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Description P/N or Spec. Supplier Purpose
C I R R U S S E R V I C E B U L L E T I N MOD E L S R 2 2
SB 2X-30-03 R1
Cirrus Design SR22 Serials 3003, 3310, 3326, 3403 Page 5
thru 3424, 3463, and 3499 w/ FIKI ice protection system.
EFFECTIVITY:
November 23, 2009
(2) Remove wing access panels LW4, LW9, RW4, and RW9. (Refer to AMM 6-00)
(3) Remove empennage access panel RE3. (Refer to AMM 6-00)
(4) Remove LH passenger seat, carpeting, and cabin access panel CF4L. (Refer to AMM 25-10)
(5) To protect from fluid, cover cables and electrical connections running through avionics bay with
drop cloth.
(6) Prepare TKS Cart. (See Figure 1), (See Figure 2)
TKS cart is configured as follows: The "5/16 System Output" port on TKS cart is run into an
equal tee with a 5/16-inch line (terminated with a nut and olive) connected to each output leg.
Each output leg contains a shut-off valve and in-line pressure gauge.
CAUTION: Do not place TKS cart directly underneath wing.
Pull up on all three pressure safety valves once before and after each procedure.
Always place TKS cart in upright position.
When TKS cart is not in use, keep air pressure and water regulator valves closed,
and cap all lines.
(a) Close both output leg valves.
(b) Adjust pressure regulator to zero by turning knob counterclockwise.
(c) Couple compressed air onto pressure vessel.
Note: Uncouple compressed air when making connections and repositioning TKS
cart.
(d) If using TKS cart p/n T10108, set air regulator to CLOSED position. (See Figure 1)
(e) If using TKS cart p/n 09301, adjust TKS cart control settings. (See Figure 2)
1 Set water regulator to CLOSED position.
2 Set air regulator to CLOSED position.
3 Set selector valve to TKS FLUID position.
4 Set output selector to 5/16 position.
5 Set feed valve position to DOWN - SINGLE FEED position.
(7) Set up fluid collection locations. (See Figure 3)
CAUTION: Do not disconnect any fluid lines at this point.
Note: Each ice panel must have its own dedicated drain trough so that fluid collection is
isolated to individual panels (and propeller slinger ring nozzle).
All fluid from each ice panel as well as propeller slinger ring nozzle must be captured
to achieve accurate ground flow test results.
Tape may be attached to lower surface of ice panel and forward side of drain
trough to prevent fluid from "weeping" past contact point of drain trough and ice
panel.
Avoid taping over perforations of ice panels.
(a) Position drain troughs below each wing porous panel to collect fluid during purging process.
(b) Position drain troughs below each horizontal porous panel to collect fluid during purging
process.
C I R R U S S E R V I C E B U L L E T I N MOD E L S R 2 2
SB 2X-30-03 R1
Cirrus Design SR22 Serials 3003, 3310, 3326, 3403 Page 6
thru 3424, 3463, and 3499 w/ FIKI ice protection system.
EFFECTIVITY:
November 23, 2009
(c) Position vertical drain trough and drain tubes around vertical stabilizer and below porous
panel to collect fluid during purging process. Tape as required to hold in place.
(d) Fabricate and position elevator tip drain troughs.
1 Trim elevator in upward position (pitch up) such that leading edge of elevator is
pointed down. (Refer to AMM 27-30)
2 Using 6" × 6" section of aluminum foil, form a "V" shaped trough.
3 Position inboard side of trough between elevator tip and horizontal stabilizer.
4 Attach aft side of trough to elevator tip with tape such that fluid from porous panel is
directed forward and downward.
5 Repeat trough fabrication on opposite elevator tip.
(e) Position tygon tubing on propeller slinger ring nozzle to collect fluid during purging process.
(f) Position clean, empty 5-gallon containers at lower end outlet of each drain trough, and
propeller tygon tubing.
(g) Connect 28 ±1 VDC external power to external power receptacle.
Note: Do not exceed aircraft bus voltages while operating ground power supply.
(h) Pull STARTER and FUEL PUMP circuit breakers.
(i) Set BAT 1 switch to ON position.
(8) Disconnect Pump#1 from J1391 connector and install Pump#1 voltage measurement harness in
series between aircraft and pump connectors.
(9) Disconnect Pump#2 from J1392 connector and install Pump#2 voltage measurement harness in
series between aircraft and pump connectors.
(10) Serials 3003, 3310, 3403, 3405, 3417, and 3420: Perform the following steps.
Note: Per aircraft temperature, subsequent purge and flow tests are also required.
(a) Serial 3310: Perform Procedure - Metering Pump Flow Output for Pump#1 only. (Refer to
Section M.)
(b) Serials 3403, 3405, and 3417: Perform Procedure - Metering Pump Flow Output for
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30-00 ICE AND RAIN PROTECTION - Alteration of TKS Anti-Ice S(3)
