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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 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 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 JUL 07. 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 factory.
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.
REASON OF AMENDMENT 3 :
Use of an endoscope to inspect the fittings.
Modification of the NOTE due to the fact that SB was not taken into account in Chapter 05 of the Maintenance Manual at the Revision dated JUL 07.
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. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 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 PROCURABLE MATERIAL :
- Parts to be ordered, if necessary from your TBM spare parts distributor.
Item Part number Description Qty/aircraft 1 Pre-MOD 70-0205-55 Expandable bolt assy (rear) 2 Z0O.N7018814671 After stock depletion, replaced by Post-MOD 70-0205-55 Z00.N7022810298 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 Tous Cotter pin 2 Z00. N5787461153 10 Z00.N5787461151 Cotter pin 2 NOTE :
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)
- Endoscope
MANPOWER
- 1 aeronautical mechanic : 3.50 hrs TECHNICAL INCIDENCES :
- None JUN 03 Page 2 / 8 Amdt. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 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 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).
All
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 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) With an endoscope, 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. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70-104 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
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).
All 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) With an endoscope, 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
g) 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
g) In compliance with Figure 3, install expandable bolt (1), washer (4) and nut (3).
Do not tighten - refer to Chapter 55-30-00, Page 401 of the Maintenance Manual.
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. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 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 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 Ibt.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 3 "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. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 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 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. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 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 - 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 5 6 10 Figure 2 - Inspection of fittings and bolts Pre-MOD 70-0205-55 JUN 03 Page 7 / 8 Amdt. 3 - DEC 07
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 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 - Expandable bolt 2 - Cotter pin 3 - Nut 4 - Washer 6 - Expandable bolt 8 - Washer 9 - Nut 10 - Cotter pin B 4 3 I4553000AAABMA14600 — 10 Figure 3 - Inspection of fittings and bolts Post-MOD 70-0205-55 JUN 03 Page 8 / 8 Amdt. 3 - DEC 07
EADS SOCATA
FORM TO BE FILLED AFTER COMPLIANCE WITH SERVICE BULLETIN
TBM AIRCRAFT SERVICE BULLETIN SB 70 - 104 55 AMENDMENT 3 ATA No.
INSPECTION OF THE VERTICAL STABILIZER ATTACHMENT FITTINGS I, the undersigned, certify that service bulletin No. SB 70-104-55 Amendment 3 has been complied with on aircraft Front fitting Rear fitting Corrosion on fitting L.H R.H L.H. 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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