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Operational Loads on Landing Gear.

N9128158

Publication Date	1990
Personal Author	Ladda, V.; Struck, H.
Page Count	16
Abstract	Prior statistics of airworthiness authorities indicate that landing gear (safe life design) often fail during scheduled aircraft service. Therefore investigations have been carried out during the last two decades in Germany with the aim of determining operational loads acting on the landing gear during service and defining the load cases which have to be taken into consideration for fatigue investigations related to landing gear and airframe. Statistics about failures on landing gear for civil and military aircraft and relevant load cases as well as information about essential fatigue requirements are presented. Some results of different landing gear load measurements are compared and discussed. These results, presented in form of cumulative frequency distributions for the taxiing and landing impact load cases, originate from the following measurements: Airbus A320; Airbus A310; Airbus A300; VFW 614; F-104 G. The impact of towing and push back operations on the nose landing gear using conventional and advanced towing methods is discussed. The primary results of the landing gear loads measurements are accentuated. Examples for the disposition of landing gear fatigue tests are considered, and essential future actions concerning load monitoring activities including hard- and overweight landing detection are reviewed.
Keywords	Aircraft reliability F-104 aircraft Failure Fatigue tests Impact loads Landing gear Landing loads Taxiing Airframes Civil aviation Frequency distribution Germany Towing Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	51C - Aircraft 51F - Test Facilities & Equipment 51B - Aeronautics
Corporate Authors	Deutsche Airbus G.m.b.H., Bremen (Germany, F.R.).; National Aeronautics and Space Administration, Washington, DC.
Supplemental Notes	In AGARD, Landing Gear Design Loads 16 p.
Document Type	Analytic Daughter
NTIS Issue Number	199123

Operational Loads on Landing Gear.

Operational Loads on Landing Gear.
N9128158

Publication Date	1990
Personal Author	Ladda, V.; Struck, H.
Page Count	16
Abstract	Prior statistics of airworthiness authorities indicate that landing gear (safe life design) often fail during scheduled aircraft service. Therefore investigations have been carried out during the last two decades in Germany with the aim of determining operational loads acting on the landing gear during service and defining the load cases which have to be taken into consideration for fatigue investigations related to landing gear and airframe. Statistics about failures on landing gear for civil and military aircraft and relevant load cases as well as information about essential fatigue requirements are presented. Some results of different landing gear load measurements are compared and discussed. These results, presented in form of cumulative frequency distributions for the taxiing and landing impact load cases, originate from the following measurements: Airbus A320; Airbus A310; Airbus A300; VFW 614; F-104 G. The impact of towing and push back operations on the nose landing gear using conventional and advanced towing methods is discussed. The primary results of the landing gear loads measurements are accentuated. Examples for the disposition of landing gear fatigue tests are considered, and essential future actions concerning load monitoring activities including hard- and overweight landing detection are reviewed.
Keywords	Aircraft reliability F-104 aircraft Failure Fatigue tests Impact loads Landing gear Landing loads Taxiing Airframes Civil aviation Frequency distribution Germany Towing Foreign technology
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	51C - Aircraft 51F - Test Facilities & Equipment 51B - Aeronautics
Corporate Authors	Deutsche Airbus G.m.b.H., Bremen (Germany, F.R.).; National Aeronautics and Space Administration, Washington, DC.
Supplemental Notes	In AGARD, Landing Gear Design Loads 16 p.
Document Type	Analytic Daughter
NTIS Issue Number	199123