|
|
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-54.
AFTER ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
(4) Remove inboard and outboard drag brace bolts.
Check bolts for deformation and perform magnetic particle
inspection. If satisfactory, return to service.
(5) Visually inspect stabilizer bar outer tubes for
bending. (Allowable deflection is 0.150 inch (3.81mm) in each
tube.)
(6) Remove main rotor pillow blocks from main rotor
yoke and check for deformation of bushings and bushing holes
in pillow blocks and yoke.
(7) Perform close visual inspection of all other main
rotor components.
BHT-212-CR&O
(8) If any discrepancies are noted as a result of
inspection in step (4) through step (7), remove and replace
main rotor hub and blade assembly, stabilizer bar assembly, and
mast assembly. Removed assemblies shall have an overhaul
evaluation performed. Make an entry in component records to
show reason for removal was compressor stall.
3.
Airframe.
a. Check tailboom fin for evidence of damaged skin panels
and/or structure and rivets for looseness and/or sheared heads.
If inspection shows no indication of damage, return helicopter to
flight status. If positive evidence of damage is found, comply
with step b through step e.
b. Remove skin from tailboom fin adjacent to tail rotor
gearbox mounting. Inspect all support structures in this area
and repair as required. Install new skin.
c. Make close visual inspection of complete tailboom
structure for distortion, buckles, skin cracks, and sheared or
loose rivets, paying particular attention to tailboom attachment
points at FS 241.43 to 243.9 and adjacent fuselage to tailboom
structure and intermediate gearbox support structure.
d. Make close visual inspection of main pylon support and
engine mount attachment structure for distortion, buckles,
cracks, sheared, or loose rivets, etc.
5-00-00
Page 216
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-54.
AFTER ENGINE COMPRESSOR STALL OR SURGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
e. If discrepancies found during inspection in step b
through step d cannot be repaired by standard procedures,
replace discrepant assembly.
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 217/218
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
NOTE
Accomplish inspection after lightning strikes.
AFTER LIGHTNING STRIKES
NOTE
In all instances in the following inspections, if
significant damage has been found in any area,
inspection shall be expanded in those areas until it
extends beyond zone of damage. Any damage found
anywhere on helicopter shall be recorded in detail
and copies of these records shall be provided along
with any component returned for overhaul to assist
overhauling facility in evaluating component.
When helicopter is suspected of receiving a lightning
strike, the following precautions shall be followed:
1.
Visually inspect all external surfaces with particular
attention to main rotor blades and hub, transmission and mast
assembly, tail rotor blades and hub, tail rotor gearbox, and
vertical fin. Check electrical instruments and systems. Verify
magnetic compass accuracy.
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 219
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
2.
If visual indications of damage are present, proceed as
follows:
a. Remove main rotor blades and visually inspect. If
blades show any of the following indications, scrap blades.
(1) Inspect blades for signs of burns. Burn marks can
be very minute.
(2) Inspect blades for debond in all bonded areas.
b. Remove main rotor hub and forward to an overhaul
facility for overhaul. Tag hub stating lightning strike as reason for
removal. Inspect main rotor hub and rotating controls for
indication of arcing or burning.
c. Remove main driveshaft for inspection.
BHT-212-CR&O
(1) Disassemble to the same extent required for
coupling. Repack and clean couplings.
(2) Visually inspect couplings for any evidence of arc
burning or pitting. Pay special attention to tips, roots, and
profiles of male and female coupling teeth. Any evidence of arc
burning or pitting is cause for rejection.
d. Remove tail rotor output coupling for inspection.
BHT-212-CR&O
(1) Disassemble to same extent required for coupling.
Repack and clean couplings.
(2) Visually inspect couplings for any evidence of arc
burning or pitting. Pay special attention to the tips, roots, and
profiles of male and female coupling teeth. Any evidence of arc
burning or pitting is cause for rejection.
5-00-00
Page 220
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
e. If main rotor blades, main rotor hub, main driveshafts, or
tail rotor output coupling exhibit evidence of damage that can be
attributed to a lightning strike, remove transmission and mast
assembly for overhaul. Tag components stating lightning strike
as reason for removal. If no evidence of damage is noted on
above mentioned components, partially remove and inspect
main transmission as follows:
Chapter 63
(1) Remove and inspect all transmission chip
detectors.
(2) If any evidence of arc burning or pitting is noted, or
excessive debris is found, remove transmission and mast
assembly for overhaul. Tag components stating lightning strike
as reason for removal.
Chapter 63
(3) If no evidence of arc burning or pitting is noted,
ground run light on skids for 1 hour. Reinspect chip detectors
and remove and inspect oil filter. Repeat these inspections after
accumulating 5 flight hours but prior to 10 flight hours.
f. Inspect tail rotor blades and hub. Scrap blades if
indications of burns or debonding are present. Remove tail rotor
hub for overhaul. Tag hub stating lightning strike as reason for
removal.
Chapter 65
g. Remove and inspect tail rotor gearbox chip detector
and intermediate gearbox chip detector.
h. If the tail rotor blades, tail rotor hub, or tail rotor output
coupling exhibit evidence of damage, which can be attributed to
a lightning strike, or excessive debris is found on chip detectors,
remove tail rotor gearbox, intermediate gearbox and tail rotor
driveshaft hangers for overhaul. Tag components stating
lightning strike as reason for removal. Additionally, the tail rotor
driveshaft tubes, disc pack couplings, and attaching hardware
shall be visually inspected for evidence of arc burns or pitting.
Any evidence of arc burns or pitting is cause for rejection.
i. If no evidence of arc burns or pitting is noted, operate
helicopter light on skids for 1 hour. Reinspect chip detector.
Repeat this inspection after accumulating 5 flight hours but prior
to 10 flight hours.
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 221
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
3.
If no visual indications of damage are present, proceed as
follows:
Chapter 63
a. Remove and inspect all transmission chip detectors.
(1) If excessive debris is found on chip detectors,
remove transmission and mast assembly for overhaul.
Chapter 63
(2) If little or no debris is found, operate helicopter light
BHT-212-CR&O
on skids for 1 hour. Reinspect chip detectors and remove and
inspect oil filter. Repeat these inspections after accumulating 5
flight hours but prior to 10 flight hours.
BHT-212-CR&O
b. Remove main rotor hub grips.
(1) Visually inspect bearings for signs of electrical
arcing, burning, or delamination.
(2) Visually inspect pitch change links at drive
assembly connections for arcing burns.
(3) If indications of arcing or burning are present,
overhaul main rotor hub and drive assembly. Replace affected
pitch change link, including attaching hardware.
(4) If no indications are found, reassemble main rotor
hub.
4.
Prior to first flight after a suspected or confirmed lightning
strike, verify proper function of all drive system component chip
detectors as follows:
a. Remove electrical connector from chip detector.
b. Remove chip detector and reinstall connector.
c. With helicopter electrical power on, bridge chip detector
gap with a clean conductive object (screwdriver).
d. Verify proper indication on the CHIP indicator panel and
caution panel. Verify illumination of MASTER CAUTION light.
e. Using a single strand of steel wool to bridge gap of one
chip detector, verify proper function of chip burn off system.
5-00-00
Page 222
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
f. Make repairs as required.
5.
When established that lightning has struck helicopter,
inspections of electrical and instrument systems that follow are
mandatory to ensure safety of flight.
a. Inspect all electrical wiring, bundles, and connectors for
burning or electrical arcing. Unplug all connectors and inspect
pins and housing for electrical arcing or burning. Inspect interior
of all circuit breaker panels for burning or electrical arcing.
Replace any wires, connectors, or circuit breakers found to be
damaged.
b. inspect main rotor blade and control links, transmission
system, driveshafts, gearboxes, and tailboom structure for
magnetization. Using a magnetometer with a range no larger
than
±5 gauss, place arrow or red dot (depending on
magnetometer model) within 0.5 inch (12.7 mm) of item being
checked, and point it directly at item. If any items or components
have a reading greater than 1 gauss, those items shall be
degaussed.
NOTE
Do not test chip detectors for magnetization. If
transmission or gearbox magnetic readings are
greater than 1 gauss near chip detector, remove chip
detector from housing and repeat test.
c. Remove and bench test voltage regulator(s).
Operationally check DC generator, starter generator, and
inverter(s) for proper operation. Visually inspect generator,
starter generator, and inverter(s) for burns or electrical arcing. If
damaged, remove for internal inspection and bench test.
d. Perform operational check of bussing system.
e. Inspect transmission and tail rotor gearbox chip
detectors for proper operation. Remove chip detectors found
inoperative.
f. Perform operational check of interior and exterior
lighting system. Replace lamps, bulbs, and lighting assemblies
as required.
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 223
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
g. Perform operational check on all instruments. Remove
and repair/replace instruments and sensor found to be
defective.
h. Perform operational check on all caution messages for
proper operation.
6.
When it has been established that lightning has struck the
helicopter, the inspections of structure that follow are mandatory
to ensure safety of flight:
NOTE
Arcing damage on metal components of airframe
structure, when cleaned out to twice its visible depth,
shall be treated as mechanical damage. Damage
limits establish repairability and/or scrapping of
component. Any other structural damage, tears,
voids, rupture, etc., directly or indirectly related to
lightning strike, shall also be treated as mechanical
damage.
a. Check sandwich panels in suspect areas for voids or
debond. If damage is apparent, proceed with normal
maintenance procedures.
b. Check fixed controls and support system components
for possible arcing damage. Bearings in rod ends, bellcranks,
and supports should be most susceptible to arcing damage.
Check bearings for smooth rotation. Visibly inspect attaching
hardware of support for signs of lightning damage, damaged
finish and/or burns. If damage is evident, remove supports and
inspect mounting holes and mating surfaces for arcing damage.
Arcing damages shall be blended out to twice its visible depth,
and repaired damages shall not exceed mechanical damage
limits.
Chapter 32
c. When apparent lightning has grounded through skid
landing gear, remove entire landing gear assembly and inspect
crosstubes and airframe support fittings for possible arcing
damage. Specifically, inspect attaching holes and mating
surfaces of the crosstubes directly beneath landing gear
bearing/retaining supports. Clean out arcing damage to twice its
visible depth. The damage, after cleanup, shall not exceed
allowable mechanical damage limits.
5-00-00
Page 224
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-55.
AFTER LIGHTNING STRIKES (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
d. Any airframe metal parts not specifically identified
above, but are suspect, shall be noted in maintenance log and
shall be reinspected prior to next 100 hours of flight.
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 225/226
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-56.
AFTER ENGINE COMBINING GEARBOX CLUTCH NONENGAGEMENT,
MISENGAGEMENT, OR IN-FLIGHT SLIPPAGE
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
DATE:
__________________
W.O.
_____________________
FACILITY:
_________________________________________
HELICOPTER S/N:
__________________________________
REGISTRY NO.:
____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:_______________________________________
NOTE
Accomplish inspection after engine combining
gearbox clutch nonengagement, misengagement, or
in-flight slippage.
AFTER ENGINE COMBINING GEARBOX CLUTCH
NONENGAGEMENT, MISENGAGEMENT, IN-FLIGHT
SLIPPAGE
NOTE
A nonengaged engine is indicated by near zero
torque, higher N2, and much cooler ITT as compared
to engaged engine.
- Inspect
1.
Nonengagement.
Pratt & Whitney
Perform inspection in accordance with Pratt & Whitney Canada
Canada PT6T-3/-3B
PT6T-3/-3B Maintenance Manual.
Maintenance Manual
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 227
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-56.
AFTER ENGINE COMBINING GEARBOX CLUTCH NONENGAGEMENT,
MISENGAGEMENT, OR IN-FLIGHT SLIPPAGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
2.
Misengagement.
NOTE
If a sprag clutch has failed to engage, and/or
subsequently engages with or without audible or
physical (helicopter jolt) indications, proceed as
follows:
Pratt & Whitney
a. Combining gearbox shall be removed and inspected in
Canada PT6T-3/-3B
accordance with Pratt & Whitney Canada PT6T-3/-3B
Maintenance Manual
Maintenance Manual.
b. Inspect transmission spiral bevel gear as follows:
SI 212-6 and
(1) Gain access to left side of transmission and
Chapter 63
remove rotor brake and quill assembly.
(2) Utilizing rotor brake quill port opening, inspect all
62 teeth of main spiral bevel gear convex side for unsatisfactory
conditions such as scoring, hard lines, nicks, dents, chipping,
metal deformation, etc. Inspect all 62 teeth on spiral bevel gear
concave side. Refer to Figure 5-6 for unacceptable conditions of
spiral bevel gear.
NOTE
Inspection mirrors and a suitable light are required.
Turn rotor slowly to permit inspection of all gear
teeth.
SI 212-6 and
(3) Remove and replace any gear that does not meet
BHT-212-CR&O
inspection requirements set forth in step (2). Overhaul rotor
brake quill.
5-00-00
Page 228
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-56.
AFTER ENGINE COMBINING GEARBOX CLUTCH NONENGAGEMENT,
MISENGAGEMENT, OR IN-FLIGHT SLIPPAGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
NOTE
Components removed from a helicopter for
evaluation following combining gearbox clutch
nonengagement, misengagement, or in-flight
slippage shall be evaluated as an interrelated group.
Removal records accompanying each component
shall cross-reference part and serial numbers of
other drive system components removed for
evaluation.
SI 212-6 and
(4) Install rotor brake and quill.
Chapter 63
(5) Install cowling and inspection panels.
(6) Perform a 15 minute ground run to determine if
any oil leaks are present at rotor brake quill assembly.
c. Perform inspection in accordance with compressor stall
or surge inspection (paragraph 5-52), except drive train shall be
inspected as follows:
(1) Visually inspect main rotor mast and controls for
damage. If signs of yielding are evident, transmission and mast
assembly and any other damaged components shall be
replaced.
(2) Visually inspect tail rotor driveshaft for damage.
BHT-212-CR&O
(3) Remove output quill from tail rotor gearbox and
inspect both sides of gear teeth for scoring, scuffing, or other
damage or marks indicating excessive load.
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 229
BHT-212-MM-1
CONDITIONAL INSPECTIONS
5-56.
AFTER ENGINE COMBINING GEARBOX CLUTCH NONENGAGEMENT,
MISENGAGEMENT, OR IN-FLIGHT SLIPPAGE (CONT)
INITIAL
DATA REFERENCE
INSPECTION TASK DESCRIPTION
MECH OTHER
NOTE
If a tail rotor driveshaft has failed or yielded, all tail
rotor driveshafts, hanger assemblies, intermediate
gearbox, and tail rotor gearbox shall be replaced,
and tail rotor drive quill in transmission shall be
removed and inspected for damage in accordance
with the compressor stall inspection (paragraph
5-46). If scoring, scuffing, or other damage or marks
indicate excessive load are found in intermediate
gearbox or tail rotor gearbox, but tail rotor driveshafts
are serviceable, gearbox(es) that are not serviceable
shall be replaced.
3.
In-flight clutch slippage.
NOTE
If clutch slippage is confirmed or suspected, proceed
as follows:
Pratt & Whitney
a. Combining gearbox shall be removed and inspected in
Canada PT6T-3/-3B
accordance with Pratt & Whitney Canada PT6T-3/-3B
Maintenance Manual
Maintenance Manual.
b. Inspect spiral bevel gear in accordance with
misengagement inspection step b, substep (2). If spiral bevel
gear is damaged, perform misengagement inspection given in
step c.
5-00-00
Page 230
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
COMPONENT OVERHAUL SCHEDULE
5-57.
COMPONENT OVERHAUL SCHEDULE
CAUTION
The Component Overhaul Schedule (Table 5-1)
provides the time interval between overhaul for each
applicable helicopter component.
OVERHAUL SCHEDULE FOR SOME KIT
COMPONENTS AND/OR PARTS IS NOT
COVERED IN THIS SCHEDULE. REFER
WARNING
TO
APPLICABLE
SERVICE
INSTRUCTIONS FOR KIT COMPONENTS
SCHEDULE.
DO NOT APPLY TOLERANCES TO
PARTS
WITH
A
LIMITED
NOTE
AIRWORTHINESS LIFE (CHAPTER 4).
Refer to paragraph 5-1 for information on
inspection and overhaul tolerance.
WARNING
NOTE
Neither assignment of a time period for
DO NOT EXCEED RETIREMENT LIFE
overhaul of a component or failure to
FOR CRITICAL COMPONENTS. REFER
assign a time period for overhaul of a
TO AIRWORTHINESS LIMITATIONS
component constitutes a warranty of any
SCHEDULE (CHAPTER 4).
kind. The only warranty applicable to
helicopter and any component is that
SOME PARTS INSTALLED AS ORIGINAL
warranty included in the Purchase
EQUIPMENT
ON
MILITARY
Agreement for the helicopter or component.
HELICOPTERS MAY HAVE A LOWER
AIRWORTHINESS LIFE AND/OR
The overhaul interval specified for any given part
OVERHAUL SCHEDULE THAN WHEN
number contained in this Component Overhaul
USED
ON A
COMMERCIAL
Schedule applies to all successive dash numbers (or
HELICOPTER. CONSEQUENTLY, PARTS
suffixes) for that item unless otherwise specified.
THAT HAVE BEEN USED ON MILITARY
HELICOPTERS SHOULD NOT BE USED
Refer to Pratt & Whitney Canada PT6T-3/-3B bulletins
ON COMMERCIAL HELICOPTERS.
for engine and related component overhaul intervals.
Table 5-1. Component Overhaul Schedule
OVERHAUL INTERVAL
NOMENCLATURE
PART NUMBER
1
(HOURS)
ROTORS
Stabilizer Bar Assembly
204-011-326-013
2
1000 hours/
On-condition
Swashplate and Support
204-011-400-017
On-condition
Assembly
5-00-00
Export Classification C, ECCN EAR99
26 JUN 2013 Rev. 14
Page 231
BHT-212-MM-1
Table 5-1. Component Overhaul Schedule (Cont)
OVERHAUL INTERVAL
NOMENCLATURE
PART NUMBER
1
(HOURS)
ROTORS (CONT)
Scissors and Sleeve
204-011-401-019
On-condition
Assembly
Main Rotor Hub Assembly
204-012-101-009
2400 hours
Main Rotor Hub Assembly
212-510-001-103
9
2400 hours
Tail Rotor Hub Assembly
212-010-701-001
1000 hours
Tail Rotor Hub Assembly
212-011-701-001
2500 hours
Tail Rotor Installation
209-011-700-003
3
Tail Rotor Installation
212-011-700-001
3
POWER TRAIN
Rotor Brake Quill
412-040-123-101
3000 hours
Transmission
212-040-001-115, -119, -123,
4
1000 hours
and -127
Transmission
212-040-001-131
4
1500 hours
Transmission
212-040-001-059, -137, and Subsequent
6000 hours
4
5
Transmission
212-540-002-103
6000 hours
4
5
9
Quill Assembly, Auxiliary
212-040-703-105
10
1000 hours
Equipment
Intermediate Gearbox
212-040-003-007
3000 hours
Assembly
Intermediate Gearbox
212-040-003-023
5000 hours
Assembly
Intermediate Gearbox
212-540-001-105
5000 hours
9
Assembly
Tail Rotor Gearbox Assembly
212-040-004-005
3000 hours
Tail Rotor Gearbox Assembly
212-040-004-009
5000 hours
Tail Rotor Gearbox Assembly
212-540-001-107
9
5000 hours
5-00-00
Page 232
Rev. 14
26 JUN 2013
Export Classification C, ECCN EAR99
BHT-212-MM-1
Table 5-1. Component Overhaul Schedule (Cont)
OVERHAUL INTERVAL
NOMENCLATURE
PART NUMBER
1
(HOURS)
POWER TRAIN (CONT)
Engine to Transmission
212-040-005-003
1000 hours
(Main) Driveshaft
Engine to Transmission
212-040-005-007
3000 hours
(Main) Driveshaft
Mast Assembly with
204-040-366-015
1000 hours
204-040-136-009 Bearing
Mast Assembly with
2500 hours
212-040-136-001 Bearing
Mast Assembly
204-040-366-017
2500 hours
Mast Assembly
204-040-366-021
6
5000 hours
Mast Assembly
212-540-002-105
6
9
5000 hours
Tail Rotor Driveshaft Hanger
212-040-600-001
3000 hours
Assembly
Tail Rotor Hub Assembly
212-011-701-125
3
2500 hours
HYDRAULIC
Cylinder Assembly
212-076-004-003
1000 hours/
7
(Servo Actuator)
On-condition
Cylinder Assembly
212-076-004-005
On-condition
(Servo Actuator)
Cylinder Assembly
212-076-005-007
2500 hours
(Flight Control)
POWER PLANT
Engine Combining
PT6T3/-3B
8
3500 hours
(Reduction) Gearbox
Starter Generator
209-060-221-001
1000 hours
Starter Generator
200SG119Q
1000 hours
Fire Extinguisher Container
209-062-908-001
11
5 years
5-00-00
Export Classification C, ECCN EAR99
15 JUL 2021 Rev. 19
Page 233
BHT-212-MM-1
Table 5-1. Component Overhaul Schedule (Cont)
NOTES:
Operating time specified for overhaul of any given part number in this schedule applies to all successive
1
dash numbers (or suffixes), unless otherwise specified.
If tube assemblies 212-010-311-ALL or 540-011-319-001 are installed on stabilizer bar assembly
2
204-011-326, overhaul interval is conditional.
Overhaul the following items every 2500 hours of operation:
3
a. Idler assembly 209-011-711-ALL
b. Lever assembly 209-011-712-ALL
c. Nut 212-010-706-ALL
d. Crosshead 212-010-707-ALL or 212-010-775-ALL
e. Link assembly 209-011-713-ALL
4
Overhaul schedule of transmission quills is same as transmission in which quills are installed, with
exception of rotor brake quill.
5
Special inspection is required at 3000 hours, and overhaul is 6000 hours.
6
Special inspection is required at 3000 hours and overhaul is 5000 hours. If mast assembly
204-040-366-021 is installed in transmission 212-040-001-115, -123, and -131, mast assembly TBO is
2500 hours.
If cylinders have Greene, Tweed type seals installed, overhaul is conditional. Cylinders with assembly
7
date of April 30, 1974 or later were fitted with Greene, Tweed type seals at manufacturer. However,
cylinders without Greene, Tweed type seals shall be overhauled at 1000 hours.
8
Engine combining gearboxes that have incorporated the preceding referenced Pratt & Whitney Canada
Service Bulletin numbers 5119, 5177, 5185, 5186, 5198, and 5199 are increased to 4000 hours TBO.
9
Refer to TB 212-91-138.
10
Refer to BHT-212-SI-87 for maintenance information.
11
Hydrostatic test in accordance with specification DOT-4 DA, DOT-4 DS700, or DOT-SP-7945, as
marked on the reservoir, every 5 years or prior to refill after leakage or discharge. Extensions to this item
are not permitted.
5-00-00
Page 234
Rev. 15
29 NOV 2013
Export Classification C, ECCN 9E991
|