Cessna tail-cone reinforcement angle splice, installation kit, and method for installation thereof
A tail-cone reinforcement angle of a Cessna 180-185 series aircraft is repaired by the removal of an aft most section of that tail-cone reinforcement angle and its replacement with an elongated splice body. The elongated splice body is attached to the remainder of the tail-cone reinforcement angle and to the tail-cone portion of the fuselage of the aircraft. The aft section of the original tail-cone reinforcement angle is subject to the development and propagation of cracks in the area of the rear pivot shaft receiving bore, which cracks render the aircraft unfit for use. The invention includes the provision of a suitable elongated splice body, a method for its installation, and a tool kit which is usable in accomplishing the removal and replacement of the aft section of the tail-cone reinforcement angle.
1. A tail-cone reinforcement angle splice configured for use with a tail-cone reinforcement angle and to replace a defective aft section of a rear blade portion of the tail-cone reinforcement angle for a tail cone section of a fuselage of a Cessna 180-185 series aircraft, the tail-cone reinforcement angle splice comprising:
an elongated splice body having a plurality of splice body sections;
a forward, overlap section of the elongated splice body and forming a first one of the plurality of elongated splice body sections, the forward, overlap section having a first thickness in a direction transverse to a length of the elongated splice body and being configured for overlapping attachment to the rear blade portion of the tail-cone reinforcement angle whose defective aft section has been removed;
a central, transition section of the elongated splice body and forming a second one of the plurality of splice body sections and having a second thickness in the direction transverse to the length of the elongated splice body; and
an aft, stabilizer pivot shaft receiving section of the elongated splice body and forming a third one of the plurality of splice body sections and configured to receive a stabilizer pivot shaft receiving bore, the aft, stabilizer pivot shaft receiving section being inclined at an acute angle, with respect to the first and second sections of the elongated splice body, to accommodate an inward curve of the tail-cone section of the aircraft fuselage.
2. The tail-cone reinforcement angle splice of claim 1 wherein the elongated splice body is generally rectangular.
3. The tail-cone reinforcement angle splice of claim 1 wherein the central, transition section of the elongated splice body includes at least first and second transition section rivet and bolt receiving holes.
4. The tail-cone reinforcement angle splice of claim 1 wherein the elongated splice body is aluminum.
5. The tail-cone reinforcement angel splice of claim 1 wherein the first thickness and the second thickness are different from each other.
6. The tail-cone reinforcement angle splice of claim 1 wherein the aft, stabilizer pivot shaft receiving section has a third thickness in the direction transverse to the length of the elongated spice body and wherein the third thickness is the same as the first thickness.
7. The tail-cone reinforcement angle splice of claim 1 wherein the elongated splice body is configured to receive a plurality of rivet and bolt receiving bores.
8. The tail-cone reinforcement angle splice of claim 7 wherein at least three of the rivet and bolt receiving bores are located in the forward, overlap section of the elongated splice body.
9. The tail-cone reinforcement angle splice of claim 1 wherein the central, transition section of the elongated splice body includes an upper surface including an intermediate step.
10. The tail-cone reinforcement angle splice of claim 9 wherein the intermediate step forms a transition between the forward, overlap section of the elongated splice body and the central, transition section of the elongated splice body.