1 PREPARATION OF WORK

Aircraft …………….…………………………………………….….On the ground, resting on landing gear

Ground safety locks……………………………………………………………………………..... In position

Wheel chocks………………………………………………………………………………….…….In position

Engines…………………………………………………………………………………….……..….Shut down

Thrust Reversers……………………………………………………………………….. .Closed and locked

Aircraft configuration…………………………………………………………………….………Clean wing

Parking brake……………………………………………………………………………….………….Applied

Aircraft electrical network…………………………………………………………….……...De-energized

Hydraulic systems…………………………………………………………………………….Depressurized

Access to the cockpit and cabin……………………………………………………….……….. Available

All circuits breakers ……………………. …………………………………………………………….Closed

All controls…………………………………………………………………. NORM, AUTO or OFF position

Differed Items, opened to limit any of MLG brakes operation………………………………Checked

NOTE: In case a specific A/C configuration is required during a maintenance procedure,

a specific paragraph is provided at task level.

2 TLB/CLB CHECK

TLB ……….……………………………………………………………..……………………….….Checked

CLB ……….……………………………………………………………..……………………….….Checked

NOTE: Check TLB/CLB records for defect and required works. Perform corrective actions if present.

3 CARGO COMPARTMENTS PANELS GVI

AMM: 255000-200-002

FWD/AFT Cargo comp. doors……………………………………………………………………….Open

Actuator safety locks………………………………………………………………………………Installed

NOTE: Check all Decompression panels for damages, proper installation & condition of seals.

ALL Cargo Compartment panels ………………………………………………………………..Checked

NOTE: Check all panels for temporary repairs by High Speed Tape. Open DI iaw SRM/AMM if there no mentions into Open Item List (OIL) about found temporary repairs.

Decompression Panels…………………………………………………………………….. …….Checked

NOTE: Check all Lining panels for correct position, damages, proper installation & condition of seals.

NOTE: Check all Lining panels fasteners are installed and in good condition.

Lining Panels (Ref: Appendix, Item 16)………………………………………………………………….Checked

NOTE: Check all Floor panels for Impact damages, deep scratches, cracks, deformation, delamination proper installation & condition of seals

Floor Panels…………………………………………………………………………………………Checked

Pressure Compensation Valves…………………………………………………………………...Closed

A/C condition…………………………………………………………………….Ready

NOTE: Check fittings & metal parts, stanchions, rubber coated fabric & mesh screen, attachments.

FWD Cargo comp door nets………………………………….…………………………………..Checked

FWD Cargo comp divider nets………………………………….………………………………..Checked

AFT Cargo comp door nets………………………………….…………………………….........Checked

AFT Cargo comp divider nets……………………………….……………………………….....Checked

A/C condition…………………………………………………………………………………………....Initial

AMM: 333400-710-001

AMM Subtask: 523512-710-050 / -051 MP: 333000-01100

FWD CC………………………………….…………………………………….………………….Checked

FWD CC selector valve bay lamp 9MJ (Push the lamp cover and make sure that the

indicator light comes on)…………….………………….…………………………………....Checked

AFT CC………………………………………………………...……………………………….....Checked

AFT CC selector valve bay lamp 8MJ (Push the lamp cover and make sure that the

indicator light comes on)…………….……………….….…………………………………….Checked

A/C condition………………………………………………………………………………………....Initial

6 EMERGENCY EXIT DOORS CYLINDER / ACCUM PRES CHECK (Ref: Appendix, Item 20)

(Only A321CEO except VQ-BDB) AMM: 522200-200-001

MP: 522200-08100

SPECIAL PRECAUTION PROCEDURE…………………………………………..………….…performed

EMERGENCY EXIT door ……………………………………………………………….…sufficiently open

NOTE: Make sure that the pressure gauge needle is in the green area of the scale. If the pressure is not in the given limits, pressurize the accumulator of the door damper (Ref. AMM TASK 52-10-00-614-002)

PRESSURE of each door cylinder……………………………………………………………….Checked

A/C condition…………………………………………………………………………………………….Initial

Paragraphs 7-11 require accomplishing of General Visual Inspection (GVI) of several aircraft zones. A Zonal

GVI requires a visual examination to detect obvious unsatisfactory conditions and discrepancies. It is considered that the person performing the inspection has an adequate knowledge of the aircraft construction and of its system installation.

The following list is clarified main types of deterioration that constitutes discrepancies that is expected to be found:

- aircraft and engine accidental damage;

- deformation;

- oil canning;

- corrosion;

- cracks;

- delamination;

- chafing;

- abnormal wear;

- deterioration of previous repairs;

- damage to hinges or latches;

- missing/damaged parts;

- missing, loosen or broken fasteners;

- damaged, blistering or missing paint;

- evidence of fluid leakage;

- accumulation of contaminants;

- illegible labels/marking.

The person performing the inspection is expected to identify such degradation / discrepancies and make assessment to determine actions to be addressed for discovered discrepancies.

All GVI procedures, given in this check list, are to be performed from the ground level, as far as visible.

Where possible (without usage of GSE) zonal inspection is to be performed within touching distance.

7 NOSE LANDING GEAR WELL

AMM: 052120-200-002

MP: 05123-01100

NLG Doors……………………………………………………………………………………………….Open

NLG safety devices……………………………………………………………………………..…..Installed

NLG Well……………………………………………………………………………………............Inspected

NLG doors ……..…..………………………………………………………………………............Inspected

A/C condition………………………………………………………………….….Ready for next check # 8

8 MLG WELL AND HYDRAULIC COMPARTMENT GVI

AMM: 052140-200-003

MP: 05147-01100

MLG Doors………………………………………………………………………………………..........Open

L/H & R/H MLG WELL……………………………………………………………………………Inspected

L/H & R/H MLG DOORS………………………………………………………………………….Inspected

HYDRAULIC COMPARTMENT……………………….…………………………………………Inspected

A/C condition………………………………………………………………….....Ready for next check # 9

9. MLG BAY GVI

AMM: 052570-200-001

MLG Doors………………………………………………………Open

MP: 05571-01100 ……… ………………………...........Open

L/H & R/H MLG BAY………………………………………………………………………………Inspected

A/C condition……………………………………………………………………………………….…...Initial

10 WING TO FUSELAGE BELLY FAIRING GVI

MP: 05100-03100

NOTE: To provide access for visual inspection of the panels 193AB, 193BB, 194AB, 194BB, it is required the extension and retraction of the flaps.

L/H side wing to fuselage fairings (Ref: Appendix, Item 17) …………………………..…….......... Inspected

R/H side wing to fuselage fairings (Ref: Appendix, Item 17) …………………………….….......... Inspected

Torque the screws (if necessary) (Ref: Appendix, Item 17).………..……………..…………….......... Checked

11 PYLONS FAIRING GVI

MP: 05400-03100

L/H pylon (Ref: Appendix, Item 18) ……………………………………………………………….......... Inspected

R/H pylon (Ref: Appendix, Item 18) …….………………………………..……………………….......... Inspected

Torque the screws (if necessary) (Ref: Appendix, Item 18) …………….……………………….......... Checked

12 CABIN EMERGENCY LIGHTING OPERATIONAL TEST

AMM: 335100-710-001

MP: 335100-01100

NOTE: During this test, make sure that all emergency lights bulbs are operative.

A/C Electrical network (Ref: AMM 244100-861-002 or Appendix, Item 2)………………………………..Energized

Cabin Intercommunicating Data System (CIDS) ………….………………………………..Energized

49VU & 122VU CBs of EMER LT SYS (3 EA)……………………………………………………Closed

EMER EXIT LT SW…………………………………………………………………………..………….OFF

190RH NO SMOKING SW (for CEO) …………………………………………………..……………..OFF

No PED switch 190RH (for NEO) ……………………………………………………..……………..OFF

LIGHT EMER PB SW ………………….……………………………………………….………………OFF

TEST EMER LIGHT/SYS (PTP) 110RH (if applicable) ........…….…………….………Pushed (3 sec)

• SYS OK LIGHT & EMER SYS TEST OK status………………………….……….ON (in 30 sec)

• SYS OK LIGHT & EMER SYS TEST OK status………………………….….......OFF (in 60 sec)

OPERATIONAL TEST ON MCDU CIDS1 key (if applicable) ..…….....………………………..Pushed

• SYSTEM TESTS key .....................................................................................................Pushed

• EPSU SYS TEST key .....................................................................................................Pushed

• START TEST key ......................................................................Pushed (test in progress 60s)

• RETURN key ..................................................................................................................Pushed

Cabin Intercommunicating Data System (CIDS)…….…………………………………De-energized

A/C Electrical network (Ref: AMM 244100-862-002 or Appendix, Item 2)………..…..….............De-energized

13 FLIGHT COMPARTMENT GENERAL INSPECTION

MP: 251000-03100

Spare bulbs box…………………………………………………………………………No missing bulbs

14 FLIGHT COMPARTMENT CLEANING

AMM: 122112-100-001/ -002

MP: 251000-01100MP: 316322-03100

FLT compartment panels (Ref: Appendix, Item 19) …………………..……………………….Cleaned

DU, MCDU (Ref: Appendix, Item 19) ………………..………………………………...…………………..Cleaned

ISIS (only for NEO) (Ref: Appendix, Item 19) …………………………….……………..……………….…..Cleaned

15 APU HOURS & CYCLES READOUT

AMM: 490000-970-001 (for 131-9(A))

AMM: 313200-860-001 (for APS 3200)

MP: 490000-01100/-01200

" APU SERVICE DATA REPORT" (MCDU CFDS - DMM DATA Page)………… Print out & attach to this card & fill out the form in the WP by data from this report

16 QAR DISC REPLACEMENT (Eff: VQ-BQW only)

AMM: 313352-600-004

QAR indicator light…………………………………………………………………………..Checked “ON”

QAR door……………………………………………………........................................................Opened

Disc ………………………………………………………………………………………………….Replaced

QAR door……………………………………………………...Closed & “STATUS” warning light is “OFF”

“DISK LOW” warning light………………………………………………………………...Checked “OFF”

NOTE: If there is a fault, the STATUS warning light is on.

NOTE: “DISK LOW” warning light is on if the storage capacity is lower than 35 percent.

17 DRAIN FUEL TANKS WATER CONTENT

AMM: 123228-281-001

MP: 281100-01200

WARNING: OBEY THE FUEL SAFETY PROCEDURES (Ref. AMM TASK 28-00-00-910-001)

CAUTION: MAKE SURE THAT THE PLUNGER OF THE TOOL ALIGNS CORRECTLY WITH THE WATER DRAIN VALVE. INCORRECT ALIGNMENT OF THE TOOL CAN CAUSE: - THE WATER DRAIN VALVE TO STAY IN THE OPEN POSITION AFTER THE TOOL IS REMOVED - A FUEL LEAK.

NOTE: During cold weather conditions perform the cold weather procedure per AMM 12-31-28 / 201, or drain the fuel/water at least 30 minutes after the refueling.

LH Wing TKs………….………………………………………………………………………………Drained

RH Wing TKs………………………………………………………………………………………….Drained

CTR TK………………..……………………………………………………………………………….Drained

18 MLG BRAKES WEAR INDICATORS CHECK

(Ref: Appendix, Item 6)

AMM: 324227-210-003

MP: 324227-01100

A/C electrical network (Ref: AMM 244100-861-002 or Appendix, Item 2)………………………..………Energized

Yellow HYD SYS (Ref: Appendix, Item 5)…………………….………….……..............................Pressurized

Yellow HYD SYS pressure (triple indicator)…………………………………………….............Green range

Yellow HYD SYS (Ref: Appendix, Item 5)……………………………………….......................De-pressurized

Wheel chocks…………………………………………………………….……………………….In position

Parking Brake control SW………………………………………………………………………………ON

Brake temperature……………………………………………………….……..…….Less than 60 deg. C

Wear indicators (See Notes below)…………………………………………………. ………….....Within limits

Piston housing & hydraulic lines……………………………………………………………….No leaks

A/C configuration…………………………………... …………………………………………………Initial

NOTE: For A319 / A320 / A321 A/Cs, if at least one wear indicator is 2 mm, or less, the appropriate brake must be replaced within 15 FC. Open Differed Defect cat. N(L).

NOTE: For A319 / A320 A/Cs, if the end of one of the two wear indicators is flush with the machined surface of the piston housing (the heat pack is fully worn), replace the brake.

NOTE: For A321 A/Cs, when the end of one of the two wear pins touches the machined surface of the piston housing (the heat pack is fully worn), the appropriate brake must be replaced.

19 LANDING GEAR WHEELS & TYRES CONDITION CHECK

AMM: 324100-210-002

MP: 324100-02100

WARNING: LET THE BRAKES AND WHEELS BECOME COOL BEFORE YOU APPROACH THE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS FIRE EXTINGUISHER DIRECTLY ON A HOT WHEEL OR BRAKE UNIT, THIS COULD CAUSE AN EXPLOSION.

MLG Tyres (Ref: Appendix, Item 14) ………...…………………………………………………………….Checked

NLG Tyres (Ref: Appendix, Item 14) ………………………...……...……………………………………..Checked

MLG L/H & R/H Wheels drive shroud of the tachometer………………………….Checked

MLG L/H & R/H & NLG……………………………………………………………………………......…Checked

- wheel rims………………….……………..…………………………………………………………No cracks

- valves…………………………….………………… …………………No leaks & thread is not damaged

- valves caps ……………………………….…...…………………………………………………Fully tighten

NOTE: If a tread groove depths is ≤ 3mm, open Deferred Defect to replace affected tire at the next 10 DAYS check.

If a tread groove depths is ≤ 2mm, open Deferred Defect to replace affected tire at the next 72 HR check.