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Amdt. 2 --- AUG 12

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

Installation of shims on hinge fittings to eliminate installation 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.N4966056123 Kit FILLER ALU 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 2

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 2

55

ATA No.

MAY 00 Page 2 / 7

Amdt. 2 --- AUG 12

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.

CONSUMABLE MATERIAL (Local purchase) :

--- Sealant PR 1422B2 (MIL ---S ---8802F Amdt 3)

--- 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 – see Figures 1 and 2

NOTE :

This procedure should be applied simultaneously on L.H. and R.H. installations.

1) Measure and register gap between pin (2) shoulder and ball joint (1) of the central

hinge fitting.

NOTE 1 :

Nominal gap is between 0.004 to 0.075 in (0.1 to 1.9 mm).
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 2

55

ATA No.

MAY 00 Page 3 / 7

Amdt. 2 --- AUG 12

NOTE 2 :

Aircraft S/N 129, 143, 144, 146 to 148, 150 to 152 and 156 are fitted with shims to get

this nominal gap. Should hinge fittings be installed with stress, remove shims and

apply this SB totally.

2) Remove horizontal stablizers – refer to Chapter 55 ---20 ---00 of the Maintenance

Manual.

3) Remove screws (3) and clamps (6).

4) Remove sealant beads (7) and unstick deicing tube (5) end of rib (8) to free outboard

hinge fitting (4).

5) Remove nuts (11), washers (10) and (13), bolts (12) and (14) and outboard hinge

fitting (4).

6) Perform a dye penetrant inspection to check for cracks on outboard hinge fitting (4)

and replace if cracked – refer to Chapter 55 ---10 ---00 of the Illustrated Parts Catalog

and Maintenance Manual.

7) If necessary, remove excess adhesive at rib (8)/end rib (15) interface ; let

over ---thickness of approximately 0.008 in (0.2 mm) in order not to damage rib (8)

skin.

8) Apply Alodine 1200 and primer P23 on spar bare end.

9) If gap between pin (2) shoulder and ball joint (1) is between 0 and 0.039 in

(0 and 1 mm), perform the following operations

a) Position and secure outboard hinge fitting (4) with bolts (12) and washers (13).

b) Using feeler gages, measure gap between outboard hinge fitting (4) and end

rib (15) at bolt (14) attaching points.

c) If there is no gap, install bolts (14), washers (10) and nuts (11).

d) If there is a gap, define shim thickness.

NOTE :

Maximum thickness of shims permissible according to bolt (14) length is 0.071 in

(1.8 mm) and sum of shim thickness and gap at central hinge fitting should be

0.075 in (1.9 mm) maximum.

Example : Gap at central hinge fitting = 0.032 in (0.8 mm)

Existing gap at upper bolt = 0.051 in (1.3 mm)

Existing gap at lower bolt = 0.036 in (0.9 mm)

Calculation of shim thickness at upper bolt :

0.032 in (0.8 mm) + 0.051 in (1.3 mm) = 0.083 in (2.1 mm), above

0.075 in (1.9 mm) nominal gap.

Shim thickness = 0.075 in (1.9 mm) – 0.032 in (0.8 mm) = 0.043 in

(1.1 mm).

Calculation of shim thickness at lower bolt :

0.032 in (0.8 mm) + 0.036 in (0.9 mm) = 0.068 in (1.7 mm), below

0.075 in (1.9 mm) nominal gap.

Shim thickness = 0.036 in (0.9 mm).
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 2

55

ATA No.

MAY 00 Page 4 / 7

Amdt. 2 --- AUG 12

e) Remove bolts (12), washers (13) and outboard hinge fitting (4).

f) Make a shim (18) made of aluminium alloy as per calculated thickness ; its shape

should be the same as end rib (15) flange.

g) Protect shim (18) with Alodine 1200 and primer P23.

h) Attach shim (18) on end rib (15) with two rivets (17), P/N Z00.N5548340066.

i) Apply primer P23 on rivets (17) and on trimmed adhesive seal.

j) Position and secure outboard hinge fitting (4) with bolts (14) and (12),

washers (10) and (13) and nuts (11).

10) If gap between pin (2) shoulder and ball joint (1) is above 0.039 in (1 mm) perform

the following operations

a) Position and secure outboard hinge fitting (4) with bolts (14), washers (10) and

nuts (11).

b) Using feeler gages, measure gap between outboard hinge fitting (4) and rib (8)

at each bolt (12) attaching points.

c) Define ”e” shim thickness :

NOTE :

Maximum permissible shim thickness is 0.055 in (1.4 mm).

”e” = existing gap less 0.008 in (0.2 mm).

d) Remove nuts (11), washers (10), bolts (14) and outboard hinge fitting (4).

e) Select necessary shim washers (16).

f) 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 resin appears.

g) Degrease rib (8) with Diestone D (ASN ---42202)

h) Prepare a compound with FILLER ALU kit, P/N Z00.N4966056123.

i) Apply release agent on outboard hinge fitting (4).

j) Position shim washers (16) on outboard hinge fitting (4) bearing face and apply

FILLER ALU sufficiently to fill gap between outoard hinge fitting (4) total bearing

face and rib (8).

k) Position and secure outboard hinge fitting (4) with bolts (14) and (12),

washers (10) and (13) and nuts (11).

l) Remove excess FILLER ALU around outboard hinge fitting (4).

m) Allow FILLER ALU to cure for 24 hours at an ambient temperature

between 59° and 68°F (15 and 20°C).

n) Remove nuts (11), washers (10) and (13), bolts (12) and (14) and outboard hinge

fitting (4).

o) If the release agent used is adhesive tape, remove it then clean possible cement

residues with Diestone D (ASN ---42202).

p) Apply primer P23 on bearing face of rib (8) and outboard hinge fitting (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 2

55

ATA No.

MAY 00 Page 5 / 7

Amdt. 2 --- AUG 12

q) Position and secrure outboard hinge fitting (4) with bolts (14) and (12),

washers (10) and (13) and nuts (11).

r) Install clamps (6) and screws (3).

s) Apply PR 1422B2 (MIL ---S ---8802F Amdt 3) sealant beads (7).

t) Apply finish paint on rib (8).

11) Make sure all the tools and materials are removed and the work area is clean and free

from debris.

12) Install horizontal stabilizers – refer to Chapter 55 ---20 ---00 of the Maintenance Manual.

UPDATING OF THE AIRCRAFT DOCUMENTATION :

Mention, in the aircraft log book, the application of Service Bulletin No. SB 70 ---080 ---55,

Amendment 2 (Reference MOD70 ---120 ---55) ”HORIZONTAL STABILIZER OUTBOARD

HINGE FITTINGS”.

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 2

55

ATA No.

MAY 00 Page 6 / 7

Amdt. 2 --- AUG 12

Figure 1 – Check and preparation

1 --- Ball joint

2 --- Pin

3 --- Screw

4 --- Outboard hinge fitting

5 --- De ---icing tube

6 --- Clamp

7 --- Sealant bead

8 --- Rib
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 2

55

ATA No.

MAY 00 Page 7 / 7

Amdt. 2 --- AUG 12

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