AD 2013-23099

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="http://www.bellcustomer.com/files/">http://www.bellcustomer.com/files/</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 <a href="/cdn-cgi/l/email-protection#0532284453562844565228343235456364642b626a73"><span class="__cf_email__" data-cfemail="70475d3126235d3123275d414740301611115e171f06">[email&#160;protected]</span></a>.

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 <a href="/cdn-cgi/l/email-protection#9cabb1ddcacfb1ddcfcbb1adabacdcfafdfdb2fbf3ea"><span class="__cf_email__" data-cfemail="80b7adc1d6d3adc1d3d7adb1b7b0c0e6e1e1aee7eff6">[email&#160;protected]</span></a>.
    (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 <a href="http://www.bellcustomer.com/files/">http://www.bellcustomer.com/files/</a>. 
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