[Federal Register Volume 78, Number 29 (Tuesday, February 12, 2013)]
[Rules and Regulations]
[Pages 9793-9796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-02899]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0098; Directorate Identifier 2011-SW-039-AD;
Amendment 39-17339; AD 2013-03-16]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the Bell Helicopter Textron (Bell) Model 212 helicopters and
adopting requirements for Bell Model 204B, 205A, 205A-1, 205B and 210
helicopters with certain part-numbered main rotor hub inboard strap
fittings (fittings). This AD requires magnetic particle inspecting
(MPI) the fittings for
[[Page 9794]]
a crack, and if a crack exists, replacing the fittings with airworthy
fittings. This AD is prompted by reports of additional cracked fittings
and the determination that additional part-numbered fittings may not
have been manufactured in accordance with approved manufacturing
processes and controls. These actions are intended to identify a crack
in the fitting, which may lead to the fitting's failure, loss of a main
rotor blade, and subsequent loss of helicopter control.
DATES: This AD becomes effective February 27, 2013.
We must receive comments on this AD by April 15, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the economic evaluation, any
comments received, and other information. The street address for the
Docket Operations Office (telephone 800-647-5227) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
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/. You may review a copy of the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601
Meacham Blvd., Fort Worth, Texas, 76137, phone: (817) 222-5170; fax:
(817) 222-5783; email: [email protected].
SUPPLEMENTARY INFORMATION:
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 prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this rulemaking during the comment period. We will consider
all the comments we receive and may conduct additional rulemaking based
on those comments.
Discussion
On March 29, 2011, the FAA issued AD 2011-08-01, Amendment 39-16651
(76 FR 18865, April 6, 2011), which superseded previously existing
emergency AD 2010-25-51, for Bell Model 212 helicopters with a fitting,
part number (P/N) 212-010-103-007 and with a certain serial number (S/
N). AD 2011-08-01 retained the requirements of AD 2010-25-51 to replace
certain serial-numbered fittings and perform an MPI for a crack on
other serial-numbered fittings, and expanded the applicability to
require performing an MPI on additional serial-numbered fittings. The
AD based the compliance time for performing an MPI on the number of
hours time-in-service (TIS) of the fitting. That AD was prompted by
reports of cracks in fittings. Subsequently, the cracking was
determined to have been caused by the manufacturer's failure to follow
approved manufacturing processes and controls during the quenching
operation from the heat treating of the fittings.
Since AD 2011-08-01 was issued, two additional fittings were found
with a crack. Based on these additional reported cracks, we have
determined that a crack may occur in a fitting regardless of the hours
TIS. In addition, fitting P/Ns 204-012-102-001, -005, -009, 212-010-
103-005, and -101, which are used on other model helicopters, are
susceptible to the same type of cracking because they are of similar
design and manufacture to fitting P/N 212-010-103-007, which was the
subject of AD 2011-08-01. Failure of a fitting in flight may result in
the loss of a main rotor blade and subsequent loss of helicopter
control. Therefore, this AD reduces the compliance time for performing
an MPI of some serial-numbered fittings by requiring an MPI for all
applicable serial-numbered fittings within 25 hours TIS or 15 days,
whichever occurs first. This AD does not require you to report a
cracked fitting to the Rotorcraft Certification Office.
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 products of the same type design.
Related Service Information
We have reviewed Bell Alert Service Bulletin (ASB) No. 212-10-141,
Revision A, dated November 18, 2010, for the Model 212 helicopter,
which specifies the immediate removal from service of fittings with
certain S/Ns.
We have also reviewed ASB No. 204-11-66 for the Model 204B
helicopters; ASB No. 205-11-107 for the Model 205A and 205A-1
helicopters; ASB No. 205B-11-58 for the Model 205B helicopters; ASB No.
210-11-08 for the Model 210 helicopters; and ASB No. 212-10-142,
Revision B for the Model 212 helicopters; all dated May 31, 2011. These
ASBs specify:
For certain serial-numbered fittings with less than 400
flight hours, performing an initial MPI within 100 flight hours but
before the fitting reaches 425 flight hours or before November 26,
2011, whichever occurs first.
For certain serial-numbered fittings with more than 400
hours, performing an initial MPI within 25 flight hours or before
November 26, 2011, whichever occurs first.
Certain serial-numbered fittings that have already had an
MPI during main rotor hub assembly maintenance or during an overhaul do
not need an additional MPI. Historical records must be annotated to
show compliance during records inspection.
If defects are found, returning the removed strap fittings
to Bell.
If no defects are found, re-identifying the fitting by
adding an ``FM'' at the end of the part number and making a record
entry.
[[Page 9795]]
Performing a recurring MPI on all fittings, regardless of
S/N and prefix, at 1,200 hours or 24 months for all models, except the
Model 210, and at the tension-torsion (TT) strap replacement for the
Model 210 helicopters.
AD Requirements
This AD supersedes AD 2011-08-01 (76 FR 18865, April 6, 2011) and
requires for any Model 204B, 205A, 205A-1, 205B, 210 and 212 helicopter
with certain fittings the following actions:
Within 25 hours TIS or 15 days, whichever occurs first,
performing an MPI of each fitting for a crack.
If a fitting is cracked, before further flight, replacing
it with an airworthy fitting.
If a fitting is not cracked, re-identifying the fitting
and its component history card or equivalent record by adding ``FM'' at
the end of the P/N.
If an MPI has previously been performed on a fitting and the
component history card or equivalent record of the fitting has been re-
identified with ``FM'' at the end of the P/N, the requirements of this
AD have been met.
Differences Between This AD and the Service Information
This AD differs from the ASBs because we require an MPI within 25
hours time-in-service or 15 days, whichever occurs first, of any
fitting with an affected P/N and S/N. Bell requires different
compliance times depending on the hours TIS of the fitting. We do not
require the immediate removal of fittings, P/N 212-010-103-007, with
certain S/Ns because the MPI provides the necessary level of safety. We
do not require returning parts to Bell.
Costs of Compliance
We estimate that this AD affects 152 helicopters of U.S. registry
and that labor costs average $85 per work-hour. Based on these
estimates, we expect the following costs to comply with this AD:
We estimate that 304 fittings (2 per helicopter) will need
to be MPI inspected for a crack and that this task will require 40
work-hours. No parts are needed for the inspection, bringing the total
cost per helicopter to $3,400; $516,800 for all U.S. operators.
If a fitting is cracked, replacement parts will cost
$2,367 per fitting. Labor costs will not be an additional expense as
they can be absorbed as part of the inspection.
According to Bell's service information, some of the costs of this
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage by Bell.
Accordingly, we have included all costs in our cost estimate.
FAA's Justification and Determination of the Effective Date
Providing an opportunity for public comments prior to adopting
these AD requirements, would delay implementing the safety actions
needed to correct this known unsafe condition. Therefore, we find that
the risk to the flying public justifies waiving notice and comment
prior to the adoption of this rule because the required corrective
actions must be accomplished within 15 days, a very short time period
based on the average flight-hour utilization rate of these helicopters.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
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
We determined that 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, 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; and
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.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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 removing Amendment 39-16651 (76 FR
18865, April 6, 2011) and adding the following new airworthiness
directive (AD):
2013-03-16 Bell Helicopter Textron (Bell): Amendment 39-17339;
Docket No. FAA-2013-0098; Directorate Identifier 2011-SW-39-AD.
(a) Applicability
This AD applies to Model 204B, 205A, 205A-1, 205B, 210 and 212
helicopters, certificated in any category, with a main rotor hub
inboard strap fitting (fitting) with a part number (P/N) and serial
number (S/N) listed in Table 1 to paragraph (a) of this AD.
Table 1 to paragraph (a)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Helicopter models Fitting P/Ns Fitting S/Ns
--------------------------------------------------------------------------------------------------------------------------------------------------------
204B.................................... 204-012-102-001............ All.
[[Page 9796]]
204B, 205A and 205A-1................... 204-012-102-005............ All.
204B, 205A and 205A-1................... 204-012-102-009............ All, except S/Ns 7500 or larger with a prefix of ``A''.
212..................................... 212-010-103-005............ All.
212..................................... 212-010-103-007............ All, except S/Ns 140 or larger with a prefix of ``SH'' and except S/Ns 11021 or
larger with a prefix of ``A''.
205A-1, 205B and 210.................... 212-010-103-101............ All, except S/Ns 486 or larger with a prefix of ``SH,'' and except S/Ns 10997 or
larger with a prefix of ``A''.
--------------------------------------------------------------------------------------------------------------------------------------------------------
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the fitting
and the determination that additional part-numbered fittings may not
have been manufactured in accordance with approved manufacturing
processes and controls. This condition could result in failure of a
fitting, loss of a main rotor blade, and loss of helicopter control.
(c) Affected ADs
This AD supersedes AD 2011-08-01, Docket No. FAA-2011-0323,
Amendment 39-16651 (76 FR 18865, April 6, 2011), Directorate
Identifier 2011-SW-005-AD.
(d) Effective Date
This AD becomes effective February 27, 2013.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Within 25 hours time-in-service or 15 days, whichever occurs
first, perform a magnetic particle inspection (MPI) of each fitting
for a crack. If an MPI was already performed on a fitting resulting
in re-identifying the fitting with ``FM'' at the end of the P/N or
at the end of the P/N on the fitting's component history card or
equivalent record, then the requirements of this AD have been met.
(2) If a fitting is cracked, before further flight, replace it
with an airworthy fitting.
(3) If a fitting is not cracked, before further flight, re-
identify the fitting by adding ``FM'' at the end of the P/N using a
vibrating stylus. The depth of the ``FM'' must not exceed 0.005
inches or extend within 0.10 inch of the part's edge. Also, add
``FM'' at the end of the P/N on the fitting's component history card
or equivalent record.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, 2601 Meacham Blvd., Fort Worth, Texas, 76137,
phone: (817) 222-5170; fax: (817) 222-5783; email:
[email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
Bell Alert Service Bulletin (ASB) No. 212-10-141, Revision A,
dated November 18, 2010; and ASBs No. 204-11-66, No. 205-11-107, No.
205B-11-58, No. 210-11-08; and No. 212-10-142 Revision B, all dated
May 31, 2011, which are not incorporated by reference, contain
additional information about the subject of this AD. For this
service information, 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/. You may review this
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor
Head.
Issued in Fort Worth, Texas, on January 28, 2013.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-02899 Filed 2-11-13; 8:45 am]
BILLING CODE 4910-13-P