[Federal Register Volume 78, Number 131 (Tuesday, July 9, 2013)]
[Rules and Regulations]
[Pages 40954-40956]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15946]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0553; Directorate Identifier 2011-SW-041-AD;
Amendment 39-17502; AD 2013-13-14]
RIN 2120-AA64
Airworthiness Directives; Various Restricted Category Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for various
restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-
1F, UH-1H, UH-1L, and UH-1P helicopters with certain main rotor hub
inboard strap fittings (fittings) installed. This AD requires a
magnetic particle inspection (MPI) of the fittings for a crack, and if
there is a crack, replacing the fitting with an airworthy fitting. This
AD is prompted by reports of cracked fittings on Bell model helicopters
and the determination that these same part-numbered fittings may be
installed on various restricted category helicopters. These actions are
intended to detect a crack in a fitting, which may lead to failure of a
fitting, loss of a main rotor blade, and subsequent loss of helicopter
control.
DATES: This AD becomes effective July 24, 2013.
We must receive comments on this AD by September 9, 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 800-647-5527) 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 www.bellcustomer.com. You may
review 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 January 28, 2013, we issued AD 2013-03-16, Amendment 39-17339
(78 FR 9793, February 12, 2013), for Bell Model 204B, 205A, 205A-1,
205B, 210, and 212 helicopters with certain part-numbered fittings
installed. AD 2013-03-16 requires a one-time MPI of the fittings for a
crack, replacing the fittings with airworthy fittings if there is a
crack, and re-identifying the fitting by adding ``FM'' to the end of
its part-number (P/N) if there is no crack. The AD was prompted by
reports of cracks in the fittings. 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.
After AD 2013-03-16 was issued, we determined that the same part-
numbered Bell fittings may be installed on various restricted category
Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L,
and UH-1P helicopters and are susceptible to the same type of cracking.
Therefore, we are mandating the inspection requirements for the
applicable restricted category helicopters. While Bell is the
manufacturer of these helicopters, the type certificates are held by
other entities. The type certificate holders for the Model HH-1K, TH-
1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P
helicopters are: Arrow Falcon Exporters Inc.; AST, Inc.; Bell
Helicopter Textron, Inc..; Global Helicopter Technology, Inc.; Hagglund
Helicopters, LLC; JJASPP Engineering Services, LLC; Northwest
Rotorcraft, LLC; Overseas Aircraft Support, Inc.; Richards Heavylift
Helo, Inc.; Robinson Air Crane, Inc.; Rotorcraft Development
Corporation; San Joaquin Helicopters; Southern Helicopter, Inc.; and
Tamarack Helicopters, Inc. Southwest Florida Aviation International,
Inc. is the type certificate holder for the UH-1B (SW204 and SW204HP)
and UH-1H (SW205) helicopters.
The actions specified in this AD are intended to detect a crack in
a fitting, leading to a failure of the fitting, loss of a main rotor
blade, and subsequent loss of helicopter control.
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 these same type
designs.
Related Service Information
We have reviewed Bell Alert Service Bulletin (ASB) No. UH-1H-11-07
for Model UH-1H helicopters, dated May 31, 2011. The procedures
provided in
[[Page 40955]]
this ASB concern all applicable helicopters. This ASB specifies:
For fittings with less than 400 hours time-in-service
(TIS), performing an MPI within 100 flight hours but before the fitting
reaches 425 flight hours or before November 26, 2011, whichever occurs
first.
For fittings with more than 400 hours, performing an MPI
within 25 flight hours or before November 26, 2011, whichever occurs
first.
If cracks are found, replacing the fitting.
If no cracks are found, visually inspecting all edges for
raised material. If raised material is found, removing the material by
hand using an India stone, repeating the MPI inspection, and re-
identifying the fitting as described below. If the raised material
cannot be removed within specified limits, replacing the fitting.
If no cracks and no raised material are found, re-
identifying the fitting and historical service records by adding an
``FM'' at the end of the part number and marking a record entry.
AD Requirements
This AD requires:
Within 25 hours TIS or 15 days, whichever comes first,
performing an MPI of each fitting for a crack.
If a fitting has a crack, before further flight, replacing
the fitting with an airworthy fitting.
If a fitting has no crack, re-identifying the fitting and
its component history card or equivalent record by adding ``FM'' at the
end of the P/N.
Differences Between This AD and the Service Information
This AD differs from the ASBs in that we require an MPI within 25
hours TIS or 15 days, whichever comes first, of any fitting with an
applicable P/N and S/N. Bell requires different compliance times based
on the hours TIS of the fitting. We also do not require returning parts
to Bell. Finally, we do not require visually inspecting all edges for
raised material (shot peen rollover) on fittings with a certain P/N.
Interim Action
We consider this AD to be an interim action. Bell is investigating
the safety risks regarding the raised material at the fittings' edges.
Depending on the outcome of the investigation, we might consider
additional rulemaking.
Costs of Compliance
We estimate that this AD affects 300 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:
MPI of each set of fittings (two per helicopter) requires
40 work-hours for a labor cost of $3,400 per helicopter, $1,020,000 for
the fleet. No parts are needed.
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.
FAA's Justification and Determination of the Effective Date
We find that the risk to the flying public justifies waiving notice
and comment prior to the adoption of this rule because of the short
compliance time of 25 hours TIS or 15 days, whichever comes first, to
magnetic particle inspect for a crack in the fitting. As these
helicopters are often used in the timber industry and for firefighting,
they may accrue 25 hours TIS within a week. Failure of these fittings
could result in a catastrophic accident.
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 adding the following new airworthiness
directive (AD):
2013-13-14 Various Restricted Category Helicopters: Amendment 39-
17502; Docket No. FAA-2013-0553; Directorate Identifier 2011-SW-041-
AD.
(a) Applicability
This AD applies to Arrow Falcon Exporters Inc.; AST, Inc.; Bell
Helicopter Textron, Inc.; Global Helicopter Technology, Inc.;
Hagglund Helicopters, LLC; JJASPP Engineering Services, LLC;
Northwest Rotorcraft, LLC; Overseas Aircraft Support, Inc.; Richards
Heavylift Helo, Inc.; Robinson Air Crane, Inc.; Rotorcraft
Development Corporation; San Joaquin Helicopters; Southern
Helicopter, Inc.; and Tamarack Helicopters, Inc. Model HH-1K, TH-1F,
TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P
helicopters, and Southwest Florida Aviation International, Inc.,
Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) 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.
[[Page 40956]]
Table 1 to Paragraph (a)
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Fitting P/Ns Fitting S/Ns
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204-012-102-001.......................... All.
204-012-102-005.......................... All.
204-012-102-009.......................... All, except 7500 or larger
with a prefix of ``A'' or
``A-FS.''
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(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the fitting
and the determination that the applicable 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) Effective Date
This AD becomes effective July 24, 2013.
(d) 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.
(e) Required Actions
Within 25 hours time-in-service or 15 days, whichever occurs
first:
(1) 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.
(f) 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) 222-5710; 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.
(g) Additional Information
Bell Alert Service Bulletin (ASB) No. UH-1H-11-07, dated May 31,
2011, which is 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 www.bellcustomer.com. 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.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor
Head.
Issued in Fort Worth, Texas, on June 18, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15946 Filed 7-8-13; 8:45 am]
BILLING CODE 4910-13-P