ADIRS/PHC Interface
Figure 003
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the heating element of the L and R static probes 3 receives 28VDC from the 28VDC BUS 1 103PP
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the heating element of the pitot probe 3 receives 115VAC from the
115VAC BUS 1 103XP. In normal configuration of the aircraft electrical generation, the distribution described before is independent of the switching selector switches.
C. ADIRS Power Supply Distribution after Loss of Main Electrical Generation
(1)
Loss of the main generation and ATT HDG selector switch in NORM position
(a)
Captain side The ADIRU 1 is supplied as in normal configuration. (Ref.Para B.(1)).
(b)
First Officer side The ADIRU 2 is no more supplied with 115VAC and 26VAC. When the 26VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28VDC from the 28VDC HOT BUS 702PP but the Time Delay Opening (TDO) relay 17FP will cut this supply after 5 minutes in emergency configuration. The ADR 2 function is lost immediately. The IR 2 function is lost after 5 minutes.
(c)
Standby side The ADIRU 3 is no more supplied with 115VAC and 26VAC. When the 26VAC is lost, the ADR detects a fault and flags the output parameters. The ADIRU is still powered with 28VDC from the 28VDC HOT BUS 701PP but the Time Delay Opening (TDO) relay 14FP will cut this supply after 5 minutes in emergency configuration. The ADR3 function is lost immediately. The IR 3 function is lost after 5 minutes.
(2)
Loss of the main generation and ATT HDG selector switch in CAPT/3 position The CAPT/3 position of the ATT HDG selector switch corresponds to the selection of the ADR 3 in place of the ADR 1. The power supply distribution must then be modified to keep the ADR 3 in emergency configuration.
(a) Captain side
The ADIRU 1 is supplied as in normal configuration
(Ref. Para. B.(1)).
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(b)
First Officer side ADIRU 2 supply: Ref. Para. (1)(b).
(c)
Standby side The ADIRU 3 is no more supplied with 115VAC. The ADIRU 3 is still powered with 28VDC from the 28VDC HOT BUS 701PP. The ADR 3 function is lost immediately. The IR 3 function is available.
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D. Circuit Breakers
The system is supplied through these circuit breakers:
-----------------------------------------------------------------------------FIN PANEL/ DESIGNATION BUS ATA. REF. AMM LOCATION P. BLOCK 001
-----------------------------------------------------------------------------4FP1 49VU NAV AND PROBES/ADIRU1/115VAC 801XP-A 34-11-00 4FP2 121VU ADIRS/ADIRU/2/115VAC 204XP-C 34-11-00 4FP3 121VU ADIRS/ADIRU/3/115VAC 101XP-C 34-11-00 5FP1 49VU NAV AND PROBES/ADIRU1 & 431XP-A 34-11-00 AOA/26VAC 5FP2 121VU ADIRS/ADIRU/2/26VAC AND AOA 231XP-A 34-11-00 5FP3 121VU ADIRS/ADIRU/3/26VAC AND AOA 131XP-A 34-11-00 6FP1 105VU ADIRS/ADIRU1/28VDC 704PP 34-11-00 6FP2 121VU ADIRS/ADIRU/2/28VDC 702PP 34-11-00 6FP3 121VU ADIRS/ADIRU/3/28VDC 701PP 34-11-00 8FP 49VU NAV AND PROBES/ADIRU 3/ 401PP 34-11-00 SWTG/SPLY 9FP 121VU ADIRS/ADIRU/3 SWTG/SPLY 301PP 34-11-00
10FP 121VU ADIRS/ADIRU/2 PWR/SHED 206PP 34-11-00 1DA1 122VU ANTI ICE/PROBES/1/TAT 101XP-A 30-31-00 1DA2 122VU ANTI ICE/PROBES/2/TAT 202XP-C 30-31-00 2DA1 49VU ANTI ICE/PROBES/PHC/1 401PP 30-31-00 2DA2 122VU ANTI ICE/PROBES/2/PHC 206PP 30-31-00 2DA3 122VU ANTI ICE/PROBES/PHC/3 101PP 30-31-00 3DA1 49VU ANTI ICE/PROBES/PITOT/1 401XP-B 30-31-00 3DA2 122VU ANTI ICE/PROBES/2/PITOT 202XP-B 30-31-00 3DA3 122VU ANTI ICE/PROBES/3/PITOT 103XP-C 30-31-00 4DA1 49VU ANTI ICE/PROBES/1/AOA 801XP-C 30-31-00 4DA2 122VU ANTI ICE/PROBES/2/AOA 202XP-B 30-31-00 4DA3 122VU ANTI ICE/PROBES/3/AOA 103XP-C 30-31-00 5DA1 122VU ANTI ICE/PROBES/1/STATIC 101PP 30-31-00 5DA2 122VU ANTI ICE/PROBES/2/STATIC 206PP 30-31-00 5DA3 122VU ANTI ICE/PROBES/3/STATIC 103PP 34-11-00
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4. Component Description
_____________________
A. Static Probes (Ref. Fig. 004) Each of the three systems (CAPT (1), F/O (2), STBY (3)) comprises two static probes which are linked to each ADR portion of the ADIRUs through five ADMs. The probe is protected from icing with a 28VDC heater circuit. The static probes linked to ADIRU 1 and ADIRU 2 are set at 48.64 deg. below the fuselage datum line (Z=0). The static probes linked to ADIRU 3 are set at 29.5 deg. below the fuselage datum line.
B. Pitot Probes (Ref. Fig. 005) Each system comprises one pitot probe (CAPT (1), F/O (2), STBY (3)) which is linked to each ADR portion of the ADIRUs through one ADM. The probe is protected from icing with a 115VAC - 400 Hz heater circuit.
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