Perform structural substantiation assessment of modified pylon box structure by using unmodified pylon torque box structural substantiation assessment as the starting base line. - aero loads shall…

Perform structural substantiation assessment of modified pylon box structure by using unmodified pylon torque box structural substantiation assessment as the starting base line. - aero loads shall be computed at each combination of airspeed and load factor on and within the boundaries of the giii design maneuvering envelope (v-n diagram). - maneuvering, flaps up and flaps down, and gust envelopes shall be computed at both maximum and minimum aircraft weights. - IT is desired that the design envelope of the modified aircraft shall be shown to be outside the existing g-III flight envelope. - increases in maximum achievable YAW angles that may result from any destabilizing effects created by the POD/modified pylon shall be considered in YAW loads analysis and resulting aircraft speed limitations (e.g. VMA, and VMC). - changes in aero loads on various parts of the aircraft due to POD and modified pylon shall be computed. - the critical inertia loads shall be computed using the most critical aircraft and POD weight and CG locations. - the most critical case inertia loads shall also encompass ground loads. - the critical inertia loads shall be at least equal to the giii design inertia loads due to maneuvering, gusts, and ground loads. - show by analysis that modified pylon, new aircraft parts, and new aircraft load paths have a design factor of safety that is at least: - without proof test: 2.25 for metallic structure 3.0 for composite structure. - show analysis that establishes the design limit loads of the aircraft attach points. - analysis showing that the margin of safety is greater than or equal to zero. - analysis showing that an additional joint or fitting factor of 1.2 is used on all joints and fittings where failure of one fastener, pin or lug could result in loss of a component, or any major portion thereof (DHB-r-006 7.3.2.2). - stress due to temperature variation shall be combined with the appropriate inertial and aero loads. - damage tolerance & fatigue evaluation must include a determination of the probable locations and modes of damage due to fatigue, corrosion, or accidental damage.