1

- POCKET GUIDE -

2

- EXPANDS THE ENVELOPE -

The Bell UH-1Y is the most modern,

capable and cost-effective tactical

utility helicopter available. It shares

a full 84% of it’s leading-edge

technologies and systems with

the Bell AH-1Z attack helicopter

for dramatically improved

maneuverability, supportability

and survivability. All of which

means you can operate the UH-1Y

with total confidence in the

harshest environments and

the hottest battle zones.

THE UH-1Y MULTI-MISSIONCHOICE OF THE USMC

FOR THE 21ST CENTURY!

. . . ANYWHERE -- ANYTIME . . .

3

Table of ContentsIntroduction ................................................................... 4Background/History ..................................................... 6General Characteristics ............................................... 8External Dimensions .................................................. 12HIRSS ........................................................................... 13Energy Attenuating Crew Seats ................................ 13Design Features .......................................................... 14Airframe ....................................................................... 14DAS [Defensive Armament System] ......................... 16Energy Attenuating Troop Seats ................................ 17Stretch Area ................................................................. 18Fast Rope ..................................................................... 18Main Support Beams .................................................. 19Aft Fuselage ................................................................ 19Landing Gear ............................................................... 20Cowlings ...................................................................... 21Northrop Grumman Integrated Cockpit& Avionics ................................................................... 22UH-1Y Integrated Cockpit .......................................... 24Multifunction & Dual Function Displays ................... 26THALES Helmet Mounted Sight& Display [HMSD] System .......................................... 32Flight Controls ............................................................ 34Center Console ........................................................... 34Pilot’s Station .............................................................. 35Automatic Flight Control System .............................. 35Weapons ...................................................................... 37Rockets ........................................................................ 37Machine Guns ............................................................. 38Powertrain System ...................................................... 39Rotor Systems ............................................................ 41Main Rotor ................................................................... 42Tail Rotor ..................................................................... 44Blade Folding .............................................................. 45Marinization ................................................................. 46Propulsion System ..................................................... 47Particle Separator & Engine Systems...................... 49Hover Infrared Suppression System........................ 50Hydraulic Systems ...................................................... 51Pneumatic Subsystem .............................................. 52Electrical Systems ...................................................... 53Battery .......................................................................... 54Electric Power Schematics ........................................ 54Fuel System ................................................................. 55Mission Profile ............................................................ 58Mission Performance .................................................. 59USMC Baseline Configuration ................................... 60H-1 Program Benefits ................................................. 62UH-1Y – AH-1Z Commonality .................................... 63

4

IntroductionThe UH-1Y is one of two new aircraft being developedfor the United States Marine Corps (USMC). The otheraircraft is the AH-1Z, a dedicated attack aircraft.Together, these two aircraft comprise the H-1 Program.The AH-1Z and UH-1Y share a common tailboom,engine, rotor system, drive train, avionics architecture,software, controls and displays, and electronic warfaresuite – greatly reducing the manufacturing/procurement costs for both the US and participatingallies.

The all new UH-1Y utility helicopter incorporates thelatest advances in military avionics and rotary wingtechnology to provide a totally integrated platform forairborne command and control, aeromedicalevacuation of casualties, transport of troops, suppliesand equipment, and search and rescue. An ImprovedDefensive Armament System (IDAS) provides theaircrew organic capability for suppressive fire from2.75 inch (70mm) rockets and a variety of machinegun systems. A state of the art, 3rd Generation staringfocal plane array FLIR is presently being fielded onthe current UH-1N, and will be carried forward to theUH-1Y.

5

The UH-1Y is fully marinized and capable of shipboardoperations anywhere in the world. Manufactured forthe US Department of Defense by Bell HelicopterTextron, Inc. the UH-1Y is the most capable utilityhelicopter of the 21st Century.

Glass Cockpit

The electro-optical system provides for day and nightoperation and during adverse weather conditions. Theexternally mounted weapon systems enhancesurvivability on both urban and conventionalbattlefields.

6

Background/History

The UH-1 family of helicopters are the most successfulmilitary helicopters ever produced. Over 16,000 UH-1 series helicopters have been produced. Theiroperations span the globe and they are well known toarmed forces throughout the world. The UH-1 set thestandard by which all other utility helicopters aremeasured. Known for it’s ease of operation andmaintenance, large cabin doors which permit rapidingress/egress, and battlefield survivability, the UH-1series aircraft are in service with over 43 armed andparamilitary forces. Many early UH-1’s are still flyingtoday, some airframes having logged over 30,000hours. The UH-1Y program offers the maximumacquisition flexibility to prospective operators. Afamiliar silhouette and proven heritage are about theonly common features that the new UH-1Y shares withits famed predecessors. Bell Helicopter Textron hasapplied the latest aerospace technologies andmanufacturing processes to create the new UH-1Ytactical utility helicopter. New four-bladed allcomposite, ballistically tolerant main and tail rotorsystems are the most noticeable external changes thathave been made. These airframe improvements, inconjunction with twin General Electric T700-GE-401Cengines, the 21st century “glass” crew station, andother advanced systems, deliver substantial increasedin tactical capability.

7

·Payload is over 170 % greater than the UH-1N,allowing the commander to move more troops andmaterial, with fewer sorties.·Range and maximum cruise speed have beenincreased by almost 50% over the UH-1N, deliveringcombat assets to their objective faster.·High G loads can be sustained during tactical orevasive maneuvers.·Significantly reduced vibration provides pilots betterresponsiveness and agility.·A fully integrated, night vision goggle (NVG)compatible “glass” cockpit maximizes situationalawareness, by easily delivering critical navigation,threat, communications, and aircraft system data tothe crew.·An advanced electronic warfare (EW) self protectionsuite and ballistically hardened components protectagainst a broad range of modern threat weapons.·A proven crashworthy fuel system reduces the riskof fire and fully stroking energy attenuation seatsprotects the crewmembers and passengers frominjury, in the event of a crash.

8

General Characteristics

The UH-1Y is a twin engine, medium class, 18,500pound maximum gross weight, utility helicopterdesigned to meet the military specifications of theUnited States Marine Corps for helicopter operationsworldwide. Dual controls accommodate single or dualpilot operation. When coupled with appropriatemission equipment, the UH-1Y is capable ofperforming the following battlefield missions:

1. Airborne command, control, and coordination forassault support operations2. Control, coordination, target acquisition, andterminal guidance for supporting arms3. Assault transport and maritime special operations4. Aerial reconnaissance5. Aeromedical evacuations of up to six litter patientsat the same time6. Search and rescue operations7. Tactical recovery of aircraft and personnel (TRAP)8. Forward air controller (Airborne) [FACA] mission9. Suppressive weapons capability against ground-to-air threats and a defensive capability against air-to-air threats10. Operations from amphibious shipping, otherfloating bases, and austere shore bases.11. Operations at night, in adverse weather, and otherinstrumented flight conditions at extended ranges.

9

The UH-1Y rotor / drive system is comprised of a lowmaintenance, highly reliable, low vibration four-bladedcomposite main rotor, a bearingless rotor head withsemiautomatic blade folding system, a new maintransmission with higher output capability, and a highoutput tail rotor drive system with a four-bladed tailrotor. The incorporation of this new drive system givesthe UH-1Y enhanced performance, increasedpayload, speed, and range, along with lowervibrations.

10

The UH-1Y comes equipped with crashworthy crewseats and provisions for either 10 crashworthy troopsseats or 6 litters, and two permanent fast rope gantryinstallations.

11

84% of the maintenance significant parts which makeup the UH-1Y are interchangeable with the AH-1Zattack helicopter.

For the USMC H-1 Upgrade Program, modified andreused components come from existing UH-1Naircraft. From Lot III and subsequent the UH-1Y willbe a totally new airframe.

12

The UH-1Y has a new fuel system with a capacity of380 U.S. Gallons internal fuel. The fuel system isballistically tolerant with built-in fire suppression andinternal, self-sealing, crashworthy tanks in thefuselage. Two 77 U.S. Gallon auxiliary fuel tanks maybe mounted to the external stores system for extendedmission range. An On Board Inert Gas GeneratingSystem (OBIGGS) prevents fuel vapor fromaccumulating in the tanks and creating a potential firehazard from ballistic penetrations.

External Dimensions

The maximum gross weight is 18,500 pounds andjacking and towing can be accomplished at this weight.Specification mission takeoff gross weights range from16,983 to 17,480 pounds. The UH-1Y is designed for2.8 g’s normal accelerations, 198 knot dive speeds,12 feet-per-second landings, and 20-g crash loads.The external cargo hook capacity is 5000 pounds.

13

Standard UH-1Y survivability equipment includes theHover Infrared Suppressor System (HIRSS) for theengine exhausts, Radar Warning Receiver,Countermeasure Dispensers, Laser Warning System,and Missile Warning Set. Energy Attenuating andArmored Seats are provided for the aircrew.

EnergyAttenuatingCrewSeats

HIRSS

14

Design FeaturesAirframe

The UH-1Y utilizes a combination of conventionalmetal aerospace construction, as well as compositematerials where applicable, to reduce cost and weightand improve reliability and ballistic tolerance. Thefuselage consists of two main sections; the forward(cockpit) section, and the aft (tailboom) section. Theforward section includes the crew cockpits, landinggear, power plant and pylon assembly. The tailboomsection supports the tail group, tail skid, tail rotor, andtail rotor drive system. The minimum design life ofthe Airframe is 10,000 flight hours.

Forward [Cockpit] Section

15

Aft [Tailboom] Section

The airframe, drive system and the rotor system havethe growth capacity to accept future increases ingross weight, allowing for heavier external storescapacity such as auxiliary fuel tanks and the fullintegration and utilization of future weapon systems.

16

The airframe consists of the main fuselage whichincludes the crew cockpit, cabin, the structure thatsupports the main transmission and houses andsupports the internal fuel cells, landing gear, andtailboom. To increase the utility of the aircraft, a 21inch stretch forward of the door post has beenincorporated. Avionics racks are also incorporated inthe stretch area. The Improved DefensiveArmament System (IDAS) of the UH-1N is beingretained. The Bomb Release Unit (BRU) ejectorshave been oriented so that the 77 gallon aux fuel tankscan be used. The provisions for the rocket pods andmachine guns are also retained.

Most of the structure for the fuselage is new toaccommodate the increased gross weight and thecrash load factor requirements. The new arrangementincludes mounting provisions for the glass cockpit,crashworthy crew seats, crashworthy troop seats,accommodations for the new landing gear, supportfor chaff/flare dispensers (in the stretch area), structurefor five new fuel cells, and tie-down provisions for cabincargo.

IDAS(ImprovedDefensiveArmamentSystem)

17

Both the fuel cells and the cargo tie-down are designedfor 20-g crash loads. The cabin floor is also designedto accept the crash loads from 10 new energyattenuating troop seats.

EnergyAttenuatingTroopSeats

18

Two Fast Rope Gantries are permanently installed andare deployable from within the cabin. They can bestowed in two different positions to permit either troopseats or litters to be installed in the cabin.

Fast Rope

The stretch area is designed for 4-g crash rolloverloads and has avionics shelves on both sides. Thecenter is open so the personnel from the cabin canaccess the flight crew.

Stretch Area

19

The new mid section is made of large componentssuch as the new machined forward and aft pylonbulkheads that support the main transmission andfuel cells. The supports for the main transmission aremade from the same forgings as those of the AH-1Z.Foam and Kevlar backing board are used forprotecting from dry bay fires caused by ballisticpenetration. The new structure has been designedfor 10,000 hours service life.

The aft portion of the main fuselage is also new. Themachined bulkheads support the aft fuel cells andthe aft bulkhead attaches to the tailboom. The aft baycontains the oil cooler and directional actuator amongother components. The cargo door tracks areremovable and steps have been incorporated toaccess the engines.

Main Support Beams

AftFuselage

20

Landing GearThe rugged, reliable, low cost skid landing gearincorporates high strength energy attenuating crosstubes to protect the airframe, crew, and troops in theevent of hard landing. Cross tube shape is optimizedto give the maximum energy absorption for minimumgear weight. Towing is possible with the aircraft at amaximum weight of 18,500 pounds using forward andaft ground handling wheels. The skid landing gear hasdemonstrated a limit sink speed of 3.66 m/sec (12fps) and a reserve energy sink speed of 4.48 m/sec(14.7 fps) @ Basic Design Gross Weight of 16,700pounds. The skid gear is attached to the lower fuselagestructure and is readily replaceable in the field.

Standard Skid Landing Gear

21

The cowlings and fairings cover the engine, APU, andtransmission area. They direct airflow around andthrough the engine and transmission areas to provideengine inlet air, cooling air for various componentsand streamlining to surfaces for flight. Additionally,some of the cowls and fairings provide cooling air forIR suppression. By ducting and mixing cool air withengine exhaust gasses, the IR signature of the aircraftis greatly reduced, increasing survivability. The IRsuppressor is a combination of components from bothGeneral Electric and Bell Helicopter.

Cowlings

22

Northrop Grumman IntegratedCockpit & Avionics

THE TOTAL INTEGRATED AVIONIC SYSTEM (IAS)Northrop Grumman has the responsibility for thedesign, development, and delivery of the H-1Integrated Avionics System (IAS), which includescockpit displays and controls, communications,navigation, external stores and weapons managementsystem, and a central mission computing subsystem.

Maximum commonality of product across platforms;achievement of redundancy and backups in all criticalareas of processing, displays, and essential sensors;and planned reserves of processing and 1553 busbandwidths are delivered within the IntegratedAvionics System (IAS). At the heart of the IAS is theMission Computer, which controls all aspects ofmission performance from flight instrumentation toweapons engagement.

The figure on the opposite page illustrates the IAS ofthe UH-1Y. The AH-1Z IAS is identical except it has aweapons module. Beyond those items of displays,sensors and weaponry are elements that supportother key functions. These include:

Communications: utilizing the new U.S. Navystandard ARC-210 integrated radio, UHF/VHF,COMSEC, SATCOM (UH-1Y only) interface with ahigh power amplifier, and a tactical data modem arecombined into a single unit.

Navigation: is primarily achieved with the U.S. NavyEmbedded GPS Inertial (EGI) and air data subsystem.Backup sensors and displays are provided in the eventof a total IAS failure. A modern, U.S. Navy standarddigital map system is also provided with full capabilityfor Digital Terrain Elevation Data (DTED) andCompressed Arc Digitized Raster Graphics (CADRG).The map is used as a navigator map display source,as a threat visibility indicator, and is part of the in-flight mission-planning mode.

23

EW/Self-Protection: consists of the NorthropGrumman APR-39B(V)2 radar warning receivertogether with the AAR-47(V)2 missile warning/laserdetection system.. The APR-39B(V)2 is upgraded toprovide full MIL-STD-1553B access of threat warning.It also provides data to the Mission Computer, foroptimal integration of threat situational awareness.The ALE-47 countermeasures dispensing subsystemis provided for 360 degree protection.

INTEGRATED COCKPIT / AVIONICSARCHITECTURE

24

The UH-1Y cockpit is designed for maximumcommonality and inter-operability. The location ofcontrols and displays at the right and left crew stationsare nearly identical, allowing crew members toperform the pilot or copilot roles from either station.Flight controls consist of a conventional cyclic,collective, and pedals. To enable maximum hands-on system control by the flying pilot, switch functionson the cyclic and collective control grips include:automatic flight control system adjustment, weaponselect and fire, TopOwl Helmet Mounted Sight andDisplay (HMSD) System boresighting, external storesselection and emergency jettison, electronic warfarecounter measures dispensing control, radio select,frequency select, press to talk, search light control,and multifunction display page selection.

UH-1Y Integrated Cockpit

COMMON* (UH-1Y / AH-1Z) COLLECTIVE & CYCLICCONTROLS

* SOME SWITCHES ONLY FUNCTIONAL ON AH-1Z

25

Cockpit

Each crew station has two 8 x 6 inch multifunctiondisplays (MFD’s) with which the crew interfaces withthe majority of subsystem functions. Each crew stationalso has a 4.2 x 4.2 inch dual function display anda data entry keyboard, both located in the console inthe center of the cockpit. During normal operationthe dual function display presents standard displaypage formats. However, in the unlikely event of a totalavionics system failure, it will present the standby flightinstrument symbology.

26

Both the multifunction and dual function displays areactive matrix liquid crystal color displays. Thedisplay page formats are organized based on missionrequirements.

The flight display presents horizontal and verticalsituation indication displays for instrument flight aswell as engine and drive train status and other statusindications.

Standby Flight Symbology on DFD

Multifunction & Dual Function Displays

27

The warning caution advisory display in conjunctionwith verbal and nonverbal signals alerts the crew thata system limitation has been exceeded or a system isoperating in a degraded mode.

The systems display presents the status of theengines, drive train, hydraulic, electrical, and criticalaircraft systems.

28

The voice communications display format presentsselectable and editable lists of frequencies and callsigns. The tactical digital communications displaypresents formats for composing and transmittingvarious tactical digital messages, as well as receivingincoming messages.

The warning caution alert function presents criticalinformation on the flight display to prompt the crew tocall up the detailed warning caution advisory page.

29

The digital moving map display in conjunction withthe aircraft’s embedded GPS/INS system allowsprecise navigation and enhanced situationalawareness by displaying battlefield graphics includingthreat locations and inter-visibility indications.

Voice Communications Display on DFD

30

The weapon display graphically depicts themunitions onboard the aircraft and allows the setupof weapon inventory and deployment modes.

The electronic warfare display provides warningindications of radar, laser, and missile launch threats,as well as allowing the setup of the counter measuresdispensing functions.

31

The UH-1Y Helicopter Integrated Avionics System(IAS) has been developed utilizing the software openarchitecture approach. The computer has a reservegrowth capacity. This growth capability in the Avionicsand Weapons Systems, plus that in the Airframe, DriveSystem, and Rotor System, add significantly to theuseful mission life and long term effectiveness of theUH-1Y Helicopter.

The Navigation Thermal Imaging System (NTIS)display presents the selected picture (standard FLIR,or future video upgrades) and provides controls forvarious NTIS modes.

32

THALES TopOwl Helmet Mounted Sightand Display System

An important functional element of the UH-1Y cockpitdisplay is the TopOwl Helmet Mounted Sight andDisplay (HMSD) System. This helmet supportsimproved communication and reduces cockpitworkload leading to improved mission effectiveness.Manufactured by THALES Avionics, the TopOwl HMSDis the most technically advanced helmet currentlyavailable and in service, offering unparalleledsupportability and the capacity of technology insertionas additional requirements develop. The TopOwlHMSD combines both avionics functions with theaircrew life support and protection functions into asingle unit.

Key features of the TopOwl HMSD include:·True 24 hour day/night capability using imageintensified night vision technology

·High accuracy head tracking system

·Provides a binocular display with a 40 degree, visor projected field of view

·Visor projection can include FLIR or video imagery

·Operational applications of navigation, target designation, and weapons aiming and firing

·Optimum center of gravity

·Custom fit helmet liner

·In production and service with 9 other countries

33

34

Flight ControlsFlight controls consist of a conventional cyclic,collective, and directional pedals at each crew station.Mechanical linkages and push-pull tubes transmit pilotinputs to the hydraulic boosted controls. The controltubes are sized for maximum tolerance to damagefrom ballistic threats.

Center Console

35

Automatic Flight Control SystemThe AFCS incorporates a four-axis (pitch, roll, yaw,and collective) fail passive Stability ControlAugmentation System (SCAS). The AFCS also hasthe following additional modes of operation: HeadingHold, Attitude Hold, Speed Hold, Cruise Hold, AltitudeHold, Hover Hold, Hover Wave-off, and Force Trim.Heading Hold mode holds heading within ±1.0degree, steady state, of the heading existing at thetime of engagement.Attitude Hold mode operates in conjunction withSCAS to provide pitch and roll attitude stabilization.This mode maintains the pitch attitude within 1.0degree, and roll attitude within 1.0 degree of theattitude existing at the time of engagement.Speed Hold mode maintains airspeed, orgroundspeed, at the time of engagement within ±3kts steady state from the reference and within ±10kts, (or ±10% of the reference speed) in moderateturbulence.

Pilot’s Station

36

Altitude Hold mode maintains the altitude existingat the time of engagement through the collective axis.This mode holds either barometric (BARO) or radar(RALT) altitude depending on the altitude referencesource selected and the flight condition.Cruise Hold mode automatically engages andmaintains heading hold, altitude hold, and speed hold.Hover Hold mode causes the helicopter to make asmooth deceleration from 15 kts (or less) groundspeedto a stable hover while maintaining a constant radaraltitude and constant heading. After achieving a stablehover, the Hover Hold mode maintains a position asmeasured by the integration of the ground velocitysignals. The position for hover hold is the position atwhich ground velocity becomes less than 0.5 kts. Ina steady wind with constant heading, the helicoptermaintains a steady state hover within a 10 footdiameter circle.Wave Off mode causes the helicopter to transitionfrom the flight condition at engagement to a terminalspeed and altitude that has been pre-selected anddisplayed via the Multi Function Display (MFD).Force Trim capabilities include pilot ability to reducethe control forces to zero by actuation of trim releaseswitches on the cyclic and collective control sticks.Incremental force trim (beep trim) capability isavailable via the trim actuators and is controlled byappropriate beep switches on the cyclic and collectivecontrol sticks.Incremental Mode Trim (beep trim) capability isprovided for all of the modes described above.Also, when any hold mode is engaged, the pilot isable to move the controls (Fly-Through) by overridingthe force feel spring force and control friction forces.Displacement of the controls from the trim positionresults in temporary disengagement of the mode.When the control is returned to the trim position, themode reengages and returns the helicopter to the trimcondition existing prior to override.

37

Weapons

Rockets

The rocket system employed on the UH-1Y uses 2.75inch (70mm) rockets. All available Mk66 rockets aresupported with warheads of three general types; i.e.unitary, airburst cargo, and training warheads.

Airburst, Cargo, and Unitary Warheads:(1) M151 High Explosive-Fragmentation

[HE-FRAG](2) M229 HE-FRAG(3) M261 HE-Multipurpose Submunition

[HE-MPSM](4) M255A1 Flechette(5) M262 Illumination Flare(6) M264 Smoke[RP]

Either LAU-68 (7 tube) or LAU-61 (19 tube) launcherscan be loaded onto the BRUs of the DAS. Withadditional software in the mission computer either M-261 (7 tube) or M-260 (19 tube) launchers can beused for the remote set fusing function. The pilotlaunches the rocket/s by a trigger squeeze, enablingsingle, pairs or salvo firing as commanded on the MFD.

38

The M-240 D, GAU-16, and GAU-17A machine gunscan be fired by the crew chiefs.M-240D 7.62-mm MachinegunThe M-240 is a belt-fed, recoil operated, air-cooled,machinegun with a rate of fire of 750 to 950 roundsper minute.GAU-16/A 50 Caliber MachinegunThe Browning GAU-16/A 50 caliber machinegun is abelt-fed, recoil-operated, air-cooled, machinegun witha rate of fire of 750 to 850 rounds per minute.GAU-17A 7.62-mm Aircraft MachinegunThe GAU-17A is an air-cooled, multibarrel, electricallypowered gun. The gun is capable of firing 3000 roundsper minute. The weapon system is broken down intothree main parts: the control box, the ammunitionstorage system, and the aircraft machinegun.The GAU-17A machine guns can also be fired byeither flight crew member when in fixed forwardposition.

Machine Guns

39

The Powertrain or Drive System transfers power fromthe two T700-GE-401C engines on the UH-1Y to themain rotor, the tail rotor, and various other aircraftaccessory systems. The drive system consists of acombining gearbox, a main drive shaft assembly, amain rotor gearbox, an oil cooling system for the mainand combining gearboxes, and a tail rotor drive systemconsisting of two gearboxes (42o and 90 o)

Powertrain System

The H-1 main rotor gearbox contains a newlydesigned drive train capable of accepting 2625 SHPfrom the engines for distribution to the main rotor, tailrotor, and various other gearbox mountedaccessories.

40

MRGBinBenchTestFixture

41

Rotor SystemsThe high performance UH-1Y Main Rotor Systemrepresents a major breakthrough in technology. Thesimplicity of the UH-1Y main rotor design haseliminated all bearings, hinges and rotor mountedvibration absorbers. The result is a highlymaneuverable, fast, long-range reconnaissancehelicopter.

Main Rotor System Features·All-composite main rotor blades, yokes and cuffsprovide very stable handling qualities and high cruisespeeds·75% fewer parts than 4 blade articulated systems·Rotor hub weighs 15% less than conventional hubs·Lower levels of vibration than any competing rotorsystems·Lower Life Cycle costs than any competing rotorsystems·10,000 hour life components·Increased ballistic survivability·Can sustain 23mm direct hit and continue to operate·Doubles the payload capabilities·Semiautomatic blade fold for shipboard operations·Field camouflage·Aircraft hangaring capabilities·Reduces spare parts by 77%

42

The primary structural members of the main rotor hubare two fiberglass yokes. Each yoke is amultifunctional component which transmits torquefrom the mast to the blades, accommodates flapping,lead-lag, and pitch change motions, and retains theblades. A stacked yoke arrangement is chosen in lieuof one four-armed yoke. It permits the use of twoidentical stacked two arm yokes, which allows higherflapping angles and reduced manufacturingcomplexity. Logistics support problems are alsoreduced due to the smaller physical size of the two-armed yoke as compared to a single four-arm yoke.The main rotor blade is constructed primarily ofcomposite materials. The blade body consists of aspar assembly, leading edge protective strips, skins,honeycomb core, and trailing edge strip.

Main Rotor

43

The blade leading edge is protected by a single pieceabrasion strip made from stainless steel. The outertwo-thirds of the strip is electroplated with nickel. Anelectroformed nickel tip cap is bonded to the bladetip to protect it from sand and rain erosion.

The main rotor blades incorporate a pilot-adjustableformation tip light on the upper surface. The rotorblades include forward and aft product balancepockets for spanwise and chordwise dynamic balance.The main rotor blade design includes adjustable trimtabs to facilitate tracking of the individual rotor blade.The main rotor blades are individually interchangeableand provide removable balance weights to ensuretrack and balance capability following field repairs. Themain rotor blades have a design life of 10,000 hours.

44

Tail RotorThe Tail Rotor Assembly consists of two stacked,teetering rotors, independently mounted on a singleoutput shaft using splined trunnions on the pusherside of the aircraft. Elastomeric bearings installed inthe trunnion provide the load path for the drive torqueand thrust loads, and provide for flapping motion.

The Tail Rotor Hub consists of titanium yokes,elastomeric flapping bearings, shear restraints, andpitch horns. The hub assembly has a design life of10,000 hours. Like the main rotor blade, the tail rotorblade leading edge is protected by a single pieceabrasion strip made of stainless steel. The outer two-thirds of the abrasion strip is electroplated with nickelfor enhanced wear characteristics.

45

Blade FoldingBlade folding is accomplished by a combination ofautomatic and manual means to lock out the bladepitch, position the blades for folding, disengage theblade pins, and rotate the blades for folding andspreading. Design of the blade pin powered lock andunlock mechanism prevents any possible motorbackdrive situation. Safeties are provided to preventthe blade pin from disengaging in flight. The lockoutand blade pin mechanisms are commanded bycontrols in the cockpit. Visual indication of the lockedcondition is also provided in the cockpit. An interlocksystem, independent of the cockpit indicator, preventsrotor start while the pins are in the unlocked condition.The ground crew is not required to climb atop theaircraft for the blade folding operation. Retracking orbalancing of blades is not required after blade folding.Manual backups are provided for the automatic bladefolding sequences in the event of failures of theautomatic system. The system is capable of foldingand unfolding the rotor blades in horizontal winds upto and including 45 kts from any azimuth direction.

46

MarinizationThe UH-1Y is fully marinized and capable of shipboardoperations including takeoff, landing, refueling andrearming, and is securable for deck motionsencountered up to sea-state 5. The UH-1Y has beendesigned for compact stowage of the assembledaircraft aboard ship and for spotting on the flight decksof the standard US Navy LHA, LHD, LPH, LPD, andLSD class ships. The UH-1Y is compatible with theelevators of the above class ships. The aircraft fits onthe deck edge (50’ X 34’ ) and stern (60’ X 35’)elevators of the LHA, and starboard and port (50’ X40’) elevators of the LHD. A minimum of 18 inchclearance between the aircraft and the ship’s structureis maintained while the elevator is in transit and at thehangar deck level.

47

The installed rated Contingency Power [2.5 minuteOEI (one engine inoperative)] for the T700-GE-401Cengine is 1828 SHP (for a sea level standard day).The installed rated Intermediate Power [Twin Engine,30 minute rating] for the T700-GE-401C engine is1695 SHP (for a sea level standard day).The installed rated Maximum Continuous Power [Twin Engine, continuous rating] for the T700-GE-401Cengine is 1546 SHP (for a sea level standard day).

Propulsion SystemWidely acknowledged for their proven reliability andlow fuel consumption, the modular designed T700series engine, two of which power the AH-1Z and UH-1Y, also power both the Bell AH-1W and 214ST, aswell as UH-60 Blackhawk and other US Governmentand International aircraft. The T700 engine has anintegral particle separator, and a self-containedlubrication system that uses fuel flow to cool the engineoil. Only ten tools are required to perform fieldmaintenance. With over 19 million service hoursaccumulated on 10,000 T700/CT7 engines in service,this engine is mature and has already earned anenviable reputation for reliability.

48

The T700-GE-401C engine has an emergencylubrication system to allow operation followingdamage that totally interrupts the normal supply ofoil. The engine accessory gearbox and C-sumpcomponents can continue to operate at least sixminutes with residual oil present. The enginespecification requirement is that the engine shalloperate at intermediate power for a period of 30seconds during which no oil is supplied to the engineoil pump inlet. As a result of this operation, there shallbe no detrimental effects to the engine during the oilflow interruption period or during engine operationthereafter.

49

Engine compressor cleaning provisions include thenecessary plumbing required to interface to the freshwater wash spray ring. The installation is apermanently installed system, which permits simpleand rapid connection of standard United States Navywash carts. An alternate fitting could be used if needto mate with other desired wash carts.The T700-GE-401C engine includes a DigitalElectronic Control Unit (DECU) for IsochronousGoverning of the engine. The DECU also maintainstight limiting of power turbine speed, measured gastemperature, and torque. The DECU providesautomatic overspeed protection, auto-relight onflameout, and loadshare between the two installedengines. Additionally the DECU contains internal faultaccommodation and external fault annunciation.A fire extinguishing system is provided for theengine bay and APU compartments.

The T700 engine has a unique inlet particle separatorintegrated into the forward main engine frames. Thefully anti-iced separator provides a high level ofcompressor protection against damage from foreignobjects such as sand, dust, birds, and ice. Theseparator imparts a swirl to the entering airflow anddirects that part of the flow containing the centrifugedsand and foreign material through a scavenge systemenergized by a mechanically driven blower. The cleanair is then deswirled before entering the engine core.

Particle Separator & Engine Systems

50

A Hover Infrared Suppression System (HIRSS) isan integral part of the exhaust system and uses enginecompartment and external air for cooling. The HIRSSis self-powered and nonselectable. The HIRSS isdesigned/sized for the worst-case temperature andflows of the T700-GE-401C.

Hover Infrared Suppression System

51

Hydraulic SystemsThe hydraulic subsystem consists of two PrimaryFlight Control Systems (PC-1 and PC-2), one rotorbrake, and one rotor blade fold system. Operatingpressure is 3000 psi. PC-1 and PC-2 systems powerthe three main rotor actuators and the one directionalactuator of the flight control system. Each actuator isof dual cylinder design. One cylinder of each actuatoris operated by PC-1 and the other cylinder is operatedby PC-2. Both PC-1 and PC-2 systems include atransmission driven hydraulic pump, bootstrap(pressurized) reservoir, filter module, flight controlactuators, integral Stability and Control AugmentationSystem (SCAS), oil cooler fan hydraulic motor, andother required components and connection lines. Inaddition PC-1 includes a rotor brake control unit.

52

Pneumatic Subsystem

Main engine starting is accomplished by first startingthe auxiliary power unit (APU) which subsequentlypressurizes the pneumatic manifold with APU bleedair. A start control valve and air turbine starter areprovided for each engine. Opening the start controlvalve initiates the starting sequence by allowingcompressed air from the manifold to drive the starter,thus turning over the engine through the engine startcycle.A ground connection valve is provided in thepneumatic manifold to allow connection of a hose forpressurized air from a ground cart or from anotheraircraft pneumatic system.The pneumatic system also supplies compressed airfor cabin bleed air heating and windshield defogging,and On Board Iner t Gas Generating System(OBIGGS) for fuel tank inertion. Shutoff valves arealso provided for these functions.

Hydraulic Schematic

53

Electrical SystemsThe primary DC generating system consists of two400 ampere brushless 28 VDC generators driven fromthe combining gearbox. Each generator is controlledby a generator control unit which provide regulated28 VDC MIL-STD-704 quality power and protectionfrom MIL-STD-704 exceedances, ground faults andgenerator overloads. No load shedding or reductionin mission capability is required, should loss of a singleDC generator occur. The aircraft AC power systemconsists of two 1500 VA three phase inverters. Theinverters provide MIL-STD-704 quality AC power andprotection from MIL-STD-704 exceedances andinverter overloads. The AC power distribution systemaccommodates load shedding for emergency power.

Sundstrand Auxiliary Power Unit

The APU driven DC generator is a 200 amperebrushless 28 VDC generator capable of providingpower to all aircraft buses. A generator control unitprovides regulated 28 VDC MIL-STD-704 qualitypower and provide protection from MIL-STD-704exceedances and generator overloads. Sufficientpower is available so that all equipment may besystematically operated and functionally checked. TheAPU generator also provides battery charging duringthis time. The APU is capable of starting on aircraftbattery power when cold soaked at a temperaturedown to -26°C (-15°F). The APU may be started froma 28 VDC external power source down to -54°C (-65°F). When either engine is operating the APU maybe started from the aircraft DC bus.

54

Electric Power Schematics

The UH-1Y’s battery is a 19 cell Nickel-Cadmium lowmaintenance type providing a minimum of 25 amp/hours. The battery is capable of providing startingand emergency power requirements for a minimumof 1 year without maintenance action. The battery iscapable of providing sole power for operation ofessential equipment for emergency operation for aminimum of at least 20 minutes.

Battery

Figure 1. Electrical DC Power System

EXT PWR RECPT

EXT PWR RLY

EXT PWR MONITOR

APU LINE RLY

SECPWR RCCB

BUSINTCONRLY

MAIN FEEDER

SEC FEEDER

AFT DC BUS

NON-ESNTLRLY

NON-ESS BUS

NON-ESS BUS

ESSENTIAL BUS

BATT RLY

BATT

100A

50A

75A

APU/

BAT

BUS

GEN CONTUNIT 1

SHUNT

INV 1

115 VAC3 PHASE1.5 KVA

SHU

NT

INV CB

100A

GEN 1LINE RLY

28 VDC400 A

GEN 1

APU GENCONT UNIT

ESNTL FEEDER

APU START RLY

75A

SHU

NT

28 VDC200 A

APUST/GEN

INV CB

100A

GEN 2LINE RLY

INV 2

115 VAC3 PHASE1.5 KVA

SHU

NT

GEN 2

28 VDC400 A

GEN CONT UNIT 2

SHUNT

Figure 2. Electrical AC Power System

N/ESNTLBUS RLY

ESNTL AC BUS

ARMT AC BUS 1

INV 1RLY

3 O WYE1500 VAINV 1

3

N/ESNTL AC BUS #2

BUS RLY

N/ESNTL AC BUS

LOAD SHED

ARMT AC BUS 2

INV 2

3

RLYINV 2

3 O WYE1500 VA

55

Fuel SystemThe crashwor thy fuel system consists of fiveinterconnected, self-sealing, rubber fuel cells; threemain cells aft of the cabin bulkhead and two feed cellsunder the cabin floor. The system includes firewallshutoff valves, low level switches, fuel feed line checkvalves, boost pump pressure switches, fuel quantitytransmitters and indicators, fuel cell interconnectvalves, self-sealing fittings and connecting lines, anddrain valves. All fuel system components have anoperational life equal to or greater than the aircraft.The fuel system is compatible with fuels JP-5, JP-8,Jet A and JP-4.

The system is equipped for either pressure or gravityrefueling. Both refueling receptacles are located onthe port side of the aircraft in the aft port fuel cell. Thepressure fueling system accepts the standardpressure-refueling nozzle. Maximum fuel flow into thecells is 90 gpm at 60-psi nozzle pressure. The gravityrefueling port accepts the standard manual-refuelingnozzle. The total usable internal fuel capacity is 1443liters (380 gallons).

56

Complete provisions are included to attach auxiliarytanks to one or both DAS mounts. The auxiliary fuelsystem utilizes 292 liter (77 gallon) tanks. With bothauxiliary tanks installed, the total fuel capacity isincreased to 2021 liters (534 gallons). Theinterconnected and crossfeed system is designedsuch that both power sections can independentlyoperate from fuel supplied by either feed tank. Thefeed tanks are gravity replenished from the aft cells.The engine and APU feed systems consist of primepumps, engine prime solenoid valves, fuel shutoffvalves, and pilot-operated controls. The engine fuelsystem is a suction feed system (only during APUoperation and engine start is boosted pressure fuelsupplied). Each forward fuel cell contains a sump, drainvalve and a submerged fuel boost (prime) pump. Acanister surrounds each suction line inlet to provide afuel reservoir during zero or negative G aircraftmaneuvers.

The feed tanks include low-level switches transmittinga caution signal to cockpit panels when the fuel levelreaches 30 minutes fuel remaining. The fuel cells arecrashworthy and provide self-sealing protection up to0.50 caliber in selected critical areas. The cells aremanufactured to maintain structural integrity in a 20gcrash and have integral fittings, which are designedto fail at a load greater than that required to fail thecell material.

57

58

Mission Profile

UH-1Y Mission Profile*

oo

Mission RadiusRequirement 110 nm

Actual 130 nm

LandingLand w ith Fuel Remaining -

Either 10% initial fuelor 20 minutes Flight

@ Max Endurance Airspeed

TakeoffSea Level 40°C

Internal Fuel onlyFour Aircrew

Basic Utility Load 5623 lb•Combat Troops (8) @ 240 lb ea.

•Chaff/Flare (120)•Fast Rope (2)

Warm up 5 minutes @ Flight IdleOne minute Take-off @ IRPClimb to 3000 ft PA / 33°C

CruiseMax Range Airspeed

3000 ft PA / 33°CReturn

Max Range Airspeed3000 ft PA / 33°C

Recon Insert5 minutes HOGE

Off-load Marines via Fast RopeLoiter 30 minutes @ Max

Endurance Airspeed3000 ft PA / 33°C

*Preliminary Performance as of November 2001

59

Mission Performance

Kilograms Pounds

Empty Weight 5,369 11,839

Max Useful Load 3,021 6,661

Max Internal Fuel 1,172 2,584

Max Gross Weight 8,390 18,500

Max Payload 1,460 3,220

HOGE Gross Weight** 7,817 17,236(Hover Out of Ground Effect)

LRC Speed** 250 km/hr 135 Kts(Long Range Cruise)

MCP Speed** 293 km/hr 158 kts(Maximum Continuos Power)

Dash Speed** 304 km/hr 164 kts

Dive Speed 367 km/hr 198 kts

Max Rate of Climb** 12.8 m/s 2,520 fpm

OEI Rate of Climb** 3.8 m/s 740 fpm(One Engine Inoperative)

Vertical Rate of Climb** 5.1 m/s 1,007 fpm

Service Ceiling 6,100 + m 20,000+ ft

Max Crosswind 65 km/hr 35 kts

Maneuverability, g’s**

Max Endurance, hours**

Mission Radius** 241 km 130 nm

990 kg Payload 2182 lb Payload

*Aircraft configured with T-701-GE-401C engines.

** Performance for Troop Insertion mission at 3000 ft / 33oC.

UH-1Y Performance*

{Preliminary performance as of November 2001}

3.3 hours

Weapons Stations2 Pintle Mounted Guns

2 External Store Hard Mounts

-0.5 to +2.8

60

USMC Baseline Configuration

AIRFRAMEComposite/Aluminum alloy fuselagePlexiglass CanopySkid Type Landing GearShipboard Capable Tie Down FittingsSemi-Monocoque tailboom and vertical finElevatorTail Skid

ROTORS & CONTROLSComposite Rigid Bearingless Rotor Heads4 Bladed Composite Main Rotor Blades w/ 10,000 Service Life4 Bladed Composite Tail Rotor Blades w/ 10,000 Service LifeSemi Automatic Main Rotor Blade Fold SystemDual Digital 4 Axis Automatic Flight Control System

TRANSMISSION / DRIVE SYSTEM5,000 Hour TBO Design Goal/10,000 Hour Service Life Drive SystemAluminum Cases

POWER PLANTSTwo General Electric T-700-GE-401C enginesSundstrand Auxiliary Power UnitMagnetic chip detectorsFuel Filter AssemblyFire Detection SystemFire Extinguishing SystemRPM warning system

COMMUNICATIONSVHF/UHF radio - AN/ARC-210 radio systemIntercommunications System

NAVIGATIONEmbedded GPS/INSARN-153 TACAN systemVHF/UHF direction finder

IDENTIFICATION FRIEND OR FOE (IFF)APX-100(V) IFF

COUNTERMEASURES GROUPALE-47 Countermeasures System APR-39B(V)2 Radar warning setAAR-47(V)2 Combined Missile Warning/Laser Warning Set

SURVIVABILITY 23mm tolerant rotor hub and bladesLarge diameter control tubes for tolerance against small arms fire 12 ft/second sink speed landing gearCrashworthy, self-sealing fuel cellsOn Board Inert Gas Generating System (OBIGGS)Engine IR suppressorsLow IR Reflective PaintVariable Capacity Energy Attenuating crew/passenger seatsHigh rotor inertia

61

MARINIZATIONSimple Semi Automatic Blade FoldCorrosion Resistant DesignWet Lay-up Manufacturing Process30 Degree Turn Over AngleEMI ShieldedMarinized Engines

INTEGRATED AVIONICS SYSTEM (IAS)Mission Computers (2)Multi Function Displays (4)Dual Function Displays (2) Keyboard Units (2) Standby attitude sensorAir Data Computer Stores Station ElectronicsStation Control Unit

DIGITAL MAP SYSTEM (TAMMAC)Advanced Memory Unit (AMU) Mission Data LoaderDigital Map System (DMS)

ELECTRICALDC Generators (2)AC Inverters (2)Ni-Cad BatteryIntegrated Flat Wiring

AVAILABLE ARMAMENTDefensive Armament System (DAS) Mounted Weapons

1. M-240D 7.62 Machinegun2. GAU-16 50 Caliber Machinegun3. GAU-17A 7.62 Aircraft Machinegun4. BRU-20 Series Bomb Ejector Rack5. LAU-61 2.75 Inch Rocket Pod (19 Rocket Capacity)6. LAU-68 2.75 Inch Rocket Pod (7 Rocket Capacity)

SENSORSFLIR Systems BRITE Star Navigation Thermal Imaging System (NTIS)THALES TopOwl Helmet Mounted Sight and Display (HMD) System

MISCELLANEOUSFlight Control Computer Flight Control Panel (2)Armament Control Panel (2)Systems Control Panel (2)Lighting Control Panel (2)Glareshield Warning Panel (2)Emergency Switch Panel (2)IMD HUMS BF Goodrich77 Gal External Aux Fuel Tank

62

H-1 Program BenefitsBell Helicopter will remanufacture USMC AH-1Waircraft into “zero time” AH-1Z attack helicopters andUH-1N aircraft into “zero time” UH-1Y transporthelicopters. Both aircraft will receive dramaticincreases in range, payload, and speed. The veryhigh level of common components between the twoaircraft will facilitate a significant reduction in spareparts inventory, number of maintenance personnelrequired, simplify training for pilots and maintenancepersonnel, simplify deployment operations, andvirtually provides two new aircraft for the price of one.

63

UH-1Y – AH-1Z Commonality

For international customers who currently operateeither the AH-1W or UH-1 series aircraft, theopportunity exists for benefiting from a similarremanufacturing program. Totally new manufacturedaircraft will also be offered.First flight for the UH-1Y took place in December2001. International customers can expect to takedelivery of new aircraft beginning in 2006 concurrentwith the USMC program.

64

Applications:

Engines:

Gross Weight:

Useful Load:

Mission Radius:

Max Endurance:

Max Cruise Speed:

Service Ceiling:

Weapon Stations:

Armaments:

Maneuverability:

Identicality with AH-1Z:

Assault TransportAirborne Command & ControlControl of Supporting ArmsAerial ReconnaissanceSearch & RescueArmed TransportAeromedicalNight & Adverse Weather Operations

(2) T-701-GE--401C

18,500 lb / 8,390 Kg

6,661 lb / 3,021 Kg

130 nm / 241 kmTen Troop InsertionCruise @ 3000 ft, 33°C

3.3 hours

158 knots / 293 km/h

20,000 ft + / 6,100 m +

2 Pintle Mounted Guns2 External Stores HardMounts

2.75 inch Rocket Pods( 7 or 19 shot )

-0.5 g’s to +2.8 g’s

84% at Part NumberLevel

65

P.O.Box 482, Fort Worth, Texas 76101Phone: (817)280-2800

An Adobe Acrobat PDFversion of this booklet is

available for download fromthe Bell Helicopter Textron

product information website

www.bellhelicopter.com

Editor: Dave WyattMarketing Publications ManagerPhone: (817) 280-6918E-Mail: dwyatt@bellhelicopter.textron.com

©2006 Bell Helicopter Textron Inc.All Rights Reserved

Printed in USAMarch 2006

66