(3)
Data will be provided by the center ADC when it is used as an alternate source for either the left or right ADC.
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(4)
Selection of the air data input source for the left IRU is controlled by the captain's air data source select switch. Selection of the air data input for the right IRU is controlled by the first officer's air data source select switch. Selection of the air data input for the center IRU is controlled by the first officer's IRS source select switch. The vertical speed displayed on the PFDs is baro-inertial vertical speed data derived by the inertial reference system. The switching arrangement ensures that vertical speed data is provided from two independent sources when one IRU is inoperative.
Ground Proximity Warning System (Ref 34-46-00)
(1)
The ground proximity warning computer of the ground proximity warning system interfaces with the the air data system.
(2)
The ground proximity system receives digital data from the left ADC on data bus No. 4.
(3)
Data will be provided by the center ADC when it is used as an
alternate source for the left ADC.ATC System (Ref 34-53-00)
(1)
Components of the ATC system that interface with the air data system are the:
(a)
Left ATC transponder
(b)
Right ATC transponder
(2)
The ATC system receives digital data from the left and right ADCs on data bus No. 4.
(3)
Data will be provided by the center ADC when it is used as an
alternate source for the left and right ADCs.Flight Management Computer System (Ref 34-61-00)
(1)
Components of the flight management computer system that interface with the air data system are the:
(a)
Left flight management computer (L-FMC)
(b)
Right flight management computer (R-FMC)
(2)
The flight management computer system receives digital data from the left and right ADCs on data bus No. 1 and data bus No. 4. The left ADC serves as the primary source for the left FMC and the alternate source for the right FMC. The right ADC serves as the primary source for the right FMC and the alternate source for the left FMC.
(3)
Data will be provided by the center ADC when it is used as an alternate source for either the left or right ADC.
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O. Central Maintenance Computer System (AMM 45-10-00/001)
(1) The central maintenance computer of the central maintenance computer system interfaces with the air data system. The CMC/ADC interface is armed by placing the ground test enable switch located on the overhead maintenance panel P461 or the remote test enable switch located on the station 400 bulkhead in the main equipment center to ENABLE. The air/ground logic which enables the ADC functional test mode, when the airplane is on the ground, is interlocked through the CMC enable relays. The CMC provides the ground to the ADC to activate the ADC functional test mode. An EICAS status message will be present on the secondary EICAS display when ground test or remote test is enabled. The EICAS status message displayed is GRD TEST ENABLE.
P. Fuel Control System (Ref 73-21-00)
(1)
Components of the fuel control system that interface with the air data system are the:
(a)
No. 1 engine electronic engine control (EEC)
(b)
No. 2 engine electronic engine control (EEC)
(c)
No. 3 engine electronic engine control (EEC)
(d)
No. 4 engine electronic engine control (EEC)
(2)
The fuel control system receives digital data from the left and right ADCs on data bus No. 3.
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