Cirrus SR20 Manual de usuario
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
57-10
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WING STRUCTURE
1. DESCRIPTION
The wing is constructed in a conventional spar, rib, and shear section arrangement. The upper and lower
skins are bonded to the spar, ribs, and aft shear web forming a torsion box that carries all of the wing bend-
ing and torsion loads. The rear shear webs are similar in construction but do not carry through the fuse-
lage.
The wing spar is manufactured in one piece and is continuous from wing tip to wing tip. The wing spar
passes under the fuselage below the two front seats and is attached to the fuselage in two locations. Lift
and landing loads are carried by the single carry-through spar, plus a pair of rear shear webs (one on each
wing) attached to the fuselage. The wing spar is laminated epoxy/glass fiber (Serials 1005 thru 1885) or
laminated epoxy/carbon fiber (Serials 1886 & subs) in a C-section.
The wing’s belly closeout panel is bonded (Serials 1005 thru 1422) or bolted (Serials 1423 & subs) to the
fuselage structure after wing attachment and provides a continuous load path along the bottom of the fuse-
lage.
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
15 Jun 2010
2. MAINTENANCE PRACTICES
A. Wing Assembly
(1) Removal - Wing Assembly
(a) Switch BAT 1, BAT 2, and AVIONICS master switches to OFF position.
(b) Pull all circuit breakers.
(c) Ensure parking brake is in OFF position and wheels are blocked.
(d) Remove engine cowling. (Refer to 71-10)
(e) Disconnect battery 1. (Refer to 24-30)
(f) Set fuel selector valve to OFF position.
(g) De-fuel airplane. (Refer to 12-10)
(h) Remove ailerons. (Refer to 57-50)
(i) Remove flaps. (Refer to 57-50)
(j) Perform Inspection/Check - Tip-to-Tip Measurement. Retain obtained values for compari-
son following reassembly. (Refer to 57-10)
(k) Perform Inspection/Check - Wing Angle of Incidence and Decalage Measurement. Retain
obtained values for comparison following reassembly. (Refer to 57-10)
(l) Remove main gear fairings. (Refer to 32-10)
(m) Remove nose gear fairing. (Refer to 32-20)
CAUTION: Ensure hands are clean while working with interior components.
(n) Remove crew and passenger seats. (Refer to 25-10)
(o) Remove cabin floor covering. (Refer to 25-10)
(p) Remove access panels CF2L, CF2R, CF3R, CF3C, CF3L, and CF5. (Refer to 06-00)
(q) Remove screws securing circuit breaker panel closed.
(r) Serials 1148 thru 1422 w/ Century HSI: Disconnect HSI gyro slaving amplifier. (Refer to
34-50)
1Disconnect HSI gyro slaving amplifier wire from gyro slaving amplifier mounted to
access panel CF2R.
2Stow HSI gyro slaving amplifier wire forward.
(s) Remove kick plates. (Refer to 25-10)
(t) Remove cabin trim panels from spar tunnel forward. (Refer to 25-10)
(u) Drain brake hydraulic fluids. (Refer to 12-10)
(v) Remove wing root fairings. (Refer to 53-50)
(w) Disassemble aileron connections. (Refer to 27-10)
1At access hole CF4C, disconnect aft aileron cable turnbuckle.
2At access hole CF4C, remove cotter pin, washer, and cable retainer clevis pin from
LH and RH kickout pulley assembly and remove cable from pulley.
Note: To facilitate re-installation, mark location of interconnect bungee
clamps on RH aileron cable.
3Serials 1005 thru 1885: At access hole CF3C, disconnect rudder/aileron intercon-
nect bungee from RH aileron cable at forward and aft locations. (Refer to 27-20)
4At access hole CF3C, disconnect forward LH and RH aileron turnbuckles.
5Stow disconnected cables to wing and forward of wing spar tunnel.
(x) Disassemble rudder connections. (Refer to 27-20)
1At access hole CF5, disconnect LH and RH rudder cable turnbuckles.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
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EFFECTIVITY:
Note: Serials 1005 thru 1885: To facilitate re-installation, mark location of
interconnect bungee clamps on RH rudder cable.
2Serials 1005 thru 1885: At access hole CF3C, disconnect rudder/aileron intercon-
nect bungee from RH rudder cable. (Refer to 27-20)
3Stow disconnected cables aft and forward of wing spar tunnel.
(y) Disassemble elevator connections. (Refer to 27-30) (Refer to 27-30)
1At access hole CF5, disconnect LH and RH elevator cable turnbuckles.
2Stow disconnected cables aft and forward of wing spar tunnel.
(z) Remove flap torque tubes. (Refer to 27-50)
1At access hole CF4C, remove bolt, washers, spacer, and nut securing torque tubes
to torque tube coupler.
2At wing root, remove bolt, washers, spacer, and nut securing thrust collar and torque
tube end fitting to torque tube. Repeat on opposite side.
3Remove LH and RH torque tubes.
(aa) Serials 1005 thru 1885: Disconnect aft fuselage wiring harness.
CAUTION: Label all wires and pins before disconnecting to facilitate re-installation.
1At access hole CF2R, disconnect J666, J667, and J697.
2At access hole CF2R, locate ground wire PG650-12N terminal ring and remove
attaching hardware.
3Serials 1005 thru 1422: At access holes CF2R and CF3R, use a mirror to locate and
remove adel clamps and cable ties securing aft fuselage wiring harness forward and
aft of the wing spar tunnel.
4Stow disconnected wires forward and aft of the wing spar tunnel.
(ab) Serials 1886 & subs: Disconnect aft fuselage wiring harness.
CAUTION: Label all wires and pins before disconnecting to facilitate re-installation.
1At access hole CF3R, disconnect J666, J667, and J1049.
2At access hole CF3R, locate ground wire PG650-12N terminal ring and remove
attaching hardware.
3Stow disconnected wires forward and aft of the wing spar tunnel.
(ac) Serials 1337 thru 1422 w/ PFD: Disconnect magnetometer cable.
1At access hole CF3R, disconnect jack J729 for magnetometer cabling and remove
cable ties.
2De-pin plug P729 to enable magnetometer cabling to pass forward through spar tun-
nel bulkhead connector.
3De-pin jack J729 to enable magnetometer cabling to pass aft through fuselage bulk-
head connector.
4Stow disconnected wires forward of the wing spar tunnel and at wing.
(ad) Serials 1423 & subs: Disconnect magnetometer cable.
1At access hole CF3R, disconnect jack J729 for magnetometer cabling and remove
cable ties.
2Route plug P729 on magnetometer cabling forward of wing spar tunnel.
3Remove backshell from jack J729 to enable magnetometer cabling to pass aft
through fuselage bulkhead connector.
4Stow disconnected wires forward of the wing spar tunnel and at wing.
(ae) Serials 2065 & subs w/ Air Conditioning: Disconnect wiring harness for condenser.
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
19 Sep 2010
1At access hole CF3R, disconnect plug P1005 for condenser cabling and remove
cable ties.
2Remove backshell from plug P1005 to enable condenser cabling to pass forward
through spar tunnel bulkhead connector.
3Stow disconnected wires forward and aft of the wing spar tunnel.
(af) Serials 1005 thru 1885: Disconnect wiring harnesses for wing.
CAUTION: Label all wires and pins before disconnecting to facilitate re-installation.
1At access hole CF4L, disconnect J300 from connector on LH longeron and remove
cable ties.
2At access hole CF4R, disconnect J400 from connector on RH longeron and remove
cable ties.
3De-pin J300 and J400 to enable wires to pass through fuselage bulkhead connector.
4Stow disconnected wires at each wing and forward of the wing spar tunnel.
(ag) Serials 1886 & subs: Disconnect wiring harnesses for wing.
CAUTION: Label all wires and pins before disconnecting to facilitate re-installation.
1At access hole CF2L, disconnect J300 from connector and remove cable ties.
2At access hole CF2R, disconnect J400 from connector and remove cable ties.
3De-pin J300 and J400 to enable wires to pass through fuselage bulkhead connector.
4Stow disconnected wires at each wing and forward of the wing spar tunnel.
(ah) Serials 1005 & subs w/ Stormscope System: Disconnect wiring harness for Stormscope.
1At access hole CF2R, disconnect J668 and remove cable ties.
2Serials 1337 & subs w/o PFD: At access hole CF2R, disconnect J557 and remove
cable ties.
3Serials 1337 & subs w/o PFD: At access hole CF2R, disconnect P698 and remove
cable ties.
4Stow disconnected wires aft and forward of the wing spar tunnel.
(ai) Disassemble Pitot-Static System. (Refer to 34-10)
1Remove fittings on pitot-static lines to enable lines to pass through fuselage grom-
met.
2At access hole CF3L, disconnect Pitot-Static System lines.
3Stow pitot line aft of wing spar tunnel and to wing.
4Stow static line aft of wing spar tunnel.
(aj) Serials 1005 thru 1885: Disconnect ELT remote control panel indicator connection.
1On circuit breaker panel, disconnect ELT remote control panel indicator connector
and grounding terminal ring. (Refer to 25-60)
2Remove cable ties and stow ELT remote control panel indicator cable aft of wing
spar tunnel.
(ak) Serials 1268 thru 1885: Disconnect battery 2.
1On circuit breaker panel, disconnect battery 2 power cable. (Refer to 24-30)
2On RH side of forward longerons, disconnect battery 2 ground wire from P602 con-
nector secured to firewall. (Refer to 24-30)
3Remove cable ties and stow battery 2 power cable and ground wire aft of wing spar
tunnel.
(al) Serials 1886 & subs: Disconnect battery 2.
1At access panel CF3R, disconnect jack J847 for battery 2 and remove cable ties.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
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EFFECTIVITY:
2At access panel CF3R, de-pin jack J847 to enable battery 2 wiring to pass through
spar tunnel bulkhead connector.
3Stow disconnected wires aft and forward of the wing spar tunnel.
(am) Serials 1005 thru 1885: Disconnect marker beacon antenna.
1Below radio rack, disconnect marker beacon antenna cable. (Refer to 34-30)
2Remove cable ties and stow marker beacon antenna cable aft of wing spar tunnel.
(an) Serials 1005 thru 1885: Disconnect COM2 antenna.
1At access panel CF5, disconnect COM 2 antenna cable from COM 2 antenna.
(Refer to 34-50)
2Remove cable ties and stow COM 2 antenna cable forward of wing spar tunnel.
(ao) Serials 1005 thru 1885: Disconnect VOR/LOC antenna.
Note: Ensure VOR/LOC antenna cable is retained above tail when remov-
ing antenna.
1Remove VOR/LOC antenna. (Refer to 34-50)
2Tie string to VOR/LOC antenna cable and route down tail. Tie upper end of string to
upper tail. Untie string at RH empennage access panel and stow in area to facilitate
re-installation of antenna cable.
3Remove cable ties and stow VOR/LOC antenna cable forward of wing spar tunnel.
(ap) Center-aft of main wing spar, disconnect fuel supply and return lines. (Refer to 28-20)
(aq) Disassemble Stall Warning System connections. (Refer to 27-31)
1At access hole CF2R, disconnect stall warning line to wing.
2Remove fitting on stall warning line to enable line to pass through fuselage bulkhead
connector.
3Remove cable ties and stow stall warning line into the wing.
(ar) Serials 1005 thru 1885: Disconnect environmental ducts. (Refer to 21-20)
1Acquire necessary tools, equipment, and supplies.
2Serials 1005 thru 1632, 1634 thru 1636: Adjacent to CF2L and CF2R access holes,
pry and remove adhesive securing environmental duct to fresh air inlet tee on LH
and RH fuselage wall.
3Serials 1005 thru 1632, 1634 thru 1636: Disconnect environmental ducts from fresh
air inlet tee(s).
4Serials 1633, 1637 & subs: Adjacent to CF2R access hole, pry and remove adhe-
sive securing environmental duct to RH fuselage wall.
(as) Serials 1005 thru 1422 w/ Sandel HSI: Disconnect HSI gyro slaving amplifier and remote
gyro. (Refer to 34-50)
1At access hole CF2R, disconnect data cable from HSI gyro slaving amplifier.
2At access hole CF3R, disconnect data cable HSI remote gyro.
3Stow data cables forward of wing spar tunnel.
(at) Serials 1005 thru 1422: Remove belly closeout panel. (See Figure 57-101)
Description P/N or Spec. Supplier Purpose
Putty Knife - Any Source Prying
Utility Knife - Any Source Cutting
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
19 Sep 2010
1Acquire necessary tools, equipment, and supplies.
2From beneath the airplane looking up through the gap between LH wing root and
fuselage, determine where the forward and aft plane of the wing spar intersects with
the belly closeout panel and mark. Repeat on RH side.
3To prevent possible damage to main spar, offset forward mark 0.25 inch (0.64 cm)
forward, and aft cut line 0.25 inch (0.64 cm) aft.
4At offset marks, use chalk snap line to locate cut lines across width of belly closeout
panel.
CAUTION: Ensure all cabling, wires, and tubes routed through wing spar are
removed before cutting into belly closeout panel.
Damage to the main spar may render the wing unusable. Do not cut
into the wing spar, wing spar tunnel, or bonding flanges.
If spar is damaged, contact Cirrus Design Customer Service for dis-
position.
5Using die grinder, cut belly closeout panel at marked lines.
Note: If screws are embedded in adhesive, it may be necessary to cut
screws and drill them out.
6Use magnet to locate mounting hardware and chisel to expose screw heads.
7At determined screw head locations, sand paint and bodywork off.
8Remove hardware fastening belly closeout panel to fuselage.
CAUTION: Do not damage underlying laminate.
9Using chisel, remove remaining portion of belly closeout panel from fuselage.
(au) Serials 1423 thru 2029: Remove belly closeout panel. (See Figure 57-101)
1Acquire necessary tools, equipment, and supplies.
Description P/N or Spec. Supplier Purpose
Chalk Snap Line - Any Source Locate Cut Lines
Die Grinder - Any Source Cutting
Metal Cut-Off Wheel and Arbor 2.0 inches (5.1 cm) Any Source Cutting
Magnet - Any Source Locate Hard-
ware
Blunt-Edged Chisel - Any Source Cutting
Sandpaper 400-grit Any Source Abrasion
Description P/N or Spec. Supplier Purpose
Blunt-Edged Chisel - Any Source Cutting
Die Grinder - Any Source Cutting
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
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EFFECTIVITY:
Note: The two middle mounting screws on the forward and aft sides of belly
closeout panel are covered by a strip of expanded metal mesh (EMM)
for lightning protection. The screw heads must be located and
exposed prior to belly closeout panel removal.
2At forward and aft belly closeout panel seam, sand at seam along row of installation
screws to locate adjacent screws covered by EMM.
3Mark cut lines on EMM where EMM overlaps the space between belly closeout
panel and fuselage.
CAUTION: Ensure all cabling, wires, and tubes routed through wing spar are
removed before cutting through EMM.
Damage to the main spar may render the wing unusable. Do not cut
into the wing spar, wing spar tunnel, or bonding flanges.
If spar is damaged, contact Cirrus Design Customer Service for dis-
position.
4Using die grinder, carefully cut through EMM at marked lines.
5Remove screws, washers, and nuts securing belly closeout panel to fuselage.
(av) Serials 2030 & subs: Remove screws, washers, and nuts securing belly closeout panel to
fuselage. (See Figure 57-101)
Metal Cut-Off Wheel and Arbor 2.0 inches (5.1 cm) Any Source Cutting
Sandpaper 80-grit Any Source Abrasion
Description P/N or Spec. Supplier Purpose
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
15 Jun 2010
Figure 57-101
Belly Closeout Panel Removal - Serials 1005 thru 1422 (Sheet 1 of 3)
SR20_MM57_1653A
0.25 inch
Offset mark away from wing spar 0.25 inch (0.64 cm).
NOTE
Mark where forward and aft plane of wing spar
intersects with belly closeout.
Mark cut lines across belly closeout.
AFT PLANE OF
WING SPAR
FORWARD PLANE
OF WING SPAR
WING SPAR
BELLY CLOSEOUT
Serials 1005 thru 1422.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
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Serials 1423 thru 2029
EFFECTIVITY:
Figure 57-101
Belly Closeout Panel Removal - Serials 1423 thru 2029 (Sheet 2 of 3)
SR20_MM57_1875B
LEGEND
1. Belly Closeout Panel
2. Screw
3. Washer
4. Nut
4
2
3
CUT LINE
FUSELAGE
NOTE
Mark cut lines where EMM overlaps space between
belly closeout panel and fuselage.
EMM
FUSELAGE
1
WING SPAR
Sand at belly closeout panel seam along row of installation
screws to locate adjacent screws covered by EMM.
Serials 1423 thru 2029.
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR20
15 Jun 2010
Figure 57-101
Belly Closeout Panel Removal - Serials 2030 & subs (Sheet 3 of 3)
SR20_MM57_3188
LEGEND
1. Belly Closeout Panel
2. Screw
3. Washer
4. Nut
4
2
3
FUSELAGEFUSELAGE
1
WING SPAR
Serials 2030 & subs.
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