-
Loss of Thrust
- -Caused by failure of t/r gearbox, intermediate gearbox, or t/r drive shaft.
- -Nose will yaw right.
- -Estb an airspeed for trimmed flight and autorotative glide above 80 KIAS to maximize the effectiveness of decel during landing.
- -Seek a headwind or left quartering crosswind to aid in maintaing heading control for landing.
-
Fixed Pitch
- -Caused by jam, binding, failure in flight controls or tail rotor quadrant.
- -Achieve level trimmed flight bt 25-145 KIAS.
- -Nose will turn right when power/as is increased. Left when collective/as is decreased.
- -Land into the wind or with a crosswind component opposite the yaw.
- -GWT, amount of anti-torque applied at time of failure, and airspeeds that allow for trimmed flight must be considered when determining landing type.
-
9.22.1
Loss of t/r thrust in cruise flight.
1. A - a t x k o a
2. A - m a a o a x k
3. E - o (d d w i p o l i a)
If auto entry is delayed, sideslip angles can developed; low IAS; stab will program down; maintaining autorotative a/s difficult.
- 1. Airspeed - adjust to 80 kts or above.
- 2. Autorotate - maintain a/s at or above 80 knots.
- 3. EPCLs - off (during deceleration when intended point of landing is assured.)
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9.22.2
Loss of T/R thrust or T/R QUADRANT caution appears with loss of control at low airspeed/hover (right rotation).
1. C - R
2. E - O (x f a t)
Loss of t/r thrust may result in extreme yaw and uncontrolled right rotation.
- 1. Collective - Reduce.
- 2. EPCLs - Off (5 to 10 ft above touchdown)
-
9.22.3
Tail Rotor Quadrant Caution appears in Cruise Flight
Warning
I t h i s d a/o h p i r w o t r c f, d o t o t r c w o w f f t b s c r a c c q s t.
T q s w d t c a b s p e t u t q c.
- If the helicopter is shut down and/or hydraulic power is removed with one tail rotor cable failure, disconnection of the other tail rotor cable will occur when force from the boost servo cannot react against control cable quadrant spring tension.
- The quadrant spring will displace the cable and boost servo piston enough to unlatch the quadrant cable.
-
9.22.3
Tail Rotor Quadrant Caution appears in Cruise flight
1. C - a t d c (F r o L)
2. L a s a p
- 1. Collective - Adjust to determine controllability (Fixed R or L)
- 2. Land as soon as practicable
-
9.22.4
Loss of Control at Low Airspeed/Hover or Tail Rotor Quadrant Caution appears (Left Rotation).
Warning
R c i a l r w i r o t w t E(s) a f d o t r a w t E(s) a r.
I i c t t p o t c m a l a, p R R a a c f t l.
- Reducing collective in a left rotation will increase rate of turn with the EPCL(s) at fly depending on the rate at which the PCL(s) are retarded.
- It is critical that the pilot on the controls maintain a level attitude, preserve RPM R and apply cushion for the landing.
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9.22.4
Loss of Control at Low Airspeed/Hover or Tail Rotor Quadrant Caution appears (Left Rotation).
1. E - R t d R b x% a b a p p d
2. C - A t p R
3. E - O (x f a t)
4. C - A f l
- 1. EPCL(s) - Retard to decrease RPM R below 100% and begin a partial power descent.
- 2. Collective - Adjust to preserve RPM R.
- 3. EPCLs - OFF (5-10 ft above td)
- 4. Collective - Adjust for landing.
-
9.22.5
Pedal bind/Restriction or Drive with no Accompanying Caution
A m w t y b o t r s c p m h f a t p a m b t o. xx l.
1. A p f t o t d
2. C o p f p o
3. T S S - B
I n c a i n r:
4. T S S - N
5. B s - O
S n r:
6. B s - O
7. C - A t d c f l
8. L a s a p
A malf within the yaw boost or tail rotor servo can produce much higher force in the pedals and must be turned off. 250 lbs.
- 1. Apply pedal force to oppose the drive.
- 2. Check other pedals for proper operation.
- 3. Tail Servo Switch - Backup
- If normal control authority is not restored:
- 4. Tail Servo Switch - Normal
- 5. Boost switch - Off
- Still not restored:
- 6. Boost switch - On.
- 7. Collective - Adjust to determine controllability for landing.
- 8. Practicable
-
9.22.6
#1 Tail RTR Servo Caution Appears and Back-Up Pump On Advisory Does Not Appear or #2 Tail RTR Servo On Advisory Does Not Appear.
A s o d n t p.
L o t #x p a b p r i b s o t-r s b u.
T y b s i s p a t m c s i s i a l t/r c.
B o t l a c r, r-o l a 4 k o a.
1. T r s s - B
2. B H P s - O
3. L a s a p
- Automatic switch over did not take place.
- Loss of the #1 pump and backup pump results in both stages of tail-rotor servo being unpressurized.
- The yaw boost servo is still pressurized and the mech control sys is still intact allowing limited t/r control.
- Because of the limited yaw control range, roll-on ldg at 40 kts or above.
- 1. Tail Rotor Servo switch - Backup
- 2. Backup HYD Pump switch - ON
- 3. Land as soon as Practicable
-
9.22.7
Main XMSN Oil Press or Main XMSN Oil Temp Caution Appears / XMSN Oil Press Low / XMSN Oil Temp High.
1. L a s a p
I t p:
2. S t x k
3. E A s
4. G x/x s - o
1. Land as soon as possible
- If time permits:
- 2. Slow to 80 kts
- 3. Emer APU Start
- 4. Generators 1/2 switches - off
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9.22.8
Chip Input MDL Lh/Rh Caution Appears
1. E s e a
2. E P C l (a e) - i
3. L a s a p
- 1. Establish single engine airspeed
- 2. EPCL (affected engine) - Idle
- 3. Possible
-
9.22.9
Chip Main Mdl sump, Chip Access MDL Lh or Rh, Chip Tail XMSN or Chip INT XMSN/TAIL XMSN Oil Temp or Int XMSN Oil Temp Caution Appears
L a s a p
Land as soon as possible
-
9.22.10
Main Transmission Failure
Warning
I %R d f x% t b x% w a i i t d s f w n e m, t m t p c m h f. D a m t p c f, i m b i t m %R a x%.
Note
D %R m b a b a d i t o p o x p o m, a p u h v
1. C - A o e t b a d w p r a t t m t t t d a l
2. L a s a p
- Warning
- If %RPMR decreases from 100% to below 96% with an increase in torque during steady flight with no engine malfunction, the main transmission planetary carrier may have failed. During a main transmission planetary carrier failure, it may be impossible to maintain %RPMR at 100%
- 1. Collective - Adjust only enough to begin a descent with power remaining applied to the main transmission throughout the descent and landing
- 2. Land as soon as possible
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