Helicopter Bell-212. MAINTENANCE MANUAL (2021)

BHT-212-MM-1

SPECIAL INSPECTIONS

5-38.

EACH 600 HOURS OF TRANSMISSION OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each

600 hours inspection of

transmission operation.

TRANSMISSION ASSEMBLY 212-040-001-115, -119, -123,

AND -127

- Inspect

Remove input pinion quill assembly and No. 2 hydraulic

pump drive quill from transmission main case. Dimensionally

inspect input pinion quill bore diameter of main case for

out-of-round condition. Input quill bore shall be 6.7521 inches

(171.5033 mm) and maximum out-of-round condition (maximum

diameter - minimum diameter) shall be 0.0030 inch (0.0762

mm). Replace case assembly if bore diameter exceeds

maximum conditions. Dimensionally inspect No. 2 hydraulic

pump quill bore of main case assembly for out-of-round

condition. Hydraulic drive quill bore maximum diameter shall be

5.0021 inches

(127.05 mm) and maximum out-of-round

condition shall be 0.0030 inch (0.0762 mm). Replace case

assembly if bore diameter exceeds maximum conditions.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-38.

EACH 600 HOURS OF TRANSMISSION OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Disassemble input pinion quill assembly sufficiently to

ascertain whether triplex ball bearing outer races have rotated

in sleeve. Note if etched V markings are still aligned. If bearing

outer races have rotated, complete the disassembly of quill.

Dimensionally inspect sleeve bore. If dimension is 5.51 inches

(139.95 mm) or greater, replacement is required. Dimensionally

inspect bearing outer diameter. If dimension is 5.51 inches

(139.95 mm) or less, replacement is required.

Inspect main input driven spiral bevel gear P/N

204-040-701-003 as follows:

a. Utilizing transmission case input quill port, inspect all 62

teeth of the main input driven spiral bevel gear convex side for

unsatisfactory conditions such as scoring, hard lines, nicks,

dents, chipping, metal deformation, etc.

NOTE

Inspection mirrors and a suitable light are required.

Turn rotor slowly to permit inspection of all gear

teeth.

b. Inspect concave side of all 62 teeth. Refer to Figure 5-6

for unacceptable conditions on concave side.

BHT-212-CR&O

c. Remove and replace any gear that does not meet

inspection requirements.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-39.

600 HOURS/12 MONTHS OF TAIL ROTOR DRIVESHAFT COUPLING OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:

_______________________________________

NOTE

Accomplish each 600 hours of component operation

months,

whichever

occurs

first.

No Non-Destructive Inspection (NDI) required.

BHT-212-CR&O

TAIL ROTOR DRIVESHAFT COUPLINGS

Chapter 65

Remove tail rotor driveshaft assemblies.

NOTE

Disassemble flexible couplings only to the extent

necessary to remove old grease and repack.

Clean, visually inspect, and repack tail rotor hanger

assembly flexible couplings.

Clean, visually inspect, and repack intermediate gearbox

flexible couplings.

Clean, visually inspect, and repack tail rotor gearbox

flexible coupling.

Clean, visually inspect, and repack transmission tail rotor

driveshaft flexible coupling.

Install tail rotor driveshaft assemblies.

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15 MAY 2020 Rev. 18

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-40.

600 HOURS/12 MONTHS OF MAIN DRIVESHAFT OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each 600 hours or 12 months of main

driveshaft operation, whichever occurs first. No

Non-Destructive Inspection (NDI) required.

MAIN DRIVESHAFT 212-040-005-003, -007, AND -103

Chapter 63

Remove main driveshaft.

NOTE

Disassemble driveshaft only to the extent necessary

to remove old grease and repack.

BHT-212-CR&O

Clean, visually inspect, and repack flexible couplings.

Install main driveshaft.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-40A. EACH 600 HOURS/12 MONTHS INSPECTION OF MAGNETIC BRAKE ASSEMBLY

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish the following inspection each 600 hours

or 12 months, whichever occurs first.

The following inspection is not required for

helicopters equipped with IFR Kit P/N 212-706-106.

MAGNETIC BRAKE ASSEMBLY P/N 204-001-376-003

ASB 212-17-157

Perform a detailed visual inspection of the magnetic brake

assembly in accordance with ASB 212-17-157.

If the mechanical damage exceeds the limitation, contact

Product Support Engineering.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-40B. EACH 600 HOURS/12 MONTHS INSPECTION OF FIRE EXTINGUISHER DISCHARGE

TUBES

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish the following inspection each 600 hours

or 12 months, whichever occurs first.

The following inspection is not required if the

discharge

tubes

212-060-921-101

and

212-060-921-102 are installed in accordance with

ASB 212-12-146.

FIRE EXTINGUISHER DISCHARGE TUBES P/N

212-060-921-001FM AND -002FM

ASB 212-12-146

Visually inspect the loop clamp AN735C16 installed on

discharge tubes 212-060-921-001FM and 212-060-921-002FM

for condition and security.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-41.

EACH 1000 HOURS OF COMPONENT OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each

1000 hours of component

operation.

Chapter 29

HYDRAULIC ACCUMULATORS

Remove hydraulic accumulators.

BHT-212-CR&O

Disassemble, clean, and visually inspect for corrosion and

damage.

Replace any unserviceable parts.

Reassemble hydraulic accumulators.

Chapter 29

Install hydraulic accumulators.

Chapter 79

OIL COOLER BLOWERS

Remove oil cooler blowers.

BHT-212-CR&O

Disassemble, clean, and visually inspect for corrosion and

damage.

Replace bearings and any other unserviceable parts.

Reassemble oil cooler blowers.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-42.

FIRST 1000 HOURS OF COMPONENT TIME AND EACH 3000 HOURS THEREAFTER OF

COMPONENT TIME

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish first 1000 hours inspection of component

time and each 3000 hours thereafter of component

time.

Applicable to flight control tube assemblies: 204-001-957-001,

205-001-017-001/-007,

212-001-051-001,

212-001-060-001,

and

212-076-151-001/-003/-005/-007/-009/-011. Supersedes

ASB 212-76-6.

ASB 212-76-6

Flight Control Tube Assemblies are identified by the following

sub-assemblies:

204-001-957-001 contains tube assembly 204-001-957-003

205-001-017-001 contains tube assembly 205-001-017-003

205-001-017-007 contains tube assembly 205-001-017-009

212-001-051-001 contains tube assembly 212-001-051-005

212-001-060-001 contains tube assembly 212-001-060-003

212-076-151-005 contains tube assembly 212-076-150-005

212-076-151-007 contains tube assembly 212-001-275-001

212-076-151-007 contains tube assembly 212-001-280-101

212-076-151-009 contains tube assembly 212-001-275-003

212-076-151-009 contains tube assembly 212-001-280-103

212-076-151-011 contains tube assembly 212-001-275-005

212-076-151-011 contains tube assembly 212-001-280-105

Control tube assemblies 212-001-280-101/-103/-105 are

fabricated from corrosion Resistant Steel (CRES),

special inspection not applicable.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-42.

FIRST 1000 HOURS OF COMPONENT TIME AND EACH 3000 HOURS THEREAFTER OF

COMPONENT TIME (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Inspect

flight

control

tube

assemblies

P/N

212-076-151-001/-003/-005/-007/-009/-011 as follows:

a. Measure and record overall length of control tube, and

then remove adjustable clevis.

BHT-212-CR&O

b. Inspect control rube for internal corrosion using a

borescope or equivalent. (Paint removal is not necessary.)

Particular attention shall be given to threaded areas. Any paint

anomalies such as blistering or discoloration will require paint

removal and further inspection. Any sighted internal corrosion is

cause for control tube rejection. If serviceable, refinish internal

surface of control tube with two coats of lacquer (C-226) using

fill and drain method.

c. Visually inspect external surfaces of control tubes for

mechanical damage and/or corrosion. Refer to the

BHT-212-CR&O manual for limits.

d. If serviceable, coat the control tube threaded area with

corrosion preventive compound (C-101), reinstall clevis into

control tube and adjust to recorded length.

Inspect P/N 204-001-957-001, 205-001-017-001 and -007,

212-001-051-001, 212-001-060-001 control tubes as follows:

a. Using a suitable container filled with 135 to 155°F (57 to

68°C) water, fully immerse the control tube for 2 minutes.

b. Any air bubbles detected from the control tube as a

result of the water immersion is cause for rejection of the tube.

c. Provided no air bubbles are detected, the control tube

may be considered serviceable.

Install flight control tubes and check rigging.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-42.

FIRST 1000 HOURS OF COMPONENT TIME AND EACH 3000 HOURS THEREAFTER OF

COMPONENT TIME (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Chapter 67

ELEVATORS

- Inspect

Remove and Inspect elevators as follows:

BHT-212-CR&O

a. Remove both elevators and inspect condition of ears on

elevator horn 205-001-914 and mating ears on elevator attach

fitting 205-030-475. Inspect ears by dye penetrant method.

Replace horn or fitting if any cracks are evident.

BHT-212-CR&O

b. Inspect elevators for general condition, cracks, and

corrosion. Repair inboard rib if any cracks exist. The inboard rib

shall be replaced if any cracks extend into rib flange.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-43.

EACH 1000 HOURS/12 MONTHS OF MAIN ROTOR BLADE OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each 1000 hours or 12 months of main

rotor blade operation, whichever occurs first.

Chapter 62

MAIN ROTOR BLADES

- Clean and Inspect

Clean blade from an area starting at butt end of blade to

several inches outboard of doublers on both upper and lower

surfaces, using aliphatic naphtha (C-305) or equivalent.

NOTE

Inspection may be accomplished with blades

installed on main rotor hub assembly.

BHT-212-CR&O

Inspect main rotor blade grip pads, grip plates, doublers,

drag plates, and adjacent surfaces for voids, edge voids,

corrosion, cracks, and condition of adhesive squeeze-out along

bond lines. Refer to BHT-212-CR&O manual for inspection

criteria and repair limits.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-44.

EACH 1200 HOURS/24 MONTHS OF COMPONENT OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each 1200 hours or 24 months of listed

component operation, whichever occurs first.

ASB 212-02-117

MAIN ROTOR HUB PINS 204-012-104-003/-005 AND

ASB 212-10-142

INBOARD STRAP FITTINGS 212-010-103-005/-007/-105

BHT-212-CR&O

Remove the four pins and two inboard strap fittings from

the main rotor hub assembly.

1A. Do a detailed visual inspection of all the surfaces of the

strap pin for mechanical or corrosion damage with a 10X

magnifying glass.

1B. If mechanical damage or corrosion pitting is found on a

strap pin, discard the pin.

Inspect pins and inboard strap fittings by magnetic particle

method.

Magnetic particle indication interpreted as cracks are not

acceptable and the pin or inboard strap fitting must be

discarded.

If strap pins are found cracked, the mating strap fitting must

also be discarded.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-44.

EACH 1200 HOURS/24 MONTHS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

If the pins are replaced (e.g., time expired), the mating

fittings will be considered serviceable only after NDI inspection

of the removed pins has confirmed they are not cracked.

Reassemble main rotor hub assembly.

Make an entry in the helicopter Historical Records (HR) to

show that the main rotor hub pins and inboard strap fittings have

been inspected in accordance with this special inspection.

MAIN ROTOR YOKE 212-011-102-ALL

- Detailed Visual Inspection

BHT 212-CR&O

Remove bearing races and spacers.

ASB 212-94-94

NOTE

Shield

204-012-116-107 does not need to be

removed to accomplish the inspection procedure.

Inspect yoke spindle for cracks and corrosion pits.

Inspect yoke spindle bearing journals for wear.

Any crack or wear beyond limits is cause for rejection of

the yoke. Remove any corrosion.

Assemble yoke.

ASB 212-90-59

MAIN ROTOR DRAG BRACE 204-011-140-ALL

- Inspect

BHT-212-CR&O

Remove drag brace assemblies.

Inspect drag brace assemblies for corrosion and

mechanical damage.

BHT-ALL-SPM

Perform a magnetic particle inspection.

Install drag brace assemblies.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-44.

EACH 1200 HOURS/24 MONTHS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

BHT-212-CR&O

MAIN ROTOR HUB GRIP 204-011-121-ALL

- Detailed Visual Inspection

Prepare both main rotor grip tangs for inspection by

cleaning exposed surfaces with denatured alcohol (C-326) as

per BHT-ALL-SPM. Wipe dry.

Inspect grip surfaces for evidence of hairline cracks on

upper and lower tangs exposed surfaces. Pay particular

attention to the lower tang lower surface from the blade bolt

bushing flange to the trailing and leading edge of the tang.

Crack indication requires the grip to be removed from service

for further evaluation (Figure 5-7).

For main rotor grip 204-011-121-009, inspect grip barrels

both leading and trailing sides for evidence of hairline cracks

(Figure 5-7).

Check for gap (360°) between flange of blade bolt bushing

and surface of grip tang. Maximum gap of

0.0025 inch

(0.0635 mm) permitted. Noted gap greater than the maximum

permitted requires bushing to be replaced.

Fit a blade bolt through both bushings simultaneously, bolt

should be able to be turned with the fingers. If this cannot be

accomplished, refer to BHT-212-CR&O, Chapter 62 for further

inspection requirements.

Inspect buffer pads on tang inner surfaces for

delamination. Any delamination will require buffer pad

replacement (Figure 5-7).

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-45A. EVERY

12 MONTHS/2500 LANDINGS HIGH FORWARD CROSSTUBE DEFLECTION

CHECK

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish the deflection check of the High Forward

Crosstubes assemblies

205-050-403-031 and

412-050-046-101 at every

12 months or

2500

landings, whichever occurs first.

HIGH FORWARD CROSSTUBES 205-050-403-031 AND

412-050-046-101

ASB 212-10-140

Carry out the deflection check of the High Forward

Crosstubes in accordance with ASB 212-10-140.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-45B. EVERY 12 MONTHS/5000 LANDINGS HIGH FORWARD CROSSTUBE FLUORESCENT

PENETRANT INSPECTION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish the fluorescent penetrant inspection of

the High Forward Crosstubes assemblies

205-050-403-031 and 412-050-046-101 at every 12

months or 5000 landings, whichever occurs first.

HIGH FORWARD CROSSTUBES 205-050-403-031 AND

412-050-046-101

ASB 212-10-140

Carry out the fluorescent penetrant inspection of the High

Forward Crosstubes in accordance with ASB 212-10-140.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-46.

EACH 24 MONTHS OF FLIGHT CONTROL SYSTEM BOLT OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each 24 months of flight control system

bolt operation.

Chapter 67

FLIGHT CONTROL SYSTEM BOLTS

NOTE

Refer to Chapter 4 for retirement life of flight control

system bolts.

- Inspect

Remove the following flight control bolts:

a. Two fixed swashplate to right and left cyclic boost tube

bolts P/N 20-057-5-24D.

b. One collective lever to collective boost tube bolt P/N

20-057-5-24D.

c. Three boost tube universal bolts P/N 20-057-24D.

d. Three universal to hydraulic cylinder tube bolts P/N

20-057-5-24D.

e. Two mixing lever to scissors tubes bolts P/N

20-057-5-27D.

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SPECIAL INSPECTIONS

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EACH 24 MONTHS OF FLIGHT CONTROL SYSTEM BOLT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

f. Two scissors tube to scissors bolts P/N 20-057-5-27D.

g. Two pitch link to universal tube bolts P/N 20-057-6-27D.

h. Two drive link to rotating swashplate bolts P/N

20-057-5-30D.

i. Two pitch horn to pitch link bolts P/N 20-057-6-31D.

j. Two universal to mixing lever bolts P/N 20-057-6-34D.

k. Four mixing lever

204-011-301, pivot bolts P/N

20-057-6S20D.

l. Four 20-057-6S24D mixing lever 212-010-302, pivot

bolts P/N 20-057-6S23D or 20-057-6S24D.

m. Two scissors to drive link bolts P/N 20-057-8S69D.

n. Two scissors

204-011-406, pivot bolts P/N

20-057-8S90D.

o. Two stabilizer bar pivot bolts P/N 20-057-10S27D or

20-057-10S29D.

p. Three hydraulic cylinder to lower support bolts P/N

212-001-304-003 or 212-001-323-001.

q. Two scissors

212-010-407, pivot bolts P/N

212-010-411-005 or 212-010-411-003-001 (ASB 212-89-56).

r. Two stabilizer bar damper tube to damper wing shaft

bolts P/N AN174-15.

s. Two stabilizer bar damper tube to stabilizer bar bolts

P/N AN174-20.

t. Two collective lever to swashplate support bolts P/N

AN178-22A.

u. Deleted

v. Deleted

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-46.

EACH 24 MONTHS OF FLIGHT CONTROL SYSTEM BOLT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Clean bolts with cloth dampened with MEK (C-309).

Inspect bolts for thread damage, shank wear, and

corrosion. Replace any bolt that has damaged threads,

detectable shank wear, or exhibits corrosion pitting.

Chapter 67

Apply corrosion preventive compound (C-104) to shanks of

bolts only and install bolts.

After bolts have been installed and nuts torqued and

safetied, coat head of bolt, nuts, and lockwire with corrosion

preventive compound (C-101).

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-47.

EACH 3000 HOURS OF COMPONENT OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish each 3000 hours of listed component

operation.

MAIN ROTOR MAST 204-040-366-021 AND 212-540-002-105

NOTE

Mast assembly

204-040-366-021 (installed in

transmission prior to 212-040-001-059/-141) with no

top case chip detector, overhaul interval is

2500

hours.

BHT-212-CR&O

Remove mast assembly from transmission and inspect inner

and outer diameters of mast for corrosion and mechanical

damage.

TRANSMISSIONS 212-040-001-059, -137 AND

SUBSEQUENT AND 212-540-002-103

- Disassembly

Visually inspect outside of transmission for evidence of

corrosion, damage, and any oil leaks before disassembling

transmission.

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-47.

EACH 3000 HOURS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

NOTE

Parts exhibiting evidence of wear or physical

damage shall be checked dimensionally. Refer to

BHT-212-CR&O manual for wear and damage limits.

BHT-212-CR&O

Disassemble transmission to accomplish the following:

a. Remove B4430 chip detector from 212-040-059 top

case. Clean chip detector using drycleaning solvent (C-304).

Visually inspect chip detector for cut packings, burrs, bent tube,

and foreign material.

b. Remove 212-040-059 top case. Inspect mast assembly

mating surface, pilot diameter and ring gear mating surface,

pilot diameter for fretting and wear.

c. Planetary component removal:

(1) Remove 204-040-360 upper planetary assembly

and 204-040-117 adapter as an assembly.

(2) Remove M27426-1220C retaining ring and

204-040-117 adapter from 204-040-360 planetary assembly. Do

not disassemble 204-040-360 planetary assembly.

(3) Remove

204-040-337 liner and

204-040-135

bearing as an assembly. Do not disassemble.

(4) Remove 205-040-231 ring gear assembly.

(5) Remove

205-040-230

upper

sun gear,

204-040-378 deflector, and RR687L retaining ring as an

assembly.

(6) Remove 204-040-784 lower planetary assembly.

(7) Remove 204-040-338 liner, 204-040-135 bearing,

and 204-040-257 liner as an assembly. Do not disassemble.

(8) Remove 205-040-229 lower sun gear.

5-00-00

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Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

SPECIAL INSPECTIONS

5-47.

EACH 3000 HOURS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Planetary component inspection:

BHT-212-CR&O

a. Visually inspect all parts of planetary assembly for

evidence of wear and/or damage.

b. Visually inspect gear tooth contact patterns on eight

pinion assemblies in upper planetary assembly. It is normal for

ring gear meshing side of planet pinions to have a double wear

pattern. Check bearings for smoothness and freedom from

binding by rotating the eight pinion assemblies. Visually inspect

all lockwire provisions.

c. Visually inspect external and internal spline teeth of

204-040-117 adapter for excessive wear and general condition.

d. Check planetary support liners and

204-040-135

bearings for smoothness and freedom of rotation.

e. Visually inspect upper flange surface and upper pilot

diameter and lower flange surface and lower pilot diameter of

205-040-231 ring gear for fretting and wear. Visually inspect

upper and lower gear teeth contact patterns for evidence of

pitting, scoring, wear, or damage.

BHT-212-CR&O

f. Visually inspect upper sun gear teeth for wear, damage,

and contact pattern.

BHT-212-CR&O

g. Disassemble 204-040-784 lower planetary to remove

204-040-785 spider.

BHT-ALL-SPM

(1) Magnetic particle inspect 204-040-785 spider.

(2) Visually inspect

204-040-785 spider spline for

evidence of wear (i.e., step, end loading, etc.).

BHT-212-CR&O

(3) Visually inspect gear tooth contact patterns on four

pinion assemblies in lower planetary assembly. It is normal for

ring gear meshing side of planetary pinions to have a double

wear pattern. Check bearings for smoothness and freedom from

binding by rotating the four pinion assemblies. Visually inspect

all lockwire provisions.

BHT-212-CR&O

h. Visually inspect 205-040-229 lower sun gear teeth for

wear, damage, and contact pattern.

5-00-00

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26 JUN 2013 Rev. 14

Page 183

BHT-212-MM-1

SPECIAL INSPECTIONS

5-47.

EACH 3000 HOURS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Remove B4429 chip detector from 212-040-053 case.

Clean chip detector as required using drycleaning solvent

(C-304). Visually inspect chip detector for cut packings, burrs,

bent tube, and foreign material.

Remove and inspect

204-040-393 manifold assembly.

Remove, clean, and inspect 204-040-388 jet No. 7 for cut

packing, burrs, and foreign material.

BHT-212-CR&O

Remove 204-040-362 quill assembly from 212-040-053

main case. Do no disassemble. Visually inspect mating flanges

and pilot diameters for evidence of corrosion, fretting, and wear.

Visually inspect all lockwire provisions. Check duplex bearing

for smoothness and freedom of rotation by manually turning

204-040-701 gear. Visually check index marks on 204-040-701

gear and inner race of 205-040-245 bearing set for alignment.

NOTE

If index marks indicate movement between gear and

inner race of bearing set, remove 204-040-701 gear,

204-040-357 plate, 204-040-348 shim, 205-040-245

bearing set, and 204-040-350 shim. Visually inspect

inside diameter of 205-040-245 bearing set for signs

of spinning. Visually inspect 205-040-245 bearing

journal on 204-040-701 gear for sign of fretting.

Inspect detail components to determine cause for

inner race rotation.

Using a torque wrench, check each of the 32 bevel gear

retaining bolts 214-040-117-005, for minimum torque of 300

inch-pounds (33.895 Nm).

NOTE

Torque check is accomplished with increasing

torque, not break away or loosening torque.

a. If torque value of any one retaining bolt is less than 300

inch-pounds (33.895 Nm), remove bevel gear and inspect

mating surfaces of gear 204-040-701, and shaft 204-040-324,

for fretting damage.

5-00-00

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Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

SPECIAL INSPECTIONS

5-47.

EACH 3000 HOURS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

b. The maximum acceptable depth of pitting is 0.0005 inch

(0.0127 mm). Pitting is acceptable only in area on gear or shaft

surface outside of diameter of bolt holes and is not acceptable

within 0.100 inch (2.54 mm) of the edge of a bolt hole. Damage

in excess of these limits is cause for rejection of part.

BHT-212-CR&O

c. Visually examine 204-040-701 gear teeth for evidence

of wear, scoring, pitting, and contact pattern.

d. Visually inspect roller bearing race on lower end of shaft

for evidence of skidding, scoring, pitting, or damage.

e. Visually inspect splines on upper and lower end of shaft

for damage and/or wear.

Visually inspect 204-040-700 pinion teeth for excessive

wear, scoring, pitting, and contact pattern. Visually inspect

vibro-etched index marks on

204-040-700 pinion and

214-040-118 bearing set for alignment. Inspection may be

accomplished with input quill installed by viewing pinion shaft

and bearing inner race between teeth and main case.

NOTE

If index marks indicate rotational movement between

pinion and inner race of bearing set, 212-040-263

quill shall be removed from main case. Disassemble

quill to remove 212-040-700 pinion and 214-040-118

bearing set.

a. Visually inspect pinion bearing journal for signs of

fretting and bearing inner race spinning.

b. Clean

214-040-097 sleeve in drycleaning solvent

(C-304).

c. Visually ensure oil holes in 214-040-097 sleeve are free

of any foreign material.

d. Inspect detail components to determine cause for inner

race rotation.

5-00-00

Export Classification C, ECCN EAR99

26 JUN 2013 Rev. 14

Page 185

BHT-212-MM-1

SPECIAL INSPECTIONS

5-47.

EACH 3000 HOURS OF COMPONENT OPERATION (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

BHT-212-CR&O

Remove tail rotor drive quill 212-040-365-025, to gain

access to accessory drive and sump gears. Visually inspect

accessory case input quill gear 212-040-150-005, and tail rotor

drive quill gear 212-040-151-009, for general condition and

wear pattern.

BHT-212-CR&O

10. Inspect components in case assembly 212-040-054:

a. Visually inspect mating flange and pilot diameter of

support case at main case joint for evidence of corrosion,

fretting, and/or wear.

b. Remove lift link fitting.

c. Visually inspect lift link fitting pads for evidence of

fretting and wear.

d. Visually inspect bearing rollers for evidence of damage.

e. Remove screws and washers from transmission

support case lateral mounts, top and bottom.

f. Visually inspect screws for corrosion and thread

damage.

g. Visually inspect washers for corrosion and thread

damage.

h. Visually inspect installed busings for corrosion and/or

pitting.

i. Visually inspect transmission support case lateral

mount surfaces and threaded holes for mechanical and

corrosion damage.

BHT-212-CR&O

11. Assemble transmission.

5-00-00

Page 186

Rev. 17

30 OCT 2019

Export Classification C, ECCN 9E991

BHT-212-MM-1

SPECIAL INSPECTIONS

5-48.

10,000 HOUR TOTAL AIRFRAME TIME AND EACH 300 HOURS/12 MONTHS MAIN BEAM

CAP OPERATION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish at 10,000 hours total airframe time and

each 300 hours or 12 months, whichever occurs first,

thereafter.

MAIN BEAM CAP

This inspection is not required after main beam cap

205-030-186-101 is installed.

Inspect main beam cap 205-030-186-005 in accordance with

TB 212-88-106.

5-00-00

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26 JUN 2013 Rev. 14

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BHT-212-MM-1

SPECIAL INSPECTIONS

5-48A.

10 YEARS COLLECTIVE STICK TUBE INSPECTION

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish inspection of pilot collective stick tube

(212-001-181-001) and copilot collective stick tube

(212-001-170-001) once every 10 years.

Chapter 67

FLIGHT CONTROLS

BHT-212-CR&O

BHT-212-SI-4

BHT-212-SI-89

TB 212-87-98

Disassemble pilot and copilot (if installed) collective stick(s)

to the extent necessary to remove throttle twist grips.

Referring to Figure 5-8, visually inspect stick tube for

cracks using a 3X magnifying glass and a bright light. Pay

particular attention to the base of the throttle slots that form the

twist grip stops.

If a crack is found, replace stick tube.

Reassemble pilot and copilot (if installed) collective

stick(s).

Check throttle controls for proper operation.

Check collective controls for proper operation.

5-00-00

Export Classification C, ECCN EAR99

15 MAY 2020 Rev. 18

Page 188A

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-49.

CONDITION INSPECTION

If applicable conditional inspection does not

provide complete information on a specific type of

Perform applicable conditional inspection of

incident or if any doubt exists as to the serviceability of

helicopter after hard landing, after blade strike or other

the helicopter of related components, contact:

rotating system torque spike, overspeed, overtorque,

compressor stall or surge, lightning strikes, and after

reduction

(combining)

gearbox

clutch

Product Support Engineering

nonengagement, misengagement, or in-flight slippage

(paragraph 5-50 through paragraph 5-56).

12800 rue de l’Avenir

Mirabel, Quebec J7J 1R4

If overhaul evaluation is specified, complete both

the conditional inspection and normal inspection

Fax:

(450) 433-0272

procedures (as applicable) for that component listed in

Tel:

(450) 437-6201or

BHT-212-CR&O manual.

800-363-8028 (U.S./Canada)

E-mail:

psemedium@bh.com

5-00-00

Export Classification C, ECCN EAR99

26 JUN 2013 Rev. 14

Page 189/190

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-50.

AFTER HARD LANDING

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish inspection after hard landing.

AFTER HARD LANDING

NOTE

Evaluate components removed from a helicopter

following a hard landing as an interrelated group.

Make entries in component records of each removed

component to cross reference part and serial

numbers of other drive system components removed

for evaluation.

Hard landing is defined as any accident or incident in

which ground impact of helicopter results in yielding

or cracking of mounting lugs of transmission support

case or noticeable yielding or cracking of fuselage

pylon support structure, landing gear, or tailboom

attachment structure. This definition is confined only

to those accidents not involving sudden stoppage of

main rotor or tail rotor.

5-00-00

Export Classification C, ECCN EAR99

26 JUN 2013 Rev. 14

Page 191

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-50.

AFTER HARD LANDING (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

- Inspect

If a hard landing is suspected, step a through step h shall

be accomplished:

a. 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.

b. Visually inspect underside of fuselage and tailboom for

evidence of ground contact.

Chapter 32

c. Perform landing gear deflection check.

(1) If crosstubes have yielded, remove landing gear

and inspect support and attaching structure for signs of yielding

or other damage.

(2) If supports and attaching structure are not

damaged, replace damaged landing gear components.

d. Inspect mast for evidence of hard rotor hub contact

sufficient enough to yield or deform mast.

e. Inspect mast area around pylon mount for loose rivets

or other damage.

f. Inspect tailboom and fuselage attachment for loose

rivets, cracks, or other damage.

g. If no damage other than yielded landing gear

crosstubes has been found at this point, it is reasonably certain

a true hard landing did not occur. For helicopters on the Part A

inspection program, complete a 100 hour /12 month inspection.

For helicopters on the Part B inspection program, complete a 25

hour/15 day inspection and return helicopter to flight status

provided no further evidence of damage is found.

h. If damage is more extensive than landing gear

crosstube yielding, a hard landing has occurred. Comply with

requirements of step 2 through step 4.

5-00-00

Page 192

Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-50.

AFTER HARD LANDING (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

If a hard landing has occurred, the following steps shall be

accomplished:

a. Remove and perform an overhaul evaluation inspection

of following components:

(1) Mast assembly

NOTE

If there is any yielding or deformation in area

contacted by main rotor hub static stops or any other

obvious damage, mast is unserviceable and

non-repairable.

(2) Transmission

(3) Main driveshaft

b. Perform a thorough visual inspection of following

components that may be kept in service if no discrepancy or

obvious damage is found. Replace any damaged component:

(1) Main rotor blades

(2) Main rotor hub

(3) Tail rotor blades

(4) Tail rotor hub

ASB 212-96-100 and

NOTE

ASB 212-96-101

Inspect trunnion assembly 212-010-738 or flapping

stop 212-011-713 for yielding as noted in Chapter 64

to determine if tail rotor yoke assembly may have

been exposed to bending.

(5) Tail rotor static stop

(6) Tail rotor yoke

(7) Intermediate gearbox

5-00-00

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26 JUN 2013 Rev. 14

Page 193

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-50.

AFTER HARD LANDING (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

(8) Tail rotor gearbox

(9) Tail rotor driveshafts

(10) Tail rotor driveshaft hangers

(11) Swashplate and support assembly

(12) Scissors and sleeve assembly and collective

levers

(13) Stabilizer bar assembly

(14) Helicopter structure directly supporting damaged

components identified in previous inspections

c. Check all cowling and doors for proper fit and

alignment. Remove cowling and inspect all attachment fittings.

NOTE

If significant damage has been found in any area of

airframe, inspection shall be expanded in those

areas until it extends beyond zone of damage.

d. Make a complete inspection, using a 10X magnifying

glass, of pylon support structure for loose or sheared rivets,

cracked brackets, buckled or cracked support angles and webs.

Pay particular attention to pylon mounts attaching points.

e. Make a complete inspection of lift link, lift link

attachment fittings, and lift beam for cracks and other evidence

of damage. Remove lift link and replace with like serviceable

item, if damaged.

f. Remove both pylon dampers, disassemble and check

for internal yielding. Assemble dampers and install if no

evidence of damage exists. Replace with like serviceable item if

any damage is found.

g. Install serviceable mast, transmission assembly, and

main driveshaft assembly. Install removed pylon control

components.

5-00-00

Page 194

Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-50.

AFTER HARD LANDING (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

h. Check all engine mount fittings and bolts for damage

and looseness.

i. Inspect engine firewalls for evidence of warping,

crushing, or other damage.

j. Make a complete inspection of area where tailboom is

attached to forward fuselage section. This includes both sets of

attachment fittings and longerons, beam caps, skins, webs,

bulkhead flanges, and other structural members. Check torque

on attachment bolts to determine if yielding has occurred.

k. Completely inspect flight control system from pilot (and

copilot) controls to rotor head for bent or damaged tubes,

bellcranks, bellcrank supports, and for damaged control system

bearings. Particular attention should be given to pylon controls,

lower cylinder attachment support fitting, and adjacent airframe

structure.

l. Pressurize hydraulic systems and check for leaks,

interference, binding, and satisfactory operation.

m. Inspect fuel, oil, and pneumatic system for damage.

Make engine ground run and visually check fuel, oil, and

pneumatic lines for leaks.

Pratt & Whitney

Inspect power plant in accordance with Pratt & Whitney

Canada PT6T-3/-3B

Canada PT6T-3/-3B Maintenance Manual.

Maintenance Manual

If no significant damage has been found, no further

inspection is necessary.

5-00-00

Export Classification C, ECCN EAR99

26 JUN 2013 Rev. 14

Page 195/196

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

To be accomplished after a main rotor blade or tail

rotor blade strike or any drive system failure that

inhibits free rotation of drive system.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM

TORQUE SPIKE

NOTE

If the blade strike or rotating system torque spike is

the result of crash damage or results in crash

damage, all rotating system components shall be

considered unserviceable and non-repairable.

Crash damage is any damage sustained beyond the

scope of that identified in the After Hard Landing

conditional inspection (paragraph 5-50).

5-00-00

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26 JUN 2013 Rev. 14

Page 197

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

NOTE

Components removed from a helicopter for

evaluation following a sudden stoppage 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.

Sudden stoppage is defined as any rapid

deceleration of drive system whether caused by

seizure within helicopter transmission or by contact

of main or tail rotor blades with the ground, water,

snow, dense vegetation, trees, or other objects of

sufficient density to cause rapid deceleration. Main or

tail rotor blade damage, when caused by striking

some object sufficient to require blade replacement

(defined as removal for repair or scrap), is

considered sudden stoppage. When sudden

stoppage occurs, inspect helicopter and replace

components as follows:

Perform a sudden stoppage inspection as follows:

NOTE

If sudden stoppage inspection is the result of a tail

rotor strike or main rotor blades striking the tail rotor

driveshaft, comply with step g through step n.

a. Main rotor blades.

(1) Visually inspect both main rotor blades for

evidence of damage. Check closely for wrinkled skin.

(2) If any blade is damaged sufficiently to require

blade repair, return both blades to an authorized overhaul

facility. Make an entry in component record to show reason for

removal was sudden stoppage.

(3) If no evidence of damage is found on either blade,

both blades may be retained in service.

5-00-00

Page 198

Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

b. Main rotor hub.

(1) If main rotor blades were not damaged sufficiently

to require blade replacement, hub may be retained in service.

BHT-212-CR&O

(2) If a main rotor blade is damaged sufficiently to

require blade replacement, perform overhaul inspection on main

rotor hub. If any doubt exists, contact Product Support

Engineering.

(3) If a main rotor blade is damaged beyond repair,

scrap 204-011-121 grips and perform overhaul evaluation on

main rotor hub. Make entry in component record to show reason

for removal was sudden stoppage.

c. Pylon control components.

BHT-212-CR&O

(1) If one or more of the following discrepancies in

step (a) through step (f) are found, swashplate assembly,

stabilizer bar assembly, and scissors and sleeve assembly shall

be removed and an overhaul evaluation performed.

(a) Severe main rotor blade damage sufficient to

require replacement.

(b) Pitch horn failure.

(d) Control tube buckled or broken.

(e) Transmission main support case mounting leg

broken.

(f)

Damaged isolation mounts.

If no condition exists as listed in preceding step (1), perform a

close visual inspection. If no evidence of damage is found, the

swashplate assembly, stabilizer bar assembly, and scissors

and sleeve assembly may remain in service.

d. Replace all bolts in rotating controls. Discard removed

bolts.

5-00-00

Export Classification C, ECCN EAR99

26 JUN 2013 Rev. 14

Page 199

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

BHT-212-CR&O

e. Remove and inspect main driveshaft visually. If

evidence of yielding or deformation is noted, scrap driveshaft

assembly and attaching bolts. If no visual evidence of damage

is detected, perform an overhaul evaluation. Make an entry in

component record to show reason for removal and sudden

stoppage.

f. Transmission and mast assembly.

(1) The following criteria are established to determine

the need for removal and overhaul of the transmission and mast

assembly. If any doubt exists contact Product Support

Engineering.

(a) Damage to the main rotor blades due to

striking a foreign object requiring removal to repair or scrap

blades.

(b) Damage to the main rotor hub due to the main

rotor blades striking a foreign object.

(d) Seizure of drive system components.

NOTE

The transmission and mast assembly must be

evaluated for serviceability as a set when removed

for inspection requirements due to sudden stoppage.

Inspect in accordance with the BHT-212-CR&O

manual, ensuring both conditional and normal

inspections are accomplished.

BHT-212-CR&O

NOTE

If mast has evidence of torsional yielding (defined as

excessive runout, bending, deformation or spline

misalignment), mast assembly (including mast

bearing), transmission top case, transmission lower

planetary spider, lower mast bearing, and pylon

mounts shall be scrapped. The transmission shall be

overhaul evaluated. If the main case is magnesium it

shall be scrapped.

5-00-00

Page 200

Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

If mast assembly does not exhibit evidence of

torsional yielding and transmission has no obvious

damage that would render it non-repairable, perform

an overhaul evaluation on both the transmission and

mast assembly.

If transmission is considered non-repairable as a

result of sudden stoppage, the mast assembly shall

be scrapped.

If a main rotor blade is damaged beyond repair, main

rotor mast assembly (204-011-450-ALL) shall be

scrapped.

In all cases, make an entry in component records to

show reason for component removal was sudden

stoppage.

g. Tail rotor driveshaft hanger assemblies:

(1) If a tail rotor driveshaft has been damaged beyond

limits due to contact with a main rotor blade or other similar

circumstance, the hanger assemblies to which the damaged

shaft was attached shall be scrapped. If a tail rotor driveshaft

fails as a result of torsional overload, all hanger assemblies and

shafts shall be scrapped.

BHT-212-CR&O

(2) If inspection reveals no damage that would render

hanger assemblies non-repairable, hanger assemblies shall

have an overhaul evaluation performed. Make an entry in

component record to show reason for removal is blade strike or

torque spike.

Chapter 65

h. Tail rotor driveshaft.

(1) Remove tail rotor driveshafts and inspect for

following conditions. If one or more of conditions listed in

step (a) through step (e) are noted, all driveshafts and bearing

hangers shall be considered unserviceable and non-repairable

and shall be scrapped.

(a) Curvic faces distorted.

(b) Evidence of overload.

5-00-00

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26 JUN 2013 Rev. 14

Page 201

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

(d) Loose or sheared rivets.

(e) Scratches in excess of limits.

(2) If inspection reveals no condition as previously

listed in step (a) through step (e) exists, driveshaft may remain

in service.

i. Tail rotor hub and blade assembly.

NOTE

Nicks, scratches, or dents on top or bottom of blade

(nonleading edge) that do not require removal of

blades for replacement may not require the tail rotor

assembly to be scrapped. If any doubt exists, contact

Product Support Engineering.

(1) Tail rotor hub and blade assembly: If sudden

stoppage originated at tail rotor blades, tail rotor hub assembly

shall be considered unserviceable and non-repairable and must

be discarded.

(a) If sudden stoppage originated at main rotor or

main rotor 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,

an overhaul of the tail rotor hub shall be performed. Make an

entry in component records to show reason for removal was

sudden stoppage.

(b) If sudden stoppage originated at tail rotor

driveshaft, intermediate gearbox, or tail rotor gearbox remove

tail rotor hub and blade assembly and perform an overhaul of

the tail rotor hub. Make an entry in component record to show

reason for removal was sudden stoppage.

to require blade repair, return both blades to an authorized

overhaul facility. Make an entry in component record to show

that reason for removal was sudden stoppage.

5-00-00

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Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

(d) If no evidence of damage is found on either

tail rotor blade, both blades may remain in service.

(2) Tail rotor hubs with 212-011-702 yoke assembly

and 212-011-713-103 flapping stop, reference ASB 212-96-101.

Tail rotor hubs with

212-010-704-ALL yoke assembly or

212-010-744-ALL yoke assembly and

212-010-738-001

trunnion assembly, reference ASB 212-96-100.

(a) Inspect

212-011-713 and

212-010-738

flapping stops for yielding, to determine if tail rotor yoke

assembly may have been exposed to bending. A yielded

flapping stop requires removal of the tail rotor yoke and flapping

stop, and they shall be considered unserviceable and

non-repairable, and must be discarded.

j. Tail rotor rotating controls.

(1) Perform a close visual inspection of the tail rotor

rotating controls. If no evidence of damage is found, the tail

rotor rotating control may remain in service. Replace all tail rotor

rotating control bolts. If damage to the tail rotor rotating controls

is found, perform an overhaul of the tail rotor rotating controls.

Make an entry in component record to show that reason for

removal was sudden stoppage.

k. Tail rotor gearbox.

(1) Remove tail rotor gearbox. Check for cracks,

sheared or bent attaching studs, and evidence of case

distortion. If any of these conditions are noted, gearbox is

unserviceable and non-repairable and shall be scrapped.

BHT-212-CR&O

(2) If inspection reveals no condition as listed in

previous step (1), perform an overhaul evaluation. Make an

entry in component record to show reason for removal was

sudden stoppage.

l. Intermediate gearbox.

(1) Remove intermediate gearbox. Check for cracks,

case distortion, or broken lugs. If any of these conditions are

noted, gearbox is unserviceable and non-repairable and shall

be scrapped.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-51.

AFTER BLADE STRIKE OR OTHER ROTATING SYSTEM TORQUE SPIKE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

BHT-212-CR&O

(2) If inspection reveals no condition as listed in

previous step (1), perform an overhaul. Make an entry in

component record to show reason for removal was sudden

stoppage.

m. Transmission sump case.

NOTE

If no evidence of damage was found in step g

through step k, or step l, omit following step (1)

through step (3).

(1) If damage was found on bearing hangers, tail rotor

driveshaft, intermediate gearbox, or tail rotor gearbox, remove

tail rotor drive output quill from transmission sump case

assembly.

(2) Inspect output quill pinion for unusual load patterns

on both sides of teeth. If no damage is found, reinstall quill.

Transmission may be retained in service.

BHT-212-CR&O

(3) If tail rotor quill reveals discrepancies, remove

transmission and perform an overhaul evaluation. Make an

entry in component record to show reason for removal was

sudden stoppage.

n. Reinstall or replace, as applicable, all removed

components with serviceable components.

Pratt & Whitney

o. Inspect engine in accordance with Pratt & Whitney

Canada PT6T-3/-3B

Canada PT6T-3/-3B Maintenance Manual.

Maintenance Manual

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-52.

AFTER OVERSPEED

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish inspection after overspeed.

AFTER OVERSPEED

NOTE

Components removed from a helicopter for

evaluation following an overspeed 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.

Overspeed is defined as any incident in which 110%

main rotor RPM is exceeded.

Perform overspeed inspection as follows:

Pratt & Whitney

a. Refer to Pratt & Whitney Canada PT6T-3/-3B

Canada PT6T-3/-3B

Maintenance Manual for engine overspeed and inspection

Maintenance Manual

requirements.

b. Main rotor hub assembly.

(1) Remove main rotor hub. Remove main rotor

blades.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-52.

AFTER OVERSPEED (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

BHT-212-CR&O

(2) Perform an overhaul conditional evaluation

inspection. Make an entry in component record to show reason

for removal was overspeed. Include amount of overspeed and

duration, if known.

BHT-212-CR&O

(3) Inspect main rotor blade retention bolts and drag

brace bolts.

c. Main rotor blades.

(1) Inspect main rotor blades skin for wrinkles and

deformation.

(2) If no discrepancies are found in inspections

outlined in step (1), main rotor blades may be retained in

service.

(3) If discrepancies are found in step (1), return both

blades to an authorized blade repair station. Make an entry in

component record to show reason for removal was overspeed.

Include amount of overspeed and duration, if known.

d. Tail rotor hub and blades.

(1) Remove tail rotor hub and blade assembly.

(2) Remove tail rotor blades.

(3) Replace tail rotor blade retention bolts.

e. Tail rotor blades.

BHT-212-CR&O

(1) Perform major overspeed inspection of tail rotor

blades. Make an entry in component record to show reason for

removal was overspeed.

f. Perform a close inspection of the following components.

If no visual damage is found, components may be retained in

service.

(1) Main transmission.

(2) Intermediate gearbox. Check gearbox for security

and retaining bolts.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-52.

AFTER OVERSPEED (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

(3) Tail rotor gearbox. Check gearbox for security and

retorque retaining nuts.

(4) Main rotor mast.

(5) Main input driveshaft.

(6) Tail rotor driveshafts.

(7) Tail rotor driveshaft hangers.

(8) Stabilizer bar.

(9) Swashplate.

(10) Scissors and sleeve.

(11) Tail rotor hub.

g. Install a serviceable main rotor hub and blade

assembly. Install serviceable tail rotor blades. Balance and

install tail rotor hub and blade assembly.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-53.

AFTER OVERTORQUE

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish inspection after overtorque.

AFTER OVERTORQUE

NOTE

Components removed from a helicopter for

evaluation following an overtorque 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.

Overtorque is defined as any incident in which

torsional loads are introduced into the helicopter

dynamic system in excess of established limits.

Pratt & Whitney

Refer to Pratt & Whitney Canada PT6T-3/-3B Maintenance

Canada PT6T-3/-3B

Manual for engine overtorque inspection limits.

Maintenance Manual

NOTE

To assist with determining engine overtorque

inspection requirements, the following table provides

a comparison between Bell Helicopter cockpit torque

gauge

% values and Pratt & Whitney Canada

Maintenance Manual FT LB values.

5-00-00

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26 JUN 2013 Rev. 14

Page 209

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-53.

AFTER OVERTORQUE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

PT6T-3

PT6T-3B

BELL %

P&WC

BELL %

P&WC

TORQUE

FT LB

TORQUE

FT LB

87.6

900

89.1

915

83.6

859

85.2

875

77.8

800

79.4

815

71.8

738

71.8

738

When overtorque has not exceeded 104% (108% for

helicopters with TB 212-91-138 incorporated), perform thorough

visual inspection of the following components. If inspection does

not reveal any discrepancies or obvious damage to

components, the components may be retained in service.

a. Tail rotor blades.

b. Main rotor hub.

c. Tail rotor hub.

d. Intermediate gearbox. Check gearbox for security and

retorque retaining bolts.

e. Tail rotor gearbox. Check gearbox for security and

retorque retaining nuts.

f. Tail rotor driveshafts.

g. Tail rotor driveshaft hangers.

h. Stabilizer bar assembly.

i. Swashplate.

j. Scissors and sleeve assembly.

k. Main driveshaft.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-53.

AFTER OVERTORQUE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

l. Mast.

m. Transmission.

When overtorque exceeds 104% (108% for helicopters

with TB 212-91-138 incorporated), but does not exceed 112%

perform the following:

a. Perform thorough visual inspection of components

listed in step 2.

b. Inspect main transmission chip detector(s).

c. Inspect main transmission internal filter or full flow

debris monitor (as applicable).

(1) If metal particles are found, indicating internal

failure, remove transmission for overhaul evaluation. Make an

entry in the component record explaining reason for removal

was overtorque. Remove all transmission system oil lines. Flush

and reinstall oil lines. Replace external oil filter element.

Remove and scrap oil cooler. Install new oil cooler.

(2) If chip detector(s) and internal filter or full flow

debris monitor (as applicable) appear normal and there is no

evidence of internal failure, return helicopter to service. Operate

normally for 5 hours and then check chip detector(s) and

internal filter or full flow debris monitor. If no metal particles are

found indicating internal failure, normal scheduled inspection

intervals may then be followed. If metal particles are present

prior to or at the 5 hour check, or if there is any evidence of

internal failure, remove transmission for overhaul evaluation.

Make an entry in the component record explaining reason for

removal was overtorque. Remove all transmission system oil

lines. Flush and reinstall oil lines. Replace external oil filter

element. Remove and scrap oil cooler. Install new oil cooler.

d. Remove fifth mount bolts and remove fifth mount.

Perform a thorough inspection of bolts and fifth mount support.

Check for bent bolts and bent fifth mount support. Check for bolt

hole alignment between transmission and fifth mount support.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-53.

AFTER OVERTORQUE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

When overtorque has exceeded

112% perform the

following:

a. Return the following components to an overhaul facility

for overhaul evaluation.

NOTE

Component removal record of dynamic components

shall reflect overtorque as reason for removal.

Include amount of overtorque and duration, if known.

(1) Transmission.

(2) Main driveshaft.

(3) Main rotor hub.

(4) Mast.

(5) Perform thorough visual inspection of other

components outlined in step 2.

b. Remove fifth mount bolts and remove fifth mount.

Perform a thorough inspection of bolts and fifth mount support.

Check for bent bolts and bent fifth mount support. Check for bolt

hole alignment between transmission and fifth mount support.

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Export Classification C, ECCN EAR99

BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-54.

AFTER ENGINE COMPRESSOR STALL OR SURGE

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

DATE:

__________________

W.O.

_____________________

FACILITY:

_________________________________________

HELICOPTER S/N:

__________________________________

REGISTRY NO.:

____________________________________

TOTAL TIME:_______________________________________

SIGNATURE:_______________________________________

NOTE

Accomplish inspection after engine compressor stall

or surge.

AFTER ENGINE COMPRESSOR STALL OR SURGE

NOTE

Discuss circumstances of reported compressor stall

with pilot, if possible. Determine N₁ (GAS PROD)

speed at which reported stall occurred. Check

helicopter and engine logs for any pertinent history.

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

Interturbine Temperature (ITT), depending on

severity of surge. When a surge has been reported,

progressively perform the following inspections as

dictated by discrepant conditions.

Components removed from a helicopter for

evaluation following a compressor stall or surge 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.

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26 JUN 2013 Rev. 14

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-54.

AFTER ENGINE COMPRESSOR STALL OR SURGE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Power plant.

a. Examine inlet screen for blockage.

Pratt & Whitney

b. Inspect engine compressor region for salt, dust, oil, or

Canada PT6T-3/-3B

other contaminants. If contaminants are found, clean and

Maintenance Manual

perform a power check in accordance with Pratt & Whitney

Canada PT6T-3/-3B Maintenance Manual.

c. Inspect for visible Foreign Object Damage (FOD) to

visible compressor blades.

Pratt & Whitney

d. If compressor stall (surge) occurred during acceleration,

Canada PT6T-3/-3B

refer to Pratt & Whitney Canada PT6T-3/-3B Maintenance

Maintenance Manual

Manual for inspection procedures.

Pratt & Whitney

e. Perform test on pneumatic sense lines.

Canada PT6T-3/-3B

Maintenance Manual

Pratt & Whitney

f. If step a through step e do not reveal cause of surge,

Canada PT6T-3/-3B

perform a hot end inspection in accordance with Pratt &

Maintenance Manual

Whitney Canada PT6T-3/-3B Maintenance Manual.

Power train.

a. If compressor stall occurs below 85% N1 (GAS PROD)

speed, comply with step b and step c.

b. Remove magnetic chip detectors from transmission,

intermediate gearbox, and tail rotor gearbox. Inspect for metal

particles.

c. If no evidence of damage is found on tailboom pylon

and no indication of metal particles are found on chip detectors,

clean chip detectors and reinstall. Return helicopter to flight

status and repeat chip detector inspection after

5 to

operating hours. If positive indication of damage is found on

tailboom pylon or metal chips are found on chip detectors,

during initial or 5 to 10 hour inspection, comply with the

following step e through step i.

d. If compressor stall occurs at 85% N₁ (GAS PROD) or

above, comply with the following step e through step i.

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BHT-212-MM-1

CONDITIONAL INSPECTIONS

5-54.

AFTER ENGINE COMPRESSOR STALL OR SURGE (CONT)

INITIAL

DATA REFERENCE

INSPECTION TASK DESCRIPTION

MECH OTHER

Chapter 65

e. Remove and inspect tail rotor driveshaft.

f. Remove input and output drive quill from intermediate

gearbox and inspect gear teeth on pinion and gear for damage

with a 10X magnifying glass. if no evidence of scoring or

scuffing is found, and there is no mechanical damage that would

render gearbox unserviceable, reassemble and return to

service. If gear teeth are scuffed or scored, or gearbox has

sustained other damage, gearbox shall be replaced with a like,

serviceable item and the following step g and step h

accomplished.

g. Remove tail rotor gearbox from helicopter and remove

input quill. Inspect gear teeth on pinion and gear for damage

with a 10X magnifying glass. If no evidence of scoring or

scuffing is found, and there is no other damage that would

render gearbox unserviceable, it may be reassembled and

reinstalled for continued use. If gear teeth are scored or scuffed,

or there is other damage that would render gearbox

unserviceable, replace gearbox with a like, serviceable item.

h. Remove tail rotor drive quill from transmission and

inspect gear teeth for damage with a 10X magnifying glass. If

there is no indication of scoring or scuffing, and there is no other

damage that would render transmission unserviceable, it is

suitable for continued use. If gear teeth are scored or scuffed, or

there is other damage and that would render transmission

unserviceable, replace transmission with a like, serviceable item

and comply with step j.

i. Install serviceable tail rotor driveshaft if transmission is

not to be replaced.

j. If transmission is to be replaced, the following

components shall also be replaced (step (1) through step (3)

and procedures outlines in step (4) through step (8) performed).

(1) Tail rotor bearing hanger assemblies.

(2) Tail rotor driveshafts.

BHT-212-CR&O

(3) Tail rotor hub and blade assembly. Perform an

overhaul. Make an entry in component record to show reason

for removal was compressor stall.

5-00-00

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15 MAY 2020 Rev. 18

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Helicopter Bell-212. MAINTENANCE MANUAL (2021) - page 4