[Federal Register Volume 76, Number 66 (Wednesday, April 6, 2011)]
[Rules and Regulations]
[Pages 18865-18869]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-8133]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0323; Directorate Identifier 2011-SW-005-AD;
Amendment 39-16651; AD 2011-08-01]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model 212
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are superseding an existing emergency airworthiness
directive (EAD) for the Bell Helicopter Textron, Inc. (Bell) Model 212
helicopters with a certain main rotor hub inboard strap fitting
(fitting) installed. That EAD requires, before further flight, removing
certain serial-numbered fittings and replacing them with airworthy
fittings. It also requires performing a magnetic particle inspection
(MPI) on fittings with certain serial numbers (S/Ns) to inspect for a
crack. If a crack is found, the cracked fitting must be replaced with
an airworthy fitting, and certain data must be reported to the FAA.
This airworthiness directive (AD) retains the requirements of that EAD
and expands the applicability to require performing an MPI for a crack
on additional serial-numbered fittings. This AD is prompted by the
determination that certain fittings were not manufactured in accordance
with the approved manufacturing processes and controls. In total, eight
fittings have been found that have cracks. We are issuing this AD to
prevent failure of a fitting, loss of a main rotor blade, and
subsequent loss of control of the helicopter.
DATES: This AD is effective April 21, 2011.
We must receive any comments on this AD by June 6, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101, telephone
(817) 280-3391, fax (817) 280-6466, or at http://www.bellcustomer.com/files/.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aerospace Engineer,
Rotorcraft Directorate, Rotorcraft Certification Office, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137, phone: (817) 222-5170; fax:
(817) 222-5783; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
[[Page 18866]]
Discussion
This AD supersedes EAD 2010-25-51, issued November 24, 2010 (EAD
2010-25-51), which superseded EAD 2010-24-52, issued November 19, 2010
(EAD 2010-24-52). EAD 2010-24-52 superseded EAD 2010-24-51, issued
November 12, 2010 (EAD 2010-24-51). EAD 2010-24-51, EAD 2010-24-52, and
EAD 2010-25-51 were all issued for the Bell Model 212 helicopters with
a certain fitting installed.
EAD 2010-24-51, the initial EAD, was issued for all Bell Model 212
helicopters with a fitting, part number (P/N) 212-010-103-007, S/Ns
9956 through 10005 with a prefix of ``A''. That EAD required, before
further flight, removing any affected fitting and replacing it with an
airworthy fitting. That EAD also prohibited installing any affected
fitting on any helicopter. That EAD was prompted by an accident that
resulted in several fatalities. During the investigation of the
accident, a crack was found on a fitting. Subsequently, four additional
fittings from the same manufacturing lot were inspected, and two were
found to exhibit the same type of cracking. We issued EAD 2010-24-51 to
remove this lot from service to prevent failure of a fitting, loss of a
main rotor blade, and subsequent loss of control of the helicopter.
After we issued EAD 2010-24-51, additional fittings from a
different manufacturing lot were found to have the same type of crack
as that found on the fitting involved in the accident. Therefore, we
issued superseding EAD 2010-24-52 to require the same actions as EAD
2010-24-51, and to expand the applicability to include additional
fittings. In addition to S/Ns 9956 through 10005 with a prefix of
``A'', EAD 2010-24-52 added S/Ns 52, 54, 55, 57 through 65, 67, 69, 70,
71, 73, 103, 112, 113, 137, and 139 with a prefix of ``SH'' to the
applicability. EADs 2010-24-51 and 2010-24-52 were issued as interim
actions to address a known unsafe condition, and Bell continued to
investigate the cause of the cracking.
Because the root cause of the cracking had not been determined, and
due to the severity of a fitting failure, we issued superseding EAD
2010-25-51 to require the same action as EAD 2010-24-52 and to also
require performing an MPI on fittings with S/Ns 9911 through 9955,
10006 through 10049, 10075 through 10174, 10455 through 10460, 10581
through 10655, 10742 through 10791, and 10862 through 10946 with a
prefix of ``A'' to detect a crack on those fittings. If you find a
crack, you are required to replace the cracked fitting with an
airworthy fitting, and within 24 hours, report the information
specified in Appendix 1 of the EAD to the Manager, Rotorcraft
Certification Office. If you do not find a crack, you are required to
reidentify and refinish the fitting in accordance with the specified
portion of Alert Service Bulletin (ASB) 212-10-142, dated November 24,
2010 (ASB 212-10-142).
Actions Since AD Was Issued
Since we issued EAD 2010-25-51, additional fittings with cracks
were found using the MPI process. In response to these findings, Bell
issued ASB 212-10-142, Revision A, dated March 21, 2011, that specifies
performing an MPI for a crack on all serial-numbered fittings with the
same part number in stock or in service. We have determined that
certain fittings were not manufactured in accordance with the approved
manufacturing processes and controls. Due to the severity of a fitting
failure, this superseding AD is being issued to continue to require
replacing certain serial-numbered fittings, and to expand the
applicability to require performing an MPI for a crack on the remaining
serial numbers of the fittings with the same part number. Serial-
numbered fittings affected by this superseding AD are listed in Table 1
of the Applicability section of this AD. This superseding AD is being
issued to prevent failure of a fitting, loss of a main rotor blade, and
subsequent loss of control of the helicopter.
Relevant Service Information
We reviewed Bell Alert Service bulletin (ASB) No. 212-10-141, dated
November 11, 2010 (ASB-212-10-141), which specified the immediate
removal of the affected fittings, S/Ns A-9956 through A-10005, from
service. We also reviewed ASB No. 212-10-141, Revision A, dated
November 18, 2010 (ASB 212-10-141 Rev. A), which incorporates
additional S/Ns of the affected fittings and specifies removing the
affected serial-numbered fittings from service. In ASB 212-10-141, Bell
states that they have determined that the fittings may not have been
manufactured in accordance with the engineering design requirements and
may fracture as a result of the nonconformance.
We have also reviewed Bell ASB 212-10-142, initial release, dated
November 24, 2010 (ASB 212-10-142) which specifies performing an MPI on
fittings with certain S/Ns to detect a crack on those fittings.
Finally, we have reviewed Bell ASB 212-10-142, Revision A, dated
March 21, 2011 (ASB 212-10-142 Rev. A), which includes all serial-
numbered fittings except those already inspected and marked with
``FM''. ASB 212-10-142 Rev. A specifies 1) within 25 hours time-in-
service (TIS) or 15 days, whichever comes first, for all fittings with
less than 400 hours TIS; or 2) within 100 hours TIS or 30 days,
whichever comes first, for all fittings with 400 or more hours but less
than 800 hours TIS; or 3) at the next main rotor teardown inspection or
next tension-torsion strap replacement, whichever comes first, for all
fittings with more than 800 hours TIS, performing a one-time MPI of the
fitting, P/N 212-010-103-007, with all S/Ns in stock or in service.
Finally, ASB 212-10-142 Rev. A states that all fittings, S/Ns A-11021
and subsequent, SH-053, SH-066, SH-072, SH-074 through SH-102, SH-104
through SH-111, SH-114 through SH-136, SH-138, and SH-140 and
subsequent are not affected by ASB 212-10-142 Rev. A. Bell states that
a one-time MPI of the affected fittings is required to ensure continued
airworthiness of the fittings.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other helicopters of this same type
design.
AD Requirements
This AD supersedes EAD 2010-25-51 and requires the following:
Before further flight, for any helicopter with a fitting,
S/N 9956 through 10005, with a prefix of ``A'', and S/N 52, 54, 55, 57
through 65, 67, 69, 70, 71, 73, 103, 112, 113, 137, and 139 with a
prefix of ``SH'', replace the fitting with an airworthy fitting. Any
fitting with a S/N identified in this paragraph is no longer eligible
for installation on any helicopter.
Before further flight, for any helicopter with a fitting,
S/N 9911 through 9955, 10006 through 10049, 10075 through 10174, 10455
through 10460, 10581 through 10655, 10742 through 10791, and 10862
through 10946, with a prefix of ``A'', perform an MPI of each fitting
for a crack. If the fitting is cracked, replace it with an airworthy
fitting. If the fitting is not cracked, reidentify and refinish the
fitting.
For any fitting with a serial number identified in
paragraph (h) in the Compliance section of this AD, perform an MPI of
each fitting for a crack:
[cir] For any fitting with 400 or less hours TIS, perform an MPI
within 25
[[Page 18867]]
hours TIS or 15 days, whichever comes first.
[cir] For any fitting with more than 400 hours but less than 800
hours TIS, perform an MPI within 100 hours TIS or 30 days, whichever
comes first.
[cir] For fittings with 800 hours or more TIS, perfrom an MPI at
the next main rotor hub teardown inspection or tension-torsion strap
replacement, whichever comes first.
[cir] If a fitting is cracked, replace it with an airworthy
fitting. If a fitting is not cracked, reidentify and refinish the
fitting.
If a crack is found on any fitting, within 24 hours,
report the information requested in Appendix 1 of this AD to the
Manager, Rotorcraft Certification Office, FAA, 2601 Meacham Blvd, Fort
Worth, Texas 76137, or e-mail [email protected].
Differences Between the AD and the Service Information
This AD differs from ASB 212-10-142 Rev. A as follows:
We do not require returning parts to Bell.
We require performing an MPI before further flight on
certain S/N fittings included in the initial release of ASB 212-10-142.
We require sending information to the Rotorcraft
Certification Office and not to Bell.
Bell uses the term ``total time-in-service'' to describe
compliance times, and we use the term ``time-in-service.''
We specify S/Ns in our AD, and Bell does not specify S/Ns
in ASB 212-10-142 Rev. A.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA finds that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because we
evaluated all the available information and determined the unsafe
condition described is likely to exist or develop in other helicopters
of this same type design. Therefore, we find that notice and
opportunity for prior public comment are impracticable because of the
short compliance times, and that good cause exists for making this
amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the Docket Number FAA-2011-0323 and ``Directorate Identifier 2011-SW-
005-AD'' at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy
aspects of this AD. We will consider all comments received by the
closing date and may amend this AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 84 helicopters of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost helicopter operators
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(a) For any fitting, S/N 9956 through 40 work-hours x $85 per $2,367 $5,767 $415,224
10005 and a prefix of ``A''; or a S/N hour = $3,400.
of 52, 54, 55, 57 through 65, 67, 69,
70, 71, 73, 103, 112, 113, 137, 139
with a prefix of ``SH''; replace the
fitting with an airworthy fitting
(assumes action affects 72 fittings).
(c) For any fitting affected by this 40 work-hours x $85 per 0 3,400 40,800
AD with a S/N not identified in hour = $3,400.
paragraph (a) of this table, perform
an MPI on each fitting for a crack
unless documentation exists of any
previous MPI performed during
regularly scheduled maintenance
(assumes action affects 12 fittings).
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We estimate a total cost of $456,024 to do the actions required by
this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction,
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 18868]]
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends Part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2011-08-01 Bell Helicopter Textron, Inc. (Bell): Amendment 39-16651;
Docket No. FAA-2011-0323; Directorate Identifier 2011-SW-005-AD.
Effective Date
(a) This AD is effective on April 21, 2011.
Other Affected ADs
(b) This AD supersedes Emergency AD 2010-25-51, issued on
November 24, 2010, Directorate Identifier 2010-SW-096-AD.
Applicability
(c) This AD applies to Model 212 helicopters certificated in any
category, with a main rotor hub inboard strap fitting (fitting),
part number (P/N) 212-010-103-007, installed, with the serial
numbers (S/Ns) listed in the following Table 1:
Table 1
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Serial numbers with a prefix of:
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``A'' or ``A-FS'': 7 through 10946.
``A1'': 430 through 7606.
``DI'': 22296 through 22681.
``EA'': 333 through 381.
``LK'': 4619 through 4631.
``MB'': 11908 through 11916.
``SH'': 52, 54, 55, 57 through 65, 67, 69, 70, 71, 73, 103, 112, 113,
137, and 139.
``WR'': 275 through 319.
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Unsafe Condition
(d) This AD is prompted by a recent accident that resulted in
several fatalities. During the investigation of the accident, a
crack was found on a fitting. We have determined that certain
fittings were not manufactured in accordance with approved
manufacturing processes and controls. Due to the severity of a
fitting failure, we are requiring replacing certain serial-numbered
fittings, and we are expanding the applicability to require
performing a magnetic particle inspection (MPI) for a crack on the
remaining serial numbers of the fittings with the same part number.
The actions specified by this AD are intended to prevent failure of
a fitting, loss of a main rotor blade, and subsequent loss of
control of the helicopter.
Compliance
(e) Required as indicated, unless accomplished previously.
(f) Before further flight, for any helicopter with a fitting,
serial number (S/N) 9956 through 10005 with a prefix of ``A'', and
S/N 52, 54, 55, 57 through 65, 67, 69, 70, 71, 73, 103, 112, 113,
137, and 139 with a prefix of ``SH'' installed, replace the fitting
with an airworthy fitting. Any fitting with a S/N identified in this
paragraph is no longer eligible for installation on any helicopter.
(g) Before further flight, for any helicopter with a fitting, S/
N 9911 through 9955, 10006 through 10049, 10075 through 10174, 10455
through 10460, 10581 through 10655, 10742 through 10791, and 10862
through 10946 with a prefix of ``A'', perform an MPI of each fitting
for a crack. If a fitting is cracked, replace it with an airworthy
fitting. If a fitting is not cracked, reidentify and refinish the
fitting using a vibrating stylus (not to exceed 0.005 inch depth nor
to extend within 0.10 inch of part edge) by adding ``FM'' at the end
of the P/N. Touch up the reworked area with brush cadmium plating or
zinc chromate primer. Reidentify the historical service records with
``FM'' at the end of the P/N.
Note 1: The Bell Model 212 Component, Repair, and Overhaul
Manual, which is not incorporated by reference, contains additional
information about MPI procedures.
(h) For any fitting with a S/N identified in Table 1 of the
Applicability section of this AD, and not identified in paragraph
(f) or (g) of this AD, perform an MPI of each fitting for a crack as
follows:
(1) For a fitting with 400 or less hours time-in-service (TIS),
perform an MPI within 25 hours TIS or 15 days, whichever comes
first.
(2) For a fitting with more than 400 but less than 800 hours
TIS, perform an MPI within 100 hours TIS or 30 days, whichever comes
first.
(3) For a fitting with 800 or more hours TIS, perform an MPI at
the next main rotor hub teardown inspection or tension-torsion strap
replacement, whichever comes first.
(4) If a fitting is cracked, replace it with an airworthy
fitting.
(5) If a fitting is not cracked, reidentify and refinish the
fitting in accordance with the instructions in paragraph (g) of this
AD.
(i) Within 24 hours after finding any cracked fitting, report
the information requested in Appendix 1 of this AD to the Manager,
Rotorcraft Certification Office, to the address, fax number, or
email specified in the Appendix.
Paperwork Reduction Act Burden Statement
(j) A federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid Office of
Management and Budget (OMB) Control Number. Under the provisions of
the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the OMB has
approved the information collection requirements contained in this
AD and has assigned OMB Control Number 2120-0056. Public reporting
for this collection of information is estimated to be approximately
5 minutes per response, including the time for reviewing
instructions, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA
at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Subject
(k) The Joint Aircraft System Component/Air Transport
Association of America Code is 6220: Main rotor hub.
Alternative Methods of Compliance (AMOCs)
(l) The Manager, Rotorcraft Certification Office, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the ACO, send it to the attention of the
person identified in the ``Additional Information'' section of this
AD.
Note 2: Before using any approved AMOC, we request that you
notify your appropriate principal inspector, or if you have no
principal inspector, your local Flight Standards District Office.
Additional Information
(m)(1) For service information identified in this AD, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101,
telephone (817) 280-3391, fax (817) 280-6466, or at http://www.bellcustomer.com/files/.
(2) You may review copies of the service information at the FAA,
Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas.
(3) Bell Helicopter Alert Service Bulletin No. 212-10-141,
Revision A, dated November 18, 2010, and Alert Service Bulletin No.
212-10-142, Revision A, dated March 21, 2011, contain additional
guidance pertaining to the subject of this AD but are not
incorporated by reference. A picture of a crack indication on an
actual fitting is shown in Figure 1 of Bell Alert Service Bulletin
212-10-142, Rev. A.
Appendix 1 to AD 2011-08-01
AD Compliance Inspection Report (Sample Format)
Provide the following information and mail, fax, or e-mail
report to: Manager, Rotorcraft Certification Office, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137, fax (817) 222-5783, e-mail
[email protected].
[[Page 18869]]
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Aircraft Registration No.
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Helicopter Serial No.
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Helicopter Owner/Operator.
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Contact Phone No.
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Fitting Part Number.
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Fitting Serial Number.
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Hours Time-in-Service on Fitting at
Time of Inspection.
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Description of Findings.
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Who Performed the Inspection?
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Date and Location the Inspection was
Performed.
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Describe the crack size, location,
orientation (provide a sketch or
pictures with the fitting part and
serial numbers).
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Provide any other comments.
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Issued in Fort Worth, Texas, on March 29, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-8133 Filed 4-5-11; 8:45 am]
BILLING CODE 4910-13-P