# Daher Mandatory Service Bulletin 70-104: Revision 4

- Rights: © Socata. Filed by the FAA in regulations.gov docket FAA-2025-2265; AD 2025-26-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Daher Mandatory Service Bulletin 70-104](https://openairdocs.org/service-documents/daher/sb-70-104.md)
- Title as filed: EADS SOCATA TBM Aircraft Mandatory Service Bulletin No. SB 70-104_ Amendment 2_dated January 2007
- Pages: 10
- PDF: https://openairdocs.org/files/sha256/6f/cd/6fcd1f9065cf55808cdfd525bae971dc6044e1814d1194e83e2cab64ce5f593a
- Page: https://openairdocs.org/service-documents/daher/sb-70-104/file/6fcd1f9065cf

## Text

This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1 (OCR)

EADS
SOCATA
EADS SOCATA
Direction des Services  TELEPHONE: 33 (0)5 62.41.73.00
65921 TARBES CEDEX 9  TELEFAX: 33 (0)5 62.41.76.54
FRANCE  TELEX :  532 835 F
TBM AIRCRAFT
SERVICE BULLETIN  SB 70 - 104  AMENDMENT 2  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  : The content of this SB will be incorporated in next revision of Chapter 05 of the
Maintenance Manual which date will be later than MAR 06. Its application will then be
cancelled when revised Chapter 05 is published.
SUBJECT  : INSPECTION OF THE VERTICAL STABILIZER ATTACHMENT FITTINGS
EFFECTIVITY : TBM 700 aircraft S/N 1 to 308, plus S/N 310.
NOTE :
From aircraft S/N 297, the modification No. MOD70-127-55 is applied at the factory.
From aircraft S/N 311, plus S/N 309, the modification No. MOD70-129-53 is applied at the
tactory.
REASON
A. PROBLEM
Cracks on a vertical stabilizer attachment fitting.
B. REASON
Corrosion on the vertical stabilizer attachment fittings.
C. SOLUTION
Inspection of the fittings and bolts and protection reinforcement.
REASON OF AMENDMENT 1 :
Closing of effectivity and addition of Note.
REASON OF AMENDMENT 2 :
Addition of new Part Numbers for expandable bolts and of associated procedure related to
Modification No. MOD 70-0205-55.
Addition of the possibility to use an equivalent process for crack detection.
SUMMARY
A. INSPECTION OF THE FITTINGS AND BOLTS
B. PROTECTION REINFORCEMENT
COMPLIANCE:  During the next 600-hrs scheduled inspection, then every 1200 hrs or every 2 annual
inspections.
JUN 03  Page 1 / 8
Amdt. 2 - JAN 07

### Page 2 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  AMENDMENT 2  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
PROCURABLE MATERIAL :
- Parts to be ordered, if necessary from your TBM spare parts distributor.
Item  Part number  Description  Qty/aircraft
Pre-MOD 70-0205-55  Expandable bolt assy (rear)  2
Z0O.N7018814671
After  stock  depletion,
replaced by
Post-MOD 70-0205-55
Z0O.N7022810298
6  Pre-MOD 70-0205-55  Expandable bolt assy (front)  2
Z0O.N7018814661
After  stock  depletion,
replaced by
Post-MOD 70-0205-55
Z00.N7022810299
After  stock  depletion,
replaced by
2  All  Cotter pin  2
Z00.N5787461153
10  Z00.N5787461151  Cotter pin  2
The difference between Pre-MOD 70-0205-55 and Post-MOD 70-0205-55 bolts is
identified on details A and B of Figure 1.
CONSUMABLE MATERIAL (Local purchase) :
- Stepladder 5 ft (1.50 m)
- Mastinox 6856KD (MIL-P-8116 D)
WADIS 24 (MIL-C-16173 D grade 3) or LPS 3 (DA-4-653-40) or ARDROX 3140
(MIL -C- 16173 D grade 2)
TOOLING
- Standard aeronautical maintenance station tools
- Torque wrench 0 - 90 Ibf.in (0 - 10 N.m)
MANPOWER
- 1 aeronautical mechanic : 3.50 hrs
TECHNICAL INCIDENCES :
- None
JUN 03  Page 2 / 8
Amdt. 2 - JAN 07

### Page 3 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  AMENDMENT 2  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
ACCOMPLISHMENT INSTRUCTIONS :
Operations required in this Service Bulletin must be accomplished by persons authorized by
their Airworthiness Authorities and according to the procedure described hereafter.
A. INSPECTION OF THE FITTINGS AND BOLTS - see Figures 1, 2 and 3
1) Position the stepladder at the front of the vertical stabilizer.
2) Open access panel 311 and remove the dorsal fin - refer to Chapter 55-30-00 of
the Maintenance Manual.
3) Remove and discard cotter pins (2) and (10). Loosen nuts (3) and (9), but do not
remove them.
4) On the L.H. side then on the R.H. side of the front fitting, perform the following
operations :
Pre-MOD 70-0205-55 - see Figure 1, Detail A
a) Remove nut (9), washer (8) and spring washers (7).
b) Remove expandable bolt (6).
Post-MOD 70-0205-55 - see Figure 1, Detail B
a) Remove nut (9), washer (8).
b) Remove expandable bolt (6).
CAUTION
MIXING BETWEEN BOLTS INSTALLED ON L.H. OR R.H. SIDE IS PROHIBITED.
MIXING BETWEEN BOLTS INSTALLED AT THE FRONT OR AT THE REAR IS
PERMITTED
c) Inspect the removed parts. The parts which do not meet the criteria as below will
be replaced and returned to SOCATA for analysis :
- bolt body, no corrosion mark,
- bolt head, nut, washer and spring washers (if installed), light pittings
accepted.
d) Check for corrosion on the fitting.
e) Apply a thin coat of Mastinox 6856KD (MIL-P-8116 D) on expandable bolt (6).
Pre-MOD 70-0205-55 - see Figure 1, Detail A
f) In compliance with Figure 2, install expandable bolt (6), spring washers (7),
washer (8) and nut (9). Do not tighten.
Post-MOD 70-0205-55 - see Figure 1, Detail B
f) In compliance with Figure 3, install expandable bolt (6), washer (8) and nut (9).
Do not tighten.
JUN 03  Page 3 / 8
Amdt. 2 - JAN 07

### Page 4 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  AMENDMENT 2  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
5) On the L.H. side then on the R.H. side of the rear fitting, perform the following
operations :
Pre-MOD 70-0205-55 - see Figure 1, Detail A
a) Remove nut (3), washer (4) and spring washers (5).
b) Remove expandable bolt (1).
Post-MOD 70-0205-55 - see Figure 1, Detail B
a) Remove nut (3) and washer (4).
b) Remove expandable bolt (1).
c)  Inspect the removed parts. The parts which do not meet the criteria as below will
be replaced and returned to SOCATA for analysis :
- bolt body, no corrosion mark,
bolt head, nut, washer and spring washers (if installed), light pittings
accepted.
d)  Check for corrosion on the fitting.
e)  Perform a crack detection by penetrant inspection - refer to Chapter 20-50-01
of the Maintenance Manual, or any other equivalent process (Eddy current...) on
the bores of the vertical stabilizer fitting and attachments.
f) Apply a thin coat of Mastinox 6856KD (MIL-P-8116 D) on expandable bolt (1).
Pre-MOD 70-0205-55 - see Figure 1, Detail A
In compliance with Figure 2, install expandable bolt (1), spring washers (5),
washer (4) and nut (3). Do not tighten.
NOTE :
It is possible to reinstall the bolt with head directed to the exterior in order to torque
the bolt easier.
Post-MOD 70-0205-55 - see Figure 1, Detail B
In compliance with Figure 3, install expandable bolt (1), washer (4) and nut (3).
Do not tighten.
NOTE :
It is possible to reinstall the bolt with head directed to the exterior in order to torque
the bolt easier.
6) If exfoliation corrosion is detected, transmit a report with photos or drawings to
SOCATA so that a repair solution is worked out.
7) If pitting corrosion is detected, refer to Chapter 20-40-01 of the Maintenance
Manual.
8) Using a torque wrench, torque nuts (3) to 62 - 71 Ibf.in (7 - 8 N.m).
9) If necessary, screw to align the notches of nuts (3) with the first pin hole.
JUN 03  Page 4 / 8
Amdt. 2 - JAN 07

### Page 5 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  AMENDMENT 2  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
With bolt replacement
10) Safety with new cotter pin (2) supplied with bolt.
Without bolt replacement
10) Safety with new cotter pin (2), P/N Z00.N5787461153.
All
11) Using a torque wrench, torque nuts (9) to 53 Ibf. in (6 N.m).
12)  If necessary, screw to align the notches of nuts (9) with the first pin hole.
With bolt replacement
13) Safety with new cotter pin (10) supplied with bolt.
Without bolt replacement
13) Safety with new cotter pin (10), P/N Z00.N5787461151.
All
14) Perform protection reinforcement - refer to Paragraph B.
B. PROTECTION REINFORCEMENT
1) Apply a coat of WADIS 24 (MIL-C- 16173 D grade 3) or LPS 3 (DA-4-653-40) or
ARDROX 3140 (MIL-C-16173 D grade 2) on the front and rear fitting parts and on
the bolts and washers.
2)  After application of this SB, please return the enclosed form to SOCATA at the
indicated address.
UPDATING OF THE AIRCRAFT DOCUMENTATION:
Upon completion of Service Bulletin No. SB 70-104-55, Amendment 2 "INSPECTION OF
THE VERTICAL STABILIZER ATTACHMENT FITTINGS", make an appropriate maintenance
record entry.
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.
JUN 03  Page 5 / 8
Amdt. 2 - JAN 07

### Page 6 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  55
AMENDMENT 2  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
Avant MOD 70 - 0205 - 55
Pre - MOD 70 - 0205 - 55
Après MOD 70 - 0205 - 55
Post - MOD 70 - 0205 - 55
I4553000AAABMA24600
Figure 1 - Identification of bolts
JUN 03  Page 6 / 8
Amdt. 2 - JAN 07

### Page 7 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  AMENDMENT 2  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 - Expandable bolt
2 - Cotter pin
3 - Nut
4 - Washer
5 - Spring washer
6 - Expandable bolt
7 - Spring washer
8 - Washer
9 - Nut
10 - Cotter pin
I4553000AAABMA4601  00
10
Figure 2 - Inspection of fittings and bolts
Pre-MOD 70-0205-55
JUN 03  Page 7 / 8
Amdt. 2 - JAN 07

### Page 8 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-104  AMENDMENT 2  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 - Expandable bolt
2 - Cotter pin
3 - Nut
4 - Washer
6 - Expandable bolt
8 - Washer
9 - Nut
10 - Cotter pin
4
3
I4553000AAABMA14600  - 10
Figure 3 - Inspection of fittings and bolts
Post-MOD 70-0205-55
JUN 03  Page 8 / 8
Amdt. 2 - JAN 07

### Page 9 (OCR)

EADS
SOCATA
FORM TO BE FILLED AFTER COMPLIANCE WITH SERVICE BULLETIN
TBM AIRCRAFT
SERVICE BULLETIN  SB 70 - 104  55
AMENDMENT 2  ATA No.
INSPECTION OF THE VERTICAL STABILIZER ATTACHMENT FITTINGS
I, the undersigned,  certify
that service bulletin No. SB 70-104-55 Amendment 2 has been complied with on aircraft
Front fitting  Rear fitting
Corrosion on fitting  L.H.  R.H  L.H. I  R.H.
Bolt and/or washer corrosion  L.H  R.H  L.H  R.H
Crack on fitting  L.H  R.H  L.H  R.H
1. Aircraft
Type  Serial No.  Registered
Flight hours  Number of landings
2. Owner
Name  Phone :  Fax
Address
E-mail :
3. User (if different from owner)
Name  Phone :  Fax
Address
E-mail :
4. Service center
Name :  Phone :  Fax :
Address
E-mail :
Approval No.
5. Remarks
DATE :  SIGNED :
To be returned to SOCATA at the following address :
EADS SOCATA
Direction des Services
65921 TARBES CEDEX 9  Fax : 33 (0)5 62 41 76 54
FRANCE  Telex : 532 835 F

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