|
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BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-25.
PROGRESSIVE INSPECTION - EVENT 10 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
b. For helicopters after TB 222-98-156, torque the nut in
the tightening direction while restraining the bolt head. If
130 inch-pounds (14.5 Nm) of torque is reached without nut
movement, increase torque to 160 inch-pounds (18 Nm) of
torque. If the nut moves below 130 inch-pounds (14.5 Nm),
proceed with 2-year Inspection.
NOTE
Examine inspection window(s) and/or glass(es) for
cracking and discoloration. If either of these
conditions are present, the part must be removed
and replaced prior to returning helicopter for service.
Chapter 12
12. Remove tail rotor gearbox fairing and inspect tail rotor
Chapter 66
gearbox for oil leakage, mechanical or corrosion damage, and
security of mounting. Check for proper oil level. T1/T2
Chapter 66
13. Remove tail rotor gearbox chip detector. Inspect and clean
detector and test electrical circuit. Install chip detector. R2
14. Inspect tail rotor gearbox retaining nuts for proper torque.
15. Inspect tail rotor pitch control assembly as follows:
a. Check for excessive radial play between the pitch
control assembly and the tail rotor gearbox output shaft due to a
worn or debonded guide bearing. Radial play in excess of 0.018
inch (0.5080 mm) is considered excessive.
b. Check for worn areas on the tail rotor gearbox output
shaft wear sleeve.
c. Check for worn or rough crosshead bearing set.
d. Check for rough or worn counterweight bellcrank
bearings.
e. Check for worn inner race in the tail rotor idler
assembly.
f. Check for unbonded bearing in the upper leg of tail rotor
input lever assembly.
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ECCN EAR99
9 SEP 2011 Rev. 7
Page 73
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-25.
PROGRESSIVE INSPECTION - EVENT 10 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
g. Check for worn bearings in the tail rotor pitch links.
Chapter 65
16. Inspect tail rotor hub and blades for cleanliness, visible
damage to blades, evidence of wear or excessive play in pitch
change bearings, and trunnion bearings, and pitch horn for
security. R2
Chapter 65
17. Inspect tail rotor hub and blades assembly retaining nut for
proper torque. R2
NOTE
This inspection is applicable to tail rotor hub and
blades assembly prior to upgrade per TB 222-06-174
(Part II).
18. Inspect tail rotor blades pitch change bearings as follows:
a. Without removing the blade, clean exposed areas of
pitch change bearings.
BHT-222-CR&O-3
b. With the blade bolts torqued to the highest value of
torque range, visually inspect each bearing inner member neck
area (full 360°) for cracks. If cracks are found, replace both
bearings in blade.
BHT-222-CR&O-3
c. Visually inspect chamfered washers installed in direct
contact with the outboard surface of the yoke for deformation.
Deformed washers must be replaced.
5-00-00
Page 74
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-26.
PROGRESSIVE INSPECTION - EVENT 11
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
GENERAL
Paragraph 5-13
1.
Perform a complete 50-hour inspection.
DETAIL
Chapter 27
1.
Open control tunnel access in the canted bulkhead behind
BHT-ALL-SPM
the pilot station. Inspect the lower and upper cyclic and
collective pitch control bellcranks for evidence of bearing wear,
corrosion or mechanical damage to clevises, and security of
attachment to supports and control tube bearings. F5/F6
Chapter 66
2.
Inspect right and left nodal beam assembly as follows:
a. Flexure assembly for cracks in fiberglass, shear pad
debond/delamination, and security. F5/F6
b. Cam bearing for evidence of grease loss, overheating,
and grease seal condition. F5/F6
c. Weight and cam arms for indications of misalignment
and chafing. F5/F6
d. Restraint arms and lift links for security, damage, and
elastomeric bearings for obvious damage.
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ECCN EAR99
9 SEP 2011 Rev. 7
Page 75
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-26.
PROGRESSIVE INSPECTION - EVENT 11 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
e. Inspect station 270 bulkhead for cracks and damage as
follows:
(1) Remove equipment installed and interior trim to
gain access to the underside of station 270 bulkhead.
(2) Remove transmission drain pan from aft cabin.
(3) Remove screws retaining door 222-031-506-043
to the bottom side of the station 270 bulkhead. Remove access
door.
(4) Using a bright light, inspect the outside and inside
surfaces of the bulkhead assembly for cracks and damage,
paying particular attention to the area around the rivets/
Hi-Locks attaching the aft nodal beam fittings 222-031-592-103
to the station 270 bulkhead.
(5) If a crack or damage is found, contact Product
Support Engineering for repair procedure.
NOTE
Examine inspection window(s) and/or glass(es) for
cracking and discoloration. If either of these
conditions are present, the part must be removed
and replaced prior to returning helicopter for service.
Chapter 66
3.
lnspect transmission for evidence of oil leakage and correct
oil level. F5/F6
Chapter 66
4.
Remove transmission chip detectors. lnspect and clean
detectors and test electrical circuits. Install chip detectors. R1
Chapter 66
5.
lnspect the left longitudinal isolation mount and support for
damage and security. F5
Chapter 66
6.
lnspect the right longitudinal isolation mount and support,
and the lateral isolation mount and support for damage and
security. F6
5-00-00
Page 76
Rev. 8
10 FEB 2020
Export Classification C, ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-26.
PROGRESSIVE INSPECTION - EVENT 11 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
Chapter 66
7.
lnspect rotor brake assembly for evidence of
hydraulic leakage, security of attachment, and excessive
wear of brake linings. Check brake disc for damage. Check
reservoir for fluid level and discoloration. R1/F6
Chapter 66
8.
lnspect tail rotor driveshaft coupling
BHT-222-CR&O-3
overtemperature indicators (TEMP-PLATES) for
evidence of overheating (discoloration) and grease
leakage. R1
Chapter 66
BHT-222-CR&O-3
9.
lnspect main driveshafts overtemperature
indicators (TEMP-PLATES) on transmission-end and
engine-end driveshaft couplings for evidence of overheating
(discoloration) and grease leakage. R1
NOTE
Examine inspection window(s) and/or glass(es) for
cracking and discoloration. If either of these
conditions are present, the part must be removed
and replaced prior to returning helicopter for service.
Chapter 12
10. lnspect right and left engine oil tanks and lines for evidence
Chapter 79
of leakage. Check for proper quantity of oil. F5/F6
Chapter 66
11. Visually inspect the outboard and inboard collective lever
idler link attachment points for condition in area of lugs in
transmission top case. R1
BHT-222-CR&O-2
12. lnspect hydraulic actuator support attaching nuts for proper
torque. R1
Chapter 65
13. lnspect cyclic and collective control levers, swashplate
assembly, drive assembly, and links for evidence of damage,
security, and corrosion. lnspect walking beam pitch change
bearings, ensuring that seals and shields are in place and pitch
link clevis is properly aligned with walking beam. If seals and/or
shields are missing or loose, bearing must be replaced. R1
BHT-222-CR&O-2
14. lnspect main rotor hub for damage and security, static
stops for damage from hard mast contact, and trunnion shims
for condition. lnspect yoke for condition in area around flapping
bearing attachment bushings. lnspect pendulum dampers for
freedom of movement. R1
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 77
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-26.
PROGRESSIVE INSPECTION - EVENT 11 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
BHT-222-CR&O-2
15. Visually inspect the accessible portion of the main rotor
elastomeric pitch axis bearings, trunnion bearings, and flapping
springs for evidence of delamination or loss of elastomer. R1
Chapter 65
16. lnspect main rotor blades for obvious damage and for
cleanliness. R1
Chapter 27
17. lnspect roof mounted cyclic and collective shaft assemblies
BHT-ALL-SPM
and control tubes for bearing corrosion or mechanical damage,
wear, and security of attachment. F5/F6
NOTE
Examine inspection window(s) and/or glass(es) for
cracking and discoloration. If either of these
conditions are present, the part must be removed
and replaced prior to returning helicopter for service.
Chapter 29
18. lnspect hydraulic lines for leaks, system PC-1 and PC-2
reservoirs for proper level and discoloration of fluid, and module
for differential pressure indication. Check for chafe guard
deterioration, and verify flexible hoses are in satisfactory
condition and exhibit no indications of chafing. F5/F6
5-00-00
Page 78
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-27.
PROGRESSIVE INSPECTION - EVENT 12
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
GENERAL
Paragraph 5-13
1.
Perform a complete 50-hour inspection.
DETAIL
Chapter 96
1.
Remove battery. lnspect vent lines for obstructions or
damage, and clean battery mounting area prior to installing a
serviceable battery. F1/F2
Chapter 52
2.
lnspect nose compartment electrical components for
Chapter 96
condition and security of mounting, all electrical harnesses and
cables for frayed wires, loose or broken clamps and fasteners.
lnspect nose door for obvious damage and security of latching.
F1/F2
Chapter 95
3.
lnspect pitot tube(s) for security of attachment. F1/F2
Chapter 52
4.
lnspect crew doors, passenger doors, and baggage
compartment doors for corrosion damage, distortion, positive
locking mechanisms, seals for tears or separations, and doors
for security of attachment. F1/F2, F3/F4
Chapter 25
5.
On helicopters equipped with emergency exit windows in
the passenger doors and/or aft window position, inspect as
follows after removing interior trim from around windows: F3/F4
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 79
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-27.
PROGRESSIVE INSPECTION - EVENT 12 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
a. On passenger door only, visually inspect window
retainer to door frame bond. Replace the retainer if it is not
securely bonded to the frame at all points except at the two
lower corners. F3/F4
b. Visually inspect the inboard side of all rubber retainers.
Any nicks or cracks in the retainer is cause for replacement of
the retainer. F3/F4
c. Check that all filler strips and pull tab are firmly seated
in their retainer grooves. F3/F4
Chapter 25
d. Install interior trim. F3/F4
Chapter 25
6.
lnspect seat cushions and seat backs for tears, excessive
deterioration, and security of attachment. F1/F2, F3/F4
Chapter 25
7.
lnspect seat assemblies for security of attachment.
F1/F2, F3/F4
Chapter 25
8.
lnspect safety belts and shoulder harnesses for
deterioration and security of attachment. F1/F2, F3/F4
Chapter 26
9.
lnspect cabin fire extinguisher for security and condition,
damage, corrosion, and quick opening clamp for operation and
security. F1/F2
Chapter 11
10. lnspect placards and instrument panel decals, and all
Chapter 95
instrument markings for appearance and legibility. F1/F2
Applicable Flight
Manual
11. lnspect first aid kit contents. Replace any items that are
damaged or time expired. Replace any items with deteriorated
packaging. F2
5-00-00
Page 80
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-27.
PROGRESSIVE INSPECTION - EVENT 12 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
CAUTION
INGESTION OF BROKEN INLET SCREEN
SEGMENTS CAN CAUSE FOREIGN OBJECT
DAMAGE TO ENGINE COMPRESSOR SECTION.
Chapter 71
12. lnspect both engine inlet screens for damage. F5/F6
Chapter 71
13. lnspect all firewalls and fireshields for cracks, distortion,
loose or missing rivets, broken spot welds, and deteriorating
seals and sealant. E1/E2
Chapter 71
14. lnspect left power plant area for evidence of fuel and oil
leaks, flexible and rigid fuel and oil lines for wear, chafing,
damage, and security of attachment. E1
Chapter 71
15. lnspect left engine mounts and accessories for damage
and security of attachment. E1
Chapter 76
16. lnspect left engine throttle control housing, push rod, and
lever for wear or lost motion and for security of attachment. E1
17. Inspect left engine ejector for security of attachment at
plenum and support link.
Chapter 71
18. Remove left engine air inlet duct assembly. Inspect duct
assembly for delamination. Inspect reverse flow baffle door for
security of attachment and general condition.
Chapter 71
19. Inspect right power plant area for evidence of fuel and oil
leaks, flexible and rigid fuel and oil lines for wear, chafing,
damage, and security of attachment. E2
Chapter 71
20. Inspect right engine mounts and accessories for damage
and security of attachment. E2
Chapter 76
21. Inspect right engine throttle control push rod, lever, and
bellcrank for lost motion and security of attachment. E2
22. Inspect right engine ejector for security of attachment at
plenum and support link.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 81
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-27.
PROGRESSIVE INSPECTION - EVENT 12 (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
Chapter 71
23. Remove right engine air inlet duct assembly. Inspect duct
assembly for delamination. Inspect reverse flow baffle door for
security of attachment and general condition.
Chapter 65
24. For all main rotor hub assemblies, verify torque of main
BHT-222-CR&O-2
rotor grip(s) retaining bolts/nuts. Apply
100 foot-pounds
(135 Nm) of torque to the nut, in the tightening direction.
Provided 100 foot-pounds (135 Nm) of torque is reached
without movement of the nut, torque the bolt/nut to
125 foot-pounds
(169 Nm). If any nut moves before
100 foot-pounds (135 Nm) of torque is reached, remove grip
from main rotor hub assembly. Inspect/repair pitch horn and grip
assemblies. R1
5-00-00
Page 82
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-28.
EVERY 100 HOURS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN BEAM/ROOF FRAME JOINT
Paragraph 5-32
NOTE
If TB
222-86-92 (Addition of Hi-Lock Fastener),
TB 222-88-114 (Installation of Main Beam) and
TB 222-91-129 (Star Doubler Installation) have been
accomplished, the inspection interval is 300 hours.
Paragraph 5-36
NOTE
Additionally, if referenced TBs have been
accomplished and roof frame 222-031-503-105 or
subsequent has been installed, the inspection
interval is 600 hours.
1.
Remove cover at FS 240, BL 12 on the right interior roof
skin and inspect outboard side of main beam 222-031-583
bulkhead joint for crack(s).
2.
Inspect attachment flange of roof frame 222-031-503 for
crack(s).
3.
At station 233, inspect front and aft portion of roof frame
222-031-503 from BL 0.0 to the right side attachment flange
with the main beam 222-031-583 for cracks. Pay particular
attention to the area in line with the inboard leg of star doubler. If
a crack is found, contact Bell Helicopter Textron Customer
Representative.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 83
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-28.
EVERY 100 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
LANDING GEAR
NOTE
This inspection is not required if landing gear
trunnion 3965001-7 is installed.
NOTE
Clean nose landing gear trunnion prior to inspection
with a 10 to 15% solution of cleaning compound
(C-318) and water.
1.
Using a bright light, visually inspect nose landing gear
trunnion webs for cracks and corrosion. Pay particular attention
to the left 45° web that extends from pivot shaft to cylinder
attachment ring.
5-00-00
Page 84
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-29.
EVERY 150 HOURS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
SWASHPLATE CONTROLS
NOTE
This inspection is applicable to drive pins
222-010-455-003 installed in rotating ring assemblies
222-010-403-005 and/or -113.
Chapter 65
1.
Disconnect both drive link assemblies from swashplate
rotating ring. Inspect trunnion bearing for roughness and/or
looseness. Replace bearing(s) if damaged or rough. F5/F6
2.
Check both swashplate rotating ring drive pins
222-010-455-003 for adequate interference fit as follows:
a. Clean and inspect drive pin
222-010-455-003 for
damage and looseness. Any defect is cause for replacement.
b. Using a marker, create a straight slip mark on the
rotating ring/drive pin joint.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 85
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-29.
EVERY 150 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
NOTE
During the drive pin(s) torque check procedure,
deflection of the torque wrench and the offset
extension may be noticed when torque is applied.
This deflection could be perceived as pin rotation.
Therefore, it is important that clear and precise index
marks on the pins and the ring exist so that rotation
can be verified by visible displacement between the
marks.
NOTE
The head of drive pin 222-010-455-003 has two flats
that fit into a clearance slot inside the rotating ring.
An unacceptable interference fit will allow the pin to
rotate within the slot at a torque less than
50 foot-pounds (67.79 Nm). The motion will be small,
but can easily be detected using procedures in
step e and step f that follow.
An acceptable interference fit will allow zero pin
rotation during the torque check procedure at
50 foot-pounds (67.79 Nm) of torque.
c. Align the rectangular hole of torque test tool
230-210-100-101 on the wrenching flats of the drive pin to be
tested. Secure the tool to the pin with one thrust washer and
nut. Torque the retaining nut 6 to 12 foot-pounds (8.13 to
16.27 Nm).
NOTE
A calibrated dial type torque wrench is recommended
for this torque check. However, if a click type wrench
is used, apply torque with a slow, smooth motion.
Otherwise, the 50 foot-pound (67.79 Nm) torque may
be exceeded.
d. Attach the torque wrench vertically (90° to the centerline
of the tool) to the outboard end of the torque test tool.
5-00-00
Page 86
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-29.
EVERY 150 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
WARNING
APPLICATION OF TORQUE IN EXCESS OF
50 FOOT-POUNDS (67.79 NM) COULD RESULT IN
A BREAKDOWN OF THE PRIMER ADHESION AND
SUBSEQUENT PIN ROTATION, WHICH IS CAUSE
FOR REMOVAL FROM SERVICE OF THE RING
ASSEMBLY.
e. Apply a maximum torque of 50 foot-pounds (67.79 Nm)
in the clockwise/right direction. Verify the slip mark on the
rotating ring/drive pin joint. Any misalignment of the slip mark
indicating rotation of the drive pin is cause for rejection of the
swashplate rotating ring.
f. Apply a maximum torque of 50 foot-pounds (67.79 Nm)
in the counterclockwise/left direction. Verify the slip mark on the
rotating ring/drive pin joint. Any misalignment of the slip mark
indicating rotation of the drive pin is cause for rejection of the
swashplate rotating ring.
BHT-ALL-SPM
g. If no rotation of the drive pin(s) is observed, inspect the
pin(s) for visible damage. Repair any raised material on the
wrenching flats of the drive pin(s) and refinish rework areas as
required.
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9 SEP 2011 Rev. 7
Page 87/88
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-30.
DELETED
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
5-00-00
10 FEB 2020 Rev. 8
Page 89/90
Export Classification C, ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-31.
AFTER FIRST 300 HOURS AND EACH 50 HOURS THEREAFTER
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
SWASHPLATE DUPLEX BEARING
NOTE
The following inspection is not required if triplex
bearing set 222-310-476-101 is installed.
1.
Disconnect swashplate drive links and inspect swashplate
duplex bearing 222-310-470-001 by applying pressure in both
up and down position while rotating the outer ring. If binding or
roughness is found, the bearing must be replaced.
5-00-00
9 SEP 2011 Rev. 7
Page 91/92
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-32.
EVERY 300 HOURS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
SWASHPLATE CONTROLS
1.
Clean and inspect collective friction collet. Inspect drive
hub assembly for interference, security of attachment,
mechanical damage, or corrosion. F5/F6
Chapter 65
2.
Check collet friction and adjust as required.
3.
Remove pitch change links and inspect the following
bearings:
a. Upper pitch link bearing for axial looseness in excess of
0.015 inch (0.38 mm). Replace bearing if limits are exceeded.
b. Lower pitch link bearing in walking beam for roughness.
Check pitch link bearing by misaligning inner race and rotating
while applying slight radial force. Replace bearing if roughness
is felt when rotating inner race.
Chapter 65
4.
Disconnect both drive link assemblies from swashplate
rotating ring. Inspect trunnion bearing for roughness and/or
looseness. Replace bearing(s) if damaged or rough.
Chapter 65
5.
Disconnect both cyclic links, check swashplate friction, and
adjust as required.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 93
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-32.
EVERY 300 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
NOTE
This inspection is applicable to drive pins
230-010-402-101 and -103 installed in any rotating
ring assembly.
Chapter 65
6.
Disconnect both drive link assemblies from swashplate
rotating ring. Inspect trunnion bearing for roughness and/or
looseness. Replace bearing(s) if damaged or rough. F5/F6
7.
Check both swashplate rotating ring drive pins
230-010-402-101/-103 for adequate interference fit as follows:
a. Clean and inspect drive pin 230-010-402-101/-103 for
damage and looseness. Any defect is cause for replacement.
b. Using a marker, create a straight slip mark on the
rotating ring/drive pin joint.
NOTE
During the drive pin(s) torque check procedure,
deflection of the torque wrench and the offset
extension may be noticed when torque is applied.
This deflection could be perceived as pin rotation.
Therefore, it is important that clear and precise index
marks on the pins and the ring exist so that rotation
can be verified by visible displacement between the
marks.
NOTE
The head of drive pin 230-010-402-101/-103 has two
flats that fit into a clearance slot inside the rotating
ring.
An unacceptable interference fit will allow the pin to
rotate within the slot at a torque less than
50 foot-pounds (67.79 Nm). The motion will be small,
but can easily be detected using procedures in
step e and step f that follow.
An acceptable interference fit will allow zero pin
rotation during the torque check procedure at
50 foot-pounds (67.79 Nm) of torque.
5-00-00
Page 94
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-32.
EVERY 300 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
c. Align the rectangular hole of torque test tool
230-210-100-101 on the wrenching flats of the drive pin to be
tested. Secure the tool to the pin with one thrust washer and
nut. Torque the retaining nut 6 to 12 foot-pounds (8.13 to
16.27 Nm).
NOTE
A calibrated dial type torque wrench is recommended
for this torque check. However, if a click type wrench
is used, apply torque with a slow, smooth motion.
Otherwise, the 50 foot-pound (67.79 Nm) torque may
be exceeded.
d. Attach the torque wrench vertically (90° to the centerline
of the tool) to the outboard end of the torque test tool.
WARNING
APPLICATION OF TORQUE IN EXCESS OF
50 FOOT-POUNDS (67.79 NM) COULD RESULT IN
A BREAKDOWN OF THE PRIMER ADHESION AND
SUBSEQUENT PIN ROTATION, WHICH IS CAUSE
FOR REMOVAL FROM SERVICE OF THE RING
ASSEMBLY.
e. Apply a maximum torque of 50 foot-pounds (67.79 Nm)
in the clockwise/right direction. Verify the slip mark on the
rotating ring/drive pin joint. Any misalignment of the slip mark
indicating rotation of the drive pin is cause for rejection of the
swashplate rotating ring.
f. Apply a maximum torque of 50 foot-pounds (67.79 Nm)
in the counterclockwise/left direction. Verify the slip mark on the
rotating ring/drive pin joint. Any misalignment of the slip mark
indicating rotation of the drive pin is cause for rejection of the
swashplate rotating ring.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 95
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-32.
EVERY 300 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
BHT-ALL-SPM
g. If no rotation of the drive pin(s) is observed, inspect the
pin(s) for visible damage. Repair any raised material on the
wrenching flats of the drive pin(s) and refinish rework areas as
required.
8.
Inspect swashplate and lever assembly paying particular
attention to ball sleeve and slider assemblies as follows:
a. Tilt the swashplate to one side and subsequently to the
opposite side to expose each slider in turn. While viewing each
slider, apply a rotational force to the swashplate non-rotating
ring in alternating directions. Carefully observe the slider bolt,
looking for radial movement. Any evidence of radial movement
or fretting residue will require further disassembly of the
swashplate for inspection and repair.
b. Inspect ball sleeve assembly for evidence of debonding
or fretting of upper and lower sleeves. Any evidence of
looseness or fretting residue will require further disassembly of
swashplate for inspection and repair.
c. Move ball sleeve up and down through full range of
travel and inspect swashplate support for surface damage and
evidence of radial play between ball sleeve assembly and
support. Surface damage and/or evidence of radial play will
require further disassembly of swashplate for inspection and
repair.
ENGINE STARTER GENERATOR
BHT-222-CR&O-V.2
NOTE
Inspection intervals may be established per the
manufacturer’s recommendations, as an alternate
means of compliance.
Chapter 96
1.
Inspect right engine starter generator brushes for wear
down to the diagonal groove wear indicator. E2
Chapter 96
2.
Inspect left engine starter generator brushes for wear down
to the diagonal groove wear indicator. E1
5-00-00
Page 96
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-32.
EVERY 300 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
MAIN BEAM/ROOF FRAME JOINT
Paragraph 5-36
NOTE
If TB 222-86-92 (Additional of Hi-Lock Fastener),
TB 222-88-114 (Installation of Main Beam) and
TB 222-91-129 (Star Doubler Installation) have been
accomplished and roof frame 222-031-503-105 or
subsequent has been installed, inspection interval is
600 hours.
1.
Remove cover at FS 240, BL 12 on the right interior roof
skin and inspect outboard side of main beam 222-031-583
bulkhead joint for crack(s).
2.
lnspect attachment flange of roof frame 222-031-503 for
crack(s).
3.
At station 233, inspect front and aft portion of roof frame
222-031-503 from BL 0.0 to the right side attachment flange
with the main beam 222-031-583 for cracks. Pay particular
attention to the area in line with the inboard leg of star doubler. If
a crack is found, contact Bell Helicopter Textron Customer
Representative.
HYDRAULIC PUMP SPLINES
Paragraph 5-37
NOTE
If
TB
222-88-115 (Hydraulic Pump, Vespel
Driveshaft) has been accomplished, inspection
interval is 1200 hours.
Chapter 12
1.
Remove left hydraulic pump. lnspect pump drive spline and
Chapter 29
transmission adapter gear spline for wear. Lubricate splines.
Chapter 12
2.
Remove right hydraulic pump. lnspect pump drive spline
Chapter 29
and transmission adapter gear spline for wear. Lubricate
splines.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 97
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-32.
EVERY 300 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
HORIZONTAL STABILIZER
NOTE
This inspection is not applicable to 222-035-250-107
and -109.
1.
X-ray horizontal stabilizer
222-035-250-103 and
-105.
Refer to ASB 222-89-53 for inspection procedure.
5-00-00
Page 98
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-33.
(MODEL 222) 300 AND 900 HOURS AFTER INITIAL INSTALLATION (SPRINGLESS
DRIVESHAFT ONLY)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
ENGINE DRIVESHAFT ADAPTER 222-044-066
A torque check of the adapter retaining bolt is required at initial
installation of the springless driveshaft assembly and after
300 and 900 hours of operation.
Chapter 66
1.
Remove main driveshaft utilizing plate assembly
T103031-107 (or a suitable alternate), hold engine adapter, and
verify retaining bolt torque (35 to 45 foot-pounds) (47.50 to
61.0 Nm). If torque is low, remove the bolt and perform visual
and magnetic particle inspection. Wear or crack indications on
the bolt are cause for rejection. Each time a low torque condition
is encountered, the torque check must be repeated at 300 and
900 hours of operation until the torque of the bolt stabilizes at
both intervals.
2.
When the torque of the bolt has stabilizes at both 300 and
900 hours of operation, the torque check inspection is no longer
required provided the same bolt, engine adapter, and engine
combination is maintained and not disassembled. Replacement
of any of these components will require the bolt torque check
inspection to be repeated.
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9 SEP 2011 Rev. 7
Page 99/100
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-34.
EVERY 600 HOURS OR 6 MONTHS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
ENGINE FIRE EXTINGUISHER AND CARTRIDGE
Chapter 26
1.
Inspect right engine fire extinguisher for dents and
Chapter 96
scratches. Perform operational test of engine fire extinguisher
system.
Chapter 26
2.
Inspect left engine fire extinguisher for dents and
Chapter 96
scratches. Perform operational test of engine fire extinguisher
system.
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9 SEP 2011 Rev. 7
Page 101/102
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-35.
EVERY 600 HOURS OR 12 MONTHS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN DRIVESHAFT
Chapter 12
1.
Inspect and lubricate the right main driveshaft.
BHT-222-CR&O-2
Chapter 12
2.
Inspect and lubricate the left main driveshaft.
BHT-222-CR&O-2
TAIL ROTOR DRIVESHAFT
Chapter 12
1.
Inspect and lubricate tail rotor driveshaft flexible coupling.
BHT-222-CR&O-3
F5/F6
MAIN ROTOR MAST ASSEMBLY
NOTE
Removal of the main rotor hub assembly and main
rotor swashplate assembly is not required to inspect
the exposed external surfaces of the mast located
above the transmission.
BHT-222-CR&O-2
1.
Inspect the electroless nickel coated area of the mast.
BHT-222-CR&O-2
2.
Inspect the exposed external surfaces of the mat located
above the transmission.
5-00-00
Export Classification C, ECCN EAR99
10 FEB 2020 Rev. 8
Page 103
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-35.
EVERY 600 HOURS OR 12 MONTHS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
3.
Inspect the Teflon liners on the inboard surface of all the
fingers of collective friction collet for condition, wear, and
debonding.
5-00-00
Page 104
Rev. 8
10 FEB 2020
Export Classification C, ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-36.
EVERY 600 HOURS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN BEAM/ROOF FRAME JOINT
Paragraph 5-28
NOTE
If TB 222-86-92 (Additional of Hi-Lock Fastener),
TB 222-88-114 (Installation of Main Beam) and
TB 222-91-129 (Star Doubler Installation) have not
been accomplished, the main beam/roof frame joint
shall be inspected every 100 hours.
1.
Remove cover at FS 240, BL 12 on the right interior roof
skin and inspect outboard side of main beam 222-031-583
bulkhead joint for crack(s).
2.
lnspect attachment flange of roof frame 222-031-503 for
crack(s).
3.
At station 233, inspect front and aft portion of roof frame
222-031-503 from BL 0.0 to the right side attachment flange
with the main beam 222-031-583 for cracks. Pay particular
attention to the area in line with the inboard leg of star doubler. If
a crack is found, contact Bell Helicopter Textron Customer
Representative.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 105
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-36.
EVERY 600 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
TRANSMISSION
NOTE
Whenever outboard collective lever idler link
bushings are inspected/measured, the inner floating
bushings 222-010-483-001 must also be inspected
for damage and wear. New bushing dimensions are:
inside diameter: 0.6250 to 0.6255 inch (15.87 to
15.89 mm) and outside diameter:
0.8740 to
0.8745 inch (22.20 to 22.21 mm).
1.
lnspect inner diameter of the two outboard collective lever
idler link bushings on the transmission top case 222-040-061 for
wear in excess of 0.8774 inch (22.28 mm). Take measurements
at two points, 90° apart. If bushing(s) wear exceeds above
limits, replace bushing(s) per TB 222-02-169.
NOTE
The following inspections are not required on
transmission modified in accordance with
TB 222-84-65 or TB 222-84-66 and 222-00-163, and
serviced with
555 lubricating oil, specification
DOD-PRF-85734 (AS).
2.
Visually inspect gear teeth of six pinions for excessive
wear or pitting. Pitting may be in the form of micropits: very
minute pit near the top or bottom edges of gear teeth, which
may cause a frosted or etched appearance in the advanced
stages.
3.
Visually inspect gear teeth of sun gear for excessive wear
or pitting.
LIFT LINK
Chapter 66
1.
Remove lift links and inspect rod end bearings
BHT-222-CR&O-2
elastomerics for separation/delamination and serviceability.
F5/F6
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Page 106
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-36.
EVERY 600 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
OIL COOLER BLOWER
Chapter 12
NOTE
If TB 222-92-132 (Oil Cooler Blower Torlon Drive)
has not been accomplished, the oil cooler blower
drive splines shall be lubricated every 300 hours.
Chapter 71
1.
Inspect left engine oil cooler blower.
Chapter 71
2.
Inspect right engine oil cooler blower.
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9 SEP 2011 Rev. 7
Page 107/108
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-37.
EVERY 1200 HOURS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
HYDRAULIC PUMP SPLINES
Paragraph 5-32
NOTE
If
TB
222-88-115 (Hydraulic Pump, Vespel
Driveshaft) has been accomplished, inspection
interval is 300 hours.
Chapter 29
1.
Remove left hydraulic pump. Inspect pump drive spline and
transmission adapter gear spline for wear. F5
Chapter 29
2.
Remove right hydraulic pump. Inspect pump drive spline
and transmission adapter gear spline for wear. F6
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9 SEP 2011 Rev. 7
Page 109/110
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-38.
EVERY 2500 HOURS OF COMPONENT OPERATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN ROTOR HUB
NOTE
This inspection is applicable to all main rotor hub
assemblies 222-011-101 and 222-012-101.
Chapter 65
1.
Remove main rotor hub and blades.
2.
Disassemble and clean main rotor hub.
NOTE
It is not necessary to remove the flapping bearings
from the trunnion to accomplish this inspection.
BHT-ALL-SPM
3.
Perform a fluorescent penetrant inspection of the following
parts:
a. Grip assembly
b. Pitch horn assembly
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 111
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-38.
EVERY 2500 HOURS OF COMPONENT OPERATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
BHT-ALL-SPM
4.
Perform magnetic particle inspection on the following parts:
NOTE
Some of the bolts used in these applications are
manufactured from non-magnetic material. For those
bolts, fluorescent penetrant inspection method
(BHT-ALL-SPM is acceptable in leu of magnetic
particle inspection requirement.
a. Pitch horn to grip attachments bolts
NOTE
Some of the bolts used in these applications are
manufactured from non-magnetic material. For those
bolts, fluorescent penetrant inspection method
(BHT-ALL-SPM is acceptable in leu of magnetic
particle inspection requirement.
b. Flapping bearing to yoke attachment bolts
BHT-222-CR&O-2
5.
Install new buffers on the pitch horn assemblies and
flapping bearing assemblies.
BHT-222-CR&O-2
6.
Reassemble main rotor hub.
Chapter 65
7.
Install main rotor hub and blades.
5-00-00
Page 112
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-39.
EVERY 6 MONTHS
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
STANDBY ATTITUDE INDICATOR
Chapter 95
1.
Test the pilot standby attitude indicator power supply.
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9 SEP 2011 Rev. 7
Page 113/114
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-40.
EVERY 2 CALENDAR YEARS
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
PITOT STATIC SYSTEM
Chapter 95
1.
Drain any accumulated moisture from the pitot-static
system piping. F1/F2
FLIGHT CONTROLS
1.
Inspect flight control bolts. R1
NOTE
More frequent inspection of control bolts may be
required when operating in adverse environmental
conditions.
Chapter 65
a. Remove the following bolts:
BHT-ALL-SPM
• Main rotor pitch link universal bearing lower (2)
• Main rotor pitch link lower (2)
• Main Rotor pitch link universal bearing upper (2)
• Collective lever to servo (1)
• Cyclic lever to servo (2)
• Swashplate horn to cyclic links (2)
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 115
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-40.
EVERY 2 CALENDAR YEARS (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
• Walking beam to drive hub (2)
• Walking beam to drive link (2)
• Idler link to transmission top case (2)
• Collective levers to idler link (2)
• Cyclic link to cyclic lever (2)
b. Clean bolts with cloth damp with MEK (C-309).
c. Visually inspect bolts for thread damage, shank wear,
and corrosion. Replace bolts that show evidence of damaged
threads, shank wear, or corrosion pitting.
Chapter 65
d. Apply corrosion preventive compound (C-104) to
BHT-ALL-SPM
shanks of bolts only and install.
e. After bolts are installed, torqued, and lockwired, coat
bolt heads and nuts with corrosion preventive compound
(C-101).
VERTICAL FIN
Chapter 53
1.
Remove vertical fin. Discard nuts.
BHT-ALL-SPM
2.
Inspect the vertical fin and tailboom fittings for cracks,
elongation of bolt holes, distortion, and corrosion.
3.
Inspect attaching bolts for serviceability.
4.
Temporarily install vertical fin to tailboom using serviceable
hardware. Tighten hardware 5 inch-pounds (0.5 Nm) plus tare.
Using feeler gauge, measure gap at eight locations where
vertical fin fitting contacts tailboom fitting. Gap shall be less than
0.003 inch
(0.076 mm). If gap is larger than
0.003 inch
(0.076 mm), fill gap using shim 120-008C40E11. Maximum
allowable shim thickness to be 0.010 inch (0.254 mm). Remove
vertical fin.
5-00-00
Page 116
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-40.
EVERY 2 CALENDAR YEARS (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
CAUTION
ATTACHING HARDWARE SHALL BE TORQUED
TO SPECIFIED TORQUE WITHIN 60 MINUTES
AFTER APPLICATION OF SEALANT.
5.
Apply sealant (C-308) to faying surface of vertical fin fitting
and tailboom fitting. Install shim (if required).
6.
Apply corrosion preventive compound (C-104) to shank
only of all attaching bolts.
CAUTION
HARDWARE AND TORQUE REQUIREMENTS OF
THE VERTICAL FIN INSTALLATION ARE
AFFECTED BY ACCOMPLISHMENT OF
TB 222-98-156.
Chapter 53
7.
Install vertical fin to tailboom using bolts, washers, and
BHT-ALL-SPM
nuts. Torque attaching bolts/nuts as required.
8.
Coat all bolt heads, nuts, and washers with corrosion
preventive compound (C-101).
5-00-00
9 SEP 2011 Rev. 7
Page 117/118
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-41.
EVERY 3 CALENDAR YEARS
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
HYDRAULIC SYSTEM RESERVOIR
Chapter 29
1.
Replace hydraulic system PC-1 reservoir baffle. F6
Chapter 29
2.
Replace hydraulic system PC-2 reservoir baffle. F5
EMERGENCY FLOTATION SYSTEM
NOTE
This inspection applies to any reservoir/cylinder that
has been manufactured or last retested prior to
July 1, 2006.
Chapter 99
1.
Remove emergency flotation system nitrogen reservoir.
BHT-222-SI-20
Perform a hydrostatic test in accordance with DOT-SP-8162
BHT-222-SI-25
cylinder inspection.
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9 SEP 2011 Rev. 7
Page 119/120
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-42.
EVERY 5 CALENDAR YEARS
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
FIRE EXTINGUISHER RESERVOIR
Chapter 4
NOTE
Refer to Airworthiness Limitations for squib
replacement intervals.
Chapter 26
1.
Remove the right fire extinguisher reservoir. Do a
hydrostatic test in accordance with specification DOT-4 DA,
DOT-4 DS, or DOT-SP-7945 as marked on container. F4
Chapter 26
2.
Remove the left fire extinguisher reservoir. Do a hydrostatic
test in accordance with specification DOT-4 DA, DOT-4 DS, or
DOT-SP-7945 as marked on container. F3
EMERGENCY FLOTATION SYSTEM
NOTE
This inspection applies to any reservoir/cylinder that
has been manufactured or last retested after July 1,
2006.
Chapter 99
1.
Remove emergency flotation system nitrogen reservoir.
BHT-222-SI-20
Perform a hydrostatic test in accordance with DOT-SP-8162
BHT-222-SI-25
cylinder inspection.
5-00-00
9 SEP 2011 Rev. 7
Page 121/122
ECCN EAR99
BHT-222/222B-MM-1
SCHEDULED INSPECTIONS
5-43.
EVERY 10 CALENDAR YEARS
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN ROTOR MAST ASSEMBLY (TORQUEMETER)
NOTE
This inspection is only applicable for mast
assemblies P/N 222-040-130-1, 222-040-130-101,
222-040-130-107 and 222-040-130-109. For mast
assemblies P/N 222-040-130-113 and subsequent,
this inspection does not need to be done.
BHT-222-CR&O-2
1.
Mast assembly must be disassembled and inspected for
corrosion, both externally and internally, in addition to the
inspection criteria of the BHT-222-CR&O-2. The torquemeter
shaft must be removed to inspect the inside diameter. The mast
assembly must be returned to Bell Helicopter Textron for
reindexing of the mast torque sensing components. R1
5-00-00
10 FEB 2020 Rev. 8
Page 123/124
ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-44.
SPECIAL INSPECTIONS
• Vertical Fin (after 5 to 10 hours of operation
following each installation)
Special inspections are a one-time inspection that
must be performed at specified times following certain
• Main Rotor Hub (after
5 to
10 hours of
maintenance actions.
operation following each installation)
The parts affected include the following:
• Hydraulic Actuator Support (after
5 to
10 hours of operation following each
• Main Rotor Hub (after every main rotor hub
installation)
disassembly)
• Main Rotor Trunnion (after the first flight
• Tail Rotor Hub and Blades (after 5 to 10 hours
following each installation)
of operation following each installation)
• Tail Rotor Hub Retention Nut (after
1 to
• Swashplate (after
25 hours of operation
5 hours of operation following each
following each installation)
installation)
• Main Rotor Trunnion (after
25 hours of
• Main Rotor Mast Nut (after 5 to 10 hours of
operation following each installation)
operation following each installation)
• Engine Tailpipe Coupling (after 5 to 10 hours
• Tail Rotor Gearbox (after
100 hours of
of operation following each installation)
operation following each installation)
5-00-00
9 SEP 2011 Rev. 7
Page 125/126
ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-45.
AFTER EVERY MAIN ROTOR HUB DISASSEMBLY
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN ROTOR HUB
NOTE
This inspection is to be performed every time the
main rotor hub is disassembled to the extent allowing
inspection of the buffers installed on the pitch horns
and the flapping bearings.
BHT-222-CR&O-2
1.
When the main rotor hub is disassembled, inspect
condition of the buffers on the pitch horns, flapping bearings,
and the yoke assembly. No defect allowed. Install new buffers
as required. R1
5-00-00
9 SEP 2011 Rev. 7
Page 127/128
ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-46.
AFTER FIRST FLIGHT FOLLOWING EACH INSTALLATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN ROTOR TRUNNION
BHT-222-CR&O-2
1.
Verify torque of main rotor trunnion bolts in the tightening
direction, minimum
45 foot-pounds
(61 Nm). Provided
45 foot-pounds (61 Nm) is reached without movement of bolts,
torque bolts to 53 foot-pounds (72 Nm). If any bolt moves before
45 foot-pounds (61 Nm) is reached, remove all six bolts and
visually inspect for crack(s) or sign(s) of yielding. If any
defective bolts are found, replace all six bolts. If no defects are
found, reinstall bolts. R1
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Page 129/130
ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-47.
AFTER 1 TO 5 HOURS OF OPERATION FOLLOWING EACH INSTALLATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
TAIL ROTOR HUB RETENTION NUT
Chapter 66
1.
Following each installation, verify torque of retention nut
attaching the tail rotor hub assembly to the tail rotor gearbox
output shaft. Repeat the torque verification every 1 to 5 hours
until torque stabilizes to 40 to 50 foot-pounds (54 to 68 Nm). R2
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ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-48.
AFTER 5 TO 10 HOURS OF OPERATION FOLLOWING EACH INSTALLATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
MAIN ROTOR MAST NUT
Chapter 65
1.
Following each installation, verify torque of nut to 475 to
675 foot-pounds (644 to 915 Nm) after a minimum of 5 hours,
but not to exceed 10 hours of service. R1
ENGINE TAILPIPE COUPLING
1.
Following each installation, verify torque of coupling nut 70
to 100 inch-pounds (7.9 to 11.3 Nm) after initial engine run, and
every 5 to 10 hours thereafter until torque remains within limit
for three consecutive inspections.
Chapter 53
VERTICAL FIN
CAUTION
HARDWARE AND TORQUE REQUIREMENTS OF
THE VERTICAL FIN INSTALLATION ARE
AFFECTED BY ACCOMPLISHMENT OF
TB 222-98-156.
1.
Following each installation, make sure the torque of the
retention bolts/nuts is correct after a minimum of 5 hours, but
not to exceed 10 hours of service. Apply the highest value of
specified torque range to the nut while restraining the bolt head.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 133
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-48.
AFTER 5 TO 10 HOURS OF OPERATION FOLLOWING EACH INSTALLATION (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
MAIN ROTOR HUB
BHT-222-CR&O-2
1.
Following each installation, verify torque of main rotor
grip(s) retaining bolt/nuts to 125 foot-pounds (169 Nm) after a
minimum of 5 hours, but not to exceed 10 hours of service.
BHT-222-CR&O-2
2.
Following each installation, verify torque of main rotor
flapping bearing(s) retaining bolts/nuts to
125 foot-pounds
(169 Nm) after a minimum of 5 hours, but not to exceed
10 hours of service.
TAIL ROTOR HUB AND BLADES
BHT-222-CR&O-3
1.
Inspect tail rotor blade attaching bolts/nuts for correct
torque after a minimum of 5 hours, but not to exceed 10 hours of
operation after each installation. Apply highest value of
specified torque range to the nut while restraining the bolt head.
Repeat the torque verification every 1 to 5 hours until torque
stabilizes. R2
HYDRAULIC ACTUATOR SUPPORT
BHT-222-CR&O-2
1.
Following each installation, verify torque of hydraulic
actuator support attaching nuts for correct torque after a
minimum of 5 hours, but not to exceed 10 hours of service.
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Page 134
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-49.
AFTER 25 HOURS OF OPERATION FOLLOWING EACH INSTALLATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
SWASHPLATE
Chapter 65
1.
Verify swashplate friction adjustment 25 hours after initial
installation. R1
MAIN ROTOR TRUNNION
BHT-222-CR&O-2
NOTE
Retorque is not required if flapping springs
222-310-117-105 are installed.
1.
Verify torque of main rotor trunnion bolts in the tightening
direction, minimum
45 foot-pounds
(61 Nm). Provided
45 foot-pounds (61 Nm) is reached without movement of bolts,
torque bolts to 53 foot-pounds (72 Nm). If any bolt moves before
45 foot-pounds (61 Nm) is reached, remove all six bolts and
visually inspect for cracks or signs of yielding. If any defective
bolts are found, replace all six bolts. If no defect(s) are found,
reinstall bolts. R1
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ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-50.
AFTER 100 HOURS OF OPERATION FOLLOWING EACH INSTALLATION
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
TAIL ROTOR GEARBOX
Chapter 66
1.
Verify torque of tail rotor gearbox retaining nuts. T1/T2
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ECCN EAR99
BHT-222/222B-MM-1
SPECIAL INSPECTIONS
5-50A. AFTER 600 HOURS OR 12 MONTHS, WHICHEVER OCCURS FIRST
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
Chapter 27
MAGNETIC BRAKE ASSEMBLY 204-001-376-105 AND
204-001-376-107
- Detailed Visual Inspection
1.
Get access to the fore and aft and lateral magnetic brake
assemblies located under the co-pilot seat.
NOTE
Make sure that stop shaft not dis-bonded from the
housing assembly.
2.
Remove the stop assemblies from original position and do
a visual inspection of the stop assemblies.
3.
If any evidence of dis-bonding, inspect the lower side of the
arm for possible chafing damage, refer to Chapter
27,
Paragraph 27-82A for repair procedure.
NOTE
The maximum allowable mechanical damage limit is
0.030 inch (0.762 mm).
4.
If no evidence of dis-bonding, install the stop assemblies.
5-00-00
10 FEB 2020 Rev. 8
Page 138A/138B
Export Classification C, ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-51.
CONDITIONAL INSPECTIONS
• Lightning Strike
Conditional inspections are unscheduled inspections
• Overspeed
or checks that must be performed following the
occurrence of unusual events reported during the
• Compressor Stall or Surge
operation of the helicopter. Such events include (but
are not limited to) the following:
Components removed from a helicopter for evaluation
• Hard Landing
as a result of conditional inspection shall be evaluated
as an interrelated group. Removal records
• Sudden Stoppage - Power ON or OFF
accompanying each component shall cross-reference
part and serial numbers of other components removed
• Overtorque
for evaluation.
5-00-00
9 SEP 2011 Rev. 7
Page 139/140
ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
A hard landing is defined as any incident or accident in which
the impact of the helicopter with the ground causes severe
pitching of the main rotor, allowing hard contact of hub with
mast, which results in cracking or yielding of the transmission or
nodal beam support structure, or imparts unusually high loads
on the landing gear.
A hard landing relative to retractable landing gear is any landing
that causes any of the tires and/or shock struts to bottom out
(when properly serviced) or induces high side loads on any of
the landing gear. The following condition at touchdown could
result in such a landing:
• Excessive rate of descent
• Excessive sideward speed
• High roll angle coupled with normal rates of descent
• High yaw angles coupled with normal forward landing
speeds
• Landing with forward airspeed in soft or unprepared soil
Following hard landing, accomplish the following:
Paragraph 5-53
1.
Inspect main and tail rotor blades for evidence of strike
damage. If such evidence is found on either rotor, perform
Sudden Stoppage - Power ON or OFF.
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9 SEP 2011 Rev. 7
Page 141
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
2.
Visually inspect underside of fuselage and tailboom for
evidence of ground contact.
3.
If, under the conditions previously noted, the landing gear
is judged to have been involved in a hard landing, place the
helicopter on jacks and perform the following inspections:
a. Visually inspect tires for cuts, damage, and deflation.
NOTE
If wheel is deformed or cracked, replace wheel and
remove landing gear assembly for disassembly and
inspection.
b. Inspect wheel rims for cracks or deformation. Check
wheel rim connecting bolts for looseness and damage. Inspect
brake assemblies for cracks or damage to housing or mounting
bolts.
c. Inspect wheel yokes for yielding and twist (removal of
yoke from landing gear is required). Fluorescent penetrant
inspect yoke for cracks. Check holes for elongation.
d. Inspect main and nose gear drag arm and landing gear
housing for deformation and for damage at airframe attachment
points. Check airframe attachment fittings for cracks and
damaged rivets.
NOTE
If the landing gear airframe attachment fittings show
indications of damage, as necessary remove lower
wing access covers and inspect all wing attachment
fittings and bolts for cracks or deformation; remove
under fuselage access panels and inspect main
beams for damage.
NOTE
If during removal of air or shock strut cycling,
hydraulic fluid is expelled from air valve, remove
landing gear for further inspection.
5-00-00
Page 142
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
e. Remove air from shock strut. Leave air valve open and
cycle shock struts by manually raising and lowering wheel from
fully extended to fully compressed position. Check shock strut
for binding. If binding occurs, remove landing gear for
disassembly and inspection.
f. Manually raise landing gear to retracted position and
check for deformation, looseness, and clearance within wheel
well.
4.
lnspect mast for evidence of hard rotor hub contact,
sufficient to yield or deform the mast.
5.
If no damage has been found at this point, it can
reasonably be decided that a true hard landing did not occur.
Complete a daily inspection and return helicopter to flight status
provided no further evidence of damage is found.
6.
If damage is more extensive than landing gear crosstube
yielding, or if a hard landing has occurred, comply with step 7
through step 22.
7.
Inspect main and tail rotor blades for evidence of strike
damage. If no obvious damage is discovered, the blades may
be retained in service for continued usage. However, if either
rotor comes into contact with the ground, tailboom or other
foreign object, the blades are to be regarded as having been
involved in a sudden stoppage and must be returned to a blade
repair station for inspection.
8.
Visually inspect underside of fuselage and tailboom for
evidence of ground contact.
9.
For transmission and mast inspection, proceed as follows:
a. lnspect mast for evidence of hard rotor hub contact,
sufficient to yield or deform mast.
5-00-00
ECCN EAR99
9 SEP 2011 Rev. 7
Page 143
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
BHT-222-CR&O-2
NOTE
If there is any yielding or deformation in areas
contacted by main rotor hub, or any other obvious
damage, the mast is unserviceable and
nonrepairable, and transmission top case must be
inspected for yielding.
b. Inspect transmission mounting points for cracks, loose,
sheared, or elongated rivets, studs, or bolts, distortion or
deformation, paying particular attention to the following areas:
(1) Restraints and restraint fittings
(2) Transmission top case and lift link attachment
fittings
(3) Transmission outboard quill case and forward lift
links
(4) Transmission redundant pylon up-stop plates and
up-stop pins
(5) Nodal beam travel (up and down) stops and
flexure fittings
(6) Main driveshaft transmission-end coupling grease
retainer sleeves and adjoining shaft area
10. For main rotor hub inspection, proceed as follows:
a. The main rotor flexure may be inspected in the following
manner without removing the hub from the helicopter:
(1) Untie the main rotor so that the blades are free to
flap.
(2) Place a 6-inch (15-cm) (or equivalent) straight
edge across the bottom surface of the flexure.
5-00-00
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Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(3) Measure the resulting gap between bottom of the
flexure and the midpoint of the straight edge with a feeler gauge
on both flexures. If the difference between the two
measurements is unequal in excess of 0.003 inch (0.076 mm),
or in excess of 0.030 inch (0.762 mm) on either flexure, the hub
should be removed and returned to an overhaul facility for
evaluation.
(4) If requirements of preceding steps are not
exceeded, the hub may be reused.
b. Inspect the static stops for yielding.
NOTE
The following procedure should be used to
determine the distance from concave surface of yoke
to concave surface of static stop. If distance is less
than 0.025 inch (0.635 mm), static stop has yielded
excessively and must be replaced. Modeling clay,
wax, or any other material that will give a suitable
impression may be used.
(1) Press small amount of modeling clay against yoke
to static stop intersection to form an impression in clay.
(2) Carefully remove clay and inspect offset with a
0.025-inch (0.635-mm) gauge.
(3) If offset is less than 0.025 inch (0.635 mm), static
stop must be replaced.
(4) Repeat procedure to inspect static stop on
opposite side of yoke.
BHT-222-CR&O-2
11. If any damage is found after completing the inspections of
step 7, step 9, and step 10, remove and perform an overhaul
inspection of following components:
a. Mast assembly
b. Transmission assembly
c. Main driveshaft assemblies
5-00-00
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9 SEP 2011 Rev. 7
Page 145
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
12. Check all cowling, fairing, windows, and doors for proper fit
and alignment. Misalignment may indicate a distorted fuselage,
resulting in major stresses and damage to components.
13. Inspect cabin roof structure in the nodal beam area for
loose, missing, or sheared rivets, and distortion or damage to
roof panels or supporting beam structure. Check for crack(s)
and loose Hi-Locks in fitting connection areas. Particular
attention should be directed to the nodal beam attachment
fittings and pylon up-stop fittings.
14. Remove lower wing access covers and inspect all wing
attachment fittings and connecting hardware for crack(s) or
deformation.
15. lnspect tailboom internally and externally for crack(s),
distortion, and loose rivets, especially in the tailboom aft
fuselage splice area and at the tail rotor gearbox attachment
fitting.
16. lnspect vertical fin for damage and distortion, paying
particular attention to the tail skid, the mounting structure, and
the vertical fin attachment fitting.
NOTE
If significant damage has been found in any area of
the airframe, inspection shall be expanded in those
areas until it extends beyond the zone of damage.
Honeywell
17. Perform engine Excessive-G Inspection.
101-650C/750C
Series Operation and
Maintenance Manual,
LTS 101-2.2
18. Perform complete visual inspection of the flight control
system from cockpit to main rotor head for bent or damaged
tubes, damaged actuator structure, bellcranks and supports,
and for damaged bearings. Particular attention should be given
to all rotating and nonrotating controls mounted above the
transmission.
5-00-00
Page 146
Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-52.
HARD LANDING (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
19. Check for leaks in the hydraulic system, interference or
binding of hydraulic actuators and controls, and for satisfactory
operation.
20. lnspect fuel and oil systems for damage and leaks.
21. lnspect fuel system breakaway valves (vent and wing/
fuselage disconnects).
a. Actuation of the vent line will be readily noticeable as
separation of the two halves is required before the valve halves
seal.
b. Actuation of the interconnect valve will be detectable by
observing a yellow ring adjacent to the frangible section. If the
ring is visible, the valve has actuated and requires replacement.
22. Perform a thorough visual inspection of the following
components. If inspection does not reveal any discrepancies or
obvious damage to components, they may be retained in
service.
a. Tail rotor hub and controls
b. Tail rotor gearbox
c. Tail rotor driveshafts
d. Tail rotor driveshaft hanger assemblies
e. Main rotor blades
f. Tail rotor blades
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9 SEP 2011 Rev. 7
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ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
Sudden stoppage is defined as any rapid deceleration of the
drive system whether caused by seizure within the helicopter
transmission or by contact of the main or tail rotor blades with
the ground, water, snow, dense vegetation, or other object of
sufficient mass to cause deceleration. Tail rotor blade damage,
when caused by striking some object sufficient to require blade
replacement, is considered sudden stoppage. When sudden
stoppage occurs, inspect helicopter and replace components as
follows:
NOTE
If sudden stoppage is the result of main rotor strike,
comply with step 1. If sudden stoppage is the result
of tail rotor strike, comply with step 2.
1.
Perform a sudden stoppage inspection as follows:
a. Main Rotor Blades
(1) Visually inspect both main rotor blades for
evidence of damage such as cracks, bonding voids, and
wrinkled skin.
(2) Model
222 with
222-015-500 Series blades:
Remove blade tip cap assembly and inspect tip cap assembly
and inspect tip cap attaching screws for deformation. Any
deformation of screws or elongation of mating holes in spar is
cause for blade to be disposed of.
5-00-00
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9 SEP 2011 Rev. 7
Page 149
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(3) If either blade is damaged, return both blades to an
authorized overhaul facility. Make an entry in component record
to show reason for removal was sudden stoppage.
(4) If no evidence of damage is found on either blade,
both blades may be retained in service.
b. Main Rotor Hub
(1) If main rotor blades were not damaged, the main
rotor hub may be retained in service.
BHT-222-CR&O-2
(2) If main rotor blades incurred damage, perform an
overhaul evaluation inspection on main rotor hub assembly.
Make an entry in component record to show reason for removal
was sudden stoppage.
c. Main Rotor Controls
BHT-222-CR&O-2
(1) If one or more of the following discrepancies in
step (a) through step (d) are found, the swashplate and levers
assembly, and the drive assembly shall be removed and an
overhaul inspection shall be performed.
(a) Main rotor blade damage requiring overhaul
or replacement
(b) Obvious damage or deformation to pitch horn
or connecting bolts
(c) Pitch change link failure of any type
(d) Damage to lift link (upper or lower)
attachment fittings, transmission up-stops, or nodal beam travel
stops
(2) If no condition exists as listed in preceding step c,
substep (1); perform a close visual inspection and if no
evidence of damage is found, the swashplate and levers
assembly and the drive assembly may be retained in service.
(3) Replace all bolts in rotating controls. Scrap
removed bolts.
5-00-00
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Rev. 7
9 SEP 2011
ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
BHT-222-CR&O-2
d. Main Driveshafts
(1) Remove and inspect main driveshafts visually.
If evidence of yielding or deformation is noted, scrap the
appropriate driveshaft assembly and the engine driveshaft
adapter and attaching bolts.
BHT-222-CR&O-2
(2) If no visual evidence of damage is detected,
perform an overhaul. Make an entry in component record to
show reason for removal was sudden stoppage.
e. Engine Mounts
(1) lnspect No. 1 and No. 2 engine mounts for cracks
or distorted mount bolts.
Honeywell Overhaul
(2) If driveshaft has been scrapped or sudden
Manual
stoppage has occurred sufficient to crack engine mounts or
yield connecting bolts, remove the affected engine and perform
an overhaul evaluation.
(3) Make an entry in component record to show
reason for removal was sudden stoppage.
BHT-222-CR&O-2
f. Transmission and Mast Assembly
(1) If mast has evidence of torsional yielding, the mast
and transmission shall be considered unserviceable and
scrapped. If a main driveshaft required replacement (step d),
the outboard quill will be unserviceable and scrapped.
BHT-222-CR&O-2
(2) If mast does not have torsional yielding, main
driveshafts were retained (step d), and transmission has no
obvious damage that would render it nonrepairable, the
transmission and mast shall have an overhaul evaluation. Make
an entry in component record to show reason for removal was
sudden stoppage.
BHT-222-CR&O-2
(3) Replace collector gear. lnspect collector gear shaft
for excessive runout of gear mounting flange. Runout of the
gear flange must not exceed 0.0004 inch (0.0102 mm) when
gear shaft is mounted on centers or on bearing journals.
5-00-00
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9 SEP 2011 Rev. 7
Page 151
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
g. Tail Rotor Driveshaft System
BHT-222-CR&O-3
(1) Visually inspect tail rotor driveshaft tubes for
evidence of torsional deformation.
(2) Remove gear coupling assembly at transmission
tail rotor output quill. Disassemble as required to visually inspect
condition of both drive and coast side of male and female
coupling teeth.
(3) lnspect torque on tail rotor gearbox retaining nuts
for 100 to 140 inch-pounds (11.3 to 16 Nm).
(4) If any of the following criteria is met, inspections
specified by sudden stoppage caused by tail rotor strike (step 2)
shall also be accomplished. If none of the four criteria is met,
completion of step 2 is not required.
(a) Main rotor blade damage is sufficient to
render blade nonrepairable.
(b) Gapping of tail rotor driveshaft disc couplings
exceeds 0.005 inch (0.127 mm).
(c) Any evidence of torsional yielding has been
found in tail rotor driveshaft tubes.
(d) Inspection of gear tooth coupling in step (2)
revealed chipping or other damage to coupling teeth.
BHT-222-CR&O-3
h. Tail Rotor Hub and Blade Assembly
BHT-222-CR&O-3
If sudden stoppage originated at main rotor or transmission, tail
rotor hub and blade assembly may remain in service provided
there is no visible external damage. If visible damage is noted
on tail rotor hub and blade assembly, remove tail rotor hub and
blade assembly and perform overhaul evaluation. Make an
entry in component record to show reason for removal was
sudden stoppage.
2.
Perform the following inspection if sudden stoppage is the
result of a tail rotor strike.
BHT-222-CR&O-3
a. Tail Rotor Driveshaft Hangers and Coupling
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(1) Visually inspect all tail rotor driveshafts hangers. If
shaft has been damaged by main rotor strike or circumstances
other than torsional overload, hangers to which damaged shaft
was attached shall be considered unserviceable and scrapped.
If any shaft fails as a result of torsional load, all hangers,
coupling, and shafts shall be considered unserviceable and
scrapped.
BHT-222-CR&O-3
(2) Remove gear coupling assembly at tail rotor output
quill. Disassemble as required to inspect condition of both drive
and coast side of male and female coupling teeth.
BHT-222-CR&O-3
(3) If inspection reveals no condition as listed in
step (1), and there is no obvious damage which would render
hanger assemblies unserviceable, the hanger assemblies shall
have an overhaul evaluation performed. Make an entry in
component record to show reason for removal was sudden
stoppage.
Chapter 66
b. Tail Rotor Driveshafts
NOTE
If one or more of conditions listed in step (a) through
step (d) are noted, all driveshaft and bearing hangers
shall be considered unserviceable and scrapped.
(1) Remove tail rotor driveshafts and inspect for
following conditions:
(a) Adapter flanges for distortion and cracks.
BHT-ALL-SPM
(b) Shafts for concentricity and distortion. Inspect
for crack(s) using fluorescent penetrant methods.
(c) Loose or sheared rivets.
Chapter 66
(d) Scratches in excess of limits.
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
NOTE
If driveshaft(s) or hanger assemblies are scrapped
as the result of step (a) or step (b), perform a
thorough inspection of hanger support structure for
cracks, loose, or missing rivets and elongated mount
holes.
Chapter 66
(2) If inspection reveals no condition as listed in
step (1), substep (a) through substep (d), then perform an
inspection. Make an entry in component record to show reason
for removal was sudden stoppage.
BHT-222-CR&O-3
c. Tail Rotor Hub and Blade Assembly
(1) If sudden stoppage originated at tail rotor blades,
the tail rotor hub and blade assembly shall be considered
unserviceable and nonrepairable.
BHT-222-CR&O-3
(2) If sudden stoppage originated at tail rotor
driveshaft or tail rotor gearbox, remove tail rotor hub and blade
assembly and perform overhaul evaluation inspection. Make an
entry in component record to show reason for removal was
sudden stoppage.
BHT-222-CR&O-3
d. Tail Rotor Gearbox
(1) Inspect torque on tail rotor gearbox retaining nuts
for 100 to 140 inch-pounds (11 to 16 Nm).
(2) Remove tail rotor gearbox. Check for cracks,
sheared or bent attaching studs, dowel pin, and evidence of
case distortion or output shaft distortion. If any of the above is
noted, the gearbox is unserviceable and shall be scrapped.
BHT-222-CR&O-3
(3) If inspection reveals no condition as listed in
step (2), perform conditional inspection and overhaul
evaluation. Make an entry in component record to show reason
for removal was sudden stoppage.
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ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-53.
SUDDEN STOPPAGE - POWER ON OR OFF (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
e. In all instances of step b and step c, perform the
following inspections:
(1) Tail rotor gearbox and vertical fin attachment
fittings for cracks, sheared rivets, or damaged connecting bolts.
(2) Boosted tail rotor flight controls from the hydraulic
actuator to the pitch change linkage for damage to tubes,
bellcranks, supports, fairleads, and bearings. Special attention
should be paid to the support, bellcranks, and links mounted on
the tail rotor gearbox.
(3) Tailboom structure for distortion, cracks, and loose
or missing rivets, especially at the tail rotor driveshaft hanger
support structure and at the tailboom to fuselage attachment
area.
BHT-222-CR&O-2
f. If damage to the tail rotor gearbox, tail rotor driveshafts,
or tail rotor driveshaft hanger assemblies is such that these
items are scrapped as unserviceable, remove transmission and
perform the following evaluation. Make an entry in component
record to show reason for removal was sudden stoppage.
BHT-222-CR&O-2
(1) Replace the collector gear.
BHT-222-CR&O-2
(2) lnspect collector gear shaft for excessive runout of
gear mounting flange. Runout of gear flange must not exceed
0.0004 inch (0.0101 mm) when gear shaft is mounted on
centers or on bearing journals. lnspect collector gear shaft using
magnetic particle method.
BHT-222-CR&O-2
(3) lnspect transmission lower case duplex bearing.
Replace bearing if rough or if any evidence of spalling or flaking
is evident.
BHT-222-CR&O-2
(4) lnspect center bearing case roller bearing. Replace
bearing if any evidence of brinelling, spalling, or flaking is
evident.
BHT-222-CR&O-2
(5) Perform an overhaul evaluation of the tail rotor
drive quill.
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ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-54.
OVERTORQUE
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
Overtorque is defined as any incident in which torsional loads
are introduced into the helicopter dynamic system in excess of
established limits. This can involve either an overtorque of mast
or engine.
Honeywell
Refer to the engine manufacturer’s manual for engine
101-650C/750C
overtorque limits and inspection requirements.
Series Operation and
Maintenance Manual,
LTS 101-2.2
1.
Model 222B - When main rotor overtorque has exceeded
105% but did not exceed 115%, perform the following:
Model 222 - When main rotor overtorque has exceeded 110%
but not more than 120%, perform the following:
a. Conduct a thorough visual inspection of the assemblies
that follow (installed on the helicopter) for any evidence of
damage, deformation, yielding, etc.
(1) Main rotor hub and blades
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-54.
OVERTORQUE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
NOTE
Cadmium plating on outside diameter of mast is
0.0003 to 0.0004 inch (0.0076 to 0.0102 mm). When
measuring mast outside diameter at six places for
out-of-round, ensure that 0.0003 to 0.0004 inch
(0.0076 to 0.0102 mm) differential is considered
when measuring plated surfaces or when plating
may have been removed.
(2) Main rotor mast. Using a suitable micrometer,
measure mast outside diameter at the minimum of six places for
out-of-round condition; two measurements 90° to each other
between the swashplate and drive hub assembly; two
measurements 90° to each other just above the collective
friction collet assembly, and two measurements 90° to each
other approximately 2 inches (51 mm) below the static stop
contact area on the mast. If any set of opposing measurements
vary in excess of 0.002 inch (0.051 mm), the mast is suspected
of bending and a runout inspection must be performed.
(3)
Start engine and check main rotor, while in a flat
pitch condition, for any evidence of a 1/rev vibration. If one or
more of the previous inspection requirements of step (1) or
step (2) reveals an unsatisfactory condition, a mast runout
inspection must be performed. If unsatisfactory conditions are
not found, the mast runout inspection is not required.
(4) Lift link upper and lower attachment fittings
(5) Nodal beam mounts, attachment fittings, and travel
stops
(6) Transmission restraints and restraint fittings
(7) Transmission top case
(8) lnspect main driveshaft couplings for indications of
overheating
(9) Tail rotor hub, blades, and attachments
(10) Swashplate and lever assembly
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-54.
OVERTORQUE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(11) Drive assembly
b. lnspect main transmission chip detectors and external
oil filter for metal particles.
(1) If chip detectors and external filter appear normal
and there is no evidence of internal failure, operate the
transmission for 5 hours, then check chip detectors and external
filter. If chip detector and filter inspection does not reveal metal
particles, the transmission is satisfactory for service.
(2) If metal particles indicating internal failure are
found or if there is any evidence of internal failure, remove and
overhaul the transmission. Make entry in component record to
show reason for removal was overtorque. Clean all
transmission system oil lines and replace oil coolers.
c. After the next
25 hours, following an overtorque,
conduct a thorough inspection of the following:
(1) Main rotor hub assembly
(2) Main rotor mast
(3) Transmission top case
(4) Transmission mount (nodal beam) link assemblies,
link attachments, and arm and support assemblies
(5) Cabin roof and beam at transmission mount (nodal
beam) attachment points
(6) Transmission restraint attachment at stop mounts,
support, and cabin roof shell, and beam
(7) Transmission electric chip detectors
(8) Tail rotor hub, blades, and attachments
(9) Swashplate and lever assembly
(10) Drive assembly
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-54.
OVERTORQUE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
2.
When main rotor overtorque exceeds 120% for Model 222
(115% for Model 222B), perform the following:
BHT-222-CR&O-2
a. Conduct a major overhaul on the following components.
BHT-222-CR&O-3
Make an entry in component record to show reason for removal
was overtorque.
(1) Main rotor hub
(2) Mast assembly
NOTE
During overhaul of the main transmission, inspect
gear patterns for scoring and top case for yielding.
(3) Transmission assembly
(4) Tail rotor hub
Chapter 65
(5) Inspect the main rotor blades. Pay particular
BHT-222-CR&O-2
attention to blade skins for distortion or debonding.
b. Perform a thorough visual inspection of the following
components. If no visual damage is found, the components may
be retained in service.
(1) Swashplate and lever assembly
(2) Drive assembly
(3) Main rotor and tail rotor blades
(a) Do a visual and tap inspection.
(b) If the blade shows sign of bond separation,
scrap the blade.
(c) If the tip or root end balance weights have
moved, scrap the blade.
(d) If the retention bushings are loose, scrap the
blade.
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-54.
OVERTORQUE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(e) If the skin on any blade is wrinkled or
deformed, scrap all blades.
(f)
If the tip block shows evidence of movement
or is loose, scrap the blade.
(g) If the blades pass the inspection in step (a)
through step (f), the blade can be returned to service.
c. After the next 25 hours following an overtorque, conduct
a thorough inspection of the following:
(1) Main rotor hub and blades
(2) Transmission mount fittings, upper and lower
attachment points
(3) Cabin roof at transmission mount fittings
(4) Transmission restraint attachments
(5) Transmission electric chip detectors
(6) Tail rotor hub, blades, and attachments
(7) Swashplate and lever assembly
(8) Drive assembly
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ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-55.
OVERTORQUE - ONE ENGINE INOPERATIVE
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
1.
Model 222 - When a One Engine Inoperative (OEI)
operation occurs in which engine torque has exceeded 87%, but
did not exceed 103%, perform the following:
Model 222B - When a One Engine Inoperative (OEI) operation
occurs in which engine torque has exceeded 86.4%, but did not
exceed 103%, perform the following:
a. Record duration and maximum engine torque in main
transmission maintenance record.
Honeywell
b. Refer to the engine manufacturer’s manuals for engine
101-650C/750C
overtorque inspection requirements if engine torque exceeded
Series Operation and
100%.
Maintenance Manual,
LTS 101-2.2
c. If engine torque exceeded
100%, inspect main
transmission chip detectors and external filter for metal
particles.
(1) If chip detectors and external filter appear normal
and there is no evidence of internal failure, the transmission is
satisfactory for service. No other component inspections are
required.
(2) If metal particles indicating internal failure are
found, remove the transmission for overhaul inspection. Make
entry in component record that reason for removal was OEI
overtorque operation. Clean all transmission system oil lines
and replace oil coolers.
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-55.
OVERTORQUE - ONE ENGINE INOPERATIVE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
d. Three OEI operations which exceed 87% (86.4% for
Model 222B), but do not exceed 103% engine torque are
permissible within the rated life of the collector gears
222-040-109-003 and -103 and -105 in Models 222 and 222B
respectively. After a third OEI occurrence, the collector gear
must be removed from service and scrapped.
2.
When an OEI operation occurs in which engine torque has
exceeded 103%, perform the following:
a. Record duration and maximum engine torque in main
transmission maintenance record.
Honeywell
b. Refer to the engine manufacturer’s manuals for engine
101-650C/750C
overtorque inspection requirements.
Series Operation and
Maintenance Manual,
LTS 101-2.2
BHT-222-CR&O-2
c. Perform overhaul of main transmission. Make entry in
component record that reason for removal was OEI overtorque
operation.
(1) The collector gear 222-040-109 shall be scrapped
at this overhaul.
(2) During overhaul of the main transmission, inspect
gear patterns for scoring.
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Rev. 7
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ECCN EAR99
BHT-222/222B-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:_______________________________________
When the helicopter has had a lightning strike, the following
precautions shall be followed:
NOTE
In all instances that follow, if significant damage has
been found in any area, inspection shall be
expanded in those areas until it extends beyond the
zone of damage.
1.
Visually inspect all external surfaces of the helicopter with
particular attention to main rotor blades and hub, the
transmission and mast assembly, tail rotor blades and hub, tail
rotor gearbox, horizontal stabilizer auxiliary fins, and vertical fin.
Check electrical instruments and systems.
2.
If visual indications of damage are present, proceed as
follows:
a. lnspect main rotor blades. If blades show any of the
following indications, scrap blades.
(1) lnspect blades for signs of burns. Burn marks can
be very minute.
(2) lnspect entire surface of all blades for voids and
delamination.
b. Remove main rotor hub for overhaul. State lightning
strike as reason for removal.
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-56.
LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
c. Remove transmission and mast assembly for overhaul
making note of lightning strike as reason for removal.
d. Remove tail rotor hub for overhaul. State lightning strike
as reason for removal. Scrap blades if indications of burns or
debonding are evident.
e. Remove tail rotor driveshaft bearing hangers and tail
rotor gearbox and return for overhaul, stating lightning strike as
reason for removal.
f. Check auxiliary fins for evidence of burning or
debonding.
g. Inspect tailboom fitting for indication of arcing burns
around mounting points of tail rotor gearbox and vertical fin.
3.
If no visual indications or damage is found:
BHT-222-CR&O-2
a. Remove main rotor hub grips.
(1) Visually inspect bearings for signs of electrical
arcing, burning, or delamination.
(2) Visually check pitch change links at the drive
assembly connections for arcing burns.
BHT-222-CR&O-2
(3) If indications of arcing or burning are present,
overhaul main rotor hub and drive assembly and replace the
affected pitch change link, including all attaching hardware.
BHT-222-CR&O-2
(4) If no indications are found, assemble main rotor
hub.
b. Remove main rotor mast assembly. Without removal of
the bearing from the 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.
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-56.
LIGHTNING STRIKE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(1) If indications of arcing, burning, or roughness of
the bearing are present, remove transmission and mast
assembly and return for overhaul. State lightning strike as
reason for removal.
(2) If no indications are found, assemble transmission
and mast assembly and return to limited service. After 5 hours,
remove the chip detectors and filter and inspect for chips. If no
indications are found, return transmission to full service. If
indications are found, remove transmission and mast assembly
and return it for overhaul. State lightning strike as reason for
removal. Clean all transmission oil lines. Replace oil cooler.
BHT-222-CR&O-3
c. Remove output 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, stating lightning strike as reason for removal.
BHT-222-CR&O-3
(2) If no indications of damage are found, and if
bearings rotate smoothly, assemble gearbox and return it to
limited service. After 5 hours, remove chip detector and inspect
for chips. If no indications are found, return gearbox to full
service. If indications are found, return gearbox for overhaul,
stating lightning strike as reason for removal.
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ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-57.
OVERSPEED
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
Honeywell
Rotor overspeed is defined as any incident in which 109% main
101-650C/750C
rotor speed is exceeded. Refer to engine manufacturer’s
Series Operation and
manual for engine overspeed limits and inspection requirement.
Maintenance Manual,
LTS 101-2.2
1.
If main rotor overspeed exceeds 109%, but not more than
113%, perform a thorough visual inspection of the following
components. If no damage is found, no further inspection is
required.
a. Main rotor hub and blades
b. Swashplate and lever assembly
c. Drive assembly
d. Tail rotor driveshafts and hanger assemblies
e. Tail rotor gearbox assembly
f. Tail rotor hub assembly
g. Tail rotor blades
(1) Perform visual and tap inspection.
(2) If bond separation on the blade exists anywhere,
scrap the blade.
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-57.
OVERSPEED (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
(3) If any movement of the tip or root end balance
weights has occurred, scrap the blade.
(4) If the retention bushings show evidence of
looseness, scrap the blade.
(5) If skin of either blade is wrinkled or deformed,
scrap both blades.
(6) If blade tip block shows evidence of movement or
is loose, scrap the tail rotor blade.
(7) If
blades pass the previous inspection
requirements and no other discrepancies exist, the blades are
acceptable for service.
h. Tail rotor controls
i. Main transmission
j. Main driveshaft
2.
Perform the following inspection if main rotor overspeed
exceeds 113%, but not more than 120%:
a. Remove and perform a thorough visual inspection as
listed in step 1.
b. Verify torque of tail rotor gearbox attachment studs.
3.
Perform the following inspections if main rotor overspeed
exceeds 120%. Remove and perform overhaul inspection on
the following components. Note overspeed as reason for
removal.
a. Main rotor hub and blades
b. Main rotor mast
c. Main transmission
d. Main driveshafts
e. Swashplate and lever assembly
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-57.
OVERSPEED (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
f. Drive assembly
g. Tail rotor driveshafts
h. Tail rotor driveshaft hanger assemblies
i. Tail rotor gearbox
j. Tail rotor hub and blades
k. Tail rotor controls
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ECCN EAR99
BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-58.
COMPRESSOR STALL OR SURGE
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
Engine compressor stall or surge is characterized by a sharp
rumble or a series of loud sharp reports, severe engine
vibration, and a rapid rise in measured gas temperature (MGT),
depending on severity of surge. When a surge has been
reported, progressively perform step 1 through step 6, as
dictated by discrepant condition.
Compressor stall may cause severe torsional loading of the
main driveshaft resulting in scoring of the transmission input
quill gears and damage to the main driveshaft, and distortion or
damage to the tail rotor gearbox attachment fitting.
1.
Power Plant
a. Examine inlet FOD screen or particle separator for
blockage.
b. Inspect leading edges and tip areas of compressor rotor
impeller for accumulation of dirt, evidence of severe erosion, or
foreign object damage.
Honeywell
(1) If contaminants are found, clean and perform a
101-650C/750C
power check.
Series Operation and
Maintenance Manual,
LTS 101-2.2
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BHT-222/222B-MM-1
CONDITIONAL INSPECTIONS
5-58.
COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH
OTHER
Honeywell
(2) If erosion or foreign object damage appears to
101-650C/750C
exceed acceptable limits, perform a teardown inspection.
Series Operation and
Maintenance Manual,
LTS 101-2.2
Honeywell
c. If compressor stall or surge occurred during
101-650C/750C
acceleration, refer to engine manufacturer’s manual for
Series Operation and
troubleshooting procedures.
Maintenance Manual,
LTS 101-2.2
Honeywell
d. If step a through step c do not reveal cause of surge,
101-650C/750C
inspect turbine assembly.
Series Operation and
Maintenance Manual,
LTS 101-2.2
2.
Power Train
a. If compressor stall occurs below 59% main rotor mast
torque, comply with the following:
(1) Remove
magnetic
chip
detectors
from
transmission and tail rotor gearbox, and inspect for metal
particles.
(2) If no indication of metal particles is found on chip
detectors, clean chip detectors and reinstall. Return helicopter
to limited flight status and repeat chip detector inspection in 5 to
10 hours. If positive indication of metal chips is found on chip
detectors on initial or 5 to 10 hour inspection, return unit for
overhaul, noting the reason.
b. If compressor stall occurs at 62% (59% for Model 222B)
mast torque or above, comply with the following:
(1) Remove
magnetic
chip
detectors
from
transmission and tail rotor gearbox, and inspect for metal
particles. If no indication of metal particles is found on chip
detectors, clean chip detectors and reinstall. If positive
indication of metal chips is found on chip detectors, return unit
for overhaul, noting the reason. Clean all affected oil lines and
replace oil coolers.
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ECCN EAR99
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