Airworthiness Directives; Bell Helicopter Textron Helicopters, 45845-45848 [2013-18079]
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Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations
(3) Use paragraph 3.A(2) of CFM Service
Bulletin (SB) No. CFM56–5 S/B 73–0182,
Revision 6, dated March 8, 2012, or CFM SB
No. CFM56–5B S/B 73–0122, Revision 8,
dated March 8, 2012, to do the inspection.
(h) Repetitive Inspections
Repeat the inspection required in
paragraph (g)(3) of this AD before 10,000
hours since last overhaul if, after last
overhaul, the HMU is exposed to TS–1 fuel.
(i) Credit for Previous Actions
If the HMU has not been exposed to TS–
1 fuel since the last overhaul, then the initial
inspection in paragraph (g) of this AD is not
required.
(j) Definitions
For the purposes of this AD, overhaul is
defined as HMU maintenance, which
includes inspection, cleaning, or replacement
of the HMU delta-P valve.
(k) 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 5 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.
(l) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
may approve AMOCs for this AD. Use the
procedures found in 14 CFR 39.19 to make
your request.
emcdonald on DSK67QTVN1PROD with RULES
(m) Related Information
(1) For more information about this AD,
contact Martin Adler, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7157; fax: 781–238–7199;
email: martin.adler@faa.gov.
(2) Refer to European Aviation Safety
Agency, AD 2012–0123, dated July 9, 2012,
for more information. You may examine this
AD on the Internet at https://
www.regulations.gov.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
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(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) CFM International, S. A. (CFM) Service
Bulletin No. CFM56–5 S/B 73–0182, Revision
6, dated March 8, 2012.
(ii) CFM Service Bulletin No. CFM56–5B
S/B 73–0122, Revision 8, dated March 8,
2012.
(3) For CFM International, S. A. service
information identified in this AD, contact
CFM International Inc., Aviation Operations
Center, 1 Neumann Way, M/D Room 285,
Cincinnati, OH 45125; International phone:
513–552–3272; USA phone: 877–432–3272;
International fax: 513–552–3329; USA fax:
877–432–3329; email: geae.aoc@ge.com; or
CFM International SA, Customer Support
Center, International phone: 33 1 64 14 88 66;
International fax: 33 1 64 79 85 55; email:
snecma.csc@snecma.fr.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(5) You may view this service information
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
July 9, 2013.
Robert J. Ganley,
Acting Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2013–17296 Filed 7–29–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0639; Directorate
Identifier 2013–SW–020–AD; Amendment
39–17518; AD 2013–15–02]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule, request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–10–
03 for Bell Helicopter Textron
Helicopters (Bell) Model 204B, 205A,
205A–1, 205B, 210, 212, 412, 412CF,
and 412EP helicopters. AD 2008–10–03
required certain checks and inspections
of each tail rotor blade assembly (T/R
blade) at specified intervals and
repairing or replacing, as applicable,
any cracked or damaged T/R blade.
Since we issued AD 2008–10–03, an
SUMMARY:
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45845
accident attributed to a T/R failure
occurred. This new AD retains the
requirements of AD 2008–10–03 and
adds a second, more detailed inspection
that allows for an earlier detection of a
crack or other damage in a T/R blade.
These actions are intended to prevent a
failure of the T/R blade and subsequent
loss of helicopter control.
DATES: This AD becomes effective
August 14, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of August 14, 2013.
We must receive comments on this
AD by September 30, 2013.
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 or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the economic
evaluation, any comments received, and
other information. The street address for
the Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
For service information identified in
this AD, contact Bell Helicopter
Textron, Inc., P.O. Box 482, Fort Worth,
TX 76101; telephone (817) 280–3391;
fax (817) 280–6466; or at
www.bellcustomer.com/. You may
review 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, Aviation Safety
Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5170; email
7-AVS-ASW-170@faa.gov.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations
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 April 22, 2008, we issued AD
2008–10–03, Amendment 39–15509 (73
FR 24858, May 6, 2008) for Bell Model
204B, 205A, 205A–1, 205B, 210, 212,
412, 412CF, and 412EP helicopters. AD
2008–10–03 required certain checks and
inspections of each T/R blade at
specified intervals and repairing or
replacing, as applicable, any
unairworthy T/R blade. AD 2008–10–03
was prompted by eight reports of fatigue
cracking of T/R blades installed on Bell
Model 212 and 412 helicopters (three
failures on the Bell Model 212 and five
failures on the Bell Model 412) with a
T/R blade, part number (P/N) 212–010–
750–009, –105, and –107. Three of the
Model 412 failures occurred during
flight.
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Actions Since AD 2008–10–03 Was
Issued
Since we issued AD 2008–10–03 (73
FR 24858, May 6, 2008), an accident
attributed to a T/R failure occurred.
Because of this accident, we have
determined that a superseding AD is
necessary to require a second, more
detailed inspection that allows for an
earlier detection of a crack or other
damage. These actions are intended to
prevent failure of T/R blade and
subsequent loss of helicopter control.
This superseding AD does not apply
to Model 204B helicopters because
those helicopters do not have the
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affected T/R blades installed and should
not have been included in the
applicability of AD 2008–10–03. We are
no longer requiring a daily check of the
T/R blades because we have determined
that the additional, more detailed
inspection and the sequence of the
inspections provide an appropriate level
of safety.
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
On February 4, 2013, Bell issued Alert
Service Bulletin (ASB) No. 205–13–109
for Model 205A and 205A–1
helicopters; ASB No. 205B–13–61 for
Model 205B helicopters; ASB No. 212–
13–147 for Model 212 helicopters; ASB
412–13–155 for Model 412 and 412EP
helicopters; and ASB No. 412CF–13–52
for 412CF helicopters. All ASBs are
dated February 4, 2013. Bell reported
that it recently examined a fractured T/
R blade and that the fracture originated
from surface damage. ASB No. 205–13–
109, No. 205B–13–61, and No. 412CF–
13–52 describe procedures for a 3X
magnifying glass inspection of the entire
T/R blade surface for damage every 25
hours time-in-service (TIS), similar to
that required by AD 2008–10–03 (73 FR
24858, May 6, 2008). ASB No. 212–13–
147 and No. 412–13–155 do not include
this 3X visual inspection, because that
inspection has been incorporated into
the maintenance manual for these
models. All five of the ASBs introduce
an additional local visual inspection
with a10X magnifying glass of each T/
R blade between blade station 20.00 to
35.00 from the leading edge to the
trailing edge. Bell added a reminder to
operators that it is critical to investigate
any paint and skin imperfections should
the inspection warrant such action. If
any skin damage exceeds the limits in
the applicable Maintenance Manual, the
ASBs call for removing the T/R blade
from service.
AD Requirements
This AD supersedes AD 2008–10–03
(73 FR 24858, May 6, 2008) and requires
for any Model 205A, 205A–1, 205B, 210,
212, 412, 412CF, and 412EP helicopter
with certain T/R blades the following
actions:
Within 25 hours TIS or 30 days,
whichever occurs first, and thereafter at
intervals not to exceed 25 hours TIS or
30 days, whichever occurs first,
cleaning and visually inspecting each T/
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R blade assembly for a crack, corrosion,
nick, scratch, or dent using a 3X or
higher power magnifying glass and a
bright light; and
Visually inspecting certain parts of
each T/R blade for a crack or other
damage using a 10X or higher power
magnifying glass and a bright light, and
if damage exists, measuring the depth of
any damage.
Before further flight, replacing any
cracked T/R blade and repairing or
replacing any damaged T/R blade.
Replacing a blade with T/R blade, P/
N 412–016–100–111, on eligible
helicopters is terminating action for the
inspection requirements of this AD.
Differences Between the AD and the
Service Information
This AD differs from the ASBs
because we include Model 210
helicopters. The Model 210 helicopter
has the same part-numbered blades as
the other applicable helicopter models.
Costs of Compliance
We estimate that this AD affects 80
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:
Visually inspecting a blade (2 per
helicopter) for a crack or other damage
will require .25 work-hour. No parts are
needed. For the expected 12 annual
inspections, the total cost per helicopter
will be $510 a year, and $40,800 for the
U.S. fleet.
Replacing a T/R assembly will require
6 work-hours for a labor cost of $510.
Parts will cost $23,048, bringing the
total cost to $23,558 per helicopter.
According to the Bell’s service
information, some of the cost may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control the
warranty coverage by Bell. Accordingly,
we have included all costs in our cost
estimate.
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 25
hours TIS or 30 days, whichever comes
first, a very short time period based on
the average flight-hour utilization rate of
these helicopters. These helicopters are
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Federal Register / Vol. 78, No. 146 / Tuesday, July 30, 2013 / Rules and Regulations
typically used for logging, firefighting,
and lifting and carrying external loads.
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.
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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 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.
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.
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2008–10–03, Amendment 39–15509 (73
FR 24858, May 6, 2008), and adding the
following new AD:
■
2013–15–02 BELL HELICOPTER
TEXTRON: Amendment 39–17518;
Docket No. FAA–2013–0639; Directorate
Identifier 2013–SW–020–AD.
(a) Applicability
This AD applies to Bell Helicopter Textron
(Bell) Model 205A, 205A–1, 205B, 210, 212,
412, 412CF, and 412EP helicopters with a tail
rotor blade assembly (T/R blade), part
number (P/N) 210–010–001–(all dash
numbers) or 212–010–750–(all dash
numbers), certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
fatigue cracking of a T/R blade, which could
lead to failure of the T/R blade and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD No. 2008–10–03,
Amendment 39–15509 (73 FR 24858, May 6,
2008).
(d) Effective Date
This AD becomes effective August 14,
2013.
(e) 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.
(f) Required Actions
(1) Within 25 hours time-in-service (TIS) or
30 days, whichever occurs first, and
thereafter at intervals not to exceed 25 hours
TIS or 30 days, whichever occurs first:
(i) Clean each T/R blade by hand using a
mild soap and cheesecloth (C–486) on both
sides of the blade in a spanwise direction and
dry thoroughly.
(ii) Using a 3X or higher power magnifying
glass and a bright light, visually inspect the
T/R blade skins, leading edge spar, doublers,
grip plates, and trailing edge on both sides
of each blade for a crack, corrosion (may be
indicated by blistering, peeling, flaking,
bubbling, or cracked paint), a nick, scratch,
dent, or other damage. Pay particular
attention to both sides of the T/R blade in the
area located 16 to 35 inches from the T/R
blade tip (blade station 20.00 to 35.00—the
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45847
T/R blade tip is located at blade station 51)
as shown by the shaded area of Figure 1 of
Bell Alert Service Bulletin (ASB) No. 205–
13–109; ASB No. 205B–13–61; ASB No. 212–
13–147; ASB 412–13–155; or ASB No.
412CF–13–52, all dated February 4, 2013, as
applicable to your helicopter. Also, pay
particular attention to the inboard blade butt
area near the attachment of the external
balance weight and screws, and to any blade
surface that was snagged by cheesecloth, as
that may be an indication of a crack or paint
chip that could lead to corrosion.
Note 1 to Paragraph (f) of this AD: Figure
1 of the Bell ASB No. 205–13–109; ASB No.
205B–13–61; ASB No. 212–13–147; ASB
412–13–155; and ASB No. 412CF–13–52, all
dated February 4, 2013, show the shaded area
as part of the 10X inspection only. This AD
requires the shaded area to be inspected
during both the 3X and 10X inspections.
(iii) Using a 10X or higher magnifying glass
and a bright light, visually inspect both sides
of each blade for a crack or other damage
between blade station 20.00 to 35.00 as
shown by the shaded area of Figure 1 of Bell
ASB No. 205–13–109; ASB No. 205B–13–61;
ASB No. 212–13–147; ASB 412–13–155; or
ASB No. 412CF–13–52, all dated February 4,
2013, as applicable to your helicopter.
(iv) If any blistering, peeling, flaking,
bubbling, or cracked paint is detected
anywhere on the blade, remove the paint
from the affected area by sanding in a
spanwise direction with abrasive cloth or
paper (C–406) 240-grit or finer, and a final
sanding using abrasive cloth or paper (C–406)
400-grit or finer. Visually inspect the affected
area for any corrosion or a crack using a 10X
or higher magnifying glass and a bright light.
If any corrosion is found, measure the depth
of the damage. (A digital optical micrometer
is one tool that can be used for this
measurement.)
(v) If a nick, scratch, or dent is found
anywhere on the blade, visually inspect for
a crack using a 10X or higher power
magnifying glass and a bright light. Measure
the depth of the damage. (A digital optical
micrometer is one tool that can be used for
this measurement.)
(2) Before further flight:
(i) Replace with an airworthy blade any
T/R blade that has a crack or that has any
corrosion, nick, scratch, dent, or other
damage that exceeds any of the maximum
repair limits.
(ii) Repair or replace with an airworthy
blade any T/R blade that has any corrosion,
nick, scratch, dent or other damage that is
within the maximum repair limits.
(3) Replacing a T/R blade with T/R blade,
P/N 412–016–100–111, on eligible helicopter
models is considered terminating action to
this AD.
(g) Special Flight Permit
Special flight permits are prohibited.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft
Certification Office, Rotorcraft Directorate,
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FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5170;
email 7-AVS-ASW-170@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) Subject
Joint Aircraft Service Component (JASC)
Code: 6410, Tail Rotor Blades.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bell ASB No. 205–13–109, dated
February 4, 2013.
(ii) Bell ASB No. 205B–13–61, dated
February 4, 2013.
(iii) Bell ASB No. 212–13–147, dated
February 4, 2013.
(iv) Bell ASB No. 412–13–155, dated
February 4, 2013.
(v) Bell ASB No. 412CF–13–52, dated
February 4, 2013.
(3) For Bell service information identified
in this AD, contact Bell Helicopter Textron,
Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280–3391; fax (817) 280–
6466; or at www.bellcustomer.com/.
(4) You may view this service information
that is incorporated by reference in the AD
Docket on the Internet at https://
www.regulations.gov.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on July 11,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–18079 Filed 7–29–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
emcdonald on DSK67QTVN1PROD with RULES
14 CFR Part 71
[Docket No. FAA–2012–1303; Airspace
Docket No. 12–ANM–29]
Amendment of Class E Airspace; Salt
Lake City, UT
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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ACTION:
Final rule.
This action modifies Class E
airspace at Salt Lake City, UT, to
accommodate aircraft using Area
Navigation (RNAV) Global Positioning
System (GPS) and Instrument Landing
System (ILS) or Localizer (LOC)
standard instrument approach
procedures at Salt Lake City
International Airport. This improves the
safety and management of Instrument
Flight Rules (IFR) operations at the
airport. This action also adjusts the
geographic coordinates of the airport,
and makes a minor change to the legal
description of Class E airspace
extending upward from 1,200 feet above
the surface, at Salt Lake City, UT.
DATES: Effective date, 0901 UTC,
October 17, 2013. The Director of the
Federal Register approves this
incorporation by reference action under
1 CFR part 51, subject to the annual
revision of FAA Order 7400.9 and
publication of conforming amendments.
FOR FURTHER INFORMATION CONTACT:
Eldon Taylor, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 1601
Lind Avenue SW., Renton, WA, 98057;
telephone (425) 203–4537.
SUPPLEMENTARY INFORMATION:
SUMMARY:
History
On May 13, 2013, the FAA published
in the Federal Register a notice of
proposed rulemaking (NPRM) to modify
controlled airspace at Salt Lake City, UT
(78 FR 27872). Interested parties were
invited to participate in this rulemaking
effort by submitting written comments
on the proposal to the FAA. No
comments were received.
Subsequent to publication, the FAA’s
Aeronautical Products Office requested
the phrase in the regulatory text ‘‘. . .
excluding that portion within Restricted
Area R–6403.’’ be moved from the
13,500 foot airspace and incorporated
into the 1,200 foot airspace. With the
exception of editorial changes and the
changes described above, this rule is the
same as that proposed in the NPRM.
Class E airspace designations are
published in paragraph 6005, of FAA
Order 7400.9W dated August 8, 2012,
and effective September 15, 2012, which
is incorporated by reference in 14 CFR
71.1. The Class E airspace designations
listed in this document will be
published subsequently in that Order.
The Rule
This action amends Title 14 Code of
Federal Regulations (14 CFR) Part 71 by
modifying Class E airspace extending
upward from 700 feet above the surface,
at Salt Lake City International Airport,
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
Salt Lake City, UT, to accommodate IFR
aircraft executing RNAV (GPS) and ILS
or LOC standard instrument approach
procedures at the airport. This action
removes reference to the exclusion of
the Price, UT; Delta, UT; and Evanston,
WY, airspace area, and the Bonneville,
UT 1,200 foot Class E airspace area, and
enhances the safety and management of
aircraft operations at the airport. The
geographic coordinates of the airport are
adjusted in accordance with the FAA’s
aeronautical database.
The FAA has determined this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. Therefore, this regulation: (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); and (3)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. Since this is a
routine matter that only affects air traffic
procedures and air navigation, it is
certified this rule, when promulgated,
does not have a significant economic
impact on a substantial number of small
entities under the criteria of the
Regulatory Flexibility Act. The FAA’s
authority to issue rules regarding
aviation safety is found in Title 49 of the
U.S. Code. Subtitle 1, Section 106
discusses the authority of the FAA
Administrator. Subtitle VII, Aviation
Programs, describes in more detail the
scope of the agency’s authority. This
rulemaking is promulgated under the
authority described in Subtitle VII, Part
A, Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it modifies
controlled airspace at Salt Lake City
International Airport, Salt Lake City,
UT.
Environmental Review
The FAA has determined that this
action qualifies for categorical exclusion
under the National Environmental
Policy Act in accordance with FAA
Order 1050.1E, ‘‘Environmental
Impacts: Policies and Procedures,’’
paragraph 311a. This airspace action is
not expected to cause any potentially
significant environmental impacts, and
no extraordinary circumstances exist
that warrant preparation of an
environmental assessment.
E:\FR\FM\30JYR1.SGM
30JYR1
]]>Agencies
[Federal Register Volume 78, Number 146 (Tuesday, July 30, 2013)]
[Rules and Regulations]
[Pages 45845-45848]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18079]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0639; Directorate Identifier 2013-SW-020-AD;
Amendment 39-17518; AD 2013-15-02]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule, request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2008-10-03 for
Bell Helicopter Textron Helicopters (Bell) Model 204B, 205A, 205A-1,
205B, 210, 212, 412, 412CF, and 412EP helicopters. AD 2008-10-03
required certain checks and inspections of each tail rotor blade
assembly (T/R blade) at specified intervals and repairing or replacing,
as applicable, any cracked or damaged T/R blade. Since we issued AD
2008-10-03, an accident attributed to a T/R failure occurred. This new
AD retains the requirements of AD 2008-10-03 and adds a second, more
detailed inspection that allows for an earlier detection of a crack or
other damage in a T/R blade. These actions are intended to prevent a
failure of the T/R blade and subsequent loss of helicopter control.
DATES: This AD becomes effective August 14, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of August 14, 2013.
We must receive comments on this AD by September 30, 2013.
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 or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the economic evaluation, any
comments received, and other information. The street address for the
Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone
(817) 280-3391; fax (817) 280-6466; or at www.bellcustomer.com/. You
may review 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, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170;
email 7-AVS-ASW-170@faa.gov.
SUPPLEMENTARY INFORMATION:
[[Page 45846]]
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 April 22, 2008, we issued AD 2008-10-03, Amendment 39-15509 (73
FR 24858, May 6, 2008) for Bell Model 204B, 205A, 205A-1, 205B, 210,
212, 412, 412CF, and 412EP helicopters. AD 2008-10-03 required certain
checks and inspections of each T/R blade at specified intervals and
repairing or replacing, as applicable, any unairworthy T/R blade. AD
2008-10-03 was prompted by eight reports of fatigue cracking of T/R
blades installed on Bell Model 212 and 412 helicopters (three failures
on the Bell Model 212 and five failures on the Bell Model 412) with a
T/R blade, part number (P/N) 212-010-750-009, -105, and -107. Three of
the Model 412 failures occurred during flight.
Actions Since AD 2008-10-03 Was Issued
Since we issued AD 2008-10-03 (73 FR 24858, May 6, 2008), an
accident attributed to a T/R failure occurred. Because of this
accident, we have determined that a superseding AD is necessary to
require a second, more detailed inspection that allows for an earlier
detection of a crack or other damage. These actions are intended to
prevent failure of T/R blade and subsequent loss of helicopter control.
This superseding AD does not apply to Model 204B helicopters
because those helicopters do not have the affected T/R blades installed
and should not have been included in the applicability of AD 2008-10-
03. We are no longer requiring a daily check of the T/R blades because
we have determined that the additional, more detailed inspection and
the sequence of the inspections provide an appropriate level of safety.
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
On February 4, 2013, Bell issued Alert Service Bulletin (ASB) No.
205-13-109 for Model 205A and 205A-1 helicopters; ASB No. 205B-13-61
for Model 205B helicopters; ASB No. 212-13-147 for Model 212
helicopters; ASB 412-13-155 for Model 412 and 412EP helicopters; and
ASB No. 412CF-13-52 for 412CF helicopters. All ASBs are dated February
4, 2013. Bell reported that it recently examined a fractured T/R blade
and that the fracture originated from surface damage. ASB No. 205-13-
109, No. 205B-13-61, and No. 412CF-13-52 describe procedures for a 3X
magnifying glass inspection of the entire T/R blade surface for damage
every 25 hours time-in-service (TIS), similar to that required by AD
2008-10-03 (73 FR 24858, May 6, 2008). ASB No. 212-13-147 and No. 412-
13-155 do not include this 3X visual inspection, because that
inspection has been incorporated into the maintenance manual for these
models. All five of the ASBs introduce an additional local visual
inspection with a10X magnifying glass of each T/R blade between blade
station 20.00 to 35.00 from the leading edge to the trailing edge. Bell
added a reminder to operators that it is critical to investigate any
paint and skin imperfections should the inspection warrant such action.
If any skin damage exceeds the limits in the applicable Maintenance
Manual, the ASBs call for removing the T/R blade from service.
AD Requirements
This AD supersedes AD 2008-10-03 (73 FR 24858, May 6, 2008) and
requires for any Model 205A, 205A-1, 205B, 210, 212, 412, 412CF, and
412EP helicopter with certain T/R blades the following actions:
Within 25 hours TIS or 30 days, whichever occurs first, and
thereafter at intervals not to exceed 25 hours TIS or 30 days,
whichever occurs first, cleaning and visually inspecting each T/R blade
assembly for a crack, corrosion, nick, scratch, or dent using a 3X or
higher power magnifying glass and a bright light; and
Visually inspecting certain parts of each T/R blade for a crack or
other damage using a 10X or higher power magnifying glass and a bright
light, and if damage exists, measuring the depth of any damage.
Before further flight, replacing any cracked T/R blade and
repairing or replacing any damaged T/R blade.
Replacing a blade with T/R blade, P/N 412-016-100-111, on eligible
helicopters is terminating action for the inspection requirements of
this AD.
Differences Between the AD and the Service Information
This AD differs from the ASBs because we include Model 210
helicopters. The Model 210 helicopter has the same part-numbered blades
as the other applicable helicopter models.
Costs of Compliance
We estimate that this AD affects 80 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:
Visually inspecting a blade (2 per helicopter) for a crack or other
damage will require .25 work-hour. No parts are needed. For the
expected 12 annual inspections, the total cost per helicopter will be
$510 a year, and $40,800 for the U.S. fleet.
Replacing a T/R assembly will require 6 work-hours for a labor cost
of $510. Parts will cost $23,048, bringing the total cost to $23,558
per helicopter.
According to the Bell's service information, some of the cost may
be covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control the warranty coverage by Bell.
Accordingly, we have included all costs in our cost estimate.
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 25 hours TIS or 30 days, whichever
comes first, a very short time period based on the average flight-hour
utilization rate of these helicopters. These helicopters are
[[Page 45847]]
typically used for logging, firefighting, and lifting and carrying
external loads.
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 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.
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.
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 removing airworthiness directive (AD)
2008-10-03, Amendment 39-15509 (73 FR 24858, May 6, 2008), and adding
the following new AD:
2013-15-02 BELL HELICOPTER TEXTRON: Amendment 39-17518; Docket No.
FAA-2013-0639; Directorate Identifier 2013-SW-020-AD.
(a) Applicability
This AD applies to Bell Helicopter Textron (Bell) Model 205A,
205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters with a
tail rotor blade assembly (T/R blade), part number (P/N) 210-010-
001-(all dash numbers) or 212-010-750-(all dash numbers),
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue cracking of a T/
R blade, which could lead to failure of the T/R blade and subsequent
loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD No. 2008-10-03, Amendment 39-15509 (73 FR
24858, May 6, 2008).
(d) Effective Date
This AD becomes effective August 14, 2013.
(e) 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.
(f) Required Actions
(1) Within 25 hours time-in-service (TIS) or 30 days, whichever
occurs first, and thereafter at intervals not to exceed 25 hours TIS
or 30 days, whichever occurs first:
(i) Clean each T/R blade by hand using a mild soap and
cheesecloth (C-486) on both sides of the blade in a spanwise
direction and dry thoroughly.
(ii) Using a 3X or higher power magnifying glass and a bright
light, visually inspect the T/R blade skins, leading edge spar,
doublers, grip plates, and trailing edge on both sides of each blade
for a crack, corrosion (may be indicated by blistering, peeling,
flaking, bubbling, or cracked paint), a nick, scratch, dent, or
other damage. Pay particular attention to both sides of the T/R
blade in the area located 16 to 35 inches from the T/R blade tip
(blade station 20.00 to 35.00--the T/R blade tip is located at blade
station 51) as shown by the shaded area of Figure 1 of Bell Alert
Service Bulletin (ASB) No. 205-13-109; ASB No. 205B-13-61; ASB No.
212-13-147; ASB 412-13-155; or ASB No. 412CF-13-52, all dated
February 4, 2013, as applicable to your helicopter. Also, pay
particular attention to the inboard blade butt area near the
attachment of the external balance weight and screws, and to any
blade surface that was snagged by cheesecloth, as that may be an
indication of a crack or paint chip that could lead to corrosion.
Note 1 to Paragraph (f) of this AD: Figure 1 of the Bell ASB No.
205-13-109; ASB No. 205B-13-61; ASB No. 212-13-147; ASB 412-13-155;
and ASB No. 412CF-13-52, all dated February 4, 2013, show the shaded
area as part of the 10X inspection only. This AD requires the shaded
area to be inspected during both the 3X and 10X inspections.
(iii) Using a 10X or higher magnifying glass and a bright light,
visually inspect both sides of each blade for a crack or other
damage between blade station 20.00 to 35.00 as shown by the shaded
area of Figure 1 of Bell ASB No. 205-13-109; ASB No. 205B-13-61; ASB
No. 212-13-147; ASB 412-13-155; or ASB No. 412CF-13-52, all dated
February 4, 2013, as applicable to your helicopter.
(iv) If any blistering, peeling, flaking, bubbling, or cracked
paint is detected anywhere on the blade, remove the paint from the
affected area by sanding in a spanwise direction with abrasive cloth
or paper (C-406) 240-grit or finer, and a final sanding using
abrasive cloth or paper (C-406) 400-grit or finer. Visually inspect
the affected area for any corrosion or a crack using a 10X or higher
magnifying glass and a bright light. If any corrosion is found,
measure the depth of the damage. (A digital optical micrometer is
one tool that can be used for this measurement.)
(v) If a nick, scratch, or dent is found anywhere on the blade,
visually inspect for a crack using a 10X or higher power magnifying
glass and a bright light. Measure the depth of the damage. (A
digital optical micrometer is one tool that can be used for this
measurement.)
(2) Before further flight:
(i) Replace with an airworthy blade any T/R blade that has a
crack or that has any corrosion, nick, scratch, dent, or other
damage that exceeds any of the maximum repair limits.
(ii) Repair or replace with an airworthy blade any T/R blade
that has any corrosion, nick, scratch, dent or other damage that is
within the maximum repair limits.
(3) Replacing a T/R blade with T/R blade, P/N 412-016-100-111,
on eligible helicopter models is considered terminating action to
this AD.
(g) Special Flight Permit
Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate,
[[Page 45848]]
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817)
222-5170; email 7-AVS-ASW-170@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) Subject
Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor
Blades.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Bell ASB No. 205-13-109, dated February 4, 2013.
(ii) Bell ASB No. 205B-13-61, dated February 4, 2013.
(iii) Bell ASB No. 212-13-147, dated February 4, 2013.
(iv) Bell ASB No. 412-13-155, dated February 4, 2013.
(v) Bell ASB No. 412CF-13-52, dated February 4, 2013.
(3) For Bell service information identified in this AD, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280-3391; fax (817) 280-6466; or at
www.bellcustomer.com/.
(4) You may view this service information that is incorporated
by reference in the AD Docket on the Internet at https://www.regulations.gov.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on July 11, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18079 Filed 7-29-13; 8:45 am]
BILLING CODE 4910-13-P
