is removed and replaced following repair or maintenance, a return to
service test is required. The System Self--Test procedures referenced in paragraph 4.A. and
4.B. are sufficient to check all system parameters.
NOTE:
Anytime the T2CAS APM is removed and replaced, the APM must be reconfigured
using the procedures in section 6.C. or 6.D.
6. Operational Software Loading Using an ARINC Portable Data Loader,
RS232 Port or Compact Flash Card
When updating the TT--950/951/952 Computer Unit with an ARINC portable data loader PDL
or Compact flash card, verify the current TT--950/951/952 Computer Unit software part
number prior to continuing for Flight Deck system only.
NOTE:
The TCAS operational software can ONLY be loaded using a conventional ADL/PDL
dataloader and the TAWS/RWS operational software and Database can ONLY be
loaded using the Compact flash card. Additionally, the TAWS/RWS APM
Configuration Data (referred to as ACD) and APM Application Data (referred to as
Aircraft Specific Database or ASDB) can be dataloaded using either a Compact Flash
card or through the RS232 interface.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
A. Current Software Verification
NOTE:
Software verification using Flight Deck systems ONLY.
(1) TCAS Software Verification
Verify the current software part number according to the extended maintenance
capabilities on status page code 0000 in the FAULT ISOLATION section of this
manual or the individual aircraft maintenance manual (refer to the onboard
maintenance system program).
(2) TAWS/RWS Software Verification
Verify the current software part number according to the extended maintenance
capabilities Part Number Page.
B. Portable Data Loader -- TCAS Operational Software Loading (While Installed on
Aircraft)
(1) Verify that the system inputs for AIR/GROUND (RMP--5K) and GEAR UP/DOWN
(RMP--13F) are grounded.
(2) Obtain an ARINC PDL and the appropriate interface cable for connecting the data
loader to the J1 (front) connector of the TT--950/951/952 Computer Unit.
The following PDLs have been tested and found to be satisfactory for performing this
task:
• DEMO Systems -- Part No. 30100 (Revision A and later versions)
• Teledyne -- Part No. 2230915--01--D
• SFIM -- Part No. YV68A110.
Other part numbers from these suppliers and ARINC 615 data loaders from other
manufacturers may perform the task successfully. However, ACSS can not verify
their usability.
(3) Shut off the PDL and remove power from the TT--950/951/952 Computer Unit.
Connect the cable between the PDL and the J1 front connector on the
TT--950/951/952 Computer Unit.
(4) Apply power to the TT--950/951/952 Computer Unit.
(5) Turn on the PDL.
(6) Obtain the operational software. Insert disk No. 1 of the operational software into the
PDL for program uploading (or follow the applicable instructions for the PDL).
(7) After the PDL indicates that the disk upload was successful, repeat step (6) for
multiple disks, if necessary.
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(8) Wait at least 20 seconds after the last disk has finished uploading. Then turn off the
PDL, remove power from the TT--950/951/952 Computer Unit, and disconnect the
interface cable.
(9) Apply power to the TT--950/951/952 Computer Unit and ensure the TCAS system is
fully operational. Push the PUSH TO TEST button located on the front panel. The
green LED indicator on the front of the panel lights at the end of the test cycle
(approximately 8 seconds) to show the TCAS system is functional.
C. Compact Flash Card -- TAWS/RWS Operational Software/ACD/ASDB Loading
(While Installed on Aircraft)
Due to the size of the TAWS/RWS operational software and database (in excess of 60
megabytes), the use of an ARINC 615 data loader is not feasible for TAWS/RWS
dataloading. As such, a high speed data loading method is provided using a Compact
PC Flash Card. The unit’s front panel has an access plate that allows a Compact PC
Flash Card to be inserted.
(1) Verify that the system inputs for AIR/GROUND (RMP--5K) and GEAR UP/DOWN
(RMP--13F) are grounded.
(2) Obtain the operational software and/or applicable TAWS/ACD/ASDB Database
(3) Apply power to the TT--950/951/952 Computer Unit.
(4) Insert the Compact Flash Card
NOTE:
When a Compact Flash Card is inserted the T2CAS will blink the front panel
”XFER IN PROCESS” LED to indicate that a Compact Flash Card is
detected, but uploading or downloading has not begun.
(5) Once Software Upload has started the Dataload status will be indicated by the LEDs
on the front of the T2CAS Computer Unit. The LED correlations expected for the
various upload events are shown in Table 5--4.
(6) After Uploading has completed (Green CF Status LED), remove the Compact Flash
Card and the T2CAS will automatically restart.
Table 5--4. Compact Flash Upload / LED correlation
Triggering Event
CF Status LED
CF Card Inserted
XFER IN
PROCESS LED
Blink
Fault Type
Logged
Ending Event
CF UPLOAD
REQUEST
CRC 1 completed
Corrupt CF header
Red
CF FILE ERROR
CF Card removed
Upload Card
Inserted while
Airborne
Red
CF FILE ERROR
CF Card removed
Incorrect
Configuration Error
Red
CF FILE ERROR
CF Card removed
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 5--4. Compact Flash Upload / LED correlation(cont)
Triggering Event
CF Status LED
XFER IN
PROCESS LED
Fault Type
Logged
Ending Event
Major/Minor
Incompatibility
Red
CF FILE ERROR
CF Card removed
File Header CRC
error
Red
CF FILE ERROR
CF Card removed
File does not exist
error
Red
CF FILE ERROR
CF Card removed
Multiple file error
Red
CF FILE ERROR
CF Card removed
File Image CRC
error (CRC 1)
Red
CF FILE ERROR
CF Card removed
CF LOAD
CF Card error is
detected or upload
completed or restart
CRC 1 completed
Green
Aborted Upload
Red
CF WRITE ERROR 10 seconds after
card removal
Airborne Upload
Red
CF FILE ERROR
CF Card removed
CF FILE ERROR
CF Card error is
detected or upload
completed or restart
Ground--to--air
transition during
upload
Green (per normal
uploading
sequence)
Flash Copy CRC
fails to match CF
File CRC (CRC 2)
Red
CF WRITE ERROR Card removal
Flash Copy 2 fails
to match CRC at
Copy 1 location
Red
FLASH EPROM
ERROR
Card removal
APM Calculated
CRC doesn’t match
CF File CRC.
Red
APM WRITE
ERROR -- CF
Upload
Card removal
APM Calculated
CRC doesn’t match
APM embedded
CRC.
Red
APM DATA FAULT
-- CF Upload
Card removal
APM write to Flash
unsuccessful
Red
APM COPY WRITE Card removal
-- CF Upload
APM Calculated
CRC doesn’t match
APM embedded
CRC
Red
APM Copy CRC -CF Upload
Card removal
Green
CF UPLOAD SET
COMPLETE
Card removal
All files loaded
successful
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
D. RS232 -- TAWS/RWS APM Configuration Data and APM Application Data Loading
The T2CAS is capable of uploading the ACD or ASDB while in the air or on the ground,
while using the RS--232 interface with the APM_LOAD XXXX command.
(1) Obtain PC software tool EDDIT (Engineering Diagnostic & Data Interface Transfer)
Part No. 9000286--001.
(2) Obtain or build an RS--232 cable. (Refer to Figure 5--3.)
(3) Turn PC power off.
(4) Remove power from the TT--950/951/952 Computer Unit.
(5) Connect the RS--232 cable from the PC (9--pin connector) to the J1 front connector
on the TT--950/951/952 Computer Unit.
(6) Apply power to the TT--950/951/952 Computer Unit.
(7) Power on the PC to Microsoft Windows operation.
(8) On the PC, follow the Online instructions provided with the EDDIT tool to load the
ASDB file and/or the ACD file.
(9) Shut down the PC and remove power.
(10) Remove power from the TT--950/951/952 Computer Unit.
(11) Disconnect the RS--232 cable from the J1 front connector on the TT--950/951/952
Computer Unit.
E.
Updated Software Verification
(1) Software Verification Using Flight Deck Systems ONLY
(a) TCAS
Verify the updated software part number according to the T2CAS TCAS
extended maintenance capabilities on status page code 0000 in the FAULT
ISOLATION section of this manual or the individual aircraft maintenance manual
(refer to the onboard maintenance system program).
(b) TAWS/RWS
Verify the current software part number according to the extended maintenance
capabilities Part Number Page.
(2) TCAS Software Verification Using a Stand--Alone PC ONLY
Verify the updated TCAS software part number using a stand--alone PC according to
the following procedure.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
(a) Obtain PC software Part No. PS4088035--101.
(b) Obtain or build an RS--232 cable. (Refer to Figure 5--3.)
(c) Shut down and power off the PC.
(d) Remove power from the TT--950/951/952 Computer Unit.
(e) Connect the RS--232 cable from the PC (9--pin connector) to the J1 front
connector on the TT--950/951/952 Computer Unit.
(f)
Apply power to the TT--950/951/952 Computer Unit.
(g) Power on the PC to Microsoft Windows operation.
(h) On the PC, go to START => PROGRAMS => HONEYWELL TOOLS and double
click “TCAS Part Number”.
(i)
Verify the updated TCAS software part number.
(j)
Shut down and power off the PC.
(k) Remove power from the TT--950/951/952 Computer Unit.
(l)
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Disconnect the RS--232 cable from the J1 front connector on the
TT--950/951/952 Computer Unit.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 5--3. RS--232 PC to TCAS Interface Cable
(3) TAWS/RWS Software Verification Using a Stand--Alone PC ONLY
Verify the updated TAWS/RWS software/Database part numbers using a stand--alone
PC according to the following procedure.
(a) Obtain PC software tool EDDIT, Part No. PS4088035--101.
(b) Obtain or build an RS--232 cable. (Refer to Figure 5--3.)
(c) Shut down and power off the PC.
(d) Remove power from the TT--950/951/952 Computer Unit.
(e) Connect the RS--232 cable from the PC (9--pin connector) to the J1 front
connector on the TT--950/951/952 Computer Unit.
(f)
Apply power to the TT--950/951/952 Computer Unit.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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(g) Power on the PC to Microsoft Windows operation.
(h) On the PC, follow the Online instructions provided with the EDDIT tool to
download the TAWS/RWS operational software/Database part numbers.
(i)
Shut down the PC and remove power.
(j)
Remove power from the TT--950/951/952 Computer Unit.
(k) Disconnect the RS--232 cable from the J1 front connector on the
TT--950/951/952 Computer Unit.
(4) TCAS Software Verification Using a Software Verification Fixture ONLY
(a) Obtain Software Verification Fixture (Part No. T326948--901) with associated
adapter cable (Part No. 200F--00084).
(b) Remove power to the TT--950/951/952 Computer Unit.
(c) Connect the adapter cable (Part No. 200F--00084) to the TT--950/951/952
Computer Unit and the software verification fixture.
(d) Apply power to the TT--950/951/952 Computer Unit.
(e) Enable the software verification fixture and verify the appropriate software part
number is displayed in the 15--digit display.
(f)
Perform a TCAS system self--test and verify that TCAS TEST PASS is
annunciated.
NOTE:
The TCAS TEST FAIL message may be annunciated if an LRU that
supplies input to the TT--950/951/952 Computer Unit is not powered on.
(g) If the software part number is not displayed, repeat step (a) thru step (f).
(5) TCAS Software Verification Using a Remote Connected VSI/TRA ONLY
On some aircraft configurations, software verification may be performed using a
remote connected VSI/TRA (Part No. 4067241--861, --862, or --863) display attached
through adapter cable (Part No. 200F--00083) to the J1 front connector of the
TT--950/951/952 Computer Unit during the extended test mode.
Verify the particular aircraft configuration can support a Flight Deck initiated self--test
and be recognized at the 8--second time period after activation.
NOTE:
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CMC/CFDS activated self--test will not be recognized at the 8--second time
period, only an approved TCAS control panel.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
FAULT ISOLATION
1. General
The T2CAS Traffic and Terrain Collision Avoidance System has three optional procedures for
fault detection and isolation to the LRU level. The first option uses the aircraft CMC or central
fault display system (CFDS) if the aircraft is equipped with an onboard maintenance system.
The second option uses a digital interface between the T2CAS Computer Unit and the display
system (Weather Radar, EFIS, or multifunction display for TAWS/RWS and VSI/TRA flat panel
display or EFIS for TCAS). The third option uses the annunciators located on the front panel
of the computer unit. The annunciators are activated by a self--test function within the T2CAS
Computer Unit. Select the procedural option for fault isolation from Fault Isolation paragraph
3 (Procedure), which is applicable to the type of aircraft and the equipment installed.
2. Equipment and Materials
NOTE:
Equivalent alternatives are permitted for equipment in this list.
Digital Multimeter -- Fluke Model 29, John Fluke Mfg Co. Inc., Everett, WA
3. Procedure
A. CMC or CFDS
Fault information can be displayed from an onboard maintenance system when the
aircraft is so equipped. Fault data is accessible only when the aircraft is on the ground.
Faults that occur at any time, on the ground or while airborne, are stored in fault memory
and reported to the CMC or CFDS. All displayed information is in the English language
with abbreviated terms used only as necessary. Refer to the appropriate CMC or CFDS
support manual for fault retrieval procedures.
B. Flight Deck Initiated Self--Test/Fault Display Systems
(1) TCAS
The TCAS display system can be used to display system status and fail messages in
the Flight Deck, making it more convenient to use than the computer unit front panel
annunciators for a quick checkout of the TCAS system. In contrast with the computer
unit self--test, which records and stores faults from previous flights, the display
system test shows only current status and failure data.
To access the Flight Deck display test modes, perform the following procedures:
NOTES:
1.
Fault detection with diagnostics can only be done on the ground. The pilot
has the option to do a pass/fail test while airborne if this feature is not
inhibited.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
2.
This procedure is valid when used with either a single or dual control panel.
(a) Make sure the aircraft configuration indicates Aircraft On Ground and Gear
Extended.
(b) Set the Mode Select switch on the ATC/TCAS control panel to STBY.
(c) Push and hold the TCAS TEST button for a minimum of 9 seconds.
(d) Set the transponder 4096 Ident Code Number to any code except 0000 thru
0007, 0011, or 0012.
NOTE:
Do not use codes 7500, 7600, or 7700; these code are reserved for
emergency operation.
(e) Make sure the TCAS TEST MENU is being displayed on the TCAS display. It
should match the screen shown in Figure 6--1.
(f)
Set the transponder 4096 Ident Code Number to 0000.
(g) If the system passes, a maintenance page similar to that shown in Figure 6--2 is
displayed. A failure results in a referral to one or more specific ident codes. Set
the indicated code on the ATC/TCAS Control Panel and follow the instructions
given.
(h) If the system passes, set the mode switch on the ATC/TCAS Control Panel to
MODE S ON. This allows you to exit the expanded test mode. If a failure is
indicated, set the transponder 4096 Ident Code to the codes indicated by the
automatic referral system. The remaining screens shown in Figure 6--3 thru
Figure 6--13 are examples of the other maintenance pages.
(i)
Set system power to OFF and correct faults by replacing indicated LRUs or by
repairing faulty wiring harness.
(j)
Test system as required after repair.
(2) TAWS/RWS
The TAWS display system (EFIS or weather Radar) can be used to display system
status and fail messages in the Flight Deck, making it more convenient to use than
the computer unit front panel annunciators for a quick checkout of the TAWS system.
In contrast with the computer unit self--test, which records and stores faults from
previous flights, the display system test shows only current status and failure data.To
access the Flight Deck display test modes, do the procedures that follow:
NOTE:
The TAWS/RWS/GPS Fault detection with diagnostics can only be done on
the ground. The pilot has the option to do a pass/fail test while airborne if
this feature is not inhibited.
(a) Make sure the aircraft configuration indicates Aircraft On Ground and Gear
Extended.
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(b) Push and hold the TAWS/RWS/GPS TEST button/switch on the Flight Deck for a
few seconds to start the standard self test.
(c) The extended self--test is then initiated by pushing and holding the
TAWS/RWS/GPS TEST button/switch on the Flight Deck for more than three
seconds, with the initiation beginning between the end of the standard self--test
aural annunciation of one of the following messages and three seconds later:
• “TERRAIN AWARENESS AND WINDSHEAR TEST COMPLETE”.
• “TERRAIN AWARENESS TEST COMPLETE”.
• “TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”.
• “TERRAIN AWARENESS TEST PASSED”.
(d) Once on Extended Self--Test Page One as shown in Figure 6--14, the T2CAS
Extended Self--Test display can be indexed to the next Extended Self--Test page
by pressing the TAWS/RWS/GPS TEST button/switch for three seconds or less.
NOTE:
If the CMC Self--Test Input initiates a standard self--test during the extended
self--test, the T2CAS will replace the extended self--test page with the
multicolor test pattern and begin standard self--test.
(e) After system fault isolation test is completed, the Extended Self--Test pages can
be exited by pressing the TAWS/RWS/GPS TEST button/switch for more than
three seconds.
(f)
Set system power to OFF and correct faults by replacing indicated LRUs or by
repairing faulty wiring harness.
(g) Test system as required after repair.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
C. T2CAS Aural and Visual Annunciations
(1) TCAS Aural and VSI/TRA Annunciations
TCAS aural and VSI/TRA annunciations are given in Table 6--1.
Table 6--1. TCAS Aural and VSI/TRA Annunciations
VSI/TRA Annunciation
Upper
Left
Upper
Right
Center
Color
Condition
Aural
TRAFFIC Display
Control ON Mode
Normal
Range ring and own
aircraft in view at all times,
along with qualifying
traffic.
TRAFFIC Display
Control AUTO
Mode
Normal
Range ring and own
aircraft come up with
traffic when a TA or RA
exists.
Transponder Only
Mode
None
TCAS
OFF
White
TCAS is not operational.
STANDBY Mode
None
TCAS
OFF
White
TCAS is not operational,
transponder is in standby.
Vertical Speed
Input Failure to
Single VSI (Dual
VSI Aircraft)
Normal
Yellow
Vertical speed needle
removed from display with
failed data. No RAs
posted on failed side.
TCAS is operational on
remaining side.
VSI Input Failure
to Both (Dual VSI
Aircraft) or Single
VSI (Single VSI
Aircraft)
None
Yellow
Vertical speed needle
removed from both VSIs
(dual VSI aircraft) or only
VSI (single VSI aircraft).
No RA information posted.
TCAS is not operational.
White
or
Yellow
Traffic alerts are the only
information displayed. No
RAs.
(The color changes from
white to yellow when a TA
actually occurs.)
TCAS
FAIL
Yellow
TCAS is not operational.
TCAS
OFF
White
TCAS is not operational.
TCAS
OFF
White
TCAS is not operational.
TA Only Mode
Traffic -Traffic
only
Transponder or
Altitude Source
Fail
None
Altitude Reporting
OFF
ATCRBS
Transponder
Selected
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None
RA FAIL
on failed
side
VSI FAIL
on failed
side
VSI FAIL
on both
sides
TCAS
FAIL on
both sides
TA ONLY
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 6--1. TCAS Aural and VSI/TRA Annunciations (cont)
VSI/TRA Annunciation
Condition
Aural
Upper
Left
Upper
Right
RA Only
(TA Display
Control to OFF)
RA Fail
RA FAIL
Traffic Display
Failure
Center
Color
Notes
RA ONLY
White
VSI/TRA displays
resolution advisories only.
Yellow
No resolution advisories
displayed.
TD FAIL
Yellow
No traffic advisories
displayed.
VSI FAIL
Single VSI/TRA
Failure (Dual VSI
Aircraft)
Normal
X across
failed
display
Red
On failed side, all
symbology removed and
replaced with a large red
X and hex--coded failure
number. TCAS
operational on good side.
Dual VSI/TRA
Failure (or Single
on Single VSI
Aircraft)
None
X across
both
displays
Red
All symbology removed
from both displays and
replaced with a large red
X and failure code. TCAS
is not operational.
Flight Deck Lamp
Test
Normal
Display full
white
During Flight Deck lamp
test, display goes full
white and displays no
symbology.
TCAS SELF--TEST (Note 1.)
TCAS Test Mode
(First Second)
TCAS
TEST
TCAS Test Mode
(2 to 8 Seconds)
TCAS Test Mode
(at 8 Seconds)
TCAS
TEST
PASS/
FAIL
TCAS
TEST
White
TCAS system self--test.
TCAS
TEST
White
TCAS test pattern shown.
TCAS
TEST
TCAS test pattern
removed and TCAS
returns to normal
operation unless the test
switch is held, the aircraft
is on the ground, and
TCAS is in STBY.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 6--1. TCAS Aural and VSI/TRA Annunciations (cont)
VSI/TRA Annunciation
Condition
Aural
Upper
Left
Upper
Right
Center
Color
Notes
TCAS EXTENDED SELF TEST (MAINTENANCE ONLY) (Note 2.)
TCAS Extended
Test Mode (Test
Switch Held at 7
Seconds for 2
Seconds and
Aircraft on the
Ground Only)
System
information
pages
White
Current status of the
TCAS system,
transponder, antennas,
radio altimeters.
barometric altitude, etc. is
presented in a series of
pages called by selection
of 4096 code.
NOTES:
1. Self--Test should only be run in STANDBY mode in flight or on the ground.
2. Extended Self--Test provides maintenance information on seven screens selected using 4096
code. This mode is available only on the ground and in STANDBY. Extended Self--Test ends
automatically with a TCAS/Transponder mode change or if the aircraft becomes airborne.
(2) TAWS/RWS Aural and Visual Annunciations
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
D. T2CAS Test Menu and System Status Pages
(1) TCAS Test Menu and System Status Pages
The extended test mode provides maintenance information on the TCAS display.
Pages are selected by 4096 codes on the transponder control panel. The extended
test mode is accessible only on the ground, with the transponder in standby.
To start the extended test mode, select STBY and push the transponder control
panel TCAS TEST switch for 8 seconds. To exit the extended test mode, move the
transponder mode control out of STBY.
(a) TCAS Test Menu
The TCAS Menu Page, Figure 6--1, can be displayed whenever a TCAS
suppression bus failure is not indicated and the 4096 Ident Code is any code
other than 0000 thru 0007, 0011 or 0012. If a TCAS suppression bus failure is
indicated, all 4096 Ident Codes other than 0000 thru 0007, 0010 thru 0012 and
0510 can be used to select the TCAS Test Menu.
Figure 6--1. TCAS Test Menu Page
(b) System Status Page
Selection of code 0000 displays the System Status page, Figure 6--2. This page
displays the PASS or FAIL status of the TCAS system and the current version of
the operating software loaded into the T2CAS computer.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--2. Typical System Status Page
In the event of a detected system failure, one or more of the messages in
Table 6--2 are displayed. Lines 6 thru 10 of the display screen are used to
display the five highest priority faults within the TCAS system. A maximum of
five messages can be displayed.
Table 6--2. System Status Page Fault Messages
Priority
Message
Description
SUPP FAULT GOTO 0010 Suppression bus failure. Select page 0010 for more
information.
TCAS CU FAIL
ANT FAIL
TOP
Antenna failure. Message field will display TOP, BOT
or BOTH to indicate which antenna failed.
DISP FAIL GOTO
0001
TCAS has lost valid signal from display. Select page
0001 for more information.
RALT INACT GOTO 0002 TCAS has lost valid signal from radio altimeter.
Select page 0002 for more information.
XPDR FAIL GOTO
0003 TCAS has lost valid signal from Mode S transponder.
Select page 0003 for more information.
ANT FAIL GOTO
0011 One of the antenna ports connected to the T2CAS CU
has failed. Select page 0011 for more information.
OPT FAIL GOTO
0012 Parity for the option selections has failed. Select
page 0012 for more information.
T2CAS TCAS function has failed BITE test.
(c) Display Status Page
Selection of code 0001 displays the Display Status page, Figure 6--3. This page
displays the current status of the Resolution Advisory and Traffic Advisory
displays.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--3. Typical Display Status Page
The message contents for the Display Status page are determined as follows:
RA DISPLAY #1
PASS Indicates valid signal (ground/low) is present at T2CAS CU
pin RMP--14C. Fail is displayed if this signal is an open/high.
TA DISPLAY #1
PASS Indicates valid signal (ground/low) is present at T2CAS CU
pin RMP--7E. FAIL is displayed if this signal is an open/high.
RA DISPLAY #2
PASS Indicates valid signal (ground/low) is present at T2CAS CU
pin RMP--13E. FAIL is displayed if this signal is an
open/high.
TA DISPLAY #2
PASS Indicates valid signal (ground/low) is present at T2CAS CU
pin RMP--7J. FAIL is displayed if this signal is an open/high.
RNG SELECT
6NM Indicates current range selection for the traffic display. For
installations using control panels without range select
switches, range defaults to 6NM.
ALT SELECT
NORM Indicates current selection of vertical display limits for traffic
display -- NORM, BELOW, or ABOVE. For installations that
use control panels without ABV--NORM--BLW switch, limits
default to NORM.
ALT TAG
RELATIVE Indicates current selection on control panel for type of traffic
symbol altitude indication, RELATIVE or FLT LVL. Default is
RELATIVE if no switch is available on control panel.
(d) RAD/ALT Status Page
Selection of code 0002 displays the RAD/ALT Status page, Figure 6--4. This
page displays the status of the selected radio altimeter interface to the T2CAS.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--4. Typical RAD/ALT Status Page
The first information line (line 3) of the RAD/ALT STATUS page indicates which
of the two radio altimeter ports is being used by the T2CAS computer. The
T2CAS computer attempts to use radio altimeter No. 1 first. If it determines this
input is invalid, it automatically switches to radio altimeter No. 2.
The current status of the two radio altimeter ports is displayed on lines 5 and 6.
If a signal is valid, the radio altitude value is displayed in either “FT” for English
type altimeters, or “M” for Metric type altimeters.
If one of the radio altitude signals is determined to be invalid, the altitude value is
replaced by INACT. Radio altitude INACT indicates the radio altimeter has failed,
is not powered, or is not connected.
The radio altimeter input is determined to be invalid if, for an analog radio
altimeter input, +28 Vdc valid is not present at T2CAS CU pin RMP--2K for Radio
Alt #1 or pin RMP--3C for Radio Alt #2, or for a digital radio altimeter input, the
sign status matrix (SSM) of the radio altimeter output indicates not valid or no
data is present on the digital bus.
If the radio altimeter output is greater than 2200 feet (source is valid, but data is
invalid), the radio altitude value is replaced by OVR RNG.
When both radio altitude sources are invalid, line 3 is blank.
(e) Transponder (XPDR) Status Page
Selection of code 0003 displays the XPDR Status page, Figure 6--5. This page
displays data for the transponder selected at the time the extended test mode
was entered.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--5. Typical Transponder (XPDR) Status Page
The message contents for the XPDR Status page are determined as follows:
XPDR #1
MODE S ADDR:
PRESS. ALT
ALT
REPORTING
PASS Indicates PASS or FAIL status of the selected transponder
(XPDR #1 or XPDR #2) as indicated by the digital
transmission from that transponder. FAIL is displayed if no
data is received on the bus.
8E78A0H Indicates the Mode S address (in hexadecimal format) of the
selected transponder as determined by program pins at the
rear connector of the transponder. (See Note 1.)
1133FT Indicates the last pressure altitude being reported by the
selected Mode S transponder before the TCAS system was
placed into STBY. This value is not updated while in extended
test mode.
ON Indicates current position of altitude reporting switch on Mode
S/TCAS control panel -- ON or OFF.
S/W PN PS7021601--903 (See Note 2.)
NOTES:
1. If the transponder detects either all 1s or all 0s, the following message will appear -ILLEGAL ADDRESS --. In addition, a fail message will appear on the front of the
transponder and on Extended Test. The message reads CHECK DISCRETE
ADDR WIRING ON XPDR PINS MP1A THROUGH MP3D.
2. The S/W PN information, line 8 of the display screen, displays general text supplied
by the ACSS ATDL transponder via label 356 (block transfer), which is equipped to
supply the text to the display. If a transponder is installed that does not have this
feature, line 8 is blank.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
(f)
Programming Pins Status Pages
The following three displays indicate the status of various option programming
pins located in the rear connector of the T2CAS computer. The 1s and 0s
following a programming option indicate the GROUND or OPEN status for those
programming pins. Each 1 and 0 is associated with a program pin. A one (1)
indicates the pin is grounded by connecting to a program common pin on the
T2CAS connector or to an aircraft ground. A zero (0) indicates the pin is left
open.
Selection of code 0004 displays the first of three pages that define program pin
status. See Figure 6--6.
Figure 6--6. Typical Program Pins 1/3 Page
Programming pins on the T2CAS computer associated with each of the functions
defined on the page 1 display are listed below. Where more than one program
pin is indicated, the listed connector pins correspond to the display digits read
from left to right. A one (1) indicates the associated pin is grounded. A zero (0)
indicates open.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
CLIMB INH
0000 Climb Inhibit inputs:
RMP--1J, RMP--13G, RBP--5J, RBP--5K.
INC CLIMB INH
0000 Increase Climb Inhibit inputs:
RBP--5E, RBP--5F, RBP--5G, RBP--5H
ADVISORY INH
0000 Advisory Inhibit inputs:
RBP--5A, RBP--5B, RBP--5C, RBP--5D
RADIO ALT TYPE 1
0000 Analog Radio Altimeter Type: RMP--12B
ARINC 552/552A (0), Collins BCA (1)
VOICE DELAY
ENABLE
AUDIO PROG PINS
CANCEL DISCRETE 2
0 Voice Delay option: RBP--7D
Enabled = (1), Disabled = (0)
000 Audio output level selection inputs:
RBP--7A, RBP--7B, RBP--7C
0 Advisory Cancel Discrete option: RMP--3D
(0) allows advisories to be cancelled. A (1) does not allow
advisories to be cancelled.
Selection of code 0005 displays the second of three pages that define the
Program Pins status. See Figure 6--7.
Figure 6--7. Typical Program Pins 2/3 Page
Programming pins on the T2CAS computer associated with each of the functions
defined on the Program Pins 2/3 page are listed below. Where more than one
program pin is indicated, the listed connector pins correspond to the display
digits read from left to right. A one (1) indicates the associated pin is grounded.
A zero (0) indicates open.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
BCA EFIS
0 RA/TA block transfer program that determines the type of
data transfer from the T2CAS CU to the TA/RA displays:
A (1) indicates Honeywell BCA EFIS format. A (0) indicates
ARINC 735 format: RMP--12C.
CABLE DELAY
PROG
TEST MODE
000 RF delay compensation program for antenna cable length
difference (top versus bottom): RBP--7G, RBP--7H, RBP--7J
0000 Shop test function (all 0s for flight mode):
RBP--9D, RBP--9E, RBP--9F, RBP--9G
FUNCT TEST INH
0 Inhibits Flight Deck self--test when airborne (0 for no inhibit):
RBP--8E
SIM SOFT ENABLE
0 Simulator Software Enable input: RBP--10K
Should always be (0) for flight mode.
MAX # INTRUDER
00000 Select maximum number of traffic symbols displayed on VSI.
Value for each digit, from left to right, is 16, 8, 4, 2, 1. The
maximum number is the sum of not selected values (0s):
RBP--8F, RBP--8G, RBP--8H, RBP--8J, RBP--8K.
DISP THREATS
ONLY
0 Selects display of traffic only when TAs or RAs occur:
(0 indicates display of any traffic): RBP--7F.
GND DISPLAY
MODE
0 Selects TCAS OFF automatically with aircraft ON GROUND
(0 indicates TCAS active ON GROUND): RBP--7E.
Selection of code 0006 displays the third of three pages that define the Program
Pins status. See Figure 6--8.
Figure 6--8. Typical Program Pins 3/3 Page
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Programming pins on the T2CAS computer associated with each of the functions
defined on the Program Pins 3/3 page are listed below. Where more than one
program pin is indicated, the listed connector pins correspond to the display
digits read from left to right. A one (1) indicates the associated pin is grounded
and a zero (0) indicates open, except for RCZ--852 MAX TAS where a one (1)
indicates an open and a zero (0) indicates a ground.
ALT LIMIT
PERF LIMIT
00000 Shows selected altitude above which TCAS will not give CLIMB
commands. Value for each digit, from left to right, is 32000, 16000,
8000, 4000, and 2000 feet. Altitude is the sum of selected values
(1s): RMP--6J, RMP--6H, RMP--6G, RMP--6F, RMP--6E.
0 Selects CLIMB command altitude limit control from external
performance computer: A ground (1) indicates performance/climb
rate is not limited. An open (0) indicates performance/climb rate is
limited: RMP--6D.
METRIC TYPE
000 Shows the status of the metric selection program pins #1, #2, and
#3: RMP--12K, RMP--12J, and RMP--12H. The metric type will
appear only with TCAS computer unit part number
7517900--XX001 and --XX002. On TCAS computer unit part
number 7517900--XX003 and --XX004, the message “METRIC
TYPE 0000” is replaced with “SINGLE TRANSPONDER 0”.
MAX TAS
000 Shows the selected maximum airspeed operating range of aircraft.
This data is obtained from ARINC label 276 of the selected
transponder. Refer to the appropriate Mode S transponder
installation manual.
NOTE:
Line 8 of the Program Pins 3/3 display indicates which transponder is currently
selected.
Help Reference Page
Selection of code 0007 displays the Help Reference page, Figure 6--9. This
page serves as a reference to assist aircraft maintenance personnel in checking
the functionality of dual transponders.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--9. Help Reference Page
In addition to the recommended procedure, the number 2 transponder must be
selected on the Mode S/TCAS control panel and the mode select switch placed
in TA only or TA/RA mode momentarily prior to restarting self-test to enter
extended maintenance mode.
(g) Suppression Bus Fail Page
The Suppression Bus Fail page, Figure 6--10, is displayed only when a TCAS
suppression bus failure is indicated and the 4096 Ident Code is 0010. This
page displays information about detected suppression bus failures. It briefly
describes the problem and instructs maintenance personnel to change the 4096
Ident Code to display the Suppression Bus Clear page for clearing instructions.
If there is no suppression bus failure, the main menu (0000) is displayed.
Figure 6--10. Suppression Bus Fail Page
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
The flight crew may report a unique problem of an intruder displayed which
appears to be co--altitude, located on the own aircraft symbol. In many of these
cases, TCAS may issue a TA followed by an RA. After the flightcrew has
initiated the advisory, the intruder may not appear to change relative to the own
aircraft symbol.
In this type of report, a failure in the mutual suppression bus, which connects the
own aircraft transponder to the T2CAS CU, could result in the T2CAS CU
developing an intruder track file on its own associated transponder. Simply
performing a DC continuity test of the connection between the T2CAS CU and
the transponders may not identify the problem. In many cases, a connector
termination or pushed back pin may be the cause.
That is why it is very important to be monitoring the suppression signal from the
active source, on both ends. The following is one method to monitor the signal.
Remove the T2CAS CU and the non--selected transponder. With an
oscilloscope, monitor the signal at the T2CAS CU rack rear connector for the
Mode S transponder suppression signal related to the squitter message sent
every second by the selected operational transponder.
Repeat the same test with the second transponder after removing the first
transponder. To test the T2CAS CU suppression pulse, install the TCAS CU,
remove the No. 1 transponder and monitor the TCAS suppression pulse during
the time of the UF16 broadcast or the WSS while in the air (if possible). This
TCAS suppression signal should also be present on the No. 2 transponder.
(h) Suppression Bus Clear Page
The Suppression Bus Clear page, Figure 6--11, is displayed only when a TCAS
suppression bus failure is indicated and the 4096 Ident Code is 0510. This page
briefly describes how to clear suppression bus failures from the fault record by
exiting the extended test mode with this page displayed. When the TCAS
extended test is exited, the failure indication is cleared and a Suppression Bus
Clear code is recorded in the current flight leg.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--11. Suppression Bus Clear Page
(i)
Antenna Port Status Page
Selection of code 0011 displays the Antenna Port Status page, Figure 6--12.
This page displays the current operational status of the top and bottom TCAS
antennas. The status of each port is indicated as PASS when valid and FAIL
when invalid. Information lines 8, 9, and 10 are not displayed when an
omnidirectional bottom antenna is installed.
Figure 6--12. Typical Antenna Port Status Page
(j)
Option Pins Status Page
Selection of code 0012 displays a page that defines the T2CAS computer option
pins. See Figure 6--13.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure 6--13. Typical Option Pins Status Page
Option pins on the T2CAS computer associated with each of the functions
defined on the Option Pins Status page are listed below. Where more than one
option pin is indicated, the listed connector pins correspond to the display digits
read from left to right.
There are eight option pins available on the T2CAS computer for selection of
various options. The OPT PINS are as follows: RMP--10G, --10H, --10J, --10K,
--11A, --11B, --11C, and --11D.
NOTE:
OPT PINS RMP--10G, --10H, --10J, and --10K are reserved for future
enhancements and are used for parity check only.
The PARITY line (line 4) displays the status of the parity program pin
(RMP--12G). Pin RMP--12G must be grounded (1) when the number of OPT
PINS grounded is an odd number (1, 3, 5, 7). If number of OPT PINS grounded
is an even number (0, 2, 4, 6, 8), then pin RMP--12G should be open (0).
The STATUS line (line 5) displays FAIL if the option pins parity is incorrect or
PASS if parity is correct.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
The ENHANCEMENTS line (line 6) displays the status of the Flight Data
Recorder ARINC 429 and Extended Maintenance Log Program input status (Pin
RMP--11D). This option enables the use of the Flight Data Recorder and the
down loading of the extended maintenance log through a PDL connected to
connector J1 located on the front of the TCAS computer. If pin RMP--11D is
open, the Flight Data Recorder is not used and normal RA display bus operation
occurs. If pin RMP--11D is grounded, high speed ARINC 429 flight data is output
on the RA Display #1 and #2 buses and maintenance log data can be
downloaded through a portable data loader.
NOTE:
The three options that follow have been defined, but the functions have
not been implemented in --XX001 and --XX002 TCAS computer
software. These options should always indicate OFF in these versions.
The three options are activated with --XX003 and --XX004 TCAS
computer software.
The MALE VOICE line (line 7) displays the Male Voice Program input status (Pin
RMP--11C). This option allows audio annunciation to be selectable for either
male or female gender. If pin RMP--11C is grounded, the male voice option is
enabled (ON). If pin RMP--11C is open, the female voice option is enabled
(OFF).
The DISPLAY FLT ID line (line 8) displays the Flight ID Program input status (Pin
RMP--11B). This program allows flight identification from the transponder to be
output on traffic display buses. If pin RMP--11B is grounded, Flight ID Display is
enabled (ON). If pin RMP--11B is open, Flight ID Display is disabled (OFF).
The ALTITUDE ALERTER line (line 9) displays the Altitude Alerter Program input
status (Pin RMP--11A). This program prevents the weakening of an RA based
on selected altitude. If pin RMP--11A is grounded, the Altitude Alerter option is
enabled (ON). If pin RMP--11A is open, the Altitude Alerter option is disabled
(OFF).
(2) TAWS/RWS Test Menu and System Status Pages
The extended test mode provides maintenance information on the TAWS
EFIS/Weather Radar display. Pages are indexed by pressing and holding the
TAWS/RWS/GPS TEST button/switch on the Flight Deck for three seconds or less.
The extended test mode is accessible only on the ground, and only after the
standard short test has completed as outlined in section 3.B.2 of this (Fault Isolation)
section.
NOTE:
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TAWS/RWS/GPS TEST button/switch for more than three seconds.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
(a) Extended Self--Test Page
The Extended Self--Test Display page layout is dependent on the selection of
display formats made in the ASDB. Some types have more viewable area than
others thus the font size and formatting will differ, but the actual text displayed
will remain the same. As such, all of the Extended Self--Test pages shown in this
section are typical WXR display formats, the actual displays will vary according to
the usable display area.
The T2CAS TAWS Extended Self--Test page is the first page displayed. The
Extended Self--Test page is divided into two pages, Figure 6--14 shows page 1,
the Instructions Page and Figure 6--15 shows Page 2, the Table of Contents
Page.
The gray shaded area represents the anticipated viewable area of the
display. The viewable area will vary with the display types as defined in
the ASDB.
ID--8000637
NOTE:
Figure 6--14. Extended Self--Test Page (Page 1)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
T A B L E O F
C O N T E N T S
P A R T N U M B E R S
2 -- 6
ID--8000638
P A G E
Figure 6--15. Extended Self--Test Page (Page 1 of 6)
(b) Part Numbers Page
The Part Numbers Page is divided into five pages. Figure 6--16 shows page 1,
which displays the Aircraft Type and OMS Type.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
ID--8000639
T2CAS / Part No. 9000000
Figure 6--16. Part Numbers Page 1 (Page 2 of 6)
ID--8000640
Pages 2 and 3, shown in Figure 6--17 and Figure 6--18 respectfully, display the
Aircraft Identifier, LRU Part Number, Software Modification Number and TAWS
Database Part Number.
Figure 6--17. Part Numbers Page 2 (Page 3 of 6)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
ID--8000641
T2CAS / Part No. 9000000
Figure 6--18. Part Numbers Page 3 (Page 4 of 6)
ID--8000642
Part Number Pages 4 (Figure 6--19) and 5 (Figure 6--20) contain APM
information including Hardware Part Number, ACD Part Number and ASDB Part
Number. Page 5 also includes a Internal System PASS/FAIL indication.
Figure 6--19. Part Numbers Page 4 (Page 5 of 6)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
ID--8000643
T2CAS / Part No. 9000000
Figure 6--20. Part Numbers Page 5 (Page 6 of 6)
E.
T2CAS Computer Unit Self--Test
The T2CAS computer unit detects system faults and displays them on its front panel
annunciators. Its flight leg memory stores system status and fault information for 10
consecutive flight legs. A flight leg is the interval between weight--off--wheels and weight-on--wheels during which T2CAS is operative. By recalling the stored data, ground
maintenance personnel can evaluate in--flight performance on the ground and fault
isolate a current or previous failure to a specific LRU or LRU interface.
Table 6--3 summarizes how the T2CAS computer unit self--test is activated at power--up,
during operation, and during commanded self--test. The computer unit can activate the
commanded self--test only when the aircraft is on the ground.
Table 6--4 lists the functions of the computer unit’s status annunciators and the
corresponding troubleshooting actions. If the annunciators indicate an antenna problem,
the antenna connections should be checked by measuring the antenna resistance values
at the computer unit mounting tray. The resistance values listed in Table 6--5 are
measured between the center conductor and shield on each LTP and LMP antenna
connector.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 6--3. Computer Unit Self--Test Execution
Test Sequence
Activation
Test Indications
Power On Self--Test
Self--Test is activated with
each application of system
power
No indication unless a fault is detected.
System status/fault data is stored in memory
for 10 consecutive flight legs. Data can be
recalled by doing the commanded self--test on
the ground.
Continuous Self--Test
Executed automatically as
part of normal TCAS inflight
operation
No indication unless a fault is detected.
System status/fault data is stored in memory
for 10 consecutive flight legs. Data can be
recalled by doing the commanded self--test on
the ground.
Commanded
Self--Test
Push the front panel PUSH
TO TEST button
• All T2CAS TCAS front panel lamps come
on during a 3--second lamp test.
• If the TCAS is operational, the TCAS PASS
green lamp comes on for a 10--second
display period and then goes off.
• If the TCAS is not operational, one or more
red fault lamps come on for a 10--second
display period. Refer to Table 6--4 for
corrective action.
• The T2CAS TAWS/RWS front panel lamps
cycle as defined in Section 5
Adjustments/Test.
• If the TAWS/RWS is operational XFER IN
PROCESS LED will be extinguished and
the TAWS P/F STATUS green lamp comes
on for approximately 11 seconds.
• If the TAWS/RWS is not operational, TAWS
P/F STATUS, TAWS I/O FAIL, TAWS APM
FAIL, and CF LOAD STATUS LEDs will be
set for approximately 11 seconds.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 6--3. Computer Unit Self--Test Execution (cont)
Test Sequence
Activation
Push the PUSH TO TEST
button again before the
previous 10--second display
period has elapsed
Test Indications
• Previous fault display is aborted
• All T2CAS TCAS lamps come on during a
1--second lamp test
• All front T2CAS TAWS/RWS LEDs will be lit
for 1 second (+/-- 0.5 seconds) in the
following colors:
-- TAWS P/F STATUS: Red
-- TAWS I/O FAIL: Red
-- TAWS APM FAIL: Red
-- XFER IN PROCESS: Green
-- C/F LOAD STATUS: Red
• The TAWS/RWS XFER IN PROCESS LED
will be extinguished.
• The TCAS Status/fault data recorded
during the preceding flight leg is displayed
for 10--seconds.
• The TAWS/RWS Status/fault data recorded
during the preceding flight leg is displayed
for approximately 11 seconds.
Push the PUSH TO TEST
button before the end of each
succeeding display period
• TCAS and TAWS/RWS Status/fault data
recorded during a total of 10 flight legs
(maximum) is displayed
• When data from the earliest recorded flight
leg has been displayed, all lamps flash at
approximately a 2.5--Hz rate for 3--seconds
if the PUSH TO TEST button is pushed.
This indicates the end of recorded test
data.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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Table 6--4. TCAS Fault Reporting and Corrective Actions
Status
Annunciator
Possible corrective Action
TCAS
PASS
The T2CAS TCAS function
passes its own internal BITE
test
T2CAS TCAS function is operational. If other
annunciators are on, the problem is in the indicated
subsystem or aircraft wiring.
TCAS
FAIL
The T2CAS TCAS function
has failed its own internal
BITE test
Replace the T2CAS computer unit.
TOP
ANT
The top antenna DC
resistance test indicates a
failure
Remove the T2CAS computer unit. Use a multimeter
to measure the DC resistances indicated in Table 6--5
for the top antenna. Repair antenna cables or replace
the antenna as required.
BOT
ANT
The bottom antenna DC
resistance test indicates a
failure
Remove the T2CAS computer unit. Use a multimeter
to measure the DC resistance indicated in Table 6--5
for the bottom antenna. Repair antenna cable(s) or
replace the antenna as required.
HDG
Heading input function not
used
Not applicable
TA
DISP
Traffic advisory display
discrete signals No.1 or No. 2
indicate a failure
Check wiring and power to TA display. (On both sides
of the Flight Deck, if two are installed.) Make sure
that RA/TA valid discrete 1 and 2 (RMP--7E and
RMP--7J) are <3.5 V dc to ground. Repair wiring or
replace display as required.
RA
DISP
Resolution advisory display
discrete signals No.1 or No. 2
indicate a failure
Check wiring and power to RA displays. Make sure
that RA valid discrete 1 and 2 (RMP--14C and
RMP--13E) are <3.5 V dc to ground. Repair wiring or
replace display as required.
RAD
ALT
Radio altitude source No.1 or
No. 2 is invalid or has failed
Check wiring and power to the radio altimeters. For
analog radio altimeters, make sure the RAD ALT No.1
and No.2 valid discrete (RMP--2K and RBP--3C) are
>18.5 V dc. Repair wiring or replace radio altimeter
as required.
XPDR
BUS
Mode S Transponder No.1 or
No. 2 is invalid or has failed.
Check wiring and power to the transponders. Check
for data on XT 429 bus No.1 and No.2 (RMP--14F/G
and RMP--14H/J). Repair wiring or replace
transponder as required. If the Single Mode S
Transponder program pin (RMP--10D) is not grounded
in installations using --XX003, --XX004 TCAS
Computer Units, a XPDR Bus Fault may be
displayed.
Attitude input function not
used.
Not applicable
ATT
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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F.
Directional Antenna Test / Fault Isolation Procedure
NOTE:
These procedures are recommended only if a T2CAS TCAS function bite or
extended test failure of the top or bottom directional antenna has occurred.
(1) Review extended maintenance or flight leg BITE data to determine which antenna
has failed.
(2) Remove T2CAS computer unit from mounting tray. Visually examine all antenna coax
cable connectors at the mounting tray side as well as the LRU connectors. Remove
any foreign material discovered and reinstall the LRU.
(3) Do a system self--test to determine if the fault has cleared. If the failure continues,
remove the T2CAS computer unit and proceed.
(4) Do a continuity test at the LRU end of each antenna cable. The resistance values
should be as specified in Table 6--5.
(5) If an open circuit, short circuit, or unacceptable resistance measurement is detected
on the directional antenna path, a failure has occurred in the connector, coax cable,
or directional antenna.
(6) Locate the directional antenna that has a suspected failure. Remove the coax cable
from the antenna port that is suspected to have failed. Isolate which section of the
antenna system is at fault by a process of elimination. The resistance values of the
antenna ports should be as specified in Table 6--5.
(7) Remove and replace the appropriate failed component in accordance with approved
Aircraft Maintenance Manual procedures.
Table 6--5. Antenna Wiring Resistance
Antenna
Connector
Section
Pin
DC Resistance
Top Directional Antenna
LTP
1000 ± 100 Ohms
8060 ± 800 Ohms
4020 ± 400 Ohms
2000 ± 200 Ohms
Bottom Directional Antenna
LMP
1000 ± 100 Ohms
8060 ± 800 Ohms
4020 ± 400 Ohms
2000 ± 200 Ohms
Optional Bottom
Omnidirectional Antenna
LMP
0 to 50 Ohms (50 Ohms maximum)
Infinite (>50K Ohms)
Infinite (>50K Ohms)
Infinite (>50K Ohms)
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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NOTE:
The procedures that follow are recommended for intermittent antenna system
failures or if the continuity tests have not identified a failed component in the
antenna system or if the flight crew detects an unacceptable visual discrepancy
between an intruder aircraft and its displayed location.
(8) If the displayed location of an intruder aircraft is believed to be in error, appropriate
ramp test equipment can be used to simulate intruder aircraft to check the suspected
discrepancy while on the ground.
(9) Remove the suspected TCAS directional antenna and terminate the antenna side of
the cable with a 50 ohm termination (Omni--Spectra Part Number 3102--6100--00 or
equivalent TNC jack with VSWR ≤1.15 : 1).
(10) Perform a thorough inspection for moisture or contamination of all coax cable
assemblies.
(11) Remove the T2CAS LRU and do a VSWR check on the coax cable from the T2CAS
computer tray side. Use approved VSWR test equipment and operating procedures.
The measured VSWR should be less than 2.0 : 1.
(12) If the VSWR test fails, isolate failed antenna coax section. Remove/repair
appropriate cable and/or connector.
(13) An additional procedure for troubleshooting TCAS antenna system failures is to
determine the RF insertion loss in the TCAS antenna coaxial cables. RF insertion
loss is equivalent to RF IxR (voltage) drop through the coax and is measured in dB
rather than volts. Each coax cable is required to have is 2.5 dB ( ±0.5 dB) of insertion
loss and the loss in all the coax cables must be within 0.5 dB of each other. Many
VSWR meters have a fixed RF source and can be used to measure RF insertion loss.
In this test, the VSWR meter is used to measure the loss up one cable and down the
other. The total loss should not exceed 6 dB.
NOTE:
The VSWR/insertion loss meter should be set up for L--band frequencies
(approximately 1.0 GHz).
To perform an RF insertion loss test, do the following:
(a) Connect two of the TCAS antenna coax cables to each other at the antenna end
with a DC shorted coupler.
(b) Before any measurements are taken on the antenna system, the meter and any
connectors/cables that are used to connect the meter to the TCAS antenna
system must be zeroed out. This is typically done with a calibration adjustment
on the VSWR meter.
(c) After the VSWR meter (and associated connectors/cables) have been calibrated
for 0 dB, connect the VSWR meter to the TCAS antenna coaxes under test (at
the LRU end). Measure and record the RF loss.
(d) Test different combinations of the TCAS antenna coax cables by connecting the
coupler (at the antenna end) to different coax cables. By process of elimination, it
can be determined if one of the TCAS antenna coax cables has excessive RF
insertion loss.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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(e) As an example, suppose the following insertion losses have been measured:
Antenna Port
Antenna Port
Measured Loss
90
8.5 dB
180
5.5 dB
90
180
8.0 dB
It can be seen that when the coax connected to the 90 degree port is included in
the measurement, there is excessive loss. Simple algebra can be used to
determine that this coax has 5.5 dB of insertion loss.
NOTE:
1 dB of excessive loss in one cable can result in about 3.5 degrees of
intruder bearing error.
(14) If the VSWR tests and RF insertion loss test comply, return the directional antenna to
the manufacturer for further testing. Install a new directional antenna in accordance
with Aircraft Maintenance Manual procedures.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
MAINTENANCE PRACTICES
1. General
This section provides instructions for removing, reinstalling, and adjusting each LRU of the
T2CAS that has been previously installed by the aircraft manufacturer or completion center.
Where applicable, instructions for replacing lamps, knobs, and set screws are included.
Adjustment information is called out as required.
CAUTION:
SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THE
REINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENT WITH THE
INSTRUCTION.
CAUTION:
TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF WHEN
REMOVING OR INSTALLING LRUS.
When removing or installing any T2CAS LRU, prepare the aircraft for safe ground
maintenance. Open and tag all applicable system circuit breakers.
2. Equipment and Materials
CAUTION:
BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL
SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE
DANGEROUS.
Maintenance materials identified with a Honeywell Material Number (HMN) are given in
Table 7-- 1.
Table 7-- 1. Materials
Name
HMN 9722878
Description
Sealing compound,
temperature--resistant,
high--adhesion, two component,
polysulfide synthetic rubber
(MIL--S--8802, Type I -dichromate cured sealing
materials, Class B1/2 -spreadable) — PR--1422 (base
and accelerator)
Source
Courtaulds Aerospace,
Glendale, CA
NOTES:
1. Equivalent alternatives are permitted for materials in this list.
2. The HMN codes in the list of materials identify the HMN given to each material.
No additional special equipment or materials, other than those commonly used in the shop,
are required to install the units in existing trays and clamps, and to adjust the system. Do not
over tighten mounting screws. Where torque values are not given, it is acceptable to finger
tighten the mounting screws.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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3. Procedure for the TT--950/951/952 T2CAS Computer Unit
A. Removal and Installation Procedure
(1) Remove the T2CAS computer unit.
(a) Loosen mounting tray hold--down knobs.
(b) Slowly pull forward on the computer unit handle to separate computer unit and
mounting tray connectors. The computer unit is now free to be removed from the
mounting tray.
(c) Place electrostatic protective covers on the computer unit and the mounting tray
electrical connectors.
(2) Reinstall the T2CAS computer unit.
(a) Remove protective plastic covers from aircraft connectors. Remove electrostatic
protective covers from computer unit electrical connectors.
(b) Slide computer unit into mounting tray.
CAUTION:
DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE COMPUTER
UNIT AND EXAMINE THE CONNECTOR FOR PINS THAT ARE BENT OR
OUT OF ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THE
RECEPTACLE IN THE MOUNTING TRAY.
(c) Carefully apply firm pressure until the computer unit connectors mate with the
connector receptacles on the mounting tray.
(d) Tighten mounting tray hold--down knobs to make sure all connectors are fully
engaged.
B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
Not Applicable.
D. Return to Service Procedures
Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section
of this manual.
4. Procedure for the APM
A. Removal and Installation Procedure
(1) Remove the APM.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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(a) If APM is attached to the T2CAS mounting tray, remove the screws that attach
the APM to the T2CAS mounting tray.
(b) Loosen the screws that attach the APM to the APM Mating Connector.
(c) Carefully disconnect the APM from the APM Mating Connector.
(2) Reinstall the APM.
(a) Carefully insert the APM connector plug into the APM Mating Connector.
(b) Tighten the screws that attach the APM to the APM Mating Connector.
(c) If APM is to be attached to the T2CAS mounting tray, reattach the APM to the
T2CAS mounting tray using the provided mounting screws.
NOTE:
If a new APM (blank or previously programmed for a different aircraft) is installed,
the APM must be reprogrammed as specified in Adjustments/Test, section 6--D.
B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
The ACSS APM is a non--repairable item. If the APM is damaged or determined to be
faulty, it must be replaced with a new APM.
D. Return to Service Procedures
Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section
of this manual.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
5. Procedure for the Directional Antenna
A. Removal and Installation Procedure
(1) Remove the directional antenna.
(a) If applicable, use a phenolic scraper to remove aerodynamic sealant around
periphery of antenna.
(b) Remove four or eight (quantity depends on dash number of antenna) non--Torx
drive screws used to attach antenna to fuselage. See Figure 2--9 for location
and number of mounting holes for each dash number antenna.
(c) Carefully lift antenna from fuselage avoiding any damage to the coaxial cables.
(d) Disconnect coaxial cables from antenna connectors J1, J2, J3, and J4.
(e) Put protective covers on the aircraft coaxial cable connectors and the antenna
coax connectors.
(2) Reinstall the directional antenna.
(a) If applicable, remove any existing aerodynamic sealant from antenna and clean
antenna mounting area.
(b) Put supplied o--ring in antenna o--ring groove. If antenna is supplied with a
Teflon gasket, install gasket between antenna and fuselage.
(c) Remove protective covers from antenna and aircraft coaxial mating connectors.
(d) Examine antenna and coaxial mating connectors to make sure they are clean
and secure.
(e) Orient antenna with respect to airframe (arrow painted on radome must point
forward). Connect four aircraft coaxial cables to antenna. Refer to Figure 2--12
for wiring information. Note the color bands on the antenna connectors and
cables: yellow = J1, black = J2, blue = J3, and red = J4.
NOTE:
(f)
Do not apply a sealant between antenna base and fuselage.
Application of a sealant will reduce lightning protection.
Align antenna mounting holes with holes in fuselage (note the non--symmetric
hole pattern).
(g) Attach antenna to fuselage with four or eight (quantity depends on dash number
of antenna) non--Torx drive screws and flat washers. See tables 3 and 4 of
Figure 2--12 for dash number mounting information. Apply a sealant to the screw
threads before installing them. Torque mounting screws to 22 ± 3 inch--pounds
(2.5 ± 0.2 Newton--Meters).
(h) Apply an aerodynamic sealant around periphery of the antenna base to prevent
seepage of water and condensation and to preclude corrosion.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
The ACSS TCAS Directional Antenna is a non--repairable item. If the antenna is
damaged or determined to be faulty, it must be replaced with a new antenna.
D. Return to Service Procedures
Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section
of this manual.
6. Procedure for the Omnidirectional Antenna
A. Removal and Installation Procedure
(1) Remove the Omnidirectional Antenna.
(a) If applicable, use a phenolic scraper to remove aerodynamic sealant around
periphery of antenna baseplate.
(b) If applicable, remove sealant from antenna mounting screw holes.
(c) Remove retaining screws used to attach antenna to aircraft fuselage.
(d) Carefully pull antenna from fuselage.
(e) Disconnect coaxial cable from antenna connector.
(f)
Put protective covers on the aircraft coaxial cable connector and the antenna
connector.
(2) Reinstall the Omnidirectional Antenna.
(a) If applicable, remove any existing aerodynamic sealant from antenna mounting
surface and clean antenna mounting area.
(b) Remove and clean sealant from baseplate and baseplate cutout.
(c) Remove protective covers from antenna and coaxial cable connectors.
(d) Examine antenna and coaxial cable connectors to make sure they are clean and
secure.
(e) Connect aircraft coaxial cable to antenna connector.
(f)
Apply a coating of sealant under heads of antenna mounting screws and position
antenna on fuselage mounting surface. Attach antenna to fuselage with
mounting screws.
(g) Apply an aerodynamic sealant around the periphery of the antenna baseplate.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
Most omnidirectional antennas are non--repairable. If the antenna is damaged or
determined to be faulty, it must be replaced with a new antenna.
D. Return to Service Procedures
Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section
of this manual.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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7. Procedure for the GPS Antenna
A. Removal and Installation Procedure
TBD
B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
TBD
D. Return to Service Procedures
8. Procedure for the Control Panel
A. Removal and Installation Procedure
(1) Remove the Control Panel.
(a) Disengage Dzus fasteners on control panel.
(b) Pull control panel out of aircraft mounting location and disconnect aircraft cable
connectors. Control panel is now free to be removed from aircraft.
(c) Put electrostatic protective covers on control panel and aircraft mating electrical
connectors.
(2) Reinstall the Control Panel.
(a) Remove protective covers from control panel and aircraft mating connectors.
(b) Connect aircraft cables to control panel connectors J1 and J2.
(c) Insert control panel into mounting location.
(d) Engage Dzus fasteners on the control panel to attach it to aircraft structure.
B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
Any repair procedures should be in accordance with the manufacturer’s repair
instructions.
D. Return to Service Procedures
Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section
of this manual.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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9. Procedure for the VSI/TRA Display
A. Removal and Installation Procedure
(1) Remove the VSI/TRA Display.
(a) Loosen screws of instrument panel mounting clamp.
NOTE:
Most installation clamps require the top screws be loosened to remove
the instrument. Other clamps require the diagonal screws be loosened.
Refer to the aircraft maintenance manual (AMM) for specific application.
(b) Pull the VSI/TRA out of the instrument panel and disconnect J1 mating
connector.
(c) Put electrostatic protective covers on display and aircraft mating electrical
connectors.
(2) Reinstall the VSI/TRA Display.
(a) Remove protective covers from display and aircraft mating connectors.
(b) Connect aircraft cable to VSI/TRA connector J1.
(c) Insert the display into the instrument panel and push all the way back against
panel.
(d) Tighten the four instrument mounting clamp screws.
B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
Not Applicable.
D. Return to Service Procedures
Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section
of this manual.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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10. Procedure for the Transponder
A. Removal and Installation Procedure
(1) Remove Transponder
(a) Loosen mounting tray hold--down knobs.
(b) Slowly pull forward on the unit handle to separate transponder and mounting tray
connectors. The transponder is now free to be removed from the mounting tray.
(c) Place electrostatic protective covers on the transponder and the mounting tray
electrical connectors.
(2) Reinstall Transponder
(a) Remove protective plastic covers from mounting tray connectors and
transponder electrical connectors.
(b) Slide transponder into mounting tray.
CAUTION:
DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE UNIT AND
EXAMINE THE CONNECTORS FOR PINS THAT ARE BENT OR OUT OF
ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THE RECEPTACLE IN
THE MOUNTING TRAY.
(c) Carefully apply firm pressure until the transponder connectors mate with the
connector receptacles on the mounting tray.
(d) Tighten mounting tray hold--down knobs making sure all connectors are fully
engaged.
B. Adjustment Procedure
Not Applicable.
C. Repair Procedure
Not Applicable.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
D. Return to Service Procedures
(1) For installations using serial data bus (ARINC 429) altitude data:
(a) The POST (automatic on power on) and PAST self--test (initiated from the control
panel) are the only required Return to Service tests for the transponder.
(b) After the transponder passes these tests, the appropriate logbook entries may
be made and the unit is ready for use.
(2) For installations using parallel (Gillham code) altitude data:
(a) The POST (automatic on power on) and PAST self--test (initiated from the control
panel) must be passed.
(b) Connect an air data tester to the aircraft pitot/static system and set up a
transponder ramp tester.
(c) Setup the air data tester to output the following altitudes. The transponder’s
encoded altitude must correspond.
• 11,700 feet
• 24,400 feet
• 30,800 feet.
NOTE:
These three altitudes check the operation of all parallel altitude wires.
(d) After the transponder passes these tests, the appropriate logbook entries may
be made and the unit is ready for use.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
11. Instructions for Continued Airworthiness, FAR Part 25.1529
Maintenance requirements and instructions for Continued Airworthiness of the T2CAS Traffic
Terrain and Collision Avoidance System components are contained in the paragraphs that
follow:
Installation of the T2CAS on an aircraft by Supplemental Type Certificate or Form 337
obligates the aircraft operator to include the maintenance information provided by this manual
in the operator’s AMMl and the operator’s Aircraft Scheduled Maintenance Program.
A.
Maintenance information for the T2CAS (system description, removal, installation, testing,
etc.) is contained in this manual.
B.
LRU part numbers and other necessary part numbers contained in this manual should be
placed into the aircraft operator’s appropriate aircraft illustrated parts catalog (IPC).
C. Wiring diagram information contained in this manual should be placed into the aircraft
operator’s appropriate aircraft Wiring Diagram Manuals.
D. The T2CAS components are considered on--condition units and no additional
maintenance is required other than a check for security and operation at normal
inspection intervals.
E.
If a system component is inoperative, remove unit, secure cables and wiring, collar
applicable switches and circuit breakers, and placard them inoperative. Revise
equipment list and weight and balance as applicable prior to flight and make a log book
entry that unit was removed (refer to FAR Part 91.213 or the aircraft’s Minimum
Equipment List [MEL]).
F.
The T2CAS components can be repaired only at a factory authorized repair center or an
appropriately rated FAA Part 145 repair station.
G. Once repaired, reinstall the LRU in the aircraft in accordance with the original Form 337
approved data or instructions in this manual. Do a Return to Service test of the system
and approve it for return to service with a log book entry in accordance with the
requirements specified in FAR Part 43.9.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
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H. Scheduled maintenance program tasks to be added to the aircraft operator’s appropriate
aircraft maintenance program are as follows:
(1) Recommended periodic scheduled servicing tasks:
None required.
(2) Recommended periodic inspections are as follows:
• The TCAS directional antennas used with the T2CAS should be removed and the
underlying structure inspected for deterioration and corrosion during zonal
inspections usually performed in conjunction with heavy maintenance D checks.
• The ATC transponder(s) used with this system have test and inspections that are
required by FAR 91.413 to be completed every 24 months.
(3) Recommended periodic scheduled preventative maintenance tests (Tests to
determine system condition and/or latent failures):
• The ACSS T2CAS Computer Unit is designed to detect its own failures as well as
failures external to the computer unit. This BITE is continuously being executed
on a periodic basis. No formal periodic maintenance is required for the T2CAS
computer unit or the VSI/TRA display.
• The ACSS RCZ--852 Diversity Mode S Transponder is designed to detect its own
failures. This BITE is continuously being executed on a periodic basis. No formal
periodic maintenance is required for the transponder other than the 24 month
recertification test required by FAR 91.413.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
INSPECTION/CHECK
1. General
The visual check procedures that follow are recommended for the T2CAS Traffic and Terrain
Collision Avoidance System components after they have been installed in the aircraft.
2. Equipment and Materials
None
3. Procedure
CAUTION:
BEFORE YOU DO ANY OF THE PROCEDURES THAT FOLLOW, MAKE SURE ALL T2CAS
SYSTEM CIRCUIT BREAKERS ARE PULLED.
A. Check T2CAS Computer Unit
(1) Visually examine all external surfaces for possible damage. Check dust cover and
external connectors for dust, corrosion, or damage.
(2) Check external parts for loose or damaged hardware.
(3) Make visual check of wiring and connectors for damage.
B. Check Antennas
(1) Visually examine all external surfaces for possible damage.
(2) Check cabling for breaks, burned areas, and damaged insulation.
C. Check Control Panel
(1) Visually examine all external surfaces for possible damage.
(2) Check external parts (connectors, control knobs, annunciators) for looseness or
damage.
(3) Check that controller is securely mounted (Dzus fasteners properly engaged).
(4) Check controls for smooth, positive action.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
D. Check VSI/TRA Display
(1) Visually examine all external surfaces for possible damage. Check dust cover and
external connector for dust or damage.
(2) Check that display is securely mounted (locking mechanism is properly engaged).
(3) Check that LCD glass is not scratched or cracked.
E.
Check Transponders
(1) Visually examine all external surfaces for possible damage. Check dust cover and
external connectors for dust, corrosion, or damage.
(2) Check external parts for loose or damaged hardware.
(3) Make visual check of wiring and connectors for damage.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
CLEANING/PAINTING
1. General
While the T2CAS Traffic and Terrain Collision Avoidance System is installed in the aircraft,
cleaning is limited to the procedures given below. Painting and more extensive cleaning
should be done during shop maintenance when the LRUs can be disassembled. Detailed
instructions are given in each applicable component--level maintenance manual.
2. Equipment and Materials
WARNING:
BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL
SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE
DANGEROUS.
Table 9--1 gives the equipment and materials required for cleaning and painting.
Table 9--1. Equipment and Materials
Name
Description
Source
Abrasive paper
No. 600, nonconductive abrasive Optional source
Air supply
Air ionizing nozzle gun
attachment for compressed air
(20 psi)
Optional source
Cleaning brush
Soft, natural--bristle
(camel hair)
Optional source
Glass cleaner
Ammoniated
Optional source
Lens tissue
Lint Free
Optional source
Sandpaper
Grit sizes 220 and 400
Optional source
HMN 110C878
Catalyst, polyurethane — No.
V66V44(--4)
Sherwin--Williams Co,
Cleveland, OH
HMN 110C978
Reducer, polyurethane — No.
R7K84
Sherwin--Williams Co,
Cleveland, OH
HMN 1130778
Solvent — Isopropyl alcohol
(99%), semigrade
Optional source
HMN 6008676
Lint free cloth — Bluewipes, No.
TX512
Texwipe Co,
Upper Saddle River, NJ
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Table 9--1. Equipment and Materials (cont)
Name
Description
Source
HMN 94C2178
Coating, Prolane 2.8TPLUS
Sherwin--Williams Co,
polyurethane, semigloss WHT,
Cleveland, OH
FED--STD--595, Color No. 27925
— No. F63EXW968--4380
HMN 9460078
Primer, coating, epoxy, low VOC
(MIL--P--23377, Type I, Class 2)
Optional source
NOTES:
1. Equivalent alternatives are permitted for equipment and materials in this list.
2. The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given
to each material.
3. Cleaning
CAUTION:
IF YOU CLEAN ELECTROSTATIC SENSITIVE COMPONENTS WITH PRESSURIZED AIR,
MAKE SURE THE HOSE HAS AN AIR IONIZING NOZZLE OR GUN. AN ELECTROSTATIC
CHARGE CAN CAUSE DAMAGE TO THE LRU COMPONENT PARTS IF THE NOZZLE OR
GUN ATTACHMENT IS NOT USED.
A. Clean T2CAS Computer Unit and Mounting Tray
(1) Loosen mounting tray hold--down clamps and pull T2CAS computer unit out of
mounting tray.
(2) Clean mounting tray with cloth or brush dampened with solvent, then dry with cloth or
compressed air.
(3) Clean all dust and foreign matter from front panel and cover air vents with a clean
cloth or brush dampened with solvent or clean with compressed air.
B. Clean Antennas
Clean antennas with a cloth dampened with solvent. Dry with a clean cloth or use
compressed air.
C. Clean Control Panel
(1) Clean dust and foreign matter from cover and connectors with a brush dampened
with solvent, then dry with a clean cloth or compressed air.
(2) Clean front of control panel with a mild glass cleaner and soft cotton cloth.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
D. Clean VSI/TRA Display
(1) Clean front panel of display with a mild glass cleaner and soft cotton cloth.
(2) Clean the glass face with a mild glass cleaner and lens tissue.
E.
Clean Transponders
Clean transponders with a cloth dampened with solvent. Dry with a clean cloth or use
compressed air.
4. Painting
A. TCAS Directional Antennas
(1) Scope
This procedure covers the removal and reapplication of coating to the TCAS
directional antenna. Localized touch--up is allowable and preferred using airbrush
techniques to ensure minimal paint thickness. The touch--up may be applied either
with the antenna on the aircraft or removed from the aircraft.
(2) Procedure
WARNING:
SOLVENTS AND COATINGS ARE COMBUSTIBLE. KEEP AWAY FROM
HEAT AND OPEN FLAME.
(a) Clean
Scrape away all filleting and adhesive material from area to be coated. Remove
surface contamination using isopropyl alcohol or reducer.
(b) Scuff Sand
If the entire antenna is to be recoated, sand to primer with 220 grit sandpaper.
An orbital sander is preferred. For localized touch--up, feather sand areas of
exposed radome material to provide a smooth transition to the painted surface.
(c) Final Sand
If the entire antenna is to be recoated, sand primer and through--holes using 400
grit sandpaper or Scotch--Brite so the primer is removed except in swirls
wherever possible.
(d) Final Clean
Clean the surface to be coated with isopropyl alcohol or reducer.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
(e) Prime
NOTE:
The pot life of the primer after mixing components is 8 hours.
Cover each Torx screw head with an adhesive dot to prevent paint from
being applied to the screw heads.
Mix components in a 1:1 ratio under slow agitation.
Allow 15 minutes before spraying.
Spray one light coat -- wet film thickness of 1.5 mils.
• Viscosity -- 18 to 20 seconds No. 2 Zahn test
• Gun orifice -- 363--A needle or equivalent
• Fluid pressure -- 5 to 10 psi recommended
• Air pressure -- 50 psi recommended.
(f)
Primer Cure
Allow the primer to air dry for a minimum of one hour and a maximum of 4 hours
before applying the top coat.
(g) Paint
Mix paint in a base to catalyst ratio of 6:1 under slow agitation.
NOTE:
The percentage of reducer used can vary to meet the applicable color
standard.
Spray one light tack coat and allow to dry 15 minutes.
• Viscosity -- 20 to 22 seconds No. 2 Zahn test
• Gun orifice -- 363--A needle or equivalent
• Fluid pressure -- 5 to 10 psi recommended
• Air pressure -- 50 psi recommended.
Apply final top coat -- total wet film thickness of 3.5 to 4.0 mils.
(h) Drying Cycle
The antenna must air dry overnight or be baked at 85 degrees Celsius for 30
minutes minimum before flying. Remove the adhesive dots from the heads of
the Torx screws.
(3) Performance Verification Testing
Perform a ramp test per approved aircraft maintenance procedure on the T2CAS
system to ensure the bearing accuracy is within specification after the coating
application.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
B. Other T2CAS System LRUs
Except for minor touch up, painting should only be done after the LRU has been removed
from the aircraft or during shop maintenance. Painting procedures and materials are
given in the applicable LRU component maintenance manual (CMM).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
REPAIRS
1. General
Major repairs to the T2CAS system components are made only during shop maintenance
when the equipment is removed from the aircraft. Detailed instructions for repair and
adjustment of each of the repairable LRUs are presented in the applicable component
maintenance manuals given in Table 10--1.
Table 10--1. LRU Maintenance Manual
ACSS Component
Maintenance Manual (CMM)
ATA Number
TT--950 T2CAS Computer Unit
Part No. 9000000--10001
TBD
34--43--11
TT--951 T2CAS Computer Unit
Part No. 9000000--55001
TBD
34--43--11
TT--952 T2CAS Computer Unit
Part No. 9000000--20001
TBD
34--43--11
Control Panel
Part No. 4052190--902, --904, --906, --908
15--3841--01
34--43--01
Control Panel
Part No. 4052190--903, --905, --907, --909
15--3841--03
34--43--05
VSI/TRA Indicator
Part No. 4067241--8XX
15--2254--01
22--54--01
XS--950 Mode S Data Link Transponder
Part No. 7517800--XXYYY
A09--3839--002
34--52--08
XS--950 S/I Mode S/IFF Data Link Transponder
Part No. 7519350--XXYYY
A09--3839--003
34--52--09
RCZ--852 Diversity Mode S Transponder
Part No. 7510700--850
A09--3800--15
23--81--01
LRU
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
APPENDIX A
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
T2CAS AIRCRAFT CONFIGURATION WORK SHEET
Please fill out a T2CASt Customer Worksheet for each aircraft type.
Aircraft Operator
Current GPWS Altitude Callout Menu
Aircraft Type (Ex. B747--200)
Aircraft Quantity
Configuration Variants (i.e., different display
types)
Aircraft Serial Number(s) / Registration Number(s)
Installation Approval Information
Please provide the following as applicable.
Installation Approval Method (i.e., ACSS FAA STC,
customer local, OEM TC, etc.)
Installer (include contact and phone number)
Are the Aircraft FAA Type Certified?
Installation Design and Kit Provider (customer, ACSS,
etc.)
Target Date for Initial Installation
Plan for Fleet Installation
Aircraft Systems Information
Please provide the following information as applicable.
Existing TCAS ll
Manufacturer
Model / Part Number
Manufacturer
Model / Part Number
Existing Mode S
Transponder(s)
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
Existing Mode S
Control Panel
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Number of Sources Available for
T2CASt Use
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Existing GPWS
Manufacturer
Model / Part Number
Windshear Detection Enabled?
Number of Sources Available for
T2CASt Use
Radio Altimeter
Air Data Computer
FMS
IRS / INS / VG
(Select Correct Input)
Directional Gyro
(If Applicable)
GPS
Yes
No
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Part Number and Software Version
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
ILS Receiver
Stall Warning
Computer
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
*Format of Data
Number of Sources Available for
T2CASt Use
Manufacturer
Model / Part Number
Angle of Attack (AOA) *Format of Data
Number of Sources Available for
T2CASt Use
A. Aircraft Flight Deck Architecture for EFIS Equipped Aircraft
Please provide the following information as applicable.
EFIS Display
EHSI
MFD
EICAS
EFIS Symbol
Generator(s)
EFIS Control Panel
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Manufacturer
Model / Part Number
Manufacturer
Model / Part Number
Manufacturer
Model / Part Number
Manufacturer
Model / Part Number
Manufacturer
Model / Part Number and Software
Version
Manufacturer
Model / Part Number
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
B. Aircraft Flight Deck Architecture for Non--EFIS Equipped Aircraft
Please provide the following information as applicable.
Manufacturer
Weather Radar
Display
Model / Part Number
Single or Dual Display Configuration
Manufacturer
Weather Radar
Model / Part Number
Single or Dual Display Configuration
Source
Display
p y Range
Selection (WXR
Control Panel)
WXR Ranges (Ex. 10, 20, 40nm,
etc.)
WXR Indicator or WXR Control
Panel Format of Data
C. Aircraft Flap and Landing Gear Data
Landing Gear Down
j Gnd / Open
Landing Flaps
j Gnd / Open
j +28 VDC / Open
j 3 Wire Synchro
Flap Angle
j Gnd / Open
j Digital
j 3 Wire Synchro
T2CASt System Integration Worksheet
The following checklist allows the user to define the level of system integration services required of
ACSS’ Certification and Applications Engineering. Please mark/select the integration services
desired by the ACSS Certification and Applications Engineering:
Option
Check
Service
Required
ACSS Aircraft
Approval
Options
Department of Services / Products Provided to Customer
Equipment Only
No Systems Integration or Certification Services Requested of
ACSS
Installation Data
Package (IDP)
ACSS Coordinates the Development of the Aircraft Installation
Data Package Sufficient to Obtain Airworthiness Approval
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Aircraft Installation
Kit
ACSS Coordinates the Fabrication of Aircraft Installation Kits
Based on The Installation Data Package
Airworthiness
Approval
ACSS Supports Customer’s Effort to Obtain a Local Approval
No Direct Approval Coordination by ACSS is Requested
Airworthiness
Approval
ACSS Coordinates the Airworthiness Approval
(FAA STC, CAA Approval, Etc.)
Installation
Support
ACSS Provides On--Site Installation Support for the First
Aircraft (Additional Aircraft as Mutually Agreed)
Physical
Installation
ACSS Coordinates the Touch Labor for the Physical Installation
of the T2CASt System
Note:
This option involves many variables and will need to
be negotiated on a case--by--case basis.
Aircraft Installation Kit Worksheet
For programs where installation kit services are requested of ACSS, the following table allows the
Customer to provide a general description of the type of kit required for its particular aircraft. It is
anticipated that one aircraft installation kit worksheet will be completed for each aircraft type and/or
of each aircraft configuration type.
Review of the previous sections provides the user with a general understanding of the various
aspects of the T2CASt installation, and provides a basis for the kit installation options.
Initial Aircraft Configuration1
Mode S
Transponder(s)
GPS
Number to Add2
Source Desired2
Existing
GPS
Position
Source
Existing
TCAS ll
Existing
GPWS
No
No
No
T2CASt
Other3
No
No
Yes
T2CASt
Other3
No
Yes
No
T2CASt
Other3
No
Yes
Yes
T2CASt
Other3
Yes
No
No
Yes
No
Yes
Yes
Yes
No
Yes
Yes
Yes
TAWS Switch
Annunicators2
Discrete
LRU(s) with
(cube)
Edge
Units
Lighted
Installed in
Panels
the
Instrument
Panel or
Glareshield
1. Select the row that best represents the current configuration of aircraft.
2. Indicate selection by blackening the appropriate cells.
3. If other compatible GPS source will be installed, please specify the manufacturer, model and part number of the unit.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
APPENDIX B
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
APPENDIX B
AIRCRAFT CONFIGURATION MATRIX
Table B--1. Aircraft Configuration
Figure
Number
B--1
Aircraft Type
King Air C90
Configuration 1
ICD
Document
No.
8000119-002
Note 1
Radio
Altimeter
Rockwell
Collins Alt--55B
Air Data
Computer
ISS ADDU-80130--16 (Air
Data Display
Unit)
Inertial
System
Dir Gyro:
Sperry C--14A
Vert Gyro:
Bendix--King
KVG--350
FMC
Not Installed
GPS/GNSS
Honeywell/
Trimble
HT9100
ILS/ MLS
Garmin GNS
530
Angle of
Attack
Not Installed
NOTES:
1. The King Air Configuration 1 is internal to ACSS. As such, no ICD was created for this configuration. The document number given is for the ASDB SRS.
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Decision
Height
Bendix--King
EFS 40
Flap/Slat
Settings
Onboard
Maintenance
System
Terrain Hazard
Display
Not Installed
Not Installed
Bendix RDR
2000
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T2CAS / Part No. 9000000
Figure B--1.
T2CAS King Air C90 Interface Block Diagram
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ACSS an L 3 Communications and Thales TT-950 TCAS II User Manual Part 2

ACSS an L-3 Communications and Thales Company TCAS II Part 2

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User Manual Part 2

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