UH60M Warnings, Cautions, Notes for Pre-flight/Run-up/Shut Down

Question 1

Before Exterior Check - W

Answer 1

*Warning*

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

Question 2

Nose Section - C

Answer 2

*Caution*

Do not deflect main rotor blade tips more than 6 inches below normal droop position when attaching tiedowns.

Question 3

APU - Check; oil level - W

Answer 3

*Warning*

The SATCOM and COM3 antennas are a trip hazard. Don’t trip on or damage these antennas.

Question 4

Before Starting Engines - W, C, N

Answer 4

*Warning*

Before engine operation can be performed, all main rotor tie-downs shall be removed.

*Caution*

Do not grasp the foam protective pad that surrounds the glare shield during adjustment of the seats. It may cause damage. *Note*

While fully restrained and in the design eye position, each pilot must be able to reach and have full access to all flight and emergency controls and all controls must have full range of movement. If the pilot cannot actuate all required items, they cannot fly the aircraft from that seat.

Question 5

APU CONT Switch ON - N, N

Answer 5

*Note #1*

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 should be pulled to attempt another start, and held until the APU has reached self-sustaining speed.

*Note #2*

If APU fails, note and analyze BITE indications before cycling BATT switch or before attempting another APU start.

Question 6

GENERATORS APU Switch ON - W, W

Answer 6

*Warning #1*

Assure stabilator area is clear prior to energizing stabilator system because the stabilator will move to the full down position.

*Warning #2*

Make sure that no person is within three feet of the TACAN antenna when power is applied to the helicopter because it will emit radiation.

Question 7

MASTER WARNING PANEL Check - N

Answer 7

*Note*

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

Question 8

SAS1, SAS2, TRIM, FPS Switches ON - N

Answer 8

*Note*

EGIs must be in ORIENT phase (attitude indicator is displayed) before AFCS switches can be turned on.

Question 9

Load Mission Data - N

Answer 9

*Note*

-Only two Unit Task Organizations (UTOs) can be loaded into the system using the mission card. -Load additional UTOs directly into the improved data modem (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).

Question 10

Flight Controls Check - C, N, W, N

Answer 10

*Caution*

Ensure the control access cover is closed and main rotor blades are not directly over the nose and tail of the aircraft to prevent contact with WSPS or IRCM.

*Note #1*

When SAS/BOOST is off, apply only enough force to contact a system stop. The yaw control system check with SAS/BOOST off should be performed with the collective restrained at approximately mid-position and pedal applied slowly in each direction. Do not increase pedal force after the yaw stop is reached.

*Warning*

Don’t fly the helicopter if the #1 or #2 PRI SERVO PRESS caution appears during collective movement, a servo bypass valve may be jammed.

*Note #2*

During steps h. and i., check for not more than 1.5 inches of freeplay in control.

Question 11

Stabilator Check - W

Answer 11

*Warning*

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

Question 12

FMS Initialization Check - N, N, N, N

Answer 12

*Note #1*

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

*Note #2*

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

*Note #3*

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

*Note #4*

The drag and performance variables must match the current aircraft configuration in order to ensure the most accurate PERFORMANCE values are displayed.

Question 13

Starting Engines - C, N

Answer 13

*Caution*

Damage to 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. Prior to starting engines, make sure that blades are aligned with aircraft centerline +/- 20 degrees before engaging rotor brake.

*Note*

Position the nose of the aircraft into the wind for extended engine operation with rotor locked.

Question 14

Gust Lock Engaged caution verify off - N

Answer 14

*Note*

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

Question 15

Rotor Brake On if Required - N

Answer 15

*Note*

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

Question 16

Engine Start - W, C, N, N, N, N, C, C, N, C, N

Answer 16

*Warning* If inadvertent rotor blade movement should occur due to rotor brake slippage, immediately shut down engine(s) or release rotor brake. *Caution #1* If start is attempted with ENGINE IGNITION switch OFF, do not place switch to ON. Abort the start. *Note #1* During rotor brake operations there will be no NP1 or NP2 until rotor brake is released. *Note #2* MAIN XMSN PRESS caution remains and there is no pressure indication until rotor brake is released. *Note #3* All corresponding No. 1 and No. 2 hydraulic cautions remain until the rotor brake is released. *Note #4* FUEL PRESS LOW caution may appear during the start process and should extinguish before the engine stabilizes at ground idle. *Caution #2* Don’t move the ENG POWER CONT lever from IDLE to OFF while pressing the starter button. *Caution #3* During the start and run-up, keep the cyclic neutral, the collective no more than one inch up, and the pedals centered until NR reaches 50%. *Note #5* If the ENGINE STARTER caution disappears when the starter button is released and the ENG POWER CONT lever is OFF, you can continue the start by pressing and holding the starter button until 52-65% Ng is reached. *Caution #4* For starts with rotor brake off and during rotor engagements, cyclic inputs shall be minimized to prevent droop-stop pounding. *Note #6* 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.

Question 17

Abort Start Criteria

Answer 17

1) No TGT increase within 45 seconds 2) No P (ENG OIL PRESS) within 45 seconds 3) No NP1 & NP2 within 45 sec (if rotor brake is off) 4) ENG STARTER ON caution disappears before 52% NG 5) TGT reaches 851 C before idle is attained

Question 18

Systems Check

Answer 18

-NP1 and NP2 - Not in avoid range 20-40% or 60-90% -NG - Greater than 63% within 3% of each other -XMSN P and P (ENG OIL PRESS) - check -HYD PUMP 1 FAIL & HYD PUMP 2 FAIL - Check Off

Question 19

Hydraulic Leak Test System Check - N, N

Answer 19

*Note #1* Don’t hold the switch in the TEST position when performing the HYD LEAK TEST. *Note #2* If the backup pump is still running following the hydraulic leak test, cycle the BACKUP HYD PUMP switch to OFF then back to AUTO.

Question 20

Tail Rotor Servo Transfer Check - N

Answer 20

*Note* If the BACK-UP PUMP ON advisory or the #2 TAIL RTR SERVO ON advisory don’t appear there is a failure in the leak detection/isolation system.

Question 21

Flight Controls - Hold - W, N

Answer 21

*Warning* Restrict the rate of ENG POWER CONT lever’s movement when the tailwheel lock pin is not engaged to prevent the helicopter from turning. *Note* For rotor brake operations ensure that approximately 45% NR for single engine and 57% NR for dual engine is reached prior to advancing PCLs.

Question 22

GEN 1 & 2 Fail cautions disappear above 97% NR - N

Answer 22

*Note* 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%.

Question 23

HIT Check - W, N

Answer 23

*Warning* Engine anti-ice bleed and start valve malfunction can cause engine flameout. *Note* 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.

Question 24

Before Taxi - W, C, C

Answer 24

*Warning* ONLY APPLIES IF USING EXTERNAL FUEL TANKS When on the ground, the ejector rack lock lever should be turned inward to allow the pilot visual confirmation form the cockpit. Ejector rack lock levers must be in the unlock position. *Caution #1* When ground taxiing, cyclic inputs should be minimized to prevent droop stop pounding. *Caution #2* Landing and Searchlight have less than one foot of ground clearance when extended. Use caution when taxiing over rough terrain if they are extended.

Question 25

Before Landing - C, N

Answer 25

*Caution* During roll on landing, The cyclic must be centered once the main wheels are on the ground to prevent contact between the main rotors and the helicopter and droop-stop pounding. *Note* Pitching the helicopter nose up as in hover may cause a transient droop in indicated main transmission oil pressure, depending on the degree of nose up attitude.

Question 26

After Landing - Avionics/mission equipment - As required - W

Answer 26

*Warning* Make sure that no person is within three feet of the TACAN antenna when power is applied to the helicopter because it will emit radiation.

Question 27

Flight Controls - Hold - C, C

Answer 27

*Caution #1* During shutdown ensure the cyclic is neutral or placed slightly into the wind, collective no more than an inch above full down, and pedals centered. *Caution #2* Restrict the rate of the ENG POWER CONT lever movement when the tail wheel lock-pin is not engaged to prevent the helicopter from turning.

Question 28

Droop stops - Verify in, about 50% NR - N, C

Answer 28

*Note* If one or more droop stops do not go in during rotor shutdown, shut down an engine to lower rotor idling RPM. 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. *Caution* Do not increase collective pitch at any time during rotor coast down.

Question 29

ENG POWER CONT levers - OFF after 2 minutes at Ng SPEED of 90% or less - C

Answer 29

*Caution* The engine must be cooled for 2 minutes at Ng of 90% or less before moving ENG POWER CONT lever to OFF. If you fail to do this and it is necessary to re-start, do it within 5 minutes of shut down, otherwise you must wait four hours before attempting restart.

Question 30

DEC/EDECU signal validation fault codes - Check - N, N

Answer 30

*Note #1* Loss of aircraft power to DEC will generate no fault codes. *Note #2* After the prescribed fault code has displayed as a Q value, the DEC codes may be found in the FMS status pages by selecting the following: STS Function Key, Air-Vehicle, DEC-1 for fault on #1 or DEC-2 for fault on #2.

Question 31

Generators APU switch - OFF - N

Answer 31

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