CIRRUS AIRPLANE MAINTENANCE MANUAL

SPECIAL PURPOSE EQUIPMENT 1. GENERAL This section describes special purpose equipment on the airplane. This equipment includes the Cirrus Airplane Parachute System (CAPS) and the aft tiedown ballast bracket. A. Cirrus Airplane Parachute System (CAPS) The airplane is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. CAPS consists of a parachute, a solid-propellant rocket to deploy the parachute, a rocket activation system, and a harness faired into the fuselage structure. A composite enclosure containing the parachute and solid-propellant rocket is mounted to the airplane structure immediately aft of the baggage compartment bulkhead. The enclosure is covered and protected from the elements by a thin composite cover. The parachute is enclosed within a deployment bag that stages the deployment and inflation sequence. The deployment bag creates an orderly deployment process by allowing the canopy to inflate only after the rocket motor has pulled the parachute lines taut. The parachute itself is a 200-square-foot round canopy equipped with a slider, an annular-shaped fabric panel with a diameter significantly less than the open diameter of the canopy. The canopy suspension lines are routed through grommets so that the slider is free to move along the suspension lines. Since the slider is positioned at the top of the suspension lines near the canopy, at the beginning of the deployment sequence, the slider limits the initial diameter of the parachute and the rate at which the parachute inflates. The canopy inflates as the slider moves down the suspension lines. A three-point attachment harness connects the airplane to the parachute. The harness consists of two forward straps faired into the fuselage skin and attached to the firewall, and one rear strap attached to FS 222 bulkhead located directly forward of the parachute compartment. The harness system is designed to control the pitch dynamics of the airplane during the deployment cycle by limiting the aft attachment strap s length until the cycle is complete. This is accomplished by utilizing a variable length strap section. The shorter section, which initially supports the load, employes a mechanical release that is activated by two pyrotechnic cutters which fire when the short section is pulled taut during extraction. The harness strap then lengthens and load is transferred to the longer section. B. Aft Tie Down Ballast Bracket The aft tie down ballast bracket is designed to offset the aircraft center of gravity. The ballast consists of two components that attach to the aft spar of the vertical stabilizer. The forward component weighs 8. lb (3.8 kg). The aft component weighs 6. lb (2.9 kg) and is integral to the aft tie down bracket. The aft tie down ballast bracket installation replaces the non-ballast equipped aft tie down bracket. (Refer to 53-20) Page 1 31 May 2011

2. DESCRIPTION (See Figure 1) A. Cirrus Airplane Parachute System (CAPS) Two separate and deliberate pilot actions are required to deploy the parachute. The first action requires the pilot to remove the access cover from the activation handle enclosure. The second action requires the pilot to pull the activation handle out, and down several inches. Upon pulling the activation handle, the activation cable compresses the igniter s steel spring, cocks the plunger and the following sequence is initiated: Serials 1005 thru 1267 before SB2X-95-20, Serials 1268 thru 122 before SB2X-95-17 Serials 123 thru 2227, Serials 123 & subs w/o Perspective before SB2X-95-18: When one half-inch of plunger travel is reached, captured ball-bearings are released allowing the plunger to strike the firing pins. The firing pins strike two primers which ignite the primary booster. Serials 1005 thru 1267 after SB2X-95-20, Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, Serials 2228 & subs: When one half-inch of plunger travel is reached, captured ball-bearings are released allowing the plunger to close the electrical contacts. The closed electrical circuit ignites the primary booster. The primary booster ignites a secondary booster initiating ignition of the larger rocket motor. Once ignited, the rocket propellant s hot gases are exhausted through the nozzle and the rocket impacts and disbonds the parachute compartment cover pulling the deployment bag from the enclosure. The deployment bag then stages the suspension line deployment and inflation of the parachute. As the parachute inflates, the forward harness assembly grows taut, pulls free of the fuselage skin, and stops at the forward attach fitting which supports the forward portion of the airplane. The aft harness is pulled taut, the line cutters are activated, and approximately eight seconds later fire and sever the nylon cord. The three-link release mechanism then opens allowing the aft harness to fully extend. The airplane then assumes its touchdown attitude; approximately ten degrees nose down, to optimize occupant protection. B. Aft Tie Down Ballast Bracket The aft tie down ballast bracket provides operators more flexibility in loading the aircraft within the prescribed weight and center of gravity limits. Note: If alternating between aft tie down installations, use recorded aircraft weight to calculate and record new weight and center of gravity values on the Weight & Balance Record of the POH. Page 2

CAPS EQUIPPED CAPSEQUIPPED CIRRUS AIRPLANE MAINTENANCE MANUAL ACTIVATION SYSTEM FORWARD ATTACH POINT ROCKET ASSEMBLY CAPS COVER FORWARD HARNESS PARACHUTE ASSEMBLY 6 - Parachute Disreef 3 - Line Extension - Initial Canopy Inflation 5 - Reefed Parachute 7 - Snub Line Release 1 - Rocket Extraction 2 - Parachute Extraction Figure 1 CAPS Deployment SR20_MM95_1273A Page 3 31 May 2011

3. MAINTENANCE PRACTICES A. Cirrus Airplane Parachute System (CAPS) WARNING: Never activate CAPS on the ground. The rocket exits the fuselage with a velocity of 150 mph in the first tenth of a second and reaches full extension in less than one second. People near the airplane may be injured and extensive damage to the airframe will occur. Ground activation will cause the airplane to be out of service until CAPS is replaced and the airframe repaired and inspected. Rocket ignition will occur at temperature above 500 F (260 C). In the event of ground fire, use necessary precautions to avoid CAPS deployment. FAA Type Certification for the SR20 is contingent on a functional Cirrus Airframe Parachute System (CAPS). The airplane may not be flown when CAPS is rendered inoperative. CAUTION: Note: CAPS must be serviced and maintained by Cirrus Design trained and authorized parachute system technicians only. Airframe and Powerplant license alone is not sufficient credentials for performing maintenance on CAPS. Refer to Cirrus Airframe Parachute System Maintenance Manual w/ Illustrated Parts List (P/N 12128-001) for additional CAPS Maintenance Practices. Licensed Airframe and Powerplant mechanics may visually inspect the parachute installation only as specified in the following inspection. (1) Inspection/Check - Cirrus Airplane Parachute System (See Figure 2) (a) Remove CAPS handle access cover and verify CAPS handle safety pin is installed. (b) Serials 1005 thru 1267 after SB2X-95-20: Disconnect battery 1 from both positive and negative terminals. (Refer to 2-30) (c) Remove bulkhead 222 trim and carpet. (Refer to 25-10) (d) Remove access panel CB6 and CB7 from bulkhead 222. (Refer to 06-00) (e) Serials 123 and subsequent: Remove access panel RE3. (Refer to 06-00) (f) Verify no moisture or mildew evident in Parachute Enclosure or CAPS Assembly. (g) At top of Rocket Assembly, verify top surface of Rocket is level with or slightly higher than Pick-Up Collar Support. (h) Serials 1005 thru 1267 before SB2X-95-20, Serials 1268 thru 122 before SB2X-95-17, Serials 123 thru 2227, Serials 123 & subs w/o Perspective before SB2X-95-18: Verify Rocket Lanyard is positioned around aft diameter of Pick-Up Collar Support. (i) Serials 1005 thru 1267 after SB2X-95-20, Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, Serials 2228 & subs: Verify Rocket Lanyard is positioned around forward diameter of Pick- Up Collar Support. WARNING: Rocket Lanyard must be positioned around diameter of Pick-Up Collar Support, NOT over top of Rocket. Failure to position Rocket Lanyard around diameter of Pick-Up Collar Support will absolutely FAIL deployment (j) Verify Rocket Lanyard is routed above Rear Harness Assembly. Page

WARNING: Rocket Lanyard must be routed above Rear Harness Assembly, NOT underneath. Failure to route Rocket Lanyard properly will absolutely FAIL deployment. (k) (l) (m) (n) (o) (p) (q) (r) (s) (t) (u) (v) (w) (x) Verify Shear Screws securing Pick-Up Collar Support to Pick-Up Collar are fully engaged. Serials 1005 thru 1267 before SB2X-95-20, Serials 1268 thru 122 before SB2X-95-17, Serials 123 thru 2227, Serials 123 & subs w/o Perspective before SB2X-95-18: Verify 0.0 inch (10.16 mm) clearance exists between Pick-Up Collar and BH 222. Serials 1005 thru 1267 after SB2X-95-20, Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, Serials 2228 & subs: Verify minimum gap of 0.13 inch (3.30 mm) exists between outer diameter of pick-up collar ring and aft side of BH 222. Serials 1005 thru 1267 before SB2X-95-20, 1268 thru 122 before SB2X-95-17: Verify Grommet installed to Rocket Shield and Activation Cable. Verify LH and RH Fuselage Harness exiting Parachute Enclosure is not twisted. Verify Protective Sheath around Aft Harness is captive by Aft Harness Bracket. Verify Lanyard is coiled behind Aft Harness and stowed neatly into Stowage Pocket on the parachute assembly. Just below Stowage Pocket, verify Aft Harness secured to Parachute Assembly either by velcro pack or stitching. Verify correct alignment of Three-Link Release Assembly. Verify Aft Harness lays flat against Parachute Assembly. Behind Rocket Shield, verify Abrasion Sheath installed to LH Fuselage Harness. Inspect for chafing or cutting on CAPS Assembly Retaining Straps along bottom and back of Parachute Enclosure. Verify correct Harness Routing through Three-Point Shackles. Serials 1005 thru 1267 after SB2X-95-20, Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, Serials 2228 & subs: Complete Electric Ignition Checkout Procedure. 1 Serials 1005 thru 1267 after SB2X-95-20: Connect battery 1 at both positive and negative terminals. (Refer to 2-30) 2 Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, 2228 & subs: Open CB880 and CB881 circuit breakers at BAT 2. 3 Serials 1005 thru 1267 after SB2X-95-20: Disconnect J2702 from P2702. Temporarily install 10 kohm resistor across positive and negative voltmeter terminals. 5 Serials 1005 thru 1267 after SB2X-95-20, Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18: Access P2700 through access panel CF5. 6 Serials 2228 & subs: Access P2700 through avionics bay. Page 5

7 Serials 1005 thru 1267 after SB2X-95-20: Verify the following voltage readings at P2700. Reference readings to P2700, socket 8 (center socket). CHECK DESCRIPTION VOLTMETER READING P2700, socket 2 CAPS BAT 0-0. V MAX. P2700, socket 3 BAT 1 + CAPS BAT DIODE OR D BUS +2 V 8 Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, Serials 2228 & subs: Verify the following voltage readings at P2700. Reference readings to P2700, socket 8 (center socket). CHECK DESCRIPTION VOLTMETER READING P2700, socket 2 BAT 2 Bus 0-0. V MAX. P2700, socket 3 BAT 1 + BAT 2 DIODE OR D BUS +2 V 9 Remove 10 kohm resistor from voltmeter and use diode check feature to verify the following readings. (-) METER LEAD (+) METER LEAD METER READING P2700, socket 3 P2700, socket 1 0.5+/-0.3 V P2700, socket 3 P2700, socket 2 0.5+/-0.3 V P2700, socket 1 P2700, socket 3 OPEN P2700, socket 2 P2700, socket 3 OPEN 10 Serials 1005 thru 1267 after SB2X-95-20: Connect J2702 to P2702. 11 Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18 2228 & subs: Close CB880 and CB881 circuit breakers. 12 Serials 1005 thru 1267 after SB2X-95-20: Perform the following voltage checks at diagnostics connector P2700. Reference all readings to P2700, socket 8 (-) lead. CHECK DESCRIPTION VOLTMETER READING P2700, socket 1 BAT 1 CLOCK POWER +2 V P2700, socket 2 CAPS BATT +10 V P2700, socket 3 IGNITER SWITCH DIAGNOSTIC +2 V P2700, socket NOT USED 0 V Page 6

CHECK DESCRIPTION VOLTMETER READING P2700, socket 5 NOT USED 0 V P2700, socket 6 TEST POINT RESISTOR 0 V P2700, socket 7 NOT USED 0 V SHIELD GND AIRCRAFT CHASSIS 0 V 13 Serials 1268 thru 122 after SB2X-95-17, Serials 123 & subs w/o Perspective after SB2X-95-18, Serials 2228 & subs: Perform the following voltage checks at diagnostics connector P2700. Reference all readings to P2700, socket 8 (-) lead CHECK DESCRIPTION VOLTMETER READING P2700, socket 1 BAT 1 CLOCK POWER +2 V P2700, socket 2 BAT 2 +2 V P2700, socket 3 IGNITER SWITCH DIAGNOSTIC +2 V P2700, socket NOT USED 0 V P2700, socket 5 NOT USED 0 V P2700, socket 6 TEST POINT RESISTOR 0 V P2700, socket 7 NOT USED 0 V SHIELD GND AIRCRAFT CHASSIS 0 V 1 Use an ohmmeter to verify the following resistances. FROM TO RESISTANCE P2700, socket 8 P2700, socket 6 100+/-10 kohms P2700, socket 8 CABLE SHIELD <1 ohm 15 Stow and secure cabling for P2700 to prevent entangling aircraft control cables or shorting nearby wiring. (y) Serials 1005 thru 1267 after SB2X-95-20: Disconnect battery 1 at both positive and negative terminals. (Refer to 2-30) (z) Serials 123 and subsequent: Install access panel RE3. (Refer to 06-00) (aa) Install access panel CB6 and CB7 to bulkhead 222. (Refer to 06-00) (ab) Serials 1005 thru 1267 after SB2X-95-20: Connect battery 1 at both positive and negative terminals. (Refer to 2-30) (ac) Install bulkhead 222 trim and carpet. (Refer to 25-10) Page 7

A B BH 222 PICK-UP COLLAR ROCKET LANYARD WARNING: Rocket Lanyard must be positioned around diameter of Pick-Up Collar support, NOT over top of rocket. WARNING: Rocket Lanyard must be routed above Rear Harness Assembly, NOT underneath. NOTE At top of Rocket Assembly, verify top surface of Rocket is level with or slightly higher than Pick-Up Collar Support. Verify Rocket Lanyard is around aft diameter of Pick-Up Collar Support. Verify Rocket Lanyard is routed above Rear Harness Assembly. Verify Shear Screws securing Pick-Up Collar Support to Pick-Up Collar are fully engaged. Serials 1005 thru 1267 before SB2X-95-20, 1268 thru 122 before SB2X-95-17, 123 thru 2227: Verify 0.0 inch (10.16 mm) clearance existsbetween Pick-Up Collar and BH 222. Serials 1005 thru 1267 before SB2X-95-20, 1268 thru 122 before SB2X-95-17: Verify Grommet installed to Rocket Shield and Activation Cable. Verify LH and RH Fusleage Harness exiting Parachute Enclosure is not twisted. Figure 2 Inspection/Check - CAPS - 1005 & subs w/o Perspective before CAPS Rocket Motor Assy. Replacement Bulletins, 2016 thru 2227 (1 of 5) Page 8 DETAIL A Serials 1005 thru 1267 before SB2X-95-20, 1268 thru 122 before SB2X-95-17. SR20_MM95_33C

BH 222 PICK-UP COLLAR WARNING: Rocket Lanyard must be positioned around diameter of Pick-Up Collar support, NOT over top of rocket. ROCKET LANYARD 2 6 VIEW B 5 B 1 B 3 WARNING: Rocket Lanyard must be routed above Rear Harness Assembly, NOT underneath. NOTE 1 2 3 5 6 At top of Rocket Assembly, verify top surface of Rocket is level with or slightly higher than Pick-Up Collar Support. Verify Rocket Lanyard is around forward diameter of Pick-Up Collar Support. Verify Rocket Lanyard is routed above Rear Harness Assembly. Verify Shear Screws securing Pick-Up Collar Support to Pick-Up Collar are fully engaged. Serials 1005 thru 1267 after SB2X-95-20, 1268 thru 122 after SB2X-95-17, 123 & subs w/ o Perspective after SB2X-95-18, 2228 & subs: Verify 0.13 inch (3.30 mm) clearance exists between Pick-Up Collar and BH 222. Verify LH and RH Fusleage Harness exiting Parachute Enclosure is not twisted. DETAIL B SR20_MM95_3633B Figure 2 Inspection/Check - CAPS - 1005 & subs w/o Perspective after CAPS Rocket Motor Assy. Replacment Bulletins, 2228 & subs (2 of 5) Page 9 15 Dec 201

Serials 1005 thru 122 before repack. NOTE Verify Protective Sheath around Aft Harness is captive by Aft Harness Bracket. Verify Lanyard is coiled behind aft harness and stowed neatly into stowage pocket on the parachute assembly. Just below Stowage Pocket, verify Aft Harness secured to Parachute Assembly either by velcro pack or stitching. Serials 123 & subs, 1005 thru 122 after repack. SR20_MM95_336 Page 10 Figure 2 Inspection/Check - Cirrus Airplane Parachute System (Sheet 3 of 5)

PARACHUTE BAG FORWARD HARNESS THREE-POINT SHACKLE RISER AFT HARNESS RETAINING STRAP D D NOTE Verify correct alignment of Three-Link Release Assembly. Verify Aft Harness lays flat against Parachute Assembly. Behind Rocket Shield, verify Abrasion Sheath installed to LH Fusleage Harness. Verify correct Harness Routing through Three-Point Shackles. SR20_MM95_30 Figure 2 Inspection/Check - Cirrus Airplane Parachute System (Sheet of 5) Page 11

NOTE Inspect for chafing or cutting on CAPS assembly Retaining Strap along bottom and back of Parachute Enclosure. CAPS COMPARTMENT ACCESS PANEL RE3 CAPS COMPARTMENT RETAINING STRAP ACCESS PANEL CB6 SR20_MM95_31 Page 12 Figure 2 Inspection/Check - Cirrus Airplane Parachute System (Sheet 5 of 5)

B. Aft Tie Down Ballast Bracket (See Figure 3) (1) Removal - Aft Tie Down Ballast Bracket (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Drop Cloth - Any Source Protect empennage. (b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (c) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (d) Remove RE1, RE2 and LE1 access panels. (Refer to 06-00) (e) Remove rudder. (Refer to 55-0) (f) Remove RH elevator. (Refer to 55-20) (g) Remove pitch trim cartridge. (Refer to 27-30) (h) Remove lower rudder attach fitting. (Refer to 55-50) (i) Position drop cloth in empennage forward of aft vertical spar. Note: Use drop cloth to protect empennage if ballast is accidently dropped during removal. (j) Remove bolt securing aft tie down to aft tie down bracket. (Refer to 53-20) Note: Aft tie down remains installed with sealant following bolt removal. (k) Remove bolts, washers, and nuts securing aft tie down bracket and ballast to aft vertical spar. (l) Remove ballast from airplane. (m) Remove drop cloth from empennage. (2) Installation - Aft Tie Down Ballast Bracket (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Drop Cloth - Any Source Protect empennage. (b) Position drop cloth in empennage forward of aft vertical spar. Note: Use drop cloth to protect empennage if ballast is accidently dropped during installation. (c) (d) Forward of aft vertical spar, position ballast to aft tie down bracket installation area. Install bolts, washers, and nuts securing ballast to aft tie down bracket and aft vertical spar. Note: Ensure bolt securing ballast engages with nut and washer with no more than five bolt threads within the ballast. (e) Remove drop cloth from empennage. (f) Install bolt securing aft tie down to aft tie down bracket. (Refer to 53-20) (g) Install lower rudder attach fitting. (Refer to 55-50) Page 13

(h) Install pitch trim cartridge. (Refer to 27-30) (i) Install RH elevator. (Refer to 55-20) (j) Install rudder. (Refer to 55-0) (k) Install RE1, RE2 and LE1 access panels. (Refer to 06-00) Page 1

5 2 5 1 LOWER RUDDER ATTACH FITTING AFT TIE DOWN 3 3 AFT TIE DOWN BOLT 3 3 3 NOTE Aft tie down remains installed with sealant following bolt removal. Ensure bolt securing ballast engages with nut and washer with no more than five bolt threads within the ballast. LEGEND 1. Aft Tie Down Bracket 2. Ballast 3. Bolt. Washer 5. Nut SR20_MM95_2755 Figure 3 Aft Tie Down Ballast Bracket Installation Page 15

C. CAPS Battery - Serials 1005 thru 1267 after SB2X-95-20 (See Figure ) (1) Removal - CAPS Battery (a) Remove CAPS handle access cover and verify CAPS handle safety pin is installed. (b) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (c) Disconnect battery 1 at both positive and negative terminals. (Refer to 2-30) (d) Remove bulkhead 222 trim and carpet. (Refer to 25-10) (e) Remove access panel CB6 from bulkhead 222. (Refer to 06-00) (f) Disconnect CAPS battery. (g) Remove screws, nuts, and washers securing battery cover assembly and shield plate to access panel. (h) Remove battery from battery cover assembly. (i) If replacing with new unit, dispose of lithium battery according to local regulations. (2) Installation - CAPS Battery (a) Secure battery in battery cover assembly. (b) Secure battery cover assembly and shield plate to access panel CB6 with screws, nuts, and washers. (c) Perform Inspection/Check - Cirrus Airplane Parachute System. (Refer to ) Page 16 Serials 1005 thru 1267 after SB2X-95-20

A 5 J2702 1 ACCESS PANEL CB6 3 6 7 2 1 DETAIL A 1 NOTE Disconnect Battery 1 at both terminals before removing access panel. LEGEND 1. Screw 2. Washer, 0.032" Thk 3. Shield Plate. CAPS Battery 5. Battery Cover Assembly 6. Washer, 0.016" Thk 7. Nut SR20_MM95_3701 Figure CAPS Battery Installation - Serials 1005 thru 1267 after SB2X-95-20 Serials 1005 thru 1267 after SB2X-95-20 Page 17 19 Sep 2017

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