DOC AIRBUS | AMM A320FFunction Test (Fan Trim Balance) [PW11]
TASK 71-00-00-710-807-A
Function Test (Fan Trim Balance)
Use this procedure to reduce fan related vibration.
For more information about the power plant, refer to (71-00-00-00U).
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 71-00-00-865-189-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-248-A ** ON A/C NOT FOR ALL
Subtask 71-00-00-860-249-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:31:45 UTC
Function Test (Fan Trim Balance)
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AND THE ADJACENT COMPONENTS AFTER ENGINE SHUTDOWN. THE ENGINE, THE ENGINE OIL AND THE ADJACENT COMPONENTS CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.
ZONE: 400
1. Reason for the JobUse this procedure to reduce fan related vibration.
For more information about the power plant, refer to (71-00-00-00U).
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| 98F10103500000 | 2 | CHOCK-MLG,ENGINE RUN-UP |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 23-73-00-860-010-A | CIDS MCDU ACCESS via FAP |
| TASK 24-41-00-861-002-A | Energize the Aircraft Electrical Circuits from the External Power |
| TASK 24-41-00-861-002-A-01 | Energize the Aircraft Electrical Circuits from the APU |
| TASK 24-41-00-861-002-A-02 | Energize the Aircraft Electrical Circuits from Engine 1(2) |
| TASK 31-60-00-860-001-A | EIS Start Procedure |
| TASK 71-00-00-860-814-A | Shutdown of the Engine |
| TASK 71-00-00-860-822-A | Start the Engine (Normal Manual Start) |
| TASK 71-00-00-860-823-A | Start the Engine (Normal Automatic Start) |
| TASK 71-00-00-910-804-A | General Warnings and Cautions and Related Safety Data |
| TASK 72-11-01-000-801-A | Removal of the Inlet Cone |
| TASK 72-11-01-400-801-A | Installation of the Inlet Cone |
Subtask 71-00-00-865-189-A ** ON A/C NOT FOR ALL
CAUTION:
DO NOT OPEN LGCIU CIRCUIT BREAKERS 1GA, 2GA AND 52GA. IF YOU DO THIS, AIRCRAFT BRAKING THROUGH BRAKE PEDALS DOES NOT OPERATE.
A. Make sure that this(these) circuit breaker(s) is(are) closed:| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | L/G/LGCIU/SYS1/NORM | 1GA | C09 |
| 121VU | HYDRAULIC/LGCIU/SYS2 | 2GA | Q35 |
| 121VU | HYDRAULIC/LGCIU/SYS1/GRND SPLY | 52GA | Q34 |
B. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002)
(2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(3) On the landing gear control and indicating panel 402VU:
(a) Make sure that the A/SKID and N/WSTRG selector switch 5GG is ON.
(4) On RUD TRIM/PARKING BRK panel 110VU:
(b) Make sure that the parking brake control-switch is set to ON.
(5) Put in position the wheel 98F10103500000 CHOCK-MLG,ENGINE RUN-UP at each forward outboard MLG wheel.
(6) Make sure there is the necessary fuel quantity in the inner tanks.
(a) One person must monitor the outside and the aircraft behavior while the other performs the engine test.
(8) If the aircraft begins to move while performing an engine run, immediately set all the thrust levers to idle position.
(9) On the air conditioning panel 30VU, make sure that the engine bleed valves are off (the OFF legend is on).
4. Procedure(1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002)
(2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(3) On the landing gear control and indicating panel 402VU:
(a) Make sure that the A/SKID and N/WSTRG selector switch 5GG is ON.
(4) On RUD TRIM/PARKING BRK panel 110VU:
CAUTION:
MAKE SURE THAT THE AIRCRAFT IS PARKED ON A CLEAN, DRY AND FLAT SURFACE. THERE MUST BE NO OIL, GREASE OR SIMILAR MATERIALS ON THE SURFACE. THE PAVEMENT MUST NOT BE BROKEN OR LOOSE, AND WE RECOMMEND CONCRETE MATERIAL BECAUSE ASPHALT CAN MELT AND CAUSE DAMAGE TO THE AIRCRAFT.
(a) If necessary, remove the ice and the snow from the surface. (b) Make sure that the parking brake control-switch is set to ON.
(5) Put in position the wheel 98F10103500000 CHOCK-MLG,ENGINE RUN-UP at each forward outboard MLG wheel.
(6) Make sure there is the necessary fuel quantity in the inner tanks.
NOTE: When the tested engine operates above N1=70% (not tested engine at N1=50%), make sure that a total of 6614 lb (3000.06 kg) (minimum) of fuel are in the inner tanks.
NOTE: This minimum fuel quantity does not include the fuel consumption of the engines necessary to do the test. This minimum quantity must stay in the inner tanks at the end of the test.
(7) There must be two qualified persons in the cockpit when performing an engine run above idle: (a) One person must monitor the outside and the aircraft behavior while the other performs the engine test.
(8) If the aircraft begins to move while performing an engine run, immediately set all the thrust levers to idle position.
(9) On the air conditioning panel 30VU, make sure that the engine bleed valves are off (the OFF legend is on).
CAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
Subtask 71-00-00-710-262-A ** ON A/C NOT FOR ALL A. Function Test - Fan (Trim Balance)
(1) Check the ground scanning report for the NF sensor fault before proceeding with the fan trim balance procedure. If present, the NF sensor fault must be corrected per the trouble shooting manual procedures before proceeding.
(2) If the fan trim balance is being performed to reduce fan vibration levels and not because of a fan blade repositioning or replacement, use the balance solution from the last flight. Go to Step 4. A. (8).
(4) Make sure that the engine temperature becomes stable before the baseline trim balance survey as follows:
(a) Start the tested engine (Ref. AMM TASK 71-00-00-860-823).
(d) Do a slow acceleration to 50 percent N1 and let the engine become stable for five minutes.
(e) Decelerate slowly to idle power and let the engine becomes stable for three minutes.
(f) Start the non-tested engine (Ref. AMM TASK 71-00-00-860-823).
(i) Aircraft thrust balance during engine operation:
1 Single-engine operation is permitted up to N1 = 70 percent.
2 If higher power is necessary, the thrust of the second engine (non-tested engine or opposite engine) must be equal to N1 = 50 percent.
(5) If a vortex destroyer is available, go to Step 4. A. (6). Perform a trim balance survey for engine runs without a vortex destroyer that follow:
(a) Push and hold the brake pedals at the full limit position.
(b) On rudder trim/parking brake panel 110VU:
1 Make sure that parking brake control switch is set to ON.
(c) Accelerate the non-tested engine to 50 percent N1 and hold the speed.
(d)
Table 501 - Engine Runs without a Vortex Destroyer ** ON A/C NOT FOR ALL
Function Test Fan - (Trim Balance) - Trim Balance Survey (Engine Runs without a Vortex Destroyer) ** ON A/C NOT FOR ALL
Dwell for 45 seconds at N1 speeds between 52.4 and 59 percent, then accelerate to max N1 speed and dwell for ten seconds. Do ten second dwell at the three speed bins at less than the max N1 speed. Do not repeat dwell at or less than 59 percent. If less than three speed bins are at more than 59 percent, lock on all available bins.
Table 501 - Trim Balance Survey (for engine runs without a vortex destroyer)
(e) Make sure that the run time at speeds above 70 percent N1 is no more than two minutes.
(f) The 10 and 45 second dwell times at each specific N1 speed are necessary to let the Prognostic and Health Management Unit (PHMU) to access the amplitude and phase data. During the dwell point, speed must be maintained within one percent.
1 If engine stability changes because of ambient winds beyond the +/- one percent from the specified dwell point, extend the dwell at that speed by ten seconds to make sure that the data is collected.
(g) Record the CUs at each dwell speed listed and go to the next step. See the figure:
(h) Do a snap deceleration by a quick movement of the thrust lever (five seconds or less) to idle.
(i) Release the brake pedals.
(j) Shut down the non-tested engine (Ref. AMM TASK 71-00-00-860-814).
(k) Operate the test engine at idle power for ten minutes.
(l) Shut down the tested engine (Ref. AMM TASK 71-00-00-860-814).
(m) Go to Step 4. A. (7) to determine if a trim balance is required.
(6) Do a trim balance survey for engine runs with a vortex destroyer as follows. Do not do this step if Step 4. A. (5) was used.
(a) Push and hold the brake pedals at the full limit position.
(b) On rudder trim / parking brake panels 110VU:
1 Make sure that the parking brake control switch is set to ON.
(c) Accelerate the non-tested engine to 50 percent N1 and hold the speed.
(d) Table 502 - Engine Runs with a Vortex Destroyer ** ON A/C NOT FOR ALL
Function Test Fan - (Trim Balance) - Trim Balance Survey (Engine Runs with a Vortex Destroyer) ** ON A/C NOT FOR ALL
Dwell for 45 seconds at N1 speeds between 52.4 and 60.2 percent then accelerate to max N1 speed and dwell for ten seconds. Do ten second dwell at the three speed bins at less than the max N1 speed. Do not repeat dwell at or less than 60.2 percent. If less than three speed bins are at more than 60.2 percent, lock on all available bins.
Table 502 - Trim Balance Survey (for engine runs with a vortex destroyer)
(e) The 10 and 45 second dwell times at each specific N1 speed are necessary to let the PHMU to get amplitude and phase data. During the dwell, the speed must be kept in one percent.
1 If engine stability is changed because of ambient winds +/- one percent from the specified dwell point, extend the dwell at that speed by one minute to make sure that the data is correct.
(f) Record the CUs at each dwell speed listed and go to the next step. See the Table 504:
(g) Do a snap deceleration by a quick movement of the thrust lever (five seconds or less) to idle.
(h) Release the brake pedals
(i) Shut down the non-tested engine (Ref. AMM TASK 71-00-00-860-814)
(j) Operate the test engine at idle power for ten minutes.
(k) Shut down the tested engine (Ref. AMM TASK 71-00-00-860-814).
(l) Go to Step 4. A. (7) to determine if a trim balance is required.
(7) Determine if a fan trim balance is required as follows:
(b) Go to the ENGINE TESTES MENU and select TRIM BALANCE. See the figure:
1 If a different flight (or engine run) is preferred for the assessment, navigate to Page 3 of 3 on the VIBRATION HISTORY / FAN DATA screen and select PREV LEG. See the sheets 1, 2 and 3 of the figure:
Function Test - Fan (Trim Balance) - (Vibration History Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
(e) From the screens on the VIBRATION HISTORY / FAN DATA, determine the maximum value of MAG. See the sheets 2 and 3 of the figure:
Function Test - Fan (Trim Balance) - (Vibration History Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
1 If the maximum value of MAG is below 0.5 CUs (80 percent N1 Speed min) or 0.4 CUs (<80 percent N1 Speed min), fan trim balance is not required.
2 If the maximum value of MAG is at or above 0.5 CUs (80 percent N1 Speed) or 0.4 CUs (<80 percent N1 Speed min), record the MAG and PHASE and go to the next step.
(a) Return to the TRIM BALANCE MAIN MENU screen as follows:
1 Select RETURN TO VIB HISTORY MAIN MENU from page 3/3 of the VIBRATION HISTORY / FAN DATA screen. See the sheet 3 of the figure:
Function Test - Fan (Trim Balance) - (Vibration History Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
2 Select RETURN TO TRIM BALANCE MENU from the VIB HISTORY MENU. See the figure:
(b) Select the REV/EDIT STORED WEIGHTS on the TRIM BALANCE MAIN MENU. See the figure:
Function Test - Fan (Trim Balance) - (Rev / Edit Stored Weights Plane Selection - MCDU Screen) ** ON A/C NOT FOR ALL
(d) Select REV/EDIT WEIGHTS for each set of weight positions (1-5, 6-10, 11-15, and 16-20). See the figure:
Function Test - Fan (Trim Balance) - (Rev / Edit Fan Weights - Select Position - MCDU Screen) ** ON A/C NOT FOR ALL
Make sure that the weight locations, part number and class number on the screen match the current physical weight locations, part numbers and class number. See the figures:
Function Test - Fan (Trim Balance) - (Select Fan Weight P/N Page - MCDU Screen) ** ON A/C NOT FOR ALL
Function Test - Fan (Trim Balance) - (Rev / Edit Fan Weights - Position 1-5 Page- MCDU Screen) ** ON A/C NOT FOR ALL
1 Remove the inlet cone (Ref. AMM TASK 72-11-01-000-801).
Function Test - Fan (Trim Balance) - (Rev / Edit Stored Weights Plane Selection - MCDU Screen) ** ON A/C NOT FOR ALL
Function Test - Fan (Trim Balance) - (Rev / Edit Fan Weights - Select Position - MCDU Screen) ** ON A/C NOT FOR ALL
(f) Select the PERFORM BALANCE screen from the TRIM BALANCE MAIN MENU. See the figure:
(h) The FAN BALANCE SOLN SELECTION - FAN PLANE SELECTED screen will be shown from the DO FAN TRIM BALANCE screen. See the figure:
Function Test - Fan (Trim Balance) - (BALANCE SOLN SELECTION Menu - MCDU Screen) ** ON A/C NOT FOR ALL
(i) Select the GENERIC COEFFICIENT screen from the BALANCE SOLN SELECTION - FAN PLANE SELECTED screen.
1 The FAN BALANCE SOLUTION screen shows the balance solution for the operator-selected balance plane and type of coefficients. The vendor screen area shows two sets of balance solutions: The GEN-1 solution is from the last engine run and the GEN-10 solution has available data from not more than ten past run (not to be used at this time). The screen also gives the confidence of improvement for each solution as a fraction of the total points. The total measurement points are the product of the number of vibration sensors (2) and the speed points used (always 10) and will be a value of 10 or 20 based on the sensors used. See the figure:
Function Test - Fan (Trim Balance) - (Fan Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
Function Test - Fan (Trim Balance) - (Fan Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
1 Print or record the balance solution. See the figure:
Function Test - Fan (Trim Balance) - (Implement Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
This identifies the locations of the holes to place the counterweights in. Hole 1 is the first hole counterclockwise from the dimple that is not a center rivet hole. Hole 2 is the second hole counterclockwise from the dimple that is not a center rivet hole. See the figure:
Function Test - Fan (Trim Balance) - Weight Locations and Counterweight Installation ** ON A/C NOT FOR ALL
Function Test - Fan (Trim Balance) - Weight Locations and Counterweight Installation ** ON A/C NOT FOR ALL
(b) Release the pin and spring to engage the end of the pin through the hole of the tab.
(10) Install the inlet cone. Refer to: (Ref. AMM TASK 72-11-01-400-801).
(11) Select CONFIRM NEW WEIGHT PLACEMENT on the page 2 of 2 in the IMPLEMENT BAL SOLUTION screen. See the sheet 2 of the figure:
Function Test - Fan (Trim Balance) - (Implement Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL
(a) Select YES on the CONFIRM USER SELECTION screen. See the figure:
(c) Select CANCEL from the TRIM BALANCE MENU to exit interactive mode. See the figure:
(12) Repeat the ground run as follows:
(a) If vortex destroyer is not used do Step 4. A. (3) through Step 4. A. (5) (I). Make sure that the fan vibration limits are 0.5 CU at each speed if run at 80 N1 percent speed during Step 4. A. (5) (d) or 0.4 at each speed if it was not run at 80 percent speed.
(b) If vortex destroyer is used, do Step 4. A. (3), Step 4. A. (4) and Step 4. A. (6), thru Step 4. A. (6) (k) (trim balance survey with vortex destroyer). Make sure that the fan vibration limits are 0.5 CU maximum at each speed if run at 80 percent N1 speed during Step 4. A. (6) (e) or 0.4 maximum at each speed if it was not run at 80 percent N1 speed.
(c) If the fan vibration levels are satisfactory by Step 4. A. (7), the fan trim balance is complete. If the fan vibration levels are not in the limits, repeat Step 4. A. (8) (a) thru Step 4. A. (12) again until all are satisfactory.
(d) After the completion of an acceptable fan trim balance, return the engine to service.
5. Close-up(1) Check the ground scanning report for the NF sensor fault before proceeding with the fan trim balance procedure. If present, the NF sensor fault must be corrected per the trouble shooting manual procedures before proceeding.
(2) If the fan trim balance is being performed to reduce fan vibration levels and not because of a fan blade repositioning or replacement, use the balance solution from the last flight. Go to Step 4. A. (8).
NOTE: The balance solution from the last flight is automatically provided in the GEN-1 solution after landing. Subsequent ground runs after landing will automatically replace the last flight solution. It is recommended that you record the trim balance solution and the associated trim balance weight part numbers and locations from the MCDU menus (accessed as described in Step 4. A. (8) (j) for the last flight run before you perform any ground run to investigate high vibration issues. This will help to retain a trim balance solution to target flight vibrations that might not be replicable during ground runs.
(3) The wind direction and velocity can make the engine unstable during static operation. Make sure that the engine is operated within the defined wind envelope (Ref. AMM TASK 71-00-00-910-804). (4) Make sure that the engine temperature becomes stable before the baseline trim balance survey as follows:
(a) Start the tested engine (Ref. AMM TASK 71-00-00-860-823).
NOTE: This is the recommended start method for normal conditions.
(b) As an option, start the engine by manual start procedure (Ref. AMM TASK 71-00-00-860-822)NOTE: : It is recommended that you use the manual start procedure at all high altitude airports.
(c) Let the engine become stable for five minutes at minimum idle. (d) Do a slow acceleration to 50 percent N1 and let the engine become stable for five minutes.
(e) Decelerate slowly to idle power and let the engine becomes stable for three minutes.
(f) Start the non-tested engine (Ref. AMM TASK 71-00-00-860-823).
NOTE: This is the recommended start method for normal conditions.
(g) As an option, start the engine by use the manual start procedure (Ref. AMM TASK 71-00-00-860-822). NOTE: It is recommended that you use the manual start procedure at all high-altitude airports.
NOTE: It is recommended that you use the manual start procedure for starts with low starter air pressure supply (external pneumatic power source).
(h) Let the engine become stable for five minutes at minimum idle. (i) Aircraft thrust balance during engine operation:
1 Single-engine operation is permitted up to N1 = 70 percent.
2 If higher power is necessary, the thrust of the second engine (non-tested engine or opposite engine) must be equal to N1 = 50 percent.
(5) If a vortex destroyer is available, go to Step 4. A. (6). Perform a trim balance survey for engine runs without a vortex destroyer that follow:
(a) Push and hold the brake pedals at the full limit position.
(b) On rudder trim/parking brake panel 110VU:
1 Make sure that parking brake control switch is set to ON.
(c) Accelerate the non-tested engine to 50 percent N1 and hold the speed.
(d)
Table 501 - Engine Runs without a Vortex Destroyer ** ON A/C NOT FOR ALL Function Test Fan - (Trim Balance) - Trim Balance Survey (Engine Runs without a Vortex Destroyer) ** ON A/C NOT FOR ALL Table 501 - Trim Balance Survey (for engine runs without a vortex destroyer)
| ILLUSTRATION STEP | PROCEDURE |
|---|---|
| A | Start the engine. |
| | NOTE |
| | Engine temperature must be stable before the baseline trim balance survey. |
| B | Start the non-tested engine. |
| C, D, E | Dwell at these points for 45 seconds. |
| F | Max N1 Speed, dwell for ten seconds. |
| G | 1st speed bin below N1 max, dwell for ten seconds. |
| H | 2nd speed bin below N1 max, dwell for ten seconds. |
| I | 3rd speed bin below N1 max, dwell for ten seconds. |
| | NOTE |
| | After the maximum N1, only lock on speed bins between max N1 and 64 percent N1 speeds. |
| | This may be less than three bins. |
| J | Snap decelerate within five seconds or less of the thrust level to idle and run the engine for ten minutes before the shutdown. |
| K | Shut down the non-tested engine. Then shut down the engine being tested. |
| | NOTE |
| | * The maximum N1 speed (point F) may differ between engines. Points G, H and I will vary accordingly. |
(f) The 10 and 45 second dwell times at each specific N1 speed are necessary to let the Prognostic and Health Management Unit (PHMU) to access the amplitude and phase data. During the dwell point, speed must be maintained within one percent.
1 If engine stability changes because of ambient winds beyond the +/- one percent from the specified dwell point, extend the dwell at that speed by ten seconds to make sure that the data is collected.
(g) Record the CUs at each dwell speed listed and go to the next step. See the figure:
(h) Do a snap deceleration by a quick movement of the thrust lever (five seconds or less) to idle.
(i) Release the brake pedals.
(j) Shut down the non-tested engine (Ref. AMM TASK 71-00-00-860-814).
(k) Operate the test engine at idle power for ten minutes.
(l) Shut down the tested engine (Ref. AMM TASK 71-00-00-860-814).
(m) Go to Step 4. A. (7) to determine if a trim balance is required.
(6) Do a trim balance survey for engine runs with a vortex destroyer as follows. Do not do this step if Step 4. A. (5) was used.
(a) Push and hold the brake pedals at the full limit position.
(b) On rudder trim / parking brake panels 110VU:
1 Make sure that the parking brake control switch is set to ON.
(c) Accelerate the non-tested engine to 50 percent N1 and hold the speed.
(d)
Table 502 - Engine Runs with a Vortex Destroyer ** ON A/C NOT FOR ALL Function Test Fan - (Trim Balance) - Trim Balance Survey (Engine Runs with a Vortex Destroyer) ** ON A/C NOT FOR ALL Table 502 - Trim Balance Survey (for engine runs with a vortex destroyer)
| ILLUSTRATION STEP | PROCEDURE |
|---|---|
| A | Start the engine. |
| | NOTE |
| | Engine temperature must be stable before the baseline trim balance survey. |
| B | Start the non-tested engine. |
| C, D, E | Dwell at these points for 45 seconds. |
| F | Max N1 Speed, dwell for ten seconds. |
| G | 1st speed bin below N1 max, dwell for ten seconds. |
| H | 2nd speed bin below N1 max, dwell for ten seconds. |
| I | 3rd speed bin below N1 max, dwell for ten seconds. |
| | NOTE |
| | After the maximum N1, only lock on speed bins between max N1 and 64 percent N1 speeds. |
| | This may be less than three bins. |
| J | Snap decelerate within five seconds or less of the thrust level to idle and run the engine for ten minutes before shutdown. |
| K | Shut down the non-tested engine. Then shut down the engine being tested. |
| | NOTE |
| | * The maximum N1 speed (Point F) may differ between engines. Points G, H and I will vary accordingly. |
1 If engine stability is changed because of ambient winds +/- one percent from the specified dwell point, extend the dwell at that speed by one minute to make sure that the data is correct.
(f) Record the CUs at each dwell speed listed and go to the next step. See the Table 504:
(g) Do a snap deceleration by a quick movement of the thrust lever (five seconds or less) to idle.
(h) Release the brake pedals
(i) Shut down the non-tested engine (Ref. AMM TASK 71-00-00-860-814)
(j) Operate the test engine at idle power for ten minutes.
(k) Shut down the tested engine (Ref. AMM TASK 71-00-00-860-814).
(l) Go to Step 4. A. (7) to determine if a trim balance is required.
(7) Determine if a fan trim balance is required as follows:
NOTE: If the number of speed bins used for the solution is less than 5, the trim balance survey (Step 4. A. (5) or Step 4. A. (6)) should be run to acquire sufficient bins for an effective solution. The number of bins used is the numerator of the fractional display value "PTS Used Gen-1".
(a) Get access to the Multifunction Control Display Unit (MCDU) (Ref. AMM TASK 23-73-00-860-010). (b) Go to the ENGINE TESTES MENU and select TRIM BALANCE. See the figure:
NOTE: If ERROR CODE 5 is displayed, contact P&W field service representative for support.
(c) From the Trim Balance Main Menu, select REVIEW VIB DATA HISTORY. See the figure: NOTE: If ERROR CODE 7 is displayed, contact P&W field service representative for support.
(d) Select FAN VIBE HISTORY from the VIB HISTORY MENU to display the Fan Vibration History from the previous flight. See the figure: 1 If a different flight (or engine run) is preferred for the assessment, navigate to Page 3 of 3 on the VIBRATION HISTORY / FAN DATA screen and select PREV LEG. See the sheets 1, 2 and 3 of the figure:
Function Test - Fan (Trim Balance) - (Vibration History Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - (Vibration History Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL 2 If the maximum value of MAG is at or above 0.5 CUs (80 percent N1 Speed) or 0.4 CUs (<80 percent N1 Speed min), record the MAG and PHASE and go to the next step.
NOTE: 0.5 CU = 0.20 IPS
0.4 CU = 0.16 IPS
(8) Develop the fan trim balance solution as follows: 0.4 CU = 0.16 IPS
(a) Return to the TRIM BALANCE MAIN MENU screen as follows:
1 Select RETURN TO VIB HISTORY MAIN MENU from page 3/3 of the VIBRATION HISTORY / FAN DATA screen. See the sheet 3 of the figure:
Function Test - Fan (Trim Balance) - (Vibration History Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL (b) Select the REV/EDIT STORED WEIGHTS on the TRIM BALANCE MAIN MENU. See the figure:
NOTE: If ERROR CODE 6 is displayed, contact P&W field representative for support.
(c) Select REVIEW/EDIT FAN WEIGHTS to verify the current installed weight locations stored in the data storage unit. See the figure: Function Test - Fan (Trim Balance) - (Rev / Edit Stored Weights Plane Selection - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - (Rev / Edit Fan Weights - Select Position - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - (Select Fan Weight P/N Page - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - (Rev / Edit Fan Weights - Position 1-5 Page- MCDU Screen) ** ON A/C NOT FOR ALL CAUTION:
THE COUNTERWEIGHTS MUST BE INSTALLED CORRECTLY IN THE TWO OUTER BALANCE FLANGE HOLES. IF COUNTERWEIGHTS ARE NOT INSTALLED CORRECTLY, ROTOR DAMAGE CAN OCCUR.
(e) For each location, if the weight part number or class number is not correct, use the EDIT button on the REV/EDIT FAN WEIGHTS screen to modify the weight. This will allow selection of "SET AS EMPTY" or "SEL P/N...". NOTE: With FCS4.2 or Electronic Engine Control (EEC) software, the EEC will reset at each weight entry. This does not affect the EEC acquisition of the new weight input, but requires the operator to access the procedure from the beginning.
1 When all the weight locations, part numbers, and class numbers are correct, select RETURN TO PLANE SELECTION, then select RETURN TO TRIM BALANCE MAIN MENU screen and continue to the next step. See the figure: Function Test - Fan (Trim Balance) - (Rev / Edit Stored Weights Plane Selection - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - (Rev / Edit Fan Weights - Select Position - MCDU Screen) ** ON A/C NOT FOR ALL NOTE: If ERROR CODE 6 is generated, contact P&W field service representative for support.
NOTE: The PERFORM BALANCE SELECT BALANCE PLANE screen gives the options to select which type of balance procedure to perform. All balance solutions are pre-calculated and kept during the previous engine runs.
(g) Select the DO FAN TRIM BALANCE screen from the PERFORM BALANCE SELECT BALANCE PLANE screen. See the figure: (h) The FAN BALANCE SOLN SELECTION - FAN PLANE SELECTED screen will be shown from the DO FAN TRIM BALANCE screen. See the figure:
Function Test - Fan (Trim Balance) - (BALANCE SOLN SELECTION Menu - MCDU Screen) ** ON A/C NOT FOR ALL 1 The FAN BALANCE SOLUTION screen shows the balance solution for the operator-selected balance plane and type of coefficients. The vendor screen area shows two sets of balance solutions: The GEN-1 solution is from the last engine run and the GEN-10 solution has available data from not more than ten past run (not to be used at this time). The screen also gives the confidence of improvement for each solution as a fraction of the total points. The total measurement points are the product of the number of vibration sensors (2) and the speed points used (always 10) and will be a value of 10 or 20 based on the sensors used. See the figure:
Function Test - Fan (Trim Balance) - (Fan Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL NOTE: If a value of 0 is generated, the PHMU did not calculate a valid solution. The Scheduled Maintenance Report (SMR) can be used to verify if a NF speed sensor faults occurred (may be cause of issue). This makes sure that the engine did not perform any extra runs between the time of the vibration survey and the trim balance procedure.
(j) Select IMPLEMENT GEN-1 SOLUTN (PER LAST FLIGHT) from page 2 of 2 of the FAN BALANCE SOLUTION screen. See the figure: Function Test - Fan (Trim Balance) - (Fan Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - (Implement Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL Function Test - Fan (Trim Balance) - Weight Locations and Counterweight Installation ** ON A/C NOT FOR ALL NOTE: If ERROR CODE -2, -3, or -4 is displayed, contact P&W field service representative for support.
(9) Install the counterweights (1) and (2) on the tabs of the fan hub as follows: See the figure: Function Test - Fan (Trim Balance) - Weight Locations and Counterweight Installation ** ON A/C NOT FOR ALL CAUTION:
THE COUNTERWEIGHTS MUST BE INSTALLED CORRECTLY IN THE TWO OUTER BALANCE FLANGE HOLES. IF COUNTERWEIGHTS ARE NOT INSTALLED CORRECTLY, ROTOR DAMAGE CAN OCCUR.
(a) Push out the pin and compress the spring on the front side of the counterweights (1) and (2) and install them on the balance flange tab. (b) Release the pin and spring to engage the end of the pin through the hole of the tab.
(10) Install the inlet cone. Refer to: (Ref. AMM TASK 72-11-01-400-801).
(11) Select CONFIRM NEW WEIGHT PLACEMENT on the page 2 of 2 in the IMPLEMENT BAL SOLUTION screen. See the sheet 2 of the figure:
Function Test - Fan (Trim Balance) - (Implement Balance Solution Menu Page - MCDU Screen) ** ON A/C NOT FOR ALL NOTE: If ERROR CODE 2, 3 or 4 is displayed, contact P&W field representative for support.
(b) Select RETURN TO TRIM BALANCE MENU from the WRITE CONFIRMATION screen. See the figure: (c) Select CANCEL from the TRIM BALANCE MENU to exit interactive mode. See the figure:
(12) Repeat the ground run as follows:
(a) If vortex destroyer is not used do Step 4. A. (3) through Step 4. A. (5) (I). Make sure that the fan vibration limits are 0.5 CU at each speed if run at 80 N1 percent speed during Step 4. A. (5) (d) or 0.4 at each speed if it was not run at 80 percent speed.
(b) If vortex destroyer is used, do Step 4. A. (3), Step 4. A. (4) and Step 4. A. (6), thru Step 4. A. (6) (k) (trim balance survey with vortex destroyer). Make sure that the fan vibration limits are 0.5 CU maximum at each speed if run at 80 percent N1 speed during Step 4. A. (6) (e) or 0.4 maximum at each speed if it was not run at 80 percent N1 speed.
(c) If the fan vibration levels are satisfactory by Step 4. A. (7), the fan trim balance is complete. If the fan vibration levels are not in the limits, repeat Step 4. A. (8) (a) thru Step 4. A. (12) again until all are satisfactory.
(d) After the completion of an acceptable fan trim balance, return the engine to service.
NOTE: Further optimization of the Fan Trim Balance Solution may be possible following the first flight after the ground run Fan Trim Balance procedure is performed. The PHMU will automatically calculate a new solution during the next flight. This post-flight solution can be incorporated if further reductions in fan vibration are desired.
Subtask 71-00-00-860-249-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.