EP & Limits practice Flashcards
1
Q
Any time an operational limit is exceeded, an appropri-ate entry shall be made on DA FORM ___________.
A
2408-13-1
2
Q
Entry shall state what limit or limits were _______, ___________, ______________, and any additional data that would aid maintenance personnel in the maintenance action that may be required.
A
exceeded, range, time beyond limits
3
Q
The helicopter shall not be _______ until corrective action is taken.
A
flown
4
Q
The minimum crew required to fly the helicopter is _____ pilots.
A
two
5
Q
Additional crewmembers, as required, will be added _______________________.
A
at the discretion of the commander, in accordance with pertinent Department of the Army regulations.
6
Q
Red and yellow striped tapes and red readouts indicate the limit _______________.
A
above or below which continued operation is likely to cause damage or shorten component life.
7
Q
Yellow tapes and readouts indicate ______________.
A
the range when special attention should be given to the parameter the instrument represents.
8
Q
Green tapes and readouts indicate the ___________________.
A
normal operating range of the parameter the instrument represents.
9
Q
Operating an engine against the gust lock is __________________.
A
prohibited.
10
Q
Rotor brake shall not be applied with engine(s) operating and rotor turning except during an ________________. Maximum rotor speed for emergency rotor brake applications is ____% NR.
A
emergency stop
76
11
Q
Routine stops will be with engine(s) off, NR below ______% and with _____-____ psi applied to stop the rotor in not less than ___ seconds.
A
40
150-180
12
12
Q
Minimum rotor brake pressure for engine start is ____ psi. Maximum rotor brake pressure for engine start is ____ psi.
A
450
690
13
Q
Use of the rotor brake with engine(s)operating is restricted to ________ and _______engine starts and operations at ________ only.
A
single
dual
IDLE
14
Q
Single and dual engine starts and operation at _______ with rotor brake on are not time limited.
A
IDLE
15
Q
If oil pressure is not steady during steady state forward flight or in a level hover, or if oil pressure is steady but under ____ psi, make ane ntry on the appropriate maintenance form. Sudden pressure drop (more than ___ psi) without fluctuation requires an entry on the appropriate maintenance form.
A
45
10
16
Q
Torque
(10 second transient)
Dual-Engine
Above 80 KIAS __________%
80 KIAS or below _________%
Single-Engine ____________%
A
100 - 144
120 - 144
135 - 144
17
Q
Torque
(Continuous)
Dual-Engine
Above 80 KIAS __________%
80 KIAS or below _________%
Single-Engine ____________%
A
0 - 100
0 - 120
0 - 135
18
Q
NG limits
12 second transient __________
Continuous _____________
A
105 - 106%
0 - 105%
19
Q
TGT limits
12 second transient \_\_\_\_\_\_\_\_\_ 2.5 minute transient (contingency power) \_\_\_\_\_\_\_\_\_\_\_ Start Abort Limit \_\_\_\_\_\_\_\_\_\_\_ 10 minute Limit \_\_\_\_\_\_\_\_\_\_\_\_ 30 minute Limit \_\_\_\_\_\_\_\_\_\_\_\_ Normal \_\_\_\_\_\_\_\_\_\_
A
903 - 949 879 - 903 851 846 - 879 793 - 846 0 - 793
20
Q
NP1 / NP2
12 second transient ___________%
Transient ____________%
Continuous ___________%
Transient _____________%
A
105 - 107
101 - 105
95 - 101
91 - 95
21
Q
NR
Power on
Transient __________%
Continuous ___________%
Transient __________%
A
101 - 107
95 - 101
91 - 95
22
Q
NR Power off (autorotation)
Maximum ____________%
Transient ____________%
Normal ____________%
A
110
105 - 110
90 - 105
23
Q
Engine oil pressure
Idle ___________ psi
Normal ________ psi
5 min. limit _______ psi
A
22 - 26
26 - 100
100 - 120
24
Q
Engine oil temperature
Continuous ________
30 min. limit _________
A
-20 - 135
135 - 150
25
Transmission oil temperature
Continuous ____________
Precautionary __________
-20 - 105
| 105 - 140
26
Transmission oil pressure
Idle and transient _________ psi
Continuous __________ psi
Precautionary __________ psi
20 - 30
30 - 65
65 - 130
27
At ambient temperatures of ___°C (59°F) and below, ____ consecutive start cycles may be made, followed by a ___ minute rest period, followed by ___ additional consecutive start cycles. A ___ minute rest period is then required before any additional starts.
15
two
3
two
30
28
At ambient temperatures above ___° up to ___°C (59° up to 126°F), ___ consecutive start cycles may be made. A ____ minute rest period is then required before any additional start cycles.
15
52
two
30
29
Crossbleed starts shall not be attempted unless the _______________ or _______________ advisory does not appear, and operating engine must be at ____% NG or above and rotor speed at ____% NR.
ENG 1 ANTI-ICE ON
ENG 2 ANTI-ICE ON
90
100
30
Engine overspeed check in flight is ___________. Engine overspeed checks, on the ground, are authorized by ______________________________ only.
prohibited
designated maintenance personnel
31
Maximum capacity for each storage compartment is ____ pounds.
125
32
Max cargo hook capacity
9,000
33
Maximum weight is further limited by cargo floor maximum capacity of ____ pounds per square foot.
300
34
External lift missions above ________ pounds can only be flown with cargo hook loads above _______ pounds and up to ________ pounds.
22,000
8,000
9,000
35
UH-60M external lift mission max ________ lbs
23,500
36
The four cabin ceiling tiedown fittings have a limited load capability of ________ pounds. The 17 tiedown fittings installed on the cargo floor can restrain a ________ pound load in any direction. The eight net restraint rings in the cargo compartment are rated at ________ pound capacity in any direction.
4,000
5,000
3,500
37
Maximum airspeed with external cargo hook loads up to 8,000 pounds is _____ KIAS
140
38
Maximum airspeed for one engine inoperative is ____ KIAS.
130
39
Maximum airspeed for autorotation at a gross weight of 16,825 pounds or less is ___ KIAS.
150
40
Maximum airspeed for autorotation at a gross weight of 16,825 pounds or more is ___ KIAS.
130
41
Sideward/Rearward flight into the wind, when combined with wind speed, shall not exceed ___ knots ( ___ knots with ESSS).
45
35
42
SAS inoperative airspeed limits:
a. One SAS inoperative - ___ KIAS.
b. Two SAS inoperative - ___ KIAS.
c. Two SAS inoperative in IMC - ___ KIAS.
170
150
140
43
Hydraulic system inoperative limits:
a. One hydraulic system inoperative - ___ KIAS.
b. Two hydraulic systems inoperative - ___ KIAS.
c. Two hydraulic systems inoperative in IMC - ____ KIAS.
170
150
140
44
Maximum airspeed for:
Landing Light
Extending _____ KIAS
Extended _____ KIAS
130
| 180
45
Maximum airspeed for:
Searchlight
Extending _____ KIAS
Extended _____ KIAS
100
| 180
46
Cabin door(s) maybe fully open up to ___ KIAS.
Gunner window(s) maybe fully open up to ___ KIAS.
Flight with cockpit door(s) removed is __________.
145
170
prohibited
47
Manual control is available:
(1) The stabilator shall be set full down at speeds below ___ KIAS.
(2) The stabilator shall be set at 0° at speeds above ___ KIAS.
(3) Autorotation airspeed shall be limited to ___ KIAS at all gross weights.
40
40
120
48
Prohibited Maneuvers
a. Hovering turns greater than ___° per second are prohibited. Intentional maneuvers beyond attitudes of ___° pitch or over ___° roll are prohibited.
b. Simultaneous moving of both ___________________ to _____ or _______ (throttle chop) in flight is prohibited.
c. __________ ground taxi is prohibited.
30
±30
60
ENG POWER CONT levers to IDLE or OFF
Rearward
49
Manual operation of the stabilator in flight is ________ except as required by formal training and maintenance test flight requirements or as alternate stabilator control in case the ________ malfunctions.
prohibited
AUTO mode
50
Prolonged rearward flight and downwind hovering are to be avoided to prevent accumulation of _______________ in the helicopter and ______________ to windows on ______________.
exhaust fumes
heat damage
open cargo doors
51
Maneuvering Limitations.
NOTE Maneuvers entered from a low power setting may result in ______________ of __% NR or greater.
transient droop
5
52
High-Speed Yaw Maneuver Limitations
Above ____ KIAS avoid _____________________ to prevent excess tail rotor system loading.
80
abrupt, full pedal inputs
53
Bank Angle Limitation
Bank angles shall be limited to ____° when a PRI SERVO FAIL caution appears.
30
54
Landing Gear Limitations.
Do not exceed a touchdown sink rate of
Up to 16,825 lb
Level terrain ________
Slopes ________
540 fpm
| 360 fpm
55
Landing Gear Limitations.
Do not exceed a touchdown sink rate of
Above 16,825 lb
Level terrain ________
Slopes ________
300 fpm
| 180 fpm
56
Landing Speed Limitations.
Maximum forward touchdown speed is limited to ____ knots ground speed on level terrain.
60
57
Slope Landing Limitations
___° nose-up, right wheel up or left wheel upslope. The slope limitations shall be further reduced by __° for every __ knots of wind. 6° nose downslope. Landing in downslope conditions with tailwinds greater than ___ knots shall not be conducted. The main gearbox may be operated up to 30 minutes at a time with pressure fluctuations when the helicopter is known to be at a _______________.
15
2
5
15
nose-up attitude (i.e., slope landings or hover with extreme aft CG).
58
Flight in Instrument Meteorological Conditions (IMC).
This helicopter is qualified for operation in IMC.
Flight in Icing Conditions.
NOTE The ice detecting system is calibrated for ____ KIAS. When flying at airspeeds above ____ KIAS, the ice rate meter will indicate higher LWC than the actual conditions.
100
100
59
Flight in Icing Conditions
Helicopters with the following equipment installed, operational, and turned on are permitted to fly into ________ or ________ icing conditions.
(5 things)
trace
light
1. Windshield Anti-ice.
2. Pitot Heat.
3. Engine Anti-ice.
4. Engine Inlet Anti-ice Modulating Valve.
5. Insulated Ambient Air Sensing Tube.
60
For flight into moderate icing conditions, ____________________________________ must be installed, operational, and turned on. Flight into heavy or severe icing is ___________.
all equipment in b. and blade deice
prohibited
61
Backup Hydraulic Pump Hot Weather Limits rotor system __________.
static
62
Backup pump limits
FAT °C (°F) *** OperatingTime (Minutes) *** Cooldown Time (Pump Off) (Minutes)
-54 - 32 (-65 - 90) *** Unlimited *** - -
33 - 38 (91 - 100) ***24 *** 72
39 - 52 (102 - 126) *** 16 *** 48
63
APU Operating Limits
To prevent APU overheating, APU operation at ambient temperatures of ___°C (109°F) and above with engine and rotor operating is limited to ___ minutes. With engine and rotor not operating, the APU may be operated ___________ up to an ambient temperature of ___°C (124°F). If APU OIL HOT caution appears a ___ minute cooling period is required, before checking oil level.
43
30
continuously
51
30
64
Windshield anti-ice check shall not be done when FAT is over ____°C (80°F).
27
65
a. Intentional flight into ________ turbulence is prohibited.
b. Intentional flight into thunderstorms is __________.
c. Intentional flight into turbulence with a ___________ and an inoperative ____________ is prohibited.
severe
prohibited
sling load attached
collective trim
66
Blue Force Tracker Temperature Limits.
CAUTION
Operating the BFT system outside this range may cause failure or erratic operation. Normal operating temperatures range: __________ to ____________.
-15°F (-26°C) to 160°F (71°C)
67
The term LAND AS SOON AS POSSIBLE is defined as _________________________________.
landing at the nearest suitable landing area (e.g., open field) without delay. (The primary consideration is to ensure the survival of occupants.)
68
The term LAND AS SOON AS PRACTICABLE is defined as __________________________________________.
landing at a suitable landing area. (The primary consideration is the urgency of the emergency.)
69
The term AUTOROTATE is defined as _______________________________________________.
adjusting the flight controls as necessary to establish an autorotational descent and landing.
70
The term ESTABLISH SINGLE-ENGINE AIRSPEED is defined as ________________________________________________.
1. ____________________.
2. ____________________.
3. ____________________.
maneuvering the aircraft to an appropriate airspeed that will allow for continued flight under partial power conditions to a suitable recovery area.
Cyclic — Adjust as required.
Collective — Adjust as required to maintain NR within normal operating range.
Establish appropriate airspeed.
71
The term EMER ENG SHUTDOWN is defined as _______________________________.
1. __________________.
2. __________________.
3. __________________.
engine shutdown without delay. Engine shutdown in flight is usually not an immediate-action item unless a fire exists. Before attempting an engine shutdown, identify the affected engine by checking ENG OUT warning lights, NP, NR, Q(torque), P(engine oil pressure), TGT, and NG.
ENG POWER CONT lever(s) — OFF.
ENG FUEL SYS selector(s) — OFF.
FUEL BOOST PUMP switch(es) — OFF.
72
The term LOCKOUT is defined as ___________________________________________.
E.P. _____________________________.
manual control of engine RPM while bypassing DEC/EDECU functions. Bypass of the engine control will be required when NP1 or 2 decreases below normal demand speed due to a malfunction of the DEC/EDECU.
ENG POWER CONT lever — Pull down and advance full forward while maintaining downward pressure, then adjust to set NR as required.
73
The term EMER APU START is defined as ______________________________________.
1. __________________.
2. __________________.
APU start to accomplish an emergency procedure.
FUEL PUMP switch — APU BOOST.
APU CONT switch — ON.
74
Single-Engine Failure
WARNING
Do not respond to ENG OUT warning and audio until checking TGT, NG, and NP1 and NP2.
1. ______________________.
2. _____________________.
If continued flight is not possible:
3. ______________________.
If continued flight is possible:
4. LAND AS SOON AS PRACTICABLE.
ESTABLISH SINGLE-ENGINE AIRSPEED.
External cargo/stores — Jettison (if required).
LAND AS SOON AS POSSIBLE.
75
Dual-Engine Failure
1. ____________________.
Autorotate
76
DEC/EDECU Low Side Failure
1. _____________________.
If partial powered flight cannot be maintained:
2. _____________________. Maintain Q approximately 10% below other engine.
3. LAND AS SOON AS PRACTICABLE.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (low Q/TGT engine) — LOCKOUT.
77
DEC/EDECU High Side Failure
1. _______________________.
2. _______________________. Maintain Q approximately 10% below other engine.
3. LAND AS SOON AS PRACTICABLE.
If the affected engine does not respond to ENG POWER CONT lever movement in the range between FLY and IDLE, the HMU may be malfunctioning internally.
If this occurs:
4. Perform _____________________ (affected engine).
5. Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (high Q/TGT engine) — Retard.
EMER ENG SHUTDOWN
78
Engine Compressor Stall
1. ________________________.
If the condition persists:
2. ________________________. (TGT should decrease).
3. ENG POWER CONT lever (affected engine) — FLY.
If the stall condition recurs:
4. __________________________ (affected engine).
5. Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (affected engine)—Retard
EMER ENG SHUTDOWN
79
ENG 1 OIL BYPASS or ENG 2 OIL BYPASS Caution Appears.
1. ________________________.
2. _________________________ (to reduce pressure).
3. LAND AS SOON AS PRACTICABLE
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (affected engine) — Retard
80
CHIP ENG 1 or CHIP ENG 2, ENG 1 OIL PRESS or ENG 2 OIL PRESS, ENG 1 OIL HOT or ENG 2 OIL HOT Caution Appears.
1. __________________________.
2. __________________________ (to reduce torque).
If oil pressure is below minimum limits or I f oil temperature remains above maximum limits:
3. __________________________ (affected engine).
4. Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (affected engine) — Retard
EMER ENG SHUTDOWN
81
Engine High-Speed Shaft Failure
1. _________________________.
2. _________________________ (affected engine).
Do not attempt to restart.
3. Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
EMER ENG SHUTDOWN
82
Lightning Strike
1. ________________________.
2. ________________________ (as required to control NP and NR).
3. ________________________.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT levers — Adjust
LAND AS SOON AS POSSIBLE.
83
Loss of Tail Rotor Thrust in Cruise Flight.
1. ___________________.
2. ___________________.
AUTOROTATE — Maintain airspeed at or above 80 KIAS.
ENG POWER CONT levers — OFF (during deceleration when intended point of landing is assured).
84
Loss of Tail Rotor Thrust or T/R QUAD FAIL Caution Appears with Loss of Control at Low Airspeed/Hover(Right Rotation).
1. ____________________.
2. ____________________.
Collective — Reduce.
ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).
85
T/R QUAD FAIL Caution Appears in Cruise Flight.
1. __________________.
2. LAND AS SOON AS PRACTICABLE.
Collective — Adjust to determine controllability (Fixed Right or Left).
86
Loss of Control at Low Airspeed/Hover or T/R QUAD FAIL Caution Appears (Left Rotation).
1. _______________________.
2. _______________________.
3. _______________________.
4. _______________________.
ENG POWER CONT lever(s) — Retard to decrease NR below 100% and begin a partial power descent.
Collective — Adjust to preserve NR.
ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).
Collective — Adjust for landing.
87
Pedal Bind/Restriction or Drive With No Ac-companying Caution.
1. ______________________.
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. SAS/BOOST switch — Off.
If normal control forces are not restored:
6. SAS/BOOST switch — ON.
7. Collective — Adjust to determine controllability for landing.
8. LAND AS SOON AS PRACTICABLE.
Apply pedal force to oppose the drive.
88
T/R SERVO 1 FAIL Caution Appears and BACK UP PUMP ON Advisory Does Not Appear or T/R SERVO 2 ON Advisory Does Not Appear.
1. ___________________.
2. BACKUP HYD PUMP switch — ON.
3. LAND AS SOON AS PRACTICABLE.
TAIL SERVO switch — BACKUP.
89
MAIN XMSN PRESS Caution Appears/MAIN XMSN OIL HOT Caution Appears.
1. ______________________.
If time permits:
2. Slow to 80 KIAS.
3. ______________________.
4. GENERATORS NO. 1 and NO. 2 switches — OFF.
LAND AS SOON AS POSSIBLE.
EMER APU START.
90
CHIP L INPUT MDL or CHIP R INPUT MDL Caution Appears.
1. ________________________.
2. ________________________.
3. ________________________.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (affected engine) — IDLE.
LAND AS SOON AS POSSIBLE.
91
CHIP MAIN MDL SUMP, CHIP L ACC MDL or CHIP R ACC MDL, CHIP TAIL XMSN, TAIL XMSN OIL HOT, CHIP INT XMSN or INT XMSN OIL HOT Caution Appears.
_________________________.
LAND AS SOON AS POSSIBLE.
92
Main Transmission Failure
1. ________________________.
2. ________________________.
Collective — Adjust only enough to begin a descent with power remaining applied to the main transmission throughout the descent and landing.
LAND AS SOON AS POSSIBLE.
93
Engine Fire in Flight
1. _______________________.
2. _______________________.
3. _______________________.
4. _______________________.
5. _______________________.
6. _______________________.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (affected engine) — OFF.
ENG EMER OFF handle — Pull.
FIRE EXTGH switch — MAIN/RESERVE as required.
FUEL BOOST PUMP switch (affected engine) — OFF (as applicable).
LAND AS SOON AS POSSIBLE.
94
Engine/Fuselage Fire on Ground
1. _____________________.
2. _____________________.
3. _____________________.
4. _____________________.
ENG POWER CONT levers — OFF.
ENG EMER OFF handle(s) — Pull if applicable.
FIRE EXTGH switch — MAIN/RESERVE as required.
Rotor brake — As required.
95
APU Compartment Fire
1. _____________________.
2. _____________________.
APU fire T-handle — Pull.
FIRE EXTGH switch — MAIN/RESERVE as required.
96
Electrical Fire in Flight
1. _______________________.
2. _______________________.
BATT and GENERATORS switches — OFF.
LAND AS SOON AS POSSIBLE.
97
FUEL 1 BYPASS and FUEL 2 BYPASS Cautions Appear
________________________.
LAND AS SOON AS POSSIBLE.
98
FUEL 1 PRESS LOW or FUEL 2 PRESS LOW Caution Appears
If the caution appears and the situation is critical:
1. ______________________.
2. ______________________.
3. ______________________.
4. ______________________.
ENG FUEL SYS selector on affected engine — XFD.
FUEL BOOST PUMP switch on side being used — ON.
LAND AS SOON AS POSSIBLE.
EMER ENG SHUTDOWN after landing.
99
FUEL 1 PRESS LOW and FUEL 2 PRESS LOW Cautions Appear.
1. ______________________.
2. ______________________.
LAND AS SOON AS POSSIBLE.
EMER ENG SHUTDOWN after landing.
100
GEN 1 FAIL and GEN 2 FAIL (NO. 1 & NO. 2 CONV and AC REF BUS DEGRAD) Cautions Appear
1. Airspeed — Adjust (80 KIAS or less).
2. GENERATORS NO. 1 and NO. 2 switches — RESET; then ON.
If electrical power is not restored:
3. GENERATORS NO. 1 and NO. 2 switches — OFF.
4. MCUs and ECS — OFF prior to EMER APU START.
5. _____________________.
6. LAND AS SOON AS PRACTICABLE.
7. If APU GEN ON advisory extinguishes, ensure MCUs and ECS — OFF prior to resetting the APU generator.
EMER APU START.
101
HYD PUMP 1 FAIL and HYD PUMP 2 FAIL Cautions Appear
_________________________. Restrict control movement to moderate rates.
LAND AS SOON AS POSSIBLE.
102
HYD PUMP 1 FAIL or HYD PUMP 2 FAIL Caution Appears and BACK UP PUMP ON Advisory Does Not Appear.
1. ______________ to a comfortable airspeed.
2. ________________________.
If BACK UP PUMP ON advisory appears:
3. Refer to HYD PUMP 1 FAIL or HYD PUMP 2 FAIL caution appears emergency procedure.
If BACK UP PUMP ON advisory still does not appear:
4. ________________________.
5. ________________________.
Airspeed — Adjust
BACKUP HYD PUMP switch — ON.
FPS and SAS/BOOST switches — Press off( switch lights off, for HYD PUMP 2 FAIL caution).
LAND AS SOON AS POSSIBLE.
103
PRI SERVO 1 FAIL or PRI SERVO 2 FAIL Caution Appears
1. _____________________.
2. _____________________.
3. _____________________.
SERVO OFF switch — Check centered.
If the caution appears with the SERVO OFF switch centered, move the SERVO OFF switch to turn off the malfunctioning servo.
LAND AS SOON AS POSSIBLE.
104
RSVR 1 LOW and HYD PUMP 1 Cautions Appear With BACK UP PUMP ON Advisory Appearing
1. LAND AS SOON AS PRACTICABLE.
If the BACK UP RSVR LOW caution also appears:
2. ___________________.
3. ___________________.
SERVO OFF switch — 1ST STG.
LAND AS SOON AS POSSIBLE.
105
RSVR 2 LOW and HYD PUMP 2 FAIL Cautions Appear With BACK UP PUMP ON Advisory Appearing
1. AUTO FLIGHT CONTROL panel CPTR 1 and/or CPTR 2 switches (if illuminated) — Press to reset FCC.
2. LAND AS SOON AS PRACTICABLE.
If BACK UP RSVR LOW caution also appears:
3. _____________________.
4. _____________________.
SERVO OFF switch — 2ND STG.
LAND AS SOON AS POSSIBLE.
106
Collective Boost Servo Hardover/Power Pis-ton Failure
1. ____________________.
2. FPS switch — Off.
3. LAND AS SOON AS PRACTICABLE.
SAS/BOOST switch — Off.
107
BOOST SERVO OFF Caution Appears
1. _____________________.
2. FPS switch — Off.
3. LAND AS SOON AS PRACTICABLE.
SAS/BOOST switch — Off.
108
Emergency Landing In Wooded Areas — Power Off
1. ______________. Decelerate helicopter to stop all forward speed at treetop level.
2. ______________ to maximum before main rotor contacts tree branches.
AUTOROTATE.
Collective adjust
109
Ditching — Power Off
1. _________________.
2. Cockpit doors jettison and cabin doors open prior to entering water.
3. Apply full collective to decay rotor rpm as helicopter settles.
4. Position cyclic in direction of roll.
5. Exit when main rotor has stopped.
AUTOROTATE.
110
Flight Control/Main-Rotor System Malfunctions
If the main rotor system malfunctions:
1. _____________________.
2. _____________________.
3. _____________________.
LAND AS SOON AS POSSIBLE.
EMER ENG(S) SHUTDOWN after landing.
Rotor brake — As required.
111
ROTOR BRAKE ON Advisory Appears in Flight
May indicate rotor brake pressure is applied to the rotor brake.
1. Rotor brake handle — Check in detent and gage pressure at zero.
2. Check for secondary indications of brake pad dragging (smoke, smell, noise, etc.).
If secondary indications present:
3. __________________________.
If no secondary indications present:
4. LAND AS SOON AS PRACTICABLE.
LAND AS SOON AS POSSIBLE.
112
Stabilator Malfunction — Auto Mode Failure
If an AUTO mode failure occurs:
1. _____________________ to arrest or prevent nose down pitch rate.
2. _____________________.
If automatic control is not regained:
3. Manually slew stabilator — Adjust to 0° for flight above 40 KIAS or full down when airspeed is below 40 KIAS. The preferred method of manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
4. LAND AS SOON AS PRACTICABLE.
If manual control is not possible, the airspeed limit indication will show the adjusted airspeed limit with a red arc.
5. Airspeed indicator — Check and fly at or below red arc shown on the indicator.
6. LAND AS SOON AS PRACTICABLE.
Cyclic mounted stabilator slew-up switch — Adjust as required
AUTO CONTROL RESET switch — Press ON once after establishing a comfortable airspeed.
113
Uncommanded Nose Down/Up Pitch Attitude Change
If an uncommanded nose down pitch attitude occurs:
1. _______________________.
2. _______________________.
3. _______________________ to arrest nose down pitch rate.
4. MAN SLEW switch — Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.
5. LAND AS SOON AS PRACTICABLE.
Cyclic — Adjust as required.
Collective — Maintain or increase.
Cyclic mounted stabilator slew-up switch — Adjust as required
114
Uncommanded Nose Down/Up Pitch Attitude Change
If an uncommanded nose up pitch attitude occurs:
1. _______________________.
2. _______________________.
3. MAN SLEW switch — Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.
4. LAND AS SOON AS PRACTICABLE.
Cyclic — Adjust as required.
Collective — Reduce as required.
115
STAB UNLOCKED Caution Appears
In flight — _______________________.
LAND AS SOON AS POSSIBLE.
116
Integrated Avionics System Malfunctions
The following component failures will result in — ________________________.
1. Loss of two data concentrator units.
2. Loss of four MFDs.
LAND AS SOON AS POSSIBLE.
117
Dual EGI Failure
1. _____________________.
2. EGI switches — OFF, then ON. If successful, an EGI in-flight alignment will automatically be done.
3. LAND AS SOON AS PRACTICABLE.
Transition to ESIS display.
118
FLT DIR FAIL, FD COUPLE FAIL Cautions Appear
1. _______________________.
2. FAILURE RESET CPTR 1 and/or CPTR 2 — Press to clear flight director cautions.
3. Check AFCS and FCC status page. Clear BITE codes if necessary.
4. Reengage affected mode when able.
5. Fly affected axis manually if not restored.
Check FD/DCP to verify which flight director modes are functioning.
