Inspection after Lightning Strike for Quick Release of the Aircraft for a Maximum of 200 Flight Cycles

TASK 05-51-18-200-802-A
Inspection after Lightning Strike for Quick Release of the Aircraft for a Maximum of 200 Flight Cycles

WARNING: IT IS MANDATORY TO DO A FULL GENERAL VISUAL INSPECTION OF THE AIRCRAFT BEFORE 200 FLIGHT CYCLES (REFER TO TASK 05-51-18). IF YOU DO NOT OBEY THIS INSTRUCTION, THE AIRCRAFT WILL NOT OBEY THE AIRWORTHINESS REQUIREMENTS.

CAUTION: WHEN YOU DO THE FULL INSPECTION:

IF YOU FIND STRUCTURAL DAMAGE THAT IS THE RESULT OF A LIGHTNING STRIKE AND
IF THE ALLOWABLE DAMAGE LIMITS FOR THAT DAMAGE ARE SPECIFIED IN THE SRM,

CALCULATE THE FLIGHT CYCLE VALUES FOR THE ALLOWABLE DAMAGE LIMITS FROM THE LIGHTNING STRIKE AND NOT FROM THE END OF THE FULL INSPECTION.

1. Reason for the Job
This procedure lets you release the aircraft for a maximum of 200 flight cycles after the lightning strike event. Before 200 flight cycles you must do a full inspection, refer to task 05-51-18-200-001-A.
To make sure that the aircraft is in the correct condition to continue in service after a lightning strike:

Do a careful inspection of the lightning strike areas to find the type and quantity of possible damage.
If you find damage, make a decision about the necessary repair or action.

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE
No specific	1	ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE
No specific	1	BINOCULARS-(7X50)
No specific	AR	CHOCK - WHEEL(S)
No specific	1	LIGHT SOURCE - HIGHPOWER
No specific	AR	SAFETY BARRIER(S)
No specific	AR	WARNING NOTICE(S)
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
315AL, 316AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 10-11-00-555-015-A	Procedure for the Installation of Wheel Chocks on Aircraft
TASK 12-34-24-869-002-A	Aircraft Grounding (Earthing) for the Maintenance Operations
TASK 12-34-24-869-002-A-01	Aircraft Grounding (Earthing) during Transit, Turnaround or Overnight Stop
TASK 21-31-00-710-002-A	Operational Test of the Pressure Control and Monitoring
TASK 21-31-00-710-003-A	Operational Test of Manual Mode Selection and Manual Mode Pressure Control and Functional Test of Manual Mode Cabin Altitude/Outflow Valve Position Indication
TASK 23-11-00-710-001-A	Operational Test of the High Frequency (HF) System
TASK 23-11-11-000-001-A	Removal of the High Frequency (HF) Antenna
TASK 23-11-11-400-001-A	Installation of the High Frequency (HF) Antenna
TASK 23-12-00-710-001-A	Operational Test of the Very High Frequency (VHF) System
TASK 23-12-00-740-001-A	BITE Test of the Very High Frequency (VHF) System
TASK 23-12-11-000-001-A	Removal of the VHF Antennas
TASK 23-12-11-000-002-A	Removal of the VHF Antenna
TASK 23-12-11-400-001-A	Installation of the VHF Antennas
TASK 23-12-11-400-002-A	Installation of the VHF Antenna
TASK 23-28-00-740-001-A	BITE Test of the SATCOM system
TASK 23-61-00-200-001-A	Resistance Check from the Tip to the Retainer and Bonding Check from the Retainer to the Aircraft Structure
TASK 24-00-00-710-003-A	Integrity Test of the Electrical Power
TASK 24-22-51-200-001-A	Check of the Lightning Protection Modules
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 25-65-00-710-001-A	Operational Check of ELT System by Manual Activation
TASK 25-65-00-740-001-A	Emergency Locator Transmitter (ELT) System - BITE Test
TASK 25-65-14-000-001-A	Removal of the Emergency Locator Transmitter (ELT) Antenna
TASK 25-65-14-400-001-A	Installation of the Emergency Locator Transmitter (ELT) Antenna
TASK 26-13-00-710-001-A	Operational Test of the APU Fire and Overheat Detection System
TASK 27-14-00-710-001-A	Operational Test of the Aileron and Hydraulic Actuation
TASK 27-14-51-000-001-A	Removal of the Aileron Servo Control
TASK 27-14-51-400-001-A	Installation of the Aileron Servo Control
TASK 27-24-00-710-001-A	Operational Test of the Rudder Hydraulic Actuation
TASK 27-24-51-000-001-A	Removal of the Rudder Servo Control
TASK 27-24-51-400-001-A	Installation of the Rudder Servo Control
TASK 27-34-00-710-001-A	Operational Test of the Elevator and Hydraulic Actuation
TASK 27-34-51-000-001-A	Removal of the Elevator Servo Control
TASK 27-34-51-400-001-A	Installation of the Elevator Servo Control
TASK 27-44-00-710-001-A	Operational Test of the Jamming Protection Device of the Trimmable Horizontal Stabilizer Actuator
TASK 27-50-00-866-008-A	Extension of the Flaps on the Ground
TASK 27-50-00-866-008-A-01	Extension of the Flaps/Slats on the Ground
TASK 27-50-00-866-009-A	Retraction of the Flaps on the Ground
TASK 27-50-00-866-009-A-01	Retraction of the Flaps/Slats on the Ground
TASK 27-54-00-710-001-A	Operational Test of the Flap System
TASK 27-60-00-866-002-A	Extension-Retraction of the Spoilers for Maintenance
TASK 27-64-00-710-001-A	Operational Test of the Spoiler Hydraulic Actuation
TASK 27-80-00-866-004-A	Extending the Slats on the Ground
TASK 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 27-84-00-710-001-A	Operational Test of the Slat System
TASK 29-00-00-864-001-A	Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action
TASK 29-22-00-710-006-A	Operational Check of Ram Air Turbine (RAT) Automatic Deployment
TASK 29-22-00-710-007-A	Operational Test of the Manual Deployment and the Retraction of the Ram Air Turbine
TASK 29-22-51-200-003-A	Detailed Inspection of RAT Assembly and Doors in Deployed Position and Lubrication of Doors Linkage Strut Joints and Bearings
TASK 30-31-00-710-001-A	Operational Test of the Probe Ice Protection
TASK 30-42-00-710-001-A	Operational Test of the Windshield Anti-Icing and Defogging
TASK 30-71-00-710-001-A	Operational Test of the Drainmast Ice Protection
TASK 30-81-00-710-001-A	Operational Test of the Ice Detection System
TASK 32-00-00-481-001-A	Installation of the Safety Devices on the Landing Gears
TASK 32-00-00-481-002-A	Installation of the Safety Devices on the Landing Gear Doors
TASK 32-11-00-200-001-A	General Visual Inspection of the Main Landing Gear
TASK 32-12-00-010-001-A	Open the Main Gear Doors for Access
TASK 32-12-00-410-001-A	Close the Main Gear Doors after Access
TASK 32-21-00-200-002-A	General Visual Inspection of the Nose Landing Gear
TASK 32-22-00-010-001-A	Nose Gear Doors - Ground Doors Opening
TASK 32-22-00-410-001-A	Nose Gear Doors - Ground Doors Closing
TASK 32-46-00-740-001-A	BITE Test of the BSCU
TASK 32-69-00-740-001-A	BITE Check of Landing-Gear Control Interface-Unit (LGCIU) With Use of MCDU to Ensure that Continuous BITE is Operative
TASK 33-41-00-710-001-A	Operational Test of the Navigation Lights
TASK 33-42-00-710-001-A	Operational Test of the Landing Lights
TASK 33-47-00-710-002-A	Operational Test of the Logo Lights
TASK 33-48-00-710-002-A	Operational Test of the Anti-Collision/Strobe Lighting
TASK 33-49-00-710-001-A	Operational Test of the Wing and Engine Scan Lights
TASK 33-51-15-400-001-A	Installation of the Emergency Overwing Lights
TASK 34-11-15-000-001-A	Removal of the Pitot Probe
TASK 34-11-15-400-001-A	Installation of the Pitot Probe
TASK 34-11-18-000-001-A	Removal of the TAT Sensor
TASK 34-11-18-400-001-A	Installation of the TAT Sensor
TASK 34-11-19-000-001-A	Removal of the Angle of Attack (AOA) Sensor
TASK 34-11-19-400-001-A	Installation of the Angle of Attack (AOA) Sensor
TASK 34-13-00-710-001-A	Operational Test of the AIR DATA Switching Function
TASK 34-22-00-710-001-A	Operational Check of the Standby Compass Including Light Test and Visual Check
TASK 34-22-00-710-001-A-01	Operational Check of the Standby Compass Including Light Test and Visual Check (with the Standby Compass Calibrator)
TASK 34-36-00-710-002-A	Operational Test of the GPS
TASK 34-36-00-710-008-A	Operational Test of the GPS
TASK 34-36-11-000-001-A	Removal of the Localizer Antenna
TASK 34-36-11-400-001-A	Installation of the Localizer Antenna
TASK 34-36-16-000-001-A	Removal of the GPS Active Antenna
TASK 34-36-16-000-001-B	Removal of the GPS Active Antenna
TASK 34-36-16-400-001-A	Installation of the GPS Active Antenna
TASK 34-36-16-400-001-B	Installation of the GPS Active Antenna
TASK 34-36-18-000-001-A	Removal of the Glide/Slope Antenna
TASK 34-36-18-400-001-A	Installation of the Glide/Slope Antenna
TASK 34-41-00-730-001-A	System Test of the Weather Radar
TASK 34-41-00-740-002-A	BITE Test of the Weather Radar
TASK 34-41-11-000-004-A	Removal of the Weather-Radar Antenna Assembly
TASK 34-41-11-000-012-A	Removal of the Weather-Radar Antenna Assembly
TASK 34-41-11-400-005-A	Installation of the Weather-Radar Antenna Assembly
TASK 34-41-11-400-014-A	Installation of the Weather-Radar Antenna Assembly
TASK 34-42-00-740-002-A	BITE Test of the Radio Altimeter
TASK 34-42-11-000-001-A	Removal of the Radio Altimeter Antenna
TASK 34-42-11-400-001-A	Installation of the Radio Altimeter (RA) Antenna
TASK 34-43-00-740-001-A	BITE Test of the TCAS
TASK 34-43-00-740-001-C	BITE Test of the TCAS
TASK 34-43-11-000-004-C	Removal of the Traffic Alert and Collision Avoidance System (TCAS) Antenna
TASK 34-43-11-000-004-E	Removal of the Traffic Alert and Collision Avoidance System (TCAS) Antenna
TASK 34-43-11-400-004-C	Installation of the Traffic Alert and Collision Avoidance System (TCAS) Antenna
TASK 34-43-11-400-004-E	Installation of the Traffic Alert and Collision Avoidance System (TCAS) Antenna
TASK 34-51-00-710-001-A	Operational Test of the DME
TASK 34-51-11-000-002-A	Removal of the DME Antenna
TASK 34-51-11-400-002-A	Installation of the DME Antenna
TASK 34-52-00-740-004-A	BITE Test of the Air Traffic Control (ATC)
TASK 34-52-11-000-001-A	Removal of the ATC Antenna
TASK 34-52-11-400-001-A	Installation of the ATC Antenna
TASK 34-53-00-710-002-A	Operational Test of the ADF
TASK 34-53-11-000-001-A	Removal of the ADF Loop and Sense Antenna
TASK 34-53-11-400-001-A	Installation of the Automatic Direction Finder (ADF) Loop and Sense Antenna
TASK 34-55-00-710-001-A	Operational Test of the VOR/MKR
TASK 34-55-11-000-001-A	Removal of the VOR Antenna
TASK 34-55-11-400-001-A	Installation of the VOR Antenna
TASK 34-55-18-000-001-A	Removal of the Marker Antenna
TASK 34-55-18-400-001-A	Installation of the Marker Antenna
TASK 34-72-00-740-001-A	BITE Test of the T/TISS
TASK 49-00-00-710-008-A	Operational Test of the APU
TASK 49-00-00-710-010-A	Operational Test of the APU
TASK 52-41-00-010-001-A	Open the APU Doors for Access
TASK 52-41-00-410-001-A	Close the APU Doors after Access
TASK 53-15-11-200-001-A	Detailed Inspection of the Radome
TASK 53-15-11-200-001-A-01	Detailed Inspection of the Radome
TASK 53-19-42-000-001-A	Removal of the Static Port Blanking-Plate
TASK 53-19-42-400-001-A	Installation of the Static Port Blanking-Plate
TASK 53-45-11-000-001-A	Removal of the Dorsal Fin
TASK 53-45-11-400-001-A	Installation of the Dorsal Fin
TASK 55-13-11-000-001-A	Remove/Open of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels
TASK 55-13-11-400-001-A	Install/Close of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels
TASK 55-32-11-000-001-A	Removal of the Vertical Stabilizer Leading-Edge
TASK 55-32-11-400-001-A	Installation of the Vertical Stabilizer Leading-Edge
TASK 55-33-13-010-002-A	Opening/Removal of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-33-13-410-002-A	Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-34-11-000-001-A	Removal of the Vertical Stabilizer Tip
TASK 56-11-11-000-001-A	Removal of the Windshield
TASK 56-11-11-000-001-A-01	Removal of the Windshield
TASK 56-11-11-200-001-A	Inspection of the Windshields
TASK 56-11-12-000-001-A	Removal of the Fixed Windows
TASK 56-11-12-200-001-A	Inspection of the Fixed Windows
TASK 56-12-11-000-001-A	Removal of the Sliding Window
TASK 56-12-11-000-001-A-02	Removal of the Sliding Windows
TASK 56-12-11-200-001-A	Inspection of the Sliding Windows
TASK 57-31-23-000-801-A	Removal of the Sharklet
TASK 57-31-23-400-801-A	Installation of the Sharklet
TASK 73-21-00-710-806-A	Test No.7 - EEC Operation Test (Self Test)
TASK 73-21-00-710-807-A	Test No.6 - EEC Operation Test (Idle Test)
TASK 73-21-60-720-040-A	Functional Test of the Electronic Control Unit (ECU)
TASK 73-21-60-720-040-B	Functional Test of the Electronic Control Unit (ECU)
TASK 73-22-00-710-040-A	Operational Test of the FADEC SYSTEM on the Ground
TASK 73-22-34-710-040-A	Operational Test of the EEC
TASK 73-29-00-710-040-A	Operational Test of the FADEC on the ground (with Engine Motoring)
TASK 73-29-00-710-040-A-01	FADEC Ground Test Without the CFDS
TASK 73-29-00-710-040-A-02	Operational Test of the FADEC on the Ground (with Engine non Motoring)
TASK 73-29-00-710-040-B	Operational Test of the FADEC on the Ground (with Engine Motoring)
TASK 73-29-00-710-040-B-02	Operational Test of the FADEC on the Ground (with Engine Non motoring)
TASK 78-31-00-710-040-A	Operational Test of the Thrust Reverser System
TASK 78-31-00-710-040-A-01	Operational Test of the Thrust Reverser without CFDS - Engine not Running
TASK 78-31-00-710-040-A-02	Operational Test of the Thrust Reverser without CFDS - Engine Running
TASK 78-31-00-710-041-A	Operational Test of the Thrust Reverser System with the CFDS
TASK 78-31-00-710-041-A-02	Operational test of the Thrust Reverser without the CFDS and Engine Running
TASK 78-31-00-710-042-A	Operational Test of the Thrust Reverser System
TASK 78-31-00-710-805-A	Operational Test of Thrust Reverser with MCDU
TASK 78-31-00-710-805-A-01	Thrust Reverser Cycling Test (Engine Running)
ESPM 205212
SRM 511113	(for corrective action)
SRM 52811401	(for corrective action)
SRM 52821101	(for corrective action)
SRM 530000	(for corrective action)
SRM 531111	(for corrective action)
SRM 532111	(for corrective action)
SRM 53251101	(for corrective action)
SRM 53351101	(for corrective action)
SRM 55300001	(for corrective action)
SRM 55321101	(for corrective action)
SRM 55410001	(for corrective action)
SRM 57211101	(for corrective action)
SRM 57312101	(for corrective action)
SRM 57312201	(for corrective action)
SRM 573123	(for corrective action)
SRM 57400001	(for corrective action)
SRM 57520001	(for corrective action)
SRM 57530001	(for corrective action)
SRM 57551101	(for corrective action)
SRM 57612101	(for corrective action)
SRM 57700001	(for corrective action)
Zone 1 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections
Zone 2 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections
Zone 3 (Phase 1 and Phase 2) Inspection
Zone 4 (Phase 1 and Phase 2) Inspection
Location on the Ground for Calibration of the Binoculars
Calibration of the Binoculars
Walk-Around Inspection Sequence from the Ground for the Bottom Part of the Aircraft
Walk-Around Inspection Sequence from the Access Platform for the Top Part of the Aircraft
Damage Reporting/Recording Sheet ** ON A/C NOT FOR ALL
Damage Reporting/Recording Sheet ** ON A/C NOT FOR ALL
Damage Reporting/Recording Sheet ** ON A/C NOT FOR ALL
Damage Reporting/Recording Sheet ** ON A/C NOT FOR ALL
Aircraft Structure
Location of the Antennas, Probes, Sensors and Exterior Lights ** ON A/C NOT FOR ALL
Location of the Antennas, Probes, Sensors and Exterior Lights ** ON A/C NOT FOR ALL
Location of the Antennas, Probes, Sensors and Exterior Lights ** ON A/C NOT FOR ALL
Location of the Antennas, Probes, Sensors and Exterior Lights ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 05-51-18-210-120-A

A. General
(1) Lightning
(a) Lightning always has two or more attachment points (one entry and one exit) on the aircraft skin.
(b) Lightning moves back along the surface of the aircraft (swept stroke zone). This can cause a sequence of random attachment points along a line in the direction of travel of the aircraft.
(c) Lightning hits some areas more frequently than others.
(2) Inspection requirements:
(a) The aircraft design keeps the effects of lightning to a minimum.
They can continue their flights and safely do the landing after a lightning strike.
(b) It is not possible to know accurately where the lightning strike will occur.
(c) Lightning strikes do not always cause the same quantity of damage. The quantity of damage comes from the intensity of the lightning strike.
(d) Therefore, it is necessary to do a full inspection after a lightning strike. This is to make an estimate of the damage and to make sure that the aircraft can, as a minimum, continue the service (which agrees with the conditions in the Master Minimum Equipment List (MMEL) and the Master Configuration Deviation List (MCDL)).
The inspection after a lightning strike is related to:

The type of system to give the tests that are necessary
The requirements of the MMEL and the MCDL.

(3) Inspection zones for walk around on the ground and on the access platform
(a) The aircraft is divided into four zones and one optional zone where lightning attachment is more frequent and for which an inspection is mandatory:

Zone 1: Forward fuselage from the radome to the forward part of the wing root (FR35) for the top part of the fuselage and from the radome to the middle of the belly fairing (FR42) for the bottom part of the fuselage.
Zone 1 also includes the NLG, MLG, Ram Air Turbine (RAT) (if used during flight) and all antennas.
Zone 1 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections
Zone 2: The nacelles and the pylons
Zone 2 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections
Zone 3: The outboard part of the wing from the wing fence/sharklet to flap-track fairing 4 included
Zone 3 (Phase 1 and Phase 2) Inspection
Zone 4: The horizontal stabilizer, the vertical stabilizer and the tail cone.
Zone 4 (Phase 1 and Phase 2) Inspection
Zone 5 (optional): Aft fuselage from the aft part of the wing root (FR47) to the forward part of the tail cone (FR70) for the top and bottom parts of the fuselage. The inspection of zone 5 is necessary only if there is damage in zone 1 or 2.
Zone 1 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections
Zone 2 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections

Subtask 05-51-18-210-122-A

B. Inspection Preparation
(1) Before you start the inspection, we recommend that you collect all the information from the crew about the flight conditions.
(2) Make sure that you have the related aircraft Post Flight Report (PFR).
(3) You must do a check of all the events in the crew report or the PFR when you do the inspection.

Subtask 05-51-18-481-052-A

C. Safety Precautions
(1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
(2) Make sure that the CHOCK - WHEEL(S) are in position (Ref. AMM TASK 10-11-00-555-015).
(3) Make sure that the safety devices are installed on the landing gears (Ref. AMM TASK 32-00-00-481-001).
(4) Ground the aircraft for maintenance operations (Ref. AMM TASK 12-34-24-869-002).

Subtask 05-51-18-866-052-A

D. Extension of the Flight Control Surfaces
(1) Extend the flaps (Ref. AMM TASK 27-50-00-866-008).
(2) Extend the slats (Ref. AMM TASK 27-80-00-866-004).
(3) Extend the spoilers (Ref. AMM TASK 27-60-00-866-002).

Subtask 05-51-18-010-052-A

E. Get Access
(1) Open the NLG doors (Ref. AMM TASK 32-22-00-010-001) and install the safety devices (Ref. AMM TASK 32-00-00-481-002).
(2) Open the MLG doors (Ref. AMM TASK 32-12-00-010-001) and install the safety devices (Ref. AMM TASK 32-00-00-481-002).

Subtask 05-51-18-860-053-A

F. Aircraft Maintenance Configuration
(1) Make sure that the hydraulic systems are depressurized
(Ref. AMM TASK 29-00-00-864-001).
(2) Make sure that the aircraft electrical circuits are de-energized
(Ref. AMM TASK 24-41-00-862-002).
(3) On the center pedestal, install the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION on the flap/slat control lever.
(4) In the cockpit, put the WARNING NOTICE(S) in position on the center pedestal to tell persons not to operate the systems.
(5) Do the calibration of the BINOCULARS-(7X50).
(6) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the inspection area for inspection with the BINOCULARS-(7X50).
(a) If you find damage during the inspection with the BINOCULARS-(7X50), put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE near the area that you must examine.
(b) If inspection with the BINOCULARS-(7X50) is unsatisfactory (for example, the BINOCULARS-(7X50) are not available or unserviceable or the calibration is not satisfactory), put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE near the area that you must examine.

Subtask 05-51-18-480-051-A

G. Calibration of the Binoculars

Location on the Ground for Calibration of the Binoculars

Calibration of the Binoculars

(1) Before you start the quick release inspection, make sure that the type of BINOCULARS-(7X50) and the luminosity are satisfactory for the task.
From the ground, when you are aligned with flap-track fairing 3 and with the lower forward edge of the vertical stabilizer, do these steps:
(a) With the BINOCULARS-(7X50), make sure that you can see the rivet line between the vertical stabilizer tip and the vertical-stabilizer spar-box interface. If you can see the rivet line, the condition is satisfactory.
(b) If the test is unsatisfactory, use the appropriate LIGHT SOURCE - HIGHPOWER to see the rivet line between the vertical stabilizer tip and the vertical-stabilizer spar-box interface.
If you can see the rivet line with the LIGHT SOURCE - HIGHPOWER, the condition is satisfactory and you must use it during your inspection with the binoculars.
If you cannot see the rivet line, the condition is unsatisfactory and the inspection with binoculars is not applicable. You must do the General Visual Inspection (GVI) from the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE.

Subtask 05-51-18-210-123-A

H. Inspection Sequence
(1) The inspections are divided into two phases:
(a) Phase 1 inspections
1 Walk-around inspection for lower zones 1, 2, 3 and 4:
a Visual inspection from the ground for primary damage and signs of other related damage.

Walk-Around Inspection Sequence from the Ground for the Bottom Part of the Aircraft

NOTE: The figures related to the walk-around inspection from the ground give the areas and the primary items for the inspection.
The phase 1 inspection subtasks give more information about the items for the inspection.

2 Walk-around inspection for upper zones 1, 2, 3 and 4:
a Use the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the applicable locations.
b Use the BINOCULARS-(7X50) to do a visual inspection for primary damage and signs of other related damage.

Walk-Around Inspection Sequence from the Access Platform for the Top Part of the Aircraft

NOTE: The figures related to the inspection from the access platform give the location of the access platform for the inspection and the primary items for the inspection.
The phase 1 inspection subtasks give more information about the items for the inspection.

c If it is not possible to do the inspection with the BINOCULARS-(7X50), do the GVI from the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE.
d If you do not find damage on the areas checked during the quick release GVI, it is not necessary to do inspection for those areas again during the full inspection (before 200 flight cycles).
3 Most phase 1 inspections are external. You must do all the phase 1 inspections.

NOTE: Some BITE and operational tests are given in phase 1 although no damage is found.

4 If you find damage during a phase 1 inspection and if there is reference to the phase 2 inspection, you must do the related phase 2 inspection.
EXAMPLE:
First step: You find burn marks or signs of damage during the walk-around inspection on the left wing fence/sharklet and on the left wing fence/sharklet static-discharger.
Second step: You must do only the phase 2 inspection subtasks "inspection after damage on the wings" and "inspection after damage on the static discharger".
5 If you do not find damage during the phase 1 inspections, it is not necessary to do the phase 2 inspections.
(b) Phase 2 inspections
1 If you find damage in zone 1:
If the longest distance (X) between two successive impacts in zone 1 is more than the distance between the last impact and the end limit of zone 1 (Y), you must continue the inspection of the fuselage skin for the distance (X) aft from the last impact that you found.

If you find damage again, continue the inspection for the distance (X) aft from the last impact that you found.
Zone 1 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections

2 If you find damage in zone 1 or 2:
a Inspection of lower zone 5:

Do a visual inspection from the ground for primary damage and signs of other related damage.

b Inspection of upper zone 5:

Use the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the applicable locations.
Use the BINOCULARS-(7X50) to do a visual inspection for primary damage and signs of other related damage.
If it is not possible to do the inspection with the BINOCULARS-(7X50), do the GVI from the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE.
If you do not find damage on the areas checked during the quick release GVI, it is not necessary to do inspection for those areas again during the full inspection (before 200 flight cycles).

3 If you find damage in zones 2, 3 and 4:

Illustrations for inspection zone for phase 2 are given below:
Zone 2 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections
Zone 3 (Phase 1 and Phase 2) Inspection
Zone 4 (Phase 1 and Phase 2) Inspection

4 For the antenna:
If you find damage on one or more antennas, do an inspection on the structure to a 1 m (3.28 ft.) radius half-circle aft of the antenna.
If the longest distance (X) between two successive impacts is more than the distance between the last impact and the end of 1 m (3.28 ft) radius half-circle aft of the antenna (distance (Y)), you must continue the inspection for the distance radius (X) aft of the last impact.
Do the inspection again in the aft direction until you find no other damage.

Zone 1 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections

5 The phase 2 inspections give more information and it can be necessary to remove components. If you find damage during phase 1, increase the external inspection area. Most phase 2 inspections are internal.
6 The list of phase 2 inspections is as follows:

Inspection after damage on the radome
Inspection after damage on the windshield, fixed windows, sliding windows, window frames and attaching fasteners
Inspection after damage on the landing gear doors
Inspection after damage on the NLG and/or the MLG
Inspection after damage on the belly fairing
Inspection after damage on the Air Data/Inertial Reference System (ADIRS) probes and sensors
Inspection after damage on the ice detection probes (if installed)
Inspection after damage on the drain masts
Inspection after damage on the exterior lights
Inspection after damage on the communication antennas
Inspection after damage on the navigation antennas
Inspection after damage on the fuselage skin
Inspection of the APU after damage on the APU exhaust
Inspection after damage on the wings
Inspection after damage on the engine nacelles and pylons
Inspection after damage on the stabilizers
Inspection after damage on the static dischargers
Inspection after damage on the RAT (if deployed during flight)
Phase 2 inspection of the fuselage (Zone 5) (if there is damage on zone 1 or 2)

7 If you find damage, put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE near the area where you find damage and report them in the damage reporting/recording sheet.

Damage Reporting/Recording Sheet ** ON A/C NOT FOR ALL

8 If you find damage on the composite parts (signs of impact, damaged paintwork, abrasions, delamination or dents), you must do an inspection of the related damaged area for delamination and internal damage. Refer to the Structural Repair Manual (SRM).

Aircraft Structure

9 If you find damage (holes, delamination, debonding, etc.) during the inspection of the total surface, refer to the applicable SRM chapter to find the allowable limits. Refer to the General Reporting and Logic Chart to make a decision after you find damage, SRM 511113.

4. Procedure
Subtask 05-51-18-210-121-A

A. Phase 1 Inspection of the Fuselage (Zone 1)

Zone 1 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections

Location of the Antennas, Probes, Sensors and Exterior Lights ** ON A/C NOT FOR ALL

For the bottom part of Zone 1:

Walk-Around Inspection Sequence from the Ground for the Bottom Part of the Aircraft

For the top part of zone 1:

Walk-Around Inspection Sequence from the Access Platform for the Top Part of the Aircraft

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the fuselage skin
	Visually examine the fuselage skin for: - Burn marks, change of color and disruption of the surface.	X
2.	Inspection of the radome
	Visually examine the external skin of the radome and the lightning arresters for burn marks.	X
3.	Inspection of the windshield, the fixed and sliding windows and the window frames
	Visually examine the windshield, the fixed and sliding windows and the window frames for: - Burn marks, change of color and disruption of the surface.	X
4.	Inspection of all the antennas
	Carefully examine all the communication and navigation antennas and the adjacent areas for burn marks, change of color, puncturing, delamination or other damage.	X
	If you find damage such as cracks, through holes or missing parts, replace the related antenna before the next flight. For other types of damage, do the specific phase 2 inspection of the related damaged antenna.		X
5.	Inspection of all the probes, sensors and drain masts
	Carefully examine all the probes, sensors and drain masts and the adjacent areas for burn marks or change of color.	X
6.	Inspection of the ice detectors (if installed) and the lighted icing indicator
	Carefully examine the ice detectors and the lighted icing indicator for burn marks.	X
7.	Inspection of all the external lights
	Carefully examine all the external lights and the adjacent area for burn marks or other damage.	X
8.	Inspection of the NLG doors
	Examine the skin of the NLG doors for: - Burn marks, change of color, puncturing and delamination.	X
9.	Inspection of the NLG NOTE: It is necessary to do the inspection if the lightning strike occurred: When the landing gear was extended, or During the extension of the landing gear, or If you find a through hole on the landing gear doors.
	Examine the NLG for: Burn marks, change of color and puncturing.	X
	Examine the landing gear structure, shock absorber, components, electrical harnesses and hydraulic pipes for: Burn marks, change of color and other damage.	X
10.	Inspection of the belly fairing to fuselage junction
	Examine the belly fairing panels and the fasteners (wing-to-fuselage fairings included) for: Burn marks, change of color, puncturing and delamination.	X
	Examine the glazing panel of the taxi light and the landing lights for burn marks.	X
	Examine the pack inlets for: Burn marks, change of color, puncturing and other damage.	X
11.	Inspection of the MLG doors
	Examine the skin of the MLG doors for: Burn marks, change of color, puncturing and delamination.	X
12.	Inspection of the MLG NOTE: It is necessary to do the inspection if the lightning strike occurred: When the landing gear was extended, or During the extension of the landing gear, or If you find a through hole on the landing gear doors.
	Examine the MLG for: Burn marks, change of color and puncturing.	X
	Examine the landing gear structure, shock absorber, components, electrical harnesses and hydraulic pipes for: Burn marks, change of color, puncturing and other damage.	X
13.	Inspection of the RAT
	If RAT used during flight, examine the RAT and the RAT doors in the belly fairing on the left side for: Burn marks, change of color, puncturing and other damage.	X

Subtask 05-51-18-210-124-A

B. Phase 1 Inspection of the Nacelles and Pylons (Zone 2)

Zone 2 (Phase 1 and Phase 2) and Zone 5 (Phase 2) Inspections

For the bottom part of Zone 2:

Walk-Around Inspection Sequence from the Ground for the Bottom Part of the Aircraft

For the top part of Zone 2:

Walk-Around Inspection Sequence from the Access Platform for the Top Part of the Aircraft

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Examine each air intake, inlet cowl, fan cowl, thrust reverser/fixed fan duct, exhaust nozzle and pylon: Burn marks, change of color and puncturing.	X

Subtask 05-51-18-210-125-A

C. Phase 1 Inspection of the Outboard Wing from the Wing Fence/Sharklet to Flap-Track Fairing 4 (Zone 3)

Zone 3 (Phase 1 and Phase 2) Inspection

For the bottom part of Zone 3:

Walk-Around Inspection Sequence from the Ground for the Bottom Part of the Aircraft

For the top part of Zone 3:

Walk-Around Inspection Sequence from the Access Platform for the Top Part of the Aircraft

ITEM	INSPECTION TASKS	PHASE 1
1.	Examine the wing leading edge for: Burn marks, change of color, puncturing and delamination.	X
2.	Examine the slats for: Burn marks, change of color and puncturing.	X
3.	Examine the wing fence/sharklet for: Burn marks, change of color, puncturing and other damage.	X
4.	Examine the navigation and obstruction lights for: Burn marks, change of color, puncturing and other damage.	X
5.	Examine the wing for missing static dischargers. Refer to the MCDL to get the maximum number of missing static dischargers permitted during flight.	X
6.	Examine the wing trailing edge from the wing fence/sharklet to the aileron for: Burn marks, change of color and puncturing.	X

Subtask 05-51-18-210-126-A

D. Phase 1 Inspection of the Vertical Stabilizer, Horizontal Stabilizer and Tail Cone (Zone 4)

Zone 4 (Phase 1 and Phase 2) Inspection

For the bottom part of Zone 4:

Walk-Around Inspection Sequence from the Ground for the Bottom Part of the Aircraft

For the top part of Zone 4:

Walk-Around Inspection Sequence from the Access Platform for the Top Part of the Aircraft

ITEM	INSPECTION TASKS	PHASE 1
1.	Inspection of the vertical stabilizer
	Examine the vertical stabilizer for missing static dischargers. Refer to the MCDL to get the maximum number of missing static dischargers permitted during flight.	X
	Examine the skin of the vertical stabilizer, the vertical-tail-plane tip, the rudder (specially the leading and trailing edges, the rudder surface in the hinge area and the antenna fairings) and the fin cap lightning diverters for: Burn marks, change of color, puncturing and other damage.	X
2.	Inspection of the horizontal stabilizer
	Examine the horizontal stabilizer for missing static dischargers. Refer to the MCDL to get the maximum number of missing static dischargers permitted during flight.	X
3.	Examine all rear end fairing.
	Examine the APU exhaust fairing and the muffler for burn marks.	X
	Examine the navigation and strobe light for burn marks.	X

Subtask 05-51-18-760-050-A

E. Phase 1 Electrical Power Check and Test

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Do a check of the lightning protection modules (Ref. AMM TASK 24-22-51-200-001).	X
2.		Do an integrity test of the electrical power (Ref. AMM TASK 24-00-00-710-003).	X

Subtask 05-51-18-710-051-A

F. Phase 1 Operational Test of the HF system (If Installed)

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Do an operational test of the HF system (Ref. AMM TASK 23-11-00-710-001).	X

Subtask 05-51-18-210-127-A

G. Inspection after Damage on the Radome

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
1.	If you find damage during the inspection:
	(1) Do the detailed inspection of the radome (Ref. AMM TASK 53-15-11-200-001). If you find a through hole:	X
	(a) Examine the Weather Radar (WR) and the WR antenna drive for burn marks, pitting and other damage.		X
	- If you find damage on the flat plate antenna, replace it (Ref. AMM TASK 34-41-11-000-004) or (Ref. AMM TASK 34-41-11-000-011) and (Ref. AMM TASK 34-41-11-400-005) or (Ref. AMM TASK 34-41-11-400-014) or (Ref. AMM D/O 34-41-11-40).		X
	- Do the BITE test of the WR (Ref. AMM TASK 34-41-00-740-002)		X
	- Do the system test of the WR (Ref. AMM TASK 34-41-00-730-001).		X
	(b) Examine the localizer antenna and the glide/slope antenna for burn marks, pitting and other damage.		X
	- If you find damage on the localizer antenna, replace it (Ref. AMM TASK 34-36-11-000-001) and (Ref. AMM TASK 34-36-11-400-001)		X
	- If you find damage on the glide/slope antenna, replace it (Ref. AMM TASK 34-36-18-000-001) and (Ref. AMM TASK 34-36-18-400-001).		X

Subtask 05-51-18-210-128-A

H. Inspection after Damage on the Windshield, Fixed Windows, Sliding Windows, Window Frames and Attaching Fasteners

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
1.	If you find damage during the inspection:
	(1) Do the inspection of the related component:	X
	(a) For the windshield (Ref. AMM TASK 56-11-11-200-001)
	(b) For the fixed windows (Ref. AMM TASK 56-11-12-200-001)
	(c) For the sliding windows (Ref. AMM TASK 56-12-11-200-001)
	(d) For the attaching fasteners:
	- If you find damage, remove the windshield, the fixed windows or the sliding windows (Ref. AMM TASK 56-11-11-000-001), (Ref. AMM TASK 56-11-12-000-001) or (Ref. AMM TASK 56-12-11-000-001).		X
	- Do the inspection of the window bearing surface (fuselage side) for damage.		X
	(2) Do the operational test of the windshield anti-icing and defogging (Ref. AMM TASK 30-42-00-710-001).	X
	(3) Do the operational test of the standby compass (Ref. AMM TASK 34-22-00-710-001).	X

Subtask 05-51-18-210-129-A

I. Inspection after Damage on the Landing Gear Doors

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	If you find damage during the inspection:
	(1) Refer to the allowable damage and repair in the SRM: - For the MLG door, SRM 52811401 - For the NLG door, SRM 52821101.	X
	(2) If you find a through hole: - Internally examine the adjacent area, the area below the hole and all the related components (pipes, items of equipment, electrical harnesses, etc.) for damage.	X
	(3) If you find damage: - Replace or repair the related component.		X
B.	If you find damage on the electrical bonding leads:
	(1) Replace the electrical bonding lead and/or the defective attachment.	X

Subtask 05-51-18-210-146-A

J. Inspection after Damage on the NLG and/or the MLG

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the NLG and/or the MLG during the inspection:
	(1) Contact Airbus.	X
	(2) Do the inspection of the landing gears:
	(a) For the NLG (Ref. AMM TASK 32-21-00-200-002)	X
	(b) For the MLG (Ref. AMM TASK 32-11-00-200-001).	X
	(3) Do a BITE test of the Landing Gear Control and Interface Unit (LGCIU) (Ref. AMM TASK 32-69-00-740-001).	X
	(4) Do a BITE test of the Braking and Steering Control Unit (BSCU) (Ref. AMM TASK 32-46-00-740-001).	X
B.	If you find damage on the components attached to the landing gears:
	(1) Contact Airbus.	X
	(2) Internally examine the electrical components, ESPM 205212.	X

Subtask 05-51-18-210-130-A

K. Inspection after Damage on the Belly Fairing

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	If you find damage on the belly fairing panel during the inspection:
	(1) Refer to the allowable damage and repair: SRM 53251101 SRM 53351101.	X
	(2) If you find damage on the RAT doors:
	(a) Do an operational test of the manual deployment and the retraction of the RAT (Ref. AMM TASK 29-22-00-710-007) or (Ref. AMM D/O 29-22-00-71).	X
	(b) Do an operational check of the RAT automatic deployment (Ref. AMM TASK 29-22-00-710-006) or (Ref. AMM D/O 29-22-00-71).	X
	(3) If you find a through hole:
	(a) Internally examine the adjacent area, the area below the hole and all the related components (pipes, items of equipment, electrical harnesses, etc.) for damage.	X
	(4) If you find damage:	X
	- Replace or repair the related component.		X

Subtask 05-51-18-210-131-A ** ON A/C NOT FOR ALL

L. Inspection after Damage on the ADIRS Probes and Sensors

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	Pitot probes
	(1) If you find damage during the inspection:
	(a) Replace the related pitot probe (Ref. AMM TASK 34-11-15-000-001) and (Ref. AMM TASK 34-11-15-400-001).	X
	(b) If you find damage on the adjacent area: - Refer to the allowable damage and repair SRM 531111.	X
B.	Static Probes, Stand-by Static Probes and around the Static Ports
	(1) If you find damage during the inspection on or around the static ports: - Refer to allowable damage SRM 531111.	X
	(2) If the damage is more than the SRM allowable damage:
	(a) For the blanking plate of the principle static port: - Do a repair of the blanking plate, SRM 531111.		X
	(b) For the blanking plate of the stand-by static port: - Do a repair of the blanking plate, SRM 531111. NOTE: If the repair is not given in the SRM, it is necessary to contact Airbus.		X
	(3) If you find damage on the adjacent area: - Refer to the allowable repair and damage SRM 532111.	X
C.	Total Air Temperature (TAT) sensors
	(1) If you find damage during the inspection:
	(a) Replace the related TAT sensor (Ref. AMM TASK 34-11-18-000-001) and (Ref. AMM TASK 34-11-18-400-001).	X
	(b) If you find damage on the adjacent area: - Refer to the allowable damage and repair SRM 531111.	X
D.	Angle Of Attack (AOA) Sensors
	(1) If you find damage during the inspection:
	(a) Replace the related AOA sensor (Ref. AMM TASK 34-11-19-000-001) and (Ref. AMM TASK 34-11-19-400-001).	X
	(b) If you find damage on the adjacent area: - Refer to the allowable damage and repair SRM 532111.	X
E.	If you find damage on the AOA sensors, TAT sensors, static probes, stand-by static probes or pitot probes:
	(1) Do an operational test of the probe ice-protection system (Ref. AMM TASK 30-31-00-710-001).	X
	(2) Do an operational test of the AIR DATA switching function (Ref. AMM TASK 34-13-00-710-001).	X

Subtask 05-51-18-210-131-B ** ON A/C NOT FOR ALL

L. Inspection after Damage on the ADIRS Probes and Sensors

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	Pitot probes
	(1) If you find damage during the inspection:
	(a) Replace the related pitot probe (Ref. AMM TASK 34-11-15-000-001) and (Ref. AMM TASK 34-11-15-400-001).	X
	(b) If you find damage on the adjacent area: - Refer to the allowable damage and repair SRM 531111.	X
B.	Static Probes, Stand-by Static Probes and around the Static Ports
	(1) If you find damage during the inspection on or around the static ports: - Refer to allowable damage SRM 531111.	X
	(2) If the damage is more than the SRM allowable damage:
	(a) For the blanking plate of the principle static port: - Do a repair of the blanking plate, SRM 531111. NOTE: If the repair is not given in the SRM, it is necessary to contact Airbus.		X
	(b) For the blanking plate of the stand-by static port: - Replace the blanking plate (Ref. AMM TASK 53-19-42-000-001) and (Ref. AMM TASK 53-19-42-400-001).		X
	(3) If you find damage on the adjacent area: - Refer to the allowable repair and damage SRM 532111.	X
C.	Total Air Temperature (TAT) sensors
	(1) If you find damage during the inspection:
	(a) Replace the related TAT sensor (Ref. AMM TASK 34-11-18-000-001) and (Ref. AMM TASK 34-11-18-400-001).	X
	(b) If you find damage on the adjacent area: - Refer to the allowable damage and repair SRM 531111.	X
D.	Angle Of Attack (AOA) Sensors
	(1) If you find damage during the inspection:
	(a) Replace the related AOA sensor (Ref. AMM TASK 34-11-19-000-001) and (Ref. AMM TASK 34-11-19-400-001).	X
	(b) If you find damage on the adjacent area: - Refer to the allowable damage and repair SRM 532111.	X
E.	If you find damage on the AOA sensors, TAT sensors, static probes, stand-by static probes or pitot probes:
	(1) Do an operational test of the probe ice-protection system (Ref. AMM TASK 30-31-00-710-001).	X
	(2) Do an operational test of the AIR DATA switching function (Ref. AMM TASK 34-13-00-710-001).	X

Subtask 05-51-18-210-147-B ** ON A/C NOT FOR ALL

M. Inspection after Damage on the Ice Detection Probes

ITEM	INSPECTION TASKS	PHASE 2
A.	Ice detection probes
	(1) If you find damage during the inspection:
	(a) Do an operational test of the ice detection system (Ref. AMM TASK 30-81-00-710-001).	X

Subtask 05-51-18-210-132-A

N. Inspection after Damage on the Drain Masts

ITEM	INSPECTION TASKS	PHASE 2
A.	Waste-water drain masts
	(1) If you find damage during the inspection:
	(a) Do an operational test of the drain-mast ice protection (Ref. AMM TASK 30-71-00-710-001).	X
B.	APU drain mast
	(1) If you find damage during the inspection:
	(a) Contact Airbus.	X

Subtask 05-51-18-210-133-C ** ON A/C NOT FOR ALL

O. Inspection after Damage on the Exterior Lights

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
A.		If you find damage on the exterior lights:
		(1) Do the operational test of the related system: (a) For the navigation lights (Ref. AMM TASK 33-41-00-710-001) (b) For the landing lights (Ref. AMM TASK 33-42-00-710-001) (c) For the logo lights (Ref. AMM TASK 33-47-00-710-002) (d) For the anti-collision/strobe lights (Ref. AMM TASK 33-48-00-710-002) (e) For the wing and engine scan lights (Ref. AMM TASK 33-49-00-710-001) (f) For the emergency overwing lights: - Do the test given in the installation of the emergency overwing lights (Ref. AMM TASK 33-51-15-400-001).		X

Subtask 05-51-18-210-133-D ** ON A/C NOT FOR ALL

O. Inspection after Damage on the Exterior Lights

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
A.		If you find damage on the exterior lights:
		(1) Do the operational test of the related system: (a) For the navigation lights (Ref. AMM TASK 33-41-00-710-001) (b) For the landing lights (Ref. AMM TASK 33-42-00-710-001) (c) For the logo lights (Ref. AMM TASK 33-47-00-710-002) (d) For the anti-collision/strobe lights (Ref. AMM TASK 33-48-00-710-002) (e) For the wing and engine scan lights (Ref. AMM TASK 33-49-00-710-001).		X

Subtask 05-51-18-210-134-A ** ON A/C NOT FOR ALL

P. Inspection after Damage on the Communication Antennas

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	VHF antennas
	(1) If you find damage during the inspection:
	(a) Do the operational test of the VHF system (Ref. AMM TASK 23-12-00-710-001).	X
	(b) If the operational test results are satisfactory, replace the VHF antenna before a maximum of 50 flight cycles (Ref. AMM TASK 23-12-11-000-001) or (Ref. AMM TASK 23-12-11-000-002) and (Ref. AMM TASK 23-12-11-400-001) or (Ref. AMM TASK 23-12-11-400-002).	X
	(c) If the operational test is unsatisfactory:
	- Do a BITE test of the VHF system (Ref. AMM TASK 23-12-00-740-001).		X
	- Replace the damaged component(s).		X
B.	HF antenna fairing (if HF antenna is installed)
	(1) If you find damage on the HF antenna fairing:
	- Refer to the allowable damage and repair SRM 55321101.	X
	(2) If you find a through hole on the HF antenna fairing during the inspection:
	(a) Remove the HF antenna fairings (Ref. AMM TASK 55-32-11-000-001) and (Ref. AMM TASK 53-45-11-000-001).		X
	(b) Examine the HF antenna and the feeder for signs of arc attachment.		X
	(c) If you find damage, do an operational test of the HF system (Ref. AMM TASK 23-11-00-710-001).		X
	(d) Install the HF antenna fairings (Ref. AMM TASK 55-32-11-400-001) and (Ref. AMM TASK 53-45-11-400-001).		X
	(e) If the operational test is satisfactory, replace the HF antenna before a maximum of 50 flight cycles (Ref. AMM TASK 23-11-11-000-001) and (Ref. AMM TASK 23-11-11-400-001).		X
C.	SATCOM antenna (if installed)
	(1) If you find damage during the inspection:
	(a) Do a BITE test of the SATCOM system (Ref. AMM TASK 23-28-00-740-002).	X
	(b) If the BITE test is satisfactory, replace the antenna and the related sub-systems before a maximum of 50 flight cycles (Ref. AMM TASK 23-28-13-000-001) (Ref. AMM TASK 23-28-13-000-004) (Ref. AMM TASK 23-28-13-400-002).		X
D.	Gatelink antenna (if installed)
	(1) If you find damage during the inspection:
	(a) Do a self-test of the Electronic Flight Bag (EFB) interface and communication unit (Ref. AMM D/O 46-26-10-70): - Make sure that the cell gatelink indicator is green on the Local Maintenance Function (LMF) main page.	X
	(b) If the self-test is satisfactory, replace the gatelink antenna before a maximum of 50 flight cycles (Ref. AMM TASK 46-26-14-000-801).		X
E.	Emergency Locator Transmitter (ELT) antenna
	(1) If you find burn mark(s) or damage during the inspection:
	- Do an operational test of the ELT (Ref. AMM TASK 25-65-00-710-001).	X
	(a) If the operational test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 25-65-14-000-001) and (Ref. AMM TASK 25-65-14-400-001).		X
	(b) If the operational test is unsatisfactory, do the BITE test of the ELT system (Ref. AMM TASK 25-65-00-740-001) .		X
	- Replace the damaged component(s).		X

Subtask 05-51-18-210-134-B ** ON A/C NOT FOR ALL

P. Check after Damage on the Communication Antennas

NOTE: If there is damage to the aircraft structure, refer to the Structural Repair Manual (SRM). The SRM gives the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	VHF antennas
	(1) If you find damage during the inspection:
	(a) Do the operational test of the VHF system (Ref. AMM TASK 23-12-00-710-001).	X
B.	HF fairing
	(1) If you find damage on the HF fairing:
	- Refer to the allowable damage and repair: SRM 55321101.	X
	(2) If you find a through hole on the HF fairing during the inspection:
	(a) Remove the HF fairing: (Ref. AMM TASK 55-32-11-000-001).		X
	(b) Examine the HF antenna for signs of arc attachment.		X
	(c) Do the operational test of the HF system: (Ref. AMM TASK 23-11-00-710-001).		X

Subtask 05-51-18-210-135-A

Q. Inspection after Damage on the Navigation Antennas

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	Distance Measuring Equipment (DME) antenna
	(1) If you find damage during the inspection:
	- Do an operational test of the DME (Ref. AMM TASK 34-51-00-710-001).	X
	- If the operational test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-51-11-000-002) and (Ref. AMM TASK 34-51-11-400-002).		X
B.	Radio Altimeter (RA) antenna
	(1) If you find damage on the antenna, replace it (Ref. AMM TASK 34-42-11-000-001) and (Ref. AMM TASK 34-42-11-400-001).	X
	(2) If you find damage on the fasteners, do a BITE test of the RA (Ref. AMM TASK 34-42-00-740-002).	X
	- If the BITE test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-42-11-000-001) and (Ref. AMM TASK 34-42-11-400-001).		X
C.	Air Traffic Control (ATC) antenna
	(1) If you find damage during the inspection:
	- Do the BITE test of the ATC (Ref. AMM TASK 34-52-00-740-004).	X
	- If the BITE test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-52-11-000-001) and (Ref. AMM TASK 34-52-11-400-001).		X
D.	VOR antenna
	(1) If you find damage on the fin tip cap (VOR fairing):
	- Refer to the allowable damage and repair SRM 55321101. If you find a through hole on the fin tip cap:	X
	- Remove the fin tip cap (Ref. AMM TASK 55-34-11-000-001).		X
	- Examine the VOR antenna for signs of the arc attachment. If you find damage on the VOR antenna:		X
	- Do an operational test of the VOR/Marker (radio) Beacon (MKR) system (Ref. AMM TASK 34-55-00-710-001).		X
	- If the operational test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-55-11-000-001) and (Ref. AMM TASK 34-55-11-400-001).		X
E.	MKR antenna
	(1) If you find damage on the MKR antenna:
	- Do an operational test of the the VOR/MKR system (Ref. AMM TASK 34-55-00-710-001).	X
	- If the operational test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-55-18-000-001) and (Ref. AMM TASK 34-55-18-400-001).		X
F.	Traffic Alert and Collision Avoidance System (TCAS) antenna
	(1) If you find damage during the inspection:
	- Do the BITE test of the TCAS (if TCAS system is installed) (Ref. AMM TASK 34-43-00-740-001) or Do the BITE test of the Traffic and Terrain Collision Avoidance System (T2CAS) (if T2CAS system is installed) (Ref. AMM D/O 34-43-00-74) or Do the BITE test of the Traffic and Terrain Integrated Surveillance System (T/TISS) (if T/TISS system is installed) (Ref. AMM TASK 34-72-00-740-001).	X
	- If the BITE test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-43-11-000-004) and (Ref. AMM TASK 34-43-11-400-004).		X
G.	Automatic Direction Finder (ADF) antenna (if installed)
	(1) If you find damage during the inspection:
	- Do an operational test of the ADF (Ref. AMM TASK 34-53-00-710-002).	X
	- If the operational test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-53-11-000-001) and (Ref. AMM TASK 34-53-11-400-001).		X
H.	GPS antenna (if installed)
	(1) If you find damage during the inspection:
	- Do an operational test of the GPS (Ref. AMM TASK 34-36-00-710-002) (Ref. AMM D/O 34-36-00-71) (Ref. AMM TASK 34-36-00-710-008) (Ref. AMM D/O 34-36-00-71).	X
	- If the operational test is satisfactory, replace the antenna before a maximum of 50 flight cycles (Ref. AMM TASK 34-36-16-000-001) and (Ref. AMM TASK 34-36-16-400-001).		X

Subtask 05-51-18-210-136-A

R. Inspection after Damage on the Fuselage Skin

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	If you find damage during the inspection:
	(1) Refer to the flow chart for the allowable damage and repair in SRM 511113 and SRM 530000.	X
	(2) If you find a through hole:
	(a) Examine internally the adjacent area of the damage, specially the components, the pipes and the electrical looms for damage.	X
	(b) If you find damage: - Repair or replace the related component.		X

Subtask 05-51-18-210-137-A

S. Inspection of the APU after Damage on the APU Exhaust

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	If you find damage on the APU exhaust during the inspection:
	(1) Open APU access doors 315AL and 316AR and safety them in the open position (Ref. AMM TASK 52-41-00-010-001).	X
	(2) Do a GVI of the interface between the APU and the APU exhaust for: - Burn marks and change of color.	X
	(3) Do a GVI of the interface of the APU suspension system with the APU and with the APU fire-compartment ceiling for: - Burn marks and change of color.	X
	(4) Close APU access doors 315AL and 316AR (Ref. AMM TASK 52-41-00-410-001).	X
	(5) Do an operational test of the APU fire and overheat detection-system (Ref. AMM TASK 26-13-00-710-001).	X
	(6) Refer to the installed APU and do the APU operational test: (a) For APU GTCP 36-300 (Ref. AMM D/O 49-00-00-71). (b) For APU 131-9 (A) (Ref. AMM TASK 49-00-00-710-010). (c) For APU APS 3200 (Ref. AMM TASK 49-00-00-710-008).	X
	(7) If you find damage when you do the above steps: - Contact Airbus.		X

Subtask 05-51-18-210-149-A ** ON A/C NOT FOR ALL

T. Inspection after Damage on the Wings

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	If you find damage on the top or bottom of the wings:
	(1) Refer to the allowable damage and repair in the SRM: - For the outer wing skin, SRM 57211101 - For the wing tip, SRM 57312101 - For the wing tip fence, SRM 57312201.	X
B.	If you find damage on the slats:
	(1) Refer to the allowable damage and repair SRM 57400001.	X
	(2) Do the operational test of the slats (Ref. AMM TASK 27-84-00-710-001).	X
C.	If you find damage on the flap track fairings:
	(1) Refer to the allowable damage and repair SRM 57551101.	X
D.	If you find damage on the flaps:
	(1) Refer to the allowable damage and repair:	X
	- For the inboard flap, SRM 57520001 - For the outboard flap, SRM 57530001.
	(2) Examine the bonding leads (on the hinges) of the related damaged flap for breakage and defective attachment.	X
	(a) If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Do the operational test of the flaps (Ref. AMM TASK 27-54-00-710-001).	X
E.	If you find damage on the spoilers:
	(1) Refer to the allowable damage and repair SRM 57700001.	X
	(2) Examine the bonding leads (on the hinges) of the related damaged spoiler for breakage and defective attachment.	X
	(a) If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Do an operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001).	X
F.	If you find damage on the ailerons:
	(1) Refer to the allowable damage and repair SRM 57612101.	X
	(2) Examine all the bonding leads of the aileron hinges and servo controls of the related damaged aileron for breakage and defective attachment.	X
	(a) If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Examine the piston rod:
	- Examine the piston rod of each aileron servo control (it must fully extend) of the damaged aileron for burn marks, damage and leaks, or	X
	- If you are at a line station and you cannot do the inspection of the rods, do this check: 1_ Fully operate the ailerons 10 times in each direction. 2_ From the ground, make sure that there are no leaks below the aileron servo controls. 3_ You must do this check before each flight until the aircraft return to the main base. 4_ You can do this check before each flight for a maximum of 3 days or 10 flights. 5_ When the aircraft returns to the main base, you must do the inspection of the piston rods.	X
	If you find a leak or damage:
	(a) Replace the related aileron servo control (Ref. AMM TASK 27-14-51-000-001) and (Ref. AMM TASK 27-14-51-400-001).		X
	(4) Do an operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001).	X

Subtask 05-51-18-210-149-B ** ON A/C NOT FOR ALL

T. Inspection after Damage on the Wings

NOTE: If you find damage to the aircraft structure, refer to the SRM. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	If you find damage on the top or bottom of the wings:
	(1) Refer to the allowable damage and repair in the SRM - For the outer wing skin, SRM 57211101.	X
B.	If you find damage on the sharklet:
	(1) Refer to the allowable damage SRM 573123.	X
	(2) If the damage is more than the SRM allowable damage:
	- Replace the sharklet (Ref. AMM TASK 57-31-23-000-801) and (Ref. AMM TASK 57-31-23-400-801).		X
C.	If you find damage on the slats:
	(1) Refer to the allowable damage and repair SRM 57400001.	X
	(2) Do the operational test of the slats (Ref. AMM TASK 27-84-00-710-001).	X
D.	If you find damage on the flap track fairings:
	(1) Refer to the allowable damage and repair SRM 57551101.	X
E.	If you find damage on the flaps:
	(1) Refer to the allowable damage and repair:	X
	- For the inboard flap, SRM 57520001 - For the outboard flap, SRM 57530001.
	(2) Examine the bonding leads (on the hinges) of the related damaged flap for breakage and defective attachment.	X
	(a) If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Do the operational test of the flaps (Ref. AMM TASK 27-54-00-710-001).	X
F.	If you find damage on the spoilers:
	(1) Refer to the allowable damage and repair SRM 57700001.	X
	(2) Examine the bonding leads (on the hinges) of the related damaged spoiler for breakage and defective attachment.	X
	(a) If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Do an operational test of the spoilers (Ref. AMM TASK 27-64-00-710-001).	X
G.	If you find damage on the ailerons:
	(1) Refer to the allowable damage and repair SRM 57612101.	X
	(2) Examine all the bonding leads of the aileron hinges and servo controls of the related damaged aileron for breakage and defective attachment.	X
	(a) If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Examine piston rod:
	- Examine the piston rod of each aileron servo control (it must fully extend) of the damaged aileron for burn marks, damage and leaks, or	X
	- If you are at a line station and you cannot do the inspection of the rods, do this check: 1_ Fully operate the ailerons 10 times in each direction. 2_ From the ground, make sure that there are no leaks below the aileron servo controls. 3_ You must do this check before each flight until the aircraft return to the main base. 4_ You can do this check before each flight for a maximum of 3 days or 10 flights. 5_ When the aircraft returns to the main base, you must do the inspection of the piston rods.	X
	If you find a leak or damage:
	(a) Replace the related aileron servo control (Ref. AMM TASK 27-14-51-000-001) and (Ref. AMM TASK 27-14-51-400-001).		X
	(4) Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001).	X

Subtask 05-51-18-210-139-A ** ON A/C NOT FOR ALL

U. Inspection after Damage on the Engine Nacelles and Pylons

NOTE: If you find damage to the aircraft structure, refer to the SRM and/or to the applicable Nacelle Structural Repair Manual. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the air intake, inlet cowl, fan cowl, thrust reverser, exhaust nozzle or the pylon:
	(1) Refer to the allowable damage and repair in the SRM table of contents, chap 54.	X
	(2) When the aircraft returns to the main base, do the inspection of the lightning protection module (Ref. AMM TASK 24-22-51-200-001).	X
	(3) If you find damage on the thrust reverser:
	(a) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-805).	X
	(4) If you find a through hole on the fan cowl:
	(a) Do the operational test of the Electronic Engine Control (EEC): (Ref. AMM TASK 73-21-00-710-806).	X
	(b) Do the Full Authority Digital Engine Control (FADEC) ground test No.6 (Ref. AMM TASK 73-21-00-710-807).	X
	(5) On the thrust-reverser inner fixed-structure, if you find a weld spot or damage caused by lightning on the pressure relief door, open the door with a screwdriver to break the weld and then close the door.	X

Subtask 05-51-18-210-139-C ** ON A/C NOT FOR ALL

U. Inspection after Damage on the Engine Nacelles and Pylons

NOTE: If you find damage to the aircraft structure, refer to the SRM and/or to the applicable Nacelle Structural Repair Manual. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the air intake, inlet cowl, fan cowl, thrust reverser, exhaust nozzle or the pylon:
	(1) Refer to the allowable damage and repair in the SRM table of contents, chap 54.	X
	(2) When the aircraft returns to the main base, do the inspection of the lightning protection module (Ref. AMM TASK 24-22-51-200-001).	X
	(3) If you find damage on the thrust reverser:
	(a) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-040).	X
	(4) If you find a through hole on the fan cowl:
	(a) Do a ground test of the Full Authority Digital Engine Control (FADEC) (Ref. AMM TASK 73-29-00-710-040).	X
	(b) Do a ground test of the Electronic Control Unit (ECU) (Ref. AMM TASK 73-21-60-720-040).	X

Subtask 05-51-18-210-139-E ** ON A/C NOT FOR ALL

U. Inspection after Damage on the Engine Nacelles and Pylons

NOTE: If you find damage to the aircraft structure, refer to the SRM and/or to the applicable Nacelle Structural Repair Manual. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the air intake, inlet cowl, fan cowl, thrust reverser, exhaust nozzle or the pylon:
	(1) Refer to the allowable damage and repair in the SRM table of contents, chap 54.	X
	(2) When the aircraft returns to the main base, do the inspection of the lightning protection module (Ref. AMM TASK 24-22-51-200-001).	X
	(3) If you find damage on the thrust reverser:
	(a) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-042).	X
	(4) If you find a through hole on the fan cowl:
	(a) Do a ground test of the Full Authority Digital Engine Control (FADEC) (Ref. AMM TASK 73-29-00-710-040).	X
	(b) Do a ground test of the Electronic Control Unit (ECU) (Ref. AMM TASK 73-21-60-720-040).	X

Subtask 05-51-18-210-139-F ** ON A/C NOT FOR ALL

U. Inspection after Damage on the Engine Nacelles and Pylons

NOTE: If you find damage to the aircraft structure, refer to the SRM and/or to the applicable Nacelle Structural Repair Manual. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the air intake, inlet cowl, fan cowl, thrust reverser, exhaust nozzle or the pylon:
	(1) Refer to the allowable damage and repair in the SRM table of contents, chap 54.	X
	(2) When the aircraft returns to the main base, do the inspection of the lightning protection module (Ref. AMM TASK 24-22-51-200-001).	X
	(3) If you find damage on the thrust reverser:
	(a) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-041).	X
	(4) If you find a through hole on the fan cowl:
	(a) Do a ground test of the Full Authority Digital Engine Control (FADEC) (Ref. AMM TASK 73-22-00-710-040).	X
	(b) Do a ground test of the Electronic Engine Control (EEC) (Ref. AMM TASK 73-22-34-710-040).	X

Subtask 05-51-18-210-140-B

V. Inspection after Damage on the Stabilizers

NOTE: If you find damage to the aircraft structure, refer to the SRM and/or to the applicable Nacelle Structural Repair Manual. The SRM will give you the approved damage limits and repair procedures.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
A.	During the inspection, if you find damage on the skin of the vertical stabilizer and the rudder, the fin tip cap, the fin and rudder tip cap lightning conductor:
	(1) Refer to the allowable damage and repair: - For the vertical stabilizer, SRM 55300001 - For the rudder, SRM 55410001.	X
	(2) Remove trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-010-002).	X
	(3) Examine all the electrical bonding leads of the rudder hinges and servo controls for breakage and defective attachment.	X
	If you find damage:
	(a) Replace the electrical bonding lead and/or the defective attachment.		X
	(4) When the aircraft returns to the main base, examine the piston rod of each rudder servo control (it must fully extend) for damage and burn marks and make sure that there are no leaks. If you find a leak or damage:	X
	- Replace the related rudder servo control (Ref. AMM TASK 27-24-51-000-001) and (Ref. AMM TASK 27-24-51-400-001).		X
	(5) Install trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-410-002).	X
	(6) Do an operational test of the rudder (Ref. AMM TASK 27-24-00-710-001).	X
B.	During inspection, if you find damage on the horizontal stabilizer and elevators:
	(1) Refer to the allowable damage and repair in the SRM. Refer to Fig. 55-10-00 Pb 001 and 55-20-00 Pb 001 to find the correct chapter location.	X
	(2) Remove trailing-edge access panels of the Trimmable Horizontal Stabilizer (THS) (Ref. AMM TASK 55-13-11-000-001).	X
	(3) Examine all the electrical bonding leads of the elevator hinges and servo controls of the related damaged elevator for breakage and defective attachment.	X
	If you find damage:
	(a) Replace the electrical bonding lead and/or the defective attachment.		X
	(4) Examine the piston rod:
	- Examine the piston rod of each elevator servo control (it must fully extend) of the related damaged elevator for burn marks, damage and leaks, or	X
	- If you are at the line station and you cannot do the inspection of the rods, do this check: 1_ Fully operate the elevators 10 times in each direction. 2_ From the ground, make sure that there are no leaks below the elevator servo controls. - You must do this check before each flight until the aircraft returns to the main base. 4_ You can do this check before each flight for a maximum of 3 days or 10 flights. 5_ When the aircraft returns to the main base, you must do the inspection of the rods.	X
	If you find a leak or damage:
	(a) Replace the applicable elevator servo control (Ref. AMM TASK 27-34-51-000-001) and (Ref. AMM TASK 27-34-51-400-001).		X
	(5) Install trailing-edge access panels of the THS (Ref. AMM TASK 55-13-11-400-001).	X
	(6) Do an operational test of the elevators (Ref. AMM TASK 27-34-00-710-001).	X
	(7) Do an operational test of the THS (Ref. AMM TASK 27-44-00-710-001).	X

Subtask 05-51-18-210-141-A

W. Inspection after Damage on the Static Dischargers

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the static dischargers of the wing or the vertical and horizontal stabilizer:
	(1) Do a check of the related static discharger (Ref. AMM TASK 23-61-00-200-001).	X
	(2) Refer to the MCDL to get the maximum permitted damage or the missing static discharger number.	X

Subtask 05-51-18-210-142-A

X. Inspection after Damage on the RAT (if deployed during flight)

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Do a detailed inspection of the RAT (Ref. AMM TASK 29-22-51-200-003) and (Ref. AMM D/O 29-22-51-21).		X
2.		Do an operational test of the RAT module automatic-deployment (Ref. AMM TASK 29-22-00-710-001).		X

Subtask 05-51-18-210-143-A

Y. Phase 2 Inspection of the Fuselage (Zone 5) (if there is Damage on Zone 1 or 2)

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
1.	Inspection of the fuselage skin
	Visually examine the fuselage skin for: Burn marks, change of color and disruption of the surface.	X
	If you find damage: Do the inspection after damage on the fuselage skin.		X
2.	Visually examine the windows and the window frames for: Burn marks, change of color and disruption of the surface.	X
	If you find damage: Do the inspection after damage on the windshield, fixed Windows, sliding windows, window frames and attaching fasteners.		X
3.	Inspection of all the external lights
	Examine all the external lights and the adjacent area for burn marks or other damage	X
	If you find damage: Do the inspection after damage on the exterior lights.		X
4.	Inspection of the outflow valves
	Examine the outflow valves for burn marks.	X
	If you find damage: Do the operational test of the pressure control and monitoring (Ref. AMM TASK 21-31-00-710-002) and Do the operational test of manual mode selection and manual mode pressure-control and functional test of manual-mode cabin altitude/outflow-valve position indication (Ref. AMM TASK 21-31-00-710-003).		X

5. Close-up
Subtask 05-51-18-410-052-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close all the access panels or the access doors that you opened during the inspections.
(3) Close the NLG doors (Ref. AMM TASK 32-22-00-410-001).
(4) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).
(5) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(6) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(7) Fully retract the slats (Ref. AMM TASK 27-80-00-866-005).
(8) Fully retract the spoilers (Ref. AMM TASK 27-60-00-866-002).
(9) Remove the access platform(s).
(10) Remove the WARNING NOTICE(S).
(11) Remove the SAFETY BARRIERS.

[Rev.10 from 2021] 2026.03.31 22:51:33 UTC