(2)
Provide system A hydraulic power (Ref 27-51-0 MP).
(3)
Set flap control lever in FLAP UP (0-unit) detent; allow 2 minutes for flaps to fully retract.
(4)
Remove system A hydraulic power (Ref 27-51-0 MP).
(5)
Position flaps as follows:
(a)
At No. 4 jackscrew, measure and record X dimension as shown in Detail A, Fig. 401.
(b)
On IDO A17301 and A17302; AL N310AU thru N320AU; AF F-GBYA thru F-GBYL; GJ B-2501 thru B-2503, reposition flaps electrically so that X dimension measured in step (a) is an additional
24.38 to 24.53 inches.
(c)
On IDO ALL EXCEPT A17301 and A17302; AL ALL EXCEPT N310AU thru N320AU; AF ALL EXCEPT F-GBYA thru F-GBYL; GJ ALL EXCEPT B-2501 thru B-2503, reposition flaps electrically so that X dimension measured in step (a) is an additional
25.52 to 25.68 inches.
5B2
Jun 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-58-12 Page 401
G42468
Flap Position Transmitter Installation 515
27-58-12 Figure 401 Jun 20/89
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
B. Install flap position transmitter.
(1)
Install electrical connector on transmitter receptacle.
(2)
On GJ B-2501 thru B-2503, rotate each transmitter input shaft until corresponding flap position indicator needle point is centered within black index mark at 15-unit position.
NOTE: Rotating transmitter shaft clockwise should move position indicator needle toward UP position. If needle moves toward 40-unit position, rotate transmitter shaft clockwise until needle moves to 15-unit position toward UP position (approximately 14.5 turns clockwise).
Tap indicator to remove friction error before checking indicator reading.
(3) On GJ ALL EXCEPT B-2501 thru B-2503, rotate each transmitter input shaft until corresponding flap position indicator needle point is centered within black index mark at 25-unit position.
NOTE: Rotating transmitter shaft clockwise should move position indicator needle toward UP position. If needle moves toward 40-unit position, rotate transmitter shaft clockwise until needle moves to 25-unit position toward UP position (approximately 14.5 turns clockwise).
Tap indicator to remove friction error before checking indicator reading.
(4)
Grease transmitter splines lightly and install transmitters onto gearboxes keeping indicator needles within black index mark. Install mounting screws and washers with wet primer. Do not lockwire.
(5)
Test position indicating system (Ref 27-58-01 A/T).
(6)
Check electrical bond between transmitter and gearbox per 20-22-01. Maximum
resistance should not exceed 0.0025 ohm.
(7)
Lockwire transmitter mounting bolts.
C. If right flap position transmitter was replaced, test stall warning system (Ref 27-32-0 A/T).
5C8
Jun 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-58-12 Page 403
D. On GJ B-2509 and B-2510, test flap position transmitter/FCC interface.
(1)
Provide system A hydraulic power (Ref 27-51-0 MP).
(2)
Provide electrical power (Ref 24-22-0 MP).
(3)
Position flap control lever to 10-unit detent to extend flaps.
(4)
Select PDC CDU to autopilot BITE by selecting STBY, pressing RCL, (-) then selecting page 5 (autopilot BITE).
(5)
Select Ground Functional Tests by pressing ENT (no) after SYMPTOM/PIREP TEST DESIRED message. Press ENG (yes) to select GROUND FUNCT TEST.
(6)
Select desired channel by pressing ENG (yes) for Channel A (left flap position transmitter) or ENT (no) to select channel B (right flap position transmitter).
(7)
Press ENT to advance displayed test number until the desired test will be the next test to display, then press ENT.
NOTE: The desired test number is:
Channel A: 2.49 for FCC -111 or -113
2.49 for FCC -112 or -114 Channel B: 52.49 for FCC -111 or -113
52.49 for FCC -112 or -114
(8)
Perform instructions using CDU switches and keyboard.
NOTE: Instructions on the CDU require the operator to position the flaps to 10 degrees.
(9)
Follow instructions to provide system diagnostic routine if a BITE fails. Replace indicated component and recycle system thru BITE until system passes.
(10)
At the completion of test, exit BITE by paging CDU away from page 5-5.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(82)
