曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

will seem much more "oily" to the touch as well. 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.)
(g) Set System Switch (and PUMP BKUP, if applicable) to OFF.
(h) Using test fluid, perform Procedure - Porous Panel Purge. (Refer to Section F.)
(i) Perform Procedure - Panel Performance Inspection. (Refer to Section H.)
(4) Test panel flow rates while operating Pump#1 and Pump#2.
(a) Record Aircraft Serial Number (ASN) and date of Ground Flow Test.
(b) Measure and record ambient temperature of area where Pump#1 Ground Flow Test is
being performed.
CAUTION: Avoid subjecting aircraft to localized areas of elevated temperatures (high
intensity lights, area heaters, etc.) as temperature gradient will cause inaccuracy
in measurements.
(c) Set System Mode switch to HIGH, and activate Pump#1 by setting System Switch to ON.
(See Figure 3)
(d) Observe voltage of Pump#1 and adjust its operating voltage to 27.85 VDC nominal via
ground power supply.
(e) Record operating voltage of Pump#1.
CAUTION: Ensure supplied voltage of ground power supply does not drift in excess of
±0.02 VDC during test.
(f) Perform Ground Flow Test:
1 Allow system to operate until flow rate from each collection location has stabilized.
(See Figure 3)
Note: Stabilization is generally characterized by observing a steady stream
of fluid at the collection points of horizontal panels. This is necessary
because there is a slight lag time as system builds pressure, forcing
panels to expel fluid, which is then directed to collection points.
To reduce time required for an observable flow rate at the horizontal
panels, slowly add test fluid to horizontal drain troughs once horizontal
porous panels begin “weeping”. Continue adding test fluid until
stream develops at trough outlet on LH and RH horizontal. This will
reduce the volume of fluid that would otherwise have to be displaced
from the trough before flow rate could be measured.
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 18
thru 3424, 3463, and 3499 w/ FIKI ice protection system.
EFFECTIVITY:
November 23, 2009
Once flow rates at each collection point have stabilized, equilibrium
will be reached that causes each drop of fluid leaving the panel to displace
another into leaving the drain trough at that collection point.
Do not add any fluid to troughs once equilibrium is obtained. To do so
will inflate flow rate measurements.
2 Collect and separate sample of fluid during each test using a small, clean and empty
container.
Note: This will later be used to measure actual viscosity of fluid that was
expelled from ice panels during the test.
Maintain a separate sample for both Pump#1 and Pump#2 tests, as
the second test generally displays a higher viscosity as the remainder
of less viscous anti-ice fluid is expelled from system.
3 To measure flow rate of propeller and each wing, horizontal, and vertical panel, use
stopwatch and graduated cylinder (1.0mL divisions maximum) to take a volume
measurement at each collection point for precisely 1 minute.
Note: Measured volume will be "Observed" flow rate of that particular panel.
Avoid making contact with drain trough as it may disrupt equilibrium of
fluid flow at that collection point.
Ensure all fluid has been removed from graduated cylinder prior to
testing next collection point.
4 To measure flow rate of elevator tips, use stopwatch and graduated cylinder (0.1mL
divisions maximum) to take a volume measurement at each collection point for precisely
3 minutes.
Note: Measured volume divided by 3 will be "Observed" flow rate of that
particular panel.
Avoid making contact with drain trough as it may disrupt equilibrium of
fluid flow at that collection point.
Ensure all fluid has been removed from graduated cylinder prior to
testing next collection point.
(g) When Pump#1 Ground Flow Test is complete, set System Switch to OFF. (See Figure 3)
(h) Measure and record ambient temperature of area where Pump#2 Ground Flow Test is
being performed.
CAUTION: Avoid subjecting aircraft to localized areas of elevated temperatures (high
intensity lights, area heaters, etc.) as temperature gradient will introduce
inaccuracy in the measurements.
(i) Set PUMP BKUP switch to ON. (See Figure 3)
(j) Observe voltage of Pump#2 and adjust its operating voltage to 27.10 VDC nominal via
ground power supply.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：30-00 ICE AND RAIN PROTECTION - Alteration of TKS Anti-Ice S(10)