and replace the packing.
(i) Remove the regulated pressure supply from the Adapter on the hose (AS13).
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A
747-400 MAINTENANCE MANUAL
(j)
Remove the Adapter from the hose (AS13).
(k)
Remove the two test clamps from the two EPR probes.
(l)
Do these steps to connect the hose (AS13) to the EEC.
CAUTION: DO NOT APPLY LUBRICANT TO ANY EEC SENSING HOSE, TUBE,
_______ ADAPTER OR PACKING. CONTAMINATION OF THE EEC CAN OCCUR.
1) Do not apply lubricant to the hose (AS13) or to the
adapter. 2) Install the hose (AS13) on the EEC adapter. 3) Hold the EEC adapter with a wrench and tighten the hose
(AS13) to 135-140 pound-inches (15.3-17.0 newton-meters). a) To safety the tube nuts install the safety wire or install the safety cable and safety cable ferrule.
(m)
AIRPLANES POST-PW-SB 77-16; Examine the four pressure sensing ports in the front of each probe to make sure that there is no damage or blockage (AMM 77-11-01/601).
(n)
AIRPLANES PRE-PW-SB 77-16; Examine the six pressure sensing ports in the front of each probe to make sure that there is no damage or blockage (AMM 77-11-01/601).
S 865-003-N00
(2) Put the Airplane Back to Its Usual Condition.
(a)
Remove the air supply equipment from the engine.
(b)
Make sure that the work area is clean and remove all tools and other items.
(c)
Close the core cowl panels (AMM 71-11-06/201).
(d)
Close the fan cowl panels (AMM 71-11-04/201).
(e)
Do this procedure: Thrust Reverser Activation After Ground Maintenance (AMM 78-31-00/201).
S 715-004-N00
(3) Do this task: Engine Pressure Ratio Indicating System Operational Test (AMM 77-11-00/501).
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ENGINE PRESSURE RATIO (PT4.95) PROBE -
______________________________________ INSPECTION/CHECK
________________
1. General_______
A. This section contains the task to do an inspection of the engine pressure ratio (EPR) probe.
B. There are two EPR (PT4.95) probes installed on the turbine exhaust case. One probe is installed at the 4 o'clock position and one probe is installed at the 10 o'clock position.
C. To get access to the EPR probe, you must open the applicable core cowl panel.
TASK 77-11-01-206-001-N00
2. Examine the Engine Pressure Ratio (PT4.95) Probe (Fig. 601)________________________________________________
A. Standard Tools and Equipment
(1)
AIRPLANES WITHOUT PW SB77-16;
Bit - Drill, 0.030 inch (0.762 mm) diameter
(2)
AIRPLANES WITH PW SB77-16;
Bit - Drill, 0.0635 inch (1.613mm) diameter
(3)
Die - thread chaser, 0.500-20UNS-3A
(4)
Ground Pneumatic Cart
B.
References
(1)
AMM 77-11-01/401, Engine Pressure Ratio (PT4.95) Probe
(2)
IPC 77-11-01 Fig. 01
C.
Access
(1)
Location Zone 412 Engine 1 - Turbine Exhaust Case 4 or 10 o'clock 422 Engine 2 - Turbine Exhaust Case 4 or 10 o'clock 432 Engine 3 - Turbine Exhaust Case 4 or 10 o'clock 442 Engine 4 - Turbine Exhaust Case 4 or 10 o'clock
(2)
Access Panel
417 Left Core Cowl Panel - Engine 1
418 Right Core Cowl Panel - Engine 1
427 Left Core Cowl Panel - Engine 2
428 Right Core Cowl Panel - Engine 2
437 Left Core Cowl Panel - Engine 3
438 Right Core Cowl Panel - Engine 3
447 Left Core Cowl Panel - Engine 4
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