DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0894; Product Identifier 2017-SW-044-AD; Amendment
39-19160; AD 2018-02-07]
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 Model
TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P helicopters with a Helicopter
Technology Company (HTC) main rotor (M/R) blade installed. This AD
requires cleaning and visually inspecting the M/R blades and, depending
on the outcome of the inspection, repairing or replacing the M/R
blades. This AD is prompted by a report of an M/R blade with a fatigue
crack in the grip plate and doublers at the blade retention bolt hole.
The actions of this AD are intended to correct an unsafe condition on
these products.

DATES: This AD becomes effective February 1, 2018.
We must receive comments on this AD by March 19, 2018.

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
by searching for and locating Docket No. FAA-2017-0894;
or in person at Docket Operations 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 Docket Operations (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 final rule, 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 the referenced service information at the FAA,
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy.,
Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer
(Structures), Los Angeles ACO Branch, Compliance and Airworthiness
Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712;
telephone 562-627-5324; email galib.abumeri@faa.gov.

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

We are adopting a new AD for restricted category Model TH-1F, UH-
1B, UH-1F, UH-1H, and UH-1P helicopters with an HTC M/R blade part
number (P/N) 204P2100-101 installed. This AD requires repetitive
inspections of the exposed areas of the lower grip pad and upper and
lower grip plates of each M/R blade for a crack, corrosion, an edge
void, loose or damaged adhesive squeeze-out, and an edge delamination.
The type certificate holders for these model helicopters are: Arrow
Falcon Exporters Inc.; AST, Inc.; California Department of Forestry;
Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC;
International Helicopters, Inc.; JJASPP Engineering Services, LLC;
Northwest Rotorcraft, LLC; OAS Parts LLC; Red Tail Flying Services,
LLC; Richards Heavylift Helo, Inc.; Robinson Air Crane, Inc.;
Rotorcraft Development Corporation; San Joaquin Helicopters; Southwest
Florida Aviation International, Inc.; and Tamarack Helicopters, Inc.
The actions of this AD are the same as those required by AD 2016-
23-09 (81 FR 83660, November 22, 2016), which applies to various
restricted category helicopters with an M/R blade P/N 204-011-250-005
or P/N 204-011-250-113 installed. AD 2016-23-09 was prompted by a
report of an M/R blade with multiple fatigue cracks around the
retention bolt hole.
This AD is prompted by a report that during a ground inspection, a
crack was discovered in the grip plate and doublers at the blade
retention bolt hole of a UH-1B helicopter model. The blade, which HTC
produced for restricted category and commercial model helicopters, had
926 hours TIS and is of the same design as the M/R blades in AD 2016-
23-09. We are issuing this AD to detect or prevent a crack, which could
lead to failure of an M/R 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 reviewed Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-
13-09, dated January 14, 2013, for the Model UH-1H helicopter. ASB No.
UH-1H-13-09 specifies a one-time visual inspection, within 10 hours
time-in-service (TIS), of the lower grip pad and upper and lower grip
plates for cracks, edge voids, and loose or damaged adhesive squeeze-
out. ASB No. UH-1H-13-09 also specifies a repetitive and more detailed
visual inspection, daily and at every 150 hours TIS, of the lower grip
pad, upper and lower grip plates, and all upper and the lower doublers
for cracks, corrosion, edge voids, and loose or damaged adhesive
squeeze-out.
We also reviewed HTC Service Notice No. 204-2100-1, dated July 5,
2017, for affected helicopters with M/R blade P/N 204P2100-101, serial numbers
A099 through A119 installed. This service notice specifies cleaning and
visually inspecting the M/R blades and depending on the outcome,
repairing or replacing the blades, in accordance with AD 2016-23-09.

AD Requirements

This AD requires within 25 hours time-in-service (TIS) or 2 weeks,
whichever occurs first, and thereafter at intervals not to exceed 25
hours TIS or 2 weeks, whichever occurs first, cleaning the upper and
lower exposed surfaces of each M/R blade from an area starting at the
butt end of the blade to three inches outboard of the doublers. Using a
3X or higher power magnifying glass and a light, this AD also requires
inspecting the M/R blade parts for a crack or corrosion. If there is a
crack, corrosion, an edge void, loose or damaged adhesive squeeze-out,
or an edge delamination, before further flight, this AD requires
repairing the M/R blade or replacing it with an airworthy M/R blade,
depending on whether the condition is within maximum repair damage
limits.
This AD also requires reporting information about any cracks found
during the inspection to the FAA within 10 days.

Differences Between This AD and the Service Information

ASB No. UH-1H-13-09 specifies a one-time inspection and then a
second repetitive inspection daily and at every 150 hours TIS. This AD
requires all inspections at intervals not to exceed 25 hours TIS or two
weeks, whichever occurs first. This AD contains more detailed
inspection requirements and a more specific inspection area than the
instructions in ASB No. UH-1H-13-09. Lastly, ASB No. UH-1H-13-09
applies to Model UH-1H helicopters with M/R blade P/N 204-011-250-113,
while this AD applies to Model UH-1H, TH-1F, UH-1B, UH-1F, and UH-1P
helicopters with HTC M/R blade part number (P/N) 204P2100-101.

Interim Action

We consider this AD to be an interim action. The notification of a
crack in the M/R blade that is required by this AD may enable us to
obtain better insight into the cause of the M/R blade cracking. This
information may help us develop additional action to address this
unsafe condition. Once this action is developed, approved, and
available, we might consider additional rulemaking.

Costs of Compliance

We estimate that this AD affects 10 helicopters of U.S. Registry
and that labor costs average $85 per work-hour. Based on these
estimates, we expect the following costs:
Cleaning and performing all inspections of a set of M/R
blades (2 per helicopter) requires 0.5 work-hour for a cost of $43 per
helicopter and $430 for the U.S. fleet per inspection cycle.
Replacing an M/R blade requires 12 work-hours and parts
cost $86,000 for a total cost of $87,020 per blade.
Reporting the inspection results required by this AD will
require about 0.5 work-hour for a cost of $43 per helicopter and $430
for the U.S. fleet.

Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting required by this AD
is 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.

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 two weeks.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
prior public comment before issuing this AD are impracticable and that
good cause exists to make this AD 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

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]

2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):