REMOVAL OF THE VERTICAL FIN
Page 2-85 Jul 01/2005 D623N004
CAUTION: BEFORE YOU START THE REMOVAL PROCEDURE, MAKE THE AIRPLANE STABLE. THIS PREVENTS A MOVEMENT OF THE AIRPLANE WHEN YOU REMOVE THE FIN. SUCH A MOVEMENT CAN CAUSE MORE DAMAGE TO THE AIRPLANE AND INJURY TO PERSONS.
CAUTION: DO NOT REMOVE THE FIN IN HIGH WINDS (HIGHER THAN 17 MPH OR 15 KNOTS). THE DIRECTION OF THE WIND MAKES NO DIFFERENCE. THE FIN CAN MOVE DANGEROUSLY (WEATHERVANE).
CAUTION: IF IT IS POSSIBLE, PUT THE AIRPLANE IN A CORRECT ATTITUDE BEFORE YOU START THE REMOVAL. IF YOU ARE IN AN EMERGENCY, YOU CAN START THE REMOVAL WITHOUT THIS STEP. ON LEVEL GROUND, THE AIRPLANE USUALLY WILL NOT SLOPE MORE THAN EIGHT DEGREES, EVEN IF ONE LANDING GEAR IS BROKEN. MOVE SLOWLY AND BE VERY CAREFUL.
4. Fin Removal Procedure
A. Install the B55001 Vertical Fin Sling and the tether fittings on the two sides of the fin (see Figure 2-41). Attach the crane hook to the eye (lift fitting) of the sling and pull up only until the lines are tight. Align the line of force on the sling with the centerline of the fin as shown in Figure 2-41. Attach ropes (guy ropes) to the tether points on the two sides of the fin.
NOTE: SEE Figure 2-41 FOR DATA ABOUT THE EFFECTS OF THE WIND.
NOTE: IF THERE IS NO CRANE WHEN YOU START THE FIN REMOVAL PROCEDURE, YOU CAN DO STEP 1 AFTER STEP 8.
B. Remove the dorsal fin. The fin is held in place by 120 screws (cross-point screws) as shown in Figure 2-41. You can ignore this step in an emergency condition.
C. Remove the access panels V70-4 (access to the forward torque box) and V70-7 (access to the fixed trailing edge). See Figure 2-40.
D. Remove the side load link (PN 174N2001-1) from the end of the fin at Left Buttock Line (LBL) 6.0. The link is installed at the bottom of the fin auxiliary spar (Body Station 1672, BWL 305). You can get access to it after you remove access panel V70-4. After you remove the link, attach two ropes (guy ropes) to the remaining clevis. Put one rope on each side of the airplane.
E. Go through door B48-1 to the internal side of Section 48.
F. Open and drain all the hydraulic lines that go from Section 48 to the fin. Find a location where it is easy to catch the hydraulic fluid. You will catch possibly two gallons (7.6 L) of fluid. Disconnect and seal all the lines in the fin and open all the support clamps.
G. Disconnect the rudder control cables. Find a safe location to coil and stow the ends of the cables in the fin and in Section 48.
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本文鏈接地址：757 Airplane Recovery Document 飛機(jī)恢復(fù)文件(54)
