Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power

TASK 24-28-00-710-001-A
Operational Test of the Static Inverter when the Aircraft Electrical Circuits are Energized from the External Power

ZONE: 210

1. Reason for the Job
Refer to the MPD TASK: 242800-01
OPERATIONAL CHECK OF STATIC INVERTER
Test of the correct power supply of the DC ESS BUS, AC ESS BUS and AC STAT INV BUS in emergency configuration when the batteries are the only power supply source.

NOTE: If the external power is not available, there is an alternative method (with the APU) for this procedure. This task gives the first method. For the alternative method, refer to the other task in this page block.

NOTE: If the external power is available and the APU is in operation, you must refer to the alternative method with the APU to do the operational test of the static inverter.

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
210	CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
812, 822

C. Referenced Information

REFERENCE	DESIGNATION
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure

3. Job Set-up
Subtask 24-28-00-860-050-A

A. Safety Precautions
(1) Do not energize the aircraft electrical circuits.
(2) On the panel 35VU, make sure that:

the BAT1 and BAT2 pushbutton switches are released,
the BUS TIE and AC ESS FEED pushbutton switches are pushed.

NOTE: On the panel 2000VU, put the MAINT BUS switch (5XX) in the OFF position during the test.

Subtask 24-28-00-010-050-A

B. Get access to the avionics compartment.
(1) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE at the access doors 812 and 822 of the avionics compartment.
(2) Open the access doors 812 and 822.

Subtask 24-28-00-865-050-A

C. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
105VU	ELEC/HOT BUS/702PP SPLY	5PB2	D02
105VU	ELEC/HOT BUS/701PP SPLY	5PB1	D01
105VU	ELEC/BAT REF/BCL2	9PB2	F02
105VU	ELEC/BAT REF/BCL1	9PB1	F01
105VU	ELEC/STAT INV/CNTOR/CTL	14XB	G02
105VU	ELEC/STAT INV/BUS 901XP/SPLY	12XB	H02
106VU	AC ESS BUS/EMER/STBY/CNTOR/SPLY	10XE	C06

4. Procedure

WARNING: TELL ALL THE PERSONS ON THE AIRCRAFT THAT:

THE LIGHTS WILL GO OFF DURING THIS TEST
THEY MUST NOT MOVE ON THE AIRCRAFT UNTIL THIS TEST IS COMPLETED.

IF NOT INJURY AND/OR DAMAGE CAN OCCUR WHEN THE LIGHTS GO OFF SUDDENLY.

Subtask 24-28-00-710-050-B

A. Operational Test of the Static Inverter

ACTION	RESULT
1.On the ELEC panel 35VU: Make sure that the voltage of the batteries 1 and 2 is higher than 25.5V.
2.Power supply the aircraft electrical circuits: Energize the aircraft electrical circuits from the external power (Ref. AMM TASK 24-41-00-861-002),
3.Do the EIS start procedure (upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
4.On the ECAM control panel: Get the ELEC page.	On the lower ECAM display unit: Make sure that the external power energizes correctly the aircraft electrical circuits.
5.On the ELEC panel 35VU: Release the BAT1 pushbutton switch.	On the ELEC panel 35VU: The OFF legend of the BAT1 pushbutton switch comes on.
Push the BAT1 pushbutton switch.	The OFF legend of the BAT1 pushbutton switch goes off.
Release the BAT2 pushbutton switch.	The OFF legend of the BAT2 pushbutton switch comes on.
Push the BAT2 pushbutton switch.	The OFF legend of the BAT2 pushbutton switch goes off.
	On the lower ECAM display unit: Make sure that the battery charge current (for BAT1 and BAT2) is lower than 60A after approximately 10 seconds. NOTE: If the current does not decrease after 10 seconds, it is necessary to do a charging cycle of the batteries. When the charging cycle is completed (batteries no longer connected to the DC BAT BUS), do the check again.
6.On the ELEC panel 35VU: Release the BAT1 and BAT2 pushbutton switches.	On the ELEC panel 35VU: The OFF legend of the BAT1 and BAT2 pushbutton switches comes on.
7.On the overhead control and indication panel 21VU, on the section EMER ELEC PWR: Open the guard, push and hold the EMER GEN TEST pushbutton switch during all the test,
On the ELEC panel 35VU: Release the BUS TIE pushbutton switch.	On the ELEC panel 35VU: The OFF legend of the BUS TIE pushbutton switch comes on.
8.On the ECAM control panel: Push and hold the ELEC key, the ELEC page comes into view and stays on during the test.	On the upper ECAM display unit: The DC ESS and AC ESS indications come on green, The amber SHED indication comes on under the DC ESS and AC ESS indications, The STAT INV indication comes on white and the related parameters come on green. NOTE: There is no green line between the STAT INV box and the AC ESS and DC ESS indications.
	On the ELEC panel 35VU: The OFF legend of the BAT1 and BAT2 pushbutton switches is off.
9.On the ELEC panel 35VU: Push the BUS TIE pushbutton switch. Push the BAT1 and BAT2 pushbutton switches.	On the panel 35VU: The OFF legend of the BUS TIE pushbutton switch goes off. The OFF legend of the BAT1 and BAT2 pushbutton switches goes off.
10.On the overhead control and indication panel 21VU: Release the EMER GEN TEST pushbutton switch.
11.On the ECAM control panel: Get the ELEC page.	On the lower ECAM display unit: Check that the external power energizes correctly the aircraft electrical circuits.

5. Close-up
Subtask 24-28-00-860-051-A

A. Put the aircraft back to its initial configuration.
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

Subtask 24-28-00-410-050-A

B. Close Access
(1) Close the access doors 812 and 822.
(2) Remove the access platform(s).

[Rev.10 from 2021] 2026.03.31 23:23:00 UTC