Inspection after a Lightning Strike

TASK 05-51-18-200-001-A
Inspection after a Lightning Strike

WARNING: YOU MUST PUT ON AND ATTACH A SAFETY HARNESS BEFORE YOU START WORK:

ON THE THS OR IN THE REAR FUSELAGE
ON TOP OF THE WINGS OR PYLONS.

WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND THE RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

1. Reason for the Job

NOTE: This is an alternative method for the inspection after a lightning strike. For the other method, refer to the relevant task in this page block.

After a lightning strike, before the aircraft continues in service, you must:

Do a general inspection of the total surface of the aircraft to find the strike areas
Carefully examine the strike areas to find the type and quantity of possible damage
If you find damage, make a decision about the necessary repair/action.
The parts that follow are necessary for the General Visual Inspection (GVI):
An adjustable access platform 2 m (6.56 ft.) to 12 m (39.4 ft.) or
A manlift aerial boom (2 m (6.56 ft.) to 11 m (36.1 ft.)).

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	AR	CHOCK - WHEEL(S)
No specific	AR	SAFETY BARRIER(S)
No specific	AR	WARNING NOTICE(S)

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 20-28-00-869-002-A	Table of the Maximum Permitted Resistance-Values
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 23-28-13-000-802-A	Removal of the Low Earth Orbit (LEO) Passive Antenna
TASK 23-28-13-400-802-A	Installation of the Low Earth Orbit (LEO) Passive Antenna
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 32-11-00-200-001-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 34-36-18-000-001-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 34-41-11-000-802-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 34-41-11-400-802-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 34-51-00-710-001-A	Operational Test of the DME
TASK 34-52-00-740-004-A	BITE Test of the Air Traffic Control (ATC)
TASK 34-53-00-710-002-A	Operational Test of the ADF
TASK 34-55-00-710-001-A	Operational Test of the VOR/MKR
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 55-32-11-000-001-A	Removal of the Vertical Stabilizer Leading-Edge
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)
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 551000	(for corrective action)
SRM 552000	(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)
Lightning Strike Inspection Areas
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 05-51-18-941-052-A

DELETED

Subtask 05-51-18-210-077-A

B. General
(1) Lightning
(a) Lightning always has two or more attachment points (one entry and one or more exits) on the aircraft skin.
(b) Lightning moves along the surface of the aircraft (swept stroke zone) between the entry and exit points. This can cause a chain of scattered attachment points along a line in the direction of travel of the aircraft.
(c) Lightning hits some areas more frequently than others.
(2) Aircraft zoning

Lightning Strike Inspection Areas

(a) The aircraft is divided into three zones related to the risk of a lightning strike:
1 Zone 1:

The surfaces with a high risk of initial lightning attachment (entry or exits).

2 Zone 2:

The surfaces with a high risk of a "swept stroke zone". The lightning strike has its initial point of attachment in zone 1 and moves into zone 2.

3 Zone 3:

This zone includes all of the aircraft surfaces that are not in zone 1 and zone 2. In zone 3, there is a low risk of attachment of a lightning strike. High lightning currents can go through zone 3 because of direct conduction between two attachment points. Zone 3 currents will also go into zones 1 and 2.

(b) Zones 1 and 2 are divided into A and B areas related to the risk of continued attachment of the arc (hang-on).
The risk of arc hang-on is low in A areas and high in B areas.
1 Zone 1A:
The area with a high risk of initial attachment and a low risk of arc hang-on, which includes:

The forward-mounted pitot probes
The radome lightning-arrester strips
The nacelle leading edges.

2 Zone 1B:
The area with a high risk of initial attachment and a high risk of arc hang-on, which includes:

The wing
The horizontal stabilizer
The vertical stabilizer and rudder tips
Some trailing edge areas.

3 Zone 2A:
A swept stroke zone with a low risk of arc hang-on, which includes:

The mid-chord regions of the wing surface
The aft of an engine
The total fuselage surface.

4 Zone 2B:
A swept stroke zone with a high risk of an arc hang-on, which includes the wing trailing edge aft of zone 2A.
(3) Effects on the aircraft structure and systems.
There are two types of possible risks to the aircraft:

Indirect effects
Direct effects.

(a) Indirect effects.
1 Electromagnetic fields:

The electromagnetic fields related to the lightning attachment can cause unwanted transient voltages and currents in the aircraft wiring and systems.
In some conditions (low intensity strike, high protection), the effect on the systems can be temporary and the systems can operate correctly again after the strike.
In other conditions (low protection, no circuit protection devices), the damage can be permanent and it will be necessary to replace parts.

(b) Direct effects
The direct effects are physical damage related to signs such as:
1 Pitting/melt-through:

This is the result of the electrical arc that occurs when a lightning strike attaches to the aircraft (arc root damage at the attachment points or damage because of current flow which can also occur far from the attachment points).
Signs of a lightning attachment are pitting, scorch marks and paint discoloration.
On composite components, not only paint discoloration and skin puncturing but also delamination of the fibers can occur. If there is skin puncturing, there can be damage to the grounded equipment below the composite material fairings.
Always compare the damage that you find with the limits given in the Structural Repair Manual (SRM).

2 Magnetic force:

The damage usually occurs in a small area with high density of the current (e.g. a bonding lead installed on a control surface hinge).

3 Resistive heating:

When the lightning currents flow through an aircraft structure, energy changes to heat along its path.
Resistive heating usually causes weld marks, specially where the lightning current flows for some time.

4 Acoustic shock wave:

When a lightning strike occurs, there is an acoustic shock wave. If the intensity of this shock wave is high, it can cause deformation of thin metal skins or rupture of thin composite skins.

(4) 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 attachment.
(b) It is not possible to accurately know where the attachment will occur. Zone 1 and zone 2 are the areas with the highest risk of a lightning attachment.
(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.

Subtask 05-51-18-210-078-A

C. Inspection Preparation
(1) Before you start the inspection, we recommend that you get information from the crew about the flight condition.
(2) Make sure that you have the related aircraft Post Flight Report (PFR).
(3) You must do a check of all the events reported by the crew or by the PFR in addition/conjunction with this inspection.
(4) 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.
(5) Refer to the General Reporting and Logic Chart to make a decision after you find damage, SRM 511113.

Subtask 05-51-18-481-050-A

D. 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 05-51-18-866-050-A

E. 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 05-51-18-010-050-A

F. Get Access
(1) Open the main gear doors and install the safety devices (Ref. AMM TASK 32-12-00-010-001).
(2) Open the nose gear doors and install the safety devices (Ref. AMM TASK 32-22-00-010-001).

Subtask 05-51-18-860-050-A

G. Aircraft Maintenance Configuration
(1) Make sure that the electrical circuits are de-energized (Ref. AMM TASK 24-41-00-862-002).
(2) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001).
(3) Put WARNING NOTICE(S) in the cockpit to tell persons not to operate the systems.
(4) Put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE in position.

4. Procedure
Subtask 05-51-18-210-089-A

A. Inspection of the Total Surface of the Aircraft

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

NOTE: All the necessary inspections are visual unless the text gives other instructions.

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the Radome
A.	Visually examine the radome external skin and the lightning arrester strips for burn marks, change of color, puncturing or other damage.	X
2.	Inspection of the Windshield, Fixed windows, Sliding Windows, Window Frames and Attaching Fasteners
A.	Visually examine the parts that follow for burn marks, change of color or other damage: - The windshield - The fixed windows - The sliding windows - The window frames - The attaching fasteners.	X
3.	Inspection of the NLG and the MLG doors
A.	Examine the skin of the NLG and MLG doors for burn marks, changes of color, puncturing and delamination.	X
B.	Examine the electrical bonding leads for breakage or defective attachment.	X
4.	Inspection of the NLG and the MLG NOTE: These checks are applicable if the lightning strike occurred: - With the Landing Gear (L/G) extended and locked down - During the extension of the L/G. They are also applicable if you find a through hole during the inspection of the landing gear doors.
A.	Examine the NLG and the MLG: (1) Examine the L/G structure and its attachment points for change of color, burn marks or other damage. (2) Examine the shock absorber for change of color or burn marks. (3) Examine all the components attached to the landing gear. Also fully examine the electrical looms and components for change of color or burn marks.	X
5.	Inspection of the Belly Fairing
A.	Examine the belly fairing panels (these include the wing-to-fuselage fairings) for change of color, burn marks, puncturing or delamination.	X
	Examine the fairing screws and fasteners for burn marks.	X
6.	Inspection of the Fuselage
A.	Externally examine all of the fuselage skin with the rivets and the screws for change of color, burn marks or small holes.	X
B.	Examine all the probes, sensors and drain masts and the adjacent area for burn marks or change of color.	X
C.	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
D.	Examine all the external lights and the adjacent area for burn marks or other damage.	X
E.	Examine the APU exhaust for burn marks or change of color.	X
F.	If Ram Air Turbine (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
7.	Inspection of the Wings
A.	Examine the top and bottom skin of the wings and the leading and trailing edges for burn marks or change of color.	X
B.	Examine the slats for burn marks or damage.	X
C.	Examine the flap track fairings for burn marks, change of color, puncturing or other damage.	X
D.	Examine the flaps for burn marks, change of color, puncturing or delamination.	X
E.	Examine the spoilers for burn marks, change of color, puncturing or delamination.	X
F.	Examine the ailerons for burn marks, change of color, puncturing or delamination.	X
G.	Examine all the static dischargers for burn marks, damaged tip or breakage.	X
H.	Examine the wing tip for burn marks or burn holes.	X
I.	Examine the lights on the wing tip for burn marks or other damage.	X
8.	Inspection of the Engine Nacelles and Pylons
A.	Examine each air intake, inlet cowl, fan cowl, thrust reverser, exhaust nozzle and pylon for burn marks, change of color, puncturing or delamination.	X
9.	Inspection of the Horizontal Stabilizer
A.	Examine all the static dischargers for burn marks, damaged tip or breakage.	X
B.	Examine the skin of the horizontal stabilizer and the elevators (specially the leading and trailing edges, the elevator surface in the hinge area and the tip) for burn marks, change of color, puncturing, delamination or other damage.	X

Subtask 05-51-18-210-116-B

B. Inspection of the Vertical Stabilizer

ITEM	INSPECTION TASKS	PHASE 1
1.	Inspection of the Vertical Stabilizer (GVI)
A.	Examine all the static dischargers for burn marks, damaged tip or breakage.	X
B.	Examine the parts that follow for burn marks, change of color, puncturing, delamination or other damage: - The skin of the vertical stabilizer and the rudder (specially the leading and trailing edges, the rudder surface in the hinge area and the antenna fairings) - The vertical stabilizer tip - The lightning conductor of the vertical stabilizer and rudder tips.	X

Subtask 05-51-18-710-050-A

C. Operational Test of the HF system (If Installed)

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

Subtask 05-51-18-760-051-A

D. 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 05-51-18-210-101-A

E. Check 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 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) (Ref. AMM TASK 34-41-11-000-011) (Ref. AMM TASK 34-41-11-000-802) (Ref. AMM TASK 34-41-11-400-005) (Ref. AMM TASK 34-41-11-400-014) (Ref. AMM TASK 34-41-11-400-013).		X
	- Do the BITE test of the weather radar (Ref. AMM TASK 34-41-00-740-002)		X
	- Do the system test of the weather radar (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) (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) (Ref. AMM TASK 34-36-18-400-001).		X

Subtask 05-51-18-210-052-A

F. Check 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) (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 05-51-18-210-055-A

G. Check after Damage on the Landing Gear Doors

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.	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
	(a) 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 05-51-18-210-053-A

H. Check after Damage on the Nose and/or the Main Landing Gear

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the nose and/or the main landing gear during the inspection:
	(1) Contact Airbus.	X
	(2) Do the inspection of the L/G:
	(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 gear:
	(1) Contact Airbus.	X
	(2) Examine the electrical components internally.	X

Subtask 05-51-18-210-054-A

I. Check after Damage on the Belly Fairing

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.	If you find damage during the inspection of a belly fairing panel:
	(1) Refer to the allowable damage and repair: SRM 53251101 SRM 53351101.	X
	(2) If there is a damage on the Ram Air Turbine (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) Get access internally and examine the adjacent area and the area below to do a check of all the components (pipes, items of equipment, electrical harnesses...) for damage. If you find damage:	X
	- Replace or repair the related component.		X

Subtask 05-51-18-210-079-A ** ON A/C NOT FOR ALL

J. Check after Damage on the ADIRS Probes and Sensors

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.	Pitot probes
	(1) If you find damage during the inspection:
	(a) Replace the pitot probe(s) (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 the SRM 531111 allowable damage.	X
	(2) If the damage is more than the SRM allowable damage:	X
	(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 TAT sensor(s) (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, TAT, static, stand-by static or pitot probes:
	(1) Do the 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 05-51-18-210-079-B ** ON A/C NOT FOR ALL

J. Check after Damage on the ADIRS Probes and Sensors

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.	Pitot probes
	(1) If you find damage during the inspection:
	(a) Replace the pitot probe(s) (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 the SRM 531111 allowable damage.	X
	(2) If the damage is more than the SRM allowable damage:	X
	(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 TAT sensor(s) (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, TAT, static, stand-by static or pitot probes:
	(1) Do the 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 05-51-18-210-080-A ** ON A/C NOT FOR ALL

K. Not Applicable

Subtask 05-51-18-210-080-B ** ON A/C NOT FOR ALL

K. Check after Damage on the Ice Detection Probes

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

Subtask 05-51-18-210-081-A

L. Check after Damage on the Drain Masts

ITEM	INSPECTION TASKS	PHASE 2
A.	Water-waste drain masts
	(1) If you find damage during the inspection:
	(a) Do the 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
C.	Drain mast of the center-tank external ventilating-system
	(1) If you find damage during the inspection:
	(a) Contact Airbus.	X

Subtask 05-51-18-210-082-C ** ON A/C NOT FOR ALL

M. Check after Damage on the Exterior Lights

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the exterior lights:
	(1) Do the operational test of the related system:	X
	(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).

Subtask 05-51-18-210-082-D ** ON A/C NOT FOR ALL

M. Check after Damage on the Exterior Lights

ITEM	INSPECTION TASKS	PHASE 2
A.	If you find damage on the exterior lights:
	(1) Do the operational test of the related system:	X
	(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).

Subtask 05-51-18-210-098-A ** ON A/C NOT FOR ALL

N. 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 burn mark(s), do the operational test of the VHF system (Ref. AMM TASK 23-12-00-710-001):	X
	(a) If the operational test results are correct, replace the 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
	(b) If the operational test results are not correct,
	- Do the 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 the 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 fairing (Ref. AMM TASK 55-32-11-000-001).		X
	(b) Examine the HF antenna and the feeder for signs of arc attachment.		X
	(c) If you find damage, do the operational test of the HF system (Ref. AMM TASK 23-11-00-710-001).		X
	(d) If the operational test results are correct, replace the 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 the BITE test of the SATCOM system (Ref. AMM D/O 23-28-00-74) (Ref. AMM TASK 23-28-00-740-001).	X
	(b) Disconnect the coaxial plug connector from the antenna.	X
	(c) Do a check of the antenna bonding (Ref. AMM TASK 20-28-00-869-002).	X
	(d) If the BITE test results are correct, 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) and (Ref. AMM TASK 23-28-13-400-001) (Ref. AMM TASK 23-28-13-400-004).		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 results are correct, 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 the operational test of the ELT (Ref. AMM TASK 25-65-00-710-001).	X
	(a) If the operational test results are correct, 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 results are not correct, do the BITE test of the ELT system (Ref. AMM TASK 25-65-00-740-001) .		X
	- Replace the damaged component(s).		X

Subtask 05-51-18-210-098-B ** ON A/C NOT FOR ALL

N. 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 05-51-18-210-095-A

O. Check after Damage on the Navigation 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.	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.		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.		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.		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.		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.		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.		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.		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.		X

Subtask 05-51-18-210-086-A

P. Check after Damage on the Fuselage Skin

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.	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:	X
	(a) Examine internally the adjacent area of the damage, specially the components, the pipes and the electrical looms for damage. If you find damage:
	- Repair or replace the related component.		X

Subtask 05-51-18-210-150-A

Q. Check 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 05-51-18-210-093-A

R. Check 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:	X
	(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).
	(7) If you find damage when you do the above steps: - Contact Airbus.		X

Subtask 05-51-18-210-088-A ** ON A/C NOT FOR ALL

S. Check after Damage on the Wings

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.	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. If you find damage:	X
	- 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
	If you find damage: - Replace the bonding lead and/or the defective attachment.		X
	(3) Do the 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. If you find damage:	X
	- Replace the bonding lead and/or the defective attachment.		X
	(3) Examine the piston rod:
	(a) Examine the piston rod of each aileron servo control (it must be fully extended) of the damaged aileron for burn marks, damage and leaks.	X
	Or
	(b) If you are at the line station and you cannot do the inspection of the rods, do this check: - Operate the ailerons 10 times fully in each direction. - Make sure from the ground that there are no leaks below the aileron servo controls. - You must do this check before each flight until the return to the main base. You can do the check before each flight for a maximum of 3 days or 10 flights. - At the first return to the main base, you must do the inspection of the rods.	X
	(4) If you find leak or damage: - Replace the applicable aileron servo control (Ref. AMM TASK 27-14-51-000-001) (Ref. AMM TASK 27-14-51-400-001).		X
	(5) Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001).	X

Subtask 05-51-18-210-088-B ** ON A/C NOT FOR ALL

S. Check after Damage on the Wings

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.	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 SRM 573123 allowable damage.	X
	If the damage is more than the SRM allowable damage:
	- Replace the sharklet (Ref. AMM TASK 57-31-23-000-801) (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. If you find damage:	X
	- 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. If you find damage:	X
	- Replace the bonding lead and/or the defective attachment.		X
	(3) Do the 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. If you find damage:	X
	- Replace the bonding lead and/or the defective attachment.		X
	(3) Examine piston rod:
	(a) Examine the piston rod of each aileron servo control (it must be fully extended) of the damaged aileron for burn marks, damage and leaks.	X
	Or
	(b) If you are at the line station and you cannot do the inspection of the rods, do this check: - Operate the ailerons 10 times fully in each direction. - Make sure from the ground that there are no leaks below the aileron servo controls. - You must do this check before each flight until the return to the main base. You can do the check before each flight for a maximum of 3 days or 10 flights. - At the first return to the main base, you must do the inspection of the rods.	X
	(4) If you find leak or damage: - Replace the applicable aileron servo control (Ref. AMM TASK 27-14-51-000-001) (Ref. AMM TASK 27-14-51-400-001).		X
	(5) Do the operational test of the ailerons (Ref. AMM TASK 27-14-00-710-001).	X

Subtask 05-51-18-210-056-A ** ON A/C NOT FOR ALL

T. Check after Damage on the Engine Nacelles and Pylons

NOTE: If there is damage to the aircraft structure, refer to the Structural Repair Manual (SRM) and/or to the applicable Nacelle Structural Repair Manual. The SRM gives 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) At the first return 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 FADEC (Ref. AMM TASK 73-29-00-710-040).	X
	(b) Do a ground test of the ECU (Ref. AMM TASK 73-21-60-720-040).	X

Subtask 05-51-18-210-056-B ** ON A/C NOT FOR ALL

T. Check after Damage on the Engine Nacelles and Pylons

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) At the first return 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 FADEC (Ref. AMM TASK 73-22-00-710-040).	X
	(b) Do a ground test of the EEC (Ref. AMM TASK 73-22-34-710-040).	X

Subtask 05-51-18-210-056-C ** ON A/C NOT FOR ALL

T. Check after Damage on the Engine Nacelles and Pylons

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
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) At the first return 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 FADEC (Ref. AMM TASK 73-29-00-710-040).	X
	(b) Do a ground test of the ECU (Ref. AMM TASK 73-21-60-720-040).	X

Subtask 05-51-18-210-056-E ** ON A/C NOT FOR ALL

T. Check after Damage on the Engine Nacelles and Pylons

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
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) At the first return 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 EEC operational test: (Ref. AMM TASK 73-21-00-710-806).	X
	(b) Do the 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 05-51-18-210-090-C

U. Check after Damage on the Stabilizers

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.	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) Examine all the electrical bonding leads of the rudder hinges and servo controls for breakage and defective attachment. If you find damage:	X
	(a) Replace the electrical bonding lead and/or the defective attachment.		X
	(3) At the first return to the main base, examine the piston rod of each rudder servo control (it must be fully extended) 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) (Ref. AMM TASK 27-24-51-400-001).		X
	(4) 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. - For the horizontal stabilizer: SRM 551000 - For the elevators: SRM 552000	X
	(2) Examine all the electrical bonding leads of the elevator hinges and servo controls of the related damaged elevator for breakage and defective attachment. If you find damage:	X
	(a) Replace the electrical bonding lead and/or the defective attachment.		X
	(3) Examine the piston rod:
	(a) Examine the piston rod of each elevator servo control (it must be fully extended) of the related damaged elevator for burn marks, damage and leaks.	X
	Or
	(b) If you are at the line station and you cannot do the inspection of the rods, do this check: - Operate the elevators 10 times fully in each direction. - Make sure from the ground that there are no leaks below the elevator servo controls. - You must do this check before each flight until the return to the main base. You can do the check before each flight for a maximum of 3 days or 10 flights. - At the first return to the main base, you must do the inspection of the rods.	X
	(4) If you find leak or damage: - Replace the applicable elevator servo control (Ref. AMM TASK 27-34-51-000-001) (Ref. AMM TASK 27-34-51-400-001).		X
	(5) Do an operational test of the elevators (Ref. AMM TASK 27-34-00-710-001).	X
	(6) Do an operational test of the THS (Ref. AMM TASK 27-44-00-710-001).	X

Subtask 05-51-18-210-091-A

V. Check 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

5. Close-up
Subtask 05-51-18-410-050-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the access doors and panels opened during the inspection.
(3) Close the nose gear doors (Ref. AMM TASK 32-22-00-410-001).
(4) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001).
(5) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(6) Fully retract the slats (Ref. AMM TASK 27-80-00-866-005).
(7) Fully retract the spoilers (Ref. AMM TASK 27-60-00-866-002).
(8) Remove the access platform(s).
(9) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.02 06:09:54 UTC