(5)
Return the WING ANTI-ICE switch to OFF. Verify that the CDU display changes to:
'AI X X X X __'
(6)
Press CDU CLEAR key.
A/I 'X X X X X'
(ENG. 1) (ENG. 2) (ENG. 3) (ENG. 4) (WING)
NOTE:____ For wing thermal anti-icing refer to 30-11-00.
(7) If the PMS is no longer required, restore airplane to normal. AG. Fuel Flow (F/F) Indicating System Interface
(1)
If required prepare for test as described in paragraph D.
(2)
Press PERF DATA key on the PMS CDU to display PERF DATA.....1/4 page. Data line 3 displays the fuel flow for engines 1, 2, 3 and 4 respectively as follows:
'F/F X.XX X.XX X.XX X.XX' (ENG. 1) (ENG. 2) (ENG. 3) (ENG. 4)
NOTE: The PMS CDU displays actual fuel flow in thousands of
____ kilograms per hour omitting the most significant digit (the tens digit).
(3) Gain access to the fuel flowmeter electronics package, M836, located in the main equipment center E3-1 shelf (Ref 73-31-00).
CAUTION: DO NOT CONDUCT A SELF TEST OF THE FUEL FLOWMETER SYSTEM
_______ UNLESS THE ENGINE FUEL FLOW LINES ARE FULL OF FUEL.
(4) On the fuel flowmeter electronics package turn ENGINE switch S1 to position 1. Turn FUNCTION switch S2 to SIG position and press switch S3. This will simulate a fuel flow of 5,300 to 5,600 kilograms per hour on the fuel flow indicator, on the P2 panel for engine No. 1.
EFFECTIVITY
AIRPLANES WITH PMS 12 Page 538 Apr 25/89
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(5)
Verify that the PMS CDU displays the value of fuel flow as 5.3 to 5.6 for engine No. 1, to correspond with the value of 5,300 to 5,600 kilograms per hour on the fuel flow indicator. Allow sufficient time for the CDU display to stabilize prior to verification.
(6)
Release switch S3 on the fuel flow electronics package. Verify that the CDU display returns to its original status prior to self-test and corresponds with the value of fuel flow on the fuel flow indicator.
(7)
Repeat steps (4) thru (6) for engines 2, 3 and 4 by selecting position 2, 3 and 4 respectively on ENGINE switch S1.
(8)
Press CDU CLEAR key.
(9) If the PMS is no longer required, restore airplane to normal. AH. Engine Pressure Ratio (EPR) Indicating System Interface (IB Airplanes)
(1)
If required prepare for test as described in paragraph D.
(2)
Press PERF DATA key on the PMS CDU to display PERF DATA.....1/4 page. Data line 2 displays actual EPR signals for engines 1, 2, 3 and 4 respectively as follows:
EPR .XXX .XXX .XXX .XXX (ENG. 1) (ENG. 2) (ENG. 3) (ENG. 4)
NOTE: The PMS CDU displays actual engine pressure ratios omitting
____ the digit (a one or a zero) to the left of the decimal point. For example, an EPR of 1.452 is displayed on the PMS CDU as .452; or an EPR of 0.998 is displayed as .998.
(3)
With the EPR flag not in view on the EPR indicators on the P2 panel; verify on the PMS CDU that the EPR display for each engine corresponds to the EPR value indicated on the appropriate EPR indicator.
(4)
Press the CDU CLEAR key.
(5) If the PMS is no longer required, restore airplane to normal. AI. Engine Speed (N1) Indicating System Interface
(1)
If required prepare for test as described in paragraph D.
(2)
On IB airplanes, press PERF DATA key on the PMS CDU. Push the CDU slew switch as required to advance the display to PERF DATA.....3/4 page. Data line 3 displays the engine speeds (N1) on a percent of idle speed, for engines 1, 2, 3 and 4 respectively as follows:
N1 XX.X XX.X XX.X XX.X (ENG. 1) (ENG. 2) (ENG. 3) (ENG. 4)
NOTE: The PMS CDU displays engine speed (N1) omitting the most
____ significant digit (the hundreds digit). For example a N1 of 112.4% is displayed on the PMS CDU as 12.4; or a N1 of 89.8% is displayed as 89.8.
EFFECTIVITY
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(3) On AF airplanes, press PERF DATA key on the PMS CDU to display PERF DATA.....1/4 page. Data line 2 displays the engine speeds (N1) on a percent of idle speed, for engines 1, 2, 3 and 4 respectively as follows:
N1 XX.X XX.X XX.X XX.X (ENG. 1) (ENG. 2) (ENG. 3) (ENG. 4)
NOTE: The PMS CDU displays engine speed (N1) omitting the most
____ significant digit (the hundreds digit). For example a N1 of 112.4% is displayed on the PMS CDU as 12.4; or a N1 of 89.8% is displayed as 89.8.
(4)
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