157 disponíveis em breve, a $2 milhões cada… poderá ser??? Com o Natal à porta… One can but hope…
https://www.defensenews.com/land/2023/12/20/us-army-to-trim-black-hawk-helicopter-fleet/
Esta é uma excelente oportunidade da FAP adquirir uma dezena/dúzia de LIMA's para os Evakuativos ou até o Exército para a UALE e ficarmos com duas frotas de helis médios mais actuais que os da 551 !!!
A 02 milhões/unidade mesmo que gastem mais 02 Milhões/heli em MRO e armamento, os dez UH-60L ficariam por 40 milhões, seria uma excelente compra, bem melhor que a dos UH-60A do Bombeiral.
The UH-60L Blackhawk represents an upgrade to the original UH-60A Blackhawk, which entered service with the US Army in 1978. Production of the UH-60L began in 1989 with the conversion of existing UH-60A aircraft to the "L" standard as well as the production of new airframes. The first UH-60L was delivered in November 1989. Over 600 have been delivered since 2006, and production is expected to continue until the UH-60L line is replaced by new production UH-60M aircraft.
Externally, the UH-60L is very similar to the UH-60A. Major improvements include the incorporation of a hover IR suppression system (HIRSS) that is designed to cool engine exhaust gasses while hovering and in forward flight. As with the UH-60A, the "L" variant is ESSS capable and rated for all of the same weapon systems. The external cargo hook limit has been improved on the UH-60L, which has a maximum lift rating of 9,000 pounds. Internal troop carrying capacity remains unchanged at 11 fully loaded, 14 high-density, and 20 lightly equipped.
The UH-60L is equipped with two General Electric T700-GE-401C turboshaft engines, each rated to 1,880 shaft horsepower. The "L" model retains the same internal fuel arrangements as in the "A" model.
General Characteristics and Performance
The performance and specifications presented below accurately describe the UH-60L model at a point in time. Some variation to these data can be expected as a result of subsequent engine power rating changes and aircraft design changes.
Main rotor diameter: 53.6 ft., 4 blades, airfoil SC1095 and SC1094R8.
Main rotor blade chord: 1.73 ft., tip swept aft 20 degrees, blade twist negative 18 degrees.
Main rotor solidity: .083, main rotor tip speed: 725 fps.
Main rotor head equivalent flapping hinge offset of 15 in.
Tail rotor diameter: 11 ft., 4 blades; chord .81 ft., airfoil SC1095.
Tail rotor solidity: .1875.
Tail rotor tip speed: 699 fps.
Main gearbox rated power: 3,400 HP.
Main gearbox input/output speeds: 20,000/258 rpm.
Installed power: Two T700-GE-701C engines, intermediate rated power: 1,857 HP at SL-STD conditions.
Weight empty of the first production UH-60L: 11,426 lb.
gross weight of the first production UH-60L: 16,976 lb.
External cargo hook capacity: 9,000 lb.
Performance of the first production UH-60L: vertical rate of climb of 1,550 fpm and cruise speed of 152 knots at 4,000 ft. 95 degrees F.
Production History
The first UH-60L was delivered to the Army in 1989 at the same time that production of the UH-60A ended.
Although production of the “L” model for the Army ended in 2006 when the UH-60M was phased in, the “L” model continued to be produced for international military organizations. As of this writing the UH-60L is still being produced for other customers and altogether over 1,000 have been built for all operator. https://www.cuttingdynamics.com/uh-60a-uh-60l-and-uh-60m-differences/Abraços
