This document provides supplemental information to the applicable manual.

This paragraph describes the procedures to calculate weight and moment for various phases of a planned flight and to ensure that the center of gravity is within approved limits.

Explain how to maintain this record when changes to the weight or moments of the airplane are made so that accurate starting data is available to calculate the weight and C.G. during normal operation of the airplane.

INSPECTION PROCEDURE sets forth the inspection procedure(s) to be utilized, such as magnetic particle, visual, etc, and may reference another document for the actual procedure, such as a nondestructive testing manual.

A review of test results applicable to the design was made. The loading conditions together with the resulting margins of safety were evaluated. The resulting data were used to determine if the component should be considered for incorporation into the CAP.

The effects of corrosion have not been considered in the rationale in selecting inspection times or in the effects on the fatigue stresses. It is very difficult to determine the effects of corrosion but, as the reports from the CAP inspections are received, the inspection times will be adjusted for any severe problems.

High-time airplanes, disassembled for major overhaul, were inspected to assist in selecting inspection items. Other high-time airplanes’ special Continuing Airworthiness Program Inspection results supplement these inspections.

In addition to understanding FAA Advisory Circulars AC 91-60 and AC 91-56, familiarity with GAMA Specification No.2, Manufacturers Maintenance Data and Air Transport Association of America Specification No.100, Specification for Manufacturers Technical Data, will aid in the preparation of a CAP for a specific airplane.

The Continuing Airworthiness Program Inspection Document (CAP) is inspection data that, when combined with the operator’s existing maintenance program, will help maintain the structural integrity and continued airworthiness of the ABC XXX Series airplanes.

REPAIR/MODIFICATION sets forth repair or modification instructions and may refer to a standard repair in another document or a special repair or modification defined elsewhere, such as in a service kit, service bulletin, etc.

SIGNIFICANT INSPECTION CONDITION (detectable crack size, wear limits, corrosion condition, ctc.) specifies, for a crack inspection, the minimum size crack expected to be discovered. Specifies, for other inspection conditions, the wear limits, corrosion pit depth. etc.