MH-60 SLAP
Abstract
The MH-60 Service Life Assessment Program (SLAP) is assessing the primary aircraft structure and subsystem condition of the MH-60S fleet in order to determine what efforts are necessary to extend the aircraft design life limits to allow it to meet Chief of Naval Operations (CNO) operational inventory requirements to bridge to a follow-on program procurement. The highest flight time MH-60S helicopters are expected to exceed the currently assumed design life limit of 10,000 flight hours in 2025, at which time as many as 30 aircraft per year could be downed without a SLAP and Service Life Extension Program (SLEP) established in FY 2018. The MH-60S has experienced significant structural issues since Initial Operational Capability in August 2002, resulting in downed aircraft and additional inspections for the operational fleet. Similar issues could very well precede the 10,000 flight hour life limit, particularly without the insight provided by a SLAP effort commenced as soon as possible. The goal of the MH-60S SLAP program is to identify critical structures, components, and subsystems that can achieve the extended service life limit goals. The initial efforts of the MH-60S SLAP is to assess the primary aircraft structure and subsystem condition of the MH-60S fleet in order to determine what efforts are necessary to validate the currently assumed design life limit of 10,000 hours and potentially extend the aircraft life limit. The MH-60 SLAP is comprised of three distinct assessments: Fatigue Life Assessment (FLA),which will establish the fatigue life of the aircraft and air vehicle systems; Subsystem Life Assessment (SLA), which will determine subsystem components that are critical to safe flight and ground operations and identify safety risk and risk mitigation strategies for critical components; and the Dynamic Component Re-life Assessment (DRLA), which recalculates and establishes life limits for preselected MH-60 dynamic components. FLA consists of structural investigations of the cockpit beams, main gearbox beams/frames, upper deck, engine mount, lower tub, main landing gear, tail landing gear, cargo hook, transition splice and tie-down fittings/structure, tailcone, tail gearbox, intermediate gearbox, stabilator, manufactured joints/splices, and flight controls support structure. SLA will evaluate engine start and engine inlet anti-ice, rotor brake, hydraulic, flight controls, etc, to identify over-and-above inspections, overhaul intervals or replacement schedules to fly beyond the current design limit assumption. FY 2018 budget request funds the completion of external loads analysis, continuation of fatigue analysis, service life risk assessments of aircraft subsystems, and development of initial dispositions for safety critical items. This initial analysis, assessment and disposition will be further refined throughout the SLAP effort, augmented with specific system teardown, inspection and test, culminating in a follow-on Service Life Extension Program (SLEP), which will design and implement the solutions resulting from the SLAP findings.
Document Details
- Document Type
- Project
- Publication Date
- Oct 01, 2018
- Source ID
- 3384_0702207N_7_1319_PB_2018
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