Airworthiness Directives; Various Restricted Category Helicopters, 21288-21290 [2016-07985]
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21288
Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Proposed Rules
(4) You may view this service
information at the FAA, Engine &
Propeller Directorate, 1200 District
Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
HPC stage 8–10 spool. We are issuing
this AD to prevent failure of the HPC
stage 8–10 spool, uncontained rotor
release, damage to the engine, and
damage to the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless
already done.
(1) Perform an eddy current
inspection (ECI) or fluorescent penetrant
inspection (FPI) of the seal teeth of the
HPC stage 8–10 spool as follows:
(i) For HPC stage 8–10 spools with
fewer than 11,000 cycles since new
(CSN) on the effective day of this AD,
inspect at the next shop visit after
reaching 6,000 CSN, not to exceed
12,500 CSN.
(ii) For HPC stage 8–10 spools with
11,000 CSN or more on the effective day
of this AD, inspect within the next 1,500
cycles in service.
(iii) Thereafter, inspect the seal teeth
of the HPC stage 8–10 spool at each
shop visit.
(2) Remove from service any HPC
stage 8–10 spool that fails the ECI or FPI
required by paragraph (e)(1) of this AD
and replace with a part eligible for
installation.
(f) Definition
For the purpose of this AD, an engine
shop visit is the induction of an engine
into the shop for maintenance during
which the compressor discharge
pressure seal face is exposed.
(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification
Office, FAA, may approve AMOCs for
this AD. Use the procedures found in 14
CFR 39.19 to make your request. You
may email your request to: ANE-ADAMOC@faa.gov.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(h) Related Information
(1) For more information about this
AD, contact John Frost, Aerospace
Engineer, Engine Certification Office,
FAA, 1200 District Avenue, Burlington,
MA 01803; phone: 781–238–7756; fax:
781–238–7199; email: john.frost@
faa.gov.
(2) GE Service Bulletins SB 72–1141,
Revision 0, dated December 2, 2015 and
SB 72–1142, Revision 0, dated
November 30, 2015 can be obtained
from GE, using the contact information
in paragraph (h)(3) of this AD.
(3) For service information identified
in this proposed AD, contact General
Electric Company, GE-Aviation, Room
285, 1 Neumann Way, Cincinnati, OH
45215, phone: 513–552–3272; email:
aviation.fleetsupport@ge.com.
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14:15 Apr 08, 2016
Jkt 238001
Issued in Burlington, Massachusetts, on
April 5, 2016.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2016–08111 Filed 4–8–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3820; Directorate
Identifier 2014–SW–024–AD]
RIN 2120–AA64
Airworthiness Directives; Various
Restricted Category Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for various
restricted category helicopters. This
proposed AD would require cleaning
and visually inspecting certain main
rotor (M/R) blades and, depending on
the outcome of the inspections,
repairing or replacing the M/R blades.
This proposed AD is prompted by a
report of an M/R blade with multiple
fatigue cracks around the blade
retention bolt hole. The proposed
actions are intended to detect a crack in
the M/R blade, and prevent failure of
the M/R blade and subsequent loss of
helicopter control.
DATES: We must receive comments on
this proposed AD by June 10, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://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.
SUMMARY:
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3820 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 proposed 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 proposed rule, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, TX 76101; telephone (817)
280–3391; fax (817) 280–6466; or at
https://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, Texas 76177.
FOR FURTHER INFORMATION CONTACT:
Charles Harrison, Project Manager, Fort
Worth Aircraft Certification Office,
10101 Hillwood Pkwy., Fort Worth,
Texas 76177; telephone 817–222–5140;
email Charles.C.Harrison@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
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 might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, 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 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 proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
E:\FR\FM\11APP1.SGM
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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Proposed Rules
Discussion
We propose to adopt a new AD for
Model TH–1F, UH–1B, UH–1F, UH–1H,
and UH–1P restricted category
helicopters. This proposed AD would
require repetitively cleaning and
visually inspecting the M/R blades for a
crack, corrosion, an edge void, loose or
damaged adhesion, and an edge
delamination. Depending on the results
of the inspections, this proposed AD
would require either repairing or
replacing the M/R blades.
This proposed AD is prompted by a
Bell Helicopter Textron Inc. (BHTI)
evaluation of an M/R blade installed on
a Model UH–1H helicopter that had
multiple fatigue cracks around the blade
retention bolt hole. The cracks resulted
from a void between the lower grip plate
and the grip pad. A ‘‘substantial’’ void
also was found at the outboard doubler
tip on the lower blade surface. A
different part-numbered M/R blade of
the same type installed on the Model
UH–1H helicopter may also be installed
on Model TH–1F, UH–1B, UH–1F, and
UH–1P helicopters. The proposed
actions are intended to detect a crack in
an M/R blade, and prevent failure of the
M/R blade, and subsequent loss of
helicopter control.
FAA’s Determination
We are proposing this AD because we
evaluated all known relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
these same type designs.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Related Service Information
Bell Helicopter issued 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-inservice (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.
Bell Helicopter Textron also issued
ASB No. 204–75–1 for Model 204B
helicopters and ASB No. 205–75–5 for
Model 205A–1 helicopters, both
Revision C and both dated April 25,
1979. ASB No. 204–75–1 and ASB No.
205–75–5 call for visually inspecting the
M/R blades during each daily inspection
and repetitively washing the blades and
VerDate Sep<11>2014
14:15 Apr 08, 2016
Jkt 238001
applying WD–40. ASB No. 204–75–1
and ASB No. 205–75–5 also provide
instructions for repetitively inspecting
the blades every 1,000 hours of
operation or every 12 months,
whichever occurs first, or within 150
hours or 30 days, whichever occurs first,
if the blades have more than 1,000 hours
of operation or have been in service
more than 12 months. While ASB No.
204–75–1 and ASB No. 205–75–5 do not
apply to the helicopters that are the
subject of this proposed AD, they do
apply to the affected M/R blades.
Proposed AD Requirements
This proposed AD would require
within 25 hours 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 surfaces of
each M/R blade from an area starting at
the butt end of the blade to three inches
outboard of the doublers. The proposed
AD also would require visually
inspecting various M/R parts for a crack
or corrosion using a 3X or higher power
magnifying glass and a light.
If there is a crack, corrosion, an edge
void, loose or damaged adhesive
squeeze-out, or an edge delamination
before further flight, this proposed AD
would require repairing the M/R blade
or replacing it with an airworthy M/R
blade, depending on the condition’s
severity.
Differences Between This Proposed 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, and ASB No. 204–75–1
and ASB 205–75–5 call for visually
inspecting the M/R blades daily and
every 1,000 hours TIS or 12 months,
whichever occurs first. The proposed
AD would require all inspections at
intervals not to exceed 25 hours TIS or
two weeks, whichever occurs first. This
proposed 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, ASB No.
204–75–1 applies to Model 204B
helicopters with M/R blade P/N 204–
011–0250 (all dash numbers), and ASB
No. 205–75–5 applies to Model 205A–
1 helicopters with M/R blade P/N 204–
011–0250 (all dash numbers). This
proposed AD would apply to Model
TH–1F, UH–1B, UH–1F, UH–1H, and
UH–1P helicopters with M/R blade P/N
204–011–250–005 or 204–011–250–113.
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21289
Costs of Compliance
We estimate that this proposed AD
would affect 607 helicopters of U.S.
Registry and that labor costs average $85
a 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) would require a total of 1⁄2
work-hour. No parts would be needed.
At an estimated 24 inspections a year,
the cost would be $1,032 per helicopter
and $626,424 for the U.S. fleet.
• Replacing an M/R blade would
require 12 work hours and parts would
cost $90,656, for a total cost of $91,676
per blade.
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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.
E:\FR\FM\11APP1.SGM
11APP1
21290
Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Proposed Rules
We prepared an economic evaluation
of the estimated costs to comply with
this proposed 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Various Restricted Category Helicopters:
Docket No. FAA–2015–3820; Directorate
Identifier 2014–SW–024–AD.
(a) Applicability
This AD applies to Model TH–1F, UH–1B,
UH–1F, UH–1H, and UH–1P helicopters with
a main rotor (M/R) blade, part number 204–
011–250–005 or 204–011–250–113, installed.
(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.
(c) Comments Due Date
We must receive comments by June 10,
2016.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(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 area 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 entire chord width,
visually inspect each layered doubler and
blade skin for a crack and any corrosion. Pay
particular attention for any cracking in a
VerDate Sep<11>2014
14:15 Apr 08, 2016
Jkt 238001
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.
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(f) Special Flight Permit
Special flight permits are prohibited.
(g) Alternative Methods of Compliance
(AMOC)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Charles Harrison,
Project Manager, Fort Worth Aircraft
Certification Office, 10101 Hillwood Pkwy.,
Fort Worth, Texas 76177; telephone 817–
222–5140; email 9-ASW-FTW-AMOCRequests@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.
(h) Additional Information
Bell Helicopter Alert Service Bulletin
(ASB) No. UH–1H–13–09, dated January 14,
2013, and Bell Helicopter Textron ASB No.
204–75–1 and ASB 205–75–5, both Revision
C and both dated April 25, 1979, 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 https://www.bellcustomer.com/
files/. You may review a copy of information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, Texas 76177.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6210, Main Rotor Blades.
Issued in Fort Worth, Texas, on March 29,
2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–07985 Filed 4–8–16; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–R06–OAR–2012–0985; FRL–9944–84–
Region 6]
Approval and Promulgation of Air
Quality Implementation Plans; Texas;
Interstate Transport of Air Pollution for
the 2008 Ozone National Ambient Air
Quality Standards
Environmental Protection
Agency (EPA).
ACTION: Proposed rule.
AGENCY:
The Environmental Protection
Agency (EPA) proposes to disapprove
the portion of a Texas State
SUMMARY:
E:\FR\FM\11APP1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Proposed Rules]
[Pages 21288-21290]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07985]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3820; Directorate Identifier 2014-SW-024-AD]
RIN 2120-AA64
Airworthiness Directives; Various Restricted Category Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
various restricted category helicopters. This proposed AD would require
cleaning and visually inspecting certain main rotor (M/R) blades and,
depending on the outcome of the inspections, repairing or replacing the
M/R blades. This proposed AD is prompted by a report of an M/R blade
with multiple fatigue cracks around the blade retention bolt hole. The
proposed actions are intended to detect a crack in the M/R blade, and
prevent failure of the M/R blade and subsequent loss of helicopter
control.
DATES: We must receive comments on this proposed AD by June 10, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3820 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 proposed 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 proposed rule, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280-3391; fax (817) 280-6466; or at https://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, Texas 76177.
FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager,
Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort
Worth, Texas 76177; telephone 817-222-5140; email
Charles.C.Harrison@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
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 might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
[[Page 21289]]
Discussion
We propose to adopt a new AD for Model TH-1F, UH-1B, UH-1F, UH-1H,
and UH-1P restricted category helicopters. This proposed AD would
require repetitively cleaning and visually inspecting the M/R blades
for a crack, corrosion, an edge void, loose or damaged adhesion, and an
edge delamination. Depending on the results of the inspections, this
proposed AD would require either repairing or replacing the M/R blades.
This proposed AD is prompted by a Bell Helicopter Textron Inc.
(BHTI) evaluation of an M/R blade installed on a Model UH-1H helicopter
that had multiple fatigue cracks around the blade retention bolt hole.
The cracks resulted from a void between the lower grip plate and the
grip pad. A ``substantial'' void also was found at the outboard doubler
tip on the lower blade surface. A different part-numbered M/R blade of
the same type installed on the Model UH-1H helicopter may also be
installed on Model TH-1F, UH-1B, UH-1F, and UH-1P helicopters. The
proposed actions are intended to detect a crack in an M/R blade, and
prevent failure of the M/R blade, and subsequent loss of helicopter
control.
FAA's Determination
We are proposing this AD because we evaluated all known relevant
information and determined that an unsafe condition exists and is
likely to exist or develop on other products of these same type
designs.
Related Service Information
Bell Helicopter issued 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.
Bell Helicopter Textron also issued ASB No. 204-75-1 for Model 204B
helicopters and ASB No. 205-75-5 for Model 205A-1 helicopters, both
Revision C and both dated April 25, 1979. ASB No. 204-75-1 and ASB No.
205-75-5 call for visually inspecting the M/R blades during each daily
inspection and repetitively washing the blades and applying WD-40. ASB
No. 204-75-1 and ASB No. 205-75-5 also provide instructions for
repetitively inspecting the blades every 1,000 hours of operation or
every 12 months, whichever occurs first, or within 150 hours or 30
days, whichever occurs first, if the blades have more than 1,000 hours
of operation or have been in service more than 12 months. While ASB No.
204-75-1 and ASB No. 205-75-5 do not apply to the helicopters that are
the subject of this proposed AD, they do apply to the affected M/R
blades.
Proposed AD Requirements
This proposed AD would require within 25 hours 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 surfaces of each M/R blade from an area starting at the butt end
of the blade to three inches outboard of the doublers. The proposed AD
also would require visually inspecting various M/R parts for a crack or
corrosion using a 3X or higher power magnifying glass and a light.
If there is a crack, corrosion, an edge void, loose or damaged
adhesive squeeze-out, or an edge delamination before further flight,
this proposed AD would require repairing the M/R blade or replacing it
with an airworthy M/R blade, depending on the condition's severity.
Differences Between This Proposed 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, and ASB
No. 204-75-1 and ASB 205-75-5 call for visually inspecting the M/R
blades daily and every 1,000 hours TIS or 12 months, whichever occurs
first. The proposed AD would require all inspections at intervals not
to exceed 25 hours TIS or two weeks, whichever occurs first. This
proposed 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, ASB No. 204-75-1 applies to Model 204B
helicopters with M/R blade P/N 204-011-0250 (all dash numbers), and ASB
No. 205-75-5 applies to Model 205A-1 helicopters with M/R blade P/N
204-011-0250 (all dash numbers). This proposed AD would apply to Model
TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P helicopters with M/R blade P/N
204-011-250-005 or 204-011-250-113.
Costs of Compliance
We estimate that this proposed AD would affect 607 helicopters of
U.S. Registry and that labor costs average $85 a 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) would require a total of \1/2\ work-hour. No
parts would be needed. At an estimated 24 inspections a year, the cost
would be $1,032 per helicopter and $626,424 for the U.S. fleet.
Replacing an M/R blade would require 12 work hours and
parts would cost $90,656, for a total cost of $91,676 per blade.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
[[Page 21290]]
We prepared an economic evaluation of the estimated costs to comply
with this proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
Various Restricted Category Helicopters: Docket No. FAA-2015-3820;
Directorate Identifier 2014-SW-024-AD.
(a) Applicability
This AD applies to Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P
helicopters with a main rotor (M/R) blade, part number 204-011-250-
005 or 204-011-250-113, installed.
(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.
(c) Comments Due Date
We must receive comments by June 10, 2016.
(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 area 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 entire 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.
(f) Special Flight Permit
Special flight permits are prohibited.
(g) Alternative Methods of Compliance (AMOC)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Charles Harrison,
Project Manager, Fort Worth Aircraft Certification Office, 10101
Hillwood Pkwy., Fort Worth, Texas 76177; telephone 817-222-5140;
email 9-ASW-FTW-AMOC-Requests@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.
(h) Additional Information
Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09,
dated January 14, 2013, and Bell Helicopter Textron ASB No. 204-75-1
and ASB 205-75-5, both Revision C and both dated April 25, 1979,
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 https://www.bellcustomer.com/files/. You may review a
copy of information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth,
Texas 76177.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor
Blades.
Issued in Fort Worth, Texas, on March 29, 2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-07985 Filed 4-8-16; 8:45 am]
BILLING CODE 4910-13-P
