Engine Start Flashcards
W W C - BEFORE STARTING ENGINES
- Before engine operation can be performed,
all main rotor tiedowns shall be removed. - All pilots shall complete the flight control
access evaluation from the seat that they
intend to use during flight. During preflight
checks, the pilot and copilot must ensure all
primary flight, propulsion, and emergency
controls can be safely and efficiently reached
and actuated while fully restrained, at the appropriate
design eye position, with maximum
stretch of the shoulder and arm muscles. The
aviator shall have full flight control movement
(cyclic, collective, pedals) and the ability to
reach and actuate the ENG POWER CONT
lever, Engine Fuel Selector Lever, and Fire
T-Handle. If the pilot cannot actuate all the
required items, he shall not operate the aircraft
from that seat.
A foam protective pad surrounds the glare
shield. Do not grasp the pad during adjustment
of the pilot and copilot seats as damage to the
material may result.
N ★ 5. Circuit breakers and switches — Set.
When flight into IMC conditions are expected to
be encountered, the STBY INST switch must be
held in the TEST position for 5 seconds. The
BATT GOOD cold capsule shall appear for the
full 5 seconds to ensure 30 minutes ESIS standalone
battery time.
N * 6. BATT NO. 1 and NO. 2 switches — ON.
Beeping tones will be heard during the digital
ICS start up checks.
N N N * 2. APU CONT switch — ON.
- If APU fails, note and analyze BITE indications
before cycling BATT NO. 1 switch or before
attempting another APU start. - If the APU does not start and the APU ACCUM
LOW advisory does not appear with the
APU CONT switch ON, the manual override
lever on the accumulator manifold may be
pulled to attempt another start, and held until
the APU has reached self-sustaining speed. - During the first 4 seconds of an APU start,
the APU FIRE T-handle and Master Warning
Panel FIRE lights may momentarily illuminate and
turn off. This is not a positive indication of an APU fire.
W W * 3. GENERATORS APU switch — ON.
- Stabilator will move to full trailing edge down
position upon application of AC power. Assure
stabilator area is clear prior to energizing
stabilator system. - Potential radiation hazard exists at the
TACAN antenna when the TACAN is turned
on. Make sure that no person is within three
feet of the antenna while power is applied to
the helicopter.
N N N O* 5. EDECU — Check signal validation code 25%.
- An engine EDECU will display an EDECU signal
validation startup code on the MFD Q indicator
approximately 20 seconds after application
of ac power. A startup code of 25% shall
be verified to indicate a 701D with a DAS plug
installed. - The EDECU configuration may also be verified
on the FMS status page. - The DEC will immediately display signal validation
fault codes on the MFD Q indicator after
application of ac power at a rate of 4 seconds
on and 2 seconds off during startup, and
30 seconds after both engines are shutdown
with ac power applied.
N * 6. BATT NO. 1 and NO. 2 switches — ON.
Beeping tones will be heard during the digital
ICS start up checks.
N N N * 2. APU CONT switch — ON.
- If APU fails, note and analyze BITE indications
before cycling BATT NO. 1 switch or before
attempting another APU start. - If the APU does not start and the APU ACCUM
LOW advisory does not appear with the
APU CONT switch ON, the manual override
lever on the accumulator manifold may be
pulled to attempt another start, and held until
the APU has reached self-sustaining speed. - During the first 4 seconds of an APU start,
the APU FIRE T-handle and Master Warning
Panel FIRE lights may momentarily illuminate and
turn off. This is not a positive indication of an APU fire.
W W * 3. GENERATORS APU switch — ON.
- Stabilator will move to full trailing edge down
position upon application of AC power. Assure
stabilator area is clear prior to energizing
stabilator system. - Potential radiation hazard exists at the
TACAN antenna when the TACAN is turned
on. Make sure that no person is within three
feet of the antenna while power is applied to
the helicopter.
N N N O* 5. EDECU — Check signal validation code 25%.
- An engine EDECU will display an EDECU signal
validation startup code on the MFD Q indicator
approximately 20 seconds after application
of ac power. A startup code of 25% shall
be verified to indicate a 701D with a DAS plug
installed. - The EDECU configuration may also be verified
on the FMS status page. - The DEC will immediately display signal validation
fault codes on the MFD Q indicator after
application of ac power at a rate of 4 seconds
on and 2 seconds off during startup, and
30 seconds after both engines are shutdown
with ac power applied.
N - 9. MASTER WARNING PANEL — Check #1
If a segment light does not illuminate, pull out ¼
inch then push back in to reset the bulb.
N * 13. Press FCC FAILURE RESET switches. EGIs must be in ORIENT phase before AFCC faults will reset.
EGIs must be in ORIENT phase before AFCC
faults will reset.
N N N ★ * 14. Load Navigation Database (NAV DB) (As required).
A navigation database must be loaded using
a PCMCIA card with a folder named NAVIGATION
which contains a NAV_DB.BIN file. Using
a PCMCIA card with only a NAVIGATION folder
and a NAV_DB. BIN file is recommended to ensure
no conflicts with the map cache process.
Adding a NAVIGATION folder to the entire AWE
structure with cache maps will significantly increase
navigation database loading
- It is recommended to load the NAV DB from the
FMS designated as the BC for this step: - Asterisks may appear in the date line on the first
FMS reset and may be cleared by forcing a BUS
swap to ensure cross talk between both FMS.
W W N N ★ 18. Flight controls — Check first flight of day.
- Prior to flight, the user must perform control
sweeps to ensure there are no flight control interference
problems with aviator worn gear. If a
restriction is found, the interfering gear must be
adjusted/moved to eliminate the restriction. - If PRI SERVO 1 FAIL or PRI SERVO 2 FAIL
caution appears during collective movement, a
servo bypass valve may be jammed. If this situation
occurs, do not fly the helicopter. - The force applied to the pedals with
SAS/BOOST off during pre-flight checks should
be limited to only that required to contact a
system stop. Additional pedal force results in
no additional tail rotor motion and has been
demonstrated to generate flight control bearing/
bolt noises. - During Step h and Step i, check for not more
than 1.5 inches of freeplay in control.
W ★ 21. Stabilator — Check.
If any part of stabilator check fails, do not fly helicopter.
N N N N ★ * 24. FMS initialization — Check as required.
- FMS defaults to the last known helicopter position.
The FMS automatically updates the date,
time and position with Global Positioning System (GPS)
data once it becomes available. - If INIT is not selected manually, it will automatically
engage once the GPS acquires satellites
and determines its location. - The Calculator PERFORMANCE function will
ONLY be used to reference PERFORMANCE
values after verifying the correct configuration
of the aircraft. - The drag and performance variables must
match the current aircraft configuration in order
to ensure the most accurate PERFORMANCE
values are displayed.
N ★ * 26. Set up MFD/FD/FMS for mission.
Only two Unit Task Organizations (UTOs) can
be loaded into the system using the mission
card. Load additional UTOs directly into the
IDM as required. Allow UTO and URN file to
load from user PCMCIA card and the IDM to
indicate a successful initialization; “OPERATIONAL”
displayed on IDM status line prior to
JVMF Initialize/Login (Approx 2 minutes).
C - STARTING ENGINES.
Prior to starting engines, ensure main rotor
blades are aligned with the aircraft centerline
±20° before engaging the rotor brake. Damage
to the main rotor blades will occur if blades are
positioned over UES during engine start with
rotor brake applied. Heat damage can occur
to blades if blades are kept in a static position
with engines operating.
N * 3. GUST LOCK ENGAGED caution — Verify off.
GUST LOCK ENGAGED caution may not be
visible on the CAS page; pilot must verify on
EICAS page.
W N * 4. STAB UNLOCKED caution — Verify off.
Engine operation and/or rotors turning with the
stabilator unlocked could allow the stabilator to
contact the tail rotor.
STAB UNLOCKED caution may not be visible
on the CAS page. Pilot must verify in the overflow
box on EICAS display.
N * 7. Rotor brake — On, if required. ROTOR BRAKE advisory appears. Minimum pressure 450 psi.
If operating conditions permit, the engines may
be started with an inoperative or not installed
rotor brake.
W C(4) N(7) ★ * 9. Engine(s) — Start.
Rotor Brake (1):
If inadvertent rotor blade movement should occur due to rotor brake slippage, immediately shut down engine(s) or release rotor brake.
EPCL (3):
* To avoid damage to the engine start switch actuators, do not move the ENG POWER CONT lever from IDLE to OFF while pressing the starter button.
- If an ENG STARTER ON caution disappears when the starter button is released, and the ENG POWER CONT lever is OFF, the start attempt may be continued by pressing and holding the starter button until 52% to 65% NG is reached; then release the starter button.
- There is a delay of approximately one second between the time the starter disengages and the ENG STARTER ON caution disappears. Consequently, the NG is permitted to indicate above 65% when starter drop out is indicated on the MFD, but the ENG STARTER ON caution must disappear by the time the engine reaches idle.
Ignition Switch (1):
* If start is attempted with ENGINE IGNITION switch OFF, do not place switch to ON. Abort the start.
MFD’s (5):
* All corresponding No. 1 and No. 2 hydraulic cautions remain until the rotor brake is released.
- During rotor brake operations there will be no NP or Q indications until rotor brake is released.
- MAIN XMSN PRESS caution remains and there is no pressure indication until rotor brake is released.
- FUEL PRESS LOW caution may appear during the start process and should disappear before the engine stabilizes at ground idle.
- The FUEL BOOST PUMP CONTROL switches shall not be used to extinguish the FUEL 1 PRESS LOW or FUEL 2 PRESS LOW caution during an engine start sequence.
Flight Controls (2):
* During engine start and runup ensure that cyclic is kept in neutral, collective no more
than one inch above full down, and pedals centered until NR reaches 50% minimum to prevent damage to anti-flap bracket bushings.
- For starts with rotor brake off and during rotor engagements, cyclic inputs shall be minimized to prevent droop-stop pounding.
N N ★ 15. Hydraulic leak test system — Check.
- When performing the HYD LEAK TEST, all LDI
system components are checked electrically.
Manually holding the HYD LEAK TEST switch
in the test position does not allow the leak
detection/isolation system to be checked automatically.
It manually holds the circuits open.
The switch must be placed in the TEST position
and released. - If the backup pump is still running following the
hydraulic leak test, cycle the BACKUP HYD
PUMP switch to OFF then back to AUTO.
N ★ 16. Tail rotor servo transfer — Check.
Failure of the BACK UP PUMP ON advisory or the T/R SERVO 2 ON advisory to appear indicates a failure in the LDI system.
W N * 1. ENG POWER CONT lever(s) — FLY.
Restrict the rate of ENG POWER CONT lever’s
movement, when the tailwheel lockpin is not
engaged. Rapid application of ENG POWER
CONT levers can result in turning the helicopter,
causing personnel injury or loss of life.
For rotor brake operations, ensure that approximately
45% NR for single engine and 57% NR
for dual engine is reached prior to advancing
ENG POWER CONT levers.
