Guidance for preflight walk-around REV02.pdf

7/24/2019 Guidance for preflight walk-around REV02.pdf

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Filename : Guidance for pre-flight walk-around REV/02 Effective date : 05.Sep.2013

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Contents..2

General / Safety exterior inspection..3-4

External walk-around items..5-9

Left forward fuselage.....10-11

Nose landing gear..12-15

Right forward fuselage...16-18

Lower center fuselage...19-20

R/H Center wing..21-22

Engine 2 L/H side23-24

Engine 2 R/H side...25-26

R/H wing leading edge27-28

R/H wing trailing edge.29

R/H Landing gear and fuselage.30-33

R/H AFT fuselage.34-35

Tail..36

APU37

Left AFT fuselage..38

L/H landing gear39

L/H wing trailing edge..40

L/H wing leading edge..41

ENG 1 L/H side42-43

ENG 1 R/H side...44

L/H center wing.45-46

Tire inspection47-59


Content

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CONTENTS


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The intention of this manual is to give guidance to Flight deck crew whileperforming 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.

*WHEEL CHOCKS CHECK IN PLACE

*LANDING GEAR DOORS ..CHECK POSITION

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.

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

General\Sa

fetyexteriorinspection

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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)

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.

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).

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

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

Exterior Walkaround

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 whichmust be performed.

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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General\

Safetyexteriorinspection


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Schematic

1.Left forward fuselage

- *AOA probes .CONDITION

- F/O and Capt static ports.CLEAR- Avionics equipment vent air inlet valveCONDITION

- Oxygen BayCLOSED

- Oxygen overboard discharge indicator.GREEN

- *Toilet servicing door ( if installed ).CLOSED

2.Nose Section

- * Pitot Probes.CONDITION

- STBY static portsCLEAR

- *TAT probes...CONDITION- *Radome and latchesCONDITION/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 pinREMOVED


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Externalwalk-arounditems


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5. Lower Center fuselage

- Potable water drain panel ( if installed )..CLOSED

- AntennasCONDITION

- Drain mast.CONDITION

- RAM air inlet flap..CONDITION

- LP and HP ground connection doorsCLOSED- 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 bladesCHECK

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 l ight / Strobe light..CONDITION

- *Wing tip or Sharklet (depends A/C conf.)...CONDITION

4. Right Forward fuselage

- RH + AFT avionics compartment doors.CLOSED

- Avionic equipment vent air outlet valve.CONDITION

- F/OCAPT static portsCLEAR

- *AOA probe.CONDITION

- Forward cargo door and selector panel..CHECK

6. RH Center wing

- Yellow hydraulic bay door..CLOSED

- Fuel panelCLOSED

- Inner tank magnetic fuel.FLUSH

- Fuel water drain valve inner tank.NO LEAK

- Landing light.CONDITION

- *Slat 1CONDITION

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


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10. RH Wing trailing edge

- Static dischargers.CHECK

- *Control surfacesCONDTION

- *Flaps and fairings ..CONDITION

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 structureCHECK

- Downlock springsCHECK

- Safety pinREMOVED- 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 doorCLOSED

- Outflow valveCONDITION

- Drain mast..CONDITION- Flight recorder access door..CLOSED


13. Tail

- *Stabilizer, elevator, fin, rudder ..CONDTION


- *Lower fuselage structure CONDITION( tail impact on runway )

14. APU

- Access doors.CLOSED

- Air intakeCONDITION

- DrainCONDITION/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

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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 structureCHECK

- Downlock springsCHECK

- 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 valveNO LEAK

- Inner and outer cell magnetic .........................FLUSH

fuel level


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 fil l access door...CLOSED


- * Thrust recovery nozzle (PW only)CLOSED/LATCHED

- Hydraulic Filter Visual door (PW only).CLOSED

- * FAN COWL doors...CLOSED/LATCHED- *Drain mastCONDITION/NO LEAK


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 exhaustCLEAR

- 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

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Stby angle of attack probe

F/O static port Capt static port

Avionic equipment

vent air inlet valve


Capt angle of

attack probe

1. Left forward fuselage

- * AOA probesCONDITION

- F/O and Capt static ports CLEAR

- Avionics equipment vent air inlet valveCONDITION

- Oxygen BayCLOSED

- Oxygen overboard discharge indicatorGREEN- *Toilet servicing door ( if installed )CLOSED

Leftforwardfuselage

-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

ATC 1 antennaDME 2 antenna

Left wing light

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

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Leftforwardfuselage/Nosesection

Left STBY static port

Oxygen overboard discharge indicator

Oxygen bayDME 1 antenna

CAPT TAT probe

CAPT pitot probe

STBY pitot probe

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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2. Nose Section

- * Pitot Probes CONDITION

- STBY static portsCLEAR

- * TAT probes.CONDITION

- *Radome and latchesCONDITION/LATCHED

- Forward avionics compartment doorCLOSED

- Ground electrical power door(if not required)..CLOSED

Check pitot probes covers are removed

NoseSection

CAPT pitot probe

STBY pitot probe

CAPT TAT probe

FO TAT probe

DME 1 antenna

radome

latch

localizer/ glideslope antenna 1&2 behind radome

Forward avionics compartment door

Ground electrical power door

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

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NoseLandingGear

Gear downlock sensor

Gear uplock roller

Gear safety pin hook

Parking brakelight

Towing lever( normal position)

Nose landing gear box

electrical cylinder

Nose wheel steering actuating cylinder

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Nose wheel steering

Actuating cylinder

Gear extend sensors

Safety pin removed

Safety pin installed

NoseLandingGear

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Rightforwardfuselage

4. Right Forward fuselage

- RH + AFT avionics compartment doors.CLOSED

- Avionic equipment vent air outlet valve.CONDITION

- F/OCAPT static portsCLEAR

- *AOA probe..CONDITION

- Forward cargo door and selector panel..CHECK

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

Right STBY static port

DME 1 antenna

F/O TAT probe

Forward RH avionics

compartment door

Battery vent exhaust

Skin temp sensor for

Avionics ventilation

F/O pitot probe

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Rightforwardfuselage

ATC 2 mode S antenna

VHF 1 antenna

F/O AOA probe

Scuff plate

DME 2 antenna

Fuselage drain

valves

ATC 2 antenna

ATC 1 antenna

R/H wing light

F/O static port

CAPT static port

Aft RH avionic compartment door

Avionics equipment

Vent air outlet valve

- 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.

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Rightfo

rwardfuselage

Forward cargo door

Locked indication ( green )

/unlocked is red/

Water drain mast

Cargo compartment light switch

Indicator light ( cargo door

Actuator extended and locked )

Forward cargo selector panelForward cargo door control valve selector

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LowerCenterfuselage

5. 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 ( see page 21)

- Pack air intakes and outlets CLEAR

Look for obvious damage

Potable water drain panel

TCAS antenna

Anti-collision light

DME 2 antenna

ATC 2 antennaMarker antenna

Forward cargo door

Right pack air inlet

Drain mast

- Engine inlet cover must be removed before flight

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Low

erCenterfuselage

RAM air inlet flap

LP ground connection

door

HP ground connection

door

Left pack air inlet


Electrical service panel

( belly fairing panel )

28 V / 50 W DC socket

Hydraulic compartment wheel

Well light switch

Interphone jack

- Check No Screws are missing or loose on panels marked area

SAFA Top 2 inspection finding.

Loose screw

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Rig

htCenterwing

6. RH Center wing

- Yellow hydraulic bay door..CLOSED

- Fuel panelCLOSED

- Inner tank magnetic fuel.FLUSH

- Fuel water drain valve inner tankNO LEAK

- Landing light..CONDITION

- *Slat 1..CONDITION

Yellow hydraulic electrical

Pump cooling air outletYellow hydraulic pump

and cooling

Seal drain container

Right main landing gear

door opening handle

Fuel water drain valve


Center tank magnetic

Fuel level indicator

Yellow hydraulic bay door

Right pack air outlet

-Check No Screws are missing or loose on panels

in marked area

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RightCenterwing

Slat 1

Fuel panel

Right landing light

Fuel water drain valve inner tank

Inner tank fuel pump

Multi tank indicator

Pre-selector switch

- Check slat / leading edges condition

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EN

G2leftside

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

- To check the FAN COWL doors closed and latched you must

lean forward and look the latches underside of the engine.

Oil fill access doorDrain mast

Master magnetic chip

Detector access door

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

FAN COWL door closed but NOT latched

Hold Open Device [ HOD ] not activated

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Filename : Guidance for pre-flight inspection REV/02 Effective date : 05.Sep.2013

EN

G2leftside

Engine inlet

Fan blades

FAN COWL doors not latchedNote : 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

properlyLatch closed

properly

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ENG

2rightside

8. ENG 2 RH side

- Vent inlet ( CFM only )..CLEAR

- Pressure-relief /start valve handle access doorCLOSED

- Nose Cowl pressure relief door ( PW only )..CLOSED

- Engine oil fill access/starter air valve overrideCLOSED

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

Fire agent bottles access door

pylon

Ram air inlet

Service interphone jack

Anti-ice discharge grille

Gearbox overboard discharge

Air cooled oil cooler outletStarter shutoff valve / pressure relief door

- Check No Screws are missing or loose on

panels

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ENG2rightside

- Fresh Oil visible in this

area may indicate oil

leakage. Inform MCC

Strut drain

Pre-cooler outlet

Turbine exhaust

Reverser cowl




- the cowl doors are correctly closed and latched.

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RHwing

leadingedge

9. RH Wing Leading edge

Check no dents , damages on the leading edge / Slats

Check for fuel leaks at lower surface and hydraulic

leaks at flight control area Wing leading edge

for FOD ( foreign object damage )

refuel coupling

Slat track shutter

slat

Magnetic fuel

Level indicator

Fuel ventilation

overpressure discWing tip

surge tank

air inlet

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- 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


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RHwingleadingedge

Wing tip

Static discharger

Right aileron

Strobe light NAV 1 light

NAV 2 light

Magnetic fuel level indicator

Fuel water drain valve 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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10. RH Wing trailing edge

- Static dischargers..CHECK

- *Control surfacesCONDTION

- *Flaps and fairings ..CONDITION

RHwingtrailingedge

WINGS, FLIGHT CONTROLS Check for fuel leaks at lower

surface and hydraulic leaks at flight control area

Flap track fairing

Right outboard flap

Static discharger

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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

- Down-lock springs..CHECK

- Safety ( gear)pin..REMOVED

- Ground hydraulic connection yellow.CLOSED

- Shroud fuel drain .CONDITION/NO LEAK

Down-lock proximity switch

LGCIU #2

Down-lock proximity switch LGCIU #1

Upper side stay

Down-lock spring

Lock stay actuator

Lock stay

Lower side stay

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.

RH normal brake module

Drag stay

L/G door

Main fitting shock stay

Servo valves

Hydr. fuse

RHL/G

andfuselage

- Check no hydraulic leak from servo valves

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RHL/G

andfuselage

Shrader valve ( yellow )

Brake wear indicator

Hydraulic quick

Disconnect ( green )

Torque link

Gear up-lock pinGround point

Hydraulic hose (green)Electrical harness

(wheel speed pick up)

Hydraulic hose (green)

Torque link

damper accumulator

Torque link damper

Fusible plug

Inflating valve

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RHL/G

andfuselage

Gear retraction jack

Lock stay actuator

Lock stay

Right landing light

Brake wear indicator pin

Schrader valve (green)

Hydraulic hose (yellow)

Electrical harness

Hydraulic hose (yellow)

Hydraulic quick

disconnect (yellow)

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RH

L/Gandfuselage

Main landing gear safety pin installed

Main landing gear safety pin removed

Ground hydraulic

Connection yellow

Yellow hydraulic

hand pump handle

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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RH

AFTfuselage

12. Right AFT fuselage

- Cargo door and selector panel..CHECK

- Bulk door ( if installed ) .CHECK

- *Toilet service access door.CLOSED

- Outflow valveCONDITION

- Drain mast..CONDITION

- Flight recorder access door..CLOSED

Radio altimeters 1 antennas

Radio altimeters 2 antennasAft cargo door

selector panel

VHF 2 antenna

Shroud fuel drain mast

( APU and center tank)

Check no damages surrounding the

cargo doors caused by ground equipments

AFT Cargo door

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RHA

FTfuselage

Rear right cabin door

Scuff plate

Toilet service access door

Outflow valve

Measurement point

Flight recorder

Access door

Stabilizer compartment drain mast

Aft water drain mast

Toilet system vacuum

generator outlet

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Ta

ilsection

13. Tail

- *Stabilizer, elevator, fin, rudder ..CONDTION


- *Lower fuselage structure CONDITION

( tail impact on runway )

FLIGHT CONTROLS Check for hydraulic leaks at flight control area

Static discharger

elevator

Trimmable horizontalstabilizer

fin

rudder

VOR antennas 1 & 2

Inside the fin

APU exhaust

NAV 1 light , Strobe , NAV 2 light

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Check trimmable horizontal

stabilizer leading edge condition

Check no hydraulic leak at

Rudder / flight control area


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APU

14. APU

- Access doors.CLOSED

- Air intakeCONDITION

- DrainCONDITION/NO LEAK

- Oil cooler air outlet.............CLEAR

- ExhaustCLEAR (see previous page)

- Navigation lightCONDITION( see prev .page)

- Fire extinguisher overpressure IN PLACE

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

Air intake nose

Air intake flap

Air inlet flow diverter

APU compartment overpressure

vent door

Access door

Oil cooler outlet

Fire extinguisher over-

pressure indication ( red disc )

Drain mast

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LHA

FTFuselage

15. Left AFT 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

- Check for correct steps positioning from below,

NO contact allowed and NO damages caused

by stairs on the fuselage

Potable water service door

Ground hydraulic

connection (blue)

door/RAT control panel

Hydraulic reservoir filling panel

and ground hydraulic connection

(green) door

Hydraulic filter,

reservoir blue

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LHLa

ndingGear

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 pinREMOVED

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.

Left landing light

Gear retraction jack

LH normal brake module

Brake pressure

transducer

Hydraulic fuse

Servo valves

Down lock spring

Upper side stay

Lower side stay

Lock stay actuator

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LHWingtrailingedge

17. LH wing trailing edge

- * Flaps and fairingCONDITION

- *Control surfacesCONDITION

- Static dischargersCHECK

WINGS, FLIGHT CONTROLS Check for fuel leaks at

lower surface and hydraulic leaks at flight control area

Left aileron

Left outboard flap

Fuel vent over-

pressure disc

Flap track fairing Static discharger

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LHWingleadingedge

18. LH wing leading edge

- *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

surge tank air inlet


Magnetic fuel level indicator

Wing tip

Navigation light

Fuel ventilation overpressure disc

Slat

Check no dents , damages on the leading edge / Slats

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Sharklet

Strobe

Navigation light

ENG 1 LH side


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ENG

1L/Hside

. ENG 1 LH side

- Oil fill access door...CLOSED


- * Thrust recovery nozzle (PW only)CLOSED/LATCHED

- Hydraulic Filter Visual door (PW only).CLOSED

- * FAN COWL doors...CLOSED/LATCHED

- *Drain mastCONDITION/NO LEAK





- the cowl doors are correctly closed and latched

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

In this picture illustrated when the FAN

COWL latches are not latched, it is visible

only if we look underside of the engine

Oil fill

access door

Drain mast

Master magnetic

chip detector

access door

EPR sensor

Engine inlet

Fan blades

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ENG

1L/Hside

- 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

Latch closed properly

Fan cowl

Reverser cowl

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ENG

1R/Hside

20. ENG 1 R/H side

Inboard strake

pylonFire agent bottles

access door

Interphone jack

Anti-ice discharge grille

Gearbox overboard dischargeStarter shut off valve /

Pressure relief door

Air cooled oil

cooler outlet

Thrust reverser

deactivated pin

If the thrust reverser

manually deactivated

by MX red pin visible

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- 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 exhaustCLEAR

- Pylon / access panel ...CONDITION / CLOSED



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LHCenterwing

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

SLAT 1

RAT doorsHydraulic reservoir

pressurization door

Left landing light

Inner tank fuel pumps

Magnetic fuel

level indicator

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LHCenterwin

g/forwardfuselage

- Check for correct steps positioning at 1L cabin door from below,

NO contact allowed and NO damages caused by stairs on the

fuselage

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.

Hydraulic reservoir

pressurization door

Anti-collision

light

Left pack

air outlet

Blue hydraulic electrical

pump cooling air outlet

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/


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Tire inspection:

1. Tread pattern:

1.1 Normal wear

1.2 Uneven wear (shoulder, center)

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 sidewall3.2 Weathering and radial cracking

4. Blisters and bulges

5. Miscellaneous

Tires contamination

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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

GrooveRib

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.

NOTE

TIRES HAVING REACHED THE ABOVE LIMITS ON ONE AIRCRAFT IN OUTSIDESTATION 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, reducesthe 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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Tireinspection


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Filename : Guidance forpre-flight walk-around REV/02 Effective date : 05.Sep.2013

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.

Over-inflated

tire uneven wear

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Tire wear and deterioration characteristics

Tireinspection

2 T d d


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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).

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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Tireinspection

2.3 Thrown tread:


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Caution: Avoid approaching wheel from either side of the tire.

Always go near the wheels from an oblique angle - direction of thetires shoulders.

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.

Early signs of tread separation can manifest themselves in the form

of tread bulges, local uneven wear (depression) or local

tread/sidewall rubber split.

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 )

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Tireinspection


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2.4 Peeled rib:

The tire has to be removed from aircraft

.

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 therelevant vendors 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.

Usually starts with a cut in the tread and results in a

circumferential delamination of the tread rib away from the tire

carcass.

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Tireinspection


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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 vendors manual for details.

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Tireinspection


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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.

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 cutare more than 13 mm (0.5 in) apart when measured in radial

direction.

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Tireinspection


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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.

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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Tireinspection


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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.

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

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Tireinspection


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2.9 Open tread splice:

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

2.10 Tread chipping and chunking:

This is a condition visible at the edge of the tread rib in which small amounts ofrubber 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.

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

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Tire

inspection

3 Sid ll


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3.1 Cuts or cracks on the sidewall:

Sidewall cuts are often caused by foreign objects

present on the operating surfaces.

3. Sidewalls:

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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Tireinspection

4 Bli t d b l


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Filename : Guidance for pre-flight inspection REV/02 Effective date : 05.Sep.2013

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.

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.

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Tireinspection


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Complemented by Christian Ambiehl

Booklet made by Capt. Laszlo Ekes

Documents

Guidance for preflight walk-around REV02.pdf