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Flashcards in MH-65 STAN CHECK Deck (79)
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1

Main Gearbox Oil Reservoir

MIL-PRF-6086E Grade "M". Oil level has to be between the MIN and MAX line. Capacity is 9.34 quarts

2

Tail Gearbox Oil Reservoir

MIL-PRF- 6086E Grade "M". Oil level at the MAX line

3

Hydraulic Fluid Reservoir

MIL-H-83282. Oil level should be midscale/ at the bulls-eye.

4

Rescue Hoist oil

MIL-L-7870. Oil level should be above the white line.

5

Floats

Helium. 3100 psi minimum

6

Fire Bottles

Bromotriflormethane/Halon. MIL-B-1218

7

Tires

Nitrogen/Compressed Air. Main: 123 psi/ Nose: 80psi

8

Fuels

Different fuels the helo can take: JP4, 5, 8, JETA, A1, A-M, B.


Prist: .07- .15% by volume

9

Blow-down bottle

Nitrogen/Compressed Air. 1600 psi minimum

10

Engine Oil Reservoir

Mobil-Jet 254. Oil level should be between bottom of the sight glass and the min line. Check the oil level within in 15 minutes of shutdown. Reservoir capacity is 2 gal.

11

Speeds/Limits

Absolute VNE Power- On: 175 KIAS
Absolute VNE Power-Off: 135 KIAS

Maximum cabin sliding door speeds:
Door Removed - 120 KIAS
Door Locked in open position: 100 KIAS
Door movement: 80 KIAS


Maximum Rescue Hatch speeds:
Hatch locked in open position: 80 KIAS, 35 kt sideward
Hatch Movement: 60 KIAS, 30kt sideward



Maximum Cargo Hook Load speed: 90 KIAS

Maximum Airspeed with float bags armed or inflated: 90 KIAS


Maximum airspeed with skis installed: 120 KIAS


Maximum Touch down speed: 60 KGS


Maximum touch down speed with skis on snow: 35 KGS


Maximum brake speed: Gross weight at or less than 8900 lb - 38 KGS

Gross weight above 8900 lb - 30 KGS


Maximum Airspeed with NR HI: 135KIAS

Maximum Sideward Flight: 35 kt

Maximum Landing Light Extension Speed: 135 KIAS

12

Oil cooling (Ram Air)

Engine oil cooling(ram air): 75 kts
MGB oil cooling (ram air): 120 kts

13

Adverse weather penetration speed

80 kts

14

NR HI Max Speed:

135 kts/ 40 degrees AOB

15

Vertical stabilizer becomes anti-torque device

60 kts

16

Cargo Loading

Cabin: 125 lb/sq ft. Max load 1320 lbs

Baggage compartment: 125 lb/sq ft. Max load 440 lbs

61.5 lb/sq ft. Metal panels

17

Aircraft Dimensions

Rotor Diameter: 39'2"

Overall Length: 44'5 (static) 44'10" (dynamic)

Overall width (at stabilizer): 10'6"

Height to top of rotor head: 12'9"

Height to top of fin 13'5"

Ground clearance: 6"

18

Flight System Limitations

IAS: >40KIAS

VS: >70 KIAS 0-3000fpm

ALT: >70KIAS

IAS-VS: >40KIAS 0-3,000 fpm

IAS-ALT: >40KIAS

HDG SEL: >40 KIAS

NAV: >40 KIAS

APPR: >40 KIAS, 12 deg GP

T-HOV: Below 2,500 RADALT

HOV AUG GA: Visual hover maneuver >25 feet AGL

19

Engine Mod overview

Mod 1: Transmission shaft/ Accessory gearbox

Mod 2: Axial compressor

Mod 3: Gas Generator ( 100% N1 = 52,00 RPM)

Mod 4: Power turbine (100% N2 = 39,000 RPM)

Mod 5: Reduction Gearbox (100% = 6,000 RPM)

20

Gas Generator

N1 52,000 RPM @ 100%

Three sensors: N1A, N1B signal used by FADEC for engine control, derived from the dual channel engine driven alternator.

N1C signal sent to EBCAU for engine control in the even of major FADEC failure and VEMD for cockpit display.

21

Power turbine

N2 39,000 RPM @ 100%

Three Sensors: N2A - transmitted directly to the pilot's NR gauge (triple-tach)
N2B, N2C - transmitted to the FADEC and VEMD for N2 speed control and overspeed protection.

Power turbine is mechanically independent from the Gas Generator turbine. Accessories driven by the power turbine include the output shaft and the engine compartment cooling fan.
*A malfunctioning stop electro-valve will inhibit overspeed protection on that engine.

22

Turbine Outlet Temperature (TOT)

The TOT for each engine is measured at the free power turbine inlet by eight dual-thermocouples connected to a temperature conformation box (T4.5). The conformation box provides an average TOT signal to the FADEC and the VEMD, but are designed to be redundant for each system.

23

Engine Fire Warning System

Each fire warning circuit consists of three bimetallic fire detectors which are wired in series; two located on the accessory section (200'C) and one located gas generator (400'C).

24

Engine Fire Extinguisher

The fire extinguisher system consists of tow spherical bottles filled with bromotrifloromethane (or Halon). The bottles are electrically controlled consisting of four pushbutton switches located on the instrument panel above the FIRE and FAIL warning lights, and two low-pressure caution lights. The caution lights, labeled L EXT and R EXT are located on the WCA, and illuminate when pressure in the bottle drops below 230 psi. One bottle may be discharged into each engine compartment or both bottles may be discharged into either engine compartment. Pressing the PRI pushbutton for the #1 engine will discharge the left extinguisher into the #1 engine compartment. Pressing the SEC pushbutton for the #1 engine will discharge the right extinguisher into the #1 engine compartment.

25

Vehicle Engine Multifunction Display

Normally, the top LCD displays the FLI while the bottom is scrollable between the Vehicle, Fuel, EPC, and System Status pages. If either screen fails, the remaining screen will be scrollable between the FLI, Vehicle , and Fuel pages. EPC and System Status pages will no longer be available.

26

FLI(first limit indicator)

Monitors all primary engine parameters and limitations (N1, TQ, TOT). The single needle in the center of the screen measures the parameter closest to reaching its limit, given the current operating condition. Anytime the FLI needle enters the yellow zone, the limiting parameter will be underline in yellow. If the FLI needle exceeds the red bar, the limiting parameter will be underlined in red.

27

FLI DEGR/FLI FAIL

An amber FLI DEGR annunciation will appear anytime a N1, TOT, or TRQ parameter will change from white to yellow. FLI FAIL will display anytime N1, TOT, or TRQ parameters are not valid on the relevant engine. ALL three parameters will change to amber and lose their numerical value.

28

FLI-AEO (all engines operating)

FLI mode when N1's are above 40 % and neither FADEC is in an OEI, training or idle state. A yellow arc runs from 8.8 FLI (maximum continuous power) to a red bar at 10.0 (maximum takeoff power). A red diode at 10.7 FLI indicates maximum transient power.

29

FLI- OEI (one engine inoperative)

FLI mode when either engine N1 is lower than 40% or either engine is ion idle. The single=engine display will include a yellow dashed bar indicating Continuous OEI power, a dashed red bar for 2-minute OEI power, and a solid red bar for 30-second OEI power. If the FLI needle passes the OEI continuous bar, the limiting parameters will be underline in yellow. If the needle passes the 2-minute OEI bar, the limiting parameters will be underlined in red. An OEI HI annunciation will appear at the onset of the single-0engine condition and may be scrolled down to the LO or CT position using the collective OEI buttons.

30

FLI- Start Mode

Start mode display will appear whenever either FADEC is in STOP mode or the N1 of one engine is increasing and lower than 60 % or decreasing and lower than 40%. A flashing Start annunciation will appear in blue in the lower information zone whenever the FADEC senses the starter is engaged. The digital value for TOT will be underlined with a flashing red line whenever TOT is greater than 750C. If TOT reaches 840C, the digital value will be underlined in solid red. The start becomes self-sustaining at 45% N1 with a normal idle speed of 68% N1. Automatic engine shutdown will occur when the FADEC detects a TOT of 840 degrees C or if the TOT does not exceed 100 degrees C by 27% N1. In the event of an in-flight restart, the start sequence will not initiate until n1 is below 17%.