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Limits / EPs > Chapter 5 > Flashcards

Chapter 5 Flashcards

1
Q

Rotor Start and Stop Limits

A

45kts wind speed from any direction.

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2
Q

Main Transmission Module Limitations

A

If oil pressure is not steady during steady state forward flight or in a level hover or if oil pressure is steady but under 45 PSI make an entry on DA Form 2408-13-1. Sudden pressure drops (more than 10 PSI) without fluctuation require an entry on DA Form 2408-13-1.

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3
Q

Engine % RPM 1-2 (NP)

A 
Transient 91-95%
Continuous 95-101%
Transient 101-105%
12 Sec Transient 105-107%
Avoid ranges 20-40% & 60-90% during start up and shutdown
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4
Q

Engine NG

A

Continuous 0-99%
30 min. Limit 99-102%
12 Sec Transient 102-105%

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5
Q

Engine Oil Temperature

A

Continuous -50-135 C

30 Min Limit 135-150 C

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6
Q

Turbine Gas Temperature

A 
Normal 0-810 C
30 Min Limit 810-858 C
10 Min Limit 858-879 C
2.5 Min Limit 879-903 C
Start Abort Limit 851 C
12 Sec Transient 903-949 C
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7
Q

Transmission Oil Temperature

A

Normal -50-105

Precautionary 105-140

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8
Q

RPMR %

A

Power On
Transient 91-95%
Continuous 95-101%
Transient 101-107%

Power Off
Normal 90-105%
Transient 105-110%
Maximum 110%

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9
Q

Fuel Quantity

A

Normal 200-1500 lbs

Precautionary 0-200 lbs

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10
Q

Engine Oil Pressure

A

Idle 22-26 PSI
Normal Operation 26-100 PSI
30 Min Limit 100-120 PSI

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11
Q

Engine % TQ

A

Continuous
Dual Engine >80 Kts: 0-100%
Dual Engine <80kts: 0-120%
Single Engine: 0-135%

12 Sec Transient
Dual Engine >80kts: 100-144%
Dual Engine <80kts: 120-144%
Single Engine: 135-144%

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12
Q

Transmission Oil Pressure

A

Idle and Transient: 20-30 PSI
Continuous: 30-65 PSI
Precautionary: 65-130 PSI

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13
Q

Engine Starter Limits

A

At ambient temperatures of 15 C and below, 3 consecutive start cycles may be made, followed by a 3 minute rest period, followed by 2 additional start cycles. A 30 minutes rest period is then required.

At ambient temperatures above 15 C up to 52 C, 2 consecutive start cycles may be made. A 30 minutes rest period is then required before any additional start cycles.

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14
Q

Pneumatic Source Inlet Limits

A

The minimum air source required to start the helicopter is 40 psig and 30 ppm at 149 C. The maximum ground air source to be applied to the helicopter is 50 psig at 249 C measured at the external air connector on the fuselage.

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15
Q

Engine % RPM Limitations

A

Transient % RPM operation in yellow range is not recommended as good operating practice. However, no damage to either engine or drive train is incurred by operations within this range. Momentary transients above 107% RPM 1 or 2 are authorized by MTPs during auto RPM checks.

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16
Q

Engine Overspeed Check Limitations

A

Engine overspeed check in flight is prohibited. Engine overspeed checks, on the ground, are authorized by designated maintenance personnel only.

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17
Q

Engine Start LImits

A

Cross bleed starts shall not be attempted unless the #1 or #2 ENG ANTI-ICE advisory does not appear, and the operating engine must be at 90% NG speed or above and rotor speed at 100% RPMR.

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18
Q

Loading Limits

A

Maximum Capacity for each storage compartment: 125 lbs
Maximum cargo hook capacity: 9000 lbs
Max weight is further limited by cargo floor maximum capacity of 300 lbs per square foot.

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19
Q

Cabin Ceiling Tiedown Fittings

A

The four cabin tiedown fittings have a limited load capability of 4,000 lbs

20
Q

Max Weight UH-60L

A

22,000 lbs

21
Q

External Lift Mission

A

External lift missions above 22,000 lbs can only be flown with cargo hook loads above 8,000 lbs and up to 9,000 lbs.

22
Q

Airspeed Limits (Single Engine)

A

130 kts

23
Q

Maximum Autorotational Airspeed

A

Above 16,825 lbs: 130 kts
Below 16,825 lbs: 150 kts
With volcano installed: 100 kts

24
Q

Maximum Airspeed UH60L

A

VNE: 193 kts

With skis installed: 155 kts

25
Q

Max Sideward/Rearward Flight

A

Hovering in winds greater tha 45 kts (35 kts with ESSS) from the sides or rear is prohibited. Sideward/rearward flight into the wind, combined with wind speed, shall not exceed 45 kts (35 kts with ESSS).

26
Q

Max Airspeed SAS/HYD Inop

A

One SAS inoperative: 170 kts
Two SAS Inoperative: 150 kts
Two SAS Inop in IMC: 140 kts

One hydraulic system inoperative: 170 kts
Two hydraulic systems inoperative: 150 kts
Two hydraulic systems inop in IMC: 140 kts

27
Q

Search Light/Landing Light Aispseed Limits

A

Landing Light
Extending: 130 kts
Extended: 180 kts

Search Light
Extending: 100 kts
Extended: 180 kts

28
Q

Flight With Cabin Doors / Windows Open

A

Cabin doors may be fully open up to 100 kts ith soundproofing installed aft of station 379.
Cabin doors may be fully open up to 145 kts with soundproofing removed aft of station 379 or with soundproofing properly secured.
The doors will not be intentionally moved from the fully open or closed position in flight. The cabin doors may be opened or closed during hovering flight. The cabin doors must be closed or fully opened and latched before forward flight.
Gunner’s window(s) may be fully open up to 170 kts.
Flight with cockpit doors removed is prohibited.

29
Q

Airspeed Limitations Following Failure of The Automatic Stabilator Control System.

A

Manual control available. If the automatic stabilator control system fails in flight and operations cannot be restored.

(1) The stabilator shall be set full down at speed 40 kts and below
(2) The Stabilator shall be set at 0 at speeds above 40 kts
(3) Autorotation airspeed shall be limited to 120 kts at all gross weights.

Manual control not available: The placard airspeed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed 120 kts.

30
Q

Prohibited Maneuvers

A

Hovering turns greater than 30 deg per second are prohibited. Intentional maneuvers beyond attitudes of 30 deg in pitch or 60 deg in roll are prohibited.

31
Q

Restricted Maneuvers

A

Manual operation of the stabilator in flight is prohibited except as required by formal training and maintenance test flight requirements or as alternate stabilaor control in case of AUTO mode malfunctions.
Prolonged rearward flight and downwind hovering are to be avoided to prevent accumulation of fumes in the helicopter and damage to windows on open cargo doors.

32
Q

Maneuvering Limitations

A

NOTE: Maneuvers entered from a low power setting may result in transient rotor droop of 5 % RPMR or greater.

33
Q

High Speed Yaw Maneuver Limitations

A

Above 80 kts avoid abrupt, full pedal inputs to prevent excess tail rotor system loading.

34
Q

Maneuvering Limitations (Sling Load)

A

Maximum 30 deg angle of bank in forward flight.
Side flight is limited by bank angle and is decreased as airspeed increases.
Rearward flight with a sling load is limited to 35 kts.

35
Q

Landing Gear Limitations

A

Below 16,825 lbs:
Level Terrain 540 fpm
Uneven Terrain 360 fpm

Above 16,825 lbs:
Level Terrain 300 fpm
Uneven Terrain 180 fpm

36
Q

Landing Speed Limitations

A

Maximum forward touchdown speed is limited to 60 kts ground speed on level terrain.

37
Q

Slope Landing Limitations

A

15 deg nose up, right or left wheel upslope, reduced by 2 deg for every 5 kts of wind
6 deg nose downslope. Landing in nose downslope conditions with tail winds greater than 15 kts shall not be conducted.
The main gearbox may be operated up to 30 minutes at a time with pressure fluctuations when the helicopter is known to be at a nose up attitude.

38
Q

Slope Landing Limitations (Caution)

A

When performing slope landings with external fuel tanks ensure tank to ground clearance.

39
Q

Slope Landing Limitations (Notes)

A

(1) Because of the flat profile of the main transmission and the forward positions of the transmission oil pumps, transmission oil pressure will drop during nose-up slope operations.
At a slope angle of 10 deg, an indicated oil pressure of 30-35 PSI normal.
At a slope angle of 15 deg, a pressure in the range of 10-15 PSI is normal due to pitching of the helicopter.

(2) The low fuel pressure indicator light(s) may intermittently light when the helicopter returns to a neutral or positive attitude after extended operation at nose down attitude with fuel boost pumps off. This may also occur during a climb to high altitude followed by a pitch up maneuver. If the light extinguishes immediately, no action is required.

40
Q

Flight In Icing Conditions

A

(1) Helicopters with the following equipment installed, operational, and turned on are permitted to fly into trace and light icing conditions. Flight into light icing is not recommended without the blade deice kit.
- Windshield Anti Ice
- Pitot Heat
- Engine Anti Ice
- Engine Inlet Anti Ice Modulating Valve
- Ambient Air Sensing tube

(2) For flight into moderate icing conditions, all equipment above and blade deice kit must be installed, operational, and turned on. Flight into heavy or severe icing is prohibited.
(3) Helicopters equipped with blade erosion kit tape are prohibited form flight into icing conditions.
(4) Flight into known or forecast icing conditions with EIBF installed is prohibited.

41
Q

Engine & Engine Inlet Anti-Ice Limitations

A

At engine power levels of 10% TRQ per engine and below, full anti-ice capability cannot be provided, due to engine bleed limitations. Avoid operation under conditions of extreme low power requirements such as a high rate of descent (.1900 fpm), or ground operation below 100% RPMR, during icing conditions. The cabin heating system should be turned off before initiating a high rate of descent.

42
Q

Backup Hydraulic Pump Hot Weather Limitations

A

During prolonged ground operation of the backup pump with the rotor system static. The backup pump is limited to the following tmeprature/time/cooldown limits because of hydraulic fluid overheating.

-54-32 C: Unlimited Op
33-39 C: 24 Op / 72 Cool
39-52 C: 16 Op / 48 Cool

43
Q

APU Operating Limitations

A

To prevent APU overheating, APU operation at ambient temperature of 43 C and above with engine and rotor operating is limited to 30 minutes. With engine and rotor not operating the APU may be run continuously up to 51 C.

44
Q

Windshield Anti-Ice Limitations

A

WIndshield anti-ice check shall not be done when FAT is over 27 C.

45
Q

Turbulence and Thunderstorm Operation

A

(1) Intentional flight into severe turbulence is prohibited
(2) Intentional flight into thunderstorms is prohibited.

(3) Intentional flight into turbulence with a sling load
attached and an inoperative collective pitch control friction
is prohibited.

46
Q

Gust Lock Limitations

A

Warning: Before engine operation can be performed with the gust lock engaged, all main rotor tiedowns shall be removed.

(1) Dual engine operation with gust lock engaged is prohibited.
(2) Single-engine operation with gust lock engaged will be performed by authorized pilots at IDLE only.
(3) Gust lock shall not be disengaged with engine running.

Limits / EPs (4 decks)

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