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5 Stab Warnings:
- 1.Accel with Stabilator full down you will lose longitudinal control
- 2.Stab hardover may cause it to move down when you press Auto Control Reset
- 3.Momentary loss of AC; may cause stab to program down
- 4.If Auto Mode repeatedly fails; no fly >70 kts in Auto
- 5.A/S Advisory Lt; no fly >70 kts in Auto
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If A/S Advisory Lt on and/or Auto Mode repeatedly fails. Do not flly over_____ kt in Auto Mode
70 kts
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Pitch Boost Hardover Force
20 lbs
-
Yaw Trim SAS Malfunction Force
30 lbs
-
Yaw Trim Actuator Jam Force
80 lbs
-
Yaw Boost and/or T/R Servo Fail Force
250 lbs
-
Required to perform HIT Check
- 1.1st Flight of the day
- 2.Engine deterioration suspected
- 3.After Salt Water Ops
-
Allowed In-Flt Hit Ck vs Ground
- 1.Discretion of crew
- 2.May ingest FOD while on ground
-
Open/Close Doors max KIAS
130 kts
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Doors Open Max KIAS (soundproofing removed)
145 kts
-
Hoist Cable Length
200 feet
-
Normal Rate Breeze Eastern Hoist
Normal Rate Lucas Western Hoist
-
Hoist rate using P/CP switch
100 fpm
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Warning: If AFCC computer is blank or "Computer Bad"....
Do not fly aircraft
-
Caution for Aux Fuel System Check
Fuel Pumps may overheat if transfering fuel while Main Tanks full
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Caution: Do not select _________ Transfer with Man Aux Flow in "Flow". May cause pump failure.
Auto
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Tie down rotor blades above _______ kts wind
45
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Fold main rotor blades when ______ kts wind.
60
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Maximum you can pull down on MR blade at nose of aircraft:
6 inches
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APU Start Checklist
- 1.Cabin Heat - OFF
- 2.Air Source Heat/Start - APU
- 3.Fuel Pump - APU Boost
- 4.APU Switch - ON
-
Warning: After dumping fuel ________ is Inoperative
Auto Fuel Transfer
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Initial action for Uncommanded Nose Down Pitch Attitude Change
Aft Cyclic, Collective maintain or raise
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At what airspeed does Uncommanded Nose Up Pitch Attitude Change become noticeable?
140 kts
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Stabilator Malfunction: Characteristic of Approach with Stab @ 0 deg.
4-5 deg nose higher than normal at 20-40 kts
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Caution for Refueling Probe Check: amount of fuel change in Main Tanks should be no more than _____ lbs. A change of ______ could indicate faulty valve allowing fuel to XFR from Main to AUX.
20-30 lbs / 80-120 lbs
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Warning: Satcom use on ground
No body should be on top of Helo when transmitting on Satcom.
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Warning: Use of RADAR on ground
RADAR has 15' hazardous area in front when on ground.
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Warning: Engine Cowlings
One person on cowling (250 lbs max) Total Max weight = 400 lbs
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Engine Start Parameters:
1.TGT < ____ deg C before Thrtl to Idle
2.If OAT < ____ deg C, obtain Max Ng before Thrtl to Idle
-
Abort Eng Start If: (5 items)
- 1.No TGT rise w/in 45 sec
- 2.No Nf/Nr w/in 45 sec
- 3.No Eng Oil Press w/in 45 sec
- 4.TGT > 851 deg C prior to 63% Ng
- 5.Starter dropout prior to 52-65%
-
If Eng Start aborted for no TGT rise...
Motor Eng 30 sec prior to next start attempt
-
Caution: If you attempt start with Ignition switch off...
Abort start, do not flip Ignition on in middle of start.
-
Note: E. AI. Lights before start should be...
Illuminated
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RADAR/VAWS Test Procedure (3 steps)
- 1.Set 80' / 800' (LO & DH lights on / Digit 0-3' & Needle +-5')
- 2.Press to Test (1000+-100' / HI light / Betty: "Check Altitude"
- 3.Release (Betty "Low Altitude" / Silence / All crew members acknowledge)
-
Accurate INU Alignment Requirements
- 1.Starting Coordinates
- 2.HSI Heading (Slaved & Aligned)
- 3.SGU Altitude (VSDS Cal)
- 4.Magnetic Variance
-
1.MR Disk Diameter:
2.Overall Length:
3.T/R to Ground:
-
Caution: APU Starting
1.If APU shuts down...
2.If APU OIL TEMP HI...
3.If no start...
- 1.don't cycle APU Cntr Sw, don't cycle Batt Sw
- 2.shut down, wait 30 min and check oil prior to starting again.
- 3.wait 2 min prior to attempting restart
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Stabilator Check
- 1.34-42 deg
- 2.Press Test, Stab Lt & Horn, Up 5-12 deg
- 3.Auto Contr Reset, Back to Orig Posn
- 4.Pil up 15 deg, CP up 15 deg, Up to 6-10 deg, Down to 0
- 5.Auto Contr Reset back to Orig Posn
-
Warning: Stabilator Check
Do not fly if it fails any portion of the check.
-
Batt Sw ON - What Caution Lights?
- C-#1 CONV
- B-BATTERY ONLY
- B-BOOST SERVO OFF
- A-A/C ESS BUS OFF
- S-SAS OFF
- S-STABILATOR
- 2xMASTER CAUTION
- Eng Off Horn
-
AHHS Check
- 1.AFSC - All ON.
- 2.AHHS HOV - ON; HOV & RDR ALT Switches
- AHHS Armed Lt; Roll/Pitch Bars; CDI/GS & CPI; GA&AHHS Fail Lts Off
- 3.TRIM - OFF; AHHS CL On
-
Flight Contr & Hydraulics Check (no AHHS)
- 1.Iso Hyd #1/#2; Cyc/Pdls>5sec, Coll <1sec (Non Iso Pri Svo does NOT Illum)
- 2.T/R Back Up - Sel; Left Pdl:Star-in, Right Pdl
- 3.Boost - OFF; Coll>5sec (1.5"), Pdls(.75" ea)
-
Before Taxi/Takeoff
1.TQs Matched w/in:
2.TQ Matched w/in Computed pwr:
3.If Test A/B pushed repeatedly:
- 1.5%
- 2.+-3%
- 3.May get 95+-3% error on TQ Gauge
-
1.TQ Loss w/ E. AI. On:
2.Max TQ Incr using DECP
-
Caution: Eng Shutdown
1.Engine Cool-down requirement
2.If C/D is not followed
- 1.Ng<90% for 2 min prior to shutdown
- 2.Eng must be restarted w/in 5 min or else cooled for 4 hrs for #4 Eng Bearing
-
Eng Shutdown: Droop stops in by _____. If not in...
50% - accel to 75% Nr and move cyc slightly then decel again.
-
Engine Inlet Anti Ice
1.Adv Light Illum when temp at Inlet =
2.EI. AI. should open when (OAT Conditions)
3.When EI. AI. turned off, Adv Lt should extinguish in ____ sec
4.When OAT<-25 degC...
5.During Start, EI.AI. should be...
- 1.93 deg C
- 2.>13 deg C; Not On / 4-13 deg C; May be On / <=4 deg C; Will be On
- 3.90 sec
- 4.TGT rise may be up to 125 degC when EI.AI. valve opens
- 5.During start EI.AI. is held close
-
Warning: Engine Anti Ice Loss of Power
May lose up to 18% power. Consider turning off while hovering, or flying at low alt/aspd
-
HIT Check Write Ups w/o Abort Req'd (2)
- 1.TGT rise w/in 5 deg of HIT Log max
- 2.TQ Matching not w/in 60+-5%
-
Warning: Flight Contr Hydraulics Check; While moving collective ensure... (2)
- Ensure Non-isolated SERVO Lt does not illum. May indicate Pri Servo Bypass Valve jam in isolated Servo.
- Ensure cyclic does not move when collective is moved. May indicate rate related discrepancy between servos.
-
Warning: HIT Check if E.AI. / EI.AI. checks fail. (2)
- 1.If TGT rise>110 deg C or EI.AI. malfunctions do not take if Icing Conditions
- 2.Malf E.AI. & EI.AI. may cause power loss up to 40%
-
WOW Functions Left Side
- B/U Pump Thermal Sw disabled in Flt
- B/U Pump Off Sw disabled in Flt
- Retracted Probe Refuel disabled on G
- AFCC MX Test disabled in Flt
- AHHS Fcns disabled on G
- Transponder Mode IV dumped unless held
- SAS Roll Fcn disabled on G
- Windshield override disabled on G
- Audio for Low Nr disabled on G
- SPS/Flare launch disabled on G
- Hyd LDI Test disabled in F
-
WOW Functions Right Side
- Underfreq protection for Gen disabled in F
- MX Fcns for CDU disabled in F
-
Caution: Starter Dropout Malfunction
- 1.Pull down on Throttle
- 2.Circuit Breaker
- --#1-DCE panel O/H Pil side
- --#2-2 DCP above Pil's head
- 3.Remove air source
-
May accomplish in Flight HIT Check In Lieu of Ground when: (2)
- 1.FOD ingestion is possible
- 2.Crew Discretion
-
Required to accomplish In Flight HIT check when: (2)
- 1.Eng Deterioration suspected
- 2.After Salt Water Ops
-
HIT Check Numbers
1.TQ Stiction limit at ___ % Nf
2.Max TGT rise for Air Source Heat Sw
3.TGT rise for E.AI.
- 1.Zero-5% / 92-98%
- 2.5 deg C
- 3.30-110 deg C
-
HIT Check Fail (6)
- 1.TQ Stiction >5%
- 2.TGT outside HIT Log limit
- 3.Air Src Sw TGT rise >5 deg C
- 4.TGT rise<30 degC or>110 degC w/ Icing
- 5.EI.AI. fails with icing
- 6.TGT does not return to previous reading
-
In Flight HIT Check
1.Pull TQ to:
2.Expect TGT to rise:
-
Post Start Engine Parameters
1.Eng Out Warning Off at:
2.Ng > ___%
3.#1 & #2 Eng Ng match within ___%
4.Avoid Nf Range ____ & ____
- 1.55%Ng
- 2.63%Ng
- 3.3%Ng
- 4.20-40 & 60-90% Nf (adv throttle as necessary)
-
Warning: APU Compartment Fire
1.With no AC power...
2.Resetting the...
- 1.Only the Reserve Bottle can be fired
- 2.Resetting the T-Handle will cause the APU to restart.
-
Turbulence Limits
1.Intentional flight into known___ prohibited
2.Intentional flight into ____ prohibited
-
Icing Limits
1.Equip req'd for ANY icing
2.Equip Req'd for Trace
3.Equip Req'd for Light
4.Equip Req'd for Moderate
Icing Definition:
- 1.E.AI. / EI.AI. / Wndshld AI. / Pitot Ht req'd for any icing.
- 2.Above
- 3.Above (not recommended w/o Bld DeIce)
- 4.Above + Blade DeIce
- Icing = Visible Moisture / OAT =<4 degC
-
Ng Alternator Powers: (3)
- 1.Ng gauge
- 2.DECU
- 3.Ignition Exciter
- Airframe power is b/u for 2 & 3
-
HMU Functions (4)
- G-Governs Ng (variable inlet guide vanes)
- M-Meters Fuel
- --Sets max power for PAS
- --Responds to LDS
- O-Overspeed Protection (Ng > 110+-2%)
- P-Pressurizes fuel for nozzles
-
AFCS Master Caution Lights
1.BOOST SERVO OFF =
2.SAS OFF =
3.FLT PATH STAB =
4.TRIM FAIL =
- 1.Hyd press from PAM to Pedal/Collective boost servos <2000+-50 psi
- 2.Hyd press from PAM to SAS Actuator <2000+-50 psi
- 3.FPS inop in one or more axes
- 4.Y,R or P trim actuators not responding properly (FPS will also be on)
-
EP Initial Action: Eng Compressor Stall
Reduce Collective, Throttle to Idle
-
EP Initial Action: High Speed Shaft Failure
Affected Engine - Idle
-
EP Initial Action:Torque Split
Suspected Engine - Idle
-
EP Initial Action: OIL FILTER BYPASS Light
Affected Engine - Idle
-
EP Initial Action: CHIP INPUT MDL
Affected Engine - Idle
-
EP Initial Action: Increasing Nr
Affected Engine - Idle
-
EP Initial Action: Engine Oil Temp
Affected Engine - Idle
-
EP Initial Action: CHIP ENGINE
Affected Engine - Idle
-
EP Initial Action: Engine Compartment Fire
Affected Engine - Off
-
EP Initial Action: Engine FOD
Affected Engine - Off
-
EP Initial Action: ENGINE OIL PRESS
Affected Engine - Off
-
#1 Hyd System Leak - 1st Stage of Leak; Lights and location of leak.
#1RSVR LOW, #1 TAIL RTR SERVO, BACKUP PUMP ON, #2 TAIL RTR SERVO ON - Leak in hydraulic lines to T/R.
-
#1 Hyd System Leak - 2nd Stage of Leak; Lights and location of leak.
#1RSVR LOW, #1HYD PUMP, BACKUP PUMP ON - Up Stream of #1Transfer Module
-
#1 Hyd System Leak - 3rd Stage of Leak; Lights and location of leak.
#1RSVR LOW, #1HYD PUMP, BACKUP PUMP ON, BACKUP RSVR LOW - Leak in #1Primary Servos; Isolate 1st Stage: #1PRI SERVO PRESS
-
#2 Hyd System Leak - 1st Stage of Leak; Lights and location of leak.
#2RSVR LOW, BOOST SERVO OFF, SAS OFF, TRIM FAIL, FLT PATH STAB - Leak in the PAM.
-
#2 Hyd System Leak - 2nd Stage of Leak; Lights and location of leak.
#2RSVR LOW, #2HYD PUMP, FLT PATH STAB, TRIM FAIL, BACKUP PUMP ON - Leak upstream of the #2 Transfer Module
-
#2 Hyd System Leak - 3rd Stage of Leak; Lights and location of leak.
#2RSVR LOW, #2HYD PUMP, FLT PATH STAB, TRIM FAIL, BACKUP PUMP ON plus BACKUP RSVR LOW - Leak in #2Primary Servo; Isolate 2nd Stage: #2PRI SERVO PRESS
-
Lights that will turn on the Backup Pump (5)
- #1TAIL RTR SERVO
- #1HYD PUMP
- #1RSVR LOW
- #2HYD PUMP
- APU ACCUM LOW
-
#1HYD PUMP Caution Light On - If Backup Pump does not operate, both T/R servos are inop and you will have limited T/R authority. Accomplish roll on landing above _____ kts
40 kts
-
NOTE: Boost Servo Malfunction - may or may not be accompanied by
Caution Lights
-
Pitch Boost Servo Hardover - how it manifests, how to eliminate?
Approximately 20lb force felt in cyclic longitudinal; turn off SAS
-
Pedal Bind/Restriction or Drive with No Accompanying Caution Light - how it manifests, how to eliminate?
SAS/FPS Yaw malfunction can create up to 30 lbs of force at pedals. Jammed Yaw Trim actuator can take 80 lbs of force to oppose. Yaw Boost and/or Tail Rotor Servo malfunction may cause up to 250 lbs of pressure. Try shutting off Trim or Boost or switching to #2TAIL RTR SERVO.
-
Tail Rotor Quadrant Caution Light On (with Loss of T/R Control): Approximate Airspeeds for Trimmed Flight: _____ and _____
Above or below those airspeeds = ____ yaw
In between those airspeeds = ____ yaw
- 25 & 145 kts
- Right Yaw
- Left Yaw
-
With SAS/FPS computer, ______ is req'd for Turn Coord to disengage and transition to Hdg Hold
Airspeed < 60 KIAS
-
If the Ground BITE check AFCC is inadvertently initiated _____.
Do not take off for approximately 2 min to ensure FPS authority is enabled
-
Flight near high power RF emitters such as _________ may cause __________
- Microwave antennas or shipboard radar
- Uncommanded AFCS and/or Stabilator inputs
-
Warning: If _____ part of the stab check fails ______.
- Any
- Do not fly the aircraft
-
With AFCC, turn coordination will disengage and transition to heading hold when:
-Roll attitude < ___
-Roll rate < ___
-Airspeed < ___
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