WINGS

SOCATA MAINTENANCE MANUAL

TB 20 MODEL

LIST OF EFFECTIVE PAGES

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CHAPTER PAGE DATE CHAPTER PAGE DATE

405 JUN 02
406 JUN 02

57-30-00 (BA) JUN 01

2 JUN 01
3 JUN 01
4 JUN 01

57-30-00 (BA) 201 JUN 01

202 JUN 01
203 JUN 01
204 JUN 01

57-30-00 (CA) 201 JUN 01

202 JUN 01
203 JUN 01
204 JUN 01

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TABLE OF CONTENTS

SUBJECT CHAPTER PAGE VALIDITY

WINGS 57-00-00 (CA) 1 1 - 9999

DESCRIPTION AND OPERATION
1. GENERAL
2. LOCATION
3. DESCRIPTION
A. Wings 1
B. Wing tips 1
C. Flaps
D. Ailerons 2

WINGS 57-00-00 (CA) 301 1 - 9999

SERVICING 301
1. REPLACEMENT OF THE ANTI-SKID COATING
ON THE WINGS 301
A. Tools and consumable materials 301
B. Procedure 301

WINGS 57-00-00 (EA) 401 1 - 9999

REMOVAL I INSTALLATION 401
1. REMOVAL OF THE WINGS 401
A. Tools and consumable materials 401
B. Procedure 401
2. INSTALLATION OF THE WINGS 402
A. Tools and consumable materials 402
B. Procedure 403

WINGS 57-00-00 (EA) 601 1 - 9999

INSPECTION I CHECK 601
1. INSPECTION - WINGS 601
A. Tools and consumable materials 601
B. Preliminary steps 601
C. Inspection of the wings 602
D. Final steps 606
2. CORROSION INSPECTION OF THE SPAR I
SKINS INTERFACE FROM N1 RIB TO N4 RIB 606
A. Tools and consumable materials 606
B. Visual examination 607
C. Thorough examination 607

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SUBJECT CHAPTER PAGE VALIDITY

WINGS 57-00-00 (CA) 801 1 - 9999

REPAIR 801
1. REPAIR - WRINKLED SKIN, LEADING EDGE BOX,
WING ROOT AREA 801
A. Tools and consumable materials 801
B. Procedure 801
2. PRINCIPLE OF BLANKING OFF A CORE SAMPLE 805
A. Tools and consumable materials 805
B. Procedure 805
3. PRINCIPLE OF CORROSION REPAIR ON THE
SPAR, FROM N1 RIB TO N4 RIB 806
A. Tools and consumable materials 806
B. Repair of the spar 807
c. Installation of the stiffener - Repairs A and B 807
D. Installation of the stiffener - Repairs C and D 808

WINGS 57-20-00 (EA) 1 1 - 9999

DESCRIPTION AND OPERATION
1. GENERAL 1
2. LOCATION 1
3. DESCRIPTION
A. Wing fittings
B. Landing gear attachment fittings

WINGS 57-20-00 (BA) 401 1 - 9999

REMOVAL I INSTALLATION 401
1. REMOVAL OF THE ARMS FITTED WITH FLAPS 401
A. Tools and consumable materials 401
B. Procedure 401
2. INSTALLATION OF THE ARMS FITTED WITH FLAPS 401
A. Tools and consumable materials 401
I B. Procedure 402
3. REMOVAL OF THE ARMS FITTED WITH AILERONS 402
A. Tools and consumable materials 402
B. Procedure 402
4. INSTALLATION OF THE ARMS FITTED WITH AILERONS 403
A. Tools and consumable materials 403
B. Procedure 403

WING FITTINGS 57-20-03 (DA) 401 1 - 9999

REMOVAL I INSTALLATION 401
1. REMOVAL OF THE WING FRONT ATTACHMENT 401
A. Tools and consumable materials 401
B. Procedure 401
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SUBJECT CHAPTER PAGE VALIDITY

WING FITTINGS (Continued) 57-20-03 (DA) 401 1 - 9999

2. INSTALLATION OF THE WING FRONT ATTACHMENT 401
A. Tools and consumable materials 401
B. Procedure 402
3. REMOVAL OF THE SPACERS 402
A Tools and consumable materials 402
B. Procedure 402
4. INSTALLATION OF THE SPACERS 404
A. Tools and consumable materials 404
B. Procedure 404
5. REMOVAL OF WING REAR ATTACHMENT 404
A. Tools and consumable materials 404
B. Procedure 404
6. INSTALLATION OF WING REAR ATTACHMENT 406
A. Tools and consumable materials 406
B. Procedure 407

WING FITTINGS 57-20-03 (BA) 601 1 - 9999

INSPECTION I CHECK 601
1. INSPECTION OF THE WING FRONT ATTACHMENT 601
A. Tools and consumable materials 601
B. Procedure 601

LANDING GEAR ATTACHMENT FITTINGS 57-20-04 (BA) 401 1 - 9999

REMOVAL I INSTALLATION 401
1. REMOVAL OF THE MAIN LANDING
GEAR BEARINGS 401
A. Tools and consumable materials 401
B. Procedure 401
2. INSTALLATION OF THE MAIN LANDING
GEAR BEARINGS 401
A. Tools and consumable materials 401
B. Procedure 401
3. REMOVAL OF THE STRUT BEARING 402
A. Tools and consumable materials 402
B. Procedure 402
4. INSTALLATION OF THE STRUT BEARING 402
A. Tools and consumable materials 402
B. Procedure 403
5. REMOVAL OF THE CYLINDER ATTACHMENT
FITTING 403
A. Tools and consumable materials 403
B. Procedure 403
6. INSTALLATION OF THE CYLINDER ATTACHMENT
FITTING 403
A. Tools and consumable materials 403
B. Procedure 404
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SUBJECT CHAPTER PAGE VALIDITY

WING TIPS 57-30-00 (BA) 1 1 - 9999

DESCRIPTION AND OPERATION 1
1. GENERAL
2. LOCATION

WING TIPS 57-30-00 (BA) 201 426 - 9999

MAINTENANCE PRACTICES 201 Pre-MOD. 151,
1. SERVICING 201 1 - 274 Post-Kit
2. REMOVAL I INSTALLATION - WING TIP 201 OPT10 9094/9500,
A. Tools and consumable materials 201 275 - 425 Post-Kit
B. Removal of the wing tip 201 OPT10 9090/9100
C. Installation of the wing tip 201
3. ADJUSTMENT I TEST 202
4. INSPECTION I CHECK - WING TIP 202
A. Tools and consumable materials 202
B. Procedure 202

WING TIPS 57-30-00 (CA) 201 1 - 9999

MAINTENANCE PRACTICES 201 Post-MOD. 151
1. SERVICING 201
2. REMOVAL I INSTALLATION - WING TIP 201
A. Tools and consumable materials 201
B. Removal of the wing tip 201
C. Installation of the wing tip 201
3. ADJUSTMENT I TEST 202
4. INSPECTION I CHECK - WING TIP 202
A. Tools and consumable materials 202
B. Procedure 202

FLAPS 57-50-00 (EA) 1 1 - 9999

DESCRIPTION AND OPERATION
1. GENERAL
2. LOCATION

FLAPS 57-50-00 (CA) 401 1 - 9999

REMOVAL I INSTALLATION 401
1. REMOVAL OF ONE FLAP 401
A. Tools and consumable materials 401
B. Procedure 401
2. INSTALLATION OF ONE FLAP 401
A. Tools and consumable materials 401
B. Procedure 401

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SUBJECT CHAPTER PAGE VALIDITY

AILERONS 57-60-00 (BA) 1 1 - 9999

DESCRIPTION AND OPERATION
1. GENERAL
2. LOCATION

AILERONS 57-60-00 (BA) 401 1 - 9999

REMOVAL I INSTALLATION 401
1. REMOVAL OF THE AILERON 401
A. Tools and consumable materials 401
B. Procedure 401
2. INSTALLATION OF THE AILERON 401
A. Tools and consumable materials 401
B. Procedure 401

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WINGS

DESCRIPTION AND OPERATION

1. GENERAL
This system consists of wing structural elements and associated components which allow aircraft lift.
The wings consist of :
- the wings,
- the wing tips,
- the flaps,
- the ailerons.

2. LOCATION (Figure 1)

COMPONENT QTY AREA ACCESS DOOR REFERENCE

Wing 2 500 I 600 I 57-20-00

Wing tip 2 500 I 600 I 57-30-00
Flap 2 500 I 600 I 57-50-00
Aileron 2 500 I 600 I 57-60-00

3. DESCRIPTION
A. Wings - refer to 57-20-00
The wings allow aircraft lift.
Wings characteristics :
Profile ......................................................................... RA16-3C3
Aspect ratio . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
Dihedral . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6°3
Aerodynamic chord . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.002 ft - 1.220 m
True chord . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.085 ft - 1.245 m
Wing area .......................................................... 128.091 sq.ft - 11.90 m2
Wing setting .......................................................................... + 3°
B. Wing tips - refer to 57-30-00
The wing tips include the navigation lights, the anti-collision lights and the recognition lights.
C. Wing flaps - refer to 57-50-00
The flaps allow to increase the lift at low speed by modifying the wing profile.

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Recoil and slotted type flaps characteristics :

Unit area ................................................................. 10 sq.ft - 0.93 m 2
Mean span . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.366 ft - 2.550 m

D. Ailerons - refer to 57-60-00

The ailerons allow aircraft maneuver around the roll axis.
Ailerons characteristics :
Unit area .............................................................. 4.897 sq.ft - 0.46 m2
Mean span .............................................................. 4.081 ft - 1.244 m

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A - Flap
B - Aileron
C - Wing tip
D - Wing

c
•

Wings - Identification and location of components

Figure 1
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WINGS

SERVICING

1. REPLACEMENT OF THE ANTI-SKID COATING ON THE WINGS

A. Tools and consumable materials
- Anti-skid coating (TB 05-919}

- Sealant (TB 09-910)

- Hot air generator
- Clean lintfree cloths

- Nylon spatula
- Cleaning agent (TB 11-003).

B. Procedure
1) Remove and discard the blanking plug on the wing upper surface.
2) Moderately heat anti-skid coating (TB 05-919) with a hot air generator to soften the adhesive.
3) De-bond defective anti-skid coating (TB 05-919} with a nylon spatula.

4) Clean the bared surface with clean lintfree cloths moistened with cleaning agent (TB 11-003).
5) Position the new coating to cut out the footstep area.
6) Bond the new anti-skid coating (TB 05-919).
7) Apply sealant (TB 09-910) on the periphery of anti-skid coating (TB 05-919), make an even bead
overlapping anti-skid coating (TB 05-919) and wing upper surface.
8) Mark the location of the blanking plug orifice, cut the anti-skid coating (TB 05-919) and clear the orifice.
9) Install a new blanking plug.

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WINGS

REMOVAL I INSTALLATION

CAUTION IT IS STRICTLY FORBIDDEN TO HOIST THE AIRCRAFT ASSEMBLY (FUSELAGE+ WINGS)

WITH FUSELAGE HANDLING TOOL P I N TB10 99000900 (RISKS OF IRREVERSIBLE
DEFORMATION). ONLY THE POWER PLANT + FUSELAGE+ STABILIZERS ASSEMBLY
MAY BE HOISTED WITH THIS TOOL.

1. REMOVAL OF THE WINGS (Figure 401)

A. Tools and consumable materials
- 2 fuselage padded supports
- 2 wing padded supports, PIN TB10 99000911
- Blanking caps and plugs
- Clean lintfree cloth
- Cleaning agent (TB 11-003)
B. Procedure
1) Drain L.H. and R.H. fuel tanks - refer to 12-11-02.
2) Remove engine cowling 121 - refer to 71-10-01.
3) Position the hoisting device over the aircraft - refer to 07-20-00.
Pre-MOD. 151
4) Remove the cowlings under hull and the front junction fairings.
Post-MOD. 151
4) Remove the cowlings under hull, the footstep fairings and the front junction fairings.
5) Remove the L.H. and R.H. footstep control cables - refer to 53-70-00.
6) Disconnect the L.H. and R.H. footstep springs - refer to 53-70-00, and hold the L.H. and R.H. footsteps
in "retracted" position with tie-wraps.
7) Remove the footstep fairing attachment brackets from the L.H. and R.H. wheel housings.
SIN 1 - 9999
8) Remove front and rear bulkheads from wheel housings.

9) Place two padded supports under the wings, at a rib.

10) Drain the landing gear hydraulic system - refer to 12-13-04 and disconnect the main landing gear
actuator hoses on the fuselage. Blank off.
11) Disconnect the flap control rods from the main bellcrank - refer to 27-50-00, retain the attaching parts
and discard the cotter pins. Clear the rods from the bellcrank.
12) Drain the brake hydraulic system - refer to 12-13-02.
13) Disconnect the brake system at wing I fuselage junction. Blank off.
14) Disconnect the fuel system at wing I fuselage junction. Blank off.
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15) Disconnect the aileron control rods from the lever at the aircraft centerline, retain the attaching parts and
discard the cotter pins.
16) Disconnect the wing electrical circuits at wing I fuselage junction.
17) Drain the air conditioning system (if installed) - refer to 12-15-02.
18) If necessary, disconnect the high and low pressure hoses from the air conditioning system. Blank off.
19} Remove the three-way union of the static system and disconnect the dynamic system at fuselage I wing
junction.
20} Remove the front seats - refer to 25-11-00 and the side upholstery panels.
21) Remove and discard locknuts (8), retain washers (9), shims (10) and bolts (11).
22) Remove and discard locknuts (14), retain washers (13) and bolts (12).
23} Remove and discard locknuts (6), retain washers (5) and, if installed, thrust washer (7).
24} Remove bolts (2), shims (3) and washers (1).
25) Remove the wing root seals located on the wing upper surface at wing I fuselage junction.
26) Hold the wing assembly on its padded supports and lift the fuselage with the hoisting device - refer
to 07-20-00.
CAUTION : TO AVOID DAMAGING THE STRUCTURE, THE SUPPORTS MUST PERFECTLY FIT
THE FUSELAGE PROFILE AND HAVE PADDED BEARING AREAS
27) If the hoist is rail-mounted, remove the fuselage, place it on two padded supports (one positioned at the
rear at a frame and the other under the wing spar tunnel) and make sure the nose landing gear rests on
the ground.

2. INSTALLATION OF THE WINGS {Figure 401)

A. Tools and consumable materials
- 2 fuselage padded supports
- 2 wing padded supports, PIN TB10 99000911
- Blanking caps and plugs
- Grease (TB 04-004A}
- Petrolatum (TB 04-012)
- Red paint
- Adhesive (TB 08-006A)
- Clean lintfree cloth
- Cleaning agent (TB 11-003)
- Teflon tape (TB 05-938)
- Hydraulic fluid (TB 02-001)
- Sealant (TB 09-013A}
- Sealant (TB 09-007)

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- Torque wrench 0 - 885 lbf.in (O - 100 N.m)

- Tie-wraps
B. Procedure
1) Inspect the splices, spacers, fittings and mounting pads for correct condition and torque - refer
to 20-00-01.
2) Inspect the wings (spars, splices, spacers, etc.) and the fuselage (skins, tunnel, frames, etc.) for
corrosion.
3) Make sure there is a Teflon tape (TB 05-938) on lower face of wing upper surface skin at footstep.
Inspect for condition. Replace if necessary.
a) Remove the Teflon tape and clean the skin with a clean lintfree cloth moistened with cleaning
agent (TB 11 -003).
CAUTION : DO NOT TOUCH THE ADHESIVE SIDE OF THE TEFLON TAPE TO AVOID BAD
BONDING.
b) Bond the Teflon tape (TB 05-938) under the wing upper surface skin.
c) Cut excess Teflon tape (TB 05-938).
4) Inspect the bead of sealant around the spacers for condition. Replace the sealant if necessary - refer
to 57-20-03.
5) If necessary, protect the wings splicing and the spacers with sealant (TB 09-007) - refer to 20-00-09.
6) Inspect the anticorrosion protection between the wing root and the rib located at 55.41 in (1406.5 mm)
from the aircraft centerline for condition. If necessary, protect with sealant (TB 09-013A) - refer
to 20-00-09.
7) Position the fuselage over the wings and lower it slowly until it perfectly aligns with the spacers and the
front and rear attachment fittings.
8) Engage the spar into the tunnel (frame C2).
9) Lubricate bolts and ball ends with grease (TB 04-004A) - refer to 12-21-04.
1O) Position the central attachment spacers against the tunnel front face.
11) Measure the gap between spacers (4) and the tunnel rear face.
12) Install suitable shims (3) - refer to Table, Figure 401 (2/2).
13) Install washers (1) and bolts (2).
Post-MOD. 167
14) Measure the dimension between the tunnel and bolt (2).
15) Install thrust washer (7) according to the recommended assembly - refer to Table, Figure 401 (2/2).
SIN 1 - 9999
16) Install washers (5) and new locknuts (6). Torque - refer to 20-00-01.
17) Measure the gaps on front fittings (frame C1).
18) Install suitable shims (10) - refer to Table, Figure 401 (2/2).
19) Install bolts (11 ), washers (9) and new locknuts (8). Torque - refer to 20-00-01.
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20) Install bolts (12), washers (13) and new locknuts (14). Torque - refer to 20-00-01.
21) Remove the two padded supports under the wings and the hoisting device.
22) Connect the flap control rods to the main bellcrank - refer to 27-50-00, install new cotter pins.
23) Remove the blanking plugs. Connect the main landing gear actuator hoses - refer to 20-00-02.
24) Replenish the landing gear hydraulic system - refer to 12-13-03.
25) Connect the wing electrical circuits at wing I fuselage junction.
26) Connect the dynamic system and install the three-way union of the static system.
27) Remove the blanking plugs. Connect the high and low pressure hoses of the air conditioning system, if
installed - refer to 20-00-02.
28) If installed, replenish the air conditioning system - refer to 12-15-01.
29) Connect the aileron control rods to the lever. Install new cotter pins.
30) Remove the blanking plugs. Connect the fuel system at wing I fuselage junction - refer to 20-00-02.
31) Remove the blanking plugs. Connect the brake system at wing/ fuselage junction - refer to 20-00-02.
32) Replenish then bleed the brake hydraulic system - refer to 12-13-01.
33) Replenish the fuel tanks - refer to 12-11-01, and check the fuel supply for correct operation - refer
to 28-20-01.
34) Check hydraulic unions and fuel unions for leaks.
35) Mark with a red paint line the hydraulic unions, the fuel unions and the bolts and nuts securing the wings
to the fuselage.
36) Inspect the anti-skid coating for condition, replace if necessary - refer to Page 301.
37) Install front and rear bulkheads of the wheel housings.
Pre-MOD. 151
38) Make sure all the tools and materials are removed and the work area is clean and free from debris.
39) Check the landing gears for correct operation (Normal - Emergency) - refer to 32-30-00.
40) Check the roll control linkage for correct operation - refer to 27-10-00.
41) Install the front junction fairings and the cowlings under hull.
42) Install and, if necessary, bond the wing root seals to the wing upper surface at wing I fuselage junction.
Use adhesive (TB 08-006A).
Post-MOD. 151
38) Lubricate the wing root seal bead with petrolatum (TB 04-012).
39) Using a spatula, install the seals on the wing upper surface at wing I fuselage junction.
NOTE : The seal must extend by 7.9 in (200 mm) aft of the wing trailing edge. This extra length
must be positioned in the cowling under hull.
40) Remove the tie-wraps and move the L.H. and R.H. footsteps in "extended" position. Secure the spring
to the L.H. and R.H. footsteps - refer to 53-70-00.
41) Install the footstep fairing attachment brackets on the L.H. and R.H. wheel housings.
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42) Install the L.H. and R.H. footsteps control cables - refer to 53-70-00.
43) Make sure all the tools and materials are removed and the work area is clean and free from debris.
44) Check the landing gears (Normal - Emergency) - refer to 32-30-00, and the footsteps for correct
operation.
45) Check the roll control linkage for correct operation - refer to 27-10-00.
46) Install the front junction fairings, the footstep fairings and the cowlings under hull.
SIN 1 - 9999
47) Install engine cowling 121 - refer to 71-10-01.
48) Install the front seats - refer to 25-11-00 and the side upholstery panels.
49) Close main switch-breaker. Check for correct operation :
Pre-MOD. 151
- the navigation and anti-collision lights - refer to 33-40-02,
if installed, the heated pitot tube - refer to 30-30-00, and the outside air temperature sensor - refer
to 34-13-00,
Post-MOD. 151
the navigation lights, anti-collision lights and recognition lights (if installed) - refer to 33-40-02,
the heated pitot tube - refer to 30-30-00, and the outside air temperature sensor - refer
to 34-13-00,
SIN 1 - 9999
- the stall warning device - refer to 27-30-04,
the fuel indication system - refer to 28-40-00,
- the airspeed indicating system - refer to 34-10-00,
the taxi and landing lights - refer to 33-40-01,
the flaps - refer to 27-50-00.
50) Open main switch-breaker.
51) Perform a triangulation check - refer to 51-50-01.
52) Perform a test flight - refer to 05-30-00.

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::!:
Wings - Removal I Installation
Figure 401 (1/2)
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TB20 MODEL

1 - Washer 8 - Locknut
2 - Bolt 9 - Washer
3 - Shim 10 - Shim
4 - Spacer 11 - Bolt
5 - Washer 12 - Bolt
6 - Locknut 13 - Washer
7 - Thrust washer 14 - Locknut

Repere
1 7
©
Item
Depassement axe : X o 1 a. 1,18.3,5 >3,5
Bolt protrusion : X Oto 0.039 0.043 to 0.137 >0.137
Epaisseur rondelle 0 2,5 3
Washer thickness 0 0.098 0.118 ~ 12

0 2

Jeu 1,1 a. 1,2 1,3 a. 1,6

1,78.2 2,18.2,4
Gap 0.043 to 0.047 0.05 to 0.063 0.067 to 0.078 0.082 to 0.094
Calage 1 1,2 1,6 2
Setting 0.039 0.047 0.062 0.078

0
0
0

""'
N
Jeu o a. o,4 o,5 a. o,s ~ o,s
>
m
<( Gap O to 0.015 0.19 to 0.03 ~ 0.035
<(
<(
0
0
0
Calage neant 0,6 1
r::.
In
Setting none 0.023 0.039
~

Wings - Removal I Installation

Figure 401 (2/2}
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PAGE INTENTIONALLY LEFT BLANK

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WINGS

INSPECTION I CHECK

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. INSPECTION - WINGS
A. Tools and consumable materials
- Flashlight
- Swivel inspection mirror

- Borescope
- Cleaning agent (TB 11-002}
- Cleaning agent (TB 11-019}
- Cleaning agent (TB 11-904)
- Cleaning agent (TB 11-905)
- Clean lintfree cloths
B. Preliminary steps
NOTE : The inspection must be carried out once the areas to be inspected (upper and lower
surface skins, landing gear box, etc ...) have been carefully cleaned.
1) Perform an external inspection of the fuel tanks, with full fuel - refer to 28-10-00.
2) Drain the fuel tanks - refer to 12-11-02.
3) Ventilate the fuel tanks - refer to 12-11-03.

4) Remove junction fairing 217L [217R] - refer to 06-30-00.

5) Remove the cowlings under hull 218A and 218F - refer to 06-30-00.
Post-MOD. 151

6) Remove footstep fairings 2111 L [2111 R] - refer to 06-30-00.

All

7) Remove the wing tips - refer to 57-30-00.

NOTE : If the wing tips are riveted, remove the rivets.
8) Extend the flaps.

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9) Install the warning sign prohibiting main switch-breaker operation.

WARNING

DO NOT OPERATE
MAINTENANCE WORK IN PROGRESS

1O) Remove all wing inspection doors - refer to 52-40-00.

NOTE : To facilitate the inspection, it is recommended to install two additional doors on the
wing lower surface, between NS and N6 ribs aft of the spar, and between N9 and N1 O
ribs forward of the spar. Order Kits OPT1 O 918700 and 918800.
11) Remove and mark the rods of the roll control in the wings.
12) Remove the anti-skid coating on the wing - refer to Page 301.
C. Inspection of the wings
NOTE : If symptoms of corrosion (blisters, tulip-deformed rivets, etc.) are detected, especially
along the spar and in particular in the N1 to N4 area (wing lower and upper surfaces),
perform a corrosion inspection - refer to Paragraph 2.
1) Inspect the overall external appearance of the upper and lower surface skins for :
impacts, distortions, scratches, cracks and blisters due to corrosion (especially in the spar aera),

loose rivets,
overall condition of the paint, especially around rivet heads,

correct condition and positioning of the wing root seal,

blockage of the drain tubes,
blockage of the fuel tank vent tube,
condition and security of the outside air temperature sensor, if installed,
condition and security of the pitot tube,
condition and security of the stall warning indicator,
condition and security of the transparent covers of the landing and taxi lights,
condition of the trailing edge closing plate and loose rivets,
condition and correct security of the electrical harness, the pitot tube hose and the deicing supply
hoses (if installed) along the closing plate,
condition and security of the deiced leading edges, if installed.
2) Inspect the junction of both spars for :
evidence of impacts, cracks and corrosion,
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
tightening of the nuts securing the upper, lower, front and rear splices,

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presence and condition of the grommets, if installed, for the passage of the deicing supply hoses
through the spars,
condition and security of the static port three-way union support,
presence of a coat of sealant {TB 09-007) over the area.
3) Inspect main landing gear actuator attachment for :
evidence of impacts, cracks and corrosion,
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
- tightening of the attachment nuts on the spar,
S I N 735 - 1999 with option 0633
S I N 2000 - 9999
- the presence of a bead of sealant (TB 09-916) around the attachment.

4) Inspect the spacers for :

impacts, cracks and evidence of corrosion,
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
tightening of the attachment nuts,
S I N 735 - 1999 with option 0633
S I N 2000 - 9999
presence of a bead of sealant (TB 09-002A) around the spacer, on spar side,
protection of the spacers with sealant (TB 09-007).
5) Inspect wing front attachment for :
distortions, impacts, cracks and evidence of corrosion,
- tightening of the attachment nuts on the small spar,
S I N 735 - 1999 with option 0633
S I N 2000 - 9999
presence of sealant (TB 09-916) between the parts,

cracks, evidence of corrosion and loose rivets on the small spar and the brackets,
- tightening of the nut securing the front attachment to the fuselage,
cracks, evidence of corrosion and loose rivets on the brackets reinforcing frame C1.
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.

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6) Inspect wing rear attachment for:

distortions, impacts, cracks and evidence of corrosion on rear fitting (wing side), the rod and the
half-fittings (fuselage side),
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
- tightening of the two nuts securing the rod to the rear fitting and the half-fittings,
- tightening of the bolts securing the half-fittings to the fuselage,
Rear fitting secured with blind rivets
loose rivets,
Rear fitting secured with bolts and nuts
- tightening of the bolts,
S I N 735 - 1999 with option 0633
S I N 2000 - 9999
installation of the fittings with sealant (TB 09-916}.
7) Inspect the main landing gear bearings for :
evidence of impacts, cracks and corrosion,
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
tightening of the attachment bolts.
8) Inspect the hinged strut bearing for :
evidence of impacts, cracks and corrosion,
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
tightening of the attachment nuts on the spar,
tightening of the nuts on the spar flange,
S I N 735 - 1999 with option 0633
S I N 2000 - 9999
presence of sealant (TB 09-916} between the bearing and the spar.
9) Inspect the landing gear box for :
distortions, impacts, cracks and evidence of corrosion on N1, N2 and N3 ribs,
loose rivets,
- tightening of the nuts securing N3 rib to the spar,
presence of the grommets and protection edgings in the clearing holes and on sharp edges, at
wiring and brake hose passages,
security and correct routing of the wiring and the brake hose with clamps and tie-wraps,

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distortions, impacts, cracks, evidence of corrosion and loose rivets on the supports of the flaps
control bellcrank,

evidence of impacts, corrosion and loose rivets of the spar flanges on upper and lower surface skins,
SIN 1607. 1615 - 1626. 1628 - 9999

I presence of a coat of sealant (TB 09-013A) or (TB 09-918) over the area,

SIN 1 - 9999

tightening of the upper and lower surface screws on the spar, on wing root side.
1O) Inspect flap and aileron arm assemblies for :
distortions, impacts, cracks and evidence of corrosion,
NOTE : In case of doubt on the presence of a crack, perform a fluorescent penetrant
inspection - refer to 20-00-14.
Attachment with rivets
loose rivets,
Attachment with bolts
tightening of the nuts,
S I N 735 - 1999 with option 0633
S I N 2000 - 9999
presence of sealant (TB 09-916) between the arm assembly and the rib.
11) Carefully inspect each box for :

NOTE : Depending on accessibility, each box must be inspected either with a swivel mirror
and a flashlight or with a borescope.
distortions, impacts, cracks and evidence of corrosion between the rib and the skin,
loose rivets,
impacts, cracks and evidence of corrosion between the spar and the skin,
Sealed areas
coating of the spar flanges and the flanged edges of the ribs with sealant (TB 09-001A),
Non-sealed areas from N1 rib to N4 rib

SIN 1607. 1615 - 1626. 1628 - 9999

I coating of the spar flanges with sealant (TB 09-013A) or (TB 09-918),
All areas
security and condition of the fuel tube support and the electrical wiring on N1 rib,
correct routing of the fuel tube from N4 rib to the filter selector,
if installed, correct passage of the deicing hoses through N1 and N2 ribs and presence of protection
strips on the clearing holes,
distortions, loose rivets, cracks and evidence of corrosion of the roll control bellcranck support
between N3 and N4 ribs,

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TB20 MODEL

presence of protection edgings on the clearing holes and the sharp edges at cable passages,
condition and security of the tank vent tube/hose and presence and condition of the grommets,
if installed, correct passage of the deicing hoses through N9 and N 10 ribs, their attachment to the
vent tube/hose and the presence of protection strips on the clearing holes,
security and routing of the wires with clamps or wire retainers and tie-wraps,
if installed, condition, security and sealing of the low level detector,
condition, security and sealing of the fuel gages,
distortions, loose rivets, cracks and evidence of corrosion of the roll control bellcrank support
between NB and N9 ribs.
D. Final steps
1) Make sure all the tools and materials are removed and the work area is clean and free from debris.
2) Bond the anti-skid coating - refer to Page 301.
3) Install the roll control rods as marked during removal.
4) Make sure the roll control moves freely.
5) Install the wing inspection doors - refer to 52-40-00.
6) Install the wing tips - refer to 57-30-00.
7) Install the cowlings under hull 21 BA and 21 BF.
8) Install junction fairing 217L [217R].
Post-MOD. 151

9) Install footstep fairing 2111 L [2111 R].

All
10) Remove the warning sign prohibiting main switch-breaker operation.
11) Retract the flaps.
12) Replenish the fuel tanks - refer to 12-11-01.
13) Perform a test run-up - refer to 05-30-02.

2. CORROSION INSPECTION OF THE SPAR I SKINS INTERFACE FROM N1 RIB TO N4 RIB

(Figures 601, 602, 603, 604, 605, 606 and 607)
A. Tools and consumable materials
- Corrosion inspection ruler TB81105Z TB20 11990003 or metrology ruler
- Feeler gage set
- 6 x magnifying glass
- Mobile lighting equipment
- Cleaning agent (TB 11-002)
- Waterproof compound (TB 05-027)
- Clean lintfree cloths
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B. Visual examination
NOTE 1 : The examination must be performed once the wing upper and lower surface skins have
been thoroughly cleaned.
NOTE 2 : This examination may be replaced by an eddy current test, for users having such
equipment at their disposal. The experience tends to demonstrate that, with eddy current
testing, the value read is doubled with respect to a visual inspection - see Figure 602.
NOTE 3 : This procedure is applicable to the wing upper and lower surface skins. Information
specific to the lower surface is given in square brackets.
1) Position ruler (15) at wing root on the upper surface skin [lower surface skin] in the spar area and
lengthways - see Figure 607.
2) With horizontal lighting, slide the ruler over the entire width of the spar, and scan the area in this way up to
N4 rib.
3) Visually check the evenness of the distance between the ruler and the skin.
4) If a defect (blister) is detected, move ruler {15) sideways and lengthways to determine the surface of the
defect and mark its outline on the skin.
5) Using a feeler gage set, measure the height of the defect.
6) Depending on the height of the defect, determine the required solution :

- for a defect< 0.0078 in (< 0.2 mm), no corrective action, the defect is certainly due to padding,
for a defect< 0.0118 in and<!: 0.0078 in(< 0.3 mm and<!: 0.2 mm), record the readings for annual
follow-up, to check for possible evolution. If acessible, perform a preventive treatment with
waterproof compound (TB 05-027),
for a defect <!: 0.0118 in (<!: 0.3 mm), perform a thorough examination - refer to Paragraph C.
C. Thorough examination
1) Depending on the extent of the suspected corrosion, partially open (core sampling, window ... ) or
completely open the skin concerned.
NOTE : Core sampling consists in cutting out the skin over a diameter of 0.78 in (20 mm),
taking as an axis the tip of the distortion.
2) Measure the depth of the defect :

For a defect s 0.0118 in (s 0.3 mm) contained within a maximum diameter of 2.36 in (60 mm),
perform the repair - refer to Page 801.

NOTE : If the defect is contained within a diameter greater than 2.36 in (60 mm), contact
the manufacturer or a station approved for this type of repair.
For a defect> 0.0118 in (> 0.3 mm), record the defects (position and dimensions) and contact the
manufacturer or a station approved for this type of repair.
NOTE : If no evidence of corrosion is detected, apply the required blanking solution - refer
to Page 801.

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SOCATA MAINTENANCE MANUAL
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VISUAL EXAMININATION OF
NON-HIDDEN SPAR
SURFACES
(WEB AND FLANGES)

CAUTION
FOR AIRCRAFT WHOSE
SERIAL NUMBER IS IN
NO
,, ACCORDANCE WITH SERIAL
NUMBERS DESCRIBED IN
I CORROSION CHAPTERS 05-20-01,
05-20-04, 05-20-05 OR
YES 05-20-06, PERFORM A
~ . THOROUGH EXAMINATION OF
I END OF EXAMINATION I THE SPAR FLANGE I SKINS
JUNCTION.
1'
IF CORROSION IS DETECTED
ON THE SPAR FLANGES OR
ASSESSMENT OF
WEB, CORROSION AT
THE DAMAGE
SPAR I SKINS INTERFACE IS
HEAVILY SUSPECTED .

...
RECORDING OF THE
DEFECTS (POSITION AND
DIMENSIONS)

~·
REPAIR PER
MANUFACTURER'S
SOLUTION OR BY STATION
APPROVED FOR THIS TYPE
OF REPAIR

Corrosion inspection (box interior) - Visual examination

Figure 601
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TB20 MODEL

CLEANING OF THE SURFACES

NOTE: TO BE INSPECTED
IF CORROSION IS FOUND
DURING VISUAL EXAMINATION
(FIGURE 601), CORROSION AT 1r
SPAR/SKINS INTERFACE IS INSPECTION FOR SYMPTOMS :
HEAVILY SUSPECTED. - BLISTERS,
- LOOSE RIVETS,
- "TULIP-DEFORMED" RIVETS,
- UNCAPPED RIVET HEADS

1r
ASSESSMENT OF THE DISTORTIONS
(BLISTER HEIGHT) THROUGH VISUAL
INSPECTION OR EDDY CURRENT
TESTING

n
VISUAL:< 0.0118 IN (0.3 MM)
1' ~,
AND:. 0.0078 IN (0.2 MM)
VISUAL::. 0.0118 IN (0.3 MM) EDDY CURRENT : VISUAL: < 0.0078 IN (0.2 MM)
EDDY CURRENT : < 0.0236 IN (0.6 MM) AND EDDY CURRENT :
:. 0.0236 IN (0.6 MM) :. 0.0157 IN (0.4 MM) < 0.0157 IN (0.4 MM)

1r
THOROUGH INSPECTION
SKIN OPENING
I+-
l
RECORDING OF THE GAPS
FOR ANNUAL CHECK
I
1r
END OF EXAMINATION I
(CORE SAMPLE, WINDOW ... ) (FOLLOW-UP OF THE
EVOLUTION)

l 1r
0 PREVENTIVE TREATMENT
WITH WATERPROOF
COMPOUND (TB 05-027)

1'
IF EVOLUTION IS FOUND
- DURING THE NEXT
INSPECTION

Corrosion inspection (spar I skins interfaces) - Thorough examination

Figure 602 (1/2)

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TB20 MODEL

0
NO
I
l
CORROSION I
I YES

0
IF DEFECT DEPTH s 0.0118 IN
~·
(0.3 MM) CONTAINED WITHIN A IF DEFECT DEPTH
MAXIMUM DIAMETER OF
2,36 IN (60 MM)
I > 0,0118 IN (0,3 MM) I
~·
1~ REPAIR PER
~
REPAIR PER MAINTENANCE MANUFACTURER'S SOLUTION
r
MANUAL, PAGE 801 OR BY STATION APPROVED
FOR THIS TYPE OF REPAIR

Corrosion inspection (spar I skins interfaces) - Thorough examination

Figure 602 (2/2)
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SO CATA MAINTENANCE MANUAL
TB20 MODEL

800 mm
Zone a inspecter
Area to be inspected 31.5 in

: : : : : : : : frll I
I II I II II II II I Ill
1 II I II II II II I llL--------
1 II I 11 ll II II I II~---~---~~
I 11 I II ll II II I 11 1 II II
I l I I I 1 I I I I II I 111 I I II
0
0

-- *-
N I II II 11 11 It II I II II
~ I II 11 11 11 II II 11 II II
>
0
F= ===== F:= ==== ==:1 == == == F:== :: : : +:== ==:: :::i:: :: : : i~::::::::::: ::::zu&~ W.4'7ff4. --~-
<{ I 11 II 11 II 11 II II Ill II
<{ I II II ll II 11 II II Ill II
<{
I 11 I I I I I I I I I I l I 111 II
0
0 I 11 II 11 11 1l 11 JI Ill Ill II
0
0
....
I
~------
11
______
II
II
J1 ______ 1
11 II II
------~L------1
II 11 Ill Ill
~-----~·~---LIL~-~
I 11
II

II
"'
:;!:
-------
II
------~~------ ------ -------------- ------ -------
I 11
----1n-1
II

I It II
I II 11
I ti 11

EMPLANTURE
E E E E E WING ROOT
E E E E
E .t;: E E .t;: E .t;: E .t;: E .t;: E .t;: E .t;: E .t;: E
C') .t;:
LO_ 0) E .t;: E .t:: E .t;:
LO_
C') ~ (!) ~
(!)
C')
~ "'- ~ Lt)
~ (!) LO_ C') LO_ (0 (!) E '<:!" E
co co 0)
co ~
0) (!) C\I
C')
...... ~
<D
co<:!" .,.._ <D C') <D co LO Lt) (!)
.,.._
<D ~
co .,.._ o) ,-- .....: LO 0) 0
co c:ci
C') C') Lt) '<:!"
0 0 <D
co N 0 N <D <:!" 0 c'5 0)
C\i ~ C\i
<:!" <:!" C') C') C') N N <D

N12 N11 N10 N9 NB N7 N6 NS N4 N3 N2 N1

Corrosion inspection - Area to be inspected

Figure 603

1 - Wing upper surface skin

2 - Spar flange
3 - Spar web
4 - Rivet
5 - Wing lower surface skin
6 - Visible corrosion
7 - Underlying corrosion

~2
3

Corrosion inspection - Type of defect

Figure 604

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TB20 MODEL

11 - Stiffener
12 - Example of corrosion
N3
N1
11 Bord d'attaque 660 mm
Leading edge 2.16 ft
+

60 mm max.
2.36 in max.

------------------ -----------------
+ + + + + + + + + + + +
+ + + + +
+ + + + +

12
Corrosion inspection (spar I skins interfaces) - Wing upper surface
Figure 605

13 - Stiffener
N3 14 - Core sample
1085 mm N1
3.56 ft 660 mm
2.16 ft
13
++
++++
+ ++ +
-----r---r--+- +--:+--~- + + + + +++ + + + + + + +
+ + + I +1 + + +
I I

+ + + +:+ +:+ + + + +++ ++~+ + + + +

I I
---------------- -+-T+-+~-+-
1 I

+:+ +:+
1+ +:
:+
I
+1 I
I++
I

+
Bord d'attaque
Leading edge

Corrosion inspection (spar I skins interfaces) - Wing lower surface

Figure 606

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TB20 MODEL

15 - Ruler
16 - Leading edge
17 - Wing root

10 mm
0.39 in
200 mm
6 mm

-+-----+---
II 0.23 in 7.87 in

1 mm ____,_....__
10 mm
0.039 in 0.39 in

30 mm 1,5 mm
1.18 in 0.06 in

Ecart detecte par

controle visuel
Gap detected during
visual inspection

0 0 0 0 0 0 0 0
0 0 0 0 0 0 0 0

Profondeur corrosion
Corrosion depth

Ecart detecte par courant de Foucault

Gap detected by Eddy current

Corrosion inspection (spar I skins interfaces) - Visual examination

Figure 607
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TB20 MODEL

PAGE INTENTIONALLY LEFT BLANK

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SOCATA MAINTENANCE MANUAL
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WINGS

REPAIR

NOTE : Apply a protection treatment - refer to 20-00-04, to all metal parts which have been bared during
repair operations.

1. REPAIR - WRINKLED SKIN, LEADING EDGE BOX, WING ROOT AREA

A. Tools and consumable materials
- A rib PI N TB 10 11016100 or a stiffener (2) - see Figure 802 for fabrication details
- A R.H. shim (3) - see Figure 802 for fabrication details
- A L.H. shim (4) - see Figure 802 for fabrication details
- 2 screws ZOO.N5122683194 (15)
- 2 screws ZOO. N5122683084 (10)
- 2 screws ZOO. N5122683087 (13)
- 2 screws ZOO. N5122683099 (14)
- 2 washers ZOO.N5701039240 (16)
- 6 washers ZOO.N5701039160 (11)
- 2 nuts ZOO. N5401458239 (17)
- 6 nuts ZOO.N5401458159 (12)
- 8 rivets ZOO.N5528371382 (8)
- 18 rivets ZOO.N5529308001 (19) and (21)
- 1 rivet ZOO.N5529308004 (5)
B. Procedure (Figure 801)
1) Remove the wings - refer to 57-00-00.
2) Inspect the fitting of front attachment (7) on the fuselage, make sure that there are no screw head marks
in the bent sections.
3) Remove wing upper surface stiffener (20) forward of footstep area.
4) Flatten the wrinkled area of the skin.
5) Install intermediate stiffener (2) with blind rivets (21).
NOTE : Stiffener (2) is to be cut from a rib PIN TB10 11016100 or fabricated from a sheet -
see Figure 802 for fabrication details.
6) Drill a hole with a drill No. 22 (dia. 4 mm) to install rivet (5) attaching the wing root half-ribs.
7) Using a drill No. 22 (dia. 4 mm) , drive out rivet (6) and flat round head rivets (18) and (9).
8) Counterdrill both holes (a) with a drill No. 9 (dia. 5 mm).
9) Install R.H. shim (3) and L.H. shim (4) on wing root rib (1 ). Replace flat round head rivets dia. 0.157 in
(4 mm) with screws (10), (13), (14) and (15), washers (11) and (16), nuts (12) and (17).

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TB 20 MODEL

10) Replace the 8 rivets dia. 0.126 in (3.2 mm) (8) securing, on the upper surface, the skin to the front small
spar with flat round head rivets (AU4G) dia. 0.157 in (4 mm) PIN ZOO.N5528371382.
NOTE : Some aircraft are already factory-fitted with rivets dia. 0.157 in (4 mm) on wing lower
surface.
11) Plug skin holes (b) with blind rivets (21).
12) Vacuum-clean any chips from the leading edge box.
13) Make sure all the tools and materials are removed and the work area is clean and free from debris.
14) Perform paint touch-ups - refer to 20-00-03.
15) Install the wings - refer to 57-00-00.

1 - Wing root rib

2 - Stiffener
3 - R.H. shim
4 - L.H. shim
5 - Rivet
6 - Rivet
7 - Front attachment
8 - Rivet
9 - Flat round head rivet
10 - Screw
11 - Washer
12 - Nut
13 - Screw
14 - Screw
15 - Screw
16 - Washer
17 - Nut
18 - Flat round head rivet
19 - Rivet
20 - Stiffener
21 - Blind rivet

Installation details
Key to Figure 801

ABAA
Validity : SIN 1 - 9999 Page 802
57-00-00 (CA) JUN 01
SOCATA MAINTENANCE MANUAL
TB 20 MODEL

I 0

( 0
'
0 0 0 0

18
17
16
15

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Installation details
Figure 801
ABAA
Validity : S I N 1 - 9999 Page 803
57-00-00 (CA) JUN 01
SOCATA MAINTENANCE MANUAL
TB 20 MODEL

Profil du raidisseur suivant profil revetement

Stiffener profile following skin profile

9 mm
3 I Bin

c l!)
e C')
~
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RAIDISSEUR AU4G1
C') 0 STIFFENER AU4G1
.i::
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Ul

c.. Q

25 mm .. I I ..
15 mm .. I I .. 1 in
5 I Bin
4 trous a contre-percer au montage 122 mm
4 holes to counterdrill during installation 4 in 13 I 16

3 mm 3 mm
1 I a in 1 I Bin

R = 10 mm --i--+++-1
R = 13 I 32 in R = 4 mm
R =5 I 32 in

6 mm
: 1 I 4 in
!\ Chanfrein 3 x 3 : 52 mm
!~ Chamfer 3 x 3
I 2 in

0
0
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"'::1: 21 I 32 in 1 I Bin 88 mm
3 in 15 I 32
13,6 mm 30 mm
17 /32 in 1 in 13 I 64

Fabrication details
Figure 802
ABAA
Validity : S I N 1 - 9999 Page 804
57-00-00 {CA) JUN 01
SOCATA MAINTENANCE MANUAL
TB20 MODEL

2. PRINCIPLE OF BLANKING OFF A CORE SAMPLE (Table 801 and Figure 806)
NOTE : If the repair area is located between N1 and N2 ribs, install an additional door on the wing
lower surface, between N1 and N2 ribs, forward of the spar. Order Kit OPT1 O 918800.
CAUTION DEPENDING ON THE LOCATION OF THE CORE SAMPLE, THE SKIN THICKNESSES
CAN BE DIFFERENT. REFER TO CHAPTER 51-30-01 TO DETERMINE THE
THICKNESSES OF THE SHEETS TO BE USED.
A. Tools and consumable materials
- AU4G1 2024 sheets, thickness 0.039 and/or 0.047 in (1 and/or 1.2 mm) (for shim and stiffener)
- Alodine (TB 13-002)
- Primer (TB 16-901)

- Finish paint (per aircraft range)

- Sealant (TB 09-001 A)
- Sealant (TB 09-002A)

- Waterproof compound (TB 05-027)

- Drill, dia. 0.13 in (3.3 mm) (No. 30)
- 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm)

- Clamping pins, dia. 1/8 in (3.2 mm)

- Rivets, PI N 5595 7 32 001
- Cleaning agent (TB 11-002)
- Pneumatic vacuum cleaner
- Clean lintfree cloths

B. Procedure
1) Fabricate a shim (17), dia. 0.75 in (19 mm), and a stiffener (16), dia. 2.05 in (52 mm), of the same
thickness as the skin.

2) Mark then, using a drill, dia. 0.13 in (3.3 mm) (No. 30), drill the holes in stiffener (16) - refer to Figure 806,
Section BB.

NOTE : Depending on the position of stiffener (16) with respect to the existing rivets, adapt
stiffener drilling with a minimum pitch of 0.787 in (20 mm).
3) If the axis of the core sample was a rivet, drill the center of shim (17) and stiffener (16) to diameter 0.13 in
(3.3 mm) (No. 30) - refer to Detail D.

4) Position and center stiffener (16) on the core sample area, then turn it correctly to obtain a regular pitch
between the existing rivets and the holes in the stiffener.

5) Counterdrill the skin and the spar to diameter 0.13 in (3.3 mm) (No. 30). Secure with pins as you
progress.

6) Remove stiffener (16). Deburr the holes and vacuum-clean the chips.

7) Using a 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm), countersink the holes in
stiffener ( 16).

ABAA
Validity : S I N 1 - 9999 Page 805
57 -00-00 (CA) JUN 02
 SOCATA MAINTENANCE MANUAL
TB20 MODEL

8) Apply a protection to stiffener (16) and shim (17) - refer to Table 801.
9) Using a cloth moistened with cleaning agent (TB 11-002), clean the spar and the skin around the
aperture.
10) Protect the edge of the skin with Alodine (TB 13-002).
11) Smear shim (17) and stiffener (16) with a coat of sealant (TB 09-001 A) and position them.

12) Cut the rivets to length (refer to Table 801) and install them wet with sealant (TB 09-001A).
13) Apply a bead of sealant (TB 09-002A) to the periphery of stiffener (16).

14) Smear the rivet shanks with sealant (TB 09-001A).

15) Perform paint touch-ups on the rivet heads and the sealant bead.
16) Protect the spar flanges I skins junctions with waterproof compound (TB 05-027).

3. PRINCIPLE OF CORROSION REPAIR ON THE SPAR, FROM N1 RIB TO N4 RIB (Table 801, Figures 803,
804, 805 and 806)
NOTE : If the repair area is located between N1 and N2 ribs, install an additional door on the wing
lower surface, between N1 and N2 ribs, forward of the spar. Order Kit OPT1 O 918800.
CAUTION DEPENDING ON THE LOCATION OF THE REPAIR AREA, THE SKIN THICKNESSES CAN
BE DIFFERENT. REFER TO CHAPTER 51-30-01 TO DETERMINE THE THICKNESSES OF
THE SHEETS TO BE USED.
A. Tools and consumable materials
- AU4G1 2024 sheets, thickness 0.039 or 0.047 and 0.063 in (1 or 1.2 mm and 1.6 mm) (for shim and
stiffener)
- Abrasive cloth (TB 05-916C)
- Activator (TB 05-925)
- Filler Alu (TB 05-911) or
Adhesive (TB 08-909) + Hardener (TB 08-930)
+ 12% Aluminium powder (TB 05-915)
- Alodine (TB 13-002)
- Wash-primer (TB 16-920)
- Primer (TB 16-901)
- Finish paint (per aircraft range)
- Sealant (TB 09-001A)
- Sealant (TB 09-002A)

I - Sealant (TB 09-013A)

- Waterproof compound (TB 05-027)
- Drills, dia. 0.13 in (3.3 mm) (No. 30), 0.15 in (3.7 mm) (No. 26), 0.16 in (4.1 mm) (No. 20) and 0.19 in
(4.9 mm) (No. 10)
- 100° micrometric countersink, with pilots dia. 1/8 in (3.2 mm), 0.157 in (4 mm) and 0.189 in (4.8 mm)

ABAA
Validity : SIN 1 - 9999 Page 806
57-00-00 (CA) SEP04
 SOCATA MAINTENANCE MANUAL
TB 20 MODEL

- Clamping pins, dia. 1/8 in (3.2 mm), 0.142 in (3.6 mm), 0.157 in (4 mm) and 0.189 in (4.8 mm)
- Rivets - refer to Table 801
- Cleaning agent (TB 11-002)
- Pneumatic vacuum cleaner
- Clean lintfree cloths
B. Repair of the spar
1) Once the area to be repaired has been opened, treat the corrosion - refer to 20-00-04.
CAUTION : PREPARATION AND APPLICATION OF FILLER ALU (TB 05-911) MUST
IMPERATIVELY BE CARRIED OUT BY QUALIFIED PERSONNEL.
2) Prepare Filler Alu (TB 05-911).
3) Using a spatula, apply Filler Alu (13) to the area to be repaired.
4) After complete curing, rework the area with abrasive cloth (TB 05-916C).
5) Fabricate a shim (2) or (8) of the same thickness as the skin and with dimensions smaller than the
opening made by 0.039 in (1 mm).
6) Hold the shim centered in its housing and counterdrill the spar holes from inside the wing.
7) Fabricate a stiffener (3) or (9), 0.047 in (1.2 mm) thick. Determine the dimensions according to the
indications below :
a) The stiffener must imperatively be secured to the spar with six existing rivets on both sides of
shim (2) or (8) - refer to Figures 803 and 804.
NOTA : Should the repair area be too close to existing stiffener (1), fabricate a stiffener (11)
or (15) including the shape of existing stiffener (1). In such a case, stiffener (11)
or (15) shall be 0.063 in (1.6 mm) thick - refer to Figures 805 and 806.
b) The stiffener must imperatively be secured to the skin with three rivets on both sides of shim (2)
or (8), forward and aft of the spar.
c) As a general rule, the pitch of the stiffener J skin attaching rivets must be 1.181 in (30 mm) in
staggered rows, and the edge distance 0.394 in (1 O mm).
C. Installation of the stiffener - Repairs A and B
1) Position stiffener (3) or (9), center it carefully and mark its outline on the skin.
2) Remove the stiffener then remove all the rivets within the outline.
3) Position again stiffener (3) or (9), hold it firmly and counterdrill all the spar holes from inside the wing.
Secure with pins as you progress.
4) Mark and drill the stiffener I skin attaching holes forward and aft of the spar.
NOTE : For stiffener (3), refer to Figure 803 ; for stiffener (9), the rivet pitch is 1.181 in (30 mm)
and the edge distance 0.394 in (1 O mm).
5) On stiffener (9), mark and drill hole (7) to dia. 0.13 in (3.3 mm) (No. 30).
6) Enlarge the spar holes to dia. 0.19 in (4.9 mm) (No. 10), and the four N2 rib attachment holes for
stiffener (3) as well.
7) Remove stiffener (3) or (9).

I
ABAA
Validity : SIN 1 - 9999 Page 807
57-00-00 (CA) SEP 04
SOCATA MAINTENANCE MANUAL
TB20 MODEL

8) Pin shim (2) or (8) onto stiffener (3) or (9). Mark and drill the four holes to dia. 0.13 in (3.3 mm) (No. 30).
NOTE : These holes are used to secure the shim to the stiffener with
countersunk/countersunk rivets - refer to Table 801 and Figure 803 or 804.
9) Using a 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm), countersink the holes in shim (2)
or (8) and in stiffener (3) or (9).
1O) Countersink the holes in stiffener (3) or (9) to dia. 1/8 in (3.2 mm) and 0.189 in (4.8 mm) as described in
Figures 803 and 804.

11) Deburr the parts and the holes, vacuum-clean the chips and filings and clean the parts and the area with
a clean cloth moistened with cleaning agent (TB 11-002).
12) Apply a protection to the stiffener and the shim - refer to Table 801.

13) Pin shim (2) or (8) to stiffener (3) or (9) with sealant (TB 09-001 A) in between.

14) Cut to length and install the four countersunk/countersunk rivets - refer to Table 801. Install the rivets
wet with sealant (TB 09-001A).
15) Position the stiffener, equipped with the shim, with sealant (TB 09-001 A) and pin every other hole.
16) Cut to length and install the round head and/or countersunk rivets - refer to Table 801. Install the rivets
wet with sealant (TB 09-001A).

17) Apply a bead of sealant (TB 09-002A) to the periphery of the stiffener and inside the wing along the spar
(on both sides, and only over the repaired length).
18) On the repaired area, smear the spar flanges (extend beyond the edge, on the skin) and the rivet shanks
with sealant (TB 09-001 A).
19) On the non-opened area included between N 1 and N4 ribs, protect the spar flanges/ skins junction with
waterproof compound (TB 05-027).
20) Perform paint touch-ups on the rivet heads and on the sealant seal.
D. Installation of the stiffener - Repairs C and D
1) Remove existing stiffener (1) and thickness shim (4).
2) Counterdrill all the holes of existing stiffener (1) on new stiffener (11) or (15). Counterdrill to the same
diameters, except for holes {14), which are to be counterdrilled to dia. 0.16 in (4.1 mm) No. 20.
3) Pin new stiffener (11) or {15) to the wing and mark its outline on the skin.
4) Remove the stiffener then remove all the rivets within the outline.
5) Position shim (2) or (8) in its housing and pin again stiffener {11) or {15).
Repair C
6) Discard thickness shim (4), insert a sheet 0,039 in (1 mm) thick between stiffener (11) and the skin. Mark
the outline of stiffener (11) on the sheet.

7) Counterdrill all the spar holes from inside the wing. Secure with pins as you progress.

8) Mark and drill the stiffener I skin attaching holes forward and aft of the spar to dia. 0.13 in (3.3 mm)
(No. 30).

ABAA
Validity : S I N 1 - 9999 Page 808
57-00-00 (CA) JUN 02
 SO CATA MAINTENANCE MANUAL
TB 20 MODEL

9) Enlarge the spar holes to dia. 0.19 in (4.9 mm) (No. 10), and the N2 rib attachment hole for stiffener (11)
as well.

Repair C
10) Remove stiffener (11), the sheet and shim (2).
11) Cut the sheet according to the marking to make a thickness shim (12).

12) Pin shim (2) to thickness shim (12), mark and drill the four holes to dia. 0.13 in (3.3 mm) (No. 30).
NOTE : These holes are used to secure the shim to the thickness shim with
countersunk/countersunk rivets - refer to Table 801 and Figure 805.
13) Using a 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm), countersink the holes in shim (2)
and in thickness shim (12).
Repair D

10) Remove stiffener (15), thickness shim (4) and shim (8).
11) Pin shim (8) to stiffener (15), mark and drill the four holes to dia 0.13 in (3.3 mm) (No. 30).
NOTE : These holes are used to secure the shim to the stiffener with
countersunk/countersunk rivets - refer to Table 801 and Figure 806.
12) Using a 100° micrometric countersink, with pilot dia. 1/8 in (3.2 mm), countersink the holes in shim (8)
and in stiffener (15).
All
14) Countersink the holes in stiffener (11) or (15) to dia. 1/8 in (3.2 mm), 0.157 in (4 mm) and 0.189 in
(4.8 mm) as described in Figures 805 and 806.

15) Deburr the parts and the holes, vacuum-clean the chips and filings and clean the parts and the area with
a clean cloth moistened with cleaning agent (TB 11-002).

16) Apply a protection to the stiffener and the shims - refer to Table 801.
17) Pin shim (8) to stiffener (15), or shim (2) to thickness shim (12), depending on the case. Apply
sealant (TB 09-001A) in between.
18) Cut to length and install the four countersunk/countersunk rivets - refer to Table 801. Install the rivets
wet with sealant (TB 09-001A).
19) Position stiffener (15) and shim (8), or stiffener (11), thickness shim (12) and shim (2) with
sealant (TB 09-001A) and pin every other hole.

20) Cut to length and install countersunk and round head rivets - refer to Table 801. Install the rivets wet with
sealant (TB 09-001A).

21) Apply a bead of sealant (TB 09-002A) to the periphery of the stiffener and inside the wing along the spar
(on both sides, and only over the repaired length).
22) On the repaired area, smear the spar flanges (extend beyond the edge, on the skin) and the rivet shanks
I with sealant (TB 09-013A).
23) On the non-opened area included between N1 and N4 ribs, protect the spar flanges Jskins junction with
waterproof compound (TB 05-027).

24) Perform paint touch-ups on the rivet heads and on the sealant seal.

ABAA
Validity : S I N 1 - 9999 Page 809
57 -00-00 (CA) SEP 04
 ~ii; MATERIAL OF STIFFENERS AND -ICI>
g'.{:; DIMENSIONS RADII RIVETS (NOTE 1)
SHIMS mo
I\) 0
~ o~
Part Number (NOTE 2)
(f) Code in mm Code in mm Symbol
Dia. Dia. Characte-
Item
Thick. Thick.
Mat. Cond.
Protec- s::~
0
--z in mm ristics Socata Std Normalized ASNA in mm ti on
c
m
r-
s

* Csk head 5595 6 32 000 2049 DCJ 032 000 2 0.047 1.2 2024 T4 NOTE3
I A 0.019 0.5 0.315 8 0.126 3.2
co
co
co
co
B

c
0.157

0.315
4

8
T

u
0.394

1.968
10

50
*~ 0.126

0.142
3.2

3.6
Csk/Csk

Round
head
5595 6 32 000

5600 7 36 001
2049 DCJ 032 000

2050 DXJ 036 000

3

8
0.047

0.039
1.2

1
2024

2024
T4

T4
NOTE4

NOTE3

F
0.394

0.709
10

18
*• 0.157

0.157
4

4
Csk head

Round
head
5595 7 40 001

5600 7 40 001
2049 DXJ 040 000

2050 DXJ 040 000

9

11
0.047

0.063
1.2

1.6
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2024
T4

T4
NOTE4

NOTE4

01
G

H
0.787

5.787
20

147 * 0.189 4.8 Csk head 5595 7 48 001 2049 DXJ 048 000 12

15

16
0.039

0.063

0.047
1

1.6

1.2
2024

2024

2024
T4

T4

T4
NOTE3

NOTE4

NOTE4

'""
17 0.047 1.2 2024 T4 NOTE3
I s::
0 NOTE 1 : All the rivets described in Table are to be used "as supplied". ~
0 z
NOTE 2 : The rivet part numbers are incomplete, the two digits before the last digit are reserved for length. -I
I E.g.: Socata Std P/N 5595 7 48 001 becomes 5595 7 48 081 for a length of 0.315 in (8 mm). m
0 z
For the same rivet, Normalized ASNA P/N 2049 DXJ 048 000 becomes ASNA 2049 DXJ 048 080. :t>
0 z
NOTE 3: Alodine (TB 13-002) and anti-corrosion primer. 0
£ m
NOTE 4 : Alodine (TB 13-002), anti-corrosion primer and finish paint per aircraft range. s::
""'() :t>
c.... tll
cco Wings - Repair z
z <D
Table 801
c
0 co :t>
I\) ......
0 r-
SOCATA MAINTENANCE MANUAL
TB20 MODEL

1 - Existing stiffener
2 - Shim
3 - Stiffener
4 - Thickness shim

Bord d'attaque
Leading edge
+ N2
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Wings - Repair A
Figure 803
ABAA
Validity SIN 1 - 9999 Page 811
57-00-00 (CA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

1 - Existing stiffener
4 - Thickness shim
7 - Hole
8 - Shim
9 - Stiffener

Bord d'attaque
Leading edge N3
N4

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::!: Wings - Repair B
Figure 804
ABAA
Validity SIN 1 - 9999 Page 812
57 -00-00 (CA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

2 - Shim
c-c 11 - Stiffener
12 - Thickness shim
13 - Filler Alu
A 14 - Hole
2

B
~11

12
13

Bord d'attaque A
Leading edge N3

+ . . ---T - -

14 u-
c
11
12

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Wings - Repair C
Figure 805
ABAA
Validity S/N1-9999 Page 813
57-00-00 (CA) JUN 02
SO CATA MAINTENANCE MANUAL
TB20 MODEL

2 - Shim

3 - Stiffener

4 - Thickness shim
8 - Shim

9 - Stiffener
13 - Filler Alu
14 - Hole
15 - Stiffener

16 - Stiffener
17 - Shim

Wings - Repair D
Key to Figure 806
ABAA
Validity : S I N 1 - 9999 Page 814
57-00-00 (CA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

A-A

15
A 9
3 8-B

8 Ref. longeron
Spar ref.
A

17
13
8 8
2
Bord d'attaque
Leading edge
+ ~16
A

8 R =U

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Wings - Repair D
Figure 806
ABAA
Validity SIN 1 - 9999 Page 815
57 -00-00 (CA) JUN 02
SOCATA MAINTENANCE MANUAL
TB 20 MODEL

PAGE INTENTIONALLY LEFT BLANK

ABAA
Validity : S I N 1 - 9999 Page 816
57 -00-00 (CA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

WINGS

DESCRIPTION AND OPERATION

1. GENERAL
The wings are metal structures, each consisting of a spar, ribs, stiffeners and reinforcement plates. The skin
panels are riveted to these structures.
The wing spar is the main structural component of the wing. It is designed to absorb the structural stresses. The
main spar is machined from an aluminium alloy section.
The L.H. and R.H. spars are spliced by means of plates and bolts.

The landing gear attachment fittings are secured to the wing spar.
The arms fitted with ailerons and those fitted with flaps are secured to rear ribs.
The fuel tanks are an integral part of the wings. They consist of stamped metal ribs attached to the wing skin and
the one-piece spar.
Inspection doors are installed in various areas of the lower and upper surfaces.

Fittings provide wing I fuselage junction.

2. LOCATION (Figures 1 and 2)

COMPONENT QTY AREA ACCESS DOOR REFERENCE

Wing fitting 8 500 I 600 I 57-20-03

Landing gear attachment fitting 8 500 I 600 I 57-20-04

3. DESCRIPTION
A. Wing fittings - refer to 57-20-03
The front attachment fitting secures the wing to frame C1.
The front spacer, attached to the front section of the wing spar, secures the wing to frame C2.
The rear spacer, attached to the rear section of the wing spar, secures the wing to frame C2.
The rear attachment fitting secures the wing to frame C3.

B. Landing gear attachment fittings - refer to 57-20-04

The front bearing assembly, attached to the wing spar, secures the main landing gear.
The rear bearing assembly, attached to the small spar, secures the main landing gear.
The strut bearing, attached to the wing spar, secures the hinged strut.
The actuating cylinder attachment, attached to the wing spar, secures the actuating cylinder.

ADAA
Validity : SIN 1 - 9999 Page 1
57-20-00 (EA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

A - Front attachment fitting

B - Front spacer
C - Rear spacer
D - Rear attachment fitting

A
+

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Wings - Identification and location of components
Figure 1
ADAA
Validity : S I N 1 - 9999 Page 2
57-20-00 {EA} JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

A - Front bearing assembly

B - Rear bearing assembly
C - Strut bearing
D - Actuating cylinder attachment

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Wings - Identification and location of components

Figure 2
ADAA
Validity : SIN 1 - 9999 Page3
57-20-00 (EA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

PAGE INTENTIONALLY LEFT BLANK

ADAA
Validity : SIN 1 - 9999 Page 4
57-20-00 (EA) JUN 02
 SOCATA MAINTENANCE MANUAL
TB20 MODEL

WINGS

REMOVAL I INSTALLATION

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. REMOVAL OF THE ARMS FITTED WITH FLAPS (Figure 401)

A. Tools and consumable materials
- Cleaning agent (TB 11-003)
- Spatula

- Clean lintfree cloths

B. Procedure
1) Remove the flaps - refer to 57-50-00.

2) Remove the inspection doors 512 [612] and 516 [616] - refer to 52-40-00.
3) Disconnect the external gage connector and the electrical wiring of the heated pitot tube, if installed.
4) Check the type of attachment of the arm assemblies (with rivets or bolts).

Attachment with rivets

5) Remove the rivets carefully - refer to 51 -40-02.
6) Remove arm assemblies (1) and (5).

7) Apply a protection treatment to the sections bared during removal - refer to 20-00-04.

NOTE : During installation, replace the rivets with bolts, washers and nuts - refer to the
Illustrated Parts Catalog.
Attachment with bolts
5) Remove and discard nuts (4), remove washers (3) and bolts (2).

6) Remove arm assemblies (1) and (5).

7) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).

2. INSTALLATION OF THE ARMS FITTED WITH FLAPS (Figure 401)

A. Tools and consumable materials
- Sealant (TB 09-916)

I - Petrolatum (TB 04-012)

- Cleaning agent (TB 11-003)
- Clean lintfree cloths

AAAA
Validity: SIN 1 - 9999 Page 401
57-20-00 (BA) SEP 04
 SOCATA MAINTENANCE MANUAL
TB20 MODEL

B. Procedure
1) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of arm assemblies (1) and (5).

I 2) Apply sealant (TB 09-916) to the bearing face of arm assemblies (1) and (5) and to bolts (2) - refer
to 20-00-09.

3) Position arm assemblies (1) and (5) and secure them with bolts (2), washers (3) and new nuts (4).

4) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).

5) Connect the external gage connector and the electrical wiring of the heated pitot tube, if installed.

6) Make sure all the tools and materials are removed and the work area is clean and free from debris.

7) Install the inspection doors 512 [612] and 516 [616] - refer to 52-40-00.

8) Install the flaps - refer to 57-50-00.

3. REMOVAL OF THE ARMS FITTED WITH AILERONS (Figure 401)

A. Tools and consumable materials
- Cleaning agent (TB 11-003)

- Spatula

- Clean lintfree cloths

B. Procedure
1) Remove the ailerons - refer to 57-60-00.
2) Remove the inspection door 516 [616] - refer to 52-40-00.

3) Remove the wing tip - refer to 57-30-00.

4) Disconnect the electrical wiring of stall warning device - refer to 27-30-04.
5) Remove harness holding clips (8) and clear electrical harness (9) to gain access to the work area.
6) Unrivet and remove coverplate (7) - refer to 51-40-02.

7) Check the type of attachment of the arm assemblies (with rivets or bolts).

Attachment with rivets

8) Remove the rivets carefully - refer to 51-40-02.

9) Remove arm assemblies (6) and (10).

10) Apply a protection treatment to the sections bared during removal - refer to 20-00-04.
NOTE : During installation, replace the rivets with bolts, washers and nuts - refer to the
Illustrated Parts Catalog.
Attachment with bolts

8) Remove and discard nuts (13), remove washers (12) and bolts (11 ).
9) Disengage and remove arm assemblies (6) and (10).

10) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).

AAAA
Validity : S I N 1 - 9999 Page 402
57-20-00 (BA) SEP04
 SOCATA MAINTENANCE MANUAL
TB20 MODEL

4. INSTALLATION OF THE ARMS FITTED WITH AILERONS (Figure 401)

A. Tools and consumable materials
- Sealant (TB 09-916)
I - Petrolatum (TB 04-012)
- Cleaning agent (TB 11-003)
- Clean lintfree cloths
- Rivets PIN ZOO.N5536342404
- Rivets PIN ZOO.N5553368406
B. Procedure
1) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of arm assemblies (6) and (10).

I 2) Apply sealant (TB 09-916) to the bearing face of arm assemblies (6) and (1 O) and to bolts (11) - refer
to 20-00-09.
3) Position arm assemblies (6) and (1 O) and secure them with bolts (11), washers (12) and new nuts (13).
4) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).
5) Position coverplate (7) and install rivets - refer to 51-40-02.
6) Perform paint touch-ups - refer to 20-00-03.
7) Position electrical harness (9) and install harness holding clips (8) on coverplate (7).
8) Connect the electrical wiring of stall warning device - voir 27-30-04.
9) Make sure all the tools and materials are removed and the work area is clean and free from debris.
10) Install the wing tip - refer to 57-30-00.
11) Install the inspection door 516 [616] - refer to 52-40-00.
12) Install the ailerons - refer to 57-60-00.

AAAA
Validity : S I N 1 - 9999 Page 403
57-20-00 (BA) SEP04
SOCATA MAINTENANC E MANUAL
TB20 MODEL

1 - Arm assembly
2 _ Bolt
3 _Washer
4 _Nut
Arm assembly
~= Arm assembly
Coverplate .
7 - Harness ho lding clip
8 - SS
9 - Electrical harne
10 - Arm assembly
11 _Bolt
12 _Washer
13 _ Nut

A-A 5

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Validity:
AAAA sIN1- 9999 Page 404
JUN 02
 SOCATA MAINTENANCE MANUAL
TB 20 MODEL

WING FITTINGS

REMOVAL I INSTALLATION

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. REMOVAL OF THE WING FRONT ATTACHMENT (Figure 401)

A. Tools and consumable materials
- 1 padded support for frame CS

- 2 wing padded supports, PIN TB10 99000911

- Cleaning agent (TB 11-003)
- Spatula
- Clean lintfree cloths

B. Procedure
1) Remove the cowling under hull 21 S F.
2) Remove junction fairing 21 ?L [217R].
CAUTION : TO AVOID DAMAGING THE STRUCTURE, THE SUPPORTS MUST PERFECTLY FIT
THE FUSELAGE PROFILE AND HAVE PADDED BEARING AREAS.
3) Install padded supports under the L.H. and R.H. wings at a rib, and under the rear fuselage at frame CS.
4) Remove and discard nut (2), remove washer (1), shim (4) and bolt (5).
5) Remove and discard nuts (9), remove washers (S) and bolts (10).
6) Remove and retain front fitting (3).

7) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).
S) If necessary, check front fitting (3) - refer to Page 601 .

2. INSTALLATION OF THE WING FRONT ATTACHMENT (Figure 401)

A. Tools and consumable materials
- 1 padded support for frame CS
- 2 wing padded supports, PIN TB10 99000911
- Grease (TB 04-004A)

I - Petrolatum (TB 04-012)

- Red paint
- Torque wrench 0 - SS5 lbf.in (0 - 100 N.m)
- Sealant (TB 09-916)
- Cleaning agent (TB 11-003)

ACAA
Validity : S I N 1 - 9999 Page 401
57-20-03 (DA) SEP 04
 SOCATA MAINTENANCE MANUAL
TB 20 MODEL

- Clean lintfree cloths

B. Procedure
1) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of front fitting (3).

I 2) Apply sealant (TB 09-916) to the bearing face of front fitting (3) and to bolts (10) - refer to 20-00-09.
3) Position front fitting (3) on the wing.
CAUTION : OBSERVE THE MOUNTING DIRECTION OF THE FITTING UPPER ATTACHMENTS.

I 4) Secure front fitting (3) with bolts ( 10), washers (8) and new nuts (9). Torque according to "Specific cases"
tightening procedure - refer to 20-00-01.
5) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).
6) Lubricate bolt (5) with grease (TB 04-004A) - refer to 12-21-04.
7) Install shim (4), bolt (5), washer (1) and new nut (2). Torque - refer to 20-00-01.
8) Mark bolts (5) and (1 O) and nuts (2) and (9) with a red paint line.
9) Remove the wing and fuselage padded supports.
1O) Make sure all the tools and materials are removed and the work area is clean and free from debris.
11) Install junction fairing 217L [217R].
12) Install the cowling under hull 218 F.

3. REMOVAL OF THE SPACERS (Figure 402)

A. Tools and consumable materials
- Cleaning agent (TB 11-003)
- Clean lintfree cloths
- Spatula
B. Procedure
1) Remove the wings - refer to 57-00-00.
2) Remove and discard nuts (5), remove washers (4) and bolts (1).
3) Remove front spacer (2) and rear spacer (3).
4) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).
5) Check the spacers for condition and replace them if necessary.

AGAA
Validity : S I N 1 - 9999 Page 402
57-20-03 (DA) SEP 04
SO CATA MAINTENANCE MANUAL
TB 20 MODEL

1 - Washer
2 - Nut
3 - Front fitting
4 - Shim
5 - Bolt
6 - Fitting on frame C1
7 - Fitting on frame C1
8 - Washer
9 - Nut
10 - Bolt

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10

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Wing front attachment - Removal I Installation

Figure 401
AGAA
Validity : SIN 1 - 9999 Page 403
57-20-03 (DA) JUN 02
 SO CATA MAINTENANCE MANUAL
TB 20 MODEL

4. INSTALLATION OF THE SPACERS (Figure 402)

A. Tools and consumable materials
- Sealant (TB 09-916)
- Sealant (TB 09-007)
I - Petrolatum (TB 04-012)
- Torque wrench O - 177 !bf.in (O - 20 N.m)
- Cleaning agent (TB 11-003)
- Clean lintfree cloths
- Red paint
B. Procedure
1) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of front spacer (2) and rear

I spacer (3).
2) Apply sealant (TB 09-916) to bolts (1) and to front spacer (2) and rear spacer (3) bearing faces - refer
to 20-00-09.
CAUTION : OBSERVE THE MOUNTING DIRECTION OF BOLTS (1).

I 3) Install front spacer (2) and rear spacer (3) on spar (6) and secure them with bolts (1), washers (4) and
new nuts (5). Torque according to "Specific cases" tightening procedure - refer to 20-00-01.
4) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).
5) Make a bead of sealant around the spacers with sealant (TB 09-916) - refer to 20-00-09.
6) Mark nuts (5) with a red paint line.
7) Protect the spacers with sealant (TB 09-007) - refer to 20-00-09.
8) Install the wings - refer to 57-00-00.

5. REMOVAL OF WING REAR ATTACHMENT (Figures 403 and 404)

A. Tools and consumable materials
- 1 padded support for frame C7
- 2 wing padded supports, PIN TB10 99000911
- Cleaning agent (TB 11-003)
- Spatula
- Clean lintfree cloths
B. Procedure
S/N 1 - 1736.1742 - 1746 Pre-Kit OPT10 920400
1) Apply Kit OPT10 920400.

AGAA
Validity : S I N 1 - 9999 Page 404
57-20-03 (DA) SEP 04
SOCATA MAINTENANCE MANUAL
TB20 MODEL

1 - Bolt
2 - Front spacer
3 - Rear spacer
4 - Washer
5 - Nut
6 - Spar

0
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Spacer - Removal I Installation
Figure 402
ACAA
Validity : S I N 1 - 9999 Page 405
57-20-03 {DA) JUN 02
 SO CATA MAINTENANCE MANUAL
TB 20 MODEL

S/N 1737 - 1741. 1747 - 9999 and S/N 1 - 1736. 1742 - 1746 Post-Kit OPT10 920400
1) Jack up the aircraft - refer to 07-10-00.
CAUTION : TO AVOID DAMAGING THE STRUCTURE, THE SUPPORTS MUST PERFECTLY FIT
THE FUSELAGE PROFILE AND HAVE PADDED BEARING AREAS.
2) Install padded supports under the L.H. and R.H. wings ata rib, and under the rear fuselage at frame C7.

3) Remove the cowlings under hull 218A and 218F.

4) Remove and discard cotter pins (14) and (19), remove nuts (15) and (20), washers (16) and (21) and
bolt (17).
5) Remove rod (18).
6) Remove and discard cotter pin (10), remove nut (11), washer (12) and bolt (13).
7) Disconnect rod (9).
8) Remove and discard cotter pin (8), remove nut (7) and washer (6).
9) Remove and discard blanking plug (1) and remove bolt (2).
1O) Remove bellcrank (3) [4] and spacer (5).
11) Remove and discard nuts (33) and (37), remove and retain washers (34) and (38), bolts (35) and (39)
and rod (36).
12) Check the type of attachment of the rear fitting (with rivets or bolts).

Attachment with AVDELOCK rivets

13) Remove and discard rivets (42) - refer to 51-40-02.
14) Remove rear fitting (30).
15) Apply a protection treatment to the sections bared during removal - refer to 20-00-04.
NOTE : During installation, replace the rivets with bolts, washers and nuts - refer to the
Illustrated Parts Catalog.
Attachment with bolts
13) Remove and discard nuts (40), remove washers (41) and bolts (43).

14) Remove rear fitting (30).

15) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).

6. INSTALLATION OF WING REAR ATTACHMENT (Figures 403 and 404)

A. Tools and consumable materials
- 1 padded support for frame C7
- 2 wing padded supports, PIN TB10 99000911
- Grease (TB 04-004A)

I - Petrolatum (TB 04-012)

- Red paint

AGAA
Validity : S I N 1 - 9999 Page 406
57-20-03 (DA) SEP04
SOCATA MAINTENANCE MANUAL
TB20 MODEL

- Torque wrench 0 - 177 !bf.in (O - 20 N.m)

- Sealant (TB 09-916)
- Cleaning agent (TB 11-003)
- Clean lintfree cloths
B. Procedure
S/N 1 - 1736. 1742 - 1746 Pre-Kit OPT10 920400
1) Apply Kit OPT10 920400.
S/N 1737 - 1741. 1747 - 9999 and S/N 1 - 1736. 1742 - 1746 Post-Kit OPT10 920400
1) Vacuum-clean any drilling chips from the work area.
2) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of rear fitting (30).

I 3) Apply sealant (TB 09-916) to the bearing face of rear fitting (30) and to bolts (43) - refer to 20-00-09.
4) Position rear fitting (30) on the wing and secure it with bolts (43), washers (41) and new nuts (40).
Torque - refer to 20-00-01.
5) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).
6) Lubricate bolts (35) and (39) with grease (TB 04-004A) - refer to 12-21-04.
7) Secure rod (36) to rear fitting (30) with bolt (39), washer (38) and nut (37). Torque - refer to 20-00-01.
8) Position rod (36) between two half-fittings (31) and (32) and engage bolt (35). Make sure fuselage rear
attachment setting is correct. Set it if necessary - refer to 53-10-01.
9) Install washer (34) and nut (33). Torque - refer to 20-00-01.
10) Mark nuts (33), (37) and (40) with a red paint line.
11) Lubricate spacer (5) with grease (TB 04-004A) - refer to 12-21-04.
12) Insert spacer (5) into bellcrank (3) [4].
13) Position bellcrank (3) [4] and secure it with bolt (2), washer (6) and nut (7). Install a new cotter pin (8).
14) Lubricate bolts (17) and (13) and bolt (22) with grease (TB 04-004A) - refer to 12-21-04.
15) Secure rod (9) to bellcrank (3) [4] with bolt (13), washer (12) and nut (11). Install a new cotter pin (10).
16) Secure rod (18) to bellcrank (3) [4] with bolt (17), washer (16) and nut (15). Install a new cotter pin (14).
17) Secure rod (18) to bolt (22) with washer (21) and nut (20). Install a new cotter pin (19).
18) Make sure all the tools and materials are removed and the work area is clean and free from debris.
19) Install a new blanking plug (1).
20) Check the flaps for correct operation - refer to 57-50-00.
21) Remove the padded supports from the wings and fuselage.
22) Install the cowlings under hull 218A and 218F.
23) Lower the aircraft to ground and remove the jacks - refer to 07-10-00.

ACAA
Validity : S I N 1 - 9999 Page 407
57-20-03 (DA) SEP 04
SOCATA EL MAINTENANC E MANUAL
TB20 MOD

1 _ Blanking plug 13 _Bolt .

2 _ Bolt 14 _ Cotter pm
L H bellcrank 15 _ Nut
3
4 -- R. .H'. bellcrank 16 _Washer
5 _Spacer 17 _Bolt
6 _Washer 18 _ Rod .
7 _Nut . 19 - Cotter pm
8 _ Cotter pm 20 _ Nut
9 _Rod . 21 _Washer
10 _ Cotter pm 22 _Bolt
11 _ Nut
12 _Washer 8--1
@>
2

17

3
[4]

0--5
9

ttachmen t - Remova I I Installation

Wing rear a Figure 403

AGAA
Validity : s I N 1 - 9999 Page 408
57-20-03 (DA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

30 - Rear fitting
31 - Half-fitting
32 - Half-fitting
33 - Nut
34 - Washer
35 - Bolt
36 - Rod
37 - Nut
38 - Washer
39 - Bolt
40 - Nut
41 - Washer
42 - Rivet
43 - Bolt

0
33
0

30
0

34
0 I
I

'' 37

0
Q\ 0

38

B -~::
:JJ
------~

® ~ 30

Wing rear attachment - Removal I Installation

Figure 404
AGAA
Validity : S I N 1 - 9999 Page 409
57-20-03 (DA) JUN 02
SO CATA MAINTENANCE MANUAL
TB20 MODEL

PAGE INTENTIONALLY LEFT BLANK

ACAA
Validity : S I N 1 - 9999 Page 410
57-20-03 (DA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

WING FITTINGS

INSPECTION I CHECK

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. INSPECTION OF THE WING FRONT ATTACHMENT (Figure 601)

A. Tools and consumable materials
- Stripper (TB 12-901) or (TB 12-902)

- Penetrant inspection material (TB 05-905)

- Cleaning agent (TB 11-003)
- Primer

8. Procedure
1) Remove the wing front attachment - refer to Page 401.
2) On fitting (1), check:
- bore (2), dia. 12H8 (+ 27 ; + O microns),
- attachment holes (3) for elongation.
NOTE : If the bore is not correct or if the holes are out-of-round, discard and replace
fitting (1).
3) Perform a dye penetrant inspection - refer to 20-00-14.
NOTE : If a defect is detected on fitting (1), discard and replace fitting (1).
4) Repaint fitting (1) - refer to 20-00-03.
5) Make sure the bolt is free of any marks.
6) Install the wing front attachment - refer to Page 401.

AAAA
Validity : S I N 1 - 9999 Page 601
57-20-03 (BA) JUN 02
SOCATA MAINTENANCE MANUAL
TB20 MODEL

1 - Fitting
2 - Bore
3 - Attachment hole
4 - Clearing hole

0 0

Wing front attachment - Inspection I Check

Figure 601
AAAA
Validity : S I N 1 - 9999 Page 602
57-20-03 (BA) JUN 02
SO CATA MAINTENANCE MANUAL
TB 20 MODEL

LANDING GEAR ATTACHMENT FITTINGS

REMOVAL I INSTALLATION

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. REMOVAL OF THE MAIN LANDING GEAR BEARINGS (Figures 401 and 402)
A. Tools and consumable materials
- Cleaning agent (TB 11-003)
- Clean lintfree cloths
B. Procedure
1) Jack up the aircraft - refer to 07-10-00.
2) Remove the inspection door 511 [611] - refer to 52-40-00.
3) Remove the main landing gear - refer to 32-10-00.
4) Remove and discard cotter pins (34) and (36), remove nuts (35) and (37), washers (33) and (38) and
bolts (31) and (40). Disengage aileron control rod (32) from bellcrank (39) and lever (30).
5) Remove aileron control rod (32).
6) Remove and discard nuts (21), remove washers (20) and bolts (16).
7) Remove bearing assembly (17), counterplate (18) and shim (19).
8) Remove bolts (15) and washers (14) and bearing assembly (13).
9) Clean the surfaces with a clean lintfree cloth moistened with cleaning agent (TB 11-003).

2. INSTALLATION OF THE MAIN LANDING GEAR BEARINGS (Figures 401 and 402)
A. Tools and consumable materials
- Torque wrench 0 - 177 lbf.in (0 - 20 N.m)
- Grease (TB 04-004A)
- Red paint
B. Procedure
CAUTION : POSITION BEARING ASSEMBLY (13) SO AS TO DIRECT GREASE NIPPLE
DOWNWARDS AND TO THE ROOT.
1) Position bearing assembly (13) and secure it with bolts (15) and washers (14). Torque according to
"Specific cases" tightening procedure - refer to 20-00-01.
CAUTION : POSITION BEARING ASSEMBLY (17) SO AS TO DIRECT GREASE NIPPLE
DOWNWARDS AND TO THE ROOT.
2) Position shim (19), counterplate (18) and bearing assembly (17) and secure them with bolts (16),
washers (20) and new nuts (21). Torque according to "Specific cases" tightening procedure - refer
to 20-00-01 .
3) Mark bolts (15) and (16) with a red paint line.

AAAA
Validity : S I N 1 - 9999 Page 401
57-20-04 {BA) JUN 02
 SOCATA MAINTENANCE MANUAL
TB20 MODEL

4) Install aileron control rod (32) on bellcrank (39) and lever (30) with bolts (31) and (40), washers (33) and
(38) and nuts (37) and (35). Install new cotter pins (34) and (36).
5) Install the main landing gear - refer to 32-10-00.
6) Lubricate bearing assemblies (13) and (17) with grease (TB 04-004A) - refer to 12-21-05.
7) Make sure all the tools and materials are removed and the work area is clean and free from debris.
8) Install the inspection door (511) [611].
9) Lower the aircraft to ground and remove the jacks - refer to 07-10-00.

3. REMOVAL OF THE STRUT BEARING (Figure 401)

A. Tools and consumable materials
- Cleaning agent (TB 11-003)
- Spatula
- Clean lintfree cloths
B. Procedure
1) Jack up the aircraft - refer to 07 -10-00.
2) Remove the cowling under hull 218F.
3) Remove the hinged strut of the main landing gear - refer to 32-30-03.
4) Remove bolts (12) and washers (11).
5) Remove and discard nut (2), remove washer (1) and bolt (10).
6) Remove and discard nuts (7), remove washers (8) and bolts (9).

7) Remove strut bearing (22).

8) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).

4. INSTALLATION OF THE STRUT BEARING (Figure 401)

A. Tools and consumable materials
- Torque wrench 0 - 177 !bf.in (0 - 20 N.m)
- Grease (TB 04-004A)
- Sealant (TB 09-916)
I - Petrolatum (TB 04-012)
- Cleaning agent (TB 11 -003)
- Clean lintfree cloths
- Red paint

AAAA
Validity : S I N 1 - 9999 Page 402
57-20-04 (BA) SEP 04
 SOCATA MAINTENANCE MANUAL
TB20 MODEL

B. Procedure
1) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of strut bearing (22).

I 2) Apply sealant (TB 09-916) to the bearing face of strut bearing (22) and to bolts (9), (10) and (12) - refer
to 20-00-09.

I 3) Position strut bearing (22) and secure it with bolts (12) and washers (11 ), bolts (9), washers (8) and new
nuts (7) and with bolt (10), washer (1) and new nut (2). Torque according to "Specific cases" tightening
procedure - refer to 20-00-01.
4) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).
5) Mark bolts (1 O) and (12) and nuts (7) with a red paint line.
6) Install the hinged strut of the main landing gear - refer to 32-30-03.
7) Lubricate strut bearing (22) with grease (TB 04-004A) - refer to 12-21-05.
8) Make sure all the tools and materials are removed and the work area is clean and free from debris.
9) Install the cowling under hull 218F.
10) Lower the aircraft to ground and remove the jacks - refer to 07-10-00.

5. REMOVAL OF THE CYLINDER ATTACHMENT FITTING (Figure 401)

A. Tools and consumable materials
- Cleaning agent (TB 11 -003)
- Spatula
- Clean lintfree cloths
B. Procedure
1) Jack up the aircraft - refer to 07-10-00.
2) Remove the cowling under hull 218F.
3) Remove the actuating cylinder attachment from cylinder attachment fitting (3) - refer to 32-30-01.
4) Disengage the actuating cylinder from cylinder attachment fitting (3).
5) Remove and discard nuts (4), remove washers (5) and bolts (6).
6) Remove cylinder attachment fitting (3).
7) Remove the sealant with a spatula and clean the surfaces with a clean lintfree cloth moistened with
cleaning agent (TB 11-003).

6. INSTALLATION OF THE CYLINDER ATTACHMENT FITTING (Figure 401)

A. Tools and consumable materials
- Torque wrench 0 - 177 !bf.in (0 - 20 N.m)
- Sealant (TB 09-916)
I - Petrolatum (TB 04-012)
- Waterproof compound (TB 05-027)
- Cleaning agent (TB 11-003)
AAAA
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 SOCATA MAINTENANCE MANUAL
TB 20 MODEL

- Clean lintfree cloths

- Red paint
B. Procedure
1) Separate the skin from spar lower surface carefully at cylinder attachment fitting (3).
2) Check the spar for corrosion marks.
3) Spray some waterproof compound (TB 05-027) between the skin and spar.
4) Apply a very thin coat of petrolatum (TB 04-012) to the bearing face of cylinder attachment fitting (3).

I 5) Apply sealant (TB 09-916) to the bearing face of cylinder attachment fitting (3) and bolts (6) - refer
to 20-00-09.

I 6) Position cylinder attachment fitting (3) and secure it with bolts (6), washers (5) and new nuts (4). Torque
according to "Specific cases" tightening procedure - refer to 20-00-01.

I
7) Wipe off excess sealant with a clean lintfree cloth moistened with cleaning agent (TB 11-003).
8) Make a bead of sealant around cylinder attachment fitting (3) with sealant (TB 09-916) - refer
to 20-00-09.
9) Mark nuts (4) with a red paint line.
10) Secure actuating cylinder to cylinder attachment fitting (3) - refer to 32-30-01.
11) Make sure all the tools and materials are removed and the work area is clean and free from debris.
12) Install the cowling under hull 218F.
13) Lower the aircraft to ground and remove the jacks - refer to 07-10-00.

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1 - Washer 12 - Bolt
2 - Nut 13 - Bearing assembly
3 - Cylinder attachment 14 - Washer
fitting 15 - Bolt
4 - Nut 16 - Bolt
5 - Washer 17 - Bearing assembly
6 - Bolt 18 - Counterplate
7 - Nut 19 - Shim
8 - Washer 20 - Washer
9 - Bolt 21 - Nut
10 - Bolt 22 - Strut bearing
11 - Washer

Landing gear attachment fittings - Removal / Installation

Figure 401
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TB20 MODEL

30 - Lever
31 - Bolt
32 - Aileron control rod
33 - Washer
34 - Cotter pin
35 - Nut
36 - Cotter pin
37 - Nut
38 - Washer
39 - Bellcrank
40 - Bolt

30

<
31

Landing gear attachment fittings - Removal I Installation

Figure 402
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TB 20 MODEL

WINGTIPS

DESCRIPTION AND OPERATION

1. GENERAL
The wing tips include the navigation lights, the anti-collision lights and the recognition lights.
The wing tips are secured with screws to the extreme rib of each wing.
The wing tips are made of composite material.

2. LOCATION (Figures 1 and 1A)

COMPONENT QTY AREA ACCESS DOOR REFERENCE

Wing tip 2 500 I 600 I 57-30-00

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A - Wing tip
B - Anti-collision light
C - Navigation light

•c

Wing tips - Identification and location of components

Figure 1 - Pre-MOD. 151
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A - Wing tip
B - Navigation and anti-collision light
C - Recognition light

DS7/DS8 - P1

0
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I'-

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Wing tips - Identification and location of components

Figure 1A - Post-MOD. 151
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WINGTIPS

MAINTENANCE PRACTICES

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. SERVICING
None

2. REMOVAL I INSTALLATION - WING TIP (Figure 201)

A. Tools and consumable materials
- Ground power unit

B. Removal of the wing tip

WARNING : ALLOW FIVE MINUTES AFTER ELECTRICAL POWER SUPPLY CUTOFF TO THE
ANTI-COLLISION LIGHTS BEFORE TOUCHING THE CONNECTORS
1) Make sure that the main switch-breaker is open.

2) Install the warning sign prohibiting main switch-breaker operation.

WARNING

DO NOT OPERATE
MAINTENANCE WORK IN PROGRESS

3) Remove screws (2).

4) Disengage wing tip (3) by clearing it by a few inches.

5) If installed, disconnect navigation light (5) and anti-collision light (4).

6) Remove wing tip (3).

C. Installation of the wing tip

1) Inspect the interfaces for cleanliness and condition.
2) Make sure all the tools and materials are removed and the work area is clean and free from debris.

3) Position wing tip (3) and, if installed, connect navigation light (5) and anti-collision light (4).
4) Position wing tip (3) on wing (1) and install all screws (2). Do not fully tighten.

5) Tighten all screws (2).

6) Remove the warning sign prohibiting main switch-breaker operation.

7) If required, connect the ground power unit - refer to 24-40-00.

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SIN 275 - 425 Post-Kit OPT10 9090/9100
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TB 20 MODEL

8) Perform the following test :

ACTION RESULT

(1) Close main switch-breaker.

(2) Close "NAV. LIGHT" switch-breaker. (a) Navigation lights come on.

(3) Open "NAV. LIGHT" switch-breaker.

(4) If installed, close "STROBE LIGHT" (a) Anti-collision lights operate.

switch-breaker.

(5) Open "STROBE LIGHT" switch-breaker.

(6) Open main switch-breaker.

9) If connected, disconnect the ground power unit - refer to 24-40-00.

3. ADJUSTMENT I TEST
None

4. INSPECTION I CHECK - WING TIP (Figure 201)

A. Tools and consumable materials
None
B. Procedure
1) Visually inspect the wing tip surface for :
- cracks,
dents.
2) Check screws (2) for tightening.
3) If installed, visually inspect navigation lights (5) and anti-collision lights (4) for condition and attachment.

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SIN 1 - 274 Post-Kit OPT10 9094/9500,
SIN 275 - 425 Post-Kit OPT10 9090/9100
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SO CATA MAINTENANCE MANUAL
TB 20 MODEL

1 - Wing
2 - Screw
3 - Wing tip
4 - Anti-collision light
5 - Navigation light

Wing tip - Removal I Installation

Figure 201
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SIN 1 - 274 Post-Kit OPT10 9094/9500,
SIN 275 - 425 Post-Kit OPT10 9090/9100
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Validity : SIN 426 - 9999 Pre-MOD. 151, Page 204
SIN 1 - 274 Post-Kit OPT10 9094/9500,
SIN 275 - 425 Post-Kit OPT10 9090/9100
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SOCATA MAINTENANCE MANUAL
TB 20 MODEL

WING TIPS

MAINTENANCE PRACTICES

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. SERVICING
None

2. REMOVAL I INSTALLATION - WING TIP (Figure 201)

A. Tools and consumable materials
- Ground power unit
B. Removal of the wing tip
WARNING : ALLOW FIVE MINUTES AFTER ELECTRICAL POWER SUPPLY CUTOFF TO THE
ANTI-COLLISION AND NAVIGATION LIGHTS BEFORE TOUCHING THE
CONNECTORS
1) Make sure that the main switch-breaker is open.
2) Install the warning sign prohibiting main switch-breaker operation.

WARNING

DO NOT OPERATE
MAINTENANCE WORK IN PROGRESS

3) Remove screws (2).

4) Disengage wing tip (3) by clearing it by a few inches.
5) Disconnect anti-collision and navigation light (4).
6) If installed, disconnect recognition light (5).
7) Remove wing tip (3).
C. Installation of the wing tip
1) Inspect the interfaces for cleanliness and condition.
2) Make sure all the tools and materials are removed and the work area is clean and free from debris.
3) Position wing tip (3) and connect anti-collision and navigation light (4) and, if installed, recognition
light (5).
4) Position wing tip (3) on wing (1) and install all screws (2). Do not fully tighten.
5) Tighten all screws (2).
6) Remove the warning sign prohibiting main switch-breaker operation.
7) Perform an operational test of the anti-collision and navigation lights (4) and, if installed, recognition
lights (5) - refer to 33-40-02.

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TB 20 MODEL

1 ADJUSTMENT/TEST
None

4. INSPECTION I CHECK - WING TIP (Figure 201)

A. Tools and consumable materials
None
B. Procedure
1) Visually inspect the wing tip surface for :
cracks,
dents.
2) Check screws (2) for tightening.
3) Visually inspect anti-collision and navigation lights (4) and, if installed, recognition lights (5) for
condition and attachment.

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Validity : SIN 1 - 9999 Post-MOD. 151 Page 202
57-30-00 (CA) JUN 01
SO CATA MAINTENANCE MANUAL
TB 20 MODEL

1 - Wing
2 - Screw
3 - Wing tip
4 - Anti-collision and navigation light
5 - Recognition light

DS1 - P1

DS1 - P2t---

DS7/DS8 - P1

Wing tip - Removal I Installation

Figure 201
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FLAPS

DESCRIPTION AND OPERATION

1. GENERAL
The flaps, of metal structure, ensure a lift increase at low speeds during takeoff and landing. These flaps are of
the large span, single-slot type, articulated on two arm assemblies.

I A static discharger is secured to the external trailing edge of each flap.

Extension and retraction, electrically controlled from the cockpit, is ensured by an electric actuator.
The flaps have three main positions :
- Retracted position 0°,

- Takeoff position 10°,

- Landing position 40°.
The control circuit powered by "BUS 1" bar is protected by a circuit breaker located on the L.H. circuit breaker
panel.

2. LOCATION (Figure 1)

COMPONENT QTY AREA ACCESS DOOR REFERENCE

Flap 2 520 57-50-00

620 I

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TB 20 MO

A _Flap

11
ff .
cation an
d location of co mponents 2
Flaps - Iden Figure 1 Page

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Validity: sIN 1- 9999
57-5 0 - 00 (EA) JUN01
SOCATA MAINTENANCE MANUAL
TB 20 MODEL

FLAPS

REMOVAL I INSTALLATION

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. REMOVAL OF ONE FLAP (Figure 401)

A. Tools and consumable materials
- Padded supports

B. Procedure
1) Close main switch-breaker.

CAUTION : MAKE SURE THE FLAP AREA IS CLEAR.

2) Set the flaps to intermediate position.
3) Open main switch-breaker.
4) Install the warning sign prohibiting main switch-breaker operation.

WARNING

DO NOT OPERATE
MAINTENANCE WORK IN PROGRESS

5) Remove cotter pin (5), nut (4) and washer (3). Discard cotter pin (5).

6) Remove bolt (1) and disengage input rod (6) from bell crank (2).

7) Hold the flap and remove cotter pins (7), nuts (8), washers (9) and bolts (1 O). Discard cotter pins (7).

8) Disengage the flap and place it on two padded supports.

2. INSTALLATION OF ONE FLAP (Figure 401)

A. Tools and consumable materials
None

B. Procedure
1) Lubricate hinges and rod end - refer to 12-21-04.
2) Position the flap and secure it to the arm assemblies with bolts (1 O), washers (9) and nuts (8).

3) Install new cotter pins (7).

4) Secure the input rod (6) to bellcrank (2) with bolt (1 ), washer (3) and nut (4). Install a new cotter pin (5).

5) Make sure all the tools and materials are removed and the work area is clean and free from debris.

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6) Close main switch-breaker.

CAUTION : MAKE SURE THE FLAP AREA IS CLEAR.

7) Retract the flaps and check travels - refer to 27-50-00.

8) Remove the warning sign prohibiting main switch-breaker operation.
9) Perform a test flight - refer to 05-30-00.

ABAA
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TB20 MODEL

1 - Bolt
2 - Bellcrank
3 - Washer
4 - Nut
5 - Cotter pin
6 - Input rod
7 - Cotter pin
8 - Nut
9 - Washer
10 - Bolt

0
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N
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<(
<(
<(

~
0
0
"'
....
"'
~
Flaps - Removal I Installation
Figure 401
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TB20 MODEL

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 SOCATA MAINTENANCE MANUAL
TB 20 MODEL

AILERONS

DESCRIPTION AND OPERATION

1. GENERAL
The metal structure ailerons allow aircraft maneuver around the roll axis. They are actuated by the pilot using a
control wheel and an aileron control linkage composed of rods and bellcranks.
I A static discharger is secured to the external trailing edge of each aileron.
With the control wheel fully turned, aileron deflection is as follows :
- Upward 15° ± 1.5,
- Downward 15° ± 1.5.

2. LOCATION (Figure 1)

COMPONENT QTY AREA ACCESS DOOR REFERENCE

Aileron 2 520 57-60-00

620 I

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TB 20 MODEL

A - Aileron
B - Balancing weight

+s

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t
I
I
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I
I
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\ I
I I I

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I I I
I I I

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lo!
I
\ I
I

Ailerons - Identification and location of components

Figure 1
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Validity : S I N 1 - 9999 Page2
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SOCATA MAINTENANCE MANUAL
TB 20 MODEL

AILERONS

REMOVAL I INSTALLATION

NOTE : This procedure is applicable to L.H. and R.H. installations. Information specific to R.H.
installation are given in square brackets.

1. REMOVAL OF THE AILERON (Figure 401)

A. Tools and consumable materials
- Padded supports
B. Procedure
1) Remove the tip - refer to 57-30-00.

2) Close main switch-breaker.

CAUTION : MAKE SURE THE FLAP AREA IS CLEAR.
3) Extend the flaps.
4) Open main switch-breaker.
5) Remove stop screw (3) and washer (2).
6) Remove bolt (5), spacer (9) and disengage input rod (7).
7) Hold the aileron and remove bolts (4) and (10), lockplates (6), washers (8) and spacers (1). Discard
lockplates (6).

NOTE : Disengage the bonding strap, if installed.

8) Disengage the aileron and place it on two padded supports.

2. INSTALLATION OF THE AILERON (Figure 401)

A. Tools and consumable materials
None
B. Procedure
NOTE : In case of repair, painting or addition of an option to the aileron, check aileron balancing -
refer to 51-60-00.
1) Lubricate hinges and rod end - refer to 12-21-04.
2) Position the aileron and secure it with bolts (4) and (1 O), new lockplates (6), washers (8) and spacers (1 ).
NOTE : Secure the bonding strap, if installed. Perform the bonding procedure - refer
to 20-00-12.

3) Secure input rod (7) to the aileron with bolt (5) and spacer (9).
4) Lock bolts (4), (5) and (10) with lockplates (6).

5) Install stop screw (3) and washer (2).

6) Make sure all the tools and materials are removed and the work area is clean and free from debris.

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7) Close main switch-breaker.

CAUTION : MAKE SURE THE FLAP AREA IS CLEAR.

8) Retract the flaps.
9) Open main switch-breaker.
10) Install the tip - refer to 57-30-00.
11) Check the roll control - refer to 27-10-00.
12) Perform a test flight - refer to 05-30-00.

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TB20 MODEL

1 - Spacer
2 - Washer
3 - Stop screw
4 - Bolt
5 - Bolt
6 - Lockplate
7 - Input rod
8 - Washer
9 - Spacer
10 - Bolt

... B

Ailerons - Removal I Installation

Figure 401
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TB20 MODEL

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