PO Box 881, Morwell, Victoria 3840, Australia

Ph + 61 (0) 3 5172 1200

Fax + 61 (0) 3 5172 1201

www.gippsaero.com

MANDATORY

Service Bulletin

SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 1 of 7

SB-GA8-2014-115

Issue 1

Subject:

Installation of fire-resistant washer and inspection of engine isolator mount orientation

Applicability:

All GA8-TC 320 aircraft up to and including serial no. GA8-TC 320-14-205

Amendments:

Issue 1: Initial issue. GippsAero Reference GAE12#1268

Background:

A recent review of the engine mount installation on the Turbo Charged GA8 Airvan has prompted the 

release of this Service Bulletin. Model GA8-TC 320 aircraft require the installation of a steel washer at 

each of the engine isolator mount locations to address a potential risk of reduced engine retention 

capability in the event of a fire. The potential loss of engine retention capability would only occur in 

the event of extreme temperatures sufficient to result in the loss of the strength of the aluminium in the 

sandwich mounts.

Service Bulletin, SB-GA8-2014-114, was recently released to require an inspection for correct 

orientation of the engine isolators in the naturally aspirated aircraft. Although the Turbo-Charged 

aircraft is at a substantially reduced risk of incorrect installation, a check for correct orientation is 

included in this Service Bulletin as a precautionary measure. The correct installation procedure is to 

install the stiffer mount on the compression side of the joint. This is to prevent premature mount 

deformation and subsequent engine sagging. Provided that correct bolt torque is maintained on the 

attachment bolt, the vibration properties of the engine installation will be unaffected.

This Service Bulletin requires operators to install the steel washer at each isolator mount location, and 

verify that the engine mounts have been installed with the correct orientation.

Compliance:

The requirements of this Service Bulletin shall be accomplished within 300 hours or 12 months 

whichever occurs earlier from the date of issue of this Service Bulletin.

Weight and Balance:

Accomplishment of this Service Bulletin results in a weight increase of approximately 200 g (0.44 lb) at 

station -356mm (-14.0 in).

Approval:

This Service Bulletin has been approved pursuant to Regulation 21.098 of CASR (1998).

Parts:

The following parts are required to accomplish this Service Bulletin.

PART No. DESCRIPTION QTY Remarks

J-2218-61 Washer 4

1 each to be installed per isolator location, 

refer Figure 1

AN7-34A Bolt, Machine, Structural, 

Undrilled 4

1 each to be installed per isolator location, 

refer Figure 1
SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 2 of 7

The following optional parts may be required to accomplish the requirement of this Service Bulletin.

PART No. DESCRIPTION QTY Remarks

J-9613-19 Lord Engine Mount Kit 4

Comprising of one J-9612-8 Sandwich 

Mount, one J-7763-1 Sandwich Mount & 

one J-7766-2 Spacer, refer Figure 2. Only 

required in the event that the installed 

isolators are found to be unserviceable.

MS20365-720C Nut, Self-Locking, All Metal 4

Replacement for existing nut if found to be 

unserviceable.

72711 O’ring 1

Induction pipe o’ring. Required in the event 

that adjacent induction pipe is removed to 

access the lower starboard isolator 

location.

71973 Gasket 1

Induction pipe gasket. Required in the 

event that adjacent induction pipe is 

removed to access the lower starboard 

isolator location.

TLPD 48LF Rivet, Pop 8 4 each per Middle Aft Baffle Cover Plate

Parts Availability:

New parts can be obtained directly from GippsAero.

Tel: +61 (0)3 5172 1200

Fax: +61 (0)3 5172 1201

Email: spares@gippsaero.com

Labour:

5 man hours should be allocated for completing the work detailed in this Service Bulletin.

Warranty:

Aircraft under warranty may claim the direct cost of carrying out the requirements of this Service 

Bulletin via GippsAero Customer Service.

Tel: +61 (0)3 5172 1200

Fax: +61 (0)3 5172 1201

Email: warranty@gippsaero.com

Accomplishment Instructions:

NOTE:

Ensure the aircraft is prepared for maintenance and that appropriate safety 

precautions are taken when performing work outlined in this Service Bulletin.

Unless otherwise specified, reference to the GA8-TC 320 Service Manual as well 

as FAA AC43.13-1B & FAA AC43.13-2B should be made when carrying out the 

procedure prescribed in this Service Bulletin. In case of discrepancy between the 

Service Manual and the AC, the Service Manual takes precedence.

1. Remove the engine cowls in accordance with the applicable Service Manual.

2. Verify that the installation of the engine isolator mounts includes a steel washer J-2218-61 (shown 

in Figure 2 below). Proceed to step 3 if the washers have not been installed, otherwise skip to 

step 10.

3. Relieve the weight of the engine from the isolator mounts using an appropriate hoist.

4. Check the orientation of the engine isolator mounts to verify that the mounts have been installed in 

accordance with Figure 1. Specifically mount part no. J-7763-1 must be positioned on the 

compression side of the engine lug. For upper mounts this would be on the forward side and for 

the lower mounts this would be on the aft side of the engine lug. The part number of the mounts 

can be found moulded into the elastomer on the periphery of the mount. A depiction of the mounts 

is shown in Figure 2. If any of the isolator mounts are not installed in accordance with Figure 1, 

proceed to step 5, otherwise skip to step 8
SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 3 of 7

5. Remove and inspect the engine isolators for eccentricity and thickness in accordance with Lord 

Quick Reference Guide No. PB6304A (see appendix A). Isolators that are found to be not 

serviceable are to be replaced with new parts of the same type.

WARNING

ENSURE TO ONLY INSPECT AND RE-INSTALL EITHER THE TOP MOUNTS 

OR THE BOTTOM MOUNTS AT A TIME. REMOVAL OF MOUNTS IN ANY 

OTHER MANNER MAY CAUSE INJURY AND/OR DAMAGE THE ENGINE.

NOTE:

If required, carefully drill out the 8 pop rivets holding the two middle aft baffle cover 

plates to gain access to the top engine mount locations (Figure 3) ensuring all 

swarf is cleared off the work area. When gaining access to the lower engine mount 

locations ensure that surrounding installations including hoses and electrical cables 

are not damaged.

6. Re-install the isolators such that they are oriented in accordance with Figure 1.

7. Inspect the cowls for evidence of damage caused by excessive drooping of the engine. If damage 

is found, contact GippsAero for further assistance.

8. Regardless of mount serviceability, a J-2218-61 steel washer is to be installed on the forward side 

of each of the four engine isolator mount locations. The AN7-33A bolt is to be replaced with an 

AN7-34A bolt, verify correct length upon installation. Depending on bolt grip length the existing 

AN960-716 washer maybe retained or discarded. Ensure that engine mount retention bolts are 

torqued to 450-500 in-lb per Chapter 20-10-00 of the Service Manual.

NOTE:

The AN960-716 washer under the head of the bolt is to be retained.

NOTE:

Installation of the lower starboard washer is impeded by the location of the 

turbocharger and induction pipe. In the event that it is not possible to replace the 

starboard lower washer without removing these components the recommended 

procedure is to remove the adjacent induction pipe, install the washer, torque the 

mounting bolt and reinstall the induction pipe in accordance with Lycoming 

instructions. When the induction pipe is re-installed a new o-ring (P/N 72711) and 

gasket (P/N 71973) will be required.

9. If removed, re-install the two middle aft baffle cover plates using 8 TLPD 48LF pop rivets.

10. Re-install the engine cowls and proceed to the documentation section of this Service Bulletin.
SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 4 of 7

LHS LOWER ENGINE

MOUNT ASSEMBLY

UPPER ENGINE

MOUNT ASSEMBLY

TYPICAL TWO UPPER MOUNTS

RHS LOWER ENGINE

MOUNT ASSEMBLY

INCLUDING INSTALLATION OF ENGINE MOUNT HEATSHIELD

Figure 1: Mount Installation
SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 5 of 7

Figure 2: Mount Depiction

J-7766-2
SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 6 of 7

Figure 3: Middle Aft Baffle Cover Plate

Documentation:

Update aircraft log book to reflect incorporation of this Service Bulletin.

Continuing Airworthiness:

During subsequent engine installation, verify that the installation of the engine mounts is in 

accordance with the instructions in this Service Bulletin. All other instructions already specified in the 

aircraft Service Manual continue to be applicable.

Future issues of the Service Manual and the Illustrated Parts Catalogue will contain clarified 

information as contained in this Service Bulletin.

Compliance Notice:

Complete the Document Compliance Notice and return to GippsAero by mail, fax or email.

Pop Rivet

Middle Aft 

Baffle Cover 

Plate
SB-GA8-2014-115 Issue 1 Date of Issue: 06.10.2014 Page 7 of 7

Appendix A – Lord Quick Reference Guide
DOCUMENT COMPLIANCE NOTICE

Document:

SB-GA8-2014-115

Issue 1

Aircraft Serial Number: GA8-______________

Service Bulletin SB-GA8-2014-115 Issue B - DRAFT has been incorporated in the above aircraft.

Date of Incorporation:_____________________

______________________________________

Signed

Print Name: ____________________________

Please post, fax or email this compliance notice to:

GippsAero Technical Services

P.O. Box 881

Morwell Victoria 3840

Australia

Fax.: +61 03 5172 1201

Email: techpubs@gippsaero.com