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a)  repairs involving a principal component of the aircraft structure, such as a frame, stringer, rib, spar of stressed skin;
b)  repairs to structural elements that were approved using damage tolerance or fail-safe evaluation;
c)  repairs to pressurized areas; d) repairs involving the installation of an item of mass necessitating structural re-evaluation; e) repairs to structural attach points intended for the stowage or retention of significant mass; f) repairs to load bearing structure of aircraft seats, harnesses, or to occupant restraint
equipment;
g)  repairs involving substitution of materials, or use of a different repair process or technique; or
h)  repairs to components, parts, appliances where form, fit, and function may be affected.
6.3.3 Minor repair category
A minor repair involves any repair that does not fall under the major repair category, meaning the repair has a negligible effect on the airworthiness of the affected product.
6.4 Approval activities
6.4.1 General
6.4.1.1   There are four key activities in the approval of a repair design, namely:
a) establishing an approval basis;
b) establishing the means or methods of compliance;
c) demonstration and findings of compliance; and
d) approving the repair design.

6.4.1.2  The main objective of the approval process is for a State of Registry to determine compliance of a proposed repair design with its applicable airworthiness requirements, such that the affected aeronautical product is restored to its approved type design.
6.4.2 Establishing an approval basis
6.4.2.1  Annex 8, Part II, Chapter 1, Type Certification, states in part that the basis of approval for a repair design should be the same airworthiness standards used in the certification of the type design by the State of Registry. The following should be the basic policy for repairs, unless otherwise established differently by a State of Registry:
a)  for an aircraft, the approval basis is the aircraft design standards recorded in the Type Certificate data sheet issued by the State of Registry or, where allowed, by the State of Design.
b)  for an engine or propeller, the approval basis is the engine or propeller design standards recorded in the Type Certificate data sheet issued by a State of Registry or, where allowed, by the State of Design of the engine or propeller. It is not the State of Design of the aircraft on which the engine or propeller is installed that applies.
c)  for a component, part, appliance or article that is not type certificated or have a separate design approval other than a Type Certificate, the approval basis is the airworthiness standard of the type certificated product (aircraft, engine, or propeller) on which the component, part, appliance or article is installed.
6.4.2.2  The approval basis for a repair design shall not include any proposal for an exemption or a finding of equivalent level of safety because a repair is a restoration to an approved type design. The intent of the repair is to maintain the same level of safety that the product was certified to.
6.4.2.3 The approval basis could be also be affected by additional requirements that are not related to the original approval or type certification of the product. For example, a supplemental structural integrity programme or a repair assessment programme for ageing aircraft may influence repair designs to be held to higher design standards or evaluation techniques. In establishing the approval basis, a State of Registry should also account for other factors, such as maintenance or operating rules, which may affect the actual installation of the repair.
6.4.3  Establishing the means of compliance
The means of compliance is usually dictated by the design standard(s) in the approval basis for which compliance will be demonstrated, and generally falls into one or any combination of the following:
　
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