W DOC AIRBUS | AMM A320F

Vibration Check [CFMB]

TASK 71-00-00-710-009-B
Vibration Check

1. Reason for the Job
The vibration monitoring system can be used to get vibration data. This task should be performed when a new non pre-tested engine is installed or after FOD/ICING and subsequent fan blades change.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
98F10103500000
2
CHOCK-MLG,ENGINE RUN-UP
 B. Referenced Information
REFERENCE
DESIGNATION
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 24-41-00-862-002-A
De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01
De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02
De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 31-60-00-860-001-A
EIS Start Procedure
TASK 31-60-00-860-002-A
EIS Stop Procedure
TASK 71-00-00-710-003-B
Engine Automatic Start
TASK 71-00-00-710-028-B
Engine Shutdown
TASK 71-00-00-869-003-A
Wind Limitations During Engine Ground Operations
TASK 71-00-00-869-004-A
Safety Precautions During Engine Ground Operations
TASK 77-32-34-860-041-A
Change the configuration of the Accelerometer
TSM 77-00-00-810-862
Fan Vibration less than 4 Units with Noise / Rumble
TSM 77-00-00-810-863
Fan Vibrations Higher than or Equal to 4 Units and less than 6 Units on Engine 1 or 2
TSM 77-00-00-810-864
Fan Vibrations Higher than or Equal to 6 Units on Engine 1 or 2
TSM 77-00-00-810-865
Core Vibrations Higher than or Equal to 4.2 Units (1.68 Ips), and Less than 5.4 Units (2.16 Ips) on Engine 1 or 2
TSM 77-00-00-810-866
Core Vibrations Higher than or Equal to 5.5 Units (2.2 Ips) on Engine 1 or 2
F Tool Installation
3. Job Set-up
Subtask 71-00-00-869-204-A ** ON A/C NOT FOR ALL
A. Safety Precautions
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.
   (1) Obey the wind limitations and safety precautions during engine ground operation (Ref. AMM TASK 71-00-00-869-003) and (Ref. AMM TASK 71-00-00-869-004).
   (2) Make sure that the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP are in position in front of each forward outboard MLG wheel.
F Tool Installation ** ON A/C NOT FOR ALL
   (3) Make sure that there is a minimum of 6614 lb (3000 kg) of fuel in the inner tanks to make sure that the aircraft is stable during the test.
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 tank at the end of the test.
   (4) There must be two qualified persons in the cockpit when performing an engine run. One must monitor the outside and the aircraft behavior while the other performs the engine test.
   (5) If the aircraft begins to move while performing an engine run, immediately set all the thrust levers to the idle position.
Subtask 71-00-00-861-064-A ** ON A/C NOT FOR ALL
B. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 71-00-00-865-100-A ** ON A/C NOT FOR ALL
C. Make sure that this(these) circuit breaker(s) is(are) closed:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUL/G/LGCIU/SYS1/NORM1GAC09
121VUHYDRAULIC/LGCIU/SYS22GAQ35
121VUHYDRAULIC/LGCIU/SYS1/GRND SPLY52GAQ34
Subtask 71-00-00-720-051-A ** ON A/C NOT FOR ALL
D. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
NOTE: On the lower ECAM display unit:
  • For the N1 module, 1 Unit = 1 MIL.
  • For the N2 module, 1 Unit = 0.4 IPS.
Subtask 71-00-00-710-083-A ** ON A/C NOT FOR ALL
E. Start the two engines and let them become stable at minimum idle (Ref. AMM TASK 71-00-00-710-003) .
4. Procedure
Subtask 71-00-00-710-192-A ** ON A/C NOT FOR ALL
A. Before N1 is more than or equal to 75 percent, do this procedure
WARNING: DO NOT LET ONE ENGINE OPERATE AT N1 GREATER THAN OR EQUAL TO 75 PERCENT WHEN ONLY THE WHEEL CHOCKS AND THE PARKING BRAKE STOP THE MOVEMENT OF THE AIRCRAFT.
CAUTION: MAKE SURE THAT THE N1 VIBRATION DOES NOT BECOME HIGHER THAN 6 MILS.DA (6 CU ON THE ECAM DU). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE CAN OCCUR.
CAUTION: DO NOT OPEN LGCIU CIRCUIT BREAKERS 1GA, 2GA AND 52GA. IF YOU DO THIS, AIRCRAFT BRAKING THROUGH BRAKE PEDALS DOES NOT OPERATE.
   (1) On landing gear control and indicating panel 402VU:
     (a) Make sure that A/SKID & N/WSTRG selector switch 5GG is ON.
   (2) On the RUD TRIM/PARKING BRK panel 110VU:
     (a) Make sure that the PARKING BRAKE control switch is in ON position.
   (3) Push and hold the brake pedals at the full limit position.
   (4) On the RUD TRIM/PARKING BRK panel 110VU:
     (a) Set the PARKING BRAKE control switch to OFF position.
Subtask 71-00-00-710-084-A ** ON A/C NOT FOR ALL
B. Vibration Check
   (1) Slowly increase power of the non tested engine to 60 percent N1.
   (2) For the tested engine do a 2 minute acceleration from the minimum idle setting to MAX CLIMB detent and let become stable 15 seconds. Follow this acceleration with a 2 minute deceleration.
     (a) Monitor the vibration readings and write down the rpm where the peak vibration occurs.
   (3) Go back to the rpm where the peak vibration occurred and let the rpm become stable for 4 minutes.
     (a) Monitor the vibration readings and write them down.
   (4) Slowly decrease power on the two engines to minimum idle and let become stable for 3 minutes.
   (5) Adjust the MCDU to read vibration values on the other accelerometer (Ref. AMM TASK 77-32-34-860-041) and repeat steps (3) to (5).
   (6) Put the aircraft in the "parking brake applied" configuration:
     (a) On the panel 110VU:
- Set the parking brake control switch to ON.
     (b) Release the brake pedals.
   (7) If the vibration for the fan assembly (N1) goes over 4 U (4 MILS) or is less than 4 U with noise or rumble, do the troubleshooting procedure relative to the triggered warning TSM 77-00-00-810-862, TSM 77-00-00-810-863 or TSM 77-00-00-810-864.
   (8) If the vibration of the core assembly (N2) goes over 4.25 U (1.7 IPS) peak, do the troubleshooting procedure relative to the triggered warning TSM 77-00-00-810-865 or TSM 77-00-00-810-866.
   (9) Adjust the MCDU to read original accelerometer (Ref. AMM TASK 77-32-34-860-041).
   (10) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002)
Subtask 71-00-00-710-192-B ** ON A/C NOT FOR ALL
C. Before N1 is more than or equal to 75 percent, do this procedure
WARNING: DO NOT LET ONE ENGINE OPERATE AT N1 GREATER THAN OR EQUAL TO 75 PERCENT WHEN ONLY THE WHEEL CHOCKS AND THE PARKING BRAKE STOP THE MOVEMENT OF THE AIRCRAFT.
CAUTION: MAKE SURE THAT THE N1 VIBRATION DOES NOT BECOME HIGHER THAN 6 MILS.DA (6 CU ON THE ECAM DU). IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE CAN OCCUR.
CAUTION: DO NOT OPEN LGCIU CIRCUIT BREAKERS 1GA, 2GA AND 52GA. IF YOU DO THIS, AIRCRAFT BRAKING THROUGH BRAKE PEDALS DOES NOT OPERATE.
   (1) On landing gear control and indicating panel 402VU:
  • Make sure that A/SKID & N/WSTRG selector switch 5GG is ON.
   (2) On RUD TRIM/PARKING BRK panel 110VU:
     (a) Make sure that the PARKING BRAKE control switch is in ON position.
   (3) Push and hold the brake pedals at the full limit position.
Subtask 71-00-00-710-084-B ** ON A/C NOT FOR ALL
D. Vibration Check
   (1) Slowly increase power of the non tested engine to 60 percent N1.
   (2) For the tested engine do a 2 minute acceleration from the minimum idle setting to MAX CLIMB detent and let become stable 15 seconds. Follow this acceleration with a 2 minute deceleration.
     (a) Monitor the vibration readings and write down the rpm where the peak vibration occurs.
   (3) Go back to the rpm where the peak vibration occurred and let the rpm become stable for 4 minutes.
     (a) Monitor the vibration readings and write them down.
   (4) Slowly decrease power on the two engines to minimum idle and let become stable for 3 minutes.
   (5) Adjust the MCDU to read vibration values on the other accelerometer (Ref. AMM TASK 77-32-34-860-041) and repeat steps (3) to (5).
   (6) Release the brake pedals to put the aircraft in the "parking-brake applied" configuration.
   (7) If the vibration for the fan assembly (N1) goes over 4 U (4 MILS) or is less than 4 U with noise or rumble, do the troubleshooting procedure relative to the triggered warning TSM 77-00-00-810-862, TSM 77-00-00-810-863 or TSM 77-00-00-810-864.
   (8) If the vibration of the core assembly (N2) goes over 4.25 U (1.7 IPS) peak, do the troubleshooting procedure relative to thetriggered warning TSM 77-00-00-810-865 or TSM 77-00-00-810-866.
   (9) Adjust the MCDU to read original accelerometer (Ref. AMM TASK 77-32-34-860-041).
   (10) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002)
5. Close-up
Subtask 71-00-00-710-085-A ** ON A/C NOT FOR ALL
A. Stop the two engines (Ref. AMM TASK 71-00-00-710-028).
Subtask 71-00-00-862-064-A ** ON A/C NOT FOR ALL
B. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
[Rev.10 from 2021] 2026.04.01 02:24:45 UTC
"Aviabrain" 2025