TextOCR
This text is OCR from a scan. OCR can misread letters and numbers.
Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = 'fc34ff6998e1f92da31e11dbfb91c742c107a7b091779d59e9be13204e5f0cee' ORDER BY p.page"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = 'fc34ff6998e1f92da31e11dbfb91c742c107a7b091779d59e9be13204e5f0cee' ORDER BY p.page
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
A DAHER-SOCATA
SOCATA SAS Direction des Services TELEPHONE: 33 (0)5 62.41.73.00 65921 TARBES CEDEX 9 TELEFAX: 33 (0)5 62.41.76.54 FRANCE
TB AIRCRAFT SERVICE BULLETIN SB 10-152 AMENDMENT 1 55 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
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 SUBJECT: HORIZONTAL STABILIZER INTERNAL STRUCTURE EFFECTIVITY: All TB aircraft
PURPOSE 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 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10 - 152 REVISION 1 55 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 APPLICATION:
1st application :
During the next scheduled inspection and at the latest, 1 year and 1 month after the Service Bulletin issuance reference date.
Further applications (except Paragraph "A"):
This inspection must be repeated every 6 years.
WARRANTY
- None PROCURABLE MATERIAL:
- Kit No. OPT10K152-01 to be ordered from your TB spare parts distributor if Type 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. OPT10K152-02 to be ordered from your TB spare parts distributor if Type 2 repair is applied Item Part number Description Qty/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 5521667505 Rivet 10 5548340253 Rivet 0.10 kg MAY 13 Page 2 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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 Item Part number Description Qty/aircraft 5431218060 Ecrou à river 3 5553368406 Rivet 5521667504 Rivet 12
- Kit No. OPT 10K152-03 to be ordered from your TB spare parts distributor if Type 3 repair is applied Item Part number Description Qty/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 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 85/87 5521668502 Rivet 45 86 5528340232 Rivet 0.010 kg 5528371314 Rivet 0.015 kg 5548340253 Rivet 0.050 kg 5521667505 Rivet 30 5521667504 Rivet 6 5521674403 Rivet 5 5521348507 Rivet 3 5528658506 Rivet 3 5431218060 Anchor nut 11 5553368406 Rivet NOTE :
The contents of the kits is given for your information and will not be updated.
MAY 13 Page 3 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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
- 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-16173D) or equivalent
- Sealant PR 1782 C2 TOOLS
- Standard aeronautical maintenance station tools
- Counterbore dia. suitable with endoscope dimensions
- Pneumatic vacuum cleaner
- Endoscope
MANPOWER
- 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 : 0.055 lbs (+ 0.025 kg)
• Arm : 217.56 in (5526 mm)
• Electrical consumption: not applicable
- If Type 3 repair is applied :
• Weight : 0.373 bs (+ 0.169 kg)
• Arm : 217.56 in (5526 mm)
• Electrical consumption: not applicable DESCRIPTION OF ACCOMPLISHMENT INSTRUCTIONS:
NOTE :
The kit installation must be accomplished by persons authorized by their Airworthiness Authorities and according to the procedure described hereafter.
MAY 13 Page 4 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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 NOTE :
Any removed anchor nut must be replaced by a new one and reinstalled at the same location as before, with rivet P/N 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. 1/8" (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 IN (- 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.
MAY 13 Page 5 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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 (*) DAHER - Direction des Services Aeroport Tarbes-Lourdes - Pyrénées 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
5) Remove rivets (25).
6) Measure Y min and Y max positions of the corroded area.
7) Remove corrosion - refer to Chapter 20-00-04 of the Maintenance Manual.
8) Measure the minimum remaining thickness (51).
9) Apply the procedure according to the table hereunder :
ON THE SPAR FLANGE (22) CORRODED AREA AIRCRAFT TYPE
GEOMETRICAL CHARACTERISTICS T: minimum remaining Y: Y max and Y min TB09 TB20 thickness (51) positions of the corroded TB200 TB10 TB21
TYPE OF REPAIR T ≥ 0.11 in (2.8 mm) AND
- 3.54 in (- 90 mm) ≤ Y ≤ 3.54 in (90 mm) Type 2 repair 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 D. TYPE 1 REPAIR - see Figures 4 and 5
1) In compliance with Figure 5, eliminate sharp edges on corroded area.
2) Inspect the corroded area to check absence of cracks - refer to Chapter 20-00-14 of the Maintenance Manual.
MAY 13 Page 6 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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 Hysol 9394. If necessary, insert shim (52).
7) Remove excess adhesive.
8) Allow adhesive to cure for 24 hours at an ambient temperature 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
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 Hysol 9394. 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).
MAY 13 Page 7 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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
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) Identity and remove ribs (23).
10) 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 Hysol 9394.
17) Fill and level corroded area with adhesive Hysol 9394. If necessary, 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.
MAY 13 Page 8 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10 - 152 REVISION 1 55 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
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 holes 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, backdrill existing holes and lower surface skin holes on angle brackets (74), (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 5529565405 and P/N 5521668402.
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 of the 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:
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.
MAY 13 Page 9 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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 WARNING 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.
MAY 13 Page 10 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10-152 REVISION 1 55 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 1 - Inspection hole 2 - Drainage hole 3 - Spar Vue de dessous Bottom view _307 14552001AAADYZ4600 Zone à inspecter Area to be inspected Figure 1 - Inspection of horizontal stabilizer internal structure MAY 13 Page 11 / 19 Amdt. 1 - APR 15
TB AIRCRAFT SERVICE BULLETIN SB 10 - 152 REVISION 1 55 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 12 - I4552001AAADYZ14600 Figure 2 - TB9 - TB10 - TB200 Area of rivets to be removed on upper surface skin MAY 13 Page 12 / 19 Amdt. 1 - APR 15