Van's Aircraft RV 12iS Production Acceptance Procedures Download | Manualshive

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Revision: 2.3

Date: 10/30/20

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RV-12iS

PRODUCTION ACCEPTANCE PROCEDURES

AIRCRAFT SERIAL NUMBER: _______________

ASTM F 3035-13 states that the manufacturer (Van's Aircraft) shall maintain a Quality Assurance
Record (QAR) for each LSA produced. The QAR shall consist of (among other records)
"Applicable final inspection records, check, and test documentation from the production
acceptance procedures"

Van's Aircraft
14401 Keil Rd. NE
Aurora, OR 97002
U.S.A.

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Summary of Contents for RV 12iS

Page 1: ...13 states that the manufacturer Van s Aircraft shall maintain a Quality Assurance Record QAR for each LSA produced The QAR shall consist of among other records Applicable final inspection records chec...

Page 2: ...last paragraph 11 15 2018 G2 2 Added Ensure trim tab in TAKEOFF position Added 1 8 to 7 5 16 measurements 2 1 Appendix Cover Page Added cover page and explanation of appendix usage 11 5 19 Appendix 2...

Page 3: ...IGHT BALANCE G7 1 SECT G8 FUEL SYSTEM CALIBRATION G8 1 SECT G9 PLACARDS CHECK G9 1 SECT G10 PREFLIGHT INSPECTION G10 1 SECT T1 TAXI TESTS T1 1 SECT F0 FLIGHT TEST PROCEDURE OVERVIEW F0 1 SECT F1 FLIGH...

Page 4: ...nitial flight This is followed by a taxi test and a series of flight tests that will verify the aircraft operation handling and performance characteristics After the flight tests are complete there is...

Page 5: ...he bus voltage to approximately 13 6 volts Follow the instructions in the downloaded Read Me file to update and configure your EFIS per the manufacturer s instructions Actuate NOSE UP side of trim swi...

Page 6: ...Revision 2 3 Date 10 30 20 G1 2 FIGURE 2 TRIM SPEED ADJUSTMENT KNOB LOCATION ON THE AFT SIDE OF THE AV 60000 POWER MODULE FIGURE 1 ACCESSING THE TRIM SPEED CONTROL KNOB...

Page 7: ...s for audio balance NOTE GTR200 EFIS warning and AOA tone levels may be adjusted within the EFIS setup menu Both of these tones summed together are controlled by the GTR200 Aux 2 input level Stall War...

Page 8: ...access covers on bottom of fuselage Verify that main landing gear attach nuts are properly torqued Verify that brake system has been filled with MIL H 5606 or equivalent and fluid reservoir is filled...

Page 9: ...om full forward to full aft Verify smooth movement of the stabilator with no binding and little or no friction Hold the stick full left while moving from full forward to full aft Verify smooth movemen...

Page 10: ...the stop Measure distance from bottom of rudder trailing edge to center of anti servo pushrod with stabilator held in full up position Distance inches nominal distance 7 1 8 inches 18 1cm measured ho...

Page 11: ...inch 3 17mm gap between the flaperon and the fuselage skin when the flaperon is deflected to its highest up position If the flaperon gap is below minimum use aluminum shears and a file to trim the ex...

Page 12: ...e brackets and the upper brace restrained in the full forward slot Verify both left and right seat cushions are in place and fit well to seat back and cabin floor Verify that at any point in sticks ra...

Page 13: ...trol knob is fully closed Fill cooling system in accordance with Rotax SI 912 016 latest revision use of standard coolant is recommended See KAI 50iS U 02 to remove the AN913 3D pipe plug that was tem...

Page 14: ...ved filter fuel and return it to the fuel tank then repeat test until fuel comes out clean Reconnect the fuel line Run fuel pumps for approximately 30 seconds each individually then both at once and r...

Page 15: ...Revision 2 3 Date 10 30 20 G4 3 Section G4 checks completed by Printed Name Title Aircraft Serial Number Signature Date...

Page 16: ...m hose to the AOA port Turn on the EFIS see Dynon setup NOTE above use the syringe to slowly and carefully push air into the AOA port Look for an airspeed indication on the EFIS push in the syringe un...

Page 17: ...altitude _______ ft after one minute Maximum allowable static system leak rate is 100 ft in one minute NOTE If leakage is excessive inspect the modeling clay seal before inspecting other static syste...

Page 18: ...four cylinders iS Positive fuel flow Once oil temperature exceeds 122 F 50 C ULS Perform carburetor synchronization procedure as called out in Section 12 of the RV 12iS Maintenance Manual ULS Run up...

Page 19: ...owls and check for debris Install Cowl Dynamically balance the propeller according to the instructions provided by the dynamic balance equipment manufacturer s instructions If balance weights are need...

Page 20: ...0 20 G7 1 Section G7 Weight and Balance Complete the weight and balance procedure found in Chapter 1 of the RV 12iS Maintenance Manual Section G7 checks completed by Printed Name Title Aircraft Serial...

Page 21: ...nge total ____ sensor value ______ visual gauge _______ total ____ sensor value ______ visual gauge _______ total ____ sensor value ______ visual gauge _______ total ____ sensor value ______ visual ga...

Page 22: ...rward Verify that CABIN HEAT is near cabin heat knobs and PULL ON is on knob ends ULS Verify that PULL ON is below choke control ULS Verify that CHOKE is on choke knob end Verify that fuel valve ON OF...

Page 23: ...ompleted signed Weight and Balance worksheet Perform a complete Preflight inspection as called out in Section 4 of the Pilot Operating Handbook All visible surfaces are free of deformation distortion...

Page 24: ...Revision 2 3 Date 10 30 20 G10 2 THIS PAGE INTENTIONALLY LEFT BLANK...

Page 25: ...on one wheel Perform this task in both directions Latch Canopy Once oil temperature has reached at least 122 degrees F 50 C perform a 4000 RPM run up and verify that the brakes can hold the aircraft s...

Page 26: ...proper engine and systems operation following POH procedures Increase the RPM to 4000 RPM Check that the Stall Warning audio tone level is loud enough to function as a warning with the engine running...

Page 27: ...plications to flying qualities structural strength and or performance Thus an RV 12iS with a configuration not conforming to the design standard must be tested as if it were a completely new design Th...

Page 28: ...ded Apply rudder as necessary to center the ball and determine whether right or left trim will be needed Add bend angle to the trim tab for right rudder effect straighten for left trim Fly the airplan...

Page 29: ...ults in significantly reduced fuel consumption at a cruise power setting The RV 12iS when equipped with an iS engine has an adjustable Eco Stop feature in the throttle quadrant to help the pilot quick...

Page 30: ...e check Optional AP Servo Calibration Cruise speed Airspeed calibration check AOA Calibration Flight Envelope Expansion 3 1050 lb Vx climb performance measurement Stall Evaulation Slow Flight Airspeed...

Page 31: ...NGS _____ ACCELERATION LIMITS 2g flaps retracted 1 5g flaps extended or full AIRSPEED LIMITS 120kt IAS with flaps up 65kt IAS with flaps or full PRE FLIGHT PREPARATION Set EFIS data log rate to 4 hert...

Page 32: ...ndicating and within limits iS Fuel Flow indicating a reasonable value All voltages indicating and within limits Amperage indicating and within limits Engine Power Output RPM appropriate during variou...

Page 33: ...ps Note amount of pitch trim change required Note amount of attitude change Note amount of roll trim change Note any controllability problems flaps to full flaps Note amount of pitch trim change requi...

Page 34: ...h Roll Yaw Stall Warning Evaluation Power Off w immediate recovery wings level ball centered no deep stalls or aggravated stalls Flaps up Vs Note indicator reading at onset of buffeting Note indicator...

Page 35: ...s Before shut down throttle to idle and verify RPM is within range called out in Section G6 Post flight activities Adjust rudder trim if required Adjust roll trim if required Adjust stall warning vane...

Page 36: ...Revision 2 3 Date 10 30 20 F1 6 THIS PAGE INTENTIONALLY LEFT BLANK...

Page 37: ...2 kt IAS with flaps or full PRE FLIGHT PREPARATION Set EFIS data log rate to 4 hertz Erase old flight data within EFIS if downloaded Familiarization with EFIS interface and AOA calibration procedure O...

Page 38: ...ght at 55 kt IAS with power at idle quickly advance the throttle as would be the case in a go around or balked landing and re trim for full throttle climb at 60 kt IAS Perform this test a minimum of t...

Page 39: ...y no unusual flying qualities or other unexpected behavior Fully extend flaps and allow speed to reach 82 kt IAS add power and or descend as required Perform easy maneuvers Verify no unusual flying qu...

Page 40: ...atter to increase RPM adjust propeller pitch in 0 1o increments Download EFIS data archive file Enter data from four way speed box into RV 12iS Flight Test Data spreadsheet Correct any engine issues l...

Page 41: ...___ ______ SURFACE WIND BEGIN _______ ______ LANDINGS _____ ACCELERATION LIMITS 4g flaps retracted 2g flaps extended or full AIRSPEED LIMITS 136 kt TAS with flaps up 82 kt IAS with flaps or full PRE F...

Page 42: ...3 000 ft to 5 000 ft 4 000 ft to 6 000 ft 5 000 ft to 7 000 ft 6 000 ft to 8 000 ft 7 000 ft to 9 000 ft 8 000 ft to 10 000 ft Stalls Power Off w recovery delayed 3 seconds after break wings level ba...

Page 43: ...ch 136 kt TAS Perform easy maneuvers Verify no unusual flying qualities or other unexpected behavior Landing Power off approach at minimum 55 kt with flaps as required for glide path control Post flig...

Page 44: ...Revision 2 3 Date 10 30 20 F3 4 THIS PAGE INTENTIONALLY LEFT BLANK...

Page 45: ...BEGIN _______ ______ LANDINGS _____ ACCELERATION LIMITS 4g flaps retracted 2g flaps extended or full AIRSPEED LIMITS 136 kt TAS with flaps up 82 kt IAS with flaps or full PRE FLIGHT PREPARATION Set E...

Page 46: ...T RPM FUEL FLOW GAL HR MAP EFIS Pitch Offset adjustment If required adjust the Pitch Attitude offset per the EFIS manufacturer s instructions If necessary climb to no lower than 3 000 ft AGL and estab...

Page 47: ...m NAV COM GTN 650Xi is working properly for approaches Post flight activities Download EFIS data and archive file Enter data from four way speed boxes into RV 12iS Flight Test Data spreadsheet Fill fu...

Page 48: ...Revision 2 3 Date 10 30 20 F4 4 THIS PAGE INTENTIONALLY LEFT BLANK...

Page 49: ...fy that main landing gear attach nuts are properly torqued FLIGHT CONTROLS Verify Stabilator Cable Tension See KAI 38iS U 17 For E LSA aircraft Van s does not require a copy of the completed PAP We st...

Page 50: ...Revision 2 3 Date 10 30 20 G11 2 THIS PAGE INTENTIONALLY LEFT BLANK...

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