Malta Helicopter RFP FK Draft Dec 2011.docx

Technical Requirements for the Acquisition of a Rotary Wing Aircraft

1.0 Introduction

The United States Government, seeks to acquire by September 2012, one used rotary-wing aircraft suitable for land and sea operations in a maritime environment. The aircraft should be capable of conducting the Search and Rescue (SAR), Maritime Patrol, Medical Evacuation (MEDEVAC), Maritime Interdiction Operations (MIO), Light Vertical Replenishment (VERTREP), VIP Transport, and general utility missions.

2.0 General Characteristics

The aircraft must comply with the following general specifications:

Multi-engine and engine start without ground support equipment is required.

Two person-crew / cockpit with dual-controls.

Aircraft capable of flight in Instrument Meteorological Conditions (EASA/ICAO IFR).

Single main rotor and anti-torque tail-rotor.

· Optimized for the maritime operating environment (Marinized airframe). Airframe components and metal body parts are to be anti-corrosion treated and paint coated for operation in environments of high saline content.

Separate compartment with sliding cargo doors on both sides of the fuselage.

Armament: floor attachment that makes it possible to install a removable light machine gun (7.62mm) door pintle mount.

3.0 Minimum Technical Requirements

· Maximum take-off weight shall not exceed 5.5 tons.

· Speed: Minimum Cruising speed as per aircraft design altitude and International Standard Atmosphere (ISA) conditions.

· Endurance: Not less than 3 hours (not including IFR reserves) at 100 knots at 2,500 feet. The aircraft must be able to operate in temperatures ranging from -20° C to + 50° C at sea level and humidity levels of 5% to 95% without performance degradation.

· External floodlight (70,000 lumens) with cockpit control.

· Integral external tie-downs for use during ship-borne operations

· Rotor:

· Main rotor: Hub height not less than 3m; no maximum height requirement.

· Tail rotor: Fenestron design not less than 1.5 meters measured from blade tip to the ground when vertically aligned downwards.

A system status/fault management system that provides continuous built in test to inform the crew of status of flight critical avionics equipment during flight.

· Overall length shall not be more than 17.5m, due to flight deck limitations.

· Rescue Hoist: Rating not less than 200 kgs.

· Preferably mounted on the Starboard side of fuselage

· Hoist control to be preferably in the cabin on the 1st pilot side and with an incorporated cable cutter normally operated by the 1st pilot. Emergency jettison control in cockpit is a requirement.

· Sliding cabin doors on both sides of fuselage. Door opening capable of accommodating Stokes-type litter with floatation devices.

· Both doors can be left open up to a minimum speed of 60kts at 2,500 feet without performance degradation.

· Cockpit and Cabin lighting is NVG compatible.

· Communication/Navigation Systems: Nominal cockpit instrumentation, communication and navigation suite should include the following articles or articles from other manufacturers that provide similar or greater operational capability:

· AUTOPILOT SYSTEM – 3 AXIS SFIM 155D

· 2 x VHF COMM KTR 908

· 2 X VOR / ILS KNR 634A

· 2 x VHF/FM NAT NPX138

· ADF KDF 806

· DME KDM 706A

· 3 x ICS TEAM TB31

· TRANSPONDER KXP 756

· RADIOALTIMETER - AHV16

· WEATHER RADAR BENDIX 1400C

· GPS – TRIMBLE 2100 T

· ELT – KANNAD 406 AF

· UNDERWATER BEACON DK 100

· COCKPIT VOICE RECORDER (Fairchild 100A)

· Aircraft flotation system such as the Marotta system or the normal emergency flotation gear that aircrafts are equipped with when operating over the water

· Landing Gear: Tricycle, preferably retractable landing gear complete with the nose wheel locking device.

· Cabin configurations for specific operations (changes to be made by crew in one hour or less):

· SAR configuration– (seated survivors) Seated (crashworthy seats c/w 5-point inertial harness) Pilot Co-Pilot Flight Technician 2 x Rescue Swimmers (Seated on web seats with 2 point restraints) 3 x survivors (Seated on web seats or floor with 2 point restraints)

· SAR – (survivor in Stokes-type litter with floats and multiple attachment points) Seated (crashworthy seats c/w 5-point inertial harness) Pilot Co-Pilot Flight Technician

· Medical Transport Seated (crashworthy seats c/w 5-point inertial harness) Pilot Co-Pilot Flight Technician 2 x Medical Personnel (Seated on web seats or floor with 2 point restraints) 1 x patient: In litter (on secured litter mount)

· Utility Seated (crashworthy seats c/w 5-point inertial harness) Pilot Co-Pilot Flight Technician 6 x personnel in webbing and with personal weapons; Seated on web seats or floor with 2 point restraints

· VIP

Seated (crashworthy seats c/w 5-point inertial harness) Pilot Co-Pilot Flight Technician 4 x VIPs (crashworthy seats with 2 point-point restraints) May be accommodated in removable passenger seats. Web seats are not acceptable for this requirement.

4.0 Additional Desired Technical Requirements:

· Single Engine operation as per "European Aviation Safety Agency Certification Specifications for Large Rotorcraft CS29 Amendment 2, 17 November 2008, Annex to ED Decision 2008/010/R Amendment ."

· Rescue Hoist capacity exceeds 200kgs.

· Minimum Cruising Speed exceeding 120kts at 2,500 feet.

· Cargo Hook: Aircraft will be structurally modified to utilize cargo sling attachment (to be included) to carry underslung loads (the European version of Vertical Replenishment "VERTREP"). Cockpit controls are not obligatory (depending on type), and are separate from rescue hoist. There is no minimum acceptable weight limit.

· Helicopter Rope Suspension System installed including cockpit controls for emergency jettison.

· Cockpit configured for single pilot IFR operation.

· Corrosion Resistant Materials optimized throughout aircraft.

· FLIR EO/IR with appropriate controls and displays for cockpit configuration.

· Cockpit voice recorder.

· Flight data recorder.

· Main Rotor Folding capability desired mainly for shipborne operations. Folding to occur at the blade grips (manually).

· Cabin Climate Control to maintain cockpit at 72 degrees F throughout the aircraft operating envelope.

· Color Scheme –

· Fuselage – Low Infrared two tone Grey (RAL 7004/RAL 7407).

· Black where applicable (RAL 9005).

· Fuel tanks have self-sealing/anti-explosive capability.

· Warranty: 12 month warranty.

5.0 Documentation and Certification Requirements

The vendor shall comply with the following additional requirements, to include documentation and certification:

The aircraft offered must be fully operational at the time of delivery.

Aircraft shall have European Aviation Safety Administration (EASA) certification and all applicable registration, airworthiness, and maintenance documentation to include:

· Aircraft operating and flight manuals in the English language

· Aircraft maintenance records

· Current weight and balance report

· Current magnetic compass swing report

· Current annual inspection and all hourly inspections

· Aircraft type certification and data sheet

· Current aircraft airworthiness certificate

· Current aircraft registration and identification numbers.

These items will be delivered with the aircraft in hardcopy and CD-ROM.

Aircraft manufactured after January 1990.

Airframe total hours shall not exceed 10,000 flight hours Time Since New (TSN) and engines not more than 2000 hrs Time Since Overhaul (TSO).

General and specialized maintenance and servicing tools and equipment shall be delivered with the aircraft.

Contractor shall demonstrate compliance with all Service Bulletins and Airworthiness Directives pertaining to the aircraft, installed systems and associated Ground Support Equipment and tools.

Aircraft will be delivered at vendor’s facility.

Aircraft must be capable of ferry flight by Armed Forces of Malta crew from vendor facility to Malta without incurring any depot maintenance requirements en route.

· Contractor shall provide type transition training and type certification to aircrew and maintainers at delivery location.

6.0 Testing, Acceptance and Delivery

6.1 Acceptance Test Plans and Procedures. The Contractor shall develop all necessary ground and flight test plans and procedures required to conduct initial inspection, and final inspection and acceptance by the U.S. Government. The Contractor shall conduct acceptance test planning, and develop and document an Acceptance Test Plans and Procedures for government review and approval for the final delivery configuration of the system. The Contractor shall coordinate with the U.S. Government and ensure acceptance planning is scheduled in such a manner to accommodate the U.S. Government’s witness of the final inspection.

6.2 Inspection and Acceptance. U.S. Government inspection of all deliverables (aircraft, publications, spares and special tools) shall occur at the Contractor or Subcontractor’s facility (unless modifications are performed at the OEM facility). For the final inspection, the equipment shall be presented in the final design configuration as defined by this SOW.

Final inspection of aircraft shall include both ground inspections and a General Maintenance Test Flight (GMTF) using procedures developed under this SOW. The final inspection shall include the Contractor execution of the U.S. Government approved Acceptance Test Plans/Procedures and U.S. Government activities in accordance with the contractor-developed test plan and procedures. A Contractor’s representative shall serve as the Pilot-in-Command for the GMTF. The Government reserves the right to observe the GMTF from the right-hand seat of the aircraft.

The Contractor shall provide written notice of inspection/acceptance readiness No Later Than 60 days prior to the proposed inspection/acceptance test date.

6.3 Delivery. All aircraft(s) shall be delivered at the vendor facility. The final destination point for all aircraft, components, equipment and spares is Valletta, Malta. Contractor responsibilities shall include all delivery preparations and aircraft assembly as required.

7.0 PROGRAM MANAGEMENT

7.1 Program Management. In order to provide insight to U.S. Government Program Management, the Contractor shall support any necessary program reviews and meetings. Agendas for these meetings shall be developed by the Contractor and coordinated with the U.S. Government in advance of the meeting. The Contractor shall publish minutes for all meetings held with the U.S. Government.

7.2 Post-Award Conference. Thirty (30) days after contract award, the Contractor shall support a Post-Award Conference (PAC) to provide the U.S. Government a plan for executing the requirements of this SOW. The Post-Award Conference shall be held at the Contractor’s facility where the principle program effort will be performed.

7.3 Technical Interchange Meetings. The Contractor shall support Technical Interchange Meetings (TIM) with the U.S. Government as needed. These meetings shall report the technical status of any required technical efforts. These meetings can be held in conjunction with the PMRs, or as determined by the U.S. Government.

7.4 Weekly Communication. As directed by the U.S. Government, the Contractor shall participate in weekly teleconference calls with the U.S. Government program team.