[Federal Register: March 13, 2008 (Volume 73, Number 50)]
[Proposed Rules]
[Page 13513-13515]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13mr08-27]
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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]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
214B and B-1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for Bell Helicopter Textron, Inc. (BHTI) Model 214B and B-1
helicopters. The AD would require creating a component history card or
equivalent for each pylon support spindle assembly (spindle), and
inspecting certain spindles for any corrosion, or a nick, scratch,
dent, or crack, and replacing any unairworthy spindle before further
flight. This proposal is prompted by three in-flight failures of
spindles that resulted in forced landings. The actions specified by the
proposed AD are intended to detect damage in the radii or cracking of a
spindle, and to prevent failure of a spindle and subsequent loss of
control of the helicopter.
DATES: Comments must be received on or before May 12, 2008.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
[[Page 13514]]
Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically;
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: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
Fax: 202-493-2251.
You may get the service information identified in this proposed AD
from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas
76101, telephone (817) 280-3391, fax (817) 280-6466.
You may examine the comments to this proposed AD in the AD docket
on the Internet at http://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2008-0288,
Directorate Identifier 2006-SW-25-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed 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 proposed rulemaking. Using the
search function of the docket Web site, you can find and read the
comments to any of our dockets, including the name of the individual
who sent or signed 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).
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information 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.
Discussion
This document proposes adopting a new AD for BHTI Model 214B and B-
1 helicopters. The AD would require, within 50 hours time-in-service
(TIS), creating a component history card or equivalent record for each
spindle, and begin recording the spindle's TIS and number of take-offs
and external load lifts accomplished with the spindle installed. It
would also require a one-time visual inspection of the outer radius of
the spindle for any corrosion or a nick, scratch, or dent, using a 3x-
power or higher magnifying glass, and a one-time magnetic particle
inspection of the spindles for a crack. The inspections would be
required within 100 hours TIS, or 325 hours TIS since the last overhaul
of the transmission assembly, whichever occurs later, for spindles with
5,000 or more hours TIS, or spindles for which the total number of
hours TIS is unknown and were installed before the last overhaul of the
transmission assembly. For spindles having 5,000 or more hours TIS, or
spindles for which the total number of hours TIS is unknown, that were
installed after the last overhaul of the transmission assembly, or the
installation history is unknown, the inspections would be required
within 100 hours TIS. The proposed AD would also require, before
further flight, replacing any spindle on which any corrosion or a crack
is discovered, and replacing any spindle that has a nick, scratch, or
dent, or repairing the spindle if the damage is within the repair
limits that are stated in the applicable component repair and overhaul
manual. This proposal is prompted by three in-flight failures of the
spindle, part number 214-030-606-005, which resulted in forced landings
and one serious injury. All three helicopters were involved in logging
operations, which put more torque cycles on the main rotor and
transmission systems. The failures occurred at 694, 810, and 1,928
hours TIS since the last overhaul of the transmission assembly on
helicopters having a total TIS of 3,500 to 17,000 hours. Currently, the
spindles do not have a retirement life on either the Model 214B or
214B-1 helicopters, and the number of hours TIS for the spindles is not
required to be tracked on a component history card or equivalent
record. The current inspections specified in the maintenance manuals
are a magnetic particle inspection at each 2,500 hours TIS transmission
overhaul, and a visual inspection for mechanical or corrosion damage,
using a 3x-power magnifying glass, at each main rotor tension-torsion
strap change. A magnetic particle inspection is also required following
the occurrence of a sudden stoppage of the main rotor system. The
actions specified by the proposed AD are intended to detect damage in
the radii or cracking of a spindle, and to prevent failure of a spindle
and subsequent loss of control of the helicopter. The actions of this
proposed AD are intended as interim actions until a retirement life for
these spindles can be developed and new replacement spindles become
available.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, the proposed AD would
require creating a component history card or equivalent for each
spindle, inspecting certain spindles for any corrosion, or a nick,
scratch, dent, or crack, and replacing any unairworthy spindle before
further flight.
We estimate that this proposed AD would affect 10 helicopters of
U.S. registry, and the proposed actions would take approximately:
15 work hours to remove and replace a set of spindles for
inspecting;
2 work hours to conduct a magnetic particle inspection;
and
15 work hours to replace a set of spindles at an average
labor rate of $80 per work hour. Required parts would cost
approximately $10,735 for a set of spindles. Based on these figures,
the total cost impact of the proposed AD on U.S. operators would be
$25,535, assuming the inspections are performed once for each
helicopter and one set of spindles is replaced.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, 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 above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
[[Page 13515]]
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 a draft economic evaluation of the estimated costs to
comply with this proposed AD. Go to the government-wide rulemaking Web
site at: http://www.regulations.gov to examine the draft 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Bell Helicopter Textron, Inc.: Docket No. FAA-2008-0288; Directorate
Identifier 2006-SW-25-AD.
Applicability
Model 214B and B-1 helicopters, with pylon support spindle
assembly (spindle), part number 214-030-606-005, installed,
certificated in any category.
Compliance
Required as indicated, unless accomplished previously.
To detect damage in the radii or cracking of a spindle, and to
prevent failure of a spindle and subsequent loss of control of the
helicopter, accomplish the following:
(a) Within 50 hours time-in-service (TIS):
(1) Create a component history card or equivalent record for
each spindle, stating the spindle's serial number. Begin recording
the number of hours TIS, and the number of take-offs and external
load lifts. An external load lift occurs when a load is picked up at
one location and is released at another location.
(2) Review the helicopter records to determine if there has been
a sudden stoppage of the main rotor system, or any hard landing, on
a helicopter with any affected spindle installed and record any such
events on the component history card or equivalent record.
(b) Record all conditional inspections of each spindle on the
component history card or equivalent record. A sudden stoppage of
the main rotor system is defined as any rapid deceleration of the
drive system, whether caused by seizure within the helicopter
transmission or by contact of a main rotor blade with the ground,
water, snow, dense vegetation, or other object of sufficient inertia
to cause rapid deceleration.
(c) For each spindle with 5,000 or more hours TIS, or any
spindle for which the number of hours TIS is unknown, perform the
inspections in paragraphs (c)(1) and (c)(2) of this AD within the
hours TIS specified in Table 1 of this AD:
Table 1
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For spindles, part number 214-030-606-
005, that were installed on the Inspect within:
transmission assembly:
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Before the last overhaul of the 100 hours TIS or 325 hours TIS
transmission assembly. since the last overhaul of the
transmission assembly,
whichever occurs later.
After the last overhaul of the 100 hours TIS.
transmission assembly or for which the
installation history is unknown.
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(1) Visually inspect each outer radius of the spindle for any
corrosion, or a nick, scratch, or dent, using a 3x-power or higher
magnifying glass; and
(2) Conduct a magnetic particle inspection of the spindle for a
crack.
(d) Before further flight, if a crack or any corrosion is found,
replace the spindle with an airworthy spindle.
(e) Before further flight, replace any spindle that has a nick,
scratch, or dent with an airworthy spindle, or repair it if it is
within the repair limits.
Note 2: The repair limits are specified in the applicable
component repair and overhaul manual.
(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 Certification Office, FAA, ATTN:
Michael Kohner, Aviation Safety Engineer, Fort Worth, Texas 76193-
0170, telephone (817) 222-5447, fax (817) 222-5783, for information
about previously approved alternative methods of compliance.
Issued in Fort Worth, Texas, on March 3, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-5060 Filed 3-12-08; 8:45 am]
BILLING CODE 4910-13-P