[Federal Register Volume 77, Number 99 (Tuesday, May 22, 2012)]
[Proposed Rules]
[Pages 30232-30233]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-12350]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0530; Directorate Identifier 2011-SW-075-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Bell Helicopter Textron (BHT) Model 412, 412EP, and 412CF helicopters.
This proposed AD is prompted by a reported failure of a collective
lever. These proposed actions are intended to detect a crack in the
collective lever, which could lead to failure of the collective lever
and subsequent loss of control of the helicopter.
DATES: We must receive comments on this proposed AD by July 23, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://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 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 proposed AD, the
economic evaluation, any comments received, and other information. The
street address for the Docket Operations Office (telephone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101, telephone
(817) 280-3391, fax (817) 280-6466, or at 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.
FOR FURTHER INFORMATION CONTACT: Martin Crane, Aerospace Engineer, FAA,
Rotorcraft Certification Office, Rotorcraft Directorate, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170, email
martin.r.crane@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
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 might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
BHT has received a report of a fractured collective lever part
number (P/N) 412-010-408-101. Their investigation revealed that
residual stresses induced during manufacturing may have contributed to
the fatigue fracture of the collective lever. This condition, if not
corrected, could lead to failure of the collective lever, and
subsequent loss of control of the helicopter.
FAA's Determination
We are proposing this AD because we evaluated all known relevant
information and determined that an unsafe condition is likely to exist
or develop on other products of the same type design.
Related Service Information
We reviewed BHT ASB 412-11-148 and ASB 412CF-11-47, which describe
procedures for repetitively inspecting the collective control with a
magnifying glass and a strong light source and, if necessary, a
fluorescent penetrant inspection. If there is a crack, the ASBs require
replacing the collective lever.
Proposed AD Requirements
This proposed AD requires, within 25 hours time-in-service (TIS),
cleaning the collective lever and inspecting it for cracks with a 10X
or higher power magnifying glass. If there is a crack in the collective
lever paint finish, this proposed AD requires removing the collective
lever from the swashplate and performing a fluorescent penetrant
inspection. If there is a crack in the collective lever, this proposed
AD requires replacing the collective lever with an airworthy collective
lever before further flight. Additionally, this AD requires repeating
this inspection every 100 hours time-in-service (TIS).
[[Page 30233]]
Differences Between This Proposed AD and the Service Information
The BHT ASBs require compliance within 100 hours of flight time for
the initial inspection; the proposed AD requires compliance within 25
hours TIS. If a crack is found, the BHT ASBs require reporting the
defect to Bell Product Support Engineering; the proposed AD does not.
The BHT ASBs allow a portion of the collective lever to be inspected by
a mirror and light only without a magnifying glass; the proposed AD
does not.
Costs of Compliance
We estimate that this proposed AD will affect 83 helicopters of
U.S. Registry. We estimate that operators may incur the following costs
in order to comply with this proposed AD. Inspecting the collective
lever requires one work-hour at an average labor rate of $85 per hour,
for a cost per helicopter of $85 and a total cost to the U.S. operator
fleet of $7,055 per inspection cycle. Replacing a cracked collective
lever requires 10 work-hours at an average labor rate of $85 per hour
and required parts will cost $12,883, for a total cost of $13,733 per
helicopter.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed 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);
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Bell Helicopter Textron: Docket No. FAA-2012-0530; Directorate
Identifier 2011-SW-075-AD.
(a) Applicability
This AD applies to Model 412 and 412EP helicopters, serial
numbers (S/N) 33001 through 33213, 34001 through 34036, and 36001
and higher; and Model 412CF helicopters, S/N 46400 and higher; with
a collective lever part number (P/N) 412-010-408-101 installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a cracked collective
lever, which could result in failure of the collective lever and
subsequent loss of control of the helicopter.
(c) 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.
(d) Required Actions
Within 25 hours time-in-service (TIS) or 30 days, whichever
occurs first, and thereafter at intervals not to exceed 100 hours
TIS:
(1) Using cleaning compound (C-318) or equivalent, thoroughly
clean the collective lever.
(2) Using a 10X or higher power magnifying glass, inspect the
collective lever in the areas shown in Figure 1 of Bell Helicopter
Textron Alert Service Bulletin (ASB) 412-11-148, Revision A, dated
December 12, 2011 or Bell Helicopter Textron ASB 412CF-11-47,
Revision A, dated December 12, 2011, as appropriate for your model
helicopter.
(3) If there is a crack in the paint, remove the collective
lever from the swashplate assembly.
(i) Remove paint and primer from the area around the crack.
(ii) Fluorescent penetrant inspect the area of the crack.
(4) If there is a crack in the collective lever, before further
flight, replace the collective lever with an airworthy collective
lever.
(e) Alternative Methods of Compliance (AMOC)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Martin Crane,
Aerospace Engineer, FAA, Rotorcraft Certification Office, Rotorcraft
Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone
(817) 222-5170, email martin.r.crane@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.
(f) Additional Information
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 http://www.bellcustomer.com/files/. You may review a copy of information at
the FAA, Office of the Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(g) Subject
Joint Aircraft Service Component (JASC) Code: 6230: Main Rotor
Mast/Swashplate.
Issued in Fort Worth, Texas, on May 10, 2012.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-12350 Filed 5-21-12; 8:45 am]
BILLING CODE 4910-13-P