FRC NORMAL Mk 21B (Initial Issue)

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FrontNormal

Intiial Issue November 2017

WTP 101C-1321B-14A

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NORMAL DRILLS

FLIGHT REFERENCE CARDS BRAZILIAN NAVY

EXTERNAL INTERNAL No 1 ENGINE START TP INITIALISATION HYDRAULIC

FCS

No 2 ENGINE START

ROTOR START

MAIN DRIVE START

ANTI-ICING

LYNX Mk 21B TAKE-OFF

Prepared and Published by Leonardo MW Ltd Yeovil, BA20 2YB England

LANDING SHUTDOWN LIMITATIONS

OPERATING DATA COMPRESSOR RINSE

Card 1

Whiteback LIST OF CARDS Card 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38

Amendment Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue

Card 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 -

Amendment Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue Initial Issue -

Card 1R

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November 2017

WTP 101C-1321B-14A

NOTES TO USERS 1. These Flight Reference Cards are complementary to the Lynx Mk 21B Aircrew Manuals (WTP 101C-1321B-15A and WTP 101C-1321B-15B) and the Operating Data Manual (WTP 101C-1321B-16A). Weapons, Avionics and Role Equipment drills are contained in WTP 101C-1321B-14B. The same conventions are used and the amendment procedure is similar 2. The Emergency Drill card tabs are coloured red or yellow according to the degree of urgency and generally follow the colour of the respective IDU Warning or Caution, with IDU Advisories coloured green 3. To reduce repetition of equipment or system identification where practical, the convention in these cards is to use an * (asterisk) where the relevant equipment or system number would be, if more than one possibility applies 4. New or amended matter of importance will be indicated by a black vertical line in the card margin opposite the change 5. Text which has been removed is denoted by  6. The convention in these cards is to differentiate between the Warnings, Cautions and Advisories, and text information displayed on the IDUs, as given in the following examples: Warning - AC ELEC FAIL Caution - [AC GEN* FAIL] Advisory - [PARK BRK ON] advisory IDU text information - OEI legend

Card 2

Whiteback

EXTERNAL CHECKS Conduct an external examination of the aircraft, particularly checking the following when conditions permit: All blanks, covers and plugs removed MASS and ESSB at SAFE Security/condition of weapons/DAS components (see Note) Starboard forward flotation bag cover secure (see Note) No 2 hydraulic reservoir level and accumulator levels Starboard side main rotor blades lower surface (see Note) Main gearbox oil level (see Note) Blade sleeve reservoir oil levels (see Note) Starboard side main rotor blades upper surface (see Note) Starboard fire access point clear (see Note) Starboard gravity fuel cap secure (see Note) Starboard fire suppression thermal discharge indicator correctly seated (see Note) Aft equipment bay fan inlet clear Tactical Processor cooling system inlet clear Starboard mainwheel aligned, lock pin in (see Note) Starboard mainwheel lock lever engaged and hydraulic hose freedom of movement (see Note) Starboard tyre condition and creep (see Note) Starboard sponson flotation bag cover secure (see Note) SDR - KSU and iMMM inserted Refuel/defuel switch at OFF and panel cover secure HF antenna condition Security of IGB cooling fan Security of tail plane Condition and alignment of tail rotor blades Intermediate and tail gearbox oil levels Rear avionics bay door secure and handle pin IN External 28 volts DC connected and OFF Security of CPI beacon Ancillary services hydraulic accumulator pressure and No 1 hydraulic reservoir level correct Nosewheel aligned, lock pin in and lock levers engaged Condition of tyres and creep Insert DASc USB as required Note: Applicable to the opposite side of the aircraft

Card 2R

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WTP 101C-1321B-14A

Card 3

INTERNAL CHECKS Harnesses

. . . . . . . . . . . . . . Strap in, adjust Check inertia release Seats . . . . . . . . . . . . . . . . . . Adjusted and positively locked, handle stowed Yaw pedals . . . . . . . . . . . . . . Fore-and-aft position adjusted, leave fully offset Wheel locks . . . . . . . . . . . . . IN Instrument lighting . . . . . . . . DAY or NIGHT DC busbar coupling: External start . . . . . . . . . . MANUAL Battery start . . . . . . . . . . . DIS Fuel jettison . . . . . . . . . . . . . SHUT No 1 and No 2 EMSS . . . . . . OFF External power . . . . . . . . . . . Connect (see Note) Battery master . . . . . . . . . . . ON: indicator yellow (green for battery start) MWAGs and MCAGs . . . . . . CANCEL DC busbar coupling indicators: External start . . . . . . . . . . GEN BUS 1 green GEN BUS 2 green Battery start . . . . . . . . . . . GEN BUS 1 yellow GEN BUS 2 yellow Fuel jettison indicators . . . . . Both black Cockpit and instrument lighting . . . . . . . . . . . . . . . . As required Telebrief . . . . . . . . . . . . . . . . Check indicator, as required Note: Where available, ground power should be used. When starting on the internal battery, consider leaving non-essential electrics off until the engine is running

continued

EXTERNAL INTERNAL

Whiteback continued Overhead Console Hoist DC Gen failure override switch . . . . . . . . . . Data erase button . . . . . . . . . Standby compass light . . . . . Anti-coll light . . . . . . . . . . . . . Nav lights . . . . . . . . . . . . . . . Rad Alt switch . . . . . . . . . . . . Instrument cooling fan . . . . . Tactical processor switch . . . Pitot heat . . . . . . . . . . . . . . .

Windscreen heating . . . . . . . Engine anti-icing . . . . . . . . . . IGI switch . . . . . . . . . . . . . . . Alternators . . . . . . . . . . . . . .

Generators

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Transfer pumps

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Booster pumps

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Fuel crossfeed . . . . . . . . . . . LP cocks . . . . . . . . . . . . . . . . Fire warning

.............

Cover closed Cover closed As required OFF As required FLT MAN: check operation of fan, set AUTO ON OFF or if icing conditions likely: ON, check E2C heading indication deviates, OFF Both OFF Both OFF ON Both ON: both indicators yellow BUS 1/2 indicator green BUS 1A indicator yellow BUS 2A indicator green Both ON: both indicators yellow Both AUTO: both indicators black Both ON: both indicators green (see Note, Card 3) SHUT: indicator black Both OPEN: both indicators green TEST: ENG 1 & 2 - FIRE button indicators illuminate BOTT 1 & 2 indicators LOW No 1 & No 2 EMSS fire indicators illuminate ENGBAY1 FIRE and ENGBAY2 FIRE displayed "FIRE ENGINE" voice warning continued

Card 3R

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WTP 101C-1321B-14A

Card 4

continued Fire extinguisher crossfeed . . . . . . . . . . . . . . NORMAL ACC/MAIN Drive switch . . . . ACC: yellow ACC indication, [ENG1 ACC] displayed Starter master . . . . . . . . . . . ON ECS . . . . . . . . . . . . . . . . . . . OFF ECU channel buttons . . . . . . Press each button twice in turn, check each changes to standby channel and back HYD P-3 . . . . . . . . . . . . . . . . Check > 80 bar (see Note) Rotor brake . . . . . . . . . . . . . PARK: PARK indicator illuminated. [RTR BRK ON] displayed Ground servicing panel . . . . All switches ON/FLT Standby compass . . . . . . . . . Note heading, check correction card current Note: If HYD P-3 pressure is below operating limits, the rotor brake should be recycled from OFF to PARK after, either recharging with the handpump or after starting No 1 engine in ACC drive Port Side Door jettison handle . . . . . . . Secure and wire locked OAT gauge . . . . . . . . . . . . . . Note temperature Harpoon engaged light . . . . . Test Co-pilot’s Instrument Panel Clock . . . . . . . . . . . . . . . . . . ADF transponder . . . . . . . . . SFI . . . . . . . . . . . . . . . . . . . . IDUs . . . . . . . . . . . . . . . . . . . Radar control unit . . . . . . . . .

Set Condition Condition Condition, set as required Condition continued

INTERNAL cont’d

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continued Centre Panel CRNU . . . . . . . . . . . . . . . . . . Heavy stores panel: RELEASE switch . . . . . . . PORT SELECT switch . . . FUZING switch . . . . . . . . . . STBD SELECT switch . . . CIG: Arming switch . . . . . . . . . . Skim height selector . . . . . ‘Armed Aircraft’ notice . . . . IFF SEL button . . . . . . . . . . . CDS control: BARO button . . . . . . . . . . . PIC button . . . . . . . . . . . . . CWS button . . . . . . . . . . . .

ON (see Note, Card 5) Cover closed Cover closed OFF Cover closed SAFE OFF Removed Condition

As required As required Select (see Note) WARN TEST1 WARN TEST2 [CAUT TEST1] [CAUT TEST2] displayed voice “CWS TEST” in Normal and REV Both MWAGs/MCAGs flashing. Cancel CDS button . . . . . . . . . . . . Select, green XFR caption illuminated IDU 3 and IDU 4 transfer Deselect, green XFR caption extinguished IDU 3 and IDU 4 revert positions Note: Where an internal battery start is to be carried out, the test is inoperative until DC Gen services power is available. The CWS test should be conducted after the first engine is started

continued Card 4R

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WTP 101C-1321B-14A

continued DAS control panel: DISPENSE button . . . . . . . LATE ARM flap . . . . . . . . . CM switch . . . . . . . . . . . . . CMDS switch . . . . . . . . . . . RWR switch . . . . . . . . . . . . DASc switch . . . . . . . . . . . Clock . . . . . . . . . . . . . . . . . . SFI . . . . . . . . . . . . . . . . . . . .

Card 5

Condition Lowered As required OFF OFF OFF Set Condition, set as required

Note: The CRNU is not available when using internal battery power Pilot’s Instrument Panel Nav mode selector . . . . . . . . As required Jettison mode select . . . . . . OFF IDUs . . . . . . . . . . . . . . . . . . . Condition, set as required Starboard Side ESSB . . . . . . . . . . . . . . . . . . SAFE: Covered Door jettison handle . . . . . . . Secure and wire locked Centre Console MASS . . . . . . . . . . . . . . . . . . ARM BUS A & B MIs . . . . . . Windscreen wash . . . . . . . . . Windscreen wipers . . . . . . . . Nosewheel . . . . . . . . . . . . . . Wheel locks . . . . . . . . . . . . . Cyclic trim master . . . . . . . . . Hoist master . . . . . . . . . . . . . Cargo master . . . . . . . . . . . . Harpoon master . . . . . . . . . . D/Ident light . . . . . . . . . . . . . Telebrief . . . . . . . . . . . . . . . .

SAFE Black OFF SLOW and OFF FLIGHT: indicator green IN ON OFF OFF OFF OFF As required continued

INTERNAL cont’d

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continued Doppler . . . . . . . . . . . . . . . . . FLIR .................. DME . . . . . . . . . . . . . . . . . . . V/UHF . . . . . . . . . . . . . . . . . Co-pilot’s station box . . . . . . Co-pilot’s audio selector . . . . Radar joystick . . . . . . . . . . . . Cursor control device . . . . . . Test controller . . . . . . . . . . .

CPI . . . . . . . . . . . . . . . . . . . . Dimming . . . . . . . . . . . . . . . . RNS252 computer . . . . . . . . I-Band transponder . . . . . . . Pilot’s station box . . . . . . . . . Pilot’s audio selector . . . . . . Radio switch box . . . . . . . . . HF . . . . . . . . . . . . . . . . . . . . FCS controller . . . . . . . . . . .

Compass controller . . . . . . . OEI training mode . . . . . . . .

OFF OFF OFF As required As required As required Condition/as required Condition/as required DEMAND and PITCH/ ROLL check P and R indicated Dimmer as required Captions extinguished As required As required OFF As required As required As required SBY Lane light switch ON Dimmer as required Trim wheels neutral SLAVED, variation set Both NORM

Flying Controls Collective lever . . . . . . . . . . . MPOG, friction set Landing light off Jettison button covered Servo selector central Cyclic stick . . . . . . . . . . . . . . WPN guard lowered HOOK guard lowered

Card 5R

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WTP 101C-1321B-14A

Card 6

ENGINE STARTING CAUTION 1: Abort the start immediately if: Ng does not reach 10% in 10 seconds Light up is not achieved within 15 seconds of IGN legend displayed PTIT cockpit indication exceeds 950°C Ng stops increasing prior to idle RPM Any unusual noise or vibration occurs ECU system failure or degrade occurs CAUTION 2: ENG 1 and ENG 2 EMSS must be moved between OFF/GI/FLY in less than 1 second, or the engine may accelerate to Flight Idle CAUTION 3: If light up is not achieved within 15 seconds of IGN legend being displayed, wait 3 minutes between attempts to start and/or vent runs (2 minutes if first start of the day). After 3 starter operations, a period of 30 minutes must elapse before another attempt to start or vent run is made on that engine CAUTION 4: If [BATT HOT] is displayed, the battery must be selected OFF immediately and no further battery starts attempted until it has cooled CAUTION 5: Following an internal battery start, there may be a momentary rapid rise of PTIT on completion of the start sequence as the engine stabilises at GI CAUTION 6: When starting Engine 1 in ACC Drive, particular attention must be paid to Np and hydraulic indications. If Np and both HYD 1/HYD 2 systems pressure fail to rise during the start, the aircraft must be shutdown immediately and the fault investigated CAUTION 7: The Np shaft has an avoid band between 29% and 50% Np. If Np does not accelerate through this band, the engine must be shutdown immediately CAUTION 8: The probability of a hot start is increased in OATs of 0°C or less, and the reliability of engine starting using the internal battery is significantly reduced continued

No 1 ENGINE

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continued Note 1: During high ambient temperature operations care must be taken not to allow [BATT HOT] to display. As an approximation, each start will increase the battery temperature by 5°C Note 2: Following a pilot or ECU aborted start, a vent run should be considered. When the aborted start takes place prior to engine light up or if in any doubt, a vent run is to be carried out Note 3: Sufficient fuel pressure can remain in the HMU for some time after engine shutdown. As a result, [FUEL* PRESS] may not be displayed if restarting a recently run engine Note 4: The starter relay will automatically disengage when Ng exceeds 50% or if engine start-up is not complete within 30 seconds Note 5: The ECU should automatically abort an engine start prior to the displayed cockpit PTIT start limit being exceeded STARTING No 1 ENGINE (In Accessory Drive) Nav lights . . . . . . . . . . . . . . . ENG 1 EMSS . . . . . . . . . . . . IDU - SMD . . . . . . . . . . . . . . Ng . . . . . . . . . . . . . . . . . . . . .

As required GI, start clock START legend displayed Rising (10% within 10 seconds) IDU - SMD . . . . . . . . . . . . . . IGN legend displayed PTIT . . . . . . . . . . . . . . . . . . . Rising within 15 seconds of IGN legend displayed (950°C max) - stabilised EOP/RGBOP . . . . . . . . . . . . Rising

continued Card 6R

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WTP 101C-1321B-14A

Card 7

continued After Starting Checks, No 1 Engine CAUTION 1: When running in ACC Drive on sloping ground/embarked operations with a rolling deck, [MGB LOPRESS] or MGB LOPRESS may display. Continued operation in ACC Drive is permissible provided that a MGBOP of at least 1.0 bar is indicated on the IDU. If normal MGBOP limits are not re-established following rotor engagement, shutdown and have the fault investigated CAUTION 2: If either alternator does not come on-line with No 1 EMSS at FLY, select OFF/RESET, shutdown and have the fault investigated Ng . . . . . . . . . . . . . . . . . . . . . 58% to 66.5% at GI Np . . . . . . . . . . . . . . . . . . . . . Approx 90% EOP . . . . . . . . . . . . . . . . . . . Above 1.4 bar (within 60 seconds) RGBOP . . . . . . . . . . . . . . . . Within limits ENG 1 EMSS . . . . . . . . . . . . FLY Np . . . . . . . . . . . . . . . . . . . . . 104% MGBOP . . . . . . . . . . . . . . . . Within limits HYD 1, 2 and 3 pressures . . Within limits Cyclic stick . . . . . . . . . . . . . . MPOG min stress position Collective lever . . . . . . . . . . . MPOG External DC (if connected) . . Disconnect IDU Warning/Caution/Advisory alerts remaining . . . . . . . . . ENG2 LOPRESS [RTR BRK ON] [DC2 FAIL] [FUEL2 PRESS] (see Note 3, Card 6R) [ENG1 ACC] [PARK BRK ON] advisory continued

No 1 ENGINE cont’d

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continued Both alternator indicators . . . BUS 1/2 coupling indicator . . BUS 1A and BUS 2A indicators . . . . . . . . . . . . . . No 1 generator indicator . . . . No 2 generator indicator . . . . DC busbar coupling . . . . . . . DC busbar coupling indicators . . . . . . . . . . . . . . Battery indicator . . . . . . . . . . Transfer pumps . . . . . . . . . . ECS . . . . . . . . . . . . . . . . . . . RADAR . . . . . . . . . . . . . . . . . IFF . . . . . . . . . . . . . . . . . . . . Engine anti-icing . . . . . . . . . .

Green Black Green Green Yellow MANUAL GEN BUS 1 green GEN BUS 2 green Green Test in MANUAL As required ON ON No 1 as required. If required complete Anti-Icing Systems Check (Card 15)

After Battery Start Booster pumps . . . . . . . . . . Both ON: both indicators green Mission systems . . . . . . . . . . Initialise iaw WARE cards

Card 7R

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WTP 101C-1321B-14A

Card 8

TP/IGI INITIALISATION IDU - TAC dedicated key . . Select, TAC view displays Select WARM ST/COLD ST as required (see Note 1) . . . . ‘In Progress’ Note 1: WARM start is when info from the iMMM is used (routes, overlays etc). Pressing COLD Start loads up Tactical Processor defaults Cold Start: SELECT TAIL NUMBER

. . Select as required, ‘CONFIRM’ TIME & DATE . . . . . . . . . . Enter if required NEXT . . . . . . . . . . . . . . . . . Select POSN & ENVIRON . . . . . . Enter if required NEXT . . . . . . . . . . . . . . . . . Select, ‘STARTUP COMPLETE’ displays IDU - TAC dedicated key . . . . . . . . . Select, Default map 1 displays, IGI status is displayed on toolbar (see Note 2 and Note 3) Warm Start: IDU - TAC View

IDU - TAC dedicated key

. . . . . . . . . Select ‘WARM ST’, ‘STARTUP COMPLETE’ displays . . . . . . . . . Select, Default map 1 displays, IGI status is displayed on toolbar (see Note 2 and Note 3)

Note 2: Detailed IGI status is available via the IDU - TOTE view and selecting the IGI tab Note 3: Subsequent IGI alignment is controlled via the IDU - TAC and TOTE view and selecting the IGI top level softkey

TP/IGI INITIALISE

IntentBlank

Note 3: Subsequent IGI alignment is controlled via the IDU - TAC and TOTE view and selecting the IGI top level softkey

Intentionally Blank

Card 8R

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WTP 101C-1321B-14A

Card 9

HYDRAULIC CHECKS WARNING 1: If the Yaw pedals move fully left or fully right, do not attempt to centralise until HYD 1 is recovered WARNING 2: If when reselecting No 2 system, the HYD P-2 pressure momentarily falls in or below the yellow band, a minimum 2 cycles of full and free cyclic and collective movements are to be conducted with both HYD P-1 and P-2 stabilised in the green band before any other system is deselected or flight is allowed Note 1: If either system is selected off, pressure in that system may reach 165 bar, this is acceptable Note 2: Check that with the application of friction, the force required to move the collective lever increases but remains equal and continuous over the whole range, without any binding Cyclic, collective and yaw controls . . . . . . . . . . . . . Full and free movement, centralise yaw pedals Servo selector . . . . . . . . . . . 1: [HYD1 LOPRESS] displayed (see WARNING 1) Cyclic and collective . . . . . . Make small movements check interlinks and blade response Servo selector . . . . . . . . . . . 2: [HYD2 LOPRESS] displayed, [HYD1 LOPRESS] clear Cyclic, collective and yaw controls . . . . . . . . . . . . Full and free movement (without trimming) Check interlinks and blade response. Check HYD P-1 display small fluctuations, but remains in the green band Servo selector . . . . . . . . . . . Centralise: [HYD2 LOPRESS] clear (see WARNING 2) Cyclic trim master . . . . . . . . . OFF: check stick free using minimum movement, ON Cyclic stick . . . . . . . . . . . . . . Check trim operation, MPOG min stress position

HYDRAULICS

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FCS CHECKS IN ACC DRIVE Note 1: Full FCS checks should be completed prior to the initial flight of the day Note 2: If dual controls are fitted, the co-pilot’s yaw pedal microswitches, collective and cyclic release (including CAC CUTOUT) should be checked in a similar manner to the pilot’s controls Basic Checks Note: When engaging yaw or collective autopilot modes, care should be taken to ensure that there is no associated control movement at the time of engagement in order to minimise the possibility of inadvertent parallel actuator electromagnetic clutch lock-on Rad Alt

Compass

...............

Main attitude displays . . . . . . FCS controller . . . . . . . . . . . Test controller . . . . . . . . . . .

FCS controller

...........

Test (100 ±10 ft) Confirm correct operation of LHWS, FLT SLAVED, synchronised, variation set Warning flags clear Set trim wheels to zero Select DEMAND and PITCH/ROLL, MIs show P and R, trim cyclic to zero null indicators. Reselect POSITION Press ASE, PITCH, ROLL and YAW lanes 1 and 2 lights on. Press PITCH and ROLL lane 2, lights out

Cyclic stick and FCS controller . . . . . . . . . . . . . . Exercise cyclic stick and trim wheels, null indicators follow. Maximum mismatch ¼ division Leave trim wheels set at zero continued

Card 9R

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WTP 101C-1321B-14A

Card 10

continued FCS controller

. . . . . . . . . . . Press ASE, PITCH, ROLL and YAW lanes 1 and 2 lights on. Press PITCH and ROLL lane 1, lights out Cyclic stick and FCS controller . . . . . . . . . . . . . . Exercise cyclic stick and trim wheels, null indicators follow. Maximum mismatch ¼ division Leave trim wheels set at zero. Press ASE, PITCH, ROLL and YAW lanes 1 and 2 lights on Test controller . . . . . . . . . . . Select YAW/COLL, MIs show Y and C FCS controller . . . . . . . . . . . Rotate HDG TRIM. Null indicators and yaw pedals move after ¾ division in correct sense with feet off pedals. Maximum mismatch ¼ division twin or single lane Yaw pedals . . . . . . . . . . . . . . Check operation of pedal microswitches in turn With feet on the pedals, null indicators and pedals do not respond to heading trim changes. Exercise pedals - null indicators stationary. Feet on, but avoid microswitch activation. Ensure yaw parallel actuator (Heading Hold Engaged) can be overridden by cycling pedals twice from stop to stop without undue force (within approx 23 kg) continued

FCS

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continued FCS controller

. . . . . . . . . . . Press COLL 1 and 2, lights on. Exercise collective lever, null indicators do not move FCS controller . . . . . . . . . . . Press BAR ALT, light on Collective lever . . . . . . . . . . . Check parallel actuator can be overridden FCS controller . . . . . . . . . . . Press RAD ALT to confirm BAR/RAD ALT inhibit Collective lever . . . . . . . . . . . Press Col Rel - BAR ALT light out. Check collective lever is free Ground servicing panel . . . . Set ADU-FLT/TEST switch to TEST Collective lever . . . . . . . . . . . Set collective lever mid travel FCS controller . . . . . . . . . . . Press BAR ALT, light on and collective lever moves down Ground servicing panel . . . . Set ADU-FLT/TEST switch to FLT, collective lever continues to move down Collective lever . . . . . . . . . . . Press Col Rel - BAR ALT light out. Collective lever stops and is free, set collective lever mid travel FCS controller . . . . . . . . . . . Press RAD ALT, light on, resistance to collective lever movement (collective lever may move up in small steps) Rad Alt . . . . . . . . . . . . . . . . . Test, confirm Rad Alt Test facility inhibited with height hold engaged

continued

Card 10R

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November 2017

WTP 101C-1321B-14A

continued Collective lever . . . . . . . . . . . Press Col Rel - RAD ALT light out. Collective lever is free Cyclic stick . . . . . . . . . . . . . . Press AFCS CUTOUT, PITCH, ROLL, YAW lanes 1 and 2 lights out, null indicators centre. Press and hold CAC CUTOUT, COLL 1 and 2 lights out, release lights on FCS controller . . . . . . . . . . . Press COLL 1 and 2, lights out Test controller . . . . . . . . . . . Select PITCH/ROLL, MIs show P and R PRPS Checks Test controller . . . . . . . . . . . Select DEMAND and PITCH/ROLL, MIs show P and R Cyclic stick . . . . . . . . . . . . . . Use cyclic stick trim to null pitch and roll indicators Displace cyclic stick forward against spring feel and hold at 1 division forward offset FCS controller . . . . . . . . . . . Press ASE, ROLL and YAW lanes 1 and 2 lights on with PITCH 1 and 2 lanes lights momentarily on, [AFCS] displays Test controller . . . . . . . . . . . Select POSITION, pitch indicators null FCS controller . . . . . . . . . . . Press PITCH lane 1, [AFCS] remains displayed. Press PITCH lane 2, [AFCS] clears Test controller . . . . . . . . . . . Select DEMAND Cyclic stick . . . . . . . . . . . . . . Release cyclic stick, indicators null continued

Card 11

FCS cont’d

Whiteback

continued FCS controller

. . . . . . . . . . . Press ASE, pitch lanes 1 and 2 lights on Test controller . . . . . . . . . . . Select POSITION, pitch indicators null. Repeat above checks and press PITCH lane 2 before PITCH lane 1 Cyclic stick . . . . . . . . . . . . . . Press AFCS CUTOUT, PITCH, ROLL, YAW lanes 1 and 2 lights out, indicators null FCS Checks in Main Drive Limit FCS checks to engagement and disengagement of ASE and COLL 1 and 2 only. Do not engage height holds

Card 11R

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WTP 101C-1321B-14A

Card 12

STARTING No 2 ENGINE CAUTION 1: With the rotor brake at PARK, if No 2 Np starts to indicate during the start cycle with the rotors stopped, select ENG 2 EMSS to OFF immediately, shutdown and have the fault investigated. If the rotor starts to turn, the rotor brake may be selected OFF if safe to do so or shutdown No 2 Engine CAUTION 2: The maximum continuous duration for operating No 2 Engine at GI with the rotor brake at PARK is 10 minutes Nav lights . . . . . . . . . . . . . . . As required Rotor brake . . . . . . . . . . . . . PARK, indicator illuminated [RTR BRK ON] displayed ENG 2 EMSS . . . . . . . . . . . . GI, start clock IDU - SMD . . . . . . . . . . . . . . START legend displayed Ng . . . . . . . . . . . . . . . . . . . . . Rising (10% within 10 seconds) IDU - SMD . . . . . . . . . . . . . . IGN legend displayed PTIT . . . . . . . . . . . . . . . . . . . Rising within 15 seconds of IGN legend displayed (950°C max) stabilised Np . . . . . . . . . . . . . . . . . . . . . Not indicating (see CAUTION 1) EOP/RGBOP . . . . . . . . . . . . Rising

continued

No 2 ENGINE

Whiteback continued AFTER STARTING CHECKS, No 2 ENGINE Ng . . . . . . . . . . . . . . . . . . . . . 58% to 66.5% at GI (approx 70% if rotor brake released) EOP . . . . . . . . . . . . . . . . . . . Above 1.4 bar (within 60 seconds) RGBOP . . . . . . . . . . . . . . . . Within limits IDU Caution alerts: Clear . . . . . . . . . . . . . . . . . [ENG2 HIACCEL] (see Note) Remaining . . . . . . . . . . . . . [RTR BRK ON] [ENG1 ACC] No 2 generator indicator . . . . Green DC busbar coupling . . . . . . . AUTO Engine anti-icing . . . . . . . . . . No 2 as required. If required complete Anti-Icing Systems Check (Card 15) Note: If [ENG2 HIACCEL] remains with collective lever at MPOG, do not select ENG 2 EMSS to fly, shutdown and have the fault investigated

Card 12R

C08White

November 2017

WTP 101C-1321B-14A

Card 13

PRE-ROTOR STARTING CHECKS Wind . . . . . . . . . . . . . . . . . . . Maximum 50 knots. If above 30 knots a/c to be within 45° of wind Rotor area . . . . . . . . . . . . . . Clear ASE and CAC . . . . . . . . . . . Disengaged, lights out Collective lever . . . . . . . . . . . MPOG: friction on Cyclic stick . . . . . . . . . . . . . . MPOG min stress position Yaw pedals . . . . . . . . . . . . . . Central Harnesses . . . . . . . . . . . . . . Locked and tight Doors . . . . . . . . . . . . . . . . . . Secure Anti-coll light . . . . . . . . . . . . . ON

ROTOR STARTING CAUTION: Before selecting MAIN or ACC Drive the engines must be both running or both stopped. If both engines are running, the ENG 1 EMSS must be at GI and the ENG 2 EMSS at FLY with Np/NR at 104% and with a minimum 3% Np split Note 1: If [RTR BRK ON] does not clear within approximately 2 seconds, shutdown No 2 engine and when the rotors have stopped, reselect rotor brake to PARK then OFF. Check [ROTOR BRAKE] clears, reselect PARK. If indications are normal No 2 engine can be restarted and the rotor engaged Note 2: If aircraft is cold soaked below 0°C, run in ACC Drive until TOP starts to rise and TOT is above minus 10°C, then start the rotor, select MAIN Drive and run at MPOG for at least 3 minutes. Collective can then be applied when TOP is between 2.3 bar and 7.0 bar. If the aircraft is not cold soaked, run in ACC Drive until TOP starts to rise. The rotor can then be started, MAIN Drive selected and collective applied when TOP is between 2.3 bar and 7.0 bar. A normally operating gearbox, warmed and at a stabilised temperature should have an oil pressure above 2.5 bar continued

ROTOR START

Whiteback

continued Rotor brake

. . . . . . . . . . . . . OFF: PARK indicator extinguished (see Note 1, Card 13) CHK RTR BRK and [RTR BRK ON] clear NR and No 2 Np . . . . . . . . . . Increasing Rotor overspeed test tone . . On at 60% NR Off above 70% NR No 2 EMSS . . . . . . . . . . . . . FLY NR . . . . . . . . . . . . . . . . . . . . . 104% No 1 EMSS . . . . . . . . . . . . . GI ACC/MAIN Drive switch . . . . With No 2 Np/NR at 104% and with a minimum 3% Np split, select MAIN Drive, green MAIN caption illuminated [ENG1 ACC] clear ENG 1 EMSS . . . . . . . . . . . . FLY ENG 2 EMSS . . . . . . . . . . . . GI, check freewheel (Np split) ENG 2 EMSS . . . . . . . . . . . . FLY WCA . . . . . . . . . . . . . . . . . . . Clear/as appropriate

Card 13R

C09White

November 2017

WTP 101C-1321B-14A

Card 14

ENGINE STARTING IN MAIN DRIVE CAUTION 1: As there will be no MGB warming up period when starting in MAIN Drive, the engine should not be started if the TOT is below minus 10°C CAUTION 2: The rotor brake is designed to hold one engine only driving the rotor system at GI Internal Checks Complete normal Internal Checks except for: ACC/MAIN Drive switch . . MAIN: green MAIN illuminated, [ENG1 ACC] clear Engine Starting Complete normal Engine Starting checks (either engine can be started first, but only one engine can be held against the rotor brake). If Np indicates without NR indication, shutdown the engine immediately After Starting First Engine Checks Complete normal After Starting checks as far as possible Note: TOP, HYD pressure and AC power will not be available. Control checks and FCS checks cannot be made Pre-Rotor Starting Checks Complete normal Pre-Rotor Starting checks WARNING: As soon as hydraulic pressure is available, the yaw pedals must be centralised and the cyclic stick and collective lever must be set to the minimum stress position (ref: sight marks) and MPOG position respectively Rotor Starting Checks Complete normal Rotor Starting appropriate EMSS up to and including: NR . . . . . . . . . . . . . . . . . . 104%

checks

using

Note: TOP and HYD pressure become available shortly after the rotor commences turning; AC power becomes available at 90% NR continued

MAIN DRIVE

Whiteback

continued After Rotor Starting Checks Check TOP, TOT and HYD pressures within limits Check appropriate generator indicator green, associated busbar coupling indicator green and both alternator indicators green WCA . . . . . . . . . . . . . . . . . . . Clear/as appropriate Subsequent Starting of Second Engine Start the second engine using the normal Starting No 2 Engine and After Starting checks except that Np should indicate after starting. Then: EMSS . . . . . . . . . . . . . . . . FLY Complete FCS Checks In Main Drive

Card 14R

C10White

November 2017

WTP 101C-1321B-14A

Card 15

ANTI-ICING SYSTEMS CHECK CAUTION: To prevent potential damage to the engine air intake heater mats, time spent on the ground running with the rotors stopped and engine anti-icing systems selected ON should be minimised No 1 engine anti-icing

. . . . . TEST

Check the following IDU alerts display for 5 seconds: [INTK1 A/ICE] [INTK2 A/ICE] [INTK1 LOTEMP] [INTK2 LOTEMP] [D/ICE1 FAIL] [D/ICE2 FAIL] No 1 engine anti-icing . . . . . ON PTIT . . . . . . . . . . . . . . . . . . . Rises Ensure: [ANTI-ICE1] advisory displayed [ENG1 A/ICE] clear [INTK1 A/ICE] clear [INTK1 LOTEMP] clear [D/ICE1 FAIL] clear Repeat checks for No 2 Engine Windscreen heating . . . . . . . Both ON PORT O/HEAT TEST switch . . . . . . . . . . . . . . . . NO 1, [L/H SCRN HOT] PORT yellow FAIL caption illuminated NO 2, [L/H SCRN HOT] PORT yellow FAIL caption illuminated Repeat checks for R/H windscreen Windscreen heating

. . . . . . As required

ANTI-ICING

Whiteback

TAKE-OFF CHECKS Before Initial Take-Off OAT . . . . . . . . . . . . . . . . . . . Note PFD and SFIs . . . . . . . . . . . . Set, cross checked and VW as required Pitot heat . . . . . . . . . . . . . . . As required Radar . . . . . . . . . . . . . . . . . . As required Screen heat . . . . . . . . . . . . . As required Engine anti-icing . . . . . . . . . . As required STARTER MASTER switch . . . . . . . . . . . . . . . . . ON MAIN drive . . . . . . . . . . . . . . Selected, green MAIN caption illuminated, [ENG1 ACC] clear ENG 1 and ENG 2 EMSS . . FLY IDU - SMD . . . . . . . . . . . . . . Checked/set as required WARE systems . . . . . . . . . . Checked/set as required EOS . . . . . . . . . . . . . . . . . . . STOW SDU ground safety pin . . . . . Removed, stowed MASS . . . . . . . . . . . . . . . . . . As required Jettison mode select . . . . . . As required Fuel . . . . . . . . . . . . . . . . . . . Contents, balanced ESSB . . . . . . . . . . . . . . . . . . LIVE Nosewheel . . . . . . . . . . . . . . FLIGHT, MI arrow forward Wheel locks . . . . . . . . . . . . . As required Harpoon master . . . . . . . . . . As required FCS . . . . . . . . . . . . . . . . . . . Select DEMAND and PITCH/ROLL, Check nulled, Engage ASE, Engage COLL 1 and 2, Select POSITION, trim null Doors . . . . . . . . . . . . . . . . . . Secure Harnesses . . . . . . . . . . . . . . Locked and tight Collective lever . . . . . . . . . . . Friction set continued

Card 15R

C11Yellow

November 2017

WTP 101C-1321B-14A

Card 16

continued After Take-Off TRQ . . . . . . . . . . . . . . . . . . . Within limits Wheel locks . . . . . . . . . . . . . As required Temps and pressures . . . . . Within limits Airborne Checks Compass

. . . . . . . . . . . . . . . Check synchronised, with Heading Hold engaged RNS 252 . . . . . . . . . . . . . . . . As required Radar . . . . . . . . . . . . . . . . . . As required IFF . . . . . . . . . . . . . . . . . . . . As required Radios . . . . . . . . . . . . . . . . . As required VOR . . . . . . . . . . . . . . . . . . . As required I-Band transponder . . . . . . . As required DAS . . . . . . . . . . . . . . . . . . . Checked/set as required EOS . . . . . . . . . . . . . . . . . . . As required Before Subsequent Take-Off WCA . . . . . . . . . . . . . . . . . . . Clear/as appropriate PFD and SFIs . . . . . . . . . . . . Set, cross checked and VW as required Fuel . . . . . . . . . . . . . . . . . . . Contents, balanced ESSB . . . . . . . . . . . . . . . . . . LIVE Nosewheel . . . . . . . . . . . . . . FLIGHT: indicator green Wheel locks . . . . . . . . . . . . . As required FCS . . . . . . . . . . . . . . . . . . . Select DEMAND and PITCH/ROLL, Check nulled, Engage ASE, Engage COLL 1 and 2, Select POSITION, trim null Doors . . . . . . . . . . . . . . . . . . Secure Harnesses . . . . . . . . . . . . . . Locked and tight

TAKE-OFF

IntentBlank

Intentionally Blank

Card 16R

C12Yellow

November 2017

WTP 101C-1321B-14A

Card 17

LANDING CHECKS Before Landing HF . . . . . . . . . . . . . . . . . . . . IFF . . . . . . . . . . . . . . . . . . . . Radar . . . . . . . . . . . . . . . . . . EOS . . . . . . . . . . . . . . . . . . . DAS switches . . . . . . . . . . . . Wheel locks . . . . . . . . . . . . . Nosewheel . . . . . . . . . . . . . . Harpoon master . . . . . . . . . . Fuel system . . . . . . . . . . . . .

SBY As required TX OFF STOW As required As required FLIGHT: indicator green As required Configured as required, contents Air bleeds . . . . . . . . . . . . . . . As required Harnesses . . . . . . . . . . . . . . Locked and tight Rad Alt low height warning . . Set After Landing

Collective lever . . . . . . . . . . . MPOG (or negative pitch as required), then friction applied Cyclic stick . . . . . . . . . . . . . . Position with reference to sight marks Harpoon . . . . . . . . . . . . . . . . As required Cyclic stick . . . . . . . . . . . . . . Press AFCS CUTOUT FCS controller . . . . . . . . . . . Disengage COLL 1 and 2, lights out MASS . . . . . . . . . . . . . . . . . . SAFE Jettison mode select . . . . . . OFF ESSB . . . . . . . . . . . . . . . . . . SAFE Harpoon master . . . . . . . . . . OFF Wheel locks . . . . . . . . . . . . . As required Nosewheel . . . . . . . . . . . . . . As required (see WARNING) WARNING: It is essential to select the wheel locks to OUT before the nosewheel is selected to CASTOR Note: Co-pilot to start stopwatch as soon as possible after landing

LANDING SHUTDOWN

Whiteback

PRE-SHUTDOWN CHECKS Note: If the No 2 engine is to be restarted, the following checks should be omitted from the Pre-Shutdown Checks: Booster pumps, Fire warning, ECS, IFF, RADAR, EOS, IGI and RNS 252 TP . . . . . . . . . . . . . . . . . . . . . Soft shutdown using IDU - TAC view softkeys Pitot heat . . . . . . . . . . . . . . . OFF Windscreen heating . . . . . . . Both OFF Engine anti-icing . . . . . . . . . . Both OFF Booster pumps . . . . . . . . . . . Both OFF (see Note) Fire warning . . . . . . . . . . . . . TEST: ENG 1 & 2 - FIRE button indicators illuminate BOTT 1 & 2 indicators LOW No 1 & No 2 EMSS fire indicators illuminate ENGBAY1 FIRE and ENGBAY2 FIRE displayed "FIRE ENGINE" voice warning ECS . . . . . . . . . . . . . . . . . . . OFF (see Note) IFF . . . . . . . . . . . . . . . . . . . . OFF (see Note) RADAR . . . . . . . . . . . . . . . . OFF (see Note) EOS . . . . . . . . . . . . . . . . . . . OFF (see Note) IGI . . . . . . . . . . . . . . . . . . . . OFF (see Note) RNS 252 . . . . . . . . . . . . . . . OFF (see Note) DAS switches . . . . . . . . . . . . As required

Card 17R

C12White

November 2017

WTP 101C-1321B-14A

Card 18

SHUTDOWN CHECKS WARNING: Monitor PTIT on shutdown for signs of an internal engine fire. If PTIT is high or rising markedly, complete the After Engine Shutdown Internal Fire drill (Card 39) CAUTION 1: The engines must be in a stabilised condition for a minimum of 2 minutes at FLY or GI before selecting the EMSS to OFF. If the engines are stabilised at FLY, then a further 10 second period at GI must be held before selecting the EMSS to OFF CAUTION 2: ENG 1 and ENG 2 EMSS must be moved between OFF/GI/FLY in less than 1 second, or the engine may accelerate to Flight Idle CAUTION 3: When running in ACC Drive on sloping ground/embarked operations with a rolling deck [MGB LOPRESS] or MGB LOPRESS may display. Continued operation in ACC Drive is permissible provided that a MGBOP of at least 1.0 bar is indicated CAUTION 4: Possible damage can be caused to the engine HMU if the LP1 and LP2 cocks are shut before selecting the EMSS to OFF. To prevent possible damage, EMSS must be selected to OFF before LP1 and LP2 cocks are shut Note: ENG 1 EMSS may remain at GI if No 1 engine is to be subsequently shutdown. Should full ACC Drive services be required, ENG 1 EMSS must be selected to FLY SHUTDOWN IN ACCESSORY DRIVE After 2 minutes at MPOG (see CAUTION 1): ENG 1 EMSS . . . . . . . . . . . . GI (see CAUTION 2) ACC/MAIN Drive switch . . . . With No 2 Np/NR at 104% and with a minimum 3% Np split, select ACC Drive, yellow ACC caption illuminated [ENG1 ACC] displayed (see CAUTION 3) continued

SHUTDOWN

Whiteback

continued ENG 1 EMSS . . . . . . . . . . . . FLY or GI (see CAUTION 2 and Note) ENG 2 EMSS . . . . . . . . . . . . GI for 10 secs ENG 2 EMSS . . . . . . . . . . . . OFF (see WARNING 1 and CAUTION 2, Card 18) Rotor brake . . . . . . . . . . . . . ON below 47% NR [RTR BRK ON] displayed When rotor stopped: Rotor brake . . . . . . . . . . . . . PARK, indicator illuminated IGI switch . . . . . . . . . . . . . . . As required ENG 1 EMSS . . . . . . . . . . . . OFF (see WARNING and CAUTION 2, Card 18) or FLY (see Note, Card 18) Aircraft lighting . . . . . . . . . . . As required AFTER SHUTDOWN CHECKS Continue with: Nav lights . . . . . . . . . . . . . . Instrument cooling fan . . . . Alternators. . . . . . . . . . . . . . . Generators . . . . . . . . . . . . . DC busbar coupling . . . . . . Transfer pumps . . . . . . . . . LP cocks . . . . . . . . . . . . . . . Tactical processor switch . . Ground servicing panel . . . Hoist master . . . . . . . . . . . . Cargo master . . . . . . . . . . . D/Ident light. . . . . . . . . . . . . . Rear avionics bay fan . . . . . Collective lever . . . . . . . . . .

As required OFF Both OFF/RESET Both OFF DIS Both OFF Both SHUT (see CAUTION 4, Card 18) OFF All switches OFF/FLT OFF OFF OFF OFF Exhaust hyd pressure (in negative pitch only) continued Card 18R

C12White

November 2017

WTP 101C-1321B-14A

continued Landing light . . . . . . . . . . . . Clock . . . . . . . . . . . . . . . . . Cockpit lighting . . . . . . . . . . Battery master . . . . . . . . . . ANTI-COLL switches . . . . . NAV LTS switch . . . . . . . . . STARTER MASTER switch . . . . . . . . . . . . . . . SDR . . . . . . . . . . . . . . . . . .

Card 19

Off and stowed Reset As required OFF As required As required OFF iMMM and KSU remove

SHUTDOWN IN MAIN DRIVE ENG 1 and ENG 2 EMSS

. . GI for 10 secs (see CAUTION 2, Card 18) ENG 1 and ENG 2 EMSS . . OFF (see WARNING and CAUTION 2, Card 18) Rotor brake . . . . . . . . . . . . . ON below 47% NR [RTR BRK ON] displayed When rotor stopped: Rotor brake

. . . . . . . . . . . . PARK, indicator illuminated

Continue with AFTER SHUTDOWN CHECKS, Card 18R

SHUTDOWN cont’d

IntentBlank

Intentionally Blank

Card 19R

C13White

November 2017

WTP 101C-1321B-14A

Card 20

LIMITATIONS The limitations quoted in Cards 20 to 31 inclusive are mandatory and are not to be exceeded unless superseded by later instructions, or in an emergency. These limits have been adjusted to show the cockpit indicated values

LIMITS

Whiteback

ENGINE/POWER OPERATING LIMITATIONS (Version 58 ECU Software Standard) Condition

Ng%

Np%

All Engines Operating (AEO) Starting/Transient (see Note 1) Max Transient -

Max TRQ% PTIT 950°C

150

Time

-

Ground Idling (see Note 2)

58.0 min 66.5 max

-

-

-

Flight Idle Take-Off Max Continuous

74.0 min 102.3 100.7

-

905°C 878°C

115

10 mins with rotor brake at PARK 5 mins -

-

-

5 seconds

-

-

5 second transient

-

112.3 to 119.2 119.2

Max Permissible Overspeed 112.0 122.4 Shutdown One Engine Inoperative (OEI) Max Continuous 905°C 102.3

-

-

155

2 Minute OEI

104.6

-

953°C

168

30 Second OEI

107.3

-

1007°C

194

2 minutes (8 minutes total cumulative per engine) 30 seconds (2 minutes total cumulative per engine)

-

-

5 seconds

-

-

-

-

-

-

5 second transient Max Permissible Overspeed Shutdown

-

112.3 to 119.2 119.2

112.0

122.4

-

continued

Card 20R

C13White

November 2017

WTP 101C-1321B-14A

Card 21

continued Note 1: The ECU should automatically abort an engine start prior to the displayed cockpit PTIT start limit being exceeded Note 2: For both Twin-Engine and Single-Engine Emergency operations, the ECUs automatically govern engine Np at 104% Note 3: The ECU will automatically shutdown the engine if Ng exceeds 112.0% or Np exceeds 122.4%. The EECU has an automatic relight function for the event of an engine failure Note 4: Ground idling Ng is nominally 58% to 65.5% but may vary depending on ambient conditions. Ng is approximately 70% with rotor brake off Note 5: The ECU limit NgC to 110% Engine and Engine RGB Oil Temperature Maximum transient

. . . . . . . 149°C (5 minute maximum) Normal operating . . . . . . . . . 49°C to 130°C Minimum for engine starting . . . . . . . . . . . . . . . . minus 26°C Engine and Engine RGB Oil Pressure Below 68.5% Ng Upper cautionary range . . Above 4.1 bar Normal operating . . . . . . . 1.7 bar to 4.1 bar Lower cautionary range . . 1.4 bar to 1.7 bar Above 80% Ng Upper cautionary range . . Above 4.1 bar Normal operating . . . . . . . 2.6 bar to 4.1 bar Lower cautionary range . . 1.4 bar to 2.6 bar Note 1: In flight, it is acceptable for oil pressure to fall below 2.6 bar at low power levels

continued

LIMITS cont’d

Whiteback continued Note 2: For engine start and initial operation the cautionary range extends from 0.4 bar to 2.6 bar for the first 10 seconds Note 3: Linear interpolation may be used for limits between 68.5% and 80% Ng Note 4: During starting, EOP must be greater than 1.4 bar within 60 seconds of start initiation Note 5: The maximum oil pressure is allowed for a maximum of 2.5 minutes during cold starts Engine Power Supply Configuration for Engine Starting, Venting and Compressor Washing Operations CAUTION: When using external DC power for engine starting, venting and compressor rinse/wash operations, the external AC power supply must be physically disconnected Engine Starting The engine can be restarted in forward flight throughout the flight envelope. Deliberate shutdown in flight is permitted only in an emergency Rotor Brake Operation The maximum continuous duration for operating No 2 engine at GI with the rotor brake at PARK is 10 minutes. Only one engine must be held against the rotor brake OEI Training Mode The OEI Training mode should not engaged above 4875 kg, except for maintenance purposes, ie, PPI Checks To avoid exceeding PTIT limits engine anti-icing and ECS heating must not be selected ON with the OEI Training mode engaged The NR trim value is not to be altered from 104% with the OEI Training mode engaged The OEI Training mode should only be disengaged at 104% NR, except in an emergency

Card 21R

C13White

November 2017

WTP 101C-1321B-14A

Card 22

TRANSMISSION LIMITATIONS Torque All Engines Operating Maximum transient . . . . . . 130% Maximum continuous . . . . 115% One Engine Inoperative Maximum transient . . . . . . OEI (30 seconds) . . . . . . . OEI (2 minutes) . . . . . . . . Maximum continuous . . . .

220% (see Note 1) 194% 168% 155%

Note 1: The ECU torque limiter controls TRQ at 214% at steady state conditions Note 2: Peak TRQ and duration above 130% AEO or 194% OEI is to be logged Rotor Speed CAUTION 1: MPOG must be achieve as soon as possible after landing in order to minimise the risk of damage to the main rotor head CAUTION 2: The cyclic stick must be positioned using the relevant sight marks. The AFCS null indicators must not be used to position the cyclic stick, as these do not indicate the minimum stress position Power On Maximum transient . . . . . . 113.0% NR (see CAUTION, Card 22R) Nominal . . . . . . . . . . . . . . 104.0% NR Minimum transient (AEO) . . . . . . . . . . . . . . 95.0% NR Minimum transient (OEI) . . . . . . . . . . . . . . . 85.0% NR continued

LIMITS cont’d

Whiteback continued Power Off Maximum transient . . . . . . . . 115.0% NR (see CAUTION) Nominal . . . . . . . . . . . . . . 105.0% NR Minimum transient . . . . . . 79.0% NR CAUTION: If the maximum transient NR is exceeded, the aircraft is to be landed as soon as practicable and placed unserviceable. Note: Rotor speed is to be set to 104% NR except during recovery following a tail rotor control failure and for maintenance test purposes The rotor brake must not be selected on at rotor speeds in excess of 47 % NR The rotor brake must not be selected on with an engine engaged The rotor brake must not be applied for longer than 10 minutes with either engine running at ground idle in MAIN drive CAUTION: The rotor brake is designed to hold the rotor stationary against only one engine driving at ground idle for a maximum of 10 minutes Maximum windspeed for rotor starting and stopping . . . . . 50 knots (into wind ±45°) 30 knots (any other direction) Main rotor blade position for rotor starting and stopping . . . . . . . . . . . 45° to aircraft centreline MGB Oil Pressure (TOP) Maximum . . . . . . . . . . . . . . . . . Normal operation . . . . . . . . . Minimum on sloping ground in ACC Drive . . . . . . . . . . . Minimum for the application of collective pitch . . . . . . . . Minimum for flight . . . . . . . . . Minimum transient (5 minutes) . . . . . . . . . . . . .

8.0 bar 2.3 bar to 7.0 bar 1.0 bar 2.3 bar 2.3 bar 1.5 bar

continued

Card 22R

C13White

November 2017

WTP 101C-1321B-14A

Card 23

continued MGB Oil Temperature (TOT) WARNING: For temperatures between 120°C to 130°C (OEP 215) and 110°C to 120°C (OEP 70) the probability of severe gearbox damage is significantly increased. Time over 120°C and the maximum temperature registered must be recorded Maximum limit

. . . . . . . . . . . (OEP 215) 120°C (OEP 70) 110°C (see WARNING) Maximum continuous . . . . . . (OEP 215) 110°C (OEP 70) 100°C Minimum for cold soak . . . . . minus 40°C Minimum for ACC Drive starting . . . . . . . . . . . (OEP 215) minus 15°C (OEP 70) minus 26°C Minimum for rotor starting or MAIN Drive start . . . . . . . minus 10°C FLIGHT LIMITATIONS OAT Subject to other system limitations the aircraft is cleared for operation from minus 26°C to 50°C or ISA+35°C if less, subject to a minimum cold soak of minus 40°C Maximum AUM 5330 kg Maximum Altitude Pressure altitude . . . . . . . . . 12,000 ft Density altitude . . . . . . . . . . . 15,000 ft Maximum Speed VNO . . . . . . . . . . . . . . . . . . . Refer to Card 30 Cabin doors fully open or removed (cockpit doors fitted and secured closed) . . . . . . . . . 120 knots Opening and closing cabin doors . . . . . . . . . . . . . 120 knots continued

LIMITS cont’d

Whiteback continued Both cockpit doors removed (cabin doors fitted and secured closed) . . . . . . Opening and closing cabin doors with both cockpit doors removed . . . . . . . . . . Either HYD system off or failed . . . . . . . . . . . . . . . Single ASE or single CAC lane disengaged or inoperative . . . . . . . . . . . . .

100 knots

In the hover 120 knots

Pitch = VNO minus 10% CAC/Roll/Yaw = VNO

Both ASE or both CAC lanes disengaged or inoperative . . . . . . . . . . . . . Pitch = VNO minus 10% Roll = VNO minus 10% CAC = VNO minus 20% Low Speed Envelope Below 40 knots . . . . . . . . . . . Refer to Card 31 and 32 Note: In low speed manoeuvring flight with relative wind from Red 045° to Red 180°, aft cyclic control limits may be encountered Centre of Gravity Refer to 28R Maximum Angle of Bank Refer to Card 30R IMC . . . . . . . . . . . . . . . . . . . . 30° Rad Alt/Bar Alt engaged . . . . 30° Autorotation . . . . . . . . . . . . . 30° CAUTION: The maximum permitted angle of bank is limited by AUM, density altitude and speed Note: The maximum angle of bank should be further reduced in conditions of severe turbulence Rates of Rotation AUM below 5125 kg . . . . . . . 60°/second continued Card 23R

C13White

November 2017

WTP 101C-1321B-14A

Card 24

continued AUM above 5125 kg or above 5000 feet density altitude . . . . . . . . . . . . . . . . 30°/second Autorotation Entry into autorotation in less than 3 seconds is prohibited, except in an emergency The aircraft is not cleared for autorotative landings, except in an emergency Electromagnetic Compatibility No clearance is available until aircraft EMC testing has been complete Instrument Flying Minimum airspeed . . . . . . . . 40 knots Maximum angle of bank . . . . 30° Running Landings Maximum estimated groundspeed . . . . . . . . . . . 30 knots Mainwheels fore and aft or toed out and wheel locks disengaged Run-on landings with AUM above 5125 kg are prohibited except in an emergency Operation on Slopes Take-Off/Landing Nose down . . . . . . . . . . . . 0° Nose up . . . . . . . . . . . . . . . 7° Lateral . . . . . . . . . . . . . . . . 12° (7.5° at AUM > 5125 kg) Stop/Start Rotors Nose down . . . . . . . . . . . . Nose up . . . . . . . . . . . . . . . . Right wheel down slope . . Left wheel down slope . . . .

0° 7° 7° 5°

LIMITS cont’d

continued

Whiteback continued Operation from Ships Decks Maximum relative wind including gusts ±20° to aircraft nose . . . . . . . . . . . . 50 knots Maximum relative wind including gusts from side or rear of aircraft . . . . . . . . . . . . . . 30 knots Particular care is necessary in the forward right sector (020° to 080°) where yaw control may not be adequate in winds above 15 knots Care should be taken when operating in the wake of the superstructure Maximum ships motion during take-off and landing: Pitch . . . . . . . . . . . . . . . . . ±2° Roll . . . . . . . . . . . . . . . . . . ±7.5° Yaw . . . . . . . . . . . . . . . . . To be minimised, no greater than 1.5° Maximum ships motion after landing or before take-off cycle Pitch . . . . . . . . . . . . . . . . . ±6° Roll . . . . . . . . . . . . . . . . . . ±15° Yaw . . . . . . . . . . . . . . . . . 13° CAUTION: The ASE system should be disengaged for all rotors running operations on deck. It should be engaged just prior to take-off and disengaged immediately after landing SYSTEMS LIMITATIONS Hydraulic Systems Pressures - No 1 and No 2 Systems Normal pressure . . . . . . . . 120.0 bar to 156.0 bar CAUTION: The No 1 and/or No 2 hydraulic systems must not be pressurised with the main rotors folded. Note: If either system is selected OFF, pressure in that system may reach 165 bar, this is acceptable Card 24R

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Card 25

APPROVED FUELS

NATO Code

UK Specification

French Spec.

US Spec. (Designation)

Standard Fuels (see Notes 1, 2 and 3) F34

Def Stan 91-87 (AVTUR FSII)

DCSEA 134/B

MIL-DTL-83133F (JP-8)

F35

Def Stan 91-91 (AVTUR)

DCSEA 134/B

MIL-DTL-83133F (JET A, A1 and B)

F40

Def Stan 91-88 (AVTAG FSII)

-

MIL-T-5624 (JP-4)

F44

Def Stan 91-86 (AVCAT FSII)

DCSEA 144/B

MIL-DTL-5624U (JP-5)

Emergency Fuels (see Notes 4, 5 and 6, Card 25R) F18

Def Stan 91-90 (AVGAS 100LL)

DCSEA 118/B

ASTM D910-07a

F46

Def Stan 91-13 (COMBAT GAS)

-

-

F50

Def Stan 91-13 (CIVGAS)

-

-

F54

Def Stan 91-9 (DIESO MILITARY)

-

-

F75/F76

Def Stan 91-4 (DIESO F76)

STM 110A/B

MIL-DTL-16884L

Fuels conforming to US specifications VV=F-800 graded F1 (DIESO

Note 1: If F35 is used below +5°C, FSII must be added Note 2: Fuel System Icing Inhibitor (FSII) (Def Stan 68-252) may be used in proportions of 0.10% to 0.15% by volume continued

LIMITS cont’d

Whiteback

continued Note 3: Use of F35 and F44 containing a fuel-soluble corrosion inhibitor/lubricity improving agent (Def Stan 68-251) is permitted Note 4: Booster pumps must be operating when the engine is running. Note 5: Use is limited to engine operation up to 6 hours at a maximum of 90% take-off power Note 6: Fuel viscosity must not exceed 12 centistokes

continued

Card 25R

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WTP 101C-1321B-14A

Card 26

continued APPROVED OILS NATO Code

UK or Mil Spec (Designation)

Type (Viscosity)

Limitations

Standard Engine Oil O-156

OX-27 Def Stan 91-101 MIL-PRF-23699

Synthetic (5cSt)

-

O-148

OX-9 MIL-PRF-7808

Synthetic (3cSt)

-

Main Gearbox Oil -

DTD 900/4981 OEP 215

-

OAT minus 15°C and above

O-155

OEP 70 Def Stan 91-122 MIL-PRF-6086

-

OAT minus 26°C to 28°C

-

OX-125

-

OAT minus 40°C to 50°C

Intermediate and Tail Rotor Gearbox Oils -

OX-125

-

OAT minus 40°C to 50°C

O-160

OX-26 Def Stan 91-100 DOD-PRF-85734

-

OAT minus 40°C to 50°C

-

-

-

-

Hydraulic Fluid H515

OM 15 Def Stan 91-48 MIL-PRF-5606

Main Rotor Head -

OEP 215

Note 1: Engine oils must not be mixed Note 2: Transmission oils must not be mixed; oil type is defined by transmission build standard

LIMITS cont’d

Whiteback

SNOW AND ICING CONDITIONS Note 1: All OAT temperatures quoted are centigrade true unless otherwise stated Note 2: Icing conditions are deemed to exist when the OAT is below 0°C and the visibility is less than 1000 m due to the presence of cloud or fog. Visibility reduction below 1000 m due to snow alone does not constitute an icing condition General Restrictions Engine anti-icing and pitot heating must be switched ON for operation in cloud, fog or rain at temperatures below 5°C OAT Note: Engine anti-icing and pitot heating is not essential for operation in clear air at low temperatures. Clear air is deemed to exist when visibility is greater than 1000 metres and no precipitation is present Windscreen heating serviceable For flight with ice accreting on the aircraft, windscreen heating must be switched ON and the wipers parked outboard Engine anti-icing must not be selected ON above 15°C, except during compressor wash drying procedures or determining system serviceability if it is anticipated that the engine anti-icing may be required later in the sortie CAUTION: Above 15°C OAT, engine operation with engine anti-icing selected ON, or with [INTK1 A/ICE] or [INTK2 A/ICE] displayed, may result in decreased engine performance. Refer to Card 28 Flight in Freezing Fog Prohibited Snow Ground running in precipitating snow conditions is prohibited Flight in precipitating and/or recirculating snow conditions is prohibited continued

Card 26R

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Card 27

continued Flight in Freezing Rain and Freezing Drizzle Prohibited Flight in Icing Conditions WARNING: An escape route must always be available to enable an exit to an area (either known or forecast) clear of icing conditions Flight in icing conditions when carrying external freight is prohibited General Limitations Ice accretion meter fitted Windscreen heating serviceable Engine anti-icing serviceable Flight Limitations Maximum speed

. . . . . . . . The lesser of 120 knots and VNO minus 20 knots IAS Maximum angle of bank . . 30° Maximum pressure altitude: Zero °C to minus 5°C OAT . . . . . . 8000 ft Minus 5°C to minus 7°C OAT . . . . . . 6000 ft Minus 7°C to minus 10°C OAT . . . . . 2000 ft Minimum OAT . . . . . . . . . . minus 10°C Autorotation . . . . . . . . . . . . Prohibited, unless in an emergency

Ice Accretion Limitations Flight may continue with ice accreting, observing the following limitations: Max rime . . . . . . . . . . . 20 mm Max glaze . . . . . . . . . . . 10 mm When ice is accreting: Windscreen heating ON Wipers parked outboard

continued

LIMITS cont’d

Whiteback continued Flight in Icing Cloud Non-icing conditions must exist for 1000 ft below the icing cloud over land or sea but, over land, clear air must exist between the surface and 250 ft AGL The maximum permitted TRQ is 100%/100% in level flight or an estimated increase of 25%/25% above the normal clear air value, whichever is reached first If the accretion limit is reached, icing conditions must be vacated immediately; re-entry is not permitted until all visible accretions are shed If the TRQ rise or vibration limits are reached, speed must be reduced towards the minimum power speed and height reduced until TRQ and vibration are within limits. If this is not possible, the icing environment must be vacated immediately Torque increase of 10% to 25 % can be expected due to increased drag resulting from aircraft (fuselage or rotor) ice accretion. Pitch attitude may be expected to change by 1° to 2° nose down Flight in Mixed Snow and Icing Conditions Flight in mixed snow and icing conditions is prohibited If snow is inadvertently encountered when in icing cloud, speed must be reduced to below 80 Knots IAS and the condition must be vacated immediately Lightning Flight into known and known-forecast lightning conditions is prohibited

Card 27R

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WTP 101C-1321B-14A

Card 28

ENGINE OPERATION IN THE SHADED REGION WITH ENGINE ANTI-ICING SELECTED ON OR FAILED ''ON'' MAY RESULT IN DECREASED ENGINE PERFORMANCE 110

Ng (%)

105 100 95 90 85 15

20

25

30

35

40

45

50

55

OAT ( o C) LWF18066L-05

Fig 1 Engine Anti-Icing System Limitations OP DATA

continued

Whiteback

continued

TO BE ISSUED

Fig 2 Centre of Gravity continued Card 28R

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WTP 101C-1321B-14A

continued

OPERATING DATA

PRESSURE ALTITUDE (ft)

12 000

0

12

00

0

11

00

00

00

20

00

10

EL

EV

L EA

S

ISA

0

00

-10

00

-20

-30

-2000

-40

ISA

-6000 -30

00

-20

2000

-4000

00

40

30

ISA

DENSITY ALTITUDE (ft)

o

( C)

-10

ISA

4000

00

50

+10

ISA

6000

00

60

+20

00

70

ISA

8000

ISA

00

80

+35 +30

90

ISA

10 000

0

00

ISA

10

PDL0220/FRC 6104/ISS 1

14 000

Card 29

-20

-10

0

10 20 OAT (oC)

30

40

50

Fig 3 Density Altitude/Pressure Altitude Conversion

continued

OP DATA cont’d

Whiteback continued

50

PRESSURE 40 ALTITUDE (ft)

20 10 0 -10

40

A-

IS

-20 -30 4000 AIRCRAFT MASS (kg)

ISA+ 0 20 00 00 2 - 10 L 0 ISA+ - S 00 00 10 1 20 000 0 3 400 00 0 0 0 0 5 00 ISA o 6 70 000 00 0 ( 8 90 C) 00 ISA10 10 0 00 11 ISA-2 000 0 12 ISA-3 0

4200 4400 4600

PDL0220/SHT 6101/ISS 1

OAT (oC)

30

ISA+35 ISA+3 0

REFERENCE LINE

4800 5000 5200 5400

MAX AUM 0

10

20 30 40 TRUE AIRSPEED (knots)

50

60

Fig 4 OEI Minimum Speed in Level Flight Engine Rating: 2 Minute OEI

continued Card 29R

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WTP 101C-1321B-14A

Card 30

continued Note 1: VNO for a given Density Altitude and OAT is the lesser of that defined by the ’AIRCRAFT’ and ’TEMPERATURE’ limits below Note 2: ’TEMPERATURE’ limit chart is only limiting for OATs of 10 oC and below Note 3: IMC limits - Minimum Airspeed 40 knots, Maximum Bank Angle 30 o Note 4: Maximum Angle of Bank limits (ASE/CAC engaged) - Refer to Fig 6

120 140 160 INDICATED AIRSPEED (knots)

-5 -15

-10

-25

-20

10oC AND BELOW

-30

100

0

80 120 160 INDICATED AIRSPEED (knots)

’TEMPERATURE’ LIMITS

OAT (oC)

PDL0220/FRC 6102A/ISS 1

5

10

ELOW ND B 4400 48005 512 5330

-6000

-2000

2000

6000

10 000

14 000

40

ALL UP MASS (kg)

’AIRCRAFT’ LIMITS

A 4000

DENSITY ALTITUDE (ft)

Fig 5 Flight Envelope - 40 Knots to Normal Operating Speed (VNO) continued

OP DATA cont’d

Whiteback

continued

Note 1: In IMC The Maximum Bank Angle is 30 O Note 2: The Maximum Angle Of Bank should be further reduced in conditions of severe turbulence

15000

10000

45o BANK ANGLE UP TO VNO MINUS 20 knots

7000

5000

PDL0220/SHT 6102B/ISS 1

DENSITY ALTITUDE (ft)

30o BANK ANGLE UP TO VNO

60o BANK ANGLE UP TO VNO MINUS 50 knots

4000

4425

4875 5125 AIRCRAFT MASS (kg)

5330

Fig 6 Maximum Angle of Bank continued

Card 30R

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WTP 101C-1321B-14A

Card 31

continued

FOR OPERATIONS ABOVE RELEVANT LINE A REDUCTION IN YAW CONTROL MAY BE EXPERIENCED

14 000

E

E

IG

10 000

OG

8000

6000

PDL0220/FRC 6103A/ISS 1

DENSITY ALTITUDE (ft)

12 000

4000

2000

FOR OPERATIONS BELOW RELEVANT LINE AIRCRAFT HEADING CAN BE MAINTAINED UP TO THE LIMITS SHOWN IN FIG 8

0 3400

3800

4200 4600 5000 ALL UP MASS (kg)

5400

Fig 7 Maximum Mass to Maintain Full Yaw Control in Low Speed Flight continued OP DATA cont’d

Whiteback continued Note 1: Normal operating limits are 30 knots wind speed from all azimuths Note 2: In case of operational necessity, the aircraft is cleared for flight at 40 knots airspeed throughout the azimuth range, at up to maximum All Up Mass A. Care must be taken as cyclic control limits may be approached, particularly at forward CGs and with winds from Red 045 to Red 180 B. With ASE pitch lanes disengaged, control limits will be further reduced C. 40 knot winds from Red 090 to Red 135 may result in fuselage roll attitude of up to 15o left wing low Note 3: When operating at Density Altitudes in excess of 5000 ft the normal operating limit must be observed at all times Note 4: Operation above the relevant line in Fig 7 will be accompanied by a progressive deterioration in yaw control capabilities particularly with relative winds from Green 045 to Green 090

ASE ENGAGED RED

000 60 030

GREEN

030 50

40

30

20

30 20 10 10

10

20

060

30

40

WIND SPEED (knots)

10 20 30

120

120

40 OPERATIONAL MAXIMUM 50 150

090 60

50

150 60 180

RELATIVE WIND DIRECTION (degrees)

PDL0220/FRC 6103B/ISS 1

50

NORMAL OPERATING LIMIT

090 60

40

NORMAL OPERATING LIMIT

060

Fig 8 Low Speed Flight Envelope

Card 31R

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November 2017

WTP 101C-1321B-14A

Card 32

Night Signals Phase

Nav Lights

Anti-Coll

Torch

Manned

Steady dim

Off

-

Start No 1 engine

Steady bright

Off

-

Disconnect external power

Steady bright

Off

Flash

Start No 2 engine

Off and on twice leave steady bright

Off

-

Engage rotor

Flash dim

Off

-

Take-Off

Flash bright

Off

-

Clear of dispersal/ship

Steady bright

On

-

Approach dispersal/ship

Flash bright

Off

-

Land-on

Flash dim

Off

-

Shutdown

Flash dim

Off

Signal

Stop No 2 engine /stop rotor

Flash dim

Off

Signal

Rotor stopped

Steady dim

Off

-

Leave aircraft

Steady dim or off as required

Off

-

-

Flash

Call groundcrew

-

OP DATA cont’d

Whiteback

COMPRESSOR RINSE CAUTION 1: Do not carry out the following procedures below minus 15°C OAT CAUTION 2: Above 15°C OAT, engine operation with engine anti-icing selected ON, or with the [INTK1 A/ICE] or [INTK2 A/ICE] displayed, may result in decreased engine performance. Refer to Card 27 CAUTION 3: The maximum continuous duration for operating No 2 Engine at GI with the rotor brake at PARK is 10 minutes Before Flight Compressor Rinse Procedure Carry out normal External (Cards 2R to 5R) Engine anti-icing . . . . . . . . . . ECS . . . . . . . . . . . . . . . . . . . No 1 engine . . . . . . . . . . . . .

No 1 EMSS

and Internal Checks Both OFF OFF Carry out Starting No 1 Engine (In Accessory Drive) checks (Card 6R)

. . . . . . . . . . . . . FLY

Confirm rig connected to No 1 engine, wash valve closed No 1 Ng . . . . . . . . . . . . . . . . Stable at FLY Rinse for 2.5 minutes Confirm wash valve closed, rig disconnected from No 1 engine No 2 engine . . . . . . . . . . . . . Carry out Starting No 2 Engine checks (Card 12) Confirm rig connected to No 2 engine, wash valve closed No 2 Ng . . . . . . . . . . . . . . . . Stable at GI Rinse for 2.5 minutes Confirm wash valve closed and rig removed from aircraft, ground crew and equipment clear of disc area Continue with normal pre-flight checks from TP Initialisation (Card 8) continued Card 32R

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WTP 101C-1321B-14A

Card 33

continued Start clock After 1 minute: Engine anti-icing

. . . . . . . . ON for 30 seconds (see CAUTION 2, Card 32R), then OFF

Wait 30 seconds After 2 minutes: ECS . . . . . . . . . . . . . . . . . . HTG Temp controller . . . . . . . . . HOT for 1 minute, then towards COLD ECS . . . . . . . . . . . . . . . . . . OFF Wait 30 seconds After 3.5 minutes: Engine anti-icing

. . . . . . . . ON for 30 seconds (see CAUTION 2, Card 32R), then OFF

Continue with Take-Off Checks (Card 15R) Fly for a minimum of 5 minutes or ground run for a minimum of 10 minutes After Flight Compressor Rinse Procedure Ensure After Landing checks are complete (Card 17) Engine anti-icing . . . . . . . . . . Both OFF ECS . . . . . . . . . . . . . . . . . . . OFF No 1 EMSS . . . . . . . . . . . . . GI Confirm rig connected to No 1 engine, wash valve closed No 1 Ng . . . . . . . . . . . . . . . . Stable Rinse for 2.5 minutes Confirm wash valve closed, rig disconnected from No 1 engine No 1 EMSS . . . . . . . . . . . . . FLY No 2 EMSS . . . . . . . . . . . . . GI Confirm rig connected to No 2 engine, wash valve closed continued COMPRESSOR RINSE

Whiteback

continued No 2 Ng . . . . . . . . . . . . . . . . Stable Rinse for 2.5 minutes Confirm wash valve closed and rig removed from aircraft, ground crew and equipment clear of disc area No 2 EMSS . . . . . . . . . . . . . FLY Carry out drying procedure by running both engines: Start clock After 1 minute: Engine anti-icing

. . . . . . . . ON for 30 seconds (see CAUTION 2, Card 32R), then OFF

Wait 30 seconds After 2 minutes: ECS . . . . . . . . . . . . . . . . . . HTG Temp controller . . . . . . . . . HOT for 1 minute, then towards COLD ECS . . . . . . . . . . . . . . . . . . OFF Wait 30 seconds After 3.5 minutes: Engine anti-icing

. . . . . . . . ON for 30 seconds (see CAUTION 2, Card 32R), then OFF

Either: Continue with Take-Off Checks (Card 15R) and fly for a minimum of 5 minutes or After 10 minutes: Carry out Shutdown Checks (Card 18)

Card 33R