SB-GA8-2012-96 - Mahindra Aerospace
Contents
1. o o o o o o o o o o o o a o O O O 0 o o Figure 8 Hole 6 Belly skin shown from above for clarity DO NOT REMOVE FLOOR SKIN SB GA8 2012 96 Date of Issue 12 August 2013 Page 8 of 14 Centre Rib No 4 RH D o o o New Hole e o le o o o o o o i i D T l r 7 B o bs le Current 1 8 o 5 Grommet gt Location o a o o o o o o e 2 8 eo o o o o o o o o o o a o o a Centre Rib No 5 RH Qoo o o Mese ne ensem ae o D amp o o D o Strut Cut Out o o ao Ie LS D IS C Figure 9 Hole 7 Belly skin shown from above for clarity DO NOT REMOVE FLOOR SKIN SB GA8 2012 96 Date of Issue 12 August 2013 Page 9 of 14 Hole 2 Hole 3 Hole 5 Hole 4 Fuel Drain Hole 7 Hole 6 Fuel Boost Pump Drain Grommet Figure 10 Hole Locations Viewed from Bottom of Belly Skin Dimensions in inches SB GA8 201 2 96 Date of Issue 12 August 2013 Page 10 of 14 Figure 11 Fluted Hole Dimensions in inches NOTE Measurements referred in Figure 11 are approximate and shall be used as a reference only Instructions Part 2 Cargo Pod if installed Guard Installation Kit SB GA8 2012 96 1 GA8 25501 4 037 Cargo Pod Guard 343 24 The following instructions are applicable to aircraft fitted with a cargo pod GA8 255004 017 or GA8 255004 019 a A fuel drain compartment must be installed in the front right section of the cargo pod The compartment will comprise of a2. 4 in hole through bottom skin located between centre rib no 2 GA8 532023 115 and centre rib no 3 assembly GA8 53201 93 055 Figure 5 SB GA8 2012 96 Date of Issue 12 August 2013 Page 2 of 14 11 Drill 4 in hole through bottom skin located in board of sump tank between centre rib no 4 GA8 532023 125 and centre rib no 3 assembly GA8 53201 3 055 Figure 6 12 Drill in hole through bottom skin located outboard of sump tank between no 3 RH rib GA8 532023 253 and no 4 RH rib assembly GA8 532013 071 Figure 7 13 Drill 4 in hole through bottom skin located inboard of sump tank between centre rib no 4 GA8 532023 125 and centre rib no 5 GA8 532013 127 Figure 8 14 Drill 14 in hole through bottom skin located outboard of the seat rail rib RH aft GA8 532021 259 adjacent to grommet Figure 9 15 To prevent moisture from entering the new drain holes Figure 10 press half moon flute into surface of skin Figure 11 approximate dimensions shown 16 Deburr holes visually check using 10X magnification to ensure no hole cracks were induced and prime with suitable aircraft primer 17 Apply PR1422 between sump tank access panel and floor skin fit access panel to floor skin ensuring good seal Refer to applicable Service Manual Chapter 28 for Fuel Tank Sealing Procedures 18 Fit floor inspection panel forward of co pilot control column 19 Fit co pilot outboard seat rail 20 Fit fuel pump mainte
3. Fuel Pump Assembly Dual Fuel Bowl Assembly Integral Fuel Sump Tank Shutoff Valve Figure 1 SB GA8 2012 96 Date of Issue 12 August 2013 Page 1 of 14 Compliance This service bulletin is to be carried out within 3 months or 100 flight hours from receipt of this Service Bulletin whichever occurs first Instructions Part 1 Fuel System Ventilation and Drainage Modification The following instructions must be carried out 1 Remove co pilot seat from aircraft cabin and stow Figure 2 Remove fuel pump maintenance inspection panel and stow Remove co pilot seat outboard seat rail and stow 2 3 4 Remove sump tank access panel and stow 5 Remove floor inspection panel forward of co pilot control column and stow 6 If applicable remove cargo pod from aircraft and stow as per installation instruction in SB GA8 2004 14 instructions part 2 applicable Floor Inspection Sump Tank Access Panel Outboard Seat Rail Fuel Pump Maintenance Inspection Panel Figure 2 7 Gain access through sump tank access panel and drill 1 4 in hole through rib no 3 RH GA8 532023 253 Figure 3 8 Refer to Figure 10 9 Gain access through floor inspection panel forward of control column and drill 1 4 in hole through bottom skin located between no 2 RH rib GA8 532023 016 and no 3 RH rib GA8 532023 253 Figure 4 10 Gain access through floor inspection panel forward left of the control panel and drill 1
4. he aircraft confirm that there are no gaps between the cargo pod and the fuselage belly skin Fill gaps using neutral cure silicone sealant NOTE If part 1 and part 2 instructions are applicable they must be incorporated simultaneously Weight and Balance Incorporation of this Service Bulletin adds 0 94 lbs 0 425 kg at 38 in 965 mm as indicated below Weight Ib in in Ib Kit SB GA8 2012 96 1 Fuel Drain Guard Installation 35 72 This modification has no appreciable change to weight and balance of the aircraft SB GA8 2012 96 Date of Issue 12 August 2013 Page 13 of 14 Parts Availability New parts can be obtained directly from GippsAero Tel 61 03 5172 1200 Fax 6103 5172 1201 Email spares 2gippsaero com Labour 3 man hours should be allocated to the incorporation of Part 1 instructions in this Service Bulletin 4 man hours should be allocated to the incorporation of Part 2 instructions in this Service Bulletin Warranty Aircraft within the warranty period may claim from warranty gippsaero com Continuing Airworthiness Please refer to Service Manual Supplement C05 96 24 All fuel drainage holes in the aircraft belly skin and cargo pod must remain free of debris Aircraft fitted with cargo pod must refer to Flight Manual Supplement C01 04 34 Compliance Notice Complete the Document Compliance Notice and return to GippsAero by mail fax or email References Should you require mo
5. nance inspection panel 21 Fit co pilot seat 22 lf applicable revise cargo pod installation instruction as specified in SB GA8 2004 14 at latest issue 23 Record completion of this Service Bulletin in Aircraft Log Book NOTE All measurements shown in the following figures are in inches SB GA8 2012 96 Date of Issue 12 August 2013 Page 3 of 14 New Hole NN i l if p LZ C N yi o J 7 7 L P per 0 l fy n l fr 0 Pd fs E a Pd o l ba fg l zd QA m Rib No 3 RH BD EDEN Figure 3 Hole 1 View looking forward on Rib No 3 New Hole SB GA8 2012 96 Date of Issue 12 August 2013 Page 4 of 14 l l l Forward Keel New Hole j 0 6 Figure 5 Hole 3 Belly skin shown from above for clarity DO NOT REMOVE FLOOR SKIN SB GA8 2012 96 Date of Issue 12 August 2013 Page 5 of 14 Q New Hole Centre Rib No 3 O o Oo o Oo 7 j Centre Rib No 4 Figure 6 Hole 4 Belly skin shown from above for clarity DO NOT REMOVE FLOOR SKIN SB GA8 2012 96 Date of Issue 12 August 2013 Page 6 of 14 New Hole Rib No 4 RH Figure 7 Hole 5 Belly skin shown from above for clarity DO NOT REMOVE FLOOR SKIN SB GA8 2012 96 Date of Issue 12 August 2013 Page 7 of 14 Centre Rib No 4 RH O O O New Hole O O O o O O d i o O O O O o o 4 o ao G o o
6. re information please contact GippsAero Customer Support Department Tel 61 0 35172 1200 Fax 61 0 3 5172 1201 Email support gippsaero com SB GA8 2012 96 Date of Issue 12 August 2013 Page 14 of 14 DOCUMENT COMPLIANCE NOTICE Document 7 54 A Mahindra Aerospace Company SB GA8 201 2 96 GIPPSAERO Issue 4 Aircraft Serial Number Cargo Pod Serial Number Aircraft Registration Incorporation Date Incorporated by certify that SB GA8 2012 96 Issue 4 Instructions Part 1 has been incorporated in the aircraft specified in this Document Compliance Notice Signed certify that SB GA8 2012 96 Issue 4 Instructions Part 2 has been incorporated in the aircraft specified in this Document Compliance Notice Signed Please email post or fax this Document Compliance Notice to GippsAero Attn Technical Publications P O Box 881 Morwell Victoria 3840 Australia Fax 61 03 5172 1201 Email techpubs gippsaero com Contact Details for GippsAero use only Contact Email Address
7. sheet metal cargo pod guard GA8 25501 4 037 with a silicon edge seal GA8 255024 075 GA8 255024 077 b The cargo pod fuel guard GA8 255014 037 and edge seals GA8 255024 075 GA8 255024 077 should be obtained from GippsAero c Align the cargo pod fuel guard within the cargo pod The left guard wall should be aligned with the right forward attachment hole The right guard wall must be aligned with the 3rd right forward attachment hole Confirm that hole 6 will drain within the SB GA8 2012 96 Date of Issue 12 August 2013 Page 11 of 14 cargo pod guard Trim cargo pod guard to suit internal geometry of cargo pod only if required See Figure 12 d Drill amp 3 16 holes in cargo pod at anchor nuts on cargo pod fuel guard flanges NOTE The optimum temperature for the application of PR 1422 sealant is 21 C Z 3C 70 F 5 T For every 10 F 5 6 rise in temperature application life reduces by a half and for every 10 5 6 CT drop it is doubled High humidity at the time of mixing shortens application life WARNING PR 1422 ACCELERATORS CONTAIN HEAVY METAL PEROXIDES KEEP AWAY FROM HEAT AND FLAME USE ONLY IN A WELL VENTILATED AREA AVOID SKIN AND EYE CONTACT WEAR EYE PROTECTION IN CASE OF EYE CONTACT FLUSH GENEROUSLY WITH WATER AND GET PROMPT MEDICAL ATTENTION e Clean all surfaces to be sealed with PR 1422 class B Apply a bead of sealant PR 1422 Class B or equivalent along lower flanges of cargo pod f
8. uel guard Enough sealant must be applied so that it will squeeze out around the joint when the parts are finally fastened together g Align cargo pod fuel guard with holes and fasten with screws AN525 832R8 f Flange for Silicon Edge Seal Cargo Pod 1 Fuel Guard Grommet MS35489 13 with Drain Hose GA8 255024 073 in Aft Corner Drain Guard Viewed from Top Figure 12 Cargo Pod Fuel Guard Installation SB GA8 2012 96 Date of Issue 12 August 2013 Page 12 of 14 h Apply additional sealant to all boundaries as well as any other area between the cargo pod fuel guard and cargo pod that could cause a fuel leak i Allow sealant adhesive to cure j Use 100 silicon neutral cure sealant adhesive to glue the fuel guard edge seals GA8 255024 075 GA8 255024 077 to the top cargo pod fuel guard flange trim to suit k Drill 0 750 hole for drainage in cargo pod at aft corner of fuel drain compartment deburr the hole ensuring no sharp edges remain Figure 12 Line the hole using the grommet MS35489 13 Figure 12 m Fit drain hose GA8 255024 073 to grommet with Loctite 406 or equivalent adhesive Trim hose flush with top of grommet and protruding slightly from the bottom of the cargo pod facing aft sheared at a 45 angle Figure 13 Figure 13 Drain Hole of Cargo Pod Fuel Drain Compartment n Install cargo pod to aircraft as per instructions in SB GA8 2004 14 o After the cargo pod is installed on t
9. wD A Mahindra Aerospace Company SB G A8 201 2 96 GIPPSAERO Issue 4 PO Box 881 Morwell Victoria 3840 Australia MANDATORY Ph 61 0 35172 1200 Fax 61 0 35172 1201 www gippsaero com Service Bulletin Subject Fuel System Ventilation and Drainage Modification Applicability GAB Type aircraft S N GA8 02 012 GA8 TC 320 02 16 GA8 TC 320 03 25 GA8 TC 320 09 120 and GA8 08 128 up to GA8 GA8 TC 320 13 205 Amendments 1 Nil initial issue 2 Figure 5 dimensions amended due to typographical error 3 Five drain holes added see Figure 5 6 7 8 and 9 Aircraft with cargo pod instructions part 2 added Applicability changed to include aircraft up to GA8 GA8 TC 320 13 205 4 Figure 12 illustration improved Part 2 instruction 24 m adhesive type added Weight and Balance implication included Background The GA8 GA8 TC 320 aircraft Mk II fuel system features an integral sump tank located in the floor structure forward of the co pilot seat Between the aircraft floor skin and the top of the collector tank a compartment exists which is currently not ventilated and drained as required by FAR 23 967 b See Figure 1 The drainage modification of the compartments adjacent to the integral sump described in earlier issues of this Service Bulletin was deemed unsatisfactory and resulted in five additional drainage holes being implemented as part of this issue as required by FAR 23 967 b Figure 10 Cockpit Centre Console
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