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