BHT-407-FM-2 TR-2

BHT-407-FM-2
ROTORCRAFT
FLIGHT MANUAL
TEMPORARY REVISION
FOR
OVERSPEED ADAPTER
Insert these Temporary Revision pages opposite like
numbered pages in the basic Flight Manual after helicopter
has accomplished ASB 407-14-102.
DO NOT remove existing pages. DO NOT remove temporary
pages until replacement pages are received or temporary
pages are canceled.
THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS
COPYRIGHT NOTICE
COPYRIGHT
2014
BELL ® HELICOPTER TEXTRON INC.
AND BELL HELICOPTER TEXTRON
CANADA LTD.
ALL RIGHTS RESERVED
Export Classification C, ECCN EAR99
POST OFFICE BOX 482
FORT WORTH, TEXAS 76101
4 MARCH 2011
REVISION 3 — 15 APRIL 2013
TEMPORARY REVISION (TR-2) — 16 DECEMBER 2013
REISSUE — 25 APRIL 2014
BHT-407-FM-2
LOG OF REVISIONS
Original ......................0 ..................... 16 DEC 13
Reissue ..................... 0 ......................25 APR 14
LOG OF PAGES
PAGE
REVISION
NO.
PAGE
REVISION
NO.
Title .............................................................. 0
A/B................................................................ 0
C/D................................................................ 0
E/F ................................................................ 0
2-8................................................................. 0
2-14 – 2-15 ................................................... 0
NOTICE
Changed information in this Temporary Revision appears in bold type.
All other information is outlined.
Export Classification C, ECCN EAR99
16 DEC 2013 — Temporary Revision (TR-2)
25 APR 2014 — Reissue
A/B
A/B
BHT-407-FM-2
LOG OF TC APPROVED REVISIONS
Original ......................0 ..................... 16 DEC 13
Reissue ..................... 0......................25 APR 14
APPROVED
DATE
CHIEF, FLIGHT TEST
FOR
DIRECTOR — NATIONAL AIRCRAFT CERTIFICATION
TRANSPORT CANADA
Export Classification C, ECCN EAR99
16 DEC 2013 — Temporary Revision (TR-2)
25 APR 2014 — Reissue
C/D
C/D
BHT-407-FM-2
LOG OF FAA APPROVED REVISIONS
Original ......................0 ......................08 JAN 14
Export Classification C, ECCN EAR99
Reissue ..................... 0..................... 09 MAY 14
16 DEC 2013 — Temporary Revision (TR-2)
25 APR 2014 — Reissue
E/F
E/F
BHT-407-FM-2
2-4. INTERIOR
CHECK
TC APPROVED
AND
PRESTART
Display units are not compatible with
use of polarized sunglasses.
1.
Cabin interior — Clean, equipment
secured.
2.
Fire extinguisher — Installed and
secured.
3.
Cabin loading — Maintain CG within
limits.
4.
Passenger seat belts — Secured.
5.
Copilot seat belt — Secured (if solo).
6.
Doors — Secured.
7.
Throttle — Closed.
8.
LDG LTS switch — OFF.
9.
Emergency pedal stop
handle — In and lockwired.
release
10. Standby altimeter — Set.
11. Overhead switches — Set:
a.
BATT switch — OFF.
b.
GEN switch — OFF.
c.
PART SEP switch (if installed) —
OFF.
d.
ANTI COLL LT switch — ANTI
COLL LT (on).
e.
HYD SYS switch — HYD SYS
17. CAS messages — ENG OUT, XMSN
OIL PRESS, HYDRAULIC SYSTEM,
GEN FAIL, L/FUEL BOOST, R/FUEL
BOOST, L/FUEL XFR, R/FUEL XFR,
FADEC DEGRADED, FADEC FAULT,
and WOG will be illuminated.
NOTE
If faults OSFlt, prim_gov_fail, and
hmu_os_sol are not displayed, or are
displayed in white (historical), select
2-8
2-8
Temporary Revision (TR-2) — 16 DEC 2013
Reissue — 25 APR 2014
Clear History and press ENT. This
will refresh the display and list the
faults in yellow (current).
17a. AUX OEM-DIAGNOSTICS/ENG/ECU
FAULTS page — Confirm faults
OSFlt,
prim_gov_fail,
and
hmu_os_sol are listed in yellow.
17b. Throttle — Idle position.
17c. FADEC MODE switch — Cycle to
MAN and back to AUTO.
NOTE
If faults OSFlt, prim_gov_fail, and
hmu_os_sol do not transition from
yellow (current) to white (historical),
select Clear History and press ENT.
This will refresh the display and clear
the faults from the page.
17d. AUX OEM-DIAGNOSTICS/ENG/ECU
FAULTS page — Confirm OSFlt,
prim_gov_fail, and hmu_os_sol are
listed in white.
17e. Select Clear History and press ENT.
This will refresh the display and clear
the faults from the page.
17f. Throttle — Closed position.
17g. CAS messages — Confirm FADEC
DEGRADED and FADEC FAULT are
extinguished.
NOTE
L/FUEL XFR and R/FUEL XFR will
not be illuminated when forward fuel
tank is empty.
18. Pedals — Centered.
PEDAL STOP TEST button — Press
— Verify PEDAL STOP message
illuminates and left pedal travel
restricted. Return to center pedal
position,
verify
PEDAL
STOP
message extinguishes, and both
Export Classification C, ECCN EAR99
BHT-407-FM-2
1.
TC APPROVED
FUEL QTY FWD TANK button —
Press, note forward fuel tank
indication.
2-11.ENGINE SHUTDOWN
F u l l fo rw a r d f u el ta n k q u a nt it y
(approximately 256.0 pounds) will be
indicated at approximately
770.0 pounds or greater total fuel.
Fuel transfer will be complete at
approximately 193.1 pounds total
fuel.
1.
Collective — Full down.
2.
Cyclic and pedals — Centered and
CYC CTR message extinguished.
3.
Cyclic friction — Increase so that
cyclic maintains centered position.
4.
LDG LTS switch — OFF.
5.
Throttle — Reduce to idle stop.
Check
RPM
warning
light
illuminated and audio on at 95% NR.
Descent and Landing
Large reductions in collective pitch
a t he a v y G W m a y p e rm it N R t o
increase independent of NP (needles
split). Main rotor may be reengaged
with a smooth increase in collective
pitch.
1.
2.
Rear facing seat headrests
Adjusted to proper position.
NOTE
If dual controls are installed, guard
th rottle to prevent inadve rten t
manipulation from copilot position.
3.
Throttle — Fly detent position. Check
99 to 100% NP.
4.
Flight path — As required for type of
approach.
ENG ANTI ICE — As required.
6.
LDG LTS switch — As desired.
RPM warning light — Press to mute
audio.
7.
MGT — Stabilize at idle for 2
minutes.
8.
ENG ANTI ICE switch — OFF.
9.
FUEL BOOST/XFR LEFT
breaker switch — OFF.
—
Flight controls — Adjust friction as
desired.
5.
6.
During run-on or slope landings,
disregard CYC CTR message and
position cyclic as required. After
landing is completed and collective
is full down, reposition cyclic so that
CYC CTR message is extinguished.
circuit
NOTE
Left fuel boost and transfer pumps
will continue to operate until either
LE F T FUE L B O OS T /XF R c ircu it
breaker switch (highlighted with
y e ll o w bo r de r ) o r F U E L V A L V E
switch is positioned to OFF. These
pumps operate directly from battery
and will not be deactivated when
BATT switch is OFF. Battery power
will be depleted if both switches
remain on.
10. ELT (if installed) — Check
inadvertent transmission.
for
11. GEN switch — OFF.
12. Deleted.
2-14
2-14
Temporary Revision (TR-2) — 16 DEC 2013
Reissue — 25 APR 2014
Export Classification C, ECCN EAR99
TC APPROVED
BHT-407-FM-2
TO SLOW ROTOR
COASTDOWN.
NOTE
With overspeed adapter installed,
overspeed shutdown test shall not
b e u s ed . If F A D E C O V S P T E S T
button is pressed with engine
running, engine will not shut down
and FADEC FAULT and FADEC
DEGRADED cautions will illuminate.
18. Pilot — Remain on flight controls
until rotor has come to a complete
stop.
19. ANTI COLL LT switch — As desired.
13. IDLE REL switch — Press and hold.
CAUTION
20. All remaining overhead switches,
except HYD SYS switch — OFF.
Ensure engine rotation has
completely stopped prior to
positioning BATT switch to OFF.
21. BATT switch — OFF, with NG at 0%.
POSITIONING THROTTLE OUT OF
CUTOFF DURING NG SPOOL DOWN
MAY CAUSE POST ENGINE
SHUTDOWN FIRE.
14. Throttle — Closed; check MGT and
NG
decreasing,
ENGINE
OUT
warning message illuminated and
audio on at 55 ±1%.
15. MASTER W/C light — Press to
extinguish and mute audio.
AVOID RAPID ENGAGEMENT OF
ROTOR BRAKE IF HELICOPTER IS
ON ICE OR OTHER SLIPPERY OR
LOOSE SURFAC E TO PREVENT
ROTATION OF HELICOPTER.
APPLICABLE MAINTENANCE
ACTION MUST BE PERFO RMED
PRIOR TO FURTHER FLIGHT IF A
FADEC
MESSAGE
HAS
ILLUMINATED DURING THE
PREVIOUS FLIGHT OR ON ENGINE
SHUTDOWN.
If shutting down at, or refueling to,
between approximately 193 to
211 pounds total fuel quantity, up to
18 pounds of fuel may remain in
forward fuel cell as unusable.
Postflight Check
If any of following conditions exist:
16. Rotor brake (if installed) — Apply full
rotor brake at or below 40% NR.
Return rotor brake handle to stowed
position just prior to main rotor
stopping.
•
Thunderstorms are in local area or
forecasted.
•
Winds in excess of 35 knots or a
gust spread of 15 knots exists or is
forecasted.
•
Helicopter is parked within 150 feet
of hovering or taxiing aircraft that
17. FUEL VALVE switch — OFF.
DO NOT INCREASE COLLECTIVE OR
APPLY LEFT TAIL ROTOR PEDAL
Export Classification C, ECCN EAR99
DURING
16 DEC 2013 — Temporary Revision (TR-2)
25 APR 2014 — Reissue
2-15
2-15

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