Home

4 - EEC (EUROCONTROL Experimental Centre)

1. Exrecrep RESULTS a b c d Verify that the increments are correctly taken into account in the target page e The corresponding page is displayed Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE Function CDU reduced display options page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 Previous TESTS OTHER CONDITIONS TesT DESCRIPTION a Set an aircraft display mode to reduced then go to the reduced display options page Highlight in cyan resp ON and OFF by clicking the 1 button at the left b Highlight in cyan resp ON and OFF by clicking the 2 button at the left c Highlight in cyan resp NO REL ABS by clicking the 3 button at the left d Highlight in cyan resp ON and OFF by clicking the 4 button at the left e Highlight in cyan resp ON and OFF by clicking the 5 button at the left f Type a number in the scratchpad then click the 1 button at the right Try 0 and a non zero number g Type a number in the scratchpad then click the 2 button at the right Try 0 and a non zero number h Click the lt TARGETS and OPTIONS gt buttons Exrecrep RESULTS a b c d e f g Verify on the ND that the options are taken into account h The corresponding page is displayed Poe Rest Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE CDU EXT Function CDU extended disp
2. TEST RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS TESTS FOLLOW UP Comments 1 6 4 Rate RESULTS Total Rate Advance Valid 6 5 5 3 4 6 4 E i A D le AAA petits KT FI lei ESA ii LULU PEE ima i SAEZ b si A ien d EF i aa E AE DRE ii be AA d 6 UG 4 Cancelled Performe NUMBER OF TESTS OK NotOK Not performe d 2 3 ii dini L AN L eden py AAA AAA ESA A EA a L HOT H A L L L ani EA ET EA si 1 Z A a E E NO Ez ece E 4 MONITORING TABLE OF BLOCKING INCIDENTS PIRE ct tht ici FORMS USED FOR TESTS PERFORMING Test Card Test Journal Tests follow up card Monitoring table of Blocking incidents VALIDATION TEST CARD Scenario Date PSA Document Software Version Author Page ____ TEST CASE FUNCTION REFERENCE DOCUMENT Initial State Previous tests Other conditions TEST RESULT Conform Blocking Not Blocking DATE INITIAL CONDITIONS TEST DESCRIPTION EXPECTED RESULTS VARIATIONS NOTED OBSERVATIONS Reproduction soumise accord pr alable TESTS JOURNAL Function tested Software Version Comments Testing 1 Conform A Date 2 Cancelled Comments 3 Not TESTS FOLLOW UP CARD Comments 1 6 4 Rate RESULTS To
3. Select a scenario and a subject aircraft C Opena cockpit CCNI Start the simulation Open the air situation display window Top level application Tested function RH 1 1 Top level application Software Version V 1 0 Comments Testing 1 Conform Description A Date 2 Cancelled Comments Test B Who 13 Not conform codes a ae eae 3 a f TT oro Selection of an aircraft TOP d Activation of the cockpit G ee ET H ro Start Stop Pause Resume controls pap ls ET Ton Full availability Cockpit Environment Tested function RH 1 2 Cockpit Environment Software Version V 1 0 Comments Testing 1 Conform Test Description A Date 2 Cancelled Comments codes B Who 13 Not conform QA B 11213 iaa OO sl pr A E Full availability Display Options Tested function RH 1 2 1 Display Options Software Version V 1 0 Comments Testing 1 Conform Test Description A Date 2 Cancelled Comments codes B Who 13 Not conform opa OnE CDTI representation absolute vs relative OPTO CDTI level of assistance Control Display Unit Tested function RH 1 2 5 Control Display Unit Software Version V 1 0 Comments Testing 1 Conform Test Description 2 Cancelled Comments codes 3 Not Conform CDU MENU CDU Menu page CDU ASAS CDU ASAS main page l I CDU ASAS Select Aircraft MS a CDU ASAS Display Aircraft List ma b CDU ASAS
4. e HH IF b ad a o o E e I ma OO ka Cees ND interactivity Tested function RH 1 2 2 5 ND interactivity Software Version V 1 0 Comments Testing 1 Conform Test Description A Date 2 Cancelled Comments codes B Who 3 Not conform A IBI1 213 INTERACT Aircraft Pointing T AS ET oe prt DD B pr orome AO o O a APRA L fii D INTERACT _ Route waypoint somes ER RE Air Situation Display RH 1 3 Air Situation Display Software version V 1 0 Testing 1 Conform Test Description A Date 2 Cancelled Comments codes 3 Not E A BESA A IE adaptability Zoom mo ig E ASD d Space reference marks ASD Airways and Sectors J ASD f Past Positions T T T ASD g AiroraftMarking __ JASD h Tracker LASD i Airoraft Representation JASDG Trajectory ASD k Configuration EFIS Control Panel Function RH 1 2 3 EFIS Control Panel Software version V 1 0 Comments a 1 Conform Test Description 2 Cancelled Comments codes EFISCP a EFIS RCE Panel so EFISCP b EFIS Control Panel ND CDTI CDTI Mode Control Panel Function tested RH 1 2 4 Mode Control Panel Software Version V 1 0 Comments Testing 1 Conform Test Code Description A Date 2 Cancelled Comments A E ENEE Predefined guidance mode MCP b
5. 2 Perform this on other aircraft 3 Perform this on an aircraft already marked h 1 Select Tracker on Tools menu 2 Perform a drag and drop thanks to left mouse button between two unspecified points 3 Repeat previous test playing with the mouse pointer before dropping and choosing an aircraft as one of the two points 4 Deselect Tracker on Tools menu i 1 Choose the scenario ThirteenAircraft 2 Perform a drag and drop from an aircraft label 3 Change aircraft status by right clicking on the chosen aircraft and selecting a new status among To be assumed Assumed Transferred and Not concerned in the Aircraft Status submenu 4 Select Aircraft on Display Options menu Play with the selections proposed j 1 Staying with scenario ThirteenAircraft right click on an aircraft symbol in the ASD then select Display Erase Trajectory in the menu 2 Display KPF789 and EJV789 trajectory k 1 Inthe Display Options menu select Velocity Vectors and change the selected value for the velocity vector look ahead 2 In the Display Options menu select Past Positions and change the selected value for the past positions number 3 In the Display Options menu select Size and Colors and change current configurations 4 In the Display Options menu select Navai
6. ExMAP a VNAV Path Pointer a sa RES RER b Cockpit Display of Traffic Information Tested function RH 1 2 2 3 Cockpit Display of Traffic Software version V 1 0 Information Comments A JIBI1 213 CDTI a Aircraft Information CDTI b Selected Aircraft CDTI JCDTIDisplav Priority Testing 1 Conform Test Description A Date 2 Cancelled Comments codes 3 Not Enhanced Cockpit Display of Traffic Information Function RH 1 2 2 4 Enhanced CDTI Software version V 1 0 Comments Testing 1 Conform Test Description A Date 2 Cancelled Comments codes A B 1 2 3 CDTI a Representation CDTI b Assistance CDTI CDTI Information Display CDTI d CDTI Display Priority CDTI e CDTI Colours CDTH CDTIH Units Approach CPA LSA Lateral distance at CPA LCPA LSA Time before CPA TCPA LSA Time before Conflict TC LSA Extrapolated lateral trajectory of target aircraft VSA Altitudes at CPA V SEP b VSA Relative altitude at CPA VCPA a V SEPO VSA Time before CPA Tp tro VSA Time before Conflict TC LP Oblique Distance L PASS b LP Closure Rate CR L PASSO LP Oblique Line LSK Along Track KEEP a Distance ATD LSK Closure Rate CR KEEP b jil g we T KEEPO ree IF a
7. RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS Scenario PFD ATT PFD Attitude and Steering Date Indications Document Software V 1 0 version Author Page A Test CASE PED ATT Function PFD Attitude and Steering indications req RH 1 2 2 1 PFD ATT a 1 REFERENCE DOCUMENT INITIAL CONDITIONS testPFDND applet launched Previous Tests None Other conditions None TEST DESCRIPTION a Enter a numerical value less than 35 then another value greater than 35 in the Bank text field b Enter a numerical value in the Slip Skid text field c Set the flap to 0 on the Flap choice menu Set the flap to a value different than 0 Set the current speed to 100 then to a value greater than 100 d Enter a numerical value in the Pitch text field e Enter 0 10 20 30 45 60 as bank value g Enter a value between 1 1 in the Steering Roll text field AND a value between 20 20 in the Steering Pitch text field h Enter a value in the Fl Pth A text field AND a value in the Drift A text field 1 Enter a value in the Selected FPA text field EXPECTED RESULTS a The bank pointer is rotated according to the bank angle It turns solid amber if bank gt 35 b The slip skid bug displaces beneath the bank pointer It turns solid amber 1f bank angle gt 35 c The pitch limit 20 set by the aircraft model is visible If flap
8. are SPD LNAV and VNAV PTH b h The aircraft switches to user control mode the LNAV VNAV lights turn off the HOLD lights turn on the current speed track and altitude values are copied in the corresponding windows of the MCP On the PFD the selected bugs appear in white and the flight mode annunciations are SPD TRK HOLD and ALT On the PFD speed tape the selected speed bug points to 330 The current speed value does not change On the PFD compass the selected track bug points to 340 The current track does not change The selected altitude bug is parked at the bottom of the PFD altitude tape The current altitude does not change c e f The speed HOLD light turns off On the PFD the selected speed bug becomes magenta The plane accelerates to reach the selected speed The HDG TRK HOLD light turns off On the PFD the selected track bug becomes magenta the roll mode becomes TRK SEL The plane turns to reach the target track On the PFD the selected vertical speed bug appears in magenta and the selected altitude bug disappears The pitch mode becomes V S The plane starts to reach the target vertical speed On the PFD the selected vertical speed bug disappears the selected altitude bug appears in white and the pitch mode is set to ALT g The altitude HOLD light turns off On the PFD the selected altitude bug becomes magenta the pitch mode becomes FLCH SPD In IAS mode the speed displayed in MACH varies and conversely because speed conve
9. b c d 1 Open the ACT RTE LEGS CDU page and click anywhere in the ND on an unspecified point 2 Click on the second or third CDU left button 3 Deactivate then reactivate NAV mode 4 Click on EXEC CDU button 5 Repeat steps 1 and 2 then click on ERASE CDU button b c e 1 Stay on the ACT RTE LEGS CDU page Press the DEL button on the CDU and click on a waypoint of the route in the ND except the active waypoint 2 Click on EXEC CDU button EXPECTED RESULTS a c 1 The DLH456 string is appended in the scratchpad 2 DLH456 is set as target aircraft corresponding information appear in the ASAS TARGET CDU page b c 1 The WP4 string is appended in the scratchpad 2 WP4 is displayed as the right beacon selected b c d 1 The Latitude and longitude of the clicked point are appended in the scratchpad 2 Anew waypoint corresponding to the clicked point is added in the ND The modified route with the new waypoint is displayed with short dashes 3 The new waypoint is added as published waypoint 4 The insertion of the point is validated it becomes a point of the active route 5 Editions made after the last EXEC are erased the modified route and introduced waypoint disappear b c e 1 CLR is displayed in the scratchpad followed by the named of the chosen waypoint The modified route excluding the chosen waypoint is displayed with
10. half of the usual representation the lower half when it is parked on the upper end of the scale the upper half when it is parked on the lower end of the scale A data tag VCPA in the target aircraft information box indicates the relative altitude at CPA of the target aircraft A sign is displayed if the target aircraft is below own aircraft at CPA time A data tag TCPA indicates the time before reaching CPA because the extrapolation up to CPA does not show any conflict between subject and target aircraft This tag is displayed in the target aircraft information box 2 A conflict is now detected The rule of definition of a vertical conflict is vertical distance between aircraft lt VSA conflict threshold A new data tag TC replaces TCPA it indicates the time before conflict between subject and target This tag is displayed in the target aircraft information box The subject aircraft lateral position at conflict is indicated graphically red triangle TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable TEST CASE L PASS a L PASS c Function L PASS REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The top level application shall have been opened by clicking the cockpit picture in the HTML Page Previous tests CDU ASAS Other conditions None TEST DESCRIPTION a c 1 Start the simul
11. in the User Requirement Document This document is composed of e A validation protocol part which fixes the procedure used between both parts e A technical part that lists the tests defined by the validation protocol and the practical modalities environment means The tests themselves are described by the means of Test Description Sheets which are given in annex VALIDATION PROTOCOL Default categories The defaults observed during the validation phase are divided by mutual agreement in several categories Blocking the defaults belonging to this category corresponds to critical perturbations of the service that can result of a system stop or a functional blocking situation involving vital components of the system Those perturbations cannot provide a minimal service quality e Not blocking Major the defaults belonging to this category have a strong negative impact on the functions or results in an overloading work to provide the sufficient service Minor the defaults belonging to this category have a limited influence on the service quality and do not have a strong impact on the use of the system or concern only rarely use cases Correcting those defaults do not present an urgency character Final acceptance The final acceptance is pronounced when the following conditions are verified e no blocking default subsist e no major default subsists Tests scheduling Tests are performed on the te
12. in the HTML Page The what if item in the Assistance Level menu shall have been selected Previous tests MCP CDU ASAS Other conditions None TEST DESCRIPTION a Repeat test L SEP a e 1 Then change the hold values on the MCP without selecting them b Repeat test V SEP a e 1 Then change the hold values on the MCP c Repeat test L PASS a e 1 Then change the hold values on the MCP d Repeat test LS KEEP a e 1 Then change the hold values on the MCP EXPECTED RESULTS a d On the right of the baseline target information box whose values are based upon current flight parameters the same indications are displayed based on target values of the MCP This information constitute the what if assistance TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS ND interactivity Date Software V 1 0 version TEST CASE INTERACT a INTERACT e Function ND Interactivity REFERENCE DOCUMENT INITIAL CONDITIONS Initial state A cockpit shall have been opened Previous tests CDU ASAS Other conditions None TEST DESCRIPTION a c 1 Open the ASAS TARGETS CDU page and select the DLH456 symbol on the ND with the mouse 2 Click on the first left line select button b c 1 Open the BEACONS CDU page and select the WP4 beacon symbol on the ND 2 Click on the first right line select button
13. minimums reference is displayed at the bottom left of the altitude tape in amber The display becomes white The minimums altitude is displayed below the minimums reference with the same color j The landing altitude reference bar is displayed along the left edge of the altitude tape in amber The bar turns white k The barometric setting is displayed in amber L STD The display turns white The barometric value is displayed in amber L 30 12 IN The display turns white 1 The display shows L 30 12 IN when In is selected and L 1020 HPA when hPa is selected m QFE is appended to the display The altitude tape background turns green n Lis always displayed since there is only the left EFIS panel o The preselected baro setting is displayed below the baro setting 30 12 IN QFE TEST RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS PFD VSPD Vertical speed indications Date Document Software V 1 0 version Author Page TEST CASE PFD VSPD Function PFD vertical speed indications REFERENCE DOCUMENT INITIAL CONDITIONS testPFDND applet launched Previous Tests None Other conditions None TEST DESCRIPTION a Enter 300 in the Verti Speed text field Enter 300 b Enter 300 in the Sel VSpd text field c Set the vertical speed to 401 Set the vertical speed to 401 EXPECTED RESULTS a The speed pointer points to the top The p
14. reference to FPA on the MCP Click the UP and DO buttons to change the test flight path angle h Start the LateralPassingl scenario choose DLH456 as a target and set the ASAS mode to LP Click the LFT and RGT buttons to change the test track Change the HDG TRK reference to HDG Click the LFT and RGT buttons to change the test heading i Start the LongitudinalStationKeepingl scenario choose DLH456 as a target and set the ASAS mode to LSK Click the ACC and DEC buttons to change the test IAS Change the IAS Mach reference to Mach on the MCP Click the ACC and DEC buttons to change the test Mach Click the OPTIONS gt button to go to the options page and set the type of manoeuvre for LSK to GS Click the lt TARGETS button to go to the targets page and edit the 1 target Click the ACC and DEC buttons to change the test GS 3 Click the lt TARGETS button to go to the target page Edit a target by clicking its left button Click the OPTIONS gt button to go to the options page Exrecrep RESULTS a The display mode changes in a circular way from none to reduced extended and so on b The ASAS mode changes in a circular way from none to LSA VSA LP LSK and so on c The LP look ahead value 1 mn is displayed in blue at the right below the string PRED The look ahead value becomes 2 The LSK look ahead value 1 mn is displayed below the string PRED The look ah
15. the ND even when setting LSA VSA LP or LSK ASAS mode 2 In RED CDTI mode no CDTI information is represented on the ND even when setting LSA VSA LP or LSK ASAS mode 3 By default in EXT CDTI mode CDTI information is represented according to the selected ASAS mode The type of representation is absolute The default level of assistance is baseline 4 The following changes occur on the ND The CDTI information disappear The CDTI information appear but no conflict information is provided the conflict position is not represented any more and TC indication is replaced by TCPA d CDTI information is brought to the front of CDTI and therefore ND baseline e f The following configuration colours are applied white for extrapolated trajectories green for current conditions on selected aircraft CR current OD yellow for predicted conditions LCPA VCPA TCPA predicted OD and ATD predicted positions at CPA red for conflict conditions TC predicted conflict positions The following units are used NM for lateral distances LCPA OD ATD Flight Level for altitude VCPA Minutes for time values TCPA TC TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable TEST CASE L SEP a L SEP e Function L SEP REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The top level applicatio
16. this software will then be re used in the FREER2 environment in order to continue the ergonomics study further on Software Objectives The objectives of the CDTI evaluation software are as follows e Present new features added to the existing CDTI thus building an Enhanced CDTI also noted CDTI along with their different options e Enable a first evaluation of the above new features typically through Internet e Allow rapid prototyping of future enhancements e Allow re use of some modules in a different software environment typically for the connection of the cockpit displays to a flight simulator To reach these objectives and more particularly to conduct the evaluation this software put the users in a simulated in flight situation Different scenarios will be used to simulate different types of encounter between aircraft A scenario simulates only one encounter During this simulation the software Updates the position of the different involved aircraft Presents to the user pilot the information he will have on bord subject of the study Enables the pilot to interact with the aircraft like in a real aircraft and reacts accordingly Automatically guides the aircraft if they are not manually piloted by the user Validation Objectives The validation document is intended to describe the conditions and the means to validate the CDTI evaluation software according to the functionalities and the performance defined
17. traffic page is displayed The targets page is displayed The options page is displayed Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE CDU ACFT Function CDU aircraft page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 Previous TESTS OTHER CONDITIONS TesT DESCRIPTION a Go to the targets page then click the lt TRAFFIC button to display the aircraft page Choose an aircraft of the list and click the right button adjacent to its display mode Click the button again Click the button one more time b Choose an aircraft that is not already a target and click the corresponding left button c Click the lt TARGETS and then the lt TRAFFIC button to return to the aircraft page Click the PREV PAGE and NEXT PAGE buttons or use the PgUp PgDown keys to scroll through the aircraft list d Click the lt TARGETS button ExPECTED RESULTS a The display mode changes in a circular way from none to reduced then to extended and so on b The aircraft is set as a target at the head of the list and is edited in the target page c The 12 aircraft are distributed out of 3 pages d The targets page is displayed Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE CDU TGT Function CDU target page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cock
18. 123 PREVIOUS TESTS OTHER CONDITIONS Test DESCRIPTION a Go to the options page by clicking lt ASAS on the menu page and then OPTIONS gt on the targets page Set the sort mode to resp SSR callsign and distance by clicking the 1 button at the left until the mode is highlighted in cyan then go to the aircraft page b Click the 2 button at the left below the string SEP CIRCLE to highlight in cyan resp ON and OFF c Change the default target display mode by clicking the 3 button at the left Add some new targets d Restart the scenario go to the options page to change the default non target display mode then go to the aircraft page e See CDU TGT i f Click resp the lt TARGETS INCREMENT gt EXTENDED gt and REDUCED gt buttons Exrecrep RESULTS a The aircraft in the aircraft page are sorted according to the sort mode b The separation circle appears and disappears on the ND c The default target display mode is extended at start up The targets appear on the targets page with the correct display mode d The planes start progressively with the correct display mode e See CDU TGT i f The corresponding pages are displayed Conform Blocking Non Blocking DATE OBSERVATIONS Test CASE CDU INC Funcrion CDU increment page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 P
19. 30 60 and 90 seconds intervals The number of segments displayed depends on the range gt range 10 NM 1 segment gt range 20 NM 2 segments gt range greater than 20 NM 3 segments L m The labels indicating the wind direction and speed are set to the values adjusted in the scenario configuration file The wind arrow is oriented in the direction of the wind n 1 The points of the route are represented by a star if they correspond to a VOR or an ADF by a triangle otherwise 2 The symbols of VOR and ADF beacons that are not on the route now appear 3 The route symbols disappear the stars are transformed in a VOR or ADF symbols according to the type of the beacon 4 Every navigation point symbol disappear o t 1 The name of the selected beacon appears in the CDU scratchline 2 The VOR ADF data appear at the downer left or the downer right corner of the ND screen according to the CDU validation Those data are The type of the Beacon followed by L if left beacon or R if right beacon The beacon identifier For VOR beacons the DME distance from the subject aircraft to the navaid u The legs of the active route alternately appear and disappear u The modified route legs represented with dashes alternately appear and disappear w y The active waypoint data alternately appear and disappear upper right corner of the ND Those data are The name of the waypoint The Estimated Time
20. Deselect Aircraft O DU ASAS Multiple Selection nn d DU ASAS Modification of target e display mode Access to Traffic and f Options pages a DU ASAS DU ACFT CDU Aircraft page i VEN D TGT TGT d J ACFT Modification of aircraft display mode oe b C C C C C C C C O nia ai A d CDU TGT a Modification of display li CDU TGT b Modification of ASAS I CDU TGTO Modification of look ee O CD Modification of separation standard D D D U U U DU ACFT Scroll through the aircraft list U U U CDU TGT e Scroll through targets list LSA what if assistance CDU TGT g VSA what if assistance U TGT h LP what if assistance U TGT i LSK what if assistance C E Q ara 2 A U TGT j Access to Targets and Options pages T CDU Options page CDU OPT a Aircraft sort CDU OPT b Separation circle display C A J E R DU OPTO Default target display mode DU OPT d Default non target display mode CDU OPT e Selection of manoeuvre for LSK CDU OPT f Access to Targets Increment Reduced options and Extended options pages CDU INC CDU INC a CDU INC b VSA increments CDU INCO LPincrements CDU INC LSK increments ai Options pages page CDU RED a SSR display CDU RED b Callsign display Altitude display REDO CDU RED d Ground speed dis
21. EUROCONTROL EXPERIMENTAL CENTRE CDTI Evaluation System Validation Test Document Division Syst mes Techniques Date 22 07 99 Identification CS CISVCDTI DTS Software Version 1 0 Name Date Signature Author s P HAFENEDER N DURAND L HUYNH Approval None Customer E HOFFMAN K ZEGHAL Distribution List External Distribution e Karim ZEGHAL Eurocontrol EC e Eric HOFFMAN Eurocontrol EC Internal Distribution e PierreHAFENEDERCS CISI Project Manager e Thierry BLOND CS CISI Project Director e PierreREHBINDER CS CISI Quality Manager Document Change Form Paragraph Change Description Authors Draft 22 07 99 Initial Drafting P Hafeneder N Durand L Huynh Draft 18 05 04 Copy of document due to corruption of T Cooper original version Updated layout and formatting Changed name from Cv Evol CDTI 26 janv doc 4 ni 6 TABLE OF CONTENT SCOPE ario mienne its 3 TE identification RE A A a 3 1 2 Document Description dd 3 1 3 Requirement Trac DAI a RA AA 3 APPLICABLE AND RELATED DOCUMENTS sssennessesnnnnsossnnnnnssonennasoeenna 3 241 Applicable Documents esy i o 3 DI A A ne at 3 DEFINITIONS AND ABBREVIATIONS 000ssssnnnnsossnnnnonseennneooesennnsoseenennesoeeena 3 Sal R 72 pE 11 42 aid i E E 3 32k ADE UNS NA ee 3 GENERAL DESCRIPTION unn di As 3 os aces E sata ad 8 aha EI ni 3 4 2 Software Objectives as 3 Aid ValidationOb
22. Flight information System Electronic Flight information System Control Panel Flight Mode Annunciation Human Machine Interface Quality Assurance Manual Manuel d Assurance Qualit Mode Control Panel Mean Sea Level Requirements Traceability Matrix Matrice de Tracabilit des Exigenges User s Manual Manuel d Utilisation et d Exploitation Navigation Display Non Directional Beacon Project Quality Assurance Plan Plan d Assurance Qualit Project Software Development Plan Plan de D veloppement Logiciel Primary Flight Display Validation Tests Plan Plan de Test de Validation Radio Altitude Recommendation Requirement Very High Frequency VHF Omnidirectional Range GENERAL DESCRIPTION Context The CDTI evaluation system is a software dedicated to Man Machine Interface Prototyping It is used to evaluate the ergonomics of new functionalities as well as new presentation of data dedicated to civil pilots in the aircraft cockpit It takes place in the frame of a study conducted to evaluate the delegation of responsibility from the controller toward the pilot concerning the assurance of separation between aircraft This software will execute through the Internet environment This environment enables many users actual pilots to make their own evaluation alone without the constraint to organise centralised evaluation sessions needing complex and expensive logistics Parts of
23. HOLD mode MCPO SELmode y MCP a MCP AP values TT A 1 1 1 MCP f Switching SEL HOLD bad AR altitude SEL to HOLD MCP h Inputs always modifiable MCP i si to HOLD stop manoeuvre MCP Re engageLNAV MCP k Re engage VNAV MCP Disengage VNAV only TEST CARDS The tests cards describe the different scenarios belonging to the group of functionalities tested Main HMI Components RH 1 Main HMI Components Date gt Document Software V 1 0 Version Author Dage TEST CASE A E Function Main HMI components REFERENCE DOCUMENT Editeur de Structure N A UND UNS INITIAL STATE The navigator window is opened on the URL corresponding to the CDTI HTML Page Previous TESTS OTHER CONDITIONS Tesr DESCRIPTION A Click on the applet picture representing a 777 cockpit panel B Select the first scenario in the scenario list and select a subject aircraft in the aircraft list C Click on the cockpit button D Change the screen resolution E Click on the start icon in the control simulation panel F Click on the Air Situation Display Button Exrecrep RESULTS A The top level application window is opened B The selection of a scenario displays the list of aircrafts contained in the scenario in the aircraft list C The cockpit window is opened with the different elem
24. N to OFF set the altitude ALT to ABS set the altitude ALT to NO set the ground speed GS to OFF set the vertical speed trend V S TRENS to OFF set the velocity vector extrapolation time VEL VECT to 240 seconds set the past position to 10 set the past position to 0 5 In the TRAFFIC CDU page set an aircraft without activation delay to none CDTI mode 6 In the TRAFFIC CDU page set an aircraft with activation delay to reduced RED CDTI mode If necessary await the appearance of this aircraft on the ND Then stop and restart the scenario and set the same aircraft to reduced CDTI mode again b 1 Select the ASAS TARGETS CDU page and click on a surrounding aircraft on the ND 2 Validate the input on the CDU press one of the six left CDU buttons corresponding to an empty line Then set the CDTI mode of this new target aircraft to RED or EXT 3 Select other aircraft click on the ND and validate on CDU c 1 Click the pause button of the Top Level Panel when CDTI information overlaps ND information and observe the overlap 2 Click the pause button of the Top Level Panel when a target aircraft overlaps another target aircraft and observe the overlap EXPECTED RESULTS a 1 The aircraft appears with the following information corresponding to default reduced options its position r
25. ND applet Four windows are opened a PFD view a ND view a cockpit view do not destroy it and a control window Previous Tests None Other conditions None TesT DESCRIPTION Select resp THR THR REF HOLD IDLE SPD on the right Autothrottle mode choice menu of the PEDNDTestPanel window Select resp LEFT and RIGHT on the left choice menu Select resp HDG HOLD HDG SEL LNAV LOC ROLLOUT TO GA TRK SEL TRK HOLD ATT on the upper Roll mode choice menu Select resp LOC ROLLOUT LNAV on the lower Roll mode choice menu Select resp TO GA ALT V S VNAV PTH VNAV SPD VNAV ALT G S FLARE FLCH SPD FPA on the upper Pitch mode choice menu Select resp G S FLARE VNAV on the lower Pitch mode choice menu Select resp FLT DIR A P LAND2 LAND3 NO AUTOLAND on the AFDS Status choice menu EXPECTED RESULTS THR THR REF HOLD IDLE SPD is resp displayed in green on the PFD autothrottle mode area A Lor R precedes the mode HDG HOLD HDG SEL LNAV LOC ROLLOUT TO GA TRK SEL TRK HOLD ATT is resp displayed in green on the PFD engaged roll mode area LOC ROLLOUT LNAV is resp displayed in small white letters on the PFD armed roll mode area TO GA ALT V S VNAV PTH VNAV SPD VNAV ALT G S FLARE FLCH SPD FPA is resp displayed in green on the PFD engaged pitch mode area G S FLARE VNAV is resp displayed in small white letters on the PFD armed pitch mode area FLT DIR A P LAND2 LAND3
26. T PAGE PREV PAGE buttons or the PgUp PgDown keys to scroll through the waypoints list Exrecrep RESULTS a WP7 is inserted before WP2 The EXEC light is illuminated and the page title changes to MOD RTE LEGS lt ERASE is displayed in front of the 6 line at the left The insertion is canceled WP7 is removed the EXEC light is switched off and the page title returns to ACT RTE LEGS Its latitude and longitude are displayed in the scratchpad A new waypoint is created and appended after the last waypoint Its constraint is the same as the wavpoint above it The insertion is validated The new waypoint is visible on the ND and is part of the route b The constraint of the waypoint is changed to 200 FL100 c The waypoint symbol is greyed on the CDU The waypoint is removed from the route d There is 5 waypoints page in ACT mode and 4 waypoints page in MOD mode Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE CDU BCN Function CDU beacons page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 PREVIOUS TESTS OTHER CONDITIONS TEST DESCRIPTION a Go to the beacons page by clicking the BEACONS gt button on the menu page Enter the WP3 string Select the first left line button Enter the WP string Select the first left line button Press the Suppr Key b Enter the WP4 str
27. al deviation from VNAV Path because 400ft lt deviation lt 400ft 4 The upper half part of the pointer parks on the bottom of the scale and the value of the vertical deviation from VNAV Path is digitally displayed below the scale because deviation lt 400ft 5 The lower half part of the pointer parks on the top of the scale and the vertical deviation from VNAV Path is digitally displayed above the scale because deviation gt 400ft TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable TEST CASE ND CenMAP a ND CenMAP b Function ND baseline Data specific to Centered Map mode REFERENCE DOCUMENT INITIAL CONDITIONS Initial state A cockpit shall have been opened and a scenario shall be running Previous tests EFISCP Other conditions None TEST DESCRIPTION a b 1 Set the ND in centered mode thanks to the CTR selector in the EFIS Control Panel then select a right beacon click it on the ND and press the CDU upper right button to validate 2 Select a left beacon click it on the ND and press the CDU upper left button to validate EXPECTED RESULTS a b 1 The pointer head resp tail representing the bearing to resp from the selected right beacon is displayed large symbol 2 The pointer head resp tail representing the bearing to resp from the selected left beacon is displa
28. alue on the compass b The HDG TRK Reference label left green label on the top of the compass changes from HDG to TRK and reciprocally The numerical value on the top of the compass represents alternately the current heading or the current track according to the selected reference c The numerical value on the top of the compass is updated to represent the new heading or track value The compass orientation changes towards the new heading or track value d 1 The selected track bug is displayed on the inside of the compass rose 2 The selected track bug indicates the MCP selected track 3 The selected track bug alternately disappear and reappear e 1 The selected heading bug is displayed on the outside of the compass rose 2 The selected heading bug indicates the MCP selected heading 3 The selected heading bug alternately disappear and reappear f 1 The selected track line links the selected track bug to the airplane symbol 2 The selected track line alternately disappear and reappear g 1 The selected heading line links the selected heading bug to the airplane symbol 2 The selected heading line alternately disappear and reappear h The MAG TRU Reference label changes alternately to MAG and TRU i j The GS and TAS labels respectively indicates the Groundspeed and True Airspeed reached by the airplane k The position trend vector indicates the predicted positions at the end of
29. and enter a new value for the selected heading 2 Select alternately TRK and HDG reference h Set alternately the MAG TRU reference to MAG and TRU i j Select a new value for the aircraft speed on the MCP k Select a new heading track value on the MCP very different from the current one Select alternately the different range values available l m Visualise the WindBearing and WindSpeed variables in the configuration file corresponding to the scenario file called Param in the scenario directory n 1 Select on the RTE switch in the EFIS control panel select off the NAV switch 2 Select on the NAV switch 3 Select off the RTE switch 4 Select off the NAV switch o t 1 Select the Beacon selection page on the CDU press B and click on a VOR or ADF beacon on the ND 2 Validate the input on the CDU press either the upper left button for left beacon or the upper right button for right beacon u Select alternately on and off the RTE switch on the EFIS Control Panel v Inthe CDU RTE LEGS page tape the name of a navaid out of the current active route and insert it in the waypoint list Then select alternately on and offthe NAV switch on the EFIS Control Panel w y Select alternately on and off the RTE switch on the EFIS Control Panel EXPECTED RESULTS a The current heading pointer reversed white triangle points to the current heading v
30. ation on scenario LateralPassing2 Open a cockpit of subject aircraft AFR123 Through ASAS TARGET CDU page select aircraft DLH456 as target aircraft this is possible after reaching its activation delay and set it on EXT CDTI mode Choose LP ASAS mode through the DLH456 aircraft page 2 Choose alternately different values for the prediction time PRED CDU 4 right button b 1 Observe the ND 2 Stop the simulation and restart it on scenario LateralPassing1 Open a cockpit on subject aircraft AFR123 Through ASAS TARGET CDU page select aircraft DLH456 as target aircraft and set it on EXT CDTI mode Choose LP ASAS mode through the DLH456 aircraft page EXPECTED RESULTS a c 1 The oblique line is displayed this is a dotted straight line that binds the target aircraft and own aircraft A data tag OD in the target aircraft information box indicates the current and trend value of the Oblique Distance 2 The trend value of the oblique distance represents the predicted oblique distance in x minutes where x is the value chosen for PRED variable on the CDU b 1 A data tag CR indicates the relative closure rate in knots for the selected target aircraft The closure rate information is also represented by a vector emanating from the target aircraft The sign character of the closure rate is and the corresponding vector is in the oblique line opposite direction because targ
31. box c Set the altitude to O and the selected altitude to 1000 Set the altitude to 200 Set the altitude to 801 d Check the Meters checkbox f Set the altitude to 0 check and uncheck the RADIO BARO checkbox Enter 200 in the Min Alt text field g Enter a value in the Landing Alt text field h i Check uncheck the RADIO BARO checkbox Enter 0 in the Min Alt textfield 3 Set the altitude to 0 and the landing altitude to 182 Set the altitude to 500 k Select STD on the Baro setting choice menu and set altitude to 0 Set the altitude to 6000 Select QNH Set the altitude to 0 D Check uncheck the In hPa checkbox m Select QFE on the Baro setting choice menu o Select STD on the Baro setting choice menu EXPECTED RESULTS a The selected altitude bug appears The bug is parked at the top or bottom of the tape with only one half the bug visible b The selected altitude is displayed in green above the altitude tape c The selected altitude value is displayed above the altitude tape The selected altitude box is highlighted in white The white border disappears d The altitude is displayed in meters above the current altitude box e The current altitude is displayed in the box at the middle of the altitude tape f When the reference is BARO the BARO minimums pointer is displayed The pointer turns amber g The crosshatched area is shifted vertically according to the landing altitude value h i The
32. ckpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 Previous TESTS OTHER CONDITIONS ATETT Click the Menu button to display the menu page Click the button adjacent to the line lt ASAS to display the ASAS targets page Click the Menu button to return to the menu page Click the button adjacent to the line BEACONS gt to display the beacons page Click the Menu button to return to the menu page Click the button adjacent to the line lt RTE LEGS to display the route legs page The menu page is displayed The ASAS targets page is displayed The menu page is displayed The beacons page is displayed The menu page is displayed The route legs page is displayed Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE CDU ASAS Function CDU targets page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 Previous TESTS OTHER CONDITIONS TesT DESCRIPTION a b Click the lt ASAS button from the menu page to display the targets page Click on the CDU screen then type on the keyboard DLH456 then click on the first left line select Button Type DLH456 a second time and select the first left line button Press Suppr on the keyboard Type XXX and click a free line button Type YYY and click a free line button Press Suppr Press Suppr c Type CLR in
33. d PFD SPD n Speed bug PFD SPD o Selected flap VREF speed TRAER PFD Attitude and Steering Indications PFD ATT a Bank pointer PFD ATT b Slip skid bug a PFD ATT Pitch limitindication PFD ATT d Horizon line and pitch scale PED ATT e JBankscale PED ATT f Airplane symbol PFD ATT g Flight director bars PED ATT h AA MAO ci O angle director system status PFD STAT a Radio altitude PFD STAT b Approach reference PFD STAT Localizer pointer and scale PFD STAT d ee scale ee scale PFD STAT e PFD ALT PFD Altitude indications PFD ALT a Selected altitude bug PFD ALT b Selected altitude in meters PFD ALT Selected altitude PFD ALT d Current altitude in meters PFD ALT f BARO minimum e indication PFD ALT h Minimums reference PFD ALT i Minimums reference bar MW PFD ALT k Barometric setting PFD ALT 1 Barometric reference PFD ALT m QFE altitude reference PFD ALT n Barometric source er EO n setting PFD VSPD _ Vertical speed Cee eee IO PFD VSPD a Vertical speed pointer PFD VSPD b Selected vertical speed AW bug PFD VSPD Vertical speed PFD HDG PFD heading track indications PFD HDG a Current heading pointer PFD HDG b Selected track bug PFD HDG Track line PFD HDG d Digital selecte
34. d pe PED HDG e Heading track reference PFD HDG f Selected heading bug PFD HDG g North reference Navigation Display Tested function RH 1 2 2 2 Navigation Display Software version V 1 0 Comments gt The test instructions preceded by must be performed on the panel of the test tool gt The expected results preceded by must be observed on the display of the test tool Testing 1 Conform Test Description A Date 2 Cancelled Comments codes B Who 13 Not conform A B 1 213 IND MAFG Current Heading Pointer A Ka el Po Reference IND MAPO Current Heading Track __ IND MAP d Selected Track Bug __ IND MAP e Selected Heading Bag 1 ND MAP f Selected Track Line pp IND MAP g Selected Heading Line ND MAP h Magnetic True ee b DITTI NDMAP Groundspeed dS IND MAP j Truc Airspeed __ __ IND MAP k Position Trend Vector TTT ND MAP Wind Direction Wind A ER A Wind Aran J ____ ND MAP m Wind Arrow ND MAP n ND MAP 0 Left VOR ADF Selection Ta ND MAP p Left VOR ADF Ident ND MAP q Len VOR DME MOTA Selection ND MAP s ND MAP t GA Fi ina RE E Sa EA IND MAP u ActiveRoute ND MAPG Modified Roue ND MAP w Active waypoint PI CP IND MAP x Active waypoint ETA LL ND MAP y Active waypoint Distance To Go ND
35. ds and play with the selections proposed EXPECTED RESULTS a 1 Itis possible to activate multiple ASD 2 When changing the scenario the ASD windows already opened remain opened contrary to the cockpits and are updated so that they always represent the currently selected scenario to that purpose the scenario files are rescanned b ASD zoom is a logical zoom all items symbols lines fonts keep the same size when zooming or unzooming c A new cockpit window of the chosen aircraft is opened d 1 When clicking on the ASD the latitude longitude position is indicated in the status bar When clicking on an object symbol the indicated position is the one of the corresponding aircraft or navaid 2 The moving scale located in the status bar indicates distances 1 2 5 10 20 and 40 NM e The airways and sector boundaries are displayed as described in the corresponding files f True fixed past positions are represented g 1 The chosen aircraft is marked by a yellow circle that appears around its symbol it is told to be marked 2 It is possible to mark multiple aircraft 3 The chosen aircraft is not marked any more h 1 The mouse pointer becomes a cross indicating that the tracker tool is activated 2 Aline is attached between the two points The distance and bearing between those points is displayed in the status bar 3 The point which is an aircraft resp the mouse poi
36. ead value becomes 0 d The horizontal separation standard 10 Nm is displayed in magenta at the left in front of the 5 button The horizontal separation standard becomes 5 Check that the LP and LSK separation standards are also changed to 5 The vertical separation standard 10 FL is displayed in magenta at the left in front of the 5 button The vertical separation standard becomes 50 FL e The corresponding target informations are displayed f What if data are displayed in cyan at the line corresponding to the 3 button Lateral separation and time to go are computed according to the input heading The HDG column changes to TRK th Lateral separation and time to go are computed according to the input track g Vertical separation and time to go are computed according to the input vertical speed The V S column becomes FPA Vertical separation and time to go are computed according to the input flight path angle h The oblique distance is computed according to the input track or heading 1 The along track distance is computed according to the input IAS Mach or GS 3 The targets page is displayed showing all the targets The options page is displayed Poe REST Conform Blocking Non Blocking DATE OBSERVATIONS TEST CASE CDU OPT Function CDU options page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR
37. ed is displayed above the speed tape b c The predicted airspeed is indicated by the speed trend vector in black d The speed box displays the current airspeed The speed scale is centered on the current airspeed e The speed box border turns amber when airspeed is below 160 and turns white when airspeed is greater than 160 f The current Mach is displayed in green at the bottom of the speed tape g The maximum speed set to 340 by the aircraft model is represented by small red squares along the right edge of the speed tape h The maximum maneuvering speed appears white bar below the maximum speed red squares and disappears 1 The speed bug points the selected speed value Only one half the bug is visible at the top or bottom of the speed tape when the value is off scale 3 VI V2 VR are displayed if the pitch mode is TO GA the Reference Speeds checkbox is set and a numerical value is entered V1 is displayed at the top of the speed tape when the value is off the scale k The flap maneuvering speeds 1 5 15 20 25 30 are displayed when the altitude is lower than 20000 ft D VREF is displayed at the right edge of the speed tape m The minimum maneuvering is visible at the bottom of the speed tape along the rignt edge as a white bar above red squares n The minimum speed is visible as red squares below the minimum maneuvering speed o The VREF speed and the selected landing flap are displayed at the bottom of the speed tape TEST
38. ents composing it the PFD ND EFIS_CP MCP CDU D The cockpit window as all other windows adapts to the new resolution E The simulation starts in predefined guidance mode F The air situation display window is opened presenting an overall view of the aircraft Test Result VARIATION NOTED Conform Blocking Non Blocking DATE OBSERVATIONS Reproduction soumise accord pr alable Top level application RH 1 1 Top Level Application Date Document Software V 1 0 Version Author Page TEST CASE A G Funcrion Top Level Application REFERENCE DOCUMENT Editeur de Structure N A OND DNS INITIAL STATE The navigator window is opened on the URL corresponding to the CDTI HTML Page The top level application is opened by clicking the cockpit picture in the HTML RE Tesrs UTHER CONDITIONS 7 y D U N 6 A B Select the Lateral Passing 1 scenario in the scenario list C Select the AFR123 aircraft in the aircraft list D Click on the Cockpit Button Select the DLH456 aircraft Click on the Cockpit Button Select the AFR123 aircraft callsign Click on the Cockpit Button E Click on the air situation display button F Click on the Start Button Click on the Pause Button Click on the Pause Button Click on the Stop Button G Click on the Start Button Use the time ratio slider to change the time ratio from to 10 and from 10 to 0 1 I Use the t
39. epresented by the symbol white diamond its callsign its relative altitude the trend of its vertical speed climbing descending or steady Its velocity vector extending from the current position of the aircraft up to its extrapolated position at 120 min b 5 6 The following changes occur on the aircraft in reduced CDTI mode the SSR code appears the callsign disappears the altitude previously relative becomes absolute the altitude disappears the ground speed appears the arrow indicating vertical speed trend disappears the velocity vector doubles its length 10 past positions appear or will appear progressively behind the aircraft symbol The aircraft is then represented with the following information corresponding to default extended options its position represented by the symbol white diamond its callsign its SSR code its relative altitude its ground speed the trend of its vertical speed climbing descending or steady its velocity vector extending from the current position of the aircraft up to its extrapolated position at 120 min five past positions appear or will appear The following changes occur on the aircraft in extended CDTI mode the SSR code disappears the callsign disappears the altitude previously relative becomes absolute the altitude disappears the ground speed disappears the arrow indicating vertical speed trend disappears the velocity vector doubles its len
40. er 4 0 Windows NT4 Server Operating system with service pack 3 installed Ilog JViews Java Graphical Library Windows NT Workstation HP Vectra Pentium 400 256 Mo 9 Go Netscape 4 51 Web navigator from Netscape IE 5 0 Web navigator from Microsoft TEST JOURNALS Tests are performed according to the following tables RH 1 Main HMI Components RH 1 1 Top level application RH 1 2 Cockpit environment RH 1 2 1 Display options RH 1 2 2 EFIS components RH 1 2 2 1 Primary Flight Display RH 1 2 2 2 Navigation Display RH 1 2 2 3 Cockpit Display of Traffic Information RH 1 2 2 4 Enhanced CDTI RH 1 2 3 EFIS Control Panel RH 1 2 4 Mode Control Panel RH 1 2 5 Control Display Unit RH 1 2 6 Aircraft designation RH 1 3 Air Situation Display RF 1 Simulation of aircraft flights RF 1 1 Initialisation files RF 1 2 Predefined Guidance RF 1 3 User Interactive Control RS 1 Java Web RS 2 Implication of a development library RQ 1 Object Modelling RQ 2 Extensibility RQ 3 Internal Data RQ 4 Configuration RQ 5 Component appearance RD 1 Deliverables RD 1 1 Delivery schedule RD 1 2 Documentation Main HMI Components Tested function RH 1 Main HMI Components Software Version V 1 0 Comments Testing 1 Conform Test Description A Date 2 Cancelled Comments Id B Who 13 Not conform roma JA Launch the top level application __
41. et aircraft moves further away from own aircraft 2 The sign character of the closure rate is and the corresponding vector follows the oblique line because target aircraft gets closer to own aircraft TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable TEST CASE LS KEEP a LS KEEP c Function LS KEEP REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The top level application shall have been opened by clicking the cockpit picture in the HTML Page Previous tests CDU ASAS Other conditions None TEST DESCRIPTION a c 1 Start the simulation on scenario LongitudinalStationKeeping2 Open a cockpit of subject aircraft AFR123 Through ASAS TARGET CDU page select aircraft DLH456 as target aircraft this is possible after reaching its activation delay and set it on EXT CDTI mode Choose LSK ASAS mode through the DLH456 aircraft page 2 Choose alternately different values for the prediction time PRED CDU 4 right button b 1 Observe the ND 2 Stop the simulation and restart it on scenario LongitudinalStationKeeping1 Open a cockpit on subject aircraft AFR123 Through ASAS TARGET CDU page select aircraft DLH456 as target and set it on EXT CDTI mode Choose LP ASAS mode through the DLH456 aircraft page EXPECTED RESULTS a c 1 The along track line
42. gth 5 more past positions appear or will appear progressively behind the aircraft symbol all the past positions disappear The aircraft does not appear any more on the ND When the scenario is restarted the aircraft with an activation delay is not displayed any more even when in reduced CDTI mode until it is reactivated The callsign and or the SSR code of the selected aircraft appears in the CDU scratchline the label content depends on the display mode and the corresponding options previously set 2 Because only one target aircraft is selected ND CDTI information conforms with its CDTI mode when this mode is EXT the symbol of the aircraft is highlighted by a green diamond and ts callsign is displayed in green text in the target information box at the bottom of the ND when this mode is RED the only CDTI information that appears on the ND is the green diamond when this mode is none no CDTI information is displayed 3 All the selected target aircraft that are in RED or EXT CDTI mode are highlighted by a green diamond The callsign that appears in the target information box is the one of the first aircraft in the list of targets which is in EXT CDTI mode if any c 1 CDTI information is brought to the front of ND baseline information 2 The priority display of CDTI information follows the list order of selected aircraft TEST RESULT VARIATION NOTED Conform B
43. ies of a software product that enables it to fulfil the requirements either explicit or implicit Contractual part of the project in which the software is subject to a predefined set of tests The result of these tests directly influences the acceptance or rejection of the produced software by the customer Part of the project whose goal is to describe what is to be realised and not how 1t would be This part leads to the production of the Specification Document Part of the project whose goal is to describe how the product will be realised This part leads to the production of the Design Document Part of the project whose goal is to test if the product realised is conform to initial specifications This part leads to the production of the Validation Document Abbreviations ADIRS AGL ASL CDTI CDU CRC DAQ DC DME DSL DTS EFIS EFISCP FMA HMI MAQ MCP MSL MTE MUT ND NDB PAQ PDL PFD PTV RA Rec Req VHF VOR Air Data Inertial Reference System Above Ground Level Above Sea Level Cockpit Display of Traffic Information CDTI Control Display Unit Test Document Cahier de Recette Quality Assurance Document Dossier d Assurance Qualit Design Document Dossier de Conception Enhanced Cockpit Display of Traffic Information Distance Measuring Equipment Software Specification Document Dossier de Sp cification du Logiciel Test Reports Dossier de Tests Electronic
44. ime ratio slider to change the time ratio from 1 to 10 and from 10 to 0 1 K Click on the Lateral passing 2 scenario Click on the Start Button Click on the Quit Button Click on the Stop Button L Click on the Help button Click on the Quit button Exrecrep RESULTS A B The selection of the scenario displays AFR123 DLH456 in the aircraft list C The show cockpit button is now activated D The cockpit panel is opened on the subject aircraft AFR123 A second cockpit is opened on the subject aircraft DLH456 A third cockpit is opened on the subject aircraft AFR123 E The air situation display window is opened presenting an overall view of the aircraft F The simulation starts in predefined guidance mode Start button becomes greyed The simulation is paused The simulation is reactivated The simulation is stopped the start button becomes active G The same scenario is reactivated from start The simulation is speed up with a factor of ten The simulation is slowed down by a factor of ten K The lateral passing 2 scenario cannot be selected because a simulation is running The start button cannot be selected because a simulation is running The Quit button cannot be selected because a simulation is running The simulation is stopped L A window is opened containing a general help on the application A dialog box is opened that propose to quit the application if the answer is yes all the current
45. ing Select the first right line button c Type clr in the scratchpad Select the first left line button Select the right line button in front ofthe CONFIRM label d Type clr in the scratchpad Select the first right line button Select the right line button in front of the CANCEL label e a b c d Ie Enter the WP4 string and select the first right line button Stop and restart the simulation thanks to the top level panel Exrecrep RESULTS The beacon page is displaved Title Beacons The beacon WP3 is displaved right to the first left line button The message Unknown beacon WP is displayed in the scratchpad The message is cleared The beacon WP4 is displayed right to the first right line button The message Delete WP3 2 Confirm Cancel is displayed The message is cleared and WP3 is removed from the beacon list The message Delete WP4 Confirm Cancel is displayed The message is cleared and WP4 is still selected as the right beacon The beacon WP4 is displayed right to the first right line button Any selection made on the CDU is cancelled Result VARIATION NOTED Conform Blocking Non Blocking DATE OBSERVATIONS Primary Flight Display PFD FM PFD Flight Mode Annunciations Date Document Software V 1 0 Version Author Dage Test CASE PFD FM Function PFD Flight Mode Annunciations req RH 1 2 2 1 PFD FM a g REFERENCE DOCUMENT INITIAL CONDITIONS Launch the testPFD
46. is displayed this is a dotted line that bind the target aircraft and own aircraft representing the track the subject aircraft has to follow For simplification purpose the along track line is chosen as the straight line that binds the target aircraft and own aircraft A data tag ATD in the target aircraft information box indicates the current and trend value of the Along Track Distance 2 The trend value of the Along Track Distance represents the predicted Along Track Distance in x minutes where x is the value chosen for PRED variable on the CDU b 1 A data tag CR indicates the relative closure rate in knots for the selected target aircraft The closure rate information is also represented by a vector emanating from the target aircraft The sign character of the closure rate is and the corresponding vector is in the oblique line opposite direction because target aircraft moves further away from own aircraft 2 The sign character of the closure rate is and the corresponding vector follows the oblique line because target aircraft gets closer to own aircraft TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable TEST CASE WHAT IF a WHAT IF d Function WHAT IF REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The top level application shall have been opened by clicking the cockpit picture
47. is displayed in green on the PFD AFSD status area NO AUTOLAND is displayed in amber Test RESULT VARIATIONS NOTED Conform Blocking Not Blocking OBSERVATIONS PFD SPD_PFD Airspeed Indications Ds Moe Document Software V 1 0 version Author Dage TEST CASE PFD SPD Function PFD Airspeed Indications req RH 1 2 2 1 PFD SPD a 0 REFERENCE DOCUMENT INITIAL CONDITIONS testPFDND applet launched Previous Tests None Other conditions None TEST DESCRIPTION a Enter a 3 digits max numerical value in the Selected Speed text field of the PFDNDTestPanel window and press Return b c Type a 3 digits max numerical value in the Predicted Speed text field d Type a 3 digits max numerical value in the Current Speed text field e Input a number lower than 160 then input a number greater than 160 in the Current Speed text field f see d g Input 300 as current airspeed h Check then uncheck the Maneuvering Speeds checkbox 1 see a Input an off scale selected speed j Set the engaged pitch mode to TO GA Check the Reference Speeds checkbox Input numerical values in the V1 V2 VR text fields k Set the current speed to 200 Set the Altitude text field to 20000 or greater I Set the pitch mode to G S or FLARE Input a value in the VREF text field m n Set the current speed to 200 o seel EXPECTED RESULTS a The selected spe
48. itude to 100 f Enter 0 75 in the Loc text field g Set the localizer deviation to 1 and the altitude to 3000 Set the altitude to 100 Clear the Loc text field Set the loc value to 1 and the altitude to 0 EXPECTED RESULTS a The radio altitude box shows 100 in amber 1000 in white disappears b The ILS identifier approach front course and DME distance are displayed c The localizer scale is white and the pointer is solid magenta The pointer turns transparent The scale turns amber and the pointer flashes d The marker beacon appears and flashes in cadence with the ILS identifier e The glideslope scale is white and the pointer is solid magenta The pointer turns transparent The scale turns amber and the pointer flashes f The expanded localizer scale appears g The rising runway symbol is not displayed The symbol appears and its stem flashes The symbol disappears The symbol appears just below the airplane symbol TEST RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS PFD ALT PFD altitude indications Date Document Software V 1 0 version Author Page d TEST CASE PFD ALT Function PFD altitude indications REFERENCE DOCUMENT INITIAL CONDITIONS testPFDND applet launched Previous Tests None Other conditions TesT DESCRIPTION a Type a number in the Selected Alti text field Enter an off scale value b Check uncheck the Meters check
49. jecives nn i ew EEEE areali 3 VALIDATION PROTOCOL iii f Sadi 3 Dal Defaultcate 151 A a a a al aka ta 3 Si Final acceptance oi fasta ated alal aio 3 DAL A at 3 DA EN O O aoa 3 3 5 2 ls A le ad 3 5 6 Elemerntidestnpliofii Rollei A ne alia 3 Vol AP A ERE 3 50 2 Windows NITA SS VE rr is 3 56 3 Mog Te iii ah 3 5 6 4 Windows NT Workstation 3 50 35 eT nL STE laicale clio nil ie 3 260 MEDIO A A A Aus e Mm aes 3 TEST JOURNALS scssestscstessadistossonsssnssassahenetuncnssvadesdedeesonsesasshededenaseateleedesensnieceienss 3 6A Main HMI Components carraio ebete 3 6 2 Top level application ai ai 3 6 3 Cockpit Environment soriana lili 3 6 4 Display Options A ja A 3 6 5 Control Display Unit i a RRE 3 6 6 Aircraft and Beacon designation Error Bookmark not defined 6 Primary Flight Display ias ds 3 6 8 Navigation DISPARA asa a he ates 3 6 9 Cockpit Display of Traffic Information eee eee eee 3 6 10 Enhanced Cockpit Display of Traffic Information 3 Gal Air Situatio Disp o 3 ES A Ta a ad 3 6 13 Mode COME o ean ae tunika 3 E TEST CARDS iii AR G Sesaat iS Siras 3 7 1 Mam AMI Components id 3 12 Jl Oplevel applicaiOna E tata 3 7 3 Cockpit Enyir nment Ta e 3 EE Display Options asia alal 3 TS Control Display United 3 7 6 Aircraft and Beacon designation Error Bookmark not defined T A Pimaty Flight Deplano 3 LA Navigation DA e a rata dk 3 7 9 Cockpi
50. l the status are selected j 1 The trajectory of the chosen aircraft is represented routes legs are represented as segments linking the different waypoints the altitude and the estimated time of arrival over each way point are indicated under the waypoint name 2 It is possible to display multiple trajectory k 1 The Velocity Vectors dialog box appears allowing the configuration of the velocity vectors look ahead 2 The Past Positions dialog box appears allowing the configuration of the number of past positions represented 3 The Sizes and Colors Configuration dialog box appears allowing the configuration of the following items Symbol width Aircraft labels font size Waypoints labels font size Trajectories width and color Airways width and color Sector boundaries width and color Sectors fill color Velocity vectors width 4 The Navaid Display dialog box appears allowing the configuration of the display on off for all types of navaid NDB VOR DME Published Waypoint TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS EFIS Control Panel RH 1 2 3 EFIS CP Date Document Software version Author Dage TEST CASE EFISCP Function EFIS Control Panel REFERENCE DOCUMENT INITIAL CONDITIONS Initial state A cockpit shall have been opened and a target aircraft selected Previous tests CDU O
51. lay options page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 PREVIOUS TESTS OTHER CONDITIONS Tesr DESCRIPTION a b c d e f g j See CDU RED a b c d e f g j h Highlight in cyan resp ON and OFF by clicking the 3 button at the right 1 Start the LateralSeparationAssurancel scenario a conflict will occur Go to the extended options page and highlight in cyan resp ON and OFF by clicking the 4 button at the right Exrecrep RESULTS a b c d e f g j See CDU RED a b c d e f g j h i Verifv on the ND that the options are taken into account Conform Blocking Non Blocking DATE OBSERVATIONS Test CASE CDU RTE Funcrion CDU route legs page REFERENCE DOCUMENT INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario ThirteenAircraft with subject aircraft AFR123 Previous TESTS OTHER CONDITIONS Test DESCRIPTION a Click WP7 on the ND then click the line in front of WP2 on the CDU Click the lt ERASE button Click an unspecified point in the ND Click the button below the last waypoint Click the EXEC button b Type 200 FL100 in the scratchpad then click the right button of the line WP2 c Click the DEL button or type CLR in the scratchpad then click a waypoint line on the CDU or a route waypoint symbol on the ND Click the EXEC button d Add many waypoints to the route then click the NEX
52. locking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable Enhanced Cockpit Display of Traffic Information Scenario RH 1 2 2 4 Enhanced CDTI Navigation Display Enhanced CDTI indications ES Document Software version TEST CASE CDTI a CDTI e Function CDTI REFERENCE DOCUMENT INITIAL CONDITIONS Initial state A cockpit shall have been opened a scenario with conflict shall be running Previous tests CDU ASAS Other conditions None TEST DESCRIPTION 1 Go to ASAS TARGET CDU page and select a target aircraft Modify the ASAS mode and observe the ND 2 Select RED CDTI mode for this target Modify the ASAS mode and observe the ND 3 Select EXT CDTI mode for this target Modify the ASAS mode and observe the ND 4 In the EXTENDED OPTIONS CDU page perform the following changes set the ASAS indications ASAS IND to OFF set the ASAS indications to ON and the conflict indications CONFLICT IND to OFF a c d Click the pause button of the Top Level Panel when CDTI information overlaps CDTI information and observe the overlap e f Select alternately the different ASAS modes and observe colours and units of information displayed on the ND EXPECTED RESULTS a c 1 By default CDTI and ASAS modes are none No CDTI information is represented on
53. ly opened Windows are closed cockpit panels air situation display top level application Test Result VARIATION NOTED Conform Blocking Non Blocking DATE OBSERVATIONS Cockpit Environment RH 1 2 Cockpit Environment Date Document Software V 1 0 Version Author Dage TEST CASE A C Function Main HMI components REFERENCE DOCUMENT N A OND DNS INITIAL STATE The navigator window is opened on the URL corresponding to the CDTI HTML Page phe top level application panel is opened OTHER CONDITIONS TEST DESCRIPTION A Select the Lateral Passing 1 scenario in the scenario list Select the AFR123 aircraft in the aircraft list Click on the Cockpit Button B Click on the cockpit menu bar entry and the select Quit C Select the DLH456 aircraft in the aircraft list and click on the show cockpit button Click on the start button Try to change a target value on the MCP when the simulation time is less than 2 minutes try again after this delay Click on the cockpit menu bar entry and the select Quit ExPECTED RESULTS A Open a cockpit on Lateral Passing 1 scenario B Close the current cockpit C Open a cockpit on Lateral Passing 1 scenario The status of the aircraft not started frozen or stopped is indicated on the cockpit here the status is STOPPED Start the simulation The status becomes NOT STARTED The MCP is inhibited while the activation delay of the ai
54. n shall have been opened by clicking the cockpit picture in the HTML Page Previous tests CDU ASAS Other conditions None TEST DESCRIPTION 1 Start the simulation on scenario LateralSeparationAssurance2 Open a cockpit of subject aircraft AFR123 Through ASAS TARGET CDU page select aircraft DLH456 as target aircraft and set it on EXT CDTI mode Choose the LSA ASAS mode through the DLH456 aircraft page 2 Set the LSA conflict threshold fifth left button on the CDU to a positive value higher than LCPA EXPECTED RESULTS a e 1 The lateral positions at closest point of approach CPA of subject and target aircraft are indicated graphically yellow triangle for subject aircraft yellow diamond for target A data tag LCPA in the target aircraft information box indicates the lateral distance between subject and target aircraft at CPA A data tag TCPA indicates the time before reaching CPA because the extrapolation up to CPA does not show any conflict between subject and target aircraft This tag is displayed in the target aircraft information box The target aircraft lateral trajectory is extrapolated up to the CPA This extrapolation is represented by a dotted line between the current position of target aircraft and its position at CPA 2 A conflict is now detected The rule of definition of a lateral conflict is lateral distance between aircraft lt LSA conflict threshold A new data tag TC
55. nter is updated to follow the aircraft position resp the mouse line distance and bearing are updated accordingly 4 The tracking line disappears i 1 The following information appear in aircraft labels Fist line Callsign and SSR code separated by They are specified in the scenario file Second line Relative altitude in FL Vertical speed trend climbing descending steady indicated by an arrow climbing vertically descending vertically or horizontal Ground Speed value in knots divided by 10 The ASAS equipped aircraft are notified by a black label border ASAS equipment on off are specified in the scenario file 2 Itis possible to put the labels anywhere in the ASD with the mouse After a label has been moved it stays at the same position relative to the aircraft symbol 3 Itis possible to change the status dynamically The aircraft status is indicated by the colour of the label assumed white callsign and white label to be assumed white callsign and pink label transferred mustard color callsign and white label not concerned black callsign and black label The default value used for aircraft status is Assumed 4 The Aircraft Display dialog box appears presenting the different aircraft status It is possible to displav not display aircraft depending on the status by selecting deselecting each status in the Aircraft Display dialog box By default al
56. of Arrival on this waypoint Its Distance To Go TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable a a TEST CASE ND ExMAP a Function ND baseline Data specific to Expanded Map mode REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The test tool shall be started Previous tests None Other conditions None TEST DESCRIPTION 1 After visualising the ClimbDescentThreshold variable in the general parameters configuration file file called GeneralParam txt in the Source directory set the Vertical Speed to a value greater than ClimbDescentThreshold 2 Set the Vertical Speed to a value lower than ClimbDescentThreshold 3 Set current and VNAV Path altitudes to arbitrary values with a difference lower than 400 feet 4 Set current and VNAV Path altitudes to arbitrary values respecting the following condition VNAV Path altitude current altitude is lower than 400 feet 5 Set current and VNAV Path altitudes to arbitrary values respecting the following condition VNAV Path altitude current altitude is greater than 400 feet EXPECTED RESULTS 1 The VNAV Path Pointer is not displayed the aircraft is not descending 2 The VNAV Path Pointer appears the aircraft is descending 3 The pointer indicates on the scale the vertic
57. oftware Specification Document DR2 The Software Design Document DR3 The requirement numbers referred to throughout this document as well as any additional information related to requirements traceability are described in the Requirements Traceability Matrix DR4 APPLICABLE AND RELATED DOCUMENTS Applicable Documents The rules advises recommendations or requirements contained in the following documents shall apply in the scope on this document DA1 Manuel d Assurance Qualit CS Cisi CIS SYSQUAL MAQ 01 DA2 Les Proc dures du Svst me Qualit CISV SYSQUAL PSQ 01 23 DA3 CDTI Evaluation System User Requirement Document CDTI ES URD V 1 4 19 10 98 EUROCONTROL Experimental Centre DA4 Syst me d valuation CDTI Proposition CS CISI Affaire 148IRR V 1 0 02 11 98 CS CISI Related Documents Related documents are those to which reference is made in this document They are guiding material helping in the understanding or in the application of this document DR1 Boeing 777 Operation Manual DR2 Software Specification Document CS CISVCDTI DLS 01 DR3 Software Design Document CS CISI CDTI DC 01 DR4 Requirements Traceability Matrix CS CISI CDTI MTE 01 DEFINITIONS AND ABBREVIATIONS The following definitions and abbreviations are used in the scope of this document Definitions Software Quality Acceptance Specification Design Validation The set of characteristics and propert
58. ointer points to the bottom b The speed bug appears in magenta c 401 is displayed below the vertical speed tape in green 401 is displayed at the top of the tape TEST RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS Scenario PFD HDG PFD heading and track Date indications Document Software V 1 0 version Author Page TEST CASE PFD HDG Function PFD heading and track indications REFERENCE DOCUMENT INITIAL CONDITIONS testPFDND applet launched Previous Tests None Other conditions None TEST DESCRIPTION a Enter 20 in the Heading text field b Check then uncheck the HDG TRK checkbox and enter 30 in the Sel Track text field c Enter 40 in the Track text field then click the Heading text field and press RETURN to re set the heading value to 20 d e Check uncheck the HDG TRK check box f Uncheck the HDG TRK check box g Check uncheck the MAG TRU checkbox EXPECTED RESULTS a The heading pointer is always at the top of the compass The compass rotates to bring the number 2 below the pointer b The selected track bug appears in magenta on the inside of the compass c The track line points to the number 4 d The digital value of the selected track or heading is displayed e A T or H is displayed according to the HDG TRK reference f The selected heading bug is displayed in magenta and points the numbe
59. pit is opened on scenario ThirteenAircraft with subject aircraft AFR123 Previous TESTS CDU ASAS OTHER CONDITIONS TEST DESCRIPTION a Go to the targets page and click the left button of the first target to edit it Click the button adjacent to the display mode line the 1 button at the right b Click the button adjacent to the ASAS mode line the 2 button at the left c Set the ASAS mode to LP Type 2 in the scratchpad then click the button adjacent to the look ahead line Set the ASAS mode to LSK Type 0 in the scratchpad then click the button adjacent to the look ahead line d Set the ASAS mode to LSA Type 5 in the scratchpad and click the button adjacent to the separation standard line Set the ASAS mode to LP and then to LSK Set the ASAS mode to VSA Type 5000 in ft in the scratchpad and click the button adjacent to the separation standard line e Click the NEXT PAGE PREV PAGE buttons or the PgUp PgDown keys to scroll through the targets f Start the LateralSeparationAssurancel scenario choose DLH456 as a target and set the ASAS mode to LSA Click the LFT and RGT buttons to change the test heading Change the HDG TRK reference to TRK on the MCP Click the LFT and RGT buttons to change the test track g Start the VerticalSeparationAssurancel scenario choose DLH456 as a target and set the ASAS mode to VSA Click the UP and DO buttons to change the vertical test speed Change the VS FPA
60. play MA ka RE ca CDU RED e Vertical speed trend display CDU RED f Velocity vector display CDU RED g Past positions display CDU RED h Access to Targets and Options pages Re N page ExT Ld Callsign display EXT le zz CDU EXTO Altitude display Ground speed displav co Vertical speed trend EXT e display ii daa in CDU EXT h ASAS display CUENTA ASAS confit dipl II CORO BCN Access to Targets and Options pages CDURTE CDU Rewte legs Td CDU RTE a Add a waypoint CDU RTE b Modification of waypoint constraint CDU RTEO Delete a waypoint PP CI CV 0 l CDU Beacon page leo pr BCN b CDU Right beacon let Ly anu BCN CDU Left beacon deselecting CDU BCN d CDU Right beacon deselecting Primary Flight Display Function tested RH 1 2 2 1 Primary Flight Display Software Version V 1 0 Comments Testing 1 Conform Test Codes Description A Date 2 Cancelled Comments 9 B Who 3 Not conform A B 1 2 3 Free I O Annunciations PFD FM a Autothrottle Mode Do PFD Airspeed Indications PFD SPD a Selected Speed PFD SPD b c Speed Trend Vector Predicted Airspeed PFD SPD d PFD SPD g PFD SPD h Maximum maneuvering speed PFD SPD f PFD SPD e Color below minimum speed speeds speeds speed PFD SPD m Minimum maneuvering spee
61. r 0 g The north reference is displayed MAG or TRU TEST RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS Navigation Display RH 1 2 2 2 Navigation Display Date Baseline indications Software V 1 0 version TEST CASE ND MAP Function Navigation Display Data common to Expanded and Centered Map Modes REFERENCE DOCUMENT INITIAL CONDITIONS Initial state A cockpit shall have been opened and a scenario shall be running The test tool shall be started Previous tests MCP CDU Other conditions None TEST DESCRIPTION a Switch the HDG TRK Reference until the left green label on the top of the compass is HDG Enter a new value for the headina b Press several times the HDG TRK Reference switch on the MCP Set current heading and track at different values and change alternately the HDG TRK reference switch c Select a new value for the current heading or track on the MCP d 1 Select TRK reference on the MCP 2 Select a new value for the track on the MCP 3 Select alternately HDG and TRK reference on the MCP e 1 Select HDG reference on the MCP 2 Select a new value for the heading on the MCP 3 Select alternately TRK and HDG reference on the MCP f 1 Select TRK reference and enter a new value for the selected track 2 Select alternately HDG and TRK reference g 1 Select HDG reference
62. rcraft 2min hasn t been reached When the delay is reached the indication NOT STARTED disappears Close the current cockpit This does not stop the simulation Test Result VARIATION NOTED Conform Blocking Non Blocking DATE OBSERVATIONS Reproduction soumise accord pr alable Display Options RH 1 2 1 Display Options Date gt Document Software V 1 0 Version Author Page O TEST CASE A C Function Display Options REFERENCE DOCUMENT Editeur de Structure INITIAL CONDITIONS INITIAL STATE A cockpit is opened on scenario Lateral Passing 1 with subject aircraft AFR123 PREVIOUS TESTS OTHER CONDITIONS TEST DESCRIPTION A select the Display Format entry menu bar B select the Representation Type entry menu bar C select the Assistance Level entry menu bar ExPECTED RESULTS A the menu presents Boeing 777 and Airbus 340 entries Airbus 340 is grayed B the menu presents Absolute and Relative entries Relative is grayed C the menu presents Baseline What if Scale of Effect Advisory All entries are grayed except Baseline Test Result VARIATION NOTED Conform Blocking Non Blocking DATE OBSERVATIONS Control Display Unit RH 1 2 5 Control Display Unit Date Document Software V 1 0 Version Author Dage TEST CASE CDU MENU Function CDU menu page REFERENCE DOCUMENT INITIAL STATE A co
63. replaces TCPA it indicates the time before conflict between subject and target This tag is displayed in the target aircraft information box The subject aircraft lateral position at conflict is indicated graphically red triangle TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise a accord pr alable TEST CASE V SEP a V SEP d Funcrion V SEP REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The top level application shall have been opened by clicking the cockpit picture in the HTML Page Previous tests CDU ASAS Other conditions None TEST DESCRIPTION 1 Start the simulation on scenario VerticalSeparationAssurance2 Open a cockpit of subject aircraft AFR123 Through ASAS TARGET CDU page select aircraft DLH456 as target aircraft and set it on EXT CDTI mode Choose the VSA ASAS mode through the DLH456 aircraft page 2 Set the VSA conflict threshold fifth left button on the CDU to positive a value higher than the absolute value of VCPA EXPECTED RESULTS a e 1 The current and CPA altitudes of subject and target aircraft are positioned on a scale indicating 50 FL deviation from the subject aircraft current altitude When an altitude exceeds display range as it happens here at the beginning and the end of the scenario its pointer parks on the corresponding end of the scale The pointer is then only the
64. revious TESTS OTHER CONDITIONS Tesr DESCRIPTION a Add a target and set its ASAS mode to LSA Go to the increment page and set the what 1f heading increment to 1 the scale of separations heading increment to 2 Change the HDG TRK reference to TRK on the MCP then set the what if track increment to 3 the scale of separations track increment to 4 Edit the target b Set the ASAS mode to VSA Set the what if V S increment to 5 the scale of separations V S increment to 6 Change the V S FPA reference to FPA on the MCP then set the what if FPA increment to 7 and the scale of separations FPA increment to 8 Edit the target c Set the ASAS mode to LP Change the HDG TRK reference to HDG then set the what 1f heading increment to 9 the scale of separations heading increment to 10 Change the HDG TRK reference to TRK on the MCP then set the what if track increment to 11 the scale of separations track increment to 12 Edit the target d Set the ASAS mode to LSK Set the what if IAS increment to 13 the scale of separations IAS increment to 14 Change the IAS Mach reference to Mach on the MCP then set the what if Mach increment to 0 1 and the scale of separations Mach increment to 0 2 Go to the options page and change the type of LSK manceuvre to GS Return to the increment page and set the what 1f GS increment to 15 the scale of separations GS increment to 16 Edit the target e Click resp the lt TARGETS and OPTIONS gt button
65. rsions depend on altitude The MCP altitude value is rounded to the hundredth just as the PFD target altitude value But there is no round off on the magnifying glass of the PFD When the target altitude is reached The altitude HOLD light turns on the PFD selected altitude bug becomes white and the pitch mode returns to ALT d The selected speed is displayed in MACH The MCP shows the selected heading value On the PFD the selected track bug disappears and the selected heading bug appears On the PFD the steering indications are displayed The flight path vector appears On the PFD the selected flight path angle symbol appears and the pitch mode becomes FPA The plane starts to climb On the PFD the selected flight path angle symbol disappears the selected altitude bug appears in white and the pitch mode becomes ALT h On the PFD the selected speed bug moves and the aircraft immediately manoeuvre to reach the target speed On the PFD the selected heading bug moves and the plane immediately turns to reach the target heading On the PFD the selected altitude bug moves and the plane immediately manceuvre to reach the target altitude i The manceuvre stops j The LNAV light is switched on The aircraft automatically follows its track but its altitude remains under user control k The VNAV light is switched on The aircraft returns in predefined guidance mode 1 The VNAV light is switched off The user can control the aircraft altitude
66. s are up the pitch limit is visible at low speed lt 100 defined in a configuration file d The horizontal line and pitch scale are shifted according to the pitch value e The bank pointer points the corresponding mark f The airplane symbol is fixed g The steering roll and pitch bars appear they are not visible if one of the above fields are empty h The flight path vector appear it is not visible if one of the above fields is empty 1 The selected flight path angle symbol appears TEST RESULT VARIATIONS NOTED Conform Blocking Not Blocking DATE OBSERVATIONS PFD STAT PFD Autopilot Flight director ST IA Svstem Status version Test CASE PFD STAT Function PFD Autopilot Flight director System Status REFERENCE DOCUMENT INITIAL CONDITIONS testPFDND applet launched Previous Tests None Other conditions None TesT DESCRIPTION a Enter 100 in the Altitude text field then enter 1000 then 2500 b Check the ILS checkbox enter an ILS name in the Ident text field a numerical value in the Front course and DME Dist text fields c Set the altitude to 3000 Enter 1 in the Loc text field Set the deviation to 2 6 Set the altitude to 100 d Select IM MM or OM on the choice menu at the right of the Glideslope text field e Set the altitude to 3000 Enter 1 in the Glideslope text field Set the deviation to 2 6 Set the alt
67. short dashes 2 The suppression of the waypoint is validated it doesn t belong to the active route any more TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable Air Situation Display IRH 1 3 Air Situation Display Date Document Software version Author Page d TEST CASE ASD Function Air Situation Display REFERENCE DOCUMENT INITIAL CONDITIONS Initial state The scenario controller panel shall have been opened Previous tests None Other conditions None TEST DESCRIPTION a 1 Select a scenario and open an ASD by clicking on the corresponding picture Then try to open another one 2 Select another scenario of the list and observe an ASD window b Play with the zoom buttons Zoom In Zoom out Rectangular Zoom In Rectangular Zoom Out and then click on Fit To Size button c Right click on an aircraft symbol in the ASD then select Open Cockpit in the menu d 1 Left click anywhere in the ASD 2 Zoom and unzoom while looking at the scale in the status bar e Observe an ASD window and have a look at the SectorsFile txt and AirwaysFile txt in the source directory f Run the simulation and look at the aircraft in an ASD window g 1 Right click on an aircraft symbol in the ASD then select Mark Unmark in the menu
68. sing the mouse button to set the selected speed to 330 Click the left part of the crown of the HDG TRK SEL button without releasing the mouse button to set the selected track to 340 Click the left part of the crown of the altitude SEL button without releasing the mouse button to set the selected altitude to 22000 c e f Click the speed SEL button Click the HDG TRK SEL button Click the V S FPA button then drag the V S FPA rotator vertically to set the vertical speed to 1200 h Click the altitude HOLD button to stop the climb g Click the altitude SEL button Click alternately the IAS MACH switch end on IAS Click the altitude HOLD button Click the altitude SEL button again d Click the IAS MACH switch Click the HDG TRK switch Set the F D switch to ON Click the V S FPA switch Drag the V S FPA rotator to set the selected flight path angle to 2 h Click the altitude HOLD button to stop the climb h Click the crown of the speed SEL button without releasing the mouse button Click the crown of the HDG TRK SEL button without releasing the mouse button Click the altitude SEL button then click the crown of the button without releasing the mouse button i Repeat the operations described in h and while the plane is maneuvering click the HOLD button 3 Click the LNAV button 3 Click the VNAV button k Click one of the V S FPA or altitude buttons EXPECTED RESULTS a The A P LNAV VNAV lights of the MCP are on The PFD flight mode annunciations
69. st plateform described in chapter The tests are executed in compliance with the present validation test document The sequence of operations is tracked by the use of advance charts forms lists The defects found are documented in Observing Cards where the category classification described in appears Test schedule The test activity advance timetable is in keeping with the following table The requirements and the codification RH are extracted from the Traceability Matrix Document CO A CE PS RTE IE E AS E EE EH EH L CR H ETH AS E AS RS RS Sa D A RETZ remet Guide AS CE H CU AS CE AUS CO AUS CO AS oom LL IG AN RTT see A A Environment This chapter describes the different elements composing the test environment i e the elements required for the execution of the tests described in the following chapter For each element the responsible of the furniture is mentioned This responsibility does not exclude the contribution of the other part for the preparation of the components included in the composition of those elements Test platform description ELEMENTS NECESSARY TO PERFORM THE TESTS HTTP server CS CS provide an http server that will serve the application Windows NT Server Client station CSP Windows NT Workstation CS Netscape 4 51 CS G OE ETT CS REA CS ____________ Element description HTTP server Dell Pentium P RO 200 128 Mo 9 Go Internet Information Serv
70. t Display of Traffic Information i 3 7 10 Enhanced Cockpit Display of Traffic Information 3 TEL Air Situation Display A A a a tal 3 TA ERLS Control Panels osn a e a e ad 3 PII Mode Control PACE a leal 3 8 TESTS FOLLOW UP site ha 3 9 MONITORING TABLE OF BLOCKING INCIDENTS see 3 10 FORMS USED FOR TESTS PERFORMING sssnosnnenzznsensnsensensenzsnnennenneena 3 SCOPE Identification Name CDTI Evaluation System Name Validation Test Document Reference 148IRR Identification CS CISI CDTI CV Customer EUROCONTROL Version Draft Experimental Centre Date 22 07 99 Document Description This Validation Document is composed of the following chapters Chapter introduces this document Chapter lists the applicable and related documents Chapter gives some definitions Chapter describes the context and the objectives of the software Chapter 5 describes the validation protocol that fixes the procedure to be followed Chapter 6 contains the journals used to report the result of each test Chapter 7 contains cards that describe the test scenarios Chapter 8 provides forms that allow tests follow up Chapter 9 presents all the forms used in validation procedure Requirement Traceability The traceability of the requirements is an identified need cf req RD 1 2 DOC e It is realised throughout the code and the following documents This Software Specification Document The S
71. tal Rate Advance Valid 6 5 5 3 4 6 4 ae a re O EA o ce di AE ina i B id KI EM A ee G KT a UE non MEA a A SAA po YAA yes d 6 Mt 4 Cancelled Performe NUMBER OF TESTS OK Not OK Not performe d 2 3 ESE A ES ME Y y eni di KATI HE AAA ly L L AA y py ETA py y yoo __ y EE IM ly 1 Z A me EE NO Ez m5 aa MONITORING TABLE OF BLOCKING INCIDENTS cident Date of Object Function not exami ate o Mridsat I oping t concerned P a A Validation Date
72. the scratchpad Select the first left line button Select the right line button in front ofthe CONFIRM label d Type the callsigns of each other aircraft involved in the scenario and use all the 5 left line Select buttons then press PgDown and use the 5 left line buttons of the second aircraft page e Choose a target in the list and click the right button adjacent to its display mode Click the button again Click the button one more time f Click the button adjacent to the lt TRAFFIC line On the traffic page click the button adjacent to the line lt TARGETS to return to the targets page Click the button adjacent to the OPTIONS gt line ExPECTED RESULTS a b The callsign is entered and displayed to the right of the first left line select button The message DLH456 is selected is displayed in the scratchpad The error message is cleared The message Unknown aircraft XXX is displayed in the scratchpad The message Unknown aircraft Y Y Y is displayed in the scratchpad Messages are stacked The message Unknown aircraft XXX is displayed in the scratchpad The scratchpad is cleared c The message Delete DLH456 Confirm Cancel is displayed The message is cleared and DLH456 is removed from the aircraft list d The 10 aircraft place holder are filled with the 10 different callsigns e The display mode is set to none The display mode switches to reduced The display mode returns to extended f The
73. ther conditions None TEST DESCRIPTION a No test required b 1 Thanks to the RANGE selector chose successively the following ND range scales 10 20 40 80 160 and 320 2 Press the CTR switch several times 3 Click several times on the RTE switch 4 With RTE activated click several times on the DATA switch 5 Click several times on the NAV switch c 1 Select OFF on the CDTI mode selector 2 Select CDTI on the CDTI mode selector d 1 Onthe CDTI mode selector chose successively LSA VSA LP LSK and OFF 2 Select LP or LSK as CDTI mode On the LP LSK PREDICT Selector chose alternately the different prediction times 30 sec 1 min 2 min 5 min EXPECTED RESULTS a No result expected b 1 Range is updated so that the distance represented from subject aircraft to compass rose along the track line takes successively the following values 10 20 40 80 160 and 320 Nautical Miles 2 The ND alternates between centered map mode where the entire compass rose is visible and expanded map mode where only a quart of compass rose appears 3 The display of subject aircraft flight plan is alternately activated and deactivated This flight plan includes The active route All the visible waypoints located on the active route The active waypoint and relating information ETA and Distance To Go 4 The display of additionnal trajectory data on the route waypoints is alternately ac
74. tivated and deactivated Those data are the altitude and the estimated time of arrival over the waypoint 5 The display of navaids is alternately activated and deactivated c 1 The whole CDTI information is deactivated 2 CDTI indications appear surrounding aircraft highlighted or not and their related information callsign of the first aircraft in the list of selected targets d 1 First CDTI displays are updated so that the information provided is successively adapted to Lateral Separation Assurance problems Vertical Separation Assurance problems Lateral Passing information problems Longitudinal Station Keeping problems Then the last selection deactivale all CDTI information 2 The predicted conditions trend OD for LP mode trend ATD for LSK mode are displayed depending on the selected prediction time TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Mode Control Panel RH 1 2 4 Mode control panel Date Document Software version Author Page Test CASE RH 1 2 4 Function Mode control panel REFERENCE DOCUMENT INITIAL CONDITIONS Launch the CDTIApplet applet choose a scenario an aircraft and open a cockpit Previous Tests None Other conditions None TEST DESCRIPTION a Start the simulation b h Click one of the HDG TRK buttons of the MCP Click the right part of the crown of the speed SEL button without relea
75. yed narrow symbol TEST RESULT VARIATION NOTED Conform Blocking Not blocking DATE OBSERVATIONS Reproduction soumise accord pr alable Cockpit Display of Traffic Information Date Software V 1 0 version TEST CASE CDTI a CDTI c Function CDTI REFERENCE DOCUMENT INITIAL CONDITIONS Initial state A cockpit shall have been opened and a scenario shall be running with at least 3 aircraft one of them having an activation delay example in scenario named ThreeAircraft DLH456 has an activation delay of 20 s Previous tests CDU ASAS Other conditions None TEST DESCRIPTION a 1 Inthe TRAFFIC CDU page set an aircraft without activation delay to reduced RED CDTI mode 2 In the REDUCED OPTIONS CDU page perform the following changes set the SSR code to ON set the callsign CALLSGN to OFF set the altitude ALT to ABS set the altitude ALT to NO set the ground speed GS to ON set the vertical speed trend V S TRENS to OFF set the velocity vector extrapolation time VEL VECT to 240 seconds set the past position to 10 3 In the TRAFFIC CDU page set an aircraft without activation delay to extended EXT CDTI mode 4 In the EXTENDED OPTIONS CDU page perform the following changes set the SSR code to OFF set the callsign CALLSG

4 - EEC (EUROCONTROL Experimental Centre)

Contents

Download Pdf Manuals

Related Search

Related Contents