CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 ELEVATOR AND PITCH TRIM SYSTEM 1. DESCRIPTION This section describes that portion of the flight control system which controls the position and movement of the elevator. Included are; elevator system torque tube, rigging, push/pull rods, pulleys, and pitch trim cartridge, and pitch relays. Serials 1005 thru 1300, 1302 thru 1306: Elevator control motion is transferred by the control yoke through a linkage to a pulley sector mounted on the elevator torque tube. From the pulley sector, control motion is passed to a single cable system which is routed through the forward pulley gang at the bottom of the center console, through to the rudder/elevator pulley gang under the baggage floor, and finally to the elevator actuation pulley. The elevator actuation pulley drives a push/pull rod attached to the elevator bellcrank which is bolted directly to the elevators. Each set of pulleys has a cable retainer to prevent fouling. Adjustable control stops at the elevator actuation pulley limit control surface travel. Serials 1301, 1307, & subs: Elevator control motion is transferred by the control yoke through a linkage to a bellcrank weldment on the elevator torque tube. From the bellcrank, control motion is transferred to a single cable system which is routed to the forward pulley gang at the bottom of the center console, through to the rudder/elevator pulley gang under the baggage floor, and finally to the elevator empennage bellcrank. The elevator empennage bellcrank drives a push/pull rod attached to the aft elevator bellcrank which is bolted directly to the elevators. Each set of pulleys has a cable retainer to prevent fouling. Fixed control stops at the elevator empennage bellcrank limit control surface travel. The pitch trim system employs a ground adjustable trim tab and a spring cartridge activated by an electric motor. The spring cartridge, directly connected to the elevator bellcrank and the electric trim motor, provides a centering force regardless of the direction of control surface deflection. When activated, the trim motor moves the spring cartridge causing the elevator bellcrank to move the elevator to a new trimmed position. A 4-way switch, mounted on both yoke grips, controls the pitch trim system. WARNING: EFFECTIVITY: All A system rigging Inspection/Check must be performed after loosening any flight control cable to assure proper control surface operation. Refer to the appropriate control system’s rigging procedures for the Inspection/Check maintenance practices. 27-30 Page 1 31 May 2011 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 2. MAINTENANCE PRACTICES A. Elevator System Cables - Serials 1005 thru 1300, 1302 thru 1306 (See Figure 27-301) (1) Removal - Elevator System Cables (a) Acquire necessary tools, equipment, and supplies. Description String (b) (c) (d) (e) (f) (g) (h) P/N or Spec. - Supplier Any Source Purpose Cable routing. Remove RH mid console trim panel. (Refer to 25-10) Remove LH mid console circuit breaker trim panel. (Refer to 25-10) Remove passenger seats. (Refer to 25-10) Remove carpet and access panels CF5. (Refer to 06-00) Remove empennage pulley gang. (Refer to 27-20) Remove cotter pin and washer securing pulley guard pin to rudder-elevator pulley gang bracket and remove pin. Remove cotter pins and washers securing pulley guard pins to forward pulley gang bracket and remove pins. Note: To facilitate cable routing during installation, attach string to end of cables prior to removing from airplane. (i) (2) (3) Remove nuts, washers, and screws securing elevator cables to elevator pulley sector. Attach strings to ends of forward elevator cable. (j) At elevator pulley sector, pull forward cables through and remove from airplane. Installation - Elevator System Cables (a) Install empennage pulley gang. (Refer to 27-20) (b) At access hole CF5, install turnbuckles on forward and aft elevator cables. (c) At access hole CF5, route forward elevator cable through mid and forward pulley gangs. (d) Install screws, washers, and nuts securing elevator cables to elevator pulley sector. (e) At forward pulley gang, verify cable routing, insert pulley guard pins, and install washers and cotter pins. (f) At rudder-elevator pulley gang, verify cable routing, insert pulley guard pin, and install washer and cotter pin. (g) At empennage pulley gang, verify cable routing. (h) Perform Adjustment/Test - Elevator System Rigging. (Refer to 27-30) (i) Perform Inspection/Check - Empennage Pulley Gang. (Refer to 27-20) (j) Install carpet and access panels CF5. (Refer to 06-00) (k) Install RH mid console trim panel. (Refer to 25-10) (l) Install LH mid console circuit breaker trim panel. (Refer to 25-10) (m) Install passenger seats. (Refer to 25-10) Adjustment/Test - Elevator System Rigging CAUTION: 27-30 Page 2 15 Jun 2010 Allow temperature to stabilize for a period of four hours before setting cable tensions. EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 CIRRUS (a) AIRPLANE MAINTENANCE MANUAL Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) MODEL SR20 P/N or Spec. Supplier Purpose 3/16” Lockout Pin - Any Source Elevator rigging. BL 60 Template 13057-115 Cirrus Design Duluth, MN 55811 218-727-2737 Elevator rigging. BL 12 Template 13057-111 Cirrus Design Duluth, MN 55811 218-727-2737 Elevator rigging. Tensiometer BT-33-75D Kent Moore Warren, MI 48092 800-345-2233 Cable tension determination. Inclinometer PRO360 Deflection angle Macklanburg Duncan Oklahoma City, OK 73125 determination. 800-654-0007 Hose Clamp #10 Any Source Neutral pitch determination. Remove baggage compartment carpet and access panel CF5. (Refer to 06-00) Remove access panels RE1 and RE2. (Refer to 06-00) Remove kick plate. (Refer to 25-10) Set control yoke to neutral pitch position. (See Figure 27-302) CAUTION: Use caution to avoid damaging yoke position placard, trim indicator, or yoke tube with hose clamp. 1 2 (f) (g) (h) (i) (j) (k) (l) Position hose clamp around trim indicator and yoke tube. Position control yoke so distance from center of push/pull rod end to front inside face of yoke carriage is 3.81 inches (9.68 cm). 3 Tighten clamp to secure control yoke firmly in place. 4 Adjust forward elevator push/pull rod so distance from center of aft rod end to center of forward rod end is 9.9 ±0.1 inches (25.15 ±0.25 cm). Insert lockout pin at elevator actuation pulley in empennage. Set elevators to neutral position using BL 12 and BL 60 templates. 1 Align elevator trailing edges to horizontal stabilizer chord line. To move elevator trailing edge up, lengthen push/pull rod by loosening jam nut and turning rod counterclockwise. Shorten push/pull rod for opposite results. Tighten turnbuckles to adjust elevator control cable tension according to ambient temperature. (See Figure 06-001) Remove lockout pin. Fasten inclinometer to elevator and set at 0°. Verify elevator neutral position remains at 0 ±1° with control yoke in neutral position. Remove hose clamp holding control yoke to neutral pitch position. EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 3 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL WARNING: MODEL SR20 Pulling back on pilot control yoke should deflect elevator trailing edge up. If this is not true, system is improperly rigged. The system MUST BE RIGGED CORRECTLY. Check for crossed or wrapped cables. (m) (n) (4) Verify pulling back on pilot control yoke deflects elevator trailing edge up. Verify that at full forward or full aft yoke movement the elevator cables on the pulley sector do not pull away or bend around sector. Elevator cables should stay in sector track through full forward or full aft yoke travel. (o) Streamline elevator. (p) Adjust stop screws at empennage elevator actuation pulley to allow 15 ±1° down and 25 +0/- 1.0° up elevator travel. In addition, adjust stop screws at empennage elevator actuation pulley so that for full forward or full aft yoke movement; 1 the empennage elevator actuation pulley stops contact before secondary stops, 2 secondary stops mounted on either control yoke assemblies show a 0.035 inch ±0.020 (0.89 mm ±0.51 mm) gap between stop and yoke bearing mount. (q) Verify trim cartridge minimum rod end thread engagement of 0.312 inch (0.79 cm). Tighten jam nuts. (r) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 27-30) (s) Remove inclinometer. (t) Install kick plate. (Refer to 25-10) (u) Install access panels RE1 and RE2.(Refer to 06-00) (v) Install baggage compartment carpet and access panel CF5. (Refer to 06-00) Inspection/Check - Elevator System Rigging (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) 27-30 Page 4 15 Jun 2010 P/N or Spec. Supplier Purpose Scale 6.0 inches (15.24 cm) - Any Source Elevator rigging. Inclinometer PRO360 Macklanburg Duncan Deflection angle Oklahoma City, OK 73125 determination. 800-654-0007 Tensiometer BT-33-75D Kent Moore Warren, MI 48092 800-345-2233 Cable tension determination. Remove baggage compartment carpet and access panel CF5. (Refer to 06-00) Remove access panels RE1 and RE2. (Refer to 06-00) Perform Inspection/Check - Elevator Gap and Overlap. (Refer to 55-20) Verify elevator control cable tension. (Refer to 27-30) Verify elevator neutral position remains at 0 ±1° with control yoke in neutral position Verify 15 ±1° down and 25 +0/-1.0° up elevator travel. (Refer to 27-30) For full forward or full aft yoke movement, verify empennage elevator actuation pulley primary stops contact before secondary stops. Inspect elevator pitch trim motor for security and condition. For full forward or full aft yoke movement, verify secondary stops mounted on either control yoke assemblies show a 0.035 inch ±0.020 (0.89 mm ±0.51 mm) gap between stop and yoke bearing mount. Verify minimum rod end thread engagement of 0.312 inch (0.79 cm). EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 CIRRUS (l) (m) (n) AIRPLANE MAINTENANCE MANUAL MODEL SR20 Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire elevator control system. Install access panels RE1 and RE2. (Refer to 06-00) Install baggage compartment carpet and access panel CF5. (Refer to 06-00) EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 5 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL 1 2 3 MODEL SR20 4 5 13 6 6 8 12 11 2 9 6 10 7 8 2 8 2 9 9 LEGEND 1. Screw 2. Washer 3. Cable Stop 4. Nut 5. Pulley Sector 6. Bracket 7. Forward Pulley Gang 8. Pin 9. Cotter Pin 10. Aft Pulley Gang 11. Elevator Cable 12. Turnbuckle 13. Rudder/Elevator Pulley Gang Serials 1005 thru 1300, 1302 thru 1306. Figure 27-301 Elevator System Cables - Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 6 15 Jun 2010 EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 SR20_MM27_1297A CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 4 5 2 1 3 9.90 ±0.10 inches (25.15 ±0.25 cm) 3.81 inches (9.68 cm) FIREWALL (REF) NOTE Clamp control yoke so distance from center of aft rod end to front inside face of yoke carriage is 3.81 inches (9.68 cm). Adjust forward elevator push/pull rod so distance from center of aft rod end to center of forward rod end is 9.90 ±0.10 inches (25.15 ±0.25 cm). Serials 1005 thru 1300, 1302 thru 1306. LEGEND 1. Yoke Carriage 2. Aft Rod End 3. End-Fitting Weldment 4. Forward Rod End 5. Hose Clamp SR20_MM27_1684C Figure 27-302 Setting Control Yoke Neutral Pitch Position - Serials 1005 thru 1300, 1302 thru 1306 EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 7 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 B. Elevator System Cables - Serials 1301, 1307 & subs (See Figure 27-303) The elevator system bellcrank, cable clevises, and cable turnbuckle ends are marked with red and black paint to allow visual verification of proper cable assembly and installation. (See Figure 27-304) Description Color Identification Top Elevator Empennage Bellcrank Forward Elevator Torque Tube Coupler Weldment Cable Clevises and Turnbuckle Ends Primary Red Bottom Elevator Empennage Bellcrank Aft Elevator Torque Tube Coupler Weldment Cable Clevises and Turnbuckle Ends (1) Black Removal - Elevator System Cables (a) Acquire necessary tools, equipment, and supplies. Description String (b) (c) (d) (e) (g) (h) (i) - Supplier Any Source Note location of pitch servo bridle cable clamps on elevator cable to facilitate reinstallation. To facilitate cable routing during installation, attach string to end of cables prior to removing from airplane. (j) 27-30 Page 8 15 Jun 2010 Cable routing. Serials 2016 & subs w/ Perspective Avionics: Remove bolts, nuts, and clamps securing pitch servo bridle cable to elevator cable. (See Figure 22-134) Remove cotter pins, nuts, washers, and bolts securing elevator cable rod ends to elevator empennage bellcrank. Remove cotter pin and washer securing pulley guard pin to rudder-elevator pulley gang bracket and remove pin. Remove cotter pins and washers securing pulley guard pins to forward pulley gang bracket and remove pins. Note: (2) Purpose Remove RH mid console trim panel. (Refer to 25-10) Remove LH mid console circuit breaker trim panel. (Refer to 25-10) Remove passenger seats. (Refer to 25-10) Remove carpet and access panels CF5. (Refer to 06-00) Note: (f) P/N or Spec. Remove cotter pins, nuts, washers, and bolts securing elevator cable rod ends to bellcrank weldment on torque tube coupler. Attach strings to ends of forward elevator cable (k) At bellcrank weldment pull forward cable through and remove cable from airplane. Installation - Elevator System Cables (a) If installing new cable, paint turnbuckle ends appropriate color. (Refer to 20-90) (b) At access hole CF5, install turnbuckles on forward and aft elevator cables. (c) At access hole CF5, route forward elevator cable through mid and forward pulley gangs. (d) Install bolts washers, nuts, and cotter pins securing elevator cables rod ends to bellcrank weldment on torque tube coupler. EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 (e) (3) At forward pulley gang, verify cable routing, insert pulley guard pins, and install washers and cotter pins. (f) At rudder-elevator pulley gang, verify cable routing, insert pulley guard pin, and install washer and cotter pin. (g) At elevator empennage bellcrank, verify cable routing, install bolts, washers, nuts, and cotter pins securing elevator cable rod end to elevator empennage bellcrank. (h) Perform Adjustment/Test - Elevator System Rigging. (Refer to 27-30) (i) Install carpet and access panels CF5. (Refer to 06-00) (j) Install RH mid console trim panel. (Refer to 25-10) (k) Install LH mid console circuit breaker trim panel. (Refer to 25-10) (l) Install passenger seats. (Refer to 25-10) Adjustment/Test - Elevator System Rigging (See Figure 27-306) CAUTION: (a) Allow temperature to stabilize for a period of four hours before setting cable tensions. Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) P/N or Spec. Supplier Purpose Rigging Lockout Tool 14905-001 Cirrus Design Duluth, MN 55811 218-727-2737 Lockout empennage bellcranks. 3/16” Lockout Pin - Any Source Lockout empennage bellcranks. BL 60 Template 13057-115 Cirrus Design Duluth, MN 55811 218-727-2737 Elevator rigging. BL 12 Template 13057-111 Cirrus Design Duluth, MN 55811 218-727-2737 Elevator rigging. Tensiometer BT-33-75D Kent Moore Warren, MI 48092 800-345-2233 Cable tension determination. Inclinometer PRO360 Macklanburg Duncan Deflection angle Oklahoma City, OK 73125 determination. 800-654-0007 Hose Clamp #10 Any Source Neutral pitch determination. Remove baggage compartment carpet and access panel CF5. (Refer to 06-00) Remove access panels RE1 and RE2. (Refer to 06-00) Remove kick plate. (Refer to 25-10) Note: EFFECTIVITY: Serials 1301, 1307 & subs Serials 2016 & subs w/ Perspective Avionics: Note location of pitch servo bridle cable clamps on elevator cable to facilitate reinstallation. 27-30 Page 9 15 Jun 2010 CIRRUS (e) (f) AIRPLANE MAINTENANCE MANUAL MODEL SR20 Serials 2016 & subs w/ Perspective Avionics: Remove bolts, nuts, and clamps securing pitch servo bridle cable to elevator cable. (See Figure 22-134) Set elevator deflection. 1 With full down elevator applied, verify elevator deflection angle is equal to 15 ±1°. Note: Adjusting push/pull rod length affects both up and down deflection. It may be necessary to set each end off of nominal to meet tolerance on both ends. 2 (g) To increase deflection angle, lengthen push/pull rod by removing bolt securing rod end to aft elevator bellcrank, loosening jam nut, and turning rod end counterclockwise. (See Figure 27-208) 3 Shorten push/pull rod for opposite results. 4 With full up elevator applied, verify elevator deflection angle is equal to 25 +0/-1.0°. 5 If necessary, repeat push/pull rod length adjustment until elevator deflections are both within tolerance. Set control yoke and torque tube to neutral pitch position. (See Figure 27-305) CAUTION: Use caution to avoid damaging yoke position placard, trim indicator, or yoke tube with hose clamp. 1 2 (h) (i) (j) (k) (l) (m) Position hose clamp around trim indicator and yoke tube. Position control yoke so distance from forward edge of yoke tube cover to aft edge of trim indicator is 2.71 ±0.5 inches (6.88 ±1.27 cm). 3 Tighten clamp to secure control yoke firmly in place. 4 Adjust forward elevator push/pull rod so distance from center of aft rod end to center of forward rod end is 9.55 inches (24.26 cm). 5 Verify angle from center of torque tube end fitting weldment to vertical plane equals 19 ±2.5°. Using rigging lockout tool and pin, lockout elevator empennage bellcrank. Set elevators to neutral position using BL 12 and BL 60 templates. 1 Align elevator trailing edges to horizontal stabilizer chord line. To move elevator trailing edge up, lengthen push/pull rod by loosening jam nut and turning rod counterclockwise. Shorten push/pull rod for opposite results. Tighten turnbuckles to adjust elevator control cable tension according to ambient temperature. (See Figure 06-001) Remove lockout pin. Fasten inclinometer to elevator and set at 0°. Remove hose clamp holding control yoke to neutral pitch position. WARNING: (n) (o) (p) 27-30 Page 10 15 Jun 2010 Pulling back on pilot control yoke should deflect elevator trailing edge up. If this is not true, system is improperly rigged. The system MUST BE RIGGED CORRECTLY. Check for crossed or wrapped cables and verify color identification is correct. Verify pulling back on pilot control yoke deflects elevator trailing edge up. Streamline elevator. Adjust forward stops on each control yoke so that for full forward or full aft yoke movement; 1 the empennage elevator bellcrank stops contact before the control yoke secondary stops, EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 2 (4) control yoke secondary stops show a 0.035 inch ±0.020 (0.89 mm ±0.51 mm) gap between stop and yoke bearing mount when the empennage elevator bellcrank stops are engaged. (q) Verify trim cartridge minimum rod end thread engagement of 0.313 inch (0.79 cm). Tighten jam nuts. (r) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 27-30) (s) Serials 2016 & subs w/ Perspective Avionics: Perform Adjustment/Test - GSM 85A/86 Pitch Servo Mount Bridle Cable Tension. (Refer to 22-13) (t) Remove inclinometer. (u) Install kick plate. (Refer to 25-10) (v) Install access panels RE1 and RE2. (Refer to 06-00) (w) Install baggage compartment carpet and access panel CF5. (Refer to 06-00) Inspection/Check - Elevator System Rigging (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) (l) (m) (n) (o) (p) P/N or Spec. Supplier Purpose Scale 6.0 inches (15.24 cm) Any Source Elevator rigging. Inclinometer PRO360 Macklanburg Duncan Oklahoma City, OK 73125 800-654-0007 Deflection angle determination. Tensiometer BT-33-75D Kent Moore Warren, MI 48092 800-345-2233 Cable tension determination. Remove baggage compartment carpet and access panel CF5. (Refer to 06-00) Remove access panels RE1 and RE2. (Refer to 06-00) Perform Inspection/Check - Elevator Gap and Overlap. (Refer to 55-20) Verify elevator control cable tension. (Refer to 27-30) Verify elevator neutral position remains at 0 ±1° with control yoke in neutral position. Verify 15 ±1° down and 25 +0/-1.0° up elevator travel. (Refer to 27-30) For full forward or full aft yoke movement, verify empennage elevator bellcrank stops contact before the control yoke secondary stops. Inspect elevator pitch trim motor for security and condition. For full forward or full aft yoke movement, verify control yoke secondary stops show a 0.035 inch ±0.020 (0.89 mm ±0.51 mm) gap between stop and yoke bearing mount when the empennage elevator bellcrank stops are engaged. At pitch trim cartridge, verify set screw securing pitch trim actuation arm is tight and no play exists between actuation arm and pitch trim motor shaft. Verify minimum rod end thread engagement of 0.313 inch (0.79 cm). Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire elevator control system. Serials 2016 & subs w/ Perspective Avionics: Verify bridle cable tension forward of bridle cable clamps is set to 25.0 +2.0/-0.0 lb (11.3 +0.9/-0.0 kg) (Refer to 22-13) Install access panels RE1 and RE2. (Refer to 06-00) Install baggage compartment carpet and access panel CF5. (Refer to 06-00) EFFECTIVITY: Serials 1301, 1307 & subs 27-30 Page 11 31 May 2011 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 1 1 2 6 2 3 5 6 3 4 12 4 13 6 5 7 11 BH306 (REF) 7 10 9 2 8 LEGEND 1. Bolt 2. Washer 3. Nut 4. Cotter Pin 5. Torque Tube Coupler Weldment 6. Elevator Cable 7. Bracket 8. Forward Pulley Gang 9. Pin 10. Rudder/Elevator Pulley Gang 11. Turnbuckle 12. Elevator Empennage Bellcrank 13. Bushing 4 9 2 4 SR20_MM27_1661 Figure 27-303 Elevator System Cables - Serials 1301, 1307 & subs 27-30 Page 12 15 Jun 2010 EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 RED 5 4 BLACK RED 3 BLACK 2 BLACK 1 RED LEGEND 1. Forward Torque Tube Coupler Weldment 2. Aft Torque Tube Coupler Weldment 3. Turnbuckle 4. Elevator Cable 5. Elevator Empennage Bellcrank SR20_MM27_1662 Figure 27-304 Color Identification - Serials 1301, 1307 & subs EFFECTIVITY: Serials 1301, 1307 & subs 27-30 Page 13 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 9 T.O . DN TRIM 0.5 ±0.1 inch (12.7 ±2.5 mm) 19° ±2.5° 8 7 10 4 6 1 2 3 2.71 ±0.50 inches (6.88 ±1.27 cm) 9.55 inches (24.26 cm) NOTE Clamp control yoke so distance from forward edge of yoke tube cover to aft edge of trim indicator is 2.71 ±0.5 inches (6.88 ±1.27 cm). LEGEND 1. Yoke Carriage 2. Aft Rod End 3. End-Fitting Weldment 4. Forward Rod End 5. Firewall 6. Yoke Tube Cover 7. Trim Indicator 8. Bracket 9. Decal 10. Hose Clamp Adjust forward elevator push/pull rod so distance from center of aft rod end to center of forward rod end is 9.55 inches (24.26 cm). Angle from vertical bracket to center of forward rod end is 19° ±2.5°. Distance from aft edge of trim indicator to middle of T.O. range on decal is 0.5 ±0.1 inches (12.7 ±2.5 mm). SR20_MM27_1663B Figure 27-305 Setting Control Yoke Neutral Pitch Position - Serials 1301, 1307 & subs 27-30 Page 14 15 Jun 2010 EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 NOTE Verify stop mounted on control yoke assembly shows a 0.035 ±0.020 inch (0.889 ±0.508 mm) gap between stop and yoke bearing mount when elevator is at full up or down deflection. With bellcrank lock-out tool in place, verify distance between center of lock-out hole and forward surface of 306 bulkhead is 0.03 inch ±0.06 inch (0.76 ±1.52 mm). 1 0.03 ±0.06 inch (0.76 ±1.52 mm) 0.035 ±0.020 inch (0.889 ±0.508 mm) 2 3 SHOWN FULL DOWN POSITION LOCK-OUT HOLE (REF) 4 LEGEND 1. Yoke Carriage 2. Control Yoke Stop 3. Elevator Bellcrank 4. Bellcrank Lock-out Tool BULKHEAD 306 (REF) SR20_MM27_1664A Figure 27-306 Elevator Rigging EFFECTIVITY: All 27-30 Page 15 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 C. Forward Elevator Push/Pull Rod (See Figure 27-307) (See Figure 27-308) (1) (2) 27-30 Page 16 15 Jun 2010 Removal - Forward Elevator Push/Pull Rod (a) Remove seat. (Refer to 25-10) (b) Remove kick plate. (Refer to 25-10) (c) Remove mid-console trim panel. (Refer to 25-10) (d) Remove cotter pin, nut, washers, and bolt securing elevator push/pull rod end to controlyoke elevator stop. (e) Remove cotter pin, nut, washers, and bolt securing elevator push/pull rod end to torque tube end-fitting weldment and remove elevator push/pull rod from airplane. Installation - Forward Elevator Push/Pull Rod (a) Position elevator push/pull rod to control-yoke stop and install bolt, washers, nut, and cotter pin. (b) Position elevator push/pull rod to torque tube end-fitting weldment and install bolt, washers, nut, and cotter pin. (c) Install mid-console trim panel. (Refer to 25-10) (d) Install kick plate. (Refer to 25-10) (e) Install seat. (Refer to 25-10) EFFECTIVITY: All CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 D. Elevator Torque Tube (See Figure 27-307) (See Figure 27-308) (1) (2) Removal - Elevator Torque Tube (a) Remove MFD. (Refer to 31-60) (b) Remove pilot and co-pilot seats. (Refer to 25-10) (c) Remove kick plate. (Refer to 25-10) (d) Remove mid-console trim panels from LH and RH sides. (Refer to 25-10) (e) Gain access to torque tube coupler through MFD opening and remove nut, washers, and bolt securing torque tube coupler to elevator torque tube. (f) Remove nut, washers, and bolt securing elevator torque tube to end-fitting weldment. Disconnect end-fitting weldment from elevator torque tube. (g) Slide torque tube outboard to disconnect from coupler then slide tube inboard to remove from console bearing plate. Installation - Elevator Torque Tube (a) From inboard side of console, insert elevator torque tube into console bearing plate, then position and slide torque tube into torque tube coupler and install bolt, washer, and nut. (b) Install bolt, washers, and nut securing end-fitting weldment to elevator torque tube. (c) Install forward center console trim panels. (Refer to 25-10) (d) Install kick plate. (Refer to 25-10) (e) Install pilot and co-pilot seats. (Refer to 25-10) (f) Install MFD. (Refer to 31-60) EFFECTIVITY: All 27-30 Page 17 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 E. Elevator Pulley Sector - Serials 1005 thru 1300, 1302 thru 1306 (See Figure 27-307) WARNING: (1) (2) F. A system rigging Inspection/Check must be performed after loosening any flight control cable to assure proper control surface operation. Refer to the appropriate control system’s rigging procedures for the Inspection/Check maintenance practices. Removal - Elevator Pulley Sector - Serials 1005 thru 1300, 1302 thru 1306 (a) Remove co-pilot seat. (Refer to 25-10) (b) Remove right mid console trim. (Refer to 25-10) (c) Remove carpet and access panel CF5 from baggage compartment floor. (Refer to 06-00) (d) Identify and loosen elevator cable tension via turnbuckle. (e) Remove nuts, washers, and screws securing cable to elevator pulley sector. (f) Remove nuts, washers, and bolts securing elevator pulley sector to torque tube coupler flange and remove from airplane. Installation - Elevator Pulley Sector - Serials 1005 thru 1300, 1302 thru 1306 (a) Position pulley sector on torque tube coupler flange and install bolts, washers, and nuts. (b) Position cable on elevator pulley sector and install screws, washers, and nuts. (c) Rig and perform Adjustment/Test - Elevator System Rigging. (Refer to 27-30). (d) Install access panel and carpet. (Refer to 06-00) (e) Install co-pilot seat. (Refer to 25-10) Bellcrank Weldment - Serials 1301, 1307 & subs (See Figure 27-308) On these airplanes, the elevator pulley sector is replaced with a bellcrank weldment located on the elevator torque tube coupler. Maintenance practices pertinent to the elevator torque tube coupler are covered under the Elevator Torque Tube section. (Refer to 27-30) 27-30 Page 18 15 Jun 2010 EFFECTIVITY: All CIRRUS 11 AIRPLANE MAINTENANCE MANUAL MODEL SR20 12 9 4 4 5 2 1 5 13 CONSOLE ASSY (REF) 5 4 4 7 14 8 2 4 3 LEGEND 1. Elevator Torque Tube - RH 2. Nut 3. Bearing Plate Assembly 4. Washer 5. Bolt 6. Coupler 7. Pulley Sector 8. Shim 9. Elevator Push/Pull Rod - Fwd 10. Elevator Torque Tube - LH 11. Castellated Nut 12. Cotter Pin 13. Thrust Collar 14. Spacer 2 4 4 4 2 4 5 10 14 6 8 7 5 Serials 1005 thru 1300, 1302 thru 1306. 4 4 5 13 SR20_MM27_1173D Figure 27-307 Elevator System - Serials 1005 thru 1300, 1302 thru 1306 EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 19 15 Jun 2010 CIRRUS 11 AIRPLANE MAINTENANCE MANUAL MODEL SR20 12 9 4 4 5 5 1 CONSOLE ASSY (REF) 4 4 13 2 4 2 4 3 LEGEND 1. Elevator Torque Tube - RH 2. Nut 3. Bearing Plate Assembly 4. Washer 5. Bolt 6. Coupler 7. Pulley Sector 8. Shim 9. Elevator Push/Pull Rod - Fwd 10. Elevator Torque Tube - LH 11. Castellated Nut 12. Cotter Pin 13. Spacer 4 5 Page 20 15 Jun 2010 4 13 2 10 4 SR20_MM27_1665 Figure 27-308 Elevator System - Serials 1301, 1307 & subs 27-30 5 6 EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 G. Forward Pulley Gang (See Figure 27-106) (See Figure 27-107) The forward pulley gang is used to route the aileron, rudder, and elevator system control cables. Maintenance practices pertinent to the forward pulley gang are covered under the Aileron and Roll Trim System. (Refer to 27-10) H. Rudder-Elevator Pulley Gang (See Figure 27-206) The rudder-elevator pulley gang is used to route the rudder and elevator system control cables. Maintenance practices pertinent to the rudder-elevator pulley gang are covered under the Rudder and Yaw Trim System. (Refer to 27-20) I. Empennage Pulley Gang - Serials 1005 thru 1300, 1302 thru 1306 (See Figure 27-207) The rudder and elevator control system utilize separate pulleys which mount to a shared pulley-gang bracket mounted inside the empennage. Maintenance practices pertinent to the empennage pulley gang are covered under the Rudder and Yaw Trim System (Refer to 27-20) J. Empennage Elevator Bellcrank - Serials 1301, 1307 & subs (See Figure 27-208) The rudder and elevator control system utilize separate bellcranks which mount directly to the FS 306 bulkhead. Maintenance practices pertinent to the empennage bellcranks are covered under the Rudder and Yaw Trim System. (Refer to 27-20) EFFECTIVITY: All 27-30 Page 21 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 K. Pitch Trim System - Serials 1005 thru 1300, 1302 thru 1306 (See Figure 27-309) (1) Servicing - Pitch Trim Cartridge Lubrication (a) Acquire necessary tools, equipment, and supplies. Description LPS Chain Mate P/N or Spec. 02416 Supplier LPS Laboratories Tucker, GA 30085-5052 800-241-8334 Purpose Lubrication of the pitch trim cartridge. (b) (c) (2) Remove empennage access panels LE1 and RE1. (Refer to 06-00) At access hole RE1, cover area below and around pitch trim cartridge with cloth to catch lubricant overspray. (d) Attach extension tube to lubricant spray nozzle. (e) At access hole LE1, apply lubricant to pitch trim cartridge inner housing for 3 seconds while working elevator up and down several times to spread lubrication. (f) Inspect elevator pitch trim motor for security and condition. (g) Remove cloth from access hole RE1. (h) Install empennage access panels LE1 and RE1. (Refer to 06-00) Removal - Pitch Trim Cartridge WARNING: A maintenance check flight must be performed after the installation of a replacement (new or different) trim cartridge. (a) (b) (3) (4) Remove RE1, RE2 and LE1 access panels. (Refer to 06-00) Remove cotter pin, nut, washers, and bolt securing trim cartridge push/pull rod to trim motor actuation arm. (c) Remove cotter pin, nut, washers, spacer, and bolt securing trim cartridge to elevator bellcrank and remove trim cartridge from airplane. Installation - Pitch Trim Cartridge (a) Insert spacer and align trim cartridge with mounting hole on elevator bellcrank and install bolt, washers, nut, and cotter pin. (b) Install bolt, washers, nut, and cotter pin securing trim cartridge push/pull rod to trim motor actuation arm. (c) Perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 27-30) (d) Install RE1, RE2, and LE1 access panels. (Refer to 06-00) (e) If replacement (new or different) trim cartridge installed, perform maintenance check flight. If airplane can not be trimmed properly during maintenance check flight, perform Adjustment/Test - Elevator Trim Tab. (Refer to 55-20) Adjustment/Test - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description 27-30 Page 22 15 Jun 2010 P/N or Spec. Supplier Purpose BL 60 Template 13057-115 Cirrus Design Duluth, MN 55811 218-727-2737 Elevator rigging. BL 12 Template 13057-111 Cirrus Design Elevator rigging. EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 CIRRUS AIRPLANE MAINTENANCE MANUAL Description Inclinometer P/N or Spec. PRO360 MODEL SR20 Supplier Macklanburg Duncan Oklahoma City, OK 73125 800-654-0007 Purpose Deflection angle determination. (b) (c) (5) Remove access panels RE1 and RE2. (Refer to 06-00) Set elevators to neutral position using BL 12 and BL 60 templates. 1 Align elevator trailing edges to horizontal stabilizer chord line. To move elevator trailing edge up, lengthen push/pull rod by loosening jam nut and turning rod counterclockwise. Shorten push/pull rod for opposite results. (d) Fasten inclinometer to elevator and set at 0°. (e) Run trim motor to full nose-down trim position until travel is stopped by lower limit switch. (f) Adjust pitch trim cartridge push/pull rod so elevator deflection angle is -10.5 ±1.0°: 1 To increase elevator trailing edge down movement, shorten pitch trim cartridge by loosening jam nut and turning push/pull rod clockwise. 2 Lengthen pitch trim cartridge for opposite results. (g) Run trim motor to full nose-up trim position until travel is stopped by upper limit switch. (h) Adjust pitch trim cartridge push/pull rod so minimum elevator deflection angle is +17°: 1 To increase elevator trailing edge up movement, lengthen pitch trim cartridge by loosening jam nut and turning push/pull rod counterclockwise. 2 Shorten pitch trim cartridge for opposite results. (i) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 27-30) (j) Verify pitch trim cartridge minimum rod end thread engagement of 0.312 inch (0.79 cm). Tighten jam nuts. (k) Install access panels RE1 and RE2. (Refer to 06-00) Inspection/Check - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description Inclinometer P/N or Spec. PRO360 Supplier Macklanburg Duncan Oklahoma City, OK 73125 800-654-0007 Purpose Deflection angle determination. (b) (c) (d) (e) (6) Verify correct elevator system rigging. (Refer to 27-30) (Refer to 27-30) Fasten inclinometer to elevator and set at 0°. Run trim motor to full nose-down trim position until travel is stopped by lower limit switch. Verify elevator deflection angle is -10.5 ±1.0°. If pitch trim is out of adjustment, perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 27-30) (f) Run trim motor to full nose-up trim position until travel is stopped by upper limit switch. (g) Verify minimum elevator deflection angle is +17°. If pitch trim is out of adjustment, perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 27-30) (h) Remove inclinometer. (i) Verify positive clearance between trim cartridge and actuation pulley under full range of trim motor positions. (j) Verify minimum rod end thread engagement of 0.312 inch (0.79 cm). (k) Verify proper installation of safety wires and cotter pins on all fasteners. Removal - Pitch Trim Motor EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 23 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 (a) (b) (c) (d) (e) (f) (g) (7) 27-30 Page 24 15 Jun 2010 Set BATTERY and AVIONICS switches to OFF positions. Pull PITCH TRIM circuit breaker. Remove access panel RE2. (Refer to 06-00) Remove composite rudder bottom. (Refer to 55-40) Remove nut, washer, and screw securing pulley gang support brace to empennage. Disconnect trim motor electrical connection. Remove cotter pin, nut, washers, and bolt securing trim cartridge push/pull rod to trim motor actuation arm. (h) Remove bolts and washers securing pitch trim motor assembly to FS 306 Bulkhead and remove from airplane. Installation - Pitch Trim Motor (a) Position pitch trim motor assembly to FS 306 Bulkhead and install bolts and washers. (b) Install bolt, washers, nut, and cotter pin securing trim cartridge push/pull rod to trim motor actuation arm. (c) Connect trim motor electrical connection. (d) Install screw, washer, and nut securing pulley gang support brace to empennage. (e) Install composite rudder bottom. (Refer to 55-40) (f) Install access panel RE2. (Refer to 06-00) (g) Reset PITCH TRIM circuit breaker. EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 16 14 12 15 18 12 LEGEND 1. Jam Nut 2. Bolt 3. Washer 4. Rod End 5. Bushing 6. Spacer 7. Pitch Trim Cartridge 8. Cotter Pin 9. Castellated Nut 10. Screw 11. Limit Switch 12. Nut 13. Backing Plate 14. Pitch Trim Motor 15. Wire Harness 16. Connector 17. Set Screw 18. Motor Bracket 19. Actuation Arm 20. Elevator Bellcrank 3 13 3 11 10 12 8 10 9 3 6 BH 306 (REF) 2 3 3 3 17 19 3 10 8 9 20 3 7 3 5 6 4 5 3 3 2 2 1 2 3 BH 306 STIFFENER (REF) Serials 1005 thru 1300, 1302 thru 1306. SR20_MM27_1681B Figure 27-309 Pitch Trim System - Serials 1005 thru 1300, 1302 thru 1306 EFFECTIVITY: Serials 1005 thru 1300, 1302 thru 1306 27-30 Page 25 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 L. Pitch Trim System - Serials 1301, 1307 & subs (See Figure 27-3010) (1) Servicing - Pitch Trim Cartridge Lubrication - Serials 1301, 1307 thru 1383 (a) Acquire necessary tools, equipment, and supplies. Description LPS Chain Mate P/N or Spec. 02416 Supplier LPS Laboratories Tucker, GA 30085-5052 800-241-8334 Purpose Lubrication of the pitch trim cartridge. (b) (c) (2) Remove empennage access panel RE1 and RE2. (Refer to 06-00) At access hole RE1, cover area below and around pitch trim cartridge with cloth to catch lubricant overspray. (d) Attach extension tube to lubricant spray nozzle. (e) Fully extend elevator down to compress pitch trim cartridge. (f) At access hole RE2, apply lubricant to forward end of pitch trim cartridge inner housing for 3 seconds while working elevator up and down several times to spread lubrication. (g) Remove cloth from access hole RE1. (h) Install empennage access panel RE1 and RE2. (Refer to 06-00) Removal - Pitch Trim Cartridge WARNING: A maintenance check flight must be performed after the installation of a replacement (new or different) trim cartridge. (a) (b) (c) (3) (4) Remove RE1, RE2 and LE1 access panels. (Refer to 06-00) Remove cotter pin, nut, washers, and bolt securing trim cartridge to aft elevator bellcrank. Loosen jam nut, unthread trim cartridge push/pull rod from rod end on trim motor assembly, and remove trim cartridge from airplane. Installation - Pitch Trim Cartridge (a) Thread trim cartridge push/pull rod into rod end on trim motor assembly and tighten jam nut. (b) Align trim cartridge to mounting hole on aft elevator bellcrank and install bolt, washers, nut, and cotter pin. (c) Perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 27-30) (d) Install RE1, RE2, and LE1 access panels. (Refer to 06-00) (e) If replacement (new or different) trim cartridge installed, perform maintenance check flight. If airplane can not be trimmed properly during maintenance check flight, perform Adjustment/Test - Elevator Trim Tab. (Refer to 55-20) Adjustment/Test - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description 27-30 Page 26 15 Jun 2010 P/N or Spec. Supplier Purpose Rigging Lockout Tool 14905-001 Cirrus Design Duluth, MN 55811 218-727-2737 Lockout empennage bellcranks. 3/16” Lockout Pin - Any Source Lockout empennage bellcranks. EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL Description Inclinometer P/N or Spec. PRO360 MODEL SR20 Supplier Purpose Deflection angle Macklanburg Duncan Oklahoma City, OK 73125 determination. 800-654-0007 (b) (c) (5) Remove access panels RE1 and RE2. (Refer to 06-00) Set elevators to neutral position: 1 Using rigging lockout tool and pin, lockout elevator empennage bellcrank. 2 Align elevator trailing edges to horizontal stabilizer chord line. To move elevator trailing edge up, lengthen push/pull rod by loosening jam nut and turning rod counterclockwise. Shorten push/pull rod for opposite results. 3 Remove lockout pin. (d) Fasten inclinometer to elevator and set at 0°. (e) Run trim motor to full nose-down trim position until travel is stopped by lower limit switch. (f) Adjust cartridge push/pull rod so elevator deflection angle is -10.5 ±1.0°: 1 To increase elevator trailing edge down movement, shorten cartridge by loosening jam nut and turning push/pull rod clockwise. 2 Lengthen cartridge for opposite results. (g) Run trim motor to full nose-up trim position until travel is stopped by upper limit switch. (h) Adjust cartridge push/pull rod so minimum elevator deflection angle is +17°: 1 To increase elevator trailing edge up movement, lengthen cartridge by loosening jam nut and turning push/pull rod counterclockwise. 2 Shorten cartridge for opposite results. (i) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 27-30) (j) At pitch trim cartridge, verify set screw securing pitch trim actuation arm is tight and no play exists between actuation arm and pitch trim motor shaft. (k) Verify trim cartridge minimum rod end thread engagement of 0.313 inch (0.79 cm). Tighten jam nuts. (l) Install access panels RE1 and RE2. (Refer to 06-00) Inspection/Check - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description Inclinometer (b) (c) (d) (e) (f) (g) (h) P/N or Spec. PRO360 Supplier Purpose Macklanburg Duncan Deflection angle Oklahoma City, OK 73125 determination. 800-654-0007 Verify correct elevator system rigging. (Refer to 27-30) (Refer to 27-30) Fasten inclinometer to elevator and set at 0°. Run trim motor to full nose-down trim position until travel is stopped by lower limit switch. Verify elevator deflection angle is -10.5 ±1.0°. If pitch trim is out of adjustment, perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 27-30) Run trim motor to full nose-up trim position until travel is stopped by upper limit switch. Verify minimum elevator deflection angle is +17°. If pitch trim is out of adjustment, perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 27-30) Remove inclinometer. EFFECTIVITY: Serials 1301, 1307 & subs 27-30 Page 27 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 (i) (6) (7) (8) Verify positive clearance between trim cartridge and forward and aft empennage bellcranks under full range of trim motor positions. (j) Verify minimum rod end thread engagement of 0.313 inch (0.79 cm). (k) Verify proper installation of safety wires and cotter pins on all fasteners. Removal - Pitch Trim Motor Assembly (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull PITCH TRIM circuit breaker. (c) Remove pitch trim cartridge. (Refer to 27-30) (d) Disconnect pitch trim motor electrical connector. (e) Remove bolts and washers securing pitch trim motor assembly to FS 306 Bulkhead and remove pitch trim motor assembly from airplane. Disassembly - Pitch Trim Motor Assembly (a) Remove set screw securing actuation arm to shaft of pitch trim motor. (b) Remove cotter pin, nut, washers, and bolt securing rod end to actuation arm. (c) Remove screws and washers securing limit switches to mounting bracket. (d) Remove screws and nuts securing pitch trim motor to mounting bracket. Assembly - Pitch Trim Motor Assembly (See Figure 27-3011) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. 5 VDC Power Supply - (b) (c) (d) (e) Supplier Any Source 1 2 3 To ease installation of pitch trim motor assembly, install actuation arm so arm contacts upper stop on mounting bracket. Connect pitch trim motor to 5 VDC power supply. Rotate pitch trim motor shaft until flat of shaft is parallel with flat on upper stop of mounting bracket. Disconnect pitch trim motor from 5 VDC power supply. Note: Actuation arm must be oriented on shaft of motor so set screw aligns with flat on shaft of motor. Incorrect alignment may result in a loose actuation arm and possible degradation of pitch trim. 4 5 27-30 Page 28 15 Jun 2010 Rotate shaft of motor to correct installation position. Position pitch trim motor to mounting bracket so wires face towards front of airplane, secure with screws and nuts. Position limit switches to mounting bracket and secure with screws and washers. Install cotter pin, nut, washers, and bolt securing rod end to actuation arm. Install actuation arm. Note: (9) Purpose Position actuation arm to shaft of pitch trim motor and secure with set screw. Verify set screw is tight and no play exists between actuation arm and pitch trim motor shaft. Installation - Pitch Trim Motor Assembly (a) Position pitch trim motor assembly to FS 306 Bulkhead and secure with bolts and washers. Bolts must engage threaded insert to within a minimum of 0.063 inch (1.6 mm) of flush with bulkhead surface or protrude past bulkhead surface. EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS (b) (c) (d) AIRPLANE MAINTENANCE MANUAL MODEL SR20 Connect trim motor electrical connector. Install pitch trim cartridge. (Refer to 27-30) Reset PITCH TRIM circuit breaker. M. Elevator Trim Tab Pitch trim adjustment is ground adjustable only and is achieved by changing the deflection angle of the elevator trim tab. For maintenance practices pertinent to the elevator trim tab, see Elevator. (Refer to 55-20) EFFECTIVITY: All 27-30 Page 29 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 3 1 4 2 BULKHEAD F.S. 306 (REF) 5 6 8 9 7 7 5 6 15 10 14 6 7 7 11 16 19 18 12 7 7 18 LEGEND 1. Pitch Trim Motor 2. Wire Harness 3. Connector 4. Nut 5. Screw 6. Bolt 7. Washer 8. Motor Bracket 9. Limit Switch 10. Actuation Arm 17 6 13 15 11. Set Screw 12. Rod End 13. Jam Nut 14. Castellated Nut 15. Cotter Pin 16. Pitch Trim Cartridge 17. Spacer 18. Bushing 19. Elevator Bellcrank SR20_MM27_1666A Figure 27-3010 Pitch Trim System - Serials 1301, 1307 & subs 27-30 Page 30 15 Jun 2010 14 EFFECTIVITY: Serials 1301, 1307 & subs CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 6 2 1 3 6 4 5 1 2 NOTE Ensure limit switches are installed in correct orientation. Rotate shaft of pitch trim motor until flat on shaft is parallel with flat on upper stop of mounting bracket. LEGEND 1. Pitch Trim Motor 2. Motor Bracket 3. Limit Switch 4. Actuation Arm 5. Set Screw 6. Upper Stop Actuation arm must be oriented on shaft of motor so screw aligns with flat on shaft of motor. SR20_MM27_1810A Figure 27-3011 Actuation Arm Installation and Adjustment - Serials 1301, 1307 & subs EFFECTIVITY: Serials 1301, 1307 & subs 27-30 Page 31 15 Jun 2010 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 N. Pitch Relays (See Figure 27-3012) CAUTION: (1) (2) 27-30 Page 32 31 May 2011 Failure of either pitch relay is cause for replacement of both relays. Replace both relays upon failure of one. Removal - Pitch Relay (a) Pull PITCH TRIM circuit breaker. (b) Serials 1005 thru 1422: Remove rear passenger seats. (Refer to 25-10) (c) Serials 1005 thru 1422: Remove access panel CF4C. (Refer to 06-00) (d) Serials 1423 & subs w/o Perspective Avionics: Remove access panel CF3R. (Refer to 0600) (e) Remove relay from socket. Installation - Pitch Relay (a) Position relay to socket and push firmly to install. (b) Serials 1005 thru 1422: Install access panel CF4C. (Refer to 06-00) (c) Serials 1423 & subs w/o Perspective Avionics: Install access panel CF3R. (Refer to 06-00) (d) Serials 1005 thru 1422: Install rear passenger seats. (Refer to 25-10) (e) Reset PITCH TRIM circuit breaker. EFFECTIVITY: All CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 FLAP CIRCUIT CARD (REF) RH LONGERON (REF) 6 ROLL AUTOPILOT RELAY (REF) 3 5 5 3 8 ROLL RELAY (REF) 3 9 FLAP RELAY (REF) 4 3 4 3 3 2 5 9 7 1 2 Serials 1005 thru 1422. CAUTION Failure of either relay is cause for replacing both relays. LEGEND 1. Pitch Autopilot Relay 2. Screw 3. Washer 4. Spacer 5. Nut 6. Bolt 7. Pitch Relay- Up 8. Pitch Relay- Down 9. Relay Socket 10. Mounting Plate SR20_MM27_3466 Figure 27-3012 Pitch Relay Assembly - Serials 1005 thru 1422 (Sheet 1 of 3) EFFECTIVITY: Serials 1005 thru 1422 27-30 Page 33 31 May 2011 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 RH LONGERON (REF) 6 3 5 ROLL RELAY (REF) 3 8 4 3 4 12 3 FLAP RELAY (REF) 5 7 2 9 RH LONGERON (REF) ROLL AUTOPILOT RELAY (REF) 6 3 5 LEGEND 1. Pitch Autopilot Relay 2. Screw 3. Washer 4. Spacer 5. Nut 6. Bolt 7. Pitch Relay-Up 8. Pitch Relay-Down 9. Relay Socket 11. Mounting Plate, Aft 12. Mounting Plate, Forward 3 4 Serials 1423 & subs w/o Perspective. CAUTION 3 9 3 4 11 3 5 Failure of either relay is cause for replacing both relays. FLAP CIRCUIT CARD (REF) 9 1 2 SR20_MM27_3462 Figure 27-3012 Pitch Relay Assembly - Serials 1423 & subs w/o Perspective Avionics (Sheet 2 of 3) 27-30 Page 34 31 May 2011 EFFECTIVITY: Serials 1423 & subs w/o Perspective Avionics CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20 RH LONGERON (REF) 6 3 5 ROLL RELAY (REF) 3 4 8 12 GROUND BUS (REF) 3 9 3 FLAP RELAY (REF) 5 7 2 9 RH LONGERON (REF) ROLL AUTOPILOT RELAY (REF) GROUND BUS (REF) 6 3 4 5 3 3 5 11 Serials 2016 & subs w/ System 55X/55SR and Perspective. CAUTION Failure of either relay is cause for replacing both relays. 9 1 2 LEGEND 1. Pitch Autopilot Relay 2. Screw 3. Washer 4. Spacer 5. Nut 6. Bolt 7. Pitch Relay-Up 8. Pitch Relay-Down 9. Relay Socket 11. Mounting Plate, Aft 12. Mounting Plate, Forward SR20_MM27_3470 Figure 27-3012 Pitch Relay Assembly - Serials 2016 & subs w/ System 55X/55SR and Perspective (Sheet 3 of 3) EFFECTIVITY: Serials 2016 & subs w/ System 55X/55SR and Perspective 27-30 Page 35 31 May 2011 CIRRUS AIRPLANE MAINTENANCE MANUAL Intentionally Left Blank 27-30 Page 36 31 May 2011 EFFECTIVITY: All MODEL SR20