Helicopter Bell-212. MAINTENANCE MANUAL (2021)

BHT-212-MM-1

PROPRIETARY RIGHTS NOTICE

These data are proprietary to Bell Textron Inc. Disclosure, reproduction, or use of

these data for any purpose other than helicopter operation or maintenance is

forbidden without prior written authorization from Bell Textron Inc.

DESTINATION CONTROL STATEMENT

WARNING - This document contains technical data whose export is restricted

by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et. seq.) or the Export

Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et. seq.

Violations of these export laws are subject to severe criminal penalties.

Disseminate in accordance with provisions of DoD Directive 5230.25.

Rev. 18

15 MAY 2020

Export Classification C, ECCN EAR99

BHT-212-MM-1

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Export Classification C, ECCN EAR99

15 MAY 2020 Rev. 18

Warning

BHT-212-MM-1

CUSTOMER SUPPORT AND SERVICES

Flying smart means that no matter where you are, or what time it is, you can make a call

and get additional information, clarification, or advice on a technical or operational issue

concerning your helicopter or information contained in our Technical Publications.

Product Support Engineering (PSE) is just a phone call away and may be contacted as

follows:

Commercial Models

Phone:

450-437-2862 or 800-363-8023 (U.S./Canada)

Fax:

450-433-0272

E-mail:

productsupport@bellflight.com

Model 210, HUEY II, and All Bell’s Active and Surplus

Military Medium Helicopter Models

Phone:

817-280-3548

Fax:

817-280-2635

E-mail:

mts-medium@bellflight.com

Model OH-58, TH-67, TH-57, Both Active and Surplus

Military

Phone:

817-280-3548

Fax:

817-280-2635

E-mail:

mts-light@bellflight.com

For additional information on Customer Support and Services as well as Product Support

Engineering (PSE) and your local Customer Service Engineering (CSE) network, please

access https://www.bellflight.com/support.

CSS

Rev. 18

15 MAY 2020

Export Classification C, ECCN EAR99

BHT-212-MM-1

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Insert latest revision pages and dispose of superseded ones.

On a revised page, the text and/or illustration affected by the latest revision is shown by a vertical line. A revised

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Export Classification C, ECCN EAR99

25 AUG 2021 Rev. 20

CUSTOMER FEEDBACK

RETURN VIA FAX TO PRODUCT SUPPORT ENGINEERING (450) 433-0272

Manual Title:

___________________________________________________________

Manual Number (if assigned):

_____________________________________________

Date of Issue:

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Date of Last Revision:

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Section, Chapter, Paragraph Affected:

______________________________________

Your Feedback:

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Now Reads:

____________________________________________________________

_______________________________________________________________________

Should Read:

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Your Name:

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Address:

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_______________________________________________________________________

Position:

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Telephone No.:

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Company:

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Fax No.:

_______________________

Reference No. (your initials and date):

_____________________________________

(If you choose to mail this form, fold in thirds with address exposed, tape and mail.)

Export Classification C, ECCN EAR99

BHT-212-MM-1

SPARE PARTS WARRANTY

WARRANTY: Seller warrants each new helicopter part or helicopter part reconditioned by

Seller to be free from defect in material and workmanship under normal use and service and if

installed on Bell model helicopters for up to 1000 hours of operation, one (1) year from date of

installation, or two (2) years from date of shipment by Seller, whichever occurs first. Seller

assigns each manufacturer’s warranty to Buyer to the extent such manufacturer’s warranty exists

and is assignable.

Parts, components and assemblies of all helicopter parts may have been restored or reworked due

to mars, blemishes, dents or other irregularities during the manufacturing process. Such

restoration and/or rework are permitted under Seller’s approved manufacturing and engineering

processes and guidelines. The restoration and/or rework so completed do not render such items

defective in material or workmanship.

Seller’s sole obligation under this warranty is limited to the repair or replacement of parts which

are determined to Seller’s reasonable satisfaction to have been defective within the applicable

warranty period as described above. Replacement of parts may be either new or reconditioned at

Seller’s election and at the lowest allowable maintenance level contained in Seller’s manuals,

service bulletins or applicable supplier manuals. Seller shall also reimburse reasonable freight

charges, excluding insurance, customs fees, duties, handling fees, and taxes. Seller shall not

reimburse Buyer for any parts repaired or replaced outside of the Seller’s Warranty Claims

Process unless express prior written authorization is granted by Seller’s Warranty Department to

Buyer for such repair or replacement.

NO FAULT FOUND: In the event Seller determines, after evaluation of a returned part, that a

defect does not exist, then Buyer shall pay all expenses incurred by Seller related to the return

including, but not limited to, costs incurred in shipping and evaluating the part and cost for any

replacement part and restocking of the part. In addition, Seller shall not reimburse Buyer for any

costs related to the removal or reinstallation of such a part.

WARRANTY CLAIM PROCESS: Defective parts must be reported in writing to the Seller’s

Warranty Administration within fourteen (14) days of being found defective. Parts may be

repaired or replaced with new or reconditioned parts, at Seller’s election. Warranty adjustment is

contingent upon the Buyer complying with the Seller’s Warranty Process as described in the Bell

Helicopter VISTA Customer Portal and with the Seller’s Warranty Administration disposition

instructions for defective parts. Failure to properly comply with Seller’s Warranty Process may,

at Seller’s sole option, void Seller’s warranty as to the allegedly defective part.

RETURN SHIPMENT: Parts returned to Seller will be eligible for remedy under this warranty

only if the part is carefully packed by the Buyer for the return shipment. Damage occurring to a

part due to improper packaging may result in the denial of a warranty claim. In the event that

Seller determines a returned part to be damaged or unsalvageable due to improper packaging, the

Buyer will be billed repair or replacement cost incurred by Seller. The party initiating shipment

bears the risk of loss or damage to parts in transit.

Export Classification C, ECCN EAR99

15 MAY 2020 Rev. 18

Warranty Page 1

BHT-212-MM-1

CORE RETURNS: Any core removed by Buyer for which Seller has furnished a replacement

part through the Warranty Process shall be shipped by Buyer, with all historical service records,

to a facility designated by Seller, within fourteen (14) days of receipt by Buyer of the

replacement part. Buyer shall provide Seller with proof of shipment within fourteen (14) days

following receipt of the replacement part. In the event that Buyer fails to provide Seller with

such proof of shipment within the fourteen (14) days or fails to provide the applicable historical

service records, Buyer shall be charged the invoiced value of the replacement part.

WARRANTY AND LIABILITY DISCLAIMERS AND EXCLUSIONS: THIS

WARRANTY IS GIVEN AND ACCEPTED IN PLACE OF (i) ALL OTHER WARRANTIES

OR CONDITIONS, EXPRESS OR IMPLIED, INCLUDING BUT NOT LIMITED TO THE

IMPLIED WARRANTIES OR CONDITIONS OF MERCHANTABILITY OR FITNESS FOR

A PARTICULAR PURPOSE AND (ii) ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR

REMEDY IN CONTRACT OR IN TORT, INCLUDING PRODUCT LIABILITIES BASED

UPON STRICT LIABILITY, NEGLIGENCE, OR IMPLIED WARRANTY IN LAW.

This warranty is the only warranty made by Seller. The Buyer’s sole remedy for a breach of this

warranty or any defect in a part is the repair or replacement of the helicopter part and

reimbursement of reasonable freight charges. Seller excludes liability, whether as a result of a

breach of contract or warranty, negligence or strict product liability, for incidental or

consequential damages, including without limitation, damage to the helicopter or other property,

costs and expenses resulting from required changes or modifications to helicopter components

and assemblies, changes in retirement lives and overhaul periods, local customs fees and taxes,

and costs or expenses for commercial losses or lost profits due to loss of use or grounding of

helicopters or otherwise.

Seller makes no warranty and disclaims all liability in contract or in tort, including, without

limitation, negligence and strict tort liability, with respect to work performed by third parties at

Buyer’s request and with respect to engines, engine accessories, batteries, radios, and avionics.

Seller makes no warranty and disclaims all liability with respect to components or parts damaged

by, or worn due to, normal wear and tear, erosion or corrosion. Seller makes no warranty and

disclaims all liability for consumables which are defined as items required for normal and routine

maintenance or replaced at scheduled intervals shorter than the warranty period. “Consumables”

include but are not limited to engine and hydraulic oil, oil filters, packings and o-rings, anti-

corrosion and/or sealing compounds, brush plating material, nuts, bolts, washers, screws, fluids,

compounds, and standard aircraft hardware that is readily available to aircraft operators from

sources other than Seller.

This warranty shall not apply to any helicopter part which has been repaired or altered outside

Seller’s factory in any way so as, in Seller’s sole judgment, to affect its stability, safety or

reliability. This warranty shall not apply to any helicopter part which has been subject to misuse,

negligence or accident, or which has been installed in any aircraft which has been destroyed.

Repairs and alterations which use or incorporate parts and components other than genuine Bell

parts or parts approved by Bell for direct acquisition from sources other than Bell itself are not

warranted by Bell, and this warranty shall be void to the extent that such repairs and alterations,

Warranty Page 2

Rev. 18

15 MAY 2020

Export Classification C, ECCN EAR99

BHT-212-MM-1

in Seller’s sole judgment, affect the stability, safety or reliability of the helicopter or any part

thereof, or damage genuine Bell or Bell-approved parts. No person, corporation or organization,

including Bell Authorized Customer Service Facilities, is authorized by Seller to assume for it

any other liability in connection with the sale of its helicopters and parts.

NO STATEMENT, WHETHER WRITTEN OR ORAL, MADE BY ANY PERSON,

CORPORATION OR ORGANIZATION, INCLUDING BELL AUTHORIZED CUSTOMER

SERVICE FACILITIES, MAY BE TAKEN AS A WARRANTY NOR WILL IT BIND

SELLER.

CHOICE OF LAW AND JURISDICTION: This warranty shall be interpreted under and

governed by the laws of the State of Texas. All legal actions based upon claims or disputes

pertaining to or involving this warranty including, but not limited to, Seller’s denial of any claim

or portion thereof under this warranty, must be filed in the courts of general jurisdiction of

Tarrant County, Texas or in the United States District Court for the Northern District of Texas,

Ft. Worth Division located in Ft. Worth, Tarrant County, Texas. In the event that Buyer files

such an action in either of the court systems identified above, and a final judgment in Seller’s

favor is rendered by such court, then Buyer shall indemnify Seller for all costs, expenses and

attorneys’ fees incurred by Seller in defense of such claims. In the event Buyer files such a legal

action in a court other than those specified, and Seller successfully obtains dismissal of that

action or transfer thereof to the above described court systems, then Buyer shall indemnify Seller

for all costs, expenses and attorneys’ fees incurred by Seller in obtaining such dismissal or

transfer.

Export Classification C, ECCN EAR99

15 MAY 2020 Rev. 18

Warranty Page 3

BHT-212-MM-1

BULLETIN RECORD

All Alert Service Bulletins (ASB) and Technical Bulletins (TB) issued prior to and including the bulletins listed below

have been incorporated in this revision/reissue or previously published editions of this manual, as applicable.

Subsequent bulletins will be incorporated in future revisions/reissues.

ALERT SERVICE BULLETINS

ASB NUMBER

SUBJECT

DATE

212-20-162

Tailboom Left Hand Fin Spar Cap P/N 212-030-447-117,

15 April 2020

Inspection of.

This bulletin and all previously issued applicable bulletins have been incorporated, except the ASB

212-00-106 is not incorporated.

TECHNICAL BULLETINS

TB NUMBER

SUBJECT

DATE

212-95-156

Pillow Block Bushing 204-011-135-105 Increase in

18 September 1995

Retirement Life

Export Classification C, ECCN EAR99

25 AUG 2021 Rev. 20

BHT-212-MM-1

LIST OF CHAPTERS

Title

Chapter

Introduction

Airworthiness Limitations Schedule

Inspections

Dimensions and Charts

Lifting and Jacking

Weight and Balance

Towing

Parking and Mooring

Placards and Markings

Servicing

Vibration and Noise Analysis

Air Distribution (Ventilation)

Equipment and Furnishings

Fire Protection

Fuel System

Hydraulic System

Ice and Rain Protection

Landing Gear

Doors and Windows

Fuselage

Main Rotor

Main Rotor Drive System

Tail Rotor

Tail Rotor Drive System

Flight Controls

Power Plant

Engine Controls

Engine Oil System

Instrument System

Electrical System

Avionics

Wiring Diagrams

Export Classification C, ECCN EAR99

30 OCT 2019 Rev. 17

i/ii

FAA APPROVED

BHT-212-MM-1

AIRWORTHINESS LIMITATIONS SCHEDULE

4-1.

AIRWORTHINESS

LIMITATIONS

Airworthiness lives assigned to helicopter

SCHEDULE

components and assemblies are based upon

experience, testing, and engineering judgment

and are subject to change at the sole discretion of

The

mandatory Airworthiness

Limitations

Bell Textron or an appropriate government

Schedule summarizes, in tabular form, the

agency.

mandatory maximum life, in hours, years or by

Retirement Index Number (RIN) of components

with a limited airworthiness life. Parts that are not

on the schedule have an unlimited airworthiness

WARNING

life.

ALL PARTS REMOVED DUE TO

NOTE

REACHING THEIR LIFE LIMITS ARE

The Airworthiness Limitations section is

DEEMED UNAIRWORTHY AND

FAA

approved

and

specifies

SHALL BE PERMANENTLY MARKED

maintenance required under Secs.

AS SCRAP OR PHYSICALLY

43.16 and

[91.403] of the Federal

DESTROYED TO THE EXTENT THAT

Aviation Regulations unless an

THERE IS NO CHANCE OF REPAIR

alternative program has been FAA

OR REINSTALLATION ON ANY

approved.

HELICOPTER OR COMPONENT.

Refer to United Aircraft of Canada Ltd.

NOTE

Service Bulletins, 5000 series, for power plant

Neither assignment of a retirement

components Airworthiness Limitations.

life to a component, nor failure to

assign a retirement life, constitutes a

warranty of any kind. The only

CAUTION

warranty applicable to the helicopter

and any component is that warranty

included in the Purchase Agreement for

AIRWORTHINESS LIFE FOR KIT

the helicopter or the component.

COMPONENT AND/OR PARTS ARE

NOT COVERED IN THIS

AIRWORTHINESS SCHEDULE.

REFER TO APPLICABLE SERVICE

INSTRUCTIONS FOR MANDATORY

AIRWORTHINESS SCHEDULE.

NOTE

The operating time specified for

retirement for any given part number

contained

this

Airworthiness

Limitations Schedule applies to all

successive dash numbers for that item

unless otherwise specified.

4-00-00

Export Classification C, ECCN EAR99

15 JUL 2021 Rev. 19

Page 5

BHT-212-MM-1

FAA APPROVED

Mandatory Airworthiness Limitations Schedule (Cont)

COMPONENT

PART NUMBER

AIRWORTHINESS LIFE

Yoke

212-011-702-001

5000 Hours

Blade

212-010-750-009 and -105

5000 Hours

Blade Assembly

412-016-100-111

5000 Hours

POWER TRAIN DRIVE SYSTEM COMPONENTS

Spider

204-040-785-003

Conditional

Spider

412-040-785-101

2500

Spider

412-040-785-103

Unlimited

Mast Bearing

204-040-136-009

1000 Hours

Bearing (When used in rotor

204-040-424

600 Hours

brake quill)

Tail Rotor Hanger Bearing

204-040-623-001

100 Hours

Tail Rotor Hanger Bearing

204-040-623-005

1000 Hours

Pinion - Offset Accessory

212-040-202-001

1000 Hours

Drive

POWER PLANT RELATED SYSTEMS

Blower, Oil Cooler

212AA3192 (Benson)

300 Hours

LANDING GEAR

Crosstubes

205-050-400-007,-029,

1000 Hours

-035 and -705

FLOAT LANDING GEAR (KIT P/N 205-706-050-001, -007, -011, -101)

Crosstube Assembly

205-050-114-001

500 Hours

Crosstube Assembly

205-050-114-011

1000 Hours

Crosstube Assembly

205-050-114-023, -025

Unlimited

Crosstube Assembly

205-706-050-005

500 Hours

Crosstube Assembly

205-706-050-013

1000 Hours

Crosstube Assembly

205-706-050-015

Unlimited

4-00-00

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Rev. 19

15 JUL 2021

Export Classification C, ECCN EAR99

BHT-212-MM-1

FAA APPROVED

Mandatory Airworthiness Limitations Schedule (Cont)

NOTES (CONT):

When the maximum RIN or retirement flight hours is reached, whichever occurs first, the

component will be removed from service

Increase RIN count by 5 for each takeoff/lift performed. If logging, increase RIN count by 10 for

each takeoff/lift performed. Logging is defined as - Repeated heavy lift events using an

external long line which involve significant torque excursions (>80%) and elevation changes.

Per ASB 212-80-18 and ASB 212-76-3.

Per ASB 212-77-17.

4-2.

CALCULATING FLIGHT HOURS ON

two hours for each flight hour of internal operation

204-011-102 YOKE.

for which the number of events cannot be

determined. Use five hours for each flight hour if

Calculate flight hours on the yoke using the table

time actually spent in external or internal

given in note

to determine the correct factor

operation cannot be determined.

based on the number of events per flight hour:

3. Perform the following operations following

1. If flight hours cannot be determined, use the

calculation or approximation of flight hours/lift

following:

events:

Enter on yoke Historical Service Record

900

hours per year from date of helicopter delivery or

If main rotor yoke flight hours exceed

3300,

date yoke was installed.

remove yoke from service within the next 300

hours.

2. If number of lift events per hour cannot be

determined, use the following:

Retire main rotor yoke at 3600 hours.

Enter on yoke Historical Service Record five

hours for each flight hour of external operation, or

4-00-00

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Rev. 19

15 JUL 2021

Export Classification C, ECCN EAR99

BHT-212-MM-1

CHAPTER 5 - INSPECTIONS

TABLE OF CONTENTS

Paragraph

Chapter/Section

Page

Number

Title

Number

INSPECTIONS

5-1

General

5-00-00

5-2

Inspection Requirements

5-00-00

5-3

Crash Damage

5-00-00

5-4

Types of Inspections

5-00-00

5-5

Definitions

5-00-00

5-6

Inspection and Overhaul Tolerance

5-00-00

SCHEDULED INSPECTIONS

5-7

Scheduled inspections

5-00-00

5-8

Daily Inspection - Part A

5-00-00

5-9

100 Hours/12 Calendar Months - Part A

5-00-00

5-10

1000 Hours - Part A

5-00-00

5-11

5000 Hours/5 Years Inspection - Part A

5-00-00

5-12

25 Hours/30 Days - Part B

5-00-00

5-13

300 Hours/12 Months Inspection - Part B

5-00-00

5-14

600 Hours/12 Months - Part B

5-00-00

5-15

5000 Hours/5 Years Inspection - Part B

5-00-00

SPECIAL INSPECTIONS

5-16

Special Inspection

5-00-00

105

5-17

Daily Inspection

5-00-00

107

5-18

Daily or Each 10 Hours of Flight Operation, Whichever Occurs

First Until 250 Hours

5-00-00

109

5-19

Between 5 and 10 Hours of Flight After Each Installation

5-00-00

115

5-20

Fin Spar Cap Inspection Every 8 Hours

5-00-00

117

5-21

Each 25 Hours for the next Four Inspections

5-00-00

119

5-22

Each 25 Hours of Flight Operation

5-00-00

121

5-23

Each Seven Days in a Corrosive Environment and Each 30 Days in a

Noncorrosive Environment

5-00-00

127

5-24

50 Hours After Installation of Components

5-00-00

129

5-25

Each 50 Hours of Component Operation

5-00-00

131

5-26

Each 100 Hours of Main Rotor Blade Operation - Deleted

5-00-00

133

5-27

Each 100 Hours/12 Months of Transmission Operation

5-00-00

135

5-28

Each 100 Hours/12 Months of Intermediate Gearbox Operation...

5-00-00

137

5-29

Each 100 Hours/12 Months of Tail Rotor Gearbox Operation

5-00-00

139

5-29A

Fin Spar Cap Inspection Every 100 Hours

5-00-00

140A

5-30

Each 100 Hours/12 Months of Battery System Operation

5-00-00

141

5-31

100 Hours After Installation of Tailboom

5-00-00

143

5-32

Each 150 Hours of Starter Generator P/N 200SG119Q

Operation

5-00-00

145

5-33

Fin Spar Cap Inspection Every 300 Hours

5-00-00

147

5-34

Each 300 Hours/12 Months of Transmission Operation

5-00-00

149

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15 MAY 2020 Rev. 18

Page 1

BHT-212-MM-1

TABLE OF CONTENTS (CONT)

Paragraph

Chapter/Section

Page

Number

Title

Number

5-35

Each 300 Hours/3 Months of Driveshaft Operation

5-00-00

151

5-35A

Each 300 Hours/12 Months Inspection of Tail Rotor

Control Tube and Bearing

5-00-00

152A

5-36

Main Rotor Grip Ultrasonic Inspection

5-00-00

153

5-37

Each 500 Hours/6 Months of Blade Service

5-00-00

155

5-38

Each 600 Hours of Transmission Operation

5-00-00

157

5-39

600 Hours/12 Months of Tail Rotor Driveshaft Coupling

Operation

5-00-00

159

5-40

600 Hours/12 Months of Main Driveshaft Operation

5-00-00

161

5-40A

Each 600 Hours/12 Months Inspection of Magnetic Brake

Assembly

5-00-00

162A

5-40B

Each 600 Hours/12 Months Inspection of Fire Extinguisher

Discharge Tubes

5-00-00

162C

5-41

Each 1000 Hours of Component Operation

5-00-00

163

5-42

First 1000 Hours of Component Time and Each 3000 Hours

Thereafter of Component Time

5-00-00

165

5-43

Each 1000 Hours/12 Months of Main Rotor Blade Operation

5-00-00

169

5-44

Each 1200 Hours/24 Months of Component Operation

5-00-00

171

5-45

Each 1200 Hours of Main Rotor Hub Pin Operation - Deleted

5-00-00

175

5-45A

Every 12 months/2500 Landings High Forward Crosstube

Deflection Check

5-00-00

176A

5-45B

Every 12 months/5000 Landings High Forward Crosstube

Fluorescent Penetrant Inspection

5-00-00

176C

5-46

Each 24 Months of Flight Control System Bolt Operation

5-00-00

177

5-47

Each 3000 Hours of Component Operation

5-00-00

181

5-48

10,000 Hour Total Airframe Time and Each 300 Hours/12 Months

Main Beam Cap Operation

5-00-00

187

5-48A

10 Years Collective Stick Tube Inspection

5-00-00

188A

CONDITIONAL INSPECTIONS

5-49

Condition Inspection

5-00-00

189

5-50

After Hard Landing

5-00-00

191

5-51

After Blade Strike or Other Rotating System Torque Spike

5-00-00

197

5-52

After Overspeed

5-00-00

205

5-53

After Overtorque

5-00-00

209

5-54

After Engine Compressor Stall or Surge

5-00-00

213

5-55

After Lightning Strikes

5-00-00

219

5-56

After Engine Combining Gearbox Clutch Nonengagement,

Misengagement, or In-flight Slippage

5-00-00

227

COMPONENT OVERHAUL SCHEDULE

5-57

Component Overhaul Schedule

5-00-00

231

5-00-00

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15 MAY 2020

Export Classification C, ECCN EAR99

BHT-212-MM-1

FIGURES

Figure

Page

Number

Title

Number

5-1

Fuselage Tailboom Attachment Inspection

5-2

Inspection of Beam Caps

5-2A

Cabin Frame Inspection - Part A

60B

5-3

Cabin Frame Inspection - Part B

104B

5-4

Inspection of Main Rotor Hub Grip Tangs, Barrel and Drag Brace Attachment

Lugs

108

5-5

Spiral Bevel Gears Serial Numbers

111

5-6

Inspection of Spiral Bevel Gear

112

5-6A

Tail Rotor Blade - Detailed Inspection

126B

5-6B

Spar Cap Inspection

140B

5-7

Inspection of Main Rotor Hub Grip (1200 Hours/24 Months)

174

5-8

Collective Stick Tube

188B

TABLES

Table

Page

Number

Title

Number

5-1

Component Overhaul Schedule

231

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BHT-212-MM-1

INSPECTIONS

5-1.

GENERAL

The helicopter may then be changed to the Part A

inspection program beginning with a Daily

This chapter contains the requirements for the

Inspection.

Scheduled, Special, and Conditional Inspections and a

Component Overhaul Schedule.

The inspection intervals given in this chapter are the

maximum permitted. Do not exceed these intervals.

The owner/operator is responsible for increasing the

scope and the frequency of the inspections as

WARNING

necessary. Make sure the helicopter is maintained

safely during all unusual local changes, such as

environmental conditions, helicopter use, etc. You can

FAILURE TO CORRECT CONDITIONS

request changes to the requirements in this chapter

SUCH AS, BUT NOT LIMITED TO,

through the local Aviation Authority.

CORROSION, EROSION, MECHANICAL

DAMAGE, OR OBVIOUS WEAR FOUND

The inspection intervals and the component overhaul

DURING A SCHEDULED INSPECTION

schedule provided in this chapter are applicable only

COULD SERIOUSLY AFFECT THE

to Bell Helicopter Textron approved parts.

AIRWORTHINESS OF THE HELICOPTER.

These inspection requirements constitute an approved

NOTE

inspection program for the Bell Helicopter Model 212.

For the convenience of the operator, two separate

The time period given for the overhaul of a

Scheduled Inspections are provided as follows:

component (or the failure to give a time

period for the overhaul of a component)

Part A scheduled inspections consists of a daily

does not constitute a warranty of any kind.

inspection, 100 hour/12 calendar month inspection,

The only warranty applicable to the

1000 hour inspection, and a

3000 hour/5 year

helicopter or any component is the

inspection.

warranty included in the Purchase

Agreement for the helicopter or the

Part B scheduled inspections consists of a 25 hour/

component.

30 day inspection, 300 hour inspection, 600 hour/

12 month inspection, and a

3000 hour/5 year

The Time Between Overhaul (TBO) and the inspection

inspection.

periods are determined through experience, tests,

Lead The Fleet (LTF), or any other special programs

Either Part A or Part B inspection program may be

and the judgement of Bell Helicopter Textron

utilized. However, once a helicopter has been started

engineers. They are subject to change only by Bell

on an inspection program, it shall be maintained on

Helicopter Textron or an approved Airworthiness

that program except as follows:

Authority.

•

If a helicopter is being inspected on the Part A

Changes to the TBO will be introduced by either

inspection program and it is preferable to change

revision to this chapter or a Technical Bulletin.

to the Part B program, a complete Part A - 1000

Hour Inspection shall be accomplished. The

Every calendar and hourly inspection is a thorough

helicopter may then be changed to the Part B

visual inspection to determine the airworthiness of the

inspection program beginning with a 25 Hour/15

helicopter and the components. Qualified persons

Day Inspection.

must do the inspections in accordance with quality

standard aircraft practices and the applicable

•

If a helicopter is being inspected on the Part B

maintenance manuals. Bell Helicopter Textron

inspection program and it is preferable to change

considers that it is mandatory to obey all the

to the Part A program, a complete Part B - 600

applicable Alert Service Bulletins (ASB) and the

Hour/12 Month Inspection shall be accomplished.

Airworthiness Directives (AD).

5-00-00

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26 JUN 2013 Rev. 14

Page 5

BHT-212-MM-1

Component operating time records are necessary for

EXTENT THAT THERE IS NO CHANCE

components that have scheduled maintenance

OF REPAIR OR INSTALLATION ON ANY

procedures, which are different from those of the

HELICOPTER OR COMPONENT.

airframe. It is the owner/operator’s responsibility to

keep the Historical Service Records (HSR) for the

Make sure all limited life parts that have

applicable component and to do the necessary

completed their published operating limits are

maintenance procedures.

replaced.

Before each inspection, remove or open the

Make sure all of the components that have

necessary cowlings, fairing, inspection doors, and

completed their published overhaul periods are

panels.

overhauled.

5-2.

INSPECTION REQUIREMENTS

Make sure all of the maintenance that is done on

the helicopter is done by an approved maintenance

This manual does not include specific inspections

organization.

required by the FAA or other government regulatory

authorities. These specific inspections are given by

your government regulatory authority. Refer to their

The maintenance organization/person doing the

requirements for these specific inspections.

maintenance is responsible for the quality of the

maintenance done.

The owner/operator of the helicopter is responsible for

the maintenance done on the helicopter. It is the

The owner/operator may choose to ask the

owner.operator’s responsibility to:

maintenance

organization/person

doing

the

maintenance to perform the tasks listed by prior

Establish, maintain, and review the log books for

arrangement through a separate formal agreement.

discrepancies.

5-3.

CRASH DAMAGE

Make sure the Alert Service Bulletins (ASB), the

Airworthiness Directives (AD), and the special

Because of the many possible combinations that can

inspections are done when they are required to be

result from crash damage, it is not possible to include

done.

the

specific repair tasks in this category. The

helicopter mechanic must make an analysis of the

Make sure the scheduled inspections, the special

crash damage for each situation. Do the repair in

inspections, and the required tests for all of the

accordance with the degree of damage to the specific

installed kits are complied with.

part and the applicable repair procedures in this

manual. Call Product Support Engineering with your

analysis of the crash damage.

Make sure all parts and components for which

Historical Service Records are required have

documented traceability to their original installation in

5-4.

TYPES OF INSPECTIONS

the helicopter.

The maintenance procedures may include

scheduled inspections, special inspections, conditional

inspections, component interim inspections, and

WARNING

component overhaul inspections.

a. Scheduled inspections must occur at specified

ALL PARTS REMOVED, DUE TO

operating intervals. The intervals may be in operating

REACHING THEIR LIMITS OR AS A

time (hours), cycles, torque events (RIN), calendar

RESULT OF AN ACCIDENT/INCIDENT

(days, months, years) or other assigned units. This

INSPECTION

AND

DEEMED

makes sure that the helicopter is airworthy.

UNAIRWORTHY,

SHALL

PERMANENTLY MARKED AS SCRAP OR

PHYSICALLY DESTROYED TO THE

•

Scheduled inspections - Part A consists of:

5-00-00

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Rev. 14

26 JUN 2013

Export Classification C, ECCN EAR99

BHT-212-MM-1

- Daily inspection - Accomplish daily before

Lubrication and servicing requirements are in

flight operation.

addition to those stated in this chapter (Chapter 12).

100 hours/12 calendar months - Accomplish

For corrosion control refer to the Corrosion

each

100 hours of flight operation or

Control Guide, CSSD-PSE-87-001

and the

12 calendar months, whichever comes first.

BHT-ALL-SPM.

1000 hours - Accomplish each 1000 hours of

For the PT6T-3/-3B engines, refer to the Pratt &

flight operation.

Whitney Canada Maintenance Manual for the

scheduled inspection, special inspection, conditional

5000 hours/5 years

- Accomplish each

inspection, and component overhaul schedule.

5000 hours of flight operation or each

60 calendar months, whichever comes first.

For the common Bell Helicopter Textron approved

•

Scheduled inspections - Part B consists of the

optional equipment that

is integrated into this

following:

maintenance manual, refer to this chapter for the

scheduled

inspection,

conditional

inspection,

component

interim inspection, and

component

–

25 hours/30 days

- Accomplish each

overhaul inspection.

25 hours of flight operation or each 30 days,

whichever comes first.

For all other Bell Helicopter Textron approved

–

300 hours/12 months - Accomplish each

equipment, refer to the applicable Service Instruction

300 hours of flight operation or each

for the scheduled inspection, special inspection,

12 calendar months, whichever comes first.

conditional inspection, component interim inspection,

and component overhaul inspection.

600 hours/12 months - Accomplish each

600 hours of flight operation or each

For the inspection requirements for optional

12 calendar months, whichever comes first.

equipment approved under Supplement Type

Certificate (STC), refer to the applicable STC

5000 hours/5 years

- Accomplish each

documentation. Maintenance and inspection of these

5000 hours of flight operation or each

items are the responsibility of the owner/operator.

60 calendar months, whichever comes first.

5-5.

DEFINITIONS

b. Special inspections are of a temporary nature

or of a special interval that is not consistent with the

scheduled inspections.

•

Inspect, check, examine - Determine condition

relative to an established standard.

c. Conditional inspections do not occur at a

specified time. A conditional inspection is the result of

•

Condition - The state of being of an item as

known or suspected unusual event, known or

related to serviceable or unserviceable standard.

suspected malfunctions, or defects.

•

Security - The presence of attaching parts that

d. An interim inspection occurs between

are properly tightened or appear to be, and the

overhauls.

presence of properly installed (as required)

locking devices such as lockwire, cotter pins, or

e. The component overhaul schedule gives the

other.

elapsed operating time at which a component must be

removed, disassembled, examined for condition, and

•

Standard - An established rule or measure to

overhauled, in accordance with data approved by Bell

determine condition.

Helicopter Textron.

Airworthiness limitations - Replace components

•

Damage - Physical deterioration whereby the

in accordance with Airworthiness Limitations Schedule

standard renders the condition or an item

(Chapter 4).

acceptable or not acceptable for continuous use.

5-00-00

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15 MAY 2020 Rev. 18

Page 7

BHT-212-MM-1

•

Discard - Reject a component that has damage

•

Special Programs

- These are approved

that cannot be repaired. To permanently remove

programs that may be initiated under certain

from service.

special conditions to meet specific requirements.

These programs will be clearly defined through a

plan and the engineering and maintenance

•

Preventive maintenance

- Simple or minor

aspects will be approved by the regulatory

preservation and the replacement of small

authorities.

standard parts not involving complex assembly

operations.

5-6.

INSPECTION

AND

OVERHAUL

TOLERANCE

•

Maintenance

- Inspection, overhaul, repair,

preservation, and the replacement of parts, but

excludes preventive maintenance.

WARNING

•

Operating time - Time required to be recorded in

historical record sheets or helicopter logs.

DO NOT APPLY THESE TOLERANCES

Operating time to be recorded may be identified

TO PARTS WITH A LIMITED

as follows:

AIRWORTHINESS LIFE (CHAPTER 4).

The Bell Helicopter Textron approved tolerance for

- Time in service - Time from the moment a

scheduled inspections, special inspections, interim

helicopter leaves the surface of the earth until

inspections, and overhaul intervals, unless otherwise

it touches down at the next point of landing.

stated, is 10% or up to a maximum of 300 hours

Time during which the engine and rotor are

operating time/6 months calendar time, whichever is

turning with the helicopter on the ground is not

less. The tolerances are established for maintenance

taken into account.

scheduling convenience only.

- Calendar time - Elapse time starts the day

Scheduled inspections, special inspections, interim

the inspection is accomplished, the

inspections, or overhaul intervals required beyond the

component is installed, or the rotor is turned

stated tolerances must be approved by Product

Support Engineering.

for the first time and ends on the last day of

the month that the time limit expires. Calendar

time shall be recorded without interruption.

NOTE

Removal of the component or storage of the

helicopter etc. does not stop calendar time.

The following is only applicable for those

operators whose governing aviation

authority requires to specifically approve

•

Planned event - Occurrence of interval in which

the inspection and overhaul tolerance.

a specific action is to be taken as in the case of

preventive maintenance, scheduled overhaul, or

If approval of the inspection and overhaul tolerance is

replacement in accordance with maximum

required by the applicable governing aviation authority,

airworthiness life guidelines.

this is the responsibility of the owner/operator.

•

Lead The Fleet (LTF) Program - This is a

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

program to validate the performance of an

Maintenance Manual for inspection and overhaul

approved product improvement or a change to a

tolerances.

maintenance interval. The engineering aspects of

this change are approved. The program is closely

The following provides examples of when hourly,

monitored by Bell Helicopter Textron in an

calendar, or hourly/calendar inspection tolerances

operational environment with selected operators.

have been applied:

5-00-00

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15 MAY 2020

Export Classification C, ECCN EAR99

BHT-212-MM-1

Hourly Example (10% or up to a maximum of 300 hours, whichever is less):

300-HOUR

NEXT 300-HOUR

MAXIMUM ALLOWED

INSPECTION CARRIED

INSPECTION

TOLERANCE

OUT AT:

DUE AT:

3400 Hours

10% of 300 hours = 30 hours

3430 Hours

3730 Hours

(10% tolerance applied)

3730 Hours

10% of 300 hours = 30 hours

3750 Hours

4050 Hours

(within 10% tolerance)

4050 Hours

10% of 300 hours = 30 hours

4050 Hours

4350 Hours

(tolerance not applied)

Calendar Example (10% or up to a maximum of 6 months calendar time, whichever is less):

12-MONTH

NEXT 12-MONTH

MAXIMUM ALLOWED

INSPECTION CARRIED

INSPECTION

TOLERANCE

OUT ON:

DUE ON:

June 10, 2010

10% of 12 months = 1.2 months

July 8, 2010

July 31, 2011

(within 10% tolerance)

July 31, 2011

10% of 12 months = 1.2 months

June 15, 2011

June 30, 2012

(completed early)

June 30, 2012

10% of 12 months = 1.2 months

June 30, 2012

June 30, 2013

(tolerance not applied)

NOTE:

Date of the first 12-Month Inspection carried out.

The last day of the month applies for the next inspection (paragraph 5-5, calendar time). For inspection

intervals that are measured in days rather than months, the calendar time ends on the day that the time limit

expires on, not the end of the month.

Hourly/Calendar Example (10% or up to a maximum of 300 hours operating time/6 months calendar time,

whichever is less):

1200-HOUR/

NEXT 1200-HOUR/

24-MONTH

MAXIMUM ALLOWED

INSPECTION CARRIED

24-MONTH

INSPECTION

TOLERANCE

OUT AT:

INSPECTION

DUE AT:

3400 Hours/

10% of 1200 hours = 120 hours

3400 Hours/July 30, 2010

4600 Hours/

June 30, 2010

(within 6 months calendar

July 31, 2012₁

10% of 24 months = 2.4 months

tolerance)

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Page 9

BHT-212-MM-1

Hourly/Calendar Example (10% or up to a maximum of 300 hours operating time/6 months calendar time,

whichever is less): (Cont)

1200-HOUR/

NEXT 1200-HOUR/

24-MONTH

MAXIMUM ALLOWED

INSPECTION CARRIED

24-MONTH

INSPECTION

TOLERANCE

OUT AT:

INSPECTION

DUE AT:

4600 Hours/

10% of 1200 hours = 120 hours

4700 Hours/April 2, 2012

5900 Hours/

July 31, 2012

(within 120 hours tolerance)

April 30, 2014

10% of 24 months = 2.4 months

5900 Hours/

10% of 1200 hours = 120 hours

5980 Hours/May 3, 2014

7180 Hours/

April 30, 2014

(within 120 hours and 2.4

May 31, 2016

10% of 24 months = 2.4 months

month calendar tolerance)

NOTE:

The last day of the month applies for the next inspection (paragraph 5-5, calendar time). For inspection

intervals that are measured in days rather than months, the calendar time ends on the day that the time limit

expires on, not the end of the month.

Hourly/Calendar Example (10% or up to a maximum of 300 hours operating time/6 months calendar time,

whichever is less):

5000-HOUR/

NEXT 5000-HOUR/

5 YEAR

MAXIMUM ALLOWED

INSPECTION CARRIED

5 YEAR

INSPECTION

TOLERANCE

OUT AT:

INSPECTION

DUE AT:

6000 Hours/

10% of 5000 hours = 500 hours

6000 Hours/January 15, 2011

9000 Hours/

December 31,

(maximum allowed is 300 hours)

(within 6 months calendar

January 31,

2010

tolerance)

2016

10% of 60 months = 6 months

9000 Hours/

10% of 5000 hours = 500 hours

9100 Hours/January 2, 2016

12,100 Hours/

January 31,

(maximum allowed is 300 hours)

(within 300 hours tolerance)

January 31,

2016

2021

10% of 60 months = 6 months

12,100 Hours/

10% of 5000 hours = 500 hours

12,175 Hours/February 20,

15,175 Hours/

January 31,

(maximum allowed is 300 hours)

2021

February 28,

2021

(within 300 hour and 6

2026

10% of 60 months = 6 months

months calendar tolerance)

NOTE:

The last day of the month applies for the next inspection (paragraph 5-5, calendar time). For inspection

intervals that are measured in days rather than months, the calendar time ends on the day that the time limit

expires on, not the end of the month.

5-00-00

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Export Classification C, ECCN EAR99

BHT-212-MM-1

SCHEDULED INSPECTIONS

5-8.

DAILY INSPECTION - PART A

DATA

INITIAL

INSPECTION TASK DESCRIPTION

REFERENCE

MECH OTHER

DATE:

__________________

W.O.

______________________

FACILITY:

__________________________________________

HELICOPTER S/N:

___________________________________

REGISTRY NO.:

_____________________________________

TOTAL TIME:________________________________________

SIGNATURE:________________________________________

NOTE

For helicopters on the Part A inspection program,

accomplish the following checks daily before flight

operation.

GENERAL

Each listed inspection item or maintenance function is to be

performed in accordance with the referenced Maintenance

Manual or BHT-212-CR&O manual chapter specified.

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

Maintenance Manual for engine inspection requirements.

PRELIMINARY REQUIREMENTS

Corrosion Control

Use medium helicopter corrosion control guide to establish

Guide,

helicopter corrosion control program.

CSSD-PSE-87-001

Chapter 4

Replace all finite life components that have completed

published operating limitations.

Chapter 5

Overhaul all components that have completed published

overhaul periods.

Chapter 12

Lubricate and service helicopter as required.

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Chapter 5

Review Special Inspections and carry out applicable

inspections.

Examine all inspection windows and sight glasses for

cracking, crazing, and discoloration. If any of these conditions are

present the part must be removed and replaced prior to returning

helicopter for service.

Service Instructions

Make sure that all required inspections of installed BHT kits

(SI)

are not covered in this inspection have been performed, as

applicable.

Chapter 21

BLEED AIR HEATING SYSTEM COMPONENTS

Visually inspect heater compartment for cleanliness,

condition, and security of heating system components, wiring,

ducts, supports, and structure for damage and corrosion.

Visually inspect overhead ventilating system components for

condition and security.

Visually inspect heat/vent air ducts for condition and

security.

Visually inspect ventilation/defog components for condition

and security.

Chapter 25

CREW/PASSENGER SEATS

Visually inspect crew seats for condition, security, and

operation.

Visually inspect crew seats restraints for condition, security,

and operation.

Visually inspect passenger seats for condition and security.

Visually inspect passenger seats restraints for condition and

security.

Chapter 25

MISCELLANEOUS FURNISHINGS

Visually inspect miscellaneous furnishings (map and data case,

first aid kit, and emergency equipment) for condition and security.

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Chapter 26

FIRE EXTINGUISHERS

Visually inspect cockpit and cabin portable fire extinguishers and

engine compartment fire extinguisher containers for security and

condition.

Chapter 28

FUEL SYSTEM

Visually inspect fuel samples for contamination.

Chapter 29

HYDRAULIC SYSTEMS

Visually inspect the following:

a. Hydraulic system 1 and 2 filter bypass indicator buttons

- not extended.

b. Collective and cyclic servo actuators and boost tubes for

leaks, damage, and security.

c. Hydraulic system 1 and 2 pumps for leaks, damage, and

security.

d. Hydraulic system 1 and 2 valve and filter modules for

leaks, damage, and security.

e. Hydraulic system 1 and 2 lines, hoses, and fittings for

leaks, damage, chafing, kinking, and security.

f. Hydraulic system 1 and 2 reservoirs for proper fluid

levels, damage, corrosion, and security.

g. Tail rotor hydraulic actuator and hoses for leakage,

corrosion, and security.

Remote hydraulic filter bypass indicator (located in right

nose window) - confirm not tripped.

Chapter 30

WINDSHIELD WIPER

Visually inspect windshield wiper blades for serviceability and

security.

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Chapter 32

LANDING GEAR SYSTEM

Visually inspect landing gear as follows:

a. Forward crosstube assembly and retention caps for

condition and security of attachment.

b. Aft crosstube assembly and retention caps for condition

and security of attachment.

c. Skid tubes and skid shoes for condition and security of

attachment. Replace skid shoes that are worn into shoe surface.

Repair weld beads as required.

d. Fuselage supports for wear, damage, and security of

attachment.

e. If installed, landing gear forward crosstube crew step

fittings for corrosion, damage, and security in area of attachment.

f. Emergency float reservoir pressure indicator for proper

charge indication (if installed).

g. Floats for proper stowage and condition (if installed).

Visually inspect tail skid for deformation and security of

attachment.

Chapter 52

DOORS, WINDOWS, AND EMERGENCY EXIT

Visually inspect nose door for obvious damage, security of

attachment, proper latching, and seal for condition.

Visually inspect all windows for damage. Crew door

windows, cargo hinged door window, passenger sliding door

windows, cabin roof windows, cabin lower nose windows and

windshields.

Visually inspect crew door emergency release pins for

security.

Visually inspect crew and cabin doors for condition, security,

and freedom of operation.

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Visually inspect avionics/electrical and heater compartment

doors for condition and security of attachment. Latches for proper

operation.

Chapter 53

FUSELAGE

- General Visual Inspection

Fuselage exterior for condition and damage to protective

finish.

Fuselage underside for evidence of fuel and hydraulic fluid

leakage.

All cowlings and fairings for condition and security, missing

fasteners, cracks, and proper operation of latches.

Inspect tailboom fuselage attachment points for security.

Pitot tube(s) and static ports for obstruction and damage.

Fuselage interior for evidence of water entrapment.

a. Nose compartment.

b. Pilot and passenger cabin.

c. Electrical compartment.

d. Heater compartment.

e. Baggage compartment.

Chapter 53

TAILBOOM

Inspect tailboom exterior structure for general condition.

Chapter 52

Inspect baggage compartment interior for condition and

cleanliness.

Check baggage compartment door for damage, proper

operation, and security.

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Inspect driveshaft and intermediate gearbox covers for

damage and security.

Chapter 62

MAIN ROTOR BLADES

- Detailed Visual Inspection

Main rotor blades for condition, damage, security, and

cleanliness.

Chapter 62

MAIN ROTOR HUB

- Detailed Visual Inspection

Main rotor hub assembly (grips, drag braces, trunnion, pillow

blocks, static stops, and mast nut) for condition and security.

Hub assembly for proper oil level or grease lubrication.

Main rotor yoke for evidence of cracks at pillow block bushing

bores. Proper sealing of pillow blocks, yoke, and attaching through

bolts, washers, nuts, and bushings.

Inspect blade retention bolts for condition and security.

Chapter 62

MAIN ROTOR CONTROLS

- Detailed Visual Inspection

Swashplate and support assembly and collective lever for

condition and security.

Scissors and sleeve assembly for security and condition.

Pitch links, damper tubes, and connecting links for condition

and security. Bearings for looseness.

Stabilizer bar assembly for condition and security.

Stabilizer bar dampers for condition, security, and proper fluid

level.

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Chapter 63

ENGINE-TO-TRANSMISSION MAIN DRIVESHAFT

Visually inspect main driveshaft for condition and security.

WARNING

CAUSE OF ANY DISCOLORATION SHALL BE

DETERMINED AND CORRECTED PRIOR TO NEXT

FLIGHT.

Visually inspect main driveshaft forward and aft couplings,

boots, seals, and surrounding area for grease leakage, damage,

corrosion, and evidence of overheat as indicated by

TEMP-PLATES or coupling discoloration. A change in color of any

yellow bordered TEMP-PLATE, from white/off-white to black, will

indicate a possible overheat condition and/or component

degradation (step 3). If one or more of the red bordered

TEMP-PLATE dots change from white/off-white to black, an

overheat condition is present and may require replacement of both

outer and inner couplings.

Visually inspect overheat TEMP-PLATES for condition and

security. TEMP-PLATES must not show evidence of

overtemperature indication, deterioration, debonding, or

excessive discoloration of the epoxy overcoating.

Chapter 63

MAIN ROTOR MAST

- Detailed Visual Inspection

Mast assembly for security, corrosion, and mechanical

damage. Pay particular attention to area contacted by main rotor

static stops and damper assembly/adapter set splines.

Mast nut for security.

Inspect lower area for evidence of oil leaks at mast bearing

cap.

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Chapter 63

TRANSMISSION

- General Visual Inspection

External oil filters bypass indication.

Proper oil level.

Transmission cases for damage, condition, and evidence of

leaking.

Accessories for condition, damage, and security of

attachment.

Information Letter

External oil lines and hoses for condition, damage, chafing,

212-00-34

and leaks, paying particular attention to lines running aft of the

thermostatic relief valve.

Transmission mount dust boots for condition.

WARNING

CAUSE OF ANY DISCOLORATION SHALL BE

DETERMINED AND CORRECTED PRIOR TO NEXT

FLIGHT.

Transmission tail rotor output quill coupling and surrounding

area for grease leakage, damage, corrosion, and evidence of

overheat as indicated by TEMP-PLATES or coupling

discoloration. A change in color of one or more of the red

bordered TEMP-PLATE dots from white/off-white to black,

indicates an overheat condition, and may require replacement of

both outer and inner couplings (step 8).

Overheat TEMP-PLATES for condition and security.

TEMP-PLATES must not show evidence of overtemperature

indication, deterioration, debonding, or excessive discoloration of

the epoxy overcoating.

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Chapter 63 and

ROTOR BRAKE QUILL AND DISC ASSEMBLY

SI 212-6

- Detailed Visual Inspection

Rotor brake quill for condition, damage, and leaking.

Rotor brake for condition, damage, and leaking.

Rotor brake disc for warpage.

Chapter 63

TRANSMISSION, ENGINE, AND COMBINING GEARBOX OIL

COOLING

- Detailed Visual Inspection

Oil coolers for leaking, damage, and obstruction.

Oil cooler hoses and tubes for leaking, damage, chafing, and

fraying.

Oil cooler blowers for damage and obstruction.

Chapter 64

TAIL ROTOR HUB AND BLADE ASSEMBLY

- Detailed Visual Inspection

WARNING

NO CRACKS ARE PERMITTED ON ANY SURFACE

OF THE TAIL ROTOR BLADES.

Tail rotor blades for condition of bond lines, cracks,

corrosion, leading edge erosion, damage, security, and

cleanliness. Clean blades are required to maintain enhanced

visibility for safety.

Tail rotor hub for security, corrosion, and condition.

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Flapping bearings and pitch change bearings for excessive

looseness and freedom of movement through full range of travel

with anti-torque pedals positioned full right and then full left.

Tail rotor pitch change links, crosshead, pitch horns,

counterweight arms, and links for security, corrosion, and

condition.

Pitch link bearing and counterweight link bearing looseness

shall not exceed 0.015 inch (0.381 mm) axial. Check freedom of

movement through full range of travel with anti-torque pedals

positioned full right nd then full left.

Pitch change links for binding with tail rotor blade moved to

both full flapping positions. Binding is not acceptable.

Chapter 65

TAIL ROTOR DRIVESHAFT

Hanger assemblies - bearings and surrounding areas for

evidence of grease leakage, condition, damage, security,

corrosion, and overheating. Discoloration of bearing (color

change to blue to blue/black in color) or multi-color appearance of

hanger that darkens adjacent to bearing is evidence of

overheating. Brown color of bearing shield is normal and is not

evidence of overheating.

Driveshaft sections for cracks, rivet failure, distortion, dents,

corrosion, and damage to anodized finish.

Clamp sets for condition, security, and proper installation.

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WARNING

CAUSE OF ANY DISCOLORATION SHALL BE

DETERMINED AND CORRECTED PRIOR TO NEXT

FLIGHT.

Flexible couplings and surrounding areas for grease

leakage, damage, corrosion, and evidence of overheat as

indicated by TEMP-PLATES or coupling discoloration. A change

in color of one or more of the red bordered TEMP-PLATE dots

from white/off-white to black indicates an overheat condition and

may require replacement of both outer and inner couplings

(step 5).

Overheat TEMP-PLATES for condition and security.

TEMP-PLATES must not show evidence of over temperature

indication, deterioration, debonding, or excessive discoloration of

the epoxy overcoating.

Chapter 65

INTERMEDIATE GEARBOX

- Detailed Visual Inspection

Gearbox assembly for security, condition, corrosion,

damage, and oil leaking.

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WARNING

CAUSE OF ANY DISCOLORATION SHALL BE

DETERMINED AND CORRECTED PRIOR TO NEXT

FLIGHT.

Input and output quill flexible couplings and surrounding

area for grease leakage, damage, corrosion, and evidence of

overheat as indicated by TEMP-PLATES or coupling

discoloration. A change in color of one or more of the red

bordered TEMP-PLATE dots from white/off-white to black

indicates an overheat condition and may require replacement of

both outer and inner couplings (step 3).

Overheat TEMP-PLATES for condition and security.

TEMP-PLATES must not show evidence of over temperature

indication, deterioration, debonding, or excessive discoloration of

the epoxy overcoating.

Gearbox for proper oil level and oil for evidence of

contamination.

Deleted.

Chapter 65

TAIL ROTOR GEARBOX

- Detailed Visual Inspection

Gearbox assembly for security, condition, corrosion,

damage, and oil leaking.

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WARNING

CAUSE OF ANY DISCOLORATION SHALL BE

DETERMINED AND CORRECTED PRIOR TO NEXT

FLIGHT.

Input quill flexible coupling and surrounding area for grease

leakage, damage, corrosion, and evidence of overheat as

indicated by TEMP-PLATES or coupling discoloration. A change

in color of one or more of the red bordered TEMP-PLATE dots

from white/off-white to black indicates an overheat condition and

may require replacement of both outer and inner couplings.

Overheat TEMP-PLATES for condition and security.

TEMP-PLATES must not show evidence of overtemperature

indication, deterioration, debonding, or excessive discoloration of

the epoxy overcoating.

Gearbox for proper oil level and oil for evidence of

contamination.

Chapter 67

ELEVATORS

- Detailed Visual Inspection

Elevators for damage and security.

Chapter 71

LEFT POWER SECTION

- Detailed Visual Inspection

Gas generator case for cracks, buckled areas, and hot

spots.

Oil and fuel hoses and tubes for chafing, leaking, and

security.

Electrical wiring for fraying, chafing, and security.

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Helicopter Bell-212. MAINTENANCE MANUAL (2021) - page 1