ENGINEERING ORDER N° IM A319/320-28/1508 - Apsyswebapp.ifrskeyes.com/GED/AMSFSKUPRD/(1508) IM-A319-A320-28-1508 Rev...NOTE (1): The location of the CB depends on the Aircraft configuration

ENGINEERING ORDER N° IM A319/320-28/1508

Engineering Management Pudahuel, Santiago, Chile

WORK ORDER : …………….

ITEM NUMBER : …………….

ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 2 of 31

Form R145-38 Rev 0

19) PART LIST

ITEM QTY PART NUMBER DESCRIPTION REMARK

01 1 281188A02R00 KIT

02 AR MAT 11-002

(SPEC MIL-PRF-680) Dry Cleaning Solvent (Varsol/White Spirit) Or any equivalent.

20) TOOL LIST

ITEM QTY PART NUMBER DESCRIPTION REMARK

21) SKY FLEET REFERENCE

AVION MSN SB

CONFIGURATION CC-ABV 1400 2 CC-ABW 1523 2 CC-ADO 0447 2 CC-AFX 2283 2 CC-AFY 2129 2 CC-AFZ 2251 2 CC-AHC 2119 2 CC-AHD 2460 2 CC-AHE 2548 2 CC-AIB 2378 2 CC-AIC 2380 2 CC-AID 2436 2 CC-AIY 2214 2 CC-AJF 2249 2 CC-AJG 3331 4 CC-AMP 3171 4





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 3 of 31

Form R145-38 Rev 0

22) REVISION RECORD

N° REVISION ITEM DESCRIPTION DATE

0

1

All

COVER ITEM 2)

ITEM 21 SKY FLEET TABLE

TASK

DESCRIPTION STEP C 1,

C1.d. ii AND REFERENCES

FIGURE

A-FWAAB

Original Release

ADDED AD 2012-0198 R1

ADDED ALL SKY FLEET AIRPLANES

ADDED CONF 2 AND CONF 4

ADDED FOR CONFIGURATION 4

Aug 05-2013 (M.L.)

Oct-27-2014 (R.G.)





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 4 de 31

TASK DESCRIPTION MEC

LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL

THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A

CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS,

ETC; AS NECESSARY ON WIRING AND COMPONENTS - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF

CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

A.- GENERAL

1.- Subtask 281188-910-001-001 Standard Practices.

Reference Aircraft Maintenance Manual (AMM) 1-00-00, Page Block 201

Task 20-21-15-912-001

Elec. Std. Practice Manual (ESPM) 20-33-00 20-46-50 20-52-21 20-54-50

a.- Tag all the parts you must remove and retain to make the subsequent

installation easier. b.- For the installation of the relays, refer to ESPM 20-46-50. c.- For the general of electrical wire harnesses, refer to ESPM 20-33-00.





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 5 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

d.- For protection of the connectors, contacts and terminals, refer to espm

20-54-50. e.- For the installation of placards, refer to AMM Task 11-00-00, Page

block 201. f.- To torque tighten the electrical component fasteners, ref to AMM Task

20-21-15- 912-001. g.- Do a continuity test of the new and/or modified wires, refer to ESPM

20-52-21.

B. PREPARATION

1.- Subtask 281188-941-001-002-Job Set-up.

Reference Aircraft Maintenance Manual (AMM) 06-41-53 Page Block 001

Task 12-34-24-869-002 52-40-00, Page Block 001

NOTE: The items given in this note shall be considered as the basic

Aircraft configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position

a.- Make sure that the aircraft is electrically grounded, (Refer to AMM

Task 12-34-24-869-002). b.- Put the access platform(s) in position at the avionics-compartment

door 822. c.- Open, safety/lock and tag these circuit breakers.:

________

________

________

XXXXXXX

XXXXXXX

XXXXXXX





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 6 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

PANEL DESIGNATION FIN LOC SEE

NOTES 121VU FUEL/CTR TK/PUMP1 SPLY 29QA 23 P (1) 121VU FUEL/CTR TK/PUMP1 SPLY 29QA 34 K (1) 121VU FUEL/CTR TK/PUMP2 SPLY 30QA 26 P (1) 121VU FUEL/CTR TK/PUMP2 SPLY 30QA 37 K (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 31QA 25 R (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 31QA 27 Q (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 32QA 26 R (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 32QA 28 Q (1) 49VU SDAC/1 AND 2/28VDC/ESS BUS 12WV 05 F 49VU SDAC/1/SPLY 3WV 04 F 49VU SDAC/1/26VAC SYNC/CAN ESS BUS 5WV 02 F 121VU EIS/SDAC/1/BUS1/26VAC SYNC AC 9WV 04 Q 121VU EIS/SDAC/1/BUS2/26VAC SYNC AC 7WV 03 Q 49VU SDAC/2/26VAC SYNC/AC ESS BUS 6WV 03 F 121VU EIS/SDAC/2/SPLY 2WV 06 Q 121VU EIS/SDAC/2/BUS1/26VAC SYNC AC 10WV 05 Q 121VU EIS/SDAC/2/BUS2/26VAC SYNC AC 8WV 02 Q

NOTE (1): The location of the CB depends on the Aircraft configuration

d.- Open the avionics-compartment doors 822 and 824 (Refer to AMM

06-41-53, Page Block 001 and AMM 52-40-00, Page Block 001). e.- Open the Contactor Box 107VU. NOTE: Retain the hardware. NOTE: Retain the hardware.

________

________

XXXXXXX

XXXXXXX

C. PROCEDURE

Configuration 002 and 004

1.- Subtask 281188-831-002-003/004 – Modify the equipment and the

Wiring in the Contactor Box 107VU

Work Zones and Access Panels Zone Access/Work location

120 Access Door 822 Electrical Panel 107VU

Work location Electrical Panel 107VU

Material necessary to do the job

Kit 281188A02R00

ITEM NEW PART N° QTY (UM) KEYWORD 1 ABS1629-28A0 2 GFI 2 E0673D0S 2 BASE 3 NAS1101-04-7 6 SCREW





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 7 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

4 ASNA2397-3L 6 WASHER 5 MS21042-04 6 NUT D9100095214295 PLACARD EN3155-017F1216 12 CONTACT EN3155-017F1620 8 CONTACT

References Aicraft Maintenance Manual (AMM) 11-00-00, Page Block 201

Task 20-28-00-912-802 Elect. Stand. Practices Manual (ESPM)

20-33-00 20-46-50 20-52-21 20-54-50

Fig. A-FBAAB Modification of the Equipment in the Contactor Box 107VU

Sheet 01 Sheet 2

Fig. A-FWAAA for configuration 002 and A-FWAAB for configuration 004 Modification of the Wiring in the Contactor Box 107VU

Sheet 01 Sheet 02

Fig. A-FWBAA Modification of the Wiring in the Contactor Box 107VU

Sheet 01 Sheet 02

Fig. A-FHAAA for configuration 002 and A-FHAAB for configuration 004 Modification of the Wiring in the Contactor Box 107VU

Sheet 01

Fig. A-FHBAA Hook up Chart of the Wiring in the Contactor Box 107VU

Sheet 01

a.- Remove 35QA from position A08 Refer to Fig. A-FBAAB Sheet 01:

FIN 35QA 1 Relay NSA932843AA01 Item (1) Discard FIN 35QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard

________

XXXXXXX





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 8 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

NOTE: Remove and discard the placards identified 35QA.

b.- Remove 36QA from position A09 (Refer to Fig. A-FBAAB Sheet 01):

FIN 36QA 1 Relay NSA932843AA01 Item (1) Discard FIN 36QAA 1 Base NSA932844AA Item (2) Discard Attached with: 3 Screw Item (3) Discard 3 Washer Item (4) Discard 3 Nut Item (5) Discard

NOTE: Remove and discard the placards identified 36QA. c.- Loosen and release the relays plate without disconnect the relays

(Refer to Fig. A-FBAAB Sheet 01).

NOTE: For access, remove and retain all the necessary wiring bracket. NOTE: Retain the hardware. d.- Install the relay GFI 69QA.

Refer to AMM Task 20-28-00-912-802 Refer to AMM 11-00-00, Page Block 201 Refer to ESPM 20-33-00 Refer to ESPM 20-46-50 Refer to ESPM 20-54-50

i.- Install at position A08:

Refer to Fig. A-FBAAB Sheet 02

FIN 69QAA

3 Screw Item (3) Discard

________

________

________

________

XXXXXXX

XXXXXXX

XXXXXXX

XXXXXXX





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 9 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

1 Base E0673D0S Item 2

Attach with

3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5

NOTE: Tighten the three nuts Item 5 to a torque value 0.10 m.daN

(8.851 in.lb). ii.- Modify the connections of the wires as shown in the wiring diagrams

Fig. A-FWAAA Sheet 01 for configuration 002 or A-FWAAB Sheet 1 for configuration 004 and and Fig. A-FWAAA Sheet 02 for configuration 002 or A-FWAAB Sheet 02 for configuration 004 and as given in the hook-up chart lines:

- 1 thru 20, refer to Fig. A-FHAAA Sheet 01 for configuration 002 and A-

FHAAB Sheet 1 for configuration 004. NOTE: If necessary, use:

6 Contact EN3155-017F1216

and


iii.- Do a continuity test of the new and/or modified electrical wires, refer to ESPM 20-52-21.

FIN 69QA

1 GFI ABS1629-28A0 Item 1

NOTE: Tighten the three screws to a torque value comprised between 0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

iv.- Near the new relay, bond the placards identified 69QA as shown in

Fig. AFBAAB Sheet 02, supplied in: Placard Set D9100095214295 e.- Install the relay GFI 70QA.

Refer to AMM Task 20-28-00-912-802 Refer to AMM 11-00-00, Page Block 201

________

________

________

________

________

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 10 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

Refer to ESPM 20-33-00 Refer to ESPM 20-46-50 Refer to ESPM 20-54-50

i.- Install at position A09:

Refer to Fig. A-FBAAB Sheet 02

FIN 70QAA

1 Base E0673D0S Item 2 Attach with 3 Screw NAS1101-04-7 Item 3 3 Washer ASNA2397-3L Item 4 3 Nut MS21042-04 Item 5

NOTE: Tighten the three nuts Item 5 to a torque value 0.10 m.daN (8.851 in.lb).

ii.- Modify the connections of the wires as shown in the wiring diagrams

Fig. AFWBAA Sheet 01 and Fig. A-FWBAA Sheet 02 and as given in the hook-up chart lines:

- 1 thru 20, refer to Fig. A-FHBAA Sheet 01.

NOTE: If necessary, use:


and 4 Contact EN3155-017F1620

iii.- Do a continuity test of the new and/or modified electrical wires, refer

to ESPM 20-52-21. FIN 70QA

1 GFI ABS1629-28A0 Item 1

NOTE: Tighten the three screws to a torque value comprised between

0.023 m.daN and 0.034 m.daN (2.036 in.lb and 3.009 in.lb).

________

________

________

XXXXXXX

________

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 11 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

iv.- Near news relays, bond the placards identified 70QA as shown in

Fig. A-FBAAB Sheet 02, supplied in:

Placard Set D9100095214295 f.- Attach the relays plate with the hardware retained at removal, refer to

Fig. A-FBAAB Sheet 01.

________

________

D.- TEST

1.- Subtask 281188-865-001-003 – Close Circuit Breakers

a.- Remove the safety clips and/or tags and close/unlock these circuit breakers.

PANEL DESIGNATION FIN LOC SEE

NOTES 121VU FUEL/CTR TK/PUMP1 SPLY 29QA 23 P (1) 121VU FUEL/CTR TK/PUMP1 SPLY 29QA 34 K (1) 121VU FUEL/CTR TK/PUMP2 SPLY 30QA 26 P (1) 121VU FUEL/CTR TK/PUMP2 SPLY 30QA 37 K (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 31QA 25 R (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 31QA 27 Q (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 32QA 26 R (1) 121VU FUEL/CTR TK/PUMPS1 AND 2/CTL AND IND 32QA 28 Q (1) 49VU SDAC/1 AND 2/28VDC/ESS BUS 12WV 05 F 49VU SDAC/1/SPLY 3WV 04 F 49VU SDAC/1/26VAC SYNC/CAN ESS BUS 5WV 02 F 121VU EIS/SDAC/1/BUS1/26VAC SYNC AC 9WV 04 Q 121VU EIS/SDAC/1/BUS2/26VAC SYNC AC 7WV 03 Q 49VU SDAC/2/26VAC SYNC/AC ESS BUS 6WV 03 F 121VU EIS/SDAC/2/SPLY 2WV 06 Q 121VU EIS/SDAC/2/BUS1/26VAC SYNC AC 10WV 05 Q 121VU EIS/SDAC/2/BUS2/26VAC SYNC AC 8WV 02 Q

NOTE (1): The location of the CB depends on the A/C configuration)

2.- Subtask 281188-710-003-002 - Testing

Reference Aircraft Maintenance Manual (AMM) Task 31-50-00-710-001

Task 31-50-00-710-003

a.- Procedure:

i.- Do the ground scanning of the Central Warning System, refer to

AMM Task 31-50-00-710-001.

NOTE: As an alternative procedure, you can do this operational test without the Centralized Fault Display System (CFDS), refer to AMM Task 31-50-00-710-003.

________

________

XXXXXXX

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 12 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

3.- Subtask 281188-800-401-003 - Preparation for Test Procedure.

Work Zones and Access Panels

Zone Access/Work location

126 Work Location Electrical Panel 107VU

Reference

Aircraft Maintenance Manual (AMM) Task 24-41-00-861-002

Fig A-UBAAA Test of Ground Fault Interrupter 69QA/70QA

Sheet 01 Sheet 02

a.- Put the access platform(s) in position at the access door 822 of the

electronics compartment. b.- Open the avionics-compartment door 822. c.- Open the access door of the contactor box 107VU. d.- Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-

861-002. e.- Examine the ABS1629-28A0 Ground Fault Interrupter (GFI), FIN

69QA

i.- On the panel 107VU, make sure that the GFI is in the reset (non-tripped) condition (metal shaft is not seen on the trip RESET plunger) (Ref to Fig. A-UBAAA Sheet 01).

ii.- If the metal shaft is in the open (tripped) position, push it (into the

ABS1629-28A0 GFI, FIN 69QA) until it latches in the closed (not tripped) position.

iii.- Make sure that you cannot see the metal shaft.

f.- Examine the ABS1629-28A0 GFI, FIN 70QA

i.- On the panel 107VU, make sure that the GFI is in the reset (non-tripped) condition (metal shaft is not seen on the trip RESET plunger) (Ref to Fig. A-UBAAA Sheet01).

ii.- If the metal shaft is in the open (tripped) position, push it (into the

ABS1629-28A0 GFI, FIN 70QA) until it latches in the closed (not tripped) position.

iii.- Make sure that you cannot see the metal shaft.

________

________

________

________

________

________

________

________

________

________

XXXXXXX

XXXXXXX

XXXXXXX

XXXXXXX

XXXXXXX

XXXXXXX

________

XXXXXXX

XXXXXXX

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 13 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

4.- Test of the Ground Fault Interrupter - 69QA

Work Zones and Access Panels

Zone Access/Work location



Reference

Aircraft Maintenance Manual (AMM) Task 28-25-00-869-001

Fig A-UBAA Test of Ground Fault Interrupter 69QA/70QA

Sheet 01 Sheet 02

WARNING: MAKE SURE THAT THE CENTER TANK HAS SUFFICIENT

FUEL TO MAKE SURE THAT THE TRANSFER FUEL PUMP WILL NOT RUN IN THE DRY CONDITION.

WARNING: MAKE SURE THAT THE CENTER TANK CONTAINS A

MINIMUM OF 200 KTG (440.9244 LB) OF FUEL.

a.- Do a Fuel Transfer Test (Left-hand Pump)

i.- On the panel 40VU, set the Push-Button Switch (P/BSW) FIN 48QA (MODE SEL) to MAN (manual) (Refer to Fig. A-UBAAA Sheet 02).

ii.- Push the P/BSW FIN 33QA (CTR TK PUMP 1) to operate the center

tank fuel pump FIN 37QA: (1).- Make sure the OFF lights in the P/BSW´s go off. (2).- Make sure that the center tank fuel pump 37QA operates

correctly (to move some of the fuel from the center tank) and gives the correct flight deck indications (as indicated in the ground transfer procedure), refer to AMM Task 28-25-00-869-001.

(3).- Push the P/BSW FIN 33QA (CTR TK PUMP 1) to stop the

center tank fuel pump FIN 37QA.

iii.- Operate the center tank fuel pump FIN 37QA to do a fuel transfer (Refer to AMM Task 28-25-00-869-001):

(1).- While the pump operates push the ’auto-test’ P/BSW on the GFI

FIN 69QA, on the panel 107VU (Refer to Fig. A-UBAAA Sheet 01).

(2).- Make sure that the GFI FIN 69QA trips (the metal shaft on the

trip RESET indicator comes out).

________

________

XXXXXXX

XXXXXXX

________

________

XXXXXXX

XXXXXXX

XXXXXXX

XXXXXXX

________

________

XXXXXXX

XXXXXXX

________

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 14 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

(3).- Make sure that the related PUMP FAULT light illuminates on

the P/BSW FIN 33QA (CTR TK PUMP 1).

iv.- Push the P/BSW FIN 33QA (CTR TK PUMP 1) to set the center tank fuel pump FIN 37QA to OFF. Make sure that the illuminated FAULT legend goes off and the OFF legend illuminates on the related P/BSW.

v.- On the panel 107VU, push in the trip RESET button of the GFI FIN

69QA until it latches in the closed (not tripped) position. Make sure that you cannot see the metal shaft (Refer to Fig. A-UBAAA Sheet 01).

vi.- Push the P/BSW FIN 33QA (CTR TK PUMP 1) to operate the center

tank fuel pump FIN 37QA:

(1).- Make sure that the center tank fuel pump FIN 37QA operates correctly (to move some of the fuel from the center tank) and gives the correct flight deck indications (as indicated in the ground transfer procedure) (Refer to AMM Task 28-25-00-869-001).


center tank fuel pump 37QA. vii.- On the panel 40VU, push the P/BSW FIN 48QA (MODE SEL) to

de-select MAN (manual) mode (Refer to Fig. A-UBAAA Sheet 02).

5.- Test of the Ground Fault Interrupter - 70QA

Work Zones and Access Panels Zone Access/Work location


Reference Aircraft Maintenance Manual (AMM) Task 24-41-00-861-002

Task 28-25-00-869-001 Fig A-UBAA Test of Ground Fault Interrupter 69QA/70QA

Sheet 01 Sheet 02

WARNING: MAKE SURE THAT THE CENTER TANK HAS SUFFICIENT

FUEL TO MAKE SURE THAT THE TRANSFER FUEL PUMP WILL NOT RUN IN THE DRY CONDITION.

XXXXXXX

________

________

________

XXXXXXX

________

________

________

XXXXXXX

XXXXXXX

XXXXXXX

________

XXXXXXX

XXXXXXX





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 15 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0

a.- Do a Fuel Transfer Test (Right-hand Pump)

i.- On the panel 40VU, set the Push-Button Switch (P/BSW) FIN 48QA (MODE SEL) to MAN (manual) (Refer to Fig. A-UBAAA Sheet 02).

ii.- Push the P/BSW FIN 34QA (CTR TK PUMP 2) to operate the center


(1).- Make sure that the center tank fuel pump 38QA operates correctly (to move some of the fuel from the center tank) and gives the correct flight deck indications (as indicated in the ground transfer procedure) (Refer to AMM Task 28-25-00-869-001).


center tank fuel pump FIN 38QA. (3).- Check the fault lamp of the LH pump.

iii.- Operate the center tank fuel pump FIN 38QA to do a fuel transfer (Refer to AMM Task 28-25-00-869-001):

(1).- While the pump operates push the ’auto-test’ P/BSW on the GFI

FIN 70QA, on the panel 107VU (Refer to Fig. A-UBAAA Sheet 01).

(2).- Make sure that the GFI FIN 70QA trips (the metal shaft on the

trip RESET indicator comes out). (3).- Make sure that the related PUMP FAULT light illuminates on

the P/BSW FIN 34QA (CTR TK PUMP 2). iv.- Push the P/BSW FIN 34QA (CTR TK PUMP 2) to set the center

tank fuel pump FIN 38QA to OFF. Make sure that the illuminated FAULT legend goes off and the OFF legend illuminates on the related P/BSW.

v.- On the panel 107VU, push in the trip RESET button of the GFI FIN

70QA until it latches in the closed (not tripped) position. Make sure that you cannot see the metal shaft (Refer to Fig. A-UBAAA Sheet 01).

vi.- Push the P/BSW FIN 34QA (CTR TK PUMP 2) to operate the center


(1).- Make sure that the center tank fuel pump FIN 38QA operates correctly (to move some of the fuel from the center tank) and gives the correct flight deck indications (as indicated in the ground transfer procedure) (Refer to AMM Task 28-25-00-869-001).

________

________

XXXXXXX

________

XXXXXXX

________

________

XXXXXXX

XXXXXXX

________

________

________

XXXXXXX

XXXXXXX

XXXXXXX

________

XXXXXXX

________

XXXXXXX

XXXXXXX

________

________

XXXXXXX

________

XXXXXXX

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 16 de 31


LICENSE & SIGNATURE

INSPECTOR &

SIGNATURE

Form R145-38 Rev 0


center tank fuel pump 38QA. vii.- On the panel 40VU, push the P/BSW FIN 48QA (MODE SEL) to

de-select MAN (manual) mode (Refer to Fig. A-UBAAA Sheet 02). viii.- De-energize the aircraft electrical circuits refer to AMM Task 24-41-

00-862-002.

________

________

________

XXXXXXX

XXXXXXX

XXXXXXX

E.- CLOSE-UP

1.-Subask 281188-942-002-001 - Close-up

a.- Make sure that the work areas are clean and clear of tools and other items of equipment.

b.- Close the Contactor Box 107VU with the hardware retained at removal. c.- Close the avionics-compartment doors 822 and 824 (Refer to AMM 06-

41-53, Page Block 001 and AMM 52-40-00, Page Block 001). d.- Remove the access platform(s). e.- Put the aircraft back to its initial configuration.

________

________

________

________

________

________

________

________

________

________





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 17 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 18 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 19 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 20 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 21 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 22 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 23 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 24 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 25 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 26 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 27 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 28 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 29 of 31

Form R145-38 Rev 0





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 30 of 31

Form R145-38 Rev 0

Deviation Record Sheet Paragraph Observation Action Authorized by Performed by





ISSUE DATE:

REV:

PAGE:

Oct-27-2014

1 31 of 31

Form R145-38 Rev 0

DISCREPANCY FOUND PARAGRAPH CORRECTIVE ACTION DETAIL MEC LICENSE

& SIGNATURE

INSPECTOR & SIGNATURE

1

2

3

4

5

6

Documents

ENGINEERING ORDER N° IM A319/320-28/1508 - Apsyswebapp.ifrskeyes.com/GED/AMSFSKUPRD/(1508) IM-A319-A320-28-1508 Rev...NOTE (1): The location of the CB depends on the Aircraft configuration