AD 2013-13-14

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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:
    <bullet> Federal eRulemaking Docket: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 <a href="http://www.bellcustomer.com">www.bellcustomer.com</a>. 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: <a href="/cdn-cgi/l/email-protection#a3948ee2f5f08ee2f0f48e929493e3c5c2c28dc4ccd5"><span class="__cf_email__" data-cfemail="7a4d573b2c29573b292d574b4d4a3a1c1b1b541d150c">[email&#160;protected]</span></a>.

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:
    <bullet> 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.
    <bullet> For fittings with more than 400 hours, performing an MPI 
within 25 flight hours or before November 26, 2011, whichever occurs 
first.
    <bullet> If cracks are found, replacing the fitting.
    <bullet> 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.
    <bullet> 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:
    <bullet> Within 25 hours TIS or 15 days, whichever comes first, 
performing an MPI of each fitting for a crack.
    <bullet> If a fitting has a crack, before further flight, replacing 
the fitting with an airworthy fitting.
    <bullet> 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:
    <bullet> 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.
    <bullet> 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
------------------------------------------------------------------------
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.''
------------------------------------------------------------------------

(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: <a href="/cdn-cgi/l/email-protection#6c5b412d3a3f412d3f3b415d5b5c2c0a0d0d420b031a"><span class="__cf_email__" data-cfemail="ecdbc1adbabfc1adbfbbc1dddbdcac8a8d8dc28b839a">[email&#160;protected]</span></a>.
    (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 <a href="http://www.bellcustomer.com">www.bellcustomer.com</a>. 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