S 432-003
(2)
Do these steps to install the shear pin:
(a)
Install the shear pin through the crank bushings and the rod end from the shear pin retainer side.
(b)
Install the cupped shaped washer on the shear pin.
(c)
Use the swaging tool and swage the shear pin until it is fully expanded against the cupped washer.
NOTE: Keep the cupped washer against the output crank during
____ the swaging process. The swaging force is between 150-300 pounds (0.667-1.33 KN).
S 822-053
(3)
Move the shims and the shear pin retainer into position over the end of the shear pin. Make sure that the clearance between the retainer and the shear pin is as shown (View A-A). Add or remove shims below the retainer to get the correct clearance.
S 392-054
(4)
Apply sealant to the shear pin retainer, the ratio-changer output crank, and the outer surface of the rivet.
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S 432-055
(5)
Do these steps to install the shear pin retainer:
(a)
Make sure that the shear pin retainer is located next to the edge of the right ratio-changer output crank as shown (View B-B).
(b)
Install the blind rivet that holds the retainer to the ratio-changer output crank.
NOTE: Tool air pressure must be approximately 90 psi to
____ install the rivet correctly.
S 322-056
(6)
Use a drill to make an inspection hole from the retainer side of the shear pin as shown (View A-A).
S 212-057
(7)
Make sure that rig pin R9 moves smoothly through the shear pin inspection hole. Remove rig pin R9.
I.
Rudder Ratio-Changer Mechanism Test
NOTE: Before you do the test, make sure the airplane is stable at
____ ambient air temperature 10.0 degrees F (5.5 degrees C) for at least one hour.
S 862-005
WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN
_______ HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
(1)
Supply pressure to the left, right, and center hydraulic systems (AMM 29-11-00/201).
S 862-058
(2)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:
(a)
11D18 or 11G10, RUD RATIO
(b)
11H17, FLT CONT SHUTOFF TAIL LEFT
(c)
11H18, FLT CONT SHUTOFF TAIL CTR
(d)
11H28, FLT CONT SHUTOFF TAIL RIGHT
S 862-059
(3) Remove the DO-NOT-OPERATE tags and move the FLT CONTROL SHUTOFF L, R, and C switches on the right side panel, P61, to ON.
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(4)
Make sure that the rudder is not more than 0.15 inch (3.8 mm) away from its neutral position.
S 222-061
(5)
Move the test switch on the left or right RRCM on the E3 and E4 shelf in the main equipment center to TEST. Stop for 30 seconds to let the rudder ratio-changer actuator extend. Do the checks that follow:
NOTE: The amber RUDDER RATIO light on the pilot's overhead panel,
____ P5, will come ON and stay ON. An amber RUDDER RATIO message will appear on EICAS when the RRCM test switch is in the TEST position.
(a)
Make sure the IN TEST light on each RRCM is ON no more than 18 seconds.
(b) 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：757 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 2(58)
