V1.12 – 9 Mar 2014
Beechcraft King Air C90
G-VBCD
OPERATIONS MANUAL
Version 1.12 – 9 March 2014
1981 Model Year, Serial Number LJ-972
Incorporates AFM updates and supplements to March 2014, including
Blackhawk XP STC (PT6A-135A engine installation), Blackhawk XLR STC
(wing locker fuel tank installation), Raisbeck EPIC STC, 10,500lb MTOM STC
Empty (Aircraft Prepared for Service) Mass and Balance measured July 2011
This document is for information only
Compliance with the PRNAV procedures in this manual is a requirement of
the UK general approval for non-AOC operators (reference ORS4-959)
Revision Log
Date
Version
Note of Revisions
1 Feb 2014
1.1
First issue of final Ops Manual following
trial use of v1.0
23 Feb 2014
1.11
NP6 amend to include Departure Brief
EP6 amend to include check of Starter if
Gen failed
1.12
NP6 Governor test RPM amend to 1750
EP6 Crossfeed proc item 4 added
EP7 Avionics Power fail proc added
Operating Manual Notes: Cold
Temperature limitations added
9 Mar 2014
V1.12 – 9 Mar 2014
Signed
V1.12 – 9 Mar 2014
GENERAL INFORMATION
NORMAL PROCEDURES
EMERGENCY PROCEDURES
OPERATING INFORMATION
General Information
Owner and Operators
Intentionally blank in this version
CAMO
Intentionally blank in this version
EGHH and EGLK Contact Details
Intentionally blank in this version
Flight Plan filing
Intentionally blank in this version
V1.12 – 9 Mar 2014
V1.12 – 9 Mar 2014
Flight Plan information
Item 8
I—IFR, V—VFR
Y—IFR then VFR, Z—VFR then IFR
In item 15, specify transition point
PR IOR IT Y
Item 10 SDFGRS/S
S for VHF, VOR, ILS
B for LPV (APV SBAS) – not at present
D for DME, F for ADF, G for GNSS
R for PBN approved (see Item 18)
Y for 9.33kHz
/S for Mode S
A D D R ESSEE( S)
<<≡ FF →
<<≡
F ILIN G T IM E
OR IGIN A T OR
→
<<≡
SPEC IF IC ID EN T IF IC A T ION OF A D D R ESSEE( S) A N D / OR OR IGIN A T OR
3 M ESSA GE T Y PE
7 A IR C R A F T ID EN T IF IC A T ION
8 F LIGHT R U LES
− GV BCD
<<≡ (FPL
9 N U M B ER
T Y PE OF A IR C R A F T
−
− G
W A KE T U R B U LA N C E C A T .
BE 9 L
<<≡
10 EQU IPM EN T
/ L
13 D EPA R T U R E A ER OD R OM E
T Y PE OF F LIGHT
−
SDFGRY / S
<<≡
T IM E
−
<<≡
15 C R U ISIN G SPEED
LEV EL
R OU T E
− N0 2 5 0
→
<<≡
T OT A L EET
HR .M IN
13 D EST IN A T ION A ER OD R OM E
−
A LT N A ER OD R OM E
2 N D . A LT N A ER OD R OM E
→
→
<<≡
18 OT HER IN F OR M A T ION
−
PBN/B2D2S1
NAV/SBAS
) <<≡
SU PPLEM EN T A R Y IN F OR M A T ION ( N OT T O B E T R A N SM IT T ED IN F PL M ESSA GES)
19 EN D U R A N C E
HR .M IN
−E/
SU R V U V A L
EQU IPM EN T
EM ER GEN C Y R A D IO
PER SON S ON B OA R D
→P/
U HF
→R/ U
V HF
ELB A
V
E
POLA R
D ESER T M A R IT IM E JU N GLE
JA C KET S
LIGHT
F LU OR ES
V HF
Item 15
Item
18 (from
Nov
12) U HF
→ S
P
D
M
J
→ J
L
F
U
V
Speed or altitude change—enter the point
For PBN/ capability enter PBN/B2D2S1
D
IN
GHIES
C
A
PA
C
IT
Y
C
OLOU
R
followed by a slash and new speed or
•B2 - RNAV 5 GNSS
altitude (e.g., LN/N0200A045).
•D2 - RNAV 1 GNSS
•S1 - RNP APCH
Flight rule change—enter the
point/designator followed by a space and
For SBAS enter NAV/SBAS
the new flight rule (e.g., LN VFR,
LN/N0200A045 IFR, etc.).
Specs & Limitations (see AFM)
ENGINE OIL
Total capacity
Refill capacity
Operating level
V1.12 – 9 Mar 2014
14 qts each engine
12.5 qts each engine
9.5 – 12.5 qts each engine
FUEL
Minimum fuel for take-off
Approved Fuel:
Capacity: Mains plus Locker
265lbs per wing & above yellow arc
Jet A, A-1, B and JP4,5
384 USg plus 78USg; total 462 USg
1454litres plus 295litres; total 1749litres
2570lbs plus 520lbs; total 3090lbs
Quantities are Useable. Anti-ice additive not req’d. See AFM for use of Avgas.
TIRE PRESSURES
51-55 psi Nose, 67-73 psi Mains(*)
(* 10 ply tires fitted, required for operation at increased MTOM 10,500lbs)
MAXIMUM OPERATING ALTITUDE
Maximum
30,000’
Without Oxy equipment
25,000’
Above 25,000’, all occupants must have a 10min Oxy supply available
Pressure Differential
0-4.7 PSI normal, 4.7 PSI max
V1.12 – 9 Mar 2014
G-VBCD Preflight Planning Sheet
G-VBCD Preflight Planning Sheet
CHECK
Mass and Balance
Empty Mass
Fuel
Crew & Pax
Baggage
subtotal
Total
6840 lbs
Max Ram p Mass
10560 lbs
Max Take-off Mass 10500 lbs
Max Landing Mass
9700 lbs
Balance
1. Crew m ass below 450lbs, m in 20lbs aft, no fw d bags
2. Mass in Side facing seat and aft area <300lbs
Departure Runway
Length Available
Mains & Locker = 3090 lbs
Max Zero Fuel Mass 9000 lbs
CoG Calculated:
Guidelines met:
Mass
Full Mains = 2570lbs
If Guidelines are met and MTOM is below Max, CG is w ithin limints
Reqd: Take-Off to 50'
@10500lbs , 25C, 2000' elev
T-O to 50'
2450'
Temp
Wind
Elevation
Accel. Stop
Reqd: Accelerate Stop
4500'
Accel. Go
Reqd: Accelerate Go
3600'
Fuel Reserves
Assume 700lbs first hour inc. Taxi, T/O and Climb
VFR
Assume 500lbs/hr Cruise
ETE + 60mins
Endurance
ETE
Alternate
If 60min Final Reserve not available
then calculate Fuel Plan (see Ops Man)
IFR
ETE + Alternate + 60mins
Destination and Alternate Weather (EU OPS)
Destination
Ceiling
Visibility
F'cast AOM
Alternate F'cast AOM
Destination > AOM
Alternate > AOM
or Destination VMC +/- 2hrs
Arrival Runway
Length Available
Destination
Alternate
@9700lbs , 25C, 2000'elev
Landing over 50'
2300'
Landing over 50', no Prop Revrs
Other Compliance Required
Aircraft
CoA, CoR
Noise Certificate
VAT docs, Intercept procedures
ARC and Phase Inspections
Insurance current
Databases current
Private Ops only, non-RVSM
RNAV1 & PRNAV Compliant
All Compliant
Crew
EASA Pilot Licence
EASA BE90/200 TR/IR current
Passport or Photo ID
24mth EASA Class 2 Medical
90 day 3 landing rule for pax
OR
V1.12 – 9 Mar 2014
GENERAL INFORMATION
NORMAL PROCEDURES
EMERGENCY PROCEDURES
OPERATING INFORMATION
V1.12 – 9 Mar 2014
NORMAL PROCEDURES 1
Airspeeds for Normal Operation
Air Minimum Control Speed (VMCA)………. 90 KIAS
Vr and V1…………………......................... 95 KIAS
Initial Climb (2 Engine, Vy)……………… 110 KIAS
Intentional One Engine Inoperative
Speed (VSSE) ............................................
97 KIAS
Two-engine Best Angle-of-Climb (Vx)…….100 KIAS
Two-engine Best Rate-of-Climb (Vy)…… 110 KIAS
Maximum Maneuvering Speed (VA)……… 170 KIAS
Turbulent Air Penetration .......................... 160 KIAS
Landing Approach VREF…….....…..…….. 100 KIAS
ICAO Approach Category………………….. B
Balked Landing Climb .............................. 95 KIAS
Maximum Demonstrated Crosswind……… 25 KIAS
Cruise Climb:
Sea Level to 10,000 feet……………
10,000 to 20,000 feet……………….
20,000 to 25,000 feet……………….
25,000 to 30,000 feet……………….
150 KIAS
140 KIAS
130 KIAS
120 KIAS
Amended by Operator
with 10KIAS increment
over AFM due PT6A135A observed
performance
Vmo Max Operating Speed……………….. 208 KIAS
Vfe Max Flaps Extended…………………… 178 KIAS (APP, 35%)
130 KIAS (FULL, 100%)
Vlo Max Gear Operation………………....... 156 KIAS – Extend
130 KIAS – Retract
Vle Max Gear Extended…………………… 156 KIAS
Vso (bottom of White Arc)…………………. 76 KIAS
Vs1 (bottom of Green Arc)………………… 89 KIAS
V1.12 – 9 Mar 2014
NORMAL PROCEDURES 2
• Propeller………CHECK
• Engine Air and Oil Cooler
Intakes…………CLEAR
Ice Vane……….CHECK
• Engine Boot......CHECK
• Engine Oil……..CHECK
• Fuel Filter….…..DRAIN
• Cowling………...CHECK
• Nacelle Fuel Tank
………………CHECK
• Heat Exchanger CLEAR
• Transfer Pump Sump
…………………DRAIN
• Antennas and Beacon
…………………CHECK
•
•
•
•
•
Ram Air Inlet…...CLEAR
Baggage Door.SECURE
Air Con Ducts….CLEAR
Nose Gear……..CHECK
Landing &Taxi Lights
…………….CHECK
• Pitot Covers…REMOVE
• Windshield Wipers
…………….CHECK
3
• Transfer Pump Sump
…………………DRAIN
• Heat Exchanger CLEAR
• Nacelle Fuel Tank
………………CHECK
• Propeller………CHECK
• Engine Air and Oil Cooler
Intakes…………CLEAR
Ice Vane……….CHECK
• Engine Boot......CHECK
• Engine Oil……..CHECK
• Fuel Filter….…..DRAIN
• Cowling………...CHECK
4
2
External inspection
5
1
•
•
•
•
•
•
•
•
•
•
•
•
•
Locker Fuel Tank CHECK
Flaps…………
CHECK
Aileron and Tab CHECK
Wing Tip (Lights) CHECK
Stall Warning… CHECK
Deice Boot…….. CHECK
Chocks…………REMOVE
Wing Fuel Tank…CHECK
Outboard Wing Sump
……………....DRAIN
• Wheel Well Sump DRAIN
• Landing Gear….. CHECK
• Boost Pump Sump DRAIN
6
•
•
•
•
•
•
•
Oxygen Door …..SECURE
Static Ports…….CLEAR
Access Panels…SECURE
Deice Boots…….CHECK
Elevator…………CHECK
Fin fittings………CHECK
Static Ports…….CLEAR
•
•
•
•
•
•
•
Boost Pump Sump DRAIN
Landing Gear….. CHECK
Wheel Well Sump DRAIN
Outboard Wing Sump
………………DRAIN
Wing Fuel Tank... CHECK
Chocks…………REMOVE
Deice Boot…….. CHECK
Wing Tip (Lights) CHECK
Aileron and Tab CHECK
Flaps…………
CHECK
Locker Fuel Tank CHECK
Cabin Checks
1. Aft area…………………..
2. Cabin…………………….
3. Fwd Partition...………….
4. Cockpit…………………..
LIFERAFT & 1ST AID KIT
LIFEJACKETS, OXY MASKS & AMENETIES
TECH LOG & AFM
OXY MASKS, FIRE EXTING, TORCH
NORMAL PROCEDURES 3
V1.12 – 9 Mar 2014
Before Starting Engines
1.
2.
3.
4.
5.
Cabin Door
Baggage
Emergency Exit
Seats & Harnesses
Passengers
LOCKED
SECURE (Mass & Balance checked)
SECURE
POSITIONED; UPRIGHT, FASTENED
BRIEFED
6. Parking Brake
SET
7. Control Locks
REMOVE
8. Pedestal Circuit Breakers IN
9. Overhead Panel
CHECK
10. Oxygen Control
ON then OFF
11. Oxygen System Pressure CHECK
12. Emergency Static Air Valve NORMAL
13. Right Circuit Breaker Panel CHECK
14. Cabin Temp Mode
OFF; Vent Blower AUTO, Elec’ Heat OFF
15. Landing Gear Handle
DOWN
16. Condition Levers
CUT OFF
17. Propeller Levers
FULL FORWARD or FEATHER
18. Power Levers
IDLE
19. Engine Ice Vanes
EXTENDED (handles pulled out)
20. Left Subpanel Switches
OFF
21. Start Clearance
Battery & Avionics ON, as req'd, then OFF
22. Fuel Panel
a. Circuit Breakers
*b. Fuel Valves (Firewall)
*c. Crossfeed
d. Boost Pumps
CHECK
*May be omitted at Pilot’s
discretion for quick turnaround
IN
CLOSED
OPEN, FUEL CROSSFEED lit, CLOSED
ON (listen for operation)
23. Battery Switch
e. Fuel Valves (Firewall)
f. Fuel Quantity
*g. Transfer Pumps
ON, check FUEL PRESSURE lights on
OPEN, check FUEL PRESSURE lights off
CHECK
ON (listen for operation), then OFF
24. Locker Fuel Panel
Switches OFF, CBs in, Test Lights
25. Voltmeters
26. Cabin Sign Switch
CHECK Battery Volts
NO SMOKE & FSB
No voltage on one side
indicates current limiter out
NORMAL PROCEDURES 4
V1.12 – 9 Mar 2014
Engine Starting
External lights ON as required
1. Right Ignition Start Switch ON,
RH ING IND
on
……….after Ng rpm stabilizes for 5s, 12% minimum;17% normal
2. Right Condition Lever
3. ITT and Ng
LOW IDLE
MONITOR ITT 1090°C maximum
……….at Ng 60% or above
4.
5.
6.
7.
Right Start Switch
Right Condition Lever
Right Generator
Right Oil Pressure
OFF
HIGH IDLE if required
ON unless external power is used
CHECK correct indication if prop unfeathered
……...after Right Generator load falls below 50%
8.Right Generator
OFF
Note LJ972 AFM: If req’d, Left Engine may be started with Right Generator ON,
or Right Generator may be turned ON after the LH Start Switch is engaged
ON, LH ING IND on
1. Left Start Switch
……….after Ng rpm stabilizes for 5s, 12% minimum;17% normal
2. Left Condition Lever
LOW IDLE
3. ITT and Ng
MONITOR ITT 1090°C maximum
……….at Ng 60% or above
4. Left Start Switch OFF
5. Left and Right Generators BOTH ON unless external power is used
6. Left Oil Pressure
CHECK correct indication if prop unfeathered
External Power disconnect and Engine Clearing – see Normal Procedures 9
After Engine Starting
1.
2.
3.
4.
5.
6.
7.
8.
9.
Transfer Pumps
Crossfeed Switch
DC Volt and Loadmeters
Inverter
Avionics Master Switch
Lights
Fuel Control Heat
Cabin Temp and Mode
Annunciator Lights
ON
AUTO
CHECK
CHECK BOTH and SELECT inverter
ON
AS REQUIRED
ON
AS REQUIRED (observe gauge limits)
TEST then CLEAR
NORMAL PROCEDURES 5
V1.12 – 9 Mar 2014
Before Taxi
1.
2.
3.
4.
5.
6.
Engine Ice Vanes
Baro setting
GTN650
Other Instruments
Propellers
Brakes
CHECK EXTENDED (handles pulled out)
ATIS copied, G600 and Altimeter SET
Self-test & database CHECK
CHECK
Max RPM, Prop Sync OFF
CHECK
Before Take-Off
1. Parking Brake
SET
2. Boost Pumps and Auto Crossfeed
a. Left Boost Pump
OFF
LH FUEL PRESS
b. Left Boost Pump
c. Crossfeed
d. Right Boost Pump
e. Right Boost Pump
f. Crossfeed
3.
4.
5.
6.
Avionics and Radar
Pressurization
Autopilot
Electric Elevator Trim
a. Tab Control Switch
b. Pilot's and Co-pilots' Switches
c. Trim Disconnect
d. Tab Control Switch
7. Trim Tabs
8. Flaps
9. Flight Controls
10. Autofeather
off, FUEL CROSSFEED on
ON
CLOSED then AUTO
OFF
RH FUEL PRESS off, FUEL CROSSFEED on
ON
CLOSED then AUTO
CHECK, radar to STBY if reqd
SET switch, rate knob & Alt to Cruise +500’
CHECK, then OFF
CHECK
ON
CHECK OPERATION
CHECK DEACTIVATION OF SYSTEM
OFF then ON
SET
CHECK AND SET UP
CHECK
TEST at Lo Idle then ARM
Autofeather test:
Set Power to 500 ft-lbs, hold test switch
L AUTOFEATHER and R AUTOFEATHER Illuminated
Individually each engine: Retard power, @400ft-lbs opposite annunciator extinguishes
@260lbs, both annunciators extinguish and prop feathers
11. Manual Prop Feathering
CHECK at Lo Idle
Continue with item 12, “Before Take-Off CONTINUED” procedure
NORMAL PROCEDURES 6
V1.12 – 9 Mar 2014
Before Take-Off CONTINUED
*May be omitted at Pilot’s discretion for quick turnaround
12. Run-Up TEST *
a. Propeller Controls
Fully FWD, Max RPM
b. Power Levers
IDLE
c. Governor Test Switch
HOLD in TEST position
d. LH Power Lever
Increase RPM to 1750, stabilize
e. LH Power Lever
Advance, check 1750rpm maintained
f. Governor Test Switch
Release
g. LH Prop Lever
Retard then fully FWD to check
h. Vacuum and Pneumatic CHECK Gauge pressure
i. LH Engine Ice Vane
RETRACT, check Torque drop, EXTEND
j. LH Power Lever
IDLE
Repeat steps c-j for RH Engine
13. Friction Locks
14. Fuel System
15.
16.
17.
18.
Instruments
Auto Ignition
Autofeather
Bleed Air Valves
SET
Boost & Transfer Pumps ON
Crossfeed AUTO, recheck Quantity
CHECK
ARM
ARM
OPEN
19. IFR Departure Checks after clearance copied
a. HDG bug
SET to runway heading
b. Departure procedure
LOADED, CHECKED
c. G600 CDI mode
SET, CDI on initial track
d. Altitude Selector
SET to cleared level
e. Baro
SET, to 1013 if cleared to FL
f. TOGA switch
PRESS, check Flight Director cue
>>> Departure Brief (Wx, Wind & Temp, Distances, Vr, V1, Alternate)
After Line-Up Clearance
20. Ice Protection
ON (Hot 5, Windshield and as reqd)
21. Landing Lights
ON
Take-Off
1. Power Levers
2. Rotate at
3. Landing Gear
ADVANCE, limit to 1520 ft-lbs Torque
95 KIAS
RETRACT with positive climb
NORMAL PROCEDURES 7
V1.12 – 9 Mar 2014
Climb
1.
2.
3.
4.
5.
Climb Power
Propeller
Alt Selector
Baro setting
Landing Lights
SET 1300 ft-lb
1900 RPM, Sync ON
SET and ARM
CAUTION
CHECK
Alt Selector and Autopilot
OFF
are coupled to analogue
when workload permits
1.
2.
3.
4.
5.
6.
Autofeather Switch
Auto Ignition
Engine Ice Vanes
Engine Instruments
Cabin Sign
Pressurization
P1 Altimeter, not G600
OFF
OFF when not in visible moisture
RETRACT when not in visible moisture
MONITOR
AS REQUIRED
CHECK, SET rate as desired
Cruise
1.
2.
3.
4.
5.
6.
7.
Altitude
Power
Gauges
Ice Protection
Navigation
Communication
Weather
CHECK
SET
CHECK (Fuel, Battery, Engine, Press’n)
CHECK and SET as required
Update avionics as appropriate
As appropriate
Radar, Stormscope, ATIS as appropriate
Descent
1.
2.
3.
4.
Pressurization
Altimeters
Altitude Selector
Ice Protection
SET rate & outer scale to Field Elev +500’
CHECK, SET Baro
SET and ARM
As required
Arrival
1.
2.
3.
4.
5.
6.
7.
Radios
Arrival and Approach
Altimeters
Pressurization
Ice Protection
Fuel
Cabin
SET, copy ATIS
LOAD procedure, BRIEF
CHECK, SET Baro
CHECK
As required
CHECK
Secure, Seat back & Harnesses, Sign
NORMAL PROCEDURES 8
V1.12 – 9 Mar 2014
Initial Approach
1.
2.
3.
4.
5.
6.
7.
Engine Ice Vanes
Auto Ignition
Auto Feather
Propeller
Prop Sync
Pressurization
Flaps
EXTEND
ARM
ARM
1900 RPM
OFF
CHECK
APPROACH (below 178 KIAS)
Final Approach and Landing
1.
2.
3.
4.
5.
6.
Landing Gear
Landing Lights
Ice
Condition Levers
Propellers
Power Levers
DOWN (below 156 KIAS) 3 GREENS
ON
CHECK
LO or HIGH IDLE as required
MAX RPM
SET
When Landing Assured
FLAPS DOWN FULL (below 130 KIAS)
After Landing
POWER in BETA or REVERSE as reqd
Go-Around
1.
2.
3.
4.
5.
TOGA switch
Power Levers
Airspeed
Flaps
Gear
PRESS
MAX POWER (1520 lbs-ft)
95 KIAS or above
UP
UP
After Landing
1.
2.
3.
4.
5.
6.
7.
Lights
Auto Ignition
Auto Feather
Ice Protection
Flaps
Trim
Electrical load
Landing OFF, Taxi ON
OFF
OFF
OFF, Engine Ice Vanes stay EXTENDED
UP
SET
Observe Limits
NORMAL PROCEDURES 9
V1.12 – 9 Mar 2014
Shutdown and Securing
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
Parking Brake
Transfer Pumps
Crossfeed
Inverter
Avionics Master Switch
Subpanel Switches
Cabin Mode Control
Blower
Bleed Air Valves
Oxygen Supply Control
ITT
SET
OFF
CLOSED
OFF
OFF
OFF
OFF
AUTO
CLOSED
OFF
BELOW 585°C FOR ONE MINUTE
12.
13.
14.
15.
Propellers
FEATHERED
Condition Levers
CUT-OFF
Boost Pumps
OFF below 10% Ng or less
DC Volt Loadmeters
CHECK VOLTAGE
(No voltage on one side indicates current limiter out)
18. Battery and Generators OFF
19.
20.
21.
22.
Tech Log
Control Lock
Cabin Lights
External Covers & Chocks
UPDATE
FIT only if aircraft will not be towed
CHECK OFF
INSTALL as required
Other Normal Procedures: After Start
External Power (if used)
Right Generator
Battery Condition
Left Generator
DISCONNECT, access door SECURED
ON
CHECK
ON
Engine Clearing
Condition Lever
Ignition and Engine Start Switch
Battery Switch
Boost Pump
Ignition and Engine Start Switch
Ignition and Engine Start Switch
Boost Pump
CUT-OFF
OFF
ON
ON
STARTER ONLY (min of 15 seconds)
OFF
OFF
NORMAL PROCEDURES 10
V1.12 – 9 Mar 2014
RNAV 1 or PRNAV Operating Procedures
• This aircraft has navigation equipment installed and approved for PRNAV & RNAV 1
• This procedures on this page have been written in accordance with JAA TGL10
• When these procedures are used, and when the Pilot-in-Command has had suitable
ground training in accordance with TGL10, for Private (non-AOC) operation the aircraft
is PRNAV and RNAV 1 compliant through the provisions of UK CAA ORS4-959
• The ICAO FPL codes are thus Item 10: SBDFGR/S Item 18: PBN/B2D2S1 NAV/SBAS
• Jeppesen hold a Type 2 LoA for the databses used in the GTN650s, thefore databse
integrity checks for private operation are not required other than as detailed below
A. Pre-Flight
(in addition to Normal Procedures)
1. Check NOTAMs for EGNOS and GPS serviceability and coverage
2. Check currency and coverage of GTN650 databases
B. Before Take-Off
1.
2.
3.
4.
5.
6.
Check both GTN650s self-test and check WAAS enabled
IF WAAS/EGNOS unavailable, perform GTN650 RAIM prediction
Enter Flight Plan and select Departure Procedure
Crosscheck procedure legs listed in the GTN650 with Jeppesen chart
Select GPS CDI mode in G600, check CDI slews to first track
Perform GPS position check on runway
After take-off
• Monitor tracking on G600 CDI scale (1nm) and GTN650 Integrity Annunciator
• Crosscheck RNAV guidance with conventional aids
C. Arrival
1.
2.
3.
4.
5.
6.
(in addition to Normal Procedures)
(in addition to Normal Procedures)
Select and load the Arrival Procedure in GTN650 #1
Crosscheck Procedure map display with Jeppesen charts
Select GPS CDI mode in G600, check CDI slews to first track
Prepare and brief the alternative non-PRNAV procedure
Complete gross error check using radio navaids
Monitor tracking on G600 CDI scale (1nm) and GTN650 Integrity Annunciator
RNAV 1 Capability Failure (eg. LoI alert)
Total failure of one GTN650
1. Revert to the working GTN650
2. Notify ATC
In the event of an LoI alert, monitor the GTN650s
for 1 minute, then initiate the procedures below
Loss of Integrity or other loss of RNAV 1 capability in both GTN650s
1. Select radio navigation aids and CDI source
2. Cancel GPS Roll Steer mode if engaged
3. Advise ATC and continue with non-RNAV procedure or as directed
NORMAL PROCEDURES 11
V1.12 – 9 Mar 2014
XLR Fuel Locker Notes
Locker useable fuel quantity is 260lbs (148l) per tank, total 520lbs (296l)
CAUTION
Do not transfer fuel from either Locker Tank when there is less than
400lbs of available fuel space in each Wing Tank
Avoid partial transfer of Locker fuel
Max lateral imbalance of combined Main and Locker fuel is 200lbs
LH and RH transfer should be concurrent to avoid imbalance
If Locker Fuel quantity is uncertain; complete the fuel transfer, or
drain or fill the tanks so that they are known to be full or empty
Locker Fuel Transfer
1. Fuel Gauges
CHECK >400lbs space each Wing tank
2. Locker Fuel Pumps
L & R both ON
3. LOCKER PUMP ON Lights L & R both continuously illuminated
4. Wing Fuel Quantity
5. Timing
Monitor L & R Fuel Gauges for increase
Note, transfer takes ~20mins
6. When L & R NO LOCKER XFR lights have illuminated:
a. Locker Fuel Pumps L & R both OFF
b. Annunciators
CHECK all OFF
c. Fuel gauges
CHECK
d. Flight planning
CHECK range and endurance
7. Verify fuel state is consistent with successful transfer by correlating
fuel gauge readings before and after transfer with engine fuel burn
during transfer. Record Locker Tanks as empty in aircraft Tech Log
“NO LOCKER XFR” Light Illumination
If the “NO LOCKER XFR” light illuminates other than upon expected completion of a
transfer, it is most likely that the illuminated-side pump has failed, or the system has
clogged or a fuel leak has occurred:
1. Locker Fuel Pumps
2. Fuel gauges
3. Flight planning
L & R both OFF
CHECK
RE-VERIFY range and endurance
NORMAL PROCEDURES 12
KFC250 Autopilot Operating Notes
V1.12 – 9 Mar 2014
(see AFM Supp for full detail)
Limitations: i. Autopilot operation is permitted up to Vmo (208 KIAS)
ii. Do not use the autopilot below the following altitudes:
Approach: 200ft AGL Climb: 500ft AGL Other: 1000ft AGL
iii. Do not use the autopilot or yaw damper during take-off or landing
1. Engage Procedure: use the Mode Controller in center pedestal
• Select the FLT DIR mode
• Push the AP engage lever to ON
2. Disengage Procedure
• Hold control wheel firmly, and monitor FD for unsatisfied commands or pitch mis-trim
• Push the Pilot’s AP YD DISC/TRIM INTRPT switch
3. ALT HOLD operation
• Press ALT switch on Mode Controller, observe ALT annunciator
• Pressure altitude from P1 analogue altimeter at time of engagement will be held
• Alternatively, use KAS297 ALT SELECT and ARM functions
4. ALT HOLD level change
• In ALT mode, press & hold the VERTICAL TRIM switch on the mode controller to climb
or descend ~600fpm and hold altitude at moment of switch release
• Or, disengage ALT mode, enter climb or descent using VERTICAL TRIM and capture
new altitude manually or with ALT SELECT and ARM
5. GPS Roll Steer Operation
• The Roll-Steer Selector/Annunciator left of the G600 toggles the autopilot’s HDG error
source in HDG mode between the G600 heading bug and the roll steer output of the
GDU620 when GPS1 or GPS2 source is displayed
• Roll-Steer mode is indicated by the GPSS symbol
on the left edge of the G600 PFD
6. NAV or APPR mode operation
• Select Nav source on G600 using CDI key, set desired course with CRS key
• Press NAV or APPR mode to intercept course and observe ARM annunciator
• Note CPLD annunciator when course intercepted and tracking coupled
7. GS operation – only in APPR CPLD operation with BCK CRS mode OFF
• GS CPLD mode automatically engages intercepting a valid glideslope signal
• GS CPLD mode disengages when any other vertical mode is selected
KFC250 Autopilot Emergency Procedures
EMERGENCY DISENGAGE OF AUTOPILOT AND ELEC TRIM
1. Control Wheel
HOLD FIRMLY
2. AP YD DISC/INTRPT button
PRESS AND HOLD, re-trim manually
3. Avionics Master switch
OFF, AP YD DISC/INTRPT button RELEASE
4. AP TRIM circuit breaker
PULL
5. Avionics Master switch
ON
ENGINE FAILURE
1. Disengage Autopilot, follow appropriate Emergency Procedure
2. Aileron and Rudder axes must be manually trimmed before Autopilot
engagement in One Engine Inoperative flight
V1.12 – 9 Mar 2014
GENERAL INFORMATION
NORMAL PROCEDURES
EMERGENCY PROCEDURES
OPERATING INFORMATION
EMERGENCY PROCEDURES 1
V1.12 – 9 Mar 2014
Emergency Airspeeds
Air Minimum Control Speed (Vmca)…………..90 KIAS
Intentional Single-Engine Speed (Vsse) ........ 97 KIAS
Single-engine Best Angle-of-Climb (Vxse)…….100 KIAS
Single-engine Best Rate-of-Climb (Vyse)… 110 KIAS
Maximum Maneuvering Speed (Va)………… 170 KIAS
Turbulent Air Penetration ............................. 160 KIAS
Maximum Range Glide Speed……...………. 100 KIAS
Engine Failure
ENGINE FAILURE AFTER TAKE-OFF – insufficient runway
Pitch UP > Power UP > Flap UP > Gear UP
Maintain 100 KIAS and control yaw
Identify failed engine – power lever IDLE
Shutdown failed engine
EMERGENCY ENGINE SHUTDOWN in the event of:
Engine Failure in flight
Engine Fire in flight
Engine Torque increase – uncontrolled, in ground or flight
Illumination of CHIP DETECT annunciator
Affected Engine:
1. Condition Lever
CUT-OFF
2. Propeller Lever
FEATHER
3. Fuel Firewall Valve
CLOSED
4. Secure inoperative engine:
a. Bleed Air Valve
AS REQUIRED
b. Engine Auto Ignition OFF
c. Boost Pump
OFF
d. Fuel Transfer Pump OFF
e. Crossfeed
CLOSED
f. Generator
OFF
g. Fuel Control Heat OFF
h. Autofeather
OFF
i. Propeller Synch
OFF
5. Electrical Load
MONITOR
EMERGENCY PROCEDURES 2
V1.12 – 9 Mar 2014
Engine Fire on Ground
Affected Engine:
1. Condition Lever
2. Fuel Firewall Valve
3. Starter Switch
4. Boost Pump
5. Fuel Transfer Pump
6. Crossfeed
CUT-OFF
CLOSED
STARTER ONLY
OFF
OFF
CLOSED
Engine Failure During Ground Roll
1. Power Levers
2. Brakes
IDLE
As Required
If insufficient runway remains for stopping:
3.
4.
5.
6.
Condition Lever
Fuel Firewall Valve
Master Switch
Boost Pumps
CUT-OFF
CLOSED
STARTER ONLY
OFF
Engine Failure In-Flight below Vmca 90KIAS
1.
2.
3.
4.
Reduce power on operative engine as req’d to maintain control
Lower nose to accelerate above minimum control speed
Adjust power as required
Secure affected engine as per EMERGENCY ENGINE SHUTDOWN
Flame-Out of Operating Engine
during One-Engine Inoperative Flight
1. Power Lever
2. Propeller
3. Condition Lever
IDLE
DO NOT FEATHER
CUT-OFF
4. Conduct AIR START procedures – see EMERGENCY PROCEDURES 3
EMERGENCY PROCEDURES 3
V1.12 – 9 Mar 2014
Air Start – STARTER ASSIST
1.
2.
3.
4.
Electrical Load
Power Lever
Condition Lever
Fuel Panel
a.
b.
c.
d.
5.
6.
7.
8.
9.
10.
11.
12.
Fuel Firewall Valve
Boost Pump
Transfer Pump
Crossfeed
Start Switch
Condition Lever
Start Switch
Generator
Propeller
Power Lever
Fuel Control Heat
Electrical Equipment
REDUCE (eg. Radar, Anti Ice, Cabin Temp Mode
IDLE
CUT-OFF
CHECK
OFF)
OPEN
ON
ON
AUTO
ON (up) Check IGNITION light ON
LOW IDLE (8 seconds after start switch ON)
OFF (Ng above 51%)
RESET momentarily, then ON
AS REQUIRED
AS REQUIRED
ON
AS REQUIRED
Air Start – WINDMILLING ENGINE AND PROP
1.
2.
3.
4.
5.
Electrical Load
Power Lever
Propeller
Condition Lever
Fuel Panel
a.
b.
c.
d.
5.
6.
7.
8.
9.
10.
11.
12.
13.
Fuel Firewall Valve
Boost Pump
Transfer Pump
Crossfeed
Generator (Inop Engine)
Airspeed
Altitude
Auto-Ignition
Condition Lever
Power and Prop Levers
Auto-Ignition
Fuel Control Heat
Electrical Equipment
REDUCE (eg. Radar, Anti Ice, Cabin Temp Mode
IDLE
MAX RPM
CUT-OFF
CHECK
OFF)
OPEN
ON
ON
AUTO
OFF
ABOVE 140 KIAS
BELOW 20,000 ft
ARM
LOW IDLE (8 seconds after Auto-Ign ARM)
AS REQUIRED (after ITT has peaked)
OFF
ON
AS REQUIRED
EMERGENCY PROCEDURES 4
V1.12 – 9 Mar 2014
Smoke or Fire or Fumes
Smoke and Fume elimination
Attempt to Identify the source of smoke or fumes. Smoke associated with electrical
failures is usually gray or tan in color, and irritating to the nose and eyes. Smoke
produced by environmental system failures Is generally white in color, and much less
irritating to the nose and eyes.
ELECTRICAL SMOKE OR FIRE
1. Oxygen
Control handle ON, Masks ON
2. Cabin Temp Mode
OFF
3. Vent Blower
AUTO
4. Avionics Master
OFF
5. Nonessential Electrics
OFF
If smoke or fire ceases
• Individually restore avionics & electrics, isolate defective equipment
If smoke or fire persists
• Cabin Pressure switch
DUMP
• Land as soon as practical
ENVIRONMENTAL SYSTEM SMOKE OR FUMES
1. Oxygen
Control handle ON, Masks ON
2. Cabin Temp Mode
OFF
3. Vent Blower
HI
4. LH Bleed Air
CLOSED
If smoke decreases
• Continue operation with LH Bleed Air closed
If smoke does not decrease
• LH Bleed Air
OPEN
• RH Bleed Air
CLOSED
• If smoke decreases, continue operation with RG Bleed Air Closed
Emergency Descent
1.
2.
3.
4.
5.
Power Levers
Propeller Controls
Wing Flaps
Landing Gear
Airspeed
IDLE
MAX RPM
APPROACH
EXTEND
156KIAS maximum
EMERGENCY PROCEDURES 5
V1.12 – 9 Mar 2014
Landing Emergencies
ONE ENGINE INOPERATIVE LANDING
When it is certain that the field can be reached:
1. Flaps
APPROACH
2. Landing Gear
DOWN
3. Propeller Controls
FULL FORWARD
4. Airspeed
110 KNOTS
When It is certain there is no possibility of go-around:
5. Flaps
DOWN
6. Airspeed
100 KNOTS
7. Execute Normal Landing
ONE ENGINE INOPERATIVE GO-AROUND
1.
2.
3.
4.
Power
Flaps
Landing Gear
Airspeed
MAXIMUM ALLOWABLE
UP
UP
107 KNOTS
Glide (both engines inoperative)
1.
2.
3.
4.
Flaps
Landing Gear
Propeller Controls
Airspeed
UP
UP
FEATHERED
150 KNOTS
Landing Gear Manual Extension
1.
2.
3.
4.
Airspeed
ESTABLISH 120 KNOTS
Landing Gear Relay CB
PULL (next to Gear handle, not on CB panel)
Landing Gear Handle
DOWN
Emergency Engage Handle:
 LIFT AND TURN CLOCKWISE TO THE STOP TO ENGAGE
5. Extension Lever
 PUMP up and down until the 3 green gear down lights are lit
Retraction after practice manual extension ONLY:
(i) Emergency Engage handle rotate counter clockwise and push down to stow
(ii) Extension lever stow (iii) Gear CB in (iv) Gear handle Up
EMERGENCY PROCEDURES 6
V1.12 – 9 Mar 2014
Low Oil Pressure
Oil Pressure values between 40 and 80 psi are undesirable: they
should be tolerated only for the completion of the flight, and then only at
a reduced power setting.
Oil pressure values below 40 psi are unsafe; they require either that
the engine be shut down, or !hat a landing be made as soon as possible,
using the minimum power required to sustain flight.
Fuel System Emergencies
BOOST PUMP FAILURE
1. Inoperative Boost Pump
OFF
2. Determine whether continuation of flight with Crossfeed open is
possible (refer to Flight Manual)
3. To continue flight with Crossfeed closed, satisfactory operation may
be obtained by reducing power, descending to a lower altitude,
waiting for fuel to cool
CROSSFEED (One Engine Inoperative operation)
1.
2.
3.
4.
Fuel Boost Pumps
Transfer Pumps
Crossfeed switch
NON-FEEDING tank
Both ON
ON
OPEN, Check FUEL CROSSFEED on
Fuel Boost Pump OFF and check
non-feeding side FUEL PRESS unlit
TO DISCONTINUE CROSSFEED
1. Fuel Boost Pumps
2. Crossfeed switch
3. Fuel Boost Pump
Both ON
CLOSED
OFF (inoperative engine only)
NOTE: The Crossfeed system is designed solely for operation in the event of a Fuel
Boost Pump failure or an Engine failure. The normal position of the Crossfeed switch
with both engines running is AUTO with the FUEL CROSSFEED annunciator unlit
Uncommanded Electric Pitch Trim operation
1.
2.
3.
4.
Attitude
CONTROL MANUALLY
AP/Trim Disconnect Switch DEPRESS FULLY
Manually re-trim airplane
ELEV TAB switch (pedestal) OFF
EMERGENCY PROCEDURES 7
V1.12 – 9 Mar 2014
Electrical System Failure
GENERATOR INOPERATIVE (DC GEN annunciator lit)
1. Starter switch
Check OFF
2. Generator switch
RESET momentarily then ON
If Generator will not reset
2. Generator Switch
OFF
3. Operating Generator
Do not exceed Load of 1.0
EXCESSIVE LOADMETER INDICATION (over 1.0)
1. Battery Switch
OFF
If Loadmeter still indicates above 1.0
2. Non-essential Electrics
OFF
If Loadmeter indicates 1.0 or below
3. Battery Switch
ON
CIRCUIT BREAKER TRIPPED
 Non-essential Circuit
DO NOT RESET IN FLIGHT
 Essential Circuit
RESET ONCE ONLY
SUBPANEL FEEDER CIRCUIT BREAKER TRIPPED
(fuel panel bus feeders and right circuit breaker panel bus feeders)
 A short is indicated
DO NOT RESET IN FLIGHT
INVERTER INOPERATIVE (INVERTER annunciator lit)
1. Select the other inverter
AVIONICS POWER SWITCH FAILURE
1. Pull the Avionics Master CB (system defaults to powered)
Pressurization System (differential pressure in red arc)
1. Cabin Altitude controller
If condition persists
2. Bleed Air valves
3. Cabin Pressure Switch
4. Bleed Air valves
SET HIGHER
CLOSED
DUMP
OPEN
Emergency Exit Hatch (third right cabin window)
1. Emergency hatch cover
OPEN
2. Release button
PUSH (or pull hooks then push button)
3. PULL handle and PUSH out hatch
Inadvertent Spin
Control wheel FWD, rudder OPPOSITE, power IDLE, aileron NEUTRAL
V1.12 – 9 Mar 2014
GENERAL INFORMATION
NORMAL PROCEDURES
EMERGENCY PROCEDURES
OPERATING INFORMATION
•
Mass and Balance
•
Performance
•
Operations
V1.12 – 9 Mar 2014
Mass and Balance 1
Loading definitions and notes
The following Loading definitions are used in this manual and associated materials:
(including Flight Planning sheet, M&B Worksheet and RocketRoute.Com aircraft model)
Cabin
Fuel tanks
“Nose Baggage” Max 350lbs
Main tank
Nose baggage area forward of
avionics bay.
Not used in normal operation.
Nacelle 4 intertank
connected
Wing tanks
“Crew”
Includes Pilot and Co-Pilot and
items stowed in the cockpit
area and cabinets
Pilot mass is NOT included
in Empty Mass of 6840lbs
“Forward Pax”
The forward pair of aft-facing
seats in the main cabin
“Aft Pax”
The rear pair of forward-facing
seats in the main cabin
Locker tank
The 4 interconnected wing tanks are
considered one single Wing tank for all
operating purposes
For fuel and mass planning, the Nacelle &
Wing tanks are treated as the “Main tank”
The “Locker tank” is a separate system, and
its fuel must be transferred to the Main Tank
The entire fuel system is symmetrical on the
left and right sides of the aircraft
Note: Fuel filling sequence
“Side Pax”
The Side-Facing seat opposite
the main cabin door
1
“Aft Baggage” Max 350lbs
The right-hand side area from the
rear partition to the aft bulkhead
Assume 20lbs for Life raft,
External Covers & other items
There is no LH/RH
imbalance limit whilst
loading fuel. In flight,
the limit is 200lbs.
2
3
Note that fuel crews are unfamiliar
with the rare C90 Locker tank
installation. If required, verify the
Locker tanks have been filled
“Lav Pax”
The aft-most belted seat, with a
lavatory beneath the seat cushion
Fuel Capacity
Both Wings
One Wing
Pounds
Main
Locker
Total
US gal
Litres
Main
1285
192
732
260
39
148
Locker
1545
231
881
Total
Pounds
US gal
Litres
2570
384
1465
520
78
296
3090
461
1761
V1.12 – 9 Mar 2014
Mass and Balance 2
Mass, Balance and Loading Limits
Max Ramp Mass
Max Take-off Mass
Max Landing Mass
Max Zero Fuel Mass
Metric MTOM
10560 lbs
10500 lbs
9700 lbs
9000 lbs
4773 kg
Empty Mass
Useful Load
Load w/Mains full
Load w/Max Fuel
Max Load
6840 lbs
3720 lbs
1150 lbs
630 lbs
2160 lbs
Mass and Balance envelope and limit examples
Fwd example 1:
2 Crew, 400lbs
No other occupants
No baggage
Fwd example 2:
1 Crew, 200lbs
No other occupants
No baggage
Aft example 1:
1 Crew,180lbs
2 Aft Pax, 400lbs
Aft bags 50lbs
Aft example 2:
1 Crew,200lbs
No other occupants
Aft bags 300lbs
Mass
10700
lbs
10500
10300
10100
3090 lbs
fuel
9900
9700
9500
2570 lbs
fuel
9300
9100
8900
2000 lbs
fuel
8700
1500 lbs fuel
8500
148
150
152
154
156
158
Centre of Gravity inches aft of datum
160
The CG limits are unlikely to be exceed with normal loading if the aircraft mass is below the
MTOM limit. Therefore, as an alternative to calculating CG, the following criteria may be used
1. With no aft load and no forward baggage, a Crew mass of 400lbs or less will assure a
CG within the forward limit at any fuel load. With 20lbs in the Aft baggage area, the
Crew mass may be 450lbs.
2. With only a single 180lb crew member on board, a mass in the Aft baggage area of
300lbs or less will assure the CG remains within the aft limit
These criteria are included in the Mass & Balance section of the Preflight Planning Sheet
V1.12 – 9 Mar 2014
Mass and Balance 3
Mass and Balance Worksheet
Note: Main Fuel arm varies with tank
contents, 150” is an approximation.
Empty Mass
Nose Bags
LH Crew
RH Crew
LH Pax Fwd
RH Pax Fwd
LH Pax Aft
RH Pax Aft
Side Pax rear
Lav Pax rear
LH Main Fuel
RH Main Fuel
LH Locker Fuel
RH Locker Fuel
Aft Bags
Load totals
Zero Fuel Mass
Ramp M&B
max 10560 lbs
less taxi fuel
Mass
Arm
Moment
lbs
in
lbs-in/100
6840
155
10602
70
129
129
168
168
212
212
245
285
150
150
189
189
282
max 9000 lbs
150
60lbs is standard taxi fuel
Take Off M&B
max 10500 lbs
less take-off fuel
less cruise fuel
Landing M&B
max 9700 lbs
150
150
V1.12 – 9 Mar 2014
Mass and Balance 4
Mass and Volume unit conversion
(6.7lbs/US Gallon 0.57litres/lb)
lbs
USgal
litres
lbs
USgal
litres
50
100
150
200
250
300
350
400
450
500
550
600
650
700
750
800
850
900
950
1000
1050
1100
1150
1200
1250
1285
7
15
22
30
37
45
52
60
67
75
82
90
97
104
112
119
127
134
142
149
157
164
172
179
187
192
One Main Full
29
57
86
114
143
171
200
228
257
285
314
342
371
399
428
456
485
513
542
570
599
627
656
684
713
732
1300
1350
1400
1450
1500
1550
1600
1650
1700
1750
1800
1850
1900
1950
2000
2050
2100
2150
2200
2250
2300
2350
2400
2450
2500
2570
194
201
209
216
224
231
239
246
254
261
269
276
284
291
299
306
313
321
328
336
343
351
358
366
373
384
Both Mains Full
741
770
798
827
855
884
912
941
969
998
1026
1055
1083
1112
1140
1169
1197
1226
1254
1283
1311
1340
1368
1397
1425
1465
1335
199
761
1385
207
789
1435
214
818
1485
222
846
1535
229
875
1545
231
881
1x Main & Locker Full
2670
399
1522
2770
413
1579
2870
428
1636
2970
443
1693
3070
458
1750
3090
461
1761
2 Main & 2 Locker Full
V1.12 – 9 Mar 2014
This page intentionally blank
V1.12 – 9 Mar 2014
GENERAL INFORMATION
NORMAL PROCEDURES
EMERGENCY PROCEDURES
OPERATING INFORMATION
•
Mass and Balance
•
Performance
•
Operations
Performance data is drawn from the Raisbeck AFM Supplement, which includes the
Blackhawk XP Engine modification and 10500lb MTOM STC and supersedes the
original AFM
The priority sequence for LJ-972’s Flight Manual is
1.
Raisbeck AFMS content
2.
Blackhawk AFMS content not available in the Raisbeck AFMS
3.
Beechcraft AFM content
The “G-VBCD Preflight Planning Sheet” is an acceptable means of planning for
all operations conforming to the simplified criteria on that sheet. This section of
the manual is for more detailed calculations and cross-checks
Take Off Distance – 0% Flaps – 2 Engines
V1.12 – 9 Mar 2014
Associated Conditions:
Power……Take-off Power set before brake release
Both Engines idle at V1
Flaps……..Up
Gear………Retract after Lift-Off
Runway…Paved, Level, Dry Surface
Braking…..Max without tires slipping
Weight - lbs
10,500
10,000
9,000
8,000
V1 KIAS
95
94
90
85
Accelerate-Stop Distance
Example:
OAT……………………………….. 25 C
Pressure Altitude…………… 3966 ft
Take-Off Weight……………. 9650 lbs
Headwind Component….. 10 knots
Accel-Stop Distance……… 3813 ft
V1……………………………….... 94 KIAS
Accelerate-STOP Distance
V1.12 – 9 Mar 2014
Accelerate-GO Distance
V1.12 – 9 Mar 2014
-50
-40
-30
Associated Conditions:
Power…… Max Continuous
Flaps…….. Up
Gear……… Up
-10
0
10
20
Outside Air Temperature: OC
-20
30000 ft
28000 ft
26000 ft
24000 ft
22000 ft
20000 ft
18000 ft
16000 ft
30
14000 ft
12000 ft
40
10000 ft
8000 ft
50
Sea Level
4000 ft
6000 ft
Climb Speed 112 KIAS (all weights)
10000
10350 ref line
10500 MTOW
Ref Line
8000
Weight: Pounds
9000
0
7000
500
1000
1500
2000
Example:
OAT……………………………….. -10 C
Pressure Altitude…………… 17000 ft
Take-Off Weight……………. 9400 lbs
Rate Of Climb………………… 1788 fpm
Climb Gradient…………...... 12.8%
2500
0%
1%
2%
3%
4%
5%
6%
7%
8%
9%
10%
11%
12%
13%
14%
15%
16%
17%
18%
20%
19%
Climb
Gradient
%
Rate of Climb fpm
Climb – Two Engines – Flap Up
Climb - 2 Engines – Flap Up
V1.12 – 9 Mar 2014
-50
-40
-30
-10
0
10
30
16000 ft
20
Outside Air Temperature: OC
-20
14000 ft
12000 ft
40
10000 ft
8000 ft
50
Ref Line
10000
10350 ref line
10500 MTOW
Sea Level
2000 ft
4000 ft
6000 ft
Climb Speed 108 KIAS (all weights)
8000
Weight: Pounds
9000
100
200
300
400
500
600
700
800
900
1000
0
7000
Example:
OAT……………………………….. -4 C
Pressure Altitude…………… 9000 ft
Take-Off Weight……………. 9400 lbs
Rate Of Climb………………… 550 fpm
Climb Gradient…………...... 4.3%
0%
1%
2%
3%
4%
5%
6%
7%
8%
Climb
Gradient
%
Rate of Climb fpm
Climb – One Engine Inoperative – Flap Up
Associated Conditions:
Power…… Max Continuous
Flaps…….. Up
Gear……… Up
Inop Prop. Feathered
Climb – One Engine Inoperative - Flap Up
V1.12 – 9 Mar 2014
Service Ceiling (OEI) : Feet
13000
-10
14000
15000
16000
17000
18000
19000
20000
-5
0
5
15
Outside Air Temperature: OC at Route Segment MEA
10
Note: Service Ceiling (OEI) is the maximum pressure altitude at which the
airplane is capable of climbing at 50fpm with one propeller feathered
Note: Use the highest (worst case) route segment MEA for this calculation
20
Service Ceiling – One Engine Inoperative
Assume Service Ceiling (OEI) at max
weight is above MEA (up to a max of
20,000ft) when conditions are ISA + 20C or
cooler, otherwise calculate from this chart
Associated Conditions:
Power…… Max Continuous
Flaps…….. Up
Gear……… Up
Inop Prop. Feathered
25
Example:
OAT of MEA…………………… 10 C
Route Segment MEA……… 9000 ft
Weight…………………………… 9500 lbs
Service Ceiling (OEI).……… 18860 ft
30
Service Ceiling – One Engine Inoperative
V1.12 – 9 Mar 2014
-30
-10
0
10
20
30
40
10000 ft
8000 ft
6000 ft
Outside Air Temperature: OC
-20
4000 ft
2000 ft
Sea Level
Associated Conditions:
Power…… Retard to maintain 800fpm
descent on final approach
Flaps…….. 100%
Brakes……… Max braking
Runway… Paved, Level, Dry Surface
10000
9700lbs MLW
ref line
9000
8000
7000
Approach Speed
100 KIAS
97 KIAS
92 KIAS
86 KIAS
Weight: Pounds
Reference Line
Weight - lbs
9700
9000
8000
7000
0
10
20
30
0
Obstacle Height: Feet
Reference Line
Wind Component: Knots
-10
Reference Line
50
500
1000
1500
2000
2500
3000
3500
Example:
OAT……………………………….. 15 C
Pressure Altitude…………… 5650 ft
Landing Weight……………. 8855 lbs
Headwind Component….. 10 knots
Ground Roll…………………… 1050 ft
Total Dist. over 50ft obst.. 2160 ft
Approach Speed……………. 96 KIAS
Total Distance for Take-Off: Feet
Landing Distance – 100% Flaps – No Prop Rvrs
Landing Distance:
100% Flap - No Prop Reverse
V1.12 – 9 Mar 2014
Cruise performance and fuel required
V1.12 – 9 Mar 2014
Cruise Performance
See also note on Cruise Performance on page “Operating Manual notes”
Altitude
KTAS
Torque
Sea Level
165
730 ft lbs
Fuel Flow 250lbs/engine/hr
FL050
FL100
FL150
FL200
FL250
180
210
225
240
255
800 ft lbs 1000 ft lbs 1040 ft lbs 1070 ft lbs 1100 ft lbs
For cruise planning purposes at FL220-250, assume
> 250 KTAS
> 250lbs/engine/hour Fuel Flow
Minimum Fuel Required
(example cruise: 250KTAS, 250lbs/hr x2)
See also note on Fuel Planning on page
“Operating Manual notes”
1 Taxi fuel
2 Take-off & Climb fuel
60
lbs
190
lbs
Guide to Minimum Fuel Required
given distance and flight conditions
IFR VFR
3090
3000
increment over cruise burn assume zero distance
Cruise (FL200-250)
3 Distance (including climb)
4 Groundspeed
5 Time Enroute
=3/4
6 Cruise fuel flow (both engines)
7 Cruise burn
250
500
nm
kts
hrs
lbs
8 Trip Fuel
=1+2+7
lbs
9 Contingency 5%
5% of 8
lbs
250
11 Total VFR Fuel Reqd
=8+9+10
=1+8+9+10
12 Alternate distance
13 Alternate time
14 Alternate fuel
=13*6
75
0.5
nm
hrs
250
lbs
1500
1000
lbs
In normal operation, load 200lbs extra
ALWAYS LOAD 200lbs EXTRA FUEL
fuel above the minimum fuel required
ABOVE FUEL REQUIRED
2000
lbs
lbs
15 Total IFR Fuel Reqd
11+14
= =1+8+9+10+14
2500
lbs/hr
=5*6
10 Final Reserve
30min hold @1500'
Fuel
lbs
Distance nm
(100nm alternate)
500
0
500
1000
1500
V1.12 – 9 Mar 2014
PERFORMANCE SUMMARY
Departure runway performance
(zero wind)
Vr 95KIAS ZERO FLAP
If actual take-off conditions are all equal to or better than this example, these performance numbers
may be assumed. Otherwise, calculate actual performance
OAT
Elevation
Take-off Mass
+25 C
2000 ft
10500 lbs
SID climb performance
Feet
Metres
Take-Off to 50ft
2450
750
Accelerate-Stop
4500
1375
Accelerate-Go
3600
1100
Normal: 112KIAS OEI: 108KIAS
Illustrative climb rate and gradient at 6000’, ISA+12 and MTOM. If conditions are more demanding,
calculate actual performance
OAT
Elevation
Mass
+15 C
6000 ft
10500 lbs
Gradient
Climb
Two Engine
13%
1830 fpm
Single Engine
3.4%
450 fpm
Service Ceiling – One Engine Inoperative
For OAT at MEA of ISA+20C or cooler, assume max OEI Service Ceiling of 20,000’ is available. For
exceptional higher temperatures, calculate actual OEI Service Ceiling.
MEA
OAT @ MEA
Mass
Service
Ceiling
20000 ft
-5C
(ISA+20C)
Single Engine
20,000’
10500 lbs
Landing runway performance
(zero wind)
100KIAS FULL FLAP
If actual landing conditions are all equal to or better than this example, these performance numbers
may be assumed. Otherwise, calculate actual performance
OAT
Elevation
Landing Mass
+25 C
2000 ft
9700 lbs
Missed Approach climb
Landing distance
over 50’ obstacle
Ground roll
Feet
Metres
2300
700
1150
350
Normal: 112KIAS OEI: 108KIAS
Illustrative climb rate and gradient at 2000’, 25C and MLM. If conditions are more demanding,
calculate actual performance
OAT
Elevation
Mass
Gradient
Climb
Two Engine
16%
2150 fpm
Single Engine
4.5%
580 fpm
+25 C
2000 ft
9700 lbs
V1.12 – 9 Mar 2014
GENERAL INFORMATION
NORMAL PROCEDURES
EMERGENCY PROCEDURES
OPERATING INFORMATION
•
Mass and Balance
•
Performance
•
Operations
Planning and Operating Procedures
V1.12 – 9 Mar 2014
Destination and Alternate weather
All operations require Destination and an Alternate with forecasts at or above applicable minima
In-flight, it is permitted, with caution, for only one of Destination or Alternate to be above minima
Destination Forecast x
SUMMARY TABLE
Alternate
Forecast
VMC
>= AOM
VMC
Acceptable
Acceptable
>= AOM
Acceptable
Acceptable
Below AOM
In-flight only
In-flight only
Below AOM
In-flight only
In-flight only
Not acceptable
Fuel requirements
The summary table below details the fuel planning and fuel state recommended under this Manual.
This is based on EASA OPS and is more demanding than the present UK ANO rules applicable
1. Taxi fuel
2. Trip fuel
3. Contingency of 5%
4. Alternate fuel
5. Final reserve, 30min
Preflight
Required
Required
Required
Required
Required, further 200lbs desirable
Enroute
n/a
Required
Not required
Subject to judgement
Required, further 200lbs desirable
Aerodrome Operating Minima: Departure
The minimum RVR for departure shall be the greater of
1. the UK statutory minimum of 150m, ref. ANO 109.2.b
2. Any minima specified by the airport operator, eg. no lower than 250m RVR
3. The landing minima, unless a take-off alternate is available within 30mins flying time
4. If a One Engine Inoperative take-off path is not available from aerodrome elevation, 800m
Aerodrome Operating Minima: Landing
1.
The minima used shall be those published in the Jeppesen plates, taking into account
- the operational status of lighting and RVR reporting
- Approach Category B
- LPV, LNAV/VNAV, ILS Cat I approvals as applicable
2.
PEC shall not apply. Temperature corrections shall not apply above a sea level OAT of -5C. Below
that, increase indicated DH 10% for every 20C below ISA. Note effect on terrain clearance of very
cold conditions but DO NOT adjust procedure or ATC cleared altitudes without ATC agreement.
3.
All non-precision approaches shall be flown using the CDFA method. The PIC may elect to add
50’ to a CDFA DA(H) in accordance with UK CAA recommendations, but this is not mandatory
RVR
4.
If single-pilot and for any procedure other than an autopilot-coupled ILS or LPV approach, use the
higher of the calculated minimum RVR and 800m
5.
In accordance with the “Approach Ban”, do not descend below 1000’ AAE or the equivalent of the
Outer Marker position unless the RVR is at or above the applicable minima
6.
It is recommended that, if RVR falls below minima after passing 1000’ AAE, the approach shall be
discontinued immediately rather than continuing descent to DA(H)
7.
Repeated approaches and missed approaches are at the pilot’s discretion. It is recommended that
a diversion shall be executed after the second missed approach
Normal Instrument Approach Procedure
(Precision or CDFA)
Normal Instrument Approach
V1.12 – 9 Mar 2014
Single-Engine Instrument Approach Procedure
(Precision or CDFA)
Single-Engine Instrument Approach
V1.12 – 9 Mar 2014
Operating Manual notes
V1.12 – 9 Mar 2014
Cruise Performance
The Blackhawk & Raisbeck FM Supplements corresponding to the PT6A-135A engine installation do not
include cruise speed or fuel burn performance tables, and refer to the Beech factory tables (corresponding to
the original PT6A-21 engines) with the comment that at comparable power settings, the PT6A-135As provide
fuel flow and TAS which is at least as good.
However, the -135As make significantly great power available at cruise altitudes and the Supplement
comment is that “pilots should be aware that increased fuel consumption results when operating this airplane
at power levels greater than achievable with the original engines”
For practical purposes, the cruise performance data in the AFM is not meaningful, and the Cruise
Performance table in this manual should be used instead. This has slightly and consistently conservative
data relative to that observed in flight in G-VBCD in a variety of conditions.
Fuel Planning
The usual method for mass & balance, range, payload and fuel planning is to use the G-VBCD aircraft model
available under the operators’ login at www.RocketRoute.com, and to have an electronic or paper version of
the Flight Briefing pack available in-cockpit.This model is accurate for mass & balance, and the aircraft may
be loaded to limits on this basis. The model is an approximation for range, payload and performance and in
typical operation the minimum fuel loaded should exceed the minimum fuel required (as calculated by
the model) by 200lbs total to allow for a margin in excess of the reserves and contingencies required under
EU OPS and the UK ANO.
The 200lbs extra fuel should also be loaded when using this manual for performance planning. If this extra
load is not practical, additional caution must be taken, using in-flight performance monitoring, enroute fuel
alternates and considering weather/traffic contingencies as appropriate
No fuel totalizer is fitted to G-VBCD and the fuel state for planning purposes should be taken as the lower of
the total indicated by the gauges and the departure fuel minus the estimated fuel burn. Prior to departure,
and for loads other than full tanks visually inspected as such, in the event of a discrepancy between the fuel
quantity indicated by the gauges and the fuel recorded in the tech log, use the lower of the two quantities
Flights requiring fuel from the XLR Fuel Lockers must have an Enroute Fuel Alternate available in case the
locker fuel transfer can not be accomplished
Cold Temperature operation
Cold Start: the engines may be started at temperatures at or above -40C
Fuel system icing inhibitor (PRIST) is NOT required except in extraordinarily cold circumstances
There is no in-flight OAT minimum limit but note that
• Fuel temperature is assumed to be equal to OAT
• The AFM Limitations section page 2-6 charts minimum Oil Temperature required for a given OAT,
to assure oil heating at the FCU will prevent fuel icing
• This limit may be simplified as
MIN OIL TEMP IN POSITIVE DEGREES C = OAT IN NEGATIVE DEGREES C
For example, at an OAT of -40C, minimum oil temp is +40C
• In practice, this limit is very unlikely to be exceeded
Rounding of numbers
This manual uses some numbers that have been rounded where this simplifies calculation and memory
items with no material effect on operation. The instances of rounding are:
AIRSPEEDS
Vx rounded from 101KIAS to 100KIAS
Vy rounded from 111KIAS to 110KIAS
Va rounded from 169KIAS to 170KIAS
Turbulent Air penetration speed from 161KIAS to 160KIAS
MASS
Aircraft Empty Mass rounded up from 6833lbs to 6840lbs
Each Main Fuel Tank full load rounded down from 1286lbs to 1285lbs
The net effect is to reduce full fuel payload by 5lbs and part fuel payload by 7lbs
V1.12 – 9 Mar 2014