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SUBTASK 27-51-22-980-002 (8) Support the aft flap assembly [2] to make sure the programming rollers [21] touch the bottom surface of the programming tracks and the aft rollers for the aft flap tracks touch the top surface of the tracks. NOTE: This is the position the rollers will be in with airloads applied to the aft flap assembly [2]. SUBTASK 27-51-22-220-004 (9) Measure the clearance between the main flap [1] and the upper surface of the aft flap assembly [2] (View C) (Figure 402). NOTE: Measure the clearance at all of the cove panel supports [51] and at the aft flap roller fittings [60]. SUBTASK 27-51-22-220-007 (10) Make sure that the rub strip [50] and teflon coating on the upper surface of the aft flap assembly [2] are not damaged (View C) (Figure 402). (a) If the rub strip [50] is damaged or missing, then do this task, do this task: Bonded Phenolic or Stainless Steel Rub Pad Repair (Heat Source Available) , TASK 51-51-00-340-802. (b) If the telfon coating is damaged, then do this task, do this task: Abrasion Resistant Teflon Finish Application, TASK 51-21-81-390-801. SUBTASK 27-51-22-820-004 (11) If the clearance between the main flap [1] and the aft flap assembly [2] is not in the limit of 0.010 +0.100/-0.010 inch (0.25 +2.54/-0.25 mm), then change the thickness of the shims [58] on the cove panel support [51] or the shims [59] on the aft flap roller fittings [60]. (a) Remove the rig pins from the bellcranks [12]. (b) Extend the aft flap assembly [2], until you can get access to the fasteners for the shims [58] and [59]. To extend the flaps, do this task: Extend the Trailing Edge Flaps, TASK 27-51-00-860-803. (c) If it is necessary, change the thickness of the shims [58] on the cove panel supports [51]: 1) Remove the nuts [57], washers [56] and bolts [55] that attach the cove panel [52] to the cove panel support [51]. 2) Remove the shim [58] from the cove panel support [51] and the cove panel [52]. 3) Change the thickness of the shim [58]. NOTE: The maximum permitted thickness of the shim [58] is 0.050 inch (1.27 mm). 4) Apply sealant, A00247 to the mating surfaces of the shim [58]. 5) Put the shim [58] in its position between the cove panel support [51] and the cove panel [52]. 6) Install the bolts [55], washers [56] and nuts [57]. (d) If it is necessary, change the thickness of the shims [59] on the aft flap roller fittings [60]: 1) Remove the nuts [63], washers [62] and bolts [61] that attach the cove panel [52] to the aft flap roller fitting [60]. 2) Remove the shims [59] from the aft flap roller fitting [60] and the cove panel [52]. 3) Change the thickness of the shims [59]. NOTE: The maximum permitted thickness of the shim [59] is 0.050 inch (1.27 mm). 4) Apply sealant, A00247 to the mating surfaces of the shims [59]. 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL EFFECTIVITY GUN ALL 27-51-22 Page 413 Oct 10/2005 D633A101-GUN BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details 5) Put the shims [59] in their position between the aft flap roller fitting [60] and the cove panel [52]. 6) Install the bolts [61], washers [62] and nuts [63]. 7) If it is necessary, trim the excess shim [59] that extends past the aft flap roller fitting [60]. (e) Retract the aft flap assembly [2] until you can install the rig pins in the bellcranks [12]. To retract the flap, do this task: Retract the Trailing Edge Flaps, TASK 27-51-00-860-804. (f) Install the rig pins in the bellcranks [12]. (g) Make sure the clearance between the main flap [1] and the upper surface of the aft flap assembly [2] is in the limit. SUBTASK 27-51-22-220-006 (12) Measure the deflection of the upper cove panel [52] of the main flap [1] at the inboard and outboard ends of the aft flap assembly [2]: NOTE: The aft flap assembly [2] can push up on the upper cove panel [52] and cause the panel to deflect. (a) Make sure the delection is a maximum of 0.200 inch (5.08 mm). SUBTASK 27-51-22-220-005 (13) Make sure the seals on the aft lower surface of the main flap [1] are in the correct position: (a) Measure the distance between the aft edge of the seal [54] and the seam on the lower surface of the aft flap assembly [2] (View A-A). NOTE: This distance is called DIMENSION Y. (b) At the inboard end of the aft flap assembly [2], make sure that DIMENSION Y is 5.76 ±0.10 inch (146.3 ±2.54 mm). (c) At the inboard side of the inboard flap support, make sure that DIMENSION Y is 5.57 ±0.10 inch (141.48 ±2.54 mm). (d) At the outboard side of the inboard flap support, make sure that DIMENSION Y is 5.46 ±0.10 inch (138.68 ±2.54 mm). www.aero.cn 航空翻譯 www.aviation.cn 本文鏈接地址：737-600-700-800-900 飛機(jī)維護(hù)手冊(cè)5 AIRCRAFT MAINTENANCE MANUA
