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Cirrus SR20 Maintenance Manual
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Cirrus SR20 Maintenance Manual

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Download this manual See also: Pilot Operating Handbook, Maintenance Manual
C I R R U S
A I R P L A N E M A I N T E N A N C E M A N U A L
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.
EFFECTIVITY:
All
WING STRUCTURE
M O D E L S R 2 0
57-10
Page 1
15 Jun 2010

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Summary of Contents for Cirrus SR20

  • Page 1 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WING STRUCTURE 1.

  • Page 2: Maintenance Practices

    C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 2.
  • Page 3 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Note: Serials 1005 thru 1885: To facilitate re-installation, mark location of interconnect bungee clamps on RH rudder cable.
  • Page 4 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 At access hole CF3R, disconnect plug P1005 for condenser cabling and remove cable ties.
  • Page 5 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 At access panel CF3R, de-pin jack J847 to enable battery 2 wiring to pass through spar tunnel bulkhead connector.
  • Page 6 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. Using die grinder, cut belly closeout panel at marked lines.
  • Page 7 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. Using die grinder, carefully cut through EMM at marked lines.
  • Page 8 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 0.25 inch WING SPAR BELLY CLOSEOUT...
  • Page 9 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WING SPAR CUT LINE FUSELAGE...
  • Page 10 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WING SPAR FUSELAGE FUSELAGE...
  • Page 11 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 (aw) Support wing and fuselage.
  • Page 12 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 APPROVED HOISTING METHOD ENGINE MOUNT...
  • Page 13 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 (ax) Detach wing assembly.
  • Page 14 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 FOAM PAD FUSELAGE CRADLE...
  • Page 15 Installation - Wing Assembly (See Figure 57-104) WARNING: Installation of the wing assembly requires a test flight performed by a Cirrus Design certified test pilot. Contact Cirrus Design prior to performing mainte- nance to schedule test flight. Acquire necessary tools, equipment, and supplies.
  • Page 16 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 AFT ATTACH BRACKET, FUSELAGE (REF) AFT ATTACH FITTING (REF)
  • Page 17 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 APPROVED HOISTING METHOD ENGINE MOUNT...
  • Page 18 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Remove wing supports and hoisting straps.
  • Page 19 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Below radio rack, connect marker beacon antenna cable.
  • Page 20 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Serials 1423 &...
  • Page 21 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 (ak) Verify correct orientation of wiring harnesses, tubing, and flight control cables from belly closeout panel opening.
  • Page 22 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 LEGEND 1.
  • Page 23 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 LEGEND 2.
  • Page 24 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 (al) Serials 1005 thru 1422: Install belly closeout panel.
  • Page 25 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Using 0.25 inch (0.64 cm) bit, match drill holes in belly closeout panel.
  • Page 26 (an) Serials 1423 & subs w/ new belly closeout panel: Install belly closeout panel. Acquire necessary tools, equipment, and supplies. P/N or Description Supplier Purpose Spec. Mylar Template T10178 Cirrus Design Transfer S/N 10716 Duluth, MN 55811 218-727-2737 Masking Tape Any Source Adhere Spray Adhesive...
  • Page 27 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Using 0.5 in (1.27 cm) countersunk bit, drill holes so installation screws will be flush with belly closeout panel.
  • Page 28 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 ADHESIVE ADHESIVE FUSELAGE...
  • Page 29 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 BELLY CLOSEOUT SUPPORT (REF) BOTTLE JACK...
  • Page 30 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 SLIT / VENT NOTE Wrap outlet with breather material to prevent scuffing.
  • Page 31 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WING SPAR FUSELAGE LEGEND...
  • Page 32 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 (ao) Serials 1005 thru 2029: Install Expanded Metal Mesh (EMM) lightning protection.
  • Page 33 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 REPLACEMENT EMM SANDED AREA 1.00 inch...
  • Page 34 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 EXISTING EMM REPLACEMENT EXISTING EMM...
  • Page 35 (bs) Perform ELT functional inspection in accordance with 14 CFR 91.207. WARNING: Installation of the wing assembly requires a maintenance check flight performed by a Cirrus Design authorized test pilot. Contact Cirrus Design prior to performing maintenance to schedule check flight. (bt) Perform Cirrus Design-Authorized Flight Test.
  • Page 36 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 CAUTION: Ensure that bonding and curing procedures are followed exactly as defined for actual belly closeout panel installation.
  • Page 37 (See Figure 57-109) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Ruler Gauges (Block), T6859-7 Cirrus Design Leveling LH and RH Duluth, MN 55811 218-727-2737 Transit Level Any Source Leveling Level airplane laterally with digital level using engine mount weldment.
  • Page 38 Verify difference in measurement locations at LH and RH ruler gauge blocks is within toler- ance of 2.0 inches (5.0 cm). Record obtained values. LH 25% Chord RH 25% Chord Variance If measurement difference is not within tolerance, contact Cirrus Design for disposition. 57-10 EFFECTIVITY: Page 38 15 Jun 2010...
  • Page 39 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WS 197.5 25% CHORD NOTE...
  • Page 40 (See Figure 57-1010) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Masking Tape Any Source Protection Horizontal Incidence Template, Cirrus Design Measurement HS36, LH T1835 Duluth, MN 55811 HS36, RH T1836 218-727-2737 Wing Incidence Template, Cirrus Design...
  • Page 41 A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Verify decalage is within tolerance (0.85 ± 0.4°). Record obtained values. Decalage If decalage is not within tolerance, contact Cirrus Design for disposition. 57-10 EFFECTIVITY: Page 41...
  • Page 42 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 LH WS197.5 LH HS36 RH HS36...
  • Page 43 Adjustment/Test - Wing Angle of Incidence and Decalage Measurement - Serials 1886 & subs Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Masking Tape Any Source Protection Horizontal Incidence Templates Cirrus Design Measurement HS36, LH T10100 Duluth, MN 55811 HS36, RH T10101 218-727-2737 Wing Incidence Templates Cirrus Design...
  • Page 44 There are no explicit requirements for decalage. The limits of wing and horizontal stabilizer incidence implicitly define the limits of decalage. If angle of incidence is not within toler- ance, contact Cirrus Design for disposition. Approved Repair - Ground Path Between Wing Skin EMM and Main Wing Attach Ground Strap (See Figure 57-1011) Acquire necessary tools, equipment, and supplies.
  • Page 45 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Note: Gradual loosening of ground strap hardware may cause chafing of countersunk washer on wing skin EMM;...
  • Page 46 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WING SKIN (REF) WING...
  • Page 47 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WING SKIN (REF) WING SKIN...
  • Page 48 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Approved Repair - Ground Path Between Wing Skin EMM and Fuel Cap Assembly (See Figure 57-1012)
  • Page 49 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Fabricate one (1) approximately 2 foot (0.6 m) length of 0.75 ±0.25 inch (1.91 ±0.64 cm) wide replacement carbon uni tape.
  • Page 50 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 0.7 inch (1.8 cm) WING...
  • Page 51 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 0.7 inch 0.7 inch (1.8 cm)
  • Page 52 Fit spacer flush to fuselage. Primer (Refer to 51-30) (Refer to 51-30) Prepare surface. 5-minute Epoxy (Refer to 51-30) (Refer to 51-30) Install spacer. Bolt AN5-7A Cirrus Larger replacement hardware. Washer NAS1149D0463J Cirrus Replace hardware. or alternate NAS1149F0463P MS21042-4 Cirrus Replace hardware.
  • Page 53 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Wet install bushing into enlarged fuselage skin hole with 5-minute epoxy.
  • Page 54 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 AFT FLOOR (REF) FUSELAGE...