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737-300/400/500MAINTENANCE MANUAL
To calculate the new tab position, Xf, add (or subtract) the value for the elevator tab rig adjustment from Fig. 510 to the measured tab position, Xm.
EXAMPLE: If the measured tab position, Xm = 0.323,
_______ the stabilizer trim wheel turns = 7 (nose up) the new tab position, Xf = 0.323-0.047 = 0.276
Adjust the left and right elevator tab pushrods until they are in |0.01 inch of the new tab position, Xf.
NOTE: If the airplane required nose up trim during the
____ test to be consistent with Fig. 510, a correct tab adjustment will be in the tab trailing edge down direction. If the airplane required nose down trim during the test to be consistent with Fig. 510, a correct tab adjustment will be in the tab trailing edge up direction.
The aft ends of the titanium pushrods have two checknuts for each pushrod. The aft ends of the aluminum pushrods have one checknut for each pushrod.
1) AIRPLANES WITH THE ALUMINUM TAB PUSHRODS; Adjust the elevator tab. a) One half turn of the 3/8 inch rod end moves the tab
trailing edge approximately 0.089 inch. b) One half turn of the 7/16 inch rod end moves the tab trailing edge approximately 0.10 inch. c) One half turn of the rod barrel moves the tab trailing edge approximately 0.017 inch.
2) AIRPLANES WITH THE TITANIUM TAB PUSHRODS; Adjust the elevator tab. a) One half turn of the rod end moves the tab trailing
edge approximately 0.1 inch. b) One full turn of the adjustment bushing moves the tab
trailing edge approximately 0.02 inch.Make sure that the right elevator trailing edge aligns with the index mark in |0.04 inch. 1) Calculate the final tab position "a" after the flight test.
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2) Make sure the right and left tab positions are in the permitted range in Table 505.
NOTE: If the temperature = 70°F, spacer thickness
____ t = 0.500 inch, and Xf = 0.765, the tab position 'a' after the flight test is 0.765 - 0.500 = 0.265 inch, which is in the limits of Table 505.
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~...................................................... | Elevator Tab Position "a" After Flight Test | | Table 505 | ........................................................
| AIR- | Final Tab | | Permitted |
| PLANE |Dimension Xf| Spacer | Tab Position "a" |
|TEMPER-| Based On |Thickness| After |
| ATURE |Flight Test | | Flight Test |
| | | | (a = Xf - t) |
........................................................ |°F |°C | | "t" | Aluminum | Titanium | | | | | | Tab Rod | Tab Rod | ........................................................ |120| 49| | |0.113-0.413|0.200-0.500| ........................................................ |110| 43| | |0.120-0.420|0.200-0.500| ........................................................ |100| 38| | |0.128-0.428|0.200-0.500| ........................................................ | 90| 32| | |0.135-0.435|0.200-0.500| ........................................................ | 80| 27| | |0.143-0.443|0.200-0.500| ........................................................ | 70| 21| | |0.150-0.450|0.200-0.500| ........................................................ | 60| 16| | |0.157-0.457|0.200-0.500| ........................................................ | 50| 10| | |0.165-0.465|0.200-0.500| ........................................................ | 40| 4| | |0.172-0.472|0.200-0.500| ........................................................ | 30| -1| | |0.180-0.480|0.200-0.500| ........................................................ | 20| -7| | |0.187-0.487|0.200-0.500| ........................................................ | 10|-12| | |0.194-0.494|0.200-0.500| ........................................................ | 0|-18| | |0.202-0.502|0.200-0.500| ........................................................ |-10|-23| | |0.209-0.509|0.200-0.500| ........................................................ |-20|-29| | |0.216-0.516|0.200-0.500| ........................................................ |-30|-34| | |0.223-0.523|0.200-0.500| ........................................................ |-40|-40| | |0.230-0.530|0.200-0.500| ........................................................ |-50|-46| | |0.238-0.538|0.200-0.500| ........................................................ |-60|-51| | |0.244-0.544|0.200-0.500| 2...…...…............….........…...........…...........1 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(118)
