Vertipedia - Mil Mi-14PL

Developed in 1967, the Mi-14PL anti-submarine warfare (ASW) helicopter is designated 'Haze-A' by NATO. There was a strike version prototype equipped with anti-ship missiles, as well. The Mi-14PL differed and started the variation of having the tail rotor on the left side of the boom, rotating in the opposite direction. Cabin capacity is 19 passengers in addition to the four crew.

Overview

Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-8/Mi-14/Mi-17

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 4 in Side-by-side arrangement

Landing gear: Wheels (all retractable)

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

Overall Dimensions
Overall Height:
Overall Length:
Overall Width:	21.30 m	69.9 ft

Airframe Dimensions
Airframe Length:
Airframe Width:
Airframe Height:

Landing Gear Dimensions
Landing Gear Base:
Landing Gear Track:

Cabin Dimensions
Cabin Internal Height:
Cabin Internal Length:
Cabin Internal Width:

Weights
Max Gross Weight (ground):	14,000 kg	30,865 lb
Max Gross Weight (airborne):
Max Take-off Weight:	14,000 kg	30,865 lb
Empty Weight:	8,902 kg	19,626 lb

Climb Performance
Max Rate of Climb:

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:

Limitations
Max Level Flight Speed:	250 km/h	135 kts
Never Exceed Speed:
Service Ceiling:	4,000 m	13,123 ft

Range and Endurance
Max Range:	800 km	432 nm
Max Endurance:

Provided powerplant data is for uninstalled, sea level, static operations.

Powerplant
Number of engines:	2
Designation:	Motor Sich TV3-117M turbine
Manufacturer:	Motor Sich

Normal Ratings
Max continuous:	1103 kW	1479 hp
Take-off / rated:	1454 kW	1949 hp
Intermediate:
Maximum:

OEI Ratings
OEI contingency:	1618 kW	2169 hp
OEI continuous:
OEI 30-second:
OEI intermediate:	1471 kW	1972 hp

Main Rotor Characteristics
Diameter:	21.30 m	69.88 ft
RPM:
Direction of Rotation:	Clockwise
Hub Type:

Main Rotor Blade Characteristics
Blade Construction:	All-metal
Blade Chord:
Blade Tip Geometry:	Conventional
Blade Twist:
Number of Blades:	5

Main Rotor Derived Characteristics
Disc Area:	356.33 m²	3835.6 ft²
Disc Loading:	39.29 kg/m²	8.047 lb/ft²
Solidity:

Main Rotor Blade Derived Characteristics
Blade area per blade:
Tip Speed:

Tail Rotor Characteristics
Diameter:	3.91 m	12.83 ft
Configuration:	Tractor
Direction of Rotation:	Top blade aft
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	3
Blade Construction:
Blade Chord:
Blade Twist:

Tail Rotor Derived Characteristics
Disc Area:	12.01 m²	129.2 ft²
Solidity:

Tail Rotor Blade Derived Characteristics
Tip Speed:
Blade Area (per blade):

References

References and sources used

Mil Moscow Helicopter Plant 50 Years

Lyubimaya Kniga
1998 (page 164)
Book

Russian Helicopters, Ka-27

Russian Нelicopters, JSC
5 July 2017 (page 212)
Website

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Overview

Attribution

Number of engines:	2 Turbines
Max Level Flight Speed:	250 km/h	135 kts
Max Range:	800 km	432 nm
Max Endurance:

Main Rotor Diameter:	21.30 m	69.88 ft
Max Gross Weight (ground):	14,000 kg	30,865 lb