MMRCA 2.0 Tech Specifications- Power Plant Intake, Fuel System & Hydraulics | News Web Series Ep- 3


In any fighter aircrafts, power plant, fuel
system and hydraulics are three very important system to give it a combat edge in a war scenario. Indian Air Force has specifically asked some
important questions to vendors who submitted their response to IAF’s MMRCA 2.0 RFI for
110 fighter aircraft. Hello and welcome. My name is Shailesh Kumar and you are watching
National Defence. In this 3rd episode of MMRCA 2.0 news web
series and second part of technical parameters, we will discuss Power plant and Intake, fuel
system, hydraulics. Power Plant and Intake (a) What is the minimum structural life of
the life limited engine modules/parts? List the parts that are life limited and specify
their life. Mission Profile for calculation of the engine
life is attached as Annexure II. (b) Does the engine have any TTL? Is there any difference in hot and cold section
modules? Provide details. (c) The aircraft should be powered by an advanced
technology dual redundant FADEC engine/s with auto throttle capability. (d) Is the starter system self-contained? How many consecutive starts can it provide
without cooling/break (between starts) requirements? (e) Does the aircraft engine/s have capability
to start at an altitude of 3300m AMSL (IRA) without any modifications/adjustments or any
special starting procedure? (f) Does the engine/s have life monitoring
mechanism such as Health Usage and Monitoring System (HUMS)? (g) Does the air-intake/ engine/s combination
permit surge free engine operation throughout the flight envelope of the aircraft? Are there any engine slam restrictions? If
yes, details thereof, to be provided. (h) Is the engine/intake design capable of
withstanding impact of a bird at the maximum low level speed as specified in the relevant
US Military specifications or equivalent standards? Quantify bird mass and CAS/ Mach number and
altitude, and the resulting condition eg restricted throttle/thrust, with/without AB operation,
with/without loss of thrust, time restriction etc. (j) Is the engine/s exhaust smoke free at
all power (including maximum after burner rating) settings within the flight envelope? (k) Is the engine capable of air start (relight
in air)? If yes, what is maximum altitude for relight? Define envelope for in- flight start? (l) Is there any requirement of warming the
engine(s) in terms of time and RPM under various temperature conditions? (m) Does the engine incorporate automatic
cold rotor thrust droop compensation? If so, what is its impact on life of hot-
end components? (n) Is the aircraft capable of scrambling
for quick reaction alert missions? Does the engine/s require engine warm-up/
special procedure for such missions? Will there be any impact on engine/s performance
or engine/s life without warm-up? (p) What is time required for engine removal
and installation using minimum manpower and Ground Support Equipment (GSE)? State time, manpower and GSE required for
this task. (q) Does engine change require any ground
running/ test flight post engine/s change? Are cold checks of the engine sufficient for
flight clearance? (r) Are any thrust check algorithms available
to validate Max Reheat thrust in the cockpit before brakes release? Is thrust deterioration expected at the end
of qualified engine life? Specify if any. (s) Describe the jet fuel starter/ starter
motor provided on the aircraft. What functions does it cover, besides autonomous
engine/s starting on the ground? Can it provide
electrical, hydraulic and pneumatic services on ground and in flight? What is its rating for maximum duration for
continuous operation? Can it assist engine start in air? Specify engine start (assisted by starter)
envelope. (t) Does the aircraft engine/s conform to
Mil-E-5007E/ any other military standard? Specify the standard. (u) What are the protection measures to prevent
engine icing? Elaborate the measures. Fuel System (a) Are all the internal fuel tanks of the
aircraft self-sealing or have redundancy mechanisms to prevent further fuel leak? Post battle damage resulting in a fuel leak,
what is the minimum duration of flying permitted before recovering safely? (b) Is the aircraft fuel system dual redundant? (c) Is it possible to refuel from a single
pressure refuelling point? (d) Are the refuelling couplings/ adapters
of NATO Standard? (e) Is there a provision for partial refuelling
and hot refuelling on the aircraft? Specify details. (f) What all types of fuel can be used on
the aircraft? Is there any requirement to mix anti-freeze
solution in the fuel? What is the limitation in flight envelope/
engine/s life in case the aircraft is flown without any anti-freeze solution? (g) Is de-fuelling the aircraft possible from
a single point without the need for extra ground support equipment? (h) Is the fuel system of the aircraft capable
of gauging the entire fuel capacity and indicate the usable fuel on cockpit gauge at all times? Is drop tank fuel also gauged? (j) Does the aircraft have day and night Air-to-Air
Refueling (AAR) capability using the „Probe and Drogue‟ method? Is it capable of replenishing all its internal
and external tanks? Is the refuelling probe fixed or retractable? If fixed, what is flight envelope or any other
restrictions due to installation of the probe? (k) What is the maximum AAR rate at 50 % of
the internal fuel capacity? (l) Does the aircraft have facility for rapid
jettisoning of fuel to facilitate immediate landing after takeoff? What is the auto cut-off value of fuel jettison,
if any? If yes, what is the endurance of the aircraft
with the remaining fuel? Are there any limitations on jettisoning of
fuel in dry and afterburner regime of the engine/s? Can drop tank fuel be jettisoned? (m) Is the aircraft integrated with a NATO
Standard buddy refueling pod? What is the minimum refuelling rate from this
pod? (n) What are the types of external removable
fuel tanks with capacity, and associated speed & g limits of the aircraft? (p) What is the maximum internal fuel capacity
(liters & kg)? Hydraulics (a) What is the type and number of hydraulic
systems with redundancy to operate essential services (such as Ram Air Turbine etc)? (b) Does failure of any single hydraulic component
result in a situation where an essential service/s cannot be operated either by the main or the
standby/ emergency system? (c) Are the hydraulic lines shielded by the
airframe protective structures? (d) What is the specification of hydraulic
fluid used and operating pressure of the system? Also, the specification of
the couplings/ adapters, are to be indicated?

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