1
Q
What should be done after doing salt water operations
A
A record entry should be made so that appropriate maintenance action can be taken
2
Q
When should you start the anti-icing systems before entering suspect or forecasted icing areas
A
5 min
3
Q
Caution associated in flight during ice
A
Continuous flight in light icing conditions below -5°C is not recommended since blade damage can occur from ice shedding
4
Q
How much will airspeed vary in turbulent air
A
40 KCAS
5
Q
Prior to entering moderate or stronger turbulent air, the following should be accomplished
A
- FLT DIR altitude modes - Deselect
- Crew - Alert
- Airspeed - Adjust as follows:
- Severe turbulence, decrease airspeed to Vne - 15 KCAS or to max range, whichever is slower
- Moderate turbulence, decrease airspeed to Vne - 10 KCAS or to max range, whichever is slower
- LCTS - Select MAN, then adjust both actuators for airspeed to be flown
- Loose equipment - Secure
- Safety belts and shoulder harnesses - Tighten
6
Q
Caution associated with entering turbulent air
A
To prevent engine over torque, do not enter forecast moderate or stronger turbulence with an inop Cockpit Control Drive Actuator (CCDA) coupled to a vertical axis of the FD
7
Q
Flight during cold conditions
A
Initial hovering with cold hydraulic fluid may produce insensitive control inputs. Hovering above 10ft is recommended under these conditions until operation is normal. With AFCS on, light pitch and roll oscillations can be expected during the first 10 - 20 min of flight.
8
Q
Embedded Digital Map operation in cold conditions
A
Cold soaked disk drives (< 0°C) may take up to 12 min before being accessible
9
Q
NOTE associated with heater function switch - OFF
A
After the heating and ventilating system has been stopped with the APU generator on, the blower will continue to operate until the temp within the heater combustion chamber is <49°C
10
Q
Caution associated with air control knob
A
Pull out the cockpit air knobs slowly to preclude dirt and debris from being blasted into the air and crew’s eyes
11
Q
NOTE associated with fuel pump switches - ON during heating and vent system normal operation
A
If the left side of the helicopter is exposed to the sun, the cabin thermostat may be heated to 34°C, which is sufficient to prevent starting the heater
12
Q
Caution associated with heating and vent system
A
Cycling the heater blower may disable the power steering control
13
Q
NOTE associated with preparation for flight during cold operations
A
Light frost when operating in temps above freezing is not cause for concern
14
Q
Cautions associated with preparation for flight during cold operations
A
- Ice removal should never be accomplished by chipping or scraping; de-icing fluid should be used.
- Operating with ice, snow, and frost on the rotor blades in freezing conditions with moisture present, will result in a more rapid accumulation of ice and degrade aircraft performance.
15
Q
At temps below ______, preheating the aircraft is recommended for a minimum of ______. Emphasis should be placed on engine fuel control units
A
- -18°C
- 90 min
16
Q
When cruising at cold temps (below _____) increased vibration levels may be encountered which can be alleviated by operating at _____ NR
A
- -10°C
- 98%
17
Q
Warning associated with multi-hook loads
A
After releasing cargo on the ground, verify that the forward and aft cargo hooks have released before accelerating the helicopter. Dragging the load may cause the helicopter to rotate into the terrain.
18
Q
Aerodynamic loads
A
- Aerodynamic loads, such as tow targets, drones, light aircraft, aircraft parts (wings and tail sections) have certain inherent dangers because of their aerodynamic lift capabilities.
- Therefore, the lift capabilities of external loads must be eliminated before they are lifted.
- Airspeed and bank angles will be governed by the reaction of the load to the airspeed.
- Drogue chutes shall also be used to streamline the load. However, the chute must be attached to the load with a swivel fitting.
19
Q
High density loads
A
Can usually be flown at cruise airspeed and in some cases up to Vne, depending on the configuration of the load, air turbulence, or accompanying vibration.
20
Q
Low density loads
A
Airspeed is limited by the amount of clearance which can be maintained between the load and the underside of the helicopter, since the load will tend to trail aft as speed is increased
21
Q
Cautions associated with cargo hook loads
A
- Do not lift or rotate the center cargo hook into the cabin area or allow the mid hook to lay on the cargo floor or access door panel during inspection or use. The excessive tension placed on the triple emergency release cable housing assembly may pertially dislodge the housing and engage or activate the forward and aft hook emergency release mechanism. This may cause inadvertent release of loaded forward and aft hook assembly in flight.
- External loads must not be rigged entirely with steel cable (wire rope) slings. To dampen vibration tendencies, a nylon vertical riser at least 6ft long must be placed between the steel cable sling and the nylon loop or metal shackle which attaches to the cargo hook. Nylon and chain leg slings and pure nylon slings must have at least 6ft of nylon in each leg.
- When a combination of internal and external loads are carried during the same flight and the external load exceeds 12,000lbs. Position the internal load forward of the utility hatch. This procedure will preclude encountering an excessively aft CG
22
Q
Types of loads carried
A
- Low density
- High density
- Aerodynamic
23
Q
DAFCS off flight will not be difficult when the following techniques are used
A
- Maintain airspeed below established limits
- Enter all maneuvers smoothly, keep control movements coordinated and avoid over control
- Constantly scan the inclinometer to maintain trimmed flight
- React positively, but smoothly to divergent movements
24
Q
What enhances DAFCS off flight characteristics
A
- Spoilers on forward pylon
- Strakes on the fuel pods and ramp
- Blunted aft pylon
25
Where can you find the instrument flight procedures for this aircraft
* -10
* TC 3-04.5
* FLIP
* AR 95-1
* FAR Part 91
26
NOTE associated with APU GEN switch - OFF during engine shutdown
The EGI must be powered off before shutdown of the electrical power. Allow 15 seconds after the EGI is turned off before removing electrical power.
27
NOTE associated with FADEC B/U PWR switch during engine shutdown
Before removing electrical power or turning off FADEC B/U PWR ensure CPHE data transfer is complete. The 3 min from the time rotor RPM reaches 10% or below allows the CPHE system to collect engine ECU data and generate a PSA file that will be stored on the MMS II CPHE SSD for download. Failure to wait 3 min will cause all the CPHE data collected during that operation to be lost.
28
NOTE associated with Power Page during engine shutdown
If logged into DAMA, log out as required in order to prevent lockup of the ARC231
29
NOTE associated with ENG COND levers - STOP during engine shutdown
It may be necessary to motor the engines if the temp does not decrease below 350°C. It may not be possible to lower the temp to 260°C. If the temp will not decrease below 260°C, terminate motoring when the temp indication stabilizes.
30
NOTE associated with the ECU display during engine shutdown
If the ECU display is other than 88, refer to the ECU BIT Fault code list/matrix for evaluation
31
Caution associated with ECU shutdown during engine shutdown
To avoid an engine over-temp during shutdown, check ECU display for the following codes: B6, BC, DB, DE, and FB. If any of the 5 codes are displayed, shutdown the respective engine using the alternate shutdown procedure
32
Caution associated with ECLs - GND during engine shutdown
If ENG COND levers are retracted past GND, do not attempt to bring ENG COND lever back to the ground position. Place ENG COND lever to STOP
33
NOTE associated with flight controls during engine shutdown
After the thrust control lever is at the ground detent position, the 2 min cool-down for engine shutdown can start. If the thrust control lever is moved up from ground detent position the 2 min cool-down is negated and can be restarted once the thrust control lever is in the ground detent position
34
Caution associated with flight controls during engine shutdown
Critical flight control components can be damaged if the thrust control lever is not in ground detent
35
NOTE associated with ERFS refueling
While helicopter sits static, failure to close the unisex valve leading out of all of the ERFS II/RSERFS tanks could result in being gravity fed into main tanks resulting in fuel venting overboard.
36
Caution associated with ERFS refueling
Failure to close the tank-to-aircraft unisex valve during pressure refueling of the ERFS II/RSERFS tanks could result in over pressurization of the helicopter main tanks
37
NOTE associated with after landing (abbreviated)
After landing and while conducting subsequent multiple takeoffs and landings, the abbreviated after landing check may be used
38
After landing (Steps)
- FLT DIR CPLR switch - Uncoupled
- Flight controls - Neutralize
- LCTs - Check GND
- Ground contact lights - Check both on
- AFCS SYSTEM SEL switch - As required
- Swivel switch - As required
- Searchlights - As required
- ANTI-ICE - OFF, as required
39
Cautions associated with landing
- Landings should be made with the ramp in the full-up position. When the situation requires a landing with the ramp in other than full-up position, avoid nose high attitudes.
- The flare or chaff dispenser may obstruct crew members view of the Aft rotor system through bubble windows installed at STA 331.0, reducing the ability to clear the aircraft during close proximity to obstacles during landing.
40
Before landing
- MFDs - Set as required
- Performance considerations - As required
- DAFCS modes - As required
- Searchlight - As required
- Parking brake - As required
- DAFCS control panel - Check and set, as required
- Swivel switch - Lock
- Crew, passengers, and mission equipment - Check
41
Cruise Check
- Ramp and cabin area - Check every 30 min
- Mission equipment - As required
- Mission management - Perform
42
Before Takeoff
- Systems - Check
- MFDs - Set as required
- Flight Director - As required
- Parking Brake - As required
- DAFCS control panel - Check and set as required
- Swivel switch - Lock
- Crew, passengers, and mission equipment - Check
43
Caution associated with cruise check
Large pitch inputs will result in rapid gain or loss if altitude hold is on, an over-torque condition can occur during large pitch-down inputs. Monitor thrust control lever movement and torquemeter during airspeed changes. Also, when operating with altitude hold, limit bank angles to 45° max. An excessive bank angle may result in an altitude loss, and if operating at high GW, an over-torque condition.
44
Warning associated with cruise check
Radar altitude hold is not a terrain following feature and may not provide adequate terrain clearance in rapidly changing terrain. Use radar altitude hold to maintain a constant absolute altitude during hover and forward flight over known water or flat terrain. It can be used up to a max of 8,000ft absolute altitude.
45
NOTE associated with inflight PAT check
If the engine torque is between 60 to 70% when the aircraft is established in flight, adjustment of the engine condition levers are not required.
46
Caution associated with in-flight PAT check
Do not rapidly move the ECLs during the in-flight PAT. If aircraft begins a descent, abort the procedure by returning the non-PAT engine condition lever to FLT and adjusting the thrust control lever
47
Caution associated with IRSS during Before Hover
With the IR Suppression System (IRSS) installed, forward pylon XMSN oil temps can increase by 10°C to 15°C. When operating in a hover condition for 10 min with OAT above 46°C. Returning to forward flight will gradually decrease forward XMSN oil temp.
48
NOTE associated with MFDs during Before Taxi Checks
Ensure the POWER TRAIN page is displayed on an MFD prior to 2 or 4 wheel taxi operations to monitor LCTs
49
Caution associated with cargo hooks during Before taxi checks
To prevent damage to the cargo hooks and structure, do not ground taxi over rough or uneven terrain with the forward and aft cargo hooks installed
50
Warning associated with Before taxi checks
Personnel injury or death may occur and damage to airframe and rotor systems will occur if the forward or aft rotor head rotor blade droop stop(s) are missing or interposer block(s) on the aft rotor head are not engaged. After engine run-up and before flight, or shutdown if flight is not conducted, the FE will scan the ground in the immediate area of the aircraft for evidence of detached droop stops
51
NOTE associated with setting FUEL CONTR switches
If using ERFS, the AUX FUEL PUMPs may be set to OFF
52
Cautions associated with turning ASE ON during ground operation
- With the IR suppressor or the standard tailpipe installed, high airframe skin temps may be experienced when rearward airspeed or tailwind exceeds 40kts. These conditions should be avoided.
- With the standard tailpipe installed, high engine XMSN oil temps may be experienced when rearward airspeed or tailwind exceeds 40kts. This condition does not exist when the IR suppressor tailpipe is installed. These conditions should be avoided.
53
Caution associated with FADEC check
Monitor NR and engine parameters when REV is selected. If an unexpected response occurs, immediately select PRI and execute an engine shutdown. Refer to maintenance personnel
54
NOTE associated with EAPS fans
The EAPS fans have a high start up electrical power requirements. To prevent an overload, the fans must be turned on one at a time. The first fan must be allowed to stabilize for 10 to 15 sec before the 2nd fan is turned on.
55
NOTE associated with turning second generator ON
Delay turning second generator ON for 3 sec. This delay will give the ECU time to sample power without causing a soft fault
56
NOTE associated with advancing ECLs to FLT
During cold weather operations, pilots should wait until all pressures and temps are within normal limits prior to advancing the ECLs to FLT
57
Cautions associated with advancing ECLs to FLT
- When the IR suppressor modification is installed, but the standard tailpipe is being used, engine mounted components can exceed their temp limits and fail during ground operations when the OAT is greater than 43°C and both ECLs remain at FLT for more than 10 min. Engine compartment temp can be mitigated by either maintaining one or both ECLs and GND until shortly before flight. This condition does not exist when the IR suppressor tailpipe is installed.
- Failure of either engine to accelerate past 70% NG from GND to FLT may be an indication of a clutch malfunction in the engine XMSN
58
Caution associated with starting second engine
After starting the first engine, the second engine must be started or motored for 10 sec within 3 min. When operating for extended periods with only one engine operating, the second engine must be motored for 10 sec every 30 min. The NP section of the second engine starts turning when the first engine is starter; however, the lubrication system of the second engine is driven by the NG section, which does not begin to turn until the START sequence is initiated. Delay in starting or motoring the second engine will result in excessive wear on the NP bearing package and seals.
59
NOTE associated with starting engine
Either engine may be started first
60
NOTE associated with EAPS fans
The EAPS fans have high start up electrical power requirements. To prevent an overload, only one EAPS fan should be turned on with APU power.
61
Caution associated with flight controls while rotors are turning
The cyclic and pedals must be manned and the thrust monitored any time the helicopter is on the ground with rotors turning
62
Warning associated with EAPS fans
Sand and debris within the EAPS will be ejected when the fans are operating. Personnel must stay clear of the EAPS fan exhaust when the fan is turned on.
63
NOTE associated with ECU Prestart BIT
If ECU display is other than 88, place the ECL to STOP, set B/U PWR switch to OFF and remove all power to the ECU by pulling the respective FADEC PRI PWR and REV PWR circuit breakers on the PDP. Reset circuit breakers and perform another ECU pre-start BIT. If ECU display is other than 88 consult ECU FAULT code list/matrix in Ch2.
64
NOTE associated with enabling navigators
During a gyro compass alignment, if INU I NAV READY and INU 2 NAV READY are displayed, ENABLE NAV may be omitted. The navigators will automatically enable when the aircraft moves.
65
NOTES associated with Flight control travel and hydraulics check
- Mixing of flight control inputs during ground operation on a single hydraulic system should be avoided.
- Check cautions as this check is being performed with slow, smooth flight control inputs, check each axis individually through full travel for smoothness of operation. Check for corresponding movement of the fore and aft rotors during check.
- For "through flight" perform steps b and c with FLT CONTR switch in BOTH
66
NOTE associated with AFCS SYSTEM SEL switch check
If a DASH 1/2 FAIL caution activates during the DAFCS check, allow the DASH to reprogram and the DASH 1/2 FAIL caution(s) to indicate before setting the AFCS SYSTEM SEL switch to OFF
67
Cautions associated with ANTI-ICE check
- Do not leave pitot heaters on for more than 5 minutes. Ground operation shortens service life.
- Windshield heat shall not be used above 24°C
68
NOTE associated with INIT SYS
Ensure GPS modes are available prior to NAV INIT and setting clocks
69
NOTE associated with the maintenance panel check
Different software versions assign dissimilar priorities for WCA messages. During the MAINTENANCE PANEL check, ensure all WCA messages listed in the procedure are verified regardless of what priorities in which they appear on the WCA summary
70
Warning associated with PWR XFER switches
If either #1 HYD FLT CONTR or #2 HYD FLT CONTR cautions do not extinguish in 30 sec after the PWR XFER switches are set to ON, set the PWR XFER switches to OFF. DO NOT FLY THE HELICOPTER.
71
NOTE associated with APU start
If the start is not completed or the APU is automatically shutdown, do not turn the BATT switch OFF. Set the APU switch to OFF, check the BITE indicators on the (ESU/DESU), and record the display for maintenance. Then turn the BATT switch OFF. Wait 1 minute for cooling before attempting restart. Failure to allow the APU to cool may cause premature shutdown on restart due to over temp.
72
Caution associated with Pedal adjustment
Uneven pedal adjustment can cause droop stop pounding during engine start and ground operations
73
Warnings associated with normal operational considerations for worn ensemble
- If performing a mission with an Air Warrior Ballistic Upgrade Plate (BUP), the seat buckle must be positioned below the BUP to prevent potential aft cyclic restriction.
- Aviator worn gear can restrict head and torso movement. Users should conduct ground familiarity drills and crew coordination exercises before flight. Since the field of regard can be restricted by aviator worn mission equipment, the user must strictly adhere to proper crew coordination procedures during switch identification.
- Prior to securing safety belt, all loose straps must be secured properly to eliminate emergency egress snag hazards.
- Prior to flight, control sweeps must be performed to ensure there are no flight control interference problems with the worn gear. If restriction is found, the interfering gear must be adjusted/moved to eliminate the restriction.
74
NOTES associated with walk around inspection and crew brief
- Accomplish steps 1 thru 4 prior to taking seats
- The cockpit, forward XMSN, flight control, and avionics compartment soundproofing should be installed during normal aircraft operation to reduce noise levels in the crew and passenger areas and to aid in venting of XMSN heat and fumes
75
NOTE associated with EAPS on preflight
Do not pull the EAPS forward for preflight inspection
76
Warning associated with ERFS tank sump
Failure to remove water and contaminants from the ERFS II/RSERFS tank sump could result in contaminants being transferred to the helicopter fuel tanks or other aircraft or equipment during FARE operations. If water and contaminants are not removed, a loss of engine power may result.
76
Warning associated with ERFS tank sump
Failure to remove water and contaminants from the ERFS II/RSERFS tank sump could result in contaminants being transferred to the helicopter fuel tanks or other aircraft or equipment during FARE operations. If water and contaminants are not removed, a loss of engine power may result.
77
Caution associated with ERFS connection security
Failure to close the unisex valves at the ERFS II/RSERFS tank end of the single point pressure refueling hose assembly could allow suctioning of fuel from the helicopter main fuel tanks during FARE operations
78
Cautions associated with hook check
Do not lift or rotate the center cargo hook into the cabin area or allow the mid hook to lay on the cargo floor or access door panel during inspection or use. The excess tension placed on the triple emergency release cable housing assembly may partially dislodge the housing and engage or activate the forward and aft hook emergency release mechanism. This may cause inadvertent release of loaded forward and aft hook assemblies in flight
79
Warning associated with Hook manual release lever check
Ensure cam roller is fully seated in locked position and hook is fully seated in cam lock or hook will release under loaded conditions
80
What does each symbol indicated:
1. F
2. O
3. ★
4. *
5. #
1. Flight Engineer
2. Requirement if equipment is installed
3. Detailed procedure for the step
4. Indicates step is mandatory for all through flights, when no change in PC
5. Duties performed by copilot station
81
Caution associated with the jettisonable doors
Aircrew members are not to place flight helmets, etc. on the cockpit jettison door handles. This may move the latch from the detent and cause unwanted jettisoning of the doors.
82
What is the PC in charge of
All aspects of mission planning, preflight and operation of the helicopter
CH47F
flashcards
Decks in class (20)
# Cards
-
Limits53
-
EPs17
-
Chapter 10
-
Chapter 5 Misc0
-
Chapter 60
-
Chapter 70
-
Chapter 883
-
Chapter 9 Misc0
-
APU0
-
DAFCS and FD0
-
Electrical0
-
Engine and related systems0
-
Environmental systems29
-
Flight control systems0
-
Fuel0
-
Hydraulic Systems0
-
Landing Gear15
-
Powertrain0
-
Rotor0
-
Seats and Emergency Equipment0
