— CAUTION —
TO PREVENT DAMAGE OR CONTAMINATION OF FUEL, HYDRAULIC AND MISCELLANEOUS LINES, PLACE A PROTECTIVE COVER OVER THE LINE FITTINGS AND ENDS.
12.
Disconnect the fuel line at the fitting located inside of the wing by removing the access panel on the forward inboard portion of the wheel well and reaching through to the fuel line coupling.
13.
Remove the clamps that are necessary to release the electrical harness assembly. Disconnect the leads from the terminal strip by removing the cover and appropriate nuts and washers.
14.
With the appropriate trim panel removed, disconnect the hydraulic brake line at the fitting located within the cockpit at the leading edge of the wing.
15.
Disconnect the landing gear hydraulic lines at the fittings aft of the spar and within the fuselage.
16.
If the left wing is being removed, it will be necessary to disconnect pitot and static tubes at the elbows located within the cockpit at the wing butt line.
57-40-00 Page 57-8 Issued: April 1, 1997
3E12
SKETCH B
57-40-00 Page 57-9 Issued: April 1, 1997
3E13
THE NEW PIPER AIRCRAFT, INC.
PA-44-180
AIRPLANE MAINTENANCE MANUAL
BOLT LEGEND 1* C-6 A-5 C-2C-3C-4C-5 A-2A-3A-4 SKETCH C A-1 C-1
POSITION BOLT NUT WASHER UNDER HEAD WASHER UNDER NUT
A-1 NAS464P6LA17 MS21042-6 (1) AN960-616 (1) AN960-616 (2 MAX.) A-2 NAS464P6LA16 MS21042-6 (1) AN960-616 (1) AN960-616 (2 MAX.) A-3 NAS464P6LA16 MS21042-6 (1) AN960-616 (1) AN960-616 (2 MAX.) A-4 NAS464P6LA16 MS21042-6 (1) AN960-616 (1) AN960-616 (2 MAX.) A-5 NAS464P6LA16 MS21042-6 (1) AN960-616 (1) AN960-616 (2 MAX.) B-1 4* NAS464P6LA15 H19300-6 (1) AN960-616L (1) K19301-63 * B-2 4* NAS464P6LA14 H19300-6 (1) AN960-616 (1) K19301-63 * B-3 4* NAS464P6LA14 H19300-6 (1) AN960-616 (1) K19301-63 * B-4 4* NAS464P6LA14 H19300-6 (1) AN960-616 (1) K19301-63 * B-5 4* NAS464P6LA14 H19300-6 (1) AN960-616 (1) K19301-63 * C-1 NAS464P5LA20 MS21042-5 (1) AN960-516L (1) AN960-516 (2 MAX.) C-2 NAS464P5LA20 MS21042-6 (1) AN960-616L (1) AN960-616 (2 MAX.) C-3 NAS464P5LA20 MS21042-6 (1) AN960-616L (1) AN960-616 (2 MAX.) C-4 NAS464P5LA20 MS21042-6 (1) AN960-616L (1) AN960-616 (2 MAX.) C-5 NAS464P5LA21 MS21042-6 (1) AN960-616L (1) 96352-3 3 * C-6 NAS464P5LA21 MS21042-5 (1) AN960-516L (1) 96352-2 3 * D-1 NAS464P5LA20 MS21042-5 (1) AN960-516L (1) AN960-516 (2 MAX.) D-2 NAS464P6LA20 MS21042-6 (1) AN960-616L (1) AN960-616 (2 MAX.) D-3 NAS464P6LA20 MS21042-6 (1) AN960-616L (1) AN960-616 (2 MAX.) D-4 NAS464P6LA20 MS21042-6 (1) AN960-616L (1) AN960-616 (2 MAX.) D-5 NAS464P6LA21 MS21042-6 (1) AN960-616L (1) 96352-3 3 * D-6 NAS464P6LA21 MS21042-5 (1) AN960-516L (1) 96352-2 3 *
NOTES 1. * TORQUE BOLT HEAD ON UPPER SPAR CAP & NUT ON LOWER SPAR CAP AS FOLLOWS: FOR A 5/16 BOLT - 205 - 225 IN. - LBS. FOR A 3/8 BOLT - 360 - 390 IN. - LBS. 2. * A MAXIMUM OF TWO AN960-616 OR TWO AN960-516 ON THE APPROPRIATE BOLT ARE ALLOWED UNDER THE SPECIAL WASHER.
D-1 B-1 D-5D-4D-3D-2 B-4B-3B-2 SKETCH D D-6 B-5
A296 B DC A
Figure 57-1. Wing Installation (cont)
57-40-00
Page 57-10
Issued: April 1, 1997
3E14
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.
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