Street’s NATOPS Chapter 7 Post Preflight HSM-50 Flashcards
If RMCU ENABLE/DISABLE is in DISABLE position when MSN PWR turned on,
TA will not indicate SEATED even if it is
Conditions when stab may autoprogram
During high wind conditions (winds greater than 30 knots) and with AC power supplied, the stabilator can automatically program. If the stab is folded, damage may occur. Consideration should be given to disengaging stab auto mode while the stab is folded.
After turning battery on, pilot station is hardwired to
V/UHF rado 1 via RCU.
to prevent APU exhaust fire, wait at least ___ after APU shutdown to attempt restart to allow residual fuel to vaporize
2 minutes
if APU shuts down during start or after running, do not ___ because ___
cycle BATT switch or turn off APU CTRL switch; it will remove cause of shutdown from APU BITE indicator
head check shall be conducted any time
BLADEFOLD switch is moved from OFF position
if PYLON FLIGHT light is not illuminated
pylon and stabilator lockpins and tail rotor indexer shall be visually inspected prior to flight. (DEMOT may have to extend pins to trigger switches).
Failure to visually inspect the pylon and stabilator lock pins and the tail rotor indexer may cause separation of the tail pylon.
hover altitude caret will not display until
mission comptuer has taken control
while performing CHIP IBIT
28 VDC is interrupted
during CHIP IBIT, WCAs and MASTER CAUTION will not correctly respond for
approx 40 seconds
CHIP IBIT will not function without
primary and backup computer on
on Fuel Quantity Test, should see
total fuel decreases to 0 (if external tank installed, total fuel will read what’s in external tank), #1/#2 FUEL LOW, MASTER CAUTION.
Indicators return to previous quantity after releasing pushbutton.
Good RadAlt Test
RadAlt tone 5 +/- 1 beeps, indicator reading 100 +/- 10 ft for 5 seconds, yellow tape up to DH setting or 100 ft, whichever is lower.
Performing a RADALT test prior to the primary computer being online may cause the RADALT to be stuck at the test altitude and will require restart of the primary computer.
Good TACAN Test
BRG 1 needle 180 +/- 3 deg for 5 sec, DME 0.0 nm (+/- 0.5 nm), NAV needle centering (within 1/2 dot), a TO (if 180)/FROM (360) indication
Good Transponder Test
Absence of IFF cautions or advisories
Tail Rotor Servo Check
#1 TR SERVO #2 TR SERVO ON BKUP MASTER CAUTION no binds or restrictions while moving pedals
AFCS Ground Checks Allowable movement
SAS 1/2 and trim - Minimal movement in flight controls acceptable
Autopilot - No movement in flight controls
Helicopter shall not be flown if stab fails
any check involving manual operation, position indications, or warnings.
Without stab auto mode, careful aircrew coordination to manually slew the stab is required to avoid undesirable and potentially dangerous flight regimes and or aircraft attitudes.
if stab auto mode fails to engage, ___ may align stab actuators and allow stab auto mode to reengage
slewing stab full up then full down with ac power.
Helicopter shall not be flown if the stabilator fails any check involving manual operation, position indications, or warnings.
Np shaft rub occurs due to
asymmetric heating of Np shaft by a hot engine
Np shaft rub definition
when rotor brake is released, Np shaft impacts Ng shaft causing compressor blades to impact casing
an unguarded cyclic may allow rotor arc to dip as low as
4 ft
if engine ignition is placed to NORM while start is in progress, __ may occur
hot start
it is normal for OIL FLTR BYPASS caution and/or high engine oil pressure to appear when
starting an engine below normal operating temps because of realtively high oil viscosity
Engine oil temp caution should disappear when engine oil reaches __ deg C
38
Ng will not indicate until __ %
6
Ground idle Ng split greater than __ is an indication of possible __. Do not fly until maintenance action is performed
3; possible rollpin failure
Engine Overspeed Test failure while testing A or B individually will
give same indications as a normal test of A and B simultaneously
During the C power check, a rapid rise in TGT may indicate what?
An engine control system malfunction
Hyd leak test lights
#1 TR Servo #2 TR Servo On Backup Pump On #1 RSVR Low #2 RSVR Low Backup RSVR Low SAS Boost Servo Off AFCS Degraded Master Caution
Tail Rotor Servo Check (Post Engagement Checks)
#1 TR Servo and Master Caution come on Within 1.5 seconds, get: #2 TR Servo On and BKUP Pump On
If electrical loads are introduced while on APU gen or external power, AFCC power sever may occur and cause ___ to appear
AFCS degraded
If droop stops not out by 100% Nr
Shutdown and investigate
Stab Check
- Check 34-42
- Test button - stab moves 5 to 12 deg up +warning/tone
- Auto control on - 34 to 42
- Man slew - 5 to 10 trailing edge up in 4 to 8 sec
- Man slew to 0
- Auto on
After start, if no xmsn oil px, ___
Zero oil px may indicate ___
shut down
A no oil flow condition –> damage to rotors if engaged for over 1 min
Moving flight controls
Moving flight controls without first or second stage pressure on the primary servos may cause damage to the flight controls.
RAST warning on takeoff
Failure to ensure the tail probe is manually retracted prior to takeoff from air capable ships may result in dynamic rollover.
Spread for more than 5-7 seconds
With a malfunctioning micro switch or blade fold logic module, keeping the BLADEFOLD switch in spread for more than 5-7 seconds may cause the blade fold lock pins to fully retract, resulting in an uncommanded blade fold and possible damage to the a/c.
Primary Servo ratcheting
With the collective in the full up position and the cyclic at the forward left corner of its movement envelope, a ratcheting may be felt through the cyclic and airframe and heard in the cockpit as the cyclic is moved to the right. This normal ratcheting of the swish plate uniball bearing on the star guide assembly will only occur at the specific flight control orientation and movement listed above.
Ratcheting or binding with the flight controls at any other position than collective full up and cyclic at the forward left corner indicates an unassociated control problem or deterioration of the Teflon coating on the uniball assembly.
Warning while turning generators on:
Power transfer from the APU generator or external power to the No 1 generator may cause disengagement of SAS 1/2, TRIM, AUTOPILOT, and stab. An unguarded cyclic may allow the rotor arc to dip as low as 4 ft above the ground.
Engine cooling on shutdown
Engines should be cooled for 2 minutes at an Ng of 90% or less before moving PCL to off. If an engine is shutdown without being cooled, it should not be restarted for 4 hours unless restart is performed within 5 mins.
Postflight
Interior and exterior equipment
Tires and struts
Leaks
Missing panels
“ITLM”
Requirements for alert launch checklist
All ground, prestart, systems, starting engines, rotor engagement, and shutdown checklists shall be completed prior to using the alert launch checklist.
EDECU Fault Code 15
EDECU fault code 15 may result in an EDECU driven engine control failure, and subsequent engine damage.
Fuel Dump restrictions
Fuel dumping should be manually terminated at no less than 600 lbs total fuel. Fuel dump checks shall be completed near a site at which a safe landing can be made in the event the fuel dump does not cease.
With less than 600 pounds of fuel, fuel starvation may occur when balanced flight is not maintained and or pitch attitudes exceed 15 degrees nose up or down.
Engine Cleaning 60 Hour TGT
Will be 71 degrees higher than normal with ENG OVSPD CBS pulled (EDECU not powered).
Additionally, engine alternator power may be insufficient to power some EDECUs at maximum started speed (also 71 degrees higher).
Low Ng Waterwash
If Ng decreases below 16% during engine cleaning, secure starter to prevent engine damage.
