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34-18-0 Page 108 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/85
5C8
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-18-0 Page 109
5C8
34-18-0 Page 110 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/88
PERFORMANCE DATA COMPUTER SYSTEM - ADJUSTMENT/TEST
1. General
A. An operational test may be performed to determine that the Performance Data Computer System is ready for operation. The self-test is performed and the STANDBY and LOAD pages are checked for correct display.
B. The system test of the PDCS tests the flight modes of operation under simulated flight conditions using air data and pitot test equipment and simulated EPR (Ref 77-11-0 A/T). The system test may be performed as a periodic maintenance function or as a fault isolation aid. On GJ B-2509 and B-2510 the AFCS-PDCS interface and the PDCS-Mach/Airspeed command bug relationships are tested in the Autopilot Adjustment/Test (Ref 22-11-01).
NOTE: During fueling, PDCS adjustment/test data values may be in error due to changing airplane gross weight caused by changing fuel weight.
NOTE: A "VALID USE EPR LIMIT" alert message will occur on PDCS CDU during flight modes of operation with less than 500 LBS of fuel in fuel tanks.
C. Adjustment procedures for the performance data computer fuel flow and drag modification factors are provided (Ref SB 737-34-1146).
NOTE: This adjustment affects all 737 airplanes with one of the following performance data computers installed: 10-61962-047-03, 10-61962-055-01, 10-61962-060-01, 10-61962-047-04, 10-61962-055-02, 10-61962-060-02.
D. When pressurizing pitot-static system, observe the cautions in pitot-static system
adjustment/test (Ref 34-11-0).
2. Referenced Procedures
A. 24-41-0, AC External Power
B. 34-11-0, Pitot-Static System
C. 77-11-0, Engine Pressure Ratio Indicating System
3. Performance Data Computer - Operational Test
A. Prepare to Test
(1)
Provide electrical power (Ref 24-41-0, AC External Power).
(2)
The following systems should be operating satisfactorily:
(a)
Air Conditioning and Pressurization System
(b)
Wing and Engine Anti-Ice Systems
(c)
Total Air Temperature System
(d)
Mach/Airspeed Warning Systems
(e)
EPR Indicating System
(f)
DME Systems
(g)
Fuel Quantity Indicating System
(h)
Air Data System
(i)
Autopilot System
(j)
Auto Throttle System
(k)
Omega Navigation System
(3)
Set CDU mode selector switch to STBY.
(4)
Push EPR and indicators bug set knobs to in (servo mode) position.
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CAUTION: WHEN THE PDCS IS INOPERATIVE OR TURNED OFF, SET THE EPR COMMAND BUG SET KNOBS TO THE MANUAL MODE (PULLED OUT). IF THE COMMAND BUG SET KNOB IS IMPROPERLY SET TO THE SERVOED MODE, WITH THE PDC INOPERATIVE OR TURNED OFF, EXCESSIVE WEAR TO THE COMMAND INDEX CLUTCH WILL OCCUR.
NOTE: FUEL SYSTEM EP GROUND FUELING circuit breaker must be closed.
(5)
Open PDCS and on GJ B-2509 and B-2510 PDC MODE ANN circuit breakers on P18 panel and check that:
(a)
EPR command bug flags in view.
(b)
CDU screen and mode annunciators blank.
(6)
Close PDCS and on GJ B-2509 and B-2510 the PDC MODE ANN circuit breakers on P18 panel. Check that:
(a)
EPR command bugs drive to 1.00 EPR, and bug flags remain in view.
(b)
CDU displays LOAD page 1-2 (page 1 of 2), and parameters show question marks.
(c)
Mode annunciators remaln blank.
B. Operational Test
(1)
Set barometric pressure on pilots' altimeters to 29.92 inches of mercury.
(2)
Turn air conditioning and anti-ice system bleed air switches off.
(3)
Using instrument/panel lighting control, verify CDU panel lights dim.
(4)
With CDU mode selector switch in STBY, press RCL and verify:
(a)
CDU displays STANDBY page 1-3.
