SB-GA Issue 1

Transcription

1 PO Box 88, Morwell, Victoria 80, Australia Ph + 6 (0) Fax + 6 (0) Service Bulletin Subject: SB-GA Issue Conversion of aircraft from CASA certificated FAR Amendment 5/8 status to CASA certificated FAR Amendment 5 status. Applicability: All GA8 aircraft serial numbers GA through GA Amendments: Nil Initial Issue Background: Gippsland Aeronautics has upgraded the certification status of the GA8 from FAR at Amendment 5/8 to FAR at Amendment 5. This Service Bulletin documents the modifications required to convert a CASA certificated Amendment 5/8 aircraft to a CASA certificated Amendment 5 aircraft. Gippsland Aeronautics has already incorporated some of the modifications listed in this Service Bulletin into certain aircraft during production. Refer to the serial number applicability listed for each modification to see if your aircraft is affected. Before commencing work, read through the contents thoroughly. In the event of any difficulties incorporating this Service Bulletin, please contact Gippsland Aeronautics for assistance. Compliance: This Service Bulletin is optional, however, it is a pre-requisite for Service Bulletin SB-GA that converts a CASA certificated Amendment 5 aircraft to an FAA certificated Amendment 5 aircraft. Weight and Balance: Negligible effect on weight and balance. Approval: This Service Bulletin has been approved pursuant to Regulation 5 of CAR988. SB-GA Issue: Date of Issue: April 00 Page of

2 Parts: Item P/N Description Qty GA8-50- Large cabin window surround GA8-50- Rear cabin window surround GA Rear LHS baggage window surround GA Rear RHS baggage window surround 5 GA LHS baggage side panel 6 GA RHS baggage side panel 7 GA Fwd LHS wall panel 8 GA Fwd RHS wall panel 9 GA8-50- Sliding door panel 0 GA8-50- Centre RHS wall panel GA Rear LHS roof trim panel GA Rear RHS roof trim panel GA Rear roof trim panel GA8-50- Centre roof trim panel 5 GA8-50- Fwd roof trim panel 6 GA Fwd LHS roof trim panel 7 GA Fwd RHS roof trim panel 8 GA Upper Fwd LHS wall panel 9 GA Rear door handle mechanism cover 0 GA Inertia reel cover (LHS) GA Inertia reel cover (RHS) GA Aft luggage bin 77 5mm Velcro hook A/R 87 5mm Velcro loop A/R 5 GA8-0-7 Trim position placard 6 GA8-0-5 Loading placard 7 GA Circuit board 8 MFR-K0 Pitot heat indicator resistor assembly 9 GA Flight instrument sub-panel 0 GA8-0-5 Manoeuvre Speed Placard A07/A06C Amber Pitot Heat light A07/A06C Red Oil light A07/A06C Blue Switch On light GA Oil pressure warning switch 5 MS09-D Plug 6 GA Oil pressure sensor fitting 7 MS08-D 5 elbow 8 MS08-D 90 elbow 9 AN- Bolt 0 AN970- Washer GA Oil pressure line GA8-0-7 Placard GA8-50- Capacitor mounting bracket assembly GA8-0- Solenoid box cover caution placard 5 ALS0A7KE F 0 volt capacitor 6 GA8-50- Solenoid box SB-GA Issue: Date of Issue: April 00 Page of

3 Item P/N Description Qty 7 GA8-50- Circuit breaker panel 8 MS07- Anchor nut 5 9 MS06AD- Rivet 0 50 GA8-60- Shunt bas bar 5 EI VA-A-50 Volt/amp indicator (includes loom and shunt) 5 MF-R090 Re-settable fuse 5 GA8-0-5 Volts placard 5 GA Diode Assembly 55 GA Excitation resistor assembly 56 MS5059- Double pole single throw switch Tee Tube clip 59 H5 SAE 0R7 /6 rubber hose 9 in. 60 MS070AD6- Rivet 6 6N0 Union tee 6 59P0 Insert stabiliser 6 6N0 Inline connector 6 59N0 Plug 65 E000-0 / NS ¼ Nylon hose 6 in. 66 C0-0-0 CASA Approved Flight Manual 67 C CASA Approved Service Manual Parts Availability: New parts can be obtained directly from Gippsland Aeronautics. Tel.: Fax.: spares@gippsaero.com Instructions:. Interior Panel Replacement NOTE: A/C serial number GA8-0-08, and serial numbers GA and up had this modification incorporated during production.. Remove the interior trim panels in the main cabin area between the rear of the cockpit and the aft bulkhead. Take care not to damage the bags of insulation fitted between the trim panels and the outer aluminium skin. Note the sequence in which the panels are removed, as the new panels will have to be installed in the opposite order due to panel overlaps.. Using the existing panels as templates, drill off holes where required.. Using the existing panels for reference, attach strips of Velcro to the new panels where required.. Install the new trim panels, and attach using hardware removed in step. SB-GA Issue: Date of Issue: April 00 Page of

4 . Aft Luggage Bin Replacement (if fitted) NOTE: A/C serial number GA8-0-08, and serial numbers GA and up had this modification incorporated during production.. Remove the existing aft luggage bin by removing the S0Z6-8 countersunk screws attaching the bin to the aft bulkhead, and the two AN- bolts attaching the bin to the cross member. Refer to Figure -.. Using the existing bin as a guide, drill off holes in the flange of the new aft luggage bin (P/N GA8-550-).. Insert the new bin and attach to the aft bulkhead using hardware removed in step.. Drill through the brackets on the cross member and attach using the AN- bolts removed in step. The cross member is accessed through the bottom skin inspection panel. Refer to Figure -. Figure - Aft luggage bin installation SB-GA Issue: Date of Issue: April 00 Page of

5 Figure - Cross member viewed through bottom skin inspection hole. Trim Position Placard Replacement. Remove the existing trim position placard.. Wind the trimming wheel to the full nose down position.. Locate the new placard (P/N GA8-0-7) so that the trim position pointer lines up with the line marking on the placard indicating full nose down. Refer to Figure -. SB-GA Issue: Date of Issue: April 00 Page 5 of

6 . Loading Placard Replacement Figure - Trim position placard location. Remove the following placards for the Cabin Baggage Shelf, Main Cargo Area and Aft Luggage Bin. SB-GA Issue: Date of Issue: April 00 Page 6 of

7 . Locate the new loading placard (P/N GA8-0-5) on the front face of the cabin baggage shelf adjacent to the sliding door opening per Figure Pitot Heat Warning Sensor Installation Figure - Load placard location NOTE: A/C serial numbers GA8-0-0 and up had this modification incorporated during production. WARNING: DO NOT PERFORM ANY SORT OF MAINTENANCE ON THE ELECTRICAL SYSTEM IN CONJUNCTION WITH MAINTENANCE ON THE FUEL SYSTEM. THE ESCAPE OF FUEL FUMES UNDER THE FLOOR AND/OR IN THE AIRCRAFT MAY CAUSE AN EXPLOSION. WARNING: IF THE ALTERNATOR EXCITATION SYSTEM INCORPORATING THE CAPACITOR CIRCUIT HAS ALREADY BEEN INSTALLED, PERFORM THE FOLLOWING ACTION TO ENSURE THAT THE CAPACITOR CIRCUIT IS DISARMED BEFORE REMOVING THE COVER PANEL TO ACCESS THE UNDERFLOOR AREA IN FRONT OF THE PILOT S SEAT (i) (ii) OPEN THE CIRCUIT BY PULLING THE BUS CONTROL BREAKER SWITCH THE BUS MASTER SWITCH ON ENSURE THAT THE BREAKER REMAINS OPEN AND THE MASTER SWITCH REMAINS ON FOR THE DURATION THAT THE COVER PANEL IS REMOVED. NOTE THAT BUS IS NOT LIVE WHILST THE BUS CONTROL BREAKER IS PULLED. SB-GA Issue: Date of Issue: April 00 Page 7 of

8 J0 FHA WHA WHB8 WHBN BUS. Remove pilot s seat and floor carpet. Remove battery box cover. Disconnect battery. Disarm the alternator excitation system if already installed.. Install circuit board (P/N GA ) and wire FHA to output terminal of the Pitot Heat Switch/Breaker in the overhead switch panel. Refer to Figure 5-.. Install pitot heat indicator resistor assembly on the pitot heat feed wire FHA at pin 5 of socket J0 of the wing root junction block. Solder one end of wire WHA to the resistor, and the other end to pin of socket J5 at the overhead electrical panel. Install wire WHBN between pin of socket J5 and a suitable earth. Install wire WHB8 between pin of socket J5 and pin 5 of plug P0, and wire WHA8 between pin 5 of socket J0 and pin of plug of the caution system controller. Refer to Figure 5-. OVERHEAD PANEL ASSY. 0A PITOT HEAT FHA J5 WHA 5 WHB8 5 WHA8 PITOT HEAT INDICATOR RESISTOR ASSEMBLY 5 FHA P0 J0 CAUTION SYSTEM CONTROLLER P Figure 5- - Pitot heat installation (overhead panel). Re-connect battery, replace battery box cover, re-install pilot s seat and floor carpet. 6. Upgraded Caution/Warning Light System WARNING: DO NOT PERFORM ANY SORT OF MAINTENANCE ON THE ELECTRICAL SYSTEM IN CONJUNCTION WITH MAINTENANCE ON THE FUEL SYSTEM. THE ESCAPE OF FUEL FUMES UNDER THE FLOOR AND/OR IN THE AIRCRAFT MAY CAUSE AN EXPLOSION. WARNING: IF THE ALTERNATOR EXCITATION SYSTEM INCORPORATING THE CAPACITOR CIRCUIT HAS ALREADY BEEN INSTALLED, PERFORM THE FOLLOWING ACTION TO ENSURE THAT THE CAPACITOR CIRCUIT IS DISARMED BEFORE REMOVING THE COVER PANEL TO ACCESS THE UNDERFLOOR AREA IN FRONT OF THE PILOT S SEAT (i) OPEN THE CIRCUIT BY PULLING THE BUS CONTROL BREAKER (ii) SWITCH THE BUS MASTER SWITCH ON ENSURE THAT THE BREAKER REMAINS OPEN AND THE MASTER SWITCH REMAINS ON FOR THE DURATION THAT THE COVER PANEL IS REMOVED. NOTE THAT BUS IS NOT LIVE WHILST THE BUS CONTROL BREAKER IS PULLED. SB-GA Issue: Date of Issue: April 00 Page 8 of

9 . Remove pilot s seat and floor carpet. Remove battery box cover. Disconnect battery. Disarm the alternator excitation system if already installed.. Remove the underside cover panels between the instrument panel and the firewall.. Disconnect the vacuum line between the vacuum pump and the vacuum regulator, and disconnect the vacuum regulator from the firewall.. Remove the 7 screws attaching the flight instrument sub-panel to the main instrument panel. 5. Disconnect caution/warning light connector J/P, turn co-coordinator connector J5, and vacuum pressure switch wires WVA and WVBN. 6. Disconnect pitot line from the airspeed indicator, and the static line from the altimeter. 7. Remove the sub-panel from the aircraft. 8. Remove all instruments, caution/warning lights, dimmer and press-to-test switches, and the Manoeuvre Speed V A - KIAS placard from the sub-panel, and transfer to the new sub-panel (P/N GA8-0-65) featuring 6 holes for caution/warning lights. Discard old sub-panel. 9. The caution/warning lights are to be arranged, from left to right, Vac, Oil, Alt, Alternate Air, Pitot Heat and Switch On. NOTE: Steps 0 and are only applicable to S/N s GA to GA Install wire WHA between pin of plug P6 of the caution system controller and pin of socket J. Refer to Figure 6- for wiring schematic (Note this wire may already be installed. If so disregard this step).. Install wire WHB between pin of plug P and the negative terminal of the PITOT HEAT light. Refer to Figure 6- for wiring schematic. NOTE: Step and are only applicable to S/N s GA8-0-0 and up. Install wire WSA between pin 7 of plug P6 of the caution system controller and pin 7 of socket J. Refer to Figure 6- for wiring schematic NOTE: This wire may already be installed. If so disregard this step.. Install wire WSB between pin 7 of plug P and the negative terminal of Switch On light. Refer to Figure 6- for wiring schematic.. Install wire WPA between pin 6 of plug P0 of the caution system controller and pin of socket J. Refer to Figure 6- for wiring schematic NOTE: This wire may already be installed. If so disregard this step. 5. Install wire WPB between pin of plug P and the negative terminal of Oil light. Refer to Figure 6- for wiring schematic. 6. Connect wire WAB between pin 0 of plug P and the positive terminal of the oil pressure warning light. Refer to Figure 6- for wiring schematic. SB-GA Issue: Date of Issue: April 00 Page 9 of

10 P6 P0 CAUTION SYSTEM CONTROLLER + WTC WTB 7. Connect wires WDB thru WDF between the positive terminals of each light, except for the oil pressure warning light. Refer to Figure 6- for wiring schematic. WDB WDB WDC WDC WARNING LIGHTS DIM P P P5 P P P P WHA WSA WPA WPA WHA WSA J WPB WHB 5 WBB 6 WVB 7 WSB 8 WKB 9 WDB 0 WAB WTB WDB WTC WDC 5 P WTB WTC WDB WDC WSB WDC WDD WHB WDD WDE WKB WDE WDF WBB WAB WPB WARNING LIGHTS TEST SWITCH ON PITOT OFF/FAIL ALTERNATE AIR WARNING ALTERNATOR WARNING OIL PRESSURE WARNING WDF -+ WVB Figure 6- Caution/warning light wiring schematic (instrument panel) - VACUUM WARNING 8. Drill a 0.89 diameter hole in the firewall 5.0 above the hot air duct and 9.5 from the left hand side cabin wall. Fit oil pressure sensor fitting (P/N GA8-790-) and attach using an AN- bolt and AN970- washer. Refer to Figure Connect oil pressure warning switch (P/N GA8-790-), MS08-D 5 elbow, MS09-D plug and MS08-D 90 elbow to the oil pressure sensor fitting. Refer to Figure Disconnect existing oil line between the oil pressure indicator on the instrument panel and the firewall fitting. Connect oil pressure line (P/N GA8-790-) between the firewall fitting and the MS08 elbow. Connect oil pressure line (P/N GA8-790-) between the MS08 elbow and the oil pressure indicator. Refer to Figure 6-. NOTE: Instead of fitting new oil lines, the existing line may be modified by cutting in half and fitting Stratoflex or Aeroquip 9- end connectors SB-GA Issue: Date of Issue: April 00 Page 0 of

11 BL 0.00 Bulkhead oil line fitting Oil pressure line GA Wire WPA MS08-D elbow +ve MS09-D plug Oil pressure line GA Wire WPBN -ve To oil pressure indicator Oil pressure warning switch GA MS08-D elbow Oil pressure sensor fitting GA Fwd AN- bolt AN970- washer Oil pressure sensor fitting P/N GA Cut away insulation to fit sensor fitting against firewall Figure 6- Oil pressure line modification SB-GA Issue: Date of Issue: April 00 Page of

12 CAUTION SYSTEM CONTROLLER Firewall. Install wire WPA between the positive terminal of the oil pressure switch (GA8-790-) and pin plug of the caution system controller. Install wire WPBN between the negative terminal of the oil pressure switch and pin of plug 5 of the caution system controller. Refer to Figure 6- for wiring schematic WPBN P5 WPA P 0 Engine Bay Sensor fitting GA Oil Pressure Indicator WPBN WPA - + Oil pressure warning switch GA Figure 6- Oil pressure switch installation. Re-connect battery, replace battery box cover, re-install pilot s seat and floor carpet.. Install Warning Lights placard (P/N GA8-0-7) around the press-to-test and dimmer switches, and Manoeuvre Speed placard (P/N GA8-0-5) under the airspeed indicator. Refer to Figure 6-.. Test that all six lights are functional by pressing the press-to-test button. 5. Perform operational test of newly installed lights by the following procedure. (i) With the Master Switches ON and the engine not running: i. check that the Oil light illuminates. ii. iii. iv. with the pitot-heat switched off, check that the Pitot Heat light illuminates. with the pitot-heat switched on, check that the Pitot Heat light extinguishes. with the pitot-heat switched on, disconnect left hand wing root electrical connector P0/J0. Check that the Pitot Heat light illuminates. v. with the fuel pump switched on, check that the Switch On light illuminates. (ii) With the engine running: i. check that the Oil light extinguishes when the oil pressure indicates above 5 psi. SB-GA Issue: Date of Issue: April 00 Page of

13 . Conduct pitot-static leak per section of the GA8 Service Manual. 7. Volt/Amp Indicator Replacement Figure 6- Caution/warning light arrangement NOTE: A/C serial numbers GA and up had this modification incorporated during production. WARNING DO NOT PERFORM ANY SORT OF MAINTENANCE ON THE ELECTRICAL SYSTEM IN CONJUNCTION WITH MAINTENANCE ON THE FUEL SYSTEM. THE ESCAPE OF FUEL FUMES UNDER THE FLOOR AND/OR IN THE AIRCRAFT MAY CAUSE AN EXPLOSION. WARNING IF THE ALTERNATOR EXCITATION SYSTEM INCORPORATING THE CAPACITOR CIRCUIT HAS ALREADY BEEN INSTALLED, PERFORM THE FOLLOWING ACTION TO ENSURE THAT THE CAPACITOR CIRCUIT IS DISARMED BEFORE REMOVING THE COVER PANEL TO ACCESS THE UNDERFLOOR AREA IN FRONT OF THE PILOT S SEAT (i) OPEN THE CIRCUIT BY PULLING THE BUS CONTROL BREAKER (ii) SWITCH THE BUS MASTER SWITCH ON ENSURE THAT THE BREAKER REMAINS OPEN AND THE MASTER SWITCH REMAINS ON FOR THE DURATION THAT THE COVER PANEL IS REMOVED. NOTE THAT BUS IS NOT LIVE WHILST THE BUS CONTROL BREAKER IS PULLED. SB-GA Issue: Date of Issue: April 00 Page of

14 . Remove pilot s seat and floor carpet. Remove battery box cover. Disconnect battery. Disarm the alternator excitation system if already installed.. Disconnect wires DAA8, DAB8 and DAD8N between the instrument panel mounted battery monitor and the ammeter shunt located on the rear of the firewall at the left lower engine mount bolt. Discard wire DAD8N.. Disconnect and discard wire DAA8 between terminal DAA of the Bus/Bus switch and the battery monitor.. Disconnect, remove and discard the battery monitor from the instrument panel. 5. Disconnect, remove and discard mode switch and wiring. The mode switch hole may be blanked with a rubber plug or similar. 6. Disconnect and remove all parts from the solenoid box. 7. Disconnect floor-mounted circuit breakers and remove circuit breaker panel. Remove circuit breakers from the existing panel and attach to new circuit breaker panel (P/N GA8-60-). NOTE: Step 8 is only applicable to S/N s GA to GA S/N s GA8-0-0 to GA8-0-0 have an alternative capacitor installation that is functionally equivalent to the following. 8. Attach capacitor and capacitor mounting bracket (P/N GA8-50-) to the new circuit breaker panel. Refer Figure 7-. Refer to Section 8 Alternator Excitation System Installation for capacitor wiring details. SB-GA Issue: Date of Issue: April 00 Page of

15 CIRCUIT BREAKER PANEL P/N GA8-60- CAPACITOR MOUNTING BRACKET P/N GA8-50- CAPACITOR ENSURE CAPACITOR IS SECURELY HELD BY MOUNTING BRACKET WITHOUT APPLYING DISTORTING PRESSURE Figure 7- Circuit breaker panel capacitor installation SB-GA Issue: Date of Issue: April 00 Page 5 of

16 Attach the new ammeter shunt to the circuit breaker panel. Connect the shunt bus bar (P/N GA8-60-) between the shunt and 00A breaker. Refer to Figure Shunt Bus Bar GA8-60- Figure 7- Shunt and bus bar installation 0. Unfasten the screws attaching the solenoid box to the floor and remove the solenoid box. SB-GA Issue: Date of Issue: April 00 Page 6 of

17 . Extend the solenoid box floor opening by.0 as per Figure 7-. Use the new elongated solenoid box (P/N GA8-50-) as a pattern to locate 5 additional anchor nut positions at the front of the extended opening. Rivet MS07- anchor nuts to the floor using MS06AD- rivets..00" MS07- Anchor Nut Pattern 5 Places Fwd Figure 7- Solenoid box floor opening extension. Fit all parts removed in step 6 into the new elongated solenoid box per Figure 7-.. Install the new elongated solenoid box into the floor and secure using the MS69S5 screws removed in step 0. SB-GA Issue: Date of Issue: April 00 Page 7 of

18 GP+ GND SOL B PBA B PBA PEA PSA GP ST. Reconnect wiring to the components in the solenoid box. AN55-0R6 SCREW AN960-0L WASHER 70A RELAY MS589-7 GROMMET MAIN BUS MS589-0 GROMMET GA8-50- SOLENOID BOX GP OVERVOLT PROTECTION RELAY MS589- GROMMET PCB LOCKING SUPPORT MS69S50 SCREW 5. Install and connect circuit breaker panel. Figure 7- Solenoid box fit-out 6. Disconnect wire PGA6 from the 00A Alt. Main circuit breaker and connect to terminal PGA of the new ammeter shunt. Install wire PGB6 between terminal PGB of the new ammeter shunt and the 00A Alt. Main circuit breaker. Refer to Figure 8- for wiring schematic. 7. Connect re-settable fuses MF-R090 to the positive and negative terminals of the ammeter shunt. 8. Solder wires DAA8 and DAB8 disconnected in step to the re-settable fuses. 9. Splice wires DAA8 and DAB8 to the orange and brown wires of the volt/amp indicator loom. 0. Connect the black wire and white with red trace wire from the volt/amp indicator loom to the Earth bus located on the left hand side of the fuselage directly above the System Controller and Caution System Controller. SB-GA Issue: Date of Issue: April 00 Page 8 of

19 . Connect the red wire from the volt/amp indicator loom to terminal DAA of the Bus /Bus switch.. Connect the white with brown trace wire from the volt/amp indicator loom to the positive terminal of the oil pressure indicator.. Install new volt/amp meter P/N VA-A-50 in the instrument panel at the location previously occupied by the battery monitor. Connect the volt/amp indicator loom to the instrument.. Re-connect battery, replace battery box cover, re-install pilot s seat and floor carpet. 5. Remove existing battery monitor placard and install new ammeter placard P/N GA Alternator Excitation System Installation NOTE: A/C serial numbers GA8-0-0 and up had an equivalent modification incorporated during production. WARNING: DO NOT PERFORM ANY SORT OF MAINTENANCE ON THE ELECTRICAL SYSTEM IN CONJUNCTION WITH MAINTENANCE ON THE FUEL SYSTEM. THE ESCAPE OF FUEL FUMES UNDER THE FLOOR AND/OR IN THE AIRCRAFT MAY CAUSE AN EXPLOSION.. Remove pilot s seat and floor carpet. Remove battery box cover. Disconnect battery.. Connect Earth wire PGB8N from capacitor earth terminal to the screw securing the 70A relay to the solenoid box.. Replace main supply wire between the alternator main and alternator field circuit breakers with diode assembly (P/N GA8-60-7). Ensure correct orientation of diode. Refer to Figure 8- for wiring schematic.. Install excitation resistor assembly (P/N GA8-60-9) between the power supply side of the alternator field circuit breaker and the positive terminal of the capacitor. Refer to Figure 8- for wiring schematic. 5. Remove the alternator field relay assembly, including diode assembly (P/N GA8-60-5) between terminals 85 and 86 of the field relay, and wires PGA8 and PGB8N. 6. Remove the existing Bus master switch located in the overhead electrical panel assembly and replace with the new double pole double throw Bus master switch (P/N MS5059-). Re-connect existing wires PBA8 and PBB8 to terminals of the new switch. Refer to Figure 8- for wiring schematic. 7. Install and secure wire PGA into the aircraft main wiring loom from the alternator field circuit breaker terminal to pin of plug P05, and wire PGB from pin of socket J05 to terminal PGB of newly installed Bus master switch. Refer to Figure 8- for wiring schematic. 8. Install and secure wire PGC into the aircraft main wiring loom from terminal PGC of the newly installed Bus master switch to pin 5 of socket J05, and wire PGD from pin 5 of plug P05 to terminal ALT. SW. of the system controller (P/N GA00-00-). Refer to Figure 8- for wiring schematic. 9. Install new solenoid box cover caution placard (P/N GA8-0-). 0. Re-connect battery, replace battery box cover, re-install pilot seat and floor carpet.. Perform operational test by the following procedure: (i) (ii) (iii) Start aircraft engine. Pull the Bus control breaker, and turn both Master Switches OFF. Wait a minimum of 0 seconds and turn the Bus Master Switch ON. Do not activate the Bus Master Switch. (iv) Ensure Bus becomes active. SB-GA Issue: Date of Issue: April 00 Page 9 of

20 CAUTION SYSTEM STALL WARNING SYSTEM OPTIONAL CLOCK ELECT. INSTRUMENT POWER PEB8 PEB PEA FIELD SYSTEM CONTROLLER St. STARTER SOLENOID PSA PGE 50A BUS MAIN PSA KSC8 PSB MAIN BUS 85 0 PSA PBA PSA STARTER RELAY PSB 87 I S PSA KSC8 PGD ALT. SW. PGD8N CAUTION SYSTEM PGD8N K WR GND LIGHT WBA8 PBA8 EARTH BUS SOLENOID BOX ASSY. PSA B BUS SOLENOID PBB8 86 PB6A8 A BUS CONTROL PB5A8 PB6A PBA PBA8 PB5D8 WBA8 FSA8 WBA8 FSA8 PB5C PB5B B BUS SOLENOID PB6A8 PBA6 A STALL A BUS CONTROL 70A BUS MAIN GA PGB8N 7000µF 0V CAPACITOR DCA8 BUS & ALT. BUS GP GND. POWER SOLENOID 0A ALT. FIELD 8R 00A ALT. MAIN DCA8 PBA8 PBB6 PGA PGA8 5 PEA PBC PBB 5 PBA PBA6 PBD8 PEA PGB6 PBC8N PB5C8N WAY BUS PEA8 RESETTEABLE FUSE PEA8 PEB8 PEB8N PEA8 OVER VOLT RELAY GROUND POWER RECEPTACLE - + SHUNT AMMETER DAA8 PGA6 PGA PEA PEA8 RESETTEABLE FUSE DAA PGB6 PGB WN ELECT. INSTRUMENT POWER PGC PGB PGC8 PGC PGB PBC PBB DAC8 R K BUS MASTER INSTRUMENT PANEL ASSY. R DAC DAB BUS MASTER 5A CAUTION SYS. BUS PGC PGB PBB8 R K POWERPLANT START OIL PRESSURE INDICATOR CAUTION SYSTEM WN WR O N VOLT/AMP INDICATOR LOOM DAB8 WR WN O N DAA BUS PBB8 PGA PGA PBB8 PGD PBA8 PBD8 PBB8 PB5A8 PB5D8 PBB6 PGD PBA8 PBD8 P05 J0 5 J05 P0 PBC8 OVERHEAD PANEL ASSY. 5A FUEL GAUGE PB5A8 PB5D8 DAB8 O N PBB6 PB5B8 PB5C8 DAA8 PGA6 ENGINE COMPARTMENT PGE PGA6 ALTERNATOR BUS/BUS SWITCH VOLT/AMP INDICATOR J0 P0 PB5C PB5B PB5B8 PB5C8 B+ F Figure 8- Capacitor installation wiring SB-GA Issue: Date of Issue: April 00 Page 0 of

21 Figure 8- Capacitor, solenoid box installation 9. Pitot Drain Installation NOTE: A/C serial numbers GA8-0-0 and up had this modification incorporated during production.. Gain access to the location of the existing static drain by removing the inspection panel positioned directly behind the pilot s seat. Pitot Line Static Line FORWARD Static Drain Figure 9- Existing static drain location SB-GA Issue: Date of Issue: April 00 Page of

22 . Identify the pitot line and locate a suitable position to install the drain line. For A/C serial numbers GA to GA Cut the pitot line and install a drain line using a 6-00 tee, tube clips, H5 SAE 0R7 /6 rubber hose and an MS070AD6- rivet. Refer to Figure 9-. For A/C serial number GA Cut the pitot line and install a drain line using a 6N0 union tee, 59N0 insert stabilisers, 6N0 inline connector, 59N0 plug and E000-0 ¼ NS nylon hose. Refer to Figure TUBE CLIP 6-00 /6" TEE H5 SAE 0R7 /6" RUBBER TUBE TO PITOT-STATIC PROBE TO INSTRUMENT PANEL H5 SAE 0R7 /6" RUBBER TUBE MS070AD6- RIVET Figure 9- Pitot drain installation (S/N GA to GA8-0-09) SB-GA Issue: Date of Issue: April 00 Page of

23 6N0 UNION TEE 59P0 INSERT STABILISER 59P0 INSERT STABILISER TO PITOT-STATIC PROBE TO INSTRUMENT PANEL 59P0 INSERT STABILISER E000-0 I/" NYLON TUBE 59P0 INSERT STABILISER 6N0 INLINE CONNECTOR 59N0 PLUG Figure 9- Pitot drain installation (S/N GA8-0-00) Documentation:. Replace existing Flight Manual C0-0-0 with Flight Manual C Replace existing Service Manual C with Service Manual C Update aircraft log book to reflect incorporation of this Service Bulletin. Compliance Notice: Complete the Service Bulletin Compliance Notice and return to Gippsland Aeronautics by fax/mail. SB-GA Issue: Date of Issue: April 00 Page of

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25 DOCUMENT COMPLIANCE NOTICE Document: Service Bulletin SB-GA Aircraft Serial Number: GA8- I/we have incorporated Service Bulletin SB-GA for the above aircraft. Signed Please post or fax this compliance notice to: Gippsland Aeronautics Attn: Technical Services P.O. Box 88 Morwell Victoria 80 Australia Fax.: