Piper PA-34-200T Seneca II, Service Manual

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PIPER SENECA II SERVICE MANUAL
01/01/09 IV - STRUCTURES
1D13
SECTION IV
STRUCTURES
4-1. INTRODUCTION.
This section explains the removal and installation procedures for the structural surfaces of the airplane.
For the removal, installation, and rigging and adjustment procedures of the controlling components of
the various structural surfaces, refer to Section V.
NOTE: When torquing structural assemblies, standard torque values are to be used as found in Section
II or the latest revision of FAA Advisory Circular 43.13-1, unless otherwise stated in this
section.
4-2. DESCRIPTION.
The PA-34-200T is an all metal semi-monocoque structure with an overall length of 28 feet 7.5 inches.
The fuselage is constructed of bulkheads, stringers and stiffeners, to which all of the outer skin is riveted.
Windows include a single pane windshield and eight side windows; all windows are single pane. A storm
window is located in the forward lower section of the left window and can be opened inward when the
latch is released. The cabin entrance door is located on the right side of the fuselage, above the wing, and
is equipped with a safety latch on the top of the door which can be operated from the inside or outside. A
door provided for entrance to the aft passenger compartment is located just aft of the left wing.
Each wing panel is an all metal, full cantilever semi-monocoque type construction with a removable
fiberglass or thermoplastic tip. Installed in each wing ahead of the main spar are two metal fuel tanks
with a capacity of 24.5 U.S. gallons each or 49.0 U.S. gallons total per wing. Attached to each wing is an
aileron, flap, main landing gear and power plant. The wings are attached to each side of the fuselage by
inserting the butt ends of the main spars into a spar box carry-through. The spar box is an integral part of
the fuselage structure which provides, in effect, a continuous main spar with splices at each side of the
fuselage. There are also fore and aft attachments at the front and rear spars.
The all metal empennage group is a full cantilever design consisting of a vertical stabilizer (fin), rudder
and stabilator, all with removable fiberglass or thermoplastic tips. The rudder and stabilator have trim
tabs attached that are controllable from the cockpit. The stabilator also incorporates one channel main
spar that runs the full length of the stabilator and hinges to the aft bulkhead assembly of the fuselage. All
exterior surfaces are coated with enamel or acrylic lacquer. As an option, the airplane may be completely
primed with zinc chromate.
4-2a. STANDARD PRACTICES.
4-2b. REMOVAL OF CHERRYLOCK RIVETS. (Refer to Figure 4-1.)
If necessity requires the removal of a cherry lock rivet, proceed as follows:
a. In thick material remove the lock by driving out the rivet stem, using a tapered steel drift pin. (See
View l.)
NOTE: Do not drill completely through the rivet sleeve to remove a rivet as this will tend to enlarge the
hole.