Operational Test of the FADEC on the Ground (with Engine Motoring) A320
WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
WARNING: MAKE SURE THAT ALL ENGINE OPERATING AREAS ARE AS CLEAN AS POSSIBLE. ALL RAMPS, TAXIWAYS, RUNWAYS AND OTHER OPERATING AREAS MUST BE VERY CLEAN TO PREVENT BAD DAMAGE TO THE ENGINE, AIRCRAFT AND PERSONS IN THE AREA.
WARNING: DO NOT TRY TO STOP THE FAN FROM TURNING BY HAND. THIS CAN CAUSE INJURY TO THE PERSONS AND DAMAGE TO THE EQUIPMENT.
WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKS ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.
WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
CAUTION: — SEE THE APPLICABLE FIGURE FOR WIND LIMIT RESTRICTIONS WHEN THE ENGINE OPERATES.
— NATURAL WINDS AND IRREGULAR FORCES FROM SUDDEN GUSTS INCREASE THE DANGEROUS AREA.
— DO NOT GO ABOVE OPEN COWLING LIMITATIONS WHEN YOU DO THE TESTS.
— THE OPERATOR MUST FULLY KNOW ALL THE OPERATING LIMITS AND PROCEDURES BEFORE THE ENGINE OPERATES.
CAUTION: DO NOT REPLACE AN IDLE LEAK CHECK BY A MOTORING TEST. YOU CANNOT DETECT POTENTIAL OIL LEAKS WITH A MOTORING TEST. IF YOU DO A MOTORING TEST INSTEAD OF AN IDLE LEAK CHECK, YOU CAN CAUSE AN ENGINE SHUTDOWN.
CAUTION: MAKE SURE THAT THERE IS NO HYDRAULIC GROUND POWER SUPPLY CONNECTED TO THE AIRCRAFT WHEN YOU DO THIS PROCEDURE. IF A HYDRAULIC GROUND POWER SUPPLY IS CONNECTED, THERE IS A RISK OF DAMAGE TO THE ENGINE PUMPS.
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
| No specific | AR | GROUND AIR-SUPPLY UNIT(HIGH PRESSURE) |
B. Work Zones and Access Panels
| ZONE/ACCESS | ZONE DESCRIPTION |
| 210 | CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD |
| 400 | POWER PLANT, NACELLES AND PYLONS |
C. Referenced Information
| REFERENCE | DESIGNATION |
| Ref. 10-11-00-555-013-A | Installation of the Aircraft Protection Equipment |
| Ref. 10-11-00-555-014-A | Removal of the Aircraft Protection Equipment |
| Ref. 12-12-29-611-001-A | Fill the Hydraulic Fluid Reservoir with a Hand Pump |
| Ref. 12-12-29-611-002-A | Fill the Hydraulic Fluid Reservoir with a Hydraulic Service Cart |
| Ref. 12-13-79-610-002-A | Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector) |
| Ref. 12-13-79-610-002-A01 | Check oil level and replenish (Pressure Filling) |
| Ref. 24-41-00-861-002-A | Energize the Aircraft Electrical Circuits from the External Power |
| Ref. 24-41-00-861-002-A01 | Energize the Aircraft Electrical Circuits from the APU |
| Ref. 24-41-00-861-002-A02 | Energize the Aircraft Electrical Circuits from Engine 1(2) |
| Ref. 24-41-00-862-002-A | De-energize the Aircraft Electrical Circuits Supplied from the External Power |
| Ref. 24-41-00-862-002-A01 | De-energize the Aircraft Electrical Circuits Supplied from the APU |
| Ref. 24-41-00-862-002-A02 | De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) |
| Ref. 29-14-00-614-002-A | Pressurization of the Hydraulic Reservoirs through the Ground Connector |
| Ref. 29-14-00-614-002-A01 | Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU) |
| Ref. 31-32-00-860-012-A | Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page |
| Ref. 36-12-00-860-001-A | Pressurization of the Bleed System with the APU |
| Ref. 36-12-00-860-002-A | Pressurization of the Bleed System through the HP Ground Connector |
| Ref. 78-36-00-010-040-B | Opening of the Thrust Reverser Doors |
| Ref. Fig. FADEC Test Engine Motoring | |
3. Job Set-up
SUBTASK 73-29-00-869-050-A
A. Safety Precautions
WARNING: DO NOT TRY TO STOP THE FAN FROM TURNING BY HAND. THIS CAN CAUSE INJURY TO THE PERSONS AND DAMAGE TO THE EQUIPMENT.
CAUTION: REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THIS PROCEDURE. IF YOU DO NOT REMOVE THEM, THE PROBES AND PROTECTIVE COVERS CAN BECOME DAMAGED OR BURNED.
(1) Remove the protective covers from the probes and sensors before you do this procedure Ref. AMM TASK 10-11-00-555-014.
(2) Make sure that:
— the engine,
— the air intake,
— the exhaust areas, are clear of equipment, persons, tools, blockages, all unwanted objects and ice.
(3) Make sure that the fan parts and the engine inlet area are in the correct condition. Make a full inspection of the fan blades.
(4) Examine the external surfaces of the cowl. Make sure that there are no leaks of fuel and oil at the drain ports.
SUBTASK 73-29-00-861-050-A
B. Energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-861-002.
SUBTASK 73-29-00-860-050-A
C. Do a check of the Aircraft Condition:
(1) On the lower display unit of the ECAM system on the ENG page:
(a) make sure that the oil level is correct.
1 If it is necessary, do the servicing of the tank Ref. AMM TASK 12-13-79-610-002.
(2) If you let the engine stay open to freezing rain, ice or snow ; make sure that the fan turns freely.
(a) If the fan does not turn freely, you must make the engine warm with hot air. You must do this step before an engine motoring.
(3) Make sure that the hydraulic reservoirs are pressurized Ref. AMM TASK 29-14-00-614-002.
(4) Make sure that the level of the hydraulic fluid in the reservoir is correct. If necessary, fill the reservoir Ref. AMM TASK 12-12-29-611-001 or Ref. AMM TASK 12-12-29-611-002.
NOTE: You can do this test with the thrust reverser doors in open position (35 deg.) Ref. AMM TASK 78-36-00-010-040.
SUBTASK 73-29-00-865-050-A
D. Make sure that this(these) circuit breaker(s) is(are) closed:
| PANEL | DESIGNATION | FIN | LOCATION |
| 49VU | ENGINE/1 AND 2/IGN/SYS A | 1JH | A03 |
| FOR FIN 1000EM1(ENGINE-1) | |||
| 49VU | FUEL/LP VALVE/MOT1/ENG1 | 1QG | A08 |
| 49VU | ENGINE/1/FADEC A/AND EIU 1 | 2KS1 | A04 |
| 49VU | ENGINE/1/HP FUEL SOV | 1KC1 | A01 |
| 121VU | FUEL/LP VALVE/MOT2/ENG1 | 3QG | M25 |
| 121VU | ENGINE/IGN/ENG1/SYS B | 3JH1 | P41 |
| 121VU | ENGINE/IGN/ENG1/SYS A BAT | 2JH1 | P39 |
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R41 |
| FOR FIN 1000EM2(ENGINE-2) | |||
| 49VU | FUEL/LP VALVE/MOT1/ENG2 | 2QG | A09 |
| 49VU | ENGINE/2/FADEC A/AND EIU 2 | 2KS2 | A05 |
| 49VU | ENGINE/2/HP FUEL SOV | 1KC2 | A02 |
| 121VU | FUEL/LP VALVE/MOT2/ENG2 | 4QG | M26 |
| 121VU | ENGINE/IGN/ENG2/SYS B | 3JH2 | P42 |
| 121VU | ENGINE/IGN/ENG2/SYS A BAT | 2JH2 | P40 |
| 121VU | ENGINE/ENG2/FADEC B | 4KS2 | Q40 |
SUBTASK 73-29-00-941-050-A
E. Connect a GROUND AIR-SUPPLY UNIT(HIGH PRESSURE) to the HP connectors or use the air from the APU Ref. AMM TASK 36-12-00-860-001 or Ref. AMM TASK 36-12-00-860-002. Make sure that the pressure of the air supply is between 25 psi (1.7 bar) and 55 psi (3.8 bar).
SUBTASK 73-29-00-860-051-A
F. Do a check of the Panels to Prepare for Test.
(1) On the AIR COND panel 30VU, make sure that the PACK 1/ENG 1 BLEED and PACK 2/ENG 2 BLEED push-button switches are released (the OFF legends are on).
(2) On the maintenance panel 50VU, push then release the FADEC GND PWR 1(2) push-button switch (on this push-button switch, the ON legend is on).
(3) On the left or right MCDU, get the SYSTEM REPORT/TEST, ENG page Ref. AMM TASK 31-32-00-860-012.
(4) On the fuel part of the fuel control panel 40VU, push all the PUMPS push-button switches. On the push-button switches, the OFF legend go off.
(5) On the ADIRS control display panel set the ADIRU to the NAV position. (the OFF light goes off).
4. Procedure
SUBTASK 73-29-00-710-050-B
CAUTION: DO NOT OPERATE THE ENGINE IF THE FUEL INLET PRESSURE IS NOT POSITIVE. THE FUEL IS NECESSARY TO LUBRICATE THE ENGINE FUEL PUMP AND THE HMU AND THUS PREVENT DAMAGE.
A. Do this test:
Ref. Fig. FADEC Test Engine Motoring
NOTE: This test is for the system 1. For the other system(s), use the indications between the parentheses.
ACTION RESULT 1.Supply the engine with fuel. NOTE:If the fuel line or fuel equipment has been disconnected/removed dowstream of the LP valve before the FADEC test with engine motoring, start the fuel pumps and open the LP valve. A.On the HYD/FUEL panel 40VU:-Make sure that the engine 1(2) pump is serviceable (the OFF legend of the ENG1(2) PUMP pushbutton switch must be off). B.Open the circuit breaker 1KC1(2) to open the LP valve. -On the upper ECAM display unit this message comes into view:-ENG 1(2) LP VALVE OPEN-The single chime operates.-The MASTER CAUT light comes on. 2.Push the line key adjacent to the FADEC 1A (2A) indication. The ENGINE 1(2) MAIN MENU comes into view. 3.Push the line key adjacent to the FADEC TEST indication. The FADEC TEST menu comes into view. 4.On the MCDU, push the line key adjacent to the PUSH BUTTON TO START THE TEST indication. A new FADEC TEST menu comes into view 5.On the ENG panel 115VU, make sure that the ENG MODE CRANK/NORM/IGN/START selector switch is set to NORM. 6.On the ENG panel 115VU, set the ENG MASTER 1(2) control switch to ON and make sure that:-The engine operates (N2).-The oil pressure indication is positive. The indication «WARNING TEST ACTIVE» comes into view. When the test is finish the FADEC TEST REPORT comes into view 7.Push the line key adjacent to RETURN The page TEST COMPLETE comes into view 8.Set the ENG MASTER 1(2) lever to OFF. 9.Push the line key adjacent to the RETURN indication until the SYSTEM REPORT/TEST ENG MENU comes into view. The ENGINE 1(2) MAIN MENU page comes into view 10.Do an ECU reset. To do this position the ENG MASTER control switch to ON then OFF. 11.Do the same procedure for channel B of the FADEC 1 (2). 12.On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view. The MCDU menu comes into view. 13.Stop the MCDU. 14.Close the circuit breaker 1KC1(2) to close the LP valve. On the upper ECAM display unit:-The ENG 1(2) LP VALVE OPEN message goes out of view. The master CAUT light goes off.
5. Close-up
SUBTASK 73-29-00-860-052-A
A. Check Panels for Close-up.
(1) On the FUEL part of the fuel control panel 40VU, release all the PUMPS pushbutton switches. On the pushbutton switches, the OFF legends come on.
(2) On the maintenance panel 50VU, push the ENG1 (2) FADEC GND PWR pushbutton switch. On the pushbutton switch, the ON legend goes off.
(3) Set the ADIRU to the OFF position.
(4) On the overhead panel 40VU, make sure that the ENG PUMP pushbutton switches are set to on (FAULT and OFF lights are off).
(5) Install the protective covers on the probes and sensors Ref. AMM TASK 10-11-00-555-013.
SUBTASK 73-29-00-942-050-A
B. Disconnect the HP ground air supply unit, or stop the APU.
SUBTASK 73-29-00-862-050-A
C. De-energize the aircraft electrical circuits Ref. AMM TASK 24-41-00-862-002.
