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Amdt. 3 --- SEP 13

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 :

--- Removal of wax in Kit No. OPT70 K069 ---55

--- 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 subject 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
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.

MAY 00 Page 2 / 8

Amdt. 3 --- SEP 13

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)

--- Abrasive cloth, grit No. 180

--- 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

--- Drill, dia. No. 40 (2.5 mm)

--- Drill, dia. No. 20 (4.1 mm)

MANPOWER :

--- Check without shiming : 3.75 hours

--- Check with shiming : 6.5 hours

TECHNICAL INCIDENCES :

--- None

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.
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.

MAY 00 Page 3 / 8

Amdt. 3 --- SEP 13

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.
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.

MAY 00 Page 4 / 8

Amdt. 3 --- SEP 13

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.
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.

MAY 00 Page 5 / 8

Amdt. 3 --- SEP 13

NOTE :

Make sure grey/blue primer is still present.

7) Define shim thickness at lower bolt (J2) and at upper bolt (J3) in order to obtain a gap

(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”.
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.

MAY 00 Page 6 / 8

Amdt. 3 --- SEP 13

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.
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.

MAY 00 Page 7 / 8

Amdt. 3 --- SEP 13

Figure 1 – Check and preparation

1 --- Ball joint

2 --- Pin

3 --- Screw

4 --- Outboard hinge fitting

5 --- Deicing tube

6 --- Clamp

7 --- Sealant bead

8 --- Rib

9 --- Central hinge fitting
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.

MAY 00 Page 8 / 8

Amdt. 3 --- SEP 13

Figure 2 --- Outboard hinge fitting shiming

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