CIRRUS AIRPLANE MAINTENANCE MANUAL

Transcription

1 FLIGHT SURFACES. DESCRIPTION The flaps are mounted to the trailing edge of each wing between the inboard end of the ailerons and the fuselage. The ailerons are located near the wing tips and hinge to the aileron spar to become part of the trailing edge of the wing. The RH aileron includes an aileron trim tab used for roll trim adjustment. The ailerons and flaps are made from aluminum. Aileron gap seals are located between the aileron and the wing trailing edge to increase aileron efficiency at high speeds and turbulent conditions. Serials 000 thru 7: Flap rub strips are located along the length of the flaps at the wing trailing edge to protect flap and wing surfaces from chafing one another. All Page

2 . MAINTENANCE PRACTICES A. Aileron Assembly - Serials 000 thru 7 (See Figure ) () Removal - Aileron Assembly (a) Remove wing tip. (Refer to 7-0) CAUTION: When removing aileron hinge bolts, exercise caution to prevent aileron from falling and becoming damaged. Prevent the aileron from being supported by only one bolt, as this could damage the bolt, hinge, and aileron. Note: Note washer stackup to facilitate aileron re-installation. (b) (c) Cut safety wire and remove bolt and washer(s) securing aileron to outboard aileron hinge. Cut safety wire and remove bolt, washer(s), and spacer securing aileron to inboard aileron hinge. Remove aileron from airplane. () Disassembly - Aileron Assembly (a) To disassemble aileron trim tab, perform the following steps: Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Drill bit inch (.89 mm) #0 Any Source Drill out rivets. Drill out rivets securing trim tab to RH aileron. () Assembly - Aileron Assembly (a) To assemble aileron trim tab, perform the following steps: Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Alodine Pen - Any Source Corrosion protection. Blind Rivet NAS90B- Cirrus Design Fastener. Duluth, MN White Hobby Paint Testers (or equivalent) Any Source Paint rivet heads. Page Using an Alodine pen, apply corrosion protection to edge of each rivet hole. Install rivets securing trim tab to RH aileron. Apply thin coat of paint to each rivet head. Perform Adjustment/Test - Aileron Balancing. (Refer to ) () Installation - Aileron Assembly (a) Insert aileron actuation pin into spherical rod end on actuation pulley. (b) Install bolt, washer(s), and spacer securing aileron to inboard aileron hinge. (c) Finger tighten bolt and washer(s) securing aileron to outboard aileron hinge. (d) Perform Inspection/Check - Aileron Gap and Overlap. (Refer to ) (e) Tighten both aileron hinge bolts to 0 - in-lb (. -.8 Nm). Serials 000 thru 7

3 (f) Safety wire aileron hinge bolts to safety wire clips. (Refer to 0-0) (g) Perform Inspection/Check - Aileron Assembly. (Refer to ) (h) Install wing tip. (Refer to 7-0) (i) If aileron trim tab was replaced, perform Adjustment/Test - Aileron Trim Tab. (Refer to 7-0) () Inspection/Check - Aileron Assembly (a) Verify hinge bolts for proper torque and installation. (Refer to ) (b) Verify proper installation of safety wire on all fasteners. (c) Ensure aileron skin is smooth and free of any defects or irregularities. (d) Inspect rivets and aileron skin for tightness. (e) Operate aileron controls and inspect for any abnormal resistance. Serials 000 thru 7 Page

4 SAFETY WIRE CLIP OUTBOARD HINGE OUTBOARD BOLT HINGE 0 AILERON SAFETY WIRE CLIP INBOARD BOLT NOTE Safety wire as shown. INBOARD HINGE No more than 0.0 inch (0.76 mm) allowed in combined washer and endplay gap. On some airplanes, there may be more than one washer installed between attach bracket and hinge. Upon removal of aileron, note stackup and replace upon installation. Washers are installed to ensure hinge does not contact aileron. Serials 87 & subs only Serials 000 thru LEGEND 8. Trim Tab. Mass Balance 7. Washer. Bolt. Spacer Serials 08 thru Inboard Hinge Attach Bracket 7. Bearing 8. Nut 9. Actuation Arm Assembly 0. Outboard Hinge Attach Bracket. Rivet Serials 000 thru, thru 9, 0 thru Serials 066 thru, thru 9, HINGE 0 thru 7. SR_MM7_F Page Figure Aileron Installation - Serials 000 thru 7 Serials 000 thru 7

5 (6) Inspection/Check - Aileron Gap and Overlap (See Figure ) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Feeler Gauge - Any Source Measure aileron hinge clearance. Inclinometer PRO60 Macklanburg Duncan Deflection angle. Oklahoma City, OK (b) (c) Lower flaps to full down position. To facilitate gap inspection, slide aileron inboard and measure maximum endplay gap on outboard end of aileron. CAUTION: If existing washer installed between the outboard aileron hinge and aileron attach bracket is 0.06 inch (0.06 mm) thick, it may be replaced with one 0.0 inch (0.8 mm) washer to prevent contact between trailing edge of hinge and aileron attach bracket. (d) At outboard and inboard aileron hinges, verify bearing is fully seated with bearing face flush with aileron hinge surface. CAUTION: Allowable gap between outboard aileron hinge and washer is between 0.00 and 0.0 inch (0.00 and 0.76 mm). Ensure aileron hinge bolts are only finger-tightened before measuring gap. (e) At outboard LH and RH aileron hinge bearings, use feeler gauge to verify gap between aileron hinge and washer does not exceed maximum endplay of 0.0 inch (0.76 mm). (f) If gap between aileron hinge and washer exceeds maximum endplay of 0.0 inch (0.76 mm), perform Inspection/Check - Outboard Aileron Hinge Shimming. (Refer to 7-0) (g) Raise flaps to full up position. WARNING: The following gap and overlap inspections need only be performed after the installation of a replacement (new or different) aileron. If aileron leading edge gap, neutral position gap, and overlap inspections do not fall within the specified clearances, contact Cirrus Design Customer Service Department for disposition. (h) (i) (j) Serials 000 thru 7 Replacement Aileron Installation Only: Verify gap between aileron leading edge and trailing edge of wing has a minimum of 0.0 inch (.79 mm) and a maximum of 0.00 inch (.700 mm) clearance before installation of flexible gap seal, when aileron is fully deflected, trailing edge down. In area near aileron actuation arm where there is no leading edge cover, the minimum shall be 0. inch (.7 mm). Replacement Aileron Installation Only: Verify overlap between aileron and wing has a minimum of 0.00 inch (0. mm) and a maximum of 0.0 inch (.6 mm) clearance. Aileron may be deflected downward 0 - to achieve upper overlap, and may be deflected upward 0 - to achieve lower overlap. Replacement Aileron Installation Only: Secure ailerons in neutral position by placing a lock-out pin in aileron actuation pulley in center console. Verify neutral position gap has a minimum of inch (. mm) and a maximum of 0.0 inch (.88 mm) clearance Page

6 between WS to WS 9, and a minimum of 0.00 inch (.06 mm) and a maximum of 0.0 inch (.88 mm) clearance between WS 9 to WS 97.. Page 6 Serials 000 thru 7

7 BEARING WASHER AILERON (LH, OUTBOARD SIDE SHOWN) NOTE Verify gap between aileron hinge and washer does not exceed maximum endplay of 0.0 inch (0.76 mm). At outboard and inboard aileron hinges, verify bearing is fully seated with bearing face flush with aileron hinge surface. Replacement Aileron Installation only: Verify leading edge gap has a minimum of 0.0 inch (.79 mm) and a maximum of 0.00 inch (.700 mm) clearance. Minimum clearance at actuation arm is 0. inch (.7 mm). Replacement Aileron Installation only: Measure tangent to the leading edge curvature. Replacement Aileron Installation only: Verify neutral position gap has a minimum of inch (. mm) and a maximum of 0.0 inch (.88 mm) clearance between WS to WS 9, and a minimum of 0.00 inch (.06 mm) and a maximum of 0.0 inch (.88 mm) clearance between WS 9 to WS 97.. Replacement Aileron Installation only: Verify overlap gap has a minimum of inch (0. mm) and a maximum of 0. 0 inch (. 6 mm) clearance. Replacement Aileron Installation only: Measure overlap tangent to the leading edge curvature. Use a 6 inch straight edge. 0-. OVERLAP GAP INSPECTION LEADING EDGE GAP INSPECTION NEUTRAL POSITION GAP INSPECTION Serials 000 thru, thru 9, 0 thru 7. SR_MM7_06C Serials 000 thru 7 Figure Aileron Gap and Overlap - Serials 000 thru 7 Page 7

8 B. Aileron Assembly - Serials 8 & subs (See Figure ) () Removal - Aileron Assembly (a) Remove wing access panel LW or RW. (Refer to 06-00) CAUTION: When removing aileron hinge bolts, exercise caution to prevent aileron from falling and becoming damaged. Prevent the aileron from being supported by only one bolt, as this could damage the bolt, hinge, and aileron. Note: Note washer stackup to facilitate aileron re-installation. (b) (c) Cut safety wire and remove bolt and washers securing aileron to outboard aileron hinge. Cut safety wire and remove bolt, washers, and spacer securing aileron to inboard aileron hinge. Remove aileron from airplane. () Disassembly - Aileron Assembly (a) To disassemble aileron trim tab, perform the following steps: Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Drill bit inch (.89 mm) #0 Any Source Drill out rivets. Drill out rivets securing trim tab to RH aileron. () Assembly - Aileron Assembly (a) To assemble aileron trim tab, perform the following steps: Acquire necessary parts, tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Alodine Pen - Any Source Corrosion protection. Blind Rivet NAS90B- Cirrus Design Fastener. Duluth, MN White Hobby Paint Testers (or equivalent) Any Source Paint rivet heads. Page 8 Using an Alodine pen, apply corrosion protection to edge of each rivet hole. Install rivets securing trim tab to RH aileron. Apply thin coat of paint to each rivet head. Perform Adjustment/Test - Aileron Balancing. (Refer to ) () Installation - Aileron Assembly (a) Insert aileron actuation pin into spherical rod end on actuation pulley. (b) Install bolt, washers, and spacer securing aileron to outboard aileron hinge. Torque bolt to 0 - in-lb (. -.8 Nm). (c) Install bolt, washers, and spacer securing aileron to inboard aileron hinge. Finger tighten bolt. (d) Perform Inspection/Check - Aileron Gap and Overlap. (Refer to ) Serials 8 & subs

9 (e) Safety wire aileron hinge bolts to safety wire clips. (Refer to 0-0) (f) Perform Inspection/Check - Aileron Assembly. (Refer to ) (g) Install wing access panel LW or RW. (Refer to 06-00) (h) If aileron trim tab was replaced, perform Adjustment/Test - Aileron Trim Tab. (Refer to 7-0) () Inspection/Check - Aileron Assembly (a) Verify hinge bolts for proper torque and installation. (Refer to ) (b) Verify proper installation of safety wire on all fasteners. (c) Ensure aileron skin is smooth and free of any defects or irregularities. (d) Inspect rivets and aileron skin for tightness. (e) Operate aileron controls and inspect for any abnormal resistance. Serials 8 & subs Page 9

10 SAFETY WIRE CLIP OUTBOARD HINGE OUTBOARD BOLT HINGE 0 AILERON SAFETY WIRE CLIP INBOARD BOLT NOTE Safety wire as shown. INBOARD HINGE 6 LEGEND. Trim Tab. Mass Balance. Washer. Bolt. Spacer 6. Inboard Hinge Attach Bracket 7. Bearing 8. Nut 9. Actuation Arm Assembly 0. Outboard Hinge Attach Bracket. Rivet HINGE SR_MM7_ Page 0 Figure Aileron Installation - Serials 8 & subs Serials 8 & subs

11 (6) Inspection/Check - Aileron Gap and Overlap (See Figure ) (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Feeler Gauge - Any Source Measure aileron hinge clearance. Inclinometer PRO60 Macklanburg Duncan Deflection angle. Oklahoma City, OK (b) (c) Lower flaps to full down position. Prior to final torque, verify distance between aileron inboard end and aileron hinge equals 0. ± 0.00 inch (7.9 ±. mm). Note: To obtain gap tolerance, it is permissible to use a different length spacer. In addition to the spacer, two washers may also be installed. (d) (e) (f) Prior to final torque, verify minimum gap between aileron inboard end and spacer equals 0.00 inch (0.0 mm) and maximum gap equals 0.06 inch (.60 mm). Torque inboard aileron hinge bolt to 0 - in-lb (. -.8 Nm). Raise flaps to full up position. WARNING: The following gap and overlap inspections need only be performed after the installation of a replacement (new or different) aileron. If aileron leading edge gap, neutral position gap, and overlap inspections do not fall within the specified clearances, contact Cirrus Design Customer Service Department for disposition. (g) (h) (i) Replacement Aileron Installation Only: Verify gap between aileron leading edge and trailing edge of wing has a minimum of 0.0 inch (.79 mm) and a maximum of 0.00 inch (.080 mm) clearance before installation of flexible gap seal, when aileron is fully deflected, trailing edge down. In area near aileron actuation arm where there is no leading edge cover, the minimum shall be 0. inch (.7 mm). Replacement Aileron Installation Only: Verify overlap between aileron and wing has a minimum of 0.00 inch (0. mm) and a maximum of 0. inch (.7 mm) clearance. Aileron may be deflected downward 0 - to achieve upper overlap, and may be deflected upward 0 - to achieve lower overlap. Replacement Aileron Installation Only: Secure ailerons in neutral position by placing a lock-out pin in aileron actuation pulley in center console. Verify neutral position gap has a minimum of inch (. mm) and a maximum of 0.0 inch (. mm) clearance between WS to WS 9, and a minimum of 0.00 inch (.06 mm) and a maximum of 0.0 inch (. mm) clearance between WS 9 to WS 97.. Serials 8 & subs Page

12 0. ± 0.00 inch (7.90 ±.0mm) 0.06 ± 0.00 inch (.600 ± 0.0mm) BEARING SPACER AILERON HINGE NOTE At outboard and inboard aileron hinges, verify bearing is fully seated with bearing face flush with aileron hinge surface. Prior to final torque, verify gap between aileron inboard end and spacer equals 0.06 ± 0.00 inch (.600 ± 0.0mm). After to final torque, verify distance between aileron inboard end and aileron hinge equals 0. ± 0.00 inch (7.9 ±.0mm). Replacement Aileron Installation only: Verify leading edge gap has a minimum of 0.0 inch (.79 mm) and a maximum of 0.00 inch (.700 mm) clearance. Minimum clearance at actuation arm is 0. inch (.7 mm). Replacement Aileron Installation only: Measure tangent to the leading edge curvature. Replacement Aileron Installation only: Verify neutral position gap has a minimum of inch (. mm) and a maximum of 0.0 inch (.88 mm) clearance between WS to WS 9, and a minimum of 0.00 inch (.06 mm) and a maximum of 0.0 inch (.88 mm) clearance between WS 9 to WS 97.. Replacement Aileron Installation only: Verify overlap gap has a minimum of 0.00 inch (0. mm) and a maximum of 0.0 inch (.6 mm) clearance. Replacement Aileron Installation only: Measure overlap tangent to the leading edge curvature. Use a 6 inch straight edge. 0-. AILERON (LH, INBOARD SIDE SHOWN) OVERLAP GAP INSPECTION LEADING EDGE GAP INSPECTION NEUTRAL POSITION GAP INSPECTION SR_MM7_ Page Figure Aileron Gap and Overlap - Serials 8 & subs Serials 8 & subs

13 C. Adjustment/Test - Aileron Balancing (See Figure ) () Adjustment/Test - Aileron Balancing Note: (a) To balance the aileron, the assembly must be painted, including the inboard and outboard hinges, actuation arm assembly, and all attaching hardware. Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Grease Pencil - Any Source Mark chord line. Close Tolerance Balance Pins - Any Source Support aileron. Knife Edge Supports - Any Source Support aileron. Balance Arm Assembly - Any Source Verify position of aileron chord line. String - Any Source Attach cup to aileron. Tape - Any Source Attach cup to aileron. Paper Cup - Any Source Determine required weight for balance. Scale - Any Source Determine required weight for balance. Lead Washers Cirrus Design Add weight to aileron. Duluth, MN (b) Verify workbench is level in all directions. (c) Ensure knife edge supports and balance arm assembly are parallel to workbench top. (d) Remove aileron. (Refer to ) Note: The chord line is defined as the line extending from the trailing edge through the hinge line. It is perpendicular to the spar. (e) (f) (g) (h) Mark the chord line on the inboard rib shear web. Place aileron assembly on knife edge supports. Determine if a static imbalance exists. The aileron is balanced if aileron chord line mark is parallel to balance arm. A static overbalance exists if aileron is leading edge heavy. A static underbalance exists if aileron is trailing edge heavy. Determine the amount of static imbalance. Note: Ensure paper cup hangs centered and vertical with no contact with aileron. All Attach paper cup to one end of string. For static underbalance condition, attach string to leading edge of aileron. For static overbalance condition, attach string to trailing edge of aileron. Add mounting hardware to paper cup. Add lead washers to cup until aileron chord line mark is parallel to balance arm. Page

14 (i) Calculate the aileron static balance. In overbalance conditions, the static balance (M) is defined as M = D W. In underbalance conditions, the static balance (M) is defined as M = D W - where D = distance perpendicular from hinge line to center of gravity (C.G.) of added mass, W = weight required to balance the aileron. Note: The value of M is positive for overbalance conditions and negative for underbalance conditions. Static balance must be within +.0 in-lb overbalance and 0.0 in-lb underbalance. Assuming a deviation of ±0. in-lb exists due to measurement error, calculated static balance must therefore fall within in-lb overbalance and 0.0 in-lb underbalance. Measure distance perpendicular from hinge line to C.G. of added mass in paper cup. Weigh string, cup, and contents with a calibrated scale. Using obtained measurements, solve formula to determine aileron static balance. Verify static balance is within in-lb overbalance and 0.0 in-lb underbalance. Example: Assume an aileron is underbalanced. If balance is achieved by adding 0.06 pounds,.7 inches forward of the hingeline, the aileron static balance is: W = 0.06 pound D =.7 inches M = (0.06.7) - = -0. in-lb In the example, -0. in-lb exceeds the tolerance for a static underbalance condition. To obtain aileron balance, 0. in-lb must be added forward of the hingeline. The balance must be rechecked to ensure static balance tolerance is not exceeded. CAUTION: Do not exceed a maximum mass balance weight of.0 pounds (0.8 kg) at each mounting location. Do not exceed a maximum of four washers per bolt or nut. Always place steel washer next to nut. (j) Add or remove weight as necessary to balance the aileron. An underbalanced condition is corrected by adding lead washers under the bolts securing the outboard and inboard mass balances. An overbalance condition is corrected by removing small amounts of material from the outboard and inboard lead mass balance in equal quantities. Typically this is done by drilling or other means. (k) Tighten mass balance bolts to 0 - in-lb (. -.8 Nm). (l) Install aileron. (Refer to ) Page All

15 In overbalance conditions, the static balance (M) = D x W. In underbalance conditions, the static balance (M) = D x W x -. D = Distance perpendicular from hinge line to center of gravity of added mass. W = Weight required to balance the aileron. D 6 W SECTION A HINGE LINE SECTION A CHORD LINE 6 D NOTE Add mounting hardware and lead washers to cup until chord line is parallel to balance arm. Add lead washers to mass balance attachment hardware to correct underbalance condition. Remove mass balance material to correct overbalance condition. LEGEND. Aileron. Knife Edge Support. Balance Arm. Tape. String 6. Cup SR_MM7_79 All Figure Aileron Balancing Page

16 D. Adjustment/Test - Aileron Trim Tab () Adjustment/Test - Aileron Trim Tab WARNING: Maintenance check flight must be performed by a qualified pilot. (a) (b) (c) (d) (e) (f) (g) Ensure both fuel tanks contain equal amounts of fuel. After airplane is in flight in smooth air, set throttle to full power. Trim airplane to achieve 60 knots indicated air speed (KIAS). Input full aileron trim left while holding wings level and let go of control yoke. Observe and note amount of time required until a 0 bank has been achieved. Input full aileron trim right while holding wings level and let go of control yoke. Observe and note amount of time required until a 0 bank has been achieved. Note: The amount of time required to achieve a 0 LH bank and a 0 RH bank should be approximately equal. If airplane rolls left too quickly, bend trailing edge of aileron trim tab down. Support trim tab at the bend when adjusting to ensure trim tab does not bend at the rivets and pull away from wing. Do not bend trailing edge of aileron trim tab up more than or down more than 0. (h) If required, bend aileron trim tab in small increments (approximately ) and repeat maintenance check flight. Page 6 All

17 E. Aileron Gap Seal - Serials 000 thru 7 (See Figure 6) () Removal - Aileron Gap Seal (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Smart Eraser Pad 00E Astro Pneumatic Tools Co. Remove residue. City Of Industry, CA General Purpose Adhesive Cleaner 0898 M Company St. Paul, MN Remove residue. Isopropyl Alcohol TT-I-7 Grade A or Grade B Any Source Clean installation area. Cotton Cloth (clean and lint free) - Any Source Clean installation area. (b) Pull aileron gap seal from edge of wing. (c) Remove tape residue from wing installation area using eraser pad. (d) Remove any remaining residue from wing installation area using cleaner. (e) Solvent clean installation area on wing. (Refer to 0-0) () Installation - Aileron Gap Seal (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Masking Tape - Any Source Limit primer application area. Two-Sided Tape Primer 9 M Company Promote tape adhesion St. Paul, MN at installation area Paper Towels - Any Source Apply primer. Two-Sided Transfer Adhesive Tape 0.00 inch (0.7 mm) thick F-969PC M Company Secure gap seal to St. Paul, MN wing Utility Knife - Any Source Trim excess tape. Squeegee - Any Source Apply surface pressure. (b) Apply masking tape 0.0 inch (0.6 cm) forward from aft edge of wing from WS ±.0 to WS ±97.. (c) With paper towel, apply tape primer from aft edge of wing forward to masked off area from WS ±.0 to WS ±97.. Serials 000 thru 7 CAUTION: Do not stretch two-sided transfer adhesive tape during installation. Apply tape straight to avoid wrinkles. Page 7

18 (d) Apply two-sided tape along aft edge length of wing from WS ±.0 to WS ±97.. CAUTION: Do not cut into the wing when trimming excess tape. (e) Use utility knife to trim excess tape from aft edge of wing. CAUTION: Verify aileron gap seal is installed glossy side up. (f) Position end of aileron gap seal 0.0 inch (0. cm) from inboard aileron hinge and 0.0 ±0.06 inch (.7 ±0. cm) over aft edge of wing. (g) Install aileron gap seal to taped installation area from WS ±.0 to WS ±97. straight along aft edge of wing. (h) Use squeegee to press aileron gap seal firmly to wing surface. Ensure all edges are firmly adhered. Page 8 Serials 000 thru 7

19 0.0 inch (0.6 cm) 0.0 ±0.06 inch (.7 ±0. cm) 0.0 inch (0. cm) WS 97. INBOARD AILERON HINGE WS.0 WING RIGHT HAND SHOWN NOTE Verify aileron gap seal is installed glossy side up. Do not stretch two-sided transfer adhesive tape during installation. Apply tape straight to avoid wrinkles. With paper towel, apply tape primer from aft edge of wing forward to masked off area from WS.0 to WS 97.. Do not cut into the wing when trimming excess tape. Serials 000 thru, thru 9, 0 thru 7. LEGEND. Masking Tape. Two-Sided Tape. Aileron Gap Seal SR_MM7_06A Serials 000 thru 7 Figure 6 Aileron Gap Seal Installation - Serials 000 thru 7 Page 9

20 F. Aileron Gap Seal - Serials 8 & subs (See Figure 7) () Removal - Aileron Gap Seal (a) TBD. Contact Cirrus Design for disposition. () Installation - Aileron Gap Seal (a) TBD. Contact Cirrus Design for disposition. Page 0 Serials 8 & subs

21 RESERVED FOR SR_MM7_67 Serials 8 & subs Figure 7 Aileron Gap Seal Installation - Serials 8 & subs Page

22 G. Flap Assembly - Serials 000 thru 7 (See Figure 8) () Removal - Flap Assembly (a) Cut safety wire securing rod end mounting bolt to flap actuation fitting. CAUTION: When disconnecting rod end, exercise caution to prevent flap from swinging downward and making contact with landing gear. (b) Remove bolt and washer securing rod end to flap. Carefully lower flap. (c) Serials 000 thru 9 before SB X-7-06: For inboard flap hinge, remove bolt, spacer, washer, and nut securing fairing to flap hinge. (d) Serials 0 thru 7, 000 thru 9 after SB X-7-06: For inboard flap hinge, remove bolts, spacers, washers, and nuts securing stiffener to flap fairing. Remove stiffener from airplane. (e) Serials 0 thru 7, 000 thru 9 after SB X-7-06: For mid and outboard flap hinges, remove bolts, spacers, washers, and nuts securing fairing to flap hinge. (f) For inboard, mid, and outboard flap hinges, remove bolt, washers, nut, and cotter pin securing flap and fairing to flap hinge. Remove flap and fairings from airplane. () Installation - Flap Assembly CAUTION: Flap mounting bolts must be installed with nuts facing inboard. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Safety Wire - Any Source Secure flap. Loctite Any Source Secure flap fairing. (b) (c) (d) (e) Position flap and fairings to hinges and secure with bolts, washers, nuts, and cotter pins. Serials 000 thru 9 before SB X-7-06: For inboard flap hinge, pivot fairing upward against flap hinge and secure with bolt, spacer, washer, and nut. Serials 0 thru 7, 000 thru 9 after SB X-7-06: Install stiffener to inboard fairing. Position slotted end of stiffener to upper edge of inboard flap hinge. Pivot fairing upward against flap hinge and over stiffener. Install bolts, washers, and nuts securing stiffener to fairing. Serials 0 thru 7, 000 thru 9 after SB X-7-06: For mid and outboard flap hinges, pivot fairing upward against flap hinge and secure with bolts, spacers, washers, and nuts. CAUTION: Flap must pivot freely on all three hinge bolts. If flap does not pivot freely, the problem must be corrected before securing actuation rod end. Page (f) Verify flap moves smoothly and uninhibited through full range of motion. (g) Position rod end to flap actuation fitting and secure with bolt and washer. (h) Safety wire rod end mounting bolt to flap actuation fitting. (i) Perform Adjustment/Test - Flap Force Limitation. (Refer to ) (j) Perform Operational Inspection - Flap System. (Refer to ) () Operational Inspection - Flap System (a) Set BAT switch to ON position. Serials 000 thru 7

23 (b) (c) (d) (e) Set flaps switch to UP position. Set flaps switch to 00% position. Verify flap moves smoothly and uninhibited through full range of motion. Verify flap position light illuminates correctly at UP, 0%, and 00% positions. Note: Serials 000 thru 7: Limited contact between flap and flap cove is permissible when the antichafe material is installed on flap. (f) Serials 000 thru 7: Visually inspect for contact or rubbing between flap and flap cove. If flap surface contacts flap cove, install flap rub strip. (Refer to ) Serials 000 thru 7 Page

24 7 9 7 TORQUE TUBE ASSEMBLY 8 NOTE Bolt, spacer, washer and nut are optional. FLAP HINGE If necessary, adjust length of spacer so that distance between outer surfaces of fairing does not exceed 0.9 inch (. cm). Nominal length of spacer is 0.67 inch (.70 cm). 6 0 FLAP HINGE 0 Page FLAP HINGE LEGEND. Flap Assembly. Bolt. Washer. Nut. Cotter Pin 0 6. Spacer 7. Rod End 8. Threaded Rod 9. Jam Nut 0. Fairing. Vinyl Trim Serials 000 thru 9 before SB X Figure 8 Flap Installation - Serials 000 thru 9 before SB X-7-06 (Sheet of ) Serials 000 thru 9 before SB X-7-06 SR_MM7_860B

25 7 9 7 TORQUE TUBE ASSEMBLY 8 FLAP HINGE 0 FLAP HINGE 6 0 Figure 8 Flap Installation - Serials 0 thru 7, 000 thru 9 after SB X-7-06 (Sheet of ) Serials 0 thru 7, 000 thru 9 after SB X-7-06 FLAP HINGE 6 0 Serials 0 thru 7, 000 thru 9 after SB X LEGEND. Flap Assembly. Bolt. Washer. Nut. Cotter Pin 6. Spacer 7. Rod End 8. Threaded Rod 9. Jam Nut 0. Fairing. Rub Strip. Stiffener. Rubber Seal SR_MM7_9A Page

26 () Adjustment/Test - Flap Force Limitation - Serials 000 thru 7 (See Figure 9) The maximum acceptable force to remove the flap from the full-up position is pounds or less. The flap force Adjustment/Test is performed at the time of installation when there is flap contact with the flap cove. Limited contact between the flap and flap cove is permissible when the antichafe material is installed on the flap. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Calibrated Spring Scale A Chatillon Largo, Florida Measure force required to deploy flaps. Safety Wire MS099C Any Source Retain part. (b) Cut safety wire securing rod end mounting bolt to flap actuation fitting. CAUTION: When disconnecting rod end, exercise caution to prevent flap from swinging downward and making contact with landing gear. (c) (d) Remove bolt and washer securing flap to push/pull rod end. Install bolt and attach spring scale to actuation fitting. Note: This test requires two people. One must prevent flap from swinging downward while the other performs spring scale test. A force of pounds or less is acceptable. If force is greater than pounds, contact Cirrus Design for disposition. Note: To replicate flap operating forces during Adjustment/Test, ensure spring scale is positioned in same orientation as installed flap push/pull rod. (e) (f) (g) Position and pull spring scale in same orientation as installed flap push/pull rod and note force required to remove flap from full-up position. Position push/pull rod end to flap actuation fitting and secure with bolt and washer. Safety wire rod end mounting bolt to flap actuation fitting. Page 6 Serials 0 thru 7, 000 thru 9 after SB X-7-06

27 INBOARD FLAP HINGE NOTE To replicate flap operating forces, during Adjustment/Test, ensure spring scale is positioned in same orientation as installed push/pull rod. Serials 000 thru, thru 9, 0 thru 7. LEGEND. Spring Scale. Flap Push/Pull Rod. Bolt. Actuation Fitting SR_MM7_00B Serials 000 thru 7 Figure 9 Flap Force Limitation Test - Serials 000 thru 7 Page 7

28 H. Flap Assembly - Serials 8 & subs (See Figure 0) () Removal - Flap Assembly (a) Cut safety wire securing rod end mounting bolt to flap actuation fitting. CAUTION: When disconnecting rod end, exercise caution to prevent flap from swinging downward and making contact with landing gear. (b) Remove bolt and washer securing rod end to flap. Carefully lower flap. (c) At inboard, mid, and outboard flap hinges, remove bolt, washers, nut, and cotter pin securing flap to flap hinge. Remove flap from airplane. () Installation - Flap Assembly CAUTION: Flap mounting bolts must be installed with nuts facing inboard. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Safety Wire - Any Source Secure flap. Loctite Any Source Secure flap fairing. (b) Position flap to hinges and secure with bolts, washers, nuts, and cotter pins. CAUTION: Flap must pivot freely on all three hinge bolts. If flap does not pivot freely, the problem must be corrected before securing actuation rod end. (c) Verify flap moves smoothly and uninhibited through full range of motion. (d) Position rod end to flap actuation fitting and secure with bolt and washer. (e) Safety wire rod end mounting bolt to flap actuation fitting. (f) Perform Operational Inspection - Flap System. (Refer to ) () Operational Inspection - Flap System (a) Set BAT switch to ON position. (b) Set flaps switch to UP position. (c) Set flaps switch to 00% position. (d) Verify flap moves smoothly and uninhibited through full range of motion. (e) Verify flap position light illuminates correctly at UP, 0%, and 00% positions. (f) Visually inspect for contact or rubbing between flap and flap cove. If flap surface contacts flap cove, contact Cirrus Design for disposition. Page 8 Serials 8 & subs

29 6 8 6 TORQUE TUBE ASSEMBLY 7 FLAP HINGE FLAP HINGE FLAP HINGE LEGEND. Flap Assembly. Bolt. Washer. Nut. Cotter Pin 6. Rod End 7. Threaded Rod 8. Jam Nut 9. Fairing 0. Screw SR_MM7_6 Serials 8 & subs Figure 0 Flap Installation - Serials 8 & subs Page 9

30 I. Flap Rub Strip - Serials 000 thru 7 (See Figure ) () Removal - Flap Rub Strip CAUTION: Do not allow the structure temperature to exceed 0 F (6. C) when applying heat with hot-air blower. Excessive heat may result in loss of structural integrity. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Denatured Alcohol - Any Source Solvent. Hot-Air Blower - Any Source Flap rub strip removal. (b) Apply heat with hot-air blower until adhesive loosens from flap surface. (c) Peel flap rub strip away from surface, using additional heat if necessary. (d) Solvent clean surface to remove residual adhesive. (Refer to 0-0) () Installation - Flap Rub Strip (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Self Adhesive Flap Rub Strip Cirrus Design Duluth, MN Flap protection. Denatured Alcohol - Any Source Solvent. Water Wash - Any Source Surface cleaning. Scotch Plastic Tape 7 Blue, 0. Inch 060 M Company Flap rub strip alignment. St. Paul, MN Squeegee - Any Source Application of surface pressure. (b) Water wash surface where flap rub strip is to be installed. (c) Solvent clean surface where flap rub strip is to be installed. (Refer to 0-0) (d) Raise flap to full up position. Note: Only 0.0 inch (0.6 cm) of flap rub strip should be visible with flap in fullup position. Use plastic tape to ensure proper alignment of flap rub strip. (e) (f) (g) Apply plastic tape along entire length of flap, leaving a margin of 0.0 inch (0.6 cm) between forward edge of tape and trailing edge of wing skin. Lower the flap. Remove protective backing from flap rub strip using care not to contaminate adhesive surface. Note: Avoid stretching flap rub strip as poor adhesion will result. Page 0 Serials 000 thru 7

31 (h) Using plastic tape as a guide, place one edge of flap rub strip on surface and work across flap to eliminate wrinkles and air pockets. (i) Press flap rub strip firmly to surface with squeegee. Ensure all edges are firmly adhered. (j) Remove plastic tape. (k) Solvent clean as necessary to remove adhesive residue. (Refer to 0-0) (l) Perform Adjustment/Test - Flap Force Limitation. (Refer to ) Serials 000 thru 7 Page

32 AILERON WING TRAILING EDGE 0.0 inch (0.6 cm) FULLY DEFLECTED DOWN (00%) FULLY DEFLECTED UP (0%) LEGEND. Flap Rub Strip. Flap Assembly. Plastic Tape Serials 000 thru, thru 9, 0 thru 7. SR_MM7_08A Page Figure Flap Rub Strip Installation - Serials 000 thru 7 Serials 000 thru 7