83 FR 2361 - Airworthiness Directives; Various Restricted Category Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 11 (January 17, 2018)

Page Range		2361-2364
FR Document		2018-00658

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.

Federal Register, Volume 83 Issue 11 (Wednesday, January 17, 2018)

[Federal Register Volume 83, Number 11 (Wednesday, January 17, 2018)]
[Rules and Regulations]
[Pages 2361-2364]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2018-00658]

[[Page 2361]]

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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

[[Page 2362]]

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

0
1. The authority citation for part 39 continues to read as follows:

[[Page 2363]]

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):

2018-02-07 Various Restricted Category Helicopters: Amendment 39-
19160; Docket No. FAA-2017-0894; Product Identifier 2017-SW-044-AD.

(a) Applicability

This AD applies to the following helicopters, certificated in
the restricted category, with a Helicopter Technology Company (HTC)
main rotor (M/R) blade part number 204P2100-101 installed:
(1) Arrow Falcon Exporters Inc.; Global Helicopter Technology,
Inc.; Hagglund Helicopters, LLC; JJASPP Engineering Services, LLC;
Northwest Rotorcraft, LLC; OAS Parts, LLC; Richards Heavylift Helo,
Inc.; Rotorcraft Development Corporation; Southwest Florida Aviation
International, Inc.; and Tamarack Helicopters, Inc., Model UH-1H
helicopters;
(2) International Helicopters, Inc.; OAS Parts, LLC; Red Tail
Flying Services, LLC; Richards Heavylift Helo, Inc.; Rotorcraft
Development Corporation; San Joaquin Helicopters; and Southwest
Florida Aviation International, Inc., Model UH-1B helicopters;
(3) Robinson Air Crane, Inc.; Rotorcraft Development
Corporation; and Tamarack Helicopters, Inc., Model TH-1F
helicopters;
(4) AST, Inc.; California Department of Forestry, Robinson Air
Crane, Inc.; Rotorcraft Development Corporation; and Tamarack
Helicopters, Inc., Model UH-1F helicopters; and
(5) Robinson Air Crane, Inc., and Rotorcraft Development
Corporation, Model UH-1P helicopters.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in an M/R blade,
which could result in failure of the M/R blade and subsequent loss
of helicopter control.

This AD becomes effective February 1, 2018.

(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

(1) 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, clean 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, inspect as follows:
(i) Visually inspect the exposed areas of the lower grip pad and
upper and lower grip plates of each M/R blade for a crack and any
corrosion.
(ii) On the upper and lower exposed surfaces of each M/R blade
from blade stations 24.5 to 35 for the chord width, visually inspect
each layered doubler and blade skin for a crack and any corrosion.
Pay particular attention for any cracking in a doubler or skin near
or at the same blade station as the blade retention bolt hole (blade
station 28).
(iii) Visually inspect the exposed areas of each bond line at
the edges of the lower grip pad, upper and lower grip plates, and
each layered doubler (bond lines) on the upper and lower surfaces of
each M/R blade for the entire length and chord width for an edge
void, any corrosion, loose or damaged adhesive squeeze-out, and an
edge delamination. Pay particular attention to any crack in the
paint finish that follows the outline of a grip pad, grip plate, or
doubler, and to any loose or damaged adhesive squeeze-out, as these
may be the indication of an edge void.
(2) If there is a crack, any corrosion, an edge void, loose or
damaged adhesive squeeze-out, or an edge delamination during any
inspection in paragraph (e)(1) of this AD, before further flight, do
the following:
(i) If there is a crack in a grip pad or any grip plate or
doubler, replace the M/R blade with an airworthy M/R blade.
(ii) If there is a crack in the M/R blade skin that is within
maximum repair damage limits, repair the M/R blade. If the crack
exceeds maximum repair damage limits, replace the M/R blade with an
airworthy M/R blade.
(iii) If there is any corrosion within maximum repair damage
limits, repair the M/R blade. If the corrosion exceeds maximum
repair damage limits, replace the M/R blade with an airworthy M/R
blade.
(iv) If there is an edge void in the grip pad or in a grip plate
or doubler, determine the length and depth using a feeler gauge.
Repair the M/R blade if the edge void is within maximum repair
damage limits or replace the M/R blade with an airworthy M/R blade.
(v) If there is an edge void in a grip plate or doubler near the
outboard tip, tap inspect the affected area to determine the size
and shape of the void. Repair the M/R blade if the edge void is
within maximum repair damage limits or replace the M/R blade with an
airworthy M/R blade.
(vi) If there is any loose or damaged adhesive squeeze-out along
any of the bond lines, trim or scrape away the adhesive without
damaging the adjacent surfaces or parent material of the M/R blade.
Determine if there is an edge void or any corrosion by lightly
sanding the trimmed area smooth using 280 or finer grit paper. If
there is no edge void or corrosion, refinish the sanded area.
(vii) If there is an edge delamination along any of the bond
lines or a crack in the paint finish, determine if there is an edge
void or a crack in the grip pad, grip plate, doubler, or skin by
removing paint from the affected area by lightly sanding in a span-
wise direction using 180-220 grit paper. If there are no edge voids
and no cracks, refinish the sanded area.
(viii) If any parent material is removed during any sanding or
trimming in paragraphs (e)(2)(vi) or (e)(2)(vii) of this AD, repair
the M/R blade if the damage is within maximum repair damage limits
or replace the M/R blade with an airworthy M/R blade.
(3) If there is a crack during any inspection in paragraph
(e)(1) of this AD, within 10 days after completing the inspection,
report the information requested in Appendix 1 to this AD by mail to
the Los Angeles ACO Branch, Compliance and Airworthiness Division,
FAA, 3960 Paramount Blvd., Lakewood, California 90712; attn. Galib
Abumeri; or by email to galib.abumeri@faa.gov.

(f) Special Flight Permits

Special flight permits are prohibited.

(g) Paperwork Reduction Act Burden Statement

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 OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 30 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.

(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs
for this AD. Send your proposal to: Galib Abumeri, Aerospace
Engineer (Structures), Airframe Section, Los Angeles ACO Branch,
Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd.,
Lakewood, California 90712; telephone 562-627-5324; email
galib.abumeri@faa.gov.
(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.

(i) Additional Information

HTC Service Notice No. 204-2100-1, dated July 5, 2017, and Bell
Alert Service Bulletin No. UH-1H-13-09, dated January 14, 2013,
which are not incorporated by reference, contain additional
information about the subject of this AD. 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
this service information at the FAA, Office of the Regional Counsel,
Southwest

[[Page 2364]]

Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

(j) Subject

Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor
Blades.

Issued in Fort Worth, Texas, on January 9, 2018.
James A. Grigg,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.

Appendix 1 to AD 2018-02-07

Please report the following by mail to the Los Angeles ACO
Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount
Blvd., Lakewood, California 90712; attn. Galib Abumeri; or by email
to galib.abumeri@faa.gov.
(1) Date of inspection:
(2) Aircraft N-number:
(3) M/R blade serial number:
(4) M/R blade hours of time-in-service:
(5) Location of each crack:
(6) Dimension of each crack:
(7) Primary operating location of the M/R blade:

[FR Doc. 2018-00658 Filed 1-16-18; 8:45 am]
BILLING CODE 4910-13-P

2362 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations

affected helicopters with M/R blade Costs of Compliance Authority for This Rulemaking
P/N 204P2100–101, serial numbers Title 49 of the United States Code
A099 through A119 installed. This We estimate that this AD affects 10
helicopters of U.S. Registry and that specifies the FAA’s authority to issue
service notice specifies cleaning and rules on aviation safety. Subtitle I,
visually inspecting the M/R blades and labor costs average $85 per work-hour.
Based on these estimates, we expect the section 106, describes the authority of
depending on the outcome, repairing or the FAA Administrator. ‘‘Subtitle VII:
replacing the blades, in accordance with following costs:
Aviation Programs,’’ describes in more
AD 2016–23–09. • Cleaning and performing all detail the scope of the Agency’s
inspections of a set of M/R blades (2 per authority.
AD Requirements
helicopter) requires 0.5 work-hour for a We are issuing this rulemaking under
This AD requires within 25 hours cost of $43 per helicopter and $430 for the authority described in ‘‘Subtitle VII,
time-in-service (TIS) or 2 weeks, the U.S. fleet per inspection cycle. Part A, Subpart III, Section 44701:
whichever occurs first, and thereafter at • Replacing an M/R blade requires 12 General requirements.’’ Under that
intervals not to exceed 25 hours TIS or work-hours and parts cost $86,000 for a section, Congress charges the FAA with
2 weeks, whichever occurs first, total cost of $87,020 per blade. promoting safe flight of civil aircraft in
cleaning the upper and lower exposed air commerce by prescribing regulations
• Reporting the inspection results
surfaces of each M/R blade from an area for practices, methods, and procedures
required by this AD will require about
starting at the butt end of the blade to the Administrator finds necessary for
0.5 work-hour for a cost of $43 per
three inches outboard of the doublers. safety in air commerce. This regulation
helicopter and $430 for the U.S. fleet.
Using a 3X or higher power magnifying is within the scope of that authority
glass and a light, this AD also requires Paperwork Reduction Act because it addresses an unsafe condition
inspecting the M/R blade parts for a that is likely to exist or develop on
crack or corrosion. If there is a crack, A federal agency may not conduct or products identified in this rulemaking
corrosion, an edge void, loose or sponsor, and a person is not required to action.
damaged adhesive squeeze-out, or an respond to, nor shall a person be subject
to penalty for failure to comply with a Regulatory Findings
edge delamination, before further flight,
this AD requires repairing the M/R collection of information subject to the We determined that this AD will not
blade or replacing it with an airworthy requirements of the Paperwork have federalism implications under
M/R blade, depending on whether the Reduction Act unless that collection of Executive Order 13132. This AD will
condition is within maximum repair information displays a current valid not have a substantial direct effect on
damage limits. OMB control number. The control the States, on the relationship between
This AD also requires reporting number for the collection of information the national Government and the States,
information about any cracks found required by this AD is 2120–0056. The or on the distribution of power and
during the inspection to the FAA within paperwork cost associated with this AD responsibilities among the various
10 days. has been detailed in the Costs of levels of government.
Compliance section of this document For the reasons discussed, I certify
Differences Between This AD and the and includes time for reviewing that this AD:
Service Information instructions, as well as completing and 1. Is not a ‘‘significant regulatory
reviewing the collection of information. action’’ under Executive Order 12866;
ASB No. UH–1H–13–09 specifies a 2. Is not a ‘‘significant rule’’ under
one-time inspection and then a second Therefore, all reporting required by this
AD is mandatory. Comments concerning DOT Regulatory Policies and Procedures
repetitive inspection daily and at every (44 FR 11034, February 26, 1979);
150 hours TIS. This AD requires all the accuracy of this burden and
suggestions for reducing the burden 3. Will not affect intrastate aviation in
inspections at intervals not to exceed 25 Alaska to the extent that it justifies
hours TIS or two weeks, whichever should be directed to the FAA at 800
Independence Ave. SW, Washington, making a regulatory distinction; and
occurs first. This AD contains more 4. Will not have a significant
detailed inspection requirements and a DC 20591. ATTN: Information
economic impact, positive or negative,
more specific inspection area than the Collection Clearance Officer, AES–200.
on a substantial number of small entities
instructions in ASB No. UH–1H–13–09. FAA’s Justification and Determination under the criteria of the Regulatory
Lastly, ASB No. UH–1H–13–09 applies of the Effective Date Flexibility Act.
to Model UH–1H helicopters with M/R We prepared an economic evaluation
blade P/N 204–011–250–113, while this Providing an opportunity for public of the estimated costs to comply with
AD applies to Model UH–1H, TH–1F, comments prior to adopting these AD this AD and placed it in the AD docket.
UH–1B, UH–1F, and UH–1P helicopters requirements would delay
implementing the safety actions needed List of Subjects in 14 CFR Part 39
with HTC M/R blade part number (P/N)
204P2100–101. to correct this known unsafe condition. Air transportation, Aircraft, Aviation
Therefore, we find that the risk to the safety, Incorporation by reference,
Interim Action flying public justifies waiving notice Safety.
We consider this AD to be an interim and comment prior to the adoption of
Adoption of the Amendment
action. The notification of a crack in the this rule because the required corrective
actions must be accomplished within Accordingly, under the authority
M/R blade that is required by this AD
two weeks. delegated to me by the Administrator,
may enable us to obtain better insight
the FAA amends 14 CFR part 39 as
into the cause of the M/R blade Since an unsafe condition exists that
ethrower on DSK3G9T082PROD with RULES

follows:
cracking. This information may help us requires the immediate adoption of this
develop additional action to address AD, we determined that notice and PART 39—AIRWORTHINESS
this unsafe condition. Once this action opportunity for prior public comment DIRECTIVES
is developed, approved, and available, before issuing this AD are impracticable
we might consider additional and that good cause exists to make this ■ 1. The authority citation for part 39
rulemaking. AD effective in less than 30 days. continues to read as follows:

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2364 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations

Region, 10101 Hillwood Pkwy., Room 6N– 11.43 and 11.45, by any of the following system indications in response to the
321, Fort Worth, TX 76177. methods: recommendations in the investigator’s report.
• Federal eRulemaking Portal: Go to The result of the evaluation was a new
(j) Subject ‘‘ERRONEOUS RADIO ALTIMETER
Joint Aircraft Service Component (JASC)
http://www.regulations.gov. Follow the INDICATION’’ abnormal procedure in the
Code: 6210, Main Rotor Blades. instructions for submitting comments. Airplane Flight Manual (AFM). This new
• Fax: 202–493–2251. procedure includes pulling the circuit
Issued in Fort Worth, Texas, on January 9, • Mail: U.S. Department of breaker of a failed RA system, and in support
2018.
Transportation, Docket Operations, M– of this, new yellow identification collars to
James A. Grigg, 30, West Building Ground Floor, Room the RA circuit breakers are to be introduced
Acting Director, Compliance & Airworthiness W12–140, 1200 New Jersey Avenue SE, to improve instantaneous recognition, both
Division, Aircraft Certification Service. Washington, DC 20590. visual and tactile, in low illumination and
under increased workload conditions.
Appendix 1 to AD 2018–02–07 • Hand Delivery: U.S. Department of In order to prevent an unsafe condition,
Transportation, Docket Operations, M– similar to the one that contributed to the
Please report the following by mail to the
30, West Building Ground Floor, Room accident described above, this [EASA] AD
Los Angeles ACO Branch, Compliance and
Airworthiness Division, FAA, 3960 W12–140, 1200 New Jersey Avenue SE, requires incorporation of the new abnormal
Paramount Blvd., Lakewood, California Washington, DC, between 9 a.m. and 5 procedure in the AFM and installation of the
90712; attn. Galib Abumeri; or by email to p.m., Monday through Friday, except new yellow RA circuit breaker identification
galib.abumeri@faa.gov. Federal holidays. collars.
(1) Date of inspection: You may examine the MCAI on the
(2) Aircraft N-number: Examining the AD Docket
internet at http://www.regulations.gov
(3) M/R blade serial number: You may examine the AD docket on by searching for and locating Docket No.
(4) M/R blade hours of time-in-service: the internet at http:// FAA–2017–1249.
(5) Location of each crack: www.regulations.gov by searching for
(6) Dimension of each crack:
and locating Docket No. FAA–2017– FAA’s Determination and Requirements
(7) Primary operating location of the M/R of This AD
blade: 1249; or in person at the Docket
Operations office between 9 a.m. and 5 This product has been approved by
[FR Doc. 2018–00658 Filed 1–16–18; 8:45 am] the aviation authority of another
p.m., Monday through Friday, except
BILLING CODE 4910–13–P
Federal holidays. The AD docket country, and is approved for operation
contains this AD, the regulatory in the United States. Pursuant to our
evaluation, any comments received, and bilateral agreement with the State of
DEPARTMENT OF TRANSPORTATION Design Authority, we have been notified
other information. The street address for
the Docket Operations office (telephone: of the unsafe condition described in the
Federal Aviation Administration
800–647–5527) is in the ADDRESSES MCAI. We are issuing this AD because
section. Comments will be available in we evaluated all pertinent information
14 CFR Part 39
the AD docket shortly after receipt. and determined the unsafe condition
[Docket No. FAA–2017–1249; Product FOR FURTHER INFORMATION CONTACT: Tom
exists and is likely to exist or develop
Identifier 2013–NM–104–AD; Amendment Rodriguez, Aerospace Engineer, on other products of the same type
39–19156; AD 2018–02–03] International Section, Transport design.
Standards Branch, FAA, 1601 Lind FAA’s Determination of the Effective
RIN 2120–AA64
Avenue SW, Renton, WA 98057–3356; Date
Airworthiness Directives; Fokker telephone: 425–227–1137; fax: 425– Since there are currently no domestic
Services B.V. Airplanes 227–1149. operators of this product, we find good
SUPPLEMENTARY INFORMATION: cause that notice and opportunity for
AGENCY: Federal Aviation
Discussion prior public comment are unnecessary.
Administration (FAA), DOT.
In addition, for the reason(s) stated
ACTION: Final rule; request for The European Aviation Safety Agency above, we find that good cause exists for
comments. (EASA), which is the Technical Agent making this amendment effective in less
for the Member States of the European than 30 days.
SUMMARY: We are adopting a new Union, has issued EASA AD 2013–0112,
airworthiness directive (AD) for all dated May 28, 2013 (referred to after Comments Invited
Fokker Services B.V. Model F28 Mark this as the Mandatory Continuing This AD is a final rule that involves
0070 and Mark 0100 series airplanes. Airworthiness Information, or ‘‘the requirements affecting flight safety, and
This AD requires contacting the FAA to MCAI’’), to correct an unsafe condition we did not precede it by notice and
obtain instructions for addressing the for all Fokker Services B.V. Model F28 opportunity for public comment. We
unsafe condition on these products, and Mark 0070 and Mark 0100 series invite you to send any written relevant
doing the actions specified in those airplanes. The MCAI states: data, views, or arguments about this AD.
instructions. This AD was prompted by Send your comments to an address
an erroneous radio altimeter reading, Following an accident * * * [of an]
aeroplane on final approach, the listed under the ADDRESSES section.
which caused certain systems to investigating body determined that an Include ‘‘Docket No. FAA–2017–1249;
respond in a way that led to loss of important contributing factor to the accident Product Identifier 2013–NM–104–AD’’
speed. We are issuing this AD to address was an erroneous reading of -7 to -8 feet from at the beginning of your comments. We
the unsafe condition on these products. the left Radio Altimeter (RA). The responses
ethrower on DSK3G9T082PROD with RULES

specifically invite comments on the
DATES: This AD becomes effective of the autothrottle and autopilot systems to overall regulatory, economic,
February 15, 2018. this erroneous RA system reading led to
speed loss and, in combination with
environmental, and energy aspects of
We must receive comments on this this AD. We will consider all comments
operational factors, caused the aeroplane to
AD by March 5, 2018. hit the ground before reaching the runway. received by the closing date and may
ADDRESSES: You may send comments, Fokker Services conducted an evaluation amend this AD based on those
using the procedures found in 14 CFR of the effects of un-flagged erroneous low RA comments.

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Document Created: 2018-10-26 09:54:59
Document Modified: 2018-10-26 09:54:59

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule; request for comments.
Dates		This AD becomes effective February 1, 2018.
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 [email protected]
FR Citation		83 FR 2361
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

83 FR 2361 - Airworthiness Directives; Various Restricted Category Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 11 (January 17, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration