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(k) Record operating voltage of Pump#2.
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 19
thru 3424, 3463, and 3499 w/ FIKI ice protection system.
EFFECTIVITY:
November 23, 2009
CAUTION: Ensure supplied voltage of ground power supply does not drift in excess of
±0.02 VDC during test.
(l) Repeat Ground Flow Test while operating system with Pump#2.
Note: The time necessary for system to stabilize will be dramatically reduced if
Pump#2 test is repeated directly after Pump#1 test.
(m) When Pump#2 Ground Flow Test is complete, set PUMP BKUP switch to OFF. (See Figure
3)
(n) For both viscosity samples, perform Procedure - Measure Kinematic Viscosity. (Refer to
Section K.)
(o) Record viscosity of test fluid.
Note: It is desirable for test fluid to be between 53 cSt and 75 cSt to best approximate
design temperature of system.
However, test fluid viscosities between 30.5 cSt (anti-ice fluid @ 0°C) and
238 cSt (anti-ice fluid @ -30°C) are acceptable. Test results achieved using
test fluid with a viscosity less than 30.5 cSt or greater than 238 cSt are
invalid.
(5) Perform Procedure - System Acceptance Criteria. (Refer to Section L.)
(6) Replace test fluid in system with anti-ice fluid.
(a) Drain test fluid from both glycol tanks on aircraft. (Refer to AMM 12-10)
(b) Fill both glycol tanks on aircraft with anti-ice fluid. (Refer to AMM 12-10)
(c) Drain test fluid from pressure tank on TKS cart.
Note: Any uncontaminated fluid, whether anti-ice fluid or test fluid, may be
retained for later use.
(d) Set System Mode switch to HIGH, and activate Pump#1 by setting System Switch to ON.
(See Figure 3)
Note: If desired, Pump#2 can be activated to increase flow rate of system by also
setting PUMP BKUP switch to ON. This will cause system to run in a "continuous"
MAX, as opposed to the standard 2 minute cycle achieved by
pressing MAX Mode button. (See Figure 3)
(e) Operate system until there is evidence of anti-ice fluid at all collection locations.
Note: Anti-ice fluid will have a slight alcohol odor and seem much less "oily" to the
touch as compared to the test fluid. Typically propeller will be first, with ice
panels following in decreasing order of their respective flow rates. (For
example, inboard ice panels, then outboard ice panels, then horizontal ice
panels, etc.)
(f) Set System Switch (and PUMP BKUP, if applicable) to OFF.
(g) To displace all test fluid with anti-ice fluid, perform Procedure - Porous Panel Purge. (Refer
to Section F.)
Note: If panel performance, per Procedure - Panel Performance Inspection, was
found acceptable during earlier purge using test fluid, re-inspecting panel
performance is not required.
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 20
thru 3424, 3463, and 3499 w/ FIKI ice protection system.
EFFECTIVITY:
November 23, 2009
K. Procedure - Measure Kinematic Viscosity
(1) Ensure viscosity cup is clean and there is no residual dried material in or around the orifice.
(2) Completely immerse viscosity cup into material to be measured in a location free from bubbles
or foam, holding viscosity cup vertically using the stainless steel split key ring.
(3) Hold viscosity cup vertically by inserting index finger into handle ring, and in a quick, steady
motion, lift viscosity cup out of sample material, starting stopwatch when top edge of viscosity
cup breaks the surface.
Note: During flow time, hold viscosity cup no more than 6 inches above level of sample
material.
(4) Stop stopwatch when first definite break in the stream at base of viscosity cup is observed.
(5) Record number of seconds of "efflux" time.
(6) Identify kinematic viscosity of test fluid. (For example, an efflux time of 31.1 seconds represents
a kinematic viscosity of 63.1 cSt.) (See Figure 4)
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 21
thru 3424, 3463, and 3499 w/ FIKI ice protection system.
EFFECTIVITY:
November 23, 2009
L. Procedure - System Acceptance Criteria
Note: It is permissible to use data contained herein as an Acceptance Test Procedure (ATP) to
determine acceptable performance of production aircraft, or as a maintenance procedure
for field service.
(1) Verify flow rates of all ten protected locations are greater than the minimum allowable flow rate.
(See Figure 7)
Note: The “A/C Flow” (design flow rates) and “MAX” flow rates are provided for reference
　
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