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Coast Guard Flight Mechanic STAN CHECK > MH-65 STAN CHECK > Flashcards

MH-65 STAN CHECK Flashcards

Utilize information to pass MH-65 STAN CHECK

1
Q

Main Gearbox Oil Reservoir

A

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

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2
Q

Tail Gearbox Oil Reservoir

A

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

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3
Q

Hydraulic Fluid Reservoir

A

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

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4
Q

Rescue Hoist oil

A

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

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5
Q

Floats

A

Helium. 3100 psi minimum

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6
Q

Fire Bottles

A

Bromotriflormethane/Halon. MIL-B-1218

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7
Q

Tires

A

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

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8
Q

Fuels

A

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

Prist: .07- .15% by volume

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9
Q

Blow-down bottle

A

Nitrogen/Compressed Air. 1600 psi minimum

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10
Q

Engine Oil Reservoir

A

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.

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11
Q

Speeds/Limits

A

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

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12
Q

Oil cooling (Ram Air)

A

Engine oil cooling(ram air): 75 kts

MGB oil cooling (ram air): 120 kts

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13
Q

Adverse weather penetration speed

A

80 kts

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14
Q

NR HI Max Speed:

A

135 kts/ 40 degrees AOB

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15
Q

Vertical stabilizer becomes anti-torque device

A

60 kts

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16
Q

Cargo Loading

A

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

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17
Q

Aircraft Dimensions

A

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”

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18
Q

Flight System Limitations

A

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

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19
Q

Engine Mod overview

A

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)

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20
Q

Gas Generator

A

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.

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21
Q

Power turbine

A

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.

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22
Q

Turbine Outlet Temperature (TOT)

A

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.

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23
Q

Engine Fire Warning System

A

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).

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24
Q

Engine Fire Extinguisher

A

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.

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25
Q

Vehicle Engine Multifunction Display

A

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.

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26
Q

FLI(first limit indicator)

A

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.

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27
Q

FLI DEGR/FLI FAIL

A

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.

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28
Q

FLI-AEO (all engines operating)

A

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.

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29
Q

FLI- OEI (one engine inoperative)

A

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.

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30
Q

FLI- Start Mode

A

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%.

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31
Q

FLI-GOV Mode

A

The FLI will switch to the OEI GOV mode whenever N1 on both engines is higher than 40% and one of the FADECs is in an OEI state, but not in an idle state. The display will resemble the AEO display with two notable exceptions: the current OEI setting will be displayed in the upper information zone and the maximum transient limit (red diode) will shift to match the maximum takeoff power (10 FLI).

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32
Q

Vehicle Page

A

The vehicle page displays the following parameters and their limits; Engine Oil Temperature, Engine Oil Pressure, MGB Oil Temperature, MGB Oil Pressure, and Primary (HYD2) and Secondary (HYD1) Hydraulic pressures. A vertical yellow bar along the side of the scale indicates caution ranges while limits are marked with a horizontal red bar. Digital numerical values can be displayed underneath each scale by pressing Select, +, and Enter.

33
Q

Fuel Page

A

The Fuel page displays fuel pressure, fuel flow, quantity , and endurance. Whenever fuel quantity drops below 3%, the bar and quantity will change to amber and a “LOW” alert will appear. The upper portion of the Fuel page contains the following annunciations: ENG 1 CHIP, ENG2 CHIP, MGB CHIP, TGB CHIP, SERVO LIMIT, PEDAL LIMIT, and LDG LOCK. The Chip indications will appear when the corresponding chip detector circuit is closed. A SERVO LIMIT VEMD Caution will illuminate in conjunction with the Hydraulic LIMIT Light. PEDAL LIMIT will appear when full right pedal deflection is achieved. A green LDG LOCK indicates that the landing gear is in the down position.

34
Q

Engine Power Check(EPC)

A

An EPC is initiated by the VEMD and performed by the FADEC and provides TOTO and TEQ margins for reach engine. The check can be performed whenever Nr is between 340 and 360 RPM, N1 is between 92 and 101%, and the bleed valve is closed.

35
Q

VEMD Maintenance Mode

A

The maintenance mode allows the recall of the past 256 internal VEMD failures, the last eight EPC results, the last seven flight reports, and the last tow flights worth of over-limit recording. To access the maintenance mode, turn the VEMD on while pressing and holding the SCROLL and RESET keys until a RELEASE KEY annunciation is displayed.

36
Q

HIPSARM

A

Helicopter improved performance search and rescue mission. If the FLI needle exceeds 8.8 for 5 minutes with either N1 or TOT as the limiting parameter, the HIPSARM counter (white pie shape will appear underneath the needle. The counter will flash for 2 minutes 30 seconds before turning solid white at 30 minutes. The HIPSARM counter will also appear anytime maximum takeoff power (10.0 FLI) is exceeded and either N1 or TOT is the liming parameter.

37
Q

EBCAU

A

Emergency Back-up Control Auxiliary Unit.

Designed to provide emergency engine control in the even of a dual channel FADEC failure.

Energized by the “Back-Up” switch located on the overhead quadrant

Aligns the N1 of the malfunctioning engine to the N1 of the normal operating engine.

38
Q

DIF N1

A

6% split between N1’s

39
Q

FADEC Failures

A

Level 1: Minor FADEC failure (loss of redundancy)
Flashing “GOV” light. Engine must be at IDLE or OFF. No effect on FADEC performance.

Level 2: Minor FADEC failure (loss of non-redundant)
Steady “GOV” light. Degraded operation state of FADEC.

Level 3: Major FADEC failure(loss of dual channel)
FADEC FAIL on WCA accompanied by illumination of red engine status light. N1 frozen at current setting. Use of engine “back-up” control required.

40
Q

Training Mode Switch

A

Simulates engine failures and allow training of single-engine flight profiles

Simulated failed engine is governed to 320 RPM N2

The VEMD displays actual N1, TOT and TRQ numerical values but the FLI needle position is simulated at a reduced value to prevent engine damage and depicts the appearance of the FLI during an actual engine failure.

Below 8.0 prior to placing switch back to flight, NR stable.

If NR droops below 320 RPM, “idle” engine will provide power up to the actual selected OEI top to prevent excessive droop.

41
Q

Engine Status Light

A

Oil pressure below 25 psi or FADEC fail

42
Q

START RBK, Low Idle Start

A

Low idle start to 52% N1, with rotor brake engaged. START RBK limited to 60 seconds, < or =16 psi oil psi Mode must be cancelled and rotor brake disengaged prior to advancing to FLT detent.

43
Q

VEMD Symbols

A

White circle in White Square: P3 bleed air used for cabin heat.

Green/white barber pole: P2 bleed valve open.

44
Q

Fuel System

A

1 system: Left center, left FWD, and right FWD

Feed Tank Capacity: 5 gallons (43lbs)

System Capacity: 284 gallons (#1: 964 lbs, #2: 1005lbs)

Max refueling pressure: 5psi

Transfer rate: 600 lbs per hour.

Jettison rate: 270 lbs per minute (40gpm)
Non-Jettisonable: LH 158 lbs, RH 174 lbs.

Max fuel during hot gas: 1500lbs.

45
Q

Electrical System

A

DC Sources: External (28VDC), Aircraft batter (24VDC), Transformer Rectifier (28VDC), Engine driven starter/generator (28VDC).

*The transformer rectifier supplies 28 VDC emergency power to both main DC buses (through the battery bus) should both generators fail. The transformer is powered by three-phase, 115 VAC from alternator No.2 of the AC system

AC Sources: External (3phase, 115VAC, 400Hz), MGB driven alternators (200 volts 3 phase, 115 VAC single phase).

Engine driven alternators: Provides 100VAC, 3 phases (48VAC, single) to their respective FADEC computer when N1 is at or above 65%.

Starter Generators: Supply 28VDC when engine is at or above 60% N1.

Battery: A fully charged battery provide power to the DC system for approximately 30 minutes, although placing CPLT AVIONICS switch to off will extend this time to 60 minutes.

46
Q

Hydraulics

A

Primary System:
1 gallon
870 psi
Upper/Right flight controls

Secondary system:
2.1 gallons
3000 psi
Hoist (3000 psi)
Landing Gear (2000 psi)
Talon (2000 psi)
Brake system (2000 psi)
Wheel brakes (875 psi)
Lower/Left flight controls

Isolation Valves:
Two electrically operated isolation valves, attached to the bulkhead on the left side of the baggage compartment, are provided to safeguard against total secondary hydraulic system depletion. If the reservoir level drops below 1 gallon, one isolation valve will close to isolate the landing gear, wheel brakes, and TALON System, as well as isolate normal electrical power to the hoist. The other isolation valve will close to isolate the left body of the tail servo. Isolation valves may also be controlled by placing the TAIL HYD ISOLATE switch to CUTOFF.

47
Q

Landing Gear

A

Gear down Indications:

  • Landing gear indicator (green)
  • VEMD annunciation
  • External blue light
  • Visual

Methods of lowering gear:

  • Landing gear selector switch
  • BKP pump
  • Emergency extension handle
  • Aircraft blow down bottle actuator pin
  • External blow down bottle (1600psi min.)

Main tires:

  • 123 psi, nitrogen or compressed air
  • No cord showing
  • Skid spots, not greater than 4 inches
  • No chunks exceeding 1 inch
  • No sidewall cuts

Nose tire:

  • 80psi, nitrogen or compressed air
  • No cord showing
  • Skid spots, not greater than 4 inches
  • No sidewall cuts
  • Inspect for movement of slippage marks

Brakes:

  • Max 3 missing brake clips, no 2 adjacent
  • Grounding chain extension (2 links touching the ground)
  • Illumination of the PARKING BRAKE light indicates parking brake handle position only. It does not mean hydraulic -pressure is applied.
48
Q

Rescue Hoist

A
  • 3000psi
  • 600lbs Max load
  • 245 ft. usable cable, 250 ft. on drum
  • Last 10ft. of cable are painted red/white stripes
  • FM controls: 0-200 fpm, first and last 10 ft (0-50fpm)
  • Manual Override: Fixed at 50 fpm
  • Pilot’s control fixed at 100 fpm, except first and last 10ft. in which it’s limited to 50 fpm.
  • Reactive overload clutch: 1500 +/- 300lbs
  • Assumed breaking strength of cable: 3200 lbs
49
Q

Rest periods

A

No load: No rest period
0-300lbs: 10 seconds
300-600: 30 seconds

50
Q

Cargo Hook

A
  • Rated at 2000 lbs
  • Gear must remain down with hook installed
  • Swings laterally 60 degrees, 30 degrees longitudinally
  • Speed limited to 90 kts with load
51
Q

Main Rotor Blades

A
  • Foam Core
  • Fiberglass main spar
  • Carbon fiber skin
  • Stainless steel leading edge
  • An integral brass weight is installed inside the leading edge of to counteract natural flapping frequency of light composite blades
52
Q

Tail Rotor Blades

A

Each blade is constructed of composite materials by means of a resin transfer molding (RTM) process, which creates a single material construction and eliminates de-bonding. The leading edge is protected by a reinforced stainless steel cap.

53
Q

Main Gearbox

A

The MGB consists of: left and right engine input housing and accessory gearboxes, shafts for driving the Nr tachometer generator and MGB oil system pump, and an accessory drive for the oil cooler and rotor brake. The left accessory gearbox drives the secondary hydraulic pump and the No. 1 alternator. The right accessory gearbox drives the primary hydraulic pump and the No. 2 alternator.

54
Q

MGB Oil Supply System

A

The MGB has two lubricating systems consisting of a two stage oil pump with main and auxiliary pumping elements connected by a shear shaft, a main system for providing oil flow through external lines and the oil cooler, and an auxiliary system for providing internal oil flow only. The total of quantity of 9.34 quarts is self contained. During normal operation, the main pump circulates oil through the oil cooler, filter, and to the MGB jets. Should pressure exceed 130.6 psi, oil is bypassed to the MGB sump through the main system relief valve. During normal operation, the auxiliary pump operates, but its output is blocked by a shuttle valve which is held closed by higher pressure from the primary system, causing auxiliary system oil flwo to return to the MGB sump via the auxiliary relief valve. In the event of a main pump failure or shaft shearing, the auxiliary pump will continue to operate. The shuttle valve opens and oil is pump from the MGB sump directly through the filter to the jets at a lower pressure and without the benefit of cooling. An increase in oil temperature and a lower oil pressure will occur when the auxiliary pump is providing MGB lubrication. Should an external oil leak develop, oil will be lost until the main pump inlet uncovers, at which time the MGB PMP main warning light will illuminate. The auxiliary pump, which draws oil from lower in the MGB, will continue to provide lubrication, but the pilot may have to reduce power to maintain MGB temperature within limits.

55
Q

Flotation System

A
  • 4 floats, 2 FWD, 2 AFT
  • 2 gas cylinders (helium) located in AFT float compartment
  • Protected by 8 circuit breakers located in baggage compartment
  • Not to be armed above 90kts
  • Effective in a Sea State 2 condition for 4 minutes
56
Q

Pyrotechnics

A

For fresh water deployments add 1 teaspoon of salt into the battery cavity
*WARNING: Do not deploy flares from a steady hover Due to the possibility of valve plug FOD after ignition.

57
Q

MK-25

A
  • Burn time: 13-18 minutes
  • Once salt has been added, flare shall be deployed
  • Should not be armed until the helicopter is 30-60seconds from the drop point
58
Q

MK-58

A
  • Burn Time 40-60 minutes
  • Once salt has been added, flare shall be deployed
  • Should not be armed until the helicopter is 30-60 seconds from the drop point
  • The MK 58 cannot be disarmed. Once armed, it must be deployed
59
Q

M-J Rescue Basket

A
  • Maximum load of 600lbs
  • Primary rescue device for hoisting
  • Normally only one survivor at a time
  • Survivors shall be brought in head first
60
Q

Rescue Litter

A
  • Maximum load of 600lbs
  • Used when survivor is not ambulatory (cannot walk/would need assistance to get into an ambulance)
  • Normally used with a trail line, except to RS in the water
61
Q

Sling

A
  • Maximum load of 600 lbs
  • Not to be used to hoist untrained or injured personnel
  • Chest straps shall be used by all personnel w/ the exception of the RS.
  • Shall be delivered open to reduce snag hazards
62
Q

SX-5 Searchlight

A
  • 15 million peak candle power
  • Adjustable focus: 2-10 degrees
  • Do not aim searchlight at the aircraft
63
Q

Datum Marker Buoy

A
  • Frequencies 240.6, 242.65 & 156.750
  • Activated by mercury switch when inverted
  • Minimum water depth for deployment: 12 feet
  • Deploy from 150 feet AWL/80 KIAS or less
  • Note position, time, frequency and serial number prior to deployment
64
Q

SLDMB

A

-Once removed from its waterproof casing, shall be deployed
-Deployment restrictions:
Hover below 25 ft. w/drogue chute remove.
25-150 ft. less than 80 kts with drogue chute.

65
Q

Passenger Vest (MD1127)

A
  • Manually inflated by CO2 or oral inflation tube

- Inventory: whistle, strobe light, & signal miror

66
Q

SAR Warrior Vest (LPU-27P)

A
  • Dual bladder (65 lbs buoyancy)
  • Right hand: Pull down & slightly outward for CO2 inflation
  • Two oral inflation tubes

Inventory:

  • SEAS-1 Bottle: 3000 psi (2-3 minutes breathing)
  • MK 124: 20 seconds DAY: Orange smoke. NIGHT: Red flare (2 raised beads)
  • MK 79: Seven flares, 4.5 seconds, 250-600 ft.
  • Knife
  • Strobe light: 8 hours continuous, 2 mile visibility min.
  • Signal Mirror: Sunny day, 8 million candlepower
  • Whistle: 1000 yards audible
  • Personal Locator Beacon: 121.5, 243.0, 406.025 MHz
  • Strap Cutting Blade
67
Q

RS Raft (RSLR-1)

A

CO2 inflated, one-man life raft

180lbs of flotation.

68
Q

Crew Life Raft (LRU-25/A)

A
  • 6 man, power inflated life raft
  • Fully inflates in 30 seconds
  • Handle pump to inflate floor
  • Water activated internal light system
69
Q

Quick Splice

A
  • Cable shall be flush with the top plate
  • Hoist up limit switch and speed reduction is inoperable
  • After use of the QS, bring the QS into the cabin and slow in the area between the raft and the window. Place hoist cable in the aft lower hatch opening and close the hatch
70
Q

Portable Fire Extinguisher

A
  • 2.5 lbs of Halon, pressurized with nitrogen (125 psi)

- Duration, 10 seconds with horizontal range of 9-15 ft.

71
Q

First Aid Kits

A

-2 first aid kits. One on 9 degree frame and one stowed in the baggage compartment

72
Q

Crash Axe

A

-Two crash axes available for emergency use. One mounted to the back of the CP seat and another mounted on the baggage compartment door.

73
Q

Emergency Locator Transmitter (ELT)

A
  • Transmits on 121.5 and 243.0 MHz to a distance of 200 miles
  • Mounted in baggage compartment above baggage door
  • Switch must be in the ARM position
  • Activated automatically with a 5g inspect
  • 9 volt battery lasts approximately 100 hrs.
74
Q

Underwater Acoustic Beacon (UAB)

A
  • Mounted in the AVRACK on the VFDR
  • Capable of immersion up to 20,000 ft.
  • Water Activated
  • Transmit signal on 37.5 kHz
  • Detection range of 2,000 - 4,000 yards
  • Operating life of 30 days by internal 9v battery
75
Q

Routine Safety Checks

A

a. Instrument panel - Check for normal indications

b. Avionics rack and overhead circuit breaker panels
- Check for popped circuit breakers.

c. General cabin area - Check for leaks and security of equipment, cabin doors, and hatch.

76
Q

Safety Harness

A

Use of the safety harness shall not be made below 1,000 ft. without authorization by the PIC.

77
Q

Indirect Pump

A
  • Weight bag connected to weak link and delivered to vessel

- Deploy from an altitude of 15-20 ft.

78
Q

Prohibited Maneuvers

A
  1. Aerobatic Flight
  2. Angles of bank:
    - a. Greater than 60 degrees less than 110 KIAS
    - b. Greater than 45 degrees at or above 110 KIAS.
  3. Abrupt cyclic movement above 110 KIAS.
  4. Takeoff and landing on slopes steeper than 10 degrees.
  5. Above 8,900 lb gross weight, the following maneuvers are prohibited:
    - a. Shipboard landings
    - b. All rotary wing air intercept maneuvers and AUF training maneuvers.
  6. Above 9,200 lb. gross weight, the following maneuvers are prohibited:
    - a. Prolonged hover operations (>1min)
    - b. Operational AUF maneuvers
79
Q

Weight Limitations

A

The maximum ramp weight is 9,590 pounds when the helicopter is static; being towed, or being ground taxied under its own power.

The maximum gross weight for flight operations, including running takeoffs, is 9,480 pounds.

Coast Guard Flight Mechanic STAN CHECK (1 decks)

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