(b)
Connect the auxiliary pitot hoses to the elevator feel computer.
S 215-012
(4) Examine the static ports for unwanted materials and rough locations on the inner and outer surfaces.
S 085-013
CAUTION: MAKE SURE THAT THE PITOT-STATIC PROBE HAS NO ADDED WEIGHT FROM
_______ THE TEST HOSES. YOU CAN BEND OR TWIST THE PITOT-STATIC PROBE OUT OF TOLERANCE.
CAUTION: DO NOT DISCONNECT THE PNEUMATIC TEST SET WHEN THE PITOT-STATIC
_______ SYSTEM IS NOT AT AMBIENT PRESSURE. YOU CAN CAUSE DAMAGE TO THE EQUIPMENT.
(5)
Disconnect the pneumatic test set from the pitot-static probe adapters.
S 085-014
(6)
Remove the probe adapters from all of the pitot-static probes.
(a) Remove the probe adapters from the probes.
NOTE: Dry off the pitot-static probes with a soft rag when you
____
use ethylene glycol.
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CAUTION: MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM
_______ EACH PITOT-STATIC PROBE. THE SYSTEM WILL NOT OPERATE CORRECTLY WHEN THE TAPE IS IN ITS POSITION.
(b) Remove the vinyl adhesive tape from all of the drain holes of the probe pitot chamber.
WARNING: FAILURE TO REMOVE THE VINYL ADHESIVE TAPE FROM THE STATIC
_______ PORTS BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED SENSING AND ALTITUDE SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
(c) Remove the vinyl adhesive tape from the upper left and lower left probe static ports (S1 and S2).
S 215-015
(7)
Examine the pitot-static probes for unwanted materials and rough locations on the inner and outer surfaces (Ref 34-11-01/601).
S 215-016
(8)
Make sure that the pitot-static probes do not show damage to the probe tip or the static ports (Ref 34-11-01/601).
S 085-017
(9)
Remove all of the pneumatic test hoses and equipment.
S 795-538
(10)
Make sure that the elevator feel computer pitot connections have been leak checked (AMM 34-11-00/201).
S 865-018
(11)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P6 Main Power Distribution Panel
1) 6D30 PROBE HEAT PITOT L
2) 6D31 PROBE HEAT PITOT R
3) 6D32 PROBE HEAT AUX PITOT L
4) 6D33 PROBE HEAT AUX PITOT R
5) 6E01 PRIM T/E FLAP CONT AC
6) 6E02 PRIM T/E FLAP CONT DC
(b)
P7 Overhead Circuit Breaker Panel
1) 7C10 FLT CONT ELEC 2LAC
2) 7C12 FLT CONT ELEC 1LAC
3) 7C14 FLT CONT ELEC 1RAC
4) 7C16 FLT CONT ELEC 2RAC
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TASK 34-11-00-795-019
3. The Captain's Pitot System Leak Test
____________________________________
A. Standard Tools and Equipment
(1)
Adapters
(a) Pitot-static probe test adapter -Rosemount Engineering, P/N 884EE with RCF kit P/N 508 or, RCF Seals & Couplings, Inc., P/N 508747, (4 required)
(2)
Pneumatic Test Set
(a) Dry air pressure source, - 30 to 35 inches of mercury (absolute). 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 导航 NAVIGATION 1(38)
