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S-70A > S-70A-9 Limits > Flashcards

S-70A-9 Limits Flashcards

0
Q

Engine Start Limits

Info

A

Crossbleed starts shall not be attempted unless:

  • The anti-ice light is NOT illuminated,
  • Operating engine is at 90% Ng or above, and
  • Rotor speed is at 100% RPMR.

When attempting single-engine starts at PA > 14,000ft, wait until max. motoring speed (about 24%) is reached before advancing the ENG POWER CONT lever to IDLE.

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1
Q

Engine Starter Limits

A 
Ambient temperature +15C and below:
Two consecutive start cycles.
3 min rest.
Two additional consecutive start cycles.
30 min rest (before any additional starts).

+16C to +52C:
Two consecutive start cycles.
30 min rest (before any additional starts).

*60 sec between all cycles

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2
Q

Engine Idle Limits with Rotor Brake On

A

Single and dual engine starts and operation in IDLE with rotor brake on are NOT time limited.

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3
Q

Limitations Imposed by Fuel Types

A

Regardless of fuel type, fuel boost pumps are to be operated at all times when aircraft is fitted with any external components of the EERFS.

When operating on F40 (Jet B), fuel boost pumps are to be operating at all times.

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4
Q

Rotor Limits

Info

A

Max wind for start/stop: 45 knots (from any direction)

Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at IDLE only.

Maximum rotor speed for emergency rotor brake application is 76% RPMR.
Rotor brake shall not be applied with engine(s) operating and rotor turning except during an emergency stop.

Min. rotor brake pressure for engine start is 450psi.
Max. rotor brake pressure for engine start is 690psi.

Engine operation with gust lock engaged is prohibited.

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5
Q

Main Transmission (Notes)

A

Oil pressure should remain steady during steady state forward flight or in level hover.
Range 45-60 psi, to ensure that when fluctuations occur, they remain in the acceptable range.

Fluctuations below 30psi (yellow range) are acceptable during transient manoeuvres or when flying pitch attitudes +6 degrees.

If fluctuation occurs in steady state forward flight, or level hover OR if steady but under 45psi make CAMM2 entry.
Sudden pressure drop (more than 10psi) require CAMM2 entry.

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6
Q

Airspeed

A

Structural Vne - 193 kts (clean configuration, below 17,000 lbs).

Max airspeed with:

  • External stores attached - 170 KIAS
  • OEI - 130 KIAS

Max airspeed for autorotation at the following gross weight:

  • =< 16,825 lbs: 150 KIAS
  • > 16,825 lbs: 130 KIAS.

Max airspeed for SAS(s) inoperative are:

  • One - 170 KIAS,
  • Two - 150 KIAS (in IMC - 140 KIAS)

Max airspeed for hydraulic pump(s) inoperative are:

  • One - 170 KIAS,
  • Two - 150 KIAS (in IMC - 140 KIAS)

Max airspeed for the positioning or adjustment of aircraft lights:

  • Landing Light:
    - Must be extended prior to reaching 130 KIAS.
    - When extended, airspeed limited to 180 KIAS.
  • Search Light:
    - Must be extended prior to reaching 100 KIAS.
    - When extended, airspeed limited to 180 KIAS.

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

Survivor Unrestrained: 40 kts
A/S Fail Advisory: 70 kts

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7
Q

Airspeed - Stabilator

Failure of Automatic Stabilator Control System

A 
0 deg - 150 kts
10 deg - 100 kts
20 deg - 80 kts
30 deg - 60 kts
40 deg - 45 kts

If the automatic milator control system fails in flight and automatic operation cannot be restored:

Manual Control Available:

  • The stabilator shall be set full down at speeds below 40 KIAS,
  • The stabilator shall be set at 0 at speeds above 40 KIAS, and
  • Autorotation airspeed shall be limited to 120 KIAS at all gross weights.

Manual Control Not Available:

  • Placard air speed limits shall be observed as not to exceed speed, except
  • In no case shall the autorotation limit exceed 120 KIAS.an
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8
Q

Airspeed

With aircraft doors/windows open or removed

A

Max airspeed with:

  • Aircrewman’s window fully open - 170 KIAS
  • Cabin door fully open - 145 KIAS
  • Cockpit doors removed - 120 KIAS

The following limitations are imposed when cockpit doors and/or windows are removed:

  • Sideslip is limited to less than one ball width out of trim,
  • Airspeed is to be limited to no greater than 120 KIAS during normal/training operations,
  • Flight in asymmetric configuration of cockpit doors or cargo door windows is prohibited,
  • All loose equipment in the cockpit shall be stowed securely,
  • Cockpit windows shall not be removed,
  • Cockpit doors shall be reinstalled after flight in order to reduce ingress of sand and debris, and
  • Flat plate drag

NOTE:

  • Cabin doors should not be intentionally moved from fully open or closed position above 80 KIAS
  • Cockpit doors sliding windows shall be fully opened or fully closed during flight at all airspeeds.
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9
Q

Manoeuvres

A

Prohibited:

  • Hovering turns greater than 30 deg/s,
  • Aerobatic manoeuvres (rolls, loops and inverted flight),
  • Flight beyond 90 deg AoB (30 deg with PRI SERV PRESS),
  • Simultaneous movement of both ENG PCLs to IDLE or OFF (other than emergency procedures),
  • Practice touchdown auto’s,
  • Manoeuvring flight that results in heavy stall.

Avoided:

  • Out of balance flight >45 kts,
  • Rapid Turns >60 AoB,
  • Any manoeuvres resulting in 4:1 vibrations,
  • Any manoeuvres resulting in droop stop poundings,
  • Abrupt manoeuvring and large control reversals,
  • Practice auto’s except for emergency procedures.
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10
Q

Manoeuvring with Sling/Rescue Hoist Load

A

Max AoB in forward flight - 30 deg.
Forward flight max for rescue hoist load - 100 KIAS.
Forward flight max for sling load - 140 KIAS.
Rearward flight limited to - 35 kts.

RoD limited to 100 fpm against rescue hoist.

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11
Q

Bank Angle

A
  • Beyond 90 AoB prohibited.

- Limited to 30 AoB when PRI SERVO PRESS caution light is illuminated.

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12
Q

Landing Gear

A

Touchdown: 60 kts (Groundspeed on level terrain)

Do not exceed a touchdown sink rate of:

  • Below 16,825 lbs:
    - Level Terrain - 540 fpm,
    - Sloped Terrain - 360 fpm.
  • Above 16,825 lbs:
    - Level Terrain - 300 fpm,
    - Sloped Terrain - 180 fpm.
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13
Q

TGT (C)

A

START max: 869
STOP max: 538

Normal: 0 - 828
30-min: 829 - 869
10-min: 870 - 883
Transient (2.5 min OEI): 884 - 919
Transient (12-sec): 920 - 965

Cool down: 2 min below 90% Ng

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14
Q

Slope Landing

A

Apply regardless of gross weight, CoG, ESSS/EERFS:
- Nose, right or left wheel upslope: 15 deg (reduced by 2 deg for every 5 kts of wind)

  • Nose down: 6 deg.
  • Landing in downslope condition with tail winds greater than 15 kts shall not be conducted.
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15
Q

Weight(s)

A

Max Gross:

  • Clean: 22,000 lb
  • ESSS configuration: 24,500 lb (ferry flight only)

Cargo Hook Weight:
Max suspended weight - 8,000 lb

Rescue Hoist Weight:
Max suspended weight - 600 lb (2 persons max)

Internal Weight:
Max - 4,000 lb

Cabin roof tie-down:

  • Rappelling: 5000lbs
  • Tie Down: 7500lbs
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16
Q

Cargo floor load limit

A

300 lb/ft^2

Compartment C - 5460 lb
Compartment D - 8370 lb
Compartment E - 8370 lb

Compartment F - 250 lb (2 x 125 lb) at 75 lb/ft^2

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17
Q

Windshield Wiper

A

Not to be used on a dry windshield

18
Q

VIDS

A

CDU or PDU is U/S if any 2 or more adjacent lamps do not illuminate OR if any lamps adjacent to a colour change on one scale do not illuminate.

19
Q

Environmental Conditions - Icing

A

Ambient air temperature +4 deg, or below and visible liquid moisture is present.

Pitot heat and anti-icing systems shall be on otherwise Stab Auto Control will cause full down - Manually slew to 0 deg if this occurs.

Liquid water content (LWC):
Trace - LWC 0 - 0.25 g/m^3
Light - LWC 0.25 - 0.5 g/m^3
Moderate - LWC 0.5 - 1.0 g/m^3
Severe - LWC greater than 1.0 g/m^3

Engine and Engine Inlet Anti-Ice Limitation:
Avoid ops under low power:
- RoD >1900fpm, or
- Ground ops <100% RPMR

If Torque is at 10% or below per engine, full anti-ice cannot be provided.

20
Q

APU

A

WARNING: To prevent fire, wait at least 2 min after APU shutdown before attempting a restart.

To prevent APU overheating, APU operating limits are:

  • With engine and rotor operating, at ambient temperature of +43 C and above - 30 min, and
  • With engine and rotor not operating, continuously to an ambient temperature of +51 C.
21
Q

Turbulence Penetration Speed

A

Moderate turbulence penetration speed is VLRC -10 kts or Vne -15 kts, whichever is less.

22
Q

Rescue Hoist Duty Cycle

A
  • Six cycles (full in/out, 300-600 lb load), with a 30 s rest between cycles, and
  • 15 min rest on completion of six total cycles.
23
Q

Engine 1 & 2 (% RPM)

A

AVOID (except during start and shutdown):
20 - 40
60 - 90

Minimum (except for idle and transient) - 91
Transient (Low): 92 - 95
Continuous: 96 - 101
Transient (High): 102 - 105
Maximum: 105
Transient (12 Sec): 106 - 121
24
Q

Main Rotor (% RPMR)

Autorotation

A

Power On:
Transient: 91 - 95
Continuous: 96 - 101
Transient: 102 - 107

Overspeed:
First Light: 127
Second Light: 137
Third Light: 142

Power-on flight:
- CAUTION:
RPMR < 100% will result in degraded aircraft controllability and significantly increased torque requirements.
- WARNING:
RPMR < 96% will result in significantly degraded aircraft controllability and extreme torque requirements that may exceed aircraft capabilities.

Power Off:
Normal: 90 - 105
Transient: 105 - 110
Maximum: 110 (120 for MTF)

25
Q

Rotor Brake

A

Starts:

  • Min pressure: 450 psi
  • Max Pressure: 690 psi

Routine stops:

  • Engines off
  • <40% RPMR
  • no faster than 12 sec

Emergency:
Not to be applied with engines operating and rotor turning, unless Emergency stop. Max rotor speed for brake application 76% RPMR.

26
Q

Torque (%)

A

Dual Engine:

=< 80 KIAS:
Continuous: 0 - 115 (2)
30-min Limit: 116 - 120
10-second Transient: 121 - 150

> 80 KIAS:
Continuous: 0 - 100 (1)
10-second Transient: 101 - 150

Single Engine:

Continuous: 0 - 115
30-min Limit: 116 - 134
10-second Transient: 135 - 150

Note 1 - Airframe/aerodynamic limit (reduce exposure to retreating blade stall)
Note 2 - Engine structural TRQ limitation (All others limited by transmission).

27
Q

Engine Oil Pressure (PSI)

A

Continuous:

  • <90% Ng: 22 - 100
  • > 90% Ng: 35 - 100

Precautionary: 101 - 120
Maximum: 120

NOTE:
Engine oil pressure at idle may reach 50 psi on cold engines. Normal idle range is 22 - 26 psi.

28
Q

Engine Oil Temperature

A

Continuous: -50 - 135
30-min: 136 - 150
Max: 150

29
Q

Ng Speed (%)

A

Continuous: 0 - 99.0
30-min: 99.1 - 102.0
12-sec: 102.1 - 105
Max: 105

30
Q

Fuel Quantity

Indications

A

Precautionary: 0 -200
Normal: 201 - 1500

EERFS Operational Restriction:
Pilots must keep a point of safe landing within main fuel tank range until EERFS transfer capability is confirmed.

Min transfer limit: 40 lbs/min

31
Q

Transmission Oil Temperature (C)

A

Continuous: -50 - 105
30-min: 106-120
Max: 120

32
Q

Transmission Oil Pressure (PSI)

A

Idle and Transient: 20 - 30
Continuous: 31 - 65
Precautionary: 66 - 130
Maximum: 130

NOTE: Pressure fluctuations will occur with pitch attitude changes.

Run dry: 30 min

33
Q

Backup HYD Pump

A
  • 54 - +32:
    • Operating time: Unlimited
    • Cool Down (pump off): N/A
33 - 38:
     - Operating time: 24 min
     - Cool Down (pump off): 72 min

39 - 52:
     - Operating time: 16 min
     - Cool Down (pump off): 48 min
34
Q

FRRD

A

Rappelling/Suspended Extraction: 330lb max (per rope)
Fast roping: 1323lb per arm

*no shock loading

35
Q

Minimum Crew

A

1 pilot

36
Q

HIT check

A

Retard PCL to: 92 - 98 Np
Residual TRQ limit: +/- 5
TRQ Accuracy check: +/- 5

37
Q

HIT Check

Anti Ice/Bleed

A

Ng <90% and OAT <15: set 90 Ng
Ng <90% and OAT >15: set 94 Ng

TGT Increase Anti Ice on: 30 - 110
TGT Increase Air Source ENG: 5

38
Q

Pneumatic Source Inlet

A

Min ground: 40 psig, 30 ppm, +149 C

Max ground: 50 psig, 249 C

39
Q

De-Ice EOT

A

Max: 38C

If above 21C operate at 100 RPMR for 5 min

40
Q

ESSS Jettison Envelope

A

Max horizontal speed: 0 - Vh
RoD (up to 60 kts): 1000 fpm
RoD (up to 120 kts): 500 fpm
Balance equal to or less than 1 skidball

41
Q

HUD Accuracy

A 
Pitch: 1 deg
HDG: 1 deg
Roll: 1 deg
Baralt: 40 ft
RoC: 50 fpm
Radalt:
- <200 ft: within 2 ft
- >200 ft: within 10 ft
Ground speed: 5 kts
Air speed: 5 kts
TGT: 15 C
Velocity Vector: 15 kts
42
Q

Obstacle Clearance

A

Airframe Clearance:
Whilst hovering, taxiing, touching down or lifting off, a minimum of 3 ft (1 m) horizontal clearance is maintained from obstacles. At all other times, a minimum of 10 ft (3 m) horizontal obstacle clearance shall be maintained.

Rotor Clearance:
Ensure that a minimum of 10 ft (3 m) rotor tip clearance is maintained horizontally from all obstacles;

additionally:

a. maintain minimum ½ rotor diameter when operating near stationary aircraft, vehicles or man made structures. This limit may be reduced to 10 ft (3 m) with blade-walkers or marshallers.
b. Maintain minimum two rotor diameter from formation aircraft.

b. Hovering:
(1) for obstacles under the rotor disc in the hover, clearance may be reduced to 5 ft (1.5m) vertically above the obstacles at AC discretion; and
(2) the rotor disc is to be maintained clear of any overhanging objects, whether man made or natural, to ensure objects cannot be pulled into the rotor disc or dislodged.

c. Landing:
(1) For obstacles under the rotor disc on landing, and once the landing has been completed, the vertical distance to the blades will be no closer than 5 ft (1.5 m).

S-70A (3 decks)

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