CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT Yaw Control and Trim CHAPTER 7-0: YAW CONTROL AND TRIM GENERAL 7-0: YAW CONTROL AND TRIM. General This section describes that portion of the flight control system which controls the position and movement of the rudder. Included are; rudder system rigging, rudder pedal assembly, cables, pulleys and bellcranks, and yaw trim system. For the optional yaw servo autopilot, see GFC 700 Automated Flight Control System section of Autoflight. (Refer to -0) For rudder flight surfaces, see Rudder section of Stabilizers. (Refer to -0) A. Yaw Control System Rudder control motion is transferred by the rudder pedals to the forward pulley gang at the bottom of the center console. From the pulley gang, control motion is transferred to a single cable system which is routed under the cabin floor through to the rudder/elevator pulley gang under the baggage floor, and finally to the rudder empennage bellcrank. The rudder empennage bellcrank drives a push/pull rod attached to the aft rudder bellcrank which is bolted directly to the rudder. The rudder and elevator control system utilize separate bellcranks connected by a shared shaft mounted directly to the FS 06 bulkhead. Fixed control stops at the rudder empennage bellcrank limit control surface travel. Two springs attached to the rudder assembly and firewall provide rudder system interconnection and determine system cable tension. B. Yaw Trim System The yaw trim system employs a ground-adjustable trim tab. Neutral rudder position is held by a ground-adjustable spring cartridge which bolts to the left rudder pedal torque tube and center console assembly. The cartridge is a captured compression spring that provides a centering force regardless of the direction of control surface deflection. Yaw trim adjustment is ground adjustable only and is achieved by changing the deflection angle of the trim tab. Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM. Maintenance Practices CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT 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. A. Rudder System Cables (See Figure 7-0-) The rudder system bellcrank, cable clevises, and cable turnbuckle ends are marked with blue and yellow paint to allow visual verification of proper cable assembly and installation. (See Figure 7-0-) Description Color Identification Top Rudder Empennage Bellcrank Left Rudder Pedal Torque Tube Arm Cable Clevises and Turnbuckle Ends Bottom Rudder Empennage Bellcrank Right Rudder Pedal Torque Tube Arm Cable Clevises and Turnbuckle Ends Primary Blue Primary Yellow () Removal - Rudder System Cables (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Spacer Block 7 /8 x (8.7 x.08 cm) - Any Source Spacer for holding neutral rudder position. String - Any Source Cable routing. (b) Remove RH mid console trim panel. (Refer to -0) (c) Remove passenger seats. (Refer to -0) (d) Remove carpet and access panels CFC, CF4C, and CF. (Refer to -0) (Refer to 6-00) (e) Remove access panels LE, LE, and RE. (Refer to 6-00) Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM (f) (g) (h) (i) (j) (k) (l) (m) Note location of yaw servo bridle cable clamps on rudder cable to facilitate reinstallation. Remove bolts, nuts, and clamps securing yaw servo bridle cable to rudder cable. (See Figure -0-6) Prior to removing turnbuckles, position spacer block between rudder pedals and firewall to support spring tension. At access panel CF, remove turnbuckles from rudder cables. Remove cotter pins, nuts, washers, and bolts securing rudder cable rod ends to rudder empennage bellcrank. At access hole CF, pull aft rudder cables through and remove cables from airplane. 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. To facilitate cable routing during installation, attach string to end of cables prior to removing from airplane. Remove cotter pins, nuts, washers, and bolts securing rudder cables to rudder pedal torque tubes. Attach string to ends of forward rudder cables. At access hole CF, pull forward rudder cables through and remove cables from airplane. () Installation - Rudder System Cables (a) If installing new cable, paint turnbuckle ends appropriate color. (Refer to 0-90) (b) At rudder pedal torque tubes, route forward rudder cable through mid and forward pulley gangs. (c) Install bolts, washers, nuts and new cotter pins securing rudder cables to rudder pedal torque tubes. (d) At forward pulley gang, verify cable routing, insert pulley guard pins, and install washers and new cotter pins. (e) At rudder/elevator pulley gang, verify cable routing, insert pulley guard pin, and install washer and new cotter pin. Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT (f) Route aft rudder cable from access hole CF to rudder empennage bellcrank. Install bolts, washers, nuts, and new cotter pins securing rudder cable rod end to rudder empennage bellcrank. (g) At access hole CF, install turnbuckles on forward and aft rudder cables. (h) Perform Adjustment/Test - Rudder System Rigging. (Refer to 7-0) (i) Perform Inspection/Check - Empennage Bellcranks. (Refer to 7-0) (j) Perform Adjustment/Test - GSM 86 Yaw Servo Mount Bridle Cable Tension. (Refer to -0) (k) Install access panels LE, LE, and RE. (Refer to 6-00) (l) Install carpet and access panels CFC, CF4C, and CF. (Refer to -0) (Refer to 6-00) (m) Install RH mid console trim panel. (Refer to -0) (n) Install passenger seats. (Refer to -0) 4 Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM Figure 7-0-: Rudder System Cables 4 4 TORQUE TUBE (REF) 6 8 BH06 (REF) 0 6 9 7 RUDDER PEDAL ASSEMBLY (REF) 7 LEGEND. Rudder Cable. Bolt. Washer 4. Nut. Cotter Pin 6. Bracket 7. Pin 8. Turnbuckle 9. Rudder/Elevator Pulley Gang 0. Forward Pulley Gang. Rudder Empennage Bellcrank. Fork End SR_MM7_4470 Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT () Adjustment/Test - Rudder System Rigging (See Figure 7-0-) 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 Spacer Block 7 /8 x (8.7 x.08 cm) - Any Source Spacer for holding neutral rudder position. Rigging Lockout Tool 490-00 Cirrus Design Lockout empennage bellcranks. /6 Lockout Pin - Any Source Lockout empennage bellcranks. Scale.0 inch (0.48 cm) - Any Source Rudder rigging. (b) Remove access panel CF. (Refer to 6-00) (c) Remove access panels LE, LE, and RE. (Refer to 6-00) (d) (e) (f) Note location of yaw servo bridle cable clamps on rudder cable to facilitate reinstallation. Remove bolts, nuts, and clamps securing yaw servo bridle cable to rudder cable. (See Figure -0-6) Prior to removing turnbuckles, position spacer block between rudder pedals and firewall to support spring tension. Loosen rudder system turnbuckles so all cable tension is removed. Set Rudder Deflection. Typically, the correct rudder deflection (0± ) is obtained by measuring.8 to 6. inches (4.7 to.8 cm) between chord line at upper leading edge of vertical stabilizer and 6 7 Dec 07
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM (g) (h) (i) chord line at lower leading edge of deflected rudder horn. (See Figure 7-0-) With full left rudder applied, verify rudder deflection angle is equal to 0±. Adjusting push/pull rod length affects the center location of the rudder deflection. The limits of deflection are not adjustable. It may be necessary to set each side off of nominal to meet tolerance on both sides. To increase deflection angle, lengthen push/pull rod by removing bolt securing rod end to aft rudder bellcrank, loosening jam nut, and turning rod end counterclockwise. Shorten push/pull rod for opposite results. 4 Repeat procedure for right rudder travel. Using rigging lockout tool and pin, lockout rudder empennage bellcrank. Set Rudder Pedal Neutral Position. Position rudder pedal pivot tubes so both left and right pedals are 0.±0. inch (.7±.4 mm) aft of gap between forward and aft torque tubes. (See Figure 7-0-) At LH outboard rudder pedal, wedge spacer block between rudder pedal tube and firewall. Tighten LH cable turnbuckle until spacer block falls away from pedal, indicating LH rudder pedals are in neutral position. Remove spacer block from airplane. 4 Repeat procedure on RH side. Remove rigging lockout tool and pin from rudder empennage bellcrank. WARNING Applying right rudder should deflect rudder trailing edge to the right. 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. (j) Verify application of right rudder deflects rudder trailing edge to the right. (k) Verify trim cartridge minimum rod end thread engagement of 0. inch (0.79 cm). Tighten jam nuts. (l) Perform Inspection/Check - Yaw Trim Cartridge. (Refer to 7-0) (m) Perform Adjustment/Test - GSM 86 Yaw Servo Mount Bridle Cable Tension. (Refer to -0) 7 7 Dec 07
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT (n) Install access panels LE, LE, and RE. (Refer to 6-00) (o) Install access panel CF. (Refer to 6-00) (4) Inspection/Check - Rudder System Rigging (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Scale 6.0 inches (.4 cm) - Any Source Rudder rigging. (b) Perform Inspection/Check - Rudder Gap and Overlap. (Refer to -40) (c) Verify rudder neutral position remains at 0± with rudder pedals in neutral position. Typically, the correct rudder deflection (0± ) is obtained by measuring.8 to 6. inches (4.7 to.8 cm) between chord line at upper leading edge of vertical stabilizer and chord line at lower leading edge of deflected rudder horn. (See Figure 7-0-) (d) Verify 0± rudder deflection angle. (Refer to 7-0) (e) Verify minimum rod end thread engagement of 0. inch (0.79 cm). (f) Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts throughout entire rudder control system. 8 Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM Figure 7-0-: Color Identification BLUE YELLOW 4 BLUE YELLOW YELLOW BLUE LEGEND. LH Rudder Pedal Torque Tube. RH Rudder Pedal Torque Tube. Turnbuckle 4. Rudder Cable. Rudder Empennage Bellcrank SR_MM7_447 9 Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT Figure 7-0-: Rudder Rigging ( of ) 0. ± 0. inch (.7 ±. mm) LOCK-OUT HOLE (REF) 4 0.0 ±0.06 inch (0.76 ±. mm) NOTE Position rudder pedal pivot tubes so both the left and right pedals are centered directly ±0. inch (±. mm) over gap between forward and aft torque tubes. Position rudder pedal pivot tubes so both the left and right pedals are 0. ±0. inch (.7 ±. mm) aft of gap between forward and aft torque tubes. With bellcrank lock-out tool in place, verify distance between center of lock-out hole and forward surface of 06 bulkhead is 0.0 ±0.06 inch (0.76 ±. mm). 6 BULKHEAD 06 (REF) LEGEND. Rudder Pedal. Pivot Tube. Torque Tube 4. Rudder Empennage Bellcrank. Bellcrank Lock-out Tool 6. Lock-out Pin SR_MM7_447 0 Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM Figure 7-0-: Rudder Rigging ( of ) 0.0 ± 0.0 ± RUDDER HORN CHORD LINE (REF) NOTE With full left/right rudder applied, verify rudder deflection angle is equal to 0 ±. Typically, the correct rudder deflection (0 ± ) is obtained by measuring.8-6. inches (4.7 -.8 cm) between chord line at upper leading edge of vertical stabilizer and chord line at lower leading edge of deflected rudder horn. SR_MM7_447 Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT B. Rudder Pedal Assembly (See Figure 7-0-4) () Removal - Rudder Pedal Assembly (a) Remove pilot and co-pilot seats. (Refer to -0) (b) Remove left mid console circuit breaker trim panel. (Refer to -0) (c) Remove carpet and access panel CF from baggage compartment floor. (Refer to -0) (Refer to 6-00) (d) Identify and loosen rudder cable tension via turnbuckle. (e) Remove yaw trim cartridge. (Refer to 7-0) (f) Remove cotter pin, nut, washers, and bolt securing cable fork ends to torque tube actuation arm. (g) Disconnect springs from firewall and torque tube actuation arms. (h) Remove cotter pins, washers, and clevis pins from upper connection at rudder pedals of each master cylinder. (i) Remove cotter pin and washers from rudder pedal pivot tube. (j) Slide rudder pedal pivot tube from bearing. (k) Detach rudder pedal from torque tube weldment. (l) Disconnect brake lines at torque tube fittings. Cap brake lines and fittings. (Refer to -4) (m) Remove carpet and forward access panels CFR and CFL to gain access to torque tube mounting nuts. (Refer to -0) (Refer to 6-00) (n) Remove cotter pin, nut, washers, and bolt securing rudder pedal assembly and bracket to floor. (o) Remove torque tube assembly from airplane. () Installation - Rudder Pedal Assembly (a) Align torque tube assembly and bracket over mounting holes on airplane floor and install bolts, washers, nuts, and new cotter pins securing torque tube assembly to airplane floor. (b) Perform Inspection/Check - Torque Tube Gap Tolerance. (Refer to 7-0) (c) Install forward access panels CFR and CFL. (Refer to 6-00) (d) Install carpet. (Refer to -0) Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM (e) Connect brake lines at torque tube fittings. (Refer to -4) (f) Align rudder pedal on torque tube weldment, insert rudder pedal pivot tube, and install washer and new cotter pin. (g) Install clevis pin, washers, and new cotter pin securing rudder pedal to upper connection on master cylinder. (h) Connect springs to firewall and torque tube actuation arms. (i) Install bolt, washers, nut and new cotter pin securing cable fork ends to torque tube actuation arms. (j) Install yaw trim cartridge. (Refer to 7-0) (k) Perform Inspection/Check - Rudder Pedal Assembly. (Refer to 7-0) (l) Install carpet and access panel CF. (Refer to -0) (Refer to 6-00) (m) Install left mid console circuit breaker trim panel. (Refer to -0) (n) Install pilot and co-pilot seats. (Refer to -0) (o) Bleed brake system. (Refer to -4) () Inspection/Check - Torque Tube Gap Tolerance CAUTION Gap between flange on bushing and rudder pedal torque tube must not exceed 0.06 inch (. mm). Prior to measuring gap, push torque tube assembly to opposing side. (a) (b) Push torque tube assembly to opposite side of where measurement is being made and place feeler gauge between bushing and torque tube to verify gap is within tolerance throughout full range of pedal motion. If necessary, adjust Torque Tube Gap Tolerance: Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Washer NAS49F046P Any Source Obtain gap tolerance. To maintain correct rudder system cable tension remove one rudder pedal bracket at a Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT time, always leaving one end of torque tube attached to cabin floor. Remove nuts, washers, and bolts securing bracket to floor. Remove bracket and bushing from end of torque tube. 4 Remove nut, washer, and bolt securing bushing to bracket. Up to two additional washers may be added on one end of torque tube to obtain gap tolerance. Add washer(s) between bracket and bushing as required to obtain gap tolerance. 6 Install bolt, washer, and nut securing bushing to bracket. Verify bolt clamps bushing tight against bracket. 7 Coat bushing with oil and insert bushing assembly into torque tube. 8 Install bolts, washers, and nuts securing bracket to airplane floor. 9 Verify gap between bushing and torque tube does not exceed 0.06 inch (. mm). If necessary, re-adjust Torque Tube Gap Tolerance. (4) Inspection/Check - Rudder Pedal Assembly (a) (b) Verify torque tube bushing attach bolt is torqued 0 to 70 in-lb (.6 to 7.9 Nm). (Refer to 0-60) Verify positive rudder pedal clearance through full range of pedal motion from brake lines and any other console structure or systems. C. Rudder Pedal Bracket (See Figure 7-0-4) During the removal and installation of the rudder pedal brackets, it is important to maintain the correct rudder system cable tension. Remove one bracket at a time, always leaving one end of torque tube firmly attached to cabin floor. () Removal - Rudder Pedal Bracket 4 Dec 06 (a) Remove pilot and co-pilot seats. (Refer to -0) (b) Remove carpet and forward access panels CFR and CFL to gain access to rudder pedal bracket mounting nuts. (Refer to -0) (Refer to 6-00) (c) Remove nuts, washers, and bolts securing bracket to floor.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM (d) (e) Remove bracket and bushing from end of torque tube. Remove nut, washer, and bolt securing bushing to bracket. () Installation - Rudder Pedal Bracket (a) Install nut, washer, and bolt securing bushing to bracket. Verify bolt clamps bushing tight against bracket. (b) Coat bushing with oil and insert bushing assembly into torque tube. (c) Install bolts, washers, and nuts securing bracket to airplane floor (d) Perform Inspection/Check - Torque Tube Gap Tolerance. (Refer to 7-0) (e) Install forward access panels CFR and CFL and carpet. (Refer to 6-00) (Refer to -0) (f) Install pilot and co-pilot seats. (Refer to -0) Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT Figure 7-0-4: Rudder Pedal Installation 4 A 8 9 0 CONSOLE (REF) 6 8 7 9 8 4 FIREWALL (REF) 0 9 NOTES Measure gap between flange on bushing and end of Rudder Pedal Torque Tube Bracket. Maximum gap tolerance is 0.06 inch (. mm). Up to two additional washers may be installed on one end of torque tube to obtain gap tolerance. 8 DETAIL 4 A LEGEND. Cotter Pin. Washer. Bushing 4. Rudder Pedal. Rudder Pedal Pin 6. Weldment Tube 7. Clevis 8. Clevis Pin 9. Castellated Nut 0 0 8 0. Spacer. Cartridge Spacer. Bolt. Yaw Trim Cartridge 4. Nut. Torque Tube Bracket 6. Torque Tube Bushing 7. Left Torque Tube 8. Right Torque Tube 7 6 4 FLOOR FWD (REF) 9. Spring 0. Eye Bolt. Brake Line. Jam Nut. Fitting 4. Master Cylinder SR_MM7_4474 6 Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM D. Forward Pulley Gang (See Figure 7-0-) (See Figure 7-0-6) 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 7-0) E. Rudder/Elevator Pulley Gang (See Figure 7-0-) () Removal - Rudder/Elevator Pulley Gang (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Spacer Block 7 /8 x (8.7 x.08 cm) - Any Source Spacer for holding neutral rudder position. (b) (c) (d) Remove carpet and access panel CF from baggage compartment floor. (Refer to -0) (Refer to 6-00) Prior to removing turnbuckles, position spacer block between rudder pedals and firewall to support spring tension. Identify and loosen rudder and elevator cable tension via turnbuckle. Remove cotter pin, nut, washers, spacers, and bolt securing pulleys to rudder/elevator pulley gang bracket and remove components from airplane. () Installation - Rudder/Elevator Pulley Gang (a) (b) Position and install bolt, spacers, washers, nut, and new cotter pin securing pulleys to rudder/elevator pulley gang bracket. Rig rudder system and perform Adjustment/Test - Rudder System Rigging. (Refer to 7-0) 7 Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT (c) Rig elevator system and perform Adjustment/Test - Elevator System Rigging. (Refer to 7-0) (d) Install fuselage floor access panel CF and carpet. (Refer to 6-00) (Refer to -0) F. Empennage Bellcranks (See Figure 7-0-6) () Removal - Empennage Bellcranks (a) Remove carpet and access panel CF from baggage compartment floor. (Refer to -0) (Refer to 6-00) Prior to removing turnbuckles, position spacer block between rudder pedals and firewall to support spring tension. (b) At access panel CF, remove turnbuckles from rudder and elevator cables. (c) Remove fuselage access panels RE, RE, LE, and LE. (Refer to 6-00) (d) Loosen jam nuts securing rudder and elevator push/pull rods to rudder and elevator empennage bellcranks. (e) Remove cotter pin, nut, washers, and bolt securing rudder push/pull rod to rudder bellcrank. (f) Remove cotter pin, nut, washers, and bolt securing elevator push/pull rod to elevator bellcrank. (g) Unscrew rudder push/pull rod from rod end attached to rudder empennage bellcrank and remove from airplane. (h) Unscrew elevator push/pull rod from rod end attached to elevator empennage bellcrank and remove from airplane. (i) Remove plug covering end of bulkhead shaft. (j) Remove bolt and washer securing bulkhead shaft to bulkhead. (k) Remove bulkhead shaft and bellcranks from airplane. (l) At access hole CF, pull rudder and elevator cables through. Remove cables airplane. 8 Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM () Installation - Empennage Bellcranks (a) (b) Route rudder and elevator cables through access hole RE forward to access hole CF. Insert bellcranks into empennage and position bulkhead shaft through bulkhead and bellcranks. Ensure bolt engages threaded insert to within 0.06 inch (.6 mm) of flush with bulkhead surface or protrudes past bulkhead surface. (c) Install bolt and washer securing bulkhead shaft to bulkhead. (d) Install plug covering end of bulkhead shaft. (e) Screw rudder push/pull rod onto rod end attached to rudder empennage bellcrank and tighten jam nut. (f) Screw elevator push/pull rod onto rod end attached to elevator empennage bellcrank and tighten jam nut. (g) Install bolt, spacer, washer, nut, and new cotter pin securing rudder push/pull rod to rudder bellcrank. (h) Install bolt, washers, nut, and new cotter pin securing elevator push/pull rod to elevator bellcrank. (i) Install rudder and elevator cables. (Refer to 7-0) (Refer to 7-0) (j) Install access panels RE, RE, LE, and LE. (Refer to 6-00) (k) Install access panel CF and carpet. (Refer to 6-00) (Refer to -0) () Inspection/Check - Empennage Bellcranks (a) Remove fuselage access panels RE, RE, LE, and LE. (Refer to 6-00) (b) Verify positive clearance of bellcranks through full range of rudder and elevator movement. (c) Verify positive clearance between pitch trim cartridge and vertical stabilizer bulkhead through full range of elevator and trim motor operation. (d) Verify minimum rod end thread engagement of 0. inch (0.79 cm). (e) Verify proper safety wire and cotter pin installation on all fasteners. (f) Install fuselage access panels RE, RE, LE, and LE. (Refer to 6-00) 9 Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT Figure 7-0-: Rudder/Elevator Pulley Gang 4 9 6 8 BULKHEAD F.S. 86 (REF) 7 LEGEND. Cotter Pin. Washer. Castellated Nut 4. Spacer. Bolt 6. Pulley Bracket 7. Backing Plate 8. Pin 9. Pulley SR_MM7_447 0 Dec 06
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT CHAPTER 7-0: YAW CONTROL AND TRIM Figure 7-0-6: Empennage Bellcranks AFT ELEVATOR BELLCRANK (REF) 0 8 4 RUDDER ASSY (REF) 4 4 9 7 BULKHEAD F.S. 06 (REF) 6 4 LEGEND. Bolt. Washer. Rod End 4. Castellated Nut. Cotter Pin 6. Rudder Bellcrank 7. Elevator Bellcrank 8. Elevator Push/Pull Rod 9. Rudder Push/Pull Rod 0. Shaft. Plug SR_MM7_4476 Dec 06
CHAPTER 7-0: YAW CONTROL AND TRIM CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT G. Yaw Trim Cartridge (See Figure 7-0-4) () Removal - Yaw Trim Cartridge (a) Remove left mid console circuit breaker trim. (Refer to -0) (b) Remove cotter pin, nut, washers, bushing, spacers, and bolt securing trim cartridge to console bracket. (c) Remove cotter pin, nut, washers, and bolt securing trim cartridge push/pull rod to left torque tube actuation arm and remove from airplane. () Installation - Yaw Trim Cartridge (a) Install bolt, washers, nut, and new cotter pin securing trim cartridge push/pull rod to left torque tube actuation arm. (b) Install bolt, washers, bushing, spacers, nut, and new cotter pin securing trim cartridge to console bracket. (c) Perform Inspection/Check - Yaw Trim Cartridge. (Refer to 7-0) (d) Install left mid console circuit breaker trim. (Refer to -0) () Inspection/Check - Yaw Trim Cartridge (a) Verify correct rudder system rigging. (Refer to 7-0) (b) Verify yaw trim cartridge is adjusted to hold rudder in neutral position ±. (c) Verify positive clearance between trim cartridge and actuation pulley under full range of trim motor positions. (d) Verify minimum rod end thread engagement of 0. inch (0.79 cm). (e) Verify proper installation of safety wires and cotter pins on all fasteners. H. Rudder Trim Tab Yaw trim adjustment is ground adjustable only and is achieved by changing the deflection angle of the rudder trim tab. For maintenance practices pertinent to the rudder trim tab, see Rudder. (Refer to -40) Dec 06