Functional Check to Monitor Internal Leak Rate of Blue Hydraulic System

TASK 29-10-00-220-002-A
Functional Check to Monitor Internal Leak Rate of Blue Hydraulic System

WARNING: MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

ZONE: 210

1. Reason for the Job
Refer to the MPD TASK: 291900-02
FUNCTIONAL CHECK TO MONITOR INTERNAL LEAK RATE OF BLUE HYDRAULIC SYSTEM
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	FLOWMETER 20.00 L.MN (5.2833 US GAL.MN)
610007AB	1	TOOL-MEASURE,HYDRAULIC FLOW
61007010-01	1	USF FIRMWARE FOR SA

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.14SBA1)	Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
210	CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
195BB
197EB

D. 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 29-00-00-280-002-A	Check of the Internal Leakage of the Blue Hydraulic System
TASK 29-10-00-863-003-A-01	Pressurize the Blue Hydraulic System with the Blue Electric Pump
TASK 29-10-00-863-003-A	Pressurize the Blue Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A-01	Pressurize the Blue Hydraulic System with the Blue Electric Pump
TASK 29-10-00-864-003-A	Depressurize the Blue Hydraulic System
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
Blue Hydraulic System - Complete Section ** ON A/C NOT FOR ALL
Blue Hydraulic System - Complete Section ** ON A/C NOT FOR ALL
Blue Hydraulic System - Complete Section ** ON A/C NOT FOR ALL
Leakage Transducer Installation Blue Complete Section ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 29-10-00-010-087-A

A. Open the access door 195BB.

Subtask 29-10-00-865-103-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/ELAC1/NORM/SPLY	15CE1	B11
49VU	FLIGHT CONTROLS/SEC1/NORM/SPLY	21CE1	B08
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/ELAC1/NORM/SPLY	15CE1	B06
49VU	FLIGHT CONTROLS/SEC1/NORM/SPLY	21CE1	B03
** ON A/C ALL
105VU	FLIGHT CONTROLS/ELAC2/STBY SPLY	16CE2	A02
105VU	FLT CTL/ELAC1/STBY SPLY	16CE1	A01
105VU	FLT CTL/SEC1/STBY SPLY	22CE	B01
121VU	HYDRAULIC/SOL VALVES/G/Y/B/LEAK/TST	1881GP	N35
121VU	FLIGHT CONTROLS/SEC3/SPLY	21CE3	Q19
121VU	FLIGHT CONTROLS/SEC2/SPLY	21CE2	Q18
121VU	FLIGHT CONTROLS/ELAC2/NORM/SPLY	15CE2	R20

Subtask 29-10-00-860-068-A ** ON A/C NOT FOR ALL

C. Aircraft Maintenance Configuration
(1) Make sure that the aircraft is in this configuration:

The spoilers 1 thru 5 retracted
All servo controls in their neutral position.

Subtask 29-10-00-860-068-B ** ON A/C NOT FOR ALL

C. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Set the ECAM system to ON (Ref. AMM TASK 31-60-00-860-001).
(3) On the ECAM control panel on the center pedestal, push the F/CTL pushbutton (P/B). Make sure that the lower display unit (DU) shows the F/CTL page.
(4) Pressurize the Blue hydraulic system
(Ref. AMM TASK 29-10-00-863-003)
(5) On the overhead panel 23VU, make sure that the ELAC 1 and SEC 1 pushbutton switches (P/BSW) are set to on (the OFF and FAULT lights are off).
(6) On the overhead panel 24VU, make sure that the ELAC 2, SEC 2 and SEC3 P/BSW are set to on (the OFF and FAULT lights are off).

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.

(7) Operate the sidestick and rudder pedals to put the control surfaces in the 0 deg. position (spoilers retracted).
(8) Keep all of the control surfaces stopped in the 0 deg (retracted) position during measurement of internal leakage.
(9) Do the checks of internal leakage with the hydraulic fluid at its usual working temperature of between 20 deg.C (68.00 deg.F) and 60 deg.C (140.00 deg.F).

4. Procedure
Subtask 29-10-00-220-051-A ** ON A/C NOT FOR ALL

A. Do this Functional Test

Blue Hydraulic System - Complete Section ** ON A/C NOT FOR ALL

(1) On the overhead maintenance panel 50VU, make sure that the HYD/LEAK MEASUREMENT VALVES/B P/BSW is set to on (the OFF light is off).
(2) Use a ground service cart with a FLOWMETER 20.00 L.MN (5.2833 US GAL.MN), calibrated to +/- 1.5% over full range, to pressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003).
(3) Make a record of the flow rate.
(4) Make sure that the flow rate is not more than 7.5 l (1.9813 USgal)/minute.
(5) If the flow rate is too high, do the full check of internal leakage to find the cause (Ref. AMM TASK 29-00-00-280-002).

Subtask 29-10-00-220-051-B ** ON A/C NOT FOR ALL

A. Do this functional test:

NOTE: You can do this test with or without an Ultrasonic Flowmeter (USF). If the internal leakage is out of limits then the USF must be used to prevent an Aircraft On Ground (AOG) condition.

(1) Measure the internal leakage of the Blue hydraulic system (complete) without a USF:
(a) On overhead maintenance panel 50VU, make sure that the HYD/LEAK MEASUREMENT VALVES/B P/BSW is set to ON (the OFF light is off).
(b) Open access door 197EB.
(c) Connect a ground service cart with the FLOWMETER 20.00 L.MN (5.2833 US GAL.MN), calibrated to +/- 1.5% over full range, to pressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-863-003).
(d) Monitor the flow shown on the ground supply flow meter.
(e) Make sure that the flow rate is not more than 7.5 l.min (1.9813 USgal.mn).
(f) If the internal leakage is more than 7.5 l.min (1.9813 USgal.mn):
1 Depressurize the Blue hydraulic system
(Ref. AMM TASK 29-10-00-864-003).
2 Disconnect the ground supply from aircraft ground test connections.
3 Install the blanking caps on the ground test connections.
4 Pressurize the Blue hydraulic system with electric pump (Ref. AMM TASK 29-10-00-863-003).
5 Close access door 197EB.
6 Do the leakage check of all sections of the Blue hydraulic system to find the cause of high leakage (Ref. AMM TASK 29-00-00-280-002).
(2) Measure the Blue hydraulic system (complete section) internal Leakage with the USF:

Blue Hydraulic System - Complete Section ** ON A/C NOT FOR ALL

(a) On the overhead maintenance panel 50VU, make sure that the HYD/LEAK MEASUREMENT VALVES/B P/BSW is set to on (the OFF light is off).
(b) Refer to the lower DU of the ECAM (HYD page) to make sure that the solenoid valve operation is correct (the flow arrow of the Blue hydraulic system is green and the system name is white).
(c) Refer to the ground instruction manual of the USF to make sure that the 61007010-01 USF FIRMWARE FOR SA is installed.
(d) Clean the tube (1) between the identification tapes (2) with a lint-free cotton cloth Textile-Lint free Cotton - (Material No.14SBA1) .
(e) Do not use detergents to clean the leakage transducer (5). Remove traces of acoustic coupling compound from the leakage transducer (5) and clean it with a lint-free cotton cloth Textile-Lint free Cotton - (Material No.14SBA1) .
(f) Apply a thin layer of the acoustic coupling compound (part of USF FLUXUS GST 6108, 610007AB TOOL-MEASURE,HYDRAULIC FLOW) to the contact surfaces of the leakage transducer (5).
(g) Install the leakage transducer (5) between the identification tapes (2) on the pipe (1)

Leakage Transducer Installation Blue Complete Section ** ON A/C NOT FOR ALL

:
1 Hold the leakage transducer (5) and turn the knurled screw (6) counterclockwise to the stop.
2 Put the leakage transducer (5) in position on the pipe (1) between the identification tapes (2) and push it tightly on the pipe (1).
3 Push the knurled screw (6) in and attach the fastening strap (4) around the pipe (1) with the threading element (3).
4 Put the fastening strap (4) through the upper slot of the strap clamp (7) and then through the lower one.
5 Make sure that the fastening strap (4) has the correct tension. And make sure that the knurled screw (6) is pushed in up to the stop.
6 Tighten the knurled screw (6) to attach the leakage transducer (5) to the pipe (1).
(h) Connect the leakage transducer cable (8) to the transmitter (9).
(i) Refer to the ground instruction manual of the USF to set:

The serial number of the airplane
The input location code on the USF to numeric code: 31437966 (Blue complete section).

(j) Obey the instructions of the ground instruction manual of the USF to do the measurement.
(k) Monitor the flow on the USF display. It must not be more than 7.5 l.min (1.9813 USgal.mn).
(l) Make a record of the flow rate.
(m) If the internal leakage is more than 7.5 l.min (1.9813 USgal.mn) do the full check for internal leakage to find the cause of the high internal leakage (Ref. AMM TASK 29-00-00-280-002).
(n) Remove the leakage transducer (5):
1 Hold the leakage transducer (5) and turn the knurled screw (6) counterclockwise to disconnect the leakage transducer (5) from the pipe (1).
2 Push the knurled screw (6) in and disconnect the fastening strap (4) from the strap clamp (7).
3 Remove the leakage transducer (5) from the pipe (1).
(o) Disconnect the leakage transducer cable (8) from the transmitter (9).

5. Close-up
Subtask 29-10-00-860-069-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to the serviceable condition.
(1) Remove the ground service cart and the flow meter from the aircraft.
(2) Depressurize the Blue hydraulic system (Ref. AMM TASK 29-10-00-864-003).

Subtask 29-10-00-860-069-B ** ON A/C NOT FOR ALL

A. Put the aircraft back to the serviceable condition.
(1) Refer to the lower DU of the ECAM (HYD page) and make sure that the solenoid valve operates correctly (the flow arrow of the Blue hydraulic system is green and the system name is white).
(2) Depressurize the Blue hydraulic system
(Ref. AMM TASK 29-10-00-864-003).
(3) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(4) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

Subtask 29-10-00-410-087-A

B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the access door 195BB.

[Rev.10 from 2021] 2026.04.01 00:14:19 UTC