S 424-015-N00
 (4)  Install the left EPR manifold.
 (a)  
Put the left manifold tube end between the cable support
 bracket (installed at the 9:30 o'clock position) and the
 turbine exhaust case (View B).

 (b)  
Put the manifold above the EGT probe and bracket locations
 (Views B and C).

 (c)  
Connect the manifold tube nuts to the EPR probe.

 (d)  
Connect the manifold tube nut to the center manifold.

 (e)  
Tighten the manifold tube nuts with your hand.

 S 434-016-N00
 (5)  Install the manifold clamps.
 (a)  
Lubricate the threads of the bolts (9 locations) with engine
 oil.

 (b)  
Install the bolts and the nuts that attach the manifold clamps to the flange T brackets (9 locations, Views A-A, F, G, and H).

 (c)  
Tighten the bolts to 36-40 pound-inches
 (4.1-4.5 newton-meters).

 S 434-017-N00
 (6)  Install the EGT cable clamps.
 (a)  
Lubricate the bolt threads with engine oil.

 (b)  
Install the EGT cable clamp to the manifold clamp (at the 10
 o'clock position) with the bolt and the nut (View E).

 (c)  
Tighten the bolt to 36-40 pound-inches
 (4.1-4.5 newton-meters).

 S 434-022-N00
 (7)  
Tighten the EEC tube nut (at the 6 o'clock position) to 270-300 pound-inches (22.6-25.4 newton-meters).

 S 434-031-N00

 (8)  
Install lockwire or the optional safety cable and ferrule to the EEC tube nut.

 S 434-020-N00

 (9)  
Tighten the manifold tube nuts (4 locations as applicable) to 135-150 pound-inches (15.3-16.9 newton-meters).

 S 434-032-N00

 (10)
 Install lockwire or the optional safety cable and ferrule to each of the manifold tube nuts (4 locations).

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 794-034-N00
 (11)
 Do this task:  Do a Leak Test of the Engine Pressure Ratio (EPR) PT4.95 Probe System (AMM 77-11-01/501).

 S 414-021-N00

 (12)
 Close the core cowl panels (AMM 71-11-06/201).

 S 714-022-N00

 (13)
 Do the operational test for the EPR indicating system (AMM 77-11-00/501).

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ENGINE TACHOMETER SYSTEM - DESCRIPTION AND OPERATION
____________________________________________________
 1.  General
_______
 A.  The engine tachometer system includes the EEC speed transducer (N1), EEC alternator (N2 transducer), engine speed card, and N1 and N2 indication on EICAS.
 2.  EEC Speed Transducer (N1) (Fig. 1)
_________________________
 A.  The probe for the EEC speed transducer (N1) is installed in the intermediate case at the 5 o'clock position. The N1 transducer is a dual coil probe installed so the coils can sense the rate at which 60 teeth on the LPC/LPT coupling pass by them, and send the frequency signal to the EEC. For more information on the EEC speed transducer, refer to AMM 73-21-00/001.
 3.  EEC Alternator (N2 Transducer) (Fig. 1)
______________________________
 A.  The EEC alternator is installed on the aft face of the main gearbox at the 6 o'clock position. A dedicated winding in the EEC alternator supplies N2 signals to the N2 speed card. The EEC also receives N2 signals and supplies signal input to the EIU's for display on EICAS. For more information on the EEC alternator, refer to AMM 73-21-00/001.
 4.  Engine Speed Card (Fig. 1)
_________________
 A.  There are four engine speed cards, one for each engine, installed in the electrical systems card file, found in the left hand area between the nose gear well and fuselage. The engine speed card receives N2 frequency signals from a dedicated winding on the EEC alternator. For N2 more than 50%, the speed card turns on engine probe heat, connects the IDG circuit, disengages the starter, and starts annunciation of engine shutdown.
　
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