Aircraft Instrument Panel

ISIS (Integrated Standby Instrument System)

• Location: main instrument panel
• Functions: air data indications, standby navigation system
• Computes and transmits air data and inertial reference
• Connected to static/pitot probe

Standby Compass

• Location: overhead panel, top of windshield center post
• Provides standby navigation system

GADIRU (Global Air Data and Inertial Reference Unit)

• Location: avionics bay
• Functions: air data and inertial reference
• Computes and provides air data and inertial reference
• Receives and processes GPS data, accelerations, and angular rates
• Normal power supply: 115VAC, backup power supply: 28VDC

ARINC 429

• Connection protocol used for air data probes, except OAT
• Used for GPS data transmission

OAT (Outside Air Temperature)

• OAT1 connected to GADIRU 1/2
• OAT2 connected to GADIRU 3
• Provides outside air temperature data

Radio Navigation System

• Tuning and displays: auto FMS, manual FMS, CDS, RMP (Radio Management Panel)
• RMP used as gateway for FMS
• Radio navigation system uses VOR (VHF Omnidirectional Range) and TACAN (Tactical Air Navigation) signals

VOR (VHF Omnidirectional Range)

• Provides azimuth orientation to a VOR ground station
• Receives and decodes bearing information from VOR signals
• Provides magnetic bearing, selected course, and deviation
• Installed with marker functions: IM (Inner Marker), MM (Middle Marker), OM (Outer Marker)

TACAN (Tactical Air Navigation)

• Provides bearing and distance information
• Uses ground stations to compute deviations
• Has no dedicated hardware controls, except for audio identifier

Radio Altimeter (RA)

• Provides RA height data to CDS and HUDS through ADCN (Air Data Computer)
• Two RA transceivers, each with one transmitting and one receiving antenna
• Power supply: 115VAC, emergency power supply available

MMR (Multi-Mode Receiver)

• Functions: ILS (Instrument Landing System), GPS (Global Positioning System), and MLS (Microwave Landing System)
• Power supply: 115VAC
• Location: lower deck avionics bay (MMR1) and main avionics bay (MMR2)
• GPS antenna and MLS omni-directional antenna installed on the aircraft

TCAS (Traffic Collision Avoidance System)

• Part of the ISS (Integrated Surveillance System)
• Provides air traffic surveillance and collision avoidance
• Two ISU (Integrated Surveillance Unit) components

Weather Radar (WXR)

• Part of the ISS
• Provides weather radar function
• Uses ISU as gateway

Military Functions

• MMRP (Multi-Mode Radar Receiver) component
• Military radar control panel
• ISU component
• Radar antenna assembly
• Power supply: 115VAC
• Location: 1100VU
• Provides high-resolution ground map image display and air-to-air functionality

Power Supplies

• No emergency power supply:
  • Transceiver 1: 1100VU
  • Transceiver 2: 1800VU
  • Antenna 1 and 3 on top, antenna 2 and 4 on bottom
• Emergency power supply:
  • RA transceiver 1 on left side and RA transceiver 2 on right side
  • Antennas in bottom area

TACAN and Radio Altimeter

• TACAN:
  • No dedicated hardware controls except for audio identifier in ACP
  • Indications: TACAN 1 lower left, TACAN 2 lower right
• Radio Altimeter:
  • 2 RA transceivers (1 transmitting and 1 receiving antenna per receiver)
  • 4 antennas
  • Provides height data to CDS and HUDS through ADCN (IOM)
  • Data sent through direct link to FWS and AFS

RA Interface and Controls

• RA interface with ICPs:
  • Engine master lever
  • EMCOM and DASS silencing
  • RA override switch
• RA override switch:
  • 2 positions: ON (works normally) and OFF (inhibited emissions according to EMCOM/DASS silencing command)
• Military functions:
  • Power management: increase aircraft discretion regarding RF emissions
  • Jamming detection

ISS, TCAS, TAWS, and WXR

• ISS:
  • TCAS
  • TAWS
  • WXR
• Main components:
  • 2 ISU
  • WXR antenna
  • 2 TCAS antennas
  • WXR control panel
• Power supply:
  • ISU 1 and 2: 1000VU
• Modes:
  • Normal mode: all functions delivered by ISU 1 (master)
  • Mixed mode: if 1 function is lost, functions shared between ISU 1 and ISU 2
  • Downgraded mode: TCAS failure or at least 2 faults in the system

Weather Radar and TAWS

• Weather Radar:
  • Single configuration: RTU 2 is a dummy RTU, enables stowage plugs from antenna drive unit and ISU
• TAWS:
  • GPWS mode 5 active less than 1000 ft AGL and L/G down

Military Radar and EVS

• Military Radar:
  • Components: MMRP, Military radar control panel, ISU 1, and Radar antenna assembly
  • Power supply: MMRP - 1100VU
• EVS:
  • Interconnection with other systems ensured by both HUDC
  • Detailed description:
    • External interfaces
    • Image automatic adjustment is continuously performed by EVS based on alignment parameter stored in HUD PMM
    • Data link with HUDC
  • Indications:
    • EVS FAULT: cannot provide video signal
    • EVS OVERHEAT: automatically removed when inner temperature returns to normal
    • EVS DEGRADED: misalignment corresponds to a lack of HUD alignment value and not to a physical misalignment of the sensor due to an external impact

VOR/DME/MMR/ADF and ISIS

• VOR/DME/MMR/ADF:
  • Location: ISIS on main instrument panel
  • Standby compass: on overhead panel, on top of windshield center post
  • Standby static: left and right
  • Standby pitot: right
• ISIS:
  • Units: GADIRU 1 and 3 using ARINC 429
  • ISIS unit:
    • Air data indications:
      • Mach number visible above 0.5 and disappears below 0.45
    • Maintenance menu:
      • Maintenance Pages to display failures and ISIS configuration
      • Air Data Testing enables access to air data testing function

Radio Navigation System

• Tuning and displays:
  • 2 tuning: automatic and manual
  • Radio navigation system components:
    • RMP 1 and 2
    • FMS
    • CDS
    • RMPs (kccu)
• RMP used as gateway for FMS

MMR and GPS

• MMR:
  • 2 functions:
    • Landing system (ILS MLS) uses ground stations which emit signals to compute deviations
    • Civil GPS (FMS) based on measures between A/C and satellites
  • Power supply: 115VAC
  • Location: MMR 1 - lower deck avionics bay, MMR 2 - main avionics bays
• GPS:
  • Components: GADIRU 1, 2, and 3
  • Normal power supply: 4 main parts GADIRU
  • Architecture: Hybrid = Mil/Civ GPS + IR

ADR and IR

• ADR:
  • Computes and provides air data and inertial reference
  • Architecture: Hybrid = Mil/Civ GPS + IR
• IR:
  • Measures accelerations: GPS and time
  • Part of hybrid system with GPS
  • Usescivil GPS (FRPA) and military GPS (CRPA) signals
  • Can switch automatically from FRPA to CRPA in case of jamming

Power Supply

• SEPDC 1 supplies TACAN 1
• SEPDC 2 supplies TACAN 2
• Transceiver 1 located at 1100VU, Transceiver 2 located at 1800VU
• Antenna 1 and 3 on top, antenna 2 and 4 on bottom

TACAN

• Does not have dedicated hardware controls except for audio identifier control in ACP
• Indicators: TACAN 1 lower left, TACAN 2 lower right
• 2 RA transceivers, 4 antennas
• RA height data sent to CDS and HUDS through ADCN (IOM) and FWS and AFS via direct link

Radio Altimeter

• 2 RA transceivers, 1 transmitting and 1 receiving antenna per receiver
• RA height provided to CDS and HUDS through ADCN (IOM) and FWS and AFS via direct link
• Power supply: EEPDC supplies RA transceiver 1, SEPDC 2 supplies RA transceiver 2
• RA transceiver 1 located on left side, RA transceiver 2 located on right side, antennas at bottom

ISS

• Components: 2 ISU, WXR antenna, 2 TCAS antennas, WXR control panel
• Power supply: PSM's ISU 1 supplied by SEPDC 1, WXR antenna supplied by PSM at 200 VDC
• Location: ISU 1 and 2 situated at 1000VU
• Normal mode: all functions delivered by ISU 1 (master), Mixed mode: if 1 function is lost, functions shared by ISU 2 master
• Downgraded mode: TCAS failure or at least 2 faults, ISU selected for WXR function is master

Weather Radar

• In single configuration, RTU 2 is a dummy RTU that enables stowage plugs from antenna drive unit and ISU

TAWS

• GPWS mode 5 active less than 1000 ft AGL and L/G down

Military Radar

• Components: MMRP, Military radar control panel, ISU 1, Radar antenna assembly
• Power supply: Military function = high-resolution ground map image display NTD, Air-to-air function
• Location: MMRP located at 1100VU
• Data interface with A/C systems performed through Ethernet using ISU as gateway

EVS

• Interconnection with other systems ensured by HUDC
• Image automatic adjustment continuously performed by EVS based on alignment parameter stored in HUD PMM
• External interfaces: data link with HUDC used
• Controls and indications: EVS FAULT, EVS OVERHEAT, EVS DEGRADED

ISIS

• Location: main instrument panel
• Standby compass on overhead panel, standby static on left and right, standby pitot on right
• GADIRU 1&3 using ARINC 429 > ISIS
• ISIS unit: detailed controls and indications
• Air data indications: Mach number visible above 0.5 and disappears below 0.45
• Maintenance menu: Maintenance Pages to display failures and ISIS configuration

Radio Navigation System

• 2 tuning: auto FMS/manual FMS CDS RMP
• RMP 3 not used for navigation
• In case of double FMC failure in manual mode, RMP will be the only means to tune
• RMP used as gateway for FMC

MMR

• 2 functions: Landing system (ILS MLS) and Civil GPS (FMS)
• Power supply: MMR1 supplied by EEPDC at 115 VAC, MMR2 supplied by SEPDC 2 at 115 VAC
• Location: MMR 1 in lower deck avionics bay at 1300VU, MMR 2 in main avionics bays at 1200VU
• 2 GPS antennas, 1 MLS omni-directional at front top, MLS landing antenna at lower part of nose fuselage

VOR/DME/MMR/ADF

• VOR provides azimuth orientation to a VOR ground station
• Marker provides indication about the passage of the aircraft over the marker beacon transmitters
• VOR receives, decodes, and processes bearing information from VOR signals
• Provides magnetic bearing, selected course and deviation, and audio signal (Morse)
• Marker installed: IM at runway threshold, MM at 0.6 NM from runway threshold, OM at 4 NM from runway threshold
• Architecture: 2 receivers, 1 common VOR semi-ant connected to each side of VOR receivers, 1 marker antenna connected only to receiver 1
• Power supply: AC EMERGENCY BUS supplies VOR/MKR 1 receiver, SEPDC 2 supplies VOR/MKR 2 receiver
• Location: VOR/Marker receiver on upper deck avionics bay (1100 and 1200VU)

DME

• Provides digital readout of slant distance and audio signal
• Components: 2 interrogators, 2 antennas
• Power supply: to cut both DME power supply = MMMS or ICPs command
• DME interrogator 1 located at 1100VU, DME interrogator 2 located at 1200VU
• Antennas at bottom fuselage, SEPDC 1 supplies DME 1 interrogator, SEPDC 2 supplies DME 2 interrogator
• In order to prevent mutual interference of L band suppression bus equipment and ensure RF interoperability, each DME connected to iff1/2, Tacan1/2, DASS, MIDS, ISU1

ADF

• Provides indication of relating bearing and aural identification
• 1 antenna and 1 receiver
• Power supply no emergency: SEPDC 1 supplies ADF receiver
• Location: receiver in upper deck avionics bay situated at 1000VU
• Antenna at bottom fuselage
• Controls and indications: on NTD and FMD