HH-60G Systems

Caution/Advisory lights when you turn the BATTERY ON

*C2B2ASS* - 1 CONV - 2 CONV - BATTERY ONLY - BOOST SERVO OFF - *BIT CHECK - AC ESS BUS OFF - SAS OFF - STABILATOR

Rated output of CONVERTERS: - VAC & Hz to - VDC & Amps

- 115/200 VAC, 400Hz to - 31-25 VDC, 200Amps

What happens during an Engine Alternator Failure?

- Loss of Ng signal to cockpit (ENG OUT & Audio) - Lost ability for restart (affected engine) - DEC receives airframe power

Cold Weather Control Exercise is required at

-17 degrees C and below

Number of CENTRIFUGAL compression stages in 701C engine

1

The Engine Alternator supplies AC power to:

1. Ignition Exciter 2. DEC 3. Ng signal for the signal data converter (SDC for the VIDS)

Functions of the ODV

1. Provides Hot Start Protection 2. Provides Nf Overspeed Protection 3. Purges fuel nozzles on engine shutdown

Amount of unusable fuel in the probe

1/2 Gallon

Main Generator AUX Bearing life (GEN BRG caution light)

10 hrs

DC Current Limiter Amperage (Between DC Primary Buses)

100 amps

Air refueling on-load rate

1000 lbs/min

Both fire bottles will automatically discharge at _____Gs

10Gs

Ng overspeed protection activates at

110+/-2% Ng

Rated output of APU GENERATOR - VAC - Kva

115/200 VAC 20/30 Kva

Rated output of MAIN GENERATORS: - VAC - Hz - Kva - #Phase

115/200 VAC 400 Hz 30/45 Kva 3 PHASE

Number of fuel injector ports in 701C engine

12

Nf overspeed protection activates at

120+/-1% Nf

ENG OIL PRESS Maximum 5 Minute (yellow) Normal (green) Idle (yellow) Minimum (red)

120: Maximum 100-120: 5 Minute (yellow) 26-100: Normal (green) 22-26: Idle (yellow) 22: Minimum (red)

Balanced flight airspeeds: TAIL ROTOR QUADRANT CAUTION LIGHT ON (WITH LOSS OF TAIL ROTOR CONTROL)

145 KIAS 25 KIAS (but this is for 16,825 GW, our numbers will be closer together)

Max nose up, left/right side slope landing condition

15 degrees

APU Fuel consumption

150 pph

ENGINE OIL TEMP Maximum (red) 30 Minute limit (yellow) Continuous (green)

150C: Maximum (red) 135-150C: 30 Minute limit (yellow) -50-135C: Continuous (green)

Design gross weight of the H-60

16,825

Usable fuel in the 185 Gallon Tanks

170 Gallons So, you will be showing about 201 lbs in the AUX tanks when that transfer pump is no longer sucking (1 bar on each side of the EFQI) 15gals x 2tanks x 6.7lbs= 201lbs; Each EFQI bar=100lbs

Fuel dumping will automatically stop at __________ lbs of fuel in each tank (hopefully)

172 lbs in each tank

FUEL LOW illuminates at approximately

172 lbs in respective tank

Maximum power (TRQ) loss with ENG ANTI ICE ON

18%

Max weight for FRIES bar - Intermediate - Fully extended FRIES: Fast Rope Insertion Extraction System

1800 lbs Intermediate 1300 lbs Fully extended

Shaft horsepower of the 701C engine

1940 SHP -1940 SHP: 2.5 min/Contingency Power -1890 SHP: 10 min -1800 SHP: 30 min -1662 SHP: Continuous

Number of deck mounted fire detectors:

2 (Both engines, not the APU)

If APU does not start, you must wait how long before restarting?

2 mins

Cool down required prior to engine shutdown

2 mins at <90%Ng

AUX tank G ratings

20 Gs forward 10 Gs vertical 18 Gs lateral

Nf avoid range

20-40%Nf 60-90%Nf

Hoist cable length

200 ft

Max gross weight of the H-60

22,000

Rated Capacity of the BATTERY: - Volts - Amps

24 VDC 9.5 Amp

Main fuel tanks hold APPROXIMATELY ______________lbs of fuel

2400 lbs of fuel

SUBMERGED BOOST PUMP output pressure

25-27 psi

Minimum accumulator charge to start the APU

2800 psi

Number of wall mounted fire detectors:

3 (Both engines and APU)

Max number on the rope ladder (clipped in)

3 persons per side

APU operating limits: Rotors turning

30 mins when OAT is 43C and above

The fuel transfer pump will fail in ______________ (time) if the AUX tanks run dry and it is left on

30 seconds

WX Radar beam width

30' diameter 15' radius 180 degrees around antenna

Acceptable TGT increase during HIT check when ENG-ANTI ICE is turned on

30-110 degrees above threshold

Max descent rate for landing >16,825 lbs (level & slope)

300 FPM Level 180 FPM Slope

Cabin Floor Load Capacity

300 lbs per square foot

GCU Under-Frequency protection: (Hz range)

370-380 Hz

Maximum power (TRQ) loss with HEATER ON

4%

Max wind velocity for rotor start/stop

45 Kts

ENGINE DRIVEN FUEL PUMP output pressure

45-90 psi

Number of AXIAL compression stages in the 701C engine

5

Total number of fire detectors:

5 (Deck & Wall for each engine, Wall for APU)

PRIME BOOST PUMP output pressure

5 psi

Prime fuel pump output psi

5 psi

Max allowable torque split (torque stiction)

5% TRQ

Engine Starter Dropout speed ("In the band...")

52-65% Ng

Post Engine Shutdown Fire can occur if TGT rises above:

538 C

Max descent rate for landing <16,825 lbs (level & slope)

540 FPM Level 360 FPM Slope

ENG OUT caution light and steady tone

55%Ng

NO FUEL XFER illuminates at

550+/-55 lbs

Number of Scavenge Elements in engine oil pump

6

Total number of current limiters in the electrical system

6 AC (60 AMP) + 1 DC (100 AMP) =7 TOTAL

Max tail up slope (nose down slope) landing condition

6 degrees

Hoist capacity

600 lbs

Inflight HIT Check torque setting

62%

Overall length of the HH-60 (Refueling Probe Retracted)

64' 10" (rotor tips)

AC Current Limiter Number & Amperage (Between AC Primary Buses)

6x60 amp current limiters

Engine Oil Tank Capacity

7.6 US Quarts

Max Cargo hook weight

8,000 lbs

Fuel dump rate

800 lbs/min

HMU Fuel vane pump maximum output pressure

832 psi

Number of wire strike cutters/deflectors

9

Requirements for a Crossbleed Start

90% Ng 100% Nr AIR SOURCE HEAT/START - ENG ENG ANTI-ICE (LIGHTs) OFF APU - OFF

ENG INCR/DCR TRIM operating range (DEC)

96-100%Nf (1% inside continuous range)

#1 or #2 ENGINE OIL PRESS illuminates

<22 psi (same as minimum on VIDs)

Battery life with & without transmitting on UHF/VHF i.e. #1 AND #2 CONV CAUTION LIGHT ON (WITHOUT AC ESS BUS OFF LIGHT)

<44 mins Not Transmitting <33 mins Transmitting

OAT in which ENG INLET ANTI-ICE MUST be on: MAY or MAY NOT be on: SHALL NOT be on:

<4C: MUST be on 4-13C: MAY or MAY NOT be on >13C: SHALL NOT be on

#1 or #2 FUEL PRESS illuminates when

<9 psi between ENGINE DRIVEN fuel pump and FUEL FILTER

#1 or #2 FUEL PRESS illuminates at

<9psi "between the Engine Driven Low Pressure Fuel Pump and the HMU High Pressure Fuel Pump" (that's per the -1, but one of the instructors said between the Engine driven fuel pump and the filter)

#1 or #2 ENGINE OIL TEMP illuminates

>150C (tripped by VIDS)

AIRFRAME

AIRFRAME

ANTI-ICE Switch - OFF: The AISB valve opens at low Ng, and _____________ when Ng> _____-_____%

AISBV will open at low Ng and *closes* when Ng>*88-92% Ng* with the ANTI-ICE OFF When ANTI-ICE ON, the AISBV will open at low Ng and remains open above 88-92% Ng

ANTI-ICE Switch - ON: The AISB valve opens at low Ng and ___________ when Ng> _____-_____%

ANTI-ICE ON: AISBV will open at low Ng and *remains open* above *88-92% Ng* ANTI-ICE OFF: AISBV will open at low Ng and close when Ng>88-92% Ng

APU ACCUM LOW Illuminates when

APU is below 2800 psi

APU operating limits: Rotors not turning

APU may be operated Continuously up to 51C

Actions if APU OIL TEMP HI illuminates

APU should be shut down immediately to prevent damage. After a 30 min cooling period, oil level should be checked prior to restart

The 4 basic modules/sections of the 701C engine

COLD HOT POWER TURBINE ACCESSORY

#1 or #2 ENG INLET ANTI-ICE will illuminate when

Engine inlet anti-icing fairing temp is >93C

Angle of Incidence required for Wire Strike Protection

Horizontal wire strung 60-90 degrees to flight path

Single-engine operation with the gust lock engaged is limited to _______ only (pg 5-3, Dash-1)

IDLE

LANDING LIMITS

LANDING LIMITS

Where does the APU get its fuel?

Left Main Tank

Hot Start Protection (HSP) is part of the DEC. When Nf and Ng are below their respective Hot Start references (Ng<____%; Nf<____%) and TGT exceeds __________C, an output from the HSP system activates a solenoid in the ODV. (pg 1-3, Dash-1)

NF<50 (f for fifty) NG<60 (shmeh... G kind of looks like a 6) TGT>900 C

Pilot can disable the HSP for emergency starting purposes by____________________________. (pg 1-4, Dash-1)

Pilot can disable the HSP for emergency starting purposes by *pressing and holding the overspeed test button (TEST A or B) for the engine being started during the start sequence*

If the APU should shut itself down, or does not start for any reason

Place the APU CONTR switch OFF Do not cycle the BATT switch with the APU CONTR switch ON as this may cause the APU to restart (possibly resulting in overspeed/overtemp of the APU) Turning the BATT switch OFF or cycling the APU CONTR switch will reset ESU and malfunction BITE indicators, resulting in loss of shutdown reason.

Slope landing limit is decreased _______ degrees for every ______ KTS of wind

Slope landing limit is decreased 2 degrees for every 5 KTS of wind

#1 or #2 FUEL FLTR BYPASS illuminates when

The fuel filter is bypassed due to clogging

What do the GCUs provide?

Voltage regulation Overvoltage protection Undervoltage protection Feeder Fault (short) protection Under frequency protection Under frequency protection is only available on the ground, in flight it is disabled by the right WOW switch