SOCATASAS 

Direction des Services 

65921 TARBES CEDEX 9 

FRANCE 

t: DAHER-SOCATA 

TELEPHONE : 33 (0)5 62.41.73.00 

TELEFAX: 33 (0)5 62.41.76.54 

1

..... 1 _s_E_RV_I_C_E_B_U_L_LE_T_IN ____ I 

TB AIRCRAFT 

AMENDMENT 1 ATA No. 

SB 10-152 55 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

I 

HORIZONTAL STABILIZERS ON WHICH ORIGINAL SB HAS ALREADY BEEN APPLIED ARE NOT 

CONCERNED BY FIRST APPLICATION OF THIS SERVICE BULLETIN 

REFERENCE MODIFICATION No. MOD10-0230-55- REPAIR SHEET No. 20-116 

I 

SUBJECT HORIZONTAL STABILIZER INTERNAL STRUCTURE 

EFFECTIVITY 

PURPOSE 

All TB aircraft 

A. PROBLEM 

Field reports of corrosion on horizontal stabilizer spar that could result in buckling and 

permanent horizontal stabilizer distortion and consequently a lower controllability of the 

airplane. 

B. REASON 

Humidity accumulation on aircraft subject to severe environmental conditions. 

C. SOLUTION 

Implementation of a regular inspection of the area. 

Implementation of a repair solution, if necessary. 

PURPOSE OF THE REVISION 1 : 

- To modify SB classification 

- To modify paragraphs A. PROBLEM and C. SOLUTION 

- To modify paragraph APPLICATION 

- To add 3 repair solutions 

SUMMARY 

A. CREATION OF INSPECTION HOLES 

B. INSPECTION 

C. MEASUREMENT OF CORRODED AREA 

D. TYPE 1 REPAIR 

E. TYPE 2 REPAIR 

F. TYPE 3 REPAIR 

G. RECONDITIONING 

MAY 13 Page 1 I 19 

Arndt. 1 -APR 15 
I 

TB AIRCRAFT 

I I SB 10-152 55 SERVICE BULLETIN REVISION 1 ATA No. 

APPLICATION: 

1 st application : 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

During the next scheduled inspection and at the latest, 1 year and 1 month after the Service 

Bulletin issuance reference date. I WARRANTY 

Further applications (except Paragraph '1\'') : 

This inspection must be repeated every 6 years. 

- None 

PROCURABLE MATERIAL : 

MAY 13 

- Kit No. OPT10K152-01 to be ordered from yourTBspare parts distributor ifType 1 repair 

is applied 

Item Part number Description Qty/aircraft 

25 5521667504 Rivet 25 

81 5536342402 Rivet 80 

82 5529565405 Rivet 60 

83 5536342404 Rivet 8 

84 5536342406 Rivet 30 

85/87 5521668502 Rivet 45 

86 5528340232 Rivet 0.010 kg 

- Kit No. OPT1 OK152-02 to be ordered from your TB spare parts distributor if Type 2 repair 

is applied 

Item Part number Description Oty /aircraft 

28/30 5528371416 Rivet 0.050 kg 

29 5521668502 Rivet 10 

31 5529565405 Rivet 15 

31 5521668402 Rivet 10 

32/36/83 5536342404 Rivet 25 

61 TB109606710100 Short doubler 1 

81 5536342402 Rivet 80 

82 5529565405 Rivet 60 

84 5536342406 Rivet 33 

85/87 5521668502 Rivet 45 

86 5528340232 Rivet 0.010 kg 

I 5521667505 Rivet 10 

I 5548340253 Rivet 0.10 kg 

Page 2/19 

Arndt. 1 -APR 15 
I TB AIRCRAFT 

I SB 10-152 55 SERVICE BULLETIN REVISION 1 ATA No. 

MAY 13 

Item Part number 

I 5431218060 

I 5553368406 

I 5521667504 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

Description Qtylaircraft 

Ecrou a river 3 

Rivet 3 

Rivet 12 

- Kit No. OPT1 OK152 -03 to be ordered from your TB spare parts distributor if Type 3 repair 

is applied 

Item Part number Description Qtylaircraft 

28130 5528371416 Rivet 0.050 kg 

29 5521668502 Rivet 10 

31 5529565405 Rivet 15 

31 5521668402 Rivet 10 

32136183 5536342404 Rivet 30 

71 TB109606710000 Long doubler 1 

74 TB109606710300 Angle bracket 1 

75 TB109606710200 Angle bracket 1 

72 TB109606710400 Rib root 1 

72 TB109606710500 Rib root 1 

73 TB109606710800 Washer 6 

81 5536342402 Rivet 80 

82 5529565405 Rivet 60 

84 5536342406 Rivet 33 

85187 5521668502 Rivet 45 

86 5528340232 Rivet 0.010 kg 

I 5528371314 Rivet 0.015 kg 

I 5548340253 Rivet 0.050 kg 

I 5521667505 Rivet 30 

I 5521667504 Rivet 6 

I 5521674403 Rivet 5 

I 5521348507 Rivet 3 

I 5528658506 Rivet 3 

I 5431218060 Anchor nut 11 

I 5553368406 Rivet 3 

NOTE: 

The contents of the kits is given for your information and will not be updated. 

Page 3 I 19 

Arndt. 1 -APR 15 
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TB AIRCRAFT 

I SERVICE BULLETIN I SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

CONSUMABLE MATERIAL or OTHER PRODUCTS (Local purchase) : 

- Alodine 1200 (Mil-C- 5541) or wash - primer 

TOOLS 

MANPOWER 

- Epoxy Primer 

- Finish paint 

- 2 grommets DKK 8/14/18-3 or equivalent 

- Clean cloths 

- Methyl - Ethyl - Ketone (M.E.K) 

- Adhesive HYSOL EA9394 

- Anti corrosion Wadis 24 (MIL- C-161730) or equivalent 

- Sealant PR 1782 C2 

- Standard aeronautical maintenance station tools 

- Counterbore dia. suitable with endoscope dimensions 

- Pneumatic vacuum cleaner 

- Endoscope 

- 1 aeronautical mechanic : 

repair type 1 : 15 hours 

repari type 2 : 30 hours 

repair type 3 : 38 hours 

- 1 helper (partially) 

TECHNICAL INCIDENCES : 

- If no corrosion is detected or Type 1 repair is applied : None 

- If Type 2 repair is applied : 

Weight: 0.0551bs (+ 0.025 kg) 

Arm : 217.56 in (5526 mm) 

Electrical consumption : not applicable 

- If Type 3 repair is applied : 

Weight : 0.373 lbs ( + 0.169 kg) 

Arm : 217.56 in (5526 mm) 

Electrical consumption : not applicable 

DESCRIPTION OF ACCOMPLISHMENT INSTRUCTIONS : 

NOTE: 

The kit installation must be accompUshed by persons authorized by their Airworthiness 

Authorities and according to the procedure described hereafter. 

MAY 13 Page 4 I 19 

Arndt. 1 -APR 15 
I 

I 

TB AIRCRAFT 

I SB 10-152 55 SERVICE BULLETIN REVISION 1 ATA No. 

MAY 13 

NOTE : 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

Any removed anchor nut must be replaced by a new one and reinstalled at the same location 

as before, with rivet PIN 5548340253, 5536342406 and 5553368406. 

A. CREATION OF INSPECTION HOLES - see Figure 1 

1) On the bottom surface, drill the 2 inspection holes (1) to dia. 118" (3.2 mm) 

2) Bore to a diameter suitable with the endoscope dimensions, the 2 inspection 

holes (1) and the 2 drainage holes (2) using a counterbore with its associated guide 

pin 0.62 in. max (16 mm max). Deburr. 

3) Vacuum chips and clean area with a clean cloth moistened with M.E.K. 

4) Protect bare metal with Alodine 1200 or wash- primer, primer and finish paint. 

B. INSPECTION - see Figure 1 

1) Insert the endoscope through the 4 holes to check corrosion on the spar. 

2) If the inspection does not reveal corroded area, spray Wadis 24 on the spar to protect 

it, plug the two inspection holes with grommets and refer to Paragraph UPDATING 

OF THE AIRCRAFT !DOCUMENTATION. 

3) If the inspection reveals a corroded area, refer to Paragraph C. 

C. MEASUREMENT OF CORRODED AREA - see Figures 2, 3, 4 and 5 

1} Remove tail cone - refer to Chapter 53-20- 04 of the Maintenance Manual. 

2) Remove horizontal stabilizer - refer to Chapter 55- 20-01 of the Maintenance 

Manual. 

3) Remove upper surface rivets as indicated on Figure 2 or Figure 3 - refer to Chapter 

51-40- 00 of the Maintenance Manual. 

NOTE: 

In order not to damage the horizontal stabilizer during removal of rivets, maintain it on 

a table using straps. 

CAUTION 

TAKE CARE NOT TO DAMAGE THE UPPER SURFACE SKIN 

4) Using an appropriate means, keep the upper surface skin open. 

CAUTION 

IF SPAR WEB (21) AND SPAR FLANGE (22) ARE AFFECTED BY CORROSION, 

HORIZONTAL STABILIZER MUST BE REPLACED BEFORE NEXT FLIGHT - REFER 

TO CHAPTER 55-20- 01 OF THE MAINTENANCE MANUAL. 

IF SPAR WEB (21) IS AFFECTED BY CORROSION AND SPAR FLANGE (22) IS NOT, 

CONTACT DAHER (*). 

IF CORRODED AREA "Y" IS NOT COMPRISED BETWEEN - 14.37 1N (- 365 MM) 

AND 14.37 IN (365 MM), HORIZONTAL STABILIZER MUST BE REPLACED BEFORE 

NEXT FLIGHT- REFER TO CHAPTER 55-20-01 OF THE MAINTENANCE MANUAL. 

Page 5 I 19 

Amdt. 1 -APR 15 
I 

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TB AIRCRAFT 

SERVICE BULLETIN I SB 10-152 55 

REVISION 1 ATA No. 

5) 

6) 

7) 

8) 

9) 

MANDATORY 

The technical content of this document is. approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

(*) 

DAHER - Direction des Services 

Aeroport Tarbes- Lourdes-Pyrenees 

65921 TARBES Cedex 9 

FRANCE 

Phone : +33 (0)5 62 41 76 59 

Fax : + 33 (0)5 62 41 76 54 

e-mail : support@daher.com 

or for the Americas : 

DAHER 

601 NE 10th St. 

Pompano Beach, FL 33060 

USA 

Phone: + 1 (954) 366 3331 

Remove rivets (25). 

Measure Y min and Y max positions of the corroded area. 

Remove corrosion - refer to Chapter 20- 00-04 of the Maintenance Manual. 

Measure the minimum remaining thickness (51). 

Apply the procedure according to the table hereunder : 

CORRODED AREA AIRCRAFT TYPE ON THE SPAR FLANGE (22) 

GEOMETRICAL CHARACTERISTICS 

T : minimum remaining Y : Y max and Y min TB09 TB20 TB10 thickness (51) positions of the corroded TB200 TB21 

area 

TYPE OF REPAIR 

T > 0.11 in (2.8 mm) AND 

Type 2 repair - 3.54 in (- 90 mm) < Y < 3.54 in (90 mm) Apply Parag. E. 

Type 1 repair 

0.098 in (2.5 mm) < T < 0.11 in (2.8 mm) OR Apply Parag. D. Type 3 repair 

-14.37 in(- 365 mm) < Y < 14.37 in (365 mm) Apply Parag. F. 

0.087 in (2,2 mm) < T < 0.098 in (2,5 mm) AND Type 3 repair 

-14.37 in(- 365 mm) < Y < 14.37 in (365 mm) Apply Parag. F. 

T <0.087 in (2,2 mm) Replace horizontal stabilizer 

0. TYPE 1 REPAIR - see Figures 4 and 5 

1) In compliance with Figure 5, eliminate sharp edges on corroded area. 

2) lnspectthe corroded area to check absence of cracks - refer to Chapter 20- 00- 14 

of the Maintenance Manual. 

MAY 13 Page 6/19 

Arndt. 1 -APR 15 
I TB AIRCRAFT I SB 10-152 55 SERVICE BULLETIN REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

3) Vacuum working area. 

4) Protect bare metal with Alodine 1200 and epoxy primer. 

5) Prepare a compound with adhesive Hysol 9394. 

6} Fill and level corroded area with adhesive Hysol9394. If necessary, insert shim (52). 

7) Remove excess adhesive. 

8) Allow adhesive to cure for 24 hours at an ambienttemperature between 59° and 68° F 

(15 and 20°C}. 

9) Install rivets (25) - refer to Chapter 51- 40- 00 of the Maintenance Manual. 

10) Reconditioning - refer to Paragraph G. 

E. TYPE 2 REPAIR - see Figures 4, 5 and 6 

MAY 13 

Arndt. 1 -APR 15 

1) Remove rivets (28), (29) and (30) -refer to Chapter 51-40-00 of the Maintenance 

Manual. 

2) Locate and remove levers (27). 

3) Pin 100% of upper surface skin. 

4) Return horizontal stabilizer. 

5) On lower surface skin, remove rivets (31} and (32}. 

6) Return horizontal stabilizer. 

7) Locate and remove ribs (26) and (24). 

8} In compliance with Figure 5, eliminate sharp edges on corroded area. 

9) Inspect the corroded area to check absence of cracks - refer to Chapter 20-00-14 

of the Maintenance Manual. 

10) From the spar flange (22), using a drill suitable with the diameter of removed rivet, 

backdrill existing hole on short doubler (61). 

11) Vacuum working area. 

12) Protect bare metal with Alodine 1200 and epoxy primer. 

13) Prepare a compound with adhesive Hysol 9394. 

14) Fill and level corroded area with adhesive Hysol9394. If necessary, insert shim (52). 

15) Remove excess adhesive. 

16) Allow adhesive to cure for 24 hours at an ambient temperature between 59° and 68° F 

(15 and 20°C}. 

CAUTION 

BEFORE INSTALLING SHORT DOUBLER (61) ON SPAR FLANGE (22), CONTROL 

THE REPAIRED AREA FLATNESS 

17) Install short doubler (61) on spar flange (22) with sealant PR 1782 C2 and rivets 

P/N 5521667505 - refer to Chapter 51 - 40-00 of the Maintenance Manual. 

18) On both sides of short doubler (61), install rivets P/N 5521667504 on spar flange (22). 

Page 7 I 19 
I TB AIRCRAFT 

I SB 10-152 55 SERVICE BULLETIN REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

19) Install rib (24) on rib (23) web and on rib (26) web with rivets (29) P/N 5521668502. 

20) Install rib (26) on lower surface skin with rivets (31} P/N 5529565405 and 

P/N 5521668402. 

21) Install rib (24) on lower surface skin with rivets (32) P/N 5536342404. 

22) Install rib (26) on spar web (21} with rivets (30) P/N 5521660503. 

23) Install levers (27} on rib (26) web with rivets (28) P/N 5528371416. 

24) Install rivets (36) P/N 5536342404 

25) Reconditioning -refer to Paragraph G. 

F. TYPE 3 REPAIR - see Figures 4, 5 and 7 

MAY 13 

Amdt. 1 -APR 15 

1) Remove rivets (28), (29) and (30) - refer to Chapter 51 -40-00 of the Maintenance 

Manual. 

2) Remove and retain lever (27). 

3) Pin 100% of upper surface skin. 

4) Turn over horizontal stabilizer. 

5) On lower surface skin, remove rivets (31), (32) and (34). 

6) Turn over horizontal stabilizer. 

7) Identify and remove ribs (26) and rib (24). 

8) Remove rivets (35). 

9) Identify and remove ribs {23). 

1 0) On table, remove and discard angle brackets (33) 

11) In compliance with Figure 5, eliminate sharp edges on corroded area. 

12) Inspect the corroded area to check absence of cracks- refer to Chapter 51 - 40- 00 

of the Maintenance Manual 

13) From the spar flange (22) and using a drill suitable with the diameter of removed rivet, 

backdrill existing holes on long doubler (71). 

14) Vacuum working area. 

15) Protect bare metal with Alodine 1200 and epoxy primer. 

16) Prepare a compound with adhesive Hysol9394. 

17) Fill and level corroded area with adhesive Hysol9394.1fnecessary, insert a shim (52). 

18) Remove excess adhesive. 

19) Allow adhesive to cure for 24 hours at an ambient temperature between 59° and 68° F 

{15 and 20°C}. 

CAUTION 

BEFORE INSTALLING LONG DOUBLER (71) ON SPAR FLANGE (22), CONTROL THE 

REPAIRED AREA FLATNESS 

20) Install long doubler (71) on spar flange (22) with sealant PR 1782 C2 and rivets 

P/N 5521667505 and P/N 5521667504 - refer to Chapter 51-40- 00 of the 

Maintenance Manual. 

Page 8 I 19 
I 

I 

TB AIRCRAFT I I SB 10-152 55 SERVICE BULLETIN REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DCA No. EASA.21J.013 

is the subject of an AD 

21) According to Figure 7, cut rib (23). 

22) Apply Alodine 1200 and epoxy primer on rib (23) bare end. 

23) Pin rib (23) on the spar web (21) and on the lower surface skin. 

24) From the rib (23) web and using a drill suitable with the diameter of removed rivet, 

backdrill existing ho'les on angle brackets (74), (75) and rib root (72). 

25) Assemble rib (23), angle brackets (74), (75) and rib root (72) on a table with rivets 

P/N 5528371314. 

26) Install the assembly on spar web (21) with rivets P/N 5548340253. 

27) From the spar web (21) and using a drill suitable with the diameter of removed rivet, 

back drill existing holes and lower surface skin holes on angle brackets (7 4), (75) and 

rib root (72). 

28) Install the assembly on lower surface skin with washers (73), and rivets 

P/N 5521674403. 

29) Install the assembly on spar flange (22) with washers (73) rivets P/N 5528658506 and 

P/N 5521348507. 

30) Install rib (24) on rib (23) web and on rib (26) web with rivets (29) P/N 5521668502. 

31) Install rib (26) on lower surface with rivets (31) P/N 5529565405and P/N5521668402. 

32) Install rib (24) on lower surface skin with rivets {32) P/N 5536342404. 

33) Install rib (26) on spar web (21) with rivets (30) P/N 5521660503. 

34) Install lever (27) on rib (26) web with rivets (28) P/N 5528371416. 

35) Install rivets (36) P/N 5536342404. 

36) Reconditioning - refer to Paragraph G. 

G. RECONDITIONING - see Figures 8 and 9 

1) In compliance with Figure 8 or 9, install upper surface skin rivets. 

NOTE : 

Check horizontal stabilizer balancing - refer to Chapter 51-60-00 of the 

Maintenance Manual. 

2) Install horizontal stabilizer- refer to Chapter 55-20-01 ofthe Maintenance Manual. 

3) Install tail cone - refer to Chapter 53-20-00 of the Maintenance Manual. 

CAUTION 

DO NOT PLUG THE DRAINAGE HOLES 

4) Plug the 2 inspection holes with grommets. 

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

from debris. 

UPDATING OF THE AIRCRAFT DOCUMENTATION : 

MAY 13 

Upon completion of Service Bulletin No. SB 10- 152-55, Revision 1 (Reference 

MOD10-0230-55) "HORIZONTAL STABILIZER INTERNAL STRUCTURE", make an 

appropriate maintenance record entry. 

If Paragraphs D, E. or F. have been applied, upon completion of Repair Sheet No. 20-116, 

make an appropriate maintenance record entry. 

Page 9 I 19 

Arndt. 1 -APR 15 
I SERVICE BULLETIN I TB AIRCRAFT 

SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 I WARNING 

is the subject of an AD 

SOCATA considers that it is MANDATORY for operators to comply with the instructions of 

this SB. 

Operators who arbitrarily ignore the compliance statement indicated in this SB do so at their 

own risk. 

MAY13 Page 10/19 

Arndt. 1 - APR 15 
I SERVICE BULLETIN 

Vue de dessous 

Bottom view 

0 

;, 

·l:I I j 

I I 

I I ,, 

2 

.,.. 

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193 

r; 

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I TB AIRCRAFT 

SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

0 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

1 - Inspection hole 

307 

;; 

~i 

2 - Drainage hole 

3- Spar 

3 

"' I 

I 

I 

I 

I 

I 

I 

I 

I 

I 

I Il l! o : I 

! • ! 

i:C>:;::::: :;;:-;c;;;::lr.J.--------"'\\ 

Zone a inspecter 

Area to be inspected 

Figure 1 - Inspection of horizontal stabilizer internal structure 

I MAY 13 

Arndt. 1 - APR 15 

Page 11 I 19 
I SERVICE BULLETIN 

TB AIRCRAFT I SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

11 - Upper surface skin 

12 - Area of rivets to be removed 

Figure 2- TB9- TB10- TB200 Area of rivets to be removed on upper surface skin 

MAY 13 Page 12/19 

Amdt. 1 -APR 15 
I SERVICE BULLETIN 

TB AIRCRAFT I SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

11 - Upper surface skin 

12 - Area of rivets to be removed 

Figure 3 - TB20 - TB21 Area of rivets to be removed on upper surface skin 

MAY13 Page 131 19 

Arndt. 1 -APR 15 
I SERVICE BULLETIN I TB AIRCRAFT 

SB 10-152 55 

REVISION 1 ATANo. 

MANDATORY 

MAY 13 

Amdt. 1 -APR 15 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

28 

27 

Figure 4 - Removal of ribs 

is the subject of an AD 

21 - Spar web 

22 - Spar flange 

23- Rib 

24- Rib 

25- Rivet 

26- Rib 

27 - Lever 

28- Rivet 

29- Rivet 

30- Rivet 

31 - Rivet 

32- Rivet 

33 - Angle bracket 

34- Rivet 

35- Rivet 

36- Rivet 

23 

Page 14 I 19 
TB AIRCRAFT 

I SERVICE BULLETIN I SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

22 

0,4 mm Max 

0.016 in Max 

MAY 13 

Arndt. 1 -APR 15 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

22 - Spar flange 

51 - Remaining minimum thickness 

52- Shim 

Selon Axe longitudinal du longeron 

According to spar longitudinal axis 

51 

----------······----·····-·-· ·-·----·--·-·w ----;y-L? .... £. 2 1 ~ 

20e I Zone corrodee I 20e 

Corroded area 

Y Min YO Y Max 

Figure 5 - Preparation of corroded area 

0,4 mm Max 

0.016 in Max 

51 

Page 15 I 19 
TBAIRCRAFT -

I SB 10-152 ~~. ~ I l SERVICE BULLETIN REVISION~ANDATORY _:::..:..:.. __________ ::: f this document is approved 

MAY 13 

Arndt. 1 _APR 15 

The technical content~ EASA.21J.013 

under the authority of DOA No. . f AD 

27 . 

Figure 6 - Type 2 repatr 

is the subject o an 

22 _ Spar flange 

23 - Rib 

24- Rib 

26- Rib 

27 _ Lever 

28- Rivet 

33 _ Angle bracket 

61 _ Short doubler 

~A 

~ 

23 

Page 16 I 19 
I SERVICE BULLETIN I TB AIRCRAFT 

SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

~A 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

22 - Spar flange 

23- Rib 

24- Rib 

26- Rib 

27- Lever 

28- Rivet 

71 - Long doubler 

72- Rib root 

73- Washer 

7 4 - Angle bracket 

75 - Angle bracket 

~~~~~~0~~ 

0 0 .m~o : 4mm --~~~~~~~~==~~~==~ ~. 2~m ~----~-=0. 16 ~ 

MAY13 

Arndt. 1 -APR 15 

- = :=\, o~~ "'I 

I.. 76 mm • 

' ' 

28~ ,fl 

Figure 7 - Type 3 repair 

3 in 

23 

Page 17 I 19 
TBAIRCRAFT I SERVICE BULLETIN I SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

11 - Upper surface skin 

81- ~ Rivet 

82- 4.) Rivet 

83- ~ Rivet 

84- 0 Rivet 

85- 69 Rivet 

86 -

-Rivet 

Figure 8- TB9- TB10- TB200 Installation of rivets on upper surface skin 

MAY 13 Page 18 I 19 

Arndt. 1 -APR 15 
TB AIRCRAFT I SERVICE BULLETIN I SB 10-152 55 

REVISION 1 ATA No. 

MANDATORY 

MAY 13 

Arndt. 1 -APR 15 

The technical content of this document is approved 

under the authority of DOA No. EASA.21J.013 

is the subject of an AD 

11 - Upper surface skin 

81- ~Rivet 

82- 4) Rivet 

83- ~Rivet 

84- 0 Rivet 

85- @ Rivet 

86- -Rivet 

87 - t.ZJ Rivet 

Figure 9- TB20- TB21 Installation of rivets on upper surface skin 

Page 19 I 19