F84910
Wing to Fuselage Attachment  500 
51-00  Figure 3  Nov 15/66 
Page 6 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5.  Empennage
A.  The empennage comprises a dorsal fin, a vertical fin, an adjustable horizontal stabilizer, rudder and elevators.
B.  Left and right horizontal stabilizers are removable from the adjustable center section truss located within the fuselage. This center section is movable, pivoting on two hinge joints attached to a bulkhead in the fuselage. Each stabilizer consists of two spars with interconnecting ribs and skin. The leading edge is removable.
C.  The elevators are skin covered, spar and rib structures, containing balance panels, stabilizer actuated elevator tab and elevator control tab.
D.  The vertical fin is composed of front and rear spars, interconnecting ribs and skin. The leading edge is removable. The fin and rudder may be removed.
E.  The rudder is a skin covered, spar and rib structure.
6.  Engine Fairing
A.  The engines, one on each wing, are supported from fittings attached to wing structure. The engine fairing covers the area between the engine nacelle and the wing.
500 
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F84970
Blowout Doors and Panels  526 
51-00Page 8   Figure 4 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/69 

REDUCED VERTICAL SEPARATION MINIMUM (RVSM) - INSPECTION/CHECK
EFFECTIVITY
All 737-200 Airplanes
1. General
A.  RVSM will permit the airplane to be separated by 1000 feet vertically from FL290 to FL410, instead of the current 2000 feet. RVSM makes more available route assignments and gives benefits to operators through better route assignments and reduced schedule delays.
B.  This procedure contains two tasks. One task is to visually examine the airplane skin for smoothness in the area of the pitot-static ports. The second task is to measure the skin waviness in the area of the pitot-static ports.
2.  Examine the Airplane Skin
A.  Equipment
(1)  C51003-1 - Skin Waviness Measurement Tool
B.  Access
(1)  Location Zone
100 Fuselage - Lower Half

3.  Part 1 - Visual Skin Inspection
A.  Procedure
(1)  
Do a visual inspection of the pitot-static probes for obvious damage (Ref AMM 34-11-11).

(2)  
Replace any damaged pitot-static probes (Ref AMM 34-11-11).

(3)  
Do a visual inspection of the fuselage skin around the pitot-static probes on the left and right sides of the airplane in Section 41, Fig. 601.

NOTE: Look for damage or previous repairs.

(4)  
If there is damage other than dents or bulges, then:

(a)  
For 737-200 airplanes built between Line Numbers 1 thru 330, do a repair as shown in Service Bulletin 737-53-1111 and drawing 65C33596, or contact Boeing.

(b)  
For 737-200 airplanes built after Line Number 330, contact Boeing.

May 01/99 51-10-0 Page 601
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G59748
 Skin Inspection Area  501 
51-10-0  Figure 601  May 01/98 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(5)  
If there are dents or bulges within the inspection area, see if you have one of the following conditions: 

(a)  
There is a dent or bulge that is beyond the limits shown in the 737 SRM, Section 51-70, Fig. 5.

(b)  
The total number of dents and bulges on the airplane is greater than 2. You can have a total of two dents or bulges on one side of the airplane or you can have one dent or bulge on both sides of the airplane.

(6)  
If you have any of the conditions in Step 3.A.(5) above, then:

(a)  
For 737-200 airplanes built between Line Numbers 1 thru 330, do a repair as shown in Service Bulletin 737-53-1111 and drawing 65C33596, or contact Boeing with details of the dents/bulges for disposition.

(b)  
For 737-200 airplanes build after Line Number 330, contact Boeing with details of the dents/bulges for disposition.

(c)  
If you contact Boeing for disposition, you should give Boeing the following
information:
1) the location of the damage
2) the shape of the damage
3) the orientation of the damage
4) the height or depth of the damage