# Daher Mandatory Service Bulletin 70-080: No revision named

- Rights: © Socata. Filed by the FAA in regulations.gov docket FAA-2014-0031; AD 2014-09-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Daher Mandatory Service Bulletin 70-080](https://openairdocs.org/service-documents/daher/sb-70-080.md)
- Title as filed: U.S. DOT/FAA - DAHER-SOCATA - SB70-080-55-R03[1]
- Pages: 8
- PDF: https://openairdocs.org/files/sha256/3d/e5/3de5696fb0721d1a2a3cafa7dcc31bc719ce90d374ca4e20cc782e06b7f71ce3
- Page: https://openairdocs.org/service-documents/daher/sb-70-080/file/3de5696fb072

## Text

Some pages are 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

Page 1 / 8MAY 00
A m d t . 3 --- S E P 1 3
APPLICATION OF THIS SERVICE BULLETIN CANCELS AND REPLACES ALERT SB No. SB 70 - - - 077 - - - 55
REFERENCE : MODIFICATION No. MOD70- - -120- - -55
SUBJECT : HORIZONTAL STABILIZER OUTBOARD HINGE FITTINGS
EFFECTIVITY : TBM 700 aircraft S/N 1 to 98, 100 to 156 and 158 to 161
NOTE :
For the other aircraft, the modification is applied at the factory.
REASON :
A. PROBLEM
Cracks on outboard hinge fittings which may cause their rupture.
B. REASON
Installation with stress of outboard hinge fittings.
C. SOLUTION
Check of play and if necessary, elimination of stress.
COMPLIANCE : During next scheduled inspection
SUPPLIED MATERIAL :
- - - Kit No. OPT70 K069- - -55 to be ordered from your TBM spare parts distributor .
Item Part number Description Qty/aircraft
16 T700A551006711000 Shim washer 4
16 T700A551006711100 Shim washer 4
16 T700A551006711200 Shim washer 4
17 Z00.N5548340066 Rivet 4
/ Z00.N4962072123 HYSOL EA9394 (Qty 200 ml) 1
REASON OF AMENDMENT 1 :
--- R e m o v a l o f w a x i n K i t N o . O P T 7 0 K 0 6 9 --- 5 5
- - - Addition of release agent in Paragraph “CONSUMABLE MATERIAL ”
- - - Addition of operation A.10 o)
SERVICE BULLETIN
TBM AIRCRAFT
MANDATORY
The technical content of this document is approved
under the authority of DOA No. EASA.21J.013
is the sub ject of an AD
SB 70-- 080
AMENDMENT 3
55
ATA No.
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

### Page 2

SERVICE BULLETIN
TBM AIRCRAFT
MANDATORY
The technical content of this document is approved
under the authority of DOA No. EASA.21J.013
is the subject of an AD
SB 70-- 080
AMENDMENT 3
55
ATA No.
Page 2 / 8MAY 00
A m d t . 3 --- S E P 1 3
REASON OF AMENDMENT 2 :
- - - Removal of periodic inspection at paragraph C. SOLUTION
- - - Removal of SB application form
- - - Suppression of AD No. 2000 - - -307 - - -A
- - - Aircraft on which the original issue or Amendment 1 of this SB has been applied to
perform shiming operation must not apply Amendment 2.
REASON OF AMENDMENT 3 :
- - - Replacement of FILLER ALU with HYSOL adhesive
- - - Replacement of sealant PR 1422 B2 with PR 1782 B2
- - - Addition of precise details in the procedure
CONSUMABLE MATERIAL (Local purchase) :
- - - Sealant PR 1782 B2 (AIMS 04 - - -05 - - -001) or equivalent
- - - Alodine 1200 (MIL- - -C - - -5541 Class I/A or MIL- - -C - - -81706)
--- A b r a s i v e c l o t h , g r i t N o . 1 8 0
- - - Diestone D (ASN- - -42202) or equivalent
- - - Primer ISOMAP P23 (BMS 1079) or equivalent
- - - Finish paint AEROMAP 1000 (MIL- - -C - - -83289)
- - - Release agent : adhesive tape SAIDIP 2245 - - -2, 3M 3703 or equivalent
wax QZ 5111, release A 4000 or equivalent
TOOLING :
- - - Standard aeronautical maintenance station tools
--- D r i l l , d i a . N o . 4 0 ( 2 . 5 m m )
--- D r i l l , d i a . N o . 2 0 ( 4 . 1 m m )
MANPOWER :
- - - Check without shiming : 3.75 hours
- - - Check with shiming : 6.5 hours
TECHNICAL INCIDENCES :
--- N o n e
ACCOMPLISHMENT INSTRUCTIONS :
NOTE :
Operations required in this Service Bulletin must be accomplished by persons authorized by
their Airworthiness Authorities and according to the procedure described hereafter :
A. PROCEDURE OF GAP CHECK – see Figure 1
NOTE :
This procedure should be applied simultaneously on L.H. and R.H. installations.
1) Measure and register existing gap J1 (1) between pin (2) shoulder and ball joint (1)
of the central hinge fitting.

### Page 3

SERVICE BULLETIN
TBM AIRCRAFT
MANDATORY
The technical content of this document is approved
under the authority of DOA No. EASA.21J.013
is the subject of an AD
SB 70-- 080
AMENDMENT 3
55
ATA No.
Page 3 / 8MAY 00
A m d t . 3 --- S E P 1 3
2) Depending on the registered gap (J1), do the following operations :
Registered gap (J1) Actions
J1 ± 0.004 in (0.1 mm) Apply Paragraph B.
0.004 in (0.1 mm) < J1 < 0.075 in (1.9 mm) No action required
J1 ² 0.075 in (1.9 mm) Apply Paragraph C.
NOTE :
Nominal gap is between 0.004 to 0.075 in (0.1 to 1.9 mm).
B. ADJUSTMENT OF OUTBOARD HINGE FITTINGS WITH J1 ± 0.004 in (0.1 mm) - - - see
Figures 1 and 2
1) Remove horizontal stablizer horns – refer to Chapter 55- - -20- - -00 of the Maintenance
Manual.
2) Remove screws (3) and clamps (6).
3) Remove sealant beads (7) and unstick deicing tube (5) end from rib (8) to free
outboard hinge fitting (4).
4) Remove nuts (11), washers (10) and (13), bolts (12) and (14) and outboard hinge
fitting (4).
5) If necessary, remove excess adhesive at rib (8)/end rib (15) interface taking care not
to damage rib (8) skin.
6) Apply Alodine 1200 and primer P23 on spar bare end.
7) Make a shim (18) made of aluminium alloy with a thickness greater than 0.004 in
(0.1 mm) ; its shape should be the same as end rib (15) flange.
NOTE :
Maximum thickness of shims permissible according to bolt (14) length is 0.071 in
(1.8 mm).
8) Protect shim (18) with Alodine 1200 and primer P23.
9) Attach shim (18) on end rib (15) with two rivets (17), P/N Z00.N5548340066.
10) Apply primer P23 on rivets (17) and on trimmed adhesive seal.
11) Sand rib (8) at outboard hinge fitting (4) interface with abrasive cloth, grit No. 180 to
remove yellow primer and white TEDLAR film until grey/blue primer appears.
NOTE :
Make sure grey/blue primer is still present.
12) Position and secure to contact outboard hinge fitting (4) with bolts (14), washers (10)
and nuts (11).
13) Using feeler gages, measure gap between outboard hinge fitting (4) and rib (8) at
each bolt (12) attaching points.
CASE 1 : GAPS ARE PRESENT
a) Define shim thickness at lower bolt (J2) and at upper bolt (J3) in order to eliminate
those gaps.

### Page 4

SERVICE BULLETIN
TBM AIRCRAFT
MANDATORY
The technical content of this document is approved
under the authority of DOA No. EASA.21J.013
is the subject of an AD
SB 70-- 080
AMENDMENT 3
55
ATA No.
Page 4 / 8MAY 00
A m d t . 3 --- S E P 1 3
NOTE :
Maximum thickness of shims permissible is 0.055 in (1.4 mm).
b) Select shim washers (16) necessary to eliminate gaps (J2) and (J3).
c) Position shim washers (16) on outboard hinge fitting contact surface.
CASE 2 : NO GAP
a) No action required.
14) Secure outboard hinge fitting (4) with bolts (12) and washers (13).
15) Install horizontal stablizers – refer to Chapter 55 - - -20 - - -00 of the Maintenance Manual.
16) Make sure that central hinge fitting (9) is not stressed.
17) Make sure that gap (J1) between pin (2) shoulder and ball joint (1) of inboard hinge
fitting is between 0.004 in (0.1 mm) and 0.075 in (1.9 mm).
If not, contact DAHER - - - SOCATA for a specific repair.
18) Remove horizontal stablizers – refer to Chapter 55- - -20- - -00 of the Maintenance
Manual.
19) Remove nuts (11), washers (10) and (13), bolts (14) and (12) and outboard hinge
fitting (4).
20) Degrease rib with Diestone D (ASN- - -42202)
21) Prepare adhesive, P/N Z00.N4962072123.
22) Apply release agent on outboard hinge fitting (4).
23) Position shim washers (16) on outboard hinge fitting (4) contact surface and apply
sufficient quantity of adhesive to fill gap between outoard hinge fitting (4) total contact
surface and rib (8).
24) Position and secure outboard hinge fitting (4) with bolts (14) and (12), washers (10)
and (13) and nuts (11).
25) Remove excess adhesive around outboard hinge fitting (4).
26) Allow adhesive to cure for 24 hours at an ambient temperature between 59 ° and 68°F
(15 and 20° C).
27) Apply Paragraph D. “RECONDITIONING”
C. ADJUSTMENT OF OUTBOARD HINGE FITTINGS WITH J1 ² 0.075 in (1.9 mm) - - - see
Figures 1 and 2
1) Remove horizontal stabillizer horn fairings - - - refer to Chapter 55- - -20- - -00 of the
Maintenance Manual.
2) Remove screws (3) and clamps (6).
3) Remove sealant beads (7) and unstick deicing tube (5) end from rib (8) to free
outboard hinge fitting (4).
4) Remove bolts (12) and washers (13).
5) Loosen nuts (11).
6) Sand rib (8) at outboard hinge fitting (4) interface with abrasive cloth, grit No. 180 to
remove yellow primer and white TEDLAR film until grey/blue primer appears.

### Page 5

SERVICE BULLETIN
TBM AIRCRAFT
MANDATORY
The technical content of this document is approved
under the authority of DOA No. EASA.21J.013
is the subject of an AD
SB 70-- 080
AMENDMENT 3
55
ATA No.
Page 5 / 8MAY 00
A m d t . 3 --- S E P 1 3
NOTE :
Make sure grey/blue primer is still present.
7 ) D e f i n es h i mt h i c k n e s sa tl o w e rb o l t( J 2 )a n da tu p p e rb o l t( J 3 )i no r d e rt oo b t a i nag a p
(J1) between pin (2) shoulder and ball joint (1) of inboard hinge fitting, between
0.004 in (0.1 mm) and 0.075 in (1.9 mm).
NOTE :
Maximum thickness of shims permissible is 0.055 in (1.4 mm).
8) Select necessary shim washers (16) .
9) Position shim washers (16) on outboard hinge fitting contact surface.
10) Secure outboard hinge fitting (4) with bolts (12) and washers (13).
11) Make sure that central hinge fitting (9) is not stressed.
12) Make sure that gap (J1) between pin (2) shoulder and ball joint (1) of inboard hinge
fitting is between 0.004 in (0.1 mm) and 0.075 in (1.9 mm).
13) Remove horizontal stablizers – refer to Chapter 55- - -20- - -00 of the Maintenance
Manual.
14) Remove nuts (11), washers (10) and (13), bolts (14) and (12) and outboard hinge
fitting (4).
15) Degrease rib with Diestone D (ASN- - -42202).
16) Prepare adhesive, P/N Z00.N4962072123.
17) Apply release agent on outboard hinge fitting (4).
18) Position shim washers (16) on outboard hinge fitting (4) contact surface and apply
sufficient quantity of adhesive to fill gap between outoard hinge fitting (4) total contact
surface and rib (8).
19) Position and secure outboard hinge fitting (4) with bolts (14) and (12), washers (10)
and (13) and nuts (11).
20) Remove excess adhesive around outboard hinge fitting (4).
21) Allow adhesive to cure for 24 hours at an ambient temperature between 59 ° and 68°F
(15 and 20° C).
22) Apply Paragraph D. “RECONDITIONING”
D. RECONDITIONING
1) Remove clamps (6) and screws (3).
2) Apply PR 1782 B2 (AIMS 04 - - -05 - - -001) sealant beads (7).
3) Apply finish paint on rib (8).
4) Install horizontal stabilizers – refer to Chapter 55- - -20- - -00 of the Maintenance Manual.
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 :
Mention, in the aircraft log book, the application of Service Bulletin No. SB 70 - - - 080 - - - 55,
Amendment 3 (Reference MOD70- - -120- - -55) ”HORIZONTAL STABILIZER OUTBOARD
HINGE FITTINGS”.

### Page 6

SERVICE BULLETIN
TBM AIRCRAFT
MANDATORY
The technical content of this document is approved
under the authority of DOA No. EASA.21J.013
is the subject of an AD
SB 70-- 080
AMENDMENT 3
55
ATA No.
Page 6 / 8MAY 00
A m d t . 3 --- S E P 1 3
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.

### Page 7 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-080  AMENDMENT 3  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 - Ball joint
2 - Pin
3 - Screw
4 - Outboard hinge fitting
5 - Deicing tube
6 - Clamp
7 - Sealant bead
8 - Rib
B  9 - Central hinge fitting
I4552000AAAIMA4601
9
Figure 1 - Check and preparation
MAY 00  Page 7 / 8
Amdt. 3 - SEP 13

### Page 8 (OCR)

TBM AIRCRAFT
SERVICE BULLETIN  SB 70-080  AMENDMENT 3  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
4 - Outboard hinge fitting
8 - Rib
10 - Washer
11 - Nut
12 - Bolt
13 - Washer
14 - Bolt
15 - End rib
16 - Shim washer
17 - Rivet
18 - Shim
13
14551000AAAMMA4600  15
8 -
18  16  4
Figure 2 - Outboard hinge fitting shiming
MAY 00  Page 8 / 8
Amdt. 3 - SEP 13

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