Rfi Naval Light Utility Helicopters

REQUEST FOR INFORMATION FOR NAVAL LIGHT UTILITY HELICOPTERS (NUH)

1. Naval Requirement. Indian Navy is planning to replace its existing fleet of existing Chetak/ MATCH with suitable new-build Light Utility Helicopters. The helicopter should be a wheeled twin engine helicopter of modern airframe design with modern, proven, reliable and fuel efficient engines and fully integrated advanced avionics. The helicopter should incorporate latest concepts to improve reliability and maintainability. In this regard the under-mentioned information is sought. It is requested that in respect of those parameters that are not complied with, the existing capabilities may be provided. Details are requested to be provided within three weeks of placing the same on MoD webs ite.

2. The name of the helicopter that would be able to meet the desired QRs is requested to be provided. In addition, the ability of the aircraft to comply with each of the under-mentioned capabilities may also be indicated.

3. Role. The navy desires that the helicopter be IFR capable with dual controls but capable of single pilot operations. The normal operational crew would be two pilots and an aircrew man diver. The roles that would need to performed by such a helicopter by day and night are as under:-

(a) Search and Rescue.

(b) Casualty Evacuation (CASEVAC).

(c) Logistics and Communication duties including under slung cargo.

(d) Limited Observation and Surveillance.

(e) Limited ELINT gathering.

(f) ASW attack with light torpedo / depth charge.

(g) Provide dynamic response during aid to civil authorities.

(h) Anti terrorism / anti piracy with small arms.

4. Condition for Use. The various conditions for the use of this helicopter are as follows: -

(a) Indian Reference Atmosphere. The performance parameters must be met in Indian Reference Atmosphere (IRA) conditions.

(b) Tropicalisation. The helicopter and its systems must be tropicalised and cleared to operate under the following conditions:-

(i) Ambient temperature range may be indicated.

(ii) Maximum Relative humidity ranges may be indicated. (iii) Ability to operate in saline environment with minimum maintenance requirements may be intimated. (iv) The equipment and associated sub-assemblies (sheltered and unsheltered), are to be certified in accordance with latest Mil Std/equivalent specifications and for operating and storage conditions in accordance with current specifications of airborne equipment.

(c) Ship borne Operations. The helicopter must be able to operate from small decks and larger decks up to Aircraft Carrier in adverse weather by day and night. The minimum dimensions of helicopter deck that could safely sustain operations of the helicopter may be indicated. It could be assumed that the helicopter deck would remain at the aft of the ship with helicopter hangar immediately in front of it. There would be no rear obstructions to the helicopter deck above the level of the deck. The dimensions of the helicopter when stowed inside the hangar with blades folded should be less than 14 Mtr Length, 3.5 Mtr Width and 4.50 Mtr height. The helicopter should be capable of being secured to an adaptive Traversing Gear for movement of helicopter on small deck. Would the vendor undertake to design and provide the same in case of a requirement? The helicopter should be able to be tied down/ lashed to ensure stability of the helicopter in rough weather conditions. The limits of roll and pitch of the ship to sustain the same may be indicated.

(d) Surface Classification. The helicopter must also be cleared to operate from surface covered with snow, sleet, sand, water, slush and must be capable of landing and taking off from upslope, down slope and lateral slopes, the values of these capabilities in degrees may be elaborated.

(e) Certification Standards. All aircraft equipment must be airborne certified (as applicable to helicopters) for military applications in accordance with relevant and latest Mil Standards (or equivalents). The helicopter must be certified to equivalent Category A operations i.a.w. latest regulations.

(f) Availability and Reliability. The average helicopter availability for Mission Reliability of at least 90%, with the helicopter Utilisation Rate (UR) of 30 hours per month may be indicated (the same should be supported by documents provided by the vendor).

Physical and General Characteristics

4. Basic Design Features. The helicopter must have the following design features:-

(a) The maximum all up weight (AUW) of the helicopter must not exceed 4500 kg.

(b) The helicopter should have multi-role strap on capability which could

be fitted and used depending on the mission.

(c) The helicopters should be of sturdy and robust design, capable of sustained operations from remote places and at sea with minimum logistics and maintenance requirements.

(d) The helicopter must incorporate external mooring points for ship deck operations.

(e) The helicopter must have the provision of sliding/ removable doors for cabin/ passenger / cargo compartment. It must be possible to fly the helicopter with these doors removed.

(f) Adequate redundancy should be provided for critical helicopter systems. No failure of a single system should lead to a catastrophic failure.

(g) The helicopter should be provided with suitable means to ensure safe exit of all aircrew and passengers in case of ditching. Up to what sea states can the helicopters carry out the ditching?

6. Power Plant. The requirements of the helicopter w.r.t. its power plant are as follows: -

(a) The helicopter must be powered with two turbo shaft engines of modem technology with low weight and SFC. It should have electronic engine control mechanism for carefree handling incorporating OEI training mode with automatic engine protection and interchangeable engines

(b) Maintenance cost should be low and engine should be modular in design.

(c) The engine air inlets must have particle separator as a removable fit on all helicopters. The system should be 'add on' type and should be easy to remove and replace.

(d) The engines must be capable of unrestricted operation with standard use Aviation Turbine Fuel (ATF).

(e) The engines must be capable of start up on internal battery. Up to what maximum altitude can this be achieved under ISA temperature conditions?

(f) The power plants must provide quick response to power changes.

(g) The engine must be capable of single-engine relight in flight . Upto what altitude can this safely take place?

(h) The engine should be of modular construction to optimise maintenance effort.

(j) It should have self-contained starter system without usage of external battery for starting the engines. What is the maximum interval in days between two such starts? (k) The engines should have a simple and quick in-flight re-lighting system. (I) Fire detection and suppression system should be available in and around engine bays. (m) Operating cost of the engine should be low. (n) The engines should have very high Time Between Overhauls (TBO), the TBO may be indicated. (p) Should have simple front line maintenance procedures facilitated by easy accessibility for accessories, sensors, actuators, control units etc.

7. Contingency Power Rating. The ratings as applicable under One Engine Inoperative (OEI) Conditions are as under.

(a) A contingency rating must be provided in the event of a single engine failure with a smooth transition to safe single engine flight under sudden OEI conditions which should be possible up to service ceiling. What would be the duration of this contingency rating? (b) For the super contingency power rating, an extra switch must be available on flying controls as a demand function and when any contingency rating is being used, there must be a positive indication to the pilot.

8. Maximum Power Rating (TOP- AEO). The requirements of this rating are that it must be continuously available for a period without any engine examination after use of this power rating. What is the duration of use of this rating?

9. Fuel System. The requirements of the helicopter fuel system should include the following:-

(a) The fuel system should be crash resistant and should be designed to ensure adequate amount of redundancy and survivability. Fuel tanks must be so located to enable easy maintainability with minimum disturbance to other aircraft system.

(b) Optional self-sealing protection must be available for the fuel tanks with provision for carriage of auxiliary fuel tank for ferry as an optional fit.

(c) The helicopter should also have provision for gravity fuelling and defueling, pressure fuelling and also being refuelled with engines running.

(d) The fuelling points should not be obstructed when the helicopter is fitted with Role Equipment/ Armament.

(e) Capability for suction de-fuelling with means to reduce fuel to the minimum. (f) The fuel management system should be automatic. In case of one engine failure, a cross feed mechanism should be available to ensure that the entire aircraft fuel could be used by the serviceable engine. Manual cross feed for selective fuel management by crew should be available.

10. Flight Controls. The requirements of the Flight Control system are:-

(a) The flight control system must be power operated or power assisted with built-in redundancy.

(b) In case of failure, reversion to standby system/ manual mode must be possible.

(c) If trim fails, the helicopter must be controllable.

(d) The helicopter should be provided with fully duplicated flying controls.

(e) All hydraulically operated actuators must operate with type of hydraulic oil, whose equivalent substitute are easily available in the Indian/ international market.

11. Gear Box. The Gear box must be robust and corrosion resistant with adequate survivability. Gear box oil and oil equivalent substitutes to be readily available in Indian / International market. It must have suitable means for detecting internal metal particles while in flight. The Gear box / main rotor head removal procedure must be simple and less time consuming (with minimum tools). Gear box/ main rotor head must be equipped with aircraft lifting points to enable fast crash and salvage operations. Would it be possible to carry out replacement of gear box at second line (‘I’ level)? 12. Undercarriage. The requirements of the undercarriage are as under:-

(a) The helicopter must be fitted with a wheeled landing gear acceptably free from ground resonance. The landing gear must be designed as per latest standards. What is the maximum rate of descent that the helicopter undercarriage would be able to sustain to whilst landing on deck of a ship'?

(b) Parking brakes must be provided with no restriction on operation of the parking brake even when the helicopter is parked in shut down condition.

(c) NUH should also be equipped with Emergency Floatation Gear. 13. Time Between Overhaul (TBO). The helicopter must have a reasonable in-service life. What would be the life of the helicopter in hours before any major overhaul? What would be the TBO in hours of major components such as engine, transmission, blades etc?

14. Rotor System. The requirements of the rotor system would include use of latest developments in design and technology. The main consideration must be to achieve the best aerodynamic performance, stability, manoeuvrability, minimum maintenance and long life with minimum rigging problems once rigging has been set. The other requirements include

(a) The rotor design must permit adequate ground and tail boom clearances during start up and shut down under gusty wind conditions.

(b) The rotor system should not require any routine lubrication of main rotor hinges.

(c) Rotor blades must be interchangeable individually (not as a set) and it must be possible to change the blades without upsetting the rigging beyond simple blade tracking adjustment.

(d) Possible to safely start and stop rotors in wind speeds up to 40 kts.

(e) The ability in terms of wind speed helicopter with blades folded would be able to withstand wind speeds, within 30 degrees relative to the helicopter axis.

(f) The main rotor blades must be foldable for storage and transportation with a simple blade fold system without involving labour intensive procedures or tools. It should be capable of being folded and unfolded by not more than three personnel within 10 minutes.

15. Cockpit and Cabin. The helicopter should have a glass cockpit concept with the use of full colour LCD based multi-channel, multi functional displays (LCD MFD) for essential flight, engine and system parameters. The glass cockpit should be capable of integrating systems like surveillance/ sighting system, armament, EW suite. Redundancy for basic instruments should be provided. The cockpit and cabin should have the following provisions: -

(a) Cockpit must be NVG compatible (Gen II or later).

(b) The crew seats must be ergonomic and crashworthy.

(c) Cockpit and cabin ventilation system should be fitted.

(d) A cockpit fire extinguisher must be provided.

(e) Noise and vibration levels in the cockpit and passenger cabin must conform to the latest standards.

(f) Windscreen demisting and wiping system must be provided. (g) The warning system must be supplemented by audio warning for critical emergencies with provision of Cautionary and advisory warning panelsto indicate vital and non-vital aircraft emergencies respectively.

(h) Adequate redundancy for critical cockpit instruments to cater for electrical failure / failure of Glass Cockpit hardware.

16. Communication Sets. The aircraft must have at least two digital and modular airborne military applications qualified V/UHF sets with Mercantile Mobile Band coverage. One additional UHF SATCOM set must be provided and one HF set must be provided. Intercom between pilot, co-pilot, aircrew man and at least two passengers must be available. The communication suite should have adaptability for homing device, Speech Secrecy Equipment and Data Link. The sets must have BITE facility, squelch facility, radio relay facility and preset frequency channels. The frequency range coverage of the VHF sets Cover the VHF spectrum. The frequency of operation with type of modulation (AM/FM) may be intimated along with the frequency spacing:-

17. The HF Communication set must be of modular design, digital and military aviation certified. The specifications must include:-

(a) Voice AM (H3E) Suppressed carrier (USB/LSB compatibility AM) and operation in fixed frequency mode.

(b) Secure mode of communication with selective calling feature.

(c) Scanning of minimum four preset features and automatic Link Establishment (ALE) facility.

18. Automatic Identification System (AIS). An AIS receiver must be provided. The same must be integrated with the radar display. 19. Data Link. A datalink capable of transmitting data received from the sensors to the mother ship using the communication sets would be required to be provided. Would the vendor be able to integrate a Buyer Nominated datalink into the aircraft? Would the vendor also be able to offer a suitable datalink to carry out the required function?

20. Auto Pilot. Would the helicopter incorporate a dual-lane, three/ four-axis autopilot (with automatic height hold)? In addition it should be coupled to the navigation system and be capable of autonomous hover. 21. Radar. The radar must be a modern weather radar with digital colour display with the weather mode capable of indicating cloud densities in colour. The radar must also be capable of surface target detection. The ranges of detection of 10/100/1000 M2 target may be intimated. 22. IFF Transponder. An IFF system is required to be fitted on the aircraft. Would the vendor be able to integrate a Buyer Nominated IFF into the aircraft? Would the vendor also be able to offer a suitable IFF to carry out the required function?

23. ESM System. A New generation ESM system is required to be fitted covering frequency range of at least 1-18 Ghz. Would the vendor be able to integrate a Buyer Nominated ESM into the aircraft? Would the vendor also be able to offer a suitable ESM to carry out the required function?

24. Navigation. The aircraft must have a modern, hybrid navigation system. The requirements of the helicopter with respect to the Navigation system are as under: -

(a) At least one of the onboard navigation systems must be capable of stand-alone operation. The inaccuracy of the system in stand-alone mode without GPS should not be more than 1 % of distance flown.

(b) The Navigation system must have quick readiness and should be capable of aligning/initialising on a moving (roll/pitch) platform. The time required for readiness of navigation system may be indicated.

(c) One of the hybrid navigation systems must be GPS / GLONASS.

(d) High accuracy of the order equal to or less than 2% RMS must be provided by the system for the entire duration of a sortie whether flying over land or sea.

(e) The navigation system coupled with the autopilot must provide accurate hover for prolonged duration at low heights over sea.

(f) Capability must be available to feed waypoints both moving and non-moving in air or on ground.

(g) The helicopter must be fitted with a radio altimeter and RMI. (h) The helicopter must be fitted with a homer to home onto a survivor at sea. The homer must be compatible with all modern aeronautical aviation frequencies in the V/UHF band. (j) The avionics system should include ILS, VOR DME/ VORTAC. (k) The helicopter should be certified for and capable of IFR flights.

25. Electro Optical Devices. The helicopter must have the provision for the following EODs as a removable fit: -

(a) FLIR.

(b) LLTV / high definition CCD camera. (c) Laser Range Finder.

(d) Control and display system in the cockpit.

(e) NVGs (with helmet).

26. FDR, CVR and Deployable ELT. The helicopter must be fitted with a solid state FDR, solid state CVR and a user defined deployable ELT. The ELT should be capable of being ejected from the helicopter on impact or by hydrostatic means. Frequency of operation of ELT should be 406.025 MHz and 243 MHz. What would be the recording duration of data in both FDR and CVR? External ports should be available for downloading data in a laptop. The ELT should be interfaced with the onboard GPS system.

27. General. The aircraft must have the following generic operational characteristics: -

(a) The crew configuration must cater for two pilots and one aircrewman diver. The aircraft must have the option of being flown with single pilot and one aircrewman.

(b) The helicopter must be fitted with a deck lock compatible with the grid fitted onboard IN ships.

(c) The helicopter must be capable of carrying an under-slung load . The max weight of this load may be indicated.

(d) There should be provision for fitment of rappelling equipment.

(e) The helicopter must be equipped with a rescue winch capable of single-handed operations by the aircrewman whilst seated carrying a weight of at least two adults and operated electrically or hydraulically.

(f) Carry at least four passengers (Seats for minimum four passengers must be provided as optional equipment on all helicopters. In addition to crew of two pilots and one crewman.

(g) Internal load and carrying capacity may be indicated. (h) Up to what distance and time an under-slung load of 750 Kgs would be carried? (j) Two stretchers with one patient each and one medical attendant.

28. Climb. The climb requirements will include the under-mentioned:-

(a) At maximum AUW at sea level in nil wind conditions, what is the helicopter vertical rate of climb using the maximum rating of both engines at ISA+20 deg C.

(b) What is the helicopter rate of climb at max AUW at sea level at ISA+20 deg C using maximum rating at the recommended climb speed.

29. Speeds. What is the maximum continuous cruise speed and the VNE at maximum AUW at ISA + 15 deg C?

30. Service Ceiling. The Service ceiling of the helicopter in pressure altitude may be indicated.

31. Range and Endurance. What would be the range/ endurance the helicopter be able to provide as per the missions below: -

(a) Mission A (Utility Role). Take-off from HOGE at sea level with three crew members and internal payload of at least 300 kg at sea level, ISA+20 deg C, fly at 1000 feet pressure altitude to land at another ship / base. The maximum distance to the next ship/ base may be indicated with a reserve of 30 mins of flying time foe emergencies.

(b) Mission B (SAR / CASEVAC Role). With three crew members and internal payload of 100 kg, the helicopter must be able to HOGE and take off from sea level, ISA+20 deg C, to what distance can the helicopter fly, loiter for 30 minutes and hover OGE for 15 minutes in search area, and return to land on the ship with two rescued members?

32. Manoeuvrability. The helicopter should be cleared for operations of instantaneous load factors at sea level and be able to execute sustained turns in level flight at bank angles of up to 60 degrees at 85% of maximum AUW. What are the maximum instantaneous load factors the helicopter is cleared for?

33. Sideward and Rearward Flight. At 90% of its maximum AUW, what are the maximum speeds at which the helicopter executes sideways and rearward flight at sea level with adequate directional control?

34. Turns on the Spot. The helicopter must be able to turn on the spot to either side What is the maximum permissible rate of turn at maximum AUW.

35. Quick Stop and Hover. From cruise speed at maximum AUW and CG at maximum permissible forward and rear positions, it must be possible to execute a level flight quick stop and hover.

36. Safety Features. The following safety features will need to be incorporated:-

(a) The airframe should be crashworthy designed to retain at least 80-85% of its flight deck and passenger space intact after vertical, lateral and longitudinal impacts in line with international standards.

(b) The rotor design must ensure that in the event of an engine failure, rotor speed decay is minimum. It is to be ensured that allowing for normal pilot reaction time before the collective is lowered to the flat pitch, the rotor RPM must still stay within the in-flight permissible limits.

(c) The helicopter must be easily controllable in autorotation from zero speed to maximum permitted speed in autorotation.

(d) Loss of power of one engine with collective control fixed must not produce unusual pitch, roll or yaw.

(e) The helicopter must be able to execute rapid zero speed power descents. In case the helicopter starts entering vortex ring state, there must be sufficient warning. Rapid recovery without excessive height loss must be possible.

(f) There should be provision of individual sea survival equipment for the crew whilst operating over sea.

37. Night Capability. The following requirements are envisaged for night operations in addition:-

(a) The helicopter must be capable of night operations from decks as mentioned earlier at para 3 (b).

(b) The internal and external lighting system must be compatible of NVG and non-NVG operations.

(c) Landing light must be fully steerable landing light to allow for different types of approach and landing.

(d) Provision and fitment of a searchlight capable of operating in the visual and IR spectra should be available.

38. Weapons. The helicopter should be capable of carrying at least one light weight Anti Submarine Torpedo or two Depth charges. There should also be provision of mounting 12.7 mm machine guns and / or rocket launcher on either side. The vendor is to offer compatible depth charges, rockets and 12.7 mm machine gun for the helicopter. Would the vendor be able to procure and integrate all the said weapons into the aircraft? Would the vendor also be able to offer suitable weapons as requested by the Indian Navy to carry out the required function? In addition would the Vendor be able to integrate weapons indicated by the Navy? 39 Maintenance, Training, and Product Support. The following in aid of Maintenance, Quality Assurance and Product support would require to be met by the prime contractor/supplier: -

(a) Maintenance. The prime contractor would be required to set up Operator level (‘O') (First line), Intermediate (‘I’) level (Second line) and 'D' level (Third/ fourth line) maintenance facilities as per IN requirement. Maintenance training of IN personnel for the level of maintenance would also be required to be imparted by the contractor.

(b) Ground Support, Tools and Test Equipment. (i) The supplier would be required to provide complete list of tools, ground support, ground handling and test equipment required for ‘O' Level; 'I' Level and 'D' Level maintenance facilities including the calibration equipment. (ii) GSE should be standardised, multipurpose, lightweight and easy to handle and their quantum should be minimal. (iii) The tool boxes for Airframe, Electrical, Avionics, and Ordnance to be of reputed, recognised International Brand.

(c) Product Support/Spares.

(i) The supplier would be required for continuous supply of spares including breakdown spares for 'O' Level; ‘I’ Level and 'D' Level maintenance and repair of airframe, engine & avionics systems of helicopter. (ii) The supplier would be required to provide continuous product support for the total life of helicopter including software backups / upgrade. (iii) The supplier to provide list of Oils and lubricants with NATO codes along with source of supply and their commercial equivalents. (iv) Contractor is required to supply spare engines, which would amount to 10% of total installed assets. (v ) A separate Manufacturer Recommended List of Spares (MRLS) is to be provided which should indicate the recommended quantity of major items like engines, engine accessories, gearboxes, main rotor head, rotor blades, helicopter system replaceable units which are required to be stocked as a float to meet scheduled and unscheduled withdrawal of equipment due to unforeseen contingencies as a result of FOD, bird hit, tyre burst etc. (vi) The MRLS must contain all spares - both permanent and consumable, required to undertake scheduled and unscheduled maintenance of 'O' and T level for two years of operation at a utilisation rate of 30 hrs per month.

(d) Documentation. The supplier would be required to supply Operation & Maintenance documentation including illustrated parts catalogue both in laminated hard copies and in electronic formats with hyper links between each other on CD ROMS i.a.w AECMA 1000 specifications for 'O' Level; ‘I’ Level and ‘D' Level maintenance.

(e) Miscellaneous. For ease of maintenance operations following requirements are required:-

(i) An integral IT based maintenance management system capable of integrating maintenance, repair and reliability aspect. (ii) Easy and simplified flight servicing procedures leading to quicker turnaround times. (iii) All external electrical supply and fuelling connectors / couplings to be of standard NATO type. (iv) Auto sequencing and bleeding of control services of hydraulic systems. (v) LRU level defect rectification and replacements of the units at front line level with easy to use and lightweight GSE. (vi) Access panel for facilitating front line servicing should be fitted with quick release fasteners to facilitate speedier front line maintenance. To reduce the chance of FOD, captive fasteners should be provided in access panels. (vii) Helicopter systems should have inbuilt capability of carrying out system checks after defect rectification/ parts replacements. The systems/ equipment should incorporate state of art technologies for both on line and off line modes for fault detection and localisation including BITE (Built in Test Equipment) facilities. The BITE system should be able to identify the defects up to PCB level. (viii) Auto recording of snags/ defects in flight and ground by the BIT/ BIST (Built in Self Test) system. The recorded data should be downloadable for analysis, rectification and archiving. (ix) Incorporation of COTS elements ruggedized and certified for military applications in the manufacture of avionics and computer hardware in order to reduce repair downtime during ‘I’ level & 'D' Level maintenance.

40. In addition to the above mentioned details with respect to the aircraft the following additional information on suitability of the vendor to meet the requirements of the Govt of India for undertaking the proposal is requested. 41 Trials. Would the Vendor undertake to carry out the Field Evaluation Trials in India on an NCNC basis? In the event of not being able to carry out specific parts of the trials in India the same may be specified. The vendor may indicate if the same equipment is being used by other Navies as well.

42. Transfer of Technology. Would the vendor be in a position to offer a transfer of technology to nominated Indian companies or designated Indian Naval Aircraft Yards for overhaul and maintenance facilities?

43. Offsets. Will the vendor undertake to comply with the offset obligation of minimum 30 % as prescribed by the Govt of India?

44. Delivery Schedule. What would be the envisaged earliest delivery schedule for the first aircraft from the date of conclusion of the contract and supply of subsequent aircraft for an order in excess of 50 airframes?

45. Option Clause. Would the vendor oblige the requirement of the Govt of India to offer an option clause of at least 50% of the numbers on the helicopters? In this it is requested the nos that the vendor would be willing to agree to the option clause may be indicated. The total validity of the duration of option clause may also be indicated from the time of contract signature.

46. Provisions of DPP 08. Would the vendor be in a position to comply with all the provisions of DPP 08. If not the relevant para/ clause may be indicated with reasons. In addition would the payment terms as indicated in the DPP 08 be acceptable to the vendor?