Page 1
BHT-206L3-MM-1
32672)),&(%2;)257:257+7(;$6
COPYRIGHT NOTICE
COPYRIGHT
201
BELL
®
HELICOPTER TEXTRON INC.
AND BELL HELICOPTER TEXTRON
CANADA LTD.
ALL RIGHTS RESERVED
MAINTENANCE MANUAL
GENERAL INFORMATION
The instructions set forth in this manual, as supplemented or modified by Alert Service Bulletins (ASB) or
other directions issued by Bell Helicopter Textron Inc. and Airworthiness Directives (AD) issued by the
applicable regulatory agencies, shall be strictly followed.
Maintenance Manual also applicable to 206L3+ helicopters (Increased Gross Weight kit 206-706-530
installed per BHT-206-SI-2052).
Export Classification C, ECCN EAR99
VOLUME 1
NOTICE
REISSUE — 27 AUGUST 1992
REVISION 24 — 25 JUNE 2019
Page 2
BHT-206L3-MM-1
PROPRIETARY RIGHTS NOTICE
These data are proprietary to Bell Helicopter 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 Helicopter 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.
Additional copies of this publication may be obtained by contacting:
PN Rev. 24 25 JUN 2019
Commercial Publication Distribution Center
Bell Helicopter Textron Inc.
P. O . B o x 4 8 2
Fort Worth, Texas 76101-0482
Export Classification C, ECCN EAR99
Page 3
WARNING
THIS MANUAL APPLIES ONLY TO HELICOPTERS AND COMPONENTS
MAINTAINED IN ACCORDANCE WITH BELL HELICOPTER TEXTRON
(BELL) APPROVED PROCEDURES USING BELL APPROVED PARTS.
ALL INSPECTION, REPAIR AND OVERHAUL PROCEDURES PUBLISHED
BY BELL, INCLUDING PART RETIREMENT LIFE, ARE BASED SOLELY ON
THE USE OF BELL PARTS THAT HAVE BEEN MAINTAINED USING BELL
APPROVED DATA. THE DATA PUBLISHED HEREIN OR OTHERWISE
SUPPLIED BY BELL IS NOT APPLICABLE TO NON-BELL PARTS OR
PARTS THAT HAVE BEEN REPAIRED USING DATA AND/OR PROCESSES
NOT APPROVED BY BELL.
BELL IS NOT RESPONSIBLE FOR ANY PART OTHER THAN THOSE THAT
IT HAS APPROVED.
BEFORE PERFORMING ANY PROCEDURE CONTAINED IN THIS MANUAL
YOU MUST INSPECT THE AFFECTED PARTS AND RECORDS FOR
EVIDENCE OF ANY MANUFACTURE, REPAIR, REWORK OR USE OF A
PROCESS NOT APPROVED BY BELL.
IF YOU IDENTIFY OR SUSPECT THE USE OF PARTS NOT AUTHORIZED
BY BELL, EITHER REMOVE THE AFFECTED ITEM FROM THE AIRCRAFT
OR OBTAIN INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FROM
THE MANUFACTURER OR THE ORGANIZATION THAT APPROVED THE
REPAIR.
BHT-206L3-MM-1
Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 Warning
Page 4
BHT-206L3-MM-1
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:
CUSTOMER SUPPORT AND SERVICES
Model 206, 407, or 505
Phone: 450-437-2862 or 800-363-8023 (U.S./Canada)
Fax: 450-433-0272
E-mail: productsupport@bellflight.com
Model 222, 230, 427, 429, or 430
Phone: 450-437-2077 or 800-463-3036 (U.S./Canada)
Fax: 450-433-0272
E-mail: productsupport@bellflight.com
Model 204, 205, 212, or 412
Phone: 450-437-6201 or 800-363-8028 (U.S./Canada)
Fax: 450-433-0272
E-mail: productsupport@bellflight.com
Model 210, HUEY II, and All Bell’s Active and
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
Military
Phone: 817-280-3548
Fax: 817-280-2635
E-mail: mts-light@bellflighth.com
Surplus
Surplus
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 http://www.bellflight.com/support-and-service/support.
CSS Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Page 5
BHT-206L3-MM-1
LOG OF REVISIONS
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
page with only a vertical line next to the page number indicates that text has shifted or that non-technical
correction(s) were made on that page.
Original ........ 0 ........... 01 AUG 82
Revision....... 1 ........... 01 MAR 83
Revision....... 2............30 APR 83
Revision....... 3 .............16 JUL 84
Revision....... 4 ........... 07 MAR 85
Revision....... 5............15 APR 87
Reissue........ 0 ............ 01 JAN 90
Reissue........ 0........... 27 AUG 92
Revision....... 1 .............21 JUL 93
Revision....... 2............23 APR 01
Revision....... 3 ............15 MAY 02
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Cover .......................................24
Title ..........................................24
PN ............................................24
Warning....................................24
CSS..........................................24
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Help..........................................20
Customer Feedback.................24
Helicopter Sales Notice............24
Warranty...................................24
BR ............................................24
TR ............................................24
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Revision ...... 5............22 DEC 03
Revision ...... 6............. 07 JUL 06
Revision ...... 7............ 30 APR 08
Revision ...... 8............ 06 APR 09
Revison ....... 9............ 26 MAY 09
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Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 A
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Cover .......................................22
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1/2 ............................................22
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VOLUME 8
Cover .......................................22
Title ..........................................22
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Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 C
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BHT-206L3-MM-1
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D Rev. 24 25 JUN 2019 Export Classification C, ECCN EAR99
Page 9
H
ELP
E
VALUATE
L
OGISTICS
P
UBLICATIONS
Have you found something wrong with this manual — an
error, an inconsistency, unclear instructions, etc.? Although
we strive for accuracy and clarity, we may make errors on
occasion. If we do and you discover it, we would appreciate
your telling us about it so that we can change whatever is
incorrect or unclear. Please be as specific as possible.
Your complaint or suggestion will be acknowledged and we
will tell you what we intend to do.
You may use the enclosed Customer Feedback form, as
applicable, to inform us where we have erred.
Your assistance is sincerely appreciated.
Export Classification C, ECCN EAR99
Page 10
Page 11
CUSTOMER FEEDBACK
RETURN VIA FAX TO PRODUCT SUPPORT ENGINEERING (450) 433-0272
Manual Title: ___________________________________________________________
Manual Number (if assigned): _____________________________________________
Date of Issue: ___________________________________________________________
Date of Last Revision: ___________________________________________________
Section, Chapter, Paragraph Affected: ______________________________________
Your Feedback: ________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
Now Reads: ____________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
Should Read: ___________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
Your Name: _____________________________________________________________
Address: _______________________________________________________________
Export Classification C, ECCN EAR99
Page 12
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12,800 rue de l’Avenir
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TAPE HERE
Export Classification C, ECCN EAR99
Page 13
IMPORTANT
HELICOPTER SALES NOTICE
Please complete this form and return by mail, e-mail (publications@bHOOIOLJKW.com), or fax
(817-280-6466, Attention: CPDC). This will ensure that the new owners/operators receive
updates to their BellHelicopter Textron Technical Manuals and Bulletins.
Model of Helicopter Sold or Purchased ___________________________________________
Serial and Registration Number _________________________________________________
Name of New Owner (company or individual) ______________________________________
Name of New Operator _______________________________________________________
Future Publications to be mailed to this address:
Address ____________________________________________________________________
City _______________________________________________________________________
State/Province _______________________________________________________________
Zip/Postal Code _____________________________________________________________
Country ____________________________________________________________________
Fax No. ___________________________ Telephone No. ____________________________
E-mail Address ______________________________________________________________
Register for access to electronic publications at www.bellIOLJKW.FRP
Export Classification C, ECCN EAR99
Export Classification C, ECCN EAR99
Page 14
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Export Classification C, ECCN EAR99
Page 15
BHT-206L3-MM-1
SPARE PARTS WARRANTY
ONE YEAR/1,000 HOURS PRORATED
WARRANTY AND REMEDY: 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. Seller’s sole obligation under this
warranty is limited to replacement or repair of parts which are determined to Seller’s reasonable satisfaction to have been defective
with 1,000 hours of operation or one (1) year after installation, whichever occurs first and reimbursement of reasonable freight charges.
After 200 hours of use, there will be a prorated charge to the Purchaser for replacement parts (prorating the hours of total use against
the then applicable part life or 2,000 hours, whichever is the lesser). Defective parts must be reported in writing to the Seller’s Warranty
Administration within 90 days of being found defective. Replacement of parts may be with either new or reconditioned parts, at Seller’s
election. Warranty adjustment is contingent upon the Purchaser complying with the Warranty Remedies as described in the
Commercial Warranty Information brochure and the Seller’s Warranty Administration disposition instructions for defective parts. Failure
to comply with all of the terms of this paragraph may, at Seller’s sole option, void this warranty.
NOTE: Parts, components and assemblies of all new helicopters may have been restored or reworked due to mars, blemishes, dents
or other irregularities during the manufacturing process. Such restoration and/or rework is permitted under Seller’s approved
manufacturing and engineering processes and guidelines. The restoration and/or rework so completed does not render such items
defective in material or workmanship.
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 MERCHANT ABILITY AND
FITNESS FOR A PARTICULAR PURPOSE AND (ii) ANY OBLIGATION, LIABILITY, RIGHT, CLAIM OR REMEDY IN CONTRACTOR
IN TORT (DELICT), INCLUDING PRODUCT LIABILITIES BASED UPON STRICT LIABILITY, NEGLIGENCE, OR IMPLIED
WARRANTY IN LAW.
This warranty is the only warranty made by Seller. The Purchaser’s sole remedy for a breach of this warranty or any defect in a part is
the repair or replacement of helicopter parts and reimbursement of reasonable freight charges as provided herein. 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 (delict), including, without limitation, negligence and strict tort
(delictual) liability, with respect to work performed by third parties at Purchaser’s request and with respect to engines, engine
accessories, batteries, radios, and avionics, except Seller assigns each manufacturer’s warranty to Purchaser to the extent such
manufacturer’s warranty exists and is assignable.
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 judgment, to affect its stability, safety or reliability, or which has been subject to misuse, negligence or accident, or which has
been installed in any aircraft which has been destroyed unless that helicopter has been rebuilt by Bell. A list of destroyed aircraft is
obtainable from Bell Product Support. 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, 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 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 CUSTOMER SERVICE FACILITIES MAY BE TAKEN AS A WARRANTY NOR WILL IT BIND SELLER.
Seller makes no warranty and disclaims all liability with respect to components or parts damaged by, or worn due to, corrosion. Seller
makes no warranty and disclaims all liability for consumables (wear items) 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.
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
Purchaser 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 Purchaser shall indemnify Seller for all costs, expenses and attorneys’ fees incurred by Seller in defense of such claims. In
the event Purchaser 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 Purchaser shall indemnify Seller for all costs, expenses and
attorneys’ fees incurred by Seller in obtaining such dismissal or transfer.
January 2007
Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 Warranty
Page 16
Page 17
TC APPROVED BHT-206L3-MM-1
TABLE OF CONTENTS
Paragraph Chapter/Section Page
Number Title Number Number
FIGURES
Figure Page
Number Title Number
TABLES
Table Page
Number Title Number
The Airworthiness Limitations Schedule is approved by the Minister and specifies the maintenance required by
any applicable airworthiness or operational rules unless an alternative program has been approved by the
Minister.
CHAPTER 4 — AIRWORTHINESS LIMITATIONS SCHEDULE
AIRWORTHINESS LIMITATIONS SCHEDULE
4-1 Airworthiness Limitations Schedule ............................................... 4-00-00 5
4-1 Tailboom Upper Left Attachment Fitting (206-032-409-001)
— Recurring 110-Hour Inspection ...................................................................... 13
4-1 Airworthiness Limitations Schedule .................................................................... 6
4-2 Inspection Limitations Schedule ......................................................................... 12
Chief Engineering
Aircraft Certification
Transport Canada
Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 Page 1
4-00-00
Page 18
BHT-206L3-MM-1 TC APPROVED
REVISION NO. DATE OF SIGNATURE APPROVAL SIGNATURE
Original N/A N/A
Reissue N/A N/A
Reissue 27 August 1992
1N/A N/A
2N/A N/A
3N/A N/A
4 09 December 2002
5 22 December 2003
6N/A
7 30 October 2007
N/A
4-00-00
Page 2 Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Page 19
TC APPROVED BHT-206L3-MM-1
REVISION NO. DATE OF SIGNATURE APPROVAL SIGNATURE
8 20 August 2008
9 26 May 2009
10 N/A N/A
11 25 September 2009
12 N/A
13 N/A
14 N/A
15 N/A
16 N/A N/A
N/A
N/A
N/A
N/A
17 8 April 2011
Export Classification C, ECCN EAR99
4-00-00
25 JUN 2019 Rev. 24 Page 3
Page 20
BHT-206L3-MM-1 TC APPROVED
REVISION NO. DATE OF SIGNATURE APPROVAL SIGNATURE
18 29 February 2012
19 1 June 2012
20 7 November 2012
21 N/A
22 N/A
23 N/A
24 25 JUNE 2019
N/A
N/A
N/A
4-00-00
Page 4 Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Page 21
TC APPROVED BHT-206L3-MM-1
AIRWORTHINESS LIMITATIONS SCHEDULE
4-1. AIRWORTHINESS LIMITATIONS
SCHEDULE
WARNING
ALL REPAIR AND OVERHAUL
PROCEDURE LIVES PUBLISHED BY
BELL HELICOPTER TEXTRON,
INCLUDING COMPONENT RETIREMENT
LIFE, ARE BASED SOLELY ON THE USE
OF BELL APPROVED PARTS AND
PROCESSES. IF PARTS OR
PROCESSES DEVELOPED OR
APPROVED BY PARTIES OTHER THAN
BELL HELICOPTER ARE USED, THEN
THE DATA PUBLISHED OR OTHERWISE
SUPPLIED BY BELL HELICOPTER ARE
NOT APPLICABLE. THE USER IS
WARNED TO NOT RELY ON BELL
HELICOPTER DATA FOR PARTS AND
PROCESSES NOT APPROVED BY BELL
HELICOPTER. ALL APPLICABLE
INSPECTIONS AND REPAIR METHODS
MUST BE OBTAINED FROM THE
SUPPLIER OF THE PARTS OR
PROCESSES NOT APPROVED BY BELL
HELICOPTER. BELL HELICOPTER IS
NOT RESPONSIBLE FOR PARTS OR
PROCESSES OTHER THAN THOSE
WHICH IT HAS ITSELF DEVELOPED OR
APPROVED.
WARNING
CONTINUED USE OF ANY TIME/
CALENDAR/RIN LIFE LIMITED
COMPONENT PAST ITS STATED LIMITS
IS NOT PERMITTED AS IT COULD
SERIOUSLY AFFECT THE
AIRWORTHINESS OF THE HELICOPTER.
THE COMPONENT MUST BE REMOVED
FROM THE HELICOPTER NOT LATER
THAN THE END OF THE LIFE LIMIT. IT
MUST EITHER BE MADE
UNSERVICEABLE OR MARKED IN A
CONSPICUOUS MANNER TO PREVENT
CONTINUED USE, EVEN INADVERTENT
USE.
WHEN A REPLACEMENT PART IS
INSTALLED, THE PART NAME, PART
NUMBER, SERIAL NUMBER, AND
CURRENT OPERATING HOURS, IF
APPLICABLE, MUST BE RECORDED IN
THE HISTORICAL SERVICE RECORD
FOR THE ASSEMBLY OR HELICOPTER.
NOTE
The requirements stated in Chapter 5 are to
be complied with and the appropriate
maintenance actions are to be performed.
NOTE
The airworthiness life or inspection interval
for any part number contained in this
schedule applies to all the successive dash
numbers for that component unless it is
otherwise specified.
The mandatory Airworthiness Limitations Schedule
(Tab le 4- 1) summarizes the 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 life. The Inspection Limitations Schedule
(Tab le 4- 2) summarizes the mandatory inspection
interval in hours.
Refer to the engine manufacturer’s publications for the
airworthiness limitations of the power plant
components.
Export Classification C, ECCN EAR99
4-00-00
25 JUN 2019 Rev. 24 Page 5
Page 22
BHT-206L3-MM-1 TC APPROVED
CAUTION
1
21
22
8
11
12
11
17
APPLICABLE SERVICE INSTRUCTION
WARNING
(SI) OR MAINTENANCE MANUAL
SUPPLEMENT (MMS) FOR KIT
COMPONENT SCHEDULES.
SOME PARTS ARE INSTALLED AS
ORIGINAL EQUIPMENT ON BOTH
MILITARY AND COMMERCIAL
HELICOPTERS AND MAY HAVE A
LOWER AIRWORTHINESS LIFE AND/OR
OVERHAUL SCHEDULE WHEN USED
ON A MILITARY HELICOPTER. IN
ADDITION, CIRCUMSTANCES
SURROUNDING THEIR USE MAY CALL
FOR OPERATION OF THE MILITARY
The retirement life given, or the failure to
give a retirement life to a component, does
not constitute a warranty of any kind. The
only warranty applicable to the helicopter or
any component is the warranty included in
the Purchase Agreement for the helicopter
or the component.
NOTE
HELICOPTER OUTSIDE OF THE
APPROVED COMMERCIAL FLIGHT
ENVELOPE. CONSEQUENTLY, PARTS
THAT HAVE BEEN USED ON MILITARY
HELICOPTERS SHOULD NOT BE USED
ON COMMERCIAL HELICOPTERS.
The airworthiness lives given to the components and
assemblies are determined by experience, tests, and
the judgment of Bell Helicopter engineers. The lives
cannot be changed without the approval of the
Minister of Transport Canada.
Prior to disposing of unsalvageable helicopter parts
and materials, caution should be exercised to ensure
that the parts and material are disposed of in a manner
that does not allow them to be returned for service.
AIRWORTHINESS LIFE OF SOME KIT
COMPONENTS IS NOT COVERED IN
THIS SCHEDULE. REFER TO
Refer to FAA Advisory Circular 21-38 for guidance on
the disposal of unsalvageable aircraft parts and
materials.
Table 4-1. Airworthiness Limitations Schedule
COMPONENT
PART NUMBER
AIRWORTHINESS LIFE
MAIN ROTOR HUB AND BLADES
Main Rotor Trunnion 206-011-120-103/-105 24,000 RIN
Strap Retention Pin 206-011-125-001 1200 hours
Main Rotor Grip 206-011-132-009/-113 4800 hours
Tension Torsion Strap 206-011-147-007 1200 hours/24 months
Strap Retention Fitting 206-011-150-101/-105 2400 hours
Tension Torsion Strap 206-011-154-103/-107 1200 hours/24 months
Latch Bolt 206-011-260-101 1200 hours
4-00-00
Page 6 Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
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TC APPROVED BHT-206L3-MM-1
1
13
31
38
31
39
24
37
25
37
26
9
21
23
14
10
Table 4-1. Airworthiness Limitations Schedule (Cont)
COMPONENT
PART NUMBER
AIRWORTHINESS LIFE
MAIN ROTOR HUB AND BLADES (CONT)
Main Rotor Blade 206-015-001-001/-103/-105/
4000 hours
-107/-109/-111/-113/-115/-117/
-119/-121
Main Rotor Blade 206-015-001-125/-127/-129/-131 2300 hours
Tension Torsion Strap 206-310-004-103 1200 hours/48 months
SWASHPLATE AND SUPPORT
Lower Cyclic Tube 206-001-193-001 4800 hours
Collective Idler Link 206-010-407-001 4800 hours
Swashplate Support Assembly 206-010-445-105 4800 hours
Swashplate Support Assembly 206-010-445-113 14,400 hours
Collective Idler Link 206-010-446-105 1200 hours
Collective Idler Link 206-010-446-107 14,400 hours
Collective Lever 206-010-447-105 1200 hours
Collective Lever 206-010-447-109 14,400 hours
Swashplate Support Assembly 206-010-452-109 4800 hours
Swashplate Support Assembly 206-010-452-113 Unlimited
Collective Sleeve Assembly 206-010-454-107/-109/-113 14,400 hours
Collective Lever 206-010-467-001/-105 4800 hours
POWER TRAIN
Tail Rotor Gearbox Duplex
206-040-410-003/-005/-101 3000 hours
Bearing
Main Rotor Mast 206-040-535-101/-105/-109 5000 hours/44,000 RIN
Sun Gear 206-040-662-101
Freewheel Assembly Clutch CL41742-1 3000 hours
Freewheel Assembly Clutch CL42250-1 3000 hours
TAIL ROTOR HUB AND BLADES
Tail Rotor Yoke 206-011-819-101/-105/-109 5000 hours
4-00-00
Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 Page 7
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BHT-206L3-MM-1 TC APPROVED
1
15321516303236
19
19
18
18
27
28
29
34
33
35
1
2
3
4
Table 4-1. Airworthiness Limitations Schedule (Cont)
COMPONENT
PART NUMBER
AIRWORTHINESS LIFE
TAIL ROTOR HUB AND BLADES (CONT)
Tail Rotor Blade 206-016-201-001/-107/-113 2400 hours
Tail Rotor Blade 206-016-201-127/-131/-135 2500 hours
AIRFRAME
Horizontal Stabilizer 206-023-119-167
MISCELLANEOUS KITS
Fixed Floats Landing Gear Aft
206-050-169-011/-013
Crosstube
Fixed Floats Landing Gear
206-050-169-031
Forward Crosstube
High Landing Gear Crosstube 206-053-109-ALL
Standard Landing Gear
206-053-119-ALL
Crosstube
Fixed Floats Landing Gear Aft
206-053-211-103
Crosstube
Emergency Floats Reservoir 1269556-3/-4 15 years
Emergency Floats Reservoir 1271226 15 years
Emergency Floats Squib 29022968
Emergency Floats Squib 94455
Hoist Cable Cutter Assembly Y-1265-11-1
POWER PLANT
Turboshaft Engine 250-C30P Refer to Rolls Royce 250-C30P Operation
and Maintenance Manual, 14W2
NOTES:
Airworthiness limitation for part number listed applies to all successive dash numbers for that component
unless otherwise specified.
Reserved.
Reserved.
Reserved.
4-00-00
Page 8 Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Page 25
TC APPROVED BHT-206L3-MM-1
567
8
9
10
11
12
13
14
15
16
17
18
19
20
Table 4-1. Airworthiness Limitations Schedule (Cont)
NOTES (CONT):
Reserved.
Reserved.
Reserved.
Selected serial numbers of main rotor grip 206-011-132-009 will have been removed from service upon
reaching 1200 hours in service. Refer to ASB 206L-80-15, dated 29 July 1980 for list of serial numbers
affected.
Selected serial numbers of main rotor mast 206-040-535-105 will have been returned to Bell Helicopter
Textron (BHT) for metallurgical evaluation no later than 31 May 1987. Affected masts inspected at BHT
and found to be acceptable have the suffix “U” added to the serial number. Refer to ASB 206L-87-44,
dated 23 April 1987 for list of serial numbers affected.
Selected serial numbers of tail rotor yoke 206-011-819-101 will have been returned to Bell Helicopter
Textron (BHT) for inspection and rework no later than 1 April 1988. Refer to ASB 206L-88-51, dated
23 April 1987 for list of serial numbers affected.
Main rotor hub tension torsion straps 206-011-147 and 206-011-154 have airworthiness lives of
1200 hours or 24 months, whichever occurs first. The calendar life of 24 months starts when new straps
are installed in a main rotor hub and blade assembly, and are subjected to rotation on the helicopter.
Refer to ASB 206L-80-12, dated 2 June 1980.
Selected serial numbers of main rotor hub tension torsion strap 206-011-147-007 must be removed from
service. Refer to ASB 206L-89-60, dated 29 August 1989 for list of serial numbers affected.
Selected serial numbers of main rotor blades 206-015-001-001/-103/-105 must be removed from service.
Refer to ASB 206L-89-64 Rev. A, dated 29 November 1989 for list of serial numbers affected.
Selected serial numbers of sun gear 206-040-662-101 must be removed from service. Refer to
ASB 206L-90-69 Rev. A, dated 15 January 1991 for list of serial numbers affected.
Selected serial numbers of tail rotor blades 206-016-201-113/-127 must be removed from service. Refer
to ASB 206L-90-70, dated 27 June 1990 for list of serial numbers affected.
Selected serial numbers of tail rotor blade 206-016-201-127 will have been returned to Bell Helicopter
Textron (BHT) for evaluation no later than 30 September 1990. Affected blades inspected at BHT and
found to be acceptable have the suffix “M” added to the serial number. Refer to ASB 206L-90-71 Rev. A,
dated 31 October 1990 for list of serial numbers affected.
Selected serial numbers of main rotor latch bolt 206-011-260-101 must be removed from service. Refer to
ASB 206L-92-86, dated 3 December 1992 for list of serial numbers affected.
Landing gear crosstubes 206-053-109-ALL and 206-053-119-ALL (all dash numbers) will have been
removed from service no later than 30 September 1994. Refer to ASB 206L-94-93, dated 11 April 1994.
Landing gear crosstubes 206-050-169-011/-031 will have been removed from service no later than
31 January 1995. Refer to ASB 206L-94-97, dated 17 August 1994.
Reserved.
4-00-00
Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 Page 9
Page 26
BHT-206L3-MM-1 TC APPROVED
21
22
23
24
25
26
27
28
29
30
31
Table 4-1. Airworthiness Limitations Schedule (Cont)
NOTES (CONT):
Each component with a retirement life sensitive to torque events will be assigned a maximum Retirement
Index Number (RIN). This RIN corresponds to maximum allowed fatigue damage resulting from lifts and
takeoffs. A torque event is defined as a takeoff (one takeoff plus subsequent landing = one RIN) or a lift
(internal or external). For example, if an operator performs six takeoffs and 10 slingloads, this would total
16 torque events; (6 takeoffs = 6 events, 10 slingloads = 10 events, 6 + 10 = 16 torque events total).
Pilots are to record total number of torque events for each flight. This allows maintenance personnel to
convert torque events to RIN by applying the appropriate RIN adjustment factor. Refer to ASB 206L-94-99
Rev. B, dated 10 August 2001. A new component will begin with an accumulated RIN of zero, that will be
increased as lifts and takeoffs are performed. Operator will record number of lifts and takeoffs (torque
events), and increase accumulated RIN accordingly. When maximum RIN is reached or retirement flight
hours, whichever occurs first, component will be removed from service.
The retirement life of trunnion 206-011-120-103/-105 is based solely on RIN. Retire trunnion when
RIN = 24,000. For each takeoff/lift, add one RIN if the trunnion is installed on 206L, 206L1, or 206L3
(includes 206L3 with Increased Power Operation kit installed per BHT-206-SI-2039) and two RIN if the
trunnion is installed on a 206L4 (also applicable to 206L3+ helicopters (Increased Gross Weight Upgrade
Kit 206-706-530 installed per BHT-206-SI-2052)). Refer to ASB 206L-94-99 Rev. B, dated
10 August 2001.
Retire main rotor mast 206-040-535-001/-005/-101/-105/-109 when RIN = 44,000. For each takeoff/lift,
add one RIN if the mast is installed on 206L, 206L1, or 206L3 (includes 206L3 with Increased Power
Operation kit installed per BHT-206-SI-2039) and two RIN if the mast is installed on a 206L4 (also
applicable to 206L3+ helicopters (Increased Gross Weight Upgrade Kit 206-706-530 installed per
BHT-206-SI-2052)). Refer to ASB 206L-94-99 Rev. B, dated 10 August 2001.
Collective idler link 206-010-446-105, serial numbers A-1 through A-27, inclusively, and serial numbers
RE-238 through and including RE-270 will be retired from service at 1200 hours service time. Refer to
ASB 206L-98-110, dated 6 May 1998.
Collective lever 206-010-447-105, serial numbers A-1 through A-22, inclusively, will be retired from
service at 1200 hours service time. Refer to ASB 206L-98-110, dated 6 May 1998.
Swashplate support assemblies 206-010-452-109 must be inspected every 50 hours after the swashplate
support has accumulated 1500 hours in service. Refer to ASB 206L-93-89 Rev. B, dated 4 April 1994.
Landing gear aft crosstube 206-053-211-103 has an airworthiness life of 33,000 landings. Refer to
ASB 206L-94-97, dated 17 August 1994.
Reservoir per DOT-3HT specification and Exemption Letter DOT-E-7218. Life starts from date of
manufacture.
Reservoir per DOT-3HT specification and Exemption Letter DOT-E-8162. This reservoir is a detail part of
reservoir assembly 206-073-848-121. Life starts from date of manufacture.
Tail rotor blade 206-016-201-127 and subsequent, retirement life increased to 2500 hours. Refer to
TB 206L-89-147, dated 2 June 1989.
Main rotor blades 206-015-001-ALL (all dash numbers). It is permissible to use any main rotor blade (mix
and match) on 206L, 206L1, 206L3, and 206L4 provided that all conditions are met. Refer to
TB 206L-87-142, dated 1 October 1987, and IL 206L-00-68 Rev. A or subsequent.
4-00-00
Page 10 Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Page 27
TC APPROVED BHT-206L3-MM-1
32
33
34
35
36
37
38
39
Table 4-1. Airworthiness Limitations Schedule (Cont)
NOTES (CONT):
Tail rotor blades 206-016-201-ALL (all dash numbers). It is permissible to use any tail rotor blade on 206L,
206L1, 206L3, and 206L4 provided that all conditions are met. Refer to TB 206L-94-167 Rev. A, dated
1 May 1995.
Part of squib assembly 30908. Retire squib no later than 15 years after date of manufacturing. Dispose of
time expired squib in accordance with local regulations.
Part of squib assembly 29022971 and approved alternate for squib 30908. Retire squib no later than
15 years after date of manufacturing. Dispose of time expired squib in accordance with local regulations.
Storage life of cutter assembly Y-1265-11-1, in original sealed container, is set at 60 months. Service life
is 36 months from the time the cutter assembly is removed from the original sealed container. The
36-month service life must be contained within the 60-month storage life. Dispose of time expired squib in
accordance with local regulations.
Example 1 – Cutter assembly stored for 24 months: 60 - 24 = 36-month service life.
Example 2 – Cutter assembly stored for 48 months: 60 - 48 = 12-month service life.
Example 3 – Cutter assembly stored for 1 month: 60 - 1 = 59 months, reduced to 36 months maximum
service life.
Affected horizontal stabilizer 206-023-119-167 must be removed from service no later than
30 September 2008. Refer to ASB 206L-06-141 for list of horizontal stabilizer serial numbers affected.
Applicable horizontal stabilizers must be inspected every 600 hours or annually until replaced. Refer to
ASB 206L-06-141 for inspection details.
Applicable to 206L3+ helicopters (Increased Gross Weight Upgrade Kit 206-706-530 installed per
BHT-206-SI-2052).
The airworthiness life of 4000 hours is only applicable to main rotor blades not affected by
ASB 206L-09-159 Rev. A, dated 13 November 2009, or subsequent. Refer to TCCA AD CF-2011-44 R1,
dated 1 February 2012, or subsequent for life applicable to blades affected by ASB 206L-09-159.
Main rotor hub tension torsion straps 206-310-004 have an airworthiness life of 1200 hours or 48 months,
whichever occurs first. The calendar life of 48 months starts when new straps are installed in a main rotor
hub and blade assembly, and are subjected to rotation on the helicopter.
4-00-00
Export Classification C, ECCN EAR99
25 JUN 2019 Rev. 24 Page 11
Page 28
BHT-206L3-MM-1 TC APPROVED
1
2
1
2
Table 4-2. Inspection Limitations Schedule
COMPONENT
Tailboom Upper Left Attachment
Fitting
NOTES:
Inspection limitation for the part number listed applies to all successive dash numbers for that
component unless otherwise specified.
You must do an inspection of the tailboom upper left attachment fitting 206-032-409-001 every
110 flight hours. Refer to ASB 206L-09-158 for a listing of affected tailbooms. Refer to Figure 4-1 for
inspection details.
PART NUMBER
206-032-409-001 110 hours
INSPECTION INTERVAL
(HOURS OPERATION TIME)
4-00-00
Page 12 Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Page 29
TC APPROVED BHT-206L3-MM-1
206LS_MM_04_0001+_c01
INSPECTION PROCEDURE:
1. Inspect upper left attachment fitting for cracks, mechanical damage, corrosion damage,
loose rivets, and general condition.
2. Refer to ASB 206L-09-158 for wear, damage, and repair limits.
3. Repair fitting in accordance with ASB 206L-09-158.
4. Replace cracked or damaged fitting or loose rivets in accordance with ASB 206L-09-158.
5. If a crack is found, contact Product Support Engineering .
(DETAILS OMITTED FOR CLARITY)
Figure 4-1. Tailboom Upper Left Attachment Fitting (206-032-409-001)
— Recurring 110-Hour Inspection
ECCN EAR99
25 JUN 2019 Rev. 24 Page 13/14
4-00-00
Page 30
Page 31
BHT-206L3-MM-1
TABLE OF CONTENTS
Paragraph Chapter/Section Page
Number Title Number Number
CHAPTER 5 — INSPECTIONS AND COMPONENT OVERHAUL SCHEDULE
INSPECTIONS
5-1 General .......................................................................................... 5-00-00 3
5-2 Items Not Covered and Inspection Responsibility ......................... 5-00-00 3
5-3 Crash Damage ............................................................................... 5-00-00 4
5-4 Types of Inspections ...................................................................... 5-00-00 4
5-5 Definitions ...................................................................................... 5-00-00 5
5-6 Inspection and Overhaul Tolerance ............................................... 5-00-00 6
SCHEDULED INSPECTIONS
5-7 Scheduled Inspections ................................................................... 5-00-00 7
5-8 Airframe Inspection Program .................................................... 5-00-00 7
5-9 Airframe Progressive Inspection Programs .............................. 5-00-00 7
5-10 100-Hour Airframe Progressive Inspection Program ................ 5-00-00 7
5-11 300-Hour Airframe Progressive Inspection Program ................ 5-00-00 8
5-12 Airframe Periodic Inspection Program ...................................... 5-00-00 9
5-13 100-Hour Airframe Periodic Inspection Program ...................... 5-00-00 9
5-14 300-Hour Airframe Periodic Inspection Program ...................... 5-00-00 9
5-15 Changing Inspection Program .................................................. 5-00-00 10
5-16 100-Hour Airframe Progressive Inspection — Event No. 1............ 5-00-00 17
5-17 100-Hour Airframe Progressive Inspection — Event No. 2............ 5-00-00 27
5-18 100-Hour Airframe Progressive Inspection — Event No. 3............ 5-00-00 33
5-19 100-Hour Airframe Progressive Inspection — Event No. 4............ 5-00-00 39
5-20 100-Hour Airframe Periodic Inspection .......................................... 5-00-00 47
5-21 300-Hour Airframe Progressive Inspection — Event No. 1............ 5-00-00 49
5-22 300-Hour Airframe Progressive Inspection — Event No. 2............ 5-00-00 55
5-23 300-Hour Airframe Progressive Inspection — Event No. 3............ 5-00-00 63
5-24 300-Hour Airframe Progressive Inspection — Event No. 4............ 5-00-00 69
5-25 300-Hour Airframe Progressive Inspection — Event No. 5............ 5-00-00 75
5-26 300-Hour Airframe Progressive Inspection — Event No. 6............ 5-00-00 83
5-27 300-Hour Airframe Periodic Inspection .......................................... 5-00-00 87
5-28 100-Hour Inspection....................................................................... 5-00-00 89
5-29 300-Hour Inspection....................................................................... 5-00-00 93
5-30 1000-Hour Inspection..................................................................... 5-00-00 101
5-31 1200-Hour Inspection..................................................................... 5-00-00 103
5-32 As Required by Manufacturer ........................................................ 5-00-00 109
5-33 Weekly Inspection .......................................................................... 5-00-00 111
5-34 12-Month Inspection ...................................................................... 5-00-00 113
5-35 12 Months of Component Operation .............................................. 5-00-00 115
5-36 24-Month Inspection ...................................................................... 5-00-00 117
5-37 60-Month Inspection ...................................................................... 5-00-00 121
5-38 300-Hour or 12-Month Inspection .................................................. 5-00-00 123
5-39 600 Hours of Component Operation .............................................. 5-00-00 125
5-40 600 Hours or 12 Months of Component Operation ........................ 5-00-00 127
5-41 1200 Hours of Component Operation ............................................ 5-00-00 129
Export Classification C, ECCN EAR99
15 MAY 2015 Rev. 22 Page 1
5-00-00
Page 32
BHT-206L3-MM-1
TABLE OF CONTENTS (CONT)
Paragraph Chapter/Section Page
Number Title Number Number
FIGURES
Figure Page
Number Title Number
TABLES
Table Page
Number Title Number
5-42 1500 Hours of Component Operation ............................................ 5-00-00 131
5-43 1500 Hours of Component Operation and Every 50 Hours
Thereafter ...................................................................................... 5-00-00 133
5-44 2250 Hours or 60 Months of Component Operation ...................... 5-00-00 135
5-45 3000 Hours of Component Operation ............................................ 5-00-00 137
SPECIAL INSPECTIONS
5-46 Special Inspections ........................................................................ 5-00-00 139
5-47 After Fuel System Maintenance and/or Component Change ........ 5-00-00 141
5-48 1 to 5 Hours After Each Installation ............................................... 5-00-00 145
5-49 3 to 8 Hours After Each Installation ............................................... 5-00-00 147
5-50 10 to 25 Hours After Each Installation ........................................... 5-00-00 149
5-51 100 Hours After Each Installation .................................................. 5-00-00 151
CONDITIONAL INSPECTIONS
5-52 Conditional Inspections .................................................................. 5-00-00 153
5-53 Hard Landing ................................................................................. 5-00-00 155
5-54 Sudden Stoppage/Acceleration ..................................................... 5-00-00 161
5-55 Overspeed Main Rotor — 114% or Greater................................... 5-00-00 169
5-56 Overtorque ..................................................................................... 5-00-00 173
5-57 Engine Compressor Stall or Surge ................................................ 5-00-00 179
5-58 Lightning Strike .............................................................................. 5-00-00 187
5-59 Engine Overtemp ........................................................................... 5-00-00 193
COMPONENT OVERHAUL SCHEDULE
5-60 Component Overhaul Schedule..................................................... 5-00-00 195
5-1 Maintenance Zones ............................................................................................ 15
5-2 Inspection of Main Rotor Flight Control Bolts/Nuts ............................................. 119
5-1 100-Hour Airframe Progressive Inspection Events ............................................. 7
5-2 300-Hour Airframe Progressive Inspection Events ............................................. 8
5-3 300-Hour Airframe Progressive or 300-Hour Airframe Periodic Inspection
Program Prerequisites ........................................................................................ 11
5-4 Component Overhaul Schedule .......................................................................... 195
5-00-00
Page 2 Rev. 22 15 MAY 2015
Export Classification C, ECCN EAR99
Page 33
INSPECTIONS
WARNING
NOTE
BHT-206L3-MM-1
5-1. GENERAL
This chapter contains the time limit intervals and the
requirements for the Scheduled Inspection, Special
Inspection, Conditional Inspection, and for the
Component Overhaul Schedule.
FAILURE TO CORRECT CONDITIONS
SUCH AS, BUT NOT LIMITED TO,
CORROSION, EROSION, MECHANICAL
DAMAGE, OR OBVIOUS WEAR FOUND
DURING A SCHEDULED INSPECTION
COULD SERIOUSLY AFFECT THE
AIRWORTHINESS OF THE HELICOPTER.
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
necessary. Make sure the helicopter is maintained
safely during all unusual local changes, such as
environmental conditions, helicopter use, etc. You can
request changes to the requirements in this chapter
through the local Aviation Authority.
Helicopter Textron or an approved Airworthiness
Authority.
Changes to the TBO will be introduced by either
revision to the Maintenance Manual, Chapter 5 or a
Technical Bulletin.
Every calendar and hourly inspection is a thorough
visual inspection to determine the airworthiness of the
helicopter and the components. Qualified persons
must do the inspections in accordance with quality
standard aircraft practices and the applicable
maintenance manuals. Bell Helicopter Textron
considers that it is mandatory to obey all the
applicable Alert Service Bulletins (ASB) and the
Airworthiness Directives (AD).
Component operating time records are necessary for
components that have scheduled maintenance
procedures, which are different from those of the
airframe. It is the owner/operator’s responsibility to
keep the Historical Service Records for the applicable
component and to do the necessary maintenance
procedures.
Before each inspection, remove or open the
necessary cowlings, fairing, inspection doors, and
panels.
The inspection intervals and the component overhaul
schedule provided in this chapter are applicable only
to Bell Helicopter Textron approved parts.
The time period given for the overhaul of a
component (or the failure to give a time
period for the overhaul of a component)
does not constitute a warranty of any kind.
The only warranty applicable to the
helicopter or any component is the
warranty included in the Purchase
Agreement for the helicopter or the
component.
The Time Between Overhaul (TBO) and the inspection
periods are determined through experience, tests,
Lead The Fleet (LTF), or any other special programs
and the judgement of Bell Helicopter Textron
engineers. They are subject to change only by Bell
Export Classification C, ECCN EAR99
5-2. ITEMS NOT COVERED AND
INSPECTION RESPONSIBILITY
This manual does not include the specific inspection
intervals for some components such as the compass
calibration and the pitot static test. These specific
inspection intervals are given by your government
regulatory authority. Refer to their requirements for
these specific inspections.
The owner/operator of the helicopter is responsible for
the maintenance done on the helicopter and for
ensuring that the specific time interval of any
inspection procedure is not exceeded. It is the owner/
operator’s responsibility to:
1. Establish, maintain, and review the log books for
discrepancies.
2. Make sure the Alert Service Bulletins (ASB), the
Airworthiness Directives (AD), and the special
5-00-00
15 MAY 2015 Rev. 22 Page 3
Page 34
BHT-206L3-MM-1
inspections are done when they are required to be
done.
3. Make sure the scheduled inspections, the special
inspections, and the required inspections for all of the
installed kits are complied with.
4. Make sure all parts and components for which
Historical Service Records are required have
documented traceability to their original installation in
the helicopter.
5. Make sure all limited life parts that have
completed their published operating limits are
replaced.
6. Make sure all of the components that have
completed their published overhaul periods are
overhauled.
7. Make sure all of the maintenance that is done on
the helicopter is done by an approved maintenance
organization.
The maintenance organization/person doing the
maintenance is responsible for the quality of the
maintenance done.
The owner/operator may choose to ask the
maintenance organization/person doing the
maintenance to perform the tasks listed by prior
arrangement through a separate formal agreement.
5-3. CRASH DAMAGE
a. Scheduled inspections must occur at specified
operating intervals. The intervals may be in operating
time (hours), cycles, torque events (RIN), calendar
(days, months, years) or other assigned units. This
makes sure that the helicopter is airworthy.
b. Special inspections are of a temporary nature
or of a special interval that is not consistent with the
scheduled inspections.
c. Conditional inspections do not occur at a
specified time. A conditional inspection is the result of
a known or suspected unusual event, known or
suspected malfunctions, or defects.
d. An interim inspection occurs between
overhauls.
e. The component overhaul schedule gives the
elapsed operating time at which a component must be
removed, disassembled, examined for condition, and
overhauled, in accordance with data approved by Bell
Helicopter Textron.
2. Lubrication and servicing requirements are in
addition to those stated in this chapter (Chapter 12).
3. For corrosion control, refer to the Corrosion
Control Guide, CSSD-PSE-87-001 and the
BHT-ALL-SPM.
4. For the 250-C30 series engine, refer to the
Rolls-Royce Operations and Maintenance Manual
(14W2) for the scheduled inspection, special
inspection, conditional inspection, and component
overhaul schedule.
Because of the many possible combinations that can
result from crash damage, it is not possible to include
the specific repair tasks in this category. The
helicopter mechanic must make an analysis of the
crash damage for each situation. Do the repair in
accordance with the degree of damage to the specific
part and the applicable repair procedures in this
manual. Call Bell Helicopter Textron Product Support
Engineering with your analysis of the crash damage.
5-4. TYPES OF INSPECTIONS
1. The maintenance procedures may include
scheduled inspections, special inspections, conditional
inspections, component interim inspections, and
component overhaul inspections.
5-00-00
Page 4 Rev. 16 25 FEB 2011
5. For the common Bell Helicopter Textron approved
optional equipment that is integrated into this
Maintenance Manual, refer to this chapter for the
scheduled inspection, conditional inspection,
component interim inspection, and component
overhaul inspection.
6. For all other Bell Helicopter Textron approved
equipment, refer to the applicable information in this
Maintenance Manual or the specific Service
Instruction (SI) for the scheduled inspection, special
inspection, conditional inspection, component interim
inspection, and component overhaul inspection.
7. For the inspection requirements for optional
equipment approved under Supplement Type
ECCN EAR99
Page 35
BHT-206L3-MM-1
Approval/Certificate (STA/STC), refer to the applicable
STA/STC documentation. Maintenance and inspection
of these items are the responsibility of the owner/
operator.
5-5. DEFINITIONS
• Check, inspect, examine — Look carefully to find
the condition of the component. Find how that
condition relates to a specific standard.
• Condition — The state of an item compared to a
known standard.
• Security — The presence of attaching parts that
are properly tightened or appear to be, and the
presence of properly installed (as required)
locking devices such as lockwire, cotter pins, or
other.
• Standard — A specified rule or measure that you
use to find the condition of a component.
• Damage — Physical deterioration of a
component.
• Preventive maintenance — To do small
maintenance action(s) on a regular basis to
prevent non-scheduled maintenance.
• Operating time — Actual flight or calendar time
that must be recorded in the Historical Service
Records or in the helicopter logs. The operating
time is specified as:
– Time in service (flight time) — The measured
time that starts the moment the helicopter
leaves the ground and continues until it
touches the ground at the next point of
landing. The time when the helicopter is on
the ground, with the engine and the rotor
turning, is not included.
– Calendar time — The elapsed time starts on
the day the inspection is completed, the
component is installed, or the rotor is turned
for the first time and ends on the last day of
the month that the time limit expires. Calendar
time is continuous. Calendar time does not
stop when you remove a component, put the
helicopter in storage, etc.
• Discard — Reject a component that has damage
that cannot be repaired. To permanently remove
from service.
• Inspection — A procedure that includes checking,
inspecting, and examining a system or a
component.
• Non-scheduled inspection — An inspection that
has not been scheduled.
• Periodic inspection — An inspection that is
repeated at equal time intervals.
• Progressive inspection — A scheduled inspection
that is divided into smaller segments. This makes
the best use of the time and the resources
available.
• Maintenance — The servicing and/or the repair of
a helicopter, a system, or a component that keeps
it serviceable.
• Maintenance zone — A specified area of the
helicopter that may contain more than one
system or more than one group of related
components. Maintenance zones (Figure 5-1) are
used when you do a progressive inspection.
• Lead-The-Fleet (LTF) Program — This is a
program to validate the performance of an
approved product improvement or a change to a
maintenance interval. The engineering aspects of
this change are approved. The program is closely
monitored by Bell Helicopter Textron in an
operational environment with selected operators.
• Special Programs — These are approved
programs that may be initiated under certain
special conditions to meet specific requirements.
These programs will be clearly defined through a
plan and the engineering and maintenance
aspects will be approved by the regulatory
authorities.
ECCN EAR99
5-00-00
25 FEB 2011 Rev. 16 Page 5
Page 36
BHT-206L3-MM-1
WARNING
NOTE
5-6. INSPECTION AND OVERHAUL
TOLERANCE
DO NOT APPLY THESE TOLERANCES
TO PARTS WITH A LIMITED
AIRWORTHINESS LIFE (CHAPTER 4).
The Bell Helicopter Textron approved tolerance for
scheduled inspections, special inspections, interim
inspections, and overhaul intervals, unless otherwise
stated, is 10% or up to a maximum of 300 hours
operating time/6 months calendar time, whichever is
less. The tolerances are established for maintenance
scheduling convenience only.
Scheduled inspections, special inspections, interim
inspections, or overhaul intervals required beyond the
stated tolerances must be approved by Product
Support Engineering.
The following is only applicable for those
operators whose governing aviation
authority requires to specifically approve
the inspection and overhaul tolerance.
If approval of the inspection and overhaul tolerance is
required by the applicable governing aviation authority,
this is the responsibility of the owner/operator.
Refer to the Rolls-Royce 250-C30 Series Operation
and Maintenance Manual (14W2) for inspection and
overhaul tolerances.
The following provide examples of when hourly,
calendar, or hourly/calendar inspection tolerances
have been applied:
Hourly Example (10% or up to a maximum of 300 hours, whichever is less):
300-HOUR
INSPECTION
DUE AT:
3400 Hours 10% of 300 hours = 30 hours 3430 Hours
3730 Hours 10% of 300 hours = 30 hours 3750 Hours
4050 Hours 10% of 300 hours = 30 hours 4050 Hours
MAXIMUM ALLOWED
TOLERANCE
INSPECTION CARRIED
OUT AT:
(10% tolerance applied)
(within 10% tolerance)
(tolerance not applied)
NEXT 300-HOUR
INSPECTION
DUE AT:
3730 Hours
4050 Hours
4350 Hours
5-00-00
Page 6 Rev. 21 7 JUN 2013 Export Classification C, ECCN EAR99
Page 37
BHT-206L3-MM-1
11111
1
1
1
Calendar Example (10% or up to a maximum of 6 months calendar time, whichever is less):
12-MONTH
INSPECTION
DUE ON:
MAXIMUM ALLOWED
TOLERANCE
INSPECTION CARRIED
OUT ON:
June 10, 2010 10% of 12 months = 1.2 months July 12, 2010
NEXT 12-MONTH
INSPECTION
DUE ON:
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:
The last day of the month applies for the next inspection (paragraph 5-5, calendar time).
Hourly/Calendar Example (10% or up to a maximum of 300 hours operating time/6 months calendar time,
whichever is less):
2250-HOUR/
60-MONTH
INSPECTION
DUE AT:
MAXIMUM ALLOWED
TOLERANCE
INSPECTION CARRIED
OUT AT:
NEXT 2250-HOUR/
60-MONTH
INSPECTION
DUE AT:
3400 Hours/
August 31, 2010
5650 Hours/
February 29, 2016
8125 Hours/
April 30, 2021
NOTE:
The last day of the month applies for the next inspection (paragraph 5-5, calendar time).
10% of 2250 hours = 225 hours
or
10% of 60 months = 6 months
10% of 2250 hours = 225 hours
or
10% of 60 months = 6 months
10% of 2250 hours = 225 hours
or
10% of 60 months = 6 months
3400 Hours/February 15, 2011
(within 10% calendar
tolerance)
5875 Hours/April 2, 2016
(10% hourly tolerance
applied)
8325 Hours/August 3, 2021
(within 10% hourly and
calendar tolerance)
5650 Hours/
February 29, 2016
8125 Hours/
April 30, 2021
10,575 Hours/
August 31, 2026
5-00-00
Export Classification C, ECCN EAR99
7 JUN 2013 Rev. 21 Page 6A/6B
Page 38
Page 39
SCHEDULED INSPECTIONS
WARNING
NOTE
NOTE
BHT-206L3-MM-1
5-7. SCHEDULED INSPECTIONS
FAILURE TO CORRECT CONDITIONS
SUCH AS, BUT NOT LIMITED TO,
CORROSION, EROSION, MECHANICAL
DAMAGE, OR OBVIOUS WEAR FOUND
DURING A SCHEDULED INSPECTION
COULD SERIOUSLY AFFECT THE
AIRWORTHINESS OF THE HELICOPTER.
Scheduled inspections include the airframe and the
component inspections. The scheduled airframe
inspection intervals are related to the airframe
operating time. The component inspection intervals
are related to the component operating time.
5-8. AIRFRAME INSPECTION PROGRAM
Bell Helicopter Textron has developed airframe
inspection programs to provide you with the flexibility
to permit maximum helicopter use. Depending on the
configuration of the helicopter, a 100 or 300-hour
airframe progressive inspection as well as a 100 or
300-hour airframe periodic inspection is available. You
may choose one of these Bell Helicopter inspection
programs or you can design your own program. You
are responsible for the selection of an inspection
program and for its approval by the governing civil
aviation authority.
5-9. AIRFRAME PROGRESSIVE INSPECTION
PROGRAMS
If you choose one of the airframe progressive
inspection programs, you must first get approval from
your local airworthiness authority. The progressive
inspections are divided into separate events of similar
workload (Table 5-1, Ta bl e 5- 2 , and Figure 5-1).
progressive inspection program or the 300-hour
airframe progressive inspection program. To
determine helicopter eligibility to utilize the 300-hour
airframe progressive inspection program, refer to
Table 5-3.
5-10. 100-HOUR AIRFRAME PROGRESSIVE
INSPECTION PROGRAM
The 100-hour airframe progressive inspection
program has 4 events. Events occur at intervals of
25 hours. After you complete event No. 4, the cycle
begins again with event No. 1 (Table 5-1). You must do
a minimum of one complete cycle (all four events)
within 12 calendar months. If you do not complete all
four events in a 12 calendar month period, the
remaining events must be completed prior to operating
the helicopter.
Table 5-1. 100-Hour Airframe Progressive
Inspection Events
AIRFRAME
HOURS
25 1 1, 2, and 3
50 2 4 and 5
75 3 6
100 4 7, 8, 9, and 10
In addition to performing the 100-hour airframe
progressive inspection program, you also need to
perform and record the following scheduled
inspections:
Every 300 hours of operation, helicopters
completing the 100-hour airframe
progressive inspection program also need
to accomplish the 300-hour inspection.
EVENT
NUMBER
MAINTENANCE
ZONES
All conditions of Table 5-3 must be met to
utilize the 300-hour airframe progressive
inspection.
Depending on the helicopter configuration, you have
the option to either use the 100-hour airframe
ECCN EAR99
• 300-hour inspection
• 1000-hour inspection
• 1200-hour inspection
5-00-00
25 FEB 2011 Rev. 16 Page 7
Page 40
BHT-206L3-MM-1
NOTE
• As required by manufacturer
• Weekly inspection
• 12-month inspection
• 12 months of component operation
• 24-month inspection
• 60-month inspection
• 300-hour or 12-month inspection
• 600 hours of component operation
• 600 hours or 12 months of component
operation
• 1200 hours of component operation
• 1500 hours of component operation
• 1500 hours of component operation and every
50 hours thereafter
• 2250 hours or 60 months of component
operation
Table 5-2. 300-Hour Airframe Progressive
Inspection Events (Cont)
AIRFRAME
HOURS
150 3 4
200 4 5 and 6
250 5 7 and 8
300 6 9 and 10
In addition to performing the 300-hour airframe
progressive inspection program, you also need to
perform and record the following scheduled
inspections:
Helicopters completing the 300-hour
airframe progressive inspection program
also need to accomplish the 100-hour
inspection.
• 100-hour inspection
• 1000-hour inspection
EVENT
NUMBER
MAINTENANCE
ZONES
• 3000 hours of component operation
5-11. 300-HOUR AIRFRAME PROGRESSIVE
INSPECTION PROGRAM
The 300-hour airframe progressive inspection
program has 6 events. Events occur at intervals of
50 hours. After you complete event No. 6, the cycle
begins again with event No. 1 (Table 5-2). You must do
a minimum of one complete cycle (all six events)
within 12 calendar months. If you do not complete all
six events in a 12 calendar month period, the
remaining events must be completed prior to operating
the helicopter.
Table 5-2. 300-Hour Airframe Progressive
Inspection Events
AIRFRAME
HOURS
50 1 1 and 2
100 2 3
EVENT
NUMBER
MAINTENANCE
ZONES
• 1200-hour inspection
• As required by manufacturer
• Weekly inspection
• 12-month inspection
• 12 months of component operation
• 24-month inspection
• 60-month inspection
• Deleted
• 600 hours of component operation
• 600 hours or 12 months of component
operation
• 1200 hours of component operation
• 1500 hours of component operation
5-00-00
Page 8 Rev. 21 7 JUN 2013 Export Classification C, ECCN EAR99
Page 41
BHT-206L3-MM-1
NOTE
NOTE
NOTE
• 1500 hours of component operation and every
50 hours thereafter
• 2250 hours or 60 months of component
operation
• 3000 hours of component operation
5-12. AIRFRAME PERIODIC INSPECTION
PROGRAM
The airframe periodic inspection combines all of the
events of the 100 or 300-hour progressive inspection
into one event.
All conditions of Table 5-3 must be met to
utilize the 300-hour airframe periodic
inspection.
Depending on the helicopter configuration, you have
the option to either use the 100-hour airframe periodic
inspection program or the 300-hour airframe periodic
inspection program. To determine the helicopter
eligibility to utilize the 300-hour airframe periodic
inspection program, refer to Ta bl e 5 -3 .
• As required by manufacturer
• Weekly inspection
• 12-month inspection
• 12 months of component operation
• 24-month inspection
• 60-month inspection
• 300-hour or 12-month inspection
• 600 hours of component operation
• 600 hours or 12 months of component
operation
• 1200 hours of component operation
• 1500 hours of component operation
• 1500 hours of component operation and every
50 hours thereafter
• 2250 hours or 60 months of component
operation
5-13. 100-HOUR AIRFRAME PERIODIC
INSPECTION PROGRAM
Do a 100-hour airframe periodic inspection program
every 12 calendar months or every 100 hours,
whichever occurs first. You must do a minimum of one
complete 100-hour airframe periodic inspection within
12 calendar months.
In addition to performing the 100-hour airframe
periodic inspection program, you also need to perform
and record the following scheduled inspections:
Every 300 hours of operation, helicopters
completing the 100-hour airframe periodic
inspection program also need to
accomplish the 300-hour inspection.
• 300-hour inspection
• 1000-hour inspection
• 3000 hours of component operation
5-14. 300-HOUR AIRFRAME PERIODIC
INSPECTION PROGRAM
Do a 300 Hour Airframe Periodic Inspection Program
every 12 calendar months or every 300 hours,
whichever occurs first. You must do a minimum of one
complete 300 Hour Airframe Periodic Inspection within
12 calendar months.
In addition to performing the 300-hour airframe
periodic inspection program you also need to perform
and record the following scheduled inspections:
Helicopters completing the 300-hour
airframe periodic inspection program also
need to accomplish the 100-hour
inspection.
• 100-hour inspection
• 1200-hour inspection
ECCN EAR99
• 1000-hour inspection
5-00-00
25 FEB 2011 Rev. 16 Page 9
Page 42
BHT-206L3-MM-1
• 1200-hour inspection
• As required by manufacturer
• Weekly inspection
• 12-month inspection
• 12 months of component operation
• 24-month inspection
• 60-month inspection
• Deleted
• 600 hours of component operation
• 600 hours or 12 months of component
operation
• 1200 hours of component operation
• 1500 hours of component operation
• 1500 hours of component operation and every
50 hours thereafter
• 2250 hours or 60 months of component
operation
• 3000 Hours of Component Operation
5-15. CHANGING INSPECTION PROGRAM
You must use either the airframe periodic inspection
program or the airframe progressive inspection
program from the start. You can change between the
two programs at any airframe operating time as
follows:
• To change from a 100-hour airframe
progressive inspection program to a 100-hour
airframe periodic inspection program, do a
complete 100-hour airframe periodic
inspection.
• To change from a 100-hour airframe periodic
inspection program to a 100-our airframe
progressive inspection program, do a
complete 100-hour airframe periodic
inspection.
• To change from a 300-hour airframe
progressive inspection program to a 300-hour
airframe periodic inspection program, do a
complete 300-hour airframe periodic
inspection.
• To change from a 300-hour airframe periodic
inspection program to a 300-hour airframe
progressive inspection program, do a
complete 300-hour airframe periodic
inspection.
5-00-00
Page 10 Rev. 21 7 JUN 2013 Export Classification C, ECCN EAR99
Page 43
206L1+
2
AND
206L3+
BHT-206L3-MM-1
IGW
UPGRADE
XX
206L 206L1 206L3 206L4
ALTERNATES
ACCEPTABLE
BULLETIN
REFERENCE
XXXX X
acceptable alternate to
206-010-450-123.
acceptable alternate
provided ASB
206L-97-108 is
accomplished.
XXXX X
TB 206L-07-226
or PSE
Instructions
XXXX X
or -203 and
206-704-727-101.
TB 206L-05-220 206-033-004-181, -199,
XXXX X
-109 are acceptable
alternates to
XX X
206-033-506-103.
TB 206L-08-229
206-010-450-123 TB 206L-00-201 206-010-450-101 is an
206-010-450-131 TB 206L-00-201 X X X
206-011-100-105 TB 206L-91-152 206-011-100-159 is an
206-011-810-153 TB 206L-09-239 X X X X X
206-031-314-157A
or
206-031-314-217B
206-031-629-103 BHT-206-SRM X X X X X
or equivalent with ASB
206L-99-115
accomplished
206-040-004-107 TB 206L-91-153
206-040-004-115 XX
Table 5-3. 300-Hour Airframe Progressive or 300-Hour Airframe Periodic Inspection Program Prerequisites
NOMENCLATURE PART NUMBER
Swashplate and
Support Assembly
Main Rotor Hub
Assembly
Tail Rotor Hub
Assembly
Tailboom Attachment
Fittings and Longeron
Forward Engine Mount
Fittings
Assembly
Tailboom Assembly 206-033-004-175/-177
Transmission Restraint 206-033-506-103 206-033-506-107 and
Transmission
Assembly
5-00-00
ECCN EAR99
25 FEB 2011 Rev. 16 Page 11
Page 44
BHT-206L3-MM-1
2
IGW
AND
206L1+
206L3+
UPGRADE
XX
206L 206L1 206L3 206L4
ALTERNATES
ACCEPTABLE
BULLETIN
REFERENCE
XXXX X
-115 are acceptable
fielded substitutes for
206-040-387-101.
XXXX X
are acceptable fielded
substitutes for
206-340-300-105M is an
acceptable fielded
substitute for
TB 206L-01-204
206-340-300-105.
TB 206L-01-205 X X
206-040-402-111.
Table 5-3. 300-Hour Airframe Progressive or 300-Hour Airframe Periodic Inspection Program Prerequisites (Cont)
NOMENCLATURE PART NUMBER
Mast Assembly 206-040-014-103 TB 206L-99-195 X X X
5-00-00
Page 12 Rev. 16 25 FEB 2011
206-040-015-011 ASB 206L-93-91 X
206-040-014-107 TB 206L-99-195 X X
206-040-015-015 ASB 206L-93-91 X X
Main Driveshaft
Assembly
(Grease Lubricated)
206-040-270-123 TB 206L-01-205 X X
Freewheel Assembly 206-040-270-117 TB 206L-01-205 X
206-040-387-101 TB 206L-02-207 206-040-370-107/-109/
Riveted Aft Short Shaft 206-040-383-101 TB 206L-02-207 X X
Riveted Tail Rotor
Driveshaft Assembly
206-040-402-111 TB 206L-99-197 206-040-402-101/-107
Tail Rotor Gearbox
Assembly
206-061-432-109 ASB 206L-86-40 X X X X X
Oil Cooler Blower
Impeller
206-340-300-105 ASB 206L-01-123
Main Driveshaft
Assembly (KAflex)
with TB 206L-02-208
and ASB 206L-07-147
accomplished.
Freewheel Assembly 406-040-500-113
ECCN EAR99
Page 45
206L1+
2
424
AND
206L3+
206L 206L1 206L3 206L4
BHT-206L3-MM-1
IGW
UPGRADE
XXXX X
ALTERNATES
ACCEPTABLE
BULLETIN
REFERENCE
Purolator Kit Number
STC # SH200GL
Table 5-3. 300-Hour Airframe Progressive or 300-Hour Airframe Periodic Inspection Program Prerequisites (Cont)
To qualify for the 300-hour airframe progressive inspection program or the 300-hour airframe periodic inspection program, the helicopter
must have all of the parts listed installed (or subsequent part numbers to those listed based on configuration/eligibility requirements).
FACET scavenge oil filter system available from Purolator Facet, Inc., www.purolator-facet.com.
prerequisite listing to determine applicability to use the 300-hour airframe progressive inspection program or 300-hour airframe periodic
NOMENCLATURE PART NUMBER
Aft Fuselage Bulkhead 407-030-027-103 TB 206L-07-226 X X X X X
FACET Scavenge Oil
Filter System
NOTES:
inspection program, as applicable. Refer to the bulletins listed within the table for configuration data as required.
1. Ta bl e 5 -3 is not to be used as a configuration listing for the installation of components on 206L Series Helicopters. It is only provided as a
inspection or the 100-hour airframe periodic inspection.
3. If the helicopter does not have all of the parts listed in this table installed, the helicopter is limited to either the 100-hour airframe progressive
5-00-00
ECCN EAR99
25 FEB 2011 Rev. 16 Page 13/14
Page 46
Page 47
206L4_MM_05_0001
ZONE 1
ZONE 3
ZONE 7
ZONE 10
ZONE 8
ZONE 9
ZONE 4
ZONE 5
ZONE 6
ZONE 2
Zone 1
Zone 2
Zone 3
Zone 4
Zone 5
Zone 6
Zone 7
Zone 8
Zone 9
Zone 10
- Main rotor hub and blade assembly
- Tail rotor hub and blade assembly
- Forward top deck
- Power plant
- Aft top deck
- Tailboom
- Cabin interior
- Foward fuselage
- Aft fuselage
- Landing gear
BHT-206L3-MM-1
ECCN EAR99
Figure 5-1. Maintenance Zones
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25 FEB 2011 Rev. 16 Page 15/16
Page 48
Page 49
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 1 — MAIN ROTOR SYSTEM
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
Chapter 62 MAIN ROTOR SYSTEM
1. Verify main rotor flap restraint for freedom of movement,
and for condition and security.
2. Examine static stops and mast for evidence of mast
bumping.
3. Remove main rotor blade leading edge erosion protection
tape, if installed.
4. Examine main rotor blades for cleanliness and overall
condition. Examine for cracks, corrosion and de-bonding of
doublers.
5. Examine leading edge of blades for corrosion and erosion.
ECCN EAR99
Restore contour as necessary.
6. Examine the tip weight cap for corrosion, cracks, erosion,
and deformation.
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25 FEB 2011 Rev. 16 Page 17
Page 50
BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
7. If applicable, reinstall main rotor blade leading edge
erosion protection tape.
8. Examine the following main rotor hub assembly
components for condition and security:
a. Mast nut
b. Trunnion
c. Pillow blocks
d. Grips
e. Pitch horns
f. Sta tic stops
9. Examine pitch horn trunnion bearings for evidence of wear,
damage, and for security.
INITIAL
MECH OTHER
10. Torque check pillow block retention hardware 84 to
107 inch-pounds (9.4 to 12 Nm). Examine for misalignment of
anti-slippage marks.
11. Examine main rotor yoke for corrosion or mechanical
damage as follows:
BHT-206L-CR&O a. Examine fillet radius of both yoke spindles inboard of
wear sleeves for evidence of corrosion. If corrosion is visible,
remove with fine abrasive pad (C-407). If corrosion cannot be
removed with pads, or is extensive, disassemble hub for
inspection and repair.
If the main rotor hub must be disassembled, omit
remaining steps.
b. Examine entire yoke centre section (inboard and
outboard surfaces) for damage.
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Page 18 Rev. 22 15 MAY 2015 Export Classification C, ECCN EAR99
Page 51
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
c. Touch up all repaired areas or areas of bare metal in
accordance with applicable main rotor hub inspection and repair
instructions.
d. Ensure no sealant voids are visible around shields or
wear sleeve, strap fittings, and grip closure. Recoat with sealant
(C-308) as required. On main rotor hub assemblies up to and
including P/N 206-011-100-025, coat the remaining exposed
fillet radius and repaired surfaces with a film of corrosion
preventive compound (C-101).
ZONE 2 — TAIL ROTOR ASSEMBLY
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
Chapter 64 TAIL ROTOR ASSEMBLY
INITIAL
MECH OTHER
1. Clean tail rotor blades to maintain visibility of warning
stripes.
BHT-206L-CR&O 2. Examine the following tail rotor hub assembly components
for condition and security of attachment:
a. Yok e
b. Pitch horns
c. Trunnion and trunnion caps
d. Counterweight hardware
Chapter 64 3. Examine tail rotor blades as follows:
a. Tip block rivets for damage, corrosion, erosion, and
looseness.
b. Skin for bulges, nicks, dents, scratches, or other
damage.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 19
Page 52
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
c. Deformed or cracked skin in the area of the chordwise
weights.
d. Leading edge for erosion, nicks, dents or scratches.
e. Bonded joints of blade skin mating area for suspected
voids or cracks. Pay particular attention in the area of tip block
and doublers.
f. Feathering bearings for looseness and cracks in uniball.
4. Examine the following tail rotor hub and blade assembly
attaching components for condition and security:
a. Spacer
b. Rubber bumper
c. Static stop
d. Nut
INITIAL
MECH OTHER
e. Balance wheel
ZONE 3 — FORWARD DECK
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
AIRFRAME (FORWARD DECK)
Chapter 71 1. Open and examine forward fairing for condition and
security.
2. Remove and examine transmission cowling for condition.
3. Examine all fairing and cowling latches and/or fasteners for
condition
4. Examine top deck for condition, leaks and security.
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Page 20 Rev. 16 25 FEB 2011
ECCN EAR99
Page 53
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 53 5. Clean transmission deck.
6. Examine air induction cowling and plenum for damage,
obstructions and cleanliness. Examine intake fairing windows
for damage and cleanliness.
7. Examine inlet screen (if applicable) for missing or damaged
wires and rivets.
8. Examine particle separator (if applicable) vortex tubes,
ejector tubes, and ejector nozzles for cleanliness, condition, and
security.
9. Examine forward deck drain(s) to ensure absence of
obstruction.
10. Examine antennas for condition and security.
Chapter 67 CONTROLS
1. Examine the following flight control components for signs
of interference, corrosion, wear, mechanical damage and
security:
INITIAL
MECH OTHER
a. Control tubes.
b. Links.
c. Rod and bearings.
d. Bellcranks.
e. Bellcrank supports.
f. Attaching bolts and nuts.
2. Inspect main rotor pitch links with a 3X magnifying glass for
damage, corrosion and cracks. Give particular attention to
swaged ends at jam nut or inserts.
Chapter 76 3. Examine N
and security. Pay particular attention to the jackshaft assembly
for damage or evidence or twisting.
ECCN EAR99
control linkages on forward deck for condition
2
25 FEB 2011 Rev. 16 Page 21
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BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
4. Verify all control tubes and bellcranks for freedom of travel
throughout range.
Chapter 62 SWASHPLATE ASSEMBLY AND MAST
1. Clean swashplate assembly and mast.
2. Disconnect main rotor pitch links from outer ring.
3. Disconnect idler (drive) link from outer ring.
4. Examine swashplate drive assembly for axial, radial, and
accumulative wear.
5. Disconnect boot from swashplate outer ring and lift up
temporarily. Examine boot for evidence of deterioration.
6. Verify condition of duplex bearing, before lubrication, as
follows:
a. Rotate outer ring to check duplex bearing for condition.
Bearing must be smooth and show no evidence of roughness,
binding, dragging, or looseness.
INITIAL
MECH OTHER
7. Examine pivot sleeve slot sidewalls for wear or
deterioration.
8. Examine pivot sleeve bearings for wear, deterioration and
evidence of excessive axial play between pivot sleeve and
swashplate support.
9. Examine collar set bushings for cracks and damage.
10. Examine swashplate support and uniball surfaces for
condition.
11. Examine collective lever to sleeve assembly pins for
condition.
12. Examine inner ring for condition. Examine for evidence of
contact with sleeve assembly.
13. Examine outer ring for condition.
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Page 22 Rev. 16 25 FEB 2011
ECCN EAR99
Page 55
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
14. Examine the upper inside diameter of swashplate support
for evidence of contact with the mast pole.
15. Connect and secure boot, idler (drive) link and main rotor
pitch links to outer ring.
16. Examine swashplate assembly for condition and security.
Chapter 63 17. Examine mast for condition.
Chapter 62 18. Ensure no sealant voids are visible around the swashplate
drive collar set. Re-coat with adhesive (C-307) as required.
Chapter 29 HYDRAULIC SYSTEM
1. Examine rigid and flexible fluid lines for chafing, leaks and
security.
2. Examine hydraulic pump for leaks and general condition.
3. Examine hydraulic reservoir for leaks and general
condition.
INITIAL
MECH OTHER
4. Examine servo actuators for leaks, condition and security.
5. Examine servo actuator support for condition.
Chapter 67 6. Verify linkage pivot bolts on hydraulic servo actuators for
freedom of rotation and security.
7. Examine hydraulic filter red indicator button (two locations).
Button should not be extended.
Chapter 12 8. Verify fluid level in hydraulic tank. Replenish as required.
Replace fluid if color has changed color or if fluid emits bad
odor.
9. Examine manifold, relief valve, and solenoid valve for
leaks, condition and security.
Chapter 63 TRANSMISSION AND PYLON ASSEMBLY
1. Examine the following pylon support components:
ECCN EAR99
25 FEB 2011 Rev. 16 Page 23
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BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
a. Transmission link assemblies and bearings for damage
and deterioration.
b. Nodal beam flexures for condition and security.
c. Forward and aft nodal beam deck supports for condition
and security. Check torque on heads of bolts only (bolts must
not rotate). If a bolt is loose, remove nut. Install new nut and
torque 75 to 95 inch-pounds (8.4 to 10.7 Nm).
d. Nodal beam stops for evidence of excessive contact
with nodal beam arms.
e. Transmission restraint for damage and spherical
bearings for excessive wear and security.
f. Stop mount for condition and security. Stop mount
bushings for wear.
g. All pylon support elastomeric components for evidence
of deterioration.
INITIAL
MECH OTHER
h. All pylon support hardware for security of attachment.
2. Examine transmission assembly for condition and security.
3. Examine transmission assembly for evidence of oil
leakage.
4. Examine all fluid lines for chafing, damage and evidence of
leakage.
5. Examine transmission oil for evidence of contamination.
6. Examine transmission oil filter bypass indicator for
condition. Bypass button should not be extended.
7. Inspect all transmission chip detectors for accumulated
material.
8. Perform functional test of all transmission chip detectors.
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Page 24 Rev. 21 7 JUN 2013 Export Classification C, ECCN EAR99
Page 57
BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
9. Ensure no sealant voids are visible around forward and aft
nodal beam deck mounted supports and isolation mount.
Recoat with sealant (C-308) as required.
Chapter 63 MAIN DRIVESHAFT
1. Examine main driveshaft as follows:
TEMP-PLATE indicator dots are of a white or gray
color that turn black when exposed to an
overtemperature condition. Chemical contamination
can also cause the indicating dots to turn black.
a. For 206L3 helicopters, examine main driveshaft for
visual damage and couplings for grease leakage. Check
driveshaft for freedom and smoothness of axial movement.
Inspect bolts for security. Inspect TEMP-PLATES for evidence
of overheating indication, deterioration, debonding, or excessive
discoloration of the epoxy overcoating.
INITIAL
MECH OTHER
2. For 206L3+ IGW Upgrade helicopters, examine the engine
to transmission KAflex driveshaft for condition and security.
Examine the components as follows:
a. Driveshaft for cracks, corrosion, and surface damage.
b. Flexframe and bolts for condition and signs of slippage.
Chapter 96 ELECTRICAL
1. Examine all electrical components, wires, cables and
connectors in the area of the forward deck and transmission for
chafing, general condition, and security.
Export Classification C, ECCN EAR99
5-00-00
7 JUN 2013 Rev. 21 Page 25
Page 58
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-16. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
GROUND RUN
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
4. Start the helicopter and conduct ground run at 100% N
check for leaks and ensure all systems are operational and
parameters are within Flight Manual limitations.
to
R
INITIAL
MECH OTHER
5-00-00
Page 26 Rev. 21 7 JUN 2013
Export Classification C, ECCN EAR99
Page 59
PROGRESSIVE INSPECTIONS
5-17. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 4 — POWER PLANT
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
AIRFRAME (POWER PLANT AREA)
Chapter 71 1. Examine firewalls for condition and security.
2. Examine engine pan area for evidence of loose fasteners
and damage. Restore cracked or missing sealant form engine
pan.
3. Examine engine pan drains. Make sure that they are not
clogged.
Chapter 28 4. Examine airframe fuel filter assembly for evidence of
leakage and security.
Chapter 71 5. Examine engine mount legs for condition and security. Pay
particular attention for loose fasteners.
Applicable Service
Instruction
ECCN EAR99
6. Examine engine mount fittings for condition and security.
7. Examine rotor brake (if installed) for condition and security.
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25 FEB 2011 Rev. 16 Page 27
Page 60
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-17. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 96 8. Examine the primary electrical ground connection in
engine pan area for condition and security
POWER PLANT
Rolls-Royce 250-C30
Series Operation and
Maintenance Manual,
14W2
Chapter 71 2. Examine engine inlet bellmouth for obstruction and general
1. Perform engine inspection per the applicable Rolls-Royce
Operation and Maintenance Manual.
condition.
3. Examine engine compartment hardware for security of
attachment.
4. Examine engine for evidence of fuel or oil leaks.
5. Examine all flexible and rigid lines for condition and
security.
INITIAL
MECH OTHER
a. Pay particular attention for chafing damage and kinked
lines.
6. Examine exhaust stack for condition and security.
7. Examine all engine-mounted accessories for condition and
security.
Chapter 75 8. Examine the engine anti-ice solenoid valve for condition
and security.
Chapter 76 9. Inspect fuel control lever bolt hole and bolt for wear.
Replace parts as required.
Chapter 71 10. Inspect engine chip detectors for accumulated material.
Chapter 96 11. Perform operational check of all engine chip detectors.
Chapter 76 12. Examine engine controls for condition and security.
13. Verify operation of engine N
a. Ensure proper throttle friction.
control as follows:
1
5-00-00
Page 28 Rev. 16 25 FEB 2011
ECCN EAR99
Page 61
BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-17. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
b. Check freedom of full throttle grip travel and idle release
operation. Return to closed position. Check copilot throttle if
installed.
c. Ensure fuel control stop lever contact with minimum and
maximum stops before throttle grip reaches travel limit.
If dual controls are installed, it is permissible for
pointer to be 0.078 inch (1.98 mm) below 40° mark
when copilot twist grip is used.
d. Rotate throttle grip to idle detent, fuel control pointer
should be no more than 0.01 inch (0.25 mm) below the 40°
mark on the quadrant.
e. Verify control linkage for excessive looseness, lost
motion, and binding.
14. Verify operation of engine N
control as follows:
2
INITIAL
MECH OTHER
a. Position N
governor actuator to full DECREASE
2
(extended).
b. Lift collective stick full up.
c. Position N
governor actuator to full INCREASE
2
(retracted).
d. Verify for clearance between governor stop and lever
stop arm.
e. Lower collective stick full down.
f. Position N
governor actuator to full DECREASE
2
(extended).
g. Verify for clearance between governor stop and lever
stop arm.
Chapter 71 h. Verify control linkage for excessive looseness, lost
motion, and binding.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 29
Page 62
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-17. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
DRIVETRAIN
Chapter 63 1. Examine freewheel assembly for condition, leaks, and
security.
Chapter 63
Chapter 96
Chapter 65 3. Examine forward short shaft (steel) disc pack couplings for
2. Examine the freewheel unit chip detector for accumulated
material. Perform operational check of freewheel unit chip
detector. (Refer to transmission chip detector caution system.)
condition and security.
4. Examine forward short shaft (steel) splined adapters for
adequate lubrication and freedom of movement.
5. Torque check forward short shaft disc pack coupling
fasteners 50 to 70 inch-pounds (5.7 to 7.9 Nm). For 206L3+
IGW Upgrade helicopters, torque check forward short shaft disc
pack coupling fasteners 150 to 180 inch-pounds (16.9 to
20.3 Nm).
INITIAL
MECH OTHER
Chapter 96 ELECTRICAL
1. Examine all electrical components, wires, cables, and
connectors in the power plant area for chafing, general
condition, and security.
2. Verify illumination of airframe fuel filter caution light by
depressing differential switch “press to test” button on filter
head.
ZONE 5 — AFT TOP DECK
PLACARDS AND MARKINGS
Chapter 11 1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
AIRFRAME (AFT TOP DECK)
Chapter 71 1. Remove and examine aft fairing and attachment fasteners
for condition and security.
5-00-00
Page 30 Rev. 17 8 APR 2011
ECCN EAR99
Page 63
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-17. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
2. Examine fairing retainer for condition.
3. Examine exterior of aft deck structure for condition.
OIL SYSTEM
Chapter 79 1. Examine oil cooler area for evidence of oil leaks. Examine
oil cooler pan for cleanliness and make sure the drain is not
blocked.
2. Examine all flexible and rigid fluid lines for condition and
security.
a. Pay particular attention for chafing damage and kinked
lines.
3. Examine oil cooler core for obstructions and cleanliness.
Chapter 65 4. Examine oil cooler blower and housing for cleanliness,
condition and security.
INITIAL
MECH OTHER
Chapter 79 5. Examine oil tank for leakage, condition and security. Check
oil for contamination.
6. Examine oil tank supports for condition and security.
Chapter 71 7. Examine the oil cooler seals bonded inside the aft fairing
for condition.
8. Examine external scavenge oil filter system (STC) (if
installed) for condition and security.
DRIVETRAIN
Chapter 65 1. Examine the blower impeller for condition.
2. Examine oil cooler blower impeller shaft for condition.
3. Examine oil cooler blower hanger bearings and brackets
for grease leakage and evidence of overheating.
4. Examine aft short shaft (aluminium) for condition and
security.
ECCN EAR99
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8 APR 2011 Rev. 17 Page 31
Page 64
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-17. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
5. Examine aft short shaft (aluminium) splined adapter for
adequate lubrication and freedom of movement.
6. Torque check disc pack coupling fasteners 50 to
70 inch-pounds (5.7 to 7.9 Nm).
Chapter 96 ELECTRICAL
1. Examine all electrical components, wires, cables, and
connectors in the area of the aft deck for chafing, and general
condition and security.
GROUND RUN
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
INITIAL
MECH OTHER
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
4. Start the helicopter and conduct ground run at 100% N
check for leaks and ensure all systems are operational and
parameters are within Flight Manual limitations.
to
R
5-00-00
Page 32 Rev. 17 8 APR 2011
ECCN EAR99
Page 65
PROGRESSIVE INSPECTIONS
5-18. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
NOTE
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 6 — TAILBOOM
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
Chapter 53 TAILBOOM STRUCTURE
In the event that cracks are found during inspection
of tailboom, contact Bell Helicopter Textron, Product
Support Engineering.
1. Examine tailbooms 206-033-004-045 and prior, modified in
accordance with ASB 206L-87-47 as follows:
a. Remove tail rotor driveshaft and gearbox fairings.
Inspect for condition and attachment of fasteners.
b. Remove a sufficient amount of anti-chafing tape to
permit inspection of tailboom skin adjacent to tail rotor driveshaft
cover retention clips aft of horizontal stabilizer, and in area of
ECCN EAR99
double row of rivets attaching tail rotor gearbox support fitting to
tailboom (BS 174).
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25 FEB 2011 Rev. 16 Page 33
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PROGRESSIVE INSPECTIONS
5-18. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
c. Prior to cleaning, use a minimum 5X magnifying glass
to inspect for cracks and signs of developing cracks at the
following locations:
(1) Aft of stabilizer assembly, around rivets, which
attach tail rotor driveshaft cover retention clips to tailboom.
(2) Area of tail rotor gearbox fairing attachment
nutplate rivets.
(3) Area of double row of rivets, which attach tail rotor
gearbox support fitting to tailboom (BS 174).
d. Clean entire tailboom taking particular care to remove
all grime and dirt in specified area of inspection and perform
inspection using minimum 5X magnifying glass.
Chapter 53 e. Examine entire tailboom for cracks, dents, deformation,
waviness, working rivets, and chafing between tailboom skin
and fairing. Pay particular attention to rivets attaching the tail
rotor gearbox support to the tailboom.
INITIAL
MECH OTHER
BHT-206-SRM f. Replace any loose or working rivets found.
g. Replace removed, damaged, or worn anti-chafing
adhesive tape (C-460) as required.
h. Inspect doubler and clip edge sealant for integrity.
Reseal as required.
i. As applicable to tailbooms modified in accordance with
ASB 206L-99-115, examine doubler around stabilizer on left
side for integrity of sealant. Reseal as required.
2. Inspect tailbooms P/N 206-033-004-143 and subsequent
as follows:
a. Remove tail rotor driveshaft and gearbox fairings.
lnspect for condition and attachment of fasteners.
b. Check anti-chafing adhesive tape (C-460) on tailboom
for condition. Replace worn or damaged tape as required.
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ECCN EAR99
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BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-18. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
c. lnspect entire tailboom for cracks, dents, deformation,
working rivets, and chafing between tailboom skin and fairing.
Pay particular attention to rivets attaching the tail rotor gearbox
support to the tailboom.
BHT-206-SRM d. Replace any loose or working rivets found.
e. Inspect all clip edges for integrity of sealant. Reseal as
required.
f. As applicable to tailbooms modified in accordance with
ASB 206L-99-115, examine doubler around stabilizer on left
side for integrity of sealant. Reseal as required.
3. Examine horizontal stabilizer for condition and security of
attachment. Verify security of all attachment bolts.
4. Examine elevators for condition, security of attachment,
and side play.
5. Examine auxiliary finlets for condition and security.
INITIAL
MECH OTHER
6. Inspect the vertical fin attachment support for condition and
damage. Pay particular attention to the vertical fin attachment
points.
7. Examine vertical fin assembly for condition and security.
Chapter 32 8. Examine vertical fin and tail skid for condition, security, and
signs of ground contact.
9. Examine for open tailboom drains on lower skin and clear
any obstructions.
10. Examine antennas for damage and security.
TAIL ROTOR DRIVESHAFTS
Chapter 65 1. Examine tail rotor driveshaft hanger bearings for excessive
grease leakage and evidence of overheating.
2. Examine segmented driveshafts and aft splined adapter for
condition and security. Check aft splined adapter for adequate
lubrication and freedom of movement.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 35
Page 68
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-18. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
3. Torque check disc pack coupling fasteners 50 to
70 inch-pounds (5.7 to 7.9 Nm).
TAIL ROTOR GEARBOX
Chapter 53 1. Examine tail rotor gearbox support for condition and
security. Pay particular attention for cracks at the gearbox
attachment holes.
Chapter 65 2. Examine tail rotor gearbox for oil leaks, condition and
security.
3. Examine gearbox oil for evidence of contamination.
4. Examine tail rotor output shaft for condition.
Chapter 65 5. Examine the tail rotor gearbox chip detector for
accumulated material.
Chapter 96 6. Perform operational check of the tail rotor gearbox chip
detector.
INITIAL
MECH OTHER
Chapter 64 TAIL ROTOR PITCH CHANGE CONTROLS
1. Examine the tail rotor pitch control mechanism for freedom
of travel throughout range and for condition and security.
2. Examine the following tail rotor pitch change components:
a. Boot for condition, security, and evidence of grease or
oil leakage.
b. Lower control mechanism rod for condition of bearings.
c. Pitch links and spherical bearings for condition and
security.
d. Crosshead for condition and security.
e. Knurled nut for condition and security and liner for
excessive play.
5-00-00
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ECCN EAR99
Page 69
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-18. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 96 ELECTRICAL
1. Examine all visible electrical components, wires, cables,
and connectors in the area of the tailboom for chafing, and
general condition and security.
2. Verify navigation lights and anti-collision light for operation,
condition, and security.
Chapter 97 3. Examine antennas for condition and security.
GROUND RUN
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
INITIAL
MECH OTHER
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
4. Start the helicopter and conduct ground run at 100% N
check for leaks and ensure all systems are operational and
parameters are within Flight Manual limitations.
to
R
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 37/38
Page 70
Page 71
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 7 — CABIN INTERIOR
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
Chapter 53 1. Examine the cabin floor for condition.
Chapter 25 2. Examine the seat assemblies for condition and security.
IL GEN-05-103 3. Examine passenger and crew restraints and webbing for
ECCN EAR99
INSTRUMENTS
1. Examine instruments and instrument panel for condition,
security and for correct markings.
EQUIPMENT AND FURNISHINGS
condition and security.
4. Verify operation of passenger and crew inertia reels and
belt buckles. Pull promptly on each reel to confirm the proper
activation of the reel locking mechanism.
5-00-00
25 FEB 2011 Rev. 16 Page 39
Page 72
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
5. Examine the interior trim for condition and security.
Chapter 52 6. Verify sliding windows for safety and smoothness of sliding.
Chapter 21 7. Examine the ventilation system for condition and security.
8. Verify nose vents for proper operation, absence of
obstructions or debris, and open drains.
Chapter 95 9. Verify for proper operation of the fuel valve switch guard.
Chapter 26 10. Inspect cabin fire extinguisher for condition, security and
proper charge.
Chapter 21 11. Verify proper operation of ventilation inlet control cables.
12. Examine first aid kit, replace missing or out of date items.
Chapter 67 CONTROLS
1. Examine the collective control stick for condition and
security. Examine copilot collective control stick if installed.
INITIAL
MECH OTHER
2. Examine the cyclic control stick for condition and security.
Examine copilot cyclic control stick if installed.
3. Examine the anti-torque control pedals for condition and
security. Examine copilot anti-torque control pedals if installed.
Chapter 96 ELECTRICAL
1. Verify operation of cockpit map reading light.
2. Verify operation of aft cabin reading lights (if installed).
USE EXTREME CARE WHEN IN PROXIMITY OF
PITOT TUBE WITH HEAT APPLIED, TOUCHING
TUBE MAY RESULT IN SERIOUS BURNS.
5-00-00
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ECCN EAR99
Page 73
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
3. Verify operation of the pitot tube heating system.
4. Verify operation of defog blowers.
5. Verify operation of ENGINE OUT and LOW ROTOR RPM
audio and mute switch (if installed).
6. Verify illumination of all caution panel annunciator light
segments by depressing test switch, or each individual light
segment, as applicable.
7. Verify instrument lighting and dimming capabilities.
ZONE 8 — FORWARD FUSELAGE
PLACARDS AND MARKINGS
Chapter 11 1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
FUSELAGE
Chapter 53 1. Examine forward fuselage for condition.
Chapter 52 2. Examine all cabin doors for condition and security. Give
special attention to the following
a. Hinges
b. Seals
c. Latches for proper adjustment, positive locking, and
wear
d. Windows
e. Handles
Chapter 95 3. Drain moisture from pitot and static piping installation.
Chapter 53 4. Examine the external power door and receptacle for
condition and security.
ECCN EAR99
5-00-00
25 FEB 2011 Rev. 16 Page 41
Page 74
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
5. Examine battery compartment door, door seal and
attachment for condition and security.
Chapter 52 6. Examine components in battery compartment for condition
and security.
Chapter 32 7. Examine cabin entry steps (if installed) for condition and
security.
Chapter 52 8. Examine windshields and skylights for condition.
Chapter 53 9. Examine upper fuselage for evidence of water leaks.
10. Examine lower fuselage for indication of fuel leaks, dents,
cracks, corrosion, delamination, loose or missing rivets, and
condition.
11. Inspect external area of fuel boost pump for interference of
wire from low fuel warning switch to fuel boost pump retainer.
12. Examine all fuselage sealant joints for condition. Restore
sealant as necessary.
INITIAL
MECH OTHER
Chapter 96 and
Chapter 97
5-00-00
Page 42 Rev. 16 25 FEB 2011
ELECTRICAL AND AVIONICS
1. Examine all visible electrical components, wires, cables,
and connectors in the area of the forward fuselage for chafing,
and general condition and security.
2. Examine battery and vent tubes for condition and security.
3. Perform operational test of the battery temperature
indicating system.
4. Verify operation of litter door open warning light.
5. Verify operation of landing lights.
6. Verify operation of lower fuselage mounted position lights
(if installed).
7. Examine antennas for condition and security.
ECCN EAR99
Page 75
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 9 — AFT FUSELAGE
PLACARDS AND MARKINGS
Chapter 11 1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
FUSELAGE (EXTERIOR)
Chapter 53 1. Examine aft fuselage for dents, cracks, corrosion,
delamination, loose or missing rivets and condition.
2. Examine aft fuselage for indications of fuel or oil leaks.
Chapter 28 3. Examine the fuel cap for condition and security.
Chapter 96 4. Examine the grounding plug for condition.
Chapter 6 and
Chapter 53
5. Examine all fuselage drains for condition and freedom from
obstructions.
INITIAL
MECH OTHER
Applicable Service
Instruction
Chapter 53 7. Examine baggage compartment door, seal, and latches for
Chapter 96 8. Verify operation of the baggage door ajar caution light, (if
Chapter 53 1. Examine baggage compartment for condition.
6. Examine heater and/or air conditioning inlets and outlets
for cleanliness and absence of obstructions, (if installed).
operation, condition, and security.
installed).
FUSELAGE (INTERIOR)
2. Gain access to inside of aft fuselage through access
panels in baggage compartment and access panel located on
the aft right hand fuselage:
a. Examine access panels and fasteners for condition.
b. Examine under engine pan for fuel, oil or water leaks.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 43
Page 76
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
c. Examine drain lines for condition and security.
d. Examine aft fuselage longerons for cracks, corrosion,
and condition. Pay particular attention to the upper left longeron
between aft fuselage frame at STA 204.49 and frame at
STA 231.48.
e. Examine interface between longerons and engine pan
structure for cracks, corrosion, distortion and loose fasteners.
f. Inspect engine mount attachment structure for
condition.
ANY CRACK, CORROSION, OR LOOSE OR
SHEARED RIVET IS CAUSE FOR IMMEDIATE
GROUNDING OF THE HELICOPTER UNTIL THE
PROBLEM IS CORRECTED.
INITIAL
MECH OTHER
Chapter 53
Chapter 4
Chapter 67 1. Examine the anti-torque control system components for
Chapter 96 and
Chapter 97
g. Examine the four tailboom attachment fittings on
fuselage aft bulkhead and tailboom forward bulkhead for cracks.
Give special attention to the tailboom attachment fittings/
intercostals and bolts, and to fasteners between the intercostal.
Particular attention must be given to inspection of the upper left
fitting (refer to Chapter 4, Inspection Limitations Schedule),
CONTROLS
condition and security.
2. Examine the stabilizer elevator control system components
for condition and security.
ELECTRICAL AND AVIONICS
1. Examine antennas for condition and security.
2. Examine all components, electrical wiring, cables, and
connectors for chafing, general condition, and security.
5-00-00
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ECCN EAR99
Page 77
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
3. Examine all optional equipment installed in the aft fuselage
area for condition and security.
4. Verify proper operation of fuel sump drain valve switch.
ZONE 10 — LANDING GEAR
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
Chapter 32 CROSSTUBES
1. Examine crosstube retaining straps, cushions, and
attaching hardware for condition and security.
2. Examine fuselage attachment fittings for condition and
security.
INITIAL
MECH OTHER
3. Examine electrical bonding strips (if installed) for condition
and security.
4. Examine fairings (if installed) for condition and security.
5. Examine crosstube riveted or clamped supports for
condition and security. Give particular attention to the sealant
joints around supports. Restore sealant (C-251) and paint finish
as required.
6. Examine crosstubes for corrosion and damage. Give
particular attention to areas where equipment is mounted.
Repair and/or restore surface protection as required.
7. Examine cabin entry steps for condition and security (if
installed).
8. Examine sealant joint at junction with skid tube saddles.
Restore sealant (C-251) and paint finish as required.
Chapter 32 SKID TUBES
1. Examine skid tubes for corrosion, damage, and security.
ECCN EAR99
5-00-00
25 FEB 2011 Rev. 16 Page 45
Page 78
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-19. 100-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 4 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
2. Examine skid shoes for condition and security.
3. Examine skid tube saddles for corrosion, damage, and
security.
4. Examine ground handling wheel attachment bolts for
condition and security.
GROUND RUN
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
INITIAL
MECH OTHER
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
Chapter 96 5. Check the voltage regulator setting.
4. Start the helicopter and conduct ground run at 100% N
check for leaks and ensure all systems are operational and
parameters are within Flight Manual limitations.
to
R
5-00-00
Page 46 Rev. 16 25 FEB 2011
ECCN EAR99
Page 79
PERIODIC INSPECTION
5-20. 100-HOUR AIRFRAME PERIODIC INSPECTION
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
1. Do this inspection every 100 hours of operation or every
12 calendar months.
Chapter 5
Paragraph 5-16
through paragraph
5-19
2. Do all four events of the 100-hour progressive inspection.
INITIAL
MUCH OTHER
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 47/48
Page 80
Page 81
PROGRESSIVE INSPECTIONS
5-21. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 1 — MAIN ROTOR SYSTEM
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
Chapter 62 MAIN ROTOR SYSTEM
1. Verify main rotor flap restraint for freedom of movement,
and for condition and security.
2. Examine static stops and mast for evidence of mast
bumping.
3. Remove main rotor blade leading edge erosion protection
tape, if installed.
4. Examine main rotor blades for cleanliness and overall
condition. Examine for cracks, corrosion and de-bonding of
doublers.
5. Examine leading edge of blades for corrosion and erosion.
ECCN EAR99
Restore contour as necessary.
6. Examine the tip weight cap for corrosion, cracks, erosion,
and deformation.
5-00-00
25 FEB 2011 Rev. 16 Page 49
Page 82
BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-21. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
7. If applicable, reinstall main rotor blade leading edge
erosion protection tape.
8. Examine the following main rotor hub assembly
components for condition and security:
a. Mast nut
b. Trunnion
c. Pillow blocks
d. Grips
e. Pitch horns
f. Sta tic stops
9. Examine pitch horn trunnion bearings for evidence of wear,
damage, and for security.
INITIAL
MECH OTHER
10. Examine main rotor yoke for corrosion or mechanical
damage as follows:
BHT-206L-CR&O a. Examine fillet radius of both yoke spindles inboard of
wear sleeves for evidence of corrosion. If corrosion is visible,
remove with fine abrasive pad (C-407). If corrosion cannot be
removed with pads, or is extensive, disassemble hub for
inspection and repair.
If the main rotor hub must be disassembled, omit
remaining steps.
b. Examine entire yoke centre section (inboard and
outboard surfaces) for damage.
c. Touch up all repaired areas or areas of bare metal in
accordance with applicable main rotor hub inspection and repair
instructions.
5-00-00
Page 50 Rev. 16 25 FEB 2011
ECCN EAR99
Page 83
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-21. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
d. Ensure no sealant voids are visible around shields or
wear sleeve, strap fittings, and grip closure. Recoat with sealant
(C-308) as required. On main rotor hub assemblies up to and
including P/N 206-011-100-025, coat the remaining exposed
fillet radius and repaired surfaces with a film of corrosion
preventive compound (C-101).
ZONE 2 — TAIL ROTOR ASSEMBLY
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
Chapter 64 TAIL ROTOR ASSEMBLY
1. Clean tail rotor blades to maintain visibility of warning
stripes.
BHT-206L-CR&O 2. Examine the following tail rotor hub assembly components
for condition and security of attachment:
INITIAL
MECH OTHER
a. Yok e
b. Pitch horns
c. Trunnion and trunnion caps
d. Counterweight hardware
Chapter 64 3. Examine tail rotor blades as follows:
a. Tip block rivets for damage, corrosion, erosion, and
looseness.
b. Skin for bulges, nicks, dents, scratches, or other
damage.
c. Deformed or cracked skin in the area of the chordwise
weights.
d. Leading edge for erosion, nicks, dents or scratches.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 51
Page 84
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-21. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
e. Bonded joints of blade skin mating area for suspected
voids or cracks. Pay particular attention in the area of tip block
and doublers.
f. Feathering bearings for looseness and cracks in uniball.
4. Examine the following tail rotor hub and blade assembly
attaching components for condition and security:
a. Spacer
b. Rubber bumper
c. Static stop
d. Nut
e. Balance wheel
5. Check dynamic balance of tail rotor hub and blade
assembly and adjust as required during ground run.
INITIAL
MECH OTHER
GROUND RUN
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
5-00-00
Page 52 Rev. 16 25 FEB 2011
ECCN EAR99
Page 85
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-21. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 1 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
4. Start the helicopter and conduct ground run at 100% N
check for leaks and ensure all systems are operational and
parameters are within Flight Manual limitations.
INITIAL
MECH OTHER
to
R
ECCN EAR99
5-00-00
25 FEB 2011 Rev. 16 Page 53/54
Page 86
Page 87
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 3 — FORWARD DECK
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Make sure
they are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
AIRFRAME (FORWARD DECK)
Chapter 71 1. Open and examine forward fairing for condition and
security.
2. Remove and examine transmission cowling for condition.
3. Examine all fairing and cowling latches and/or fasteners for
condition.
4. Examine top deck for condition, leaks and security.
Chapter 53 5. Clean transmission deck.
6. Examine air indication cowling and plenum for damage,
obstructions and cleanliness. Examine intake fairing windows
ECCN EAR99
for damage and cleanliness.
7. Examine inlet screen (if applicable) for missing or damaged
wires and rivets.
5-00-00
25 FEB 2011 Rev. 16 Page 55
Page 88
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
8. Examine particle separator (if applicable) vortex tubes,
ejector tubes, and ejector nozzles for cleanliness, condition, and
security.
9. Examine forward deck drain(s) to ensure absence of
obstruction.
10. Examine antennas for condition and security.
Chapter 67 CONTROLS
1. Examine the following flight control components for signs
of interference, corrosion, wear, mechanical damage and
security:
a. Control tubes.
b. Links.
c. Rod and bearings.
INITIAL
MECH OTHER
d. Bellcranks.
e. Bellcrank supports.
f. Attaching bolts and nuts.
2. Inspect main rotor pitch links with a 3X magnifying glass for
damage, corrosion and cracks. Give particular attention to
swaged ends at jam nut or inserts.
Chapter 76 3. Examine N
and security. Pay particular attention to the jackshaft assembly
for damage or evidence or twisting.
4. Verify all control tubes and bellcranks for freedom of travel
throughout range.
Chapter 62 SWASHPLATE ASSEMBLY AND MAST
1. Clean swashplate assembly and mast.
2. Disconnect main rotor pitch links from outer ring.
control linkages on forward deck for condition
2
5-00-00
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ECCN EAR99
Page 89
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
3. Disconnect idler (drive) link from outer ring.
4. Examine swashplate drive assembly for axial, radial, and
accumulative wear.
5. Disconnect boot from swashplate outer ring and lift up
temporarily. Examine boot for evidence of deterioration.
6. Verify condition of duplex bearing, before lubrication, as
follows:
a. Rotate outer ring to check duplex bearing for condition.
Bearing must be smooth and show no evidence of roughness,
binding, dragging, or looseness.
7. Examine pivot sleeve slot sidewalls for wear or
deterioration.
8. Examine pivot sleeve bearings for wear, deterioration and
evidence of excessive axial play between pivot sleeve and
swashplate support.
INITIAL
MECH OTHER
9. Examine collar set bushings for cracks and damage.
10. Examine swashplate support and uniball surfaces for
condition.
11. Examine collective lever to sleeve assembly pins and
bushings for condition.
12. Examine inner ring for condition. Examine for evidence of
contact with sleeve assembly.
13. Examine outer ring for condition.
14. Examine the upper inside diameter of swashplate support
for evidence of contact with the mast pole.
15. Verify and adjust swashplate tilt friction as required.
a. Value must be between 15 to 32 pounds (67 to 142 N).
If out of limits, adjust to 15 to 32 pounds (67 to 142 N) and
check again.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 57
Page 90
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
16. Connect and secure boot, idler (drive) link and main rotor
pitch links to outer ring.
17. Examine swashplate assembly for condition and security.
18. Examine mast for condition.
Chapter 62 19. Ensure no sealant voids are visible around the swashplate
drive collar set. Re-coat with adhesive (C-307) as required.
Chapter 29 HYDRAULIC SYSTEM
1. Examine rigid and flexible fluid lines for chafing, leaks and
security.
2. Examine hydraulic pump for leaks and general condition.
3. Examine hydraulic pump shaft splines, rotor tachometer
splines, and oil pump splines for excessive wear.
Chapter 12 4. Lubricate hydraulic pump shaft splines and rotor
tachometer splines.
INITIAL
MECH OTHER
5. Examine hydraulic reservoir for leaks and general
condition.
6. Examine servo actuators for leaks, condition and security.
7. Examine servo actuator support for condition.
Chapter 67 8. Verify linkage pivot bolts on hydraulic servo actuators for
freedom of rotation and security.
9. Examine hydraulic filter red indicator button (two locations).
Button should not be extended.
Chapter 12 10. Verify fluid level in hydraulic tank. Replenish as required.
Replace fluid if color has changed color or if fluid emits bad
odor.
11. Examine manifold, relief valve, and solenoid valve for
leaks, condition and security.
5-00-00
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ECCN EAR99
Page 91
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 63 TRANSMISSION AND PYLON ASSEMBLY
1. Examine the following pylon support components:
a. Transmission link assemblies and bearings for damage
and deterioration.
b. Nodal beam flexures for condition and security.
c. Forward and aft nodal beam deck supports for condition
and security.
d. Nodal beam stops for evidence of excessive contact
with nodal beam arms.
e. Transmission restraint for damage and spherical
bearings for excessive wear and security.
f. Stop mount for condition and security. Stop mount
bushings for wear.
INITIAL
MECH OTHER
g. All pylon support elastomeric components for evidence
of deterioration.
h. All pylon support hardware for security of attachment.
2. Examine transmission assembly for condition and security.
3. Examine transmission assembly for evidence of oil
leakage.
4. Examine all fluid lines for chafing, damage and evidence of
leakage.
5. Examine transmission oil for evidence of contamination.
6. Examine transmission oil filter bypass indicator for
condition. Bypass button should not be extended.
7. Inspect all transmission chip detectors for accumulated
material.
Chapter 96 8. Perform functional test of all transmission chip detectors.
ECCN EAR99
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25 FEB 2011 Rev. 16 Page 59
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BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
9. Ensure no sealant voids are visible around forward and aft
nodal beam deck mounted supports and isolation mount.
Recoat with sealant (C-308) as required.
Chapter 63 MAIN DRIVESHAFT
1. Inspect main driveshaft as follows:
TEMP-PLATE indicator dots are of a white or gray
color that turn black when exposed to an
overtemperature condition. Chemical contamination
can also cause the indicating dots to turn black.
a. For 206L3 helicopters, inspect main driveshaft for visual
damage and couplings for grease leakage. Check driveshaft for
freedom and smoothness of axial movement. Inspect bolts for
security. Inspect TEMP-PLATES for evidence of overheating
indication, deterioration, debonding, or excessive discoloration
of the epoxy overcoating.
INITIAL
MECH OTHER
2. For 206L3+ IGW Upgrade helicopters, examine the engine
to transmission KAflex driveshaft for condition and security.
Examine the components as follows:
a. Driveshaft for cracks, corrosion, and surface damage.
b. Flexframe and bolts for condition and signs of slippage.
Chapter 96 ELECTRICAL
1. Examine all electrical components, wires, cables and
connectors in the area of the forward deck and transmission for
chafing, general condition, and security.
5-00-00
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ECCN EAR99
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BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-22. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 2 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
GROUND RUN
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
4. Start the helicopter and conduct ground run at 100% N
check for leaks and ensure all systems are operational and
parameters are within Flight Manual limitations.
to
R
INITIAL
MECH OTHER
ECCN EAR99
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Page 94
Page 95
PROGRESSIVE INSPECTIONS
5-23. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3
DATE: __________________W.O. _____________________
FACILITY: __________________________________________
HELICOPTER S/N: ___________________________________
REGISTRY NO.: _____________________________________
TOTAL TIME:_______________________________________
SIGNATURE:________________________________________
BHT-206L3-MM-1
DATA REFERENCE INSPECTION TASK DESCRIPTION
ZONE 4 — POWER PLANT
Chapter 11 PLACARDS AND MARKINGS
1. Examine the placards, decals and markings. Ensure they
are readable, correctly applied and in agreement with the
applicable configuration of your helicopter.
INITIAL
MECH OTHER
AIRFRAME (POWER PLANT AREA)
Chapter 71 1. Examine firewalls for condition and security.
Chapter 53 2. Examine engine cowlings and doors for condition and
security. Using a bright light and mirror, inspect exposed upper
and lower edges of the joints between aluminium longerons and
titanium engine pan. Edge of sealant coating should be visible.
No indications of corrosion or cracks are acceptable.
3. Examine engine pan area for evidence of loose fasteners
and damage. Restore cracked or missing sealant form engine
pan.
4. Examine engine pan drains. Make sure that they are not
clogged.
Chapter 28 5. Examine airframe fuel filter assembly for evidence of
leakage and security.
ECCN EAR99
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BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-23. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 71 6. Examine engine mount legs for condition and security. Pay
particular attention for loose fasteners.
7. Examine engine mount fittings for condition and security.
Applicable Service
Instruction
Chapter 96 9. Examine the primary electrical ground connection in
Rolls-Royce 250-C30
Series Operation and
Maintenance Manual,
14W2
Chapter 71 2. Examine engine inlet bellmouth for obstruction and general
8. Examine rotor brake (if installed) for condition and security.
engine pan area for condition and security
POWER PLANT
1. Perform engine inspection per the applicable Rolls-Royce
Operation and Maintenance Manual.
condition.
INITIAL
MECH OTHER
3. Examine engine compartment hardware for security of
attachment.
4. Examine engine for evidence of fuel or oil leaks.
5. Examine all flexible and rigid lines for condition and
security.
a. Pay particular attention for chafing damage and kinked
lines.
6. Examine exhaust stack for condition and security.
7. Examine all engine-mounted accessories for condition and
security.
Chapter 75 8. Examine the engine anti-ice solenoid valve for condition
and security.
Chapter 76 9. Inspect fuel control lever bolt hole and bolt for wear.
Replace parts as required.
Chapter 71 10. Inspect engine chip detectors for accumulated material.
5-00-00
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ECCN EAR99
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BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-23. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 96 11. Perform operational check of all engine chip detectors.
Chapter 95 12. Perform operational check of turbine outlet temperature
system.
Chapter 76 13. Examine engine controls for condition and security.
14. Verify operation of engine N
control as follows:
1
a. Ensure proper throttle friction.
b. Check freedom of full throttle grip travel and idle release
operation. Return to closed position. Check copilot throttle if
installed.
c. Ensure fuel control stop lever contact with minimum and
maximum stops before throttle grip reaches travel limit.
If dual controls are installed, it is permissible for
pointer to be 0.078 inch (1.98 mm) below 40° mark
when copilot twist grip is used.
INITIAL
MECH OTHER
ECCN EAR99
d. Rotate throttle grip to idle detent, fuel control pointer
should be no more than 0.01 inch (0.25 mm) below the 40°
mark on the quadrant.
e. Verify control linkage for excessive looseness, lost
motion, and binding.
15. Verify operation of engine N
a. Position N
governor actuator to full DECREASE
2
control as follows:
2
(extended).
b. Lift collective stick full up.
c. Position N
governor actuator to full INCREASE
2
(retracted).
d. Verify for clearance between governor stop and lever
stop arm.
25 FEB 2011 Rev. 16 Page 65
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BHT-206L3-MM-1
NOTE
PROGRESSIVE INSPECTIONS
5-23. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
e. Lower collective stick full down.
f. Position N
governor actuator to full DECREASE
2
(extended).
g. Verify for clearance between governor stop and lever
stop arm.
Chapter 71 h. Verify control linkage for excessive looseness, lost
motion, and binding.
Chapter 71
Chapter 12
16. Examine N
and N2 tachometer generator shaft splines
1
and gearbox adapter splines for condition. Clean and lubricate
shaft splines.
FUEL SYSTEM
Chapter 28 1. Inspect airframe fuel filter head as follows:
INITIAL
MECH OTHER
The following step does not apply to helicopters
equipped with fuel filter assembly 222-366-621-103.
a. Remove outlet port fitting from filter head.
b. Pass a 0.020 inch (0.50 mm) wire through the bleed
hole in outlet port side of filter head to ensure hole is not
obstructed.
2. Replace airframe fuel filter element.
Chapter 28 3. Purge airframe and engine fuel system as follows:
a. Turn both fuel boost pumps ON.
b. Depress airframe fuel filter bypass valve “press to test”
button on fuel filter head until there is no evidence of air coming
out the lower fuel filter drain port and out of the fuel filter outlet
supply line.
5-00-00
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ECCN EAR99
Page 99
BHT-206L3-MM-1
PROGRESSIVE INSPECTIONS
5-23. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Rolls-Royce 250-C30
Series Operation and
Maintenance Manual,
14W2
Chapter 71 1. Remove starter generator. Examine mounting pad and
Chapter 96 2. Examine commutator for wear. Replace starter generator if
Chapter 71 4. Examine cooling duct and retention clamp for condition
c. Then proceed with Rolls-Royce engine fuel system
purging procedure.
4. Ensure air is purged from fuel filter head and check for fuel
leaks during ground run.
STARTER GENERATOR
clamp for condition.
not smooth and bright or if showing excessive wear.
3. Inspect brushes for wear.
and security.
INITIAL
MECH OTHER
5. Examine the splines on starter generator shaft and engine
gear shaft.
DRIVETRAIN
Chapter 63 1. Examine freewheel assembly for condition leaks and
security.
Chapter 63
Chapter 96
Chapter 65 3. Examine forward short shaft (steel) disc pack couplings for
Chapter 12 5. Lubricate forward short shaft (steel) splined adapters.
2. Examine the freewheel unit chip detector for accumulated
material. Perform operational check of freewheel unit chip
detector. (Refer to transmission chip detector caution system.)
condition and security.
4. Examine forward short shaft (steel) splined adapters for
wear.
ECCN EAR99
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8 APR 2011 Rev. 17 Page 67
Page 100
BHT-206L3-MM-1
CAUTION
PROGRESSIVE INSPECTIONS
5-23. 300-HOUR AIRFRAME PROGRESSIVE INSPECTION — EVENT NO. 3 (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
Chapter 65 6. Torque check forward short shaft disc pack coupling
fasteners 50 to 70 inch-pounds (5.7 to 7.9 Nm). For 206L3+
IGW Upgrade helicopters, torque check forward short shaft disc
pack coupling fasteners 150 to 180 inch-pounds (16.9 to
20.3 Nm).
Chapter 96 ELECTRICAL
1. Examine all electrical components, wires, cables, and
connectors in the power plant area for chafing, general
condition, and security.
2. Verify illumination of airframe fuel filter caution light by
depressing differential switch “press to test” button on filter
head.
GROUND RUN
INITIAL
MECH OTHER
GROUND RUN OF HELICOPTER TO BE
ACCOMPLISHED BY QUALIFIED PERSONNEL
ONLY.
Chapter 12 1. Make sure applicable servicing requirements have been
carried out.
2. Check oil level of transmission, hydraulic tank, engine and
rail rotor gearbox prior to running helicopter.
3. Make sure that helicopter is ready for ground run and that
surrounding area is clear.
BHT-206L3-FM-1
(BHT-206L4-FM-1 for
206L3+ IGW
Upgrade)
4. Start the helicopter and conduct ground run at 100% N
a minimum of 2 minutes to check for leaks and ensure all
systems are operational and parameters are within Flight
Manual limitations.
R
for
5-00-00
Page 68 Rev. 17 8 APR 2011
ECCN EAR99
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