Method, implemented in part by a computer including a processor, a user graphical interface and a storage device, of analyzing structural damage to an aircraft, the method comprising: using the user graphical interface for inputting data related to structural damage; with the processor, suggesting a damage disposition by: with the processor, analyzing the inputted structural damage data and suggesting a damage disposition based on the analying, which includes automatically comparing the input damage data with predetermined limits specified in an Structural Repair Manual associated with the aircraft; and in case the user deems it necessary, with the processor performing a specific structural analysis for the damage considering plural parameters including at least one of damages type, geometry and dimensions of damaged areas, material parameters, and structural loads and suggesting a thereby improved damage disposition; wherein said structural analysis includes at least one of static, fatigue and damage tolerance structural analysis; said damage disposition includes defining categories as allowable damage, fly-by damage allowed only for a specific period, temporary repair, permanent repair and/or contacting the aircraft manufacturer for specific disposition; and automatically, with the processor, a user is enabled to to manage structural damage, repairs and maintenance information. using the user graphical interface for inputting data related to structural damage; with the processor, suggesting a damage disposition by: with the processor, analyzing the inputted structural damage data and suggesting a damage disposition based on the analying, which includes automatically comparing the input damage data with predetermined limits specified in an Structural Repair Manual associated with the aircraft; and in case the user deems it necessary, with the processor performing a specific structural analysis for the damage considering plural parameters including at least one of damages type, geometry and dimensions of damaged areas, material parameters, and structural loads and suggesting a thereby improved damage disposition; with the processor, analyzing the inputted structural damage data and suggesting a damage disposition based on the analying, which includes automatically comparing the input damage data with predetermined limits specified in an Structural Repair Manual associated with the aircraft; and in case the user deems it necessary, with the processor performing a specific structural analysis for the damage considering plural parameters including at least one of damages type, geometry and dimensions of damaged areas, material parameters, and structural loads and suggesting a thereby improved damage disposition; wherein said structural analysis includes at least one of static, fatigue and damage tolerance structural analysis; said damage disposition includes defining categories as allowable damage, fly-by damage allowed only for a specific period, temporary repair, permanent repair and/or contacting the aircraft manufacturer for specific disposition; and automatically, with the processor, a user is enabled to to manage structural damage, repairs and maintenance information. said structural analysis includes at least one of static, fatigue and damage tolerance structural analysis; said damage disposition includes defining categories as allowable damage, fly-by damage allowed only for a specific period, temporary repair, permanent repair and/or contacting the aircraft manufacturer for specific disposition; and automatically, with the processor, a user is enabled to to manage structural damage, repairs and maintenance information.