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ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Nav...

ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Navigation Page Question Answer 6 What are the KCCU used for as - 2 Keyboard and Cursor Control Units (KCCUs), on the ADIRS is concerned? pedestal, used for manual position IR alignment and to give access to the status of the ADIRS on the Multi- Function Displays (MFDs) via FMS function. 8 Where is MFP located FWD fuselage 8 What is ISIS and where located Integrated Standby Instrument Systems. Two ISIS located in the center of the main instrument panel, are the back-up systems in case of ADIRS, CDU failures 10 Where is OAT sensor located and Two Outside Air Temperature (OAT) probes, on the Nose how are they connected Landing Gear structure, that give the Outside Air Temperature. OAT probe 1 is only connected to ADIRU 1 and OAT probe 2 is only connected to ADIRUs 2 & 3 10 Explain Anti icing for the Air probes Each probe (but not the OAT probes) has an integrated anti-icing protection, which can be activated automatically by the ADIRS or manually with a PROBE/WINDOW HEAT P/B switch on the ICP. 12 How can you manually align IR You can also use the KCCU and MFD to align the IR part manually through the FMS. 14 How are OAT probes energised and Directly energised by ADIRU. They are not heated. They who do they communicate to and communicate in analog to ADIRU how 15 When is anti icing operated Anti-icing function is automatically operated when: automatically - At least one engine is running, - Or the IR Ground Speed (GS) is higher than 30 kts. 15 How is anti icing operated Anti-icing can be operated manually by the means of manually "PROBE/WINDOW HEAT" P/BSW installed on ICP- ADIRS, when the A/C is on ground with no engine running. 18 What kind of signal is GND/FLT Discrete signal from LGERS 18 From which IR does data go to ISIS ADIRU 1 and 3 20 When there is a partial failure of ATT the related IRU, what position of the rotary selector is used 20 Describe the “IR” push button One "IR" P/BSW normally in "ON" position (no light), to Switch be selected to the "OFF" position (white light) in case of failure of the IR part of the ADIRU, leading to the lighting of the amber "FAULT" light of the P/BSW. 20 Describe the “ADR” push button Same as above philosophy Switch 24 Where can you see ADIRU data PFD ND 24 Where can you see ADIRU status The ADIRs status and parameters can be shown after and parameters manual selection on the MFDs "POSITION/IRS" page 28 Explain what happens when ISIS 1 In case of failure of ISIS1, ISIS 2 is automatically fails reconfigured in standby flight display mode. In this configuration, it is possible to recover the BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer standby navigation display again by an action on the MODE P/BSW, installed at the front face of the ISIS. 30 What activates the discrete anti This discrete is activated from the Air Data and Inertial ice going to the standby probes Reference Unit (ADIRU) 1 or 3 with the following conditions: - one engine is running, - or Ground Speed (GS) is higher than 30 kts, 30 Explain the link between the A link exists between ISIS and the two Flight Guidance PRIMary systems and the ISIS Computer Units (FCGUs) included in each one of the three PRIMary (PRIM) systems through an ARINC 429 bus. This interface is used to send air data and inertial data to the FCGUs in case of two ADIRS failure. 31 Describe electrical configuration In normal conditions, the 2 ISIS are supplied by normal of the two ISIS DC busses. In case of emergency electrical configuration, their supply changes to DC essential bus. 36 What happens when pressing the - Transpose the SFD and SND modes between the upper MODE button successively with and lower ISIS. This could be used when one has a partial partial failure of any ISIS fault, such as no speed data available on ISIS 1. 36 When one ISIS has completely The MODE switching is inhibited when one ISIS display failed, what happens screen has failed. PFD is the priority mode and must remain on the serviceable ISIS 42 What are the main functions of the The main functions computed by an MMR are as follows: MMR - the ILS computes Localizer (LOC) and Glide/Slope (G/S) deviations, for precision approach and landing, - the Flight management Landing System (FLS) computes pseudo LOC and pseudo G/S deviations, for non-precision approach 50 With respect to FLS (Flight FMS management Landing System), who calculates the beam data 66 Which system is responsible for OANS showing the brake to vacate and Runway Overrun Protection 68 Where is the ADB and the OANS OANC hosted 68 How can you display the OANS “ZOOM” position on the EFIS CP Range selector 76 What happens when single RA an amber alert message is shown on the Electronic fault is detected Centralized Aircraft Monitoring (ECAM). Multiple failure combinations will produce a Master Caution and single Chime. 76 Describe the RA and LGERS Each RA transceiver is connected to the Landing Gear connection Extension and Retraction System (LGERS) via a discrete link. The LGERS gives flight/ground information to the RA in order to let or forbid interactive mode 76 Describe the RA and Master Lever Each RA transceiver is connected to the MASTER connection LEVER ON ownside via a discrete link. The MASTER BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer LEVER ON gives engine power ON/OFF information to the RA in order to inhibit the interactive mode during the flight 84 Why is DME connected to both to give to the crew the morse audio identification of the AMU? selected ground stations 86 Where is VOR , Marker info PFD and ND displayed? 88 In Radio Navigation tuning, what is None the indication for Auto Tune 88 In Radio Navigation tuning, what is On this mode a "M" underlined and dimmed is displayed the indication for Manual Tune near the navaid identification on NDs 88 In Radio Navigation tuning, what is On this mode a "R" underlined and dimmed the indication for Backup Tuning 102 What are the interfaces for the The EFIS control panels select the different modes of AESS view on the NDs. The Keyboard and Cursor Control Units (KCCUs) interface on the surveillance pages on the MFDs. In case of failure, the system may be reconfigured using the AESS control panel due to the redundancy between the 2 AESUs. 106 How can the crew modify The crew can see and modify the transponder code either transponder code? on this MFD page or on RMP 1 & 2 & 3 (SQuaWK page). 112 What occurs when a “RA” happens In case of a Resolution Advisory, the TCAS sends to the on TCAS? AFS the data necessary to compute an escape maneuver. It also computes and displays on the PFDs a "safe vertical speed" scale. 118 On ground when does the WXR On the ground, the weather radar function operates operate automatically automatically when at least one engine starts and if the CAPT (or F/O) EFIS "WX" key is pushed. In flight, it operates without conditions BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Autoflight Page Question Answer 10 Weight and Balance Backup The WBBC computation is used to consolidate FQMS data in Computation in regard to Flight case of FQMS failure, or in case of FQMS/WBBC envelope protection discrepancy. 12 Important note about data flow in NOTE: Although the WBBC and FCDC applications are FEP hosted in the same CPIOMs, the WBBC applications receive the primary flight control surfaces positions from the FCDC applications not internally to the CPIOMs but via the ADCN. 16 Who calculates the Characteristic The FE calculates the characteristic speeds, which are shown speeds shown on the PFD on the PFD, for Auto Flight Guidance (FG) function, for Flight Management (FM) function or for flight control laws function. 18 What is the reactive windshear Reactive Windshear: function The windshear detection is based on wind law computation by the PRIM only (from vertical and lateral accelerations data given by the Inertial Reference System (IRS) and actual AOA). 18 What is the reactive windshear warning "WINDSHEAR WINDSHEAR WINDSHEAR". A warning red WINDSHEAR message is also shown on the PFDs. 18 When is reactive windshear At least one thrust lever set to TOGA inhibited? 18 Describe Alpha floor The FE activates the protection against excessive angle-of- attack (AOA), called alphafloor protection, by sending an alphafloor detection signal to the FG, which activates the A/THR with full thrust (on all engines without engine failure or on symmetrical running engines). 22 With regard to Guidance Order ADCN computation input, how do the managed targets from the FMC come to the PRIM 22 With regard to Thrust target The vertical mode from AP FD computation inputs, name one input that comes to the PRIM 23 Who computes the landing The overall landing capability is computed by the FCDC capability computation applications hosted in the CPIOMs-C 26 What is status of TCAS RA with AP When the A/C is in flight with the A/P engaged, the TCAS engaged mode engages and automatically does the avoidance maneuver, in case of resolution advisory detection by the TCAS. 28 One important condition for AP Aircraft in flight for more than 5 seconds engagement 28 One important condition for AP All engines off with low hydraulic pressure engagement on ground 29 What are FD engagement logic The FD is automatically engaged at aircraft electrical power- up. However, the FD guidance orders will be displayed from takeoff only. BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer 30 Reasons for FD disengagement The FD is disengaged if one of these conditions occurs: - The FD key on the FCU is released, - The aircraft gets to VLS in the DES or OP CLB mode, - The aircraft gets to Vmax op in the CLB or OP CLB mode, - A fault is detected. 32 What is PRIM priority if all PRIMS If all PRIMs have the same capability, the priority is PRIM 1, have same capability? PRIM 2 and PRIM 3 being defined as slave 1 and slave 2. 32 What happens if MASTER PRIM If the master PRIM fails or just loses the best capability, an Fails? automatic reconfiguration occurs without any AP, FD & A/THR disengagement: - The slave 1 PRIM becomes the master PRIM, - The slave 2 PRIM becomes the slave 1 PRIM. 33 What does 1FD2 mean? The FD operates normally in dual configuration whatever the AP engagement status. Both FDs are active and 1FD2 is displayed on the Flight Mode Annunciator (FMA) of both PFDs meaning that: - The FD 1 guidance orders are displayed on the CAPT PFD, - The FD 2 guidance orders are displayed on the F/O PFD. 33 What does 1FD1 mean When side 2 guidance inputs are not available, only FD 1 is active and 1FD1 is displayed on both FMAs meaning that the FD 1 guidance orders are displayed on both PFDs. 36 What is the FCU channel selection If the master PRIM is either PRIM 1 or PRIM3, the selected logic channel is channel 2. If the master PRIM is PRIM 2, the selected channel is channel 1. 40 What happens to ATHR when the - If the AP/FD vertical mode controls the vertical trajectory APFD vertical mode controls the or if there is no active AP/FD vertical mode, the A/THR vertical trajectory? mode controls the speed/Mach by ordering a variable thrust target, 42 What is the active range of A/THR Between IDLE and Climb with no engine INOP 42 Where are the Throttle levers set in To CL normal operation? 42 What is the condition of ATHR with - With one engine INOP, the A/THR active range is between one Engine INOP 0 and MCT. To get the A/THR active, the thrust levers of all operative engines have to be set in this range. 44 Describe AT Disengagement As the normal operation, the A/THR can be manually disengaged through the outer thrust levers by pressing at least one of the two A/THR instinctive disconnect pushbuttons. The disengagement order is sent to the PRIMs via dedicated discrete. If the A/THR instinctive disconnect pushbuttons are pressed for more than 15 seconds, the disengagement is definitive for the whole flight. As the normal operation during landing, the A/THR is disengaged when all thrust levers are set to idle. BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer 44 Describe Memo Thrust control Note that the thrust is only frozen when the A/THR is mode disengaged through the FCU A/THR pushbutton or by system failure. The memo thrust control mode does not apply when the A/THR disengagement directly results from a cockpit crew action through one of the A/THR instinctive disconnect pushbutton or the throttle control levers. The engines thrust is adapted with the thrust levers positions. 48 What does the performance The performance database, with aircraft aerodynamic and database in the FMS do engine models, enables vertical flight plan construction and optimization. 58 What is FM independent mode The FM automatically sets to independent mode when the dual function is lost (cross-talk mismatch or failure between the relatives FMCs) 58 What is Flight Planning backup in In case of loss of 3 FMCs, the flight crew is able to use the FM Integrated Standby Instrument System (ISIS) as a flight- planning backup. 64 Describe the ACMS inputs The AFS transmits, via the ADCN and the Centralized Data Acquisition Module (CDAM), system parameters to the ACMS for real time monitoring and reports generation. - The autopilot (AP) engagement and the selected heading from the PRIMs. Communication Page Question Answer 10 What is special about the data On ground only, some NSS data link applications can communication on ground exchange data with the AOC centers through the optional Wireless Airport Communication System (WACS). 14 Describe the data mode of HF In data mode, the ACR receives data mode status from the transveivers. The frequency used is managed by the transceiver itself. The transceiver includes a frequency database and, depending on the aircraft position sent by the Air Data/Inertial Reference Units (ADIRUs), will tune itself on the related frequency. 14 HF transmitting >60 sec. What The HFDR transceivers transmit HF EMITTING discrete to happens? the FWS for level 2 alert computation need (COM: HFx EMITTING message appears on the EWD when transmission exceeds 60 seconds). 16 Describe VHF data mode VDR 3 transceiver is connected to the ACR for VHF datalink. In data mode, the VDR 3 transceiver sends its data mode status to the ACR and the ACR tunes the VDR 3 transceiver. 16 VDR transmitting more than 30 The VDR transceivers transmit VHF EMITTING discrete to sec/60 sec. What happens the FWS for alert computation need (COM: VHFx EMITTING message appears on the EWD) which triggers level 1 alert when transmission exceeds 35 seconds then level 2 alert when transmission exceeds 60 seconds. BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer 18 What is the function of The Diplexer/Low Noise Amplifier (D/LNA) segregates Diplexer/LNA transmitted and received signals and amplifies the received signal. The Beam Steering Unit (BSU) controls the pointing of the airborne antenna. 22 What is backup to tuning radio As a back-up, the RMPs (1 and 2) can also tune the radio nav systems? navigation systems if the tuning through the Flight Management System is not possible. 30 Characteristics of RMP It is possible to select, display and modify the operating frequencies of all communication transceivers from one RMP. 30 Characteristics of RMP Note: After each power ON, a context saving allows the recall of the previous frequencies and modes of each radio means. 30 Explain the INT/RAD switch - using the INT/RAD switch in the INT position; this is a stable position and it enables permanent flight interphone transmission, - using the INT/RAD pushbutton in the RAD unstable position or by action on any PUSH TO TALK switch; this will activate the transmission mode for the selected radio set. 31 How is logon confirmed in Logon is confirmed by a green LOGGED ON AUTO or SATCOM LOGGED ON MANUAL indication on the SATCOM CONFIG page of the SATCOM menu. 31 Failure indication of RMP Failure indications If a system is defective (RMP, dialog bus,...), the RMPs operate in degraded mode. In case of RMP failure, the EWD shows a warning. The red light on the RMP is just an indicator to tell the crew to switch off the defective RMP(s), as appropriate crew procedure. When it is off, an ECAM memo appears to tell the flight crew that RMP 3 will be used as an alternative to the defective RMP (reconfiguration). 38 AMU 1 and 2 distribution The AMU1 is dedicated to captain and 3rd occupant sides and the AMU2 is dedicated to the first officer and fourth occupant 38 What happens with total loss of A total loss of one AMU causes a total loss of all functions one AMU on the side concerned as well as the loss of the flight interphone. If the AMU1 is lost, all the RAIMS has lost its connection to the OMS and no fault report can be sent to the FWS. 40 Who will prevent one cockpit The AMUs user from using several communication means at the same time, as well as prevent the use of the same communication mean by several users. 44 Who also sends the VHF Data The ACR Service Provider (DSP) list to the RMPs for manual selection. BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer 50 From where can the users display Via the RMPs the ACR status and initialization parameters as well as communication means and ACARS sub-networks status. 54 Describe the WIRELESS Upon the "radio power enable" signal, the WLM will check if AIRPORT COMMUNICATION the aircraft is on ground and the airport is capable of wireless SYSTEM connection. If it's the case, the WLM will trigger the "power ON/OFF" discrete. The CTLR-WACS will then be operative. The GATELINK P/BSW can force the WACS off. 60 Describe the CVR test and The CVR system test on ground operates as follows: erase function - push the TEST pushbutton. - release it in order to listen to the tone that indicates the CVR is operational. This 600 Hz tone can be listened to through a boomset plugged to the CVR CU. The audio recording can be manually erased on ground with the park brake set, by pressing during more than 2 seconds 62 What are the CVR recording the CVR is in recording mode if the following conditions are modes met: - on the ground, during the first five minutes after nergization of the aircraft electrical network, - on ground with at least 1 engine master switch ON, - in flight, - on the ground, during five minutes after the last engine shutdown. 68 Who gives ETACS activation The EFIS control panels give the ETACS activation demand demand on PFDs directly to the CIU. 68 When is the camera switched When the crew are using the "LANDSCAPE & T AXI off? CAMERA" pushbutton in the cockpit, the camera output is switched off. 70 Who can inhibit the ETACS On the PFDs, the taxi aid cameras can be displayed only when aircraft is on the ground and the ground speed does not exceeds 60 kts. The EFIS control panels receive from the PRIMary system, "ETACS inhibition" information, which deactivate the switch. 70 What is SD priority for ETACS On SD, the ETACS pictures belong to the VIDEO page. This page has the same priority than the other system pages. That is to say that if no other page is automatically called by the system like warning or advisory display, or flight phases inhibition, BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 ATC Page Question Answer 4 What indicates the arrival of an - CAPT, F/O "ATC MSG" P/Bs and loudspeakers to indicate ATC message the arrival of an ATC message, 6 What is the Controller-Pilot CPDLC Data Link Communications The CPDLC function allows a dialogue between the flight (CPDLC), crew and the ATC by managing uplink and downlink messages. 6 What Is the ATIS function CPDLC The CPDLC function allows a dialogue between the flight crew and the ATC by managing uplink and downlink messages. Lights Page Question Answer 22 Which unit receives discrete ECAM CONTROL panel signals from the dimming unit 36 Connections to DEU B The vacant/occupied indicator in the cockpit for lavatory installed at area of door M1L and the stand-alone signs are connected to DEU B. 38 Where cabin lighting scenarios The cabin lighting scenarios are also loaded in the CAM loaded according to the airline definition. 40 DEU A capability Each DEU A can transmit lighting requests to 8 IBUs maximum, via a modified RS485 interface. 44 What is used to make the , two different types of adapted interface boxes are used: Understep LED Lights (ULLIs) - Stair Electrical Load Adapter ( STELLA) for cabin CIDS controllable staircase, - Mini Light Adapter (MILA) for cockpit staircase 46 If cockpit door in unlocked with Independent of all light settings and running light scenarios, engines running the intensity of some lights installed in the cockpit access area is automatically dimmed to 10% (in standard) if the cockpit door is unlocked with engines running. The involved lights are: - two spotlights in the FWD entrance area and - one single IBU in the cockpit staircase ceiling. 46 What happens in loss of CIDS independent of all light settings and running light scenarios, the intensity of the cabin general lighting is automatically dimmed to 50% (in standard) in the case of: - either a total loss of the serial data bus system, - or FAP failure, - or loss of the CIDS. 46 What happens in cabin The cabin general lighting is automatically bright to 100% in decompression case of cabin decompression. BUSINESS DOCUMENT This document is intended for business use and should be distributed to intended recipients only.  ENGINEERING TRAINING Study Guide Airbus A380 (EA GP7200 & RR RB211 Trent 900) B1/B2 Page Question Answer 48 How lav lightings go to 10 For cleaning and maintenance purposes, the lavatory lightings can be switch to 100% brightness from the "LAV MAINT" P/B installed on the FAP hard key panel. This 50 PISA how many reading lights Each PISA can supply up to four reading lights. 52 Describe attendant work light The attendant work lights are supplied either: - by PISAs, when the light is installed in the PSU channel (above attendant seat), or - by Stand-Alone PISAs (StA PISAs), when the light is installed in any other location. In both cases, these adapters are connected to DEUs A with a LVDS interface and supply the attendant work lights with 6 VDC. 64 Describe the 3 way nose light The three-way NOSE switch operates the taxi and takeoff switch lights. - The taxi lights operate if the NOSE switch is set to the TAXI position. - When the NOSE switch is set to the "T.O" position, the taxi lights stay activated and the takeoff lights operate if the NLG is locked down. 76 When do logo lights operate If the LOGO switch is set to the "AUTO" position, the logo lights come on automatically when one of these following conditions occurs: - NLG on ground or - slats extended 20º. 82 Describe the Taxi aid camera The system is connected to the LGERS and the Concentrator light logic and Multiplexer for Video (CMV). Thus, when the RWY TURN OFF & CAMERA switch is set to the "ON" position, the taxi camera lights come on only if: - the ETACS is "ON" and - the NLG is on ground. 96 Exit signs auto on logic- The system is connected to the LGERS and the Concentrator and Multiplexer for Video (CMV). Thus, when the RWY TURN OFF & CAMERA switch is set to the "ON" position, the taxi camera lights come on only if: - the ETACS is "ON" and - the NLG is on ground. 96 Emer slide lights and emer door The emergency slide lights and the emergency door lights lights logic come on automatically when the escape slides are deployed (DSMS signal to EPSUs), provided that the EMER EXIT LT switch is not on the "OFF" position. 96 Cockpit way lights logic When entering or going out the A/C with general lights in MAIN OFF status, crew can put the light on for 60 seconds in the way to the cockpit or to the exit door M1L with cockpit way lights. 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