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 (6)  S 865-132Stop for a minimum of one minute.
 (7)  S 975-095Collect the third set of samples: (a) Read the weight on each wheel from the scales and write the data in Figure 505, in the WHEEL WEIGHT, SAMPLE 3 column. (b) Read the counts for each load sensor with WBC mode-22 and write the data in Figure 506, in the SENSOR COUNTS, SAMPLE 3 column.

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AXLE  WHEEL TION LOCA- WHEEL NO.  WHEEL WEIGHT (lbs.)  (AXLE WEIGHT) Y (ADD AVERAGES FOR AXLE)  VALUE) (WEIGHT-ING V 
SAMPLE 1  SAMPLE 2  SAMPLE 3  AVERAGE 
FWD L WING  OUTBD  1  4 
INBD  2 
AFT L WING  OUTBD  3  4 
INBD  4 
L BODY FWD  OUTBD  5  1 
INBD  6 
L BODY AFT  OUTBD  7  1 
INBD  8 
R BODY FWD  INBD  9  1 
OUTBD  10 
R BODY AFT  INBD  11  1 
OUTBD  12 
R WING FWD  INBD  13  4 
OUTBD  14 
R WING AFT  INBD  15  4 
OUTBD  16 

MAIN LANDING GEAR

WHEEL  WHEEL  WHEEL WEIGHT (lbs.)  V ING (WEIGHT-VALUE) 
LOCATION  NO.  SAMPLE 1  SAMPLE 2  SAMPLE 3  Y (AVERAGE) 
LEFT  17  1 
RIGHT  18  1 

NOSE LANDING GEAR

Wheel Weights at Low Wing Strut Pressures
Figure 505

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AXLE  TION LOCA-SENSOR  NO. SENSOR  SENSOR COUNTS  COUNTS (SUM OF AVERAGES FOR AXLE) AXLE  X (DELTA COUNTS) (AXLE COUNTS -AXLE IDEAL ZERO) 
SAMPLE 1  SAMPLE 2  SAMPLE 3  AVERAGE 
FWD L WING  OUTBD  1 
INBD  2 
AFT L WING  OUTBD  3 
INBD  4 
L BODY FWD  OUTBD  5 
INBD  6 
L BODY AFT  OUTBD  7 
INBD  8 
R BODY FWD  INBD  9 
OUTBD  10 
R BODY AFT  INBD  11 
OUTBD  12 
R WING FWD  INBD  13 
OUTBD  14 
R WING AFT  INBD  15 
OUTBD  16 

MAIN LANDING GEAR

SENSOR  SENSOR  SENSOR COUNTS  (AVERAGE -(DELTA COUNTS) X IDEAL ZERO) 
LOCATION  NO.  SAMPLE 1  SAMPLE 2  SAMPLE 3  AVERAGE 
LEFT FWD  17F 
LEFT AFT  17R 
RIGHT FWD  18F 
RIGHT AFT  18R 

NOSE LANDING GEAR

Sensor Counts at Low Wing Strut Pressures
Figure 506

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 J. Collect Data at Normal Strut Pressure - Second Time (Figures 507 and 508)
 NOTE: In the steps that follow, you will increase the shock strut
____ pressures of the wing landing gear to normal. Then you will collect scales data for Figure 507 and WBC data for Figure 508.
 S 865-134
 (1)  
Increase the pressure in the shock struts of the wing landing gear to within 50 psi of the pressures written in Figure 502.

 S 865-041

 (2)
Stop for five minutes to let the strut pressures become stable.

 S 865-099

 (3)  
　
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