W DOC AIRBUS | TSM A320F

Fan Vibrations Higher than or Equal to 6 Units on Engine 1 or 2

TASK 77-00-00-810-864-A
Fan Vibrations Higher than or Equal to 6 Units on Engine 1 or 2

1. Possible Causes
  • wiring, connectors and receptacles
  • SENSOR-NO. 1 BRG VIB [4002EV]
  • TRF vibration sensor
  • EVMU
  • fan blades
  • LPT Stage 4 blades
  • fan blades mid-span shrouds
  • LPTACC valve manifold
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
BRUSH - BRISTLED
No specific
AR
PLIERS - NOSE, SOFT, LONG
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.CP2011)
stoddard solvent
 C. Referenced Information
REFERENCE
DESIGNATION
AMM 70-51-00-230-002
Fluorescent-Penetrant Inspection-Portable-Water Washable
AMM 71-00-00-710-006
Minimum Idle Check
AMM 71-00-00-750-001
Fan Trim Balance - 1 Sensor 3 Speed
AMM 72-21-00-210-004
Detailed Inspection and Relubrication of Fan Blade Dovetails, Midspan Shrouds, Retainers, Spacers, Dampers and Fan Disk Dovetail Slots
AMM 72-21-00-210-009
Inspection of Fan Rotor Blades Installed on the Fan Disk
AMM 72-21-00-210-025
Inspect Fan Rotor Blades Installed on the Fan Disk
AMM 72-21-00-290-001
Standard Borescope Inspection of Booster Rotor Blades, Stages 2, 3 and 4 through the Booster Inlet and Borescope Port SO
AMM 72-21-00-290-003
Borescope Inspection of the Booster Rotor Blades, Stages 2, 3, 4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5
AMM 72-31-00-290-001
Inspection of the High Pressure Compressor Rotor Assembly
AMM 72-31-00-290-002
Inspection of the High Pressure Compressor Rotor Assembly
AMM 72-52-00-290-001
Borescope Inspection of HPT Blades (from the front and the rear)
AMM 72-54-00-290-001
Inspection of the Stage 1-3 Blades
AMM 72-54-00-290-002
Inspection of the Stage 4 Blades
AMM 72-54-00-290-005
Inspection of the Stage 1-3 Blades
AMM 72-54-00-290-006
Inspection of the Stage 4 Blades
AMM 73-11-30-000-001
Removal of the LPTACC Fuel Tube Manifold
AMM 73-11-30-200-003
Inspection/Check of the LPTACC Fuel Manifold
AMM 73-11-30-400-001
Installation of the LPTACC Fuel Tube Manifold
AMM 73-21-50-210-001
Visual Inspection of the Wiring Harness
AMM 73-21-50-210-002
Visual Inspection of the Wiring Harnesses
AMM 77-31-10-720-001
Electrical Test of the No. 1 Bearing Vibration Sensor
AMM 77-31-10-720-002
Electrical Test of the No. 1 Bearing Vibration Sensor
AMM 77-31-30-000-001
Removal of the Turbine Rear Frame Vibration Sensor
AMM 77-31-30-000-002
Removal of the Turbine Rear Frame Vibration Sensor
AMM 77-31-30-400-001
Installation of the Turbine Rear Frame Vibration Sensor
AMM 77-31-30-400-002
Installation of the Turbine Rear Frame Vibration Sensor
ASM 773202
AMM 77-32-34-710-040
Operational Check of EVMU through CFDS for Advisory Indication on ECAM
AMM 77-32-34-860-041
Change the configuration of the Accelerometer
AMM 77-32-34-869-041
Change the configuration of the Accelerometer
AMM 79-00-00-281-002
Check of the Electrical Master Chip Detector (EMCD) for Particles
AMM 79-00-00-281-003
Check of FWD Sump, AFT Sump, AGB, and TGB Scavenge Screens
AMM 79-21-10-210-001
Check Supply and Scavenge Filters Clogging Indicator Position
AMM 79-21-10-210-002
Check of the Lubrication Unit Magnetic Plugs and Scavenge Screens
F Fan Vibrations Higher than or Equal to 6 Units on Engine 1 or 2 ** ON A/C NOT FOR ALL
F Fan Vibrations Higher than or Equal to 6 Units on Engine 1 or 2 ** ON A/C NOT FOR ALL
3. Fault Confirmation
Subtask 77-00-00-710-153-A ** ON A/C NOT FOR ALL
A. Test
   (1) Not applicable, the fault is evident.
NOTE: Vibration level is reported through a pilot report or mechanical report <07> or EVMU unbalance report.
4. Fault Isolation
Subtask 77-00-00-810-121-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified on the lower ECAM display unit by the crew observation: ENG 1(2)-FAN VIBRATION higher than 6 units:
   (1) Do the following checks if no aircraft structure vibration/rumble was also reported by the crew.
NOTE: If momentary vibration on ECAM is greater than 6 units but in order of less than 1 minute, no maintenance action is required provided indication is not associated with aircraft vibration felt by the crew and the indication did not repeat during the flight or following flights.
NOTE: Trouble Shooting is recommended at next maintenance opportunity not interfering with Revenue Service operation.
     (a) Do a check of the wiring, connectors and receptacles between ASM 773202:
  • The No. 1 vibration sensor (4002EV) to the EVMU (2EV)
  • The TRF vibration sensor (4003EV) to the EVMU (2EV).
     (b) Check for damaged pins or connector oxidation:
       1 If damage is found, repair or replace as necessary.
       2 Do a cleaning of the connectors using a BRUSH - BRISTLED with stoddard solvent (Material No.CP2011) AMM 73-21-50-210-001.
     (c) Do the electrical test of the No. 1 bearing vibration sensor (4002EV) AMM 77-31-10-720-002.
       1 If the resistance values are out of the limits, replace the SENSOR-NO. 1 BRG VIB [4002EV] at the next shop maintenance opportunity.
NOTE: The No. 1 bearing vibration sensor cannot be replaced on-wing.
     (d) Do an electrical test of the TRF vibration sensor:
       1 Disconnect the aircraft harness from the vibration sensor connectors. If necessary, use PLIERS - NOSE, SOFT, LONG.
       2 Measure the insulation resistance with a Megohmeter 0-100 Megohms, U= 50 VDC between:
. Pins 1 and 2
. Pins 1 and 3
. Pin 2 and connector body
. Pin 3 and connector body.
       3 The insulation resistance is expected to be greater than 20 Megohms. If any of these measurements are less than 20 Megohms, the sensor is not serviceable.
       4 If the TRF vibration sensor is not serviceable, it must be replaced AMM 77-31-30-000-001 and AMM 77-31-30-400-001.
     (e) If the checks (a), (b) and (c) are correct:
  • Do the operational test of the Engine Vibration Monitoring Unit EVMU through the Centralized Fault Display System (CFDS) AMM 77-32-34-710-040.
     (f) If the checks (a), (b), (c) and (d) are correct:
   (2) Do the following checks if aircraft structure vibration/rumble was also reported by the crew.
NOTE: During descent or approach in icing conditions, ice may build up on the fan blade and spinner cone and consequently lead to increase the fan vibration level on the engine(s).
     (a) If the engine has operated in icing conditions:
       1 Do a visual inspection around the engine to make sure that there is no ice ingestion damage, and especially do a check of the inlet cowl, fan blades, spinner cone, abradable material, OGV, acoustical panels (forward and mid) and splitter fairing.
       2 Do a check and an inspection of the accessories and QEC components. This includes the check and inspection of:
  • The accessory gearbox mounts,
  • The link and brackets of the accessories to make sure that they are not loose or broken,
  • The cowling brackets, hinges and rigging, and
  • The pneumatic system for correct condition and rigging.
         a If no damage is found:
  • No maintenance action is required.
         b If damage is found:
  • Repair or replace as required.
       3 If during the following flight you record an important decrease of EGT margin:
     (b) If the engine has not operated in icing conditions:
       1 Do a check of the fan blades AMM 72-21-00-210-025 and LPT Stage 4 blades for shingling or damage.
NOTE: A black light inspection of the fan blades can improve the detection of soft body impact. Refer to CFMI SPM 70-00-06-800-007.
         a If the check is not correct:
  • If fan blade damage or mid-span shroud shingling, repair as necessary.
  • If LPT Stage 4 blades shingling, use procedure AMM 72-54-00-290-002.
       2 Do a check and an inspection of the accessories and QEC components. This includes the check and inspection of:
  • The accessory gearbox mounts
  • The links and brackets of the accessories to make sure they are not loose or broken
  • The cowling brackets, hinges and rigging
  • The pneumatic system for correct condition and rigging.
         a If the check is not correct, repair or replace as necessary.
       3 Do a check of the Lube Supply and Common Scavenge Filters Clogging Indicator AMM 79-21-10-210-001 and do a check of the Magnetic Plugs and Screens AMM 79-21-10-210-002.
         a If you find magnetic particles, follow instructions per AMM and NDT Manual (Section CHIP ANALYSIS).
       4 Do a borescope inspection of booster assembly AMM 72-21-00-290-001.
       5 Do a borescope inspection of the Low Pressure Turbine AMM 72-54-00-290-001 and AMM 72-54-00-290-002.
       6 If the checks are correct:
Subtask 77-00-00-810-121-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified on the lower ECAM display unit by the crew observation: ENG 1(2)-FAN VIBRATION higher than 6 units:
   (1) Do the following checks if no aircraft structure vibration/rumble was also reported by the crew.
NOTE: If momentary vibration on ECAM is greater than 6 units but in order of less than 1 minute, no maintenance action is required provided indication is not associated with aircraft vibration felt by the crew and the indication did not repeat during the flight or following flights.
NOTE: Trouble Shooting is recommended at next maintenance opportunity not interfering with Revenue Service operation.
     (a) Do a check of the wiring, connectors and receptacles between ASM 773202:
  • The No. 1 vibration sensor (4002EV) to the EVMU (2EV)
  • The TRF vibration sensor (4003EV) to the EVMU (2EV).
     (b) Check for damaged pins or connector oxidation:
       1 If damage is found, repair or replace as necessary.
       2 Do a cleaning of the connectors using a BRUSH - BRISTLED with stoddard solvent (Material No.CP2011) AMM 73-21-50-210-002.
     (c) Do the electrical test of the No. 1 bearing vibration sensor (4002EV) AMM 77-31-10-720-001.
       1 If the resistance values are out of the limits, replace the SENSOR-NO. 1 BRG VIB [4002EV] at the next shop maintenance opportunity.
NOTE: The No. 1 bearing vibration sensor cannot be replaced on-wing.
     (d) Do an electrical test of the TRF vibration sensor:
       1 Disconnect the aircraft harness from the vibration sensor connectors. If necessary, use PLIERS - NOSE, SOFT, LONG.
       2 Measure the insulation resistance with a Megohmeter 0-100 Megohms, U= 50 VDC between:
. Pins 1 and 2
. Pins 1 and 3
. Pin 2 and connector body
. Pin 3 and connector body.
       3 The insulation resistance is expected to be greater than 20 Megohms. If any of these measurements are less than 20 Megohms, the sensor is not serviceable.
       4 If the TRF vibration sensor is not serviceable, it must be replaced AMM 77-31-30-000-002 and AMM 77-31-30-400-002.
     (e) If the checks (a), (b) and (c) are correct:
  • Do the operational test of the Engine Vibration Monitoring Unit EVMU through the Centralized Fault Display System (CFDS) AMM 77-32-34-710-040.
     (f) If the checks (a), (b), (c) and (d) are correct:
   (2) Do the following checks if aircraft structure vibration/rumble was also reported by the crew.
NOTE: During descent or approach in icing conditions, ice may build up on the fan blade and spinner cone and consequently lead to increase the fan vibration level on the engine(s).
     (a) If the engine has operated in icing conditions:
       1 Do a visual inspection around the engine to make sure that there is no ice ingestion damage, and especially do a check of the inlet cowl, fan blades, spinner cone, abradable material, OGV, accoustical panels (forward and mid) and splitter fairing.
       2 Do a check and an inspection of the accessories and QEC components. This includes the check and inspection of:
  • The accessory gearbox mounts,
  • The links and brackets of the accessories to make sure that they are not loose or broken,
  • The cowling brackets, hinges and rigging, and
  • The pneumatic system for correct condition and rigging.
         a If damage is found:
  • Repair or replace as required.
       3 If during the following flight you record an important decrease of EGT margin:
  • Do a borescope inspection of the HPC and do a check of HPC blades for damage AMM 72-31-00-290-002.
  • Do a borescope inspection of the HPT and do a check of HPT blades for damage AMM 72-52-00-290-001.

    PRE CFM SB 72-0696

    In case of high vibration above 8 units, verify the LPTACC valve manifold. Refer. 4. A.(3).

    END OF PRE CFM SB 72-0696

     (b) If the engine has not operated in icing conditions:
       1 Do a check of the fan blades AMM 72-21-00-210-009 and LPT Stage 4 blades for shingling or damage.
NOTE: A black light inspection of the fan blades can improve the detection of soft body impact. Refer to CFMI SPM 70-00-06-800-007.
         a If the check is not correct:
  • If fan blade damage or mid-span shroud shingling, repair as necessary.
  • If LPT Stage 4 blades shingling, use procedure AMM 72-54-00-290-006.
       2 Do a check and an inspection of the accessories and QEC components. This includes the check and inspection of:
  • The accessory gearbox mounts
  • The links and brackets of the accessories to make sure they are not loose or broken
  • The cowling brackets, hinges and rigging
  • The pneumatic system for correct condition and rigging.
         a If the check is not correct, repair or replace as necessary.
       3 Do a check of the Magnetic Chip Detector visual indicator, of the Magnetic Chip Detector AMM 79-00-00-281-002 and the Scavenge Screens Plugs AMM 79-00-00-281-003.
         a If you find magnetic particles, follow instructions per AMM 79-00-00-281-002 and NDT Manual (Section CHIP ANALYSIS).
       4 Do a borescope inspection of booster assembly AMM 72-21-00-290-003.
       5 Do a borescope inspection of the Low Pressure Turbine AMM 72-54-00-290-005 and AMM 72-54-00-290-006.
       6 If the checks are correct:
   (3) In case of High vibration above 8 units, verify the LPTACC valve manifold.
     (a) Perform an idle leak check AMM 71-00-00-710-006.
       1 If the check is not correct, repair or replace as necessary.
       2 If the check is correct, do a visual inspection of the LPTACC manifold AMM 73-11-30-200-003.
         a If the check is not correct (No cracks or indications are permitted), replace the LPTACC valve manifold AMM 73-11-30-000-001 and AMM 73-11-30-400-001.
         b If nothing is found during the visual check, perform a local fluorescent penetrant inspection AMM 70-51-00-230-002 within 5 cycles.

END OF PRE SB CFM 72-0696

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