IN Brief:
- The US Navy has ordered a Power Margin Increment Two main-rotor-blade development programme.
- Design, integration, ground work, and flight qualification will be led from Sikorsky’s Stratford operation.
- The improved blade is intended to increase VH-92A power margin and aircraft performance.
Sikorsky has received a $107.3 million US Navy order to design, integrate, test, and qualify an improved main rotor blade for the VH-92A presidential helicopter. The effort, known as Power Margin Increment Two, is intended to increase the aircraft’s available power margin and improve performance rather than replace the helicopter or its propulsion system.
Work will be concentrated in Stratford, Connecticut, which accounts for 72 per cent of the programme. West Palm Beach, Florida, will carry 25 per cent, Fort Worth, Texas, two per cent, and King of Prussia, Pennsylvania, one per cent. Completion is scheduled for March 2031, giving Sikorsky almost five years to complete design, integration, testing, and qualification.
The Navy has initially obligated $18.4 million in fiscal 2026 research, development, test, and evaluation funding. The order was not competed. No blade geometry, material, manufacturing process, weight change, or quantified performance target has been published.
Power margin is the difference between the power available from an aircraft’s engines and transmission and the power required for a given flight condition. On a helicopter, that reserve can be affected by weight, temperature, altitude, manoeuvre, and the aerodynamic efficiency of the rotor system. Improving the main rotor blade can increase lift or reduce the power needed to produce it, but the benefit has to be demonstrated across the approved operating envelope.
The VH-92A is based on the Sikorsky S-92 and is configured to transport the US president, vice-president, heads of state, and other official parties. The programme integrated government mission systems into a commercial-derived helicopter while retaining Federal Aviation Administration airworthiness considerations. The final aircraft in the 23-strong production programme was delivered in 2024, shifting attention towards sustainment, modification, and performance improvement across the completed fleet.
Changing a main rotor blade after production is not a simple component substitution. The blade affects loads, vibration, handling qualities, rotor balance, fatigue life, transmission demand, and interaction with the flight-control system. An improved design must be compatible with the hub and aircraft structure, manufacturable to tight tolerances, inspectable in service, and supportable over the remaining life of the fleet.
The extended schedule reflects the assurance burden attached to a rotor-system change. A qualification programme normally requires analytical models, test articles, structural and fatigue work, aircraft integration, and flight evidence across relevant conditions. The data must show that the new blade delivers the intended margin without introducing unacceptable vibration, maintenance, or handling effects.
The contract assigns 72 per cent of the work to Stratford, 25 per cent to West Palm Beach, two per cent to Fort Worth, and one per cent to King of Prussia. It does not attribute specific engineering, manufacturing, or test tasks to those locations.
The programme is an example of how a relatively small fleet can generate substantial engineering work after delivery. Presidential transport aircraft have specialised communications, interiors, security equipment, and operating requirements that add weight and constrain modification. Performance improvements must fit around those systems and remain supportable without disrupting availability across a fleet with little spare capacity.
No installation timetable has been published, and the March 2031 date covers development and qualification rather than confirmation that every VH-92A will receive the new blade. A later retrofit decision may depend on test results, production planning, and fleet maintenance schedules. The present order establishes the engineering route to an improved rotor system and funds the evidence needed to qualify it.
Manufacturing a redesigned blade also demands process qualification. Whatever material system and construction method are selected, the process must control geometry, mass balance, bonding, surface finish, and inspection to a repeatable standard. The Navy has not confirmed the materials or manufacturing route for the new blade, so the contract cannot support assumptions about a particular technology. It does establish that production evidence will have to accompany aerodynamic performance before the design can enter fleet use.
Sustainment planning will follow the qualification work. New blades would need spares, repair limits, inspection criteria, technical publications, and trained maintainers before fleet introduction. Those through-life products are not itemised in the notice, but a rotor-blade improvement cannot remain supportable if the qualification evidence is separated from the maintenance system that follows it.
Blade qualification will also have to connect the engineering definition to a repeatable production process. Test articles and eventual fleet hardware must match closely enough for structural, aerodynamic, and fatigue evidence to remain valid. Tooling, inspection methods, material controls, and repair limits will therefore be developed alongside the blade rather than added after flight testing.
