ICE PROTECTION - AIRFOIL

Transcription

1 ICE PROTECTION - AIRFOIL 1. DESCRIPTION This section describes the portion of the Ice Protection System pertaining to the airfoils. This includes the porous panels. Each porous panel consists of a front titanium plate, porous plastic membrane interior, and back titanium plate. The titanium plates are sealed together and the proportioning unit delivers deicing fluid to a central reservoir between the two plates. The front plate contains small laser drilled holes that allow the fluid to weep to the exterior surface. Serials & subs, 22T-0001 & subs w/ Basic or Basic² Ice Protection: Inboard and outboard porous panels are installed to the leading edge of the wing. Two porous panels are installed on the leading edge of the horizontal stabilizer. Serials w/ FIKI: Inboard and outboard porous panels are installed to the leading edge of the wing. Two porous panels are installed on the leading edge of the horizontal stabilizer. One porous panel is installed on the leading edge of the vertical stabilizer. A porous panel is installed on each elevator tip. WARNING: Installation of the inboard porous panels on the wing requires a flight test be performed by a Cirrus Design authorized test pilot. Contact Cirrus Design prior to performing maintenance to schedule a test flight. Installation of the outboard wing, horizontal, elevator tip, and vertical stabilizer porous panels requires a maintenance flight check to be performed following installation. This flight check can be completed by anyone who possess the necessary training, ratings, and currency in accordance with the FAR's, provided the ice panels are fit back into their original positions. If the panel is not able to be fit into its original position or if the flying qualities of the aircraft are changed contact Cirrus Design for further disposition. WARNING: Porous panels cannot be re-used. If removed, porous panel must be discarded and replaced with new porous panel. Do not wax the leading edge of porous panels. Certain solvents may damage the panel membrane. Only the following materials are approved for use on the porous panel; soap and water, approved deicing fluid, avgas, jet fuel, isopropyl alcohol, and ethyl alcohol. Do not allow acetone to contact porous panel membranes; the material is soluble in acetone. Do not expose the porous panels to temperatures higher than 158 F (70 C). For information on porous panel cleaning refer to the Scheduled Servicing Section of Chapter 12 - Servicing. (Refer to 12-20) Page 1 01 May 2012

2 2. MAINTENANCE PRACTICES A. Wing Porous Panels (See Figure 1), (See Figure 2) Do not allow acetone to contact porous panel membranes; the material is soluble in acetone. (1) Removal - Wing Porous Panels (See Figure 1) (a) Acquire necessary tools, equipment, and supplies. Drill Bit #30 Any Source Rivet removal. Putty Knife 2-Inch, Thin Any Source Panel removal. (b) (c) (d) (e) (f) (g) (h) Round off edges of putty knife blade to obtain approximately 1/8-inch radius. If removing inboard wing porous panel, remove wing root fairing: 1 Serials thru w/ Basic Ice Protection: Remove wing access panels LW6 and LW16 or RW6 and RW16. 2 Serials & subs, 22T-0001 & subs: Remove wing access panels LW4 and LW9 or RW4 and RW9. Place container below coupling to catch fluid drip. Disconnect nut(s), olive(s), and O-ring(s) securing feed line(s) to porous panel. Cap feed lines to prevent system contaminates. Drill out rivets securing porous panel to wing. Apply 3 strips of duct tape above, below, and parallel to porous panel for paint protection. Carefully use low angle of attack at sealant with putty knife upside-down. To avoid inflicting damage to composite surfaces, position long edge of putty knife blade toward porous panel. If cracking of composite is perceived, stop procedure and contact Cirrus Design for disposition. (i) At edge of inboard and/or outboard porous panel, position putty knife at 45 angle and work around porous panel until loosened from adhesive. (j) Inboard porous panel: Disconnect de-ice line at inboard porous panel. (k) Remove and discard porous panel. (2) Installation - Wing Porous Panels (See Figure 2) (a) Acquire necessary tools, equipment, and supplies. Low Tack Masking Tape No M St. Paul, MN Protect porous panel from contaminates. Putty Knife 2-Inch, Thin Any Source Adhesive removal. Page 2

3 Scotch-Brite Scouring Pads M St. Paul, MN Adhesive removal. Sandpaper 120-grit to 400-grit Any Source Abrade bonding surface. Compressed Air (contaminate free) - Any Source General cleaning. Acetone - Any Source Solvent cleaning. Isopropyl Alcohol 99% or higher purity Any Source Solvent cleaning. Wax and Grease Remover Cotton Cloth (clean and lint free) DX330 Any Source Solvent cleaning. - Any Source General cleaning. Sealant Per MIL-S-8802F AC-240 B½ Quick Cure Dynamold Aerospace Products Fort Worth, TX Porous panel adhesive. Sealant Per AMS 3277, Type 2 PR2001 Class B ½ PRC - Desoto International Glendale, CA Porous panel adhesive. Adhesion Promoter PR182 Pink PRC - Desoto International Glendale, CA Porous panel adhesive. Pull Straps - Any Source Bonding tool. Rivet CR Any Source Fastener. WS 58 Template WS 75 Template WS 92 Template WS 109 Template WS 127 Template WS 133 Template WS 148 Template WS 163 Template WS 178 Template WS 194 Template WS 211 Template T10584 T10585 T10586 T10587 T10588 T10589 T10590 T10591 T10592 T10593 T10599 Cirrus Design Duluth, MN Verify leading edge contour. Page 3 15 Dec 2014

4 Serials & subs, 22T-0001 & subs: WS 30.7 Template WS 63.2 Template WS 97.2 Template WS Template WS 132 Template WS Template WS Template WS Template T7366 T7367 T7368 T7369 T7370 T7371 T7372 T7373 Cirrus Design Duluth, MN Verify leading edge contour. Foam Block - Any Source Protect trailing edge. (b) Cover fluid dispensing holes of porous panel with low tack tape and cap inlet valves to prevent contaminates. (c) Remove aileron. (Refer to 57-50) (d) Remove flap assembly. (Refer to 57-50) (e) Prepare wing surface. Exercise caution to prevent cutting into composite laminate. 1 Using putty knife and scouring pads, carefully remove any remaining adhesive from wing. Exercise caution when sanding composite surfaces to prevent sanding into the laminate. Cover any system that may be contaminated by dust. 2 Lightly sand the bonding area with 120-grit sandpaper. 3 Blow surface clean with compressed air. Wipe surface in one direction only to prevent smearing contaminates. For maximum results, wipe dry with clean white cloths in one direction only, while the surface is still wet. (f) (g) (h) (i) (j) (k) 4 Using acetone, solvent clean prepared surface. 5 Using isopropyl alcohol, solvent clean prepared surface. Ensure outboard porous panel is the correct length. 1 Align inboard end of panel with inboard edge of wing cuff. 2 Align outboard end of panel with end of wing cuff offset. 3 If necessary, trim outboard end of panel to fit. Ensure inboard porous panel is the correct length. 1 Align outboard end of panel with inboard edge of wing cuff. 2 Align inboard end of panel with inboard wing offset. 3 If necessary, trim inboard end of panel to fit. Using templates, verify aerodynamic contour of leading edges. Fit-up porous panel and verify that rivet holes are aligned. While holding porous panel in place, mask around perimeter of panel with tape. Attach inboard porous panel. Page 4

5 Only use adhesion promoter with PR2001 Class B ½ sealant. Do not use adhesive promoter with AC-240 B½ Quick Cure sealant. Do not apply adhesion promoter to composite bonding surface. 1 If using PR2001 Class B ½ sealant, apply adhesion promoter to porous panel and allow to dry minutes. Mix adhesive thoroughly. Avoid entrapping air during the mixing process. No color swirls or variation is allowed. 2 Apply 3/16 inch diameter bead of adhesive approximately 1/4 inch from edges of porous panel bonding area, top and bottom. 3 Connect nut(s), olive(s), and new O-ring(s) securing feed line(s) to porous panel by hand tightening nut and then turning additional 180 with wrench. 4 Position porous panel to wing and press into place. 5 Fill gap beneath cuff end of porous panel with adhesive. Place shop towel between pull strap buckle and wing to protect wing surface. Place foam block between strap and trailing edge of wing to prevent damage to trailing edge. (l) 6 Serials thru w/ Basic Ice Protection: Strap porous panel into place with four evenly spaced pull straps. 7 Serials & subs, 22T-0001 & subs: Strap porous panel into place with five evenly spaced pull straps. 8 Skim excess adhesive away from edge of porous panel and remove tape. Attach outboard porous panel. Only use adhesion promoter with PR2001 Class B ½ sealant. Do not use adhesive promoter with AC-240 B½ Quick Cure sealant. Do not apply adhesion promoter to composite bonding surface. 1 If using PR2001 Class B ½ sealant, apply adhesion promoter to porous panel and allow to dry minutes. Mix adhesive thoroughly. Avoid entrapping air during the mixing process. No color swirls or variation is allowed. 2 Apply 3/16 inch diameter bead of adhesive approximately 1/4 inch from edges of porous panel bonding area, top and bottom. 3 Position porous panel to wing and press into place. Place shop towel between pull strap buckle and wing to protect wing surface. Place foam block between strap and trailing edge of wing to prevent damage to trailing edge. 4 Serials thru w/ Basic Ice Protection: Strap porous panel into place with three evenly spaced pull straps. 5 Serials & subs, 22T-0001 & subs: Strap porous panel into place with four evenly spaced pull straps. 6 Skim excess adhesive away from edge of porous panel and remove tape. Page 5

6 Certain solvents may damage the panel membrane. Use only isopropyl alcohol, ethyl alcohol, or industrial methylated spirit. (m) Solvent clean to remove any excess adhesive from wing surface. (Refer to 20-30) (n) ow adhesive to cure for 24 hours. Ensure rivet holes are clean and free of debris. (o) Transfer drill and countersink rivet holes. Install rivets securing porous panel to wing assembly. Use the porous panel finishing procedures to seal gap between trailing edge of porous panel and airframe. Finishing Method #3 is preferred for new porous panel installations. If replacing porous panel on only one side of airplane, Finishing Method #1 or #2 may be used to maintain a uniform appearance between RH and LH porous panels. (p) Perform Procedure - Porous Panel Finishing. (Refer to ) Porous panels incorporate vents opposite the fluid inlets. Do not cover these vents as poor system performance will result. (q) Fill interface at both ends of inboard panel with adhesive and allow to cure for 24 hours. (r) Fill interface at outboard end of outboard panel with adhesive and allow to cure for 24 hours. (s) Remove low tack tape covering fluid dispensing holes of porous panel. (t) Using templates, verify completed joint meets aerodynamic contour requirements. (u) Connect nut(s), olive(s), and new O-ring(s) securing feed line(s) to porous panel by hand tightening nut and then turning additional 180 with wrench. (v) Install flap assembly. (w) Install aileron. (Refer to 57-50) (x) Install stall strips. (Refer to 57-20) (y) Perform Procedure - Wing Porous Panel Purge. (Refer to 30-00) (z) Perform Operational Check - Ice Protection System. (Refer to 30-00) (aa) If replacing inboard wing porous panel, install wing root fairing: 1 Serials thru w/ Basic Ice Protection: Install wing access panels LW6 and LW16 or RW6 and RW16. 2 Serials & subs, 22T-0001 & subs: Install wing access panels LW4 and LW9 or RW4 and RW9. Page 6

7 B. Horizontal Stabilizer Porous Panel (See Figure 1), (See Figure 2) Do not allow acetone to contact porous panel membranes; the material is soluble in acetone. (1) Removal - Horizontal Stabilizer Porous Panel (See Figure 1) (a) Acquire necessary tools, equipment, and supplies. Drill Bit #30 Any Source Rivet removal. Putty Knife 2-Inch, Thin Any Source Panel removal. (b) (c) (d) (e) (f) (g) (h) Round off edges of putty knife blade to obtain approximately 1/8-inch radius. Remove horizontal stabilizer access panel. Place container below coupling to catch fluid drip. Disconnect nuts, olives, and O-rings securing feed line to porous panel. Cap feed lines to prevent system contaminates. Drill out rivets securing porous panel to horizontal stabilizer. Apply 3 strips of duct tape above, below, and parallel to porous panel for paint protection. Carefully use low angle of attack at sealant with putty knife upside-down. To avoid inflicting damage to composite surfaces, position long edge of putty knife blade toward porous panel. If cracking of composite is perceived, stop procedure and contact Cirrus Design for disposition. (i) At edge of porous panel, position putty knife at 45 angle and work around porous panel until loosened from adhesive. (j) Remove and discard porous panel. (2) Installation - Horizontal Stabilizer Porous Panel (See Figure 2) (a) Acquire necessary tools, equipment, and supplies. Low Tack Masking Tape No M St. Paul, MN Protect porous panel from contaminates. Putty Knife 2-Inch, Thin Any Source Adhesive removal. Scotch-Brite Scouring Pads M St. Paul, MN Adhesive removal. Sandpaper 120-grit to 400-grit Any Source Abrade bonding surface. Compressed Air (contaminate free) - Any Source General cleaning. Page 7

8 Acetone - Any Source Solvent cleaning. Isopropyl Alcohol 99% or higher purity Any Source Solvent cleaning. Cotton Cloth (clean and lint free) - Any Source General cleaning. Sealant Per MIL-S-8802F AC-240B½ Quick Cure Dynamold Aerospace Products Fort Worth, TX Porous panel adhesive. Sealant Per AMS 3277, Type 2 PR2001 Class B ½ PRC - Desoto International Glendale, CA Porous panel adhesive. Adhesion Promoter PR182 Pink PRC - Desoto International Glendale, CA Porous panel adhesive. Pull Straps - Any Source Bonding tool. Rivet CR Any Source Fastener. HS 12 Template T2267 Cirrus Design Verify leading edge contour. HS 24 Template T2268 Cirrus Design Verify leading edge contour. HS 36 Template T2269 Cirrus Design Verify leading edge contour. HS 48 Template T2270 Cirrus Design Verify leading edge contour. HS 60 Template T2271 Cirrus Design Verify leading edge contour. HS 72 Template T2272 Cirrus Design Verify leading edge contour. Foam Block - Any Source Protect trailing edge. (b) Cover fluid dispensing holes of porous panel with low tack tape and cap inlet valves to prevent contaminates. (c) Remove elevator. (Refer to 55-20) (d) Prepare bonding surface of horizontal stabilizer. Exercise caution to prevent cutting into laminate. Page 8 15 Dec 2014

9 1 Using putty knife and scouring pads, carefully remove any removing adhesive from horizontal stabilizer. Exercise caution when sanding composite surfaces to prevent sanding into the laminate. Cover any system that may be contaminated by dust. 2 Lightly sand the bonding area with 120-grit sandpaper. 3 Blow surface clean with compressed air. Wipe surface in one direction only to prevent smearing contaminates. For maximum results, wipe dry with clean white cloths in one direction only, while the surface is still wet. (e) (f) (g) (h) (i) 4 Using acetone, solvent clean prepared surface. 5 Using isopropyl alcohol, solvent clean prepared surface. Ensure porous panel is the correct length. 1 Align outboard end of panel with outboard end of horizontal stabilizer. 2 Align inboard end of panel with inboard offset. 3 If necessary, trim inboard end of panel to fit. Using templates, verify aerodynamic contour of leading edge. Fit-up porous panel and verify that rivet holes are aligned. While holding porous panel in place, mask around perimeter of panel with tape. Attach porous panel. Only use adhesion promoter with PR2001 Class B ½ sealant. Do not use adhesive promoter with AC-240 B½ Quick Cure sealant. Do not apply adhesion promoter to composite bonding surface. 1 If using PR2001 Class B ½ sealant, apply adhesion promoter to porous panel and allow to dry minutes. Mix adhesive thoroughly. Avoid entrapping air during the mixing process. No color swirls or variation is allowed. 2 Apply 3/16 inch diameter bead of adhesive approximately 1/4 inch from edges of porous panel bonding area, top and bottom. 3 Position porous panel to horizontal stabilizer and press into place. 4 Fill gap beneath outboard end of porous panel with adhesive. Place shop towel between pull strap buckle and horizontal to protect horizontal surface. Place foam block between strap and trailing edge of horizontal to prevent damage to trailing edge. 5 Strap porous panel into place with three evenly spaced pull straps. 6 Skim excess adhesive away from edge of porous panel and remove tape. Certain solvents may damage the panel membrane. Use only isopropyl alcohol, ethyl alcohol, or industrial methylated spirit. (j) (k) Solvent clean to remove any excess adhesive from surface of horizontal stabilizer. ow adhesive to cure for 24 hours. Page 9

10 Ensure rivet holes are clean and free of debris. (l) Transfer drill and countersink rivet holes. Install rivets securing porous panel to horizontal stabilizer. Use the porous panel finishing procedures to seal gap between trailing edge of porous panel and airframe. Finishing Method #3 is preferred for new porous panel installations. If replacing porous panel on only one side of airplane, Finishing Method #1 or #2 may be used to maintain a uniform appearance between RH and LH porous panels. (m) Perform Procedure - Porous Panel Finishing. (Refer to ) Porous panels incorporate vents opposite the fluid inlets. Do not cover these vents as poor system performance will result. (n) (o) (p) (q) Fill interface at inboard end of porous panel with adhesive and allow to cure for 24 hours. Remove low tack tape covering fluid dispensing holes of porous panel. Using templates, verify completed joint meets aerodynamic contour requirements. Connect nut, olive, and new O-ring securing feed lines to porous panel by hand tightening the nut and then turning additional 180 with wrench. (r) Install elevator. (Refer to 55-20) (s) Perform Procedure - Horizontal Stabilizer Porous Panel Purge. (Refer to 30-00) (t) Perform Operational Check - Ice Protection System. (Refer to 30-00) (u) Install horizontal stabilizer access panel. Page 10

11 C. Vertical Stabilizer Porous Panel - Serials w/ FIKI (See Figure 1), (See Figure 2) Do not allow acetone to contact porous panel membranes; the material is soluble in acetone. (1) Removal - Vertical Stabilizer Porous Panel (See Figure 1) (a) Acquire necessary tools, equipment, and supplies. Drill Bit #30 Any Source Rivet removal. Putty Knife 2-Inch, Thin Any Source Panel removal. (b) (c) (d) (e) (f) (g) (h) Round off edges of putty knife blade to obtain approximately 1/8-inch radius. Remove vertical stabilizer access panel. Place container below coupling to catch fluid drip. Disconnect nuts, olives, and O-rings securing feed line to porous panel. Cap feed lines to prevent system contaminates. Drill out rivets securing porous panel to vertical stabilizer. Apply 3 strips of duct tape above, below, and parallel to porous panel for paint protection. Carefully use low angle of attack at sealant with putty knife upside-down. To avoid inflicting damage to composite surfaces, position long edge of putty knife blade toward porous panel. If cracking of composite is perceived, stop procedure and contact Cirrus Design for disposition. (i) At edge of porous panel, position putty knife at 45 angle and work around porous panel until loosened from adhesive. (j) Remove and discard porous panel. (2) Installation - Vertical Stabilizer Porous Panel (See Figure 2) (a) Acquire necessary tools, equipment, and supplies. Low Tack Masking Tape No M St. Paul, MN Protect porous panel from contaminates. Putty Knife 2-Inch, Thin Any Source Adhesive removal. Scotch-Brite Scouring Pads M St. Paul, MN Adhesive removal. Sandpaper 120-grit to 400-grit Any Source Abrade bonding surface. Serials w/ FIKI Compressed Air (contaminate free) - Any Source General cleaning. Page 11

12 Acetone - Any Source Solvent cleaning. Isopropyl Alcohol 99% or higher purity Any Source Solvent cleaning. Cotton Cloth (clean and lint free) - Any Source General cleaning. Sealant Per MIL-S-8802F AC-240B½ Quick Cure Dynamold Aerospace Products Fort Worth, TX Porous Panel adhesive. Sealant Per AMS 3277, Type 2 PR2001 Class B ½ PRC - Desoto International Glendale, CA Porous panel adhesive. Adhesion Promoter PR182 Pink PRC - Desoto International Glendale, CA Porous panel adhesive. Pull Straps - Any Source Bonding tool. Rivet CR Any Source Fastener. VS Template, Lower T10882 Cirrus Design Verify leading edge contour. VS Template, Mid T10883 Cirrus Design Verify leading edge contour. VS Template, Upper T10884 Cirrus Design Verify leading edge contour. Foam Block - Any Source Protect trailing edge. (b) (c) Cover fluid dispensing holes of porous panel with low tack tape and cap inlet valves to prevent contaminates. Prepare bonding surface of vertical stabilizer. Exercise caution to prevent cutting into laminate. 1 Using putty knife and scouring pads, carefully remove any removing adhesive from vertical stabilizer. Exercise caution when sanding composite surfaces to prevent sanding into the laminate. Cover any system that may be contaminated by dust. Page Dec Lightly sand the bonding area with 120-grit sandpaper. 3 Blow surface clean with compressed air. Serials w/ FIKI

13 Wipe surface in one direction only to prevent smearing contaminates. For maximum results, wipe dry with clean white cloths in one direction only, while the surface is still wet. (d) (e) (f) (g) (h) 4 Using acetone, solvent clean prepared surface. 5 Using isopropyl alcohol, solvent clean prepared surface. Ensure porous panel is the correct length. 1 Align upper end of panel with upper end of vertical stabilizer. 2 Align lower end of panel with lower offset. 3 If necessary, trim lower end of panel to fit. Using templates, verify aerodynamic contour of leading edge. Fit-up porous panel and verify that rivet holes are aligned. While holding porous panel in place, mask around perimeter of panel with tape. Attach porous panel. Only use adhesion promoter with PR2001 Class B ½ sealant. Do not use adhesive promoter with AC-240 B½ Quick Cure sealant. Do not apply adhesion promoter to composite bonding surface. 1 If using PR2001 Class B ½ sealant, apply adhesion promoter to porous panel and allow to dry minutes. Mix adhesive thoroughly. Avoid entrapping air during the mixing process. No color swirls or variation is allowed. 2 Apply 3/16 inch diameter bead of adhesive approximately 1/4 inch from edges of porous panel bonding area, top and bottom. 3 Position porous panel to vertical stabilizer and press into place. Place shop towel between pull strap buckle and vertical to protect vertical surface. Place foam block between strap and trailing edge of vertical to prevent damage to trailing edge. 4 Strap porous panel into place with three evenly spaced pull straps. 5 Skim excess adhesive away from edge of porous panel and remove tape. Certain solvents may damage the panel membrane. Use only isopropyl alcohol, ethyl alcohol, or industrial methylated spirit. (i) (j) Solvent clean to remove any excess adhesive from surface of vertical stabilizer. ow adhesive to cure for 24 hours. Ensure rivet holes are clean and free of debris. (k) Transfer drill and countersink rivet holes. Install rivets securing porous panel to vertical stabilizer. (l) Perform Procedure - Porous Panel Finishing Method #3. (Refer to ) Porous panels incorporate vents opposite the fluid inlets. Do not cover these vents as poor system performance will result. (m) Serials w/ FIKI Fill interface at ends of porous panel with adhesive and allow to cure for 24 hours. Page 13

14 (n) (o) (p) (q) (r) Remove low tack tape covering fluid dispensing holes of porous panel. Using lower template positioned 1 inch (2.54 cm) above bottom of ice panel, verify completed joint meets aerodynamic contour requirements. Using mid template positioned at middle of ice panel, verify completed joint meets aerodynamic contour requirements. Using upper template positioned 1 inch (2.54 cm) below top of ice panel, verify completed joint meets aerodynamic contour requirements. Connect nut, olive, and new O-ring securing feed lines to porous panel by hand tightening the nut and then turning additional 180 with wrench. (s) Perform Procedure - Vertical Stabilizer Porous Panel Purge. (Refer to 30-00) (t) Perform Operational Check - Ice Protection System. (Refer to 30-00) (u) Install vertical stabilizer access panel. Page 14 Serials w/ FIKI

15 D. Elevator Tip Porous Panel - Serials w/ FIKI (See Figure 1), (See Figure 2) Do not allow acetone to contact porous panel membranes; the material is soluble in acetone. (1) Removal - Elevator Tip Porous Panel (See Figure 1) (a) Acquire necessary tools, equipment, and supplies. Drill Bit #30 Any Source Rivet removal. Putty Knife 2-Inch, Thin Any Source Panel removal. (b) Round off edges of putty knife blade to obtain approximately 1/8-inch radius. (c) Remove elevator tip. (Refer to 55-20) (d) Place container below coupling to catch fluid drip. (e) Remove cable tie securing feed line to elevator tip. (f) Disconnect nut, olive, and O-ring securing feed line to porous panel. (g) Cap feed line to prevent system contaminates. (h) Drill out rivets securing porous panel to elevator tip. (i) Apply 3 strips of duct tape above, below, and parallel to porous panel for paint protection. Carefully use low angle of attack at sealant with putty knife upside-down. To avoid inflicting damage to composite surfaces, position long edge of putty knife blade toward porous panel. If cracking of composite is perceived, stop procedure and contact Cirrus Design for disposition. (j) At edge of porous panel, position putty knife at 45 angle and work around porous panel until loosened from adhesive. (k) Remove and discard porous panel. (2) Installation - Elevator Tip Porous Panel (See Figure 2) (a) Acquire necessary tools, equipment, and supplies. Low Tack Masking Tape No M St. Paul, MN Protect porous panel from contaminates. Putty Knife 2-Inch, Thin Any Source Adhesive removal. Scotch-Brite Scouring Pads M St. Paul, MN Adhesive removal. Sandpaper 120-grit to 400-grit Any Source Abrade bonding surface. Serials w/ FIKI Page 15

16 Compressed Air (contaminate free) - Any Source General cleaning. Acetone - Any Source Solvent cleaning. Isopropyl Alcohol 99% or higher purity Any Source Solvent cleaning. Cotton Cloth (clean and lint free) - Any Source General cleaning. Sealant Per MIL-S-8802F AC-240B½ Quick Cure Dynamold Aerospace Products Fort Worth, TX Porous Panel adhesive. Sealant Per AMS 3277, Type 2 PR2001 Class B ½ PRC - Desoto International Glendale, CA Porous panel adhesive. Adhesion Promoter PR182 Pink PRC - Desoto International Glendale, CA Porous panel adhesive. Pull Straps - Any Source Bonding tool. Rivet CR Any Source Fastener. Foam Block - Any Source Protect trailing edge. (b) (c) Cover fluid dispensing holes of porous panel with low tack tape and cap inlet valves to prevent contaminates. Prepare bonding surface of elevator tip. Exercise caution to prevent damaging elevator tip. 1 Using putty knife and scouring pads, carefully remove any removing adhesive from elevator. Exercise caution when sanding composite surfaces to prevent sanding into the laminate. Cover any system that may be contaminated by dust. 2 Lightly sand the bonding area with 120-grit sandpaper. 3 Blow surface clean with compressed air. Wipe surface in one direction only to prevent smearing contaminates. For maximum results, wipe dry with clean white cloths in one direction only, while the surface is still wet. Page Dec Using acetone, solvent clean prepared surface. Serials w/ FIKI

17 (d) (e) (f) (g) (h) 5 Using isopropyl alcohol, solvent clean prepared surface. Ensure porous panel is the correct length. 1 Align inboard end of panel with outboard end of horizontal. 2 Align outboard end of panel with outboard offset. 3 If necessary, trim inboard end of panel to fit. Using templates, verify aerodynamic contour of leading edge. Fit-up porous panel and verify that rivet holes are aligned. While holding porous panel in place, mask around perimeter of panel with tape. Attach porous panel. Only use adhesion promoter with PR2001 Class B ½ sealant. Do not use adhesive promoter with AC-240 B½ Quick Cure sealant. Do not apply adhesion promoter to composite bonding surface. 1 If using PR2001 Class B ½ sealant, apply adhesion promoter to porous panel and allow to dry minutes. Mix adhesive thoroughly. Avoid entrapping air during the mixing process. No color swirls or variation is allowed. 2 Apply 3/16 inch diameter bead of adhesive approximately 1/4 inch from edges of porous panel bonding area, top and bottom. 3 Position panel connector tube through hole in elevator tip. 4 Position porous panel to elevator tip and press into place. Place shop towel between pull strap buckle and elevator to protect elevator tip surface. Place foam block between strap and trailing edge of elevator tip to prevent damage to trailing edge. 5 Strap porous panel into place with one pull strap. 6 Skim excess adhesive away from edge of porous panel and remove tape. Certain solvents may damage the panel membrane. Use only isopropyl alcohol, ethyl alcohol, or industrial methylated spirit. (i) (j) Solvent clean to remove any excess adhesive from surface of elevator tip. ow adhesive to cure for 24 hours. Ensure rivet holes are clean and free of debris. (k) (l) (m) Transfer drill and countersink rivet holes. Install rivets securing porous panel to elevator tip. Connect nut, olive, and new O-ring securing feed line to porous panel by hand tightening the nut and then turning additional 180 with wrench. Install cable tie securing feed line to elevator tip. (n) Install elevator tip. (Refer to 55-20) (o) Perform Procedure - Porous Panel Finishing Method #3. (Refer to ) Porous panels incorporate vents opposite the fluid inlets. Do not cover these vents as poor system performance will result. (p) Serials w/ FIKI Fill interface at ends of porous panel with adhesive and allow to cure for 24 hours. Page 17

18 (q) Remove low tack tape covering fluid dispensing holes of porous panel. (r) Perform Adjustment/Test - Elevator Balancing. (Refer to 55-20) (s) Perform Procedure - Elevator Tip Porous Panel Purge. (Refer to 30-00) (t) Perform Operational Check - Ice Protection System. (Refer to 30-00) Page 18 Serials w/ FIKI

19 MASKING TAPE SEALANT MASKING TAPE COMPOSITE (REF) NOTE Apply 3 strips of duct tape above, below, and parallel to porous panel for paint protection. Carefully use low angle of attack at sealant with putty knife upside-down. To avoid inflicting damage to composite surfaces, position long edge of putty knife blade toward porous panel. LEGEND 1. Porous Panel 2. Adhesive SR22_MM30_3530 Figure 1 Porous Panel Removal Page 19

20 LEGEND 1. Porous Panel 2. Rivet 1 NOTE Serials w/ FIKI. 2 1 SR22_MM30_3126 Page 20 Figure 2 Porous Panel Installation (Sheet 1 of 2)

21 0.1 inch MAX 0.3 inch MIN 2 NON ZERO THICKNESS 1 LEADING EDGE SKIN (REF) NOTE Bond must meet requirements for at least 90% of the total bond length. No one area that does not meet requirements shall exceed 3 inches in length. LEGEND 1. Porous Panel 2. Adhesive SR22_MM30_1562A Figure 2 Porous Panel Installation (Sheet 2 of 2) Page 21

22 E. Porous Panel Finishing (See Figure 3) Do not allow acetone to contact porous panel membranes; the material is soluble in acetone. Use the porous panel finishing procedures to seal gap between trailing edge of porous panel and airframe. Finishing Method #3 is preferred for new porous panel installations. If replacing porous panel on only one side of airplane, Finishing Method #1 or #2 may be used to maintain a uniform appearance between RH and LH porous panels. (1) Procedure - Porous Panel Finishing Method #1 (a) Acquire necessary tools, equipment, and supplies. Sealant Per MIL-S-8802F AC-240B½ Quick Cure Dynamold Aerospace Products Fort Worth, TX Panel adhesive. When applying surface filler, leave a 0.13 ±0.06 inch (3.30 ±1.5 mm) gap around porous panel. The gap will be filled with adhesive after topcoat has fully cured. (b) Fill area behind trailing edge of porous panel with surface filler. (Refer to 51-20) (c) Prime and paint prepared surface. ow to fully cure. (Refer to 51-20) (d) Fill in gap around porous panel with adhesive and allow to cure for 24 hours. (2) Procedure - Porous Panel Finishing Method #2 (a) Acquire necessary tools, equipment, and supplies. Moisture Resistant Filler #77 AdTech Charlotte, MI Bodywork finishing. (b) Fill area behind trailing edge of porous panel with moisture resistant filler. (Refer to 51-20) (c) Prime and paint prepared surface. ow to fully cure. (Refer to 51-20) (3) Procedure - Porous Panel Finishing Method #3 (a) Acquire necessary tools, equipment, and supplies. Filler, P-17 High-Heat Resistant Filler, P-11 Flexible #17 AdTech Charlotte, MI #11 Type 1 Blk AdTech Charlotte, MI Bodywork finishing. Bodywork finishing. Page 22

23 Low Tack Masking Tape No M St. Paul, MN Bodywork finishing. Scotch-Brite Scouring Pads M St. Paul, MN Bodywork finishing. Edge Sealant OR CA8000/ B900B PRC-Desoto Pittsburgh, PA Bodywork finishing. Single Stage Top Coat, Black a DCC 9300 WO1955 PPG Fleet Coatings Sherwin Williams a.any gloss black from an approved single stage system is permissible. (b) Fill area behind trailing edge of porous panel with high-heat resistant filler or flexible filler. ow to fully cure. (Refer to 51-20) (c) Mask wing area aft of porous panel so to inch (3.18 to 6.35 mm) of filler will be visible around trailing edge of porous panel after applying primer and paint. (d) Prime and paint prepared surface. ow to fully cure. (Refer to 51-20) Edge sealant/top coat application is optional. (e) Apply optional edge sealant/top coat as follows: 1 Mask edge sealant/top coat application area from trailing edge of porous panel to 0.03 to 0.08 inch (0.76 to 2.03 mm) onto painted surface. 2 Do not allow solvent to contact porous panel. 3 Solvent clean edge sealant/top coat application area with DX solvent. (Refer to 20-30) 4 Using ultra-fine scouring pad, lightly abrade surface of edge sealant/top coat application area. 5 Solvent clean edge sealant/top coat application area with isopropyl alcohol. (Refer to 20-30) 6 Mix edge sealant/top coat according to manufacturer s instructions. 7 Apply a thin coat of edge sealant/top coat to abraded surface until evenly covered. 8 Remove masking tape before edge sealant/top coat fully cures to allow the material to flow slightly. 9 Cure edge sealant/top coat. Page Sep 2017

24 0.13 inch (3.30mm) LEADING EDGE SKIN (REF) FINISHING METHOD #1: NOTE When applying surface filler, primer, and topcoat, leave a gap around trailing edge of porous panel. After topcoat has fully cured, fill gap with adhesive LEADING EDGE SKIN (REF) FINISHING METHOD #2: NOTE Fill gap around trailing edge of porous panel with moisture resistant filler and cover with primer and topcoat. LEGEND 1. Porous Panel 2. Adhesive 3. Surface Filler, Primer, and Topcoat 4. Moisture Resistant Filler 5. Primer and Topcoat SR22_MM30_1619A Page 24 Figure 3 Porous Panel Finishing Methods (Sheet 1 of 2)

25 0.125 to 0.25 inch (3.18 to 6.35 mm) LEADING EDGE SKIN (REF) 0.03 to 0.08 inch (0.76 to 2.03 mm) LEGEND 1. Porous Panel 5. Primer and Topcoat 6. High-Heat Resistant Filler FINISHING METHOD #3: NOTE Fill gap around trailing edge of porous panel with high-heat resistant filler, or flexible filler. Apply primer and topcoat so that to 0.25 inch (3.18 to 6.35 mm) of filler remains visible around trailing edge of porous panel. Optional: Apply edge sealant to exposed filler. Sealant should extend from trailing edge of porous panel to 0.03 to 0.08 inch (0.76 to 2.03 mm) onto painted surface. SR22_MM30_2062B Figure 3 Porous Panel Finishing Methods (Sheet 2 of 2) Page Sep 2017

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