5.
Gasket

6.
Plug

7.
Gasket

8.
Screen

9.
Screen Housing

10.
Washer

11.
Bolt

Figure 7-15. Oil Cooling Adapter and Oil Pressure Screen Assembly
OVERHAUL MANUAL LYCOMING 76 SERIES AIRCRAFT ENGINES Section7 Crankcase,Crankshaft andReciprocatingParts
1.
Oil Filter

2.
Converter Plate Stud

3.
Converter Plate

4.
Oil Filter Adapter

5.
Temp. Control Valve

6.
Breather Fitting

7.
Adapter Gasket

8.
Oil Cooler Fittings

Figure 7-16. Oil Filter Adapter Assembly
OVERHAUL  MANUAL  LYCOMING  76  SERIES  AIRCRAFT  ENGINES  Section8 
Test Procedure 
SECTION  8 
TEST  PROCEDURE 

8-1. At the completion of the engine after overhaul, it is recommended that the engine be mounted upon a test stand for its initial or run-in operation. The run-in serves a two-fold purpose; first, to seat piston rings and burnish any new parts that may have been installed and second, to give the operator control over the first critical hours of operation, during which time he can observe the function-ing of the engine by means of the test cell instruments. Also, at this time any malfunction can be corrected and oil leaks repaired.
8-2. The test stand should be installed in a test cell that is clean and free of any articles that could be moved by the test club air blast.
8-3. The following instruments should be used, plus any additional instruments that may be deemed necessary by the operator. 0° to 600°F. temperature gage, counter tachometer, fuel flow meter, fuel pressure gage, manifold pressure gage, oil temperature gage, oil pressure gage and an oil flow measuring device.
NOTE

Lycoming recommends that a test cell be used for run-in of engines after overhaul Consult engine test eq uip-ment, SSP1169, for more detail list of cell equipment and schematic of oil supply system and fuel. In the event a test cell is not available, it is permissible to mount the engine in the airframe for the run-in providing the follow-ing requirements are observed
1.
Consult Table 8-4 for the correct configuration of test club adapter and bolts to be used during test. Do not use a flight propeller during test.

2.
A cooling shroud equivalent to a test cell cooling shroud is installed.

3.
The airframe gages may not be used. All necessary calibrated gages shall be installed independent of the airframe.

8-4. Test stand oil supply pressure to engines which can be run simulated wet sump shall be held to 1.5 -2.0 psi throughout the run. Test stand oil supply pressure to engines run simulated dry sump shall be held to 0.5 -3.0 psi at rated conditions. Personnel should consult Service Bulletin No. 113 when desiring to use dry sump test stand
　
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