P180 Avanti-air Data System
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PILOT’S OPERATING HANDBOOK
P.180 AVANTI II
DESCRIPTION AND OPERATION
AIR DATA SYSTEM
2.26. AIR DATA SYSTEM GENERAL The Air Data System is a dual (pilot‘s and copilot’s side) ADS-3000 system. Two Air Data Computers (ADC) are installed in the nose avionics bay. Each ADC receives data from the Pitot/Static System, the Total Air Temperature (TAT) probe, installed on the lower left side of the front fuselage, and the Angle of Attack (AOA) probe. Each ADC has also embedded pre-programmed airplane data on SSEC (Static Source Error Correction) and maximum allowable airspeed (VMO/MMO). The pilot’s and co-pilot’s side ADC and associated sensors are functionally isolated and each side acts as a self-contained, stand-alone system. Inputs to each ADC include operator/display inputs from the on-side Display Control Panel (DCP), reference inputs from the Integrated Avionics Processor System (IAPS) and alternate air data from the cross-side ADC. The ADCs supply processed air data to the Flight Guidance System (FGS), Attitude Heading Reference System (AHRS), Electronic Flight Instrument System (EFIS), Integrated Avionics Processor System (IAPS) and navigation equipment. The ADC processes the raw data, then sends digital air data to the Primary Flight Display (PFD) and other aircraft subsystems that use air data inputs, via the IAPS and system bus structure. A redundant system bus supplies the digital air data directly to the PFD and MFD. Processed air data provided by the ADC include: – uncorrected pressure altitude, – baro corrected altitude, – vertical speed (VS), – airspeed (IAS/CAS), – IAS trend, Mach, – VMO/MMO, – – – –
true airspeed (TAS), total air temperature (TAT), static air temperature (SAT) International Standard Atmosphere (ISA) delta temperature.
Issued: May 22, 2006 Rev. A0
Rep. 180-MAN-0030-01102 Page 2.26-1
P.180 AVANTI II
PILOT’S OPERATING HANDBOOK
DESCRIPTION AND OPERATION A R DATA SYSTEM
The Primary ADS is powered by the Essential Avionics Bus through the “ADC 1” 3-ampere circuit breaker and by the DC-DC Converter 1 CH1 through the “ADC1 BACKUP” 3-ampere circuit breaker located on the copilot’s C/B panel. The Secondary ADS is powered by the Right Avionics Dual Feed Bus through the “ADC 2” 3-ampere circuit breaker located on the copilot’s C/B panel. The electrical power for TAT probe heating is delivered from the Left Dual Feed Bus through the TAT HEATER 15-ampere circuit breaker, on the pilot’s C/B panel, and controlled by the PITOT/STATIC HR R&TAT switch on the ANTI-ICE control panel.
Figure 2.26-1. Air Data System block diagram Rep. 180-MAN-0030-01102 Page 2.26-2
Issued: May 22, 2006 Rev. A0
PILOT’S OPERATING HANDBOOK
P.180 AVANTI II
DESCRIPTION AND OPERATION
AIR DATA SYSTEM
OPERATIONS Speed and altitude references are controlled by the pilot’s and copilot’s side Display Control Panels and PFDs line select keys. When a DCP function switch is pushed, the PFD shows the appropriate menu. While the menu is in view, the line select keys are active. A rocker switch ADC1/ADC2, installed on the REVERSIONARY/MISCELLANEOUS Panel, is used to select Air Data Computer reversion. ADC reversion allows either pilot and copilot to select an alternate source of air data in case of an onside air data failure. Upon selection of ADC reversion, on-side ADC data is replaced by the cross-side ADC data which becomes the common air data source. ADC reversion is allowed on one side only. Refer to Collins “Pro Line 21 Avionics System Operator’s Guide, for the Piaggio P.180 Avanti”, doc. n. 523-0806484, for details about ADS operations.
Issued: May 22, 2006 Rev. A0
Rep. 180-MAN-0030-01102 Page 2.26-3
P.180 AVANTI II
DESCRIPTION AND OPERATION
AIR DATA SYSTEM
2.26. AIR DATA SYSTEM GENERAL The Air Data System is a dual (pilot‘s and copilot’s side) ADS-3000 system. Two Air Data Computers (ADC) are installed in the nose avionics bay. Each ADC receives data from the Pitot/Static System, the Total Air Temperature (TAT) probe, installed on the lower left side of the front fuselage, and the Angle of Attack (AOA) probe. Each ADC has also embedded pre-programmed airplane data on SSEC (Static Source Error Correction) and maximum allowable airspeed (VMO/MMO). The pilot’s and co-pilot’s side ADC and associated sensors are functionally isolated and each side acts as a self-contained, stand-alone system. Inputs to each ADC include operator/display inputs from the on-side Display Control Panel (DCP), reference inputs from the Integrated Avionics Processor System (IAPS) and alternate air data from the cross-side ADC. The ADCs supply processed air data to the Flight Guidance System (FGS), Attitude Heading Reference System (AHRS), Electronic Flight Instrument System (EFIS), Integrated Avionics Processor System (IAPS) and navigation equipment. The ADC processes the raw data, then sends digital air data to the Primary Flight Display (PFD) and other aircraft subsystems that use air data inputs, via the IAPS and system bus structure. A redundant system bus supplies the digital air data directly to the PFD and MFD. Processed air data provided by the ADC include: – uncorrected pressure altitude, – baro corrected altitude, – vertical speed (VS), – airspeed (IAS/CAS), – IAS trend, Mach, – VMO/MMO, – – – –
true airspeed (TAS), total air temperature (TAT), static air temperature (SAT) International Standard Atmosphere (ISA) delta temperature.
Issued: May 22, 2006 Rev. A0
Rep. 180-MAN-0030-01102 Page 2.26-1
P.180 AVANTI II
PILOT’S OPERATING HANDBOOK
DESCRIPTION AND OPERATION A R DATA SYSTEM
The Primary ADS is powered by the Essential Avionics Bus through the “ADC 1” 3-ampere circuit breaker and by the DC-DC Converter 1 CH1 through the “ADC1 BACKUP” 3-ampere circuit breaker located on the copilot’s C/B panel. The Secondary ADS is powered by the Right Avionics Dual Feed Bus through the “ADC 2” 3-ampere circuit breaker located on the copilot’s C/B panel. The electrical power for TAT probe heating is delivered from the Left Dual Feed Bus through the TAT HEATER 15-ampere circuit breaker, on the pilot’s C/B panel, and controlled by the PITOT/STATIC HR R&TAT switch on the ANTI-ICE control panel.
Figure 2.26-1. Air Data System block diagram Rep. 180-MAN-0030-01102 Page 2.26-2
Issued: May 22, 2006 Rev. A0
PILOT’S OPERATING HANDBOOK
P.180 AVANTI II
DESCRIPTION AND OPERATION
AIR DATA SYSTEM
OPERATIONS Speed and altitude references are controlled by the pilot’s and copilot’s side Display Control Panels and PFDs line select keys. When a DCP function switch is pushed, the PFD shows the appropriate menu. While the menu is in view, the line select keys are active. A rocker switch ADC1/ADC2, installed on the REVERSIONARY/MISCELLANEOUS Panel, is used to select Air Data Computer reversion. ADC reversion allows either pilot and copilot to select an alternate source of air data in case of an onside air data failure. Upon selection of ADC reversion, on-side ADC data is replaced by the cross-side ADC data which becomes the common air data source. ADC reversion is allowed on one side only. Refer to Collins “Pro Line 21 Avionics System Operator’s Guide, for the Piaggio P.180 Avanti”, doc. n. 523-0806484, for details about ADS operations.
Issued: May 22, 2006 Rev. A0
Rep. 180-MAN-0030-01102 Page 2.26-3
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