V2500 TS

(1)

A3318 A320 A/C Registration

Tech LLog

g

A3319 A321

_HC-HSD

289423_01

Date (UTC) Flight No. From To ATA Chapter Pos / FIN Code

Apr 27, 2009 SRT123 OVB-ZRHH 70-00

Complaint:

Signature Crew Commpl. Maint. Coompl. Scheduled Maintennance

Action:

Transf. To Reference (MEL orr other) A C Limitations None Flt Hours

ADD B D Final Date Cycles

'XULQJGHVFHQW0$,17676(1*)$'(&

ST

A

TUS P

AGE

ENG 1: ACC ACTUATOR 4027KS REPLACED ACC. AMM 75-24-52 REV.

FEB 01/09

(2)

(3)

LAST LEG REPORT FADEC 1A

INTERROGATE CFDS (FADEC PWR ON)

LAST LEG REPORT FADEC 1B

ON

OFF

ON

HYD

APU

ENG

BLUE PUMP

OVRD

BLUE PUMP

OVRD

G

LEAK MEASUREMENT VALVES

B

Y

TEST

AUTO EXTING

RESET

FADEC GND PWR

1

2 ON

OK

(4)

(5)

(6)

(7)

TASK 75-24-00-810-801

Failure of the Active Clearance Control-Actuator on Engine 1

Fault Symptoms

** ON A/C ALL 75-24-00-810-801 Warnings/malfunctions ATA Message 77-11 ENG 1 FADEC Fault messages

ATA Message Source Class

75-24-52 ACC ACT/HC/EEC1 EIU1FAD 2

Isolation Procedure

1. Possible Causes

- wiring from the ACC actuator (4027KS) to the EEC (4000KS) - ACTUATOR ACC (4027KS)

- EEC (4000KS) 2. Job Set-up Information

A. Referenced Information

REFERENCE DESIGNATION

73-00-00-810-900 Multiple Dual Track Check Faults on the Engine 1

AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power

AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power

AMM 31-60-00-860-002 EIS Stop Procedure

AMM 70-23-15-912-010 Connection of Electrical Connectors

AMM 71-00-00-710-013 Test No.11 : High Power Assurance Test

AMM 71-50-00-210-010 Wire Harness Visual Inspection - All Power Plant Electrical Cables

AMM 73-22-00-710-040 Operational Test of the FADEC SYSTEM on the Ground

AMM 73-22-34-000-010 Removal of the Electronic Engine Control (EEC) (4000KS)

AMM 73-22-34-400-010 Installation of the Electronic Engine Control (EEC) (4000KS)

AMM 75-24-52-000-010 Removal of the High Pressure Turbine/Low Pressure Turbine (HPT/LPT) Valve Actuator (4027KS)

AMM 75-24-52-400-010 Installation of the High Pressure Turbine/Low Pressure Turbine (HPT/LPT) Valve Actuator (4027KS)

AMM 78-32-00-010-010 Opening of the Thrust Reverser Halves

AMM 78-32-00-410-010 Closing of the Thrust Reverser Halves

ASM 73-25/18

TSM 70-00-00 P.Block 301 STANDARD PRACTICES - ENGINE - GENERAL

(Ref. Fig. 201/75-24-00-991-001 SHEET 201.1)

3. Fault Confirmation A. Job Set-Up

** ON A/C ALL

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

(8)

(Ref. Fig. 201/TASK 75-24-00-991-001 SHEET 201.1)

NOTE: Multiple Dual Track Check Faults may indicate a failed fuel pump. Four control units on the engine are driven by HP fuel: the VSV actuator, the 2.5 Bleed Controller, the ACOC Air Modulating Valve and the Active Clearance Control Actuator. If you have faults with two or more of these units, you must follow the Multiple Dual Track Check Faults procedure

(Ref. TSM TASK 73-00-00-810-900) .

(1) Energize the aircraft electrical circuits AMM TASK 24-41-00-861-002 .

(2) On the panel 50VU, release the ENG FADEC GND PWR 1 and 2 pushbutton switches. B. FADEC Ground Test

(1) Do the CFDS Message Decoding and read the Scheduled Maintenance Report (Ref. TSM TSM 70-00-00 P.Block 301) .

(2) If the readout gives one of the following fault codes in FADEC 1A or FADEC 1B (Fault Acronym: HCCWAF): - do the FADEC Ground Test

AMM TASK 73-22-00-710-040 for fault confirmation. - continue with Fault Isolation Para 4.

(3) If the fault code readout in (1) does not give one of the above listed fault codes: - continue with fault confirmation by Engine Ground Run Section 4.B below. C. Test

(1) On the panel 50VU, push the ENG FADEC GND PWR 1 pushbutton switch and release it again. NOTE: This action resets the FADEC memory.

(2) Do the test No. 11: high power assurance test AMM TASK 71-00-00-710-013 .

(3) Read the LAST LEG REPORT and the scheduled maintenance report of the FADEC (1A and 1B) menu on the MCDU (Ref. TSM TSM 70-00-00 P.Block 301) and make a record of the maintenance message and the fault code for the applicable fault cells.

4. Fault Isolation

A. If the test gives the maintenance message ACC ACT/HC/EEC1: - open the thrust reverser halves 451AL and 452AR

AMM TASK 78-32-00-010-010

- examine the harness

AMM TASK 71-50-00-210-010 from the EEC (4000KS) to the ACC actuator (4027KS) ASM 73-25/18 . (1) If the fault continues:

- disconnect the connector from the ACC actuator - examine the connector and receptacle

AMM TASK 71-50-00-210-010

- connect the connector to the ACC actuator

AMM TASK 70-23-15-912-010 . (2) If the fault continues:

read the fault code shown on the FLIGHT DATA and GROUND DATA of the FADEC (1A and 1B) menu on the MCDU

(Ref. TSM TSM 70-00-00 P.Block 301) - make a record of the fault code.

(a) If the FADEC 1A menu gives the fault code HCCL:

- disconnect the electrical harness connector (4000KS-J2) from the EEC (4000KS) - examine the connector and the receptacle

-

at the electrical connector (4000KS-J2), do a check of the resistance between: . pins P and f (86 to 146 ohms)

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

Print Date: Apr 27/09 Local Time

Page 2 of 8

A. If the test gives the maintenance message ACC ACT/HC/EEC1: - open the thrust reverser halves 451AL and 452AR

AMM TASK 78-32-00-010-010

- examine the harness

AMM TASK 71-50-00-210-010 from the EEC (4000KS) to the ACC actuator (4027KS) ASM 73-25/18 . (1) If the fault continues:

- disconnect the connector from the ACC actuator - examine the connector and receptacle

AMM TASK 71-50-00-210-010

- connect the connector to the ACC actuator

AMM TASK 70-23-15-912-010 . (2) If the fault continues:

- read the fault code shown on the FLIGHT DATA and GROUND DATA of the FADEC (1A and 1B) menu on the MCDU

(Ref. TSM TSM 70-00-00 P.Block 301) - make a record of the fault code.

(9)

. pins R and g (40 to 67 ohms)

1 If the resistance between the pins P and f is not between 86 and 146 ohms:

a Disconnect the electrical harness connector (4027KS-A) from the ACC actuator (4027KS). b Do a check of the resistance between the pins 10 and 3. If the resistance is not between 86 and

146 ohms:

- Remove and replace the ACTUATOR-ACC (4027KS)

AMM TASK 75-24-52-000-010 and AMM TASK 75-24-52-400-010 .

- If the resistance is between 86 and 146 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/10, 3 to pins J2/P, f

ASM 73-25/18

- connect the electrical connector (4000KS-J2) to the EEC (4000KS)

AMM TASK 70-23-15-912-010 .

2 If the resistance between the pins R and g is not between 40 and 67 ohms:

67 ohms:

- remove and replace the ACTUATOR-ACC (4027KS)

AMM TASK 75-24-52-000-010 and AMM TASK 75-24-52-400-010

- If the resistance is between 40 and 67 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/8, 9 to pins J2/R, g

ASM 73-25/18

AMM TASK 70-23-15-912-010 . (b) If the FADEC 1B menu gives the fault code HCCL:

- at the electrical connector (4000KS-J8), do a check of the resistance between: . pins P and f (86 to 146 ohms)

. pins R and g (40 to 67 ohms)

a Disconnect the electrical harness connector (4027KS-A) from the ACC actuator (4027KS). b Do a check of the resistance between the pins 11 and 12. If the resistance is not between 86

and 146 ohms:

ASM 73-25/18

AMM TASK 70-23-15-912-010 .

and 67 ohms:

ASM 73-25/18

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

(10)

AMM TASK 70-23-15-912-010 .

(c) If the FADEC 1A menu gives the fault code HCCWAF:

at the electrical connector (4000KS-J3), do a check of the resistance between pins p and n (17 to 32 ohms).

1 If the resistance between the pins p and n is not between 17 and 32 ohms:

32 ohms:

- If the resistance is between 17 and 32 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/5, 14 to pins J3/p, n

ASM 73-25/18

AMM TASK 70-23-15-912-010 .

(d) If the FADEC 1B menu gives the fault code HCCWAF:

and 32 ohms:

ASM 73-25/18

AMM TASK 70-23-15-912-010 . (e) If the FADEC 1A menu gives the fault code HCCTK:

. pins R and g (40 to 67 ohms).

146 ohms:

ASM 73-25/18

AMM TASK 70-23-15-912-010 .

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

Print Date: Apr 27/09 Local Time

Page 4 of 8

(d) If the FADEC 1B menu gives the fault code HCCWAF:

- at the electrical connector (4000KS-J9), do a check of the resistance between pins p and n (17 to 32 ohms).

and 32 ohms:

AMM TASK 75-24-52-000-010and AMM TASK 75-24-52-400-010.

ASM 73-25/18

AMM TASK 70-23-15-912-010.

in varianta pt elevi este trecut canalul FADEC 1B cu codul

HCCWAF

(11)

67 ohms:

ASM 73-25/18

AMM TASK 70-23-15-912-010 . 3 If the resistance values are in the specified limits:

a If the resistance between the pins p and n is not between 17 and 32 ohms:

- Disconnect the electrical harness connector (4027KS-A) from the ACC actuator (4027KS). - Do a check of the resistance between the pins 5 and 14. If the resistance is not between 17

and 32 ohms:

Remove and replace the ACTUATOR-ACC (4027KS) AMM TASK 75-24-52-000-010 and

AMM TASK 75-24-52-400-010 .

If the resistance is between 17 and 32 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/5, 14 to pins J3/p, n ASM 73-25/18

connect the electrical connector (4000KS-J3) to the EEC (4000KS) AMM TASK 70-23-15-912-010 .

(f) If the FADEC 1B menu gives the fault code HCCTK:

1 If the resistance between the pin P and F is not between 86 and 146 ohms:

and 146 ohms:

ASM 73-25/18

AMM TASK 70-23-15-912-010 .

and 67 ohms:

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

(12)

ASM 73-25/18

a If the resistance between the pins p and n is not between 17 and 32 ohms:

and 32 ohms:

remove and replace the ACTUATOR-ACC (4027KS) AMM TASK 75-24-52-000-010 and

AMM TASK 75-24-52-400-010

If the resistance is between 17 and 32 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/16, 15 to pins J9/p, n ASM 73-25/18

AMM TASK 70-23-15-912-010 .

(g) If the FADEC 1A and FADEC 1B menus give the fault code HCCXCF:

146 ohms:

ASM 73-25/18

AMM TASK 70-23-15-912-010 .

67 ohms:

ASM 73-25/18

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

(13)

a If the resistance between the pins P and f is not between 86 and 146 ohms:

and 146 ohms:

AMM TASK 75-24-52-400-010

If the resistance is between 86 and 146 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/11, 12 to pins J8/P, f ASM 73-25/18

b If the resistance between the pins R and g is not between 40 and 67 ohms:

and 67 ohms:

AMM TASK 75-24-52-400-010

If the resistance is between 40 and 67 ohms then do a check and repair the wiring from the ACC actuator (4027KS) to the EEC (4000KS) pins A/19, 18 to pins J8/R, g ASM 73-25/18

(3) If the fault continues:

- Replace the ACTUATOR ACC (4027KS)

AMM TASK 75-24-52-000-010 AMM TASK 75-24-52-400-010 . (4) If the fault continues:

- Replace the EEC (4000KS)

B. Repeat the fault confirmation as given in Para. 3 using the same method (FADEC Ground Test or Engine Ground Run) as before and confirm fault elimination.

5. Close-up

A. Put the aircraft back to its initial configuration.

(1) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF. AMM TASK 31-60-00-860-002 .

(2) On the panel 50VU, release the ENG FADEC GND PWR 1 and 2 pushbutton switches. (3) De-energize the aircraft electrical circuits AMM TASK 24-41-00-862-002 .

(4) Make sure that the thrust reverser halves 451AL and 452AR are closed AMM TASK 78-32-00-410-010 .

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

(14)

CH A CH B p p CH A CH B

T/M RESISTANCE (ohms) LVDT RESISTANCE (ohms)

CH A

CH B p

p 40 - 67

40 - 67

Figure 75-24-00-991-001 / SHEET 201.1/1 - ACC Actuator ** ON A/C ALL

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1 For training purpose only

(15)

BL EED 4 3 5 (4 4 5 ) ST A4 8 0 A 402 2K S A C T U A T OR -V S V 45 3(4 63) S T A 520 A A A A 4027 K S A C T U A T OR -A C C 45 4(4 64) S T A 5 20 A R D D R AI N T/ M C H .A T /M CH. B D VAL V E G R O D 4020 K S 1 S O L-H P C P R S R ST G 7 BL V1 4 3 6 (4 4 6 ) ST A4 5 0 A 4020 K S 2 S O L-H P C P R S R ST G 7 BL V2 4 3 6 (4 4 6 ) ST A4 5 0 4020 K S 3 S O L-H P C P R S R S T G7 B L V 3 436 (4 46) S T A 4 50 4029 K S S O L-S E R V IC E S T A G E 10 43 6(4 46) S T A 450 400 0K S EEC 43 6(4 46) S T A 450 CHA NN E L A CH A N N E L B J3 J3 J2 J2 J3 J3 J4 J4 A A A SA M E A S 40 20 K S 3 SA M E A S 40 20 K S 3 BL EE D VA L V E 12 32 13 14 33 34 10 12 13 14 15 16 17 18 19 20 15 16 35 36 17 18 37 38 BL E E D VA L V E C L O S ED B L EE D VA L V E O P E N K L J4 J5 J5 J4 J3 J3 VEN T SE R V O VEN T P3 S U PP L Y P3 S U PP L Y J2 J2 T C AV SW IT C H ST G 1 0 SVC E S O L AC O C T /M AC O C L V D T EX C N AC O C L V D T ST G 1 0 BL SO L T C AV SO L T C AV SO L ST G 1 0 BL SO L K L AC O C L V D T AC O C L V D T EX C N AC O C T /M 22 23 24 25 26 27 28 29 30 T C AV SW IT C H ST G 1 0 SVC E S O L 32 33 34 35 36 37 38 39 40 CH A LV D T 16 15 14 19 18 12 10 L P T U R B IN E CO N T RO L LV D T CH B T/ M CH A T/ M CH B 23 24 19 20 39 40 22 30 29 28 27 10 25 26 401 9K S M O D U LA T IN G V A L V E -A C O C 43 6(4 4 6 ) S T A 450 T/ M CH A T/ M CH B A J1 0 J1 0 J9 J9 J8 J8 B S BVA L V D T BS BV A L V D T EXC N BS BV A T /M SVA T /M SV A L V D T SV A L V D T E X C N A CC L V DT A C C L V DT E X CN AC C T /M J9 A K C A LV D T CH .B LV D T CH .A 10 12 13 14 15 16 33 34 25 26 27 28 13 14 15 16 23 24 10 35 36 17 18 19 20 J9 AC C T /M A C C L V DT E X CN A CC L V DT SV A L V D T E X C N SV A L V D T SVA T /M BS BV A T /M 29 30 32 17 18 19 20 22 12 B S BVA L V D T BS BV A L V D T EXC N L V DT CH. B L V DT CH .A A A T O AIR VAL V E AC T U AT IN G R O D A A A A SO L C H .B S O L CH. A S O L CH. B SO L C H .A ST A G E 1 0 4025K S PN EU M A T IC SER VO HP TU R B IN E MA N IFO L D TU R B IN E MA N IFO L D H P T URB IN E C O NT RO L LV D T CH .A LV D T CH .B CH .B CH. A A A M E C H AN IC AL LI N K A G E F _R VAN ES A A A A J1 0 J1 0 J9 J9 J8 J8 SO L EN ER G IZ E D SO L D E -EN ER G IZ E D 22 23 24 25 26 27 28 29 30 32 33 34 35 36 BL EE D VA L V E 45 3 (4 63) S T A 570 ST G 7 BL SO L ( 5 1 ,9 ) ST G 7 BL SO L ( 1 0 8 ,8 ) ST G 7 BL SO L ( 2 2 8 ) ST G 7 BL SO L ( 5 1 ,9 ) ST G 7 BL SO L ( 2 2 8 ) ST G 7 BL SO L ( 1 0 8 ,8 ) SC H 0 4 4021K S A C T U A T OR -M A S T E R ,L P C 4023 K S S O L V A L V E -H P C O M P R E S S OR S T G 1 0 43 6( 44 6) S T A 4 50 4028 K S S O L V A L V E -S T A G E 10 A IR 43 6(4 46) S T A 450 VA L V E -ST A G E 10 T O H P T A IR N D 5 7 3 2 518 S 03 002 A C

V2500 TS

Tech LLog

g

HC-HSD

289423_01

'XULQJGHVFHQW0$,17676(1*)$'(&

ST

A

TUS P

AGE

ENG 1: ACC ACTUATOR 4027KS REPLACED ACC. AMM 75-24-52 REV.

FEB 01/09

LAST LEG REPORT FADEC 1A

INTERROGATE CFDS (FADEC PWR ON)

LAST LEG REPORT FADEC 1B

ON

OFF

OFF

OFF

ON

ON

HYD

APU

ENG

BLUE PUMP

OVRD

BLUE PUMP

OVRD

G

LEAK MEASUREMENT VALVES

B

Y

TEST

AUTO EXTING

RESET

FADEC GND PWR

1

2

ON

OK

Fault Symptoms

Isolation Procedure

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1

For training purpose only

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1

For training purpose only

Print Date: Apr 27/09 Local Time

Page 2 of 8

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1

For training purpose only

Customer: ASL

Type: A319

Rev. Date: Feb 01/09

Manual: TSM

Selected effectivity: ALL

75-24-00-810-801 - Failure of the Active Clearance Control-Actuator on Engine

1

For training purpose only

Print Date: Apr 27/09 Local Time

Page 4 of 8

in varianta pt elevi este trecut canalul FADEC 1B cu codul

HCCWAF

_HC-HSD

'XULQJGHVFHQW0$,17676(1*)$'(&