Marking and Recording of Inspection Results. Mark and record as required by paragraph 1.3.
Backup Method. None required.
4.6.5 System Securing. If removed, the cabin equipment support structures require installation in accordance with the
applicable technical manuals listed in Table 1-1. Secure any access panels that were used.
4.7.1 Description (Figure 4-1, Index No.7). The pods are located on each side of the fuselage system containing the
fuel tanks. The forward end of each pod contains components of the electronic and electrical systems. A hinged panel
in each pod provides access to the forward landing gear.
4.7.2 Defects. Void damage may occur on any area of the skin/honeycomb structure. The primary purpose of this
inspection is to verify void indications found visually.
A void is defined as an unbonded area that is supposed to be bonded. Many sub-definitions of
voids are given such as lack of adhesive, gas pocket, misfit, etc. However, this manual makes no
distinction among these, grouping them all under one general term (void").
Primary Method. Bond Testing.
a. Bond Test Unit
d. Cable Assembly
e. Test Block, metal honeycomb with skin thickness closest to that of the panel to be inspected.
Test Block, Composite Defect Standard #1
g. Test Block, Composite Defect Standard #3
Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance. Partial inspection
for cause (visual indications, sites of mechanical damage, corrosion, etc.) may be performed on all exposed surfaces of
the installed part using this procedure. If required, the pods shall be removed in accordance with applicable technical