NATOPS Ch12 Emergency Procedures Flashcards
Following should be performed for all emergencies:
- Maintain control of the aircraft
- Alert crew
- Determine the precise nature of the problem.
- Complete the applicable emergency procedure or take action appropriate for the problem
- Determine landing criteria and land as required
What is single engine condition and how do you achieve it?
A flight regime that permits sustained flight with OEI. Establishing single-engine conditions may include increasing power available (turning C-power on and engine anti-ice off), decreasing power required (dumping fuel and jettisoning cargo), and achieving single-engine airspeed.
Engine Malfunction in Flight
- Control Nr
WARNING
Flying with greater than 110% torque with one engine inoperative may result in unrecoverable decay of Nr in the event of a dual-engine failure
- CONTGCY PWR switch - ON
- Single-engine conditions - Establish
- ENG ANTI-ICE switched - As required
WARNING
With engine anti-ice on, up to 18% torque available is lost. Torque may be reduced as much as 49% with improperly operating engine inlet anti-ice valves
- External cargo/stores/fuel - Jettison/dump, as required
- Identify Malfunction
Engine High Side Failure in Flight (conditions)
All of the following conditions exist:
- TRQ is 10% or greater than other engine
- Ng is 5% or greater than other engine
- Np is matched within 5% of other engine
- Nr is at or above 103%
Engine High Side Failure in Flight
- EMIF ep - Perform
- PCL (malfunctioning engine) - Retard to set:
- a. Torque 10% below the good engine
- b. Matched Ng
- c. Matched TGT
CAUTION
If an Np overspeed condition is reached (120%), the overspeed system will flame out the engine and the auto-ignition system will relight the engine. If Nr is not controlled and Np accelerates back to 120%, the overspeed system will flame out the engine again and auto-ignition system will reset the igniter 5-second timer. The Np overspeed/auto-ignition system will continue cycling until Np/Nr is controlled. A yaw kick may be experienced each time the engine relights.
NOTE
With high collective settings, Nr may increase slowly, making high-side failure confirmation difficult. Reducing collective will reveal increasing Nr and verify high-side failure.
Engine High Side Failure on Deck
- PCLs - IDLE
Engine Low Side Failure (conditions)
All of the following conditions will exist:
- TRQ is 10% below the good engine
- Ng is 5% or less than the good engine
- NP is at or below 98%
- Nr is at or below 97%
Engine Low Side Failure
- EMIF ep - Perform
CAUTION
When an engine is manually controlled with the ENG POWER CONT lever in LOCKOUT, the engine response is much faster and the TGT-limiting system is inoperative. Care must be taken to prevent exceeding TGT limits and keeping Nr and Np in their operating ranges; however, the Np overspeed system will still be operative.
Engine Torque or TGT Spiking/Fluctuations
If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng. Np, and/or Nr:
- EMIF ep - Perform
If fuel contamination is suspected:
- LAND AS SOON AS POSSIBLE
WARNING
PCL movement during engine fluctuations may precipitate an engine failure. Consider performing APU Emergency Start procedure prior to manipulating the PCL. Maintaining a lower power setting when moving the PCL will minimize Nr decay rate if the malfunctioning engine fails.
What are the indiciations of a compressor stall?
Rapid increase in TGT, hangup or rapid decrease in Ng, loss of power, or a change in engine noise level varying from barely audible to muffled explosions.
Compressor Stall
- EMIF ep - Perform
- PCL (malfunctioning engine) - IDLE
CAUTION
If the Ng decay relight feature attempts to relight the engine, subsequent compressor stalls may occur and damage the engine. A yaw kick may be experienced each time the engine relights. The engine must be manually shut down.
What are the indiciations of a High Speed Shaft Failure?
What if theres a failure at the high speed shaft seal?
Np is greater than Nr by more than 3% and engine torque is below 10%. May manifest itself as high-intensity, med to high-frequency vibration that may be felt throughout the aircraft. A howl may accompany the vibration.
Cockpit indications may initially remain normal; however, if the high-speed shaft seal at the input module is damaged and transmission oil is lost, secondary indications of impending failure (transmission oil pressure and temperature) may be present. Consideration should be given to securing the engine, thereby precluding catastrophic failure of the high-speed shaft
Engine High Speed Shaft Failure
CAUTION
Following a high-speed shaft failure, the engine will overspeed, the Np overspeed system will flame out the engine, and the auto-ignition system will activate the relight feature. The engine Np governor will eventually bring Np down toward 100%. The engine must be manually shut down to prevent damage.
- EMIF ep - Perform
- PCL (malfunctioning engine) - OFF
NOTE
The Engine Np sensor is unreliable with Np <20%. For this reason any (#1/#2) DRVSHAFT FAIL should be acknowledged and ignored when Engine Np <20%. No maintenance action is required when in this condition. (During engine water washes)
Indications of a LDS or Roll-Pin Failure while on deck
A Roll pin failure will result in maximum LDS input to the HMU, regardless of collective position. This condition may result in excess power driving the main rotor during an autorotative descent beacuse the DECU will not have enoughdown-trimming authority to reduce torque to zero.
- PCLs in IDLE - Ng of malf eng 3-4% higher Rotor
- Engagement - Eng with failed LDS will indicate higher torque as PCLs are evenly advance to FLY. Good eng may not indicate torque until PCL is in FLY
- PCLs in FLY, collective full down - May range from matched torque , 100% Np/Nr (no indications of failure), to possible 1-2% torque split with Nr and both Np’s matched 1-2% above 100%
Indications of a LDS or Roll-Pin Failure while in flight
- Initial collective increase - Torque split. Torque of engine with failed LDS will be lower
- Stable hover - matched torques
- Collective increases (below approx 75% full up) - Torque split. Torque of engine with failed LDS will be lower
- Collective increases (above appox 75% full up) - No split. Both LDS are at max setting
- Collective decrease (to position below approx 75% full up) - Torque split. Torque of engine with failed LDS will be above good eng
- Stable flight - Matched torques
- Auto - Rapid Np/Nr rise. Engine with failed LDS may show a residual torque of approx 12% with collective full down
What are the Criteria for executing an Abort Start?
Abort engine start if any of the following limits are exceeded:
- Ng does not reach 14% within 6 sec after starter initiation
- No oil pressure within 30 sec after starter initiation (do not motor engine)
- No light-off within 30 sec after moving PCL to IDLE
- ENG STARTER advisory disappears before reaching 52% Ng
- TGT is likely to exceed 851°C before idle speed is attained
Abort Start
To abort start:
- PCL - OFF
- ENGINE IGNITION switch - OFF
If engine oil pressure is indicated:
- Starter - ENGAGE
CAUTION
During aborted starts, failure to immediately stop fuel flow may result in engine over temperature.
Engine Malfunction During Hover/Takeoff
- Control Nr
- CONTGCY PWR swtich - ON
If a suitable landing site exists or unable to transition to forward flight:
- Set level attitude, eliminate drift, cushion landing.
If able to transition to forward flight:
- EMIF ep - Perform
Dual-Engine Failure
- Autorotation - Establish
- Immediate Landing/Ditching ep - Perform
If time and altitude permit:
- Engine Air Restart ep - Perform
Single-Engine Failure in Flight
- EMIF ep - Perform
ENG OUT Warning light is activated by the vertical insturment when Ng decreases below 55%. In the event of an isolated Ng signal failure, the ENG OUT light will be illuminated with the engine operateing normally. TORQUE SPLIT Warning light is illuminated when Difference between engine torques is greater than 10%
Engine Air Restart
- APU Emergency Start procedure - As required
- ENGINE IGNITION switch - NORM
- Fuel Selector Lever(s) - DIR or XFD
- PCL(s) - OFF
- Starter(s) - Engage, motor engine
- PCL(s) - IDLE (TGT 80°C or less, if time permits)
- PCL(s) - Advance to FLY after starter dropout
WARNING
If APU is unavailable, and a crossbleed start is necessary, maximum torque available will be reduced during the start sequence. Depending on operating conditions, level flight may not be possible. Ensure AIR SOURCE ECS/START switch is placed to ENG for crossbleed starts.
CAUTION
For a crossbleed start, the donor engine should indicate the maximum Ng safely obtainable. Receiving engine Ng less than 24% prior to advancing PCL to IDLE may result in a hot start.
NOTE
Either a single- or dual-engine restart may be attempted following dual-engine failure. Decision should be based on applicability of respective start envelopes and considerations of longer time to idle when executing a dual-engine restart.
NOTE
In the event of an alternator failure, the Ng signal may be unavailable. Engine start will not be possible without ac power provided to the ignition exciter.
What are the indications of a Malfunctioning Anti-Ice/Start Bleed Valve?
A malfunctioning anti-ice start/bleed valve is indicated by any of the following:
- Illumination of the ENG ANTI-ICE ON advisory with above 90% Ng or above 94% Ng if OAT is 15º or greater.
- No illumination of the ENG ANTI-ICE ON advisory when Ng drops below approximately 88% Ng.
- No illumination of the ENG ANTI-ICE ON advisory when the ENG ANTI-ICE switch is selected ON.
- No rise in TGT when ENG ANTI-ICE switch is selected ON. (Should rise 30-100°)
APU Emergency Start
- ECS - OFF
- AIR SOURCE ECS/START switch - APU
- FUEL PUMP switch - APU BOOST
- APU CONTR switch - ON
- APU GENERATOR switch - ON
Unusual Vibrations on Deck
- Collective - Lower
- PCLs - OFF
- Rotor brake - Apply as required
CAUTION
Application of the rotor brake may aggravate lead/lag tendencies and cause a mechanical failure.
Hung Droop Stops
- Reengage rotor to greater than 75% Nr
NOTE
While operating in cold weather, consideration should be given to turning the BLADE DE-ICE control panel POWER switch to the POWER ON position. This will activate the droop-stop heaters and aid the droop stops in seating.
Low Rotor RPM
- Control Nr
Warning light is activated by the vertical instrument when Nr is less than 96%
Main Transmission Malfunction
WARNING
Possible indications of main transmission imminent failure may include: yaw attitude excursion with no control input, an increase in power required for fixed collective setting, failure of a main generator or hydraulic pump, increased noise, increased vibration levels, or abnormal fumes in the cabin.
If failure is imminent:
- LAND IMMEDIATELY
If secondary indications are present:
- LAND AS SOON AS POSSIBLE
WARNING
Operation of the main gearbox with no oil pressure may result in failure of the tail rotor drive takeoff pinion gear and subsequent loss of tail rotor drive.
NOTE
Consideration should be given to performing the applicable steps of the Immediate Landing/Ditching ep and transiting at a minimum power airspeed and low altitude flight profile (approx 80 ft/80 KIAS) to permit a quick flare followed by an immediate landing/ditching.
NOTE
A loss of all main transmission libracating oil may result in unrelable temp indications from the main transmission temp guage and temp sensor (caution)
NOTE
Continued operations in the precautionary range for temp and pressure are acceptable provided that the ambient conditions and flight regime of the aircraft correspond with the guidance set forth in the transmission limitations.
Tail/Intermediate Transmission Malfunction
Failure is imminent when accompanied by strong medium-frequency vibrations, hot metal fumes, or any other associated indications
If failure is imminent:
- LAND IMMEDIATELY
If failure is not imminent:
- LAND AS SOON AS POSSIBLE
WARNING
High power settings require maximum performance of the tail rotor drive system and may precipitate ultimate drive failure.
WARNING
Consideration should be given to transiting at an altitude sufficient to enter an autorotation and performing the applicable steps of the Immediate Landing/Ditching ep.