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HH-60M (2020) > Chapter 8 > Flashcards

Chapter 8 Flashcards

1
Q

Mission planning begins when the __1__ and extends to the __2__.

A
  1. mission is assigned
  2. preflight check of the helicopter
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2
Q

The manner in which each crewmember performs his related duties is the responsibility of the _____.

A

pilot in command

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3
Q

The pilot in command is responsible for all aspects of __1__, __2__, and __3__.

He will assign duties and functions to all other crewmembers as required.

A
  1. mission planning
  2. preflight
  3. operation of the helicopter
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4
Q

The pilot in command must be familiar with __1__ and the __2__.

The pilot will assist the pilot in command as directed.

A
  1. pilot duties
  2. duties of the other crew positions
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5
Q

The crew chief/medic will perform all duties as assigned
by the _____.

A

pilot

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6
Q

BEFORE EXTERIOR CHECK

WARNING

A

Do not preflight until armament systems are safe, switches off, safety pins installed, and locking levers in locked position.

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7
Q

Fuel sample (main and external) — Check.

A

a. For contamination before first flight of the day.
b. For contamination after adequate settling time after cold refueling.
c. If the fuel source is suspected to be contaminated.

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8
Q

NOSE SECTION

CAUTION x2

A

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.

Ensure no heat damage (blistering, charring or disbanding) to main rotor blades with UES installed.

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9
Q

Avionics compartment — Check equipment as required.

CAUTION

A

Ensure avionics compartment door is closed and latches are secure prior to securing the FLIR door.

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10
Q

FLIR — Check condition (remove locking pin).

CAUTION

A

Optical lens of FLIR is easily scratched. To avoid damage, use cleaning procedures and supplies referenced in the maintenance manual.

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11
Q

APU — Check; oil level.

CAUTION

A

The SATCOM and COM3 antennas are a trip hazard. Care must be taken while accessing the APU compartment not to trip on or damage these antennas.

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12
Q

BEFORE STARTING ENGINES

WARNING x2

A

Before engine operation can be performed, all main rotor tiedowns shall be removed.

All pilots shall complete the flight control access evaluation from the seat that they intend to use during flight. During preflight checks, the pilot and copilot must ensure all primary flight, propulsion, and emergency controls can be safely and efficiently reached and actuated while fully restrained, at the appropriate design eye position, with maximum stretch of the shoulder and arm muscles. The aviator shall have full flight control movement (cyclic, collective, pedals) and the ability to reach and actuate the ENG POWER CONT lever, Engine Fuel Selector Lever, and Fire T-Handle. If the pilot cannot actuate all the required items, he shall not operate the aircraft from that seat.

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13
Q

BEFORE STARTING ENGINES

CAUTION

A

A foam protective pad surrounds the glare shield. Do not grasp the pad during adjustment of the pilot and copilot seats as damage to the material may result.

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14
Q

APU CONT switch — ON.

NOTE x2

A

If APU fails, note and analyze BITE indications before cycling BATT NO. 1 switch or before attempting another APU
start.

If the APU does not start and the APU ACCUM LOW advisory does not appear with the APU CONT switch ON, the manual override lever on the accumulator manifold may be pulled to attempt another start, and held until the APU has reached
self-sustaining speed.

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15
Q

GENERATORS APU switch — ON.

WARNING x3

A

Stabilator will move to full trailing edge down position upon application of AC power. Assure stabilator area is clear prior to energizing stabilator system.

Potential radiation hazard exists at the TACAN antenna when the TACAN is turned on. Make sure that no person is within three feet of the antenna while power is applied to the helicopter.

During power-up,
IBIT/SBIT, or rebooting during flight, the CMWS/ICMD will be offline for approximately 2 to 5 minutes and unable to protect the helicopter until complete.

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16
Q

GENERATORS APU switch — ON.

CAUTION

A

Do not transition power from APU generator to main
generator while CMWS is booting. Transitioning power source during booting can cause damage and/or system resets,
resulting in mission delays or possible permanent damage to the CMWS hardware.

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17
Q

EDECU — Check signal validation code
25%.

NOTE x3

A

An engine EDECU will display an EDECU signal validation startup code on the MFD Q indicator approximately 20 seconds after application of ac power. A startup code of 25% shall be verified to indicate a 701D with a DAS plug installed.

The EDECU configuration may also be verified on the FMS status page.

The DEC will immediately display signal validation fault codes on the MFD Q indicator after application of ac power at a
rate of 4 seconds on and 2 seconds off during startup, and 30 seconds after both engines are shutdown with ac power applied.

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18
Q

MASTER WARNING PANEL — Check #1 ENG OUT, #2 ENG OUT, LOW ROTOR R.P.M segment lights are illuminated.

NOTE

A

If a segment light does not illuminate, pull out 1⁄4 inch then push back in to reset the bulb.

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19
Q

Press FCC FAILURE RESET switches.

NOTE

A

EGIs must be in ORIENT phase before AFCC faults will reset.

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20
Q

Flight controls — Check first flight of day.

WARNING x2

A

Prior to flight, the user must perform control sweeps to ensure there are no flight control interference problems with aviator worn gear. If a restriction is found, the interfering gear must be adjusted/moved to eliminate the restriction.

If PRI SERVO 1 FAIL or PRI SERVO 2 FAIL caution appears during collective movement, a servo bypass valve may be jammed. If this situation occurs, do not fly the helicopter.

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21
Q

Flight controls — Check first flight of day.

CAUTION

A

When the hydraulic access cover is open, ensure the main rotor blades are not directly over the nose to prevent contact with the WSPS.

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22
Q

Flight controls — Check first flight of day.

NOTE

A

The force applied to the pedals with SAS/ BOOST off during pre-flight checks should be limited to only that required to contact a system stop. Additional pedal force results in no additional tail rotor motion and has been demonstrated to generate flight control bearing/bolt noises.

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23
Q

Stabilator — Check.

WARNING

A

If any part of stabilator check fails, do not fly helicopter.

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24
Q

Blade deice system — Test as required.

WARNING x2

A

A risk of low current shock exists when blade deice system is turned on for ground checks. Injury to personnel can result if contact is made with main rotor blade cuff, spindle, and droop stop cam while blade deice test is in progress. Clear aircraft upper deck of personnel during blade deice test until blade deice control panel TEST IN PROGRESS lamp is off and Test switch is placed in OFF position.

Droop stop hinge pins and cams may become very hot during test. Use care when touching those components.

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25
Q

Blade deice system — Test as required.

CAUTION x2

A

Do not perform blade deice test when blade erosion kit is installed.

To prevent overheating of droop stops, blade deice test shall not be done more than one time within a 30-minute period when rotor head is not turning.

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26
Q

Blade deice system — Test as required.

NOTE

A

PWR MAIN RTR and PWR TAIL RTR monitor lights may flicker during tests in steps f. through s. and the M/R DE-ICE FAULT caution may appear during tests in steps j. through q.

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27
Q

FMS initialization — Check as required.

NOTE x3

A

FMS defaults to the last known helicopter position. The FMS automatically updates the date, time and position with GPS data once it becomes available.

If INIT is not selected manually, it will automatically engage once the GPS acquires satellites and determines its location.

The Calculator PERFORMANCE function will ONLY be used to reference PERFORMANCE values after verifying the correct configuration of the aircraft.

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28
Q

Set up MFD/FD/FMS for mission.

NOTE

A

Only two Unit Task Organizations (UTOs) can be loaded into the system using the mission card. Load additional UTOs directly into the IDM as required. Allow UTO and URN file to load from user PCMCIA card and the IDM to indicate a successful initialization; “OPERATIONAL” displayed on IDM status line prior to JVMF Initialize/Login (Approx 2 minutes).

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29
Q

STARTING ENGINES

CAUTION

A

Prior to starting engines, ensure main rotor blades are aligned with the aircraft centerline 620° before engaging the rotor brake. Damage to the main rotor blades will occur if blades are positioned over UES during engine start with rotor brake applied. Heat damage can occur to blades if blades are kept in a static position with engines operating.

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30
Q

GUST LOCK ENGAGED caution — Verify
off.

NOTE

A

Gust lock caution may not be visible on the CAS page; pilot must verify on EICAS page.

31
Q

STAB UNLOCKED caution — Verify off.

WARNING

A

Engine operation and/or rotors turning with the stabilator unlocked could allow the stabilator to contact the tail rotor.

32
Q

STAB UNLOCKED caution — Verify off.

NOTE

A

STAB UNLOCKED caution may not be visible on the CAS page. Pilot must verify in the overflow box on EICAS display.

33
Q

Rotor brake — On, if required. ROTOR BRAKE advisory appears. Minimum pressure 450 psi, and rotor blades aligned with aircraft centerline +/-20°.

NOTE

A

If operating conditions permit, the engines may be started with an inoperative or not installed rotor brake.

34
Q

Engine(s) — Start.

WARNING

A

If inadvertent rotor blade movement should occur due to rotor brake slippage, immediately shut down engine(s) or release rotor brake.

35
Q

Engine(s) — Start.

CAUTION x4

A

If start is attempted with ENGINE IGNITION switch OFF, do not place switch to ON. Abort the start.

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.

During engine start and runup ensure that cyclic is kept in neutral, collective no more than one inch above full down, and pedals centered until NR reaches 50% minimum to prevent damage to anti-flap bracket bushings.

For starts with rotor brake off and during rotor engagements, cyclic inputs shall be minimized to prevent droop-stop pounding.

36
Q

Engine(s) — Start.

NOTE x3

A

During rotor brake operations there will be no NP or Q indications until rotor brake is released.

MAIN XMSN PRESS caution remains and there is no pressure indication until rotor brake is released.

All corresponding No. 1 and No. 2 hydraulic cautions remain until the rotor brake is released.

37
Q

Engine(s) — Start.

NOTE x2

A

FUEL PRESS LOW caution may appear during the start process and should disappear before the engine stabilizes at ground idle.

The FUEL BOOST PUMP CONTROL switches shall not be used to extinguish the FUEL 1 PRESS LOW or FUEL 2 PRESS LOW caution during an engine start sequence.

38
Q

Engine(s) — Start.

NOTE x2

A

If an ENG STARTER ON 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 is reached; then release the starter button.

There is a delay of approximately one second between the time the starter disengages and the ENG STARTER ON caution disappears. Consequently the NG is permitted to indicate above 65% when starter drop out is indicated on the MFD, but must be out by the time the engine reaches idle.

39
Q

If any of these indications occur during start sequence, abort the start.

A

(1) No TGT increase (light off) within 45 seconds.

(2) No P (engine oil pressure) within 45 seconds.
(3) No NP1 or NP2 within 45 seconds (if rotor brake is off).
(4) ENG STARTER ON caution disappears before reaching 52% NG.
(5) TGT reaches 851°C before idle is attained (above 63% NG).

40
Q

Hydraulic leak test system — Check.

NOTE x2

A

When performing the HYD LEAK TEST, all LDI 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.

If the backup pump is still running following the hydraulic leak test, cycle the BACKUP HYD PUMP switch to OFF then back to AUTO.

41
Q

Tail rotor servo transfer — Check.

NOTE

A

Failure of the BACK UP PUMP ON advisory or the T/R SERVO 2 ON advisory to appear indicates a failure in the LDI system.

42
Q

ENG POWER CONT lever(s) — FLY.

WARNING

A

Restrict the rate of ENG POWER CONT lever’s movement, when the tailwheel lockpin is not engaged. Rapid application of ENG POWER CONT levers can result in turning the helicopter, causing personnel injury or loss of life.

43
Q

ENG POWER CONT lever(s) — FLY.

NOTE

A

For rotor brake operations, ensure that approximately 45% NR for single engine and 57% NR for dual engine is reached prior to advancing ENG POWER CONT levers.

44
Q

GEN 1 FAIL and GEN 2 FAIL cautions
disappear above 97% NR.

NOTE

A

During single engine ground operation with the collective full down NP/NR may indicate 99%, even when the engine speed trim is increased to the maximum setting. This is a normal characteristic, and may be observed more frequently during hot weather. Raising the collective slightly (approximately 1⁄2 inch) will bring the NP/NR to 100%.

45
Q

DEICE EOT — Check as required.

CAUTION

A

In ambient temperatures above 21°C (70°F), operate rotor at 100% NR for 5 minutes before doing the deice EOT check, to prevent blade overheating. Do not do the deice EOT check if OAT is above 38°C (100°F).

46
Q

DEICE EOT — Check as required.

NOTE

A

If helicopter engine was started using external air source and/or external ac power, the APU must be started to do APU generator backup check.

47
Q

ECS panel switches — As desired.

CAUTION x2

A

Due to ECS noise levels, personnel using only Foam Earplugs are restricted to three flight hours per 24- hour period. The rubber style earplugs are prohibited.

During operation of the air conditioner system, the right cabin door should remain closed. If opening is required, the right cabin door should not remain open for more than one minute.

48
Q

ECS panel switches — As desired.

NOTE

A

Turning the ECS on may cause the AFCS computer CPTR capsule and the TRIM and FPS lights to illuminate. Press FAILURE RESET CPTR1 or CPTR2 to clear failure.

49
Q

CEFS — Check.

NOTE

A

When CEFS is installed there is a communications timing error between the DCUs and the CEFS signal conditioners during power up. When this occurs, the external fuel tank configuration and fuel amounts will not be shown correctly and a TANK ID CHANGED caution will appear on one or both EICAS displays. To correct the error, wait 3 minutes after APU or external power is applied to allow the DCU to complete the CHIP IBIT test, then recycle power to the DCUs using the DCU 1 and DCU 2 circuit breakers. This is a temporary work around until a permanent fix is in place.

50
Q

Operational Engine Health Indicator Test
(HIT) / Anti-Icing Check.

NOTE x3

A

The Health Indicator Test (HIT) is an operational check done on the ground to find a significant performance shift, trend engine performance, and to verify proper operation of the anti-icing bleed and start valve.

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.

Perform the Operational Engine Health Indicator Test / Anti-Ice Systems Check prior to each mission day.

51
Q

ANTI-ICE SYSTEMS CHECK

WARNING x2

A

If any part of the engine anti-ice valve check fails, do not fly the helicopter.

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 rapid collective movements. Do not fly the helicopter if TGT rise is less than 30°C (54°F) or switch cycling is required.

52
Q

ANTI-ICE SYSTEMS CHECK

CAUTION

A

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.

53
Q

Sequential Operational HIT Check.

NOTE

A

During a sequential operational HIT check, the FORCE option is disabled, but the FORCE function remains visible.

54
Q

In-Flight HIT Check.

NOTE

A

The In-Flight HIT Check may be used in a desert environment to minimize engine sand ingestion in a heavy sand environment, and shall be accomplished at an altitude where there is a minimum of sand intrusion.

55
Q

Ejector rack lock levers unlocked.

WARNING

A

When on the ground, the ejector rack lock lever should be turned inward to allow the pilot visual confirmation from the cockpit. Prior to flight, the ejector rack lock lever must be in the unlock (vertical) position to allow emergency jettisoning of the tanks in flight.

56
Q

GROUND TAXI

CAUTION x2

A

When performing these maneuvers, cyclic inputs should be minimized to prevent droop stop pounding.

Landing and searchlight have less than one foot ground clearance when extended. Use caution when taxiing over rough terrain when landing light and/or searchlight are extended.

57
Q

BEFORE TAKEOFF

WARNING

A

Pitot heat and anti-ice shall be on during operations in visible moisture with ambient temperature of 4°C (39°F) and below. Failure to turn pitot heat on in icing conditions can cause the stabilator to program trailing edge down during flight. If this occurs, manually slew the stabilator to 0°.

58
Q

TAKEOFF

WARNING

A

If the stabilator has not begun trailing edge up movement by 30 to 50 KIAS, and manual control is not available, do not exceed KIAS limits or longitudinal control may be lost.

59
Q

CEFS transfer — As required.

WARNING

A

If external fuel transfer is not done in the automatic mode, fuel transfer sequence must be carefully planned and executed in order to maintain CG within limits.

60
Q

DISP control panel ARM SAFE switch — As required.

WARNING

A

Launched flares may cause injury and severe burns to personnel. Ensure CMWS ARM/SAFE switch is SAFE and crew safety pin is installed when use is not required.

61
Q

LANDING

CAUTION

A

During roll-on landing aerodynamic braking with aft cyclic is permitted with the tail wheel contacting the ground. Once the main wheels touch down, the cyclic must be centered prior to reducing collective. Excessive aft cyclic may cause droop stop pounding and contact between main rotor blades and other portions of the helicopter. Aerodynamic braking is prohibited once the main landing gear touches down. Use brakes to stop the helicopter.

62
Q

LANDING

NOTE

A

Because of the flat profile of the main transmission, pitching the helicopter nose up as in hover, may cause a transient drop in indicated main transmission oil pressure, depending on degree of nose-up attitude.

63
Q

A roll-on landing may be used when __1__; __2__; __3__; or when operating with __4__.

A
  1. the helicopter will not sustain a hover
  2. to avoid hovering in snow or dust
  3. if tail rotor control is lost
  4. one heavy external tank
64
Q

Slope landing. The __1__ and the __2__. For slope landings and all ground operations, avoid using combinations of __3__ and __4__. Where minimum collective is used, maintain cyclic near neutral position and avoid abrupt cyclic inputs. During nose-down slope landings, low-frequency oscillations may be eliminated by moving cyclic toward neutral and lowering collective.

A
  1. tailwheel should be locked
  2. parking brake should be set
  3. excessive cyclic
  4. low power settings
65
Q

Crew safety pin — Installed and locked.

WARNING

A

After install, pull on crew safety pin to ensure installed securely.

66
Q

PARKING AND SHUTDOWN

NOTE x2

A

If external electrical power is required for shutdown, it shall be connected and EXT PWR switch placed to RESET.

If ac power is not available and a blind shutdown must be performed, complete normal shutdown on No. 2 engine before continuing.

67
Q

ENG POWER CONT levers — IDLE.

WARNING

A

Restrict the rate of ENG POWER CONT lever’s movement, when the tailwheel lockpin is not engaged. Rapid application of ENG POWER CONT levers can result in turning the helicopter, causing personnel injury or loss of life.

68
Q

ENG POWER CONT levers — IDLE.

CAUTION

A

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.

69
Q

Cyclic — As required to prevent anti-flap pounding.

CAUTION

A

To prevent damage to anti-flap stops, do not increase collective pitch at any time during rotor coast down.

70
Q

Droop stops — Verify in, about 50% NR.

NOTE

A

If one or more droop stops do not go in during rotor shutdown, shut down an engine to lower rotor idling NR in an attempt to seat the droop stops. If droop stops still do not go in, accelerate rotor to above 75% NR. 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.

71
Q

ENG POWER CONT levers — OFF after 2
minutes at NG of 90% or less.

CAUTION

A

Before moving ENG POWER CONT lever OFF, engine must be cooled for 2 minutes at an NG of 90% or less. If an engine is shut down from a high power setting (above 90%) without being cooled for 2 minutes, and it is necessary to restart the engine, the restart should be done within 5 minutes after shutdown. If the restart cannot be done within 5 minutes, the engine should be allowed to cool for 4 hours before attempting an engine start.

72
Q

DEC/EDECU signal validation fault codes —
Check.

NOTE x2

A

Loss of aircraft power to DEC will generate no fault codes.

After the prescribed fault code has displayed as a Q value, the DEC codes may be found in the FMS status pages.

73
Q

Pressure refueling — If required for auxiliary
fuel systems.

NOTE

A

All switches for refuel on the AUX FUEL MANAGEMENT PANEL shall be set with power applied to ensure all valves are in the proper position for the tank(s) selected to be refueled.

74
Q

GENERATORS APU switch — OFF.

NOTE

A

Wait 15 seconds before turning off the APU generator after EGI 1 and EGI 2 switches are turned off.

HH-60M (2020) (3 decks)

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