Airworthiness Directives; Bell Helicopter Textron Helicopters, 9793-9796 [2013-02899]
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
street address for the Docket Office
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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:
(g) Other FAA AD Provisions
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 AD:
■
2013–03–09 DG Flugzeugbau GmbH:
Amendment 39–17344; Docket No.
FAA–2012–1250; Directorate Identifier
2012–CE–043–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 19, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to DG Flugzeugbau GmbH
Model DG–1000T gliders equipped with Solo
Kleinmotoren Model 2350 C engines, all
serial numbers, certificated in any category.
(d) Subject
Air Transport Association of America
(ATA) Code 72: Engine.
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(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as a material
defect within the propeller shaft, most likely
caused by a manufacturing error. We are
issuing this AD to prevent failure of the
propeller shaft and detachment of the
propeller, which could result in reduced
control of the aircraft or injury to persons on
the ground.
(f) Actions and Compliance
Unless already done, do the following
actions:
(1) Within 25 hours time-in-service (TIS)
after March 19, 2013 (the effective date of
this AD) or 6 months after March 19, 2013
(the effective date of this AD), whichever
occurs first, remove the propeller pulley
assembly (module) from the engine and
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15:05 Feb 11, 2013
Jkt 229001
inspect the transition region of the part
number (P/N) 20 31 211 shaft following the
Actions section of Solo Kleinmotoren GmbH
Service Bulletin Nr. 4603–13, Issue 1, dated
September 24, 2012.
(2) If, during the inspection required by
paragraph (f)(1) of this AD, cracks are
detected in the P/N 20 31 211 shaft, before
further flight, do the following:
(i) Replace the P/N 20 31 211 shaft with
an airworthy P/N 20 31 211 shaft; or
(ii) Replace the propeller pulley assembly
(module) with an airworthy propeller pulley
assembly (module).
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4165; fax: (816) 329–
4090; email: jim.rutherford@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, 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.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2012–0197, dated
September 25, 2012; and Solo Kleinmotoren
GmbH Service Bulletin Nr. 4603–13, Issue 1,
dated September 24, 2012, for related
information.
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9793
(i) 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) Solo Kleinmotoren GmbH Service
Bulletin Nr. 4603–13, Issue 1, dated
September 24, 2012.
(ii) Reserved.
(3) For Solo Kleinmotoren GmbH service
information identified in this AD, contact
Solo Kleinmotoren GmbH, Postfach 60 01 52,
D 71050 Sindelfingen, Germany; telephone:
+49 07031–301–0; fax: +49 07031–301–136;
email: aircraft@solo-germany.com; Internet:
https://aircraft.solo-online.com/.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(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/
index.html.
Issued in Kansas City, Missouri, on
February 1, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–02718 Filed 2–11–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0098; Directorate
Identifier 2011–SW–039–AD; Amendment
39–17339; AD 2013–03–16]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
the Bell Helicopter Textron (Bell) Model
212 helicopters and adopting
requirements for Bell Model 204B,
205A, 205A–1, 205B and 210
helicopters with certain part-numbered
main rotor hub inboard strap fittings
(fittings). This AD requires magnetic
particle inspecting (MPI) the fittings for
SUMMARY:
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
a crack, and if a crack exists, replacing
the fittings with airworthy fittings. This
AD is prompted by reports of additional
cracked fittings and the determination
that additional part-numbered fittings
may not have been manufactured in
accordance with approved
manufacturing processes and controls.
These actions are intended to identify a
crack in the fitting, which may lead to
the fitting’s failure, loss of a main rotor
blade, and subsequent loss of helicopter
control.
DATES: This AD becomes effective
February 27, 2013.
We must receive comments on this
AD by April 15, 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.
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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
800–647–5227) 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 https://
www.bellcustomer.com/files/. You may
review a copy of the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
Michael Kohner, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, 2601 Meacham
Blvd., Fort Worth, Texas, 76137, phone:
(817) 222–5170; fax: (817) 222–5783;
email: mike.kohner@faa.gov.
SUPPLEMENTARY INFORMATION:
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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 March 29, 2011, the FAA issued
AD 2011–08–01, Amendment 39–16651
(76 FR 18865, April 6, 2011), which
superseded previously existing
emergency AD 2010–25–51, for Bell
Model 212 helicopters with a fitting,
part number (P/N) 212–010–103–007
and with a certain serial number (S/N).
AD 2011–08–01 retained the
requirements of AD 2010–25–51 to
replace certain serial-numbered fittings
and perform an MPI for a crack on other
serial-numbered fittings, and expanded
the applicability to require performing
an MPI on additional serial-numbered
fittings. The AD based the compliance
time for performing an MPI on the
number of hours time-in-service (TIS) of
the fitting. That AD was prompted by
reports of cracks in fittings.
Subsequently, the cracking was
determined to have been caused by the
manufacturer’s failure to follow
approved manufacturing processes and
controls during the quenching operation
from the heat treating of the fittings.
Since AD 2011–08–01 was issued,
two additional fittings were found with
a crack. Based on these additional
reported cracks, we have determined
that a crack may occur in a fitting
regardless of the hours TIS. In addition,
fitting P/Ns 204–012–102–001, –005,
–009, 212–010–103–005, and –101,
which are used on other model
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helicopters, are susceptible to the same
type of cracking because they are of
similar design and manufacture to
fitting P/N 212–010–103–007, which
was the subject of AD 2011–08–01.
Failure of a fitting in flight may result
in the loss of a main rotor blade and
subsequent loss of helicopter control.
Therefore, this AD reduces the
compliance time for performing an MPI
of some serial-numbered fittings by
requiring an MPI for all applicable
serial-numbered fittings within 25 hours
TIS or 15 days, whichever occurs first.
This AD does not require you to report
a cracked fitting to the Rotorcraft
Certification Office.
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 the same
type design.
Related Service Information
We have reviewed Bell Alert Service
Bulletin (ASB) No. 212–10–141,
Revision A, dated November 18, 2010,
for the Model 212 helicopter, which
specifies the immediate removal from
service of fittings with certain S/Ns.
We have also reviewed ASB No. 204–
11–66 for the Model 204B helicopters;
ASB No. 205–11–107 for the Model
205A and 205A–1 helicopters; ASB No.
205B–11–58 for the Model 205B
helicopters; ASB No. 210–11–08 for the
Model 210 helicopters; and ASB No.
212–10–142, Revision B for the Model
212 helicopters; all dated May 31, 2011.
These ASBs specify:
• For certain serial-numbered fittings
with less than 400 flight hours,
performing an initial MPI within 100
flight hours but before the fitting
reaches 425 flight hours or before
November 26, 2011, whichever occurs
first.
• For certain serial-numbered fittings
with more than 400 hours, performing
an initial MPI within 25 flight hours or
before November 26, 2011, whichever
occurs first.
• Certain serial-numbered fittings that
have already had an MPI during main
rotor hub assembly maintenance or
during an overhaul do not need an
additional MPI. Historical records must
be annotated to show compliance
during records inspection.
• If defects are found, returning the
removed strap fittings to Bell.
• If no defects are found, reidentifying the fitting by adding an
‘‘FM’’ at the end of the part number and
making a record entry.
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
• Performing a recurring MPI on all
fittings, regardless of S/N and prefix, at
1,200 hours or 24 months for all models,
except the Model 210, and at the
tension-torsion (TT) strap replacement
for the Model 210 helicopters.
AD Requirements
This AD supersedes AD 2011–08–01
(76 FR 18865, April 6, 2011) and
requires for any Model 204B, 205A,
205A–1, 205B, 210 and 212 helicopter
with certain fittings the following
actions:
• Within 25 hours TIS or 15 days,
whichever occurs first, performing an
MPI of each fitting for a crack.
• If a fitting is cracked, before further
flight, replacing it with an airworthy
fitting.
• If a fitting is not cracked, reidentifying the fitting and its component
history card or equivalent record by
adding ‘‘FM’’ at the end of the P/N.
If an MPI has previously been
performed on a fitting and the
component history card or equivalent
record of the fitting has been reidentified with ‘‘FM’’ at the end of the
P/N, the requirements of this AD have
been met.
Differences Between This AD and the
Service Information
This AD differs from the ASBs
because we require an MPI within 25
hours time-in-service or 15 days,
whichever occurs first, of any fitting
with an affected P/N and S/N. Bell
requires different compliance times
depending on the hours TIS of the
fitting. We do not require the immediate
removal of fittings, P/N 212–010–103–
007, with certain S/Ns because the MPI
provides the necessary level of safety.
We do not require returning parts to
Bell.
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Costs of Compliance
We estimate that this AD affects 152
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:
• We estimate that 304 fittings (2 per
helicopter) will need to be MPI
inspected for a crack and that this task
will require 40 work-hours. No parts are
needed for the inspection, bringing the
total cost per helicopter to $3,400;
$516,800 for all U.S. operators.
• If a fitting is cracked, replacement
parts will cost $2,367 per fitting. Labor
costs will not be an additional expense
as they can be absorbed as part of the
inspection.
According to Bell’s service
information, some of the costs of this
AD may be covered under warranty,
thereby reducing the cost impact on
affected individuals. We do not control
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 15
days, a very short time period based on
the average flight-hour utilization rate of
these helicopters.
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
opportunity for public comment before
issuing this AD are impracticable and
that good cause exists for making this
amendment effective in less than 30
days.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, I certify
that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska to the extent that it justifies
making a regulatory distinction; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by Reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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 Amendment 39–16651 (76 FR
18865, April 6, 2011) and adding the
following new airworthiness directive
(AD):
■
2013–03–16 Bell Helicopter Textron (Bell):
Amendment 39–17339; Docket No.
FAA–2013–0098; Directorate Identifier
2011–SW–39–AD.
(a) Applicability
This AD applies to Model 204B, 205A,
205A–1, 205B, 210 and 212 helicopters,
certificated in any category, with a main rotor
hub inboard strap fitting (fitting) with a part
number (P/N) and serial number (S/N) listed
in Table 1 to paragraph (a) of this AD.
TABLE 1 TO PARAGRAPH (A)
Helicopter models
Fitting P/Ns
204B ........................................................
204–012–102–001 ..................................
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Fitting S/Ns
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9795
All.
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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations
TABLE 1 TO PARAGRAPH (A)—Continued
Helicopter models
Fitting P/Ns
Fitting S/Ns
204B, 205A and 205A–1 .........................
204B, 205A and 205A–1 .........................
212 ..........................................................
212 ..........................................................
204–012–102–005
204–012–102–009
212–010–103–005
212–010–103–007
205A–1, 205B and 210 ...........................
212–010–103–101 ..................................
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the fitting and the determination that
additional part-numbered fittings may not
have been manufactured in accordance with
approved manufacturing processes and
controls. This condition could result in
failure of a fitting, loss of a main rotor blade,
and loss of helicopter control.
(c) Affected ADs
This AD supersedes AD 2011–08–01,
Docket No. FAA–2011–0323, Amendment
39–16651 (76 FR 18865, April 6, 2011),
Directorate Identifier 2011–SW–005–AD.
(d) Effective Date
This AD becomes effective February 27,
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.
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(f) Required Actions
(1) Within 25 hours time-in-service or 15
days, whichever occurs first, perform a
magnetic particle inspection (MPI) of each
fitting for a crack. If an MPI was already
performed on a fitting resulting in reidentifying the fitting with ‘‘FM’’ at the end
of the P/N or at the end of the P/N on the
fitting’s component history card or
equivalent record, then the requirements of
this AD have been met.
(2) If a fitting is cracked, before further
flight, replace it with an airworthy fitting.
(3) If a fitting is not cracked, before further
flight, re-identify the fitting by adding ‘‘FM’’
at the end of the P/N using a vibrating stylus.
The depth of the ‘‘FM’’ must not exceed
0.005 inches or extend within 0.10 inch of
the part’s edge. Also, add ‘‘FM’’ at the end
of the P/N on the fitting’s component history
card or equivalent record.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Michael Kohner,
Aerospace Engineer, FAA, Rotorcraft
Directorate, Rotorcraft Certification Office,
2601 Meacham Blvd., Fort Worth, Texas,
76137, phone: (817) 222–5170; fax: (817)
222–5783; email: mike.kohner@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
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15:05 Feb 11, 2013
Jkt 229001
..................................
..................................
..................................
..................................
All.
All, except S/Ns 7500 or larger with a prefix of ‘‘A’’.
All.
All, except S/Ns 140 or larger with a prefix of ‘‘SH’’ and except S/Ns 11021 or larger with a prefix of ‘‘A’’.
All, except S/Ns 486 or larger with a prefix of ‘‘SH,’’ and
except S/Ns 10997 or larger with a prefix of ‘‘A’’.
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 Alert Service Bulletin (ASB) No. 212–
10–141, Revision A, dated November 18,
2010; and ASBs No. 204–11–66, No. 205–11–
107, No. 205B–11–58, No. 210–11–08; and
No. 212–10–142 Revision B, all dated May
31, 2011, which are not incorporated by
reference, contain additional information
about the subject of this AD. For this service
information, contact Bell Helicopter Textron,
Inc., P.O. Box 482, Fort Worth, TX 76101,
telephone (817) 280–3391, fax (817) 280–
6466, or at https://www.bellcustomer.com/
files/. You may review this service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6220, Main Rotor Head.
Issued in Fort Worth, Texas, on January 28,
2013.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–02899 Filed 2–11–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1273; Directorate
Identifier 2012–CE–045–AD; Amendment
39–17350; AD 2013–03–15]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Cessna Aircraft Company Models 172R
and 172S airplanes. This AD was
prompted by reports of chafing of a new
configuration of the fuel return line
SUMMARY:
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assembly, which was caused by the fuel
return line assembly rubbing against the
right steering tube assembly during
rudder pedal actuation. This AD
requires you to install the forward and
aft fuel return line support clamps and
brackets; inspect for a minimum
clearance between the fuel return line
assembly and the steering tube assembly
and clearance between the fuel return
line assembly and the airplane
structure; and, if any damage is found,
replace the fuel return line assembly.
We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective March 19,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 19, 2013.
ADDRESSES: For service information
identified in this AD, contact Cessna
Aircraft Company, Customer service,
P.O. Box 7706, Wichita, KS 67277;
telephone: (316) 517–5800; fax: (316)
517–7271; email:
customercare@cessna.textron.com;
Internet: https://
www.cessnasupport.com. You may
review copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
MO 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Jeff
Janusz, Aerospace Engineer, Wichita
E:\FR\FM\12FER1.SGM
12FER1
]]>Agencies
[Federal Register Volume 78, Number 29 (Tuesday, February 12, 2013)]
[Rules and Regulations]
[Pages 9793-9796]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-02899]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0098; Directorate Identifier 2011-SW-039-AD;
Amendment 39-17339; AD 2013-03-16]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for the Bell Helicopter Textron (Bell) Model 212 helicopters and
adopting requirements for Bell Model 204B, 205A, 205A-1, 205B and 210
helicopters with certain part-numbered main rotor hub inboard strap
fittings (fittings). This AD requires magnetic particle inspecting
(MPI) the fittings for
[[Page 9794]]
a crack, and if a crack exists, replacing the fittings with airworthy
fittings. This AD is prompted by reports of additional cracked fittings
and the determination that additional part-numbered fittings may not
have been manufactured in accordance with approved manufacturing
processes and controls. These actions are intended to identify a crack
in the fitting, which may lead to the fitting's failure, loss of a main
rotor blade, and subsequent loss of helicopter control.
DATES: This AD becomes effective February 27, 2013.
We must receive comments on this AD by April 15, 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 800-647-5227) 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 https://www.bellcustomer.com/files/. You may review a copy of the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601
Meacham Blvd., Fort Worth, Texas, 76137, phone: (817) 222-5170; fax:
(817) 222-5783; email: mike.kohner@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
On March 29, 2011, the FAA issued AD 2011-08-01, Amendment 39-16651
(76 FR 18865, April 6, 2011), which superseded previously existing
emergency AD 2010-25-51, for Bell Model 212 helicopters with a fitting,
part number (P/N) 212-010-103-007 and with a certain serial number (S/
N). AD 2011-08-01 retained the requirements of AD 2010-25-51 to replace
certain serial-numbered fittings and perform an MPI for a crack on
other serial-numbered fittings, and expanded the applicability to
require performing an MPI on additional serial-numbered fittings. The
AD based the compliance time for performing an MPI on the number of
hours time-in-service (TIS) of the fitting. That AD was prompted by
reports of cracks in fittings. Subsequently, the cracking was
determined to have been caused by the manufacturer's failure to follow
approved manufacturing processes and controls during the quenching
operation from the heat treating of the fittings.
Since AD 2011-08-01 was issued, two additional fittings were found
with a crack. Based on these additional reported cracks, we have
determined that a crack may occur in a fitting regardless of the hours
TIS. In addition, fitting P/Ns 204-012-102-001, -005, -009, 212-010-
103-005, and -101, which are used on other model helicopters, are
susceptible to the same type of cracking because they are of similar
design and manufacture to fitting P/N 212-010-103-007, which was the
subject of AD 2011-08-01. Failure of a fitting in flight may result in
the loss of a main rotor blade and subsequent loss of helicopter
control. Therefore, this AD reduces the compliance time for performing
an MPI of some serial-numbered fittings by requiring an MPI for all
applicable serial-numbered fittings within 25 hours TIS or 15 days,
whichever occurs first. This AD does not require you to report a
cracked fitting to the Rotorcraft Certification Office.
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 the same type design.
Related Service Information
We have reviewed Bell Alert Service Bulletin (ASB) No. 212-10-141,
Revision A, dated November 18, 2010, for the Model 212 helicopter,
which specifies the immediate removal from service of fittings with
certain S/Ns.
We have also reviewed ASB No. 204-11-66 for the Model 204B
helicopters; ASB No. 205-11-107 for the Model 205A and 205A-1
helicopters; ASB No. 205B-11-58 for the Model 205B helicopters; ASB No.
210-11-08 for the Model 210 helicopters; and ASB No. 212-10-142,
Revision B for the Model 212 helicopters; all dated May 31, 2011. These
ASBs specify:
For certain serial-numbered fittings with less than 400
flight hours, performing an initial MPI within 100 flight hours but
before the fitting reaches 425 flight hours or before November 26,
2011, whichever occurs first.
For certain serial-numbered fittings with more than 400
hours, performing an initial MPI within 25 flight hours or before
November 26, 2011, whichever occurs first.
Certain serial-numbered fittings that have already had an
MPI during main rotor hub assembly maintenance or during an overhaul do
not need an additional MPI. Historical records must be annotated to
show compliance during records inspection.
If defects are found, returning the removed strap fittings
to Bell.
If no defects are found, re-identifying the fitting by
adding an ``FM'' at the end of the part number and making a record
entry.
[[Page 9795]]
Performing a recurring MPI on all fittings, regardless of
S/N and prefix, at 1,200 hours or 24 months for all models, except the
Model 210, and at the tension-torsion (TT) strap replacement for the
Model 210 helicopters.
AD Requirements
This AD supersedes AD 2011-08-01 (76 FR 18865, April 6, 2011) and
requires for any Model 204B, 205A, 205A-1, 205B, 210 and 212 helicopter
with certain fittings the following actions:
Within 25 hours TIS or 15 days, whichever occurs first,
performing an MPI of each fitting for a crack.
If a fitting is cracked, before further flight, replacing
it with an airworthy fitting.
If a fitting is not cracked, re-identifying the fitting
and its component history card or equivalent record by adding ``FM'' at
the end of the P/N.
If an MPI has previously been performed on a fitting and the
component history card or equivalent record of the fitting has been re-
identified with ``FM'' at the end of the P/N, the requirements of this
AD have been met.
Differences Between This AD and the Service Information
This AD differs from the ASBs because we require an MPI within 25
hours time-in-service or 15 days, whichever occurs first, of any
fitting with an affected P/N and S/N. Bell requires different
compliance times depending on the hours TIS of the fitting. We do not
require the immediate removal of fittings, P/N 212-010-103-007, with
certain S/Ns because the MPI provides the necessary level of safety. We
do not require returning parts to Bell.
Costs of Compliance
We estimate that this AD affects 152 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:
We estimate that 304 fittings (2 per helicopter) will need
to be MPI inspected for a crack and that this task will require 40
work-hours. No parts are needed for the inspection, bringing the total
cost per helicopter to $3,400; $516,800 for all U.S. operators.
If a fitting is cracked, replacement parts will cost
$2,367 per fitting. Labor costs will not be an additional expense as
they can be absorbed as part of the inspection.
According to Bell's service information, some of the costs of this
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control 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 15 days, a very short time period
based on the average flight-hour utilization rate of these helicopters.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-16651 (76 FR
18865, April 6, 2011) and adding the following new airworthiness
directive (AD):
2013-03-16 Bell Helicopter Textron (Bell): Amendment 39-17339;
Docket No. FAA-2013-0098; Directorate Identifier 2011-SW-39-AD.
(a) Applicability
This AD applies to Model 204B, 205A, 205A-1, 205B, 210 and 212
helicopters, certificated in any category, with a main rotor hub
inboard strap fitting (fitting) with a part number (P/N) and serial
number (S/N) listed in Table 1 to paragraph (a) of this AD.
Table 1 to paragraph (a)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Helicopter models Fitting P/Ns Fitting S/Ns
--------------------------------------------------------------------------------------------------------------------------------------------------------
204B.................................... 204-012-102-001............ All.
[[Page 9796]]
204B, 205A and 205A-1................... 204-012-102-005............ All.
204B, 205A and 205A-1................... 204-012-102-009............ All, except S/Ns 7500 or larger with a prefix of ``A''.
212..................................... 212-010-103-005............ All.
212..................................... 212-010-103-007............ All, except S/Ns 140 or larger with a prefix of ``SH'' and except S/Ns 11021 or
larger with a prefix of ``A''.
205A-1, 205B and 210.................... 212-010-103-101............ All, except S/Ns 486 or larger with a prefix of ``SH,'' and except S/Ns 10997 or
larger with a prefix of ``A''.
--------------------------------------------------------------------------------------------------------------------------------------------------------
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the fitting
and the determination that additional part-numbered fittings may not
have been manufactured in accordance with approved manufacturing
processes and controls. This condition could result in failure of a
fitting, loss of a main rotor blade, and loss of helicopter control.
(c) Affected ADs
This AD supersedes AD 2011-08-01, Docket No. FAA-2011-0323,
Amendment 39-16651 (76 FR 18865, April 6, 2011), Directorate
Identifier 2011-SW-005-AD.
(d) Effective Date
This AD becomes effective February 27, 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 or 15 days, whichever occurs
first, perform a magnetic particle inspection (MPI) of each fitting
for a crack. If an MPI was already performed on a fitting resulting
in re-identifying the fitting with ``FM'' at the end of the P/N or
at the end of the P/N on the fitting's component history card or
equivalent record, then the requirements of this AD have been met.
(2) If a fitting is cracked, before further flight, replace it
with an airworthy fitting.
(3) If a fitting is not cracked, before further flight, re-
identify the fitting by adding ``FM'' at the end of the P/N using a
vibrating stylus. The depth of the ``FM'' must not exceed 0.005
inches or extend within 0.10 inch of the part's edge. Also, add
``FM'' at the end of the P/N on the fitting's component history card
or equivalent record.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, 2601 Meacham Blvd., Fort Worth, Texas, 76137,
phone: (817) 222-5170; fax: (817) 222-5783; email:
mike.kohner@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 Alert Service Bulletin (ASB) No. 212-10-141, Revision A,
dated November 18, 2010; and ASBs No. 204-11-66, No. 205-11-107, No.
205B-11-58, No. 210-11-08; and No. 212-10-142 Revision B, all dated
May 31, 2011, which are not incorporated by reference, contain
additional information about the subject of this AD. For this
service information, contact Bell Helicopter Textron, Inc., P.O. Box
482, Fort Worth, TX 76101, telephone (817) 280-3391, fax (817) 280-
6466, or at https://www.bellcustomer.com/files/. You may review this
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor
Head.
Issued in Fort Worth, Texas, on January 28, 2013.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-02899 Filed 2-11-13; 8:45 am]
BILLING CODE 4910-13-P
