SOCATASAS Direction des Services 6592 1 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.2 1 J.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 appl i cation : 

# 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 Desc ription Qty/airc raft 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 0.0 10 kg

- Kit No . OPT1 OK152-02 to be ordered f rom your TB spare parts distributor 

### ifType 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 5536342 404 Rivet 25 61 TB109606710100 Short double r 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 5 548340253 Rivet 0.10 kg Page 2/19 Arndt. 1 -APR 15

# I TB AIRCRAFT 

# I SB 10-152 55 

# SERVICE BULL ETIN REVISION 1 ATA No.

MAY 13 I tem Part number 

### I 5431218060 

### I 5553368406 

### I 5521667504 

## MANDATORY The technical conten t of this document is approved under the authorit y of DOA No. EASA.21J .013 is the subject of an AD Desc r iption Qtylaircraft Ecrou 

# a river 3 Rivet 3 Rivet 12

- Kit No. OPT 1 OK 1 52 -03 to be ordered fro m your TB spare parts distri b utor 

### ifType 3 repair is ap p lied I tem Part number Description Qtyla i rcraft 28130 5528371416 Rivet 0 .050 kg

29 5521668502 Rivet 10 31 5529565405 Rivet 15 31 5521668402 Rivet 10 32 1 36183 5536342404 Rivet 30 7 1 T B 1 09606710000 Long double r 1 74 TB 1 09606710300 Angle bracket 1 75 T B 1 09606710200 Angle bracket 1 72 TB 1 096067 1 0400 Rib root 1 72 TB 1 09606710500 Rib root 1 73 T B 1 096067 1 0800 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 552837 1 314 Rivet 0. 015 kg 

### I 5548340253 Rivet 0 .050 kg 

### I 5521667505 Rivet 30 

### I 5521667504 Rivet 6 

### I 552 1 674403 Rivet 5 

### I 5521348507 Rivet 3 

### I 5528658506 Rivet 3 

### I 5431218060 Anchor nut 11 

### I 5553368406 Rivet 3 NOTE: The contents ofthe kits 

### is given for your information and 

### will not be updated . Page 3 

### I 19 Arn d t. 1 -APR 15

## I I 

# •



# I 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 subj ect of an AD CONSUMABLE MATER I AL or OTHER PRODUCTS (Loca l purchase) :

- Alodine 1200 (Mil-C- 5541) or wash - prime r

TOOLS

MANPOWER - Epoxy Prime r

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

- Clean cloths

- Me t hyl - Ethyl - Ketone (M.E.K)

- Adhesive HYSOL EA9394

- Anti corrosion Wadis 24 (MI L - 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 mechan i c : repair type 1 : 15 hours repari type 2 : 30 hou rs repair type 3 : 38 ho u rs

- 1 helper (partially) TECHNICAL INCIDENCES :

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

- If Type 2 repa i r 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) Electrica l consumpt ion : not applicable DESCRIPTION OF ACCOMPLISHMENT INSTRUCTIONS : NOTE: The kit insta llation must be accompUshed by persons authorized by their Airworthiness Authorities and according to the procedure described hereafter. M AY 13 Page 4 

### I 19 A rndt. 1 -APR 15

# I I TB AIRCRAFT 

# I SB 10-152 55 

# SERVICE BULLETIN REVI S I ON 1 ATA No.



### MAY 13 NOTE : 

## MANDATORY The technical content of this docu ment is approved under the authority of DOA No. EASA.21J . 013 is the subject of an AD Any removed anchornut must be replaced by

### a new one and reinstalled at the same location as before, with rivet 

### PIN 5548340253, 5536342406 and 5553368406 . 

### A. CREA TI ON OF IN SPECT ION 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 d iameter suitab le with the endoscope d im ensions , the 2 i nspection holes (1) and the 2 drainage holes (2) using a counterbore with its associated guide pin 0.62 i n . max (16 mm max). Deburr. 3) Vacuum chips and clean area with a c lean cloth moistened with M.E. K . 4) Protect ba re meta l with Alod i ne 1 200 or wash - p rim er , primer and finish paint. B . INSPECTION - see Fig ure 1 1) Insert the endoscope through the 4 holes to check corrosion on the spar. 2) If the ins p ection does n ot reveal corroded area, spray Wadis 24 on the spar to p rotect it, plug th e two i nspection holes with grommets and refer to Paragraph UPDATING OF THE AIRCRAFT !DOCUMENTATION. 3) If the i nspection reveals a corroded area, refer to Paragraph C . C. MEASUREM ENT OF CORRODED AREA - see Fi gures 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) Re m ove upper surface rivets as i ndicated on Figu re 2 or Figure 3 - refer to Chapter 51-40 - 00 of the Maintenance Manual. NOTE: In ordernot to damage the horizontal stabilizer during removal ofr ivets, maintain it on a table using straps. 

### CAUTI ON TAKE CARE NOT TO DAMAGE TH E UPPER SURFACE SKIN 4) Using an appropriate means , keep the upper surface skin open . CAUTION IF SPAR WE B (21) AND SPAR FLANG E (22) ARE AFFECTED BY CORROS I ON , HORI ZONTAL STAB ILIZER MUST BE REPLACED BEFORE NEXT FLIGHT - REFER TO C HAPTER 55-20 - 01 OF THE M A INTENANCE MAN UAL. IF S PAR WEB (21) I S A FFECTED BY CO RR OS I ON A N D S PAR FLANGE (22) I S NOT, CO NT ACT DAHER 

### ( *). IF CORRODED AREA " Y" I S NOT CO M PRISED BETWEEN - 14.37 1N ( - 365 MM) AND 14.37 IN (365 MM), HORI ZO NTAL STAB ILI ZER MU ST BE REPLACED BEFORE NEXT FLIGHT- REFER T O C HAPTER 55-20-01 OF THE MAINTENANCE MANUAL. Page 5 

### I 19 Amdt. 1 -APR 1 5

# I I

I 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 - Direct ion des Services Aeroport T arbes - Lourdes-Py ren ees 6592 1 TARBES Cedex 9 FRANC E Phone : +33 (0)5 62 41 76 59 Fax : + 33 (0)5 62 41 76 54 e-mail : support@daher
.com or for the Ame ri cas : DAHER 601 NE 10th St. Pompano Beach, FL 33060 USA Phone: + 1 (954) 366 3331 Remove rivets (25). Measure Y min and Y max pos iti ons ofthe corroded area . Remove cor ros ion - refer to Chapter 20 - 00 -04 of the Maintenance Manual. Measure the min i mum remaining thickness (51). Apply the p rocedure according to the table hereunder : CORRODED AREA AIRCRAFT TYPE ON T HE SPAR FLANGE (22) GEOMETRICAL CHARACTERISTICS T : min imu m remaining Y : Y max and Y min TB09 TB20 TB10 th i ckness (51) positi ons 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 i n (2 .8 mm) OR App ly 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. TYP E 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 app roved 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 w ith adhesive Hysol9394. If necessary, i nsert shim (52) . 7) Remove excess adhes ive . 8) Allow adhes ive to cure for 24 hours at an ambi enttemperature between 59° and 68° F (15 and 20° C}. 9) Install rivets (25) - refer to Chapter 5 1 - 40 - 00 of the Maintenance Manual. 10) Recond itioning - refer to Paragraph G . 

### E. TYPE 2 REPA I R - see Figures 4, 5 and 6

MAY 13 Arn dt. 1 -APR 15 1) Remove rivets (28), (29) and (30) -refer to Chapter 51-40-00 of the Maintenance Manual. 2) Locate and remove l eve rs (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 s tabilize r. 7) Locate and remove ribs (26) and (24) . 8} In compl i ance with Figure 5 , elim i nate sharp edges on corroded area . 9) Inspect the corroded area to check ab sence of cracks - refer to Chapter 20 -00 -14 of the Maintenance Manual. 10

) From the spar fl ange (22), usi ng a drill su itable 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 . 1 4) Fill and level corroded area with adhes ive Hysol9394. If necessa ry, in sert s him (52). 1 5) Remove excess adhesive. 16

) Allow adhesiveto cu re for 24 hours at an a m bienttemperature between 59° and 68° F ( 15 and 20°C} . CAUTION BEFORE INSTALLING SHORT DO U BLE R (6 1) O N SPAR FLANGE (22), CONTROL THE REPAI RED AREA FLATNESS 17) I nstall s hort double r (6 1 ) on spar flange (22) with sea l ant PR 1 782 C2 and rivets P/N 552 1 667505 - 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 fl ange (22). Page 7 

### I 1 9

# I TB AI RCRAFT 

# I SB 10-152 55 

# SERV I C E 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 ri b (23) web and on rib (26 ) web w i th 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 ri b (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) Recond itioning -refer to Paragraph G . 

### F. TYPE 3 REPAIR - see Fi gures 4 , 5 and 7

MAY 13 Amdt. 1 -APR 15 1) Remove rivets (28), (29) and (30) - refer t o Chapter 51 -40-00 of the Mai ntenance Manual. 2) Remove an d retain lever (27). 3) Pin 100% of upper surface ski n. 4) Turn over horizontal stabilizer. 5) On lower su rface s ki n, r emove rivets (31), (32) and (34). 6) Turn over horizontal stabilize r. 7) I dentify and remove ribs (26) and rib (24) . 8) Remove rivets (35) . 9) I dentify and remove ribs {23). 1 0) On table, remove and discard angle brackets (33) 11) I n compliance with Figure 5 , eliminate sharp edges on corroded area . 12) Inspec t t he corroded area to check absence of c racks- refer to Chapte r 51 - 40 - 00 of the Maintenance Manual 1 3) Fr om the spar flange (22) and us i ng a d rill suitable with the d iameter of removed rivet, backdrill existing holes on long doubler (71). 14) Vacu u m working area. 15) Protect b are metal with Alodine 1200 and epoxy primer . 16) Prepare a compou nd with adhesive Hysol9394. 17) Fill a nd l evel corroded area with adhesive Hysol9394 . 1fnecessary, insert a s him (52) . 18) Remove excess adhes ive. 19) Allow adhesive to cu re for 24 hours at an amb ientt emperatu re between 59° and 68° F {15 and 20°C}. CAUTI O N BEFORE INSTALLING LONG DOUB L ER (7 1 ) ON SPAR FLANGE 

### (22), CONTROL THE REPAI RED AREA FLATNESS 

### 20) Install long doubler (71) on spar flange (22) wit h sealant PR 1782 C2 a nd rivets P/N 5521667505 and P / N 552 1 667504 - refer to Chapte r 51-40 - 00 of the Maintenance Manual. Page 8 

### I 19

# I I TB A I RCRAFT 

# I 

# I SB 10-152 55 

# SERVICE BULLETIN REVISION 1 ATA No . 

## MANDA TORY 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 r ib (23) . 22) Apply Alodine 1200 and epoxy primer on rib (23) bare end . 23) Pi n rib (23) on the spar web (21) and on the lowe r surface skin. 24) From the rib (23) web and using a drill suitable with the diameter of removed r ivet, 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) In stall 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 , backd rill existing holes and lower surface skin holes on angle brackets (74), (75) and rib root (72). 28) I nstall the assembly on lowe r surface ski n with washers (73), an d rivets P

/N 552 1 674403. 29) I nstall the assembly on spar flange (22) with washers (73) rivets P/N 5528658506 and P/N 552 1 348507 . 30) Install rib (24) on rib (23) web and on rib (26) web with rivets (29) P /N 5521668502 . 31) Install rib (26) on l ower surface with rivets (31) P/N 5529565405and P/N5521668402 . 32) Install ri b (24) on lower s urface skin with rivets {32) P/N 5536342404 . 33) Install ri b (26) on spar web (21) with rivets (30) P/N 552 1 660503 . 34) Install lever (27) on rib (26) web with rivets (28) P/N 5528371416 . 35) In stall ri vets (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 Maint en

ance Manual. 2) Install ho rizonta l sta bilizer- refer to Chapter 55-20-01 ofthe Maintenance Manual. 3) Install ta il cone - ref er to Chapter 53-20-00 of the Mai ntenance Manual. CAUTI ON DO NOT PLUG THE DRA INAGE HOLES 4) Plug the 2 inspection holes with grommets. 5) Make sure all the tools and materia ls are removed and the work area is clean and free from debris. UPDATIN G OF THE AIRCRAFT DOCUMENTATI ON :

MAY 13 Upon completion of Service Bulletin No . SB 10 - 152-55, Revision 1 (Reference MOD 10-0230-55) "HORIZONTAL STABILIZER IN TERNAL STRUCTURE", make an appropriate maintenance record entry. If Paragraphs D, E . o r 

### F. have been applied , upon compl etion of Repa i r 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 REVISI ON 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 subj ect of an AD SOCATA considers that it is MANDA TORY fo r operators to comply with the instructions of this SB. Operators who arbitrarily ignore the compl iance statement i ndicated 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

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# · l:j I I I I I I 

## , , 2



### .,.. I I I

I I I 193



### r; I I

0 

# I TB AIRCRAFT 

# SB 10-152 55 REVI S I ON 1 ATA No. 

# MANDA TORY 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 I 

# Il l ! o : ! • ! 

### i:C >:;::::: :;;:-;c;;;:: lr .J.
---

----- "'\\

Zone 

## a in spect er 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 T he technical content of this document is approved unde r 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 - Ang le bracket 34- Rivet 35- Rivet 36- Rivet

23



### Page 1 4 

### 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 1 5 The techn ical content of this document is approved under the authority of DOA No. EASA .2 1 J .0 1 3 is the subject of an AD 22 - Spar flange 51 - Remain i ng minimum thickness 52- Shim 

### Selon Axe lo ngitudinal du longeron According to spar longitudinal axis

5 1



# - ---------······- - --·····-·-· ·-·----·--·-·w ----;y -

# L? ....£. 2 1**~** 20e 

# I Zone co rrod ee 

# I 20e Corroded area



### Y Min 

## YO Y Max

Figu re 5 - Preparation of corroded area 0 ,4 mm Max 

### 0.016 in Max

51



### Page 15 

### I 19

### TBAIRCRAFT



## - 

# I SB 10-152

# ~~**. ~**  

# I SERVICE BULLETIN

# REVISION~ANDATORY l _:::..:..:..__________::: f th is 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 BULL ETI N 

# I TB AIRCRAFT 

# SB 10-152 55 REVISION 1 ATA No. 

# MANDATORY**~A** The techn ical content of this document is approved under the authority of DOA No. EASA.21J . 013 is th e 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 A TA No. 

# MANDATORY The techn ical 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 Installat ion of rivets on upper surface ski n MAY 13 Page 18 

### I 19 Arndt. 1 -A PR 15

# TB AIRCRAFT 

# I SERVICE BULLETIN 

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## 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-**~Rive t**  

### 82- 4) 

### Rivet 83-**~R ivet**  

### 84- 

## 0 Rivet 85- @ Rivet 86- -Rivet 87 - 

## t.ZJ Rivet

Figu re 9- TB20- TB21 Installation of rivets on upper surface sk in Page 19 

### I 19