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Cirrus Airplane Maintenance Manual Model Sr22

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Cirrus Airplane Maintenance Manual Model Sr22 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 RUDDER 1. GENERAL The rudder provides airplane directional (yaw) control and includes a rudder trim tab used for yaw trim adjustment. The rudder is of conventional design with skin, spar and ribs manufactured of aluminum. The rudder is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bellcrank. Rudder motion is transferred from conventional rudder pedals to the rudder by a single cable system under the cabin floor to the elevator sector pulley in the aft fuselage. A push-pull tube from the sector to the rud- der bellcrank translates cable motion to the rudder. Springs connected to the rudder pedal assembly close the loop and provide centering force. EFFECTIVITY: All 55-40 Page 1 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 2. MAINTENANCE PRACTICES A. Rudder Assembly (See Figure 55-401) (1) Removal - Rudder Assembly (a) Remove cotter pin, nut, washers, and bolt securing rudder push/pull rod to rudder. (b) Remove cotter pins from bolts securing rudder to vertical stabilizer. (c) Remove lower bolt, washers, and castellated nut securing rudder to vertical stabilizer. (d) Serials 0004 thru 0168: Disconnect rudder trim wire harness. (e) While supporting rudder assembly, remove upper and center bolts, washers, and castel- lated nuts securing rudder assembly to vertical stabilizer. Remove rudder assembly from vertical stabilizer. (2) Disassembly - Rudder Assembly Rudder assembly may be further disassembled through removal of trim tab and rudder bottom. (a) Rudder Trim Tab 1 Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Drill bit #40 Any Source Drill out rivets. 2 Drill out rivets securing trim tab to rudder. (b) Rudder Bottom 1 Remove screws securing rudder bottom to rudder. (3) Assembly - Rudder Assembly (a) Rudder Trim Tab 1 Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Alodine Pen - Any Source Corrosion protec- tion. 2 Using an Alodine pen, apply corrosion protection to edge of each rivet hole. 3 Install rivets securing trim tab to rudder. 4 Apply thin coat of paint to each rivet head. (Refer to 51-30) 5 Perform Adjustment/Test - Rudder Balancing. (Refer to 55-40) (b) Rudder Bottom 1 Position rudder bottom to rudder and install screws securing rudder bottom to rud- der. (c) Serials 0002 thru 1519: Rudder Bottom Replacement 1 Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Permanent Marker - Any Source Mark Drill bit 0.191 inch (0.485 cm) Any Source Match Drill 2 Position rudder bottom to rudder and ensure gap is equal to or less than 0.5 inch (1.27 cm). Verify reveal line between rudder bottom and rudder are consistent along EFFECTIVITY: 55-40 All Page 2 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 length of seam, and trailing edge of rudder bottom is flush with trailing edge of rud- der. CAUTION: Verify marked locations for match drilling obtain the proper edge mar- gin required for hole and nutplate installation. 3 Use marker to mark match drill locations in rudder bottom. 4 Using 0.191 inch (0.485 cm) drill bit, drill at marked locations on rudder bottom. 5 Install rivets and nutplates at drilled hole locations on rudder bottom inboard flange. 6 Apply thin coat of paint to each rivet head. (Refer to 51-30) 7 Install screws securing rudder bottom to rudder. (4) Installation - Rudder Assembly Note: Verify threaded end of bolts are installed downward. (a) Position rudder assembly to vertical stabilizer. Install bolts, washers, and new castellated nuts to upper and center hinges securing rudder assembly to vertical stabilizer. (b) Torque bolts at upper and center hinges to 20 - 25 in-lb (2.3 - 2.8 Nm). (c) Tighten bolt at center hinge to 50 - 70 in-lb (5.6 - 7.9 Nm). (d) Serials 0004 thru 0168: Connect rudder trim wire harness. Note: Maximum of two washers are added between bottom hinge and rudder assembly to obtain proper clearance. (e) Install bolt, washers, and castellated nut to lower hinge securing rudder assembly to verti- cal stabilizer. (f) Tighten bolt at lower hinge to 50 - 70 in-lb (5.6 - 7.9 Nm). (g) Secure all bolts with cotter pins. (h) Position rudder push/pull rod to rudder and secure with bolt, washers, nut, and cotter pin. (i) Perform Inspection/Check - Rudder Gap and Overlap. (Refer to 55-40) (j) Perform Inspection/Check - Rudder Assembly. (Refer to 55-40) (k) If rudder trim tab was replaced, perform Adjustment/Test - Rudder Trim Tab. (Refer to 55- 40) (5) Inspection/Check - Rudder Assembly (a) Verify hinge bolts for proper torque and installation. (Refer to 55-40) (b) Verify proper installation of safety wire and cotter pins on all fasteners. (c) Ensure rudder skin is smooth and free of any defects or irregularities. (d) Inspect rivets and rudder skin for tightness. (e) Operate rudder controls and inspect for any abnormal resistance. EFFECTIVITY: All 55-40 Page 3 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 RUDDER HORN (REF) 1 2 3 3 2 2 VERTICAL STABILIZER 5 (REF) 6 3 2 2 11 6 5 3 3 2 2 10 13 7 2 5 9 2 6 4 8 2 5 LEGEND 6 1. Lead Washer 11 2. Washer NOTE 3. Bolt Maximum of two washers are added between 12 4. Washer, Large Area bottom hinge and rudder assembly 5. Castellated Nut to obtain proper clearance. 6. Cotter Pin 7. Rudder On replacement rudder bottom, verify marked 8. Rudder Bottom locations for match drilling obtain the proper edge 9. Screw margin required for hole and nutplate installation. 10. Trim Tab 11. Rivet 12. Nutplate 13. Rod End SR22_MM55_1242D Figure 55-401 Rudder Assembly EFFECTIVITY: 55-40 All Page 4 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 (6) Inspection/Check - Rudder Gap and Overlap (See Figure 55-402) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Inclinometer PRO360 Macklanburg Duncan Deflection angle determination. Oklahoma City, OK 73125 800-654-0007 (b) Adjust rudder to the fully leftmost position. CAUTION: Allowable gap between rudder horn and vertical stabilizer is between 0.150 and 0.300 inch (3.81 and 7.62 mm). (c) At rudder horn, verify gap between rudder horn and vertical stabilizer is between 0.150 and 0.300 inch (3.81 and 7.62 mm). If gap between rudder horn and vertical stabilizer does not fall within the specified clear- ance, contact Cirrus Design Customer Service Department for disposition. (d) Repeat gap measurement with rudder to the fully rightmost position. Note: The following gap and overlap inspections need only be performed after the installation of a replacement (new or different) rudder or after repairing the lower rudder hinge. If rudder leading edge gap and overlap inspections do not fall within the specified clearances, contact Cirrus Design Customer Service Department for disposition. (e) Replacement Rudder Installation Only: Verify gap between rudder leading edge and trail- ing edge of vertical stabilizer has a minimum of 0.060 inch (1.524 mm) and a maximum of 0.350 inch (8.890 mm) clearance when rudder is fully deflected right and left. Note: The rudder overlap inspection applies only to the area between the water- line of the horizontal stabilizer to the tip of the vertical stabilizer. (f) Replacement Rudder Installation Only: Verify overlap between rudder and vertical stabi- lizer has a minimum of -0.125 inch (-3.175 mm) and a maximum of 0.125 inch (3.175 mm) clearance. Rudder may be deflected left 0 - 5° to achieve right overlap, and may be deflected right 0 - 5° to achieve left overlap. EFFECTIVITY: All 55-40 Page 5 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 45 +5° NEUTRAL -5° NOTE 4 1 Verify gap between rudder horn and OVERLAP GAP INSPECTION vertical stabilizer is between 0.150 and 0.300 (3.81 and 7.62 mm). 2 Replacement Rudder Installation only: 23 Verify leading edge gap has a minimum of 0.060 inch (1.524 mm) and a maximum of 0.350 inch (8.890 mm) clearance. 3 Replacement Rudder Installation only: Measure tangent to the leading edge curvature. 4 Replacement Rudder Installation only: 20.0° Verify overlap gap has a minimum of -0.125 inch (-3.175 mm) and a maximum of 0.125 inch (3.175 mm) clearance. LEADING EDGE GAP INSPECTION 5 Replacement Rudder Installation only: Measure overlap tangent to the leading edge curvature. Use a 6 inch straight edge. 1 SR22_MM55_2088A Figure 55-402 Rudder Gap and Overlap EFFECTIVITY: 55-40 All Page 6 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 (7) Adjustment/Test - Rudder Balancing (See Figure 55-403) CAUTION: When balancing, the rudder assembly must be complete including mounting brackets, paint, stripes, rudder bottom, and rudder tip. The bench used to support knife edge supports must be level. Maximum mass balance weight is 2.5 pounds (1.13 kg). (a) Acquire necessary tools and equipment. Description P/N or Spec. Supplier Purpose Close Tolerance Balance Pins - Any Source Support rudder assembly. Balance Fixture - Any Source Balance rudder assembly. Straight Edge - Any Source Mark chord line and hinge centerline. Grease Pencil - Any Source Make reference marks. (b) Remove rudder. (Refer to 55-40) Note: The chord line is defined as the line extending from the trailing edge through the hinge line. This line runs perpendicular to the rudder spar. (c) Using reference holes in rib, mark chord line on inboard rib shearweb.
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