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Van's Aircraft RV 12iS Maintenance Manual

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Rev: 2
Date: 11/15/18
MAINTENANCE
MANUAL
Aircraft Serial Number: ___________________________
i

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Summary of Contents for Van's Aircraft RV 12iS

  • Page 1 Rev: 2 Date: 11/15/18 MAINTENANCE MANUAL Aircraft Serial Number: ___________________________...
  • Page 2 Rev: 2 Date: 11/15/18 THIS PAGE INTENTIONALLY LEFT BLANK...
  • Page 3 Rev: 2 Date: 11/15/18 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.
  • Page 4  Maintenance Manual and continued airworthiness information and instructions provided by Van's Aircraft Inc. Each owner/operator of an RV-12iS shall provide Van's Aircraft Inc. with up to  date contact information so that Van's Aircraft may send the owner/operator supplemental notification bulletins.

  • Page 5: Table Of Contents

    Rev: 2 Date: 11/15/18 TABLE OF CONTENTS CHAPTER 1- GENERAL ......................... 1-1 NTRODUCTION Purpose ........................1-1 Summary ........................1-1 Scope .......................... 1-2 Replacement Parts ...................... 1-3 Method ........................1-3 ....................1-4 PPLICABLE HROUGHOUT General Safety ......................1-4 Safety of Flight Reporting Procedure ................1-5 Helpful Terminology ....................
  • Page 6 Rev: 2 Date: 11/15/18 Firewall Forward ......................3-8 Fuselage ........................3-12 Landing Gear ......................3-13 Wing / Center Section/AOA ..................3-14 Empennage ....................... 3-10 Angle-Of-Attack System .................... 3-16 Paperwork ......................... 3-17 CHAPTER 4 - STRUCTURAL REPAIRS ................. 4-1 ........................4-1 VERVIEW ....................
  • Page 7 Rev: 2 Date: 11/15/18 ........................10-3 ENTILATION ........................10-4 ERVICE CHAPTER 11 - PROPELLER ..................11-1 ........................11-2 VERVIEW ........................11-2 ERVICE Prop & Hub ....................... 11-3 CHAPTER 12 - FIREWALL FORWARD ................. 12-1 ........................12-2 VERVIEW Engine ........................12-3 ........................
  • Page 8 Rev: 2 Date: 11/15/18 NOTE: Pages 1-21/22 and 1-23/24 correspond to a particular EFIS installation. Please remove all pages that do not correspond to your EFIS. Specific EFIS type is noted next to the page number. APPENDIX ‘A’ - KIT ASSEMBLY INSTRUCTIONS (KAI) NOT PART OF, BUT AN APPENDIX TO THIS MANUAL) Addendum Documents list...

  • Page 9: Chapter 1- General

    Rev: 2 Date: 11/15/18 Chapter 1 - GENERAL INTRODUCTION PURPOSE The purpose of this manual is to provide guidance to RV-12iS owners, pilots, mechanics, regulatory officials, and aircraft/component manufacturers that are certified to perform maintenance, repairs, and alterations on the light sport aircraft covered in this manual.

  • Page 10: Scope

    Rev: 2 Date: 11/15/18 SCOPE • NOTE: This maintenance manual is intended to be used in conjunction with the RV-12iS Kit Assembly Instructions (KAI) when completing maintenance or repair processes. All of the service and maintenance requirements that are unique to the RV-12iS S-LSA are included in this manual.

  • Page 11: Replacement Parts

    Rev: 2 Date: 11/15/18 REPLACEMENT PARTS The RV-12iS KAI is the primary reference for replacement part information. Section Four in the KAI is a directory of all part numbers with reference information of where to find it within the main KAI manual. The documentation produced by third party parts manufacturers (listed above) should be used as the primary reference for part information for those components.

  • Page 12: Applicable Throughout

    Rev: 2 Date: 11/15/18 References’ that may be helpful or necessary to complete the task. Each hardware item to be removed in the service instructions will be followed by the quantity (if greater than one) in parenthesis. For example, an instruction step that requires the removal of one bolt, six washers and two nuts will appear as follows: 1.

  • Page 13: Safety Of Flight Reporting Procedure

    Rev: 2 Date: 11/15/18 to reuse nylock and all steel style self-locking nuts if it is determined that the self-locking feature has not been degraded. Always replace questionable hardware. Operation in Extreme Conditions: Exposure to extreme climatic conditions, including but not limited to dust, salt, debris, bugs, will warrant more frequent inspections of air filters, coolant radiator, and oil cooler as defined in the Rotax maintenance manual.

  • Page 14: Abbreviations

    Rev: 2 Date: 11/15/18 BBREVIATIONS A&P* Airframe and Power-plant Kilometers per hour Mechanic Anti-knock index (octane rating) Knots American Petroleum Institute U.S. pound AST* Anti-servo/trim tab Low-Lead AVGAS Aviation Gasoline Light Sport Aircraft Celsius LSA-RM* Light Sport Aircraft – Repairman Maintenance rating Center of Gravity Liter...

  • Page 15: Units

    Rev: 2 Date: 11/15/18 NITS Speed: 1 mph 1.64 kph 0.869 kts Distances: 1 in 2.54 cm 1 ft 12 in 0.305 m 1 mi 5,280 ft 1.61 km 1 naut mi 1.15 mi 1.85 km Mass: 1 oz 28.3 grams 1 lb 16 oz 0.454 kg...

  • Page 16: Tools And Expendables

    Rev: 2 Date: 11/15/18 TOOLS AND EXPENDABLES There are many aircraft tool suppliers available. An Internet search can be conducted to determine which supplier can provide the necessary tools ● NOTE: T HIS TOOL LIST DOES NOT INCLUDE ALL OF THE TOOLS THAT MAY BE REQUIRED FOR NSPECTION AND AINTENANCE PROCEDURES CCESS TO A TYPICAL GENERAL TOOL KIT...
  • Page 17 Rev: 2 Date: 11/15/18 Combination Wrenches Ratchet Screwdrivers Sockets Allen Wrenches Gap Gauge Oil Filter Cutter Heavy Stands Step Ladder Oil Filter Wrench Battery Charger Multi-meter Magnifying Glass Square Air Pressure Gauge Figure 1...
  • Page 18 Rev: 2 Date: 11/15/18 Razor Knife Flashlight Needle-nose Pliers C-clamp Terminal Crimper Wire Cutter Locking Pliers Blind Riveter Power-drill Hardware Dual Vacuum Gauge Tensile Weight Scale Figure 1 1-10...
  • Page 19 Rev: 2 Date: 11/15/18 ■ C AUTION EPLACEMENT PARTS MUST BE OF THE EQUIVALENT SIZE TYPE AND RATING AS THE ORIGINAL PARTS FROM THE MANUFACTURER EXPENDABLE PARTS PART NUMBER Oil filter Rotax 825 701 (or equivalent) Fuel Filter [iS] Rotax 874 060 Copper crush ring (for oil tank drain Rotax 250010 plug)

  • Page 20: Engine

    Rev: 2 Date: 11/15/18 ENGINE DESCRIPTION The LSA covered by this manual may be equipped with either a Rotax 912ULS or a Rotax 912iS power plant. Both are an over-head valve four-stroke, horizontally opposed four-cylinder. The cylinder heads are liquid cooled. The cylinder barrels are air- cooled.

  • Page 21: Lubrications And Capacities

    Rev: 2 Date: 11/15/18 LUBRICATION AND CAPACITIES ENGINE OIL ■ CAUTION: ONLY USE API 'SG' CLASS OR HIGHER ■ CAUTION: DO NOT USE O ILS WITH FRICTION MODIFIER ADDITIVES ■ CAUTION: DO NOT USE O ILS FOR “ ” CONVENTIONAL AIRCRAFT ENGINES ■...

  • Page 22: Engine Coolant

    Rev: 2 Date: 11/15/18 ENGINE COOLANT UITABLE OOLANTS OOLANT MIX • 50% ethylene glycol concentrate with anticorrosion additives designed for aluminum without sulfates or phosphates. • 50% distilled or de-mineralized water. See the latest version of the Rotax Operators Manual and Service Instruction SI 912- 016 for further information on coolant types and limitations.

  • Page 23: Torque Values

    Rev: 2 Date: 11/15/18 TORQUE VALUES Torque applied is for the size of the bolt shank not the wrench size. On smaller bolts use a torque wrench calibrated in inch pounds, not foot pounds. When tightening fasteners installed with self-locking nuts or nutplates, the chart values must be modified.

  • Page 24: General Procedures

    Rev: 2 Date: 11/15/18 GENERAL PROCEDURES IRE REMOVAL EFER TO ING REMOVAL ANOPY REMOVAL OWL REMOVAL 12-1 EFER TO IL LEVEL CHECK UEL SYSTEM DRAINING 13-1 EFER TO UEL TANK REMOVAL LIFTING & SUPPORTING THE FUSELAGE ▲ WARNING: U SE STURDY SUPPORT STANDS THAT ARE EACH CAPABLE OF SUPPORTING AT LEAST POUNDS ■...
  • Page 25 Rev: 2 Date: 11/15/18 IFTING WITH A JACK ■ C AUTION SE APPROPRIATE JACK LOCATING FIXTURES TO ENSURE A STABLE JACKING SURFACE ■ C AUTION NSTALL A JACKPOINT WHEN LIFTING AT THE WING TIE DOWN LOCATION 1. Place a jack as necessary to lift at the lower end of the nose gear-leg. 2.

  • Page 26: Weight And Balance

    Rev: 2 Date: 11/15/18 WEIGHT AND BALANCE It is the pilot’s responsibility to insure that the aircraft is loaded properly and within the weight and balance limitations. The weight and balance of the aircraft are factors that will affect all flight performance, and handling characteristics of the aircraft. Find the actual licensed empty weight and CG of the aircraft on the Weight and Balance Form.
  • Page 27 Rev: 2 Date: 11/15/18 RV-12 & B EIGHT ALANCE ORKSHEET AIRCRAFT: _________ (registration)_________ (serial number) DATE: _________ TABLE 1 LEFT WHEEL NOSE WHEEL RIGHT WHEEL WEIGHT _______ lb _______ lb _______ lb (W1) (W2) (W3) DISTANCE FROM AXLE CENTER TO _______ inches _______ inches _______ inches...
  • Page 28 Rev: 2 Date: 11/15/18 EIGHT AND ALANCE ECORD As of this date: ___/___/___ the following values represent current Weight and Balance Calculations. Revised Empty Weight: __________________ lb Revised Empty Moment: __________________ in-lb Revised Empty Arm: __________________ in Signed: ___________________________ As of this date: ___/___/___ the following values represent current Weight and Balance calculations resulting from the installation of the _______________________________.

  • Page 29: E Quipment L Ist

    Rev: 2 Date: 11/15/18 INSTALLED EQUIPMENT LIST ITEM WEIGHT MOMENT in-lbs. DYNON 57.90 SV-D1000 DYNON 57.90 SV-D1100(T) DYNON (DUAL) 57.90 SV-D1100(T) DYNON 47.12 SV-EMS-220 DYNON 47.66 SV-XPNDR-261 DYNON 54.58 SV-BAT-320 DYNON 141.73 SV-ADAHRS-200 DYNON 43.13 SV-GPS-250 DYNON 43.13 SV-GPS-2020 GARMIN 54.13 GTR 200 ACK 406...
  • Page 30 Rev: 2 Date: 11/15/18 INSTALLED EQUIPMENT LIST ITEM WEIGHT MOMENT lbs. in-lbs. GARMIN GTR225 PS ENGINEERING PM3000-RV TOTAL -------- SKYVIEW 1-22...
  • Page 31 Rev: 2 Date: 11/15/18 INSTALLED EQUIPMENT LIST ITEM WEIGHT MOMENT lbs. in-lbs. GARMIN 57.90 GDU 460 GARMIN 57.90 GDU 465 GARMIN 57.57 GMC 305/307 GARMIN 47.12 GEA 24 GARMIN 50.93 GTX 23ES GARMIN 141.73 GMU 22 50.73 IBBS-12V-3AH GARMIN 118.76 GSU 25 GARMIN 43.13...
  • Page 32 Rev: 2 Date: 11/15/18 INSTALLED EQUIPMENT LIST ITEM WEIGHT MOMENT lbs. in-lbs. GARMIN GTR225 TOTAL -------- 1-22...

  • Page 33: Chapter 2- Service Schedule

    Rev: 2 Date: 11/15/18 Chapter 2 - SERVICE SCHEDULE OVERVIEW Adherence to the service schedule is essential for maintaining airworthiness and maximizing aircraft longevity. There are specific requirements for who can perform line maintenance, heavy maintenance, or annual condition inspections on an S-LSA. ●...
  • Page 34 Rev: 2 Date: 11/15/18 ● NOTE: F 18-3. OR THE ERVICE CHEDULE HECKLIST SEE UPPLEMENT PAGE The service schedule checklist serves as an index of the 'Service Procedures' section of each applicable chapter. The 'Service Procedure' section includes the recommended tools to complete each task. Applicable hardware will be stated using the most general terms.

  • Page 35: Chapter 3- Inspection

    Rev: 2 Date: 11/15/18 Chapter 3 - INSPECTION ..............................3-1 VERSTRESS ..............................3-2 VERVIEW ..........................3-3 NSPECTION ESCRIPTION Special Tools ............................3-3 Pre-inspection / Post-inspection ....................... 3-3 Cockpit ..............................3-5 Radio ................................. 3-6 Communication ............................. 3-6 Intercom ..............................3-6 Transponder ............................3-6 Optional Equipment ..........................

  • Page 36: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW The condition inspection is performed annually or every 100 hours of operation, depending on the terms of use for the aircraft. The condition inspection is essential for insuring safe operation throughout the aircraft's service life. In order for anyone to perform a condition inspection on an S-LSA category RV-12iS aircraft they must possess at least one of the following SPECIFIC CERTIFICATION REQUIREMENTS: A person certified as “Repairman (light-sport aircraft)-Maintenance”...

  • Page 37: Inspection Description

    Rev: 2 Date: 11/15/18 INSPECTION DESCRIPTION PECIAL OOLS Wing Retention Pin Bushing Gauge Multi-meter ♦ ♦ Jack Compression tester ♦ ♦ Padded stands Carburetor vacuum gauges ♦ ♦ Step ladder Torque wrench (in/lbs & ft/lbs) ♦ ♦ Tensile weight scale Tire pressure gauge ♦...
  • Page 38 Rev: 2 Date: 11/15/18 Figure 4: Remove for inspection *Ref. Name *Ref. # Name Right Wing Left Wing Upper Fwd Fuse Skin Cover Plates (6) Fuselage Side Cover (2) Baggage Floor Cover Top Cowl Baggage Cover Spinner Baggage Bulkhead Corrugation Bottom Cowl Lower Tailcone Fairing Tunnel Fwd Side Cover...

  • Page 39: Cockpit

    Rev: 2 Date: 11/15/18 COCKPIT • Inspect the aft face of the firewall for corrosion, deformation or cracks, especially around fasteners. • Inspect the welded rudder pedal assemblies for cracks / damage, smooth movement with no heavy resistance, etc. • Test the operation of the brake pedals. With constant pressure they should feel firm and not spongy.
  • Page 40 Rev: 2 Date: 11/15/18 • Inspect each Seat Belt Harness latching mechanism, the condition of the webbing material, and all stitching for damage or wear. • Check the installation, fasteners and condition of each seat back. • Inspect the canopy windscreen and aft window for deterioration or breakage. The canopy latch and latch block must be in good condition and installed correctly.

  • Page 41: Optional Equipment

    Rev: 2 Date: 11/15/18 OPTIONAL EQUIPMENT • Confirm that optional equipment installed on the aircraft is correct and authorized. Optional equipment is offered and installed on the aircraft by the manufacturer at the time of purchase. Refer to the related manual for special procedures for inspection. (See applicable manual provided with the component) EMERGENCY LOCATOR TRANSMITTER •...

  • Page 42: Firewall Forward

    Rev: 2 Date: 11/15/18 ▲ WARNING: T MUST HE MASTER POWER AND BOTH IGNITION SWITCHES BE SHUT OFF DURING INSPECTION OF THE ENGINE UNLESS INSTRUCTED OTHERWISE ERIOUS INJURY OR DEATH WILL RESULT IF ENGINE IS UNINTENTIONALLY STARTED ▲ WARNING: A LLOW THE ENGINE AND APPLICABLE COMPONENTS TO COOL BEFORE PERFORMING SERVICE OR INSPECTION OT ENGINE COMPONENTS WILL...
  • Page 43 Rev: 2 Date: 11/15/18 against firewall (when 'OFF'). • Check the engine throttle control cable for security and condition along the route to the firewall. The throttle must be securely connected to the throttle body and be in good condition. Confirm that the Throttle control operates the throttle body arm through its entire travel range from stop-to-stop.

  • Page 44: Empennage

    Rev: 2 Date: 11/15/18 EMPENNAGE • Inspect the exterior of the fuselage skins and fasteners. Check the fasteners by sighting along each rivet pattern for any inconsistent rivet profile among properly installed rivets as shown in Figure 6. Figure 6: Rivet Inspection ERTICAL TABILIZER •...
  • Page 45 Rev: 2 Date: 11/15/18 • Check the fiberglass fairing for condition and security. • Check for interference or signs of wear from the rudder. • Look through the forward spar lightening holes to inspect the rear spar, ribs, and rib flanges for cracks.

  • Page 46: Fuselage

    Rev: 2 Date: 11/15/18 inconsistent rivet profile among similar properly installed rivets. • Check the spar and attach hinge for deformation and signs of fatigue. • Inspect the control horns and surrounding area for deformation, cracks, and signs of fatigue. Check the control horn fasteners for wear and security. •...

  • Page 47: Landing Gear

    Rev: 2 Date: 11/15/18 LANDING GEAR ▲WARNING: A LIFTED AIRCRAFT MUST BE SECURELY SUPPORTED BY STATIC STANDS OTHER THAN THE JACKING DEVICE HE AIRCRAFT MAY NOT MOVE FROM ATTEMPT TO SHAKE HORIZONTALLY OR VERTICALLY ■CAUTION: A LWAYS USE PADDED STANDS AND ALWAYS DISTRIBUTE THE LOAD ALONG A RIVET PATTERN WITH SEVERAL INTERSECTING RIVET PATTERNS ●NOTE: R –...
  • Page 48 Rev: 2 Date: 11/15/18 • Check the nose gear-leg coating, welds, and brackets for cracks and signs of fatigue. • Remove the nose fork from the nose gear leg. Clean and inspect for corrosion or wear. Re-lube and reinstall. Check the break-out force per KAI, and safety with a new cotter pin.
  • Page 49 Rev: 2 Date: 11/15/18 • Inspect each fuselage pin and all wing retention pin bushings for wear or cracks. Inspect the center section area around the bushings for deformation or cracks. Use the Main Spar Bushing Gauge Pin to check the wear of both ends of all of the wing retention pin bushings.

  • Page 50: Angle-Of-Attack System

    Rev: 2 Date: 11/15/18 • If the measurement is less than 0.050 no repair is required. • If it is 0.050 or more refer to repair instructions in Section 5. Figure 7.1: Inspect Rear Spar Doubler ANGLE-OF-ATTACK SYSTEM TEST Special Tools Syringes - two req'd (35cc or similar) Modeling clay ♦...

  • Page 51: Paperwork

    Rev: 2 Date: 11/15/18 • Move the left wing tip back and forth while performing the AOA system leak test to verify AOA system integrity. • The maximum allowable AOA system leak rate is less than full AOA indicator scale, from red to green, in one minute.
  • Page 52 Rev: 2 Date: 11/15/18 THIS PAGE INTENTIONALLY LEFT BLANK 3-18...

  • Page 53: Chapter 4 - Structural Repairs

    Rev: 2 Date: 11/15/18 Chapter 4 - STRUCTURAL REPAIRS OVERVIEW Visible deformation of or damage to any aircraft skin warrants a complete inspection of the underlying parts or structures. If all damaged parts are replaced in accordance with the Kit Assembly Instructions KAI no consultation of the manufacturer is necessary.

  • Page 54: M Inimum C Ertification

    KAI Chapter 5; Construction Materials, Processes & Useful Information. • NOTE: Stop drill cracks per AC 43.13. Report any cracks to Van's Aircraft using the feedback form found at the back of this manual. MINIMUM CERTIFICATION The minimum certification for completing a repair to aircraft skins is an LSA Repairman –...

  • Page 55: Chapter 5 - Structures

    Rev: 2 Date: 11/15/18 Chapter 5 - STRUCTURES ..........5-2 Installation ..........5-14 VERVIEW Main wheel and tire assembly removal ..5-15 ........... 5-2 USELAGE Installation ..........5-15 Components ........5-3 Nose wheel and tire assembly removal ..5-16 ......5-4 Installation ..........

  • Page 56: O Verview

    Rev: 2 Date: 11/15/18 OVERVIEW The RV-12iS airframe uses blind (pop style) rivets as the primary fastener. Screws, bolts and solid rivets are used where necessary. The wings are removable without the need of tools. • NOTE: P RIOR TO PERFORMING STRUCTURAL REPAIRS READ HAPTER FOR LIMITATIONS •...
  • Page 57 Rev: 2 Date: 11/15/18 Figure 9: Fuselage COMPONENTS Quantity Part or Assembly Name Part Number or Reference Canopy and Frame C-1201 & WD-1219 Fuselage Refer to KAI Fuselage Pin WD-1217 Wing Retention Pin Bushing W-1206U Latch Block C-01205-2 Occupant Harness System See shaded items below &...

  • Page 58: Wing And Flaperon

    Rev: 2 Date: 11/15/18 WING AND FLAPERON The wing and flaperon are removable as an assembly from each side of the fuselage. Each wing mates to the fuselage at three points; the stub spar, the main spar and the rear spar. Two fuselage pins secure both main spars to the center section of the fuselage.
  • Page 59 Rev: 2 Date: 11/15/18 COMPONENTS Quantity Part or Assembly Name Part Number or Reference Left Wing See shaded items below & Refer to KAI Wing Retention Pin Bushing W-1206U Stub Spar W-1208B-L / W-1208C-L Rear Spar W-1207A-L / W-1207B Stall Warning See 5-4 and KAI Right Wing See shaded items below &...

  • Page 60: E Mpennage

    Rev: 2 Date: 11/15/18 EMPENNAGE The empennage components include the vertical stabilizer, rudder, anti- servo/trim tab, and stabilator assemblies. The vertical stabilizer front and rear spar attach to the tailcone. Fiberglass fairings finish the top of the vertical stabilizer, rudder and are optional on the ends of the Stabilator.
  • Page 61 Rev: 2 Date: 11/15/18 COMPONENTS Quantity Part or Assembly Name Part Number or Reference Vertical Stabilizer See shaded items below & Refer to KAI Lower Hinge VS-1210 / VS-1211A / COM-3-5 Upper Hinge VS-1210 / VS-1211B / COM-3-5 Fwd Skin VS-1204 Rudder See shaded items below &...

  • Page 62: Landing Gear

    Rev: 2 Date: 11/15/18 LANDING GEAR The landing gear includes the gear-legs, wheels and tires, nose fork and mounting brackets. The nose gear-leg is steel, with welded brackets. The aluminum nose fork attaches and pivots at the lower end. An axle bolt and nut fastens the axle, spacers, and wheel and tire assembly to the nose fork.
  • Page 63 Rev: 2 Date: 11/15/18 COMPONENTS Quantity Part or Assembly Name Part Number or Reference Left Main Gear U-1220-L Right Main Gear U-1220-R Outbd. Main Gear Attach Brkt. U-01202-1 Outbd Wear Plate U-01202A Inbd. Main Gear Attach Brkt. U-01203-1 Inbd. Wear Plate U-01203B-1 Doubler Plate U-01203C-1...
  • Page 64 Rev: 2 Date: 11/15/18 NOSE WHEEL AND GEAR LEG FAIRINGS The optional nose wheel and gear leg fairings include the glass fabric/epoxy resin nose leg fairing, wheel fairing front and the wheel fairing aft. See Figure 13. The nose leg fairing is clamped about the nose leg using a piano hinge held in place by a single screw.
  • Page 65 Rev: 2 Date: 11/15/18 WHEEL FAIRINGS The optional main wheel fairings include the glass fabric/epoxy resin wheel fairing front and the wheel fairing aft. See Figure 14. The fairings are attached to the wheel fairing brackets which in turn attach to the bracket mount. MATCO GROVE Figure 14: Main Wheel Fairings...

  • Page 66: Service

    Rev: 2 Date: 11/15/18 SERVICE SUPPLIES PECIAL OOLS XPENDABLE Tensile weight scale Cotter pins ♦ ♦ 1/4 drive socket slightly less than Safety wire ♦ ♦ 5/8in in diameter. (A common Wheel bearing grease ♦ standard 7/16 socket generally Spray lubricant ♦...
  • Page 67 Rev: 2 Date: 11/15/18 GENERAL ING REMOVAL No special tools or certification required. ■ C AUTION E PREPARED WITH A HELPER OR SUPPORT STAND TO HANDLE THE WEIGHT AND AWKWARDNESS OF THE OBJECT TO BE REMOVED ■ CAUTION: A LWAYS SUPPORT THE FLAPERON DURING WING REMOVAL AND STORAGE 1.
  • Page 68 Rev: 2 Date: 11/15/18 2. Tap the new bushing into place with the flanged end toward the wing spars. PARS 3. Tap out the bushing from the non-flanged end of the bushing. 4. Tap the new bushing into place with the flanged end to be on the forward side of the wing spar.
  • Page 69 Rev: 2 Date: 11/15/18 AIN WHEEL AND TIRE ASSEMBLY REMOVAL Expendable Cotter pins Safety wire Replaceable None Service Rating Line Minimum Certification Owner and SPC, LSA-RM, or A&P Additional References Matco User Manual Grove User Manual 1. Lift and support the aircraft. (1-16) 2.
  • Page 70 Rev: 2 Date: 11/15/18 OSE WHEEL AND TIRE ASSEMBLY REMOVAL Expendable None Replaceable None Service Rating Line Minimum Certification Owner and SPC, LSA-RM, or A&P Additional References Matco User Manual 1. Lift and support the aircraft. (1-16) 2. Remove the axle bolt, washers (2), nut, axle, spacers, wavy washers, and wheel and tire assembly.
  • Page 71 Rev: 2 Date: 11/15/18 – G AIN INNER TUBE REPLACEMENT ROVE HEEL ROVE WHEEL CAN BE IDENTIFIED BY HAVING BEARING HUBS THAT ARE INTEGRAL WITH THE WHEEL HALVES Expendable Inner tube Safety wire Replaceable Main wheel assembly Tire Service Rating Line Minimum Certification Owner and SPC, LSA-RM,...
  • Page 72 Rev: 2 Date: 11/15/18 Reassemble and install the wheel and tire assembly. LAPERON HINGE REPLACEMENT Expendable Loctite 243 or Equiv. Replaceable Bearing MD3614M Service Rating Line Minimum Certification LSA-RM or A&P Additional References ■ C AUTION E PREPARED WITH ADDITIONAL PERSONEL OR TOOLS TO HANDLE THE WEIGHT AND AWKWARDNESS OF THE OBJECT TO BE REMOVED 1.
  • Page 73 Rev: 2 Date: 11/15/18 UDDER HINGE REPLACEMENT Expendable None Replaceable Lower rudder hinge Upper rudder hinge Service Rating Line Minimum Certification LSA-RM or A&P Additional References ■ C AUTION E PREPARED WITH ADDITIONAL PERSONEL OR TOOLS TO HANDLE THE WEIGHT AND AWKWARDNESS OF THE OBJECT TO BE REMOVED 1.
  • Page 74 Rev: 2 Date: 11/15/18 TABILATOR HINGE BEARING REPLACEMENT Special Tools 1/4 drive socket slightly less than 5/8in in diameter. (A common standard 7/16 socket generally works). 3/8 drive, 3/4 socket Hex Bolt 1/4 diameter 3 inches long (must be threaded at least 50% of its length) 1/4 Flat Washer(2) and Hex Nut Expendable...
  • Page 75 Rev: 2 Date: 11/15/18 Figure 16: Extracting the DW4K2X bearing 11. Carefully clean the new bearing and the inner bore of the VA-146A Flange Housing using denatured alcohol. After cleaning, handle the bearings with care as to not re-contaminate the outer surface. 12.
  • Page 76 Rev: 2 Date: 11/15/18 AIN GEAR REMOVAL Expendable Hydraulic fluid Replaceable Left Main Gear Leg Right Main Gear Leg Outbd. Main Gear Attach Brkt Outbd. Wear Plate Inbd. Main Gear Attach Brkt Inbd. Wear Plate and Spacer Service Rating Line Minimum Certification LSA-RM, or A&P Additional References...
  • Page 77 Rev: 2 Date: 11/15/18 4. Remove the lower engine vibration-isolator bolts (2). 5. Remove the nose gear-leg to fuselage attach bolts (13), and washers (13). ● NOTE: T HE ENGINE CAN BE LIFTED BY HAND AT THE GEARBOX 6. Lift the front of the engine only enough to remove the engine weight from the gear-leg bracket.
  • Page 78 Rev: 2 Date: 11/15/18 TEP REPLACEMENT Expendable Fuel tank sealant Replaceable Left or Right Step Service Rating Line Minimum Certification Owner, LSA-RM, or A&P Additional References 1. Remove the step attach bolts (2), washers (2) and the step. 2. Install the new step and attach hardware. 3.
  • Page 79 Rev: 2 Date: 11/15/18 5. Final drill the holes in the new doubler to #30 (except the identifier holes) and cleco it to the rear spar. 6. Test fit the wing with the new doubler clecoed in place (the hinge assembly does not need to be in place for this step.) If the fit is too tight to allow normal Spar Pin insertion, remove the wing, un-cleco the doubler and file the contour of the curve to reduce its profile by a few thousandths of an inch and test fit again.
  • Page 80 Rev: 2 Date: 11/15/18 SERVICE SCHEDULE PROCEDURES ING ATTACH LOCATION LUBRICATION WINGS REMOVED Expendable Wheel bearing grease Anti-seize compound Silicone Grease Replaceable Fuselage Pin AOA Connector Tube Service Rating Line Minimum Certification Owner and SPC, LSA-RM, or A&P Additional References USELAGE PINS 1.
  • Page 81 Rev: 2 Date: 11/15/18 LAPERON BEARINGS LUBRICATION Expendable Spray lubricant Replaceable None Service Rating Line Minimum Certification Owner and SPC, LSA-RM, or A&P Additional References Flaperon hinge replacement (5-17) 1. Wipe away any dirt accumulation from each of the flaperon bearings (3). 2.
  • Page 82 Rev: 2 Date: 11/15/18 tap around its outer perimeter. 6. Press a new wheel-bearing into each wheel half by reversing the process. 7. Reassemble the wheel and tire assembly. 8. SLOWLY inflate the tire. Deflate it fully and re-inflate it SLOWLY a couple more times to work out any wrinkles in the tube.
  • Page 83 Rev: 2 Date: 11/15/18 HEEL SSEMBLY ALANCING ROCEDURE ● NOTE: I T IS NOT A MAINTENANCE REQUIREMENT THAT THE OSE OR RV-12 HEEL SSEMBLIES ON THE BE BALANCED BECAUSE OF THE RELATIVELY LOW TAKEOFF AND LANDING SPEED HOULD A VIBRATION BE DETECTED THAT IS SUSPECTED TO BE CAUSED BY A WHEEL TIRE IMBALANCE THIS PROCEDURE...
  • Page 84 Rev: 2 Date: 11/15/18 THIS PAGE INTENTIONALLY LEFT BLANK 5-30...

  • Page 85: Chapter 6 - Flight Controls

    Rev: 2 Date: 11/15/18 Chapter 6 - FLIGHT CONTROLS Overview ............................... Components ........................... Service ..............................Supplies ..............................Special Tools ............................6-3 Expendable ............................6-3 Replaceable ............................6-3 General ..............................Stabilator pulley replacement and cable tension adjustment ............... 6-3 Control cable replacement ........................6-6 Rod end replacement ...........................

  • Page 86: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW The flight control system enables the pilot to operate the control surfaces. Forward or aft movements of the control stick control the pitch. The pitch control linkage is a pair of cables, each routed around a pulley and attached to control horns on the stabilator.

  • Page 87: Service

    Rev: 2 Date: 11/15/18 SERVICE Annual lubrication will maximize the longevity of the control system. Refer to the service schedule checklist for the specific service frequency of the components. See Supplement for service schedule checklist. SUPPLIES PECIAL OOLS XPENDABLE Cable tension meter Cotter pins ♦...
  • Page 88 Rev: 2 Date: 11/15/18 1. Remove the right seat ramp cover and baggage bulkhead corrugation. (3-4) 2. Remove the stabilator control cable barrel lock clips from one barrel as shown in Figure 17. Locking clips are one use only. Clips must be discarded after removal.
  • Page 89 Rev: 2 Date: 11/15/18 NOTE: Cable tension will change significantly with changing temperature. The cable tensions given below are for an aircraft stabilized at a temperature of 70 8. Position one of the WD-1212 Control Sticks so that the top end is 10 inches from the instrument panel.

  • Page 90: Expendable

    Rev: 2 Date: 11/15/18 ONTROL CABLE REPLACEMENT ■ C AUTION HE CONTROL SURFACE WILL SWING FREELY WHEN THE CONTROL CABLES ARE REMOVED ● NOTE: A LWAYS REPLACE CONTROL CABLES AS A SET Special Tools String Cable tension meter Spring clamps (3) Stick, 41"...

  • Page 91: Rod End Replacement

    Rev: 2 Date: 11/15/18 OD END REPLACEMENT Expendable Cotter pins Replaceable Applicable rod end Service Rating Line Minimum Certification LSA-RM, or A&P Additional References 1. Remove applicable combination of the seat ramp cover, Center console and, baggage cover 2. Remove the control rod attach hardware from the rod end for replacement; Control stick –...

  • Page 92: Rudder Pedal Removal

    Rev: 2 Date: 11/15/18 page 5-20, Figure 16. 5. Installation procedure is reverse of the removal procedure. UDDER PEDAL REMOVAL Expendable Cotter pins Replaceable Rudder pedal Service Rating Line Minimum Certification LSA-RM, or A&P Additional References KAI Section 28 Matco user manual 1.

  • Page 93: Cable End Hardware Lubrication

    Rev: 2 Date: 11/15/18 2. Apply lubricant sparingly to the rod-end bearings on each end of the following components: Flap handle pushrod ♦ Control stick pushrod ♦ Flaperon pushrod ♦ Trim / Servo pushrod ♦ 3. Allow lubrication to penetrate then wipe away excess. ABLE END HARDWARE LUBRICATION Expendable Spray lubricant...
  • Page 94 Rev: 2 Date: 11/15/18 THIS PAGE INTENTIONALLY LEFT BLANK 6-10...

  • Page 95: Chapter 7 - Brake System

    Rev: 2 Date: 11/15/18 Chapter 7 - BRAKE SYSTEM ........................7-2 VERVIEW Components ........................ 7-2 .......................... 7-2 ERVICE Supplies ........................7-3 Special Tools ................................. 7-3 Expendable ................................7-3 Replaceable ................................7-3 General ........................7-3 Master cylinder removal............................7-3 Removal ................................7-3 Disconnection ..............................

  • Page 96: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW The brake system includes the necessary components to provide directional control and stopping ability while taxiing. The left and right brakes are independently controlled hydraulic disc brakes. The fluid reservoir supplies the master cylinders with hydraulic fluid.

  • Page 97: Supplies

    Rev: 2 Date: 11/15/18 SUPPLIES ■ CAUTION: U ONLY MIL-H-5606A ! DO NOT MIL SPEC HYDRAULIC FLUID AUTOMOTIVE BRAKE FLUID AMAGE TO RING SEALS MAY RESULT PECIAL OOLS XPENDABLE Brake bleeding fluid pump Hydraulic fluid ♦ ♦ Container Wheel bearing grease ♦...

  • Page 98: Installation

    Rev: 2 Date: 11/15/18 NSTALLATION 1. Installation procedure is reverse of the removal procedure. 2. Bleed the brake system. (7-5) SERVICE SCHEDULE PROCEDURES RAKE PEDAL TORQUE TUBE LUBRICATION Expendable Cotter pins Wheel bearing grease Replaceable None Service Rating Line Minimum Certification LSA-RM, or A&P Additional References KAI Section 28...

  • Page 99: Hydraulic Fluid Drain, Flush, And Replace

    Rev: 2 Date: 11/15/18 4. Remove the brake pedal block from the brake pedal. 5. Remove the WD-1209 brake pedal from the rudder pedal. 6. Clean the pivot tube then apply grease to the exterior of the tube. 7. Installation procedure is reverse of the removal procedure. YDRAULIC FLUID DRAIN FLUSH AND REPLACE...

  • Page 100: Brake Lining Replacement

    Rev: 2 Date: 11/15/18 RAKE LINING REPLACEMENT ● NOTE: I T IS RECOMMENDED TO REPLACE OF THE BRAKE LININGS ON BOTH SIDES EVEN IF ONLY ONE LINING REQUIRES REPLACEMENT Expendable Brake linings Safety wire Replaceable Brake disc Service Rating Line Minimum Certification LSA-RM or A&P Additional References...

  • Page 101: Chapter 8 - Electrical System

    Rev: 2 Date: 11/15/18 Chapter 8 - ELECTRICAL SYSTEM ........................8-2 VERVIEW Components ........................ 8-2 Optional Lighting ......................8-3 Optional Components ....................8-3 .......................... 8-4 ERVICE Supplies ........................8-4 Special Tools ................................. 8-4 Expendable ................................8-4 Replaceable ................................8-4 General ........................8-5 Battery removal ..............................

  • Page 102: Overview

    Rev: 2 Date: 11/15/18 ● NOTE: F OR A SCHEMATIC OF THE ELECTRICAL SYSTEM REFER TO THE POH OR GO TO THE DOWNLOADS PAGE AT WWW VANSAIRCRAFT OVERVIEW ▲ WARNING: T RV-12 S (ULS) F ODULE IS NOT SERVICEABLE ERIOUS RISK OF ELECTRIC SHOCK REMAINS AFTER THE POWER SUPPLY IS REMOVED The RV-12iS electrical system is a 12 VDC, negative ground system equipped with either an EarthX Lithium (LiFePO4) (iS) or Odyssey lead/acid dry cell (ULS) style...

  • Page 103: Optional Lighting

    Rev: 2 Date: 11/15/18 OPTIONAL LIGHTING The lighting components include the wing tip light assembly, extension, landing light rib, landing light, lens backing strip, landing light lens and red eyeball cockpit light. See Figure 20. The wing tip light mounts in the extension which attaches to the wing tip. The landing light is mounted to the landing light rib which is attached inside the wing skin.

  • Page 104: Service

    Rev: 2 Date: 11/15/18 SERVICE ▲WARNING: A LWAYS HAVE AN APPROPRIATE FIRE EXTINGUISHER READILY AVAILABLE ▲WARNING: B EFORE PERFORMING ANY MAINTENANCE OR REPAIRS TURN THE MASTER SWITCH AND DISCONNECT THE NEGATIVE BATTERY CABLE FROM THE BATTERY ■ C AUTION EPLACEMENT COMPONENTS WIRE TERMINALS AND FUSES MUST BE OF...
  • Page 105 Rev: 2 Date: 11/15/18 GENERAL ATTERY REMOVAL Expendable None Replaceable Battery Service Rating Line Minimum Certification Owner and SPC, LSA-RM or A&P Additional References EarthX or Odyssey owner’s manual 1. Remove the top cowl. (12-4) 2. Remove the negative (-) battery cable. 3.
  • Page 106 Rev: 2 Date: 11/15/18 USE REPLACEMENT ■ C AUTION LOWN FUSES MUST BE REPLACED ONLY WITH FUSES OF THE SAME TYPE AND RATING AS SPECIFIED BY THE MANUFACTURER ■ C ‘ ’ AUTION HE MASTER SWITCH MUST BE IN THE POSITION BEFORE REPLACING ANY FUSE ●...

  • Page 107: Special Tools

    Rev: 2 Date: 11/15/18 ITCH TRIM SERVO REPLACEMENT Special Tools D-sub pin extractor Expendable None Replaceable Pitch-Trim servo Service Rating Line Minimum Certification LSA-RM, or A&P Additional References KAI Section 11 EMOVAL 1. Disconnect the negative (-) battery cable. 2. Remove the upper and lower tailcone fairing. (3-4) 3.

  • Page 108: Electrical Component Replacement

    Rev: 2 Date: 11/15/18 LECTRICAL COMPONENT REPLACEMENT ▲WARNING: B EFORE PERFORMING ANY MAINTENANCE OR REPAIRS TURN THE MASTER SWITCH AND DISCONNECT THE NEGATIVE BATTERY CABLE FROM THE BATTERY ■ C AUTION EPLACEMENT COMPONENTS WIRE TERMINALS AND FUSES MUST BE OF THE SAME TYPE AND RATING AS THE ORIGINAL PARTS Special Tools Wire cutter...

  • Page 109: Wire Repair

    Rev: 2 Date: 11/15/18 IRE REPAIR Special Tools Wire cutter Wire stripper Wire terminal crimper Multi-meter Expendable Wire terminals Replaceable Wire Service Rating Line Minimum Certification LSA-RM, or A&P Additional References ASTM F39 F2639 ■ C AUTION HE REPLACEMENT WIRE SIZE AND TYPE MUST BE EQUAL TO THE ORIGINAL 1.
  • Page 110 Rev: 2 Date: 11/15/18 1. Bypass the existing wire with a new wire of equal length. 2. Install new terminals on the new wire that are the same type as those on the existing wire. 3. Connect the new wire terminals to the terminals that are connected by the existing wire.

  • Page 111: Snap Bushing Replacement

    Rev: 2 Date: 11/15/18 NAP BUSHING REPLACEMENT Special Tools Razor knife Expendable None Replaceable Snap bushing Service Rating Line Minimum Certification LSA-RM, or A&P Additional References 1. Extract the failed snap bushing by compressing the two locking tabs and pushing it out of the mounting hole. 2.

  • Page 112: Service Schedule Procedures

    Rev: 2 Date: 11/15/18 SERVICE SCHEDULE PROCEDURES ■ C AUTION ARTH ITHIUM BATTERY IF EQUIPED REQUIRES A SPECIAL BATTERY CHARGER EFER TO ARTH DUCUMENTATION FOR DETAILS Special Tools Battery charger (special type required for EarthX battery) Expendable None Replaceable None Service Rating Line Minimum Certification...

  • Page 113: Chapter 9 - Instruments & Avionics

    Rev: 2 Date: 11/15/18 Chapter 9 - INSTRUMENTS & AVIONICS ........................9-2 VERVIEW Instruments and Avionics Components ................... 9-2 Optional Components ......................9-3 & S ......................... 9-3 ITOT TATIC Components ........................... 9-4 .......................... 9-4 ERVICE Supplies ........................9-4 Special Tools ........................9-4 Expendable .........................

  • Page 114: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW The Dynon SkyView HDX or Garmin G3X EFIS (Electronic Flight Information System) / EMS (Engine Monitoring System) replaces the traditional mechanical flight information and engine monitoring instruments. For removal, installation, inspection, or servicing of the avionics components refer to the manufacturer user manuals. The pitot and static systems provide static and dynamic pressure sources for flight data calculations.

  • Page 115: Optional Components

    Rev: 2 Date: 11/15/18 OPTIONAL COMPONENTS Autopilot Servo See Dynon or Garmin Manual SV-AP-PANEL See Dynon Manual SV-KNOB-PANEL See Dynon Manual Garmin GMC 307 Autopilot Controller See Garmin Manual Landing light See Aero LED Manual Navigation / Strobe light See Aero LED Manual Cockpit light LC ELC-01 SkyView HDX or G3X Dual EFIS / EMS...

  • Page 116: Service

    Rev: 2 Date: 11/15/18 PITOT, STATIC & AOA COMPONENTS Quantity Part or Assembly Name Part Number or Reference Static Source Rivet SD-42-BSLF F Plastic Tee 125 X 125 X 125 TEE Pitot Block FF-1201, UHMW Pitot Tube FF-1202, AT6-058X5/16 FLF-00012 AOA Fitting FLF-00015 Tube Guide...

  • Page 117: General

    Rev: 2 Date: 11/15/18 GENERAL OMPONENT REPLACEMENT See 9-2 through 9-4. OMPONENT EMOVAL BY OWNER OPERATOR Using the KAI as a guide, owner/operators are authorized to remove a screen or any electrical component that is to be sent in for service. ITOT TATIC AND SYSTEM COMPONENT REPLACEMENT...

  • Page 118: Light Replacement

    Rev: 2 Date: 11/15/18 IGHT REPLACEMENT ▲WARNING: B EFORE PERFORMING ANY MAINTENANCE OR REPAIRS TURN THE MASTER SWITCH AND DISCONNECT THE NEGATIVE BATTERY CABLE FROM THE BATTERY Special Tools Wire cutter Wire terminal crimper Wire Stripper Expendable Wire terminals Replaceable Light Module Service Rating Line...
  • Page 119 Rev: 2 Date: 11/15/18 & UDIO INPUT ADJUSTMENT All audio levels are set at the factory to default settings for audio balance. Audio volume levels may need adjustment following component replacement. Following is a list of signals and the corresponding adjustment within the component. (Example: Stall Warning tone level is controlled by the GTR200 “AUX 1”...

  • Page 120: Service Schedule Procedures

    Rev: 2 Date: 11/15/18 SERVICE SCHEDULE PROCEDURES NOTE: T HERE IS NO SCHEDULED MAINTENANCE OR SERVICE ON ANY OF THE AVIONICS OR OPTIONAL EQUIPMENT OTHER THAN THE PERIODIC REPLACEMENT OF THE UNIT BATTERY EFER TO THE OWNERS MANUAL FOR THIS PROCEDURE ERIODIC CHECKS SHOULD BE MADE AT A MINIMUM OF EACH CONDITION INSPECTION TO EFIS/EMS...

  • Page 121: Chapter 10 - Utility Systems

    Rev: 2 Date: 11/15/18 Chapter 10 - UTILITY SYSTEMS ........................10-2 VERVIEW ..........................10-2 Components ......................10-3 ........................10-3 ENTILATION Components ......................10-4 ........................10-4 ERVICE Supplies ........................10-4 Expendable ................................10-4 General ........................10-4 Vent door adjustment ............................10-4 Service Schedule Procedures ...................

  • Page 122: O Verview

    Rev: 2 Date: 11/15/18 OVERVIEW The aircraft utility systems are the systems that are not critical to flight. The heat system enables the occupants to control the cockpit temperature at each seating position with a push/pull cable. Hot air diverted from a heat muff on the exhaust system muffler provides cockpit heat.

  • Page 123: V Entilation

    Rev: 2 Date: 11/15/18 HEAT COMPONENTS Quantity Part or Assembly Name Part Number or Reference Heat Muff Assy. FF-00090 Heat Control Valve Vent-00001 Assy. Heat Muff Hose, 2” SCAT FF-00091 Push / Pull Cable CT A-740 BLACK VENTILATION A hand-operated vent on each side of the cockpit provides cockpit ventilation. Each vent is a tip-out door installed on each fuselage side skin.

  • Page 124: S Ervice

    Rev: 2 Date: 11/15/18 COMPONENTS Quantity Part or Assembly Name Part Number or Reference Vent brackets F-1086 Vent doubler F-1096 Vent door sub-assembly See shaded items below Vent slide F-1087 Vent door doubler F-1092 Vent door F-1093 SERVICE The heating and vent systems do not require regular maintenance. If the push / pull cable’s operation is not smooth at any time, lubricate the interior of the cable with spray lube.
  • Page 125 Rev: 2 Date: 11/15/18 SERVICE SCHEDULE PROCEDURES NONE 10-5...
  • Page 126 Rev: 2 Date: 11/15/18 THIS PAGE INTENTIONALLY LEFT BLANK 10-6...
  • Page 127 Rev: 2 Date: 11/15/18 Chapter 11 - PROPELLER ........................11-2 VERVIEW Components ......................11-2 ........................11-2 ERVICE Supplies ........................11-2 Special Tools ............................... 11-2 Expendable ................................11-2 Replaceable ................................. 11-2 Spinner and Pitot Tube 11-3 ..........................Prop & Hub ........................ 11-3 11-1...

  • Page 128: O Verview

    Rev: 2 Date: 11/15/18 OVERVIEW The RV-12iS is equipped with a ground adjustable Sensenich propeller. For instructions regarding adjust the propeller pitch, refer to the KAI and user manual provided with the propeller. The current propeller manuals and/or specifications take precedence over referenced information in this manual.

  • Page 129: Prop & Hub

    Rev: 2 Date: 11/15/18 SPINNER AND PITOT TUBE Inspect the Pitot tube and bushing for excessive wear using a clearance gauge. Make the clearance gauge by cutting a ¾ inch X 4 inch paper strip from common note book paper (typical thickness is about .003 inch). Make a mark on the strip ¾ inch from one end.
  • Page 130 Rev: 2 Date: 11/15/18 • Whenever there is evidence of rough operation check for proper bolt torque. For new installations it often helps to remove the propeller, rotate it 180˚ and reinstall. • If the propeller shows any of the following signs of damage it must either be repaired (if possible) or retired from service: Cracks in the metal hub or bolts ♦...
  • Page 131 Rev: 2 Date: 11/15/18 Chapter 12 - FIREWALL FORWARD ..................................12-2 VERVIEW Components ..................................12-2 Engine ..................................... 12-3 Rotax 912iS ................................. 12-3 Rotax 912ULS ..............................12-3 Spark Plugs ..............................12-4 Ignition ................................12-4 ..................................12-4 ERVICE Supplies ................................... 12-4 Special Tools ............................... 12-4 Expendable ................................

  • Page 132: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW Engine information is taken from Rotax documentation. For complete engine information refer to the Rotax engine documentation. Note: Rotax is the primary authority for specifying the level of certification required by an individual performing maintenance or repair on a Rotax 912ULS or 912iS engine. Refer to the Rotax documentation to determine the qualifications or training required for any maintenance or repair action.

  • Page 133: Engine

    Rev: 2 Date: 11/15/18 ENGINE Figure 26iS: Rotax 912iS Sport Figure 26ULS: Rotax 912ULS Current engine product manuals and/or specifications take precedence over any 12-3...

  • Page 134: Service

    Rev: 2 Date: 11/15/18 associated information referenced in this manual for convenience. This manual will not reflect current revisions to products or specifications made by the engine manufacturer. Refer to the engine manufacturer's operators manual for specifications. PARK LUGS Type: NGK DCPR8E Socket: 5/8”...

  • Page 135: Special Tools

    Rev: 2 Date: 11/15/18 GENERAL OWLING REMOVAL Expendable None Replaceable Hinge pins Service Rating Line Owner and SPC, LSA-RM or A&P Minimum Certification Additional References Top Cowl: 1. Remove the screws (2) in the F-1240B Cover Plate located at the top rear of the cowling to access the aft cowl attach hinge pins.

  • Page 136: Engine Oil Level Check

    Rev: 2 Date: 11/15/18 IL FILTER REPLACEMENT Special Tools Oil filter wrench Expendable Oil Filter Replaceable None Service Rating Line Minimum Certification Owner and SPC, LSA-RM or A&P Additional References Rotax 912 Line Maintenance manual 1. Refer to the Rotax manual. NGINE OIL LEVEL CHECK ▲...

  • Page 137: Engine Coolant Level Check

    Rev: 2 Date: 11/15/18 NGINE COOLANT LEVEL CHECK ▲ WARNING: DO NOT REMOVE THE RADIATOR CAP FROM A HOT COOLING SYSTEM CALDING COOLANT WILL SPRAY ▲ WARNING: B EFORE PERFORMING ANY INSPECTION OR SERVICE ALLOW THE ENGINE COMPONENTS TO COOL Expendable Engine coolant Replaceable...
  • Page 138 Rev: 2 Date: 11/15/18 (ULS) ARBURETOR YNCHRONIZATION Special Tools 1 - Vacuum gauge set Expendable None Replaceable None Service Rating Line Minimum Certification LSA-RM with Rotax Service certification or A&P with Rotax Service certification Additional References Rotax Line Maintenance Manual Refer to the Rotax Line Maintenance manual 12-8...

  • Page 139: Verify Functionality Of Throttle Return Spring

    Rev: 2 Date: 11/15/18 ● NOTE: W HEN CHECKING THE IDLE SPEED DURING THE ADJUSTMENT PROCEDURE ONLY PULL LIGHTLY ON THE THROTTLE CONTROL UNTIL YOU JUST FEEL THE IDLE STOPS ON THE CARBURETORS HEAVY PULL ON THE THROTTLE CONTROL WILL FLEX THE THROTTLE ARMS AND GIVE AN INACCURATE IDLE SPEED ●...

  • Page 140: Throttle Return Spring Replacement

    Rev: 2 Date: 11/15/18 1. This section must be done with the aircraft outside. 2. Chock main wheels, tie-down tail. 3. BRAKES: Apply FULL. 4. Start engine, check for oil pressure functioning and showing pressure. 5. Warm the engine to 122°F. 6.

  • Page 141: Service Schedule Procedures

    Rev: 2 Date: 11/15/18 Special Tools None Expendable None Replaceable SPRING-00002-L/R-1 (ULS) Service Rating Line Owner and SPC, LSA-RM or A&P Minimum Certification Additional References EMOVAL 1. Remove SPRING-00002 as shown in KAI Section 49U. NSTALLATION 1. Installation procedure is reverse of the removal procedure. 2.

  • Page 142: Oil Hose Replacement

    Rev: 2 Date: 11/15/18 EPLACEMENT ▲ WARNING: B EFORE PERFORMING ANY INSPECTION OR SERVICE ALLOW THE ENGINE COMPONENTS TO COOL Expendable Plastic tie-wrap 8in Replaceable Oil Supply Hose, Oil Cooler Hose, Oil Return Hose, Oil Tank Vent Tube, Oil Vent Interconnect Service Rating Line Minimum Certification...

  • Page 143: Manifold Pressure Hose Replacement

    Rev: 2 Date: 11/15/18 (ULS) ANIFOLD RESSURE EPLACEMENT Tools Wire cutters, straight slot screwdriver(for prying hose) Expendable Tie wrap Replaceable Manifold pressure hose Service Rating Line Minimum Certification LSA-RM with Rotax Service certification or A&P with Rotax Service certification Additional References EMOVAL 1.
  • Page 144 Rev: 2 Date: 11/15/18 ■ W ARNING XPECT SOME FUEL DRAINAGE TO OCCUR AS THE HOSE CONNECTIONS ARE REMOVED SE PROTECTIVE GLOVES AND HAVE SHOP RAGS CLOSE BY 7. Disconnect fuel hoses at firewall. Some fuel may still be in hoses. 8.

  • Page 145: Chapter 13 - Fuel System

    Rev: 2 Date: 11/15/18 Chapter 13 - FUEL SYSTEM ULS SYSTEM iS SYSTEM 13-1...

  • Page 146: Overview

    Rev: 2 Date: 11/15/18 ........................13-2 VERVIEW Components ......................13-3 Fuel System Schematic .................... 13-4 ........................13-6 ERVICE Supplies ........................13-6 Special Tools ............................... 13-6 Expendable ................................13-6 Replaceable ................................. 13-6 General ........................13-6 Draining the fuel system ............................13-7 Fuel tank removal ..............................

  • Page 147: Components

    Rev: 2 Date: 11/15/18 pressure transducer main fuel filter with a check valve and by-pass line (safety bypass in case of restricted fuel filter), a metered bypass/loop-back manifold assy. located below the throttle control, main line routing to the firewall, hose routing from firewall to inlet port on fuel rail (engine right rear), hose connecting outlet of fuel pressure regulator (engine left rear) to firewall fitting and line feeding back to low pressure side of the bypass manifold assy., and then back to the fuel tank.
  • Page 148 Rev: 2 Date: 11/15/18 13-4...
  • Page 149 Rev: 2 Date: 11/15/18 13-5...

  • Page 150: Service

    Rev: 2 Date: 11/15/18 SERVICE ▲WARNING: A LWAYS HAVE AN APPROPRIATE FIRE EXTINGUISHER READILY AVAILABLE ▲WARNING: B EFORE PERFORMING ANY MAINTENANCE OR REPAIRS TURN THE MASTER SWITCH AND DISCONNECT THE NEGATIVE BATTERY CABLE FROM THE BATTERY ■ C AUTION EPLACEMENT FUEL SYSTEM COMPONENTS MUST BE EQUIVALENT TO THE ORIGINAL PARTS ●...

  • Page 151: Draining The Fuel System

    Rev: 2 Date: 11/15/18 RAINING THE FUEL SYSTEM Special Tools 1/8”NPT x 3/8” hose barb 12” x 3/8” I.D. fuel hose Fuel Container Protective Gloves Expendable Pipe Thread Sealant Replaceable None Service Rating Line Minimum Certification Owner and SPC, LSA-RM or A&P Additional References •...

  • Page 152: Fuel Tank Removal

    Rev: 2 Date: 11/15/18 the open end of the fuel drain hose that is connected to the bottom of the gascolator or fuel drain assy. This will evacuate the majority of the fuel held within the system, and help prevent fuel loss if system components are being removed.

  • Page 153: Installation

    Rev: 2 Date: 11/15/18 Expendable None Replaceable None Service Rating Line Minimum Certification LSA-RM or A&P Additional References 1. Isolate the component from fuel flow with either the fuel shutoff valve or by draining the fuel tank/system (13-17). 2. Label, and then disconnect the electrical connections attached to the component, if applicable.

  • Page 154: Installation

    Rev: 2 Date: 11/15/18 NSTALLATION 1. Installation procedure is reverse of the removal procedure. Use thread sealant on the threads when re-installing the quick-drain valve. OARSE FUEL TANK SCREEN REMOVAL Expendable pipe thread sealant Replaceable None Service Rating Line Minimum Certification LSA-RM or A&P Additional References 1.
  • Page 155 Rev: 2 Date: 11/15/18 Installation: 1. Installation of new hose assembly is reverse of removal procedure. Rotax specifies that new copper crush washers be used. 2. Torque banjo bolt M8X1X17 to 90 in-lbs. Figure 31: Fuel Pressure Hose Flush RESSURE LUSH VA-216 H LEFT SIDE OF...
  • Page 156 Rev: 2 Date: 11/15/18 2. Loosen VA-216 Fuel Return Assembly hose coupling while supporting elbow with second wrench. 3. Place container beneath hose and remove hose from fitting. 4. With end of hose inside container, flush hose by turning on fuel boost pump for two seconds.

  • Page 157: Fuel Drain Hose Replacement

    Rev: 2 Date: 11/15/18 (ULS) UEL DRAIN HOSE REPLACEMENT Expendable Tie wraps (2) Replaceable Fuel interconnect and drain hoses Service Rating Line Minimum Certification LSA-RM with Rotax Service certification or A&P with Rotax Service certification Additional References Removal 1. Cut the tie wraps attaching the drain hose to the gascolator-to-fuel-pump hose.
  • Page 158 Rev: 2 Date: 11/15/18 7. Remove safety wire from end of filter and thread the end of the filter out of the filter body. 8. Inspect / clean the filter and interior of filter body. 9. Reassemble the filter and install safety wire. 10.

  • Page 159: Long Term Storage

    Rev: 2 Date: 11/15/18 5. Disconnect the upper end of the F-12127G Fuel Line from the Fuel Pump Manifold, and if available seal the fitting with a cap to prevent fuel spillage. 6. Disconnect the wiring harness from both fuel pumps and the fuel pressure sensor.
  • Page 160 Rev: 2 Date: 11/15/18 ■ W ARNING XPECT SOME FUEL DRAINAGE TO OCCUR AS THE BOWLS ARE REMOVED SE PROTECTIVE GLOVES AND HAVE SHOP RAGS CLOSE BY 3. Slide the wire bail aft, remove the bowl, and drain the fuel. 4.

  • Page 161: Chapter 14 - Exhaust System

    Rev: 2 Date: 11/15/18 Chapter 14 - EXHAUST SYSTEM ........................14-2 VERVIEW Components ......................14-2 ........................14-2 ERVICE Supplies ........................14-2 Special Tools ............................... 14-2 Expendable ................................14-2 Replaceable ................................. 14-2 General ........................14-3 Exhaust system removal............................14-3 Installation ................................ 14-3 Service Schedule Procedures ...................

  • Page 162: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW The primary purpose of the exhaust system is to direct engine combustion gasses and heat away from the aircraft, components and occupants. The purpose of the muffler is to reduce engine noise and allow attachment of a heat muff for heating cabin air.

  • Page 163: Service

    Rev: 2 Date: 11/15/18 GENERAL XHAUST SYSTEM REMOVAL INSTALLATION ▲ WARNING: A LLOW THE EXHAUST COMPONENTS TO COOL BEFORE PERFORMING INSPECTION OR SERVICE Expendable Anti-seize compound, High Temp. RTV, High Temp. Safety Wire Replaceable Joint spring Service Rating Line Minimum Certification LSA-RM or A&P Additional References 1.

  • Page 164: S Ervice

    Rev: 2 Date: 11/15/18 SERVICE SCHEDULE PROCEDURES ALL JOINT LUBRICATION ▲ WARNING: A LLOW THE EXHAUST COMPONENTS TO COOL BEFORE PERFORMING INSPECTION OR SERVICE Required tools Locking pliers Required expendables Anti-seize compound Replaceable None Service rating Line Minimum Certification LSA-RM or A&P Additional Reference 1.

  • Page 165: Chapter 15 - Painting And Coatings

    Rev: 2 Date: 11/15/18 Chapter 15 - PAINTING AND COATINGS ........................15-2 VERVIEW ........................15-3 ERVICE Supplies ........................15-3 Tools ..................................15-3 Expendable ................................15-3 Replaceable ................................. 15-3 Service Schedule Procedures ................... 15-3 Powder coat repair .............................. 15-3 Primer repair ................................ 15-4 Decorative paint repair ............................

  • Page 166: Overview

    Rev: 2 Date: 11/15/18 OVERVIEW ● NOTE: R KAI – S EFER TO ECTION FOR ADDITIONAL INFORMATION The aluminum skins used on the RV-12iS aircraft are all 2024-T3 alloy. They are "Alclad", meaning both sides of the sheet are coated with pure aluminum during manufacture.

  • Page 167: Service

    Rev: 2 Date: 11/15/18 SERVICE ▲ WARNING: P AINT OR SOLVENT MUST USED IN ACCORDANCE WITH THE MANUFACTURERS INSTRUCTIONS ▲ WARNING: DO NOT USE ANY TYPE OF BODY FILLER ON THE AIRCRAFT ▲ WARNING: DO NOT DAMAGE ANY RIVET HEADS WHEN PREPARING A SURFACE FOR TOUCH UP PAINT ■...
  • Page 168 Rev: 2 Date: 11/15/18 Special Tools Sandpaper Scotchbrite® type pad Expendable Primer Touch-up paint Replaceable None Service Rating Line Total area 4 in² or less - Owner and SPC Minimum Certification Total area greater than 4 in² - LSA-RM or A&P Additional References 1.
  • Page 169 Rev: 2 Date: 11/15/18 ECORATIVE PAINT REPAIR ■ CAUTION: A NY SCRATCH THAT HAS PENETRATED TO THE METAL MUST BE CLEANED AND PRIMED PRIOR TO APPLYING DECORATIVE PAINT ● NOTE: W HEN PRIMING A REMOVABLE PART BETTER RESULTS CAN BE ACHIEVED BY REMOVING THE PART Special Tools Scotchbrite®...
  • Page 170 Rev: 2 Date: 11/15/18 THIS PAGE INTENTIONALLY LEFT BLANK 15-6...

  • Page 171: Chapter 16 - Troubleshooting

    Rev: 2 Date: 11/15/18 Chapter 16 - TROUBLESHOOTING Symptom Possible Causes Related Chapter Recurring blown fuse Short in circuit ♦ Overloaded circuit ♦ Engine will turn over, Insufficient ignition source ♦ fails to start Insufficient fuel supply to engine ♦ Insufficient air supply to engine ♦...
  • Page 172 Rev: 2 Date: 11/15/18 Symptom Possible Causes Related Chapter Low frequency Out of balance nose wheel assembly vibration in flight Vibration at idle Propeller installed incorrectly ♦ Propeller unbalanced ♦ Idle RPM too low Rotax line maint. ♦ Carb. sync. out of balance (ULS) Rotax line maint.
  • Page 173 Rev: 2 Date: 11/15/18 BRP U (BUDS) TILITY AND IAGNOSTIC OFTWARE A maintenance port is located beneath the instrument panel to the right of the center console to accommodate the BUDS ECU 9 pin d-sub. See Figure. BUDS is a ROTAX product designed to read and extract data from the 912iS ECU (Engine Control Unit).
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  • Page 175: Chapter 17 - Feedback & Replacement Parts

    • Brief description of the type and frequency of aircraft use (may include; runway conditions, flying conditions, storage methods, etc.) REPORTING METHODS Mail to: ATTN: RV-12iS Safety Alert Van's Aircraft, Inc. 14401 Keil Road, NE Aurora, OR 97002 USA Fax to: 'RV-12iS Safety Alert' (on cover page) 503.678.6560...

  • Page 176: Replacement Parts

    Van's Aircraft Inc. reserves the right to update, modify or discontinue any part without notice. Van's Aircraft Inc. is not liable for the use of any part or material by the owner that does not appear on the kit's part list. Use of any unauthorized part or material will be at the owner/operators own risk.

  • Page 177: Substitute Parts

    Rev: 2 Date: 11/15/18 SUBSTITUTE PARTS The following parts are approved for substitution. Either the original part or substitute part is acceptable for installation in the aircraft. Oil System (Note: There was no 'original part' in this case.) FUMOTO F107N 12mm-1.75 Quick Oil Drain Plug ↔ CCA-2450 Valve and CCA-2474 Extension ↔...
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  • Page 179: Chapter 18 - Supplement

    Rev: 2 Date: 11/15/18 Chapter 18 - SUPPLEMENT ............................18-3 ERVICE CHEDULE CHECKLIST ..............................18-7 NSPECTION HECKLIST ………….........................18-29 LECTRICAL SYSTEM SCHEMATIC .....................................18-31 ................................18-33 EEDBACK 18-1...
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  • Page 181 Rev: 2 Date: 11/15/18 SERVICE SCHEDULE CHECKLIST Service Next What Action When Date Initial Aircraft Inspection Annual or 100 hours AOA wing root connection Lubricate and Test Every wing removal 5-26 AST attach hinge Lubricate Annual or 100 hours 5-27 Battery Charge As needed...
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  • Page 183 Rev: 2 Date: 11/15/18 SERVICE SCHEDULE CHECKLIST (CONTINUED) Service Next What Action When Date Initial Fuel Tank Finger Strainer Clean & inspect Annual or 100 hours 13-8 Gascolator (ULS) Clean & inspect Annual or 100 hours 13-7 Landing gear attach hardware Torque Annual or 200 hours 3-13...
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  • Page 185: Service Schedule

    Rev: 2 Date: 11/15/18 INSPECTION CHECKLIST RV-12iS Aircraft Inspection Reg. Number: Airframe S/N: Engine S/N: Airframe TT: Engine TT: Inspection Date: Inspector: Check all that apply to inspector and inspection: ____ Owner ____ Operator ____ Pilot ____ A&P ____ LSA Repairman Inspection ____ LSA Repairman Maintenance ____ 100 hour ____ Annual ____ Extreme Conditions ____ After Hard Landing Category:...
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  • Page 187 Rev: 2 Date: 11/15/18 Pass Fail Left and Right Wing Secure / Smooth operation of ailerons and flaps Brake System Operation Fuel Level Correct Indication Verify function of throttle return springs Springs pull throttle to wide open with friction control off (see procedure page 12-10) Static RPM at full throttle Operational / RPM ________________ Electrical System...
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  • Page 189 Rev: 2 Date: 11/15/18 Notes: Cockpit Check Complete Pre-Inspection procedure Step 1-5 (Page 3-3) Pass Fail Aft Face of Firewall Cracks / Deformation Rudder Pedal Assemblies Cracks / Proper operation Brake Pedal Assemblies Proper Operation / Leaks Control Sticks Proper Operation Control system cables Wear / Fraying Control system...
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  • Page 191 Rev: 2 Date: 11/15/18 Roll Bar, and Canopy Frame Security / Cracks / Proper Latch Operation Control / Instrument Panels Proper Placards Installed Control / Instrument Panels Security / Connections Fuses Security / Condition / Spares Air & Heat Vents Operation / Security Engine Throttle Control Cable Operation / Kinks / Interference...
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  • Page 193 Rev: 2 Date: 11/15/18 Emergency Locator Transmitter Comply with current FAR 91.207 Pass Fail "G" Switch Also refer to current CFR 91.207 Calendar date Also refer to current CFR 91.207 Battery Condition Also refer to current CFR 91.207 Audio Alert Indicator Battery See Manufacturer’s Manual Remote Control Panel Ind.
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  • Page 195 Rev: 2 Date: 11/15/18 Engine Refer to Rotax Manual Pass Fail Engine and components Comply with Rotax manufacturer inspection recommendations and procedures (Rotax Line Maintenance Manual) Firewall Forward Check Pass Fail Overall insp. of Engine Compartment Leakage / Corrosion / Wear Fwd.
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  • Page 197 Rev: 2 Date: 11/15/18 Empennage Check Pass Fail Vertical Stabilizer Skins Deformation / Cracks / Signs of Wear / Corrosion Vertical Stabilizer Skin Rivets Missing / Deformed Vertical Stabilizer Fwd. Spar Deformation / Cracks / Signs of Wear Vertical Stabilizer Rear Spar Deformation / Cracks / Signs of Wear Vertical Stabilizer Fiberglass Fairing Condition / Security...
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  • Page 199 Rev: 2 Date: 11/15/18 Empennage (Continued) Check Pass Fail Anti-Servo Tab Skins Deformation / Cracks / Signs of Wear / Corrosion Anti-Servo Tab Skin Rivets Missing / Deformed Anti-Servo Tab Spar / Hinge Deformation / Cracks / Signs of Wear Anti-Servo Tab Control Horn Attach.
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  • Page 201 Rev: 2 Date: 11/15/18 Fuselage Check Pass Fail Skins Deformation / Cracks / Signs of Wear / Corrosion Footprint Area of Left & Right Wing Signs of Wear / Cracks / Damaged Fasteners Bulkheads & Stringers Deformation / Cracks / Signs of Wear / Corrosion Left &...
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  • Page 203 Rev: 2 Date: 11/15/18 Wings / Center Section Check Pass Fail Skins Deformation / Cracks / Signs of Wear / Corrosion Ribs & Attach Angles Deformation / Cracks / Signs of Wear / Corrosion Main, Fwd. & Aft Spars Deformation / Cracks / Signs of Wear / Corrosion Flaperon Deformation / Cracks / Signs of Wear / Corrosion Hinges...
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  • Page 205 Rev: 2 Date: 11/15/18 Paperwork Completed Record Findings Aircraft Log Record Inspection Aircraft Log Record Maintenance Aircraft Log Notes and explanation of discrepancies found: End of inspection checklist 18-27...
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  • Page 207 Rev: 2 Date: 11/15/18 Electrical System Diagrams Refer to P. O. H. or the Downloads Section under the Support tab of Van’s Aircrafts web site www.vansaircraft.com 18-29...
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  • Page 209: 3-View

    3 VIEW Rev: 2 Date: 11/15/18 18-31...
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  • Page 211: Feedback Form

    Rev: 2 Date: 11/15/18 Feedback Form Owner: Name Phone: Number Aircraft: Model Contact: Name Phone: Number Total Time Serial Number Inspector: Name Phone: Number Engine: Model Inspection: Date Storage: Inside/outside/etc Total Time Serial Number Location: City State Country Affected Parts: Problem Description: 18-33...
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  • Page 213: Chapter 19 - Glossary

    Some aircraft maintenance may be performed by an "Approved Approved Owner Owner" found competent by Van's Aircraft. Approval will be for a specific task, person(s) and aircraft. Refers to the FAA Advisory Circular ‘Acceptable Methods, Techniques, and Practices – Aircraft Inspection and Repair.
  • Page 214 Rev: 2 Date: 11/15/18 EMS. Refers to the Dynon D-180, Dynon Skyview or Garmin G3X. Engine The portion of the EFIS unit that compiles and displays engine Management System information. Extreme Heavily contaminated air; dust, bugs, smoke, debris, ash, sand, etc. or adverse climatic conditions conditions Flaperon...
  • Page 215 Rev: 2 Date: 11/15/18 Maintenance, inspection, repair, or alterations that are only to be Overhaul accomplished by the original manufacturer or a facility approved by the original manufacturer of the product. Facility specifically authorized by the aircraft or component Overhaul Facility manufacturer to overhaul the product originally produced by that manufacturer.
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  • Page 217: Chapter 20 - Index

    Rev: 2 Date: 11/15/18 Chapter 20 - INDEX AOA (see Angle-Of-Attack) Abbreviations ............. 1-6 Air filter ............. 12-3 Oil ..............1-11 Inspection ............3-9 Installation ............ 12-7 Removal ............12-7 Angle-Of-Attack Sys. Press. Check..3-16, 5-13 Anti-servo / trim tab ........5-6, 5-7 Inspection .............
  • Page 218 Rev: 2 Date: 11/15/18 Inspection ............3-5 Control cable ............6-1 Replacement ..........6-6 Control Stops ............. 3-5 Control system ........... 6-1 Rod-End Lubrication ........6-8 Coolant ..........See Engine Cowl Hinge ........... 12-2, 12-11 Cowling Installation ............ 12-5 Removal ............12-5 Decorative paint ..........
  • Page 219 Rev: 2 Date: 11/15/18 Draining ............13-4 Fuel Tank ............13-7 Installation ............ 13-8 Removal ............13-8 Fuselage............. 5-2 Inspection ............. 3-12 Lift and Support..........1-16 Fuselage Pins ............ 5-3 Fuses ..............8-6 Garmin ............9-2, 9-4 Gascolator Cleaning ............13-9 Installation ..........
  • Page 220 Rev: 2 Date: 11/15/18 Removal ............5-22 Main Wheel and Tire Inspection ............. 3-13 Installation ............ 5-15 Removal ............5-15 Main Wheel Assembly ........5-9 Master cylinder Installation ............7-4 Removal ............7-3 Nose Gear Leg Fairing ........5-10 Nose Landing Gear ..........5-8 Inspection .............
  • Page 221 Rev: 2 Date: 11/15/18 Lubrication ............. 6-8 Replacement ..........6-7 Rudder Pedals Installation ............6-8 Removal ............6-8 Rudder ..............5-6 Inspection ............. 3-11 Hinge Replacement ........5-19 RV-12iS 3-View ............18-31 Summary ............1-1 Safety ..............1-4 Feedback ............. 17-1 Feedback Form ..........
  • Page 222 Rev: 2 Date: 11/15/18 Wheel Bearings Main ............. 5-28 Nose ............. 5-27 Wing Attach Location Lubrication ....5-26 Fuselage Pins ..........5-26 Stub Spar and Rear Spar ......5-26 20-6...

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