[Federal Register: March 16, 2009 (Volume 74, Number 49)]
[Rules and Regulations]
[Page 11001-11003]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16mr09-1]
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Rules and Regulations
Federal Register
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0169; Directorate Identifier 2008-SW-42-AD;
Amendment 39-15833; AD 2009-05-09]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Inc. Model 412,
412CF, and 412EP Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Bell Helicopter Textron Inc. (Bell) model helicopters.
This action requires reidentifying a certain part-numbered main rotor
yoke (yoke) based on whether it was ever installed on a Model 412CF
helicopter or on a Model 412 or 412EP helicopter with a slope landing
kit. This AD also requires reducing the retirement life of the
reidentified yokes from 5,000 hours time-in-service (TIS) to 4,500
hours TIS. Also, this AD requires recording the reidentified yoke part
number (P/N) and the reduced retirement life on the component history
card or equivalent record. This amendment is prompted by fatigue
analysis that shows that the retirement life should be reduced on
certain yokes. The actions specified in this AD are intended to prevent
fatigue cracking of a yoke, failure of a yoke, and subsequent loss of
control of the helicopter.
DATES: Effective March 31, 2009.
Comments for inclusion in the Rules Docket must be received on or
before May 15, 2009.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
You may get the service information identified in this AD from 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/.
Examining the Docket: You may examine the docket that contains the
AD, any comments, and other information 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 Docket Operations office (telephone (800) 647-5527) is
located in Room W12-140 on the ground floor of the West Building at the
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5170, fax (817) 222-
5783.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the
specified Bell model helicopters. This action requires reidentifying a
certain part-numbered yoke based on whether it was ever installed on a
Model 412CF helicopter or on a Model 412 or 412EP helicopter with a
slope landing kit. This AD also requires reducing the retirement life
of the reidentified yokes from 5,000 hours TIS to 4,500 hours TIS.
Also, this AD requires recording the reidentified yoke P/N and the
reduced retirement life on the component history card or equivalent
record. This amendment is prompted by fatigue analysis that shows that
the retirement life should be reduced on certain yokes. This condition,
if not corrected, could result in fatigue cracking of a yoke, failure
of a yoke, and subsequent loss of control of the helicopter.
We have reviewed Bell Alert Service Bulletin (ASB) No. 412-08-128,
dated March 4, 2008, for the Model 412 and 412EP helicopters and ASB
No. 412CF-08-35 dated March 4, 2008, for the Model 412CF helicopters.
The ASBs specify reducing the life limit of certain part-numbered yokes
from 5,000 hours TIS to 4,500 hours TIS. The ASBs also describe
procedures for reidentifying the yoke P/N and recording the information
on a component history card or equivalent record.
This unsafe condition is likely to exist or develop on other
helicopters of these same type designs. Therefore, this AD is being
issued to prevent fatigue cracking of a yoke, failure of a yoke, and
subsequent loss of control of the helicopter. This AD applies to Bell
Model 412 and 412EP helicopters with a yoke, P/N 412-010-101-123, -127,
-129, or -133, with a (BHT-412-SI-62) slope landing kit, installed.
This AD also applies to Model 412CF helicopters with yoke, P/N 412-010-
101-127 or -129, installed. This AD requires the following actions
within 10 hours TIS for each affected model helicopter:
Review the helicopter records to determine all of the
helicopter models on which the affected yoke has been installed since
its production and the hours TIS of each yoke.
If an affected part-numbered yoke has ever been installed
on a Model 412CF or on a Model 412 or 412EP helicopter with a (BHT-412-
SI-62) slope landing kit, P/N 412-704-012-101, do the following:
[cir] Reidentify the P/N on the existing yoke data plate by using a
vibrating stylus and etching two lines through the last three digits of
the existing P/N and etching ``137FM'' adjacent to where you etched
through the last three digits of the original P/N. This converts each
affected yoke P/N to a new yoke P/N, 412-010-101-137FM. The serial
number remains the same.
[cir] Record the reidentified P/N on the applicable component
history card or equivalent record.
If you cannot determine all the model helicopters on which
an affected
[[Page 11002]]
yoke has been installed since its production or whether it has ever
been installed on a Model 412 or 412EP helicopter with a (BHT-412-SI-
62) slope landing kit, P/N 412-704-012-101, installed, reidentify the
yoke as P/N 412-010-101-137FM using a vibrating stylus. Record the
reidentified P/N on the applicable component history card or equivalent
record.
For each reidentified yoke, P/N 412-010-101-137FM, record
the revised 4,500-hour TIS life limit on the applicable component
history card or equivalent record.
This AD revises the Airworthiness Limitations section of the
applicable maintenance manual or the Instructions for Continued
Airworthiness (ICAs) by reducing the retirement life from 5,000 hours
TIS to 4,500 hours TIS for reidentified yoke, P/N 412-010-101-137FM.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
structural integrity and controllability of the helicopter. Therefore,
to prevent fatigue cracking, the actions described previously are
required within 10 hours TIS. Also, replacing certain yokes that have
exceeded 4,500 hours TIS but have not reached their previous 5,000
hours TIS retirement life is required before further flight, and this
AD must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
We estimate that this AD will affect 115 helicopters and will take
about:
1 hour to review the records,
2 hours to revise the maintenance manual or ICAs, record
the new retirement life, reidentify the P/N, and
20 hours to replace a yoke.
The average labor rate is estimated to be $80 per work hour. Required
parts will cost about $40,157 per helicopter. Based on these figures,
we estimate the total cost of the AD on U.S. operators will be $278,142
($27,600 to review and revise the records and $250,542 to replace the
yokes, assuming 5 percent of the fleet or a total of 6 yokes have
exceeded the 4,500-hour life limit).
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2009-0169; Directorate
Identifier 2008-SW-42-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the AD. We will consider all
comments received by the closing date and may amend the AD in light of
those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD. Using the search function of our
docket Web site, you can find and read the comments to any of our
dockets, including the name of the individual who sent the comment. You
may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78).
Regulatory Findings
We have 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 above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. 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. See the AD docket to examine the economic evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2009-05-09 Bell Helicopter Textron, Inc.: Amendment 39-15833. Docket
No. FAA-2009-0169; Directorate Identifier 2008-SW-42-AD.
Applicability: The following model helicopters with the listed
part-numbered main rotor yoke assembly (yoke), installed,
certificated in any category.
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Model With yoke part number (P/N) installed
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412 and 412EP................................ 412-010-101-123, -127, -129, or -133
412CF........................................ 412-010-101-127, -129
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Compliance: Within 10 hours time-in-service (TIS), unless
accomplished previously:
To prevent fatigue cracking of a yoke, failure of the yoke, and
subsequent loss of control of the helicopter, do the following:
(a) Review the helicopter records to determine all of the
helicopter models on which the affected yoke has been installed
since its production and the hours TIS of each affected yoke.
(b) If an affected part-numbered yoke is installed or has ever
been installed on a Model 412CF helicopter or on a Model 412 or
412EP helicopter with a (BHT-412-SI-62) slope landing kit, P/N 412-
704-012-101, installed, do the following:
(1) Reidentify the P/N on the existing yoke data plate by using
a vibrating stylus and etching two lines through the last three
digits of the existing P/N and etching ``137FM'' adjacent to where
you etched through the last three digits of the original P/N. This
converts each affected yoke P/N to a new yoke P/N 412-010-101-137FM.
The serial number remains the same.
Note 1: The ``FM'' P/N suffix denotes a field modified part.
(2) Record the reidentified P/N on the applicable component
history card or equivalent record.
(c) If you cannot determine all the model helicopters on which
an affected yoke has been installed since its production or whether
it has ever been installed on a Model 412 or 412EP helicopter with a
(BHT-412-SI-62) slope landing kit, P/N 412-704-012-101, installed,
reidentify the yoke P/N as P/N 412-010-101-137FM using a vibrating
stylus in accordance with paragraph (b)(1) of this AD. Record the
reidentified P/N on the applicable component history card or
equivalent record.
(d) For each reidentified yoke, P/N 412-010-101-137FM, reduce
the retirement life from 5,000 hours TIS to 4,500 hours TIS. Record
the revised life limit on the applicable component history card or
equivalent record.
Note 2: Bell Helicopter Textron, Inc. Alert Service Bulletins
No. 412-08-128 and No. 412CF-08-35, both dated March 4, 2008,
pertain to the subject of this AD.
(e) This AD revises the Airworthiness Limitations section of the
applicable maintenance manual or the Instructions for Continued
Airworthiness (ICAs) by reducing the retirement life from 5,000
hours TIS to 4,500 hours TIS for each reidentified yoke, P/N 412-
010-101-137FM.
(f) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Rotorcraft Directorate, FAA, ATTN: Michael
Kohner, Aviation Safety Engineer, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5170, fax (817)
222-5783, for information about previously approved alternative
methods of compliance.
(g) Special flight permits will not be issued.
(h) This amendment becomes effective on March 31, 2009.
Issued in Fort Worth, Texas, on February 12, 2009.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-4950 Filed 3-13-09; 8:45 am]
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