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5's Flashcards

(75 cards)

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1
Q

What is the minimum crew required to fly this helicopter

A

Two Pilots and a Flight Engineer

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2
Q

ENGINE OIL PRESSURE
The displays appear in green when the pressure is _ to _ psi, change to yellow if the pressure is greater than _ psi, and change to red when the pressure is less than _ psi or greater than _ psi.

A

The displays appear in green when the pressure is 5 to 90 psi, change to yellow if the pressure is greater than 90 psi, and change to red when the pressure is less than 5 psi or greater than 110 psi.

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3
Q

Engine Oil Pressure Limits

A

5 psi - NG at Ground Idle
32 psi - Minimum Pressure for NG 80-95%
50 psi - Minimum Pressure for NG Equal to or greater than 95%
35-90 psi - Normal Operation
110 psi - Maximum for Contingency Power
150 psi - Maximum for Cold Weather Starts

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4
Q

ENGINE OIL TEMPERATURE
The displays appear in green when the temperature is equal to or less than _°C and change to red, with the respective ENG1 (2) OIL HOT caution displayed, when the temperature is greater than _° C.

A

The displays appear in green when the temperature is equal to or less than 149°C and change to red, with the respective ENG1 (2) OIL HOT caution displayed, when the temperature is greater than 149°C.

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5
Q

Engine Oil Temperature Limit

A

149° C

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6
Q

ENGINE TRANSMISSION OIL TEMPERATURE LIMITS
The displays appear in green when the temperature is equal to or less than _° C and change to red, with an ENG1 (2) XMSN OIL HOT caution displayed when the temperature is greater than _° C. An ENG 1 (2) XMSN warning will be displayed when the temperature is greater than _° C.

A

The displays appear in green when the temperature is equal to or less than 140° C and change to red, with an ENG1 (2) XMSN OIL HOT caution displayed when the temperature is greater than 140° C. An ENG 1 (2) XMSN warning will be displayed when the temperature is greater than 190° C.

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7
Q

TRANSMISSION OIL TEMPERATURE LIMITS
The displays appear in green when the temperature is less than or equal to _° C and change to red when the temperature is greater than _° C with the respective COMB, AFT, or FWD XMSN OIL HOT caution displayed.

A

The displays appear in green when the temperature is less than or equal to 140° C and change to red when the temperature is greater than 140° C with the respective COMB, AFT, or FWD XMSN OIL HOT caution displayed.

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8
Q

Transmission Oil Temperature Limit

A

140° C

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9
Q

TRANSMISSION OIL PRESSURE LIMITS
The displays appear in green when the pressure is equal to or grater than _ psi and change to red when the pressure is less than _ and NR is equal to or greater than _%.

A

The displays appear in green when the pressure is equal to or grater than 20 psi and change to red when the pressure is less than 20 psi and NR is equal to or greater than 25%.

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10
Q

TRANSMISSION OIL PRESSURE LIMITS
An ENG1, ENG2, COMB, AFT, or FWD XMSN PRESS HI advisory is displayed when the pressure in any transmission is greater than _ psi.

A

An ENG1, ENG2, COMB, AFT, or FWD XMSN PRESS HI advisory is displayed when the pressure in any transmission is greater than 90 psi.

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11
Q

TRANSMISSION OIL PRESSURE LIMITS
An XMSN AUX PRESS LO caution will be displayed when there is les than _ psi auxiliary oil pressure in the forward or aft transmission, or less than _ psi in the combining transmission.

A

An XMSN AUX PRESS LO caution will be displayed when there is les than 20 psi auxiliary oil pressure in the forward or aft transmission, or less than 10 psi in the combining transmission.

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12
Q

Transmission Oil Pressure Limits

A

7 psi - Minimum at ground idle
20 psi - Minimum at 100% NR
20 to 90 psi - Normal Operation

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13
Q

HYDRAULIC SYSTEM LIMITATIONS
The respective No. 1 (No. 2) HYD FLT CONTR caution will be displayed when hydraulic pressure is less than approximately _ psi.

A

The respective No. 1 (No. 2) HYD FLT CONTR caution will be displayed when hydraulic pressure is less than approximately 1,800 psi.

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14
Q

ROTOR LIMITATIONS
Should _ NR power-off be inadvertently exceeded, no entry need be made on _ unless the rotor system accelerates and exceeds _ NR. Even though no action is required when NR exceeds _ NR power-off, but remains at or below _, willful operation shall not be conducted in this range.

A

Should 108% NR power-off be inadvertently exceeded, no entry need be made on DA FORM 2408-13-1 unless the rotor system accelerates and exceeds 111.5% NR. Even though no action is required when NR exceeds 108% NR power-off, but remains at or below 111.5%, willful operation shall not be conducted in this range.

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15
Q

NR Limits

A

Minimum Transient Power on - 91%
Transient - 91-97%
Normal - 97-101%
Transient - 101-106%
Maximum Transient Power-on - 106%
Maximum during Autorotation - 108%
Maximum Transient - 111%

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16
Q

Flight equal to or less than _ NR with an inoperative CGI is prohibited.

A

Flight equal to or less than 98% NR with an inoperative CGI is prohibited.

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17
Q

STARTING AND SHUTDOWN LIMITS
The APU shall not be started with a tailwind in excess of _ knots. Main engines shall not be started with a tailwind in excess of _ knots.

A

The APU shall not be started with a tailwind in excess of 25 knots. Main engines shall not be started with a tailwind in excess of 10 knots.

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18
Q

STARTING AND SHUTDOWN LIMITS
If it becomes necessary to shutdown in conditions outside the limits shown in Figure 5-6/5-7 (Wind Chart A/B), the following precautions are recommended:

A
  1. Aircraft should land in an area which is clear, as level as possible, and at least 300 ft away from any vertical obstruction or abrupt changes in ground terrain
  2. Aircraft should be oriented such that the wind would be coming in at the left side.
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19
Q

Flight Control Hydraulic Pressure Limits

A

Low: 2,500 psi
Normal: 2,500 to 3,200 psi
High: 3,200 psi

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20
Q

Utility System Hydraulic Pressure Limits

A

Low: 2,500 psi
Normal: 2,500 to 3,500 psi
High: 3,500 psi

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21
Q

Hydraulic System Temperature Limitsq

A

Yellow/White (Caution Range) - 95 to 120° C
Red/White (Maximum) - 120° C

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22
Q

CGI Color Ranges

A

Green: Normal Operation
Yellow: Transient
Red: Avoid
White: Test

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23
Q

ENGINE TEMPERATURE LIMITS
The digital display and tapes on the scale appear in green for temperatures equal to or less than _° C, change to yellow when greater than _° C to _° C, and change to red when equal to or greater than _° C.

A

The digital display and tapes on the scale appear in green for temperatures equal to or less than 816° C, change to yellow when greater than 816° C to 932° C, and change to red when equal to or greater than 932° C.

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24
Q

ENGINE TEMPERATURE LIMITS
If the PTIT in either engine is equal to or greater than _° C, the ENG1 (2) _ advisory will be displayed. If the PTIT in either engine is equal to or greater than _° C, the ENG1 (2) _ advisory will be displayed. Should the temperature reach _° C for _ or longer, the ENG1 (2) _ advisory will be displayed. The ENG1 (2) advisory will be displayed before actually reaching contingency power, providing a _° buffer to advise the pilot he is about to enter this range.

A

If the PTIT in either engine is equal to or greater than 816° C, the ENG1 (2) 30M TMP advisory will be displayed. If the PTIT in either engine is equal to or greater than 854° C, the ENG1 (2) 10M TMP advisory will be displayed. Should the temperature reach 899° C for 2 seconds or longer, the ENG1 (2) 2.5M TMP advisory will be displayed. The ENG1 (2) advisory will be displayed before actually reaching contingency power, providing a 5° buffer to advise the pilot he is about to enter this range.

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25
PTIT Limits
816° C - Maximum Continous 854° C - 30 minute limit 899° C - 10 minute limit 932° C - 2.5 minute limit (Contingency Power) 943° C - 12 seconds maximum transient >943° C - Maximum transient for not more than 4 seconds
26
CONTINGENCY POWER Contingency Power is only to be used during actual emergency conditions. Usage of contingency power up to _° C is permissible for an unlimited number of occurrences, as long as each occurrence is _ or less. Transient power _° C to _° C PTIT is not to be greater than _. If PTIT in either engine is equal to or greater than _° C ENG1 (2) _ advisory will be displayed, also a ENG1 (2) TEMP HI caution will be displayed.
Contingency Power is only to be used during actual emergency conditions. Usage of contingency power up to **932° C** is permissible for an unlimited number of occurrences, as long as each occurrence is **2 minutes 30 seconds** or less. Transient power **932° C to 943° C** PTIT is not to be greater than **12 seconds**. If PTIT in either engine is equal to or greater than **932° C** ENG1 (2) **12S TMP** advisory will be displayed, also a ENG1 (2) TEMP HI caution will be displayed.
27
GAS GENERATOR LIMITS Engine Gas Generator speed is digitally shown in green when NG is between _%, changes to yellow when less than _%, and changes to red when greater than _%.
Engine Gas Generator speed is digitally shown in green when NG is between **50% to 111%**, changes to yellow when less than **50%**, and changes to red when greater than **111%**.
28
NG Limits
50% - Ground Idle Minimum 111% - Maximum
29
ENGINE OVERSPEED An NG overspeed exists when a speed of _ NG is exceeded. An NG overspeed can cause over-temperature and/or over-torque.
An NG overspeed exists when a speed of **111%** NG is exceeded. An NG overspeed can cause over-temperature and/or over-torque.
30
POWER TURBINE (NP) LIMITS A power turbine (NP) overspeed may exist, depending on power being used when _% NP is exceeded. The maximum limit for power turbine is _%.
A power turbine (NP) overspeed may exist, depending on power being used when **106% NP** is exceeded. The maximum limit for power turbine is **111.5%**.
31
NP Limits
111.5% - Maximum
32
ENGINE TORQUE (TQ) LIMITS The display appears in green if TQ is equal to or less than _%, changes to red when greater than _%, dual operations, or red at _% single engine operation. A voice alert "TORQUE" will be triggered when torque is greater than _% dual or single engine.
The display appears in green if TQ is equal to or less than 100%, changes to red when greater than **100%**, dual operations, or red at **123%** single engine operation. A voice alert "TORQUE" will be triggered when torque is greater than **95%** dual or single engine.
33
Torque Limits
100% - Maximum Dual Engine 123% - Maximum Single Engine
34
FUEL LIMITATIONS _ is not considered "Emergency Fuel". A DA Form 2408-13-1 entry will be made as described in Appendix C. Only those fuels listed in _ shall be used. Emergency fuel shall not be used for more than _ cumulative time.
**JP8 + 100** is not considered "Emergency Fuel". A DA Form 2408-13-1 entry will be made as described in Appendix C. Only those fuels listed in **Chapter 2** shall be used. Emergency fuel shall not be used for more than **6 Hours** cumulative time.
35
Maximum Gross Weight
50,000 lbs
36
Cargo Hook Limitations
26,000 lbs - Center Hook Max 25,000 lbs - FWD and AFT Dual Point/Tandem 17,000 lbs - FWD and AFT individual
37
When a combination of internal and external loads are carried during the same flight and the external load exceeds _, position the internal load _. This procedure should preclude encountering _.
When a combination of internal and external loads are carried during the same flight and the external load exceeds **12,000 lbs**, position the internal load **forward of the utility hatch**. This procedure should preclude encountering **an excessively aft CG**.
38
Winch/Hoist Limitations
Rescue Hoist - 600 lbs Maximum Winch: 3,000 lbs Straight Line Pull 6,000 lbs One Pulley 9,000 lbs Two Pulleys 12,000 lbs Three Pulleys
39
CRUISE GUIDE INDICATOR LIMITS Any excursion into the red or yellow band for more than _ requires an entry on the _. Provide the following information: (6 Items)
Any excursion into the red or yellow band for more than 45 seconds requires an entry on the DA Form 2408-13-1. Provide the following information: 1: Free Air Temperature 2: Pressure Altitude 3: Gross Weight 4: Knots Calibrated Airspeed 5: Total time in red or yellow band 6: Needle position within red or yellow band (i.e., upper or lower half)
40
Reduction in aerodynamic loading includes one or more of the following:
1: Lowering the Thrust 2: Reducing the severity of the maneuver 3: Reducing Airspeed
41
Maximum crosswind or sideward flight
45 KCAS
42
Maximum airspeed for rearward flight
40 KCAS
43
Maximum Tailwind for Hover
40 KCAS
44
Maximum airspeed with the lower section of the cabin entrance door open and locked
60 KCAS
45
The rescue hatch door shall not be opened or closed above
90 KCAS
46
Windshield wipers shall be off at airspeeds above
130 KCAS
47
Upper section of the cabin entrance: Ensure that airspeed is less than _ before closing door in flight.
100 KCAS
48
Left side Escape Hatch: Do not _ or _ in forward flight.
**Install or Remove**
49
EXTERNAL CARGO AIRSPEED LIMIT If a sling or hook should fail while carrying a tandem load, limit airspeed to a maximum of _.
If a sling or hook should fail while carrying a tandem load, limit airspeed to a maximum of **60 KCAS**.
50
CAUTION A Dual FADEC primary channel failure may occur when rearward flight or a tailwind exceeds _. NOTE Aircrew should be alert to the potential for large _ during rearward flight operations.
CAUTION A Dual FADEC primary channel failure may occur when rearward flight or a tailwind exceeds **40 KCAS**. NOTE Aircrew should be alert to the potential for large **engine torque oscillations** during rearward flight operations.
51
At negative density altitudes, the helicopter design VNE is equivalent to _. At positive density altitudes, the helicopter design VNE is equivalent to _.
At negative density altitudes, the helicopter design VNE is equivalent to **170 KCAS**. At positive density altitudes, the helicopter design VNE is equivalent to **170 KTAS**.
52
Do not manually extend the LCT beyond the GND position on the cyclic trim indicators at calibrated airspeeds below _. Use of extended cyclic trim at low airspeeds will result in _.
Do not manually extend the LCT beyond the GND position on the cyclic trim indicators at calibrated airspeeds below **60 KCAS**. Use of extended cyclic trim at low airspeeds will result in **high aft rotor blade stresses**.
53
DAFCS LIMITATIONS The airspeed limit when operation of a single DAFCS is _ or VNE, whichever is slower. The helicopter may be operated with both DAFCS off up to _ or VNE, whichever is slower, provided _.
The airspeed limit when operation of a single DAFCS is **100 KCAS** or VNE, whichever is slower. The helicopter may be operated with both DAFCS off up to **160 KCAS** or VNE, whichever is slower, provided **both DAFCS are disabled below 100 KCAS**.
54
AEROBATICS PROHIBITION Aerobatics are prohibited with this helicopter. Aerobatics are defined as intentional maneuvers beyond _ and/or _.
Aerobatics are prohibited with this helicopter. Aerobatics are defined as intentional maneuvers beyond **+/- 30° pitch** and/or **60° roll**.
55
With an operative CGI, bank angles are limited by CGI, but no greater than _. When operating with BALT/RALT engaged, limit bank angles to _ maximum.
With an operative CGI, bank angles are limited by CGI, but no greater than **60°**. When operating with BALT/RALT engaged, limit bank angles to **45°** maximum.
56
Maximum groundspped and nose-up attitude for Roll-On landings
60 KGS 20°
57
Maximum Rates of Descent at Touchdown
492 ft/min - <33,000 lbs 450 ft/min - 33,000 to 40,000 lbs 360 ft/min - >40,000 lbs
58
Ground Operation Limits
2 in. Aft Cyclic 1 in. Lateral Cyclic 3/4 in. Right/Left Pedal Thrust Control Lever no lower than ground detent
59
When will a blade watcher and taxi director be positioned?
When ground taxiing less than 75 feet from an obstruction on an unimproved/unfamiliar airfield not designated for CH-47F helicopters.
60
When will engine bypass panels be removed?
Temperatures below 4° C
61
This helicopter is qualified for IMC Flight provided the following conditions exist:
1: Both DAFCS are operational 2: Both SFDs are operating. 3: Three MFDs (1, 4, and either 2 or 3), two ADCs, two CDUs, two DCUs, two EGIs, and two GPPUs are operational.
62
Should _ during IMC flight, the flight may be continued to destination. Should _ during IMC flight, _.
Should **one DAFCS fail** during IMC flight, the flight may be continued to destination. Should **both DAFCS fail** during IMC flight, **exit IMC as soon as practical**.
63
Coupled ILS Approaches at localizer intercept angles of greater than _ are prohibited.
Coupled ILS Approaches at localizer intercept angles of greater than **60°** are prohibited.
64
The shock absorber vent valve must be open for operation _° C. The valve must be closed for operation _° C. At _ to _° C, the valve may be opened or closed.
The shock absorber vent valve must be open for operation **below -18° C**. The valve must be closed for operation **above -1° C**. At **-18 to -1° C**, the valve may be opened or closed.
65
Continuous flight in light icing conditions below _° C is not recommended since blade damage can occur from asymmetric ice shedding.
Continuous flight in light icing conditions below **-5° C** is not recommended since blade damage can occur from asymmetric ice shedding.
66
If any _ or _ are missing or broken, _ flight in or near thunderstorms, especially in areas of observed or anticipated lightning discharges.
If any **lightning cables** or **straps** are missing or broken, **avoid** flight in or near thunderstorms, especially in areas of observed or anticipated lightning discharges.
67
Day/Night/NVG operations over water is permissible provided:
1: Both DAFCS are operational 2: Pilot and Co-Pilot Radar Altimeter is operational 3: A visible horizon is present at the operation site 4: Helicopter drain plugs are installed
68
Air to Ground towing operations
PROHIBITED
69
APU operation in flight is prohibited except _.
APU operation in flight is prohibited except **during emergencies**.
70
The PITOT HEAT switch shall not be on for more than _ on the ground.
The PITOT HEAT switch shall not be on for more than **5 MINUTES** on the ground.
71
Windshield head shall not be used above _° C.
Windshield head shall not be used above **24° C**.
72
The maximum rate for pressure refueling is _ at _.
The maximum rate for pressure refueling is **300 gal.min** at **55 psi**.
73
The maximum capacity of one ERFS II tank assembly is _ when gravity refueled. The usable fuel in one ERFS II tank assembly is _ when single point pressure refueled.
The maximum capacity of one ERFS II tank assembly is **825.5 US Gallons** when gravity refueled. The usable fuel in one ERFS II tank assembly is **800 US Gallons** when single point pressure refueled.
74
The maximum internal pressure of the ERFS II tank should not exceed _.
The maximum internal pressure of the ERFS II tank should not exceed **5 psi**.
75
The maximum allowable suction defueling pressure is _.
The maximum allowable suction defueling pressure is **-11 psi**.

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