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SYSTEM DESCRIPTION AND INSTALLATION MANUAL

CAS/Part No.9005000

Table 4-1: T

CAS Computer Unit Interface Description (cont)

(Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203)

Connector

Designation

Functional Description

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 TCAS 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.

RMP-3E

Reserved Discrete Output (Lamp Driver)

RMP-3F, 3G

600-Ohm Audio Output: [RMP-3F (HI), RMP-3G (LO)]

This is a synthesized voice output supplied by the T

CAS computer unit. Its level is

programmable up to 80 mW 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

Program Pin Parity Input

RMP-3J

Program Pin Parity Input

RMP-3K

Traffic Selection Device Input #1 (Rotate Right)

RMP-4A

Reserved

RMP-4B

Reserved

RMP-4C

Reserved

RMP-4D

Reserved

RMP-4E

Reserved

RMP-4F

Reserved

RMP-4G

Reserved

Pub. No. 8600200-001, Revision 004

34-45-29

4-13

04 Nov 2014

Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.

Summary of content (261 pages)

PAGE 1
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description 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.
PAGE 2
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No.
PAGE 3
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-6D Performance Limit Discrete Input (NO) 3 This input provides the T CAS computer unit with an input from the Flight Management Computer (or equivalent) which indicates when the aircraft cannot achieve a 1500 FPM (457.2 m/min) climb rate.
PAGE 4
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-7E TA Display No.1 Status Discrete Input (NO) Two display status ground/open discrete inputs (Note 1) are provided by the 3 T CAS computer unit at RMP-7E (TA Display No.1) and RMP-7J (TA Display No.2).
PAGE 5
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-10A RMP-10B Reserved Program Pin Inputs Reserved for future use. RMP-10C APM Installed Program Input (NO) A ground on this pin indicates that an Aircraft Personality Module (APM) is 3 connected to the T CAS.
PAGE 6
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-11G, 11H ARINC 429 Input: FMC #1:EIS [RMP-11G (A), RMP-11H (B)] This high-speed 429 input from the Flight Management Computer (FMC) Electronic 3 Instrument System (EIS) provides position information from the FMC to the T CAS.
PAGE 7
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RMP-12B (Continues) Functional Description Radio Altimeter Type Select Program Input No.4 (NO) 3 The T CAS 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.
PAGE 8
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RMP-12B (Continued) Functional Description ARINC 552/552A -20 < H < 480 ft: Voltage = [ 0.02 x (H + 20) ] V dc 480 < H < 2500 ft: Voltage = [ 10 x ( 1 + ln((H + 20)/500)) ] V dc Where H = Radio Altitude in ft. Maximum Voltage output is 26.2 V dc at any height above 2500 ft .
PAGE 9
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RMP-12B (Continued) Functional Description LPIA 1.0 to 9.0 V dc: H = 50V - 50 > 9.0 to 21.0 V dc: H = 383.14V - 3048 Where H = Radio Altitude in ft and V = Voltage in V dc. NR-AS-10A Alternate 0.0 to 1.2 V dc: H = 2105.7V Where H = Radio Altitude in ft and V = Voltage in V dc.
PAGE 10
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-12D Analog Radio Altimeter Type Select Program Input No.3 (NO) See RMP-12B. RMP-12E Analog Radio Altimeter Type Select Program Input No.2 (NO) See RMP-12B. RMP-12F Analog Radio Altimeter Type Select Program Input No.1 (NO) See RMP-12B.
PAGE 11
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-13F Landing Gear Discrete Input (NO) 3 The T CAS computer monitors this discrete that indicates the landing gear position.
PAGE 12
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RMP-14D, 14E FCU #2: Selected Altitude 701/720 ARINC 429 Bus Input Optional TCAS input for ARINC 429 low-speed Selected Altitude labels 025 or 102.
PAGE 13
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RBP-1E Functional Description Reserved RBP-1F, G GPS #2 Time Mark Input: [RBP-1F (A), RBP-1G (B)] These RS422 differential pair inputs are provided to receive the Time Mark signal from an external GPS receiver in order to provide synchronization with other aircraft systems.
PAGE 14
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RBP-3F Reserved for TCAS/ADS-B Pin Strobing. RBP-3G TCAS/ADS-B Parity. 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.
PAGE 15
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RBP-5A Functional Description Advisory Inhibit Discrete Input No.
PAGE 16
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description 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.
PAGE 17
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RBP-7A Functional Description Audio Level Program Pin No.1 (NO) Two synthesized voice outputs with programmable output levels are provided by 3 the T CAS computer unit. The output at RMP-2F and -2G supply high-level (up to 8 W) audio signals to an 8-ohm speaker.
PAGE 18
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description RBP-7E Ground Display Mode Program Pin (NO) 3 The T CAS computer unit monitors this programming pin to select the TCAS ground display mode while the aircraft is on the ground.
PAGE 19
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation RBP-8A Thru RBP-8D Functional Description Reserved Program Pins 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.
PAGE 20
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description 3 T CAS 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 0degree port because it produces a transmission pattern in the forward quadrant of the aircraft.
PAGE 21
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description LMP-2 Bottom Antenna 90-Degree Port J2 on the antenna is color-coded black. This antenna port (Note 2) is called the 90degree port because it produces a transmission pattern in the right-wing quadrant of the aircraft.
PAGE 22
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description LBP-9 Fan 115 V ac Power Output (C) See LBP-5. LBP-10 28 VDC Power Input (+) LBP-11 Chassis Ground 3 Connect to aircraft frame. The T CAS Chassis and signal ground pins should use the same AWG as the power connections (See LBP-1 and LBP-10).
PAGE 23
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description 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 Reserved. J1-19 PDL Link B Common Reserved..
PAGE 24
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description J1-41 RS-232 Data Output #1 3 This output is used by the T CAS function to transmit RS-232 data to a portable maintenance terminal.
PAGE 25
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-1: T CAS Computer Unit Interface Description (cont) (Applicable to Part No. 9005000-10000, -10101, -10202, -10204, and -11203) Connector Pin Designation Functional Description NOTE 1: Ground = Voltage of 0.0 V dc to +3.5 V dc or Resistance of less than 10 ohms applied to input. Open = Voltage of +18.5 to +36 V dc or Resistance greater than 100k ohms applied to input.
PAGE 26
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description 3 T CAS Computer Unit Right Top Plug (RTP) RTP-1A, 1B ARINC 453 Terrain Display Output No.1: (RTP-1A [A], RTP-1B [B]) 3 T CAS output number 1 to the terrain awareness display. RTP-1C, 1D ARINC 429 Input: Spare RTP-1E, 1F ARINC 453 Terrain Display Output No.
PAGE 27
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RTP-3G, 3H EWEU #2 (Slat/Flap Control Computer #2) [RTP-3G (A), RTP-3H (B)] 3 This high-speed bus inputs flap angle and body angle of attack to T CAS.
PAGE 28
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RTP-6E Discrete Input (Gnd/Open) XPDR Mode S Address Bit A13. RTP-6F Strobed Program Pin TAWS/XPDR #2: Aircraft Type. Refer to Table 4-19: Aircraft Type Configurations RTP-6G Strobed Program Pin TAWS/XPDR #3: Lateral Position Priority. Refer to sub-section 3.C.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RTP-8A, 8B Functional Description ARINC 429 TAWS Output #1 This bus outputs TAWS and Ground Collision Avoidance Module (GCAM) data. RTP-8C Discrete Input (Gnd/Open) Internal XPDR SDI #1 Refer to Note 6 following the table.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No.
PAGE 31
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RTP-12A Strobed Program Pin DO-260B Config Data #1 Refer to sub-section 3.B. TAWS/RWS/XPDR/DO-260B Data Configuration RTP-12B Strobed Program Pin DO-260B Config Data #2 Refer to sub-section 3.B.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No.
PAGE 33
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RTP-15F APM Clock This is 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. Connect to APM J1-2.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description 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.
PAGE 35
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description 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 3 sources.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RMP-3F, 3G Functional Description 600-Ohm Audio Output: [RMP-3F (HI), RMP-3G (LO)] 3 This is a synthesized voice output supplied by the T CAS computer unit. Its level is programmable up to 80 mW into a 600-ohm audio distribution system.
PAGE 37
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RMP-5H Reserved: No Connection RMP-5J Reserved: No Connection RMP-5K Air Ground Discrete Input (NO): (Weight-On-Wheels) 3 This ground/open-type discrete input (Note 1) to the T CAS computer unit indicates the status of the Air/Ground or Weight-On-Wheels (WOW) switch.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RMP-7A, 7B ARINC 429 Air Data/Inertial Reference Unit (ADIRU) #1 (Left), Inertial Reference Part (IRS) Input: [RMP-7A (A), RMP-7B (B)] This high-speed input is provided for applications to receive Inertial Reference System information. RMP-7C, 7D ARINC 429 TA/RA Display No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RMP-9A, 9B ARINC 429 ADLP Comm C Output: [RMP-9A (A), RMP-9B (B)] These pins serve as the input interface to the transponder function ADLP Comm C protocol. RMP-9C, 9D Reserved for ARINC 735B Data Bus Output. RMP-9E, 9F Reserved for ARINC 735B Data Bus Output.
PAGE 40
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RMP-11E, 11F ARINC 429 Input: MMR/GPS #1 (Left) [RMP-11E (A), RMP-11F (B)] This high-speed 429 input is used to receive GPS label input containing position, velocity and quality information for the use of ADS-B IN applications and by the transponder function of ADS-B OUT.
PAGE 41
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RMP-12B (Continues) Functional Description Radio Altimeter Type Select Program Input No.4 (NO) 3 The T CAS 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.
PAGE 42
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RMP-12B (Continued) Functional Description -20 < H < 480 ft: Voltage = [ 0.02 x (H + 20) ] V dc 480 < H < 2500 ft: Voltage = [ 10 x ( 1 + ln((H + 20)/500)) ] V dc Where H = Radio Altitude in ft. Maximum Voltage output is 26.2 V dc at any height above 2500 ft . Collins BCA -20 < H < 500 ft: Voltage = [ 0.
PAGE 43
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RMP-12B (Continued) Functional Description NR-AS-10A Alternate 0.0 to 1.2 V dc: H = 2105.7V Where H = Radio Altitude in ft and V = Voltage in V dc. NR-AS-10A Curve Fit 4 3 2 0.0 to 18.1 V dc: H = 0.0833V - 1.8887V + 15.5169V - 21.9374V + 14.8097 Where H = Radio Altitude in ft and V = Voltage in V dc.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RMP-12G Traffic Generator (Ethernet RX+) 3 The T CAS computer unit may be configured in some lab installations to receive simulated traffic over an Ethernet connection rather than RF interface. Also serves as the A615A Dataloader Interface.
PAGE 45
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RMP-13H, 13J Radio Altimeter No.1 (Left) Input: [RMP-13H (A), RMP-13J (B)] This input is provided for low-speed ARINC 429 (12.5k bits/s) altitude inputs from an ARINC 707 digital radio altimeter.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No.
PAGE 47
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description RBP-3F TCAS/ADS-B In #10 Pin Strobing Discrete Input See RBP-2A. RBP-3G TCAS/ADS-B In #11 Pin Strobing Discrete Input See RBP-2A. 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RBP-5A Functional Description Advisory Inhibit Discrete Input No.
PAGE 49
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description 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.
PAGE 50
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RBP-7A Functional Description Audio Level Program Pin No.1 (NO) Two synthesized voice outputs with programmable output levels are provided by the 3 T CAS computer unit. The output at RMP-2F and -2G supply high-level (up to 8 W) audio signals to an 8-ohm speaker.
PAGE 51
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) 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 sec and are preceded by a tone. If pin is left open, no delays or tones occur.
PAGE 52
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation RBP-7K RBP-8A Thru RBP-8D Functional Description Program Common This is the ground source for use with program pins. Reserved: Program Pin Inputs RBP-8E Self-Test Test Inhibit Program Pin (NO) This program pin determines if self-test will be inhibited while airborne.
PAGE 53
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description 3 T CAS 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 0degree port because it produces a transmission pattern in the forward quadrant of the aircraft.
PAGE 54
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description LMP-2 Bottom Antenna 90-Degree Port J2 on the antenna is color-coded black. This antenna port (Note 2) is called the 90degree port because it produces a transmission pattern in the right-wing quadrant of the aircraft.
PAGE 55
SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description LBP-9 Fan 115 V ac Power Output (C) See LBP-5. LBP-10 28 VDC Power Input (+) LBP-11 Chassis Ground 3 Connect to aircraft frame. The T CAS Chassis and signal ground pins should use the same AWG as the power connections (See LBP-1 and LBP-10).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description 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 Reserved. J1-19 PDL Link B Common Reserved..
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation Functional Description J1-41 RS-232 Data Output #1 3 This output is used by the T CAS function to transmit RS-232 data to a portable maintenance terminal. J1-42 RS-232 Data Input #2 3 This input is used by the T CAS function to receive RS-232 data from a portable maintenance terminal.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 4-2: T CAS Computer Unit Interface Description (Applicable to Part No. 9005000-11801 and -55801) Connector Pin Designation NOTE 1: Functional Description Ground = Voltage of 0.0 V dc to +3.5 V dc or Resistance of less than 10 ohms applied to input. Open = Voltage of +18.5 to +36 V dc or Resistance greater than 100k ohms applied to input.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-3: Gables Control Panel Interface Descriptions Connector Pin Designation Functional Description J1-1, 2 PANEL AND DISPLAY LIGHTING INPUT: (J1-1 HIGH, J1-2 LOW) 5-V ac, 2.3-A maximum lighting input for front panel and display lighting. Lighting is provided by incandescent lamps. J1/J2-3, 4 +28 V dc INPUT POWER: (J1/J2-3 HIGH, J1/J2-4 LOW) The control panel is powered from a +28-V dc power bus.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-3: Gables Control Panel Interface Descriptions (cont) Connector Pin Designation Functional Description J1/J2-12 XPDR 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-3: Gables Control Panel Interface Descriptions (cont) Connector Pin Designation Functional Description 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 3 T CAS/Part No.9005000 Table 4-4: Thales 41-Pin VSI-TCAS Interface Description (cont) Connector Pin Designation Functional Description 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 V ac, 400-Hz reference signal is received on pin 5, (HI) and pin 16, (LO).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-4: Thales 41-Pin VSI-TCAS 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-4: Thales 41-Pin VSI-TCAS Interface Description (cont) Connector Pin Designation Functional Description J1-26 ARINC 429 (A) TCAS TA/RA DATA INPUT: 3 Traffic and Resolution Advisory data is supplied to the VSI-TCAS from the T CAS computer unit via this high-speed ARINC 429 data bus. Paired with pin 11. J1-27 ARINC 429 (A) VERTICAL SPEED NO.1 INPUT: This is the primary ARINC 429 input bus to the VSI-TCAS.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-4: Thales 41-Pin VSI-TCAS Interface Description (cont) Connector Pin Designation Functional Description J1-32 CONFIGURATION STRAP #0 INPUT (NO): See pin 31. J1-33 CONFIGURATION STRAP #1 INPUT (NO): See pin 31. J1-34 CONFIGURATION STRAP #2 INPUT (NO): See pin 31. J1-35 CONFIGURATION STRAP #4 INPUT (NO): See pin 17.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-4: Thales 41-Pin VSI-TCAS Interface Description (cont) Connector Pin Designation Functional Description J1-39 dc GROUND INPUT: To be connected to aircraft dc Ground. J1-40 115-V ac, 400-HZ POWER INPUT (HI): This pin, along with its return line (pin 23) supplies power to the VSI-TCAS. Connect power through a 1-A circuit breaker.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-5: ACSS 41-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1-5 VERTICAL SPEED 26 V ac, 400-HZ REFERENCE INPUT (HI): See pins 4 and 16. J1-8 VERTICAL SPEED VALID DISCRETE INPUT: The VSI/TRA receives a 28-V dc 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-5: ACSS 41-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1-18 PRESSURE TRANSDUCER MODULE POWER OUTPUT (COMMON): An optional ACSS PTM may be used in an installation to supply ARINC 429 vertical speed information to the VSI/TRA. Pins 18, 19, and 20 supply input power to the PTM. Pin J1-18 is the power return pin and is connected to PTM pin 8.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-5: ACSS 41-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description 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 3 T CAS/Part No.9005000 Table 4-5: ACSS 41-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-34 Functional Description CONFIGURATION STRAP #2 INPUT (NO): For -84X and -88X units, this pin programs the VSI/TRA to use the remote light sensor input at pins 24 and 25. If CS2 is open, a Boeing Airplane Company remote light sensor type (-10 to +10 V) is expected at pins 24 and 25.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-5: ACSS 41-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-35 (Continued) Functional Description For -84X units, CS4 is paired with CS3 (pin 17) to program the Display Range Format.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-5: ACSS 41-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1-40 115-V AC, 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-A circuit breaker. J1-41 CONFIGURATION STRAP #8 INPUT (NO): For -88X and -89X units, CS8 is paired with CS3 (pin 17) to program the Filter Time Constant.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1-4 BOOTSTRAP REFERENCE OUTPUT: This output sends the bootstrap ARINC 565 ac reference voltage to the cross-side display. The output is connected to the Secondary 26-V ac Reference Input (pin 7) of the cross-side display. J1-5 VERTICAL SPEED NO.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-17 Functional Description CONFIGURATION STRAP #5 INPUT (NO): For -84X units, CS5 is paired with CS6 (pin 37) to program the altitude band.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-22 Functional Description CONFIGURATION STRAP #8 INPUT (NO): For -84X and -86X units, CS8 is not used and pin J1-22 must remain Open. For -88X and -89X units, CS8 is paired with CS3 (pin 35) to program the Filter Time Constant. The following apply: O = Open, G = Ground Pin CS8 22 CS3 35 O O 5.0-sec Delay O G 6.4-sec Delay G O 3.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-29 Functional Description SOURCE SELECT #2 DISCRETE INPUT: This discrete input is used in conjunction with source select discrete #1 (SS1) and configuration straps CS0 and CS1 to program the VSI/TRA to accept and use the vertical speed data being supplied. The following applies: O = Open, G = Ground, 28V = 28 V dc and X = Don’t Care.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-34 Functional Description J1-34 CONFIGURATION STRAP #2 INPUT (NO): For -84X and -88X units, this pin programs the VSI/TRA to use the remote light sensor input at pins 23 and 24. If CS2 is open, a Boeing Airplane Company remote light sensor type (-10 to +10 V) is expected at pins 23 and 24.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1-36 CONFIGURATION STRAP #4 INPUT (NO): For -84X units, CS4 is paired with CS3 to program the Range Format. See pin 35. For -86X, -88X, and -89X units, CS4 is paired with CS5 to program the Display Format. See pin 17.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-6: ACSS 55-Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1-52 3. Functional Description PRESSURE TRANSDUCER MODULE +15 V dc POWER OUTPUT: Connects to PTM pin 5. See pin 50. TAWS/RWS and Transponder Specifications The Ground Collision Avoidance Module (GCAM) function performs the core TAWS and reactive windshear detection processing.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 ● The Aircraft Installation references a Table that assigns the TAWS/RWS signals to an Analog, Discrete or Digital Input/Output. For example, Digital Input FMC #1 could be 3 assigned to pins RTP-1G, 1H. Table 4-1 and Table 4-2 of sub-section 2 T CAS Interface Description would then be referenced to obtain the specifics (pin numbers, usage, tolerances, etc.) of Digital Input FMC #1.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 A. TAWS/RWS/XPDR/DO-260B Data Configuration (1) ASDB 3 The ASDB is a field loadable database that customizes the T CAS operation for a specific aircraft. The ASDB defines the Input/Output definition for the specific aircraft type and the aircraft climb performance data to support of the TAWS functionality. 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (2) ● 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 nonstandard conversion allows for a number of operations to be performed on the data. Operations which may be performed include mathematical, comparison and branching.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Verification of the correct APM contents may be accomplished by the RS-232 3 port or on the TAWS display. After the APM is programmed, the T CAS, 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 3 aircraft configuration data.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-7: Callout Configuration Items (NOTE 1) (cont) Configuration Option ACD Setting Option 50-ft (15.24-m) Callout Enable Flag Enable/Disable Callout 40-ft (12.192-m) Callout Enable Flag Enable/Disable Callout 35-ft (10.668-m) Callout Enable Flag Enable/Disable Callout 35-ft (10.668-m) (Tone) Callout Enable Flag Enable/Disable Callout Tone 30-ft (9.144-m) Callout Enable Flag Enable/Disable Callout 20-ft (6.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-8: Operator Selectable Options – Default Settings (cont) Operator Selectable Options Store GCAM Parameters Enable Store GFM Parameters Enable TAWS Caution Flash Enable TAWS Warning Flash Enable Data Parameter Selectable Option 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-8: Operator Selectable Options – Default Settings (cont) Operator Selectable Options Data Parameter Selectable Option 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-8: Operator Selectable Options – Default Settings (cont) Operator Selectable Options Data Parameter Selectable Option Mode 1 Disable MODE_1_DISABLE TAL LookAhead 30 Seconds MAAS Disable TAL_LOOKAHEAD_30S_MAAS_DISABLE Narrow TAL Roll Limit TAL ILS Deviation Limit Display Alert Line Aperture Runway Location Error 4-106 04 Nov 2014 NARROW_TAL_ROLL_LIMIT If the value of Narrow TAL Roll Limit is set to 0.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-8: Operator Selectable Options – Default Settings (cont) Operator Selectable Options Data Parameter Selectable Option BASIC_RUNWAY_INHIB_ANNUN The zero (0) state is the disabled state for this option. The one (1) state enables the ”TERR N/A” annunciator to activate when GCAM indicates Basic Airport.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-8: Operator Selectable Options – Default Settings (cont) Operator Selectable Options Data Parameter Selectable Option OCPA_MODE_CAUTION This setting defines the verbal transmission (words) intended to occur during this alert. OCPA_MODE_A_WARNING This setting defines the verbal transmission (words) intended to occur during this alert.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-8: Operator Selectable Options – Default Settings (cont) Operator Selectable Options Data Parameter Selectable Option Eleview Water Texture ELEVIEW_WATER_SLICE_TE XTURE Not selectable by customer. Eleview Rasterized Text Disable ELEVIEW_RASTERIZED_TEX T_DISABLE Not selectable by customer. Eleview Text Offset X ELEVIEW_TEXT_OFFSET_X Not selectable by customer.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The ARINC 429 Sign Status Matrix Bit definitions for Binary data and Binary Coded Decimal data are shown in Table 4-10 and Table 4-11 respectively.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (c) RS-422 Signals 3 The T CAS 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-12: APM/ASDB Programmable Discrete Inputs (Applicable to Part Numbers 9005000-10000, -10101, -10202, -10204, -11203) Digital Signal Definition Pin# Notes (Typical Allocation Shown) GND Program Input RTP-12B Spare Or DO-260B Config Data #2 (For Part No.-11203) GND Program Input RTP-12C Spare Or DO-260B Config Data #3 (For Part No.-11203) GND Program Input RTP-12D Spare Or DO-260B Config Data #4 (For Part No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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 3 being loaded to ground when power is removed from the T CAS. NOTE: (b) 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 3 T CAS/Part No.9005000 RTP-9K is the parity pin for DO-260B Config Data #1 through #7, inclusive. RTP-9K should be connected to RTP-13B if an even number of DO-260B Config Data #1 through #7 are set to ground. In other words, among Config Data #1 through #7 and the parity pin, an odd number of pins should be connected.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-17: DO-260B Configuration Pins (Applicable to Part Numbers 9005000-11203, -11801, -55801) RTP-9J DO-260B Config Data #7 RTP-9K DO-260B Config Data Parity ADS-B Receive Capability bit 1 VFOM Adjust bit 0 VFOM Adjust bit 1 NOTE: If the number of DO-260B Config Data #1 through #7 pins connected is even, connect RTP-9K to RTP-13B, else RTP-9K should be left Open.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 B. TAWS/XPDR Pin Programming (1) Aircraft Type Configurations (See Table 4-19) Table 4-19: Aircraft Type Configurations Definition No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-19: Aircraft Type Configurations (cont) Definition No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-19: Aircraft Type Configurations (cont) Definition No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-19: Aircraft Type Configurations (cont) Definition No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 CPA Warning (Audio Menu Selection programming Pin is a don’t care) - “AVOID TERRAIN” Note that a single “TERRAIN AHEAD, PULL-UP, AVOID TERRAIN” or “TERRAIN TERRAIN, PULL-UP, PULL-UP, AVOID TERRAIN” is provided when an Avoid Terrain condition exist before a Pull-Up occurs.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Lamp Format 2 - the warning alert discrete output (RTP-13D) are grounded only for the warning audio messages containing the phase “PULL-UP” or “AVOID TERRAIN and the caution alert discrete output (RTP-13B) is used for all other alert messages. (4) Spare Configuration/Automatic CPA-THD Deactivation/CPA-THD Function. (See Table 4-22.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (6) Runway Alerting Function/GPS Source/Topographical Mode Function. (See Table 4-24.) Table 4-24: Runway Alert Function/GPS Source/Topographical Mode Function Configuration Number Runway Alerting Function (Provisional) (NOTE 1) GPS Source (NOTE 2) Topographical Mode Function (Provisional) (NOTE 3) Connect RTP 7F to: 1 Disable Indirect Disable Open 2 (Spare Conf.) Disable Indirect Enable RTP-13B 3 (Spare Conf.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (7) ADLP Installed/Terrain Data Comparison Function/Flight Plan Assessment Trajectory Function. (See Table 4-25.) Table 4-25: ADLP/Terr Data Comparison/Flight Function Configuration Number ADLP Installed (NOTE) Terrain Data Comparison Function Flight Plan Assessment Trajectory Function Connect RTP 7G to: 1 Disable Disable Disable Open 2 (Spare Conf.) Disable Disable Enable RTP-13B 3 (Spare Conf.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (8) Lateral Position Priority/Simulator Environment. (See Table 4-26.) Table 4-26: Lateral Position Priority/Simulator Environment Configuration Number Spare 1 Disable 2 Lateral Position Priority Simulator Environment Connect RTP 6G to: FMS First Disable Open Disable FMS First Enable RTP-13B 3 Disable GPS/GPIRS First (Config. Invalid if GPS not configured) Disable RTP-13C 4 Disable GPS/GPIRS First (Config.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (9) Alternate Altitude Source Selection, Autonomous GPS Present, and Hybrid GPS Present. (See Table 4-27.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (10) Maximum Cruising True Airspeed. (See Table 4-28.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (12) Terrain Advisory Line. (See Table 4-30.) Table 4-30: Terrain Advisory Line Configuration Number Spare Spare Terrain Advisory Line Display Connect RTP 11A to: 1 Disable Disable Disable Open 2 Disable Disable Enable RTP-13B 3 (Spare Conf.) Disable Enable Disable RTP-13C 4 (Spare Conf.) Disable Enable Enable RTP-13D 5 (Spare Conf.) Enable Disable Disable RTP-13E 6 (Spare Conf.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (14) Obstacle Function. (See Table 4-32.) Table 4-32: Obstacle Function Configuration Number Spare Spare Obstacle Function Connect RTP 11F to: 1 Disable Disable Disable Open 2 Disable Disable Enable RTP-13B 3 (Spare Conf.) Disable Enable Disable RTP-13C 4 (Spare Conf.) Disable Enable Enable RTP-13D 5 (Spare Conf.) Enable Disable Disable RTP-13E 6 (Spare Conf.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-34: Program Pin Parity Inputs Pin Number (16) Pin Connector 1 RTP-6D 2 RTP-6F 3 RTP-6J 4 RTP-7A 5 RTP-7C 6 RTP-7D 7 RTP-7F 8 RTP-7G 9 RTP-6G 10 RTP-7J 11 RTP-11J 12 RTP-5K 13 RTP-7K 14 RTP-11A 15 RTP-11C 16 RTP-11F 17 RTP-11G 18 RTP-11H TCAS Bottom Antenna Deactivation and XPDR Top Antenna Deactivation. (See Table 4-35.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (18) Internal Transponder SDI The pins RTP-8C/8D define the SDI pin programming for the position of the internal transponder. Refer to Table 4-37. Table 4-37 Internal Transponder SDI Configuration Number Description: Internal Transponder No. 1 Not Applicable Open Open 2 1 Open RTP-15E 3 2 RTP-15E Open 4 3 RTP-15E RTP-15E C.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-44: Aircraft Altitude Limit Pin Description Connected to: RMP 6E 2000 ft (609.6 m) RMP 6F 4000 ft (1219.2 m) 1 = Connected to RMP – 6 K 0 = Open RMP 6G 8000 ft (2438.4 m) RMP 6H 16000 ft (4876.8 m) RMP 6J 32000 ft (9753.6 m) (26) This section defines the Display All Traffic Pin Programming.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (29) This section defines the Audio Level Select In-Air Pin Programming. Table 4-48: Audio Level Select In-Air RBP 7A RBP 7B RBP 7C Low level 2 output DBM MW 1= Open 0= Connected to RBP 7K (30) 1 1 1 16 40 1 1 0 13 20 1 0 1 10 10 1 0 0 7 5 0 1 1 4 2.5 0 1 0 1 1.25 0 0 1 -2 0.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (32) This section defines the RMP-5G Traffic Simulation Enable Pin Programming: Table 4-51: RMP 5G: Traffic Simulation Enable Configuration Number No Traffic In-Air when TCAS Unavailable Connect RMP-5G to: 1 Traffic Simulation Disable Open 2 Traffic Simulation Enable RBP-7K D.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 E. TAWS/RWS and Transponder Input Data Signals 3 The T CAS TAWS/RWS and Transponder functions require a minimum set of data that is needed to perform within the standard specifications (detailed in RTCA DO-161A [GPWS], TSO-C151 [TAWS], TSO-C117 [RWS], TSO-C112 [XPDR], DO-260 [MOPS ADS-B] and DO-181 [MOPS XPDR], refer to NOTE following this paragraph).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The minimum External Sensor input accuracy accepted is 68 feet per minute (20.726 meters per minute) when GPS is the source or 30 feet per minute (9.144 meters per minute) when IRS, ADIRS, AHRS or ADC (alternate Baro Altitude Rate variable) is the source. (a) Digital Input 3 T CAS accepts ARINC 429 Vertical Speed inputs from Inertial Systems, GPS Systems and Digital Air Data Systems (DADC).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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) 3 T CAS 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. TAWS, TCAS and RWS require the Radio altitude input.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 NOTE: The maximum radio altitude input currently used in TCAS is +37.5 V dc for a metric system. The common mode ranges allow for a ±2.5 V dc 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Alternate Horizontal Position Sources: Retaining TAWS functionality during GNSS outage or unavailability provides a safety benefit. It is acceptable and recommended to incorporate a secondary, non GNSS position source, to provide horizontal position when the GNSS is not available or reliable.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-55: Navigation Accuracy (10) Phase of Flight Accuracy Tolerance Approach 0.5 NMI Terminal 0.5 NMI Enroute FMS not in Degrade Oceanic FMS not in Degrade Static Air Temperature 3 The T CAS 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (14) Glideslope Deviation (Digital/Analog) 3 The T CAS 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. The minimum External Sensor input accuracies accepted for Glideslope Deviation are as follows: (15) ● 0.00455 for ddm < 0.0455 ● 10% for ddm < 0.175 ● Non-decreasing for ddm < 0.800.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 The T CAS 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 3 where T CAS is performing the RWS function.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The minimum External Sensor input accuracy accepted for AOA is 0.6 degrees with 95% confidence. (24) Body Axis Normal/Longitudinal Acceleration The Body Axis Normal/Longitudinal Acceleration input parameters are only used 3 on installations where T CAS is performing the RWS function.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-57: 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 3 The T CAS Display Range input parameter is updated from the EFIS Control Panel. The range selections are dependent on the type of Display installed.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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 backcourse 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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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (11) Altitude Callout Disable The Altitude Callout Disable Discrete input is used to disable all altitude callouts. NOTE: (12) Altitude callouts are not applicable for part numbers 9005000-10000, 10101, -10202, -10204, and -11203. 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 event.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 4-60: Transponder ARINC 429 Output Interface to OMS Label Number H. Data Name 275 Mode S Address Part 1 276 Mode S Address Part 2 350 XPDR Status 352 XPDR Discrete Input Status 353 XPDR P/P Status 354 LRU Identification (P/N - S/N) 356 OMS Normal Mode 377 XPDR Equipment Identification TAWS/RWS Discrete Output Data (1) Ground Discrete Parameters 3 This section describes the T CAS TAWS/RWS ground discrete outputs.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (c) Glideslope Cancel Indicator The Glideslope Cancel Indicator output discrete is activated when the 3 T CAS detects the Glideslope Cancel input discrete is active AND the aircraft is at a low altitude (below 2000 feet (609.6 meters) radio altitude). (d) TAWS Caution Alert Used to activate the TAWS Caution Alert lamp. (e) TAWS Warning Used to activate the TAWS Warning Alert lamp.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (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. 4-162 04 Nov 2014 34-45-29 Pub. No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 ADJUSTMENT/TEST 1. General The procedures that follow are designed to check for proper operation and satisfactory installation 3 of the T CAS Integrated Platform 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 5-2: Computer Unit Harness Checkout Connector Pin No. B. Pin Function 3 P1C-1 (LBP) 115 V ac (H) T CAS Power P1C-5 (LBP) 115 V ac (H) External Fan P1C-10 (LBP) 28 V dc T CAS Power 3 T3CAS 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. C.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 ● 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. Strobes the watchdog timer to keep the red X and status displayed. (4) NOTE: If the ACSS VSI/TRA displays error code 10, 11, 12, 29, 30, 31, or 40 an internal ACSS VSI/TRA failure has been detected. Figure 5-1: VSI/TRA Fault Warning Display 4. System Self-Tests A.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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 white (some displays may be red) TCAS TEST annunciation are displayed on the applicable display(s). Refer to Figure 1-17 for a typical test pattern display on the VSI/TRA.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 the OMS/CFDIU. 3 NOTE: The extended self-test is not applicable for T CAS part numbers 900500010000, -10101, -10202, -10204, or -11203. 3 One of the three types of diagnostic testing can be utilized on the T CAS to obtain status on the system, depending on the users purpose (status report vs. troubleshooting). First, the standard self-test results in a high-level pass/fail of the unit LRU and overall system status.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 ● “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 3 Selectable Options chosen during installation of the T CAS unit.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 ● The following aural annunciation will occur: “TERRAIN AWARENESS TEST COMPLETE” 3 If the TAWS standard test fails, execute the T CAS Computer Unit Self-Test procedures referenced in paragraph 4.C. to determine which subsystem is not functioning properly. Execute the Extended Test Mode in paragraph 4.B.(2) to determine which external LRU has failed. To troubleshoot the system, refer to the procedures in the FAULT ISOLATION section.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 5-2: Active Fault Annunciation 5-10 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 ● 3 When the extended TAWS self test mode becomes active the T CAS will aurally annunciate: “TERRAIN AWARENESS EXTENDED TEST START” NOTE: During extended test, the above aural annunciation will be performed in place of the standard self-test annunciations.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The maintenance report is initiated under the following conditions: ● The ACD entry for BITE_FAULT_AURALS is enabled and the TAWS flight deck self-test pushbutton/switch transitions from not initiated to initiated, and is held active for a period greater than 3 seconds. AND ● No other self-test operation (self-test, active fault annunciation, past fault annunciation, maintenance pages) is currently active.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 5-3: Past Fault Annunciation (Non-OMS System) Pub. No. 8600200-001, Revision 004 34-45-29 5-13 04 Nov 2014 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The maintenance pages are initiated under the following conditions: ● The aircraft is On Ground AND ● The TAWS flight deck self-test pushbutton/switch is activated (again) either during the standard self-test or within 5 seconds after the end of the standard self test complete annunciation (“TERRAIN AWARENESS TEST COMPLETE”). ● The TAWS flight deck self-test pushbutton/switch is activated for 3 or more seconds.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 5-4: Maintenance Pages Flow 5-16 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Upon activating the maintenance pages, the T CAS unit will display the maintenance introduction page on both the captain’s and first officer’s TAWS displays. While in the maintenance pages: 3 (a) The T CAS unit will display the next maintenance page when the TAWS flight deck self-test pushbutton/switch is active for less than or equal to 3 seconds.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 3 ● If the T CAS is operational, the T CAS P/F Status green annunciator comes on for a 10-second display period and then goes off. ● If the T CAS is not operational, one or more of the amber fault annunciators comes on for a 10-second display period.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (5) 5. If a fault is detected, refer to the Fault Isolation section for troubleshooting information. Return-to-Service Test 3 Any time a T CAS LRU or APM 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: 6.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 B. Compact Flash Card - Operational Software/ACD/ASDB Loading (While Installed on Aircraft) NOTE: All Aircraft Personality Modules (APMs) directly out of the ACSS factory are 3 blank. The error checking routine of the T CAS expects the ACD and ASDB to be loaded simultaneously from the same media. If this is not done, the CF Load Status LED will illuminate red after the first software load.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (a) The DATA STATUS LED will then blink green to indicate the unit is reading the CF card and verifying the files on the card, programming the files to memory, and finally performing a CRC on the programmed files. (b) The DATA STATUS LED will change from blinking to solid green when the load is complete and there were no errors.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 NOTE 1: When inserting compact flash cards, make sure that the part numbers on label are facing in the correct direction, as shown in Figure 5-5. Align the card with the slot and push in firmly. When removing, use finger to push the ejector at the top of the slot until the card pops out slightly on its own. After that, pull the card freely out of the slot.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 C. Updated Software Verification (1) Software Verification Using Flight Deck Systems ONLY (a) TCAS 3 Verify the updated software part number according to the T CAS TCAS extended-maintenance capabilities on status page code 0000 in the FAULT ISOLATION section of this manual or the individual AMM (refer to the onboard maintenance system program).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 1. Obtain a New or Blank Compact Flash (CF) card. 2. Copy to the New or Blank CF card the appropriate ‘Header File’ a) Header files are files copied to the New or Blank CF card that will instruct the computer unit what is desired to be downloaded. b) Header files needed to download Maintenance Data, Event Data and CRC Part Numbers can be obtained from ACSS Customer Services at +1-623-445-7070 or crc.acss@l-3com.com. 3.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3. Header files are files copied to the New or Blank CF card that will instruct the computer unit what is desired to be downloaded. 4. For Flight Data Recording, the aircraft does not need to be in an on-ground configuration. 5. Apply power to the computer unit. 6. Insert the CF card. a) The DATA STATUS LED will blink green once. This indicates the unit recognized that a CF card was inserted.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Blank Page Pub. No. 8600200-001, Revision 004 34-45-29 5-27 04 Nov 2014 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 FAULT ISOLATION 1. General 3 The T CAS Integrated Platform has three optional procedures for fault detection and isolation to the LRU level. The first option uses the aircraft OMS or central fault display system (CFDS) if the aircraft is equipped with an onboard maintenance system.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 NOTES: 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. 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 not have the option to allow entry into the maintenance pages. The maintenance report performs the same function as the extended self-test but also includes the aural annunciation of external BITE faults for the past five flight legs. In addition, the maintenance report will also automatically enter into the maintenance pages. The extended self-test and maintenance report should be used as a means of troubleshooting and diagnostic testing.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-1: TCAS Aural and VSI/TRA Annunciations VSI/TRA Annunciation Upper Left Upper Right Condition Aural Center 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-1: TCAS Aural and VSI/TRA Annunciations (cont) VSI/TRA Annunciation Condition ATCRBS Transponder Selected Aural Upper Left Upper Right None RA Only (TA Display Control to OFF) RA Fail RA FAIL Traffic Display Failure Center Color Notes TCAS OFF White TCAS is not operational RA ONLY White VSI/TRA displays resolution advisories only. Yellow No resolution advisories displayed.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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, 3.) TCAS Extended Test Mode (Test Switch Held at 7 Seconds for 2 Seconds and Aircraft on the Ground Only) System Informati on pages White Current status of the TCAS system transponder antennas, radio altimeters barometric altitude, etc.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-2: TAWS/RWS Display Aural State Indications and Conditions (cont) Display Color (Windshear systems, not applicable to part numbers 900500010000, -10101, -10202, -10204, or -11203) (Non-Windshear systems) (Multiple) Pub. No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-2: TAWS/RWS Display Aural State Indications and Conditions (cont) Display (Windshear systems, not applicable to part numbers 900500010000, -10101, -10202, -10204, or -11203) Maintenance Pages (0 to 15) Color (Multiple) (Multiple) Pub. No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 D. T3CAS 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. NOTE: Not all displays support this extended test mode.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-2: Typical System Status Page In the event of a detected system failure, one or more of the messages in Table 6-3 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 6-3: System Status Page Fault Messages Priority Message Description 1 SUPP FAULT GOTO 0010 Suppression bus failure.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (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 3 T CAS/Part No.9005000 ALT TAG (d) 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. 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 3 the T CAS.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 If the radio altimeter output is greater than 2,200 feet (670.56 meters) (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 3 T CAS/Part No.9005000 NOTES: 1. 2. (f) If the transponder detects either all 1’s or all 0’s, 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 CLIMB INH 0000 Climb Inhibit inputs: RMP-1J, RMP-13G, RBP-5J, RBP-5K.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-8: Typical Program Pins 3/4 Page 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. Figure 6-9: Typical Program Pins 4/4 Page Where more than one program pin is indicated, the listed connector pins correspond to the display digits read from left to right.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-10: 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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 flight crew has initiated the advisory, the intruder may not appear to change relative to the own aircraft symbol.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-12: Suppression Bus Clear Page (j) Antenna Port Status Page Selection of code 0011 displays the Antenna Port Status page, Figure 6-13. 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (k) Part Numbers Page 1 The Part Numbers page 1 includes the OP part numbers as well as the IO FPGA part number, RF FPGA part number, and Dataloader Application part number. See Figure 6-14. Figure 6-14: Part Numbers Page 1 (Code 0013) (l) Part Numbers Page 2 The Part Numbers page 2 includes the DL part numbers, as well as the ASDB part number, ACD part number and ACD CRC number. See Figure 6-15.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (m) ADS-B Test Menu Page (Code 2000) The ADS-B Test Menu Page displays a menu of ADS-B pages available while in the Extended Test mode. See Figure 6-16. Figure 6-16: ADS-B Test Menu Page (Code 2000) (n) ADS-B Self-Test Page (Code 0020) The ADS-B Self-Test page shows the GPS acquisition status as well as the pass/fail status of other systems that interface with the ADS-B. See Figure 6-17.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Failure are displayed if active or if the required input is unavailable. See Figure 6-18. Figure 6-18: ADS-B Fault Page 1 (Code 0030) (p) ADS-B Fault Page 2 (Code 0031) The ADS-B Fault page 2 displays ADS-B fault information, if available. Specifically the ADS-B Traffic Display Failure, the Transponder 1 Failure and the Transponder 2 Failure are displayed if active or if the required input is unavailable. See Figure 6-19.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-20: ADS-B Fault Page 3 (Code 0032) (r) ADS-B Fault Page 4 (Code 0033) The ADS-B Fault page 4 displays ADS-B fault information, if available. Specifically the Internal LRU Failure is displayed if active or if the required input is unavailable. See Figure 6-21.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-22: Unassigned 4096 Code Select Default Page (2) TAWS/RWS Test Menu and System Status Pages The Maintenance Pages provide maintenance information on the TAWS EFIS/Weather Radar display. Pages are indexed by pressing and holding the TAWS/RWS pushbutton/switch on the flight deck for 3 seconds or less.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (b) Table of Contents Page The Table of Contents page, shown in Figure 6-24, follows the Instruction page and provides the user with a page breakdown of the remaining Maintenance Pages.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-27 shows Part Number Page 3, which displays the LRU Part Number and Software Modification Version Number separated by a “/ ”. 3 The entire T CAS LRU Part number is of the form XXXXXXX-YYTZZ where: ● XXXXXXX is the unique 7 digit base part number. ● YY represents the unique hardware and BOOT SW configuration (not externally loaded). ● T represents the unique TCAS OPS SW.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-29: Part Number (Page 6/25) Figure 6-30: Part Number (Page 7/25) Figure 6-31: Part Number (Page 8/25) Part Number Page 8 (Figure 6-32) shows the APM ACD Part Number if applicable (up to 16 characters). Part Number Page 9 (Figure 6-33) contains APM ASDB Part Number if applicable (up to 16 characters). 6-36 04 Nov 2014 34-45-29 Pub. No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-32: Part Number (Page 9/25) Figure 6-33: Part Number (Page 10/25) (d) System Test Page 3 The T CAS Maintenance System Test Page (Figure 6-34) follows the Part Numbers pages. The System Test Page will display the Pass/Fail status of the most recently run Standard Self-Test.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 The T CAS Maintenance System Test Page displays “LRU FAIL” (FAIL displayed in red) on row 3 if the “Terrain Awareness System Fail” aural has been annunciated and the “Terrain Awareness LRU Pass” aural has not been annunciated. NOTE: There is no LRU fail aural annunciation. However, the absence of an “LRU PASS” aural annunciation along with a “Terrain Awareness System Fail” aural annunciation indicates that the 3 T CAS LRU has failed.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 NOTE: The MSB is the left most bit in the Hex value (MSB .. LSB).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-5: ACD Callout Options (cont) Callout Option ACD Callout Option Bit Option 500 ft (152.4 m) Callout Enable Flag Hex Char 3 (MSB), bit 4 1 = 500 ft (152.4 m) Callout Enabled, 0 = 500 ft (152.4 m) Callout Disabled 500 ft (152.4 m) (Tone) Callout Enable Flag Hex Char 3 (MSB), bit 3 1 = 500 ft (152.4 m) (Tone) Callout Enabled, 0 = 500 ft (152.4 m) (Tone) Callout Disabled 400 ft (121.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-5: ACD Discrete Options (cont) ACD Discrete Option ACD Discrete Option Bit Option ACD Discrete Option Bit Setting Mode 6 Volume Level Disable System Test Callouts Hex Char 7, bit 2 1 = Cause System Test Callouts to be annunciated at the High-Impedance or Low-Impedance Normal Volume Levels. 0 = Cause System Test Callouts indicated to be annunciated at the Mode 6 Volume Level.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-6: ACD Boolean Options (cont) ACD Discrete Option Modified Eleview Logic Enable ACD Boolean Option Bit Position Hex Char 2, bit 1 ACD Selectable Option 1 = Selects between flat terrain coloration logic of all black vs all light-density green at terrain spreads less than or equal to 110 ft (33.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-8: Table of Enumerated Configuration Option ACD Discrete Option ACD Enumerated Option Bit Position ACD Selectable Option Bank Angle Repetition Hex Char 1 1, 2, 3, 4, F (infinity) – Bank Angle warning will repeat based on the input number.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-8: Table of ACD Enumerated Values (cont) ACD Enumerated Option Bit Position ACD Discrete Option ACD Selectable Option OCPA Mode A Warning Hex Char 4 1 = “OBSTACLE AHEAD PULL-UP“ 2 = “OBSTACLE OBSTACLE PULLUP PULL-UP” 3 = “~~PULL UP” “~~” Designates a pair of constantly varying tones from 400 to 800 Hz. The tones are 0.3 sec each, separated by 0.1 sec and followed by 0.1 sec of silence.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The Maintenance ACD Options Page 18/25 displays the ACD Mode 6 Volume Level Options as shown in Figure 6-42. The correlations table for the displayed volume level values is shown in Table 6-9. In the example shown in Figure 6-42, the volume levels are set to a middle level value of 128.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 If set to 0, GCAM will disable Mode 2 when CPA is active. Figure 6-45: ACD Option Page (Page 21/25) – Mode 2 Activation Vertical Offset The Maintenance ACD Options Page 22/25 displays the ACD Narrow TAL Roll Limit Options, as shown in Figure 6-46. This ACD option sets the roll angle at which the sensor begins to draw TAL in the direction of the turn.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Figure 6-48: ACD Option Page (Page 24/25) – Display Alert Line Aperture The Maintenance ACD Options Page 25/25 displays the ACD Runway Location Error Options, as shown in Figure 6-49. This value plus 100 meters (328.084 feet) or 0.05 nautical miles represents the runway location error used for the landing tunnel half-width computation in the CPA logic (unit Nm), when navigation accuracy is high (accurate).
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-11: 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 internal memory. These faults can be displayed on its front panel annunciator for (up to) the last 10 flight legs. Data can be recalled by doing the commanded self-test on the ground.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 6-10: Computer Unit Self-Test Execution (cont) Test Sequence Commanded Self-Test Pub. No. 8600200-001, Revision 004 Activation Test Indications Push the PUSH-TOTEST button again before the previous 11sec display period has elapsed ● Previous fault display is aborted. 3 ● All T CAS lamps come on during a 1-sec lamp test. 3 ● All front T CAS LEDs will be lit for 1 sec (±0.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 3 Table 6-12: T CAS Fault Reporting and Corrective Actions Status Annunciator Failure Possible Corrective Action The T CAS function passes its own internal BITE test 3 T CAS function is operational. If other annunciators are on, the problem is in the indicated subsystem or aircraft wiring. 3 Replace the T CAS computer unit.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (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 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 G. Hybrid Surveillance Test / Fault Isolation Procedure 3 The installer of the T CAS unit with hybrid surveillance (Part No. 9005000-11801 and 55801) should be aware of the requirement (TSO-C119d and AC 20-151B) to either have a failure annunciation on the flight deck indicating to the pilot when hybrid surveillance functionality has failed or perform a scheduled maintenance task to verify that the function is (and has been) functional.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Page Break 6-60 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 MAINTENANCE PRACTICES 1. General This section provides instructions for removing, reinstalling, and adjusting each LRU of the 3 T CAS 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. 2.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (b) Slide the computer unit into its mounting tray. CAUTION: B. DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE COMPUTER UNIT AND EXAMINE THE CONNECTOR FOR CONTACTS THAT ARE BENT OR OUT OF ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THE CONNECTORS’ POLARIZATION KEYS AND POSTS. (c) Carefully apply firm pressure until the computer connector mates with the tray connector receptacle.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 4. Procedure for the APM (Not applicable for part numbers 9005000-10000, -10101, 10202, -10204, or -11203) A. Removal and Installation Procedure (1) (2) Remove the APM If the APM is attached to the T CAS mounting tray, remove the screws 3 that attach the APM to the T CAS 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (2) (b) Remove four or eight (quantity depends on dash number of antenna) non-Torx drive screws used to attach antenna to fuselage. See Figure 28 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 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 (Applicable to part numbers 900500011203, -11801 and -55801) A. Removal and Installation Procedure (1) (2) B. Remove the Omnidirectional Antenna. (a) If applicable, use a phenolic scraper to remove aerodynamic sealant around periphery of antenna baseplate.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 D. Return-to-Service Procedures Do the Return-to-Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. 7. Procedure for the Control Panel A. Removal and Installation Procedure (1) (2) B. 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 8. 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: (2) B. Most installation clamps require the top screws be loosened to remove the instrument. Other clamps require the diagonal screws be loosened. Refer to the AMM for specific application.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 9. Instructions for Continued Airworthiness, FAR Part 25.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 diagrams and Section 3 – ELECTRICAL INSTALLATION for tray mating connector and connector contact definition. E. T3CAS Components 3 The T CAS components are considered on-condition units and no additional maintenance is required other than a check for security and operation at normal inspection intervals. F.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 CFR Secs. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternate program has been FAA approved.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 INSPECTION/CHECK 1. General 3 The visual check procedures that follow are recommended for the T CAS Integrated Platform components after they have been installed in the aircraft. 2. Equipment and Materials None 3. Procedure CAUTION: A. B. C. BEFORE YOU DO ANY OF THE PROCEDURES THAT FOLLOW, MAKE SURE ALL T3CAS SYSTEM CIRCUIT BREAKERS ARE PULLED.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 D. 8-2 04 Nov 2014 Check VSI/TRA Display (1) Visually examine all external surfaces for possible damage. Check dust cover and external connector including Pressure Boss (if applicable) for dust or damage. (2) Check that the display is securely mounted (locking mechanism is properly engaged). (3) Check that the LCD glass is not scratched or cracked. 34-45-29 Pub. No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 CLEANING/PAINTING 1. General 3 While the T CAS Integrated Platform 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Table 9-1: Equipment and Materials (cont) Name AMN 9460078 Description Source Primer, coating, epoxy, low VOC (MIL-P-23377, Type I, Class 2) Optional source NOTES: 3. 1. Equivalent alternatives are permitted for equipment and materials in this list. 2. The AMN codes in the list of materials identify the ACSS Material Number (AMN) given to each material. Cleaning CAUTION: A. B.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 4. Painting A. TCAS Directional Antennas (1) Scope This procedure covers the removal and re-application 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: (a) SOLVENTS AND COATINGS ARE COMBUSTIBLE.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 (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 1 Mix paint in a base (coating) to catalyst ratio of 6:1 under slow agitation. NOTE: 2 3 (h) 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.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 REPAIRS 1. General 3 Major repairs to the T CAS 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 CMMs given in Table 10-1. Table 10-1: LRU Maintenance Manual ACSS Component Maintenance Manual (CMM) ATA Number 8007552-001 34-09-01 Control Panel Part No.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Blank Page 10-2 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 APPENDIX A Pub. No. 8600200-001, Revision 004 34-45-29 A-1 04 Nov 2014 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Blank Page A-2 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 T3CAS™ Aircraft Configuration Work Sheet Pub. No. 8600200-001, Revision 004 34-45-29 A-3 04 Nov 2014 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 A-4 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Pub. No. 8600200-001, Revision 004 34-45-29 A-5 04 Nov 2014 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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SYSTEM DESCRIPTION AND INSTALLATION MANUAL 3 T CAS/Part No.9005000 Blank Page A-6 04 Nov 2014 34-45-29 Pub. No. 8600200-001, Revision 004 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.