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F70207-69, -78 or -83 - Rig Pins Kit ~............................................................................... | | | DIAMETER | LENGTH | | | REF NO. | F70207-( ) | (INCHES) | (INCHES) | FUNCTION | ................................................................................. | R-1 | -14 | 0.309-0.311 | 12.7 |0.25 |CAPTAINS RUDDER PEDAL | | R-2 | -14 | 0.309-0.311 | 12.7 |0.25 |FIRST OFFICERS RUDDER PEDAL| | R-3 | -11 | 0.309-0.311 | 6.7 |0.25 |CAPTAINS RUDDER FORWARD | | | | | | QUADRANT | | R-4 | -11 | 0.309-0.311 | 6.7 |0.25 |FIRST OFFICERS RUDDER | | | | | | FORWARD QUADRANT | | R-5 | -11 | 0.309-0.311 | 6.7 |0.25 |RUDDER FEEL AND CENTERING | | | | | | UNIT | 2.........…............…..............….............…...........................1

 B.
Consumable Materials

 (1)
D00015 Grease - BMS 3-24

 C.
References

 (1)
27-09-17/201, Flight Control Cables Air Pressure Seals

 (2)
27-21-00/201, Rudder and Rudder Trim Control System

 (3)
32-51-00/501, Nose Wheel Steering System

 D.
Access

 (1)  
Location Zones
 101 Control Cabin, LH
 102 Control Cabin, RH
 202 Lower Nose Compartment
 706 Vertical Fin
 708 Rudder

 

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 27-21-00
 ALL  ú ú 01 Page 501 ú Mar 15/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

RIG PIN R-1 AT
THE FORWARD
THE PEDAL ARM
QUADRANT
(FIG. 503)
(FIG. 502)
TABLE I
TEMPERATURE  RIGGING LOAD RA, 
`F |5`  RB +10/-10 POUNDS 
1  2 
110 168 
90 159 
70 150 
50 142 
30 134 
10  125 
-10  117 
-30  109 
-40  103 

THE TEMPERATURE OF THE AIR AROUND THE AIRPLANE MUST BE STABLE
(|5`) FOR A MINIMUM OF ONE HOUR BEFORE YOU ADJUST THE CABLES.

FOR THE NECESSARY PERIODIC CHECKS WITHOUT A SYSTEM DISCREPANCY REPORT,
THE CABLE TENSIONS CAN BE +15/-30 POUNDS FROM THE VALUES IN THE TABLE I.
IF YOU DO A CHECK ON THE CABLE TENSION BECAUSE OF A SYSTEM DISCREPANCY
REPORT, THE CABLE TENSIONS CAN BE |15 POUNDS FROM THE VALUES IN THE
TABLE. WHEN YOU ADJUST THE CABLE TENSION, YOU MUST GET THE TENSION
IN THE LIMITS SHOWN IN THE TABLE.

Rudder Control System Adjustment Figure 501
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 27-21-00
 ALL  ú
 ú  01  Page 502
 ú  Nov 15/91 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (2)  
Access Panels
 1103 Forward Access Door
 3103 Forward Nose Wheel Well Panel, RH
 3104 Forward Nose Wheel Well Panel, LH
 3105 Forward Nose Wheel Well Panel, RH
 3106 Forward Nose Wheel Well Panel, LH
 9515L TE Access Panel - Rudder
 9528R Access Door - Rudder
 9529R Access Door - Rudder
 9555R Cover - Rudder Nose
 9556L Cover - Rudder Nose

 E.
Procedure

 S 865-018
 WARNING:_______MAKE SURE YOU DO THE STEPS IN THE TASK BELOW. THE AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY IF YOU DO NOT REMOVE THE HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (1)  
Remove the rudder hydraulic power systems A, B, and standby (Ref 27-21-00/201).

 S 825-019

 (2)  
Adjust the rudder forward quadrants:

 (a)  
Operate the adjustment crank for the rudder pedals to set the jackshaft yoke to the middle position (Fig. 503).

 NOTE: The middle position of the yoke travel is where the
____ number of turns of the shaft from the full forward and the full aft adjustment are the same.
 (b)  
Open the access door 1103.

 (c)  
Remove the access panels 3104 and 3106, or 3103 and 3105.

 (d)  
　
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