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Hard Landing confirmed: Maintenance inspection
Inspection is divided in different phases
•
Phase 1: general inspection for primary damage and indication of remote damage (mainly external)
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If damage = perform further inspection (phase 2) and required maintenance actions.
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If no damage = end of inspection
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No damage = Aircraft can temporarily return to service
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Grace period (e.g. 30 days or 100 - 200 cycles)
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Waiting for further elaborated analysis of the event by Airbus

Required structural strength is maintained

Risk is only stress corrosion (e.g. gear not achieving full life)
© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Avoiding Hard Landings - 15th Performance & Operations conference April 2007
Identification of Hard Landing
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Pilot: Subjective judgment
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Maintenance: Objective but incomplete data
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Maintenance system only covers straightforward hard landing events
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Rebounds, drift landing, landing with roll and high derotation on nose landing gear are not addressed by the current logic

Pilot should provide additional information on landing conditions
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Cockpit instrument indications, aircraft weight, quantity of fuel in each tank
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If the touchdown was on main gears or on main and nose gears, or fast derotation of the nose gear.
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If the landing was straight, drifting, unsymmetrical, bounced,
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If the crew heard a noise possibly related to a structural failure
© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Avoiding Hard Landings - 15th Performance & Operations conference April 2007
Identification of Hard Landing: New problem
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The pilots’ perception judgment and reporting has proven to be effective
•
However, the perception of the severity of the landing is not so obvious for:

Long aircraft

Flexible aircraft

Complex landing gear system
© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Avoiding Hard Landings - 15th Performance & Operations conference April 2007
Future: Hard Landing Detector
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Design of new automatic self-reliant system with specific sensors and adapted high synchronized sampling rate
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This future system should

Provide a rapid and direct “Go” OR “No Go and inspect” decision for all circumstances

Indicate which part of the aircraft has been impacted and to which level
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Medium term (during development of this self-reliant system)
　
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