ATA 34.odt

GADIRS(17q)(no frames) : OAT 1 =\> Gadiru 1/3 (gps crpa/crpau not gadiru 3..) mfp 3/1 left FRPA,CRPA(fuselage top area) ,CRPAU(fairing center fuselage) ADR architecture: ***IR architecture:*** Hybrid = Mil/Civ gps + IR measure the accelerations: GPS and time architecture: ***!!Normal power...

GADIRS(17q)(no frames) : OAT 1 =\> Gadiru 1/3 (gps crpa/crpau not gadiru 3..) mfp 3/1 left FRPA,CRPA(fuselage top area) ,CRPAU(fairing center fuselage) ADR architecture: ***IR architecture:*** Hybrid = Mil/Civ gps + IR measure the accelerations: GPS and time architecture: ***!!Normal power supply:*** (**4 main parts gadiru !!! attention pas de crpau sur gadiru 3 , just normal condition) isp ½ vdc 28 ! GADIRU cant be triggered during the flight..** **If DC ESS BUS lost backup is ensured through 10s in the TDO relay, time necessary for RAT deployment** Control and indications: Locations: !GADIRS =\> avionics bay Detailed description: ADR computes and provides: ** ** Air data probes: all probes except OAT transmits via **ARINC 429** Analog OAT ADR monitoring: **internal monitoring** includes 2 checks: - comparison between **L** and **R static pressures** - **comparison** of air data computed by **ADR** **with other system** (like ISIS) which use their own probes and FADEC **external monitoring** performed by PRIM and FWS - **PRIM** monitors **airspeed/mach** and the **altitude** - **FWS** compares **altitude** displayed on CM1 with CM2 IR PART: ** (b.b) ***MIL GPS:*** delivers data with superior accuracy GADIRU 3 uses always FRPA(civ), crpa(mil) In case of jamming , switch in auto will switch automatically from FRPA to CRPA Hybridization: 2 hybridization: - civil is made through IR/GPS simple filter - military is used to fuse the measurement from different source GADIRIS connectors : 3 electrical connector in front face are used for GPS function Battery: the operational effect of failed: Probes: MFP: 115VAC MFP module receives: - Automatic de-icing - manual de-icing - electronic power for electronics and de-icing heater ISP: 115VAC for de-icing and 28VDC for electronics SSA: 115VAC ** ***OAT:*** OAT 1 =\> G1/2 OAT2 =\> G3 Operation on ground: Start procedure Indications when gadirs turned on: ***IR FAST ALIGNEMENT** **:*** I love you duo and au q la chasse Standby navigation system: Static/pitot probe connected directly to ISIS architecture: ISIS computes and transmits air data and inertial reference Power supply:\-\--? Location: ISIS = **main instrument panel** Standby compass = on the **overhead panel**, on the top of windshield centre post standby static = left and right standby pitot = right Detailed description: ** GADIRU **1**&**3** using ***ARINC 429 =\> ISIS*** ISIS unit: Detailed controls and indications: ISIS: Air data indications: - Mach number = visible above 0,5 and disapears below 0,45 Maintenance menu: - **Maintenance Pages** to display the failures and the ISIS conf. - **Air Data Testing** enables to access to the air data testing function Radio navigation system: Tuning and displays: Resumer : 2 tuning :auto fms/manuel fms cds rmp... pas rmp3 en nav, si fmc fail en manuel utiliser rmp **2** tuning: - **Automatic** = supported by **FMS** - **Manual** = supported by FMS, CDS, RMPs **(kccu)** 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 Detailed description: In normal = RMP is transparently, tune is made FMC -\> IOM trough RMP MMR(sub system): 2 function : - **Landing system (ILS MLS)** = uses **ground stations** which emit signals in order to computes deviations - **Civil GPS(FMS)** = based on the measure between A/C and satelites Power supply: MMR1 is supplied by EEPDC at 115 VAC MMR2 is supplied by SEPDC 2 at 115 VAC Location: - **MMR 1** = lower deck avionics bay **1300VU** - **MMR 2** = main avionics bays **1200VU** - **2 gps antenna/ 1 MLS omi directional at front top** - **MLS landing antenna at lower part of nose fuselage** Detailed description: (savoir connection) ILS: The MMR receives by ILS ground station: - LOC emitter (lateral deviation) - G/S emitter (vertical deviation) Detailed controls and indications: ***VOR/Marker (sub system) :*** **VOR** provide the aircraft during navigation with **azimut 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 the VOR signals provides: - magnetic bearing - selected course and deviation - audio signal (Morse) Marker installed: - IM at the runway threshold - MM at 0,6 NM from runway threshold - OM at 4 NM from the runway threshold Architecture: - 2 receivers - 1 common VOR semi-ant connected to each side of VOR receivers - 1 marker antenna connected only to the receivers 1 ***Power supply:*** AC EMERGENCY BUS supply VOR/MKR 1 receiver SEPDC 2 supply VOR/MKR 2 receiver ***Location:*** VOR/Marker receiver on the upper deck avionics bay (1100 and 1200) Detailed description: Only the VOR 1 embeds the Marker functions... DME: Is a radio aid to medium range navigation, provides crew: - Digital readout of slant distance - audio signal constitued of: - 2 interrogators - 2 antennas Power supply: to **cut** both DME power supply = **MMMS or ICPs command** DME interrogator 1 localisation = **1100VU** DME interrogator 2 localisation = **1200VU** Antennas at bottom fuselage SEPDC 1 supply DME 1 interrogator SEPDC 2 supply DME 2 interrogator Detailed description: In order to prevent the mutual interference of the **L band suppression** bus equipment and to **ensure RF interoperability each DME** is connected to (schèma) iff1/2 , Tacan1/2,DASS,MIDS, ISU1 Detailed control and indications: on the **NTD** in **ARC** and **ROSE** modes: - DME : station identifier , distance, frequency (LEFT SIDE of pfd for dme1 right for 2) ADF: provides: - indication of the relating bearing - an aural identification 1 antenna and 1 receiver Power supply no emerg: SEPDC 1 supply ADF RECEIVER Location: receiver in the upper deck avionics bay situated at **1000VU** Antenna Bottom fuselage Detailed Control and indication: on the NTD and FMD TACAN(vor-dme short-mid range nav): is a system for **radio orientation** and **radio distance measurement** for **mid and short range navigation** provide to crew: - **azimut** and **distance data** - audio signals... - 2 transceivers - 4 antennas (2 antenna /transceivers) !emcon : stop dme function. **Power supply (no emergency): SEPDC 1 supply TACAN 1 SEPDC 2 supply TACAN 2 ***Location:*** Transceiver 1 = **1100VU** Transceiver 2 = **1800VU** antenna 1 and 3 on TOP antenna 2 and 4 on bottom (used by mids if installed ) Detailed controls and indications: TACAN does not have dedicated hardware controls except for the control of the audio identifier located in ACP Indication ntd: TACAN 1 lower left TACAN 2 lower right Radio altimeter (important): - 2 RA transceiver (1 transmitting /1 receiving antenna per receiver) - 4 antenna RA height provided to CDS and HUDS trough ADCN (IOM) The RA height data are also sent trough direct link: - FWS - AFS Power supply ( emergeeeeency) : EEPDC supply RA transceiver 1 SEPDC 2 supply RA transceiver 2 ***Location:*** RA trancsceiver 1 on **left side** and RA transceiver 2 on **the right side** **Ant bottom area** Detailed description: RA interface with ICPs: - engine master lever - EMCOM and DASS silencing - RA ovveride switch Detailed control and indications: 2 positions RA override: - ON = works normally - OFF = RA emissions are inhibited or not according to EMCOM/DASS silencing command Military functions: RA military has 2 functions: - power management = increase aircraft discretion regarding RF emission - Jamming detection = when interference ISS: - TCAS - TAWS - WXR Main component: - 2 ISU - WXR antenna - 2 TCAS antennas - WXR control panel Power supply: both PSM's ISU 1 is supplied by SEPDC 1 WXR antenna is supplied by PSM at 200 VDC Location: - ISU 1 and 2 situated 1000VU Detailed description: Normal mode = all functions delivred by ISU 1 (master) Mixed mode = if 1 function is lost, the functions as shared ISU 2 master Downgraded mode = TCAS failure or at least 2 fault in the system, the ISU that is selected for WXR function is the master Weather radar: Detailed description: In single configuration RTU 2 =is a dummy RTU which enables the stowage plugs from antenna drive unit and ISU TAWS: Detailed description: GPWS mode 5 active less than 1000 ft AGL and L/G down TCAS: Military radar: Component: - 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 **1100VU** Detailed description: Data interface of the MMRP with A/C systems performed trough Ethernet using the ISU as gateway EVS: interconnection with others systems is ensured by both HUDC Detailed description: External interfaces: The image automatic adjustment is continuously performed by EVS based on alignment parameter stored in HUD PMM, in this case both data link with HUDC are used Detailed control and indications: EVS FAULT = cannot provide video signal EVS OVERHEAT =automatically removed when the inner temperature turned back to normal EVS DEGRADED = The misalignment corresponds to a lack of HUD alignment value and not to a misalignment caused by a physical misalgnment of the sensor due to an external impact VOR/DME/MMR/ADF/ test p/b more than 3s !