Guidance for preflight walk-around REV02.pdf

Filename : Guidance for pre-flight walk-around

REV/02

Effective date : 05.Sep.2013

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CONTENTS

Contents………………………………………………..2

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Tail……………………………………………………..36

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General / Safety exterior inspection…..3-4

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APU……………………………………………………37

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External walk-around items…………….….5-9

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Left AFT fuselage………………………………..38

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Left forward fuselage………………….....10-11

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L/H landing gear…………………………………39

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Nose landing gear…………………………..12-15

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L/H wing trailing edge………………………..40

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Right forward fuselage…………………...16-18

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L/H wing leading edge………………………..41

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Lower center fuselage…………………...19-20

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ENG 1 L/H side………………………………42-43

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R/H Center wing……………………………..21-22

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ENG 1 R/H side…………………………………...44

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Engine 2 L/H side……………………………23-24

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L/H center wing…………………………….45-46

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Engine 2 R/H side…………………………...25-26

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Tire inspection………………………………47-59

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R/H wing leading edge……………………27-28

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R/H wing trailing edge………………………….29

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R/H Landing gear and fuselage……….30-33

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R/H AFT fuselage…………………………….34-35


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Content

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The intention of this manual is to give guidance to Flight deck crew while performing exterior inspection. This Manual is based on FCOM and used as reference FCOM/PRO/NOR-Normal Procedures/Standard Operating Procedures. Safety Exterior Inspection Items marked by asterisks ( * ) are the only steps to be completed during a transit stop. This inspection ensures that the aircraft and its surroundings are safe for operations. While arriving at the aircraft, check for obstructions in the vicinity , engineering activity , refueling , etc.

WARNING

If any gear door is open, DO NOT pressurize the green hydraulic system without clearance from ground personnel. Remember that the green hydraulic system is pressurized if the yellow system is pressurized and the PTU is on AUTO.

* APU AREA …………………………………………………………..CHECK Observe that the APU Inlet and Outlet are clear.

Note : Wheel chocks must be placed in the manner that they do not touch the tires (a small gap not exceeding 1 cm between the chocks and the tires must be maintained)

General \ Safety exterior inspection

* WHEEL CHOCKS ………………………………………………………CHECK IN PLACE * LANDING GEAR DOORS …………………………………………..CHECK POSITION

During preflight walk-around, the items of FCOM/PRO/NOR-normal procedures/Standard Operating Procedures must be followed.

WARNING

Flight Crew requested to carefully check the belly panels fasteners , screws. [see page 19-20] . Loose, missing screws fasteners always required maintenance evaluation & action. Depending on the place of the missing fastener it might be a no-go item. If you find loose or missing fasteners advise MCC and to make a record in the WO following the advice of MCC.


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Exterior inspection GENERAL The exterior inspection ensures that the overall condition of the aircraft and its visible components and equipment are safe for the flight. Complete inspection is normally performed by a flight crew member before each originating flight. Items marked by asterisks ( * ) must be performed again by a flight crew member before each flight. The parking brake must be ON during the exterior inspection to allow the flight crew to check brake wear indicators. If the control pin is visible on the inner side of the brake, brakes can be considered in limit.

- Check structure for impact damage - Check that there is no evident fuel , oil or hydraulic leaks.

WARNING If a landing gear door is open, contact maintenance crew before applying hydraulic power.

Exterior Walk – around Remember for walk around you must be prepared, it needs time. Use a flashlight when it is dark. The exterior inspection should be performed closing off the ‘ hurry up syndrome ’ while full attention is needed on items which must be performed.

General \ Safety exterior inspection

NOTE: Warmer brake will show more wear pin. As the carbon gets colder, the pin retracts. When the end of either wear pin touches the machined surface of the piston housing ( Flush ) it reached the limit. Inform MCC. In that case, measure the wear pin when the brake is cold (Brake temperature less than 60 deg.C).

NOTE: This manual does not include the following : -Information about contaminated wings/ critical surfaces and De/Anti icing procedures Check relevant documentations.


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Schematic

1.Left forward fuselage -

* AOA probes ……………………………….……………CONDITION F/O and Capt static ports……………….……………………CLEAR Avionics equipment vent air inlet valve………CONDITION Oxygen Bay………………………………………………………CLOSED Oxygen overboard discharge indicator……………….GREEN * Toilet servicing door ( if installed )………………….CLOSED

-

External walk-around items

2.Nose Section * Pitot Probes……………………………….……………CONDITION STBY static ports…………………………………………………CLEAR * TAT probes..…………………………………………….CONDITION * Radome and latches…………………CONDITION/LATCHED Forward avionics compartment door………………..CLOSED Ground electrical power door(if not required)....CLOSED

3.Nose Landing Gear -

* Nose wheel chocks..…………….according OMB 2.12.28 * Wheels and tires..……………………………….……CONDITION Nose gear structure……………………………….……CONDITION Taxi, TO, turn-off lights……………………………….CONDITION Hydraulic lines and electrical wires……………..CONDITION Wheel well………………………………………………………….CHECK Safety pin………………………………………………………REMOVED

Items marked by asterisks ( * ) must be performed again by a flight crew member before each flight.


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4. Right Forward fuselage -

RH + AFT avionics compartment doors…………….CLOSED Avionic equipment vent air outlet valve…….CONDITION F/O – CAPT static ports………………………………………CLEAR * AOA probe……………………………………………….CONDITION Forward cargo door and selector panel……………..CHECK

RH Center wing

-

Yellow hydraulic bay door………………………………..CLOSED Fuel panel…………………………………………………………CLOSED Inner tank magnetic fuel…………………………………….FLUSH Fuel water drain valve inner tank…………………….NO LEAK Landing light……………………………………………….CONDITION * Slat 1…………………………………………………………CONDITION

8.

ENG 2 RH side

-

Vent inlet ( CFM only )…………………………………………CLEAR Pressure-relief /start valve handle access door….CLOSED Nose Cowl pressure relief door ( PW only )……….CLOSED Engine oil fill access/starter air valve override…..CLOSED access door ( PW only ) Master chip detector access door (PW only )…….CLOSED IDG servicing access door ( PW only ) ……………….CLOSED Turbine exhaust…………………………………………………..CLEAR Pylon / access panel …………………...CONDITION / CLOSED

-

Lower Center fuselage

-

Potable water drain panel ( if installed )…………..CLOSED Antennas……………………………………………………CONDITION Drain mast………………………………………………….CONDITION RAM air inlet flap………………………………………..CONDITION LP and HP ground connection doors…………………CLOSED Anti-collision light ……………………………………………..CHECK CTR Tank magnetic fuel level…………………………..…FLUSH Pack air intakes and outlets………………………………..CLEAR

7.

ENG 2 LH side

-

Oil fill access door.……………………………………………CLOSED Master magnetic chip detector access door.…….CLOSED * Thrust recovery nozzle ( PW only )...CLOSED/LATCHED Hydraulic Filter visual access door(PW only)…….CLOSED * FAN COWL doors..………………………….CLOSED/LATCHED * Drain mast..………………………………CONDITION/NO LEAK * Engine inlet and fan blades………………………………CHECK

9.

RH Wing Leading edge

-

* Slats 2,3,4,5……………………………………………….CONDITION Inner and outer cells Magnetic fuel level…………….FLUSH Fuel water drain valves ( outer cell, surge tank).NO LEAK Refuel coupling …………………………………………………..CLOSED Surge tank air inlet ……………………………………………….CLEAR * Fuel ventilation overpressure disc..…………………..INTACT Navigation light / Strobe light………………………..CONDITION * Wing tip or Sharklet (depends A/C conf.)..….CONDITION


6.

5.



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10. RH Wing trailing edge -

Static dischargers…………………………………….CHECK * Control surfaces………………………………CONDTION * Flaps and fairings …………………………..CONDITION

13. Tail -

11. RH L/G and fuselage

* Chocks………………………….according OMB 2.12.28 * Wheels and tires……………………………..CONDITION Brakes and brake wear ind………………..CONDITION Torque link damper ( if installed )………CONDITION Hydraulic lines…………………………………………..CHECK Landing gear structure………………………………CHECK Downlock springs………………………………………CHECK Safety pin……………………………………………REMOVED Ground hydraulic connection yellow……….CLOSED Shroud fuel drain ……………….CONDITION/NO LEAK

12. Right AFT fuselage -

Cargo door and selector panel…………………..CHECK Bulk door ( if installed ) …………………………….CHECK * Toilet service access door………………………CLOSED Outflow valve……………………………………CONDITION Drain mast………………………………………..CONDITION Flight recorder access door……………………..CLOSED

14. APU -

Access doors…………………………………………….CLOSED Air intake……………………………………………CONDITION Drain……………………………………CONDITION/NO LEAK Oil cooler air outlet………………………….............CLEAR Exhaust……………………………………………………….CLEAR Navigation light………………………………….CONDITION Fire extinguisher overpressure ………………IN PLACE indication ( red disc )

15. Left AFT fuselage -

* Stabilizer, elevator, fin and rudder……..CONDITION * Potable water service door……………………….CLOSED Ground hydraulic connection blue door ……..CLOSED Hydraulic connection green and …………………CLOSED reservoir filling door


-

* Stabilizer, elevator, fin, rudder …………..CONDTION Static dischargers………………………………………….CHECK * Lower fuselage structure ……………………CONDITION ( tail impact on runway )



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16. LH landing gear -

* Chocks …………………………………..according OMB 2.12.28 * Wheels and tires………………….......................CONDITION Brakes and brake wear indicator………………….CONDITION Torque link damper ( if installed )………………..CONDITION Hydraulic lines……………………………………………………..CHECK Landing gear structure…………………………………………CHECK Downlock springs…………………………………………………CHECK Safety pin……………………………………………………….REMOVED

17. LH wing trailing edge


-

* Flaps and fairing…………………………………………..CONDITION * Control surfaces…………………………………………..CONDITION Static dischargers….………………………..………………………CHECK

18. LH wing leading edge

-

* Wing tip or Sharklet (depends on A/C config.)..CONDITION Navigation light / Strobe light…………..……………….CONDITION Surge tank air inlet……………………………………………………..CLEAR * Fuel ventilation overpressure disc..………………………..INTACT Fuel water drain valve……………………………………………NO LEAK Inner and outer cell magnetic …………….........................FLUSH fuel level * Slats 2,3,4,5………………….…………………………………CONDITION

Items marked by asterisks ( * ) must be performed again by a flight crew member before each flight


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19. ENG 1 LH side -

Oil fill access door………………………………..…………….CLOSED Master magnetic chip detector access door……..CLOSED * Thrust recovery nozzle (PW only)……CLOSED/LATCHED Hydraulic Filter Visual door (PW only)……………….CLOSED * FAN COWL doors.…………………………..CLOSED/LATCHED *Drain mast…………………………………CONDITION/NO LEAK * Engine inlet and fan blades………………………………CHECK

20. ENG 1 RH side

-


-

Pressure-relief /start valve handle access door… CLOSED Nose cowl pressure relief door (PW only)………….CLOSED Engine oil fill access/starter air valve override access door (PW only)………………………….CLOSED Master chip detector access door (PW only)……..CLOSED IDG servicing access door (PW only)…………………..CLOSED Turbine exhaust……………………………………………………CLEAR Pylon / access panel …………………...CONDITION / CLOSED

21. LH Center Wing -

* SLAT 1..…………………………………………………..CONDITION Wing leading edge ventilation intake………….…….CLEAR ( if installed ) Fuel water drain valves………………………………....NO LEAK Inner tank magnetic fuel……………………………….…..FLUSH Landing lights…………………………………………….CONDITION Hydraulic reservoir pressurization door……….….CLOSED RAT doors…………………………………………………….….CLOSED

Items marked by asterisks ( * ) must be performed again by a flight crew member before each flight Filename : Guidance for pre-flight walk-around

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1.

Left forward fuselage

Stby angle of attack probe -

* AOA probes…………………………………………CONDITION F/O and Capt static ports……………………………… CLEAR Avionics equipment vent air inlet valve……CONDITION Oxygen Bay……………………………………………………CLOSED Oxygen overboard discharge indicator……………GREEN * Toilet servicing door ( if installed )………………CLOSED

Avionic equipment vent air inlet valve

F/O static port

Capt static port

Capt angle of attack probe

Left forward fuselage

-Check static ports, TAT probe, pitot probes and AOA sensor for obvious damage. Check A/C skin in the vicinity of pitot probes and static probes for any signs of damage. - Check pitot probes covers are removed

Left wing light ATC 1 antenna

DME 2 antenna - Check antennas , it can break away and hang on cable.


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Left STBY static port Oxygen overboard discharge indicator

Left forward fuselage / Nose section

CAPT pitot probe

STBY pitot probe

CAPT TAT probe DME 1 antenna Oxygen bay NOTE: The green oxygen overboard disc will blow out and change to yellow if there is an: - overpressure in the bottle > 2500 psi - overpressure in the pressure regulator


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Forward avionics compartment door

2.

Nose Section

-

* Pitot Probes ……………………………………………CONDITION STBY static ports…………………………………………………CLEAR * TAT probes……………………………………………….CONDITION * Radome and latches…………………CONDITION/LATCHED Forward avionics compartment door…………………CLOSED Ground electrical power door(if not required)…..CLOSED

Check pitot probes covers are removed

FO TAT probe CAPT pitot probe

STBY pitot probe

Nose Section

Ground electrical power door

CAPT TAT probe DME 1 antenna

radome latch - Check integrity of arrestor strip , dent and delamination on radome

localizer/ glideslope antenna 1&2 behind radome Filename : Guidance for pre-flight walk-around

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3.

Nose Landing Gear

-

* Nose wheel chocks…………………..according OMB 3.4.25 * Wheels and tires………………………………………..CONDITION Nose gear structure………………………………………CONDITION Taxi, TO, turn-off lights……………………………….…CONDITION Hydraulic lines and electrical wires……………….CONDITION Wheel well.………………………………………………….……….CHECK Safety pin.…………………………………………………….…REMOVED

Taxi light

Take-off light

Do a check of the landing gear and make sure: - the NLG shock absorber shows normal extension, -there is no sign of under-inflation on the tires, -Safety pin is removed

Downlock spring Nose Landing Gear

Right turn-off light

Nose landing gear electrical box

Left turn-off light Nose wheel steering actuating cylinder - Check absorber normal extension and NO hydraulic leak


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Gear downlock sensor Gear uplock roller

Gear safety pin hook Parking brake light

Nose Landing Gear

Towing lever ( normal position)

Nose landing gear box electrical cylinder

Nose wheel steering actuating cylinder


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Safety pin removed Nose wheel steering Actuating cylinder

Nose Landing Gear

Safety pin installed

Gear extend sensors


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Right STBY static port 4. Right Forward fuselage -

RH + AFT avionics compartment doors……………….CLOSED Avionic equipment vent air outlet valve……….CONDITION F/O – CAPT static ports…………………………………………CLEAR * AOA probe.……………………………………………….CONDITION Forward cargo door and selector panel………………..CHECK

Forward RH avionics compartment door

DME 1 antenna F/O TAT probe

Right forward fuselage

Check static ports, TAT probe, pitot probes and AOA sensor for obvious damage. Check A/C skin in the vicinity of pitot probes and static probes for any signs of damage. Look for obvious damage on fuselage

Skin temp sensor for Avionics ventilation F/O pitot probe

Battery vent exhaust


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F/O AOA probe

ATC 2 mode S antenna - Check each door ( passenger and cargo ) surroundings. Look for obvious damages, dents which could be caused by stairs or ground equipments. NOTE: Passenger stairs should not touch the fuselage.

VHF 1 antenna

Scuff plate

R/H wing light

Aft RH avionic compartment door

Fuselage drain valves F/O static port


DME 2 antenna

ATC 2 antenna

CAPT static port Avionics equipment Vent air outlet valve


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ATC 1 antenna


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Forward cargo door


Locked indication ( green ) /unlocked is red/

Cargo compartment light switch

Indicator light ( cargo door Actuator extended and locked ) Water drain mast Forward cargo selector panel


Forward cargo door control valve selector REV/02


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5.


-

Potable water drain panel ( if installed )…………CLOSED Antennas……………………………………………… CONDITION Drain mast……………………………………….………CONDITION RAM air inlet flap…………………………………… CONDITION LP and HP ground connection doors…………… CLOSED Anti-collision light ………………………………………… CHECK CTR Tank magnetic fuel level…….FLUSH ( see page 21) Pack air intakes and outlets…………………………… CLEAR

- Engine inlet cover must be removed before flight

Marker antenna

ATC 2 antenna

Look for obvious damage


Forward cargo door

Right pack air inlet Anti-collision light

Drain mast

DME 2 antenna

TCAS antenna Potable water drain panel Filename : Guidance for pre-flight walk-around

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RAM air inlet flap - Check No Screws are missing or loose on panels marked area SAFA Top 2 inspection finding. Loose screw

LP ground connection door

HP ground connection door

Anti-collision light Interphone jack


Left pack air inlet

Electrical service panel ( belly fairing panel )

28 V / 50 W DC socket Hydraulic compartment wheel Well light switch


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6.

RH Center wing

-

Yellow hydraulic bay door………………………………..CLOSED Fuel panel…………………………………………………………CLOSED Inner tank magnetic fuel…………………………………….FLUSH Fuel water drain valve inner tank……………………NO LEAK Landing light………………………………………………..CONDITION * Slat 1……..…………………………………………………CONDITION

Yellow hydraulic electrical Pump cooling air outlet

Yellow hydraulic pump and cooling

Right main landing gear door opening handle

Yellow hydraulic bay door

Right pack air outlet -Check No Screws are missing or loose on panels in marked area

Right Center wing

Seal drain container

Anti-collision light

Fuel water drain valve Center tank magnetic Fuel level indicator


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- Check slat / leading edges condition

Slat 1

Fuel panel

Right Center wing

Multi tank indicator

Pre-selector switch

Fuel water drain valve inner tank Inner tank fuel pump Right landing light


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7.

ENG 2 LH side

-

Oil fill access door……………………………………….…….CLOSED Master magnetic chip detector access door…….CLOSED * Thrust recovery nozzle ( PW only )..CLOSED/LATCHED Hydraulic Filter visual access door( PW only )…..CLOSED * FAN COWL doors….………………………..CLOSED/LATCHED * Drain mast………….……………………CONDITION/NO LEAK * Engine inlet and fan blades..……………………………CHECK

Do a check of the engines and make sure: - there are no foreign objects in the engine air intake and fan outlet, - there is no fluid leakage on the drain mast, - the cowl doors are correctly closed and latched FAN COWL door closed and latched

- To check the FAN COWL doors closed and latched you must lean forward and look the latches underside of the engine.

FAN COWL door closed but NOT latched Hold Open Device [ HOD ] not activated

Oil fill access door

ENG 2 left side

Master magnetic chip Detector access door

Drain mast

Items marked by asterisks ( * ) must be performed again by a flight crew member before each flight. Filename : Guidance for pre-flight walk-around

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Fan blades

Engine inlet

Latch NOT closed properly

Filename : Guidance for pre-flight inspection

FAN COWL doors not latched

ENG 2 left side

Note : Oil fill access door must be checked closed and properly latched as well as the master magnetic chip detector access door. Loss of Oil fill access door will result in lengthy AOG and expensive damages to the fan cowl.

Latch closed properly

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8. -

ENG 2 RH side

Ram air inlet

Fire agent bottles access door

Vent inlet ( CFM only )………………………………………..…CLEAR Pressure-relief /start valve handle access door…CLOSED Nose Cowl pressure relief door ( PW only )………..CLOSED Engine oil fill access/starter air valve override……CLOSED access door ( PW only ) Master chip detector access door (PW only )…….CLOSED IDG servicing access door ( PW only ) ………………...CLOSED Turbine exhaust…………………………………………………....CLEAR Pylon / access panel …………………....CONDITION / CLOSED

ENG 2 right side

pylon - Check No Screws are missing or loose on panels

Service interphone jack

Anti-ice discharge grille

Gearbox overboard discharge

Air cooled oil cooler outlet

Starter shutoff valve / pressure relief door


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Reverser cowl

Pre-cooler outlet

Strut drain

Turbine exhaust


- Fresh Oil visible in this area may indicate oil leakage. Inform MCC

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ENG 2 right side

Do a check of the engines and make sure: - there are no foreign objects in the engine air intake and fan outlet, - there is no fluid leakage on the drain mast, - the cowl doors are correctly closed and latched.


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9.

RH Wing Leading edge

-

* Slats 2,3,4,5……………………………………………….CONDITION Inner and outer cells Magnetic fuel level…………….FLUSH Fuel water drain valves ( outer cell, surge tank).NO LEAK Refuel coupling …………………………………………………..CLOSED Surge tank air inlet ……………………………………………….CLEAR * Fuel ventilation overpressure disc..………………….INTACT Navigation light / Strobe light……………………….CONDITION * Wing tip or Sharklet (depends A/C conf.)..…CONDITION

slat Slat track shutter

Check no dents , damages on the leading edge / Slats

RH wing leading edge

Check for fuel leaks at lower surface and hydraulic leaks at flight control area Wing leading edge for FOD ( foreign object damage )

Magnetic fuel Level indicator

surge tank air inlet

refuel coupling

Wing tip

Fuel ventilation overpressure disc



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NAV 2 light Strobe light

Wing tip

NAV 1 light

Static discharger

Right aileron

surge tank air inlet

Fuel vent overpressure disc NOTE: If the white cross is not visible the disc might be broken.

NOTE: The surge tank overpressure disc breaks in case of a blocked NACA VENT, preventing structural damage to the wings during refueling


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RH wing leading edge

Fuel water drain valve

Magnetic fuel level indicator


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10. RH Wing trailing edge -

Static dischargers.…………………………………….CHECK * Control surfaces………………………………CONDTION * Flaps and fairings …………………………..CONDITION

WINGS, FLIGHT CONTROLS Check for fuel leaks at lower surface and hydraulic leaks at flight control area

Right outboard flap

RH wing trailing edge

Flap track fairing

Static discharger


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11. RH L/G and fuselage -

Down-lock proximity switch LGCIU #2

Down-lock proximity switch LGCIU #1

* Chocks…..……………………according OMB 2.12.28 * Wheels and tires.…………………………...CONDITION Brakes and brake wear ind………………..CONDITION Torque link damper ( if installed )………CONDITION Hydraulic lines………………………………….………..CHECK Landing gear structure……………………..……….CHECK Down-lock springs…………………………….……….CHECK Safety ( gear)pin…………………………………..REMOVED Ground hydraulic connection yellow……….CLOSED Shroud fuel drain ……………….CONDITION/NO LEAK

Upper side stay

Down-lock spring

Hydr. fuse

Lock stay actuator

RH L/G and fuselage

Do a check of the landing gears and make sure: - the MLG shock absorber shows normal extension, no hydr. leak on it. - there is no sign of under-inflation on the tires, - there is no hydraulic fluid leakage on the brake units.

Drag stay Servo valves

Lock stay

L/G door Lower side stay Main fitting shock stay RH normal brake module - Check no hydraulic leak from servo valves Filename : Guidance for pre-flight walk-around

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Brake wear indicator

Shrader valve ( yellow ) Ground point

Gear up-lock pin

Torque link damper accumulator

RH L/G and fuselage

Fusible plug

Torque link damper Inflating valve

Hydraulic hose (green) Hydraulic quick Disconnect ( green )

Hydraulic hose (green)

Electrical harness (wheel speed pick up)

Torque link


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Gear retraction jack Lock stay actuator

Lock stay Schrader valve (green) Brake wear indicator pin

Right landing light

Hydraulic hose (yellow)

RH L/G and fuselage

Hydraulic quick disconnect (yellow)

Hydraulic hose (yellow)

Electrical harness


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Main landing gear safety pin installed

Ground hydraulic Connection yellow

Yellow hydraulic hand pump handle

RH L/G and fuselage

Main landing gear safety pin removed

NOTE: in case of electrical failure or if the electric pump fails the crew can close or open the cargo doors using manual operation. To operate : See LPC Browser/PER/loading/CGO Loading/CGO door op.


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12. Right AFT fuselage

-

Cargo door and selector panel…………………..CHECK Bulk door ( if installed ) …………………………….CHECK * Toilet service access door.……………………CLOSED Outflow valve……………………………………CONDITION Drain mast………………………………………..CONDITION Flight recorder access door……………………..CLOSED

AFT Cargo door

VHF 2 antenna

Shroud fuel drain mast ( APU and center tank)

Radio altimeters 2 antennas

RH AFT fuselage

Check no damages surrounding the cargo doors caused by ground equipments

Aft cargo door selector panel

Radio altimeters 1 antennas


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Measurement point

Rear right cabin door

Scuff plate

RH AFT fuselage

Flight recorder Access door

Toilet system vacuum generator outlet

Outflow valve Toilet service access door

Stabilizer compartment drain mast Aft water drain mast


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13. Tail -

* Stabilizer, elevator, fin, rudder …………..CONDTION Static dischargers………………………………………….CHECK * Lower fuselage structure ……………………CONDITION ( tail impact on runway )

fin

FLIGHT CONTROLS Check for hydraulic leaks at flight control area rudder Static discharger

VOR antennas 1 & 2 Inside the fin

elevator

APU exhaust

Tail section

Trimmable horizontal stabilizer

Check no hydraulic leak at Rudder / flight control area

NAV 1 light , Strobe , NAV 2 light Check trimmable horizontal stabilizer leading edge condition Filename : Guidance for pre-flight walk-around

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14. APU -

Access doors…………………………………………….CLOSED Air intake……………………………………………CONDITION Drain……………………………………CONDITION/NO LEAK Oil cooler air outlet………………………….............CLEAR Exhaust………………………CLEAR (see previous page) Navigation light…………CONDITION( see prev .page) Fire extinguisher overpressure ………………IN PLACE indication ( red disc )

Fire extinguisher overpressure indication ( red disc )

Note : - A missing red disc shows that the APU fire bottle has been discharged due to overpressure, caused by over temperature in the stabilizer compartment - Look for significant oil leakage at APU AREA

APU

APU compartment overpressure vent door

Drain mast Air inlet flow diverter Air intake nose

Air intake flap

Access door Oil cooler outlet Filename : Guidance for pre-flight walk-around

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15. Left AFT fuselage -

- Check for correct steps positioning from below, NO contact allowed and NO damages caused by stairs on the fuselage

* Stabilizer, elevator, fin and rudder..…..CONDITION * Potable water service door…………..………….CLOSED Ground hydraulic connection blue ……….……CLOSED doors Ground hydraulic connection green and……..CLOSED reservoir filling door

Hydraulic filter, reservoir blue

LH AFT Fuselage

Ground hydraulic connection (blue) door/RAT control panel

Hydraulic reservoir filling panel and ground hydraulic connection (green) door

Potable water service door


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16. LH landing gear -

Gear retraction jack

* Chocks ……………………according OMB 2.12.28 * Wheels and tires……….………….......CONDITION Brakes and brake wear indicator…..CONDITION Torque link damper ( if installed )….CONDITION Hydraulic lines…………………………………...….CHECK Landing gear structure…………………………..CHECK Downlock springs…………………………………..CHECK Safety pin…………………………………………REMOVED

LH normal brake module

Left landing light

Lower side stay

Upper side stay

Brake pressure transducer

Hydraulic fuse

LH Landing Gear

Lock stay actuator

Down lock spring

Do a check of the landing gears and make sure: - the MLG shock absorber shows normal extension, no hydraulic leak on it. - there is no sign of under-inflation on the tires, - there is no hydraulic fluid leakage on the brake units.

Servo valves


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17. LH wing trailing edge

-

* Flaps and fairing…………………………CONDITION * Control surfaces…………………………CONDITION Static dischargers…………………………………CHECK

Left aileron

Fuel vent overpressure disc

Left outboard flap WINGS, FLIGHT CONTROLS Check for fuel leaks at lower surface and hydraulic leaks at flight control area

LH Wing trailing edge

Flap track fairing

Static discharger


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18. LH wing leading edge

-

Slat

Navigation light

* Wing tip or Sharklet (depends on A/C config.)..CONDITION Navigation and Strobe light….…………………………..CONDITION Surge tank air inlet…………………………………………………….CLEAR * Fuel ventilation overpressure disc..……………………….INTACT Fuel water drain valve…………………………………………..NO LEAK Inner and outer cell magnetic …………………………………..FLUSH fuel level * Slats 2,3,4,5 …………………………………………………..CONDITION

Wing tip

Check no dents , damages on the leading edge / Slats

LH Wing leading edge

surge tank air inlet Fuel water drain valve

Fuel ventilation overpressure disc

Strobe Sharklet

Magnetic fuel level indicator Navigation light Items marked by asterisks ( * ) must be performed again by a flight crew member before each flight. Filename : Guidance for pre-flight walk-around

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. ENG 1 LH side -

Oil fill access door………………………………..…………….CLOSED Master magnetic chip detector access door……..CLOSED * Thrust recovery nozzle (PW only)……CLOSED/LATCHED Hydraulic Filter Visual door (PW only)……………….CLOSED

-

* FAN COWL doors.…………………………..CLOSED/LATCHED *Drain mast…………………………………CONDITION/NO LEAK * Engine inlet and fan blades………………………………CHECK

Do a check of the engines and make sure: - there are no foreign objects in the engine air intake and fan outlet, - there is no fluid leakage on the drain mast, - the cowl doors are correctly closed and latched

EPR sensor

- To check the FAN COWL doors closed and latched you must lean forward and look the latches underside of the engine.

Engine inlet

Oil fill access door Drain mast

Master magnetic chip detector access door

ENG 1 L/H side

Fan blades

In this picture illustrated when the FAN COWL latches are not latched, it is visible only if we look underside of the engine



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- Oil fill access door must be checked closed and properly latched as well as the master magnetic chip detector access door. Loss of Oil fill access door will result in lengthy AOG and expensive damages to the fan cowl.

Latch not closed

ENG 1 L/H side

Latch closed properly

Reverser cowl Fan cowl


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20. ENG 1 R/H side Fire agent bottles access door -

pylon

Pressure-relief /start valve handle access door… CLOSED Nose cowl pressure relief door (PW only)………….CLOSED Engine oil fill access/starter air valve override access door (PW only)………………………….CLOSED Master chip detector access door (PW only)……..CLOSED IDG servicing access door (PW only)…………………..CLOSED Turbine exhaust……………………………………………………CLEAR Pylon / access panel …………………...CONDITION / CLOSED

Inboard strake

ENG 1 R/H side

If the thrust reverser manually deactivated by MX red pin visible Thrust reverser deactivated pin Interphone jack

Anti-ice discharge grille

Air cooled oil cooler outlet Starter shut off valve / Pressure relief door

Gearbox overboard discharge


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Fuel water drain valve 21. LH Center Wing

-

* SLAT 1………………….………………………………..CONDITION Wing leading edge ventilation intake………….…….CLEAR ( if installed ) Fuel water drain valves………………………………....NO LEAK Inner tank magnetic fuel……………………………….…..FLUSH Landing lights…………………………………………….CONDITION Hydraulic reservoir pressurization door……….….CLOSED RAT doors…………………………………………………….….CLOSED

- Check no dents and damages on the slat / leading edges

Inner tank fuel pumps

Magnetic fuel level indicator

SLAT 1

Hydraulic reservoir pressurization door


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RAT doors

LH Center wing

Left landing light


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Blue hydraulic electrical pump cooling air outlet

Hydraulic reservoir pressurization door Left pack air outlet

- Check for correct steps positioning at 1L cabin door from below, NO contact allowed and NO damages caused by stairs on the fuselage

LH Center wing / forward fuselage

Anti-collision light

During an aircraft walk-around. Make sure that there is no: - Damage, - Foreign objects, - Fluid leakages, - Missing or loose parts, - Missing overpressure discharge discs, - Obstruction of inlets/outlets.


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Note: The following annex is based on Service Information letter from Airbus / SIL number 32-121 and the references are :

-Bridgestone: Tire Specification & Maintenance Manual -Goodyear: The Comprehensive Guide to Aircraft Tire Care and Maintenance -Michelin: Aircraft Tire Care & Service Manual -NOTE: the following annexes are information only, if in doubt contact MCC ( Maintenance Control Center ) Tire inspection:

Rib

Groove

1. Tread pattern: • 1.1 Normal wear • 1.2 Uneven wear (shoulder, center)

Tire inspection

2. Tread damage: • 2.1 Flat spots • 2.2 Tread rubber reversion • 2.3 Thrown tread • 2.4 Peeled rib • 2.5 Chevron cutting • 2.6 Tread cuts • 2.7 Groove cracking • 2.8 Rib undercutting • 2.9 Open tread-splice • 2.10 Tread chipping and chunking 3.Sidewalls • 3.1 Cuts or cracks on the sidewall • 3.2 Weathering and radial cracking 4. Blisters and bulges 5. Miscellaneous • Tires contamination


Tread (surface)

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1. Tread wear pattern : 1.1 Normal wear: An even tread wear indicates that the tire has been properly maintained during its service life.

At the main base (or maintenance base), the tire shall be removed from aircraft if:  the tread wear level reaches the bottom of any groove at any point of the tread surface, or  the reinforced ply (bias tire) or the protector ply (radial tire) is exposed at any point of the tread surface.

Tire inspection

NOTE TIRES HAVING REACHED THE ABOVE LIMITS ON ONE AIRCRAFT IN OUTSIDE STATION MUST BE REPLACED AT THE NEXT CONVENIENT MAINTENANCE OPPORTUNITY.

1.2 Uneven wear: In general, under inflation will lead to excessive tread shoulder wear and subsequent heat build-up which may result in severe internal tire damage. Over inflation accelerates the center tread wear, reduces tire traction, reduces the number of cycles and make the tire more susceptible to cutting and foreign object damage (FOD) Under inflated tire uneven wear


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Over-inflated tire uneven wear

Tire wear and deterioration characteristics

Tire inspection

At the main base (or maintenance base), the tire shall be removed from the aircraft if the wear limits are reached.

NOTE TIRES HAVING REACHED THE ABOVE LIMITS ON ONE AIRCRAFT IN OUTSIDE STATION MUST BE REPLACED AT THE NEXT CONVENIENT MAINTENANCE OPPORTUNITY.


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2. Tread damage:

2.1 Flat spots: Flat spot may result from locking of the wheel during braking, hard touchdown or severe steering maneuver (for the nose tires).

The tire shall be removed from aircraft if the flat spot reaches the reinforcing ply (bias tire) or the protector ply (radial tire).

Tire inspection

NOTE IF THE FLAT SPOT DOES NOT REACH THE ABOVE-MENTIONED LIMIT, IF THERE IS SUFFICIENT GROOVE DEPTH IN THE WHOLE FLAT SPOT AREA, IF THERE IS NO INCIPIENT SEPARATION AND IF VIBRATION IS NOT DETECTED DURING ROLLING, THE TIRE CAN REMAIN IN SERVICE.

2.2 Tread rubber reversion: Tread rubber reversion is generally caused by wheel locking on wet or ice covered runways. The affected area is similar in shape to a flat spot (oval), but the rubber appears to be melted.

The tire shall be removed from aircraft if: - the reinforcing ply (bias tire) or the protector ply (radial tire) is reached, - or shimmy or unbalance problem are experienced


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2.3 Thrown tread: Partial or complete loss of tread down to the carcass. Tire must be removed immediately from service. Note: Pieces from the tread must be requested from airport authorities and returned to the home base for potential analysis by the vendor. If the tire is still inflated after aircraft is at parking position, record the pressure after it has cooled down (allow 3 hours). Then deflate the tire before removing the wheel assembly. ( performed by maintenance )

Warning: Remove ( maintenance ) the valve core when the tire is fully deflated. Removal of the wheel valve core on an inflated tire could project the core with high velocity and force. This can cause injury to persons.

Tire inspection

Caution: Avoid approaching wheel from either side of the tire. Always go near the wheels from an oblique angle - direction of the tire’s shoulders.

Early signs of tread separation can manifest themselves in the form of tread bulges, local uneven wear (depression) or local tread/sidewall rubber split.


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2.4 Peeled rib:

Usually starts with a cut in the tread and results in a circumferential delamination of the tread rib away from the tire carcass. The tire has to be removed from aircraft

Tire inspection

.

2.5 Chevron cutting: Tread damage (small z-, s- or v-shaped cracks) caused by running and / or braking on cross-grooved runways. Due to different technologies and tire constructions, tolerance to damages can be different for each manufacturer and even each tire reference for a same manufacturer. Refer to the relevant vendor’s manual for details. In the absence of specific cut limits in documentation, the tire shall be removed from the aircraft if:  tread cut criteria are reached, or  the tread reinforcing ply (bias tire) or the protector ply (radial tire) is exposed.


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2.6 Tread cuts: Foreign objects that are present on the runway, taxiway and parking areas cause cuts to the tires. The definition of cut limits is complex. It is based on the service experience of each vendor and is not easy to harmonize.

Due to different technologies and tire constructions, tolerance to damages can be different for each manufacturer and even each tire reference for a same manufacturer. Refer to the relevant vendor’s manual for details.

Tire inspection


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In the absence of specific cut limits in documentation, the tire shall be removed from the aircraft if:  cut or embedded object exposes or penetrates the reinforcing ply (bias tire) or the protector ply (radial tire): o Cut penetrates the outer casing ply (bias tire) or the outer layer (radial tire). o Cut length is greater than 50 mm (2 in) or o Cut width is greater than 3 mm (0.118 in) or o Cut is not contained within one rib. o Cut is contained within one rib but the ends of the cut are more than 13 mm (0.5 in) apart when measured in the radial direction.

Tire inspection

 cut or embedded object does not expose or does not penetrate the reinforcing ply (bias tire) or the protector ply (radial tire): o cut length is greater than 300 mm (12 in) or o cut width is greater than 3 mm (0.118 in) or o Cut is not contained within one rib. o Cut is contained within one rib but the ends of the cut are more than 13 mm (0.5 in) apart when measured in radial direction.


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2.7 Groove cracking:

Groove cracking may result from environmental aggression of the rubber (ozone attack for example) or from an excessive mechanical solicitation of the tire. These cracks occur at the bottom of the tread groove.

Tire inspection

The tire shall be removed from the aircraft if:  the groove cracking exposes the reinforcing ply (bias tire) or the protector ply (radial tire).  the groove cracking is undercutting the adjacent rib.


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2.8 Rib undercutting :

This is an extension of groove cracking resulting from mechanical solicitation and progressing under a tread rib. It can lead to tread chunking, peeled rib or thrown tread.

Tire inspection

The tire shall be removed from aircraft as soon as the crack extends under the rib.


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2.9 Open tread splice:

This is a crack in the rubber where tread joint or splice separates.

A tire having this defect must be removed from the aircraft.

Tire inspection

2.10 Tread chipping and chunking:

This is a condition visible at the edge of the tread rib in which small amounts of rubber begins to separate from the tread surface. Tread chunking can be caused by high lateral loading of the tire, sometimes caused by tight turning.

The tire shall be removed from the aircraft if fabric is exposed.


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3. Sidewalls: 3.1 Cuts or cracks on the sidewall: Sidewall cuts are often caused by foreign objects present on the operating surfaces.

Tire inspection

The tire shall be removed from the aircraft if sidewall cords are exposed or damaged. Cuts or cracks in the rubber that do not reach the cord plies are not detrimental to tire performance. The tire can remain in service.

3.2 Weathering and radial cracking: Weathering and cracking occur when tires are exposed to aggressive environmental conditions. The tire shall be removed from the aircraft if sidewall cords are exposed.


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4. Blisters and bulges: They normally indicate a separation of components.

The tire shall be removed from the aircraft immediately. Mark the affected area before deflating the tire for easy identification and analysis by the vendor.

Tire inspection

5. Miscellaneous: • Tires contamination ( hydraulic fluid, fuel, …) In case of contamination, check for rubber condition. Call MCC .The tire has to be cleaned quickly with denatured alcohol to remove the contaminant then washed with a soap and water solution. Caution: If the rubber feels soft or spongy when probed or bulges are present, then tire is no more suitable for service. The wheel assembly shall be removed from aircraft.

Filename : Guidance for pre-flight inspection

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Complemented by Christian Ambiehl Booklet made by Capt. Laszlo Ekes


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Guidance for preflight walk-around REV02.pdf

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