57-50-00 Page 57-14 Issued: April 1, 1997
3E18
D F CE G ABBC
A322 SKETCH A AN3-13A AN960-10 MS20365-1032C 63900-20 (2 REQ.) SKETCH B AN3-11A AN960-10 MS20365-1032C 63900-19 (2 REQ.) 2 REQ. A322
A288 WING HINGE AILERON HINGE A288
SKETCH C AN3-7A AN960-10 (3 REQ.) 2 REQ UNDER NUT MS20365-1032C AILERON HINGE SKETCH D AN3-7A AN960-10 (3 REQ.) 2 REQ UNDER NUT MS20365-1032C WING HINGE
Figure 57-2. Aileron and Flap Installation
3E19 57-50-00 Page 57-15 Issued: April 1, 1997
A380 A381 AN3-11A AN960-10L MS20365-1032C
SKETCH E SKETCH F
A313
BOLT AN23-18
NUT AN310-3
WASHER AN960-10
COTTER PIN
MS24665-132
SKETCH G
Figure 57-2. Aileron and Flap Installation (cont)
57-50-00 Page 57-16 Issued: April 1, 1997 3E20
BALANCING EQUIPMENT AND PROCEDURE. (Refer to Figure 57-3.)
The balancing must be done using a suitable tool capable of measuring unbalance in inch-pounds from the hinge pin center line of the control surface. A suggested tool configuration is shown in Chapter 91 . Other tool configurations may be used, provided accuracy is maintained and recalibration capability is provided. The tool shown in Figure 57-3 is calibrated by placing it on the control surface to be balanced with the balance points over the control surface hinge center line and the balance bar parallel to the cord line. Position the trailing edge support to align the tool with the control surface cord line and secure in this position. Remove the tool without disturbing the trailing edge support and balance the tool by adding weight to the light end as required. (The movable weight must be at the center line of the bar.) Place the tool on the control surface perpendicular to the hinge center line as shown in Figure 57-3. Read scale when the bubble level has been centered by adjustment of the movable weight and determine the static balance. If the static balance is not within the limits specified. proceed as follows:
1.
Leading Edge Heavy: This condition is highly improbable; recheck measurements and calculations.
2.
Trailing Edge Heavy: There are no provisions for adding weight to balance weight to counteract a trailing edge heavy condition; therefore, it will be necessary to determine the exact cause of the unbalance. If the aileron is too heavy because of painting over old paint, it will be necessary to strip all paint from the aileron and repaint. If the aileron is too heavy resulting from repair to the skin or ribs, it will be necessary to replace all damaged parts and recheck the balance.
57-50-00 Page 57-17 Issued: April 1, 1997
AILERON SKIN REPAIR.
1. Repair of minor cracks in PA-44-180 aileron skin surfaces is authorized, but limited as follows:
a.
cracks of no more that 0.5 inch at the ends of the skin stiffening beads;
b.
no more than two cracks per surface side;
c.
cracks are limited to either end of a bead (refer to Figure 57-4), but not on the same bead;
d.
for wrap-around skins, two crack repairs are acceptable per side, but repairs may not be opposite to one another on opposite sides (i.e. - top and bottom).
2. Proceed as follows:
a.
only cracks confined to the bead end area shown in Figure 57-4 may be repaired;
b.
cracks 0.5 inch long or less may be repaired by stop drilling;
c.
stop drill the extreme ends of the crack with a #50 (0.070) drill.
— Note —
Cracks stop drilled once cannot be stop drilled again, should crack grouwth continue.
57-50-00 Page 57-18 Issued: April 1, 1997
3E22
WING FLAP.
REMOVAL OF WING FLAP. (Refer to Figure 57-2.)
1.
Extend the flaps to their fullest degree and remove the bolt and bushing from the rod end bearing by use of an angle or offset screwdriver.
2.
Remove the nuts, washers, bushing, and hinge bolts that hold the flap to the wing assembly.
3.
Pull the nap straight back off the wing.
INSTALLATION OF WING FLAP. (Refer to Figure 57-2.)
1.
Replace the wing flap by placing the flap into its proper position and inserting the hinge bolts, bushings, washers and nuts.
2.
With the flap control in the full flap position, place the bushing on the outboard side of the rod end bearing and insert and tighten the bolt.
3. 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(55)
