9.  
Install the wing jacks and tail support to the tail skid with approximately 250 pounds of ballast on the base of the tail support. Remove the fuselage cradle and wing supports.

10.
If the left wing was removed, it is necessary that the pitot and static tubes be connected at the elbows located within the cockpit at the wing butt line.  Replace or install clamps where found necessary.

11.
Connect the hydraulic brake line onto the fitting located within the cockpit at the leading edge of the wing and the landing gear hydraulic lines at the fittings within the fuselage aft of the spar.

12.
Connect the leads to the appropriate posts on the terminal strip and install the washers and nuts.   (For assistance in connecting the electrical leads, refer to the electrical schematics in Chapter 91.) Place the clamps along the electrical harness to secure it in position and install the terminal strip dust cover.

13.
Connect the fuel line at the fitting located inside the wing, by reaching through the access panel on the forward inboard portion of the wheel well.

14.
Connect the aileron balance and control cables at the turnbuckles that are located within the fuselage aft of the spar.  After the left balance cable has been inserted through the bracket assembly and connected, install a cotter pin cable guard into the hole that is provided in the bracket assembly.

15.
Connect the nap by placing the nap handle in the full flap position; place the bushing on the outside of the rod end bearing and insert and tighten bolt.

16.
Install the engine. (Refer to Installation of Engine, Chapter 71.)

17.
Check the rigging and control cable tension of the ailerons and naps.  (Refer to Rigging and Adjustment of Ailerons, and Rigging and Adjustment of Flaps, Chapter 27.)

18.
Service and refill the brake system with hydraulic fluid in accordance with Servicing Brake System, Chapter 12. Bleed the system as outlined in Chapter 32 and check for fluid leaks.

19.
Check the fluid level of the landing gear hydraulic system and fill in accordance with Servicing Hydraulic Pump/Reservoir, Chapter 12.  With the airplane sitting on jacks, operate the gear through several retraction and extension cycles to be certain that there are no hydraulic leaks.  Bleed the hydraulic system in accordance with Chapter 29. Ascertain that the landing gear is down and locked.

57-40-00 Page 57-11 Issued: April 1, 1997
20.
Service and fill the fuel system in accordance with Servicing Fuel System, Chapter 12.   
Open the fuel valve and check for leaks and fuel flow.

21.
Check the operation of all electrical equipment, pitot and static systems.

22.
Remove the airplane from jacks.

23.
Install the cockpit trim panel assembly, spar box carpet, the front and back seats and wing root rubber. Replace all the access plates and panels.

THIS SPACE INTENTIONALLY BLANK

57-40-00 Page 57-12 Issued: April 1, 1997
3E16
THIS PAGE INTENTIONALLY BLANK

57-50-00 Page 57-13 Issued: April 1, 1997
FLIGHT SURFACES.
AILERON.
REMOVAL OF AILERON.  (Refer to Figure 57-2.)
1.  
Disconnect the aileron control rod at the center hinge by removing the nut, washers, and bolt from the rod end bearing. To simplify installation, note the location of the washers.

2.  
Support the aileron and disconnect the inboard, outboard and center aileron hinges by removing the nuts, washers and hinge bolts.  Remove the aileron by lifting and pulling aft.

INSTALLATION OF AILERON.  (Refer to Figure 57-2.)
1.  
Position the aileron in the wing and install the bolts, washers, and nuts at the hinges.

2.  
Connect the aileron control rod to the aileron at the center hinge brackets with bolt, washers and nut.

AILERON BALANCE. (Refer to Figure 57-3.)
The ailerons have been statically balanced at the time of installation at the factory and normally should not require rebalancing. Where possible the ailerons were set with the balance weight on the heavy side of the limits to permit limited repair or paint touch-up without adjusting the balance weight. It should be noted, however.  that spare ailerons are delivered unpainted and the static balance will not necessarily fall within the limits provided.  The completed ailerons including paint should be within the limits given in Figure 57-3. If the ailerons are not to be painted, the balance weight will probably require adjustment.  All replacement ailerons or ailerons that have been repainted or repaired should be rebalanced according to the procedures given in this chapter.  The static balance of the ailerons must be as specified in the figures referenced above.
Before balancing any control surface, it must be complete including tip, trim/servo tabs as applicable and tab actuating arms or push rods with bearings as applicable and all optional equipment which is mounted on or in the control surface when it is flown, including paint, position lights and wiring, static wicks, scuff boots, etc.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：西門諾爾飛機維護手冊 simenole PA-44-180 AMM 2(54)