SNS SUBJECT: SPECIAL PURPOSE EQUIPMENT - CAPS Rocket Motor Assembly Replacement

Transcription

1 CIRRUS SRX Service Bulletin Number: Issued: Revised: 09 Mar 07 SNS SUBJECT: SPECIAL PURPOSE EQUIPMENT - CAPS Rocket Motor Assembly Replacement. COMPLIANCE Mandatory: Cirrus Aircraft considers this Service Bulletin to be MANDATORY. Accomplish this Service Bulletin at next Cirrus Airframe Parachute System (CAPS) parachute and rocket motor assembly replacement (Refer to AMM 04-00). Compliance time begins upon receipt of this Service Bulletin. Concurrent compliance with SBX CAPS Rocket Shelf Ground Wire. WARNING: This Service Bulletin may only be accomplished by a Cirrus Aircraft trained and authorized parachute system technician. Airframe and Powerplant license alone is not sufficient credentials for performing this Service Bulletin. This bulletin was revised to correct an illustration and update compliance information. Operators who have successfully complied with the original release of this Service Bulletin, dated 09 Mar 07, need take no further action.. EFFECTIVITY SR0 Serials 907, 06 thru 3, 5 thru 7 w/ Perspective Avionics SR Serials 487, 979 thru 394 w/ Perspective Avionics SRT Serials 000 thru APPROVAL FAA approval has been obtained on all technical data in this Service Bulletin that affects type design. For aircraft not operating under FAA requirements and regulatory oversight, it is the operator's responsibility to ensure that installation of this Service Bulletin has been accepted by the local airworthiness authority. 4. PURPOSE On affected aircraft, modifications are required to install new rocket motor assemblies. 5. DESCRIPTION This Service Bulletin contains instructions for the accomplishment of modifications to install new rocket motor assemblies. 6. WARRANTY INFORMATION Part and labor costs for this Service Bulletin are at the owner's expense. 7. MANPOWER REQUIREMENTS 30.0 man-hours. 8. OTHER PUBLICATIONS AFFECTED SR0 Airplane Maintenance Manual (p/n 37-00) SR0 Illustrated Parts Catalog (p/n 38-00) SR0 Wiring Manual (p/n 9-00) Page

2 SR0 Component Maintenance Manual (p/n 8-00) SR / SRT Airplane Maintenance Manual (p/n ) SR / SRT Illustrated Parts Catalog (p/n ) SR / SRT Wiring Manual (p/n ) SR / SRT Component Maintenance Manual (p/n ) 9. WEIGHT AND BALANCE Component Weight Arm Rocket and Shelf Assembly.34 lb 3.4 inches Electrical Wiring Modifications 0.78 lb 6.0 inches 0. MATERIAL INFORMATION The following parts are required to comply with this Service Bulletin. Parts can be obtained from an Authorized Cirrus Service Center or Parts Distributor. Reference Kits and , or order the following parts. Item No. Description P/N or Spec. Supplier Quantity Resistor, 0 kohm, 5%, /4 Watt Cirrus W065 Battery Harness Assembly Cirrus 3 Console Harness Assy, Electric Ignition Retrofit Cirrus 4 Fuse Holder, 5x0mm, CAPS Clock Power Cirrus 5 Fuse, 5A Slow, 5x0mm, CAPS Clock Power Cirrus 6 Remanufactured MCU Label Cirrus 7 Wire, 8AWG, Single Conductor, 60 inches Cirrus 8 Connector Pin, 0 AWG, for J00 M3909/4-0 Cirrus 9 Connector Socket, 0 AWG, for P00 M3909/5-5 Cirrus 0 Grommet, Flexible, Panel, inches MS66-N Cirrus Nipple, Electrical Terminal MS57-S Cirrus Locknut, Brass, Nylon Insert, # Cirrus 3 Washer, # Cirrus 4 Socket, for MCU 40 P83 M3909/3-59 Cirrus 5 Terminal, Insulated Spade, 0 AWG,.50 X Cirrus 6 Connector Assembly, Battery Cirrus 7 Assembly, Shelf, Rocket, 3400 lb Cirrus 8 CAPS Ignition Harness & Shield Assembly Cirrus 9 Assembly, Ignitor Switch Cirrus Page

3 Item No. Description P/N or Spec. Supplier Quantity 0 Washer, #0 NAS49D033K Cirrus 8 Washer, /4 NAS49D043K Cirrus 3 Screw, #0-3 X 0.8 MS4694-S47 Cirrus 3 Nut, #0-3 MS04-3 Cirrus 4 Screw, /4-0 X 5/8 AN Cirrus 3 5 Bolt, #0-3 X 0.78 AN3-6A Cirrus 6 Fitting, Retaining, CAPS Cable Cirrus 7 Strike Plate, CAPS Cover Cirrus 8 Nutplate MS059L3 Cirrus 9 Bolt, #0-3 X AN3-5A Cirrus 30 Screw, 8-3, 5/3 X 9/6 AN55-83R9 Cirrus 3 3 Rivet CCR64SS3-3 Cirrus 4 3 Rivet NAS9303B4 alternate for CR34-4 Cirrus 3 33 Terminal spade, female, 8- AWG.50 x Cirrus. ACCOMPLISHMENT INSTRUCTIONS A. SR0 Serials thru 3, 5 thru 7: Contact Cirrus for Field Repair/Alteration R085. () Reference R085 and omit the following steps from this service bulletin: H. Removal of Crew and Passenger Seats. L. Separate J847 from P847 at BAT enclosure. T. Modify upper CAPS compartment. U. Modify lower CAPS compartment V. Attach strike plate patch to CAPS cover. X. Modify LH side of CAPS compartment. AN. Removal of EMI Shielding, PFD, MFD, and Glareshield. AM. Install firewall forward harness. AN. Install console wiring harness. AO. Install Battery wire harness. AU. Install EMI Shielding AV. Install PFD and MFD AW Install Glareshield. Note: CAPS handle does not need to be replaced. Complete step P(). Page 3

4 () Complete airplane records by noting compliance with SBX-95-9 in Aircraft Logbook. No further action is required. Page 4

5 B. Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Safety Wire MS0995C3 Any Source Retain part. Threadlocker, Medium Loctite 4 Henkel Technologies Bond threads. Voltmeter - Any Source Measure voltage. Ohmmeter - Any Source Measure resistance. Die Grinder - Any Source Cut CAPS compartment. Diamond Coated Mini Cutting Disc 0.75 inch (9.05 mm) Any Source Cut CAPS compartment. Drill bit 0.94 inch (0.503 cm) Drill bit inch (.489 mm) #0 Any Source Drill CAPS compartment. #40 Any Source Drill rivet holes. Sanding Drum 80-grit Any Source Abrade. Straight edge - Any Source Measure marks. Sharpie Permanent Fine Point Marker Heat Shrink Sleeving 3/ 6 Heat Shrink Sleeving 3/ (Black) Sanford Mark cut out area Any Source Label wires Any Source Label wires. Solder Sleeve Any Source Splice wires. Cable Tie, nylon, mini MS Any Source Secure wires. Cable tie, black, heat stabilized, nylon,.50 diameter Panduit Corp Secure wires. Cable Tie Anchor Any Source Secure cable ties. Fusion Tape Newark Electronics Secure wires. Epoxy Adhesive 5 Minute Epoxy Devcon Adhesive. High Temperature Silicone Sealant RTV 736 Dow Corning Corporation Sealant. Sealant Per AMS 377, Type or AMS-S-880 Type PR00 Class B ½ alternate for AC40 Class B ½ PRC - Desoto International Adhesive. Vacuum Cleaner - Any Source Clean. Sandpaper 0-grit Any Source Abrade. Page 5

6 Description P/N or Spec. Supplier Purpose Alodine Pen 3 - Any Source Corrosion protection. Nutplate Jig Double wingstandard spacing #0 screw Any Source Install nutplates. Countersink 00 degree Carbide Any Source Countersinking. CAPS Warning Placard Cirrus Install new placard if required. C. SR0 Serials: () Obtain latest revision of SR0 CAPS CMM 8-00 and all applicable temporary revisions from Cirrus Aircraft Service Center website, or Insert revisions into CMM. () Obtain latest revision of SR0 AMM and all temporary revisions from Cirrus Aircraft Service Center website, or Insert revisions into AMM. D. SR and SRT Serials: () Obtain latest revision of SR/T CAPS CMM and all temporary revisions from Cirrus Aircraft Service Center website, or Insert revisions into CMM. () Obtain latest revision of SR/T AMM and all applicable temporary revisions from Cirrus Aircraft Service Center website, or Insert revisions into AMM. E. Remove key from ignition. F. Set BAT, BAT, and AVIONICS switches to OFF positions. G. Perform Removal - Upper and Lower Engine Cowling. (Refer to AMM 7-0) H. Perform Removal - Crew and Passenger Seats. (Refer to AMM 5-0) I. Perform Removal - FS BH Trim Panel and Carpet. (Refer to AMM 5-0) J. Perform Removal - Access Panels CFL, CF3L, CF4L, CF5, CB6, CB7, and RE3. (Refer to AMM 06-00) K. Disconnect battery from both positive and negative terminals. (Refer to AMM 4-30) L. Separate J847 from P847 at BAT enclosure. M. To prevent debris and components from falling into bottom of empennage, place catch cloth below CAPS compartment. N. Ensure safety pin is installed. O. Perform Removal - Pyrotechnic Line Cutters. (Refer to CMM ) P. Perform Removal - Rocket Assembly. (Refer to CMM ) () SR0 Serials, 3, 5-7: Using R085 Figure 0, for reference, remove and discard bolts and washers installed in nutplates on lower CAPS bucket flange. () Remove and retain existing cross beam and hardware. (3) Discard existing rocket shield and hardware. Q. Perform Removal - Parachute Assembly. (Refer to CMM ) R. Perform Inspection/Check - Activation Handle and Cable Assembly. (Refer to CMM ) S. Position vacuum cleaner nozzle near work area to reduce dust/debris migration. T. Modify upper CAPS compartment. (See Figure 0) WARNING: Do not damage airplane attachment harness straps. Page 6

7 Note: Do not measure from foam core. () Using straight edge and permanent marker, measure 0.0 inch (.54 mm) below tangent line of upper CAPS compartment radius and mark a straight line parallel to tangent line of upper CAPS compartment. () Measure 4.0 inches (0.6 cm) aft of FS BH and mark a straight line parallel to FS BH angle. (3) Measure 3.35 inches (8.5 cm) below tangent line of upper CAPS compartment radius and mark a straight line parallel to tangent line of upper CAPS compartment. (4) Measure.0 inch (.54 cm) aft of FS BH and mark a straight line parallel to FS BH angle. (5) Ensure minimum radius of 0.30 inch (7.6 mm) at all corners of cut out area. (6) Using 0.75 inch (9.05 mm) die grinder at marked cut out area, remove material from CAPS compartment. (7) Deburr all edges of cut out hole. (8) Solvent clean modified edges with isopropyl alcohol. (Refer to AMM 0-30) U. Modify lower CAPS compartment. () Using sanding drum, enlarge center hole at bottom of CAPS compartment to.75 inches (4.45 cm). () Deburr all edges of modified hole. Solvent clean modified hole with isopropyl alcohol. (Refer to AMM 0-30) V. Attach strike plate patch to CAPS cover. (See Figure ) () Using sandpaper, lightly abrade existing strike plate and strike plate patch (item 7). () Solvent clean bonding surfaces of strike plate patch and existing strike plate with isopropyl alcohol. (Refer to AMM 0-30) (3) Apply a thin layer of Type sealant to bonding surface of strike plate patch. (4) Position strike plate patch (item 7) along outboard edge of existing strike plate, 0.0±0.50 inch (0.0±3.8 mm). Hold in place until sealant has cured. (5) If interference exists when bonding strike plate patch, replace empennage cover placard. (Refer to AMM -0) W. Assemble rocket shelf (item 7) and rocket shield (item 8) assembly. (See Figure 0) X. Modify LH side of CAPS compartment. (See Figure 0) () Remove rivets two thru six counting down from top. () Using 00 degree countersink, countersink holes two, three, and four counting down from top for flush rivets. Note: Ensure rivet holes are clean and free of debris. (3) Replace rivets two, three, and four counting down from top with rivets (item 3). Ensure rivets are flush with surface. (4) Locate rivet hole six and using #0 drill bit, enlarge hole to 0.94 inch (4.93 mm). (5) Temporarily secure rocket shield, and rocket shelf assembly to cross beam with existing bolts and washers. (6) Position cross beam to opening of CAPS compartment. Hand tighten inside bolts in alternating pattern, temporarily securing cross beam to FS BH. (7) Using a scribe, trace around lower bracket hole on side of rocket shield, marking on CAPS compartment location of new hole to be drilled. (8) Using a flashlight, illuminate area behind CAPS compartment to mark where rivet hole six is visible on shield. Or, using a hole finder, mark where rivet hole six is visible on shield. Page 7

8 (9) Remove cross beam and rocket shelf and shield assembly from airplane. (0) Using #0 drill bit, drill 0.94 inch (4.93 mm) hole in side of shield where marked. () Using #0 drill bit, drill 0.94 inch (4.93 mm) hole in side of CAPS compartment where marked. () Solvent clean holes with isopropyl alcohol. (Refer to AMM 0-30) Y. Install nutplates. (See Figure 0) Note: Cirrus recommends nutplate installation be performed by two authorized parachute system technicians. One technician located outside of the airplane should reach through the avionics compartment to hold nutplates in position on outside of CAPS compartment, while the other technician, located in baggage compartment, installs rivets into nutplates through inside of CAPS compartment. () Using nutplate jig and #40 drill bit, drill four inch (.489 mm) rivet holes into CAPS compartment. () Place nutplates (item 8) at hole locations on outside of CAPS compartment. (3) Install rivets (item 3) into nutplates through inside of CAPS compartment. Z. Adhere cable anchors and grommets. () Using sandpaper at rocket launch tube, abrade bonding surface for cable anchor installation. () Using cloth, clean bonding surface with isopropyl alcohol. (Refer to AMM 0-30) (3) Install cable anchors to bonding surface and secure with 5 Minute Epoxy. (See Figure 04) (4) Reseal exposed aluminum with alodine pen. (5) At CAPS compartment hole, abrade bonding surface for flexible grommet installation. (6) Clean bonding surface with isopropyl alcohol. (Refer to AMM 0-30) (7) Install flexible grommet (item 0) in CAPS compartment hole and secure with 5 Minute Epoxy. (See Figure 03) (8) At bottom of CAPS compartment, abrade bonding surface for cable anchor installation. (9) Clean bonding surface with isopropyl alcohol. (Refer to AMM 0-30) (0) Install cable anchor to bonding surface and secure with 5 Minute Epoxy. (See Figure ) () Abrade rough epoxy as required to obtain smooth surface. AA. Perform Assembly - Rocket Motor. (Refer to CMM ) AB. Assemble rocket, rocket shelf, and rocket shield assembly. (See Figure 0) () Install screws (item 4) and washers (item ) securing rocket shelf (item 7) to rocket. () Safety wire. (Refer to AMM 0-50) (3) Install screws (item 30) securing rocket shield (item 8) to rocket shelf (item 7). AC. Install CAPS ignition harness. () Locate P046, temporarily secured to side of rocket launch tube and route with CAPS ignition harness through cable ties on side of rocket launch tube and inside shield. (See Figure 04) Note: Do not tighten cable ties until instructed. () Loosely secure wires to cable anchors on rocket launch tube using cable ties. (3) Place nipples (item ) on TR70 and TR70. (4) Connect TR70 and TR70 to igniter switch with washers (item 3) and locknuts (item ). (5) Position nipples over terminals. (6) Apply medium threadlocker to screws (item ). (7) Install screws (item ) and washers (item 0) securing igniter switch assembly (item 9) to rocket shield. (See Figure 0) Page 8

9 WARNING: To avoid short circuit and possible shock, do not connect P70 and J70 until instructed. AD. Perform Installation - Parachute Assembly. (Refer to CMM ) AE. Perform Installation - Rocket Assembly. () Record rocket serial number in airplane log book. () Slide pick-up collar assembly onto rocket assembly. (3) Verify pick-up collar slides freely on rocket assembly. (4) Verify anchor blocks are perpendicular to pick-up collar assembly. If pick-up collar assembly is not fully seated against the anchor blocks, use pliers to gently adjust anchor blocks as required. CAUTION: If anchor blocks require realignment, inspect anchor block security. If anchor blocks are loose, contact Cirrus for disposition. (5) Apply medium threadlocker per manufacturer s instructions to aluminum tension screws. CAUTION: Do not overtighten aluminum tension screws. (6) Install aluminum tension screws securing pick-up collar assembly to rocket launch tube using nut driver. Torque to - 5 in-lb ( - 56 Ncm). (7) Install frangible link. (See Figure 04) WARNING: Position frangible link such that perforated break line is on end closest to rocket. Failure to comply will absolutely FAIL rocket deployment! (a) (b) (c) Secure frangible link to rocket assembly using screws, washers and standoffs provided with the rocket motor assembly. Secure terminal rings (TR453 and TR455) from wiring harness to frangible link with screws and washers provided with rocket kit. Secure terminal rings (TR454 and TR456) from rocket igniter to frangible link with screws and washers provided with rocket kit. Note: Position terminal rings so that wires are routed low and clear of CAPS cover. (d) Secure TR453 and TR455 wires to standoff using cable tie. (e) Tighten cable ties securing wires to cable anchors on rocket shield and launch tube. Wrap wires with fusion tape as required to ensure secure hold under cable ties. (See Figure 04) (8) Use ohmmeter to verify resistance between pins in connector P70 per table below. Note: Throughout this Service Bulletin, consider a resistance of less than ohm to be equal to 0 ohm, and a resistance greater than 0 Mohms to be OPEN. FROM TO RESISTANCE P70, socket A P70, socket B 00±0 kohms P70, socket A P70, socket C OPEN P70, socket A P70, socket D OPEN P70, socket A P70, socket E OPEN P70, socket B P70, socket C OPEN P70, socket B P70, socket D OPEN P70, socket B P70, socket E OPEN Page 9

10 FROM TO RESISTANCE P70, socket C P70, socket D 0 ohm P70, socket C P70, socket E OPEN P70, socket D P70, socket E OPEN (9) Verify rocket extends beyond upper end of pick-up collar support. (0) Verify pick-up collar assembly is properly seated to the anchor blocks. () Verify rocket lanyard is engaged with the retaining grooves on the pick-up collar assembly. () At top of parachute assembly, locate and feed lanyard aft towards stowage pocket in parachute assembly to facilitate initial recoiling of lanyard. CAUTION: Ensure ends of lanyard routed aft do not wrap around forward portion of rocket assembly. (3) Install Rocket, Shelf, and Shield Assembly. (See Figure 0) (a) Apply medium threadlocker to bolts (item 9). (b) Insert bolts through washers (item 0), bracket, holes on side of rocket shield, and holes on side of CAPS compartment into nutplates (item 8) securing rocket, shelf, and shield assembly to CAPS compartment. (c) Using a mirror and a flashlight, inspect frangible link to verify no damage occurred during installation. Note: Ensure lanyard is fed into stowage pocket prior to cross beam installation. (4) Perform Installation - Cross Beam. (a) Position existing cross beam to FS BH and secure hand-tightened with existing bolts and washers. (b) Secure cross beam to rocket shelf with existing bolts and washers. (5) Torque bolts securing cross beam to FS BH. (Refer to AMM 0-60) (6) Verify LH edge of pick-up collar is oriented approximately 45 away from FS BH. (7) Verify minimum gap of 0.3 inch (3.30 mm) exists between outer diameter of pick-up collar ring and aft side of FS BH. (See Figure 03) (8) If gap between outer diameter of pick-up collar ring and aft side of FS BH is less than 0.3 inch (3.30 mm), add washers between rocket shelf and FS BH as needed to achieve minimum gap. WARNING: Incorrect gap between outer diameter of pick-up collar and aft side of FS BH may result in deployment failure. Do not measure at lanyard legs extending outward from pickup collar. Note: Equal number of added washers must be used on inboard and outboard sides of shelf. If more than 0.5 inch (0.635 cm) of washers is required to achieve minimum gap, contact Cirrus. (9) Feed remaining lanyard aft until slack is removed and lanyard is coiled back into stowage pocket in parachute assembly. Ensure ends of lanyard routed aft do not wrap around forward portion of rocket assembly and lanyard coil in the stowage pocket is not twisted. WARNING: Verify rocket lanyard is positioned around top outer diameter of pick-up collar support, NOT over top of the rocket. Failure to comply will absolutely FAIL rocket deployment! Page 0

11 WARNING: Verify rocket lanyard is routed around back of rocket and aft parachute harness, NOT around front. Failure to comply will absolutely FAIL rocket deployment! (0) Verify rocket lanyard is positioned around top outer diameter of pick-up collar support. () Ensure Airplane Attachment Harness is positioned straight and vertical. AF. Secure existing activation assembly to shield. (See Figure 0) () Line up activation cable to activation bracket. () Apply medium threadlocker to retaining fitting (item 6). (3) Insert retaining fitting (item 6) into bracket and into activation cable cone. Note: TR705 and cable loop must be captured by isolating links. (4) Install bolt (item 5) through isolating links at base of igniter switch securing activation cable loop and TR705 with washers (item 0) and nut (item 3). (5) Torque to 5-0 in-lb ( Nm). WARNING: Note: Activation of rocket igniter requires 5 lb (.5 kg) pull force. The following verification is meant only to ensure firing pin capture. A very slight pull force of /3 lb (0.3 kg) is all that is required to verify capture. Orient linkage as shown and position ring lug downward and towards front of aircraft. Isolator may be temporarily rotated for hardware installation. Return to original position when hardware installation is complete. (See Figure 04) (6) Slightly pull activation cable projecting from igniter switch to verify capture. AG.Connect plug P046 to jack J046 and secure wire harness with cable ties to existing cable anchors on rocket shield. AH. Remove catch cloth from below CAPS compartment. AI. Route P70 outside CAPS compartment through modified hole at bottom of CAPS compartment and secure with cable tie to cable anchor. AJ. Perform Installation - Pyrotechnic Line Cutters. (Refer to CMM ) AK. Serials with MCU part number : Do not replace external fuse holder and fuse in the following step. AL. Serials with MCU part number : Replace external fuse holder and fuse. (See Figure 08) () If necessary to remove fuse holder and wiring, remove MCU. (Refer to AMM 4-30) () Remove MCU cover. (Refer to AMM 4-30) (3) Locate external fuse holder. (Refer to AMM 4-30) (4) Uninstall external fuse holder. (a) Remove external fuse holder from MCU chassis. (b) Pull terminals TR95 and TR96 from fuse holder. (c) Discard fuse holder and fuse. (5) Using nut provided with fuse, secure new fuse holder (item 4) to MCU chassis. (6) Attach existing spade terminals TR95 and TR96 to fuse holder. (7) Install new external fuse (item 5). (Refer to AMM 4-30) (8) Install remanufactured MCU label (item 6). Page

12 Note: Contact Cirrus if part number of MCU installed in airplane is not listed in the following table. (a) Using cloth, clean existing label surface with isopropyl alcohol. (Refer to AMM 0-30) (b) Select the appropriate remanufactured MCU label and install over existing MCU label. MCU ORIGINAL REMANUFACTURED (9) Reassemble MCU. (Refer to AMM 4-30) (0) Reinstall MCU into airplane. (Refer to AMM 4-30) AM.Install forward firewall wiring. (See Figure 07) WARNING: Prior to removing P00 and J00 from firewall connector, ground P-leads at magnetos to prevent accidental firing of the engine. () Remove P00 and J00 from firewall connector. Remove heatshrink to access wires. () Remove PGCP07-0 and existing contact from MCU connector P83, socket G. Cap and stow or discard. (3) Remove heatshrink from wire bundle at connectors. (4) Route new 8 AWG wire (item 7) and trim to appropriate length. (5) Label new 8 AWG wire CPCI (6) For MCU connector P83, add socket (item 4). (7) For firewall connector P00, add connector socket (item 9). (8) Insert CPCI700-8 into connector P83 position G. (9) Insert CPCI700-8 into connector P00 socket. (0) Wrap harness with fusion tape to ensure wires are secured in backshell. AN. Install console wire harness. () Remove glareshield. (Refer to AMM 5-0) () Remove MFD and PFD. (Refer to AMM 3-60) (3) Remove EMI shielding. (Refer to AMM 5-0) (4) Remove console wire harness J847 and attached wiring. (a) Disconnect TR847 at the BAT circuit breaker in the circuit breaker panel. (See Figure 06) (b) Disconnect BAPR848-0N at forward ground block terminal, P60. (See Figure 09) (5) Route new J847 branch through spar tunnel. (See Figure 09) WARNING: Do not connect P847 and J847 at this time. (6) Install console harness assembly (item 3) forward of spar tunnel and secure along fuselage forward harness. (See Figure 09) Note: Route BAPR847-0 (TR847) branch up through hole in floor and immediately to circuit breaker panel. It is not required to follow former routing path. (7) Route BAPR847-0 (TR847) to circuit breaker panel and connect to BAT circuit breaker. (See Figure 06) (8) Route BAPR848-0N and overbraid shield (TR848) to ground block P60. (See Figure 09) (9) Install TR848 on ground block P60. (0) Connect CPCI700-8 (from J847 Pin C). Page

13 (a) Route CPCI700-8 to J00 and trim wire to appropriate length, with allowance for connector terminals. (b) Attach connector pin (item 8) to CPCI (c) If J00, pin has been previously populated, remove pin and discard. (d) Install CPCI700-8 into J00, pin. () Wrap harness with fusion tape to ensure wires are secured in backshell. () Install J00 and P00 connectors back into firewall. (3) Remove ground wire from P-leads at magnetos. (4) Ensure BAT and BAT switches are set to OFF positions. (5) Connect battery to both positive and negative terminals. (Refer to AMM 4-30) (6) Complete the following voltage and resistance checks. CAUTION: Use caution during electrical checks. Do not short MCU fuse. FROM (-) TO (+) RESISTANCE VOLTAGE J847, pin A J847, pin B - 0 V J847, pin D CENTER CONSOLE FRAME 0 ohm 0 V J847, pin B J847, pin D 0 ohm 0 V J847, pin B J847, pin C - +4 V (7) Set BAT switch to ON position. (8) Complete the following checks. AO. Install BAT wiring harness. () Disconnect vent line from top of BAT. (See Figure 05) () Disconnect wiring from BAT and K50. (a) Ensure J847 is separated from P847. (b) Disconnect TR678 (CSMS87-) from K50. Retain for later reconnection. (3) Open CB880 and CB88 circuit breakers at BAT. (4) Remove BAT, K50, relay mounting plate, circuit breakers, and attached wiring from aircraft. Retain hardware. (5) Separate BAT enclosure halves. Discard fasteners. Retain bulkhead union for vent tube. (See Figure 05) (6) Disconnect TR860 and TR86 from battery positive and negative terminals. (7) Route BAT connector assembly (item 6) through grommeted holes in BAT enclosure top. (8) Strip wires to obtain clean and bright conductors. CAUTION: Ensure correct terminal ring label is assigned to each wire. (See Figure 05) (9) Insert ends of wires into terminal rings (item 5) and crimp. Label terminals TR860 and TR86 using white heat shrink and black or blue indelible ink. (See Figure 05) FROM (-) TO (+) VOLTAGE J847, pin B J847, pin A +4 V J847, pin B J847, pin C +4 V Page 3

14 WARNING: To prevent short circuit and possible shock, do not connect J69 to P69 until instructed. (0) Perform the following connector checks on new BAT connector assembly. FROM TO RESISTANCE P69, socket A P69, socket B 0 ohm P69, socket A P69, socket C OPEN P69, socket A TR860 0 ohm P69, socket B P69, socket C OPEN P69, socket B TR860 0 ohm P69, socket C TR86 0 ohm () Connect TR860 and TR86 to BAT positive and negative terminals. Observe proper polarity of battery terminals TR860 (-) and TR86 (+). () Reassemble battery enclosure using existing hardware. (3) Perform the following BAT enclosure voltage checks. Note: Throughout this bulletin, consider a voltage of +3±3 volts to be equal to +4 volts. FROM (-) TO (+) VOLTAGE P69, socket A P69, socket B 0 V P69, socket A P69, socket C +4 V P69, socket B P69, socket C +4 V (4) Reinstall BAT with new BAT harness assembly and wiring into airplane. WARNING: To prevent short circuit and possible shock, do not connect J70 to P70, J69 to P69, or J847 to P847 until instructed. (a) (b) If BAT relay contact with FS BH cannot be avoided, contact Cirrus for disposition. Ensure BAT and BAT switches are set to OFF positions. Stow P700 for later in this procedure. Note: If P847 is pre-assembled, it may be necessary to temporarily separate the connector body from the contacts to fit the wires through the hole. (c) Route new P847 branch of BAT harness through hole in bulkhead and under floor to spar tunnel. (See Figure 0) (d) Ensure contacts are properly installed in connector body. (See Figure 08) (e) Connect TR678 (CSMS87-) to TR485 in new BAT assembly. (See Figure 07) Page 4

15 Note: If TR678 and TR485 don't mate properly, replace TR678 with (item 33), and relabel TR678. (f) Reattach BAT vent line. (g) Route J70 to outside of CAPS compartment. (See Figure ) (h) Using sandpaper, abrade bonding surface. (i) Using cloth, clean bonding surface with isopropyl alcohol. (Refer to AMM 0-30) (j) Secure cable anchors to bonding surfaces using 5 Minute Epoxy. (k) Secure J70 wires to cable anchors using cable ties. (l) Secure BAT enclosure using existing hardware. (See Figure 05) (m) Secure relay plate (part of (item )) using existing hardware. (See Figure 05) (n) Secure wires to existing cable anchors using cable ties. (o) Perform the following BAT Harness resistance checks. (p) Close CB880 and CB88 circuit breakers. (q) Connect J69 to P69. (r) FROM TO RESISTANCE P847, socket A P847, socket B OPEN P847, socket A P847, socket C OPEN P847, socket A P847, socket D OPEN P847, socket B P847, socket C OPEN P847, socket B P847, socket D OPEN P847, socket C P847, socket D OPEN Perform the following BAT Harness voltage checks. FROM (-) TO (+) VOLTAGE P847, socket B P847, socket A 0 V P847, socket B P847, socket C 0 V P847, socket B P847, socket D 0 V (s) (t) Temporarily jumper P847 socket B to the center console metal frame. Set BAT switch to ON position. Note: An audible click will indicate that the relay has switched on. (u) Perform the following voltage check. FROM (-) TO (+) VOLTAGE P847, socket B P847, socket A +4 V (5) Set BAT switch to OFF position. (6) Remove jumper from P847 socket B previously attached to the center console metal frame. Page 5

16 AP. Perform basic connections. () Set BAT and BAT switches to OFF positions. () Ensure P70 is separated from J70. (3) Connect P847 to J847. (See Figure 0) (4) Ensure CB880 and CB88 circuit breakers are closed. (5) Perform the following voltage checks at diagnostics connector P700. Reference all readings to P700, socket 8 (-) lead. (See Figure ) CHECK DESCRIPTION VOLTMETER READING P700, socket BAT CLOCK POWER +4 V P700, socket BAT +4 V P700, socket 3 IGNITER SWITCH DIAGNOSTIC 0 V P700, socket 4 NOT USED 0 V P700, socket 5 NOT USED 0 V P700, socket 6 TEST POINT RESISTOR 0 V P700, socket 7 NOT USED 0 V SHIELD GND AIRCRAFT CHASSIS 0 V (6) Verify the following voltages at J70. Reference all readings to J70, pin A (-) lead. CHECK DESCRIPTION VOLTMETER READING J70, pin B FR. LINK TEST RESISTOR 0 V J70, pin C IGNITER SWITCH VOLTAGE 0 V J70, pin D IGNITER SWITCH POWER +4 V J70, pin E SHIELD 0 V Page 6

17 AQ.Perform safety configuration. () Set BAT and BAT to OFF positions. () Open CB880 and CB88 circuit breakers at BAT. (3) Disconnect battery from both positive and negative terminals. (Refer to AMM 4-30) (4) Verify the following voltages at J70. Reference all readings to J70, pin A (-) lead. CHECK DESCRIPTION VOLTMETER READING J70, pin B FR. LINK TEST RESISTOR 0 V J70, pin C IGNITER SWITCH VOLTAGE 0 V J70, pin D IGNITER SWITCH POWER 0 V J70, pin E SHIELD 0 V AR. Perform active configuration. () Connect P70 to J70. () Stow and secure cabling for P70 and J70 to prevent entangling aircraft control cables or shorting nearby wiring. WARNING: Once battery is connected, CAPS system is active. (3) Connect battery to both positive and negative terminals. (Refer to AMM 4-30) AS. Perform diode checks. () Ensure CB880 and CB88 circuit breakers are open. () Temporarily install 0 kohm resistor (item ) across positive and negative voltmeter terminals. (3) Verify the following voltage readings at P700. Reference readings to P700, socket 8 (center socket). (See Figure 08) CHECK DESCRIPTION VOLTMETER READING P700, socket BAT Bus V MAX. P700, socket 3 BAT + BAT DIODE OR D BUS +4 V (4) Remove 0 kohm resistor from voltmeter and use DIODE CHECK feature to verify the following readings. (-) METER LEAD (+) METER LEAD METER READING P700, socket 3 P700, socket 0.5±0.3 V P700, socket 3 P700, socket 0.5±0.3 V P700, socket P700, socket 3 OPEN P700, socket P700, socket 3 OPEN (5) Close CB880 and CB88 circuit breakers. Page 7

18 AT. Perform final checks. () Switch the voltmeter back to the VOLTAGE function and perform the following voltage checks at the diagnostics connector P700. Reference all readings to P700, socket 8 (-) lead. CHECK DESCRIPTION VOLTMETER READING P700, socket BAT CLOCK POWER +4 V P700, socket BAT +4 V P700, socket 3 IGNITER SWITCH DIAGNOSTIC () Use an ohmmeter to verify the following resistances. +4 V P700, socket 4 NOT USED 0 V P700, socket 5 NOT USED 0 V P700, socket 6 TEST POINT RESISTOR 0 V P700, socket 7 NOT USED 0 V SHIELD GND AIRCRAFT CHASSIS 0 V FROM TO RESISTANCE P700, socket 8 P700, socket 6 00±0 kohms P700, socket 8 CABLE SHIELD < ohm (3) Set BAT and BAT switches to OFF positions. (4) Cap and stow P700 and secure cabling to prevent entangling aircraft control cables or shorting nearby wiring. (See Figure ) AU. Install EMI shielding. (Refer to AMM 5-0) AV. Install PFD and MFD. (Refer to AMM 3-60) AW.Install glareshield. (Refer to AMM 5-0) AX. Install engine cowling. (Refer to AMM 7-0) Note: It is not necessary to perform Electric Ignition Checkout Procedure, as defined in AMM AY. Perform Inspection/Check - Cirrus Airplane Parachute System. (Refer to AMM 95-00) AZ. Using vacuum cleaner, remove all debris from baggage floor, CAPS compartment, and fuselage belly below the CAPS compartment. BA. Visually inspect CAPS compartment for security, leaks, loose or missing hardware, moisture, and general condition. BB. Perform Installation - Access Panels CFL, CF3L, CF4L, CF5, CB6, CB7, and RE3. (Refer to AMM 06-00) BC. Perform Installation - FS BH Trim Panel and Carpet. (Refer to AMM 5-0) BD. Perform Installation - Crew and Passenger Seats. (Refer to AMM 5-0) BE. Obtain latest revision of applicable POH and all current temporary revisions from Cirrus Aircraft Service Center website, or and insert into POH. BF. Using recorded aircraft weight, calculate and record new weight and center of gravity values on the Weight & Balance Record of the POH. Page 8

19 BG.Complete airplane records by noting compliance with in Aircraft Logbook. To submit a Technical Publication change request, visit: or contact us by at techpubs@cirrusaircraft.com. Page 9

20 B C D A G A A DETAIL A 4.00 inches (0.6 cm).00 inch (.54 cm) BULKHEAD RADIUS TANGENT 0.0 inch (.54 mm) 3.35 inches (8.5 cm) CAPS COMPARTMENT R 0.3 inch (7.6 mm) TYPICAL NOTE Measure from tangent of radius. VIEW A SR_SB95_494B Figure 0 CAPS Compartment Modification ( of ) Page 0

21 BULKHEAD (RIVET ) (RIVET 3) (RIVET 4) (RIVET 5) CAPS COMPARTMENT (RIVET 6) NOTE Remove rivets two thru six counting down from top. Replace rivets two, three, and four counting down from top with rivets. 3 Locate rivet hole six and using #0 drill bit, enlarge hole to 0.94 inch (4.93 mm). 4 Using a scribe, trace around lower bracket hole on side of rocket shield, marking on CAPS compartment location of new hole to be drilled. 5 Using a flashlight, illuminate area behind CAPS compartment to mark where rivet hole six is visible on shield. Or, using a hole finder, mark where rivet hole six is visible on shield. DETAIL B SR_SB95_498 Figure 0 CAPS Compartment Modification ( of ) Page

22 NOTE Torque to 5-0 in-lb ( Nm). C C ROCKET TR C ACTIVATION CABLE C DETAIL C LEGEND. Cross Beam. Washer 3. Bolt 4. Nutplate 5. Bracket 6. Screw 7. Nut 8. Retainer 9. Igniter Switch 0. Rocket Shelf. Rocket Shield SRX_SB95_493A Figure 0 CAPS Rocket and Shelf Assembly Page

23 45 BH CAPS COMPARTMENT PICK-UP COLLAR 4 Ø.75 inches (4.45 cm) inch (3.30 mm) VIEW C VIEW C 3 4 NOTE Incorrect gap between outer diameter of pick-up collar and aft side of BH may result in deployment failure. Verify LH edge of pick-up collar is oriented approximately 45 away from BH. Ensure ends of lanyard routed aft do not wrap around forward portion of rocket assembly. Enlarge existing hole to Ø.75 inch (4.45 cm). LEGEND. Flexible Grommet SRX_SB95_49A Figure 03 CAPS Compartment Modification and Pick-up Collar Page 3

24 TR453 (POSITIVE) TR455 (NEGATIVE) 3 D D PLC'S E 4 5 D D TR705 R700 3 R700 P046 3 TR705 P70 P046 P70 LH-SIDE VIEW LOOKING RIGHT FORWARD-SIDE VIEW LOOKING AFT NOTE Install anchors and cable ties to prepared surface on side of launch tube using adhesive. Wrap wires with fusion tape as required to ensure secure hold under cable ties. Install TR705 with hardware provided. Orient linkage as shown and position ring lug downward and towards front of aircraft. 3 Secure TR453 and TR455 wires to standoff using cable tie. LEGEND. Wiring Harness. Cable Tie 3. Cable Anchor 4. Igniter Switch 5. Rocket Shield 6. Standoff 7. Sleeving DETAIL D SR_SB95_495A Figure 04 CAPS Electric Ignition Assembly ( of ) Page 4

25 3 TR456 TR455 (NEGATIVE) PLC'S TR453 (POSITIVE) TR70 4 TR70 TR PLC'S VIEW C ORIENTATION OF TERMINAL RINGS SECTION C TR70 TR DETAIL D 5 NOTE Position frangible link such that perforated break line is on end closest to rocket. Failure to comply will absolutely FAIL rocket deployment! At igniter switch, position nipples over terminals. LEGEND 4. Igniter Switch 5. Rocket Shield 8. Washer 9. Nut 0. Screw. Frangible Link. Rocket Igniter 3. Launch Tube 4. Nipple SR_SB95_479C Figure 04 CAPS Electric Ignition Assembly ( of ) Page 5

26 VENT LINE 5 P69 CONNECTOR BULKHEAD UNION BATTERY ENCLOSURE, UPPER TR859 TR858 TR860 PART OF BULKHEAD UNION 3 TR86 BATTERY BATTERY ENCLOSURE, LOWER J69 CONNECTOR 6 MOUNTING TRAY 4 LEGEND. Screw. Washer 3. Battery Connector Assembly 4. Battery Harness Assembly 5. Nut 6. Spacer Figure 05 Battery Assembly SR_SB95_568 Page 6

27 (TR847) AV ESS SHED ESS MB ESS MB BAPR847-0 AV NON-ESS NON-ESS LOCK WASHER (TR847) NOTE Use existing lock washer. LEGEND. Battery Circuit Breaker. Screw SR_SB95_48 Figure 06 Circuit Breaker Panel Page 7

28 CR70 CR70 J70 P70 SHIELD E E SHIELD CIOP70-8 D D CIOP70-8 CIFL704-8N CDOP706- CDFI70- A C B A C B CIFL704-8N CDOP706- CDFI70- P700 CDFI70- CDOP706- CDMB708- CDSB707- CDFO709-N CAPS DIAGNOSTIC CONNECTOR FRANGIBLE IN CONTACTOR IN BAT BAT GROUND IGNITER SWITCH R700 TR70 TR70 TR453 TR V GND TR454 TR456 IGNITER ASSEMBLY.0-.5 AWG CIFI7-8 K TO BOLSTER PANEL SWITCH CB AWG CB88 30 PGSB74- CSMS87- J69 P69 BATTERY TR859 + TR86 BAPR705-0 C C BAPR705-0 CIFL704-8N BAPR848-0N TR705 FRANGIBLE LINK - 87 K AWG SBCI70-8 B B A A 8 AWG BAPR848-0N + P847 BAPR847-0 J847 SHIELD BAPR848-0N D CPCI700-8 BAPR847-0 BAPR848-0N B CPCI700-8 BAPR847-0 P60 D B C A C A TR707 CIRCUIT BREAKER PANEL CB67 BAPR847-0 BATTERY 0 ESSENTIAL BUS TR847 FIREWALL 0 AWG J00 P00 P83 J83 MCU RE-PIN CPCI700-8 G G FUSELAGE FORWARD TR860 TR858 CAP AND STOW PGCP07-0 SR_SB95_567 Figure 07 Wiring Schematic Page 8

29 8 A K J J00/J0 8 H J83 A J847 J K P00/P0 A P83 H P847 A A A J69 J70 7 P700 P69 A P70 A MCU TR95 TR96 LEGEND. Fuse Holder. Nut SR_SB95_569 Figure 08 Connector Bodies and Fuse Holder Modification Page 9

30 A B C CIRRUS S ERVICE BULLETIN (J00) (CPCI700-8) (BAPR848-0N) (P60) (BAPR847-0) (TR847) (J847) SPAR TUNNEL CONSOLE - LOOKING DOWN SR_SB95_570 Figure 09 Console Wiring Page 30

31 A B C A B C D E A B C A B C D E CIRRUS S ERVICE BULLETIN G P69 J69 P847 J847 TR847 TO J00 G P700 TR848 J70 TR848 TO J00 TR847 BATTERY HARNESS P847 J847 F SR_SB95_57 Figure 0 Battery Wiring Page 3

32 J70 P700 DETAIL F BATTERY HARNESS BULKHEAD CAPS COMPARTMENT J70 P70 P700 NOTE Cap and stow P700 and secure cabling to prevent entagling aircraft control cables or shorting nearby wiring. VIEW G SR_SB95_57 Figure CAPS Compartment and Battery Assembly Page 3

33 CAPS COVER!! DANGER PELIGRO ACTIVATION CABLE CABLE DE ACTIVAIÓN DO NOT CUT NO CORTAR CAPS COVER CUBIERTA DE CAPS ROCKET COHETE PARACHUTE ASSEMBLY ENSAMBLADO DEL PARACAÍDAS Explosion and Fire Hazard. Peligro de Explosión o Fuego. Airplane is equipped with a rocket deployed parachute system. Access and maintenance performed by authorized personnel only. El avión esta equipado con un sistema de paracaídas activado por cohete. Acceso y mantenimiento restringido a personal autorizado. Cirrus Design Corp (USA) BOTTOM VIEW OF CAPS COVER LOOKING UP FROM INSIDE CAPS ENCLOSURE. NOTE Position strike plate patch along outboard edge of existing strike plate, 0±0.50 inch (0±0.38 mm). DETAIL G LEGEND. Strike Plate Patch. Placard Locate placard approximately as shown. SR_SB95_496A Figure CAPS Cover Modification Page 33

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