Wing Installation - Piper PA-44-180 SEMINOLE Maintenance Manual

INSTALLATION OF WING. (Refer to Figure 57-1.)
1. Ascertain that the fuselage is positioned solidly on a support cradle.
2. Place the wing in position for installation, with the spar end a few inches from the side of the fuselage and
set on trestles.
3. Prepare the various electrical leads, fuel lines, control cables, and power plant controls for insertion into the
wing or fuselage when the wing is eased into place.
4. Slide the wing into position on the fuselage.
5. Install the main spar bolts in accordance with the information given in Figure 57-1, Sketches C and D.
6. Install the bolt, washers, and nut that attaches the front spar and fuselage fitting. A minimum of one washer
is required under the bolt head; then add washers as needed to leave a maximum of one and one-half threads
visible or a minimum of bolt chamfer exposed. (Refer to Sketch A, Section A-A of Figure 57-1.)
7. Install the bolt, washers, and nut that attaches the rear spar and fuselage fitting. It is acceptable to have the
faces of the fittings against each other in which case the AN960-616L washer should be used under the bolt
head. The AN960-616 washer may be added under the nut when not used as a shim. (Refer to Sketch B,
Section B-B of Figure 57-1.) Check to insure that no threads are bearing on the forward plate prior to
installing the nut.
8. Torque the main spar bolts in accordance with specifications given in the bolt legend of Figure 57-1 . The
forward spar attachment bolt should be torqued to a maximum of 70 to 90 inch-pounds. The rear spar
attachment bolt should be torqued to a maximum of 360-390 inch-pounds.
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.
PIPER AIRCRAFT
PA - 4 4 - 1 8 0 / 1 8 0 T
AIRPLANE MAINTENANCE MANUAL
3C16
5 7 - 4 1 - 0 2
Page 57-05
Revised: May 15, 1989