757 Airplane Recovery Document 飞机恢复文件(56)

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C.  100N1142 Baseline, Service and Access Panels
D.  170N0001 Vertical Tail Installation
E.  170N3101 Hoisting Point Diagram, Vertical Fin
F.  174N2001 Link Assembly, Fin to Body, Auxiliary Spar
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AIRPLANE RECOVERY DOCUMENT

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Figure 2-40 EXTERNAL ACCESS, VERTICAL FIN

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WIND VELOCITY  F S FIN SIDE LOAD BECAUSE OF WIND  A D LATERAL DEFLECTION AT THE BOTTOM OF THE FIN 。 ANGULAR DEFLEC-TION FROM THE VERTICAL (DEGREES) 
MPH  KNOTS  POUNDS  KILOGRAMS  FEET  METERS 
12 17 23 35  10 15 20 30  125 280 500 1,130  57 127 227 513  2 4.5 78 18  0.61 1.4 2.4 5.5  5 11 19 47 
THE BOEING COMPANY RECOMMENDS THAT YOU NOT REMOVE THE FIN IN WINDS OF MORE THAN 17 MILES/HOUR OR 15 KNOTS IN ANY DIRECTION. THE FIN CAN POSSIBLY WEATHERVANE IN CROSSWINDS 

NOTE:  1. THE BOEING COMPANY RECOMMENDS THAT YOU NOT REMOVE THE FIN IN WINDS OF MORE THAN 17 MILES/HOUR OR 15 KNOTS IN ANY DIRECTION. THE FIN CAN POSSIBLY WEATHERVANE IN CROSSWINDS
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Figure 2-41 GUST LOADS ON THE VERTICAL FIN DURING REMOVAL (Continued)
NOTE:  1. FIN DEFLECTION CAN CHANGE WITH THE METHOD OF LIFT. VALUES SHOWN ARE APPROXIMATE ONLY AND ARE FOR REFERENCE ONLY. THE VALUES ARE GIVEN AS AN INDICATION OF THE INTENSITY OF THE FORCES THAT OCCUR
2.
THE FIN MUST HAVE A MINIMUM OF SIX GUY LINES ATTACHED DURING REMOVAL (INSTALL THREE ON EACH SIDE)

3.
BECAUSE OF THE EFFECTS OF WIND ON THE FIN AIRFOIL, WINDS OF A SPECIFIED SPEED IN ANY DIRECTION FROM APPROXIMATELY A 15 DEGREE TO A 165 DEGREE ANGLE OF INCIDENCE WILL CAUSE SIDE LOADS OF ALMOST EQUAL INTENSITY

 

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AIRPLANE RECOVERY DOCUMENT
Figure 2-44 DORSAL FIN SCREW LOCATIONS

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3 MAKE THE AIRPLANE STABLE TO LIFT 3-00 GENERAL 3-00-1 General Stabilizing Data
1.  
　
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