s70a Technical Information

SIKORSKY INTERNATIONAL BLACK HAWK HELICOPTER

S-70A Technical Information

UH-60A/L BLACK HAWK

U.S. ArmyArmy National Guard

Army ReserveU.S. Customs

Medical Service Corps

SH-60B SEAHAWK

U.S. Navy LAMPS Mk III

EH-60A QUICK FIX

U.S. Army

EH-60B SOTAS

U.S. Army

HH-60D NIGHT HAWK

U.S. Air Force

VH-60N EXECUTIVE TRANSPORT

U.S. Marine Corps

MH-60G PAVE HAWK

U.S. Air ForceAir Force ReserveAir National Guard

UH-60Q MEDICAL EVACUATION

U.S. Army

MH-60KSPECIAL OPERATIONS

U.S. Army

S-70B FMS

SpainThailand

S-70B

Australia (RAN)JapanGreeceTurkey

S-70A

ArgentinaAustralia (RAAF)

BrazilBruneiChile

Hong KongJapanJordan

MalaysiaMexico

MoroccoPhilippines

Turkey

S-70C

BruneiPRC

Taiwan

UH-60A/L FMS

BahrainColombia

EgyptIsrael

Saudi Arabia

UH-60P

Korea

S-70A Firehawk

Various Operators

SH-60F CV HELO

U.S. Navy

HH-60H HCS

U.S. Navy Reserve

HH-60J JAYHAWK

U.S. Coast Guard

CH-60S

U.S. Navy

SH-60R

U.S. Navy

H-60/S-70ALINEAGE

S-70A INTERNATIONAL BLACK HAWK HELICOPTER

1

JULY 2000

H-60/S-70ALINEAGE

Since its introduction,the Black Hawkhelicopter and its derivatives haveamassed over fivemillion flight hours

VIP TRANSPORT

SEARCH AND RESCUE

UTILITY

NAVAL

ARMY

MARINE CORPS

NAVY

ARMY NATIONAL GUARD

AIR FORCE

COAST GUARD

TECHNICALINFORMATION

2

JULY 2000


H-60/S-70 PROGRAM

STATUS

UNITED STATES MILITARY CUSTOMERS

INTERNATIONAL CUSTOMERS MISSIONS

H-60 BLACK HAWK SERIES

Delivered 1,725Fleet Flight Hours 3,200,000

SH-60 NAVAL HAWK SERIES

Delivered 354Fleet Flight Hours 1,500,000

S-70A/B INTERNATIONAL HAWK

Delivered 583Fleet Flight Hours 700,000Countries 24


1

JULY 2000


Weights and Performance

WEIGHTS

Maximum takeoff gross weight 22,000 lb 9,977 kgEmpty weight, standard configuration 11,744 lb 5,326 kgMaximum gross weight, external load 23,500 lb 10,658 kgMaximum external load 9,000 lb 4,082 kg

POWERPLANT

ratings per engine, standard day, sea level

Type Two General Electric T700-GE-701C2.5-minute OEI contingency 1,940 shp 1,447 kw10-minute takeoff power 1,890 shp 1,409 kw30-minute intermediate power 1,800 shp 1,342 kwMaximum continuous power 1,662 shp 1,239 kwNormal fuel capacity, usable 359.7 gal 1,362 l

PERFORMANCE

22,000 lb gross weight, standard day, sea level unless otherwise noted

Maximum speed (VNE) 195 kts 361 km/hrMaximum cruise speed (VH) 149 kts 276 km/hrMaximum rate of climb 2,250 ft/min 11.43 m/secService ceiling 13,200 ft 4,021 mHover ceiling, out of ground effect 4,300 ft 1,311 mHover ceiling, in ground effect 9,000 ft 2,743 mOEI service ceiling 3,700 ft 1,128 mRange at Long Range Cruise Speed*- Internal fuel 248 nm 460 km- Internal fuel plus two 230 US gallon external aux tanks 591 nm 1,095 km

* 4,000 feet, 132 knots, 20-minute reserve

BLACK HAWKs are powered by two T700-GE-701Cengines, which provideefficient, reliablepower in all types ofoperating conditions


2

JULY 2000


Specifications

DIMENSIONS

Overall length 64.83 ft 19.76 mOverall width 53.67 ft 16.36 mOverall height 17.50 ft 5.33 mFuselage length 50.04 ft 15.26 mFuselage width 14.33 ft 4.37 mFolded length * 41.33 ft 12.60 mFolded width * 9.72 ft 2.96 mFolded height * 8.98 ft 2.74 mWheelbase 28.92 ft 8.82 mMain wheel tread 8.88 ft 2.71 m

ROTORS

Main rotor diameter 53.67 ft 16.36 mTail rotor diameter 11.00 ft 3.35 m

* Air transport configuration: main rotor hub lowered, main rotor blades, stabilator and tail pylon folded.

53' 8" (16.36m)

3°12' 4"

(3.76m)

9' 5"(2.87m) 7' 8.5"

(2.35m) 5' 9"(1.75m) 6' 6"

(1.98m)

28' 11" (8.82m)

Length - Rotors and Pylon Folded 41' 4" (12.60m)

50' .75" (15.26m)

64' 10" (19.76m)

11' 0"(3.35m)

9' 8.6"(2.96m)

21’ 2"(6.45m)

14' 4"(4.37m)

8' 10.6"(2.71m)


3

JULY 2000


Large sliding cabindoors on both sides of the aircraft allowfast and easy ingressand egress

Cabin Dimensions

84" at cabin doors

72" at floor level

54.25" 53.5"

Drippan

Main rotorcenter line

Cabin Floor

STA247.0

STA256.5

STA341.2

STA398.0

STA266.0

68.0"Cabin doors

151.0"

GENERAL DATA

Cabin length 12.58 ft 3.84 mCabin width 7.00 ft 2.14 mCabin height 4.50 ft 1.37 mCabin area 88.00 sq ft 8.18 sq mCabin volume 396.00 cu ft 11.22 cu mStorage compartment volume 20.34 cu ft 0.58 cu mCapacity, normal 12 passengers plus 2 pilotsCapacity, maximum 20 passengers plus 2 pilots

SEARCH AND RESCUE

Ten rescueesTwo crew

CASUALTY EVACUATION

Six littersFive crew

TROOP TRANSPORT

12-20 troop seatsTwo crew

S-70 Offers Flexible Cabin ArrangementsTECHNICALINFORMATION

4

JULY 2000


Roomy cabin and large doors enhance HAWK helicopter effectiveness in SAR missionsWell-placed tie-down fittings contribute to S-70cabin flexibility


5

JULY 2000


Stroking crew seatsare armored, offeringmaximum crash andballistic protection

Survivability and Crashworthiness Design Features

SAFETY

Designed with state-of-the-artsafety and reliability featuresPadded cabin designed to FAAregulations for G-loading,egress, flammabilityLoad limiting crew and troopseatsJettisonable cockpit doorsCrashworthy fuel cells (65 footdrop)Energy absorbing landing gear(30 fps limits)Anti-plow keel beamsHigh mass components areretained in 20/20/18G crashconditions

23mmtolerant

mainrotorblade

Modulartransmissionwith fail-safelubrication

Ballisticallytolerant

upper controlsand hub

IR suppressors

Redundant fail-safe tail rotor controls

Superior OEIperformance Large vertical

tail providesdirectional

stability aftertail rotor loss

Self-sealingfuel tanksand lines

23mm tolerantstructure

Redundantcontrol system

Triple redundanthydraulic and

electrical systems

Armored pilot andco-pilot seats

Spall resistantwindshield and

cockpit structure

Wire cutters

23mmtolerant

mainrotorblade

Modulartransmissionwith fail-safelubrication

Ballisticallytolerant

upper controlsand hub

IR suppressors

Redundant fail-safe tail rotor controls

Superior OEIperformance Large vertical

tail providesdirectional

stability aftertail rotor loss

Self-sealingfuel tanksand lines

23mm tolerantstructure

Redundantcontrol system

Triple redundanthydraulic and

electrical systems

Armored pilot andco-pilot seats

Spall resistantwindshield and

cockpit structure

Wire cutters

Troop seats with five-point harness provides max-imum protection for cabin passengers

Large cabin doors and windows allow quickescape in emergency conditions

Landing gear absorb energy of up to 30 feet persecond and provide wirestrike protection

Swing-out armor side panels protect pilot andcopilot from ballistic threats


6

JULY 2000


Utility Configuration

AIRFRAME

Nose and transition section equipmentcompartmentsTwo hinged jettisonable cockpit doors withemergency “pop-out” windowsTwo cabin gunner stations with sliding hatchesTwo cabin sliding doors with two jettisonablewindows eachHeated glass windshieldsWindshield and gunners’ stations windowsdefogging and defrostingDual windshield wipersBleed-air heating systemBlower ventilation systemArmored pilot and copilot seats410 cubic foot cabin with 300 psf cabin floor andprovisions for up to 20 seatsCrashworthy cabin troop seating for 15 troopsQuilted cabin head and side linersTwo 20 cubic foot storage compartmentsUpper and lower wire strike protection systemsDoor and ignition locks9000 lb capacity cargo hookGunner station hardpoints for 7.62 mm pintle-mounted gunsFixed, tail-wheel type main landing gearDual oleo main landing gear with kneelingcapability for transport configurationSwiveling tail wheel with locking capabilityTwo hand-held fire extinguishersHard points for External Stores Support System(ESSS) or External Tank System (ETS)Manual tail pylon foldLow reflective paintSlewable stabilator with automatic and manualcontrol

POWERPLANT AND FUEL SYSTEM

Two General Electric T700-GE-701C engines withintegral particle separatorsAPU for engine start, ground power, and in-flightemergency powerDual suction fuel systems with self-sealing lines,breakaway fittings and crossfeed capabilityDual crashworthy, self-sealing fuel tanks with atotal capacity of 360 gallonsFuel boost pumps for prime and high altitudeoperationSingle point gravity and pressure fueling anddefuelingLow level fuel warning systemEngine and APU fire detection and extinguishingsystemsEngine anti-icing systemHover Infrared Suppression System (HIRSS)Main transmission with two isolatedinput/accessory modulesIntermediate and tail gearboxes withinterconnecting drive shaftsMagnetic chip detectors with fuzz burn-offcapability

ROTOR AND CONTROLS

Four-blade articulated main rotor system with one-piece titanium hub and elastomeric bearingsBallistically tolerant main rotor blades with titaniumspars, fiberglass skins, and honeycomb coresBifilar vibration suppression systemProvisions for manual blade fold (four blades aft)Dual, redundant and isolated pilot flight controlsDual, redundant parallel primary and tail rotorservos with jam protectionTail rotor centering quadrantDual, independent, transmission-powered 3000 psihydraulic systemsThird, back-up, electrically-powered 3000 psihydraulic systemRedundant stability augmentation system withairspeed, attitude and heading holdFour-blade, cross beam tail rotorComplete provisions for main and trail rotor bladede-ice systemsManual rotor brake

BLACK HAWKs can liftexternal loads up to9000 pounds

Tail landing gearswivels to improvemaneuverability of aircraft when on the ground


7

JULY 2000


Utility Configuration

ELECTRICAL

Two 30/45 KVA AC generatorsTwo 200 amp DC convertersSingle 20/23.8 KVA APU-driven AC generatorSingle 10.0 amp-hour batteryExternal power monitor panelControllable landing lightControllable IR searchlightStandard and IR position lightsTwo anti-collision strobe lightsNVG-compatible cockpit and cabin lightingPortable maintenance/inspection lightTwo cabin DC receptaclesTwo cabin AC receptaclesControllable search light

AVIONICS

Command instrument systemDual AN/ARC-222 VHF/AM-FM communication radiosFM homing system for single AN/ARC-222 Five-station C-6533 ICSSingle AN/ASN-43 gyro magnetic compassSingle AN/ARN-149 ADFSingle AN/ARN-147 VOR/ILS/MBSingle TNL-8100 GPSSingle AA-300 radar altimeterSingle AN/APX-100 IFF transponderComplete provisions for:- AN/APR-39(V)1 radar warning system- AN/ALQ-144 IR jammer- M-130 chaff dispenser- Single AN/ARC-164 UHF-AM

INSTRUMENTS

Airspeed indicators (2)Vertical velocity indicators (2)Barometric altimeterEncoding altimeterStandby magnetic compassOutside air temperature indicatorMaster warning panels (2)Caution advisory panelVertical situation indicators (2)Horizontal situation indicators (2)VSI/HSI mode selectors (2)Stabilator angle indicators (2)Digital clocks with sweep second hands (2)Dual, heated pitot static systemVertical Instrument Display System (VIDS)containing:- Dual power turbine tachometers - Dual main rotor speed tachometers- Dual engine torquemeters- Fuel quantity indicators and totalizer- Main transmission oil temperature and pressureindicators

- Engine oil temperature and pressure indicators- Power turbine inlet temperature indicators- Rotor overspeed monitor

The BLACK HAWK's cockpit features large, easy-to-read displays and well-organized controls

Central Display Unit(CDU) providesinstant, easy-to-readinformation on engineand transmissionperformance

Optional Mission EquipmentS-70 flexibility is enhanced with a wide range of optional mission equipment


8

JULY 2000


External Stores Support System (ESSS) External Tank System (ETS)

30-million candlepower Nightsun

600-pound capacity external rescue hoist

ANVIS/HUDEmergency flotation system

Six-patient litter system

Loudhailer


9

JULY 2000


Optional Electronic EquipmentAvailable optional electronics satisfy the most stringent mission requirements

NAVIGATION/COMMUNICATIONS

ADF-60MDF-124DME-42FMS-800 flight management systemTDR-90 transponderELT

MISSION SYSTEMS

Color weather radarFLIRDigital map

“Glass” cockpit

Weather radar and FLIR

Moving digital mapdisplays are offered asa component of thedigital “glass” cockpit

Digital multi-function display panels combine information from multipleanalog displays, reducing cockpit clutter and aircrew workload

Overhaul Periods and Retirement TimesTECHNICALINFORMATION

10

JULY 2000


SCHEDULED OVERHAUL PERIOD (TBO)

The following overhaul periods apply to the latest configuration of the affected component. Please refer toManual TM 1-70-23AW-2 for current official TBOs.

COMPONENT

Main rotor blade spindle nut 500 hoursOil cooler axial fan 2,000 hoursTail rotor pitch change shaft 2,000 hours

SCHEDULED RETIREMENT TIMES

The following retirement times apply to the latest parts and components available for the S-70A helicopter. The list below includes all significant items with retirement life limits less than 5,000 flight hours. Please refer toManual TM 1-70-23AW-2 for current official life limits.

LIFE LIMIT

Oil cooler viscous bearing 500 hoursTail rotor drive shaft bearing 2,000 hoursPitch control shaft bearing 2,000 hoursMain rotor blade spindle nut 2,500 hoursTail landing gear shock strut piston 3,000 hoursMain rotor blade expandable pin 4,700 hours

Retractable steps and recessed hand- andfootholds allow easy access to entire aircraft

Engine cowlings which open to become stablework platforms and designated walk areas allowaccess and protect aircraft during maintenance

Retractable and pop-out steps and handhold easefield and base maintenance by providing easyaccess to work areas

The operating data provided herein are estimates only. Sikorsky endeavors to ensure that this data is cur-rent and meaningful for operating cost evaluations. Sikorsky, however, does not warrant, and you shouldnot rely upon, this data as defining the operating costs or overhaul/retirement times for any particular S-70aircraft or its components.

Direct Operating CostUtility Service

Survivability

Crashworthiness

Lower cost

Mission flexibility

Black Hawk: the multi-mission choice

Superior performance

The following information is supplied to aid in the preparation of estimates of the cost of operation for theS-70A helicopter in utility service. Costs have been calculated in general accordance with the practices describedin Guide For Presentation of Helicopter Operating Cost Estimates, published by the Committee on HelicopterOperations Cost. The estimates presume a mature operation in which there has been opportunity for costs tostabilize and assumes no benefit from warranties.

Direct operating costs are calculated for an S-70A flying 345 hours per year for eight years. Unscheduledremovals and overhauls are based on historical fleet-wide data.

Sikorsky Estimate

Fuel and Lubricants $335.39- Average fuel consumption at 162 gallons/hour- Fuel cost per gallon: $2.01- Cost for lubricants at 3% of fuel

Labor $245.43- 4.55 Total maintenance MH/FH- Labor rate at $54 per hour

Reserve for Retirement Items $152.00Reserve for Overhaul and Unscheduled Repairs $365.00

- Airframe and avionics- Engine parts

Reserve for Engine Overhaul $188.00

Total direct cost per hour $1,285.82

Multi-missionflexibility makes Black Hawk theaffordable choice formedium lift helicopters


11

JULY 2000


Payload/Range PerformanceBasic Configuration


12

JULY 2000


MISSION

Takeoff at maximum gross weightCruise at 4,000 feet, ISA, Long Range Cruise Speed*Reserve: 20 minutes at Long Range Cruise Speed*

ESSS with two ESSS with fourClean 230 gallon tanks 230 gallon tanks

WEIGHTS

Basic Empty Weight 11,744 lb 11,744 lb 11,744 lb

ESSS and External Fuel Provisions 60 lb 60 lb 60 lbESSS (Four Station) – 660 lb 660 lb230 US Gallon Aux Fuel Tanks (0, 2, 4) – 320 lb 640 lbCrew (3) 705 lb 705 lb 705 lbFluids 60 lb 60 lb 60 lbOperating Weight 12,569 lb 13,549 lb 13,869 lb

* Speed for 99% best specific range


13

JULY 2000


Hover CeilingFive Foot Wheel Height, Ten Minute Rating, HIRSS Active

Hot and high, Arcticcold…and everythingin between - BlackHawks perform theirmissions safely andreliably


14

JULY 2000


Hover Ceiling - Out of Ground EffectTen Minute Rating, HIRSS Active


15

JULY 2000

Twin Engine Service CeilingIRP, 100 fpm ROC, VBROC


The Black Hawk’slegendary ruggednessand survivability havemade it the world’spremier medium utility helicopter


16

JULY 2000


Single Engine Service CeilingIRP, 100 fpm ROC, VBROC

Level Flight Fuel Consumption - Sea Level-701C Engines, Clean, HIRSS Active


17

JULY 2000


External fuel tanksextend the range of the S-70 - allowingit to cover the vastdistances required inmany SAR missions.


18

JULY 2000


Level Flight Fuel Consumption - 4,000 Feet-701C Engines, Clean, HIRSS Active


19

JULY 2000



Speed, power, rangeand reliability - thequalities Black Hawkoperators know theycan rely on


20

JULY 2000



www.sikorsky.com

SEPTEMBER 2002 S70A TI S70-046

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s70a Technical Information