MSB1078-186/1

Page 1 of 5

08 March 2012 Replaces Issue: 15. Feb 2012

1078-186_1 MSB, Inspection of elevator trim tab ar m Rev.1 

# G 115E/EG

Grob Aircraft AG, Lettenbachstrasse 9, D-86874 Tuss enhausen-Mattsies 

# SERVICE BULLETIN NO. MSB1078-186/1

I. TECHNICAL DETAILS

1.1 Category:

Mandatory

1.2 Airplanes affected:

G 115E all S/N

G 115EG all S/N

1.3 Time of Compliance:

Next 50 hours inspection or next regular inspection whichever comes first.

1.4 Subject:

ATA-Code: 55-20 Elevators and Trim tab Inspection of elevator trim tab arm

1.5 Reason:

Grob received a report from a fleet operator that a n elevator trim tab arm P/N 115E-3758 was found cracked from a rear mounting hole (either L/H or R/H) to the rear edge of the trim tab arm.

Fig. 1 Location of crackMSB1078-186/1

Page 2 of 5

08 March 2012 Replaces Issue: 15. Feb 2012

1078-186_1 MSB, Inspection of elevator trim tab ar m Rev.1 

# G 115E/EG

Grob Aircraft AG, Lettenbachstrasse 9, D-86874 Tuss enhausen-Mattsies Dye penetrant check of defective items revealed, th at a visual inspection of an installed item may not be sufficient to detect every crack on the bracket (Fig. 2).

Fig. 2

Therefore a dye penetrant check or more significant NDT of the dismounted parts is mandated by this MSB1078-186/1. This measure will ensure saf e operation until a terminating action is mandated by a later revision of this Service Bullet in.

Note: If the affected item has been already replaced while accomplishing MSB1078-186, the

instructions in 1.8 of MSB1078-168/1 may be considered as accomplished.

1.6 Concurrent documents:

G 115E: AMM TR No. 05-21 G 115EG: AMM / JG TR No. 05SMC-03, 05SMC-04, 05GV-0 4

1.7 Approval Note:

The technical content of this document is approved under the authority of EASA Design Organization Approval No. EASA.21J.030.

1.8 Accomplishment/ Instructions

1.8.1 Ensure that the aircraft is safe for parking I.A.W. G 115E AMM chapter 10-10 and G 115EG Job Guide in analogy.

1.8.2 Inspect elevator trim tab operating arm for s igns of cracking, especially both upper and lower surfaces from the rear bolt mounting holes to the rear of the operating arm.

1.8.3 Remove trim tab I.A.W. G 115E AMM chapter 55- 20 para. 3B and G 115EG Job Guide in analogy

1.8.4 Remove trim tab arm (item 10) by removing nut , washer and bolt (item 20, 30, 40)MSB1078-186/1

Page 3 of 5

08 March 2012 Replaces Issue: 15. Feb 2012

1078-186_1 MSB, Inspection of elevator trim tab ar m Rev.1 

# G 115E/EG

Grob Aircraft AG, Lettenbachstrasse 9, D-86874 Tuss enhausen-Mattsies 10 20

30

40 Left Elevator

Fig. 3

1.8.5 Perform dye penetrant check or more significa nt NDT on trim tab arm P/N 115E-3758

1.8.6 If no crack is found , clean trim tab bracket and proceed with 1.8.8

1.8.7 If a crack is confirmed , the trim tab arm has to be replaced by a new item.

Note: Any finding has to be reported to Grob with aircraf t S/N and flight hours.

1.8.8 Install trim tab arm P/N 115E-3758 (item 10) using bolt, washer and new locking nut (item 20, 30, 40). Apply correct torque value I.A.W . G 115E AMM chapter 20-10 and G 115EG Job Guide in analogy.

1.8.9 Install trim tab I.A.W. G 115E AMM chapter 55-20 pa ra. 3C and G 115EG Job Guide in analogy

Note: Make sure, that the bolt holes of trim rods 3 are i n alignment with the trim arm and the bolts may be installed easily. If necessary adjust accordingly I.A.W. G 115E AMM chapter 27-31 para. B and G 115EG Job Guide in analogy.

1.8.10 Return aircraft to service as per relevant procedur es and regulations.

1.9 Repetitive Actions

Repeat special inspection in para 1.8 every 500FH u ntil the terminating action is accomplished. For regular inspection r efer to G 115E AMM, Chap. 05-20, para. 10 and G 115 EG Job Guide in analogy.MSB1078-186/1

Page 4 of 5

08 March 2012 Replaces Issue: 15. Feb 2012

1078-186_1 MSB, Inspection of elevator trim tab ar m Rev.1 

# G 115E/EG

Grob Aircraft AG, Lettenbachstrasse 9, D-86874 Tuss enhausen-Mattsies



## II. PLANNING INFORMATION

2.1 Weight and CG

N/A

2.2 Material and Availability

Item P/N Description Qty. / A/C

1 115E-3758 Trim Tab Arm 1

2 LN9348-05 Lock Nut 4

3 LN9348-06 Lock Nut 1

2.3 Special Tools

N/A

2.4 Labor costs

N/A

2.5 Reference documents

Corresponding AMM and IPC

2.6 Credit

N/AMSB1078-186/1

Page 5 of 5

08 March 2012 Replaces Issue: 15. Feb 2012

1078-186_1 MSB, Inspection of elevator trim tab ar m Rev.1 

# G 115E/EG

Grob Aircraft AG, Lettenbachstrasse 9, D-86874 Tuss enhausen-Mattsies



## III. REMARKS

The instructions in paragraph 1.8 have to be accomp lished and certified in the logbook by

authorized staff:

- in EASA countries according to Article 5 VO EG 2042/03 (VO EG 1056/2 008) Appendix III –

Part 66

- in non-EASA countries according to national regulations with respect to maintenance.

If you have sold your aircraft in the meantime, we kindly ask you to forward this information to the new owner and to provide us with the name and a ddress of the new owner as well as with the respective serial number.

For questions and assistance please contact:

Rudi Vodermeier, Head of Customer Service & Suppo rt,

phone: +49 8268 998139

fax: +49 8268 998200

e-mail: productsupport@grob-aircraft.de

SB-Index: http://www.grob-aircraft.eu/service-and-support/g-1 15.html

Order: http://www.grob-aircraft.eu/service-and-support/gen eral/order-form.html