(3)  
Differential and Absolute Pressure Controllers - Schwien and Son, Model 114

(4)  
Pitot-Static Test Set for measurement of pitot-static pressure. Absolute Pressure Indicator. Accuracy to 0.01 in. Hg. Differential Pressure Indicator. Accuracy to 0.01 in. Hg.

NOTE:  The pressure test equipment should have: A pitot-static bypass valve for bypassing static to pitot during connection of lines. An automatic means of preventing back pressure (static pressure exceeding total pressure) of more than 1/10 in. Hg. A means of limiting differential pressure (pitot minus static) to less than 10 in. Hg. A vent valve to vent static lines to ambient pressure slowly before disconnecting or connecting test equipment. A rate of climb indicator on the static line.

(5)  
Appropriate gage-saver restrictors

(6)  
Regulated air pressure source

(7)  
Absolute pressure gage

(8) 
 Shutoff valve

(9)  
Hose and connectors to couple pressure and vacuum source to test equipment and airplane fittings

(10)
Stop watch

(11)
Decade Resistance Box - General Radio 1432-K

(12)
Transponder/DME test set IFR Model ATC-600A

B.  Perform Performance Data Computer System Operational Test.
C.  Perform System Test.
5C1 
34-18-0 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Sep 20/82 

(1)  
Install pitot-static test equipment (Ref 34-11-0 A/T). Obey all precautions.

(2)  
Connect decade resistance box in place of total air temperature probe. Set resistance to 501.3 ohms.

(3)  
Move mode select switch to TO (takeoff). Verify that FULL 1-2, an OAT of 0oC and takeoff EPR limit value for each engine is displayed and ENGAGE light is illuminated.

(4)  
Press TRIP performance function key and enter following values:

   DIST NM 947    ISA oC 8    WIND -10

(5)  
Verify that the TRIP FL (trip flight level) is displayed.

(6)  
Press RCL (recall) and verify that the CDU displays TO information.

(7)  
Press ENGAGE and verify that:

(a)  
ENGAGE key light extinguished.

(b)  
EPR bug failure flags retracted.

(c)  
Airspeed command bug warning flag in view.

(d)  
Mode annunciator indicates TO mode selected and engaged.

(e)  
EPR command bugs drive to CDU values.

(f)  
Mode annunciator (TO) is dimmable.

(8)  
At P5 overhead panel, set BLEED 1 switch on air conditioning module to ON. Verify that the No. 1 EPR CDU value decreases. Check that No. 1 EPR command bug drives to reduced CDU value.

(9)  
Set BLEED 1 switch to OFF, verify that CDU No. 1 EPR value returns to original value and No. 1 EPR command bug drives to CDU value.

(10)
Repeat steps (8) and (9) for BLEED 2 switch and No. 2 EPR values and indications. Verify that EPR reduction displayed is same as reduction for engine 1.

(11)
Set mode select switch to CLB (climb). Set decade resistance box to 501.3 ohms (0oC). Using the air data test set, establish an IAS of 120 knots and verify that:

(a)  
CDU ENGAGE light illuminated.

(b)  
EPR and airspeed command bugs do not change.

(c)  
Mode annunciator displays TO.

(d)  
CDU displays page 1 of 4 for CLB mode.

(12)
Press ENGAGE and verify that:

(a)  
ENGAGE light extinguished.

(b)  
EPR command bugs drive to CDU values + .005.

(c)  
On GJ ALL EXCEPT B-2509 and B-2510 Airspeed command bug drives to CDU value +1.

(d)  
Mode annunciator indicates CLB mode selected and engaged.

(e)  
On GJ ALL EXCEPT B-2509 and B-2510 Airspeed bug failure flag retracted from view.

(13)
At P5 overhead panel, set ENG ANTI-ICE 1 switch on engine and surface thermal anti-ice module to ON. Verify CDU No. 1 EPR value decreases. Check that No. 1 EPR command bug drives to reduced CDU value.

(14)
Set ENG ANTI-ICE 1 switch to OFF and verify No. 1 EPR indications return to original values.

(15)
Using EPR values and indications for engine 2, repeat steps (13) and (14) for ENG ANTI-ICE 2 switch. Verify that the EPR reduction displayed is same as reduction for engine 1.

(16)
Set both air conditioning system bleed switches (BLEED 1 and BLEED 2) to ON. Set decade resistance box to 540 ohms (approx. +200C), and establish flight conditions of 250 knots IAS and altitude of 5000 feet, using air data test set.

(17)
Open each engine inlet switch in turn and verify that CDU indicates that using anti-ice when outside air temperature is greater than +100C is invalid. Each time, move switch back to OFF and verify that the display returns to normal.
　
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