CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
RUDDER AND YAW TRIM SYSTEM
1. DESCRIPTION
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,
rudder-aileron interconnect, and yaw trim system.
Serials 1005 thru 1300, 1302 thru 1306: 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 passed to
a single cable system which is routed under the cabin floor to the rudder-aileron interconnect, through to
the rudder/elevator pulley gang under the baggage floor, and finally to the rudder actuation pulley. The rudder actuation pulley drives a push/pull rod attached to the rudder bellcrank which is bolted directly to the
rudder. The rudder and elevator control system utilize separate actuation pulleys which mount to a shared
pulley-gang bracket mounted inside the empennage. Each set of pulleys has a cable retainer to prevent
fouling. Adjustable control stops at the rudder actuation pulley limit control surface travel. Two springs
attached to the rudder pedal assembly and firewall provide rudder system interconnection and determine
system cable tension.
Serials 1301, 1307 & subs: 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 to the rudder-aileron interconnect (Serials 1005 thru
1885), 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 306 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.
The yaw trim system employs a ground-adjustable trim tab. Neutral rudder position is held by a groundadjustable 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.
EFFECTIVITY:
All
27-20
Page 1
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2. MAINTENANCE PRACTICES
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 - Serials 1005 thru 1306 (See Figure 27-201)
(1)
Removal - Rudder 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
To facilitate cable routing during installation, attach string to end of cables
prior to removing from airplane.
(i)
27-20
Page 2
15 Jun 2010
Cable routing.
Remove RH mid console trim panel. (Refer to 25-10)
Remove passenger seats. (Refer to 25-10)
Remove carpet and access panels CF3C, CF4C, and CF5. (Refer to 06-00)
Remove nut, washers, clamps, bushings, spacer, and bolt securing right rudder cable to
interconnect arm. (Refer to 27-20)
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:
(2)
Purpose
Remove cotter pins, nuts, washers, and bolts securing rudder cables to rudder pedal
torque tubes. Attach string to ends of forward rudder cables.
(j)
At access hole CF5 pull forward rudder cables through and remove cables from airplane.
Installation - Rudder System Cables
(a) Install empennage pulley gang. (Refer to 27-20)
(b) At access hole CF5, install turnbuckles on forward and aft rudder cables.
(c)
At rudder pedal torque tubes, route forward rudder cable through mid and forward pulleys
gangs.
(d) Install bolts, washers, nuts, and cotter pins securing rudder cables to rudder pedal torque
tubes.
(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) Install bolt, washers, clamps, bushings, spacer, and nut securing right rudder cable to
interconnect arm. (Refer to 27-20)
(i)
Perform Adjustment/Test - Rudder System Rigging. (Refer to 27-20)
(j)
Perform Adjustment/Test - Rudder-Aileron Interconnect. (Refer to 27-20)
(k)
Perform Inspection/Check - Empennage Pulley Gang. (Refer to 27-20)
(l)
Install carpet and access panels CF3C, CF4C, and CF5. (Refer to 06-00)
(m) Install RH mid console trim panel. (Refer to 25-10)
EFFECTIVITY:
Serials 1005 thru 1306
CIRRUS
(3)
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
(n) Install passenger seats. (Refer to 25-10)
Adjustment/Test - Rudder System Rigging (See Figure 27-204)
Note:
(a)
Allow temperature to stabilize for a period of four hours before setting cable tensions.
Acquire necessary tools, equipment, and supplies.
Description
3/16” Lockout Pin
(b)
(c)
(d)
(e)
(f)
(g)
(h)
(i)
Supplier
Purpose
-
Any Source
Rudder rigging.
Spacer Block
7 3/8” x 2” (18.73 x 5.08 cm)
Any Source
Spacer for holding neutral
rudder position.
Scale
12.0 inch (30.48 cm)
Any Source
Rudder rigging.
-
Remove left mid console circuit breaker trim. (Refer to 25-10)
Remove access panel CF5. (Refer to 06-00)
Remove access panels LE1, LE2, and RE2. (Refer to 06-00)
Remove cotter pin, nut, washers, and bolt securing yaw trim cartridge to rudder pedal
actuation arm. (See Figure 27-205)
Set rudder pedal neutral position and cable tension.
1
Position spacer block between LH outboard rudder pedal tube and firewall to support spring tension.
2
Position spacer block between RH outboard rudder pedal tube and firewall to support spring tension.
3
Loosen rudder system turnbuckles so all cable tension is removed.
4
Insert lockout pin at rudder actuation pulley in empennage.
5
Position rudder pedal pivot tubes so both left and right pedals are centered directly
over gap between forward and aft torque tubes within 0.10 inch (2.54 mm). (See
Figure 27-204)
6
Tighten LH cable turnbuckle until spacer block falls away from pedal, indicating LH
rudder pedals are in neutral position. Remove spacer block from airplane.
7
Tighten RH cable turnbuckle until spacer block falls away from pedal, indicating RH
rudder pedals are in neutral position. Remove spacer block from airplane.
Adjust rudder-to-vertical stabilizer alignment such that the rudder horn aligns with the vertical stabilizer with no more than 0.1 inch (0.25 cm) misalignment:
1
To move rudder trailing edge right, lengthen push/pull rod by removing bolt securing
rod end to aft rudder bellcrank, loosening jam nut, and turning rod end counterclockwise.
2
Shorten push/pull rod for opposite results.
Remove lockout pin from rudder actuation pulley in empennage.
Position yaw trim cartridge to rudder pedal actuation arm and secure with bolt, washers,
nut, and cotter pin. (See Figure 27-205)
WARNING:
(j)
P/N or Spec.
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.
Verify application of right rudder deflects rudder trailing edge to the right.
EFFECTIVITY:
Serials 1005 thru 1306
27-20
Page 3
15 Jun 2010
CIRRUS
(k)
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Determine rudder travel.
Note:
Typically, the correct rudder deflection (20° ±1°) is obtained by measuring
5.6 - 6.0 inches (14.2 - 15.2 cm) between chord line at upper leading edge
of vertical stabilizer and chord line at lower leading edge of deflected rudder
horn. (See Figure 27-204)
1
(4)
With full left rudder applied, verify rudder deflection angle is equal to 20° ±1°. Adjust
stop screws at empennage rudder actuation pulley if necessary.
2
Repeat procedure for right rudder travel.
3
Ensure that rudder actuation pulley stops limit rudder travel and not yaw trim cartridge.
(l)
Verify trim cartridge minimum rod end thread engagement of 0.312 inch (0.79 cm). Tighten
jam nuts.
(m) Perform Inspection/Check - Yaw Trim Cartridge. (Refer to 27-20)
(n) Install left mid console circuit breaker trim. (Refer to 25-10)
(o) Install access panel CF5. (Refer to 06-00)
(p) Install access panels LE1, LE2, and RE2. (Refer to 06-00)
Inspection/Check - Rudder System Rigging
(a)
Acquire necessary tools, equipment, and supplies.
Description
Scale
6.0 inches (15.24 cm)
(b)
(c)
27-20
Page 4
15 Jun 2010
Supplier
Any Source
Purpose
Rudder rigging.
Perform Inspection/Check - Rudder Gap and Overlap. (Refer to 55-40)
Verify rudder neutral position remains at 0 ±1° with rudder pedals in neutral position.
Note:
(d)
(e)
(f)
(g)
P/N or Spec.
Typically, the correct rudder deflection (20° ±1°) is obtained by measuring
5.6 - 6.0 inches (14.2 - 15.2 cm) between chord line at upper leading edge
of vertical stabilizer and chord line at lower leading edge of deflected rudder
horn. (See Figure 27-204)
Verify 20° ±1° rudder deflection angle. (Refer to 27-20)
Perform Inspection/Check - Rudder-Aileron Interconnect. (Refer to 27-20)
Verify minimum rod end thread engagement of 0.312 inch (0.79 cm).
Verify proper installation of safety wires and cotter pins on all fasteners and engagement
of all jam nuts throughout entire rudder control system.
EFFECTIVITY:
Serials 1005 thru 1306
CIRRUS
AIRPLANE MAINTENANCE MANUAL
2
3
MODEL SR20
12
3
6
4
5
11
3
3
6
TORQUE TUBE
(REF)
7
1
3
1
RUDDER/AILERON
INTERCONNECT (REF)
10
8
5
5
6
9
7
3
7
3
5
RUDDER PEDAL
ASSEMBLY (REF)
Serials 1005 thru 1300, 1302 thru 1306.
LEGEND
1. Rudder Cable
2. Bolt
3. Washer
4. Nut
5. Cotter Pin
6. Bracket
7. Pin
8. Turnbuckle
9. Rudder/Elevator Pulley Gang
10. Forward Pulley Gang
11. Empennage Pulley Gang
12. Fork End
SR20_MM27_1295B
Figure 27-201
Rudder System Cables - Serials 1005 thru 1306
EFFECTIVITY:
Serials 1005 thru 1306
27-20
Page 5
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
B. Rudder System Cables - Serials 1307 & subs (See Figure 27-202)
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 27-203)
Description
Color Identification
Top Rudder Empennage Bellcrank
Left Rudder Pedal Torque Tube Arm
Cable Clevises and Turnbuckle Ends
Primary Blue
Bottom Rudder Empennage Bellcrank
Right Rudder Pedal Torque Tube Arm
Cable Clevises and Turnbuckle Ends
Primary Yellow
(1)
Removal - Rudder System Cables
(a)
Acquire necessary tools, equipment, and supplies.
Description
(b)
(c)
(d)
(e)
(f)
(i)
(j)
(k)
Supplier
Any Source
Spacer for holding
neutral rudder position.
String
Any Source
Cable routing.
-
Remove RH mid console trim panel. (Refer to 25-10)
Remove passenger seats. (Refer to 25-10)
Remove carpet and access panels CF3C, CF4C, and CF5. (Refer to 06-00)
Remove access panels LE1, LE2, and RE2. (Refer to 06-00)
Serials 1307 thru 1885: Remove nut, washers, clamps, bushings, spacer, and bolt securing right rudder cable to interconnect arm. (Refer to 27-20)
Prior to removing turnbuckles, position spacer block between rudder pedals
and firewall to support spring tension.
At access panel CF5, remove turnbuckles from rudder cables.
Remove cotter pins, nuts, washers, and bolts securing rudder cable rod ends to rudder
empennage bellcrank.
At access hole CF5, 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.
Note:
To facilitate cable routing during installation, attach string to end of cables
prior to removing from airplane.
(l)
(2)
27-20
Page 6
15 Jun 2010
Purpose
Spacer Block
7 3/8” x 2” (18.73 x 5.08 cm)
Note:
(g)
(h)
P/N or Spec.
Remove cotter pins, nuts, washers, and bolts securing rudder cables to rudder pedal
torque tubes. Attach string to ends of forward rudder cables.
(m) At access hole CF5, 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 20-90)
EFFECTIVITY:
Serials 1307 & subs
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
(b)
(3)
At rudder pedal torque tubes, route forward rudder cable through mid and forward pulley
gangs.
(c)
Install bolts, washers, nuts and 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 cotter pins.
(e) At rudder/elevator pulley gang, verify cable routing, insert pulley guard pin, and install
washer and cotter pin.
(f)
Route aft rudder cable from access hole CF5 to rudder empennage bellcrank. Install bolts,
washers, nuts, and cotter pins securing rudder cable rod end to rudder empennage bellcrank.
(g) At access hole CF5, install turnbuckles on forward and aft rudder cables.
(h) Serials 1307 thru 1885: Install bolt, washers, clamps, bushings, spacer, and nut securing
right rudder cable to interconnect arm. (Refer to 27-20)
(i)
Perform Adjustment/Test - Rudder System Rigging. (Refer to 27-20)
(j)
Serials 1307 thru 1885: Perform Adjustment/Test - Rudder-Aileron Interconnect. (Refer to
27-20)
(k)
Perform Inspection/Check - Empennage Bellcranks. (Refer to 27-20)
(l)
Install access panels LE1, LE2, and RE2. (Refer to 06-00)
(m) Install carpet and access panels CF3C, CF4C, and CF5. (Refer to 06-00)
(n) Install RH mid console trim panel. (Refer to 25-10)
(o) Install passenger seats. (Refer to 25-10)
Adjustment/Test - Rudder System Rigging (See Figure 27-204)
Note:
(a)
Allow temperature to stabilize for a period of four hours before setting cable tensions.
Acquire necessary tools, equipment, and supplies.
Description
(b)
(c)
Supplier
Purpose
Spacer Block
7 3/8” x 2” (18.73 x 5.08 cm)
Any Source
Spacer for holding
neutral rudder position.
Rigging Lockout Tool
14905-001
Cirrus Design
Lockout empennage
bellcranks.
3/16” Lockout Pin
-
Any Source
Lockout empennage
bellcranks.
Scale
12.0 inch (30.48 cm)
-
Any Source
Rudder rigging.
Remove access panel CF5. (Refer to 06-00)
Remove access panels LE1, LE2, and RE2. (Refer to 06-00)
Note:
(d)
(e)
P/N or Spec.
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.
EFFECTIVITY:
Serials 1307 & subs
27-20
Page 7
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Note:
MODEL SR20
Serials 1307 thru 1422: Typically, the correct rudder deflection (20° ±1°) is
obtained by measuring 5.6 - 6.0 inches (14.2 - 15.2 cm) between chord line
at upper leading edge of vertical stabilizer and chord line at lower leading
edge of deflected rudder horn. (See Figure 27-204)
Serials 1423 & subs: Typically, the correct rudder deflection (20° ±1°) is
obtained by measuring 5.8 - 6.2 inches (14.7 - 15.8 cm) between chord line
at upper leading edge of vertical stabilizer and chord line at lower leading
edge of deflected rudder horn. (See Figure 27-204)
1
With full left rudder applied, verify rudder deflection angle is equal to 20° ±1°.
Note:
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.
2
(f)
(g)
(h)
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.
3
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.
1
Serials 1307 thru 1422: Position rudder pedal pivot tubes so both left and right pedals are centered directly over gap between forward and aft torque tubes within 0.10
inch (2.54 mm). (See Figure 27-204)
2
Serials 1423 & subs: Position rudder pedal pivot tubes so both left and right pedals
are 0.5 ±0.1 inch (12.7 ±2.54 mm) aft of gap between forward and aft torque tubes.
(See Figure 27-204)
3
At LH outboard rudder pedal, wedge spacer block between rudder pedal tube and
firewall.
4
Tighten LH cable turnbuckle until spacer block falls away from pedal, indicating LH
rudder pedals are in neutral position. Remove spacer block from airplane.
5
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.
(i)
(j)
(4)
27-20
Page 8
15 Jun 2010
Verify application of right rudder deflects rudder trailing edge to the right.
Verify trim cartridge minimum rod end thread engagement of 0.313 inch (0.79 cm). Tighten
jam nuts.
(k)
Perform Inspection/Check - Yaw Trim Cartridge.(Refer to 27-20)
(l)
Install access panels LE1, LE2, and RE2. (Refer to 06-00)
(m) Install access panel CF5. (Refer to 06-00)
Inspection/Check - Rudder System Rigging
EFFECTIVITY:
Serials 1307 & subs
CIRRUS
(a)
AIRPLANE MAINTENANCE MANUAL
Acquire necessary tools, equipment, and supplies.
Description
Scale
6.0 inches (15.24 cm)
(b)
(c)
MODEL SR20
P/N or Spec.
-
Supplier
Any Source
Purpose
Rudder rigging.
Perform Inspection/Check - Rudder Gap and Overlap. (Refer to 55-40)
Verify rudder neutral position remains at 0 ±1° with rudder pedals in neutral position.
Note:
Serials 1307 thru 1422: Typically, the correct rudder deflection (20° ±1°) is
obtained by measuring 5.6 - 6.0 inches (14.2 - 15.2 cm) between chord line
at upper leading edge of vertical stabilizer and chord line at lower leading
edge of deflected rudder horn. (See Figure 27-204)
Serials 1423 & subs: Typically, the correct rudder deflection (20° ±1°) is
obtained by measuring 5.8 - 6.2 inches (14.7 - 15.8 cm) between chord line
at upper leading edge of vertical stabilizer and chord line at lower leading
edge of deflected rudder horn. (See Figure 27-204)
(d)
(e)
(f)
(g)
Verify 20° ±1° rudder deflection angle. (Refer to 27-20)
Serials 1307 thru 1885: Perform Inspection/Check - Rudder-Aileron Interconnect. (Refer
to 27-20)
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 rudder control system.
EFFECTIVITY:
Serials 1307 & subs
27-20
Page 9
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
3
5
2
RUDDER/AILERON
INTERCONNECT (REF)
12
3
4
2
1
3
4
11
5
3
3
6
TORQUE TUBE
(REF)
1
Serials 1005 thru 1877,
1879 thru 1885.
8
BH306
(REF)
1
5
10
9
6
7
7
3
5
RUDDER PEDAL
ASSEMBLY (REF)
3
LEGEND
1. Rudder Cable
2. Bolt
3. Washer
4. Nut
5. Cotter Pin
6. Bracket
7. Pin
8. Turnbuckle
9. Rudder/Elevator Pulley Gang
10. Forward Pulley Gang
11. Rudder Empennage Bellcrank
12. Fork End
SR20_MM27_1657A
Figure 27-202
Rudder System Cables - Serials 1307 & subs
27-20
Page 10
15 Jun 2010
EFFECTIVITY:
Serials 1307 & subs
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
BLUE
5
YELLOW
4
BLUE
3
2
1
YELLOW
YELLOW
BLUE
LEGEND
1. LH Rudder Pedal Torque Tube
2. RH Rudder Pedal Torque Tube
3. Turnbuckle
4. Rudder Cable
5. Rudder Empennage Bellcrank
SR20_MM27_1658
Figure 27-203
Color Identification - Serials 1307 & subs
EFFECTIVITY:
Serials 1307 & subs
27-20
Page 11
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
1
2
3
3
Serials 1423 & subs.
0.5 ± 0.1 inch
(12.7 ±2.5 mm)
0.03 ±0.06 inch
(0.76 ±1.52 mm)
1
2
4
3
LOCK-OUT HOLE
(REF)
3
Serials 1005 thru 1422.
6
NOTE
Position rudder pedal pivot tubes so both the left
and right pedals are centered directly ±0.1 inch
(±2.5 mm) over gap between forward and aft
torque tubes.
5
Position rudder pedal pivot tubes so both the left
and right pedals are 0.5 ±0.1 inch (12.7 ±2.5 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 306 bulkhead is 0.03 ±0.06 inch (0.76 ±1.52 mm).
LEGEND
1. Rudder Pedal
2. Pivot Tube
3. Torque Tube
4. Rudder Empennage Bellcrank
5. Bellcrank Lock-out Tool
6. Lock-out Pin
BULKHEAD 306
(REF)
Serials 1301, 1307 & subs.
SR20_MM27_1659D
Figure 27-204
Rudder Rigging (Sheet 1 of 2)
27-20
Page 12
15 Jun 2010
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
20.0° ±1°
20.0° ±1°
RUDDER HORN
CHORD LINE
(REF)
NOTE
With full left/right rudder applied, verify rudder deflection angle is equal to 20° ±1°.
Serials 1005 thru 1422: Typically, the correct rudder deflection (20° ±1°) is obtained
by measuring 5.6 - 6.0 inches (14.2 - 15.2 cm) between chord line at upper leading edge
of vertical stabilizer and chord line at lower leading edge of deflected rudder horn.
Serials 1423 & subs: Typically, the correct rudder deflection (20° ±1°) is obtained by
measuring 5.8 - 6.2 inches (14.7 - 15.8 cm) between chord line at upper leading edge of
vertical stabilizer and chord line at lower leading edge of deflected rudder horn.
SR20_MM27_2689
Figure 27-204
Rudder Rigging (Sheet 2 of 2)
EFFECTIVITY:
All
27-20
Page 13
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
C. Rudder Pedal Assembly (See Figure 27-205)
(1)
(2)
(3)
Removal - Rudder Pedal Assembly
(a) Remove pilot and co-pilot seats. (Refer to 25-10)
(b) Remove left mid console circuit breaker trim panel. (Refer to 25-10)
(c)
Remove carpet and access panel CF5 from baggage compartment floor. (Refer to 06-00)
(d) Identify and loosen rudder cable tension via turnbuckle.
(e) Remove yaw trim cartridge. (Refer to 27-20)
(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.
(m) Remove carpet and forward access panels CF1R and CF1L to gain access to torque tube
mounting nuts. (Refer to 06-00)
(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 cotter pins securing torque tube assembly to airplane floor.
(b) Perform Inspection/Check - Torque Tube Gap Tolerance. (Refer to 27-20)
(c)
Install forward access panels CF1R and CF1L. (Refer to 06-00)
(d) Install carpet. (Refer to 25-10)
(e) Connect brake lines at torque tube fittings. (Refer to 32-42)
(f)
Align rudder pedal on torque tube weldment, insert rudder pedal pivot tube, and install
washer and cotter pin.
(g) Install clevis pin, washers, and 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 cotter pin securing cable fork ends to torque tube actuation
arms.
(j)
Install yaw trim cartridge. (Refer to 27-20)
(k)
Perform Inspection/Check - Rudder Pedal Assembly. (Refer to 27-20)
(l)
Install carpet and access panel CF5. (Refer to 06-00)
(m) Install left mid console circuit breaker trim panel. (Refer to 25-10)
(n) Install pilot and co-pilot seats. (Refer to 25-10)
(o) Bleed brake system. (Refer to 32-42)
Inspection/Check - Torque Tube Gap Tolerance
Note:
27-20
Page 14
15 Jun 2010
Gap between flange on bushing and rudder pedal torque tube must not exceed
0.06 inch (1.5 mm). Prior to measuring gap, push torque tube assembly to opposing side.
EFFECTIVITY:
All
CIRRUS
(a)
(b)
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
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:
1
Acquire necessary tools, equipment, and supplies.
Description
Washer
Note:
2
3
4
P/N or Spec.
NAS1149F0463P
Supplier
Any Source
Purpose
Obtain gap tolerance.
To maintain correct rudder system cable tension remove one rudder
pedal bracket at a 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.
Remove nut, washer, and bolt securing bushing to bracket.
Note:
Up to two additional washers may be added on one end of torque
tube to obtain gap tolerance.
5
6
(4)
Add washer(s) between bracket and bushing as required to obtain gap tolerance.
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 (1.5 mm). If
necessary, re-adjust Torque Tube Gap Tolerance.
Inspection/Check - Rudder Pedal Assembly
(a) Verify torque tube bushing attach bolt torque is 50 - 70 in-lb (5.6 - 7.9 Nm)
(b) Verify positive rudder pedal clearance through full range of pedal motion from brake lines
and any other console structure or systems.
EFFECTIVITY:
All
27-20
Page 15
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
D. Rudder Pedal Bracket (See Figure 27-205)
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.
(1)
(2)
27-20
Page 16
15 Jun 2010
Removal - Rudder Pedal Bracket
(a) Remove pilot and co-pilot seats. (Refer to 25-10)
(b) Remove carpet and forward access panels CF1R and CF1L to gain access to rudder
pedal bracket mounting nuts. (Refer to 06-00)
(c)
Remove nuts, washers, and bolts securing bracket to floor.
(d) Remove bracket and bushing from end of torque tube.
(e) 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 27-20)
(e) Install forward access panels CF1R and CF1L and carpet. (Refer to 06-00)
(f)
Install pilot and co-pilot seats. (Refer to 25-10)
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
1 2
MODEL SR20
4
2
3
5
3
CONSOLE
(REF)
1
9
2
2
6
1
8
12
7
11
2
13
2
3
12
2
2
1
10
2
1
9
18
19
20
21
14
2
FIREWALL
(REF)
23
2
18
17
24
22
21
Serials 0002 thru 1072.
10. Spacer
11. Cartridge Spacer
12. Bolt
13. Yaw Trim Cartridge
14. Nut
15. Torque Tube Bracket
16. Torque Tube Bushing
17. Left Torque Tube
18. Right Torque Tube
16
10
2
1
12
2
NOTES
LEGEND
1. Cotter Pin
2. Washer
3. Bushing
4. Rudder Pedal
5. Rudder Pedal Pin
6. Weldment Tube
7. Clevis
8. Clevis Pin
9. Castellated Nut
12
10
2
14
17
2
12
19. Spring
20. Eye Bolt
21. Brake Line
22. Jam Nut
23. Fitting
24. Master Cylinder
15
12
2
2
2
14
14
Measure gap between flange on bushing
and end of Rudder Pedal Torque Tube Bracket.
Maximum gap tolerance is 0.06 inch (1.5 mm).
Up to two additional washers may be installed on
one end of torque tube to obtain gap tolerance.
Serials 1601 & subs,
Serials 1005 thru 1600 after SB 2X-32-13.
SR20_MM27_1167E
Figure 27-205
Rudder Pedal Installation
EFFECTIVITY:
All
27-20
Page 17
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
E. 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)
F.
Rudder/Elevator Pulley Gang (See Figure 27-206)
(1)
Removal - Rudder/Elevator Pulley Gang
(a)
Acquire necessary tools, equipment, and supplies.
Description
Spacer Block
7 3/8” x 2” (18.73 x 5.08 cm)
(b)
P/N or Spec.
Supplier
Any Source
Prior to removing turnbuckles, position spacer block between rudder pedals
and firewall to support spring tension.
(c)
(d)
27-20
Page 18
15 Jun 2010
Spacer for holding
neutral rudder position.
Remove carpet and access panel CF5 from baggage compartment floor. (Refer to 06-00)
Note:
(2)
Purpose
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) Position and install bolt, spacers, washers, nut, and cotter pin securing pulleys to rudder/
elevator pulley gang bracket.
(b) Rig rudder system and perform Adjustment/Test - Rudder System Rigging. (Refer to 2720) (Refer to 27-20)
(c)
Rig elevator system and perform Adjustment/Test - Elevator System Rigging. (Refer to 2730) (Refer to 27-30)
(d) Install fuselage floor access panel CF5 and carpet. (Refer to 06-00)
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
G. Empennage Pulley Gang - Serials 1005 thru 1306 (See Figure 27-207)
(1)
Removal - Empennage Pulley Gang
(a)
Acquire necessary tools, equipment, and supplies.
Description
Spacer Block
7 3/8” x 2” (18.73 x 5.08 cm)
(b)
P/N or Spec.
Supplier
Any Source
Purpose
Spacer for holding
neutral rudder position.
Remove carpet and access panel CF5 from baggage compartment floor. (Refer to 06-00)
Note:
Prior to removing turnbuckles, position spacer block between rudder pedals
and firewall to support spring tension.
(c)
(d)
(e)
(2)
At access panel CF5, remove turnbuckles from rudder and elevator cables.
Remove fuselage access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
Loosen jam nuts securing rudder and elevator push/pull rods to rudder and elevator actuation pulleys.
(f)
Remove cotter pin, nut, washer, spacer, and bolt securing rudder push/pull rod to rudder
bellcrank.
(g) Remove cotter pin, nut, washers, and bolt securing elevator push/pull rod to elevator bellcrank.
(h) Unscrew rudder push/pull rod from rod end attached to rudder actuation pulley and
remove from airplane.
(i)
Unscrew elevator push/pull rod from rod end attached to elevator actuation pulley and
remove from airplane.
(j)
Remove nut, washer, and screw securing support brace to empennage, loosen jam nut
securing support brace to pulley gang, and remove support brace from airplane.
(k)
Gain access to pulley gang mounting bracket through access hole in FS 306 bulkhead
and remove bolts securing pulley gang to bulkhead. Remove gang assembly from airplane.
(l)
Remove cotter pins and washers securing pulley guard pins to empennage pulley gang
bracket and remove pins.
(m) Cut safety wire securing cables to actuation pulleys.
(n) At access hole CF5, pull rudder and elevator cables through. Remove cables from airplane.
Installation - Empennage Pulley Gang
(a) Prior to empennage pulley gang installation, secure rudder and elevator cables to actuation pulleys with safety wire and insert pulley guard pins, install washers and cotter pins
(b) Route rudder and elevator cables through access hole RE1 forward to access hole CF5.
(c)
Insert pulley gang into empennage and position gang assembly over holes in FS 306 bulkhead. Install bolts securing pulley gang to bulkhead.
(d) Screw rudder push/pull rod onto rod end attached to rudder actuation pulley and tighten
jam nut.
(e) Screw elevator push/pull rod onto rod end attached to elevator actuation pulley and
tighten jam nut.
(f)
Install bolt, spacer, washer, nut, and cotter pin securing rudder push/pull rod to rudder bellcrank.
EFFECTIVITY:
Serials 1005 thru 1306
27-20
Page 19
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
(g)
(3)
27-20
Page 20
15 Jun 2010
MODEL SR20
Install bolt, washers, nut, and cotter pin securing elevator push/pull rod to elevator bellcrank.
(h) Install screw, washer, and nut securing pulley gang support brace to empennage.
(i)
Install rudder and elevator cables. (Refer to 27-20) (Refer to 27-20)
(j)
Install access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
(k)
Install carpet and access panel CF5. (Refer to 06-00)
Inspection/Check - Empennage Pulley Gang
(a) Remove fuselage access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
(b) Verify positive clearance of pulleys through full range of rudder and elevator movement.
(c)
Verify positive clearance between pitch trim cartridge and FS 306 bulkhead through full
range of elevator and trim motor operation.
(d) Verify minimum rod end thread engagement of 0.312 inch (0.79 cm).
(e) Verify proper safety wire and cotter pin installation on all fasteners.
(f)
Install fuselage access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
EFFECTIVITY:
Serials 1005 thru 1306
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
H. Empennage Bellcranks - Serials 1307 & subs (See Figure 27-208)
(1)
Removal - Empennage Bellcranks
(a) Remove carpet and access panel CF5 from baggage compartment floor. (Refer to 06-00)
Note:
Prior to removing turnbuckles, position spacer block between rudder pedals
and firewall to support spring tension.
(b)
(c)
(d)
(2)
At access panel CF5, remove turnbuckles from rudder and elevator cables.
Remove fuselage access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
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 CF5, pull rudder and elevator cables through. Remove cables airplane.
Installation - Empennage Bellcranks
(a) Route rudder and elevator cables through access hole RE1 forward to access hole CF5.
(b) Insert bellcranks into empennage and position bulkhead shaft through bulkhead and bellcranks.
Note:
Ensure bolt engages threaded insert to within 0.063 inch (1.6 mm) of flush
with bulkhead surface or protrudes past bulkhead surface.
(c)
(d)
(e)
(3)
Install bolt and washer securing bulkhead shaft to bulkhead.
Install plug covering end of bulkhead shaft.
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 cotter pin securing rudder push/pull rod to rudder bellcrank.
(h) Install bolt, washers, nut, and cotter pin securing elevator push/pull rod to elevator bellcrank.
(i)
Install rudder and elevator cables. (Refer to 27-20), (Refer to 27-20)
(j)
Install access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
(k)
Install carpet and access panel CF5. (Refer to 06-00)
Inspection/Check - Empennage Bellcranks
(a) Remove fuselage access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
(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.
EFFECTIVITY:
Serials 1307 & subs
27-20
Page 21
15 Jun 2010
CIRRUS
(d)
(e)
(f)
27-20
Page 22
15 Jun 2010
AIRPLANE MAINTENANCE MANUAL
Verify minimum rod end thread engagement of 0.313 inch (0.79 cm).
Verify proper safety wire and cotter pin installation on all fasteners.
Install fuselage access panels RE1, RE2, LE1, and LE2. (Refer to 06-00)
EFFECTIVITY:
Serials 1307 & subs
MODEL SR20
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
4
1
2
2
9
13
3
1
2
5
6
8
7
1
2
BULKHEAD
F.S. 186 (REF)
LEGEND
1. Cotter Pin
2. Washer
3. Castellated Nut
4. Spacer
5. Bolt
6. Pulley Bracket
7. Backing Plate
8. Pin
9. Pulley
SR20_MM27_1168B
Figure 27-206
Rudder/Elevator Pulley Gang
EFFECTIVITY:
All
27-20
Page 23
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
ELEVATOR BELL CRANK
(REF)
5
2
ELEVATOR
HINGE (REF)
5
2
5
2
2
2
1
7
5
2
3
2
1
3
9
8
5
2
RUDDER
ASSY (REF)
7
4
3
2
1
2
7
2
1
6
2
3
10
7
2
1
6
BULKHEAD
F.S. 306 (REF)
11
LEGEND
1. Cotter Pin
2. Washer
3. Castellated Nut
4. Spacer
5. Bolt
6. Nut
7. Rod End
8. Elevator Push/Pull Rod
9. Rudder Push/Pull Rod
10. Support Brace
11. Screw
Serials 1005 thru 1300, 1302 thru 1306.
Figure 27-207
Empennage Pulley Gang - Serials 1005 thru 1306 (Sheet 1 of 2)
27-20
Page 24
15 Jun 2010
EFFECTIVITY:
Serials 1005 thru 1306
SR20_MM27_1169D
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
BULKHEAD
F.S. 306 (REF)
14
1
2
5
6
13
5
2
14
16
12
1
2
4
11
16
3
12
1
17
15
2
18
6
12
10
LEGEND
1. Cotter Pin
2. Washer
3. Castellated Nut
4. Spacer
5. Bolt
6. Nut
10. Support Brace
11. Screw
12. Jam Nut
13. Pulley Bracket
14. Pin
15. Pulley
16. Stop Bolt
17. Pulley Stop
18. Support Rod Weldment
6
2
4
15
2
11
17
Serials 1005 thru 1300, 1302 thru 1306.
SR20_MM27_1179C
Figure 27-207
Empennage Pulley Gang - Serials 1005 thru 1306 (Sheet 2 of 2)
EFFECTIVITY:
Serials 1005 thru 1306
27-20
Page 25
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
AFT ELEVATOR
BELLCRANK
(REF)
1
2
3
2
11
5
1
4
2
8
10
RUDDER
ASSY (REF)
2
3
1
2
4
9
5
4
5
2
1
2
2
1
7
3
BULKHEAD
F.S. 306 (REF)
6
3
LEGEND
1. Bolt
2. Washer
3. Rod End
4. Castellated Nut
5. Cotter Pin
6. Rudder Bellcrank
7. Elevator Bellcrank
8. Elevator Push/Pull Rod
9. Rudder Push/Pull Rod
10. Shaft
11. Plug
5
2
4
SR20_MM27_1660
Figure 27-208
Empennage Bellcranks - Serials 1307 & subs
27-20
Page 26
15 Jun 2010
EFFECTIVITY:
Serials 1307 & subs
CIRRUS
I.
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Yaw Trim Cartridge (See Figure 27-205)
(1)
(2)
(3)
Removal - Yaw Trim Cartridge
(a) Remove left mid console circuit breaker trim. (Refer to 25-10)
(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 cotter pin securing trim cartridge push/pull rod to left torque
tube actuation arm.
(b) Install bolt, washers, bushing, spacers, nut, and cotter pin securing trim cartridge to console bracket.
(c)
Perform Inspection/Check - Yaw Trim Cartridge. (Refer to 27-20)
(d) Install left mid console circuit breaker trim. (Refer to 25-10)
Inspection/Check - Yaw Trim Cartridge
(a) Verify correct rudder system rigging. (Refer to 27-20) (Refer to 27-20)
(b) Verify yaw trim cartridge is adjusted to hold rudder in neutral position ±1°.
(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 0.312 inch (0.79 cm).
(e) Verify proper installation of safety wires and cotter pins on all fasteners.
J. 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 5540)
EFFECTIVITY:
All
27-20
Page 27
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
K. Rudder-Aileron Interconnect - Serials 1005 thru 1885 (See Figure 27-209)
(1)
(2)
(3)
Removal - Rudder-Aileron Interconnect
(a) Remove rear passenger compartment carpet. (Refer to 25-10)
(b) Remove cabin floor access panel 3C. (Refer to 06-00)
(c)
Remove passenger seats. (Refer to 25-10)
(d) Remove nuts, washers, cable clamps, and screws securing bungee cord to RH aileron
cable.
(e) Remove nut, washers, spacer, cable clamps, and bolt securing RH rudder cable to rudderaileron interconnect arm.
(f)
Remove washers, bolts, and shim securing interconnect bracket to LH longeron and
remove rudder-aileron interconnect arm from airplane.
Disassembly - Rudder-Aileron Interconnect
(a) Remove nut, washers, bungee clamp, and bolt securing bungee cord to rudder-aileron
interconnect arm.
Assembly - Rudder-Aileron Interconnect
Note:
(a)
(b)
Verify bungee cord fits to contour of channel between clamps.
Position upper and lower bungee clamps over center of bungee cord.
Position bungee clamps to end of rudder-aileron interconnect arm so that arm is located
between upper and lower bungee clamps.
Note:
If required, add an additional washer to ensure correct thread engagement.
(c)
(4)
Install bolt, washers, bungee clamps, nut, and cotter pin securing bungee cord to rudderaileron interconnect arm. Torque bolt to 45 ±2 in-lb (5.1 ±0.2 Nm).
Installation - Rudder-Aileron Interconnect
(a) Install shim, bolts, and washers securing interconnect bracket to LH longeron.
CAUTION:
(b)
To prevent interference with adjacent control cables, forward edge of rudder-aileron interconnect arm must be oriented 90° +5°/-0° to the control cables.
Verify forward edge of rudder-aileron interconnect arm is positioned at 90° +5°/-0° perpendicular to the control cables.
Note:
(c)
Install bolt, cable clamps, spacer, washers, and nut securing RH rudder cable to rudderaileron interconnect arm.
CAUTION:
(d)
(e)
(f)
(g)
(h)
(i)
27-20
Page 28
15 Jun 2010
To increase clearance between LH and RH rudder cables, install rudder
cable clamps so that RH rudder cable is inboard of cable clamp attach bolt.
If not oriented properly, the cable clamps may interfere with attaching hardware at the bungee clamps. Verify cable clamps are positioned so that
screws are oriented vertically.
Install screws, cable clamps, washers, and nuts securing bungee cord adel clamps to RH
aileron cable. Torque nuts between 45 - 50 in-lb (5.1 - 5.6 Nm).
Perform Adjustment/Test - Rudder-Aileron Interconnect. (Refer to 27-20)
Perform Inspection/Check - Rudder-Aileron Interconnect. (Refer to 27-20)
Install passenger seats. (Refer to 25-10)
Install cabin floor access panel 3C. (Refer to 06-00)
Install rear passenger compartment carpet. (Refer to 25-10)
EFFECTIVITY:
Serials 1005 thru 1885
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
RUDDER-AILERON
INTERCONNECT ARM
(REF)
5
8
12
4
LH LONGERON
(REF)
5
4
4
7
3
14
7
4
RUDDER-AILERON
INTERCONNECT ARM
(REF)
11
Serials 1005 thru 1010.
7
13
LH LONGERON
(REF)
9
2
4
14
4 5
12
1
6
4
5
ELEVATOR
CABLE (REF)
RIGHT RUDDER
CABLE (REF)
11
LEFT RUDDER
CABLE (REF)
10
11
13
LEFT AILERON
CABLE (REF)
4
12
10
RIGHT AILERON
CABLE (REF)
Serials 1005 thru 1877, 1879 thru 1885.
NOTE
It is allowable to add an additional washer to ensure correct thread engagement.
If not oriented properly, the cable clamps may interfere with attaching hardware at the
bungee clamp. Verify cable clamps are positioned so that screws are oriented vertically.
Torque nut between 45 - 50 in-lb (5.1 - 5.6 Nm).
Do not install washer below head of screw. Only one washer is required at nut.
LEGEND
1. Bungee
2. Adel Clamp
3. Spacer
4. Washer
5. Bolt
6. Screw
7. Bushing
8. Cotter Pin
9. Shim
10. Turnbuckle
11. Cable Clamp
12. Nut
13. Cable Tie
14. Bungee Clamp
SR20_MM27_1171H
Figure 27-209
Rudder-Aileron Interconnect Installation - Serials 1005 thru 1885
EFFECTIVITY:
Serials 1005 thru 1885
27-20
Page 29
15 Jun 2010
CIRRUS
(5)
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
Adjustment/Test - Rudder-Aileron Interconnect (See Figure 27-2010)
Note:
Improper rudder-aileron interconnect adjustment may effect autopilot roll trim and
roll performance.
Verify that ailerons and rudder are properly rigged in accordance with 27-10 and
27-20 to ensure proper flight control surface operation prior to modification of rudder-aileron interconnect system. (Refer to 27-10) (Refer to 27-20)
The interconnect must be adjusted so that full rudder application will meet the requirements of
14 CFR 23.177 or optionally:
full LH rudder deflection causes 5° minimum, 8° maximum RH aileron trailing edge down;
full RH rudder deflection causes 5° minimum, 8° maximum LH aileron trailing edge down.
To adjust the interconnect, perform the following procedure:
(a)
Acquire necessary tools, equipment, and supplies.
Description
WS 144 Rigging Template
(b)
(c)
(d)
(e)
(f)
(g)
(h)
(i)
(j)
(k)
(l)
(m)
(n)
27-20
Page 30
15 Jun 2010
P/N or Spec.
13057-109
Supplier
Cirrus Design
Duluth, MN 55811
218-727-2737
Purpose
Aileron rigging.
Remove rear passenger compartment carpet. (Refer to 25-10)
Remove cabin floor access panel 3C. (Refer to 06-00)
Verify rudder and aileron are in the neutral position.
Verify rudder-aileron interconnect arm is perpendicular to the control cables.
Verify the forward aileron bungee clamp is positioned aft, against the swage end of the
cable terminal.
Verify the aft aileron bungee clamp is positioned forward, against the swage end of the
cable terminal.
Position WS 144 rigging template on wing.
Verify full LH rudder deflection causes 5° - 8° RH aileron trailing edge down.
Verify full RH rudder deflection causes 5° - 8° LH aileron trailing edge down.
If downward motion is less than 5°, too much slack exists. Reduce slack by pulling bungee
cord from forward and aft aileron cable clamps away from interconnect arm.
If downward motion is greater than 8°, too much tension exists. Reduce tension by pulling
bungee cord from forward and aft aileron cable clamps toward interconnect arm.
If excess bungee cord exists at ends:
1
Fold bungee cord end towards the cable clamps and install cable tie securing bungee cord end to itself.
2
Position excess bungee cord below cable clamps to eliminate any interference with
bottom of interconnect arm.
3
Ensure cable tie is tightly secured and snug against the clamps.
4
Repeat with opposite end of bungee cord.
With rudder and aileron neutral, verify that at full aileron trim travel, the bungee cord does
not interfere with trim travels or cause rudder movement.
1
To ensure bungee cord is not interfering with full RH trim travels, trim roll trim to full
right. Verify rudder does not move.
EFFECTIVITY:
Serials 1005 thru 1885
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2
(6)
To ensure bungee cord is not interfering with full LH trim travels, trim roll trim to full
left. Verify rudder does not move.
(o) Verify that steady rudder application will move the ailerons the required travel.
(p) Cycle RH aileron cable forward and aft several times. Verify cable clamps remain positioned so that screws are oriented vertically. If clamp orientation is altered due to cable
rotation, loosen screw, correct clamp orientation, and re-torque nut.
(q) Install cabin floor access panel 3C. (Refer to 06-00)
(r)
Install rear passenger compartment carpet. (Refer to 25-10)
Inspection/Check - Rudder-Aileron Interconnect
(a) Verify interconnect adjustment will meet the requirements of 14 CFR 23.177 or optionally:
1
full LH rudder deflection causes 5° minimum, 8° maximum RH aileron trailing edge
down.
2
full RH rudder deflection causes 5° minimum, 8° maximum LH aileron trailing edge
down.
(b) Verify bungee cord ends are folded back upon themselves and secured with cable ties.
(c)
Verify cable ties are tightly secured and do not slide on bungee cords.
(d) Verify positive bungee cord clearance under slack and full cross control movement.
(e) With full LH rudder and full RH aileron applied, verify that in crossed controls condition that
attaching hardware at bungee clamp does not interfere with attaching hardware at aileron
cable clamps.
(f)
With full RH rudder and full LH aileron applied, verify that in crossed controls condition that
attaching hardware at bungee clamp does not interfere with attaching hardware at aileron
cable clamps.
EFFECTIVITY:
Serials 1005 thru 1885
27-20
Page 31
15 Jun 2010
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
1
RUDDER-AILERON
INTERCONNECT ARM
(REF)
1
90°
+5°
-0°
RH RUDDER
CABLE (REF)
LH RUDDER
CABLE (REF)
Serials 1005 thru 1877, 1879 thru 1885.
SWAGE
(REF)
CABLE
TERMINAL
(REF)
NOTE
Verify adel clamps are parallel to cable clamps.
Install cable clamp against the swage end of the cable terminal. Ensure cable clamps are
not installed over tapered end of swage.
Fold bungee cord end towards the clamp and install cable tie securing bungee cord end
to itself. Position excess bungee cord below cable clamps to eliminate any interference
with bottom of interconnect arm.
Ensure cable tie is tightly secured and snug against the clamps.
To prevent interference with adjacent control cables, forward edge of rudder-aileron
interconnect arm must be oriented 90° +5°/-0° to the control cables.
RH rudder cable only: To facilitate increased clearance between LH and RH rudder
cables, install rudder cable clamps so that RH rudder cable is inboard of cable clamp attach bolt.
Figure 27-2010
Rudder-Aileron Interconnect Adjustment/Test - Serials 1005 thru 1885
27-20
Page 32
15 Jun 2010
EFFECTIVITY:
Serials 1005 thru 1885
LEGEND
1. Cable Tie
SR20_MM27_2644B