barfield 1811GA Series, Руководство пользователя

Страница: 30 / 68

56-101-00184 / 00185 Rev. I CH. 3
September 24, 2014 Page 18 of 56
C. Applying Leak Correction
(1) If the leak rate does not exceed 2 knots or 100 feet in 1 minute, determine the
actual aircraft system leak rate by adding the observed rate obtained from a
previous aircraft leak test to the recorded rate.
D. Instrument Calibration Correction
Before attempting calibration tests of aircraft instruments, ensure that instrument
correction card calibration dates are within the approved recertification periods.
Note: Calibration cards are based on tests performed with instruments vertically
mounted (i.e., face up) and at a 75° F (25° C) temperature. An attitude change of
more than 30° from level, and / or a temperature difference of more than 15° F
(90°C), could affect the precise calibration accuracy.
6. PITOT SYSTEM TEST
Note: If the aircraft is non-pressurized, the Pitot System and Pitot Leak Tests may be
omitted and the Static System Test performed.
A. Pitot System Connection
Using the specific aircraft-plumbing diagram, connect the PITOT PORT (#1) to the
aircraft pitot system. Ensure that the test will not harm aircraft components.
Caution: Ensure the connections between the T/S and the aircraft are secure since a
sudden break or leak could cause severe instrument damage.
B. Pitot Leak Test
(1) Open the PITOT VENT (#17) and STATIC VENT (#10) fully CCW.
(2) Close PITOT CONTROL (#19), CROSSBLEED (#8) and STATIC CONTROL (#7)
values fully CW.
(3) Operate PRESSURE PUMP (#16) to develop 10 psi on PRESSURE GAUGE (#18).
(4) Close PITOT VENT (#17) fully.
Note: If any of the following steps fail, close the PITOT CONTROL (#19) fully
CW. Gently open the PITOT VENT (#17) CCW to return the system to
ambient atmosphere before disconnecting the T/S.
(5) Monitor aircraft and T/S AIRSPEED (#2) while gently opening the PITOT
CONTROL CCW (#19) until aircraft airspeed reaches approximately 75% of full
range.