[Federal Register Volume 78, Number 190 (Tuesday, October 1, 2013)]
[Rules and Regulations]
[Pages 60182-60185]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-23099]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0288; Directorate Identifier 2006-SW-25-AD;
Amendment 39-17587; AD 2013-19-05]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc.,
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for Bell
Helicopter Textron, Inc. (Bell), Model 214B, 214B-1, and 214ST
helicopters. This AD requires creating a component history card or
equivalent record for certain pylon support spindle assemblies
(spindles), establishes a new retirement life for spindles installed on
Model 214B and 214B-1 helicopters, reduces the retirement life for
spindles installed on Model 214ST helicopters, and requires replacing
any spindle that has reached its airworthiness retirement life. This AD
was prompted by three in-flight failures of the spindle that resulted
in forced landings. The actions of this AD are intended to prevent
failure of a spindle and subsequent loss of control of the helicopter.
DATES: This AD is effective November 5, 2013.
ADDRESSES: For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101;
telephone (817) 280-3391; fax (817) 280-6466; or at http://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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 (phone: 800-647-5527) is U.S. Department of
Transportation, Docket Operations Office, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
[[Page 60183]]
FOR FURTHER INFORMATION CONTACT: Martin Crane, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5056;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On March 13, 2008, at 73 FR 13513, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Bell Model 214B and
214B-1 helicopters with a certain spindle installed. The NPRM proposed
to require creating a component history card or equivalent record for
each spindle, inspecting the spindles for any corrosion, or a nick,
scratch, dent, or crack, and repairing or replacing any unairworthy
spindle before further flight. The actions proposed in the NPRM were
intended to be interim actions until a retirement life for the affected
spindles could be developed and new replacement spindles became
available. The NPRM was prompted by three in-flight failures of
spindles which resulted in forced landings and one serious injury.
On May 28, 2013, at 78 FR 31860, the Federal Register published our
supplemental notice of proposed rulemaking (SNPRM), which revised some
of the actions of the NPRM. The SNPRM added Bell Model 214ST to the
proposed applicability, revised the proposed recording requirements,
removed the proposed inspection requirements, established a new
proposed retirement life for spindle part number (P/N) 214-030-606-005,
reduced the proposed retirement life for spindle P/N 214-030-606-103,
and added a proposed requirement to replace any spindle that has
exceeded its retirement life. The Model 214ST was added after a crack
was reported in a Model 214ST spindle, P/N 214-030-606-103. Bell
determined it necessary to establish a retirement life for the spindles
because the speed at which a crack can propagate is such that a more
frequent inspection interval would not be practical. In addition, the
cost of compliance information was updated in the SNPRM by correcting
the estimated number of work-hours to replace both spindles, by
updating the estimated labor cost per work-hour from $80 to $85, and by
updating the cost of required parts to current replacement parts cost.
The proposed actions in the SNPRM were intended to prevent failure
of a spindle and subsequent loss of control of the helicopter.
Comments
We gave the public the opportunity to comment on the NPRM (73 FR
13513, March 13, 2008) and the SNPRM (78 FR 31860, May 28, 2013). We
received comments to the NPRM which we addressed in the SNPRM. The
following presents those comments and the FAA's response to each
comment.
Request
Bell stated that results from analysis and review of the pylon
spindle assembly, P/N 214-030-606-005, identified the requirement to
assign an airworthiness retirement life to that assembly. They also
stated that alert service bulletins would detail the retirement life of
the spindle. We agreed and revised the SNPRM (78 FR 31860, May 28,
2013) accordingly.
Bell commented that the NPRM (73 FR 13513, March 13, 2008) did not
address conversion of torque events to retirement index number (RIN).
We agreed and revised the SNPRM accordingly.
Bell also stated that the NPRM mis-identified the visual inspection
requirements of using a magnifying glass on each outer radius of the
spindle; that this visual inspection requirement is for the main rotor
hub spindle, not the transmission spindle. They also stated that once
cracks start, they progress very rapidly and visual inspection at a
frequency designed to discover cracking would not be manageable. We
agreed. With establishment of a maximum airworthiness life limit for
the spindle and after further review, we determined that deleting the
proposed visual inspections in the NPRM will not impact the overall
level of safety.
FAA's Determination
We have reviewed the relevant information, considered the comments
received, and determined that an unsafe condition exists and is likely
to exist or develop on other products of these same type designs and
that air safety and the public interest require adopting the AD
requirements as proposed in the SNPRM (78 FR 31860, May 28, 2013).
Related Service Information
We reviewed Bell ASB No. 214-08-70, Revision C, dated April 14,
2009 (214-08-70), which establishes a maximum airworthiness limit of
1,250 hours time-in-service (TIS) or a total accumulated RIN of 20,000,
whichever occurs first, for any spindle, P/N 214-030-606-005, that is
installed on a Model 214B or Model 214B-1 helicopter. We have also
reviewed Bell ASB No. 214ST-08-86, Revision B, dated April 14, 2009,
which reduces the maximum airworthiness life limit from 5,000 hours TIS
to 2,500 hours TIS or a total accumulated RIN of 50,000, whichever
occurs first, for any spindle, P/N 214-030-606-103, that is installed
on a Model 214ST helicopter. The ASBs also specify determining the
accumulated RIN by calculating a RIN factor of 1 for each lift or
takeoff performed during normal operation and of 2 for each lift or
takeoff performed during logging operation. When actual lift events are
unknown or cannot be determined, both ASBs specify calculating RIN at
30 lift events per flight hour; ASB No. 214-08-70 further specifies
calculating flight hours at a rate of 900 hours per year. Both ASBs
specify replacing any spindle that has reached its maximum
airworthiness limit.
Additionally, we reviewed Bell Information Letter 214ST-12-23,
dated January 30, 2012, which was issued to advise owners and operators
of the first actual reported crack in a Model 214ST spindle, P/N 214-
030-606-103.
Differences Between This AD and the Service Information
The service information specifies, as part of determining the life
of a currently installed spindle, accumulating a RIN factor of 2 for
each lift or takeoff performed during a logging operation. This AD
requires using a RIN factor of 2 for any external load lift or takeoff
in which the helicopter achieves a vertical altitude difference of
greater than 200 feet indicated altitude between the pick-up and drop-
off point. We determined that other external load lift operations with
the specified vertical altitude difference or greater will experience
the same double torque cycle as in logging operations, and that a RIN
factor of 2 needs to be used for those types of operations as well.
Also, the service information for Models 214B and 214B-1 specify an
initial compliance time of 150 flight hours, while we require an
initial compliance time of 50 hours TIS.
Costs of Compliance
We estimate that this AD will affect 12 Model 214B/B-1 and 24 Model
214ST helicopters of U.S. Registry. We estimate that operators may
incur the following costs in order to comply with this AD. It will take
about 1 work-hour for the record keeping requirements of this AD, and
about 24 work-hours to replace both spindles. Labor costs are estimated
at $85 per work-hour and the
[[Page 60184]]
cost of parts will be about $39,806 for both spindles for a Model 214B
or 214B-1, and $40,802 for both spindles for a Model 214ST. Based on
these estimates, for record keeping and the replacement of a pair of
spindles, the total per helicopter cost will be $41,931 for a Model
214B or 214B-1 and $42,927 for a Model 214ST. The total cost of
recordkeeping will be about $3,060.
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
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 above, 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 adding the following new airworthiness
directive (AD):
2013-19-05 Bell Helicopter Textron, Inc., Helicopters: Amendment 39-
17587; Docket No. FAA-2008-0288; Directorate Identifier 2006-SW-25-
AD.
(a) Applicability
This AD applies to Bell Helicopter Textron, Inc. (Bell), Model
214B, 214B-1, and 214ST helicopters, with pylon support spindle
assembly (spindle), part number (P/N) 214-030-606-005 or -103,
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue cracking of a
spindle. This condition could result in failure of the spindle and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective November 5, 2013.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Within 50 hours time-in-service (TIS):
(i) Create a component history card or equivalent record for
each spindle, P/N 214-030-606-005 and 214-030-606-103, recording the
spindle's P/N and serial number.
(ii) Review the helicopter records to determine the hours TIS of
each spindle, if the hours TIS are not already recorded for your
model helicopter. For each month for which the hours TIS is unknown,
record 75 hours TIS.
(iii) Determine the total accumulated retirement index number
(RIN) for each spindle. For the purpose of this AD, count 1 RIN for
each takeoff and 2 RIN for each external load lift in which the
helicopter achieves a vertical altitude difference of greater than
200 feet indicated altitude between the pick-up and drop-off point.
For any time period for which the accumulated RIN cannot be
determined while the spindle was installed on a helicopter, multiply
the hours TIS by 30 to calculate the spindle's accumulated RIN.
(iv) Record the hours TIS and total accumulated RIN for each
spindle on the component history card or equivalent record.
(2) Revise the Airworthiness Limitations section of the
applicable maintenance manual or Instructions for Continued
Airworthiness as follows:
(i) By establishing a new retirement life for the spindle, P/N
214-030-606-005, of 1,250 hours TIS or a total accumulated RIN of
20,000, whichever occurs first.
(ii) By reducing the retirement life for the spindle, P/N 214-
030-606-103, from 5,000 hours TIS to 2,500 hours TIS or a total
accumulated RIN of 50,000, whichever occurs first.
(3) Replace any spindle, P/N 214-030-606-005, that has been in
service for 1,250 or more hours TIS, or a total accumulated RIN of
20,000 or more, whichever occurs first.
(4) Replace any spindle, P/N 214-030-606-103, that has been in
service for 2,500 or more hours TIS, or a total accumulated RIN of
50,000 or more, whichever occurs first.
(5) Continue to count and record the accumulated RIN count and
hours TIS for each spindle on its component history card or
equivalent record.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Martin Crane,
Aviation Safety Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222-5056; email [email protected].
(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.
(g) Additional Information
Bell Alert Service Bulletin (ASB) No. 214-08-70, Revision C,
dated April 14, 2009; Bell ASB No. 214ST-08-86, Revision B, dated
April 14, 2009; and Bell Information Letter 214ST-12-23, dated
January 30, 2012, which are not incorporated by reference, contain
additional information about the subject of this AD. For service
information identified in this AD, contact Bell Helicopter Textron,
Inc., P.O. Box 482, Fort Worth, Texas 76101; telephone (817) 280-
3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/.
You may review a copy of this service information at the FAA, Office
of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6330, Transmission
Mount.
[[Page 60185]]
Issued in Fort Worth, Texas, on September 13, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-23099 Filed 9-30-13; 8:45 am]
BILLING CODE 4910-13-P