pratt & whitney canada maintenance manual procedures/textron... · v pw30x transfer module - a...

(h) Push in the circuit breaker for the EEC (FADEC) channel A (located behind thepilot).

(i) The EICAS N1 and ITT indications will start flashing red to amber for tenseconds, wait for the color to stop changing so they are flashing in amber only.This shows that the conditions for data transfer are set and the datatransmitting direction will be from the EEC to the EDU. The data transfer mustnow be triggered within sixty seconds or the process will be aborted.

(j) Push the CONFIRM button on the CMC (if the CMC is used) to trigger the datatransfer or if the CMC is not used, push the TOGA button once per seconduntil the N1 and ITT indications stop flashing and display the new trim valueswith a solid amber background. This indicates that the EDU has been updated.

(k) Verify the data as follows:

1 Make sure the correct (according to the engine data plate) N1 trim (in %N1) and T4.5 trim (in °C) are displayed on the EICAS N1 and ITT displayin amber color.

2 Set the Fuel/Ignition switch to off.

3 Set the TLA to idle and cycle the aircraft 28 VDC power.

4 Make sure that no applicable EEC fault codes are displayed. Do theapplicable fault isolation procedures for these faults (Ref. Chapter 72-00-00,FAULT ISOLATION 1).

7. EDU Data Access With Portable Computer Programs PCTS422 or GBS

A. Accessing EDU Data With the PCTS422 Program (Ref. Figs. 202, 203, 204)

(1) The EDU provides an RS-422 channel for communicating with a portable computer(laptop) that has the PCTS422 program and/or the GBS program.

(a) To connect the laptop computer to the aircraft’s maintenance panel for EDUdata access, refer to the procedure in the AMM, Chapter 45-202.

(b) Turn on the aircraft electrical power, if it is not already on.

(c) If possible, plug the laptop computer into an external power source instead ofrunning off its battery.

(d) Turn the computer on. Click on the ‘‘Start’’ button, select ‘‘Programs’’ thenselect ‘‘P&WC PCTS422’’ and finally select ‘‘PCTS422’’ to start the program.

(e) The ‘‘PWC Configuration’’ window will appear. Select the left or right engine asapplicable.

NOTE: The left or right selection must match the engine that the downloadcable is connected to.

PRATT & WHITNEY CANADAMAINTENANCE MANUAL

MANUAL PART NO. 3043622

77-40-01 Page 206ENGINE DIAGNOSTIC UNIT - MAINTENANCE PRACTICES Nov 09/2007

(f) Make sure the laptop computer is configured correctly for communication.Typically it uses COM1.

(g) Once connected, the display will change to that shown on Figure 202.

(h) Use the keyboard function keys to navigate through the screens, as indicatednear the bottom of the display screen.

(2) PCTS422 Fault Display (Ref. Fig. 203)

(a) The ‘‘Fault Display’’ option will assist the operator in engine troubleshooting bydisplaying real time engine faults and the last 7 flight legs fault history.

(b) Access the ‘‘Selection Menu’’ (Ref. Fig. 202) and select ‘‘Fault Display’’ byusing key F3. The display will change to that shown on Figure 203.

NOTE: 1. The line that starts with an asterix (*) displays the current faults (notyet stored in the permanent memory).

NOTE: 2. Lines 0-6 are the faults that are stored in permanent memory fromthe 7 previous flight legs (maximum of 6 faults per flight leg).

(c) Scroll through the faults using the function keys, and a simple description ofthe highlighted fault will be displayed near the bottom of the screen on line24.

NOTE: For complete details on installing and using PCTS422 software youmay refer to the PCTS422 Users Guide and Reference Manual.

(3) PCTS422 Real Time Display (Ref. Fig. 204)

(a) In the ‘‘Real Time Display’’ option, live EEC data is displayed from bothchannels.

(b) Access the ‘‘Selection Menu’’ (Ref. Fig. 202) and select ‘‘Real Time Display’’by using key F3. The display will change to show continuous data with a twosecond refresh rate.

(c) Seven pages of engine data are available. Use the function keys to scrollbetween the pages (Ref. Fig. 204).

(4) PCTS422 Cumulative Operational Data

(a) The ‘‘Cumulative Operational Data’’ option is used to read the following data:

v Number of flight legs

v Total flight duration

v Total operational duration

v Number of engine starts

v Cycles/hours ratio



77-40-01 07ENGINE DIAGNOSTIC UNIT - MAINTENANCE PRACTICES Nov 09/2007

v Average flight hours per month

(b) To display the above data, access the ‘‘Selection Menu’’ (Ref. Fig. 202) andselect ‘‘Cumulative Operational Data’’ by using key F3.

(5) PCTS422 Historical Event Data

(a) A data snapshot and a data recording (of approx. 5 minutes) are automaticallytaken for the following events:

v Starting T4.5 exceedance

v Operating T4.5 exceedance

v N1 exceedance

v N2 exceedance

v Oil temperature or pressure below min. exceedance

v Oil temperature or pressure above max. exceedance

v Time at take-off exceedance

v Faults

v Flameout

v Commanded shutdown in flight

v APR activation

(b) To display a list of the above events, access the ‘‘Selection Menu’’ (Ref. Fig.202) and select ‘‘Historical Event Data’’ by using key F3.

NOTE: To analyze the content of the snapshots and recordings you must usethe GBS.

(6) PCTS422 Pilot Request Data

(a) When the ‘‘Pilot Rec’’ button on the cockpit pedestal is pressed, a datasnapshot and a data recording (of approx. 5 minutes) are taken.

(b) To display a list of the pilot requested data, access the ‘‘Selection Menu’’ (Ref.Fig. 202) and select ‘‘Pilot Request Data’’ by using key F3.

NOTE: To analyze the content of the snapshots and recordings you must usethe GBS.

(7) PCTS422 Installation Configuration Data

(a) The EDU stores the following data:

v Aircraft Make, Model, S/N, Tail Number, Timestamp

v Engine Model, S/N, Left/Right Position, Timestamp, N1/T4.5 Trims

v EEC S/N, Timestamp, S/W Version




v EDU S/N, Timestamp, S/W Version, Trim Table S/W Version

(b) To display the above data, access the ‘‘Selection Menu’’ (Ref. Fig. 202) andselect ‘‘Installation Configuration Data’’ by using key F3.

B. Ground Based Software (GBS)

(1) GBS-PWC is a windows based application used for engine management. It hasfour main software components:

v GBS Administrative - provides Transient plotting, Trend data extraction and exportto engine condition trend monitoring (ECTM) software, Mission analysis, andHistogram analysis

v PW30X Transfer Module - a communication (download/upload) program

v PW30X Trim Editor - a program to modify operational, configuration, and N1/T4.5trim files

v PCTS422 - a real time interface program (Ref. Para. A.)

NOTE: For more detailed information about installing and using GBS refer to theGBS-PWC Software Users Guide and Reference Manual.

(2) To start the GBS program:

(a) Click on the ‘‘Start’’ button.

(b) Select ‘‘Programs’’.

(c) Select ‘‘GBS-PWC’’.

(d) Select ‘‘Ground Based Software’’, the program will start and show the copyrightscreen.

(3) Creating directories for downloads:

(a) If they have not already been set-up, creating new folders with WindowsExplorer will help you keep track of your downloads.

(b) In Windows Explorer open the folder in which you want to create a new folder(example C:), in the following format C:\Eng_Data.

(c) On the ‘‘File’’ menu, point to ‘‘New’’, then click ‘‘Folder’’.

(d) A temporary folder will appear with the highlighted name ‘‘New Folder’’.

(e) Type in the name you wish to apply to the folder (example: Eng_Data), pressenter.

(f) Inside C:\Eng_Data create a new folder again. On the ‘‘File’’ menu, point to‘‘New’’, then click ‘‘Folder’’.

(g) Rename this temporary folder to the name of the aircraft (example: N498FA).




C87207

PCTS422 Selection MenuFigure 202




FAULT DISPLAY

12345678901234567890123456789012345678901234

12 LEFT PROPULSION SYSTEM DIAGNOSTICS CE006234 FLIGHT FAULT DATA56 CHANNEL A7 * >SA SC SL DB FB HA8 0 SA SC9 110 211 312 413 514 615 CHANNEL B16 * SA SC17 018 119 220 321 422 523 624 SA − WOW DISCRETE CHECK2526 UP DOWN <− −> BACK27 F1 F2 F3 F4 F528

_12345678901234567890123456789012345678901234

C87209

PCTS422 Flight Fault Data (Example Only)Figure 203




C87211

PCTS422 Real Time Data (Example Only)Figure 204




(h) Create two new subdirectories (folders) in the directory ‘‘N498FA’’. Rename thefirst new folder to the engine S/N (example: CF0917) and the second to theother engine S/N (example: CF0918).

(i) When downloading, configure the GBS so the downloads will be stored in theapplicable engine directories, example: C:\Eng_Data\N498FA\CF0917\ orC:\Eng_Data\N498FA\CF0918\.

(4) EDU Data Downloading:

(a) Double click on the ‘‘Pw30X Transfer Module’’ icon.

(b) When the window appears, log-in by clicking on ‘‘File’’ and selecting ‘‘Login’’.

(c) Type in the password ‘‘toronto’’ and click ‘‘OK’’.

(d) The ‘‘Pw30X Transfer Module Windows Application’’ window will appear andask if you want to change the level 2 and 3 passwords. Click on the ‘‘No’’button, unless you need to change them.

(e) Make sure the EEC is powered on and the download cable is connected to theapplicable maintenance connector (Ref. Para. A.).

(f) See that communication is working by clicking on ‘‘Transfer’’ and select ‘‘CheckData Line’’.

(g) Make sure a window appears, stating ‘‘Communication OK’’. If not, recycle theprogram and check the communications setup.

(h) Downloading Current EDU Data:

1 This procedure copies the data that is stored in the EDU memory onto alaptop computer (hard drive or floppy disk). When the data is stored inthe computer it can be modified as necessary and uploaded to the sameEDU or a replacement EDU.

2 To download EDU Data Recordings, click on the ‘‘Transfer’’ pull downmenu.

3 For routine data downloading select ‘‘Read ECTM data from EDU’’, (thiswill produce files ending in ‘‘.bec’’ and will take approximately 3 minutes).For comprehensive troubleshooting select ‘‘Read All Recordings from EDU’’,(this will produce files ending in ‘‘.brc’’ and will take approximately 20minutes).

4 When the computer has read the data, a conversion window will appear,select ‘‘Convert All’’.

5 To download the Installation Configuration Data, click on the ‘‘Transfer’’ pulldown menu and select ‘‘Read Installation Configuration from EDU’’. Whenthe computer has read the data, a conversion window will appear,select ‘‘Convert All’’.




6 This completes the downloading of the EDU data.

(5) Trim Editor:

(a) If required, the Trim Editor can be used to modify the stored EDU data files asapplicable and then initialize them. The Pw30X Transfer Module can be leftopen during this step.

(b) The trim editor allows the modification of the following files:

v Installation/Configuration:- Aircraft ID, Engine ID, EDU ID, and N1/T4.5 Trimvalues.

v Operational:- # of Flight Legs and Flight Duration etc.

(c) Double click on the ‘‘PW30X Trim Editor’’ icon.

1 When the ‘‘Edittrim Windows Application’’ window appears, you can selectthe items you wish to modify.

(d) Select the ‘‘Installation Configuration’’ button in the ‘‘Edittrim WindowsApplication’’.

1 Type in the password ‘‘toronto’’ and click ‘‘OK’’.

2 Click on the ‘‘No’’ button in the change password request, unless you needto change the password.

3 The ‘‘Select an Install Config file’’ window will appear, select the file(xxxxxxx.bec or.brc) you created when you downloaded the EDU data andclick ‘‘OK’’.

NOTE: The file name ‘‘xxxxxxx.bec’’ is derived from the engine S/N andthe number of down loads. Example - the first download fromengine S/N CF0062 would appear as ‘‘f0062001.bec’’. This is theconvention used for all the downloads completed.

4 The ‘‘Installation Configuration’’ window will appear, the two choices in itare :

v Aircraft ID

v Engine ID

5 Click on the ‘‘Aircraft ID’’ button, modify the aircraft’s S/N, registration andowner/operator as applicable. Click on ‘‘Save and Exit’’.

6 Click on the ‘‘Engine ID’’ button, modify the engine S/N, model number,service plan number, N1 trim value and T4.5 trim value as applicable.Click on ‘‘Save and Exit’’.

7 In the ‘‘Installation Configuration’’ window, click on the ‘‘DONE’’ button tosave all the changes.




(e) Select the ‘‘Operational’’ button in the ‘‘Edittrim Windows Application’’.

1 The ‘‘Select a Binary Recording File’’ window will appear, select the file(xxxxxxx.bec or .brc) you created when you downloaded the EDU dataand click ‘‘OK’’.

2 The ‘‘Operational Data’’ window will appear with a ‘‘Cumulative Data’’button.

3 Click on the ‘‘Cumulative Data’’ button and a window will appear with manyfields of operational data.

4 The only fields that should be modified if necessary, to agree with thelogbook are the ‘‘# of Flight Legs’’ and ‘‘Flight Duration’’. All other fieldsshould not be changed.

NOTE: The duration times are in seconds.

5 When you are finished, click on ‘‘Save and Exit’’.

6 Click on the ‘‘Done’’ button in the ‘‘Operational Data’’ window. All files arenow corrected, initialized and ready for uploading.

7 Exit from the ‘‘Edittrim Windows Application’’ by clicking on the ‘‘File’’pull-down menu and selecting ‘‘Exit’’.

(6) EDU File Uploading:

(a) The Pw30X Transfer Module is now used to upload the initialized files that youhave modified in the previous steps.

(b) To Upload the Installation Configuration data to the EDU:

1 Click on the ‘‘Transfer’’ pull-down menu and select ‘‘Write InstallationConfiguration to EDU’’

2 The ‘‘Select an Install Config file’’ window will appear. Select the file(xxxxxxx.bic) that was created in the previous steps and click ‘‘OK’’.

3 The ‘‘Progress’’ window will appear. After the EDU Installation Configurationis uploaded the ‘‘Progress’’ window will disappear.

(c) To Upload the Operational data to the EDU:

1 Click on the ‘‘Transfer’’ pull-down menu and select ‘‘Write Operational Datato EDU’’

2 The ‘‘Select a Cumulative Operational Data file’’ window will appear. Selectthe file (xxxxxxx.boc) that was created in the previous steps and click OK.

3 The ‘‘Progress’’ window will appear. After the Cumulative Operational Datais uploaded the ‘‘Progress’’ window will disappear.




(d) The uploading of all files is now complete. Exit from the ‘‘PW30X TransferModule’’ window by clicking on the ‘‘File’’ pull-down menu and selecting‘‘Exit’’.

(e) The EDU is now updated with the necessary files. Cycle the EEC power andcheck for fault codes. Give special attention to fault codes with the prefix letter‘‘Y’’, which indicate EDU faults. Refer to Chapter 72-00-00, FAULTISOLATION for fault code troubleshooting.

8. Engine Diagnostic Unit (EDU) Bracket

A. Removal (Ref. Fig. 205)

(1) Remove two bolts (7), two washers (6) and two nuts (5) securing the EDU frontsupport bracket (1) to the front flange of the fan case (9).

(2) Remove two bolts (2), two washers (3) and the EDU front support bracket (1) fromthe EDU rear support bracket (4).

(3) Remove two nuts (8) and the EDU rear support bracket (4) from the rear flange ofthe fan case.

B. Installation (Ref. Fig. 205)

(1) Lubricate threads of nuts (8) with engine oil (PWC03-001). Install the EDU rearbracket (4) onto the rear flange of the fan case using two nuts (8). Torque nuts75 to 85 lb.in. (8.7-9.8 Nm.).

(2) Lubricate threads of bolts (2) with engine oil (PWC03-001). Install the EDU frontsupport bracket (1) onto the EDU rear support bracket (4), using two washers (3)and two bolts (2). Torque bolts 36 to 40 lb.in. (4.2-4.6 Nm.).

NOTE: Assemble the washers (3) between the bolt heads and the EDU frontsupport bracket (1).

(3) Lubricate threads of bolts (7) with engine oil (PWC03-001). Secure the forward tabsof the EDU front support bracket (1) to the front flange of the fan case (9), usingtwo bolts (7), two washers (6) and two nuts (5). Torque bolts 85 to 95 lb.in.(9.8-11.0 Nm.).

NOTE: Assemble the washers (6) between the bolt heads and the front flange ofthe fan case (9).




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