Limitations.txt

0-107 deg Celsius cont. operation

107 deg Max

Y-50 psi minimum below 78% N1 (engine speed)

G-90 psi minimum from 78%-94% N1

G-115 psi min aboove 94% N1 (dbl wide arc)

R-50 psi min, 130 psi max

G- 30 to 50 psi cont. operation

R- 30 psi min, 70 psi max

G- 15 deg C to 110 deg C cont. operation

R- 110 deg C max

R- 4 psi min

G- 4 to 30 psi cont op

R- 30 psi max

R- 8 psi min-type A, A-1, JP-5, JP-8 fuel below -18 deg C (0 deg F) to -32 deg C (-25 deg F)

R- 70% max

G- 0 to 130 knots cont op

R- 130 knots max

B- 100 knots max for autorotation

Autorotation above 100 KIAS will result in high rates of descent and low rotor RPM

78 KIAS, not to exceed placarded VNE

Turbine outlet Temp

G- 100 to 738 deg C cont op

Y- 738 to 810 deg C Take-off Power Range (5 min limit)

R- 810 deg C max (810-843 deg C, 6 sec transient, not to be used intentionally)

R- 927 deg C max during starting and shutdown (10 sec max)

810-927 deg C for 10 sec, or higher than 927 deg C

Exceeding the limits of 810 deg C TOT or 100% torque may cause N1 topping with resultant rotor droop

G- 60 to 105% cont op

R- 105% max

* 105 to 106% transient (15 sec max)

R- 90% min op

Y- 50-60% accelerate through this range

G- 90-107% norm op

R- 107% max

*power on transient rotor droop limit=95% (5 sec max)

R- 97% min op

G 97-100% cont op

R- 100% max

*N2 75%-88%, 60 sec max (time not cumulative)

Use of throttle to control rpm is not authorized. (Refer to ch 9, EP's and USAAWC Flight Training Guide for exceptions)

N2 transient overspeed limit is 15 sec max, shaded area represents allowable overspeed. (look at chart)

*Increase RPM=Decrease torque

G- 0 to 85% cont op

Y- 85 to 100% take-off power range (5 min limit)

R- 100% max

100 to 110% (5 sec max)

*Intentional use is prohibited

110 knots

78 KIAS, not to exceed placarded VNE

This helicopter must be operated in compliance with the operating limitations specified in the approved helicopter flight manual.....min pilot wt=170lbs

250lbs

*Cargo must be secured in accordance with the flight manual instruction

86lbs

176.5lbs

The nickel cadmium battery has been replaced with a sealed lead acid battery. Battery temp monitoring system has been deactivated

• Max op-
• *VFR 20,000ft press. altitude
• *IFR 14,000ft press. altitude

• Max op-
• *VFR 13,500ft press altitude
• *IFR 8,000ft press altitude

The helicopter can be started in a max wind velocity of 45 knots and max gust spread of 15 knots

*Gust spreads are not normally reported. To obtain spread, compare min and max velocities

35 knots max

30 knots max

IGE maneuvers-refer to ch 8

OGE maneuvers-calm wind only

Prolonged op of standby generator while it is the primary power supply to essential #1 bus is prohibited at airspeeds less than 50 KIAS (Vmini) to assist with generator cooling

With main gen. on, standby gen loadmeter should indicate 10% or less, momentary testing of standby gen under full bus load is permitted on ground or in air

4 deg C

4 deg C or below

Takeoff with LOW INLET PRESSURE caution light illuminated is PROHIBITED

• External Power Battery
• 25 sec on 40 sec on
• 30 sec off 60 sec off
• 25 sec on 40 sec on
• 30 sec off 60 sec off
• 25 sec on 40 sec on
• 30 min off 30 min off

• External/Battery Power
• 1 min on
• 1 min off
• 1 min on
• 1 min off
• 1 min on
• 30 min off

* If N1 doesn't reach 58% in a total time of 45 sec (or 60 sec below 10 deg C FAT), close throttle and press starter button until TOT is below 200 deg C.

* If engine fails to start on third attempt, abort start and make an entry on DA form 2408-13-1.

* Starter engage time limits above do not apply to engine starting limitations should abort start procedures become necessary.

Turbine fuel ASTM D-1655, (Type B) or MIL-T-5624 (JP-4) may be used at all ambient temps with no restrictions

* 8 psi at temps of -18C to -32C (0 to -25 deg F)

* 4 psi at temps above -18C (0F)

* Must be performed if prior to the first flight of each day if fuels other than Type B or JP-4 are used

* Must be performed if Power Off maneuvers are to be performed

Helicopters equipped with airframe mounted fuel filter do not require the use of anti-icing additive at any ambient temps.

Refer to Allison 250-C20 series OP and Maint Manual for AVGAS Mix, Cold weather fuel, and blending instructions

*The use of AVGAS in TH-67 is prohibited

Any fuels other than Jet B or JP-4 are used at ambient temps below 5C

-Method by which the aviator in day-to-day flying monitors the aircraft engine condition

-TOT is compared to a predicted value within a certain tolerance and differences are logged

-differences -/+20C or greater between the recorded TOT and baseline TOT=2408-13-1

-differences -/+ 40C grounded aircraft

106.0-114.2

CH 6

106-110 at GW of 2,400-3,200lbs

106.9 at GW above 3,200lbs

CH 6

No change from basic helicopter CG with only aft cabin doors off

With one or both forward doors off, long. CG limits are same as with doors on

Actual wt. change is determined after doors, etc., have been removed and ballast readjusted, if nec., to return basic wt. CG to within allowable limits

Station 0 (datum) is located 55.6 in forward of forward jack point centerline

3 in left of helicopter centerline

4 in right of helicopter centerline

Lat. CG limits vary depending on long. CG location

3,350lbs

3,350lbs

170lbs

****Use ballast as required to maintain basic wt CG within limits

All airspeed values are Indicated Airspeed (IAS), except when Calibrated Airspeed (CAS) is specifically stated

VMC Vne 130 KIAS sea level to 3,000 ft density alt.

Decrease Vne 3.5 KIAS per 1,000 ft above 3,000 ft. density alt

Max dens. alt= 20,000 ft

VMC Vne 122 knots sea level to 3,000 ft density alt.

Decrease Vne 7.0 KIAS per 1,000 ft above 3,000 ft density alt

Max density alt=13,500 ft

78 KIAS, not to exceed placarded Vne

70KIAS

50 KIAS

110 KIAS, or placarded Vne, whichever is less

78 KIAS, or placarded Vnei, whichever is less

Vne 80 knots with > 85% to 100% torque applied

AIRSPEEDS IN EXCESS OF AIRSPEED LIMITATIONS DOOR(S) OFF WILL CAUSE CYCLIC FORE AND AFT STICK REVERSAL AND FUSELAGE BUFFERING

Vne 87 KIAS or placarded airspeed, whichever is less, power ON or OFF

ON

OFF

**with one or both forward doors off, both rear sliding windows must be closed above 70 KIAS

with both forward doors removed, the aircraft is approved for day and night VFR ops only. IFR is prohibited

Prohibited-Any intentional maneuver involving an abrupt change in aircraft attitude, an abnormal attitude, pitch angle greater than 30 deg or roll angles greater than 60 deg, or abnormal acceleration not necessary for normal flight

flight at less than +0.5g is prohibited

For GW geater than 3,000lbs and density alt. greater than sea level, the directional control margin may be significantly reduced while hovering in winds from the right greater than 20 knots or for right sideward flight at speeds greater than 20 knots

*reported surface winds must not exceed 20 knots

*surface crosswind component must not exceed 10 knots from crosswind chart

*wind gust spread must not exceed 10 knots

*touchdown autorotations downwind are prohibited

*airspeed during autorotation shall not be less than est. for minimum rate of descent

*ground speed at touchdown should be approx. 5 knots

*Touchdown in a level attitude prior to passing through 70% rotor RPM

*Upon ground contact, collective pitch shall be reduced smoothly while maintaining the cyclic near the neutral or centered position

*If skid "chatter" is encountered, a SLIGHT increase in collective may be temp. used to stop it

*Continue to reduce collective as soon as practicable when chatter stops

3,200lbs

*Relatively long ground runs with the collective up, or any tendency to float for long distance prior to skid contact shall be avoided

*If abnormal vibrations are felt before or after touchdown, immediate lowering of collective is recommended to dampen

*Under normal conditions, the collective will be smoothly and slowly lowered to the full down position after skids on ground.

*Cyclic will remain near neutral with aft cyclic inputs avoided.

limited to 8 degrees or less

*Caution is to be excercised on slopes greater than 5 degrees since rigging, loading, terrain, and wind conditions may alter the slope landing capability

The anti-collision light may be turned off during flight or in near visible moisture to prevent reflections and possible pilot vertigo

Keep cabin glass clean to prevent halation

Maximum precision approach angle is 4.7 deg

Max rate of climb and descent=1000ft/min

• -Cyclic force trim system
• -main gen
• -standby gen
• -batt. protection circuit
• -pilot's flight instruments
• -co-pilot's flight instruments
• -standby attitude gyro-automatically powered by approved standby battery source in event of primary pwr loss
• -2 comm systems
• -2 nav systems appropriate to routes flown
• -other equip as req. by operating rules

Flight in falling and/or blowing snow is prohibited unless the Particle Separator Engine Air Induction System Kit and the Deflector Kit are installed to reduce possibility of engine flameout.

If Kit is installed, hover flight is limited to 20min, then helicopter must be landed and checked for snow/ice accumulation

Flight ops are prohibited when visibility is less than 1/2 statute mile

prolonged hovering over salt water which results in spray ingestion, indicated by spray on windshield, should be avoided

Operations in heavy sand or dusty conditions without the improved nozzles will result in lower inlet particle separator (IPS) efficiency which in turn severely shortens the engine life

If the inlet air barrier filter is installed and the AIR INLET PRESSURE caution light illuminates or ENGINE AIR ALTERNATE switch is turned on, appropriate entries on Da 2408-13-1 to alert maint

entry on DA 2408-13-1 to alert maint

entry on DA 2408-13-1 and state what limts were exceeded, range, time beyond limits, and any additional data that would aid maint. personnel in the inspection

Fuel boost pump shall be ON during normal ops