Wing Structure. 1. General

Transcription

1 CIRRUS AIRPLANE MAINTENANCE MANUAL Wing Structure CHAPTER 57-10: WING STRUCTURE GENERAL 57-10: WING STRUCTURE 1. General 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 bending and torsion loads. The rear shear webs are similar in construction but do not carry through the fuselage. 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/carbon fiber in a C-section. The wing s belly closeout panel is bolted to the fuselage structure after wing attachment and provides a continuous load path along the bottom of the fuselage. 1

2 CHAPTER 57-10: WING STRUCTURE 2. Maintenance Practices CIRRUS AIRPLANE MAINTENANCE MANUAL A. Wing Assembly (1) Removal - Wing Assembly (a) Switch BAT 1, BAT 2, and AVIONICS switches to OFF positions. (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 Adjustment/Test - Tip-to-Tip Measurement. Retain obtained values for comparison following reassembly. (Refer to 57-10) (k) Perform Adjustment/Test - 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) 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 6-00) (q) Remove screws securing circuit breaker panel closed. (r) Remove kick plates. (Refer to 25-10) (s) Remove cabin trim panels from spar tunnel forward. (Refer to 25-10) (t) Drain brake hydraulic fluids. (Refer to 12-10) (u) Serials w/ Ice Protection: Drain ice protection system. (Refer to 12-10) (v) Remove wing root fairings. (Refer to 53-50) 2

3 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (w) Disassemble aileron connections. (Refer to 27-10) 1 At access hole CF4C, disconnect aft aileron cable turnbuckle. 2 At access hole CF4C, remove cotter pin, washer, and cable retainer clevis pin from LH and RH kickout pulley assembly and remove cable from pulley. 3 At access hole CF3C, disconnect forward LH and RH aileron turnbuckles. 4 Stow disconnected cables to wing and forward of wing spar tunnel. (x) Disassemble rudder connections. (Refer to 27-20) 1 At access hole CF5, disconnect LH and RH rudder cable turnbuckles. 2 Stow disconnected cables aft and forward of wing spar tunnel. (y) Disassemble elevator connections. (Refer to 27-30) 1 At access hole CF5, disconnect LH and RH elevator cable turnbuckles. 2 Stow disconnected cables aft and forward of wing spar tunnel. (z) Remove flap torque tubes. (Refer to 27-50) 1 At access hole CF4C, remove bolt, washers, spacer, and nut securing torque tubes to torque tube coupler. 2 At wing root, remove bolt, washers, spacer, and nut securing thrust collar and torque tube end fitting to torque tube. Repeat on opposite side. 3 Remove LH and RH torque tubes. (aa) Disconnect aft fuselage wiring harness. Label all wires and pins before disconnecting to facilitate re-installation. 1 At access hole CF3R, disconnect J666, J667, and J At access hole CF3R, locate ground wire PG650-12N terminal ring and remove attaching hardware. 3 Stow disconnected wires forward and aft of the wing spar tunnel. (ab) Disconnect magnetometer cable. 1 At access hole CF3R, disconnect jack J729 for magnetometer cabling and remove cable ties. 2 Route plug P729 on magnetometer cabling forward of wing spar tunnel. 3 Remove backshell from jack J729 to enable magnetometer cabling to pass aft through fuselage bulkhead connector. 4 Stow disconnected wires forward of the wing spar tunnel and at wing. 3

4 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (ac) Serials w/ Air Conditioning: Disconnect wiring harness for condenser. 1 At access hole CF3R, disconnect plug P1005 for condenser cabling and remove cable ties. 2 Remove backshell from plug P1005 to enable condenser cabling to pass forward through spar tunnel bulkhead connector. 3 Stow disconnected wires forward and aft of the wing spar tunnel. (ad) Serials w/ Ice Protection: Disconnect wiring harness for pump. (ae) Label all wires and pins before disconnecting to facilitate re-installation. 1 At access hole CF3R, disconnect jack J707 for pump wiring and remove cable ties. 2 Stow disconnected wires aft and forward of the wing spar tunnel. Disconnect wiring harnesses for wing. Label all wires and pins before disconnecting to facilitate re-installation. 1 At access hole CF2L, disconnect J300 from connector and remove cable ties. 2 At access hole CF2R, disconnect J400 from connector and remove cable ties. 3 De-pin J300 and J400 to enable wires to pass through fuselage bulkhead connector. 4 Stow disconnected wires at each wing and forward of the wing spar tunnel. (af) Serials w/ Stormscope: Disconnect wiring harness for Stormscope. 1 At access hole CF2R, disconnect J668 and remove cable ties. 2 Stow disconnected wires aft and forward of the wing spar tunnel. (ag) Disassemble Pitot-Static System. (Refer to 34-10) 1 Remove fittings on pitot-static lines to enable lines to pass through fuselage grommet. 2 At access hole CF3L, disconnect Pitot-Static System lines. 3 Stow pitot line aft of wing spar tunnel and to wing. 4 Stow static line aft of wing spar tunnel. 4

5 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (ah) Disconnect battery 2. 1 At access panel CF3R, disconnect jack J847 for battery 2 and remove cable ties. 2 At access panel CF3R, de-pin jack J847 to enable battery 2 wiring to pass through spar tunnel bulkhead connector. 3 Stow disconnected wires aft and forward of the wing spar tunnel. (ai) Center-aft of main wing spar, disconnect fuel supply and return lines. (Refer to 28-20) (aj) Disassemble Stall Warning System connections. (Refer to 27-31) 1 At access hole CF2R, disconnect stall warning line to wing. 2 Remove fitting on stall warning line to enable line to pass through fuselage bulkhead connector. 3 Remove cable ties and stow stall warning line into the wing. (ak) Serials w/ Ice Protection: Disassemble Ice Protection System connections. (Refer to 30-07) 1 At access hole CF2L, disconnect lines from proportioning unit running to RH and LH wing porous panels. 2 At access hole CF2L, disconnect line from proportioning unit running aft to metering pump. 3 At wing access panel LW2, disconnect lines from fluid tank and fluid tank strainer. 4 Remove cable ties and stow disconnected lines into wings and aft of the wing spar tunnel. (al) Remove screws, washers, and nuts securing belly closeout panel to fuselage. (See Figure ) 5

6 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Belly Closeout Panel Removal A WING SPAR (REF) 1 FUSELAGE (REF) DETAIL A LEGEND 1. Belly Closeout Panel 2. Screw 3. Washer 4. Nut SR22_MM57_4589 6

7 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (am) Support wing and fuselage. (See Figure ) 1 Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Saw Horses - Any Source Support High Density Foam Padding - Any Source Protection 2 Prepare airplane for hoisting. (Refer to 7-20) To assure stability and safety during hoisting operations, raise airplane slowly. 3 Raise airplane enough to place saw horses with foam padding at LH and RH wing support locations. 7

8 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Fuselage Hoist and Wing Support Stands APPROVED HOISTING METHOD ENGINE MOUNT APPROVED HOISTING METHOD WING STATION 41 FOAM PAD FUSELAGE STATION 289 SR22_MM57_4590 8

9 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (an) Detach wing assembly. (See Figure ) Verify all components routed underneath wing main spar have been disconnected and removed. 1 Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Tailstand 300 pounds (136 kg) minimum weight Any Source Support Fuselage Cradle 2000 pounds (907 kg) capacity Any Source Support Casters - Any Source Mobility High Density Foam Padding - Any Source Protection 2 Serials w/o Fan: Remove bolts and washers securing vent assembly cover to fuselage. (Refer to 21-20) 3 Serials w/ Fan: Remove bolts and washers securing fan assembly cover and fan assembly to fuselage. Position fan assembly as required to permit access to attach fittings. (Refer to 21-20) 4 Serials w/ Air Conditioning: Remove bolts and washers securing evaporator cover and evaporator to fuselage. Position evaporator as required to permit access to attach fittings. (Refer to 21-50) 5 At aft attach fittings, remove bolt, washers, nut, and cotter pin securing wing to fuselage. 6 At forward attach fittings, remove bolt, washers, spacer, and nut securing wing to fuselage. Discard bolt. When raising fuselage, align wing and fuselage at bolt locations so as to take tension off bolts and facilitate the wing sliding off smoothly. While separating wing from fuselage, observe and assist in routing of wiring and tubing between wing and fuselage. 7 Slowly raise hoist to detach fuselage from wing structure assembly. (See Figure ) 8 Cover fuselage cradle with foam padding to protect the fuselage surface. 9

10 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Verify clearance exists at fuselage cradle for transponder antenna prior to lowering fuselage onto cradle. 9 If necessary for fuselage cradle clearance, remove transponder antenna. (Refer to 34-50) 10 Lower fuselage onto fuselage cradle and tailstand. (Refer to 7-20) 11 Secure tailstand to aft tail tiedown. (Refer to 7-10) 10

11 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE Figure : Fuselage and Wing Separation FOAM PAD FUSELAGE CRADLE TAIL TIEDOWN TAIL STAND WING STATION 41 FOAM PAD SR22_MM57_

12 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (2) Installation - Wing Assembly (See Figure ) (See Figure ) 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. (Refer to AMM-Intro-00) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Wing Attach Guide Pins T Cirrus Design Alignment Bolts, Forward Wing Attach MS alternate for NAS6614D46 Any Source Replacement (b) Position wing assembly under fuselage. While lowering fuselage, verify clearance and route wiring and tubing from wing through fuselage bulkhead fittings. (See Figure ) (c) Lower fuselage onto wing assembly. (Refer to 7-20) (d) Install wing attach guide pins at the forward wing attach location to facilitate alignment of wing and fuselage attach points. (e) Secure forward wing attach hardware. 12

13 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (f) Ensure Belleville washers are installed in correct orientation. Position washer next to bolt head with beveled cut towards bolt head. 1 Remove wing attach guide pins. 2 Install new bolts with existing washers, spacers, and nuts securing wing to fuselage. 3 Torque nut 400 to 500 in-lb (45 to 56 Nm). (Refer to 20-60) 4 Verify bolt shows at least one thread past end of nut when installed. 5 Serials w/o Fan: Install bolts and washers securing vent assembly cover to fuselage. (Refer to 21-20) 6 Serials w/ Fan: Install bolts and washers securing fan assembly cover and fan assembly to fuselage. (Refer to 21-20) 7 Serials w/ Air Conditioning: Install bolts and washers securing evaporator cover and evaporator to fuselage. (Refer to 21-50) Secure aft wing attach hardware. Hard contact between aft wing attach fitting and bracket is not allowed on forward side of bracket. Do not compress aft wing attach fittings by overtightening. 1 Install bolts, washers, and nuts securing wing to fuselage. 2 Tighten nut until snug then loosen nut enough to install new cotter pin. 3 Verify gap under bolt head or nut does not exceed 0.01 inch (0.25 mm). 13

14 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Wing Attach AFT ATTACH BRACKET, FUSELAGE (REF) WING MAIN SPAR (REF) FWD ATTACH FITTING (REF) AFT ATTACH FITTING (REF) WING (REF) WING ATTACH PLATE (REF) SPACER (REF) SEAT ATTACH (REF) NOTE Position washer with beveled cut towards bolt head. Hard contact between attach fitting and bracket not allowed on forward side of bracket. Do not compress attach fittings. Verify gap under bolt head or nut does not exceed 0.01 inch (0.25 mm). Washer installation required. LEGEND 1. Bolt 2. Washer 3. Belleville Washer 4. Spacer 5. Nut 6. Cotter Pin SR22_MM57_

15 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE Figure : Fuselage to Wing Connectivity APPROVED HOISTING METHOD ENGINE MOUNT 1 APPROVED HOISTING METHOD FUSELAGE STATION 289 PITOT LINE AND W301 WIRING HARNESS FLAP TORQUE TUBE ICE PROTECTION LINE LH FUSELAGE MAGNETOMETER AND W401 WIRING HARNESS FLAP TORQUE TUBE RH FUSELAGE STALL WARNING AND ICE PROTECTION LINE SR22_MM57_

16 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (g) (h) (i) Remove wing supports and hoisting straps. Perform Adjustment/Test - Tip-to-Tip Measurement. Compare with values obtained previously. (Refer to 57-10) Perform Adjustment/Test - Wing Angle of Incidence and Decalage Measurement. Compare with values obtained previously. (Refer to 57-10) (j) Serials w/ Ice Protection: Assemble Ice Protection System connections. (Refer to 30-07) 1 At access hole CF2L, connect lines from proportioning unit running to RH and LH wing porous panels. 2 At access hole CF2L, connect line from proportioning unit running aft to metering pump. 3 At wing access panel LW2, connect lines from fluid tank and fluid tank strainer. 4 Remove cable ties and stow disconnected lines into wings and aft of the wing spar tunnel. (k) Assemble Stall Warning System connections. (Refer to 27-31) 1 Route Stall Warning System line to access hole CF2R from right wing. 2 At access hole CF2R, install fitting and connect wing stall warning line. 3 Secure lines with cable ties as required. (l) Center-aft of main wing spar, connect fuel supply and return lines. (Refer to 28-20) (m) Connect battery 2. 1 Route secondary battery power/ground forward of wing spar tunnel. 2 Replace cable ties for lines as required. 3 At access panel CF3R, re-pin jack J847 to enable battery 2 wiring to pass through spar tunnel bulkhead connector. 4 At access panel CF3R, connect jack J847 for battery 2. (n) Assemble Pitot-Static System. (Refer to 34-10) 1 Route pitot line from left wing and forward to access hole CF3L. 2 Route static line forward to access hole CF3L. 3 At access hole CF3L, install fittings and connect Pitot-Static lines. 4 Secure lines with cable ties as required. (o) Serials w/ Stormscope: Assemble wiring harness for Stormscope. 1 Route Stormscope wires to access hole CF2R. 2 At access hole CF2R, connect J Secure wire harnesses with cable ties as required. 16

17 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (p) (q) Assemble wiring harnesses for wing. 1 At access hole CF2L, connect J300 connector. 2 At access hole CF2R, connect J400 connector. 3 Secure wire harnesses with cable ties as required. Serials w/ Ice Protection: Assemble wiring harness for pump. 1 Route wiring harness through spar tunnel bulkhead connector to access hole CF2R. 2 At access hole CF3R, connect jack J707 to P Secure wire harnesses with cable ties as required. (r) Serials w/ Air Conditioning: Connect wiring harness for condenser. 1 Route condenser cabling forward to access hole CF3R. 2 Assemble P1005 connector. 3 At access hole CF3R, connect plug P1005 for condenser cabling. 4 Secure wire harnesses with cable ties as required. (s) Assemble magnetometer cable. 1 Route magnetometer cables to access hole CF3R. 2 At access hole CF3R, install backshell onto J Connect J729 to P729. (t) Assemble aft fuselage wiring harness. 1 Route aft fuselage wiring harness to access hole CF3R. 2 At access hole CF3R, secure ground wire PG650-12N terminal ring with attaching hardware and cover with heatshrink material. 3 At access hole CF3R, connect J666, J667, and J Only secure wiring bundles with adel clamps. Ensure control cables for rudder, elevator, and aileron are not secured by adel clamps. (u) Assemble flap torque tubes. (Refer to 27-50) 1 Install LH and RH torque tubes. 2 At wing root, position thrust collar and torque tube end fitting to torque tube and secure with bolt, washers, spacer, and nut. Repeat on opposite side 3 At access hole CF4C, torque tubes to torque tube coupler and secure with bolt, washers, spacer, and nut. (v) Install flaps. (Refer to 57-50) 17

18 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (w) Assemble aileron connections. (Refer to 27-10) 1 Route disconnected cables stowed from wing to access hole CF3C. 2 At access hole CF3C, connect LH and RH aileron cable turnbuckles. 3 Route disconnected cables stowed in aft area to access hole CF4C. 4 At access hole CF4C, connect aft aileron cable turnbuckle. 5 At access hole CF4C, install cable retainer pins, washers, and new cotter pins to LH and RH kickout pulley assemblies. (x) Install ailerons. (Refer to 57-50) (y) Assemble elevator connections. (Refer to 27-30) 1 Route disconnected cables to access hole CF5. 2 Connect LH and RH elevator cables turnbuckles. (z) Assemble rudder connections. (Refer to 27-20) 1 Route disconnected cables to access hole CF5. 2 At access hole CF5, connect LH and RH elevator cable turnbuckles. (aa) Inspect fuel system for leaks. (Refer to 28-10) (ab) Bleed brake system. (Refer to 32-42) (ac) Verify correct orientation of wiring harnesses, tubing, and flight control cables from belly closeout panel opening. (See Figure ) 18

19 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE Figure : Fuselage Spar Tunnel Routing A DETAIL A LEGEND 1. Magnetometer Cable 2. Aft Fuselage Wire Harness W65x 3. Flight Control Cables 4. Ice Protection Line 5. Battery 2 Power/Ground 6. Pitot/Static Line SR22_MM57_

20 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (ad) Serials w/ originally installed belly closeout panel: Install belly closeout panel. 1 Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Sandpaper 80-grit Any Source Abrasion (ae) 2 To remove residual adhesive, carefully sand edges of belly closeout panel and mating surfaces of fuselage. 3 Position belly closeout panel to fuselage and secure with screws, washers, and nuts. (See Figure ) Serials w/ new belly closeout panel: Install belly closeout panel. 1 Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Mylar Template T10178 S/N Cirrus Design Transfer Masking Tape - Any Source Adhere Spray Adhesive Unlimited Quality Products Adhere Drill Bit 0.25 inch (0.64 cm) Any Source Drilling Countersunk Drill Bit 0.50 inch (1.27 cm) Any Source Drilling Citrus Base Cleaner M Company Cleaning 2 To facilitate template alignment, backlight tooling holes of belly closeout panel. 3 Position template to belly closeout panel by aligning tooling hole markings on template with tooling holes on belly closeout panel. 4 Tape down one end of template to belly closeout panel. 5 Lift up free end of template and evenly apply adhesive over surface of belly closeout panel. 6 Carefully lay template down on belly closeout panel, aligning tooling hole markings with tooling holes on belly closeout panel. 7 Using 0.25 inch (0.64 cm) bit, match drill installation holes from template to belly closeout panel. 20

21 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE Ensure countersunk holes are drilled flush with belly closeout panel. 8 Using 0.5 in (1.27 cm) countersunk bit, drill holes so installation screws will be flush with belly closeout panel. (Refer to 20-70) 9 Remove template from belly closeout panel. 10 Solvent clean belly closeout panel to remove residual adhesive. (Refer to 20-30) 11 Position belly closeout panel to fuselage and secure with screws, washers, and nuts. 21

22 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Belly Closeout Panel Installation 4 3 A WING SPAR (REF) 2 1 FUSELAGE (REF) LEGEND 1. Belly Closeout Panel 2. Screw 3. Washer 4. Nut DETAIL A SR22_MM57_

23 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (af) Install wing root fairings. (Refer to 53-50) (ag) Install main gear fairings. (Refer to 32-10) (ah) Install nose gear fairing. (Refer to 32-20) (ai) If removed for fuselage cradle clearance, install transponder antenna. (Refer to 34-50) (aj) Install kick plates. (Refer to 25-10) (ak) Install access panels CF2L, CF2R, CF3R, CF3C, CF3L, and CF5. (Refer to 6-00) (al) Install cabin floor covering. (Refer to 25-10) (am) Install screws securing circuit breaker panel closed. (an) Install cabin trim panels. (Refer to 25-10) (ao) Install crew and passenger seats. (Refer to 25-10) (ap) Connect battery 1. (Refer to 24-30) (aq) Install engine cowling. (Refer to 71-10) (ar) Reset all circuit breakers. (as) Serials w/ Ice Protection: Replenish deicing fluid tank with approved fluid. (Refer to 12-10) (at) Fuel airplane. (Refer to 12-10) (au) Replenish brake system. (Refer to 12-10) (av) Perform Operational Inspection - Flap System. (Refer to 57-50) (aw) Perform Inspection/Check - Empennage Bellcranks. (Refer to 27-20) (ax) Perform Functional Test - Static System Plumbing. (Refer to 34-10) (ay) Perform Functional Test - Pitot System Plumbing. (Refer to 34-10) (az) Perform Inspection/Check - Aileron Assembly. (Refer to 57-50) (ba) Perform Inspection/Check - Aileron System Rigging. (Refer to 27-10) (bb) Perform Inspection/Check - Rudder System Rigging. (Refer to 27-20) (bc) Perform Inspection/Check - Elevator System Rigging. (Refer to 27-30) (bd) Perform Inspection/Check - Roll Trim Cartridge (Refer to 27-10) (be) Perform Inspection/Check - Torque Tube Gap Tolerance. (Refer to 27-20) (bf) Perform ELT functional inspection in accordance with 14 CFR (bg) Serials w/ Ice Protection: Perform Operational Check - Ice Protection System. (Refer to 30-00) 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 23

24 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL maintenance to schedule check flight. (Refer to AMM-Intro-00) (bh) Perform Cirrus Design-Authorized Flight Test. (3) Adjustment/Test - Tip-to-Tip Measurement (See Figure ) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Ruler Gauges (Block), LH and RH T Cirrus Design Leveling Transit Level - Any Source Leveling (b) Level airplane laterally with digital level using engine mount weldment. (Refer to 8-10) (c) Locate 25% chord at WS on both wings. (See Figure ) (d) At LH and RH wing, position ruler gauge blocks on WS with ruler edge aligned with 25% chord. (e) Position transit level approximately 10 feet (3 m) forward from propeller. (f) Using transit level, locate ruler gauge block. Note location on ruler at which crosshair intersects ruler measurement. (g) Repeat measurement location on opposite ruler gauge block. (h) Verify difference in measurement locations at LH and RH ruler gauge blocks is within tolerance 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. (Refer to AMM-Intro-00) 24

25 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE Figure : Tip-to-Tip Measurement WS % CHORD NOTE Position ruler gauge block on WS with ruler edge aligned with 25% chord. Position transit level approximately 10 feet (3 m) forward from propeller. Verify difference in measurement location at LH and RH ruler gauge blocks is within tolerance of 2.0 inches (5.0 cm). LEGEND 1. Transit Level 2. Ruler Gauge ( Block) 3. Saw Horse SR22_MM57_

26 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (4) Adjustment/Test - Wing Angle of Incidence and Decalage Measurement (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Masking Tape - Any Source Protection Horizontal Incidence Templates HS36, LH HS36, RH T10100 T10101 Cirrus Design Measurement Wing Incidence Templates WS40, LH WS40, RH WS130, LH WS130, RH WS213, LH WS213, RH T10072 T10073 T7508 T10007 T10145 T10146 Cirrus Design Measurement Digital Level, 0.25 Resolution - Any Source Measurement (b) (c) (d) Apply masking tape to template feet to protect contact locations on wing surface. At LH and RH sides of wing, identify wing incidence templates for WS213, WS130, and WS40 and position templates to wing as marked. At LH and RH sides of horizontal stabilizer, identify horizontal incidence templates for HS36 and position templates to horizontal stabilizer as marked. NOTE To ensure consistent and accurate readings, position digital level so that the display faces one direction at all template locations (for example, outboard on RH side and inboard on LH side). Position digital level at each template and measure angle of incidence. NOTE Negative readings indicate leading edge down. Positive readings indicate leading edge up. 26

27 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (e) Verify angle of incidence at all template locations is measured at 0.25±0.20. Record obtained values. LH WS LH WS LH WS 40.0 RH WS RH WS RH WS 40.0 LH HS 36.0 RH HS 36.0 (f) (g) Determine decalage by adding absolute value obtained at HS36 template to actual value obtained at WS40 template. For example: ( LH HS36 ) + (LH WS40) = Decalage ( ) + (0.20) = Decalage = Decalage 0.99 = Decalage Record obtained values. Decalage 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 tolerance, contact Cirrus Design for disposition. (Refer to AMM-Intro-00) 27

28 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (5) Approved Repair - Ground Path (Wing Skin EMM and Main Wing Attach Ground Strap) (See Figure ) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Ohmmeter - Any Source Check resistance. Sandpaper 80-grit Any Source Paint/primer removal and EMM burnishing. Countersunk Screw MS24693S28 (or equivalent) Any Source Main wing attach ground strap installation. Countersunk Washer NAS1169-6L (or equivalent) Any Source Main wing attach ground strap installation. Washer NAS1149FN616P (or equivalent) Any Source Main wing attach ground strap installation. Self-Locking Nut MS (or equivalent) Any Source Main wing attach ground strap installation. (b) Remove only paint and bodywork necessary to expose rivets/screws and countersunk washers that secure main wing attach ground strap to upper wing skin. Remove ground path between main wing attach ground strap and wing skin EMM. 1 Remove paint and bodywork exposing wing skin EMM. (Refer to 51-20) 2 Remove and discard rivets and countersunk washers securing main wing attach ground strap to upper wing skin. Do not damage wing skin EMM while burnishing the surface. NOTE Gradual loosening of ground strap hardware may cause chafing of countersunk washer on wing skin EMM; repair wing skin EMM as 28

29 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE required to re-establish ground path. (Refer to 51-20) 3 Burnish exposed wing skin EMM to ensure adequate electrical bonding connection to washers. 4 Burnish mating surface of each countersunk washer to ensure adequate electrical bonding to wing skin EMM. (c) Replace ground path between main wing attach ground strap and wing skin EMM. 1 Install countersunk screws, countersunk washers, washers, and self-locking nuts securing main wing attach ground strap to wing skin EMM. 2 Measure resistance between main wing attach ground strap and wing skin EMM to ensure ground path has been successfully reestablished. (d) It is permissible to repeat Approved Repair - Ground Path (Wing Skin EMM and Main Wing Attach Ground Strap) for aft, inboard wing attach grounding strap to reduce resistance of fuel cap assembly ground path between wing skin EMM and fuselage. (e) Perform Functional Test - Fuel Cap Assembly Ground Resistance. (Refer to 28-10) (f) Repair wing skin and paint. (Refer to 51-20) 29

30 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Approved Repair - Ground Path Between Wing Skin EMM & Main Wing Attach Ground Strap A1 2 3 A1 4 5 A A DETAIL A WING SKIN (REF) WING SKIN (REF) 1 WING SKIN EMM (REF) 1 WING SKIN EMM (REF) VIEW A1 NOTE Remove only paint and body work necessary to expose rivets and countersunk washers that secure main wing attach ground strap to upper wing skin. Burnish exposed wing skin EMM to ensure proper connection to washers. Burnish mating surface of each countersunk washer to ensure adequate electrical bonding to wing skin EMM. VIEW A2 LEGEND 1. Grounding Strap 2. Screw 3. Countersunk Washer 4. Washer 5. Nut SR22_MM57_

31 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (6) Approved Repair - Ground Path (Wing Skin EMM and Fuel Cap Assembly) (See Figure ) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Carbon Uni Tape, Prepreg (Refer to 51-30) (Refer to 51-30) Ground path. Expanded Metal Mesh, Aluminum, lb-ft² (0.137 kg-m²) Expanded Metal Mesh, Aluminum, lb-ft² (0.293 kg-m²) Expanded Metal Mesh, Copper, lb-ft² (0.142 kg-m²) (Refer to 51-30) (Refer to 51-30) Ground path at fuel cap assembly offset. (Refer to 51-30) (Refer to 51-30) Repair wing skin EMM and ground path. (Refer to 51-30) (Refer to 51-30) Ground path. (b) Remove ground path between wing skin EMM and fuel cap assembly. Remove only paint and bodywork necessary to expose fuel cap assembly ground path between wing skin EMM and fuel cap assembly. Minimize wing skin EMM removal as much as possible while removing paint and bodywork. 1 Remove paint and bodywork exposing wing skin EMM, copper mesh EMM, carbon uni tape, and aluminum mesh EMM. (Refer to 51-20) Do not damage underlying composite structure. 2 Completely remove copper mesh EMM, carbon uni tape, and aluminum mesh EMM. 31

32 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (c) Repair ground path between wing skin EMM and fuel cap assembly. 1 Burnish all mating surfaces to ensure adequate electrical bonding. 2 Fabricate one (1) approximately 4 inch (10 cm) length of 0.75±0.25 inch (1.91±0.64 cm) wide replacement carbon uni tape. 3 Fabricate two (2) squares of inches ( cm) replacement copper mesh EMM. 4 Trim aluminum mesh EMM to match inner diameter of fuel cap assembly hole. 5 Install carbon uni tape, copper mesh EMM, and aluminum mesh EMM. (Refer to 51-20) 6 Repair wing skin EMM. (Refer to 51-20) NOTE It is permissible to burnish wing skin EMM to facilitate a suitable test point. (Refer to 51-20) 7 Measure resistance between aluminum mesh EMM and wing skin EMM to ensure ground path has been successful re-established. (d) Perform Functional Test - Fuel Cap Assembly Ground Resistance. (Refer to 28-10) (e) Repair wing skin and paint. (Refer to 51-20) (f) Install fuel cap assembly. (Refer to 28-10) 32

33 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE Figure : Approved Repair - Ground Path Between Wing Skin EMM and Fuel Cap Assembly 0.7 inch (1.8 cm) 0.2±0.1 inch (0.5±0.25 cm) C L 0.7 inch (1.8 cm) WING SKIN EMM (REF) A FUEL CAP OFFSET (REF) 0.7 inch (1.8 cm) WING SKIN (REF) 0.7 inch (1.8 cm) 0.2±0.1 inch (0.5±0.25 cm) SECTION A1 A1 Ø 6.00±0.25 inches (15.24± 0.64 cm) A WING SKIN (REF) 0.75±0.75 inch (1.91±1.91 cm) WING SKIN EMM (REF) 0.2±0.1 inch (0.5±0.25 cm) 0.2±0.1 inch (0.5±0.25 cm) 0.75±0.25 inch (1.91±0.64 cm) DETAIL A NOTE Remove only paint and body work necessary to expose fuel cap assembly ground path between wing skin EMM and fuel cap assembly. Ensure 0.2±0.1 inch (0.5±0.25 cm) gap exists between carbon uni tape and wing skin EMM. Ensure 0.2±0.1 inch (0.5±0.25 cm) gap exists between carbon uni tape and aluminum mesh EMM. Ensure forward and aft ends of carbon uni tape is centered with copper mesh EMM by inboard/outboard overlap of 0.75±0.75 inch. Press copper tape into place. Minor wrinkling is allowed but ensure copper tape is pressed flat. Copper tape may be darted or sliced to allow it to lie flat. Trim copper tape to match inner diameter of fuel cap assembly hole. It is permissible to burnish wing skin EMM to facillitate a suitable test point. LEGEND 1. Copper Mesh EMM 2. Carbon Uni Tape 3. Aluminum Mesh EMM SR22_MM57_

34 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL (7) Approved Repair - Aft Wing Attachment (See Figure ) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Drill - Any Source Enlarge hardware holes. Sandpaper - Any Source 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 or alternate NAS1149F0463P Cirrus Replace hardware. Nut MS or alternate MS21044C4 Cirrus Replace hardware. Screw MS24694S106 Cirrus Replace hardware. Washer NAS1149D0463J or alternate NAS1149F0463P Cirrus Replace hardware. Bushing NAS Cirrus Install into enlarge fuselage skin holes. Nut MS or alternate MS21044C4 Cirrus Replace hardware. Bolt AN5-7A Cirrus Larger replacement hardware. (b) Perform Removal - Wing Root Fairing. (Refer to 53-50) (c) Perform Removal - Passenger Seats. (Refer to 25-10) (d) Remove floor covering. (Refer to 25-10) (e) Remove CF4L and CF4R access panels. (Refer to 6-00) (f) Remove and discard existing nuts, washers, and bolts securing aft wing attachment clips to fuselage and aft floor Dec 2017

35 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 57-10: WING STRUCTURE (g) (h) Only enlarge holes in the fuselage skin, aft attach clip holes that correspond to aft floor holes, and aft floor. DO NOT enlarge holes on aft wing attach bracket, radius fills or the aft attach clip holes that correspond to the radius fills. Measure holes in fuselage skin, aft attach clips, and aft floor to determine which holes need to be enlarged. Drill through aft attach clips and aft floor separately. 1 Using drill, enlarge any holes inch (5.715 mm) or greater in diameter to inch (9.576 mm). Install bushing to enlarged fuselage skin holes. 1 Wet install bushing into enlarged fuselage skin hole with 5-minute epoxy. NOTE Bushing may be up to inch (0.127 mm) underflush on both toolside and bagside fuselage. 2 Sand bushing if necessary to ensure it is flush with the bagside and toolside fuselage. 3 If bushing is sanded, prime all exposed fuselage surfaces. (Refer to 51-30) (i) Install new larger bolt washer and nut through clips and aft floor. 1 Torque fastener to 80 to 95 in-lb (9.04 to Nm). Apply torque stripe. (j) Install replacement hardware through aft wing attach brackets, fuselage skin, clip, and radius fills. 1 Torque fastener to 80 to 95 in-lb (9.04 to Nm). Apply torque stripe. (k) Install CF4L and CF4R access panels. (Refer to 6-00) (l) Install floor covering. (Refer to 25-10) (m) Perform Removal - Passenger Seats. (Refer to 25-10) (n) Perform Removal - Wing Root Fairing. (Refer to 53-50) (o) Note repair in Aircraft Logbook Dec 2017

36 CHAPTER 57-10: WING STRUCTURE CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : Approved Repair - Aft Wing Attachment AFT FLOOR (REF) FUSELAGE SKIN (REF) 3 NOTE Drill through aft attach clips and aft floor seperately. Only enlarge holes in fuselage skin. DO NOT enlarge holes on aft wing attach bracket, radius fill, or aft attach clip holes corresponding to holes on radius fills. LEGEND 1. Bolt 2. Washer 3. Screw 4. Bushing 5. Nut 6. Radius Fill 7. Bracket, Aft Wing Attach 8. Clip SR22_MM57_ Dec 2017