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Aircraft - Rotary-wing - Military, United States

Date Posted: 08-Sep-2011

Jane's All the World's Aircraft

Bell UH-1Y Venom

Type

Programme

Customers

Costs

Design Features

Flying Controls

Structure

Landing Gear

Power Plant

Accommodation

Systems

Avionics

Comms

Flight

Instrumentation

Mission

Self-defence

Equipment

Armament

Contractor

Type TOP

Multirole medium helicopter.

Programme TOP

Single-engined XH-40 (Bell 204) first flew 20 October 1956 and ordered in large numbers for US Army and numerous other

air arms as UH-1 (briefly HU-1); enlarged cabin introduced from UH-1D (Bell 205) onwards; and twin-engines from UH-1N

(Bell 212) in 1969.

When launched in 1996, UH-1Y programme intended as an upgrade, involving remanufacture of 100 existing US Marine

Corps UH-1Ns, offering 84 per cent commonality with similarly enhanced AH-1Z SuperCobra combat helicopter. New

General Electric T700 turboshaft engines and four-blade rotor assembly were key features of remanufacture, in conjunction

with new avionics suite, 'glass cockpit' and other improvements; resulting UH-1Y designed to operate with twice the payload

and at least twice the range of the UH-1N it will replace.

Maiden flight of first of two UH-1Y prototypes (160446) occurred on 20 December 2001 at Bell's Arlington, Texas, factory, the

helicopter thereafter demonstrating 190 kt (352 km/h; 219 mph) in shallow dive and 166 kt (307 km/h; 191 mph) in level

flight before being transferred to Naval Air Test Center at Patuxent River, Maryland, on completion of just over 50 hours of

company flight testing.

First flight at Patuxent River accomplished on 3 July 2002; maiden flight of second UH-1Y (159193) on 20 September 2002,

this subsequently arriving at Navy test facility by end of 2002; these two helicopters re-serialled 166475 and 166476,

respectively, at end of May 2003. By September 2003, both UH-1Y prototypes undergoing reconfiguration, in which new

avionics suite incorporated and preparations made for addition of Thales TopOwl helmet-mounted sighting system

(HMSS). Following this, flight trials resumed and continued throughout 2004, test activity including initial evaluation of

defensive aids subsystem and first weapons trials, with launch of unguided 2.75 in rockets and firing of gun armament.

Decision also taken in 2004 to incorporate HIRSS (hover infra-red suppression system) featuring so-called 'turned exhaust'.

In this, efflux nozzles canted outward, thus diverting exhaust plume away from tailboom and significantly alleviating heat-

induced fatigue, while not affecting aircraft performance and handling qualities. 'Turned nozzle' configuration first flown on

AH-1Z in June 2004; subsequently applied to UH-1Y by end of that year.

Delivery of UH-1Y to US Marine Corps for operational evaluation (OpEval) was originally expected in late 2004, but was

delayed until after completion of developmental testing, which finally accomplished on 17 February 2006. Phase 1 of OpEval

began 9 May 2006 on departure from Patuxent River of two helicopters destined to spend six months at China Lake,

California. First phase of OpEval successfully concluded in October 2006, with aircraft being transferred from VX-9 to VX-31

to permit start of training for USMC personnel; first UH-1Y prototype (and one AH-1Z) temporarily assigned to Camp

Pendleton, California, to support training task. Phase 2 of OpEval accomplished by VX-9 using low-rate initial production

helicopters; first UH-1Y (166753) delivered January 2007 and was engaged on OpEval in July 2007 at China Lake.

Development testing eventually entailed some 3,048 sorties and 3,324 flight hours by two UH-1Ys and three AH-1Zs

assigned to the test programme. During the course of this, at the beginning of June 2005, the combined helicopter fleet

recorded the 3,000th hour, this milestone being passed during trials of weapons accuracy at Yuma, Arizona. Less than a

month earlier, on 7 May, single examples of the UH-1Y and AH-1Z successfully completed the first shipboard operations

aboard USS Bataan by both day and night.

Defense Acquisition Board approval to begin low-rate initial production (LRIP) received in October 2003, with FY04 budget

appropriation covering six UH-1Ys (and three AH-1Zs), all being re-manufactured machines; four more UH-1Ys (and three

AH-1Zs) funded in FY05, these also being remanufactured. However, following a review undertaken in 2004 which identified

a potential serious shortfall in UH-1N numbers if the remanufacture programme proceeded as planned, it was announced

on 15 April 2005 that subsequent acquisitions will all be new-build helicopters, starting with seven in FY06.

Initial deliveries (remanufactured aircraft) to training unit HMLAT-303 at Camp Pendleton, California, with Fleet Marine Force

Pacific front-line squadrons transitioning thereafter, followed by conversion of Fleet Marine Force Atlantic squadrons. IOC

achieved on 8 August 2008, with maiden deployment aboard USS Boxer as part of Marine Medium Helicopter Squadron

HMM-163 (Reinforced) beginning on 9 January 2009, following work-up trials in last quarter of 2008; total of three UH-1Ys

involved in this deployment, which concluded with return to Camp Pendleton on 1 August 2009. Authorisation to proceed

with full-rate production granted 17 September 2008, following achievement of IOC. Total of 21 UH-1Ys delivered at end of

2009, rising to 43 by June 2011. First operational squadron to transition to UH-1Y was HMLA-367 at Camp Pendleton,

which began conversion from UH-1N in February 2009. Second squadron was HMLA-369, which began transition at

beginning of April 2009, followed by HMLA-169 and HMLA-267 in 2010. HMLA-367 deployed to Camp Bastion, Afghanistan

in October 2009, with first local mission on 4 November marking combat debut of UH-1Y.

Temporary grounding order imposed on six UH-1Ys (and one AH-1Z) in late April 2009, following two separate incidents in

which UH-1Ys sustained severe damage to gear boxes; failure of a bearing retainer was subsequently identified as the

cause. Flight operations resumed following inspections of helicopters thought likely to be affected.

UH-1Y VENOM PROCUREMENT

Fiscal Year Quantity Cumulative Total First Aircraft

04 6 6 166753

05 4 10 166768

06 7 17 167793

07 9 26 167800

08 11 37 167989

09 15 52

10 19 71

11 18 89

12 15 104

13 15 119

14 15 134

15 15 149

16 11 160

Total 160

Note: Helicopters funded in FY04 and FY05 are remanufactured examples; all subsequent helicopters are new-build machines. Original plan anticipated procurement of 100 UH-1Ys, but was increased in December 2008 to 123and further raised to present level of 160 in FY11 Marine Aviation Plan.

Customers TOP

See table. US Marine Corps initially sought to acquire 100 UH-1Y helicopters (10 remanufactured machines and 90 new-

build examples). Marine Corps plans and programmes document (April 2007) referred to procurement objective of 137 UH-

1Ys, but announcement of IOC achievement in August 2008 stated that total programme requirement was 123 helicopters

of this type. Authorisation to move ahead with revised total of 123 UH-1Ys granted December 2008. Further increase to 160

helicopters revealed in FY11 Marine Aviation Plan.

Costs TOP

Total procurement cost of H-1 programme (UH-1Y and AH-1Z) estimated at USD6.68 billion (FY06 budget projection). This

had risen to USD7.36 billion according to FY08 budget documentation.

Design Features TOP

Four-blade main rotor and four-blade anti-torque rotor; tailplane with sweptback leading-edges. Aerodynamic elements of

rotors foldable outboard of arm yokes, to facilitate stowage; limiting wind speed 45 kt (83 km/h; 52 mph). Two blades folded

(one fore, one aft) for normal stowage; all four (two forward, two aft) in heavy weather. Main rotors mounted on two stacked

glass fibre yokes and can function after direct hit by 23 mm cannon fire. Adjustable trim tabs for main rotor tracking

adjustment. Tail rotor assembly of two stacked, teetering rotors on a single output shaft using spined trunnions on the

pusher side of the helicopter; elastomeric bearings in trunnions provide load path for drive torque and thrust loads, and

permit flapping motion. A 0.53 m (1 ft 9 in) plug has been added to the forward section ahead of the door post, mainly for the

purpose of housing avionics racks. Airframe design life, including main blades, is 10,000 flight hours.

Flying Controls TOP

Conventional cyclic, collective and directional pedals for pilot and co-pilot. Mechanical linkages and pushrods relay inputs to

hydraulically boosted controls.

Structure TOP

Embodies combination of conventional metal construction and some composites materials to reduce cost and weight as

well as offer improved reliability and greater tolerance of battle damage. Main rotor principally of composites, combining

spar assembly, leading-edge protective strip, skins, honeycomb core and trailing-edge strip. Fuselage comprises two main

assemblies, specifically the forward section (including cockpit, cabin, landing gear, power plants and transmission) and the

aft section (including boom, tail rotor assembly and tail rotor drive).

Landing Gear TOP

Non-retractable, energy-absorbing, tubular skid type with limiting sink speed of 3.66 m (12 ft)/s.

Power Plant TOP

Two General Electric T700-GE-401C turboshaft engines, each rated at 1,153 kW (1,546 shp) max continuous; 1,264 kW

(1,695 shp) for 30 minutes; and 1,363 kW (1,828 shp) OEI, 2 min 30 s. Transmission rated at 1,957 kW (2,625 shp). Internal

fuel capacity 1,438 litres (380 US gallons; 316 Imp gallons), plus provision for carriage of two 291 litres (77.0 US gallon;

64.1 Imp gallon) external fuel tanks; total capacity 2,021 litres (534 US gallons; 445 Imp gallons).

Accommodation TOP

Two pilots, crew chief and gunner; up to eight troops in main cabin on energy-attenuating crashworthy seats. Can

accommodate six litters when used for casualty evacuation.

Systems TOP

On board inert gas generating system (OBIGGS) reduces fire hazard in event of sustaining combat damage to fuel tanks.

Hamilton Sundstrand APU. Primary DC generation by two 400 A, 28 V DC generators driven by the combining gearbox; AC

power system of two 1,500 VA three-phase inverters; system accommodate load-shedding for emergency power. Ni-Cd

battery, 25 Ah, able to power all essential systems for 20 minutes. Hydraulic system of two primary flight control systems

(PC-1 and PC-2); pressure 207 bar (3,000 lb/sq in); systems power three main rotor actuators and one directional actuator

of flight control system. One cylinder of each actuator powered by PC-1; other by PC-2. Both systems include transmission-

driven hydraulic pump, bootstrap (pressurised) reservoir, filter module, flight control actuators, integral stability and control

augmentation system, oil cooler fan hydraulic motor and other components; PC-1 also includes rotor brake control unit.

Automatic, four-axis flight control system with heading, altitude, attitude, speed and hover holds, hover wave-off and force

trim.

Avionics TOP

Comms TOP

AN/ARC-210 UHF/VHF radio with satcom and comsec features.

Flight TOP

Embedded GPS/INS; AN/ARN-153 Tacan, VHF/UHF direction finder.

Instrumentation TOP

Two 203 × 152 mm (8 × 6 in) multifunction displays at each crew station; single 107 × 107 mm (4.2 × 4.2 in) dual function

display and data entry keyboard for each crew member in centre cockpit console.

Mission TOP

FLIR Systems BRITE Star Block II navigation thermal imaging system (NTIS). Thales TopOwl helmet-mounted sighting

system (HMSS).

Self-defence TOP

Northrop Grumman AN/APR-39A(V)2 RWR; AN/AAR-47(V)2 missile approach warning system; AN/AVR-2A laser warning

receiver; AN/ALE-47 countermeasures dispenser system with 360° coverage.

Equipment TOP

Fast rope gantries permanently installed on each side are deployable from within cabin.

Armament TOP

Unguided Mk 66 2.75 in rockets in either LAU-61 (19 tube) or LAU-68 (seven tube) launcher pods; can be launched singly,

in pairs or as salvo. IOC with Advanced Precision Kill Weapon System (APKWS) expected to be achieved during FY11. GAU-

16A 0.50 in machine gun, GAU-17A 7.62 mm minigun or M240D 7.62 mm lightweight machine gun.

Dimensions, External

Main rotor diameter 14.63 m (48 ft 0 in)

Main rotor blade chord 0.63 m (2 ft 1 in)

Tail rotor diameter 2.97 m (9 ft 9 in)

Length: overall, rotors turning 17.78 m (58 ft 4 in)

fuselage, tail rotor turning 14.88 m (48 ft 10 in)

Height overall, tail rotor turning 4.44 m (14 ft 7 in)

Main rotor minimum ground clearance: static 2.62 m (8 ft 7 in)

rotors turning 3.78 m (12 ft 5 in)

Width: over skids 2.59 m (8 ft 6 in)

rotors folded 4.60 m (15 ft 1 in)

Tailplane span 3.05 m (10 ft 0 in)

Fuselage ground clearance 0.43 m (1 ft 5 in)

Areas

Main rotor disc 168.11 m2 (1,809.6 sq ft)

Tail rotor disc 6.94 m2 (74.66 sq ft)

Weights and Loadings

Weight empty 5,370 kg (11,838 lb)

Max underslung load 2,268 kg (5,000 lb)

Max internal fuel weight 1,172 kg (2,584 lb)

Max T-O weight 8,391 kg (18,500 lb)

Max disc loading 49.9 kg/m² (10.22 lb/sq ft)

Transmission loading at max T-O weight and power 4.29 kg/kW (7.05 lb/shp)

Performance

Max level speed 198 kt (366 km/h; 227 mph)

Normal cruising speed 153 kt (283 km/h; 176 mph)

Max rate of climb at S/L 768 m (2,520 ft)/min

Rate of climb at S/L, OEI 226 m (740 ft)/min

Service ceiling 6,100 m (20,000 ft)

Mission radius, with eight troops, 30 min on station and 20 min reserves 129 n miles (239 km; 148 miles)

Max range 350 n miles (648 km; 402 miles)

Endurance, absolute 3 h 30 min

g limit +2.8

Contractor TOP

Bell Helicopter Textron Inc

Bell UH-1Y Venom operating in Afghanistan with HMLA-367 (Cpl Justis Beauregard, USMC)

1427971

Bell UH-1Y Venom naval utility helicopter (Paul Jackson)

1358229

Bell UH-1Y Venom of US Marine Corps

1389903

Bell UH-1Y Venom in combat pose (Ted Carlson)

1358228

Bell UH-1Y Venom of Marine Light Attack Helicopter Training Squadron 303 at Camp Pendleton(L/Cpl Christopher O'Quin)

1163693

Bell UH-1Y Venom parachuting trials (US Navy)

1300845

Rocket firing trials of Bell UH-1Y Venom

1037996

Bell UH-1Y Venom multirole medium helicopter (US Navy)

1037907

Bell UH-1Y Venom during early shipboard trials (US Navy)

1151440

Bell UH-1Y Venom and AH-1Z Viper (nearest) with rotors in normal folded position (US Navy)

1151476

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