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C.  If the aft control cable is not installed, install per Step 2.
D.  Connect the cable to the aft cable at the turnbuckle in the aft section of the fuselage.
E.  For the right control cable, install the cotter pin cable guard at the pulley in the forward area of the tunnel.
F.  Within the forward area of the floor opening aft of the main spar, install the cable rub blocks to the spar housing and secure with screws.
G.  In the aft area of the floor opening, install the cotter pin cable at the pulley cluster.
H.  Install the cable guard under the pulley cluster located in the aft area of the aft floor tunnel and secure with screws.
I.  Set cable tension and check rigging and adjustment.
J.  Install the tunnel plate directly aft of the tee bar assembly and secure with screws.
K.  Put the floor carpet in place and secure.
L.  Install the lower and upper selector covers and secure with screws.
M.  Place the fuel selector knobs on the selector torque tube and secure with set screws.
N.  Install the floor panel aft of the main spar and secure with screws. Install the seat belt attach-ments and seats.
0.  Install the cover and carpet of the aft floor tunnel.
2.  To install either aft stabilator control cable:
A.  Route the cable under pulley.
B.  Connect the cable to the stabilator bellcrank and secure with bolt, washer, nut and cotter pin. (Tighten nut “finger tight” only.)
C.  Connect the cable to the forward cable at the turnbuckle in the aft section of the fuselage. The upper aft cable connects to the right forward cable and the lower cable to the left cable.
D.  Connect assist springs to bulkhead sta. 156 and orient cable plates so that they align with horizontal plate ±10°.  (Refer to Figure 27-18.)
E.  Install the cable guard pin at the pulley.
F.  Set cable tension and check rigging and adjustment.
3.  Install the access panels to the aft section of the fuselage.
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27-30-00 Page 27-43 Issued: April 1, 1997

STABILATOR
STABILATOR TRIM TAB

NOTES

1.  
MAXIMUM FREE PLAY FOR CONTROL SURFACE TAB IS 0.15 OF AN INCH MEASURED AT TAB TRAILING EDGE.

2.  
REFER TO CHAPTER 55.

3.  
NEUTRAL POSITION OF STABILATOR IS WITH THE STABILATOR CHORD LINE PARALLEL WITH THE FRONT SEAT TRACKS.

Figure 27-19. Stabilator Rigging
27-30-00 Page 27-44 Issued: April 1, 1997
2C20
RIGGING AND ADJUSTMENT OF STABILATOR CONTROLS
1.  To check and set the correct degree of stabilator travel, the following procedure may be used:
A.  Level the airplane. (Refer to Leveling, Chapter 8.)
B.  Place the stabilator in neutral position. Neutral position is obtained when a level placed on stabi-lator rigging tool (Figure 27-19) indicates that stabilator chord line is parallel with the top of the front seat tracks.
C.  Check the stabilator travel by placing a rigging tool on the upper surface of the stabilator as shown in Figure 27-19. (This tool may be fabricated from dimensions given in Chapter 91.)
D.  Set on a bubble protractor the number of degree up travel as given in Figure 27-19 and place it on the rigging tool. Raise the trailing edge of the stabilator and determine that when the stabilator contacts its stops the bubble of the protractor is centered.
— Note — The stabilator should contact both of its stops before the control wheel contacts its stops.
E.  Set on the protractor the number of degrees down travel as given in Figure 27-19 and again place it on the rigging tool. Lower the trailing edge of the stabilator and determine that when it contacts its stops, the bubble of the protractor is centered.
F.  Should the stabilator travel be incorrect in either the up or down position, remove the fin tip by removing the attachment screws and with the use of the rigging tool and bubble protractor turn the stops located at the stabilator hinge in or out to obtain the correct degree of travel. (Refer to Figure 27-20.)
G.  Ascertain that the locknuts of the stop screws are secure and then reinstall the fin tip.
2.  To check and set stabilator control cable tension, the following procedure may be used:
A.  Ascertain that the stabilator travel is correct.
B.  Remove the access panel to the aft section of the fuselage and fin tip and disconnect the assist springs from bulkhead sta. 156.
C.  Secure the control column in the near forward position. Allow one-quarter inch ± 0.031 between the column and the stop bumper.
D.  Check each control cable for the correct tension as given in Figure 27-19.
　
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