COWLING.
REMOVAL OF ENGINE COWLING.
1. Release the cowl fasteners, two on each side of the cowl.
2. Lift the aft end of the cowl and then slide it forward to release the two stud type front fasteners.
Remove the top cowl.
3. Disconnect the landing light lead at the quick disconnect at the left rear side of the bottom cowl.
4. Disconnect the nose gear door rods by removing the nuts, washers and bolts.
5. Remove the screws securing the bottom cowl at its aft end. Remove the bottom cowl.
INSTALLATION OF BUSHINGS AND PINS FOR FIBERGLAS TYPE COWLINGS.
a. With cowlings removed, locate bushings on lower cowling. (See Figure 71-4.)
b. Using snap ring pliers, remove snap ring and old bushing.
c. Install new bushing and new snap ring.
NOTE
Bushings should be inspected each 100 hours and should be
replaced upon condition, but no later than 500 hours time in
service.
d. Locate pins in upper cowling.
NOTE
It should not be necessary to replace the pins unless bushing in
lower cowling has worn enough to allow damage to the pin. Any
noticeable notching or cutting of the pin requires replacement.
e. If it is necessary to remove the pins, appropriate tools should be used to remove the fiberglas resin
from around the pin and plate assembly. (A template or adequate measurements should be made to assure
proper alignment of the new pin and plate assembly.)
f. Remove pin and plate assembly
g. To install new pin and plate assembly it will be necessary to prepare the fiberglas surface to accept the
new plate. (See FIBERGLAS REPAIRS, Chapter 51.)
1. Clean area as required, and roughen.
2. Prepare cowling surface by applying resin. Do not allow to harden.
3. Install plate and pin.
4. Lay in a layer of resin impregnated fiberglas cloth over the plate and surrounding fiberglas. (Use
template or measurements from step e to assure alignment.) Allow to cure.
CLEANING, INSPECTION AND REPAIR OF ENGINE COWLING.
1. The cowl should be cleaned with a suitable solvent and then wiped with a clean cloth.
2. Inspect the cowling for dents, cracks, loose rivets, damaged or missing fasteners, and damaged
fiberglass areas.
3. Repair all defects to prevent further damage.
Effectivity 71-20-01
PA-28RT-201 Page 71-21
Interim Revision: February 27, 1995
3C10
PIPER AIRCRAFT
PA-28RT-201 / 201T
MAINTENANCE MANUAL
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