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8.8 Before Exterior Check - W
Do not preflight until armament systems are safe, switches off, safety pins installed, and locking levers in locked position.
8.10 Nose Section (Area 1) - C
Do not deflect main rotor blade tips more than 6 inches below normal droop position when attaching tiedowns. Do not tie down below normal droop position.
2. Shoulder harness locks – Check for proper operation . . . - W, W
W- If using the Air Warrior ballistic upgrade plate, the seat belt buckle must be below the BUP to prevent potential cyclic restriction.
W- Prior to putting on the safety belt, all loose straps must be secured to eliminate egress snag hazards.
8.19 Cockpit Equipment Checks. – N
N- I must be able to reach and actuate all primary flight, propulsion, and emergency controls while fully restrained from design eye height or I cannot fly from this seat.
1. APU CONTR switch – ON. - C, N, N
C- Ensure that the mask blowers are disconnected and position the BCA MCU control knobs to OFF prior to switching from main power to APU power.
N- If the APU does not start and the APU ACCUM LOW advisory does appear with the APU CONTR switch ON, the manual override lever on the accumulator manifold should be pulled to attempt another start, and held until the APU has reached self-sustaining speed.
N- If APU fails, note and analyze BITE indications before cycling BATT switch or before attempting another APU start.
3.APU generator switch – ON. - W
W- Stabiliator will move to full trailing edge down position upon application of AC power. Assure stabilator area is clear prior to energizing stabilator system.
5. Doppler/GPS - On and program. - N
N- Only use datum WGS-84 and NAD-27. Other map datum's were not verified using AMPS and should not be used.
10. Caution/advisory/warning panels - Check as required. - N, N
N- Pulsating of any cautions or advisories with the LOW ROTOR RPM warnings may occur in DIM mode.
N- The switch legend on the VSI/HSI and the CIS mode select panel may change when the caution/advisory panel BRT/DIM- Test switch is set to TEST. This can also occur in flight. The original indications may be restored by pressing the applicable switches.
20. Flight Controls – Check first helicopter flight of the day. - W, W, N
W- Prior to flight, the user must perform control sweeps to ensure that there are no flight control interference problems with aviator worn gear. If a restriction is found, the interfering gear must be adjust/moved to eliminate the restriction.
W- If #1 or #2 SERVO PRESS caution appears during collective movement, a servo bypass valve may be jammed. If this situation occurs, do not fly the helicopter.
N- During collective and pedal movement, check for not more than 1.5 inches of free play in control.
24. Stabilator- Check. - W, N
W- If any part of stabilator check fails do not fly helicopter.
N- For the purpose of this check, the right STAB POS indicator shall be used. The left STAB POS indicator may vary from right indicator as much as +/- 2 throughout the check.
7. Engines – Start. – C, N, C, C, N
C- If start is attempted with ENGINE IGNITION switch OFF, do not place switch ON. Abort the start.
N- During engine start, the #1 or #2 FUEL PRESS cautions may appear briefly during an engine start. The FUEL BOOST PUMP CONTROL switches shall not be used to extinguish the #1 or #2 FUEL PRESS cautions during an engine start sequence.
C- To avoid damage to the engine start switch actuators, do not move the ENG POWER CONT lever from IDLE to OFF while pressing the starter button.
C- During engine start and run up, ensure that cyclic is kept in neutral, collective no more than one inch above full down and pedals centered until % RPM R reaches 50% minimum to prevent damage to anti-flap bracket bushings.
N- If an ENGINE STARTER caution disappears when the starter button is released and the ENG POWER CONT lever is OFF, the start attempt may be continued by pressing and holding the starter button until 52% to 65% Ng SPEED is reached, then release button.
8.20 Starting Engines
Abort Start Criteria
- Within 45s
- -No Rise in TGT
- -No Eng Oil Press indication
- -No %RPM R/1/2
- TGT reaches 850 before idle (63%Ng)
- Enging Starter Caution disappears before reaching 52%Ng.
8. Systems Check
- Ng Speed - 63%+ w/in 3% of each other.
- %RPM 1/2 - Not avoid ranges (20-40 & 60-90)
- XMSN Press at least 20psi.
- Eng Oil Press at least 20psi.
- #1/#2 Hyd Pump Cautions have disappeared.
11. Hydraulic leak test system – Check. - N, N
N- When performing the HYD LEAK TEST, all leak detection/isolation system components are checked electrically. Manually holding the HYD LEAK TEST switch in the test position does not allow the leak detection/isolation system to be checked automatically. It manually holds the circuits open. The switch must be placed in the TEST position and released.
N- If the backup pump is still running following the hydraulic leak test, cycle the BACKUP HYD PUMP switch to OFF then back to AUTO.
12. Tail Rotor Servo Transfer. - Check -N
N- Failure of the Back-up Pump On advisory or the #2 Tail Rotor Servo On Advisory to illuminate indications a failure of the leak detection/isolation system.
8.21 Engine Runup. – C
C- Do not transition power from APU generator to main generator while the CMWS is booting. Transition power source during booting can cause damage and/or system resets, resulting in mission delays or possible permanent damage to CMWS hardware.
2. Eng Power Cont lever. – Fly. – W
W- Restrict the rate of ENG POWER CONT lever’s movement, when the tail wheel lock pin is not engaged. Rapid application of ENG POWER CONT levers can result in turning the helicopter, causing personnel injury or loss of life.
15. GPS/DPLR Nav Mode selector - As desired. -N
N- If a consecutive or random route was programmed, do not allow the system to perform the test function. Performing the test function will delete any preprogrammed routes.
16. Collective friction – As required. - N
N- A slight amount of collective friction (~3 lbs) should be used to prevent pilot induced collective oscillations.
22. Fuel Boost Pump Control switches - Check before every flight to determine operabilitiy. Leave on if required. - W
W- Fuel boost pump control switches shall remain on during all pressurized fuel transfer operations and remain on for 10 minutes after transfer operations have ceased. Failure to observe this warning may cause engine flameout.
25. Operational Engine HIT / Anti-Ice Check – Accomplish. – W, N, W, W, C
W- Engine anti-ice bleed and start valve malfunction can cause engine flameout.
N- HIT/Anti-Ice checks while operating in adverse conditions (e.g. dust, desert, coastal beach area, dry river beds) may be deferred (maximum of 5 flight hours) until a suitable location is reached.
W- If any part of the engine anti-ice valve check fails, do not fly the helicopter.
W- Do not cycle the anti-ice bleed and start valve more than once. Valve malfunctions can cause engine flameout at low-power settings or during rapoid collective movements. Do not fly the helicopter if TGT rise is less than 30 deg C, switch cycling is required, or the ENG ANTI-ICE ON advisory will NOT go off.
C- A malfunctioning engine anti-ice and engine inlet anti-ice system may result in power losses as much as 40% maximum torque available at 30-minute TGT demands. If any part of the engine inlet anti-ice check fails, do not fly the helicopter.
8.31 Parking and Shutdown
20. APU CONTR switch – ON. – N
N- If external electrical power is required for shut down, it shall be connected and EXT PWR switch placed to RESET; then ON. If external ac power is not available, complete normal shutdown on right engine before continuing.
23. Generators No.1 and No.2 – OFF. – N
N-(AHRS) During shutdown, when ENG POWER CONT levers are moved from FLY to IDLE position or generator switch is moved to OFF position, and electrical power assignment is changed from Main Generator to APU Generator. An uncommanded right or left pedal drive of up to ¼ inch may occur, returning to neutral position within 3 seconds.
24. ENG POWER CONT levers – Idle. – C, C
C- During shutdown ensure that cyclic is kept in neutral or displaced slightly into prevailing wind, collective no more than one inch above full down and pedals centered.
C- Restrict the rate of ENG POWER CONT lever movement, when the tail wheel lock-pin is not engaged. Abrupt application of ENG POWER CONT lever can result in turning the helicopter.
27. Droop stops – Verify in, about 50% RPM R. – C
C- To prevent damage to anti-flap stops, do not increase collective pitch at any time during rotor coast-down.
28. ENG POWER CONT levers – OFF. – C, N
C- Cool engine at Ng SPEED of 90% or less for 2 minutes. If proper cooldown is not completed, and restart is necessary, accomplish within 5 minutes, otherwise let cool for 4 hours before starting engine.
- N- If one or more droop
- stops do not go in during rotor shutdown, shut down an engine to lower rotor
- idling RPM in an attempt to seat the droop stops. If droop stops still do not go in, accelerate rotor to above 75% RPM R. Repeat rotor shutdown procedures slightly displacing cyclic in an attempt to dislodge jammed droop stop. If droop stops still do not go in, make certain that rotor disc area is clear of personnel and proceed with normal shutdown procedures while keeping cyclic in neutral position.