INSTALLATION MANUAL Electrical SPEEDBRAKE 2000 Series

Transcription

1 PRECISE FLIGHT, INC POWELL BUTTE Installation Report Number: Document Number: 211SMAN0001 Revision Number: D Aircraft Serial Number: STC Number: SA2602NM Make: CESSNA INSTALLATION MANUAL Electrical SPEEDBRAKE 2000 Series Models: 210G, T210G, 210H, 210J, 210K, T210J, 210L, T210L, 210M, T210M, 210N, P210N, T210N, P210R, T210R, 210R, T210H NOTICE The Airworthiness Limitations section (Section 4.0) is FAA Approved and Specifies maintenance required under Sections and of the Federal Aviation Regulations unless an alternative program has been FAA Approved. These Documents must be Kept with the Aircraft Records NOTE: READ THESE DIRECTIONS BEFORE STARTING! CHECK FOR EQUIPMENT THAT MAY INTERFERE WITH INSTALLATION BEFORE PROCEEDING! ALL WORK MUST BE DONE IN CONJUNCTION WITH APPLICABLE AIRCRAFT MAINTENANCE MANUAL! THIS DOCUMENT CONTAINS PROPRIETARY INFORMATION ON THE PRECISE FLIGHT, INC. (PFI) COMPANY AND ITS RECEIPT OR POSSESSION DOES NOT CONVEY ANY RIGHTS TO REPRODUCE, DISCLOSE ITS CONTENTS, OR TO MANUFACTURE, USE, OR SELL ANYTHING IT MAY DESCRIBE. REPRODUCTION, DISCLOSURE, OR USE WITHOUT SPECIFIC WRITTEN AUTHORIZATION OF PFI IS STRICTLY FORBIDDEN. FAA Approval Date: Page 1 of 47

2 REVISIONS HISTORY Rev. Description of Changes Author Date Approved Approved By Date - (08062) Initial release - - STP 10/26/99 A (08062) Added attachment angle P/N & - - drawing 211S0004 EWL 11/19/99 B (08062) Revised P-210 Instructions - - EWL 02/03/00 C (08062) Revised Annual CONTRA instructions; - - revised ALC P/N DJC 04/16/01 D Changed document name to current PFI standards: Is: 211SMAN0001 (Was: 08062); New document format; updated all sections to new company standards; updated Section 2.13 and 2.14 by changing the ALC P/N to 010S0303-1; Corrected typos and part code number references to match install drawing package. Appendices: Removed parts list and Installation Instruction drawings, provided electrical load analysis form. W. Ashforth R. Norris 2/26/10 8/1/12 Page 2 of 47

3 LIST OF ACTIVE PAGES Original Added Pages Original Added Pages PAGE REV PAGE REV PAGE REV PAGE REV 1 D 35 D 2 D 36 D 3 D 37 D 4 D 38 D 5 D 39 D 6 D 40 D 7 D 41 D 8 D 42 D 9 D 43 D 10 D 44 D 11 D 45 D 12 D 46 D 13 D 47 D 14 D 15 D 16 D 17 D 18 D 19 D 20 D 21 D 22 D 23 D 24 D 25 D 26 D 27 D 28 D 29 D 30 D 31 D 32 D 33 D 34 D Page 3 of 47

4 TABLE OF CONTENTS REVISIONS HISTORY... 2 LIST OF ACTIVE PAGES... 3 TABLE OF CONTENTS... 4 LIST OF TABLES... 5 LIST OF FIGURES OVERVIEW INSTALLATION OVERVIEW HOW TO USE THIS MANUAL AND READ THE DRAWINGS Notes and Warnings Drawing Interpretation Parts Lists IMPORTANT INSTALLATION NOTES LIST OF TOOLS REQUIRED LIST OF SUPPLIES REQUIRED LIST OF ABBREVIATIONS MANUAL AND ICA REVISIONS INSTALLATION INSTRUCTIONS LOCATING WING CUTOUTS RIVET REMOVAL DOUBLER PLACEMENT UPPER WING CUTOUTS LOCATING LOWER WING CUTOUTS LOWER WING CUTOUTS UPPER DOUBLER INSTALLATION (PRELIMINARY) UPPER DOUBLER INSTALLATION (PERMANENT) SPEEDBRAKE CARTRIDGE INSTALLATION (TEMPORARY) LOWER DOUBLER ASSEMBLY AND INSTALLATION WING BAY STIFFENER ATTACHMENT EXTERIOR PANEL AND INTERIOR REMOVAL INSTALLATION OF THE ASYMMETRIC LOGIC CONTROL (ALC) (NON-PRESSURIZED) INSTALLATION OF THE ASYMMETRIC LOGIC CONTROL (ALC) (PRESSURIZED) Page 4 of 47

5 2.15 WIRING THE SPEEDBRAKE CARTRIDGES TO THE ALC (NON-PRESSURIZED) WIRING THE SPEEDBRAKE CARTRIDGES TO THE ALC (PRESSURIZED) WIRING THE ASYMMETRICAL LOGIC CONTROL (ALC) (NON-PRESSURIZED) WIRING THE ASYMMETRICAL LOGIC CONTROL (ALC) (PRESSURIZED) CIRCUIT BREAKER AND SWITCH SPEEDBRAKE CARTRIDGE INSTALLATION (PERMANENT) PLACARDS SPEEDBRAKE OPERATIONAL TEST DOCUMENTATION TROUBLE SHOOTING GUIDE SPEEDBRAKE CARTRIDGE FAILS TO OPERATE CORRECTLY WARNINGS FOR ADDITIONAL TECHNICAL ASSISTANCE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS INTRODUCTION SYSTEM DESCRIPTION SPECIAL TOOLS REQUIRED MAINTENANCE INSTRUCTIONS TROUBLE SHOOTING GUIDE AIRWORTHINESS LIMITATIONS SCHEDULED MAINTENANCE INTERVALS AND INSPECTIONS FOR CONTINUED AIRWORTHINESS APPENDICES ELECTRICAL LOADS ANALYSIS FORM: LIST OF TABLES Table 1 - Tools Required Table 2 Supplies Required Table 3 List of Abbreviations Table 4 - Scheduled Maintenance Intervals and Inspections LIST OF FIGURES Figure 1 - Third Angle Projection Example (Earle, James. Engineering Design Graphics ) 8 Figure 2 - Sample Parts List from Drawing 211S Figure 3 Upper Wing Template (NTS Reference Only) Figure 4 Upper Doubler Placement Page 5 of 47

6 Figure 5 - Wing Cutout Figure 6 Lower Wing Cutout Figure 7 - Suggested FAA Form 337 Description of Work Statement Page 6 of 47

7 1.0 OVERVIEW 1.1 INSTALLATION OVERVIEW 1. Read through the entire manual, and become familiar with the drawings, before beginning any part of the installation process. 2. The installation of Precise Flight, Inc. SpeedBrakes consists of cutting openings in the top and bottom of each wing skin and using locating templates (Drawings). 3. Doublers are installed to reinforce the cutout areas, which will require removing existing rivets and installing new rivets. 4. Stiffener angles are installed to reinforce wing bays. 5. The asymmetric logic control unit (ALC) and wiring is installed, which will require removing the interior, running wires through the fuselage from the ALC unit to the switch location, installing wiring from the ALC to the individual SpeedBrake Cartridges in the wing, and installing a breaker to protect the system with a switch to actuate the ALC and SpeedBrake Cartridges. 6. SpeedBrake operation is checked for functionality. 7. FAA paperwork and logbook entries are completed to return the aircraft to service. 8. Warranty information is returned to PFI. ( Each section will include a list of tools and parts required. Page 7 of 47

8 1.2 HOW TO USE THIS MANUAL AND READ THE DRAWINGS Notes and Warnings Because of the uniqueness of this installation in existing aircraft, Precise Flight has added notes, cautions, and warnings to the installation manual. NOTE Notes are used to emphasize certain steps to prevent problems with the installation. We at Precise Flight have added these notes to prevent problems before they occur based on our experience installing these systems, or from your feedback.! CAUTION! Cautions are used if aircraft damage can occur due to a missed step. Please remember, we only have these in key locations based on previous experience. It is the installer s responsibility to make sure the installation is done correctly, and to airworthiness standards.!! WARNING!! Warnings are used to emphasize a part of the installation where if done incorrectly can pose a serious hazard to the installer or the pilot Drawing Interpretation All drawings produced by Precise Flight Inc, are based on ASME Y standards, measurements in Inches, and Third Angle Projection. Information on the drawings including notes, parts, etc. are part of the FAA approved design and in most cases do include important installation and manufacturing information. Third Angle Projection is the method drawing views are produced as shown in Figure 1. Figure 1 - Third Angle Projection Example (Earle, James. Engineering Design Graphics ) Page 8 of 47

9 Parts Lists A source of possible confusion when reading drawings is the proper interpretation of the parts list. This STC includes multiple aircraft models, and voltages, in the same drawing package. Because of the difference between the Cessna Models (210G, T210G, 210H, 210J, 210K, T210J, 210L, T210L, 210M, T210M, 210N, P210N, T210N, P210R, T210R, 210R, T210H) aircraft installations, special care must be taken to make sure the correct installation is used. Figure 2 below shows a 24V Model installation, and which drawings are applicable. - 2 PL PLACARD, SPEEDBRAKE * - 211S FEED-THROUGH INSTALLATION S ALC INTERCONNECT INSTALLATION S CARTRIDGE INSTALLATION-RIGHT S CARTRIDGE INSTALLATION-LEFT S COCKPIT CONTROL PANEL INSTALL 24 V 211S COCKPIT CONTROL YOKE INSTALL 24 V \ - 211S SPEEDBRAKE INSTALLATION, 24V QTY REQ D CODE PART NO. DESCRIPTION MATERIAL/MFG. ITEM Figure 2 - Sample Parts List from Drawing 211S0001 This chart shows part number 211S Because all models listed on the STC are applicable, this installation would be used for any 24V electrical system as described in section 2.0 of this document, or on the STC certificate. From here, the installer moves to the left until a \ marks that applicable installation. Follow the column up to see what quantity is greater than 0. Then follow the chart back to the right to find the drawing/part number for the applicable installation. Drawings are shown in this example, but parts work on the same principle on the other installation drawings. Page 9 of 47

10 1.3 IMPORTANT INSTALLATION NOTES This section lists specific installation notes of importance for this STC installation. NOTE It is the installer s responsibility to verify that the installation of the SpeedBrake 2000 system will not interfere with any existing modification on the aircraft prior to starting the installation. Contact Precise Flight if there appears to be an installation conflict.! CAUTION! Verify aircraft voltage and SpeedBrake kit voltage prior to installation. Failure to use correct installation kit may damage aircraft systems, or SpeedBrake installation. 1.4 LIST OF TOOLS REQUIRED Each section will include a list of tools required and all necessary parts for that section. Table 1 - Tools Required TOOLS REQUIRED Automatic Center Punch Bucking Bars Tape Measure, 12 min Inspection Mirror Micro Adjust Countersink, 100 Chip Chaser Needle Nose Pliers Clecos: 3/32, 1/8, side grip Nutplate Jig #8-32 Cleco Pliers Pencil Rivet Squeezer (optional) 3/32 & 1/8 Countersink Die Set Riveter: Cherry-Max (optional) Deburring Tool 2x or 3x Rivet gun Flush, 3/32, and 1/8 rivet sets Metal Snips: Right, left offset Machinists Scale: 12 (minimum) Wrench 11/32 Drum sander, 2 Screwdrivers: Slotted and Philips Drill Motors Straight & 90 Clamps Felt Marker Ultra Fine Point Soldering iron, electronic solder Files: ¼ Round, 6 Flat FAA Advisory Circulars , -2 Heat Gun Volt Ohm meter Hole-Finder Wire Cutter and Strippers Scotch-Brite Die Grinder w/ Abrasive cutoff wheel Panel Punch: ¾ Contact Crimper: M22520/1-01 With M22520/1-02 turret (Machined barrel contacts) Drills: #40, #30, N, 5/16, 5/8, and 3/4 Unibit TOOLS REQUIRED (Pressurized A/C) Contact Extraction Tool: MS24256R20 Contact Crimper: AMP Pro Crimper II with die Or equivalent Contact Insertion Tool: MS24256A20 Page 10 of 47

11 1.5 LIST OF SUPPLIES REQUIRED Table 2 Supplies Required SUPPLIES REQUIRED Carbon Paper 2-8 ½ x 11 Sheets Masking Tape ¾ Double Sided Tape Primer (per Mil-P-23377), or zinc Solder: Rosin Core for electronics Isopropyl Alcohol rich, or equivalent 3M Adhesive or Equivalent Loctite 222 Ultra-fine tip felt marker ProSeal A-½ or B-½ or equivalent per AMS-S LIST OF ABBREVIATIONS This section is to provide the reader with a complete state of the abbreviations used in this document and installation. A/R AC AFM AFMS ALC FAA FS In Lb, lbs PFI N/A or - V VDC WS Table 3 List of Abbreviations As Required Advisory Circular Aircraft Flight Manual Aircraft Flight Manual Supplement Asymmetric Logic Controller Federal Aviation Administration Fuselage Station Inch Pounds Precise Flight, Inc. Not Applicable Volts Volts Direct Current Wing Station 1.7 MANUAL AND ICA REVISIONS To ensure the maintenance of your existing aircraft fleet, possible revisions to this manual and especially section 4.0 Instructions for Continued Airworthiness may require updating over the life of the aircraft. Per the applicable Federal Aviation Regulations, an update process is required to properly maintain these instructions, in addition to the aircraft itself. Because of this, it is imperative to complete the online registration for the aircraft once the system is installed. Revisions can be made by a service letter from Precise Flight, an Airworthiness Directive as issued by the administrator, by single page updates, or a complete replacement of all pages of the manual. It must be clearly noted as to the revision level of the pages listed in The List of Active Pages. If a single sheet(s) is replaced, replace the list of active pages with the new one provided, or update the list manually and initial and date the list. Page 11 of 47

12 2.0 INSTALLATION INSTRUCTIONS Read all installation instructions prior to starting the installation, or modifying the aircraft. If necessary, please contact Precise Flight Incorporated at (800) and ask for SpeedBrake assistance, or write us at the address above, if you have any questions.! CAUTION! Verify aircraft voltage and SpeedBrake kit voltage prior to installation. Failure to use correct installation kit may damage aircraft systems, or SpeedBrake system. 2.1 LOCATING WING CUTOUTS TOOLS REQUIRED Automatic Center Punch Masking Tape Tape Measure Felt tip marker PARTS REQUIRED Part Number Qty Description 211S Upper Left Wing Template 211S Upper Right Wing Template Left Wing 1. Using template 211S0005-1, place the template on the left aircraft wing between WS and and align template with the critical rivet line. Adjust template so that the rows of rivets marked CRITICAL RIVET LINE maintains a 2D edge clearance on doubler edge as shown on template. Once aligned, secure the template to the wing skin using masking tape. 2. Identify and mark the 16 existing #4 rivets to be removed. 3. Locate the two points labeled CORNER RIVET LOCATION and center punch transfer these two locations. 4. Remove the template and set aside. 5. Repeat steps 1 thru 4 on the right wing using Template 211S Page 12 of 47

13 Figure 3 Upper Wing Template (NTS Reference Only) Page 13 of 47

14 2.2 RIVET REMOVAL TOOLS REQUIRED Drills: #30 (0.129) Drill Motor - Left Wing 1. On the left wing upper skin, with the rivets identified in section 2.1, step 2, determine all rivet types and sizes to be removed. 2. Drill out all rivets using the proper size drill. A rivet centering drill tool may be helpful in drilling out the rivets. 3. Drill the two CORNER RIVET LOCATION holes using a #30 bit (0.129). Reference drawing 211S Repeat steps 1 thru 3 on the right wing upper skin. Reference drawing 211S Page 14 of 47

15 2.3 DOUBLER PLACEMENT TOOLS REQUIRED Clecos: 1/8 Drill Bits: #30, #32 Felt Marker: Ultra Fine line Cleco Pliers Drill Motor Deburr tool PARTS REQUIRED Part Number Qty Description 211S Upper Doubler 211S Upper Left Wing Template 211S Upper Right Wing Template Left Wing 1. On the upper left wing, Cleco an Upper Doubler (211S0009-1) onto the wing skin using the 2 corner rivet location holes and 1/8 Clecos. See Template 211S Using a #30 drill bit (0.129), drill through the remaining new rivet holes on the doubler into the wing. Use Clecos to secure the doubler as you go. 3. Using a #32 drill bit (0.116), drill through the 8 cartridge mounting holes in the doubler as shown on the template. 4. With an ultra fine felt marker or carbon paper trace the wing cutout onto the wing skin. This line will be used in making the cutout in the wing skin. 5. Remove the doubler and identify it for the left wing then set aside and deburr all holes. 6. Repeat steps 1 thru 5 on the right wing using the other upper doubler (211S0009-1). See Template 211S Figure 4 Upper Doubler Placement Page 15 of 47

16 2.4 UPPER WING CUTOUTS TOOLS REQUIRED Die Grinder w/abrasive Wheel Drill Motor Snips: Offset Left and Right Drill Bit: ¼ Files: ¼ round & 6 Flat Masking tape and paper Cleco Pliers Clecos: 1/8 PARTS REQUIRED Part Number Qty Description 211S Upper Left and Right Doublers Various methods may be employed to make the cutouts in the wings. Use Extreme Care! It has been proven helpful to do the following: Left Wing 1. Mask off the wing around the area to be cut. 2. Drill a 1/4 inch hole well inside all 4 radiused corners. 3. Using a 1/4 inch round file, file close to the traced lines. 4. Using a die grinder and abrasive cutter, or snips, cut lines between the holes, staying well within the traced lines. 5. File the openings up to the traced lines using a combination of the 1/4 inch round and 6-inch flat files. 6. Cleco the doubler on top of the wing skin and finish filing the opening to the doubler. 7. Repeat steps 1 thru 6 on the right wing. NOTE The cutouts will be the finished product. Care must be taken when finishing these openings. Figure 5 - Wing Cutout Page 16 of 47

17 2.5 LOCATING LOWER WING CUTOUTS TOOLS REQUIRED Automatic Center Punch Carbon Paper Tape Measure Masking Tape PARTS REQUIRED Part Number Qty Description 211S Lower Left Wing Template 211S Lower Right Wing Template 211S Lower Doubler 211S Access Cover Left Wing 1. Using template 211S0006-1, place the template on the lower left aircraft wing between wing stations and and align template with the CRITICAL RIVET LINE. Once aligned, secure the template to the wing skin using masking tape. 2. Transfer the INSIDE OVAL to the wing skin using carbon paper and the lower doubler (211S0010-1). 3. Transfer the WING CUTOUT OVAL to the wing skin using carbon paper and the Access Cover (211S0010-2). 4. Transfer the DRAIN HOLE location using an automatic center punch. 5. Remove the template partially and leave attached to the wing for accurate alignment later. 6. Repeat steps 1 thru 5 on the right wing using template (211S0006-2). Page 17 of 47

18 2.6 LOWER WING CUTOUTS TOOLS REQUIRED Die grinder w/abrasive wheel Carbon Paper Drum Sander: 2 Drill Bits: ¼, #40 and 5/16 Felt Marker: Ultra Fine Drill Motor: Right Angle Files: ¼ round & 6 flat Snips; Offset Left, Right Deburring Tool Masking Tape and paper Cleco Pliers Clecos: 3/32, side grip PARTS REQUIRED Part Number Qty Description 211S Lower Left Wing Template 211S Lower Right Wing Template 211S Lower Doubler 211S Access Cover Various methods may be employed to make the cutouts in the wings. USE EXTREME CARE! It has been proven helpful to do the following: Left Wing 1. Mask off the wing around the area to be cut. Reference figure Drill a ¼ hole well inside all radiuses. 3. Using a die grinder with abrasive wheel, or snips, cut lines between drilled holes, staying well within the traced lines. 4. Place the Lower Doubler (211S0010-1) inside the wing and verify it does not overlap the stringer edges. Adjust as necessary inside the wing. Mark a new outline if needed and use access cover to double check wing cutout oval position. 5. Clamp the lower doubler in place inside the wing and drill TRANSFER RIVET LOCATIONS holes using a right angle drill and a #40 drill bit (0.098). 6. Cleco the lower doubler outside the lower wing skin and transfer the rest of the 16 rivet locations using a #40 drill bit (0.098). 7. Re-align the template on the hole pattern drilled in the previous step. Using carbon paper, access cover, (211S0010-2) and a pencil or ultra fine marker, transfer the final WING CUTOUT oval to the wing skin. 8. Finish the cutout using die-grinder, drum sander, round and flat files. Use the lower doubler and access cover (211S0010-2) to check wing cutout size. Access cover should fit inside oval cut out with minimal gap all around. Page 18 of 47

19 NOTE The cutouts will be the finished product. Care must be taken when finishing these openings. 9. Remove the lower doubler and identify it for the Lower Left Wing and set aside. 10. Drill the DRAIN HOLE using a 5/16 (0.312 ) drill and deburr all drilled holes. 11. Repeat steps 1 thru 10 on the Lower Right Wing. Figure 6 Lower Wing Cutout Page 19 of 47

20 2.7 UPPER DOUBLER INSTALLATION (PRELIMINARY) TOOLS REQUIRED Drill Bits: #30 Chip Chaser Deburring Tool Cleco Pliers Felt Marker: Ultra Fine Drill Motor Clecos: 1/8 PARTS REQUIRED Part Number Qty Description 211S Upper Left Wing Template 211S Upper Right Wing Template 211S Upper Doubler Note: The Upper Doublers are positioned under the skin and on top of the stringers. Left Wing 1. Reference the Upper Left Wing drawing template (211S0005-1). 2. Insert the Upper Doubler (211S0009-1) into the wing through the lower cutout. 3. Position the Upper Doubler between the wing skin and stringers. 4. Orient the holes in the Upper Doubler with the holes in the wing skin and Cleco in place. NOTE The upper Doubler may need to be trimmed to allow hole alignment. Insure that 2D rivet spacing is maintained after trimming. 5. Using a felt tip marker, transfer the rivet locations for the stringers onto the doubler. 6. Remove Clecos and Doubler; confirm 2D edge distance on all holes. 7. Position the Upper Doubler again between the wing skin and stringers and Cleco in place. 8. Using a #30 drill bit (0.129), drill through the wing skin into the Upper Doubler for all the rivets previously removed from the stringer. 9. Remove the Upper Doubler and deburr. Remove all bucked ends and any chips inside the wing. 10. Repeat steps 1 thru 9 on the Right Wing. Reference drawing 211S Page 20 of 47

21 2.8 UPPER DOUBLER INSTALLATION (PERMANENT) TOOLS REQUIRED Drill Bits: #30 Chip Chaser Deburring Tool Cleco Pliers Felt Marker: Ultra Fine Drill Motor Clecos: 1/8 ProSeal A-1/2 or B-1/2 PARTS REQUIRED Part Number Qty Description PFI Code 211S Upper Left Wing Template - 211S Upper Right Wing Template - 211S Upper Doubler - MS20470AD Rivet, 1/8 x 3/16, universal head MS MS20470AD Rivet, 1/8 x ¼, universal head MS Left Wing Reference Drawings 211S and 211S Place a layer of ProSeal on the wing side of the upper doubler (211S0009-1). 2. Insert the upper doubler through the opening in the lower wing skin. 3. Position the upper doubler between the upper wing skin and stringer. Orient with the cutout in the top skin and the previously drilled holes. 4. Cleco the upper doubler in place. Reference drawings 211S and 211S for correct rivets. 5. Rivet upper doubler in place using the provided rivets (p/n MS 00480, MS ) 6. Clean the excess ProSeal with a rag and Isopropyl Alcohol. 7. Repeat steps 1 thru 6 on the right wing using the upper right wing template (211S0005-2). Page 21 of 47

22 2.9 SPEEDBRAKE CARTRIDGE INSTALLATION (TEMPORARY) TOOLS REQUIRED Drill Bits: #19, #30 Double Sided Tape Deburring Tool Cleco Pliers Felt Marker: Ultra Fine Drill Motor Clecos: 1/8, side grip Philips #2 screwdriver Zinc Rich Primer Loctite 222 or equiv. PARTS REQUIRED Part Number Qty Description PFI Code 211S Cartridge Installation - AN R6 20 Screw, #8-32 x 3/8, Washer head, Cd Steel MS AN R7 2 Screw, #8-32 x 7/16, Washer head, Cd Steel MS AN R9 2 Screw, #8-32 x 9/16, Washer head, Cd Steel MS NAS1149FN816P 20 Washer, flat, #8, light MS MS21044N08 20 Nut, self-locking #8-32 MS A114 4 Pin, hinge, Safety HD S Hinge, attachment - 573S Hinge, cartridge - 573S Angle, extrusion, Al - 211S Angle, attachment, outboard - 211S Angle, attachment, inboard - 010S * Speedbrake cartridge, 12V, Right - 010S * Speedbrake cartridge, 12V, Left - 010S * Speedbrake cartridge, 24V, Right - 010S * Speedbrake cartridge, 24V, Left - MS Screw, #4-40 x ¼, PHP, Cd Steel MS Bushing, snap, ½ x 5/16 HD *Voltage option depends on aircraft electrical system. See packing list Left Wing IMPORTANT: Reference Drawing 211S Apply zinc rich primer to the drain hole and install a Snap Bushing (P/N HD 06062). 2. The SpeedBrake cartridges are not symmetrical. There is a forward orientation. Reference 211S0003 for correct orientation. Orient the Drain Tube to the inboard side. The SpeedBrake cartridges are marked left and right confirm you have the correct cartridge for the left installation. 3. Enlarge the holes in cartridge hinges (573S0013-2) using a #19 bit (0.166) and deburr. 4. Install an extruded angle (573S0012-1) on the outboard end of the speedbrake cartridge using 2 #8-32 screws and Loctite 222 (P/N MS 00436). Install a cartridge Page 22 of 47

23 hinge (573S0013-2) on the extruded angle using 2 screws, washers, and nuts (P/N MS 00436), (P/N MS 00452) and (P/N MS 00485). 5. Install a cartridge hinge (573S0013-2) on the inboard end of the cartridge using 2 #8-32 screws (P/N MS 00436) and Loctite Attach the attachment hinges (573S0013-1) to the cartridge hinges (573S0013-2) using safety pin (P/N HD 06024). Reference drawing 211S0003 for correct alignment. 7. Place the SpeedBrake cartridge through the Lower Wing cutout and orient with the upper doubler. Temporarily install the SpeedBrake cartridge with the supplied 4-40 screws (P/N MS 01655).! CAUTION! The supplied screws are the proper length - Use of alternate screws to attach the cover plate will interfere with proper SpeedBrake operation and will compromise the component warranty. 8. Attach double sided tape to the outside flanges of the attachment angles (P/Ns 211S & 211S0011-3). Using drawing 211S0003 as a reference, adhere attachment angles (P/N 211S0011-1) to the outboard attachment hinge trailing edge and to the side of the rib. Using a #30 drill bit (0.129), drill 2 holes through the attachment angle into the rib. Be sure to maintain a 2D edge distance with holes. Cleco in place. Use a felt tip marker to mark the attachment angle through the 2 holes of the attachment hinge where they contact. A side grip cleco may help hold the attachment angle to the attachment hinge. 9. Remove the clecos from the attachment angle and the pin from the outboard attachment hinge. Remove the attachment angle and hinge (still stuck together) from the wing, and drill the 2 holes marked in step 8 above using a #30 drill bit (0.129). Cleco together. Replace the outboard attachment angle inside the wing and Cleco in place to the rib. 10. Place the inboard attachment angle (211S0011-3) so that it covers 2 of the existing rivets running vertically on the rib. Check to ensure that 2D edge distance is maintained. Mark the 2 rivets and remove using the appropriate size drill bit. 11. Using drawing 211S0003 as a reference, adhere the inboard attachment angle (211S0011-3) to the inboard trailing edge attachment hinge and to the side of the rib, covering the 2 removed rivet holes. Using a felt tip marker, mark the 2 removed rivet locations on the attachment angle. Mark the 2 holes where the attachment hinge contacts the attachment angle. A side grip cleco clamp may help hold the attachment hinge to the inboard attachment angle. Page 23 of 47

24 12. Remove the safety pin attaching the inboard attachment angle to the attachment hinge. Remove the inboard attachment angle and hinge (still stuck together). Using a #30 bit (0.129), drill the 2 holes through the attachment angle using the attachment hinge holes as a guide and cleco together. Using a #30 drill bit (0.129), drill 2 holes in the attachment angle marked from the holes in the rib. Replace the inboard attachment angle inside the wing and Cleco in place to the inboard rib. 13. Enlarge the 2 holes in each attachment angle and each rib with a #19 drill bit (0.166) and deburr. 14. Apply Zinc rich primer to the holes in each rib to prevent corrosion. 15. Using drawing 211S0003 as reference for position and #8-32 hardware, install the attachment hinges and attachment angles as shown. 16. Remove the Safety Pins (P/N HD 06024) and remove the SpeedBrake from the wing to prepare for wiring. 17. Repeat steps 1 thru 16 for the right wing, taking note of which side of the right hand speedbrake is forward. Page 24 of 47

25 2.10 LOWER DOUBLER ASSEMBLY AND INSTALLATION TOOLS REQUIRED Rivet Gun Rivet sets and bars or Rivet Squeezer and dies Cleco Pliers Clecos: 3/32 PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Left wing Lower Template - 211S Drawing, Right wing Lower Template - 211S Lower Doubler - 211S Access Cover - MS20470AD Rivet, 3/32 x 3/16, Universal Head MS Left Wing Reference Drawing 211S Place the lower doubler in the wing and cleco in place. 2. Double-check that the lower doubler opening is large enough for the access cover (211S0010-2). 3. Rivet the Lower doubler in place using the provided rivets (P/N MS 07006). 4. Repeat steps 1 through 3 on the right wing. Reference drawing 211S Page 25 of 47

26 2.11 WING BAY STIFFENER ATTACHMENT TOOLS REQUIRED Rivet Gun Rivet sets and bars Drill Bit: #30 Cleco Pliers Clecos: 3/32, 1/8 Drill Motor Tape Measure Deburring Tool Automatic Center Punch Masking Tape Felt tip marker PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Left Upper Wing Stiffener Template - 211S Drawing, Right Upper Wing Stiffener Template - 211S Stiffener Angle - MS20470AD4-3 6 Rivet, 1/8 x 3/16, Universal Head MS Right Wing Reference drawings 211S & 211S Using template 211S0007-2, place the template on the right wing between Wing Stations and and align template with the CRITICAL RIVET LINE. Once aligned, secure the template to the wing skin using masking tape. 2. Identify and mark the 3 new rivet holes to be drilled. 3. Center punch transfer and drill the hole closest to the leading edge using a #40 drill bit (0.098). 4. Cleco the stiffener angle (211S0011-2) to the wing skin with the flange towards the wing root. 5. Align the stiffener angle with the remaining holes on the template. Use the stiffener angle as a drill guide and drill the remaining two #40 (0.098) holes. Final drill all 3 holes to #30 (0.129) and deburr. Remove all chips inside the wing. 6. Remove the template and set aside. 7. Place the stiffener angle through the inspection panel on the bottom of the wing and cleco in place with the flange towards the wing tip using 1/8 Clecos. 8. Rivet the stiffener angle in place using rivets (P/N MS 00480). Cherry-Max 4-3 rivets may be substituted since limited space is available to buck the rivets. 9. Repeat steps 1 thru 8 on the left wing template 211S Page 26 of 47

27 2.12 EXTERIOR PANEL AND INTERIOR REMOVAL TOOLS REQUIRED Screw Drivers: Philips #1, #2 Needle Nose Pliers 1. Disconnect all electrical power from aircraft. 2. Remove the front seats. For a P210, also remove the middle row seats. 3. Remove the co-pilot s side panel molding. 4. Remove the main spar inspection panels out to the SpeedBrake cartridges. 5. Remove the inspection panels AFT of the main spar out to the SpeedBrake cartridges. 6. Remove the lower wing root fairings. 7. Remove the headliner only as necessary in the following steps. Page 27 of 47

28 2.13 INSTALLATION OF THE ASYMMETRIC LOGIC CONTROL (ALC) (NON-PRESSURIZED) TOOLS REQUIRED Screw Driver: Philips #2 Zinc Rich Primer Drill Bit: #19 Drill Motor Felt tip marker Automatic Center Punch PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Speedbrake Installation (Non-Pressurized) - 211S Drawing, Interconnect installation - 010S0303-1* 1 ALC Assembly - MS21044N08 4 Nut, self-locking, #8-32 MS AN R9 4 Screw, #8-32 x 9/16, washer head MS NAS1149FN816P 4 Washer, flat, #8 MS AS Cable tie, nylon HD *= 010S is the preferred ALC, but p/n 010S and 010S can be used for repair and warranty work. If ALC p/n is changed, then speedbrake cartridge up stops need to be readjusted. Call Precise Flight for details. Right Wing Large Inspection Panel 1. The ALC is mounted on the right side inboard wing root rib. Reference 211S0001 and 211S Reference drawing 211S Place the ALC (P/N 010S0303-1) in place at wing station Mark holes with felt tip marker and dimple with automatic center punch. 3. Drill 4 holes using a #19 drill bit (0.166) and deburr. 4. Apply zinc rich primer to the 4 holes for corrosion protection. 5. Install the ALC as shown using the four #8-32 screws, #8 washers and #8-32 nuts (P/Ns MS 00722, MS 00452, and MS 00485). 6. Loosely secure wire harnesses to rib with two cable ties. Leave cable ties loose for later connection with wire harnesses. 7. Check to ensure that the ALC unit and wiring installation does not interfere with any other aircraft system. Page 28 of 47

29 2.14 INSTALLATION OF THE ASYMMETRIC LOGIC CONTROL (ALC) (PRESSURIZED) TOOLS REQUIRED Screw Driver: Philips #2 Zinc Rich Primer Isopropyl Alcohol Scotch-Brite Felt tip marker PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Speedbrake Installation, P210 (sheet 2) - 211S Drawing, Interconnect installation, P S0303-1* 1 ALC Assembly - MS21044N08 4 Nut, self-locking, #8-32 MS NAS1149FN816P 4 Washer, flat, #8 MS MS21919WDG8 2 Clamp, Adel MS CS CR 4 Stud, Click-Bond, #8 HD CB92 1 Epoxy, Click-Bond HD AS Cable tie, nylon HD *P/N 010S is the preferred ALC, but 010S and 010S can be used for repair and warranty work. If ALC p/n is changed, then speedbrake cartridge up stops need to be readjusted. Call Precise Flight for details. Right Wing Large Inspection Panel 1. The ALC is installed on the cabin floor, underneath the back seats. 2. Place the Click-Bond studs (P/N HD 06071) on the ALC using the four #8 washers and #8-32 nuts (P/Ns HD and MS 00485). 3. Reference Drawing 211S Place the ALC (P/N 010S0303-1) on the cabin floor at FS Be sure that the ALC clears all rivets and screws. Trace around the Click Bond Studs with an ultra-fine line felt marker. Remove the ALC. 4. Using Scotch-Brite and isopropyl alcohol, remove the paint inside the traced lines being sure that the Click-Bond studs will not come into contact with any paint. 5. Place the ALC in position and again trace around the Click-Bond studs. 6. Remove the Click Bond studs from the ALC and place in the plastic holding clamps. Bond the studs to the cabin floor using the bonding instructions and epoxy (P/N HD 06072) provided with the studs. Be sure to place the studs within the traced lines. Allow proper bonding time before installing the ALC. 7. Install the ALC as shown using the two Adel clamps, four #8 washers and 8-32 screws (P/Ns MS 07014, HD and MS 00485). 8. Check to ensure that the ALC installation does not interfere with any other aircraft system. Page 29 of 47

30 2.15 WIRING THE SPEEDBRAKE CARTRIDGES TO THE ALC (NON-PRESSURIZED) TOOLS REQUIRED Screwdriver: Philips #2 Soldering Iron or Drill Bit: 5/16 Rosin Core Solder Contact Crimper Drill Motor Tape Measure Deburring Tool Wire Cutter, Stripper Zinc Rich Primer Needle Nose Pliers PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Speedbrake Installation - 211S Drawing, Speedbrake Cartridge installation - 211S Drawing, Aircraft Schematic or Contact, Pin, Solder or EL Contact, Pin, Crimp EL Connector housing, CPC Plug, Sockets, 8 cont. EL Connector backshell clamp EL or Contact, Socket, solder or EL Contact, Socket, Crimp EL Connector housing, CPC, Receptacle, Pins, 8 cont. EL M81969/ Tool, contact extractor EL A/R Cable, 8 conductor, 22awg SP Bushing, Snap, ½ x 5/16 HD Right Wing Lower Reference drawings 211S0003 and 211S In the forward main spar inspection panel directly in front of the SpeedBrake bay, use a 5/16 drill bit (0.313) to drill a hole in the center of the main spar web. Use existing holes if possible. 2. Deburr and apply zinc rich primer to the hole for corrosion protection. 3. Install a snap bushing (P/N HD 06062) in the hole. 4. Route the cable (P/N SP 02029) from the right SpeedBrake bay in the wing, through the main spar, and inboard to the ALC mount in the Right Wing root. Allow for routing through the wing with sufficient slack at both ends to attach contacts and connectors, and cut the cable (P/N SP 02029) to length. Save the remainder. Secure the cable using cable ties or lacing cord. 5. On the ALC end of the Wiring Harness strip the jacket back exposing 5/8 of wires. 6. Remove ¼ of insulation from each wire. 7. Solder (or crimp) a contact pin to the end of each wire (P/N EL or EL 02413) Page 30 of 47

31 8. Insert the ends thru a connector backshell clamp (P/N EL 01727). 9. Referring to Drawing 211S0004 for wire color to pin code, insert the pins into their respective holes in the connector receptacle housing (P/N EL 01729). 10. Attach the backshell (P/N EL 01727) to the receptacle housing (P/N EL 01729). Tighten the strain relief clamp to the cable jacket. Connect the ALC plug and wire harness receptacle together. 11. Repeat Steps 6 thru 10 on the SpeedBrake end of the wiring harness using socket contacts, backshell, and connector plug housing. (P/Ns EL or EL 02414, EL and EL 01727). 12. For the left SpeedBrake cartridge, repeat Steps 1 thru 11, routing the wire through the cabin in front of the main spar and above the headliner to the ALC location. 13. Check to insure that cable routing does not interfere with any other aircraft systems. Page 31 of 47

32 2.16 WIRING THE SPEEDBRAKE CARTRIDGES TO THE ALC (PRESSURIZED) TOOLS REQUIRED Screwdriver: Philips #2 Soldering Iron Drill Bit: 5/16 Rosin Core Solder Volt-Ohm Meter Drill Motor: Right Angle Tape Measure Deburring Tool Wire Cutter, Stripper Contact Crimper: M22520/1-01 Zinc Rich Primer With M22520/1-02 turret (Machined barrel contacts) Needle Nose Pliers Machinists scale: 12 Panel Punch or Unitbit: ¾ ProSeal A-1/2 or B 1/2 PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Speedbrake installation - 211S Drawing, Aircraft Schematic - 211S Drawing, Feedthrough Installation - MS21044N04 12 Nut, self locking, #4-40 MS NAS1149FN432P 12 Washer, Flat, #4 MS MS Screw, #4-40 x 5/8, PHP MS MS3126F12-10P 2 Connector, receptacle, 10 pin EL MS3126F12-10S 2 Connector, plug, 10 sockets EL MS3119E-12-10PS 2 Connector, bulkhead feedthrough EL M81969/ Tool, contact extractor EL Connector backshell clamp EL Connector housing, CPC Plug, Sockets, 8 cont. EL or Contact, Pin, Solder or EL Contact, Pin, Crimp EL Connector housing, CPC, Receptacle, Pins, 8 cont. EL or Contact, Socket, solder or EL Contact, Socket, Crimp EL A/R Cable, 8 conductor, 22awg SP Bushing, Snap, ½ x 5/16 HD Right Wing Reference Drawings 211S0001, 211S0003, 211S0004 and 211S In the forward main spar inspection panel directly in front of the SpeedBrake bay, drill a 5/16 (0.313) hole in the center of the main spar. Reference 211S Deburr and apply zinc rich primer to the hole for corrosion protection. 3. Install a snap bushing (P/N HD 06062) in the hole. 4. Reference drawing 211S0015. Using the appropriate drill bit, drill a pilot hole for the panel punch bolt, or Unibit. Page 32 of 47

33 ! CAUTION! Before drilling any holes, be sure that both sides of the bulkhead are clear of obstacles and provide adequate room for each connector Make the bulkhead receptacle hole using a ¾ panel punch or Unibit. NOTE Be sure that the panel punch makes a final hole size of ¾ Use a deburring tool to enlarge the hole enough to insert the bulkhead feedthrough conncector. 5. Route the wire harness cable (P/N SP 02029) from the bulkhead connector location along the existing wire harness in the main spar inspection panels, and through the snap bushing into the SpeedBrake bay. Allow sufficient slack at both ends to attach contacts and connectors. Secure the cable with cable ties or lacing cord. Cut the wiring harness cable (P/N SP 02029) to length. Save the remainder. 6. Reference drawing 211S0015. Install bulkhead connector (P/N EL 02408) with gasket through the bulkhead at the right wing root form the cabin side. Be sure that the long portion of the receptacle is placed thru the bulkhead. Use #4-40 hardware (P/Ns MS 07022, MS 01312, and MS 01291) to secure receptacle to the bulkhead. Use ProSeal on the inside and outside of the bulkhead connector to seal around the connector. 7. Repeat steps 1 through 6 on the left wing root. Reference drawing 211S On the SpeedBrake end of the wiring harness cable, strip the jacket back exposing 5/8 of wires. 9. Remove ¼ of insulation from all wires. 10. Solder (or crimp) the end of each wire to the short end of a Socket (P/N EL or EL 02414). 11. Insert the ends through a connector backshell (P/N EL 01727). 12. Referring to drawing 211S0004 for wire color to pin code, insert the sockets into their respective holes in the connector plug housing (P/N EL 01726). 13. Attach the backshell (P/N EL 01727) to the connector plug (P/N EL 01726). Tighten the strain relief to the cable jacket. 14. At the wing root, strip the wiring harness jacket back exposing 5/8 of wires. 15. Remove ¼ of insulation from all wires. 16. Crimp the end of each wire to the short end of a pin contact (included with P/N EL 02410). Page 33 of 47

34 17. Insert the ends through the strain relief (included P/N EL 02410). 18. Referring to Drawing 211S0015 for wire color to pin code, insert the pins into their respective holes in the Cannon connector plug (P/N EL 02410). 19. Attach the backshell to the connector plug. Tighten the strain relief to the jacket. Check for pin continuity to the other end with a Volt-Ohm meter. 20. Connect the Cannon plug and bulkhead feedthrough connector together. 21. On the cabin side of the right wing root, at the bulkhead feedthrough connector, route the wire harness cable along the existing wire harness, down the doorpost, and along the co-pilot s side wall wiring harness back to the ALC. Allow sufficient slack at each end to attach contacts and connectors. Cut the cable to length. Save the remainder. NOTE Be sure to keep wiring harness clear of aileron cable and pulley, and clear of fuel lines. Secure the cable with cable ties or lacing cord. 22. At the bulkhead feedthrough connector, strip the wiring harness jacket back exposing 5/8 of conductors. 23. Remove ¼ of insulation from all conductors. 24. Crimp the end of each wire to the short end of a socket contact (included with P/N EL 02409). 25. Insert the ends through the strain relief (included with P/N EL 02409). 26. Referring to Drawing 211S0015 for wire color to contact code, insert the sockets into their respective holes in the Cannon connector (P/N EL 02409). 27. Attach the backshell to the connector. Tighten the strain relief to the cable jacket. 28. Connect the bayonet plug to the bulkhead connector. 29. On the ALC end of the right wing wiring harness cable, strip the jacket back exposing 5/8 of wires. 30. Remove ¼ of insulation from all wires. 31. Solder (or crimp) the end of each wire to the end of a pin contact (P/N EL or EL 02413). 32. Insert the ends through a backshell (P/N EL 01727). 33. Referring to drawing 211S0004 for wire color to pin code, insert the pins into their respective holes in the connector receptacle housing (P/N EL 01729). Page 34 of 47

35 34. Attach the backshell (P/N EL 01727) to the receptacle (P/N EL 01729). Tighten the strain relief to the cable jacket. Check for pin continuity with a Volt-Ohm Meter. 35. Repeat Steps 9 thru 34 for the left wing. For step 21 route the wire harness down the door post and behind the instrument panel utilizing an existing wire harness to secure. Then route the Wire Harness along the co-pilot s sidewall with the other SpeedBrake wire harness to the ALC. Save the remainder of the cable. NOTE Be sure to keep wiring harness clear of aileron cable and pulley, and clear of fuel lines. Secure the cable using cable ties or lacing cord. Page 35 of 47

36 2.17 WIRING THE ASYMMETRICAL LOGIC CONTROL (ALC) (NON-PRESSURIZED) TOOLS REQUIRED Needle Nose Pliers Soldering Iron Rosin Core Solder Contact Crimper Volt-Ohm Meter Wire Cutter, Stripper PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Speedbrake installation - 211S Drawing, Aircraft Schematic - M81969/ Tool, contact extractor EL Connector backshell clamp EL Connector housing, CPC Plug, Sockets, 8 cont. EL or Contact, Socket, solder or EL Contact, Socket, Crimp EL A/R Cable, 8 conductor, 22awg SP Route the remaining wire harness cable (P/N SP 02029) from the ALC mount in the right wing, through the wing root, into the cabin behind the headliner and with the existing wire harness, down the co-pilot s side panel, and behind the instrument panel, leaving sufficient slack at both ends. Secure the wire with cable ties or lacing cord. Cut the wire harness and save the remainder. 2. On the ALC end of the wire harness strip the jacket back exposing 5/8 of wires. 3. Remove ¼ of insulation from all wires. 4. Solder (or crimp) the end of each wire to a socket contact (P/N EL or EL 02414). 5. Insert the ends through a backshell (P/N EL 01727). 6. Referring to Drawing 211S0004 for wire color to pin code, insert the sockets into their respective holes in the connector plug housing (P/N EL 01726). 7. Attach the backshell (P/N EL 01727) to the plug housing (P/N EL 01726). Tighten the strain relief to the jacket. Check for pin continuity with a Volt-Ohm Meter. 8. Connect the ALC connector receptacle and wire harness plug together. On the Instrument Panel end of the wiring harness, strip the jacket back exposing 5/8 of wires. 9. Check to ensure that cable routing does not interfere with any other aircraft system. Page 36 of 47

37 2.18 WIRING THE ASYMMETRICAL LOGIC CONTROL (ALC) (PRESSURIZED) TOOLS REQUIRED Needle Nose Pliers Soldering Iron Rosin Core Solder Contact Crimper Volt-Ohm Meter Wire Cutter, Stripper PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Speedbrake installation - 211S Drawing, Aircraft Schematic - 211S Drawing, Feedthrough Istallation - M81969/ Tool, contact extractor EL Connector backshell clamp EL Connector housing, CPC Plug, Sockets, 8 cont. EL or Contact, Socket, solder or EL Contact, Socket, Crimp EL A/R Cable, 8 conductor, 22awg SP MS3126F12-10S 1 Connector, plug, 10 sockets EL MS3126F12-10P 1 Connector, receptacle, 10 pin EL Route the remaining wire harness cable (P/N SP 02029) from the ALC mount in the aft cabin to the back of the instrument panel. Route the cable along the co-pilot s sidewall, leaving sufficient slack behind the instrument panel to connect the circuit breaker, switch, and annunciator. Secure the wire using cable ties or lacing cord. Cut the wiring harness to length and save the remainder. 2. On the ALC side of the cable strip the jacket back exposing 5/8 of wires. 3. Remove ¼ of insulation from all wires. 4. Solder (or crimp) the end of each wire to the end of a socket contact (P/N EL or EL 02414). 5. Insert the ends through the connector backshell (P/N EL 01727). 6. Referring to drawing 211S0004 for wire color to pin code, insert the sockets into their respective holes in the plug housing (P/N EL 01726). 7. Attach the backshell (P/N EL 01727) to the plug housing (P/N EL 01726). Tighten the strain relief to the jacket. Check for pin continuity with a Volt-Ohm meter. 8. Connect the Wire harness plug and ALC receptacle together. 9. Check to ensure that cable routing does not interfere with any other aircraft system. Page 37 of 47

38 2.19 CIRCUIT BREAKER AND SWITCH TOOLS REQUIRED Needle Nose Pliers Soldering Iron Rosin Core Solder Contact Crimper Drill Bits: 7/16, 5/8 Unibit Wire Cutter, Stripper Drill Motor PARTS REQUIRED Part Number Qty Description PFI Code 211S Drawing, Cockpit Control Installation - 211S Drawing, Aircraft Schematic - GE336 2* Lamp Bulb, 12V EL GE334 2* Lamp Bulb, 24V EL Circuit Breaker, 3A EL P-12 1 Cord, Coiled EL A3-12V 1* Light Assembly, Annunciator, Round, 12V (STD) EL A3-28V 1* Light Assembly, Annunciator, Round, 28V (STD) EL /6 1 Lens, Switch, Blue (STD) EL Annunciator/Switch, Pushbutton, Panel Mount (STD) EL S Placard, Switch (STD) - PB-12331ZQ 1 Switch, Pushbutton, Yoke Mount (OPT) EL *Voltage option depends on aircraft electrical system. See packing list Reference Drawings 211S0002 and 211S At the instrument panel, install and wire the circuit breaker (P/N EL 01270). Reference drawing 211S0004 for proper wiring. 2. Insert the lamp bulbs into the annunciator/switch (P/N EL 02596), and install placard (P/N 010S0201-1) into switch lens assembly (P/N EL 2307). Install lens onto switch. Reference 211S0002. If desired, due to panel space constraints, yoke switch (P/N EL 01265) and optional round annunciator (P/N EL or EL 02186) may be installed instead of annunciator/switch. 3. Install the annunciator/switch within full view and easy access of the pilot. Use drawing 211S0002, 211S0004 for reference. If using yoke switch, install onto yoke and wire per 211S0004, and wire annunciator/switch as annunciator only, or install round annunciator. NOTE For switch and light locations other than that shown, obtain separate FAA engineering approval. Page 38 of 47