CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
RECOVERY
1. GENERAL
This section describes systems, units, and components used to recover air vehicles and equipment. This
equipment includes the Cirrus Airframe Parachute System (CAPS).
A. Cirrus Airframe Parachute System (CAPS)
The airplane is equipped with a Cirrus Airframe 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 2400-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.
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
2. DESCRIPTION
(See Figure 90-001)
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:
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.
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AIRPLANE MAINTENANCE MANUAL
MODEL SR20
ACTIVATION
SYSTEM
ROCKET ASSEMBLY
CAPS COVER
FORWARD
ATTACH POINT
FORWARD
HARNESS
PARACHUTE
ASSEMBLY
6 - Parachute Disreef
3 - Line Extension
4 - Initial Canopy Inflation
5 - Reefed Parachute
7 - Snub Line Release
1 - Rocket Extraction
2 - Parachute Extraction
SR20_MM90_5235
Figure 90-001
CAPS Deployment
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR20
3. MAINTENANCE PRACTICES
A. Cirrus Airframe 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:
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.
Licensed Airframe and Powerplant mechanics may visually inspect the parachute installation only as specified in the following inspection.
Note:
(1)
Refer to Cirrus Airframe Parachute System Maintenance Manual w/ Illustrated Parts List
(P/N 15994-002) for CAPS Maintenance Practices.
Inspection/Check - Cirrus Airframe Parachute System
(See Figure 90-002)
(a)
(b)
(c)
(d)
(e)
(f)
(g)
Remove CAPS handle access cover and verify CAPS handle safety pin is installed.
Remove bulkhead 222 trim and carpet. (Refer to 25-10)
Remove access panel CB6 and CB7 from bulkhead 222. (Refer to 06-00)
Remove access panel RE3. (Refer to 06-00)
Verify no moisture or mildew evident in Parachute Enclosure or CAPS Assembly.
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 positioned around forward diameter of Pick-Up Collar Support.
WARNING:
(h)
Verify Rocket Lanyard is routed above Rear Harness Assembly.
WARNING:
(i)
(j)
(k)
(l)
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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
Rocket Lanyard must be routed above Rear Harness Assembly, NOT
underneath. Failure to route Rocket Lanyard properly will absolutely
FAIL deployment.
Verify Shear Screws securing Pick-Up Collar Support to Pick-Up Collar are fully engaged.
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.
Verify LH and RH Fuselage Harness exiting Parachute Enclosure is not twisted.
Verify Protective Sheath around Aft Harness is captive by Aft Harness Bracket.
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(m)
(n)
(o)
(p)
(q)
(r)
(s)
(t)
MODEL SR20
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.
Complete Electric Ignition Checkout Procedure.
1
Open CB880 and CB881 circuit breakers at BAT 2.
2
Temporarily install 10 kohm resistor across positive and negative voltmeter terminals.
3
Access P2700 through avionics bay.
4
Verify the following voltage readings at P2700. Reference readings to P2700, socket
8 (center socket).
5
6
7
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CHECK
DESCRIPTION
VOLTMETER
READING
P2700, socket 2
BAT 2 Bus
0-0.4 V MAX.
P2700, socket 3
BAT 1 + BAT 2
DIODE OR’D BUS
+24 V
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
Close CB880 and CB881 circuit breakers.
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
+24 V
P2700, socket 2
BAT 2
+24 V
P2700, socket 3
IGNITER SWITCH
DIAGNOSTIC
+24 V
P2700, socket 4
NOT USED
0V
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CIRRUS
8
AIRPLANE MAINTENANCE MANUAL
CHECK
DESCRIPTION
VOLTMETER
READING
P2700, socket 5
NOT USED
0V
P2700, socket 6
TEST POINT RESISTOR
0V
P2700, socket 7
NOT USED
0V
SHIELD GND
AIRCRAFT CHASSIS
0V
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
9
(u)
(v)
(w)
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MODEL SR20
Stow and secure cabling for P2700 to prevent entangling aircraft control cables or
shorting nearby wiring.
Install access panel RE3. (Refer to 06-00)
Install access panel CB6 and CB7 to bulkhead 222. (Refer to 06-00)
Install bulkhead 222 trim and carpet. (Refer to 25-10)
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CIRRUS
AIRPLANE MAINTENANCE MANUAL
A
MODEL SR20
BH 222
(REF)
PICK-UP COLLAR
(REF)
WARNING:
Rocket Lanyard must
be positioned around
diameter of Pick-Up
Collar support,
NOT over top of rocket.
ROCKET
LANYARD
(REF)
2
5
VIEW A1
6
A1
1
A1
4
4
3
WARNING: Rocket Lanyard must
be routed above Rear Harness
Assembly, NOT underneath.
NOTE
1 At top of Rocket Assembly, verify top surface of
2
3
4
5
6
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.
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 A
SR20_MM90_5237
Figure 90-002
Inspection/Check - CAPS (Sheet 1 of 4)
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AIRPLANE MAINTENANCE MANUAL
MODEL SR20
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.
SR20_MM90_5239
Figure 90-002
Inspection/Check - CAPS (Sheet 2 of 4)
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AIRPLANE MAINTENANCE MANUAL
MODEL SR20
PARACHUTE BAG
(REF)
FORWARD HARNESS
THREE-POINT
SHACKLE
(REF)
RISER
AFT
HARNESS
RETAINING
STRAP
(REF)
D1
D1
D1
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_MM90_5241
Figure 90-002
Inspection/Check - CAPS (Sheet 3 of 4)
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AIRPLANE MAINTENANCE MANUAL
MODEL SR20
NOTE
Inspect for chafing or cutting on CAPS assembly
Retaining Strap along bottom and back of
Parachute Enclosure.
CAPS COMPARTMENT
(REF)
ACCESS PANEL RE3
(REF)
CAPS COMPARTMENT
RETAINING STRAP
(REF)
ACCESS PANEL CB6
(REF)
SR20_MM90_5243
Figure 90-002
Inspection/Check - CAPS (Sheet 4 of 4)
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