Bell Helicopter model 206L4. MAINTENANCE MANUAL (GENERAL INFORMATION) - page 6

 

  Index      Manuals     Bell Helicopter model 206L4. MAINTENANCE MANUAL (GENERAL INFORMATION) - 2011

 

Search            copyright infringement  

 

 

 

 

 

 

 

 

 

 

 

Content      ..     4      5      6     

 

 

 

 

Bell Helicopter model 206L4. MAINTENANCE MANUAL (GENERAL INFORMATION) - page 6

 

 

BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-54. OVERTORQUE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
e. Transmission spindles, pylon support links, and mount
fittings.
f. Cabin roof shell and beam at transmission mount
attachment points.
g. Transmission restraint attachment.
h. Transmission electric chip detectors.
i. Tail rotor gearbox chip detectors and gearbox
attachments.
j. Tail rotor hub, blades, and attachments.
Page 165/166
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
DATE: __________________W.O. _____________________
FACILITY: _________________________________________
HELICOPTER S/N: __________________________________
REGISTRY NO.: ____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
NOTE
An engine compressor stall or surge can be
described as a sharp rumble, a series of loud sharp
pops, severe engine vibration, or a rapid rise in
Turbine Outlet Temperature (TOT) depending on the
severity of stall or surge. When a stall or surge is
suspected, follow steps as dictated by reported
conditions.
NOTE
The components removed from the helicopter for
evaluation following a compressor stall or surge shall
be evaluated as a matched group. The records
accompanying
each
component
shall
cross-reference part and serial numbers of other
drive system components removed for evaluation.
1.
Obtain a pilot's report of the circumstances related to the
suspected compressor stall or surge to determine if it
corresponds to one of the following conditions:
If the stall or surge occurred on the ground or in flight at
any NR speed or torque setting and there was no
noticeable yaw of the helicopter, do Part I and Part II of
this inspection.
Page 167
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
If the stall or surge occurred on the ground or in flight at
any NR speed or torque setting and there was a
noticeable yaw of the helicopter, do Part I, Part II, and
Part III of this inspection.
PART I: INVESTIGATE CAUSE OF COMPRESSOR
STALL OR SURGE
POWER PLANT
Rolls-Royce 250-C30
1.
Examine the induction fairing for blockage. If the induction
Series Operation and
fairing is found obstructed, refer to the appropriate Rolls-Royce
Maintenance Manual,
Operation and Maintenance Manual for further maintenance
14W2
action. If no blockage is found, do step 2.
2.
Remove the induction fairing and examine the compressor
intake area as follows:
a. Examine the compressor rotor for contamination. If
contamination is found, perform a compressor wash. Refer to
applicable BHT-206L4-MM-9, Chapter 71.
b. Inspect compressor rotor for foreign object damage in
accordance with the appropriate Rolls-Royce Operation and
Maintenance Manual for proper action.
3.
If step 1 and step 2 do not reveal an obvious cause for stall
or surge, refer to the appropriate Rolls-Royce Operation and
Maintenance Manual for further maintenance action.
Page 168
Rev. 18
7 JUN 2013
Export Classification C,
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
NOTE
Removal or dismantling of components is not
required while performing the following inspection.
Chapter 63
PART II: INSPECTION FOR COMPRESSOR STALL OR
Chapter 65
SURGE WITHOUT NOTICEABLE YAW
DRIVE SYSTEM
1.
Examine the chip detectors of the transmission, freewheel
assembly, and the tail rotor gearbox. If the chip detector shows
signs of metal particles, perform a serviceability check.
Components that fail the serviceability check shall be removed.
Make an entry on the applicable components Historical Service
Record and attach a tag and write, “THIS COMPONENT WAS
REMOVED FROM SERVICE BECAUSE OF A COMPRESSOR
STALL/SURGE”. Send the component to a Bell Helicopter
Textron approved facility for overhaul.
2.
Examine the tail rotor driveshafts for condition and security
of attachment.
3.
Examine the tail rotor disc pack couplings for cracks or
gapping greater than 0.015 inch (0.38 mm).
4.
Examine the tail rotor steel driveshaft and adapters for
structural failure or distortion exceeding specified limits.
5.
Examine the bond lines on all bonded tail rotor driveshaft
adapters (if installed) for any evidence of cracks and voids.
6.
If any defect is detected in step 2 through step 5, all
bonded tail rotor driveshafts shall be considered unserviceable
and discarded.
7.
Examine the tail rotor driveshaft segments having riveted
adapters (if installed) for condition.
8.
Examine the oil cooler shaft and forward short shaft for
condition.
9.
Examine the engine-to-transmission main driveshaft for
condition.
Page 169
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
10. If no defects were detected that may have been caused by
the compressor stall or surge, all drivetrain components are
serviceable.
Chapter 62
ROTATING CONTROL SYSTEM
1.
Examine the swashplate and support assembly,
swashplate drive components, the tail rotor pitch change
mechanism, and all rotating controls (main and tail). Replace
any unserviceable parts as necessary.
Chapter 64
TAIL ROTOR HUB AND BLADES
BHT-206L-CR&O
1.
Examine the tail rotor hub assembly for condition. If any
damage suspected to be related to the stall or surge is found,
remove the tail rotor hub assembly. Make an entry on the
Historical Service Record and attach a tag on the tail rotor hub
assembly and write, "THIS COMPONENT WAS REMOVED
FROM SERVICE BECAUSE OF A COMPRESSOR STALL OR
SURGE". Send the hub to an approved facility for overhaul.
2.
Examine the tail rotor blade(s) for condition. If any damage
suspected to be related to the stall or surge is found, remove the
tail rotor blade(s). Make an entry on the Historical Service
Record and attach a tag on the tail rotor blade(s) and write
"THIS BLADE WAS REMOVED FROM SERVICE BECAUSE
OF A COMPRESSOR STALL OR SURGE". Send the tail rotor
blade(s) assembly to a Bell Helicopter Textron approved rotor
blade repair facility for further inspection and repair.
3.
Examine the tail rotor blade bolts for security of
attachment. If damage suspected to be related to the stall or
surge is found, discard them.
4.
If any defect is detected in step 1 through step 3, all
bonded tail rotor driveshafts shall be considered unserviceable
and discarded.
Chapter 62
MAIN ROTOR HUB AND BLADES
1.
Examine the main rotor blades for damage. Check for
wrinkled skin, delamination, deformation, and cracks.
Page 170
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
BHT-206L-CR&O
2.
If any blade has visible damage suspected to be related to
the stall or surge, make an entry on the Historical Service
Record and attach a tag on blades and write, "THIS BLADE
WAS REMOVED FROM SERVICE BECAUSE OF A
COMPRESSOR STALL/SURGE." Send the blade(s) to a Bell
Helicopter Textron approved rotor blade repair facility for further
inspection and repair.
3.
If no defects were detected on any blade, the blade(s) are
serviceable.
NOTE
This inspection does not require disassembly or
removal from the helicopter.
4.
Examine the main rotor hub for condition. If any damage is
suspected to be related to the stall or surge, remove the main
rotor hub assembly. Make an entry on the Historical Service
Record and attach a tag on the main rotor hub and write, "THIS
MAIN ROTOR HUB ASSEMBLY WAS REMOVED FROM
SERVICE BECAUSE OF A COMPRESSOR STALL/SURGE."
Send the component to a Bell Helicopter Textron approved
facility for overhaul.
5.
If no defects were detected on main rotor hub, the main
rotor hub is serviceable.
6.
If defects are detected in step 1, step 2, and step 4 through
step 5, discard all bonded tail rotor driveshafts and perform a
main rotor sudden stoppage inspection.
SPECIAL INSPECTION
After
25 hours of operation, examine chip detectors of
transmission, freewheel assembly, and tail rotor gearbox. If the
chip detector shows signs of metal particles, perform a
serviceability check. Components that fail the serviceability
check shall be removed. Make an entry on the applicable
components Historical Service Record and attach a tag and
write “THIS COMPONENT WAS REMOVED FROM SERVICE
BECAUSE OF A COMPRESSOR STALL/SURGE”. Send the
component to a Bell Helicopter Textron approved facility for
overhaul.
Page 171
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
PART III: INSPECTION FOR COMPRESSOR STALL
OR SURGE WITH NOTICEABLE YAW
CAUTION
WHEN A COMPRESSOR STALL OR SURGE WITH
NOTICEABLE YAW HAS OCCURRED, DISCARD
ALL TAIL ROTOR BONDED DRIVESHAFTS.
BHT-206L-CR&O
1.
Remove and examine the engine-to-transmission main
driveshaft for condition.
2.
If any damage suspected to be related to the stall or surge,
make an entry on the Historical Service Record and attach a tag
on the driveshaft and write,
“THIS COMPONENT WAS
REMOVED FORM SERVICE BECAUSE OF A COMPRESSOR
STALL”. Send the driveshaft to Bell Helicopter Textron CPR for
evaluation.
3.
If
no defects
were detected,
return
the
engine-to-transmission main driveshaft to service.
TRANSMISSION ASSEMBLY
BHT-206L-CR&O
1.
Remove the transmission input pinion and triplex bearing.
2.
Inspect the following gear teeth for scoring and other
mechanical damage.
a. Input pinion gear.
b. Main input driven bevel gear.
3.
If any damage suspected to be related to the stall or surge
is found, make an entry on the Historical Service Record and
attach a tag on the transmission assembly and write, “THIS
COMPONENT WAS REMOVED FROM SERVICE BECAUSE
OF A COMPRESSOR STALL”. Send the component to a Bell
Helicopter Textron approved facility for overhaul.
4.
If no defects were detected on the gears, the transmission
assembly is serviceable.
Page 172
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
TAIL ROTOR GEARBOX
BHT-206L-CR&O
1.
Remove the tail rotor gearbox input pinion.
2.
Inspect the following gear teeth for scoring and other
mechanical damage.
a. Input pinion gear.
b. Spiral bevel gear.
3.
If any damage suspected to be related to the stall or surge
is found, make an entry on the Historical Service Record and
attach a tag on the tail rotor gearbox and write,
“THIS
COMPONENT WAS REMOVED FROM SERVICE BECAUSE
OF A COMPRESSOR STALL”. Send the tail rotor gearbox to a
Bell Helicopter Textron approved facility for overhaul.
4.
If no defects were detected on the gears, the tail rotor
gearbox is serviceable.
Chapter 53
FUSELAGE
1.
Examine the complete tailboom structure for distortion,
buckles, cracks in the skin, and sheared or loose rivets.
2.
Inspect tailboom attachment fittings for cracks.
3.
Inspect the vertical fin for condition and security of
attachment.
Chapter 63
GROUND RUN
Chapter 65
BHT-206L4-FM-1
1.
Perform a ground run for a minimum of 30 minutes with the
helicopter light on its skids. Remove and examine the chip
detectors of the transmission assembly, freewheel assembly,
and tail rotor gearbox.
Export Classification C,
7 JUN 2013
Rev. 18
Page 173
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-55. ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
2.
If the chip detector shows signs of metal particles, perform
a serviceability check. Components that fail the serviceability
check shall be removed. Make an entry on the applicable
components Historical Service Record and attach a tag and
write, “THIS COMPONENT WAS REMOVED FROM SERVICE
BECAUSE OF A COMPRESSOR STALL/SURGE”. Send the
component to a Bell Helicopter Textron approved facility for
overhaul.
3.
If no metal particles were found, the transmission
assembly, freewheel assembly, and/or tail rotor gearbox are
serviceable.
Page 174
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-56. LIGHTNING STRIKE
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
DATE: __________________W.O. _____________________
FACILITY: _________________________________________
HELICOPTER S/N: __________________________________
REGISTRY NO.: ____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
NOTE
This inspection must be accomplished after
helicopter is suspected of receiving a lightning strike.
LIGHTNING STRIKE
NOTE
In all of the following instances, if significant damage
has been found in any area, inspection shall be
expanded in those areas until it extends beyond the
zone of damage. Scrap any component that shows
evidence of severe arc burns.
Because lightning behavior is difficult to predict,
conduct a thorough inspection of the entire
helicopter. Lightning damage may appear as burn
marks, heat discoloration, arc marks, or small weld
marks (where metal has melted and resolidified).
Honeycomb and other composite materials may
exhibit delamination.
Export Classification C,
7 JUN 2013
Rev. 18
Page 175
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-56. LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
1.
Visually inspect all external surfaces of the helicopter
paying particular attention to main rotor blades and hub, main
rotor mast and controls, transmission and mounts, power plant
and mounts, main and tail rotor driveshafting, tail rotor gearbox,
tail rotor blades and hub, vertical fin, and horizontal stabilizer.
Inspect landing gear skid tubes, crosstubes, and their fuselage
attachment points. Check electrical instruments and systems.
Check standby compass for erroneous indications. Remove and
overhaul defective and/or damaged electrical instruments and
systems.
2.
If visual indications of damage are present, proceed as
follows:
NOTE
Evaluate components removed from a helicopter
following a lightning strike as an interrelated group.
Make entries in component records to
cross-reference part and serial numbers of other
drive system components removed for evaluation.
a. Inspect main rotor blades. Blades that exhibit severe
arcing shall be scrapped. Blades that exhibit light to moderate
arcing shall be returned to a Bell Helicopter Textron approved
blade repair facility for evaluation.
(1) Inspect blades for signs of burns and arcing at tip
cap, root end closure, buffer pads, and blade bolt bushings.
Burn marks can be very minute.
(2) lnspect main rotor blade bonded areas for
debonding.
b. Remove main rotor hub for overhaul. State lightning
strike as reason for removal.
c. Remove swashplate and support assembly for
overhaul. State lightning strike as reason for removal.
d. Remove main driveshaft, freewheel assembly,
transmission, and mast assembly for overhaul making note of
lightning strike as reason for removal.
Page 176
Rev. 18
7 JUN 2013
Export Classification C,
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-56. LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
e. Inspect nodal beam, transmission mount fittings, and
engine mounts.
BHT-206L-CR&O
(1) Visually inspect exterior surfaces for evidence of
arcing or burning. Special attention should be given to contact
surfaces of transmission and engine to their mounting systems,
and of mounting systems to the airframe.
(2) If indications of arcing or burning are present,
overhaul parts.
f. Inspect tail rotor blades and hub. Scrap blades if
indications of burns or debonding. Remove tail rotor hub for
overhaul. State lightning strike as reason for removal.
g. Remove tail rotor driveshaft bearing hangers and tail
rotor gearbox and return for overhaul. State lightning strike as
reason for removal.
h. Check auxiliary fins for evidence of burning or
debonding.
i. lnspect tailboom fitting for indication of arcing burns
around mounting points of tail rotor gearbox and vertical fin.
Rolls-Royce 250-C30
j. Inspect power plant assembly.
Series Operation and
Maintenance Manual,
14W2
3.
If no indications of damage are found, do the following:
NOTE
If no visual indications of damage are present, check
all ferrous dynamic components by magnetometer. If
magnetism is present, perform procedure indicated
in step 2. Demagnetize all parts.
BHT-206L-CR&O
a. Remove main rotor hub and blade assembly. Remove
main rotor grips.
(1) Visually inspect needle bearings for signs of
electrical arcing, burning, or delamination.
Export Classification C,
7 JUN 2013
Rev. 18
Page 177
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-56. LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
(2) Visually check pitch horns and trunnion bearing
connections for arcing burns.
BHT-206L-CR&O
(3) If indications of arcing or burning are present,
overhaul main rotor hub assembly and scrap pitch links and all
attaching hardware.
BHT-206L-CR&O
(4) If no indications are found, reassemble main rotor
hub.
b. Remove main rotor mast assembly. Without removing
bearing from mast, inspect visible portions of the bearing for
signs of electrical arcing or burning. Rotate bearing during
inspection. Check bearing for smooth rotation. Visually inspect
the lower mast bearing race and driving spline on the mast for
signs of arcing or burning. If indications of arcing, burning, or
roughness of the bearing are present, transmission, mast
assembly, and freewheel assembly shall be returned for
overhaul. State lightning strike as reason for removal.
c. Remove transmission top case and inspect for entry
and exit of lightning strike. Special attention should be given to
the planetary pinion and sun gear, ring gear, spiral bevel gear,
and quill pinion. Check all bearings for smooth rotation and
damage. If evidence of arcing or burning is found or bearings do
not rotate smoothly, remove gearbox and return for overhaul,
stating lighting strike as reason for removal. Scrap all parts that
exhibit signs of arcing.
BHT-206L-CR&O
(1) If no indications of arcing are found, reassemble
transmission and mast assembly and return to limited service.
(2) After 5 hours, remove the chip detectors and filter
and inspect for chips.
(a) If no chip indications are found, return
transmission to full service.
(b) If chip indications are found, remove
transmission, mast assembly, and freewheel assembly and
return for overhaul. State lightning strike as reason for removal.
Scrap all parts that exhibit signs of arcing.
Page 178
Rev. 18
7 JUN 2013
Export Classification C,
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-56. LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
d. Inspect nodal beam, transmission mount fittings, and
engine mounts.
(1) Visually inspect exterior surfaces for evidence of
arcing or burning. Special attention should be given to contact
surfaces of transmission and engine to their mounting systems,
and of mounting systems to the airframe.
BHT-206L-CR&O
(2) If indications of arcing or burning are present,
overhaul parts.
e. Remove input quill assembly from tail rotor gearbox.
Visually inspect gear teeth for signs of electrical arcing or
burning. Rotate tail rotor mast to check for smooth rotation of
bearings.
(1) If evidence of arcing or burning is found or if
bearings do not rotate smoothly, remove gearbox and return it
for overhaul. State lightning strike as reason for removal.
BHT-206L-CR&O
(2) If no indications of damage are found and bearings
rotate smoothly, reassemble gearbox and return it to limited
service. After 5 hours, remove chip detector and inspect for
chips. If no chip indications are found, return gearbox to full
service. If chip indications are found, return gearbox for
overhaul. State lightning strike as reason for removal.
f. Inspect main driveshaft for evidence of arcing or
burning.
BHT-206L-CR&O
(1) If no evidence of arcing is found, return to service.
(2) Shafts that exhibit arcing or burning shall be
scrapped.
(3) If indications of arcing or burning are found on the
main driveshaft or on any component of the tail rotor driveshaft
installation, return freewheel assembly for overhaul. State
lightning strike as reason for removal.
BHT-206L-CR&O
g. Disassemble swashplate and support assembly.
Visually inspect for evidence of burning or arcing. Inspect
bearings for smooth rotation and all hardware for evidence of
arcing.
Export Classification C,
7 JUN 2013
Rev. 18
Page 179
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-56. LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
BHT-206L-CR&O
(1) If indications of arcing or burning are present or
bearings do not rotate smoothly, overhaul swashplate assembly.
Replace the affected hardware.
BHT-206L-CR&O
(2) If no indications are found, reassemble the
swashplate assembly and return to service.
h. Inspect tailboom, horizontal stabilizer, auxiliary fins, and
vertical fin for evidence of arcing, burning, or debonding paying
particular attention to area around the mounting points for the
tail rotor driveshaft hangers and tail rotor gearbox.
Rolls-Royce 250-C30
i. Inspect power plant assembly.
Series Operation and
Maintenance Manual,
14W2
Page 180
Rev. 18
7 JUN 2013
Export Classification C,
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-57. ENGINE OVERTEMP
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
DATE: __________________ W.O. _____________________
FACILITY: _________________________________________
HELICOPTER S/N: __________________________________
REGISTRY NO.: ____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
ENGINE OVERTEMP
— Inspect.
Rolls-Royce 250-C30P
Perform hot end inspection of power plant assembly if start or
Series Operation and
transient turbine outlet temperature limits have been exceeded.
Maintenance Manual,
14W2
Page 181/182
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-58.
STRIKE IMPACT TO AUXILIARY FINLETS BY MAIN ROTOR BLADES
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
DATE: __________________W.O. _____________________
FACILITY: _________________________________________
HELICOPTER S/N: __________________________________
REGISTRY NO.: ____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
STRIKE IMPACT TO AUXILIARY FINLETS BY MAIN
ROTOR BLADES
A strike impact to the auxiliary finlets by main rotor blades is an
incident in which a main rotor blade collides with either one or
both auxiliary finlets and leaves a noticeable damage to either a
main rotor blade or an auxiliary finlet.
When a strike impact has occurred, do the steps that follow:
MAIN ROTOR BLADES
1.
Examine if a main rotor blade has contacted the tail rotor
driveshaft cover. If the tail rotor driveshaft cover is damaged, do
the conditional inspections listed in SUDDEN STOPPAGE -
MAIN ROTOR - POWER “ON” or “OFF”. If not, do the steps that
follow:
2.
Examine the blade skin and bonded doublers for visible
damage.
3.
If
damage to a blade cannot be repaired per
BHT-206L4-MM-6, remove it. Put a tag on the blade and write
“THIS BLADE WAS REMOVED FROM SERVICE BECAUSE
OF STRIKE IMPACT TO AUXILIARY FINLETS”. Send the
blade to an approved facility for repair.
4.
If you do not find damage on the blade, the blade is
serviceable.
Export Classification C,
31 AUG 2021
Rev. 25
Page 183
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-58.
STRIKE IMPACT TO AUXILIARY FINLETS BY MAIN ROTOR BLADES (Cont)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
AUXILARY FINLETS
If the upper end of the finlets has a strike damage, put a tag on
the auxiliary finlet and write “THIS AUXILIARY FINLET WAS
REMOVED FROM SERVICE BECAUSE OF STRIKE IMPACT
FROM A MAIN ROTOR BLADE”. Fill out a structural repair
request per IL GEN-04-96 or Section 2 of the BHT-ALL-SRM
and forward to Product Support Engineering (PSE) for repair
evaluation.
STABILIZER ELEVATOR
1.
For stabilizer elevator not equipped with end finlet fittings
206-021-103-ALL, do the steps that follow:
a. If an auxiliary finlet is damaged due to a main rotor
strike, remove the stabilizer elevator for inspection.
b. Examine the external surface for skin deformation,
bucking, or cracks.
c. Examine all inserts for looseness and bond condition.
d. If the stabilizer elevator is more than the repairs
described in Chapter
53, put a tag on it and write
“THIS
STABILIZER ELEVATOR WAS REMOVED FROM SERVICE
BECAUSE OF STRIKE IMPACT FROM MAIN ROTOR BLADE
TO THE FINLETS”. Fill out a structural repair request per IL
GEN-04-96 or Section 2 of the BHT-ALL-SRM and forward to
PSE for a repair evaluation.
2.
For stabilizer elevator equipped with end finlet fittings
206-021-103-ALL, do the steps that follow:
a. If an auxiliary finlet is damaged due to a main rotor
strike, remove the stabilizer elevator for inspection.
b. Examine the external surface for skin deformation,
bucking, or cracks.
c. Examine all inserts for looseness and bond condition.
d. Examine the end fitting fasteners for condition.
Page 184
Rev. 25
31 AUG 2021
Export Classification C,
BHT-206L4-MM-1
CONDITIONAL INSPECTIONS
5-58.
STRIKE IMPACT TO AUXILIARY FINLETS BY MAIN ROTOR BLADES (Cont)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
e. Remove damaged finlets and do an Eddy current
inspection to its adjacent end fitting of the stabilizer elevator. If
one of the end fittings fails the Eddy current inspection, discard
the stabilizer elevator.
f. If the end fitting has no damage but the damage to the
stabilizer elevator is more than the repairs described in Chapter
53, put a tag on it and write “THIS STABILIZER ELEVATOR
WAS REMOVED FROM SERVICE BECAUSE OF STRIKE
IMPACT FROM THE MAIN ROTOR BLADE TO THE FINLETS”.
Fill out a structural repair request per IL GEN 04-96 or Section 2
of the BHT-ALL-SRM and forward to PSE for a repair
evaluation.
TAILBOOM
1.
Examine all closing plates and support angles of stabilizer
elevator for deformation or cracks.
2.
Examine the tailboom skin aperture for stabilizer elevator
for waviness, deformation, bucking, or cracks. If the damage to
the skin is more than the repairs described in Chapter 53, put a
tag on the tailboom and write
“THIS TAILBOOM WAS
REMOVED FROM SERVICE BECAUSE OF STRIKE IMPACT
FROM MAIN ROTOR BLADE TO THE FINLETS”. Fill out a
structural repair request per IL GEN-04-96 or Section 2 of the
BHT-ALL-SRM and forward to PSE for repair evaluation.
31 AUG 2021
Rev. 25
Page 185/186
Export Classification C,
BHT-206L4-MM-1
COMPONENT OVERHAUL SCHEDULE
5-59. COMPONENT OVERHAUL SCHEDULE
CAUTION
The Component Overhaul Schedule (Table 5-4) gives
the time interval between overhaul for each applicable
helicopter component.
OVERHAUL SCHEDULE FOR SOME KIT
COMPONENTS AND/OR PARTS IS NOT
COVERED IN THIS SCHEDULE. REFER
WARNING
TO APPLICABLE
SERVICE
INSTRUCTIONS FOR KIT COMPONENTS
SCHEDULE.
DO NOT APPLY TOLERANCES TO
PARTS
WITH A
LIMITED
AIRWORTHINESS LIFE (CHAPTER 4).
NOTE
Refer to paragraph 5-6 for information on
WARNING
inspection and overhaul tolerance.
NOTE
DO NOT GO MORE THAN RETIREMENT
LIFE FOR CRITICAL COMPONENTS.
Neither assignment of a time period for
REFER TO AIRWORTHINESS
overhaul of a component or failure to
LIMITATIONS SCHEDULE (CHAPTER 4).
assign a time period for overhaul of a
component constitutes a warranty of any
SOME PARTS INSTALLED AS ORIGINAL
kind. The only warranty applicable to
EQUIPMENT
ON
MILITARY
helicopter and all components is that
HELICOPTERS CAN HAVE A LOWER
warranty included in the Purchase
AIRWORTHINESS LIFE AND/OR
Agreement for the helicopter or component.
OVERHAUL SCHEDULE THAN WHEN
USED ON A COMMERCIAL
HELICOPTER. CONSEQUENTLY, PARTS
The
overhaul interval specified for all given
part
THAT HAVE BEEN USED ON MILITARY
numbers contained in this Component Overhaul
HELICOPTERS MUST NOT BE USED ON
Schedule applies to all successive dash numbers (or
COMMERCIAL HELICOPTERS.
suffixes) for that item unless otherwise specified.
Export Classification C,
31 AUG 2021
Rev. 25
Page 187
BHT-206L4-MM-1
Table 5-4. Component Overhaul Schedule
OVERHAUL INTERVAL
NOMENCLATURE
PART NUMBER
1
(HOURS)
MAIN ROTOR CONTROLS
Swashplate and Support
206-010-450-101
4800 hours
MAIN ROTOR HUB
Hub Assembly
206-011-100-159/-105
2400 hours
POWER TRAIN
Transmission
206-040-004-115
4500 hours
Mast Assembly
206-040-014-107
3000 hours
Input Driveshaft
206-340-300-101/-105
2
2500 hours
Freewheel Unit
406-040-500-113
3000 hours
TAIL ROTOR SYSTEM
Tail Rotor Hub Assembly
206-011-810-139
2500 hours
Tail Rotor Gearbox
206-040-402-101
6000 hours
HYDRAULIC SYSTEM
Hydraulic Servo Actuators
206-076-062-101
3600 hours
POWER PLANT
Turboshaft Engine
250-C30P
Refer to Rolls-Royce 250-C30
Series Operation and Maintenance
Manual, 14W2
STARTER GENERATORS
Starter Generator
ALL
1000 hours
NOTES:
The operating time specified for overhaul of all given part numbers listed applies to all successive dash
1
numbers (or suffixes) for that component, unless otherwise specified.
2
Input driveshafts 206-340-300-101/-105 must be overhauled at 5000 hours of operation and every
2500 hours of operation thereafter. Overhaul is to be done by Kamatics Corporation only.
Return driveshaft to Bell Textron per Information Letter (IL) GEN-04-98.
Page 188
Rev. 25
31 AUG 2021
Export Classification C,

 

 

 

 

 

 

 

Content      ..     4      5      6