CIRRUS AIRPLANE MAINTENANCE MANUAL

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 100 thru 100, 10 thru 10: 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 101, 107, & 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 -way switch, mounted on both yoke grips, controls the pitch trim system. WARNING: 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. All 7-0 Page 1 1 May 011

. MAINTENANCE PRACTICES A. Elevator System Cables - Serials 100 thru 100, 10 thru 10 (See Figure 7-01) (1) Removal - Elevator System Cables (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose String - Any Source Cable routing. (b) Remove RH mid console trim panel. (Refer to -10) (c) Remove LH mid console circuit breaker trim panel. (Refer to -10) (d) Remove passenger seats. (Refer to -10) (e) Remove carpet and access panels CF. (Refer to 0-00) (f) Remove empennage pulley gang. (Refer to 7-0) (g) Remove cotter pin and washer securing pulley guard pin to rudder-elevator pulley gang bracket and remove pin. (h) 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) 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 7-0) (b) At access hole CF, install turnbuckles on forward and aft elevator cables. (c) At access hole CF, 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 7-0) (i) Perform Inspection/Check - Empennage Pulley Gang. (Refer to 7-0) (j) Install carpet and access panels CF. (Refer to 0-00) (k) Install RH mid console trim panel. (Refer to -10) (l) Install LH mid console circuit breaker trim panel. (Refer to -10) (m) Install passenger seats. (Refer to -10) () Adjustment/Test - Elevator System Rigging CAUTION: Allow temperature to stabilize for a period of four hours before setting cable tensions. 7-0 Page 1 Jun 010 Serials 100 thru 100, 10 thru 10

(a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose /1 Lockout Pin - Any Source Elevator rigging. BL 0 Template 107-11 Cirrus Design Duluth, MN 811 18-77-77 BL 1 Template 107-111 Cirrus Design Duluth, MN 811 18-77-77 Tensiometer BT--7D Kent Moore Warren, MI 809 800-- Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Elevator rigging. Elevator rigging. Cable tension determination. Deflection angle determination. Hose Clamp #10 Any Source Neutral pitch determination. (b) Remove baggage compartment carpet and access panel CF. (Refer to 0-00) (c) Remove access panels RE1 and RE. (Refer to 0-00) (d) Remove kick plate. (Refer to -10) (e) Set control yoke to neutral pitch position. (See Figure 7-0) CAUTION: Use caution to avoid damaging yoke position placard, trim indicator, or yoke tube with hose clamp. 1 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.81 inches (9.8 cm). Tighten clamp to secure control yoke firmly in place. 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 (.1 ±0. cm). (f) Insert lockout pin at elevator actuation pulley in empennage. (g) Set elevators to neutral position using BL 1 and BL 0 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. (h) Tighten turnbuckles to adjust elevator control cable tension according to ambient temperature. (See Figure 0-001) (i) Remove lockout pin. (j) Fasten inclinometer to elevator and set at 0. (k) Verify elevator neutral position remains at 0 ±1 with control yoke in neutral position. (l) Remove hose clamp holding control yoke to neutral pitch position. Serials 100 thru 100, 10 thru 10 7-0 Page 1 Jun 010

WARNING: 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) (o) 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. Streamline elevator. (p) Adjust stop screws at empennage elevator actuation pulley to allow 1 ±1 down and +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, secondary stops mounted on either control yoke assemblies show a 0.0 inch ±0.00 (0.89 mm ±0.1 mm) gap between stop and yoke bearing mount. (q) Verify trim cartridge minimum rod end thread engagement of 0.1 inch (0.79 cm). Tighten jam nuts. (r) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 7-0) (s) Remove inclinometer. (t) Install kick plate. (Refer to -10) (u) Install access panels RE1 and RE.(Refer to 0-00) (v) Install baggage compartment carpet and access panel CF. (Refer to 0-00) () Inspection/Check - Elevator System Rigging (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Scale.0 inches (1. cm) - Any Source Elevator rigging. Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Deflection angle determination. Tensiometer BT--7D Kent Moore Warren, MI 809 800-- Cable tension determination. 7-0 Page 1 Jun 010 (b) Remove baggage compartment carpet and access panel CF. (Refer to 0-00) (c) Remove access panels RE1 and RE. (Refer to 0-00) (d) Perform Inspection/Check - Elevator Gap and Overlap. (Refer to -0) (e) Verify elevator control cable tension. (Refer to 7-0) (f) Verify elevator neutral position remains at 0 ±1 with control yoke in neutral position (g) Verify 1 ±1 down and +0/-1.0 up elevator travel. (Refer to 7-0) (h) For full forward or full aft yoke movement, verify empennage elevator actuation pulley primary stops contact before secondary stops. (i) Inspect elevator pitch trim motor for security and condition. (j) For full forward or full aft yoke movement, verify secondary stops mounted on either control yoke assemblies show a 0.0 inch ±0.00 (0.89 mm ±0.1 mm) gap between stop and yoke bearing mount. (k) Verify minimum rod end thread engagement of 0.1 inch (0.79 cm). Serials 100 thru 100, 10 thru 10

(l) Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire elevator control system. (m) Install access panels RE1 and RE. (Refer to 0-00) (n) Install baggage compartment carpet and access panel CF. (Refer to 0-00) Serials 100 thru 100, 10 thru 10 7-0 Page 1 Jun 010

1 1 11 1 8 9 7 10 8 9 8 9 LEGEND 1. Screw. Washer. Cable Stop. Nut. Pulley Sector. Bracket 7. Forward Pulley Gang 8. Pin 9. Cotter Pin 10. Aft Pulley Gang 11. Elevator Cable 1. Turnbuckle 1. Rudder/Elevator Pulley Gang Serials 100 thru 100, 10 thru 10. SR0_MM7_197A 7-0 Page 1 Jun 010 Figure 7-01 Elevator System Cables - Serials 100 thru 100, 10 thru 10 Serials 100 thru 100, 10 thru 10

1 9.90 ±0.10 inches (.1 ±0. cm).81 inches (9.8 cm) FIREWALL NOTE Clamp control yoke so distance from center of aft rod end to front inside face of yoke carriage is.81 inches (9.8 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 (.1 ±0. cm). LEGEND 1. Yoke Carriage. Aft Rod End. End-Fitting Weldment. Forward Rod End. Hose Clamp Serials 100 thru 100, 10 thru 10. SR0_MM7_18C Figure 7-0 Setting Control Yoke Neutral Pitch Position - Serials 100 thru 100, 10 thru 10 Serials 100 thru 100, 10 thru 10 7-0 Page 7 1 Jun 010

B. Elevator System Cables - Serials 101, 107 & subs (See Figure 7-0) 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 7-0) Description Top Elevator Empennage Bellcrank Forward Elevator Torque Tube Coupler Weldment Cable Clevises and Turnbuckle Ends Bottom Elevator Empennage Bellcrank Aft Elevator Torque Tube Coupler Weldment Cable Clevises and Turnbuckle Ends Color Identification Primary Red Black (1) Removal - Elevator System Cables (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose String - Any Source Cable routing. (b) Remove RH mid console trim panel. (Refer to -10) (c) Remove LH mid console circuit breaker trim panel. (Refer to -10) (d) Remove passenger seats. (Refer to -10) (e) Remove carpet and access panels CF. (Refer to 0-00) Note: Note location of pitch servo bridle cable clamps on elevator cable to facilitate reinstallation. (f) (g) (h) (i) Serials 01 & subs w/ Perspective Avionics: Remove bolts, nuts, and clamps securing pitch servo bridle cable to elevator cable. (See Figure -1) 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: To facilitate cable routing during installation, attach string to end of cables prior to removing from airplane. (j) 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 0-90) (b) At access hole CF, install turnbuckles on forward and aft elevator cables. (c) At access hole CF, 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. 7-0 Page 8 1 Jun 010 Serials 101, 107 & subs

(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 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 7-0) (i) Install carpet and access panels CF. (Refer to 0-00) (j) Install RH mid console trim panel. (Refer to -10) (k) Install LH mid console circuit breaker trim panel. (Refer to -10) (l) Install passenger seats. (Refer to -10) () Adjustment/Test - Elevator System Rigging (See Figure 7-0) CAUTION: Allow temperature to stabilize for a period of four hours before setting cable tensions. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Rigging Lockout Tool 190-001 Cirrus Design Duluth, MN 811 18-77-77 Lockout empennage bellcranks. /1 Lockout Pin - Any Source Lockout empennage bellcranks. BL 0 Template 107-11 Cirrus Design Duluth, MN 811 18-77-77 BL 1 Template 107-111 Cirrus Design Duluth, MN 811 18-77-77 Tensiometer BT--7D Kent Moore Warren, MI 809 800-- Elevator rigging. Elevator rigging. Cable tension determination. Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Deflection angle determination. Hose Clamp #10 Any Source Neutral pitch determination. (b) Remove baggage compartment carpet and access panel CF. (Refer to 0-00) (c) Remove access panels RE1 and RE. (Refer to 0-00) (d) Remove kick plate. (Refer to -10) Note: Serials 01 & subs w/ Perspective Avionics: Note location of pitch servo bridle cable clamps on elevator cable to facilitate reinstallation. Serials 101, 107 & subs 7-0 Page 9 1 Jun 010

(e) (f) Serials 01 & subs w/ Perspective Avionics: Remove bolts, nuts, and clamps securing pitch servo bridle cable to elevator cable. (See Figure -1) Set elevator deflection. 1 With full down elevator applied, verify elevator deflection angle is equal to 1 ±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. 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 7-08) Shorten push/pull rod for opposite results. With full up elevator applied, verify elevator deflection angle is equal to +0/-1.0. If necessary, repeat push/pull rod length adjustment until elevator deflections are both within tolerance. (g) Set control yoke and torque tube to neutral pitch position. (See Figure 7-0) CAUTION: Use caution to avoid damaging yoke position placard, trim indicator, or yoke tube with hose clamp. 1 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.71 ±0. inches (.88 ±1.7 cm). Tighten clamp to secure control yoke firmly in place. Adjust forward elevator push/pull rod so distance from center of aft rod end to center of forward rod end is 9. inches (. cm). Verify angle from center of torque tube end fitting weldment to vertical plane equals 19 ±.. (h) Using rigging lockout tool and pin, lockout elevator empennage bellcrank. (i) Set elevators to neutral position using BL 1 and BL 0 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. (j) Tighten turnbuckles to adjust elevator control cable tension according to ambient temperature. (See Figure 0-001) (k) Remove lockout pin. (l) Fasten inclinometer to elevator and set at 0. (m) Remove hose clamp holding control yoke to neutral pitch position. WARNING: 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. (n) (o) (p) 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, 7-0 Page 10 1 Jun 010 Serials 101, 107 & subs

control yoke secondary stops show a 0.0 inch ±0.00 (0.89 mm ±0.1 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 0.1 inch (0.79 cm). Tighten jam nuts. (r) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 7-0) (s) Serials 01 & subs w/ Perspective Avionics: Perform Adjustment/Test - GSM 8A/8 Pitch Servo Mount Bridle Cable Tension. (Refer to -1) (t) Remove inclinometer. (u) Install kick plate. (Refer to -10) (v) Install access panels RE1 and RE. (Refer to 0-00) (w) Install baggage compartment carpet and access panel CF. (Refer to 0-00) () Inspection/Check - Elevator System Rigging (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Scale.0 inches (1. cm) - Any Source Elevator rigging. Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Tensiometer BT--7D Kent Moore Warren, MI 809 800-- Deflection angle determination. Cable tension determination. (b) Remove baggage compartment carpet and access panel CF. (Refer to 0-00) (c) Remove access panels RE1 and RE. (Refer to 0-00) (d) Perform Inspection/Check - Elevator Gap and Overlap. (Refer to -0) (e) Verify elevator control cable tension. (Refer to 7-0) (f) Verify elevator neutral position remains at 0 ±1 with control yoke in neutral position. (g) Verify 1 ±1 down and +0/-1.0 up elevator travel. (Refer to 7-0) (h) For full forward or full aft yoke movement, verify empennage elevator bellcrank stops contact before the control yoke secondary stops. (i) Inspect elevator pitch trim motor for security and condition. (j) For full forward or full aft yoke movement, verify control yoke secondary stops show a 0.0 inch ±0.00 (0.89 mm ±0.1 mm) gap between stop and yoke bearing mount when the empennage elevator bellcrank stops are engaged. (k) 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. (l) Verify minimum rod end thread engagement of 0.1 inch (0.79 cm). (m) Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire elevator control system. (n) Serials 01 & subs w/ Perspective Avionics: Verify bridle cable tension forward of bridle cable clamps is set to.0 +.0/-0.0 lb (11. +0.9/-0.0 kg) (Refer to -1) (o) Install access panels RE1 and RE. (Refer to 0-00) (p) Install baggage compartment carpet and access panel CF. (Refer to 0-00) Serials 101, 107 & subs 7-0 Page 11 1 May 011

1 1 1 1 7 11 BH0 7 10 9 8 LEGEND 1. Bolt. Washer. Nut. Cotter Pin. Torque Tube Coupler Weldment. Elevator Cable 7. Bracket 8. Forward Pulley Gang 9. Pin 10. Rudder/Elevator Pulley Gang 11. Turnbuckle 1. Elevator Empennage Bellcrank 1. Bushing 9 SR0_MM7_11 7-0 Page 1 1 Jun 010 Figure 7-0 Elevator System Cables - Serials 101, 107 & subs Serials 101, 107 & subs

RED RED BLACK BLACK 1 BLACK RED LEGEND 1. Forward Torque Tube Coupler Weldment. Aft Torque Tube Coupler Weldment. Turnbuckle. Elevator Cable. Elevator Empennage Bellcrank SR0_MM7_1 Serials 101, 107 & subs Figure 7-0 Color Identification - Serials 101, 107 & subs 7-0 Page 1 1 Jun 010

TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL 9 T.O. DN 0. ±0.1 inch (1.7 ±. mm) 19 ±. 8 7 10 1.71 ±0.0 inches (.88 ±1.7 cm) 9. inches (. cm) NOTE Clamp control yoke so distance from forward edge of yoke tube cover to aft edge of trim indicator is.71 ±0. inches (.88 ±1.7 cm). Adjust forward elevator push/pull rod so distance from center of aft rod end to center of forward rod end is 9. inches (. cm). Angle from vertical bracket to center of forward rod end is 19 ±.. Distance from aft edge of trim indicator to middle of T.O. range on decal is 0. ±0.1 inches (1.7 ±. mm). LEGEND 1. Yoke Carriage. Aft Rod End. End-Fitting Weldment. Forward Rod End. Firewall. Yoke Tube Cover 7. Trim Indicator 8. Bracket 9. Decal 10. Hose Clamp SR0_MM7_1B 7-0 Page 1 1 Jun 010 Figure 7-0 Setting Control Yoke Neutral Pitch Position - Serials 101, 107 & subs Serials 101, 107 & subs

NOTE Verify stop mounted on control yoke assembly shows a 0.0 ±0.00 inch (0.889 ±0.08 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 0 bulkhead is 0.0 inch ±0.0 inch (0.7 ±1. mm). 1 0.0 ±0.0 inch (0.7 ±1. mm) 0.0 ±0.00 inch (0.889 ±0.08 mm) SHOWN FULL DOWN POSITION LOCK-OUT HOLE LEGEND 1. Yoke Carriage. Control Yoke Stop. Elevator Bellcrank. Bellcrank Lock-out Tool All Figure 7-0 Elevator Rigging BULKHEAD 0 SR0_MM7_1A 7-0 Page 1 1 Jun 010

C. Forward Elevator Push/Pull Rod (See Figure 7-07) (See Figure 7-08) (1) Removal - Forward Elevator Push/Pull Rod (a) Remove seat. (Refer to -10) (b) Remove kick plate. (Refer to -10) (c) Remove mid-console trim panel. (Refer to -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 -10) (d) Install kick plate. (Refer to -10) (e) Install seat. (Refer to -10) 7-0 Page 1 1 Jun 010 All

D. Elevator Torque Tube (See Figure 7-07) (See Figure 7-08) (1) Removal - Elevator Torque Tube (a) Remove MFD. (Refer to 1-0) (b) Remove pilot and co-pilot seats. (Refer to -10) (c) Remove kick plate. (Refer to -10) (d) Remove mid-console trim panels from LH and RH sides. (Refer to -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 -10) (d) Install kick plate. (Refer to -10) (e) Install pilot and co-pilot seats. (Refer to -10) (f) Install MFD. (Refer to 1-0) All 7-0 Page 17 1 Jun 010

E. Elevator Pulley Sector - Serials 100 thru 100, 10 thru 10 (See Figure 7-07) WARNING: 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. (1) Removal - Elevator Pulley Sector - Serials 100 thru 100, 10 thru 10 (a) Remove co-pilot seat. (Refer to -10) (b) Remove right mid console trim. (Refer to -10) (c) Remove carpet and access panel CF from baggage compartment floor. (Refer to 0-00) (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 100 thru 100, 10 thru 10 (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 7-0). (d) Install access panel and carpet. (Refer to 0-00) (e) Install co-pilot seat. (Refer to -10) F. Bellcrank Weldment - Serials 101, 107 & subs (See Figure 7-08) 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 7-0) 7-0 Page 18 1 Jun 010 All

11 1 9 1 7 CONSOLE ASSY 1 1 8 LEGEND 1. Elevator Torque Tube - RH. Nut. Bearing Plate Assembly. Washer. Bolt. Coupler 7. Pulley Sector 8. Shim 9. Elevator Push/Pull Rod - Fwd 10. Elevator Torque Tube - LH 11. Castellated Nut 1. Cotter Pin 1. Thrust Collar 1. Spacer 1 1 8 10 7 Serials 100 thru 100, 10 thru 10 Serials 100 thru 100, 10 thru 10. Figure 7-07 Elevator System - Serials 100 thru 100, 10 thru 10 SR0_MM7_117D 7-0 Page 19 1 Jun 010

11 1 9 1 CONSOLE ASSY 1 LEGEND 1. Elevator Torque Tube - RH. Nut. Bearing Plate Assembly. Washer. Bolt. Coupler 7. Pulley Sector 8. Shim 9. Elevator Push/Pull Rod - Fwd 10. Elevator Torque Tube - LH 11. Castellated Nut 1. Cotter Pin 1. Spacer 1 10 SR0_MM7_1 7-0 Page 0 1 Jun 010 Figure 7-08 Elevator System - Serials 101, 107 & subs Serials 101, 107 & subs

G. Forward Pulley Gang (See Figure 7-10) (See Figure 7-107) 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 7-10) H. Rudder-Elevator Pulley Gang (See Figure 7-0) 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 7-0) I. Empennage Pulley Gang - Serials 100 thru 100, 10 thru 10 (See Figure 7-07) 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 7-0) J. Empennage Elevator Bellcrank - Serials 101, 107 & subs (See Figure 7-08) The rudder and elevator control system utilize separate bellcranks which mount directly to the FS 0 bulkhead. Maintenance practices pertinent to the empennage bellcranks are covered under the Rudder and Yaw Trim System. (Refer to 7-0) All 7-0 Page 1 1 Jun 010

K. Pitch Trim System - Serials 100 thru 100, 10 thru 10 (See Figure 7-09) (1) Servicing - Pitch Trim Cartridge Lubrication (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose LPS Chain Mate 01 LPS Laboratories Tucker, GA 008-0 800-1-8 Lubrication of the pitch trim cartridge. (b) Remove empennage access panels LE1 and RE1. (Refer to 0-00) (c) 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 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 0-00) () Removal - Pitch Trim Cartridge WARNING: A maintenance check flight must be performed after the installation of a replacement (new or different) trim cartridge. (a) Remove RE1, RE and LE1 access panels. (Refer to 0-00) (b) 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 7-0) (d) Install RE1, RE, and LE1 access panels. (Refer to 0-00) (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 -0) () Adjustment/Test - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose BL 0 Template 107-11 Cirrus Design Duluth, MN 811 18-77-77 Elevator rigging. BL 1 Template 107-111 Cirrus Design Elevator rigging. 7-0 Page 1 Jun 010 Serials 100 thru 100, 10 thru 10

Description P/N or Spec. Supplier Purpose Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Deflection angle determination. (b) Remove access panels RE1 and RE. (Refer to 0-00) (c) Set elevators to neutral position using BL 1 and BL 0 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. ±1.0 : 1 To increase elevator trailing edge down movement, shorten pitch trim cartridge by loosening jam nut and turning push/pull rod clockwise. 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. Shorten pitch trim cartridge for opposite results. (i) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 7-0) (j) Verify pitch trim cartridge minimum rod end thread engagement of 0.1 inch (0.79 cm). Tighten jam nuts. (k) Install access panels RE1 and RE. (Refer to 0-00) () Inspection/Check - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Deflection angle determination. (b) Verify correct elevator system rigging. (Refer to 7-0) (Refer to 7-0) (c) Fasten inclinometer to elevator and set at 0. (d) Run trim motor to full nose-down trim position until travel is stopped by lower limit switch. (e) Verify elevator deflection angle is -10. ±1.0. If pitch trim is out of adjustment, perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 7-0) (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 7-0) (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 0.1 inch (0.79 cm). (k) Verify proper installation of safety wires and cotter pins on all fasteners. () Removal - Pitch Trim Motor Serials 100 thru 100, 10 thru 10 7-0 Page 1 Jun 010

(a) Set BATTERY and AVIONICS switches to OFF positions. (b) Pull PITCH TRIM circuit breaker. (c) Remove access panel RE. (Refer to 0-00) (d) Remove composite rudder bottom. (Refer to -0) (e) Remove nut, washer, and screw securing pulley gang support brace to empennage. (f) Disconnect trim motor electrical connection. (g) 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 0 Bulkhead and remove from airplane. (7) Installation - Pitch Trim Motor (a) Position pitch trim motor assembly to FS 0 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 -0) (f) Install access panel RE. (Refer to 0-00) (g) Reset PITCH TRIM circuit breaker. 7-0 Page 1 Jun 010 Serials 100 thru 100, 10 thru 10

1 1 1 1 18 LEGEND 1. Jam Nut. Bolt. Washer. Rod End. Bushing. Spacer 7. Pitch Trim Cartridge 8. Cotter Pin 9. Castellated Nut 10. Screw 11. Limit Switch 1. Nut 1. Backing Plate 1. Pitch Trim Motor 1. Wire Harness 1. Connector 17. Set Screw 18. Motor Bracket 19. Actuation Arm 0. Elevator Bellcrank BH 0 1 1 1 10 10 11 8 9 17 10 19 9 8 0 7 1 BH 0 STIFFENER Serials 100 thru 100, 10 thru 10 Serials 100 thru 100, 10 thru 10. Figure 7-09 Pitch Trim System - Serials 100 thru 100, 10 thru 10 SR0_MM7_181B 7-0 Page 1 Jun 010

L. Pitch Trim System - Serials 101, 107 & subs (See Figure 7-010) (1) Servicing - Pitch Trim Cartridge Lubrication - Serials 101, 107 thru 18 (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose LPS Chain Mate 01 LPS Laboratories Tucker, GA 008-0 800-1-8 Lubrication of the pitch trim cartridge. (b) Remove empennage access panel RE1 and RE. (Refer to 0-00) (c) 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 RE, apply lubricant to forward end of pitch trim cartridge inner housing for 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 RE. (Refer to 0-00) () Removal - Pitch Trim Cartridge WARNING: A maintenance check flight must be performed after the installation of a replacement (new or different) trim cartridge. (a) Remove RE1, RE and LE1 access panels. (Refer to 0-00) (b) Remove cotter pin, nut, washers, and bolt securing trim cartridge to aft elevator bellcrank. (c) 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 7-0) (d) Install RE1, RE, and LE1 access panels. (Refer to 0-00) (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 -0) () Adjustment/Test - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Rigging Lockout Tool 190-001 Cirrus Design Duluth, MN 811 18-77-77 Lockout empennage bellcranks. /1 Lockout Pin - Any Source Lockout empennage bellcranks. 7-0 Page 1 Jun 010 Serials 101, 107 & subs

Description P/N or Spec. Supplier Purpose Inclinometer PRO0 Macklanburg Duncan Oklahoma City, OK 71 800--0007 Deflection angle determination. (b) Remove access panels RE1 and RE. (Refer to 0-00) (c) Set elevators to neutral position: 1 Using rigging lockout tool and pin, lockout elevator empennage bellcrank. 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. 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. ±1.0 : 1 To increase elevator trailing edge down movement, shorten cartridge by loosening jam nut and turning push/pull rod clockwise. 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. Shorten cartridge for opposite results. (i) Perform Inspection/Check - Pitch Trim Cartridge. (Refer to 7-0) (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 0.1 inch (0.79 cm). Tighten jam nuts. (l) Install access panels RE1 and RE. (Refer to 0-00) () Inspection/Check - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Inclinometer PRO0 Macklanburg Duncan Deflection angle Oklahoma City, OK 71 determination. 800--0007 (b) Verify correct elevator system rigging. (Refer to 7-0) (Refer to 7-0) (c) Fasten inclinometer to elevator and set at 0. (d) Run trim motor to full nose-down trim position until travel is stopped by lower limit switch. (e) Verify elevator deflection angle is -10. ±1.0. If pitch trim is out of adjustment, perform Adjustment/Test - Pitch Trim Cartridge. (Refer to 7-0) (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 7-0) (h) Remove inclinometer. Serials 101, 107 & subs 7-0 Page 7 1 Jun 010

(i) 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 0.1 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, and AVIONICS switches to OFF positions. (b) Pull PITCH TRIM circuit breaker. (c) Remove pitch trim cartridge. (Refer to 7-0) (d) Disconnect pitch trim motor electrical connector. (e) Remove bolts and washers securing pitch trim motor assembly to FS 0 Bulkhead and remove pitch trim motor assembly from airplane. (7) 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. (8) Assembly - Pitch Trim Motor Assembly (See Figure 7-011) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose VDC Power Supply - Any Source Rotate shaft of motor to correct installation position. (b) (c) (d) (e) 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: To ease installation of pitch trim motor assembly, install actuation arm so arm contacts upper stop on mounting bracket. 1 Connect pitch trim motor to 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 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. 7-0 Page 8 1 Jun 010 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. (9) Installation - Pitch Trim Motor Assembly (a) Position pitch trim motor assembly to FS 0 Bulkhead and secure with bolts and washers. Bolts must engage threaded insert to within a minimum of 0.0 inch (1. mm) of flush with bulkhead surface or protrude past bulkhead surface. Serials 101, 107 & subs

(b) Connect trim motor electrical connector. (c) Install pitch trim cartridge. (Refer to 7-0) (d) 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 -0) All 7-0 Page 9 1 Jun 010

BULKHEAD F.S. 0 1 8 7 9 7 1 10 1 7 7 11 19 1 18 LEGEND 1. Pitch Trim Motor. Wire Harness. Connector. Nut. Screw. Bolt 7. Washer 8. Motor Bracket 9. Limit Switch 10. Actuation Arm 18 17 11. Set Screw 1. Rod End 1. Jam Nut 1. Castellated Nut 1. Cotter Pin 1. Pitch Trim Cartridge 17. Spacer 18. Bushing 19. Elevator Bellcrank 7 1 1 7 1 1 SR0_MM7_1A 7-0 Page 0 1 Jun 010 Figure 7-010 Pitch Trim System - Serials 101, 107 & subs Serials 101, 107 & subs

1 1 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. Actuation arm must be oriented on shaft of motor so screw aligns with flat on shaft of motor. LEGEND 1. Pitch Trim Motor. Motor Bracket. Limit Switch. Actuation Arm. Set Screw. Upper Stop SR0_MM7_1810A Serials 101, 107 & subs Figure 7-011 Actuation Arm Installation and Adjustment - Serials 101, 107 & subs 7-0 Page 1 1 Jun 010

N. Pitch Relays (See Figure 7-01) CAUTION: Failure of either pitch relay is cause for replacement of both relays. Replace both relays upon failure of one. (1) Removal - Pitch Relay (a) Pull PITCH TRIM circuit breaker. (b) Serials 100 thru 1: Remove rear passenger seats. (Refer to -10) (c) Serials 100 thru 1: Remove access panel CFC. (Refer to 0-00) (d) Serials 1 & subs w/o Perspective Avionics: Remove access panel CFR. (Refer to 0-00) (e) Remove relay from socket. () Installation - Pitch Relay (a) Position relay to socket and push firmly to install. (b) Serials 100 thru 1: Install access panel CFC. (Refer to 0-00) (c) Serials 1 & subs w/o Perspective Avionics: Install access panel CFR. (Refer to 0-00) (d) Serials 100 thru 1: Install rear passenger seats. (Refer to -10) (e) Reset PITCH TRIM circuit breaker. 7-0 Page 1 May 011 All

RH LONGERON FLAP CIRCUIT CARD ROLL AUTOPILOT RELAY FLAP RELAY ROLL RELAY 9 8 9 1 7 CAUTION Failure of either relay is cause for replacing both relays. Serials 100 thru 1. LEGEND 1. Pitch Autopilot Relay. Screw. Washer. Spacer. Nut. Bolt 7. Pitch Relay- Up 8. Pitch Relay- Down 9. Relay Socket 10. Mounting Plate SR0_MM7_ Serials 100 thru 1 Figure 7-01 Pitch Relay Assembly - Serials 100 thru 1 (Sheet 1 of ) 7-0 Page 1 May 011

RH LONGERON ROLL RELAY 8 1 9 FLAP RELAY 7 RH LONGERON 9 CAUTION Serials 1 & subs w/o Perspective. 11 Failure of either relay is cause for replacing both relays. FLAP CIRCUIT CARD ROLL AUTOPILOT RELAY 9 1 LEGEND 1. Pitch Autopilot Relay. Screw. Washer. Spacer. Nut. Bolt 7. Pitch Relay-Up 8. Pitch Relay-Down 9. Relay Socket 11. Mounting Plate, Aft 1. Mounting Plate, Forward SR0_MM7_ 7-0 Page 1 May 011 Figure 7-01 Pitch Relay Assembly - Serials 1 & subs w/o Perspective Avionics (Sheet of ) Serials 1 & subs w/o Perspective Avionics

RH LONGERON GROUND BUS 1 9 ROLL RELAY 8 FLAP RELAY 7 RH LONGERON 9 Serials 01 & subs w/ System X/SR and Perspective. 11 ROLL AUTOPILOT RELAY GROUND BUS LEGEND 1. Pitch Autopilot Relay. Screw. Washer. Spacer. Nut. Bolt 7. Pitch Relay-Up 8. Pitch Relay-Down 9. Relay Socket 11. Mounting Plate, Aft 1. Mounting Plate, Forward CAUTION 9 Failure of either relay is cause for replacing both relays. 1 SR0_MM7_70 Figure 7-01 Pitch Relay Assembly - Serials 01 & subs w/ System X/SR and Perspective (Sheet of ) Serials 01 & subs w/ System X/SR and Perspective 7-0 Page 1 May 011

Intentionally Left Blank 7-0 Page 1 May 011 All