JUN 08 Page 1 / 6

Amdt. 2 --- JUL 08

ALERT

SUBJECT : ALTERNATOR AND VAPOR CYCLE COOLING SYSTEM COMPRESSOR DRIVE SHAFT

EFFECTIVITY : TBM 850 aircraft from S/N 434 to 9999.

NOTE :

From aircraft S/N 460, Paragraph F. is applied at the factory.

REASON :

A. PROBLEM

Breaking of alternator and vapor cycle cooling system drive shaft found on one aircraft

and cracks on standby alternator and compressor support as well as on pulley drive

assembly which could generate loss of parts and possible damage in engine

compartment.

B. REASON

Accelerated fatigue most probably due to vibrations.

C. SOLUTION

Check for cracks on compressor support and on pulley drive assy and removal of

compressor belt and torque limiter pending application of terminating solution.

REASON OF AMENDMENT 1 :

Modification of SB application time taking into account :

--- the history of shaft removal and installation due to application of SB70 ---156 ---24 and

original issue of the present Service Bulletin,

--- Magnaflux inspection of the shafts performed before delivery.

REASON OF AMENDMENT 2 :

Complete modification of the document.

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 -- 161

AMENDMENT 2

21

ATA No.

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
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 -- 161

AMENDMENT 2

21

ATA No.

JUN 08 Page 2 / 6

Amdt. 2 --- JUL 08

SUMMARY :

A. OPERATIONAL PROCEDURE

B. PREPARATION

C. REMOVAL OF PULLEY DRIVE ASSEMBLY AND ALTERNATOR/COMPRESSOR

SUPPORT

D. CHECK FOR CRACKS

E. SHAFT REPLACEMENT

F. INSTALLATION OF PULLEY DRIVE ASSEMBLY AND ALTERNATOR/COMPRESSOR

SUPPORT

G. RECONDITIONING

COMPLIANCE : As per flow chart hereafter

S/N 2 460 ?

S/N ± 451 ?

Shaft already

replaced ?

Shaft less than 30 hours ?

Apply Paragraphs B,

C, D, E, F and G

Apply

Paragraphs B, C,

D, F and G

YES

NO

YES

NO

YES

NO

NO

YES

During next 100 hours scheduled

inspection,

and then during each 100 hours

scheduled inspection

Apply Paragraphs B, C, D, F and G

On receipt of this SB, apply Paragraph A
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 -- 161

AMENDMENT 2

21

ATA No.

JUN 08 Page 3 / 6

Amdt. 2 --- JUL 08

WARRANTY : Manpower and replaced parts will be taken under warranty within granted time limit.

PROCURABLE MATERIAL :

--- Parts to be ordered from your TBM spare parts distributor.

Chapter

Topic

Item Part number Description Qty/aircraft

(if required)

24 ---30 ---06 12 T700G215505700000 Pulley drive assy 1 NOTE

21 ---55 ---01 24 T700G2155007000 Compressor/alternator

support assy

1 NOTE

24 ---30 ---06 25 T700G2155045100 Shaft 1 NOTE

NOTE :

Components marking is made in compliance with Maintenance Manual related Chapter

Topic.

NOTE :

Some additional parts are necessary for assembly. Please contact your distributor.

CONSUMABLE MATERIAL (Local purchase) :

--- Refer to 24 ---30 ---06 (01) of Maintenance Manual.

TOOLING :

--- Standard aeronautical maintenance station tools

MANPOWER :

--- 1 aeronautical mechanic :

. Removal of compressor drive belt : 1 hour

. Re ---equipment of drive pulley assembly : 1.30 hour

. Removal / Installation of pulley drive assy : 10 hours

. Removal / Installation of compressor/alternator support assy : 6 hours

. Dye penetrant inspection : 2 hours

. Repair of compressor/alternator support assy : 2 hours

--- For repair, certified and qualified personnel in accordance with AC 43.13 for Group 1,

4130 Steel.

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. OPERATIONAL PROCEDURE

CAUTION

IT IS MANDATORY TO INFORM ALL PERSONS WHO MAY FLY THE AIRCRAFT

ABOUT THIS OPERATIONAL PROCEDURE
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 -- 161

AMENDMENT 2

21

ATA No.

JUN 08 Page 4 / 6

Amdt. 2 --- JUL 08

1) Perform a one time flight to reach a maintenance center for application of this SB, it

is mandatory to keep ”AIR COND” switch set to ”OFF” position for this one time flight.

B. PREPARATION

1) Make sure the ”SOURCE” selector is set to ”OFF”.

2) Install the warning sign prohibiting ”SOURCE” selector operation

WARNING

DO NOT OPERATE

MAINTENANCE WORK IN PROGRESS

3) Open engine cowlings 131 and 132.

C. REMOVAL OF PULLEY DRIVE ASSEMBLY AND ALTERNATOR/COMPRESSOR

SUPPORT

NOTE :

Components marking is made in compliance with Maintenance Manual related chapter.

1) Remove pulley drive assy (12) --- refer to Chapter 24 ---30 ---06 (01), Paragraph 1 of the

Maintenance Manual.

2) Remove torque limiter (4) --- refer to Chapter 21 ---55 ---11 (01), Paragraph 1 of the

Maintenance Manual.

3) Separate compressor (21 ---55 ---01, Item 19) and alternator (24 ---30 ---05, Item 8) from

the support (21 ---55 ---01, Item 24), but do not remove electrical connections or

disconnect refrigerant lines --- refer to Chapters 21 ---55 ---01 (01), Paragraph 1 and

24 ---30 ---05 (01) of the Maintenance Manual.

4) Remove support (24) --- refer to Chapter 21 ---55 ---01, Paragraph 1 of the Maintenance

Manual.

D. CHECK FOR CRACKS

1) Using dye penetrant inspection, check for cracks on support (24) weldings and on

all pulley drive (26) surfaces.

2) Should a crack be detected, replace pulley drive assy and/or support and

imperatively return the defective part(s) to EADS SOCATA. However, should the crack

be detected on the welding, repair as per the procedure AC43.13 ---1B, CHG 1

Chapter 4, Section 5 “Welding and Brazing” (Group 1 ; 4130 Steel), Pages 4 ---53 and

up.

NOTE :

--- Support (24) material : 15CDV6 (chromium, molydenum, steel alloy similar to 4115)

thickness 0.06in

--- Filler metal 8CD12 or equivalent as per MIL ---R ---5632 Type I specification

--- Original welding process : Gas Tungsten Arc Welding (GTAW)
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 -- 161

AMENDMENT 2

21

ATA No.

JUN 08 Page 5 / 6

Amdt. 2 --- JUL 08

E. SHAFT REPLACEMENT

1) Re ---equip pulley drive with a new shaft (25) P/N T700G2155045100, apply

Removal/Installation procedure --- refer to Chapter 24 ---30 ---06 (01), Paragraphs 2

and 3 of the Maintenance Manual.

NOTE :

In order to avoid shaft replacement, it is possible to install a new pulley drive assembly

P/N T700G215505700000.

F. INSTALLATION OF PULLEY DRIVE ASSEMBLY AND ALTERNATOR/COMPRESSOR

SUPPORT

1) Install support (24) --- refer to Chapter 21 ---55 ---01 (01), Paragraph 1 of the

Maintenance Manual.

2) Re ---assemble compressor (21 ---55 ---01, Item 19) and alternator (24 ---30 ---05, Item 8)

to the support (21 ---55 ---01, Item 24) --- refer to chapters 21 ---55 ---01 (01), Paragraph 1

and 24 ---30 ---05 (01) of the Maintenance Manual.

CAUTION

DO NOT INSTALL TORQUE LIMITER (21 -- 55 -- 11, ITEM 4) AND ITS DRIVE BELT

3) Install drive pulley assy --- refer to Chapter 24 ---30 ---06 (01) of the Maintenance

Manual.

4) Install alternator belt, then apply belt tension --- refer to Chapter 24 ---30 ---05 (01) of

the Maintenance Manual.

G. RECONDITIONING

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

from debris.

2) Remove the warning sign prohibiting ”SOURCE” selector operation.

3) Close engine cowlings 131 and 132.

4) Position a placard with the following indications on the instrument panel.

“AIR COND” INOPERATIVE

RECOMMENDED “AIR COND” SWITCH POSITION : “MANUAL”

5) After insertion of this SB in the Pilot’s Operating Handbook, fill in the enclosed form

and return it by fax to SOCATA to the indicated address.

UPDATING OF THE AIRCRAFT DOCUMENTATION :

Upon completion of Service Bulletin No. SB 70 ---161 ---21, Amendment 2 ”ALTERNATOR

AND VAPOR CYCLE COOLING SYSTEM COMPRESSOR DRIVE SHAFT”, 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.
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 -- 161

AMENDMENT 2

21

ATA No.

JUN 08 Page 6 / 6

Amdt. 2 --- JUL 08

Figure 1 --- Pulley drive assy

1 --- Pulley drive assy
FORM TO BE FILLED AND SENT BACK BY FAX

SERVICE BULLETIN

TBM AIRCRAFT

SB 70 -- 161

AMENDMENT 2

21

ATA No.

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

ALTERNATOR AND VAPOR CYCLE COOLING SYSTEM COMPRESSOR DRIVE SHAFT

I, the undersigned, ............................................................................................................ certify

that service bulletin No. SB 70 ---161 ---21, Amendment 2 has been complied with on aircraft.

Replaced support Repaired support

Replaced pulley drive assy Replaced shaft

Removal of drive belt and torque limiter

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 :