HH-60W Boldface + Ops Limits

Crossbleed starts shall not be attempted unless: (x3)

- ENG ANTI ICE light extinguishes on source engine - 90% NG - 100% NR

TGT limiting does not prevent overtemperature during: (x3)

- Engine starts - Compressor stall - When the engine is operated in LOCKOUT.

-1 Prohibited Maneuvers (x6)

- Hovering turns greater than 30° per second - Simultaneous movement of both PCLs to IDLE or OFF (PCL chop) in flight - Practice touchdown autorotations - Flight beyond a 90° AOB or 45° nose up/down - Aerodynamic braking with collective full down once mains touch down - Rearward ground taxi

Ng Limits: NOTE On the PFD power pod, Ng digital readout will appear when: (x3)

- Ng exceeds 100% - Difference between Ng1 and Ng2 exceeds 5% - Either engine is out

NOTE: On the power pod, TGT will appear when: (x3):

- TGT exceeds 793C (transitions from normal to 30 min limit) - The difference between TGT 1 and TGT2 exceeds 75 degrees C - Either engine is out

Helicopters with the following equipment installed, operational, and turned on are permitted to fly into trace or light icing conditions: (x5)

- Windshield Anti-ice - Pitot heat - Engine Anti-ice - Engine Inlet Anti-ice modulating valve - Insulated Ambient Air Sensing Tube

Do not power up the EO/IR in temperatures below _______. For reliable performance the EO/IR must be stabilized at temperatures of _______ or greater for 30 minutes prior to operation. After the EO/IR has stabilized for 30 minutes, and powered up and running for an additional 30 minutes, the EO/IR can operate down to -55°C reliably.

-40°C

Backup Hydraulic Pump Hot Weather Limits: -54-32 C Operating time: Cooldown time:

-54-32 C Operating time: UNLIMITED Cooldown time: NA

BOLDFACE: DUAL ENGINE FAILURE

1. AUTOROTATE.

BOLDFACE: LOSS OF TAIL ROTOR THRUST IN CRUISE FLIGHT

1. AUTOROTATE. 2. PCLs - OFF.

Alternate Fuel Limitations: Fuel boost pumps shall be ON when operating with JP-4 or equivalent and either: (x2)

1. At 5,000 ft pressure altitude and above, or 2. At any altitude with either fuel selector in crossfeed.

BOLDFACE: LOSS OF TAIL ROTOR THRUST OR T/R QUAD FAIL CAUTION ILLUMINATES WITH LOSS OF CONTROL AT LOW AIRSPEED/HOVER (RIGHT ROTATION)

1. Collective - REDUCE. 2. PCLs - OFF.

The automatic contingency power limiting will switch to a higher single engine 2.5-minute TGT limiting value of approximately 903 C (upper end of 2.5 min) when any of the following conditions are met: (x3)

1. NP drops below 96%. (95 is bottom of continuous range) 2. Greater than 3% droop between reference NP and actual NP. (Ng is 5%) 3. Greater than 5% per second NP droop rate exists and NP less than or equal to NP reference speed.

Transmission Oil Pressure: Sudden pressure drop (more than ______ psi) without fluctuation requires an entry on the appropriate maintenance form.

10 psi

At engine power levels of ______% Q per engine and below, full anti-ice capability cannot be provided, due to engine bleed limitations

10%Q

Maximum airspeed for autorotation is ______ KIAS.

120

Landing light. If use is required, the landing light must be extended prior to reaching a maximum forward airspeed of ______KIAS

130

Maximum airspeed for one engine inoperative is _____ KIAS.

130

Maximum airspeed with external cargo hook loads up to 8,000 lbs is _____ KIAS.

140

Two SAS inoperative in IMC — _____ KIAS

140

Two hydraulic systems malfunctioning in IMC — ______ KIAS.

140

Cabin door(s) may be fully open up to _____ KIAS.

145

Nose downslope landings with tail winds greater than _____ kts are prohibited.

15

Two SAS inoperative — _____ KIAS

150

Two hydraulic systems malfunctioning — _____ KIAS

150

Rescue hoist searchlight. If use is required, the rescue hoist searchlight must be extended prior to reaching a maximum forward airspeed of _____ KIAS.

155

Searchlight. If use is required, the searchlight must be extended prior to reaching a maximum forward airspeed of ______ KIAS

155

Maximum airspeed the gunner's window can be open is ______ KIAS

170

One SAS inoperative — ______ KIAS

170

One hydraulic system malfunctioning — _____ KIAS

170

Sec 7 With ENGINE ANTI-ICE-ON, the available torque per engine is reduced by _____%

20%

Sec 7 With COCKPIT HEATER-ON, reduce torque available with the engine Anti-Ice on by an additional ______%

20% So 5.3% + 20% = 25.3%

CAUTION: To avoid aircraft damage, do not operate the engine steady state in the NP ranges of ________ and ________.

20-40% 60-90%

The maximum gross weight is ____________ lbs when payload on the cargo hook is at least 1,000 lbs, but not more than 8,000 lbs.

23,500

Maximum weight limit per platform on the litter is _____ lbs distributed weight.

246

Windshield anti-ice shall not be used when OAT is over ________

27 C

Nose upslope and right/left wheel upslope landing limitations shall be further reduced by _____ for every _____ kts of wind.

2°/5 kts wind

The main gear box may be operated up to ______ minutes at a time with pressure fluctuations when the helicopter is known to be at a nose-up attitude (i.e. slope landings or hover near aft CG).

30

Actions if APU OIL HOT illuminates:

30 Minute cooling period Check oil level

Landing Limits: Maximum touchdown sink rate is ______ fpm on level terrain, and ______ fpm on slopes.

300 FPM - Level 180 FPM - Slopes

Bank angles shall be limited to _______ when a PRI SERVO 1 FAIL or PRI SERVO 2 FAIL caution is illuminated

30°

During insertion/extraction of personnel with the FRIES bar, maximum pitch and/or bank angles are limited to:

30°

Backup Hydraulic Pump Hot Weather Limits: 33-38 C Operating time: Cooldown time:

33-38 C Operating time: 24 Minutes Cooldown time: 72 Minutes

Backup Hydraulic Pump Hot Weather Limits: 39-52 C Operating time: Cooldown time:

39-52 C Operating time: 16 Minutes Cooldown time: 48 Minutes

WARNING A 3-5 kts crosswind or tailwind may increase torque required by up to _____% over zero wind values.

4

If the automatic stabilator control system fails in flight and operation cannot be restored (Manual mode available): 1. The stabilator shall be set full down at speeds below _____ KIAS. 2. The stabilator shall be set to 0° at speeds above ______ KIAS.

40

Sideward/rearward flight limits. Hovering in winds greater than _____ kts from the sides or rear is prohibited. Sideward/rearward flight into the wind, when combined with windspeed, shall not exceed _____ kts.

45

Transmission Oil Pressure: If oil pressure is not steady during steady state forward flight or in a hover, or if oil pressure is steady but under ______ psi, make an entry on the appropriate maintenance form.

45 psi Note, this pressure will show as green with no applicable caution light

Transmission Oil Pressure: Oil pressure should remain steady and should be in the _____________ psi range to ensure that when fluctuations occur, they remain in the acceptable range.

45-60 psi

WARNING Power required to hover can vary significantly (greater than ____% torque) in light winds, due to their highly unpredictable nature.

5

Sec 7 With COCKPIT HEATER-ON at sea level, the available torque per engine is reduced by _____% at sea level.

5.3% (worst case)

Maximum forward touchdown ground speed on level terrain is _____kts.

60

After fuel dumping has ceased, the fuel quantity indicator may take up to ______________ to stabilize at the actual fuel quantity. Indicated fuel quantity may lag actual fuel quantity by as much as _________ lbs.

60 seconds 600 lbs

The maximum weight that may be suspended from the rescue hoist is ______ lbs.

600

The maximum weight that may be suspended from the FRIES release arm, in either the intermediate or fully extended position, is ______ lbs on either side or both sides simultaneously for a total weight of __________ lbs.

750 1500

Rotor Brake/Gust Lock limits: Rotor brake shall not be applied with engine(s) operating and rotor turning except during an emergency stop. Maximum rotor speed for emergency rotor brake applications is ______ NR.

76% Nr

The maximum weight that may be suspended from the cargo hook is _______ lbs.

8,000

Maximum airspeed during FRIES extraction operations is ____ KIAS.

80

To prevent excess tail rotor system loading, avoid abrupt, full pedal input above _____ KIAS.

80

TGT Limits: Start Abort Limit (prior to 63%NG):

851 C prior to 63%NG (idle), same as the G

The TGT limiting system limits fuel flow when the TGT reaches the dual engine 10-minute limiting value of approximately _____ C (top end of 10 min range).

879 C - 10 Min Limiting Value 6CF: DECU 10 min limiting 879+/-9 (870-888)

Sec 7 With COCKPIT HEATER and CABIN HEATER both ON, reduce torque available by ______% at sea level.

9.6%

The automatic contingency power limiting will switch to a higher single engine 2.5-minute TGT limiting value of approximately _____ C (top end of 2.5 min range)

903 C - 2.5 Min Limiting Value 6CF: DECU 2.5 min limiting 903 +/-10 (893-913)

If any limits included in this section are exceeded, remarks concerning the degree and the duration the limits were exceeded shall be entered in ________________.

AFTO Form 781A or aircraft forms.

WARNING When performing hover operations with light and variable winds, at high gross weight and/or in a high density altitude environment:

Add a margin to the power required computations (i.e. maybe OGE+10 or 10'Hover + 15)

The airspeed operating limits charts define VNE as a function of __________, __________, and __________ not to exceed 176 KIAS

Altitude Temperature Gross weight

For crossbleed starts, how much donor NG should be used?

As much NG as possible without breaking ground to a hover

The _____________ system should be turned off before initiating a high rate of descent.

Cabin Heating System

Engine Oil Pressure: 5 Minute Limit Normal Idle ENG 1/2 OIL PRESS Illumination (not in -1)

Engine Oil Pressure: 100-120 psi - 5 Minute Limit 26-100 psi - Normal 22-26 psi - Idle 22 psi - ENG 1/2 OIL PRESS Illumination (not in -1)

Engine Oil Temp: ENG 1/2 OIL HOT Illumination (not in -1) 30 Minute Limit Continuous

Engine Oil Temp: 150C - ENG 1/2 OIL HOT Illumination (not in -1) 135-150C - 30 Minute Limit -20-135C - Continuous

Flight into _________ or __________ icing is prohibited

Flight into heavy or severe icing is prohibited

NOTE The ice detecting system is calibrated for 100 KIAS. When flying at airspeeds above 100 KIAS, the ice rate meter will indicate ______________ Liquid Water Content (LWC) than the actual conditions.

Higher

Rotor Brake/Gust Lock limits: Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at _______ only.

IDLE

Avoid operation under conditions of extreme low power requirements, such as high rate of descent (1,900 fpm or greater), or ground bleed air HEATER operation below 100% NR, during __________ conditions.

Icing

Alternate Fuel Limitations: When a helicopter operating with ________ is restarted within 2 hours of engine shutdown and the air temperature is above 21 C, a minimum of 2 minutes of dual engine ground operation at 100% NR is required prior to takeoff to purge possible hot fuel from engine area.

JP-4

Flight into _________ icing is not recommended without blade de-ice

Light

Rotor Brake/Gust Lock limits: Minimum rotor brake pressure for engine start is ______ psi. Maximum rotor brake pressure for engine start is ______ psi.

Minimum rotor brake pressure for engine start is 450 psi. Maximum rotor brake pressure for engine start is 690 psi.

With the 5 requirements for icing and blade de-ice, flight into ____________ icing is permitted.

Moderate

Ng Limits: 12 Second Transient Continuous

Ng Limits: 105-106%: 12 Second Transient 0-105%: Continuous

Rotor Brake/Gust Lock limits: Are single/dual engine starts and operation at IDLE time limited?

No

A low-frequency lateral oscillation may occur when landing nose ________ -slope with the cyclic near the _____ stop.

Nose Down-Slope Aft

Np Limits: 12 Sec Transient: Transient: Continuous: Transient:

Np Limits: 105-107%: 12 Sec Transient 101-105%: Transient 95-101%: Continuous 91-95%: Transient

Nr Power OFF Limits: Maximum Upper Red Range Begins Transient Continuous

Nr Power OFF Limits: 120%: Maximum 110%: Upper Red Range Begins 105-120%: Transient 90-105%: Continuous

Nr Power ON Limits: Transient Continuous Transient

Nr Power On Limits: 101-107%: Transient 95-101%: Continuous 91-95%: Transient

Starter Limitations: OAT: _____C-_____C After _____ start cycle allow starter to rest a minimum of ______. 1st: 1 Minute 2nd: 30 Minutes

OAT 16C-52C

Starter Limitations: OAT<_____C After _____ start cycle allow starter to rest a minimum of ______. 1st: 1 Minute 2nd: 3 Minutes 3rd: 1 Minute 4th: 30 Minutes

OAT<16C

Sec 7: Can you run cabin heat and anti-ice at the same time?

Only if the APU is on. NOTE: Cabin heater shuts off when anti-ice is turned on. Power to the heater returns when the anti-ice is turned off, or the APU is turned on.

Operation of the cabin door (opening/closing) is permitted in straight and level flight up to _____ KIAS, as well as, in descents and ascents up to _____ fpm and _____fpm, respectively at _____ KIAS maximum

Operation of the cabin door (opening/closing) is permitted in straight and level flight up to 120 KIAS, as well as, in descents and ascents up to 1,500 fpm and 500 fpm, respectively at 120 KIAS maximum

Transmission Oil Temperature: With transmission oil temperature operation in the _____________ range (_____ to _____ C), an entry should be made on the appropriate maintenance form except when hovering in adverse conditions described in Adverse Environmental Conditions.

Precautionary Range (105-140 C)

When attempting single engine starts at pressure altitudes above 14,000 ft, what must you do prior to going to IDLE.

Press the start switch with the PCL off until maximum motoring speed (about 24%) is reached prior to going to IDLE. But we won't be operating above 14,000' without supplemental oxygen.

Flight with cockpit door(s) removed is ________________.

Prohibited

Rotor Brake/Gust Lock limits: Operating an engine against the gust lock is __________.

Prohibited

Rotor Brake/Gust Lock limits: Routine stops will be with engine(s) off, NR below _____% and with ____________ psi applied to stop the rotor between 12 and 18 seconds.

Routine stops will be with engine(s) off, NR below 40% and with 150-180 psi applied to stop the rotor between 12 and 18 seconds.

Intentional flight into __________ turbulence is prohibited.

Severe

TGT Limits: Normal

TGT Limits: 0-793 - Normal

TGT Limits: 30 Minute Limit

TGT Limits: 793-846 - 30 Minute Limit (2 in photo)

TGT Limits: 10 Minute Limit

TGT Limits: 846-879 - 10 Minute Limit (3 in photo)

TGT Limits: 2.5 Minute Transient (Contingency Power)

TGT Limits: 879-903 - 2.5 Minute Transient (Contingency Power) (4 in photo)

TGT Limits: 12 Second Transient 2.5 Minute Transient (Cont Power) 10 Minute Limit 30 Minute Limit Normal

TGT Limits: 903-949 - 12 Second Transient 879-903 - 2.5 Minute Transient (Cont Power) 846-879 - 10 Minute Limit 793-846 - 30 Minute Limit 000-793 - Normal

The NG tape ranges from 0-110% on the EICAS display. The NG tape is marked with a yellow maximum continuous limit line (104.6%) and a red upper limit line at _____% (top end of 12 sec transient).

The NG tape ranges from 0-110% on the EICAS display. The NG tape is marked with a yellow maximum continuous limit line (104.6%) and a red upper limit line at 106% (top end of 12 sec transient).

The NR and NP tapes are marked with a red lower limit line (_____%), a yellow minimum continuous limit line (_____%), a yellow maximum continuous limit line (_____%), and a red upper limit line (_____% NR and _____% NP). In addition, the NR/NP tape on the PFD power pod is marked with a green _____% line for reference.

The NR and NP tapes are marked with a red lower limit line (91%), a yellow minimum continuous limit line (95%), a yellow maximum continuous limit line (101%), and a red upper limit line (110% NR and 105% NP). In addition, the NR/NP tape on the PFD power pod is marked with a green 100% line for reference.

Why should Radar altimeter indications not be relied upon exclusively during FRIES operations?

The altimeter may either measure the distance from the aircraft to the top of trees in heavy foliage or from the aircraft to the ground in lighter foliage.

Slope Landing Limits are based on the slope of the terrain and not the angle indicated on the attitude indicator. Why?

The angle indicated on the attitude indicator may show greater than the slope of the terrain due to compression of the downslope landing gear strut(s).

Intentional flight into __________________ is prohibited.

Thunderstorms

To prevent APU overheating, APU operation at ambient temperature of ______ C and above with engine and rotor operating, is limited to ______ minutes.

To prevent APU overheating, APU operation at ambient temperature of 43 C and above with engine and rotor operating, is limited to 30 minutes

Torque: Dual Engine +80KIAS - Transient - Continuous

Torque: Dual Engine +80KIAS 100-144% - Transient 0-100% - Continuous

Torque: Dual Engine <80KIAS - Transient - Continuous

Torque: Dual Engine <80KIAS 120-144% - Transient 0-120% - Continuous

Torque: Single-Engine - Transient - Continuous

Torque: Single-Engine 135-144% - Transient 0-135% - Continuous

Transmission Oil Pressure: Precautionary Steady State (Sec V) Continuous Idle and Transient MAIN XMSN PRESS Caution Light

Transmission Oil Pressure: 65-130 psi - Precautionary 45-60 psi - Steady State (Sec V) 30-65 psi - Continuous 20-30 psi - Idle and Transient 14 +/-2 psi MAIN XMSN PRESS Caution Light

Transmission Oil Temp: MAIN/INT/TAIL XMSN OIL HOT Illumination Precautionary Continuous

Transmission Oil Temp: 140C - MAIN/INT/TAIL XMSN OIL HOT Illumination 105-140C- Precautionary -20-105C - Continuous

Intentional flight into ______________ with a sling load attached and an inoperative collective trim is prohibited.

Turbulence

With engine and rotor not operating, the APU may be operated ____________ up to an ambient temperature of ______ C.

With engine and rotor not operating, the APU may be operated continuously up to an ambient temperature of 51 C.

Transmission Oil Pressure: Momentary fluctuations in oil pressure may occur during transient maneuvers (i.e., hovering in gusty wind conditions), or when flying with pitch attitudes above +6 . These types of oil pressure fluctuations are acceptable, even when oil pressure drops into the _________ range (below _____ psi).

Yellow Range (below 30 psi)

FRIES insertion of personnel shall be conducted from:

a hover only

Alternate Fuel Limitations: CAUTION Due to fuel volatility, when converting from JP-4 to JP-5/JP-8, three helicopter refueling operations must be completed before performing operations with ________________.

fuel boost pumps off

Fuel system quantity indications are inaccurate during fuel dump operations due to ___________________.

fuel quantity indicator latency

The cabin door(s) ________ be opened or closed during hovering flight.

may

NOTE Because of the flat profile of the main transmission and the forward location of both transmission oil pumps, transmission oil pressure may drop during __________ slope operations.

nose-up

The door(s) __________ be intentionally moved from the fully open or closed position in flight unless specific missions dictate otherwise (rescue hoist operations, FRIES, etc.)

shall not

Prolonged rearward flight and downwind hovering are to be avoided to prevent: (x2)

- Accumulation of exhaust fumes in the helicopter - Heat damage to windows on open cargo doors