Service Bulletin SB-GA8-2014-115
GIPPSAERO GA8 AIRVAN · Service Bulletins
Overview
This document is a mandatory service bulletin for the GippsAero GA8-TC 320 aircraft, detailing the installation of fire-resistant washers and inspection of engine isolator mount orientation. It aims to enhance engine retention capability in the event of a fire and includes compliance instructions for operators.
- Applies to all GA8-TC 320 aircraft up to serial no. GA8-TC 320-14-205.
- Requires installation of steel washers at engine isolator mounts.
- Includes inspection of engine isolator mount orientation.
- Compliance is required within 300 hours or 12 months.
- Installation results in a weight increase of approximately 200 g.
- 5 man hours are estimated for completion of the work.
- Parts can be obtained directly from GippsAero.
- Aircraft under warranty may claim costs for compliance.
Document
Source
Originally published by regulations.gov. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Service Bulletins
- Year ·
- 2014
- File size ·
- 566 KB
- Publisher ·
- regulations.gov
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Weight increase g ·
- 200
- Weight increase (lb) ·
- 0.44
What is the Service Bulletin SB-GA8-2014-115?
The Service Bulletin SB-GA8-2014-115 is a service bulletins for the GIPPSAERO GA8 AIRVAN, dated 2014.
Where does the Service Bulletin SB-GA8-2014-115 come from?
This copy of the Service Bulletin SB-GA8-2014-115 was originally published by regulations.gov and is hosted on Sprinkle as a free, searchable reference copy.
What year was the Service Bulletin SB-GA8-2014-115 published?
The Service Bulletin SB-GA8-2014-115 — the GIPPSAERO GA8 AIRVAN service bulletins on file — is dated 2014.
Most owners only have the POH. Here's the essential set for the GIPPSAERO GA8 AIRVAN.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
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In this document
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.
Compliance
Requirements must be accomplished within 300 hours or 12 months from the date of issue.
Parts
Details required and optional parts for the service bulletin, including part numbers and quantities.
Accomplishment Instructions
Step-by-step instructions for installing washers and inspecting engine mounts.
Documentation
Instructions to update the aircraft log book and return compliance notice.
Safety notes
- 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.
Full document text
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:
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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