SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Figure 2--13 (Sheet 2). Directional Antenna Baseplate Outline and Installation Diagram 34-43-20 2--53/(2--54 blank) 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 Figure 2--14. Gables G130--XX Control Panel Outline and Installation Diagram 34-43-20 2--55/(2--56 blank) 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 Figure 2--15. VSI/TRA Outline and Installation Diagram 34-43-20 2--57/(2--58 blank) 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 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.
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 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 Figure 3--1. Typical TCAS Installation Types 34-43-20 3--3 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Figure 3--2. T2CAS Computer Tray Mating Connector 34-43-20 3--5 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 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 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 Figure 3--5. Contact Arrangement for Left Bottom Plug (LBP) Insert 34-43-20 3--7 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 Figure 3--6. Contact Arrangement for Right Top Plug (RTP) Insert 3--8 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 Figure 3--7. Contact Arrangement for Right Middle Plug (RMP) Insert 34-43-20 3--9 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 Figure 3--8. Contact Arrangement for Right Bottom Plug (RBP) Insert 3--10 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 Figure 3--9. TCAS Computer Unit Data Loader Connector (J1) Pin Layout 34-43-20 3--11 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 E. Control Panels Table 3--1 contains the interconnect data for the Gables G7130 series control panels. Table 3--1.
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.
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.
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 S | T S | Digital ADC No.2 or IRS No.2 S T S Digital ADC No.2 or GND IRS No.2 l l (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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Figure 3--10. VSI/TRA 41--Pin Connector Layout 34-43-20 3--17 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Figure 3--11. Typical T2CAS Single Terrain Hazard Display Interface 34-43-20 3--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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--3.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--4.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--4.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--4.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--4.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 3--5.
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.
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).
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.
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.
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.
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.
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.
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.
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).
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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).
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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”.
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.
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.
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.
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.
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.
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.
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”.
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.
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.
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.
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.
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.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 • 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).
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--6.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 • 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--8. Operator Selectable Options -- Default Settings(cont) Operator Selectable Options 4--58 15 Feb 2003 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--8.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--8. Operator Selectable Options -- Default Settings(cont) Operator Selectable Options 4--60 15 Feb 2003 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--9.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--9.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--9.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--11.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--13.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--14.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--17. Sign Status Matrix (SSM) [BCD] BITS Meaning 30 31 0 0 North/Plus 0 1 No Computed Data 1 0 Functional Test 1 1 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--18.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--19.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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).
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--23.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--23.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 4--26.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Blank Page 4--94 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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).
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 5--3.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 • “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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Figure 5--2. Extended Self--Test of TAWS/Windshear Functional Areas 5--8 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 • 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.
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).
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).
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Table 5--4.
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.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
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.
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.
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.
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.
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 1 SUPP FAULT GOTO 0010 Suppression bus failure.
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.
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.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 CLIMB INH 0000 Climb Inhibit inputs: RMP--1J, RMP--13G, RBP--5J, RBP--5K.
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.
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.
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.
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.
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.
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.
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.
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.
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. 6--22 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 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.
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.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (e) As an example, suppose the following insertion losses have been measured: Antenna Port Antenna Port Measured Loss 0 90 8.5 dB 0 180 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Blank Page 6--32 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 11. Instructions for Continued Airworthiness, FAR Part 25.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 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.
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.
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.
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.
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.
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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 (e) Prime NOTE: The pot life of the primer after mixing components is 8 hours. 1 Cover each Torx screw head with an adhesive dot to prevent paint from being applied to the screw heads. 2 Mix components in a 1:1 ratio under slow agitation. 3 Allow 15 minutes before spraying. 4 Spray one light coat -- wet film thickness of 1.5 mils. • Viscosity -- 18 to 20 seconds No.
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). 34-43-20 9--5 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 Blank Page 9--6 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Blank Page 10--2 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 APPENDIX A 34-43-20 A--1 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 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.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No.
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.
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 g Selection (WXR Control Panel) WXR Ranges (Ex. 10, 20, 40nm, etc.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 3 Aircraft Installation Kit ACSS Coordinates the Fabrication of Aircraft Installation Kits Based on The Installation Data Package 4 Airworthiness Approval ACSS Supports Customer’s Effort to Obtain a Local Approval No Direct Approval Coordination by ACSS is Requested 5 Airworthiness Approval ACSS Coordinates the Airworthiness Approval (FAA STC, CAA Approval, Etc.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 APPENDIX B 34-43-20 B--1 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 Blank Page B--2 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 APPENDIX B AIRCRAFT CONFIGURATION MATRIX Table B--1. Aircraft Configuration Figure Number B--1 Aircraft Type King Air C90 Configuration 1 ICD Document No.
SYSTEM DESCRIPTION AND INSTALLATION MANUAL T2CAS / Part No. 9000000 Figure B--1. T2CAS King Air C90 Interface Block Diagram 34-43-20 B--5/(B--6 blank) 15 Feb 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
