Van's Aircraft RV 12iS Manual

Revision: 2.3 Date: 10/30/20
i
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.

Revision: 2.3 Date: 10/30/20
ii
REVISION SUMMARY
Whenever revisions are issued, they must be inserted in the appropriate place in the
manual. A black vertical line along the left margin of the page will identify revised text
and illustrations. Changes in spelling, punctuation and formatting will not be marked.
To verify the latest revision of the PAP, compare the revision level found on the cover
page with the latest revision posted on the RV-12iS Service Information page of the
Van’s Aircraft web site.
Rev Page Change Date
0 None Initial Release 05/03/2018
1 Multiple Publication 10/22/2018
2 G1-1 Deleted “SV-AP optional panel or” from 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 SLSA Flight Test completely re-written
Appendix 4 Service documentation updated to new terminology (SD,
SB, SL) was (SA,SB,N).
2.2 F4-3 Replaced Garmin GTN 650 with Garmin GTN 650Xi. 10/06/20
G1-1 Clarify cooling fans should move air in opposite directions.
G4-1 Replaced “torqueing” with “tightening” for radiator pipe
plug install.
G6-2 Added instruction to dynamically balance the propeller after
the initial ground run.
Appendix
A3-1 Replaced GTN 650 with GTN 650Xi.
2.3 G1-3 Change trim adjustment knob position for Garmin autopilot
installations
10/30/20
G6-2 Added note to define acceptable timeframe for dynamic
propeller balance
completion.

Revision: 2.3 Date: 10/30/20
iii
TABLE OF CONTENTS
COVER PAGE i
REVISION SUMMARY ii
TABLE OF CONTENTS iii
INTRODUCTION iv
SECT G1 SYSTEMS CHECK G1-1
SECT G2 FLIGHT CONTROLS CHECK G2-1
SECT G3 SEATS & SAFETY BELTS G3-1
SECT G4 ENGINE CHECK G4-1
SECT G5 PITOT, STATIC, & AOA SYSTEM G5-1
LEAK CHECK
SECT G6 ENGINE GROUND RUN G6-1
SECT G7 WEIGHT & 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 FLIGHT TEST CARD - FLIGHT #1 F1-1
SECT F2 FLIGHT TEST CARD - FLIGHT #2 F2-1
SECT F3 FLIGHT TEST CARD - FLIGHT #3 F3-1
SECT F4 FLIGHT TEST CARD - FLIGHT #4 F4-1
SECT G11 POST FLIGHT TEST CHECK G11-1
APPENDIX 1 SLSA PFT FINAL INSPECTION
APPENDIX 2 SLSA FLIGHT TEST CARD
APPENDIX 3 SLSA FINAL INSPECTION CHECKLIST
APPENDIX 4 SLSA DELIVERY CHECKLIST

Revision: 2.3 Date: 10/30/20
iv
INTRODUCTION
This manual provides the Production Acceptance Procedures for the RV-12iS
Light Sport Aircraft, in accordance with ASTM Standard F3035-13. These test
procedures are designed to efficiently ensure your aircraft and systems
function properly and meet handling expectations and performance
requirements set forth in the Pilot’s Operating Handbook. The test
procedures should be completed in the order in which they are presented.
The process starts with a series of ground tests and procedures that ensure
all systems are functioning properly and prepare the airplane for initial 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 a final Post Flight Test Check.
Some of these procedures are specific to the engine installed on your RV-
12iS. Procedures denoted by (iS) are specific to the 912iS engine, while
procedures denoted by (ULS) are specific to the 912ULS engine. Procedures
which do not have a specific notation apply to both engine installations.
These procedures will help you to become familiar with your RV-12iS. Upon
completion of these tests you should continue exploring the performance
and handling characteristics of your aircraft within the approved flight
envelope. More information can be found in the Flight Training Supplement.

Revision: 2.3 Date: 10/30/20
G1-1
Section G1 - Systems Check
SWITCHES & CIRCUITS:
 Download the latest “Read Me” file, firmware, and configuration files for your EFIS from the
Downloads page of the Van’s Aircraft website.
NOTE: The read me document explains the process of downloading and installing
Van’s Aircraft factory settings for the RV-12iS, including TRIM take off and AP servo
configuration, etc.
 Check (during the first 5 mins after the hour) ELT function using test switch in the remote
panel.
 Master switch “ON”.
 Verify that the avionics cooling fans come on and move air in opposite directions, one into the
instrument bay and one out of the instrument bay.
 (ULS) Verify that the electric auxiliary fuel pump turns on (noticeable clacking noise).
 (ULS) Master switch “OFF”
 (ULS) Remove fuel pump fuse and tape it to the top of the pilot control stick
 (ULS) Master switch “ON”.
 (iS) “Fuel Pump 1” switch “ON”.
 (iS) Verify that Fuel Pump #1 turns on.
 (iS) “Fuel Pump 2” switch “ON”.
 (iS) Verify that Fuel Pump #2 turns on.
 (iS) Turn both fuel pump switches off.
 Verify EFIS display comes on.
 Connect a battery charger (compatible with your battery) to bring the 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 switch.
 Verify that when holding the trim switch the motor stops after 6 seconds and requires cycling
the switch “OFF” then “ON” to continue motion. NOTE: The built in “Runaway Trim”
function prevents a stuck switch from moving the trim tab too far in order to avoid
extreme “out of trim” conditions.
 Continue to cycle the switch until the trim motor reaches full “NOSE UP” travel.
 Verify that the tab is trailing edge down from the stabilator trailing edge.
 Actuate “NOSE DOWN” side of trim switch and use a stopwatch to determine how long it
takes the motor to run full travel. Remember to quickly cycle the switch off every 4 seconds
to allow nearly continuous motion. Run time: seconds.
NOTE: Auto Trim is provided when the SV-AP optional panel or Garmin AP pitch
servo is installed. On the ground the trim speed will run faster with auto trim.
Auto trim overrides the AV-60000 trim speed adjustment. This is true for Garmin when
the AP is on. If the SV AP Knobs is installed auto trim is always active.
The trim motor will not operate if AV-60000 trim speed adjustment is set too low when
the Garmin AP Pitch Servo is installed.

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

Revision: 2.3 Date: 10/30/20
G1-3
If no Autopilot Installed:
 Adjust AV-60000 to set run time for the trim motor to be between 25 and 30 seconds. See
Figure 1 and Figure 2 for the location of the 1-turn knob that allows adjustment of the trim
speed.
If a Garmin Autopilot is Installed:
 Adjust AV-60000 trim adjustment knob to the maximum position.
If a Dynon Autopilot is Installed:
 Adjust AV-60000 trim adjustment knob to the maximum position.
 Avionics switch “ON”.
 Verify that GPS source is functioning. (Note: Aircraft must be outside to get a GPS fix)
 Verify that COM radio powers up and can receive and transmit. Check for “Tx” on radio
display when activating PTT switches.
 Verify right and left seat COM PTT function.
 Verify that intercom powers up and is functioning for both pilot & co-pilot. Two headsets
should be plugged in for this test. Check that side tone is present.
 Verify that transponder powers up.
 Verify transponder indication on EFIS.
 Verify ADS-B is functioning.
 Reference Chapter 9 of the RV-12iS MM to adjust the sound levels within your aircraft.
NOTE: All audio levels are set at the factory to default settings 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 Warning tone level is controlled by the GTR200 Aux 1 input level. Music
levels are controlled by the GTR200 Music input level.
NOTE (GMA245): EFIS warning and AOA tone levels may be adjusted within the EFIS setup
menu. Both of these tones summed together are controlled by the GMA245 Alert 1
input level. Stall Warning tone level is controlled by the GMA245 Aux 1 input level.
Music levels are controlled by the GMA245 Entertainment 1 input level.
Within the EFIS setup menu:
 Check that the Stall Warning is louder than example AOA tones.
 Check that AOA example tones are louder than example EFIS warnings.
 Check that XM or Bluetooth music is not louder than Stall Warning, AOA tones or EFIS
warnings.
 Check dimmer control of lighted switches and avionics.
 Avionics switch “OFF”.
If optional combination Navigation/Strobe lights have been installed:
 Nav & Strobe switch “NAV”.
 Verify that only nav and position lights are illuminated - red on left and green on right.
 Nav & Strobe switch “NAV STROBE”. Verify that both side’s nav and strobe lights come on.
 Check dimmer function controls the roll bar mounted cabin light.
 Nav & Strobe switch “OFF”.

Revision: 2.3 Date: 10/30/20
G1-4
If optional single landing light has been installed:
 Landing light switch “STEADY”.
 Verify that landing light is on steady.
 Landing light switch “PULSE”.
 Verify that landing light pulses on and off.
If optional second landing light has been installed:
 Landing light switch “PULSE”.
 Verify that landing lights pulse in synchronized “wig-wag” pattern.
 Landing light switch “OFF”.
OTHER APPROPRIATE SYSTEMS:
 Lower canopy and engage latch while sitting in the left seat using your right hand.
 Verify that canopy can easily be latched and unlatched.
 Verify that canopy “WARNING” shows on EFIS when unlatched.
 Master switch "OFF".
 Remove battery charger.
 (ULS) Reinstall fuel pump fuse.
LANDING GEAR & BRAKES:
 Remove main landing gear 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 to approximately 2/3 – 3/4.
 Sit in pilot seat and actuate brake pedals several times to take-up clearance in brake
calipers then apply force and hold for at least 30 seconds.
 Verify that pedals feel firm and hold steady position.
 Verify no leaks at all brake line connections.
 Verify effectiveness (have a helper try to move the aircraft while holding brakes).
 Sit in passenger seat and actuate brake pedals several times then apply force and hold.
 Verify pedal firmness.
 Verify no fluid leaks.
 Check tire pressure as specified in the POH.
 If wheel fairings are installed, verify minimum ½ inch gap between fairing cutouts and tire
around entire opening.
Section G1 checks completed by:
Printed Name/Title Aircraft Serial Number
Signature Date

Revision: 2.3 Date: 10/30/20
G2-1
Section G2 – Flight Controls Check
FLIGHT CONTROLS:
 Remove empennage fairing.
 Verify that top stabilator cable is attached and safetied.
 Verify that bottom stabilator cable is attached and safetied.
 Verify that both rudder cables are attached and safetied.
 Verify that the trim motor tray is attached and safetied.
 Verify that at both rudder hinge points (upper and lower), the bolt/nut/washers are properly
installed as specified in KAI Section 11iS-02.
 Verify that at both stabilator hinge points (right and left), the bolt/washers are properly
installed as specified in KAI Section 11iS-03.
 Move the stick full aft and hold firmly against the stop.
 Verify that the stabilator is in the trailing edge up position.
 Vary the amount of force on the stick and verify that the stick can move slightly off its stop
before the stabilator begins to move.
 Move the stick full forward and hold firmly against the stop.
 Verify that the stabilator is in the trailing edge down position.
 Vary the amount of force on the stick and verify that the stick can move slightly off its stop
before the stabilator begins to move.
 Hold the stick full right while moving from 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 movement of the stabilator with no binding and little or no friction.
 Turn the master switch “ON” and actuate “NOSE UP” side
of trim switch until the motor reaches the stop.
NOTE: this will take several switch flips due to
software preventing “runaway trim”
 Move the stabilator to the full trailing edge (T.E.) up
position and measure the tab position.
 Distance from center of AST (Anti-Servo Tab) T.E. at one
outboard tip to the center of adjacent stabilator T.E:
(nominal distance: 9/16 inch [14.29mm]) See
Figure 3.
 Standing alongside the stabilator, move stabilator from full-up to full-down and check for
binding/interference of the anti-servo tab and actuating mechanism.
 Move the stabilator to the full trailing edge up position and hold it there.
 Verify that there is at least 1/4 inch [6.3mm] clearance between the bottom of the rudder and
the AST pushrod. Reference KAI 11iS-09.
 Actuate “NOSE DOWN” side of trim switch until limit is reached.
Move the stabilator to the full trailing edge down position and measure the tab position.
 Distance from center of AST T.E. to center of stabilator T.E: (nominal
distance: 3/8 inch [9.5mm]) See Figure 3.
Anti
-
servo tab
Stabilator
FIGURE 3: AST TAB
MEASUREMENT

Revision: 2.3 Date: 10/30/20
G2-2
 Standing alongside the stabilator, move stabilator from full-up to full-down and check for
binding/interference of the anti-servo tab and actuating mechanism.
 Move the stabilator to the full trailing edge up position and hold it there.
 Verify that there is at least 1/4 inch [6.3mm] clearance between the bottom of the rudder and
the AST pushrod.
 Actuate trim switch to place the trim in the TAKEOFF position on the EFIS.
Move the stabilator to the full trailing edge up position and measure the tab position.
 Distance from center of AST T.E. to center of stabilator T.E: (nominal
distance: 2.0 inches [50.8mm]) See Figure 3.
 Turn the master switch “OFF”.
 Install the empennage fairing.
 Verify that there is no interference between the empennage fairing and the stabilator or anti-
servo tab pushrod at any point in their full ranges of travel.
Using a 12 inch or 30cm. straightedge, verify that:
 The rudder skin, anti-servo tab, and stabilator skin are flat between the spar and trailing edge
and that there is no pillowing or bulging between ribs. (If necessary, re-shape trailing edge
bend using the procedure described in Section 5.7 of the KAI).
 Ensure the trim tab is in the TAKEOFF position.
 Move the rudder full left and hold against 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 horizontal, 7 5/16±1/8 inches [18.57±.3 cm] - measured
diagonally from point-to-point)
 Move the rudder full right and hold against 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 horizontal, 7 5/16±1/8 inches [18.57±.3 cm] - measured
diagonally from point-to-point)
While seated in pilot seat, move rudder through its full range of motion.
 Verify that when the left pedal is pushed, the rudder moves trailing edge left and when the
right pedal is pushed, the rudder moves trailing edge right.
 Verify smooth movement of the rudder from stop-to-stop with no binding and little or no
friction.
 Verify that the left flaperon moves trailing edge up when the stick is moved left and vice
versa.
Using a 12 inch or 30 cm. straightedge, verify that:
 The flaperon skin is flat between the spar and trailing edge and that there is no pillowing or
bulging between ribs. (If necessary, re-shape trailing edge bend using the procedure detailed
in KAI Section 5.7).
 Turn the master switch “ON”
 Calibrate the Flap Position Indicator per the EFIS manual.
 Cycle flaps through entire range. Verify smooth operation and position readout on EFIS.

Revision: 2.3 Date: 10/30/20
G2-3
 Place flaps in "retracted" position and have a helper hold the left flaperon trailing edge in line
with tip trailing edge (in trail) position.
 Verify right flaperon trailing edge is 1/4 inch [6.3mm] to 1/2 inch [12.6 mm] below trail
position.
 Verify that when a 10lb [4.5kg] upward load is applied to the trailing edge of the right flaperon,
the trailing edge does not flex above trail position more than 1/2 inch [12.6 mm].
 Move stick full aft and hold against the aft stop while moving the stick left stop-to-right stop.
 Verify smooth operation, no interference or binding, and a minimum of 1/8 inch [3.17mm] gap
between each flaperon (top and bottom skins) and the fuselage skin when the flaperon is
deflected to its highest trailing edge up position. If the flaperon gap is below minimum, mark
the trim line for proper gap and use aluminum shears and a file to trim the excess.
 Move stick full forward and hold against the forward stop while moving the stick left stop-to-
right stop.
 Verify smooth operation, no interference or binding, and a minimum of 1/8 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
excess.
 Place flaps in "50%" position.
 Move stick full aft and hold against the aft stop while moving the stick left stop-to-right stop.
Verify smooth operation, no interference or binding.
 Move stick full forward and hold against the forward stop while moving the stick from left stop-
to-right stop. Verify smooth operation, no interference or binding.
 Place flaps in "full" position.
 Move stick full aft and hold against the aft stop while moving the stick from left stop-to-right
stop. Verify smooth operation, no interference or binding.
 Move stick full forward and hold against the forward stop while moving the stick from left stop-
to-right stop. Verify smooth operation, no interference or binding.
 Place flaps in the “retracted” position.
 Turn the master switch “OFF”.
 Verify that the stabilator cable turnbuckles have safety pins installed.
 Verify that the stabilator cable tension is adjusted such that when the stick is "pulsed" fore
and aft, the cables do not slap against the aircraft structure.
Section G2 checks completed by:
Printed Name/Title Aircraft Serial Number
Signature Date

Revision: 2.3 Date: 10/30/20
G3-1
Section G3 - Seats and Safety Belts
OCCUPANT RESTRAINT:
-Pilot side Lap Belt:
 Verify security of attachment, 2 places, left and right.
 Verify no visual defects (signs of fraying, wear, loose stitching, etc)
-Pilot side Shoulder Belt:
 Verify security of attachment.
 Verify no visual defects (signs of fraying, wear, loose stitching, etc)
-Pilot side Crotch Belt:
 Verify security of attachment.
 Verify no visual defects (signs of fraying, wear, loose stitching, etc)
-Passenger side Lap Belt:
 Verify security of attachment, 2 places, left and right
 Verify no visual defects (signs of fraying, wear, loose stitching, etc)
-Passenger side Shoulder Belt:
 Verify security of attachment.
 Verify no visual defects (signs of fraying, wear, loose stitching, etc)
-Passenger side Crotch Belt:
 Verify security of attachment.
 Verify no visual defects (signs of fraying, wear, loose stitching, etc)
Seat backs and cushions:
 Verify both left and right seat backs are in full forward positions with the pins secured in the
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' range of motion there is no interference with seat cushion.
 Adjust seat backs to desired seating position and verify proper latching.
Occupant restraint latching/unlatching:
 Sit in the seat, latch and adjust the belts such that the lap belt is low on hips, the crotch belt is
adjusted such that restraint buckle cannot be pulled higher than occupant's navel, and the
shoulder belt is adjusted with minimum amount of slack such that all controls can be reached
and operated.
 Verify that pilot side restraint system stays latched and adjusted while throwing body weight
alternately against shoulder belts then seatback. When unbuckling check that handle must be
pulled beyond 45° to release.
 Verify that passenger side restraint system stays latched and adjusted while throwing body
weight alternately against shoulder belts then seatback. When unbuckling check that handle
must be pulled beyond 45° to release.
Section G3 checks completed by:
Printed Name/Title Aircraft Serial Number
Signature Date

Revision: 2.3 Date: 10/30/20
G4-1
Section G4 - Engine Check
ENGINE:
 Remove cowling, upper and lower.
 Verify proper engine attachment.
 Verify proper exhaust system attachment.
Throttle control:
 Verify proper attachment.
 (iS) Verify proper operation through the entire range (observe the throttle arm while having a
helper move the throttle lever from the cabin).
 (iS) Verify the Eco Stop is set at the transition from 97% to 98% throttle.
 (ULS) Verify proper operation through the entire range (observe carburetors while having a
helper operate the throttle lever from the cabin)
 (ULS) Check that throttle arms reach the Wide Open Stop concurrently and that there is no
interference with other systems.
(ULS) Choke control:
 Verify proper attachment.
 Verify proper operation (observe carburetors while having a helper operate the choke control
from the cabin).
Cabin heat control:
 Verify proper attachment.
 Verify proper operation of each heat door (observe cabin heat doors while operating the
heater control knobs from fully open to fully closed).
 Verify each heat door rests against its seat when the heater control 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
temporarily installed. Ensure that the radiator fills to fill plug height before tightening and
safetying the plug. Observe that threads do not get wet before inserting the plug. Check for
leaks.
 Fill oil system in accordance with Rotax SI-912-018 (latest revision) procedure.
 Add approximately 4 gallons of fuel to the tank and check for leaks.
(ULS) Fuel System and Gascolator Testing:
 Master Switch “ON”
 Move fuel valve to “ON” position.
 Listen at fuel filler neck for fuel splashing back from the return system.
 Master switch "OFF", Fuel Valve “OFF”. Verify no fuel leaks.
 Disconnect fuel line at Engine Fuel Pump inlet fitting.
 Feed fuel hose into a fuel container that will show an internal fuel level of 1 gallon. Fuel
container should be at fuel pump height. Observe fire and ventilation safety.
 Charge battery to full. Voltage should read at least 12.7v when the charger is removed.
 Have a helper turn Master Switch "ON", reduce load on the electrical system by turning off
strobes and nav lights, dimming screens, etc.
 Fuel valve "ON".
 Record time from Valve “ON” until 1 gallon has emptied into container.

Revision: 2.3 Date: 10/30/20
G4-2
Time to pump one gallon: (Max Time: 180 seconds)
 Master Switch “OFF”.
 Re-connect fuel line to fuel pump.
(iS) Fuel System Testing:
 Remove the fuel supply hose from the RH fuel manifold on the engine.
 Feed fuel hose into a fuel container that will show an internal fuel level of 1 gallon. Fuel
container should be at fuel pump height. Observe fire and ventilation safety.
 Master Switch “ON”
 “Fuel Pump 1” switch “ON”. Pump at least one gallon of fuel through the fuel system into a
clean fuel container.
 “Fuel Pump 1” switch “OFF”
 Check for debris in the container. If debris is observed filter fuel and return it to the fuel tank
then repeat test until fuel comes out clean.
 “Fuel Pump 2” switch “ON”. Pump at least one gallon of fuel through the fuel system into a
clean fuel container.
 “Fuel Pump 2” switch “OFF”
 Check for debris in the container. If debris is observed 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
record system pressure:
Fuel Pump 1 switch:
Fuel Pump 2 switch:
Both:
 Master Switch “OFF”.
 Check entire fuel system for leaks.
 Remove lower spark plug from each cylinder.
Propeller and spinner installation:
 Remove spinner.
 Check prop blade pitch setting (blades both at same pitch angle). See KAI Section 47iS/U.
 Check prop bolt torque.
 Check prop tracking (difference between blades must be less than 1/8 inch (3.17mm)).
 Re-install spinner.
 Check pitot tube tracking (max difference must be less than 1/16 inch (1.6mm)).
 Master Switch “ON”.
 Confirm Ignition Lane A and B – “OFF”
 Unlatch one wing pin at a time and verify red warning light comes on.
 Verify starter circuit is disabled while red warning light is on.
 While red warning light is on, check that holding the spar pin warning light button enables
starter circuit.
 Master Switch “OFF”.
 Install lower spark plugs in all cylinders.
 Install cowl.

Revision: 2.3 Date: 10/30/20
G4-3
Section G4 checks completed by:
Printed Name/Title Aircraft Serial Number
Signature Date

Revision: 2.3 Date: 10/30/20
G5-1
Section G5 - Pitot, Static, and AOA System Leak Check
 Move the flight controls through all extents multiple times to confirm there is no
Move the flight controls through all extents multiple times to confirm there is no
interference between any tubing or wires and any flight controls or the flaperon linkage. Inspect
for interference with the flaps in all positions.
NOTE: When performing any AOA, Static or Pitot system pressure test on a Dynon
SkyView system it is required to be at Software Version 15.0.4 (or greater) and all testing
must be performed in the SETUP MENU > HARDWARE CALIBRATION > ADAHRS
CALIBRATION > PITOT/STATIC TEST MODE.
CAUTION: During initial AOA system installation testing the AOA tubing will be temporally
connected to the ADAHRS Pitot port. Do not fly the airplane without connecting all AOA,
Pitot and Static tubing to the proper ADAHRS ports.
This test must be used to test AOA system plumbing integrity during initial AOA system
installation.
 Install both wings and engage both spar pins.
 Disconnect the pitot tubing from the ADAHRS pitot fitting, connect the AOA tubing to the
ADAHRS pitot fitting.
 Using a 35cc syringe, push the plunger in to 7.5cc, use modeling clay to hook-up the syringe
and a vacuum 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 until 130 kt
indicates.
Start stopwatch when EFIS indicates 130 kts and note the airspeed ______ kts after one minute.
 Move the left wing tip back and forth, as per the RV-12 Maintenance Manual Chapter 3 Rear
Spar Doubler section, while performing the AOA system leak test to verify AOA system
integrity.
 Maximum allowable AOA system leak rate is 10 kts in one minute.
NOTE: If the AOA system does not hold test pressure for the required time inspect the
modeling clay to wing seal before inspecting other AOA system components. Inspect and
repair or replace any faulty AOA system components as necessary. Re-test AOA system
plumbing integrity any time the system is “opened”.
 Reattach the pitot and AOA tubes to the proper ADAHRS port fittings.
NOTE: The AOA system plumbing must pass this leak test during every inspection.
 Using 35cc syringe or equivalent, push plunger in to 7.5cc, hook-up syringe & vacuum hose
to pitot tube, turn-on EFIS, use syringe to slowly and carefully push air into the pitot tube, look
for airspeed indication on EFIS, push-in syringe until 130 kts indicates then stop pushing-in.
Start stopwatch when EFIS indicates 120 kts and note the airspeed ______ kts after one minute.
(Maximum allowable pitot system leak rate is 10 kt in one minute.)

Revision: 2.3 Date: 10/30/20
G5-2
 Note current altitude indication:_________
 Tape-over one of the static ports with electrical tape, fully push-in syringe plunger and use
modeling clay to hook-up syringe & vacuum hose to the other static port, use syringe to draw-
out air from static system. Look for altitude indication on EFIS, draw syringe out until 1,200 ft
above current altitude indicates, stop drawing-out.
Start stopwatch when EFIS indicates 1000 ft above field elevation.
Note the 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 system components. Inspect and repair or replace any faulty static system
components as necessary
Configure your EFIS to display AOA information using the Dynon or Garmin AOA setup
instructions, as necessary. Also refer to the Van’s Aircraft downloadable “Read Me” file that
pertains to your EFIS system for additional information.
AOA calibration must be done in flight, take all necessary precautions.
Section G5 checks completed by:
Printed Name/Title Aircraft Serial Number
Signature Date

Revision: 2.3 Date: 10/30/20
G6-1
Section G6 - Engine Ground Run (Note: This section must be done with the aircraft outside.)
 Confirm at least 2 gallons of fuel in the tank.
 Chock main wheels, tie-down tail.
 Master switch "ON".
Check EFIS for:
 Ammeter functioning and showing discharge.
 Voltmeter functioning and showing more than 12.0 volts.
 (iS) Fuel pressure indication = zero.
 (ULS) Fuel pressure indication in the “green range”.
 Start engine per relevant POH checklist.
Check EFIS for:
 Tachometer function.
 Oil pressure functioning and showing pressure (oil pressure may take up to 10 seconds to
acquire).
WARNING: If no oil pressure is shown within 10 seconds, shut down the engine
immediately.
 Ammeter functioning and showing charge.
 Voltmeter functioning and showing 13 volts or higher.
 (ULS) CHT functioning (both cylinders).
 (iS) Cylinder coolant temps indicating.
EGT functioning:
 (ULS) Left and Right.
 (iS) All four cylinders.
 (iS) Positive fuel flow.
Once oil temperature exceeds 122°F [50º C]:
 (ULS) Perform carburetor synchronization procedure as called-out in Section 12 of the RV-
12iS Maintenance Manual.
 (ULS) Run-up to 4000 RPM then check each ignition per the relevant POH checklist.
 (iS) Run-up to 4000 RPM then check each Lane per the relevant POH checklist.
 At 4000 RPM latch and unlatch the canopy to verify audio and visual of canopy latch open.
Move canopy handle back and forth in the detent within the canopy latch block to insure that
no condition exists in which the canopy is latched but the switch shows the canopy is open.
 Reduce to 2500 RPM, latch and unlatch canopy and verify no warning is given.
 (iS) Check fuel pump function and fuel pressure per POH Section 4.7 BEFORE TAKEOFF
RUN UP.
 Check heater control operation.
 Throttle to idle, note RPM, smoothness of run.
Once oil temperature exceeds 165º F [74º C]:
 Check tachometer indication, engine idle at 1550-1650 RPM
 Verify functionality of throttle springs. (See RV-12iS Maintenance Manual Section 12)
 Shut down aircraft.
 Remove lower cowl.

Revision: 2.3 Date: 10/30/20
G6-2
Check for:
 Oil, coolant, and fuel leaks
 Check oil level.
WARNING: Only check coolant expansion tank level when engine has cooled down
(CHT below 110 degrees).
 Anything missing or loose (nuts, wires, sensor connections, etc)
 Remove remaining fuel by disconnecting fuel line as previously done in Section G4 Fuel
System Testing. Run electric fuel pump until pump sound changes then reattach fuel line.
 (ULS) remove Gascolator bowl. Note presence of any debris in gascolator bowl and clean
screen then re-install gascolator bowl and safety.
 (ULS) Remove carburetor bowls 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 needed, drill holes in
the appropriate locations on the rear spinner bulkhead and install the weights there.)
NOTE: The following items are of concern without a dynamic prop balance. Please
note this list is not exhaustive.
•Decreased AHRS accuracy and failure of EFIS components
•Fatigue of components
•Pitot tube failure
NOTE: It is preferred that this step be completed prior to first flight, but if a dynamic
balance cannot be completed at this time, it shall be completed within the first 15
hours.
Section G6 checks completed by:
Printed Name/Title Aircraft Serial Number
Signature Date

Revision: 2.3 Date: 10/30/20
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 Number
Signature Date