[Federal Register Volume 78, Number 146 (Tuesday, July 30, 2013)]
[Rules and Regulations]
[Pages 45845-45848]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-18079]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0639; Directorate Identifier 2013-SW-020-AD;
Amendment 39-17518; AD 2013-15-02]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule, request for comments.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2008-10-03 for
Bell Helicopter Textron Helicopters (Bell) Model 204B, 205A, 205A-1,
205B, 210, 212, 412, 412CF, and 412EP helicopters. AD 2008-10-03
required certain checks and inspections of each tail rotor blade
assembly (T/R blade) at specified intervals and repairing or replacing,
as applicable, any cracked or damaged T/R blade. Since we issued AD
2008-10-03, an accident attributed to a T/R failure occurred. This new
AD retains the requirements of AD 2008-10-03 and adds a second, more
detailed inspection that allows for an earlier detection of a crack or
other damage in a T/R blade. These actions are intended to prevent a
failure of the T/R blade and subsequent loss of helicopter control.
DATES: This AD becomes effective August 14, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of August 14, 2013.
We must receive comments on this AD by September 30, 2013.
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 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 www.bellcustomer.com/. You
may review 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: Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170;
email [email protected].
SUPPLEMENTARY INFORMATION:
[[Page 45846]]
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, 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 resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, 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 them 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 rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.
Discussion
On April 22, 2008, we issued AD 2008-10-03, Amendment 39-15509 (73
FR 24858, May 6, 2008) for Bell Model 204B, 205A, 205A-1, 205B, 210,
212, 412, 412CF, and 412EP helicopters. AD 2008-10-03 required certain
checks and inspections of each T/R blade at specified intervals and
repairing or replacing, as applicable, any unairworthy T/R blade. AD
2008-10-03 was prompted by eight reports of fatigue cracking of T/R
blades installed on Bell Model 212 and 412 helicopters (three failures
on the Bell Model 212 and five failures on the Bell Model 412) with a
T/R blade, part number (P/N) 212-010-750-009, -105, and -107. Three of
the Model 412 failures occurred during flight.
Actions Since AD 2008-10-03 Was Issued
Since we issued AD 2008-10-03 (73 FR 24858, May 6, 2008), an
accident attributed to a T/R failure occurred. Because of this
accident, we have determined that a superseding AD is necessary to
require a second, more detailed inspection that allows for an earlier
detection of a crack or other damage. These actions are intended to
prevent failure of T/R blade and subsequent loss of helicopter control.
This superseding AD does not apply to Model 204B helicopters
because those helicopters do not have the affected T/R blades installed
and should not have been included in the applicability of AD 2008-10-
03. We are no longer requiring a daily check of the T/R blades because
we have determined that the additional, more detailed inspection and
the sequence of the inspections provide an appropriate level of safety.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Related Service Information
On February 4, 2013, Bell issued Alert Service Bulletin (ASB) No.
205-13-109 for Model 205A and 205A-1 helicopters; ASB No. 205B-13-61
for Model 205B helicopters; ASB No. 212-13-147 for Model 212
helicopters; ASB 412-13-155 for Model 412 and 412EP helicopters; and
ASB No. 412CF-13-52 for 412CF helicopters. All ASBs are dated February
4, 2013. Bell reported that it recently examined a fractured T/R blade
and that the fracture originated from surface damage. ASB No. 205-13-
109, No. 205B-13-61, and No. 412CF-13-52 describe procedures for a 3X
magnifying glass inspection of the entire T/R blade surface for damage
every 25 hours time-in-service (TIS), similar to that required by AD
2008-10-03 (73 FR 24858, May 6, 2008). ASB No. 212-13-147 and No. 412-
13-155 do not include this 3X visual inspection, because that
inspection has been incorporated into the maintenance manual for these
models. All five of the ASBs introduce an additional local visual
inspection with a10X magnifying glass of each T/R blade between blade
station 20.00 to 35.00 from the leading edge to the trailing edge. Bell
added a reminder to operators that it is critical to investigate any
paint and skin imperfections should the inspection warrant such action.
If any skin damage exceeds the limits in the applicable Maintenance
Manual, the ASBs call for removing the T/R blade from service.
AD Requirements
This AD supersedes AD 2008-10-03 (73 FR 24858, May 6, 2008) and
requires for any Model 205A, 205A-1, 205B, 210, 212, 412, 412CF, and
412EP helicopter with certain T/R blades the following actions:
Within 25 hours TIS or 30 days, whichever occurs first, and
thereafter at intervals not to exceed 25 hours TIS or 30 days,
whichever occurs first, cleaning and visually inspecting each T/R blade
assembly for a crack, corrosion, nick, scratch, or dent using a 3X or
higher power magnifying glass and a bright light; and
Visually inspecting certain parts of each T/R blade for a crack or
other damage using a 10X or higher power magnifying glass and a bright
light, and if damage exists, measuring the depth of any damage.
Before further flight, replacing any cracked T/R blade and
repairing or replacing any damaged T/R blade.
Replacing a blade with T/R blade, P/N 412-016-100-111, on eligible
helicopters is terminating action for the inspection requirements of
this AD.
Differences Between the AD and the Service Information
This AD differs from the ASBs because we include Model 210
helicopters. The Model 210 helicopter has the same part-numbered blades
as the other applicable helicopter models.
Costs of Compliance
We estimate that this AD affects 80 helicopters of U.S. Registry
and that labor costs average $85 per work-hour. Based on these
estimates, we expect the following costs to comply with this AD:
Visually inspecting a blade (2 per helicopter) for a crack or other
damage will require .25 work-hour. No parts are needed. For the
expected 12 annual inspections, the total cost per helicopter will be
$510 a year, and $40,800 for the U.S. fleet.
Replacing a T/R assembly will require 6 work-hours for a labor cost
of $510. Parts will cost $23,048, bringing the total cost to $23,558
per helicopter.
According to the Bell's service information, some of the cost may
be covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control the warranty coverage by Bell.
Accordingly, we have included all costs in our cost estimate.
FAA's Justification and Determination of the Effective Date
Providing an opportunity for public comments prior to adopting
these AD requirements would delay implementing the safety actions
needed to correct this known unsafe condition. Therefore, we find that
the risk to the flying public justifies waiving notice and comment
prior to the adoption of this rule because the required corrective
actions must be accomplished within 25 hours TIS or 30 days, whichever
comes first, a very short time period based on the average flight-hour
utilization rate of these helicopters. These helicopters are
[[Page 45847]]
typically used for logging, firefighting, and lifting and carrying
external loads.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
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 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, I certify that this AD:
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 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 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 removing airworthiness directive (AD)
2008-10-03, Amendment 39-15509 (73 FR 24858, May 6, 2008), and adding
the following new AD:
2013-15-02 BELL HELICOPTER TEXTRON: Amendment 39-17518; Docket No.
FAA-2013-0639; Directorate Identifier 2013-SW-020-AD.
(a) Applicability
This AD applies to Bell Helicopter Textron (Bell) Model 205A,
205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters with a
tail rotor blade assembly (T/R blade), part number (P/N) 210-010-
001-(all dash numbers) or 212-010-750-(all dash numbers),
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue cracking of a T/
R blade, which could lead to failure of the T/R blade and subsequent
loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD No. 2008-10-03, Amendment 39-15509 (73 FR
24858, May 6, 2008).
(d) Effective Date
This AD becomes effective August 14, 2013.
(e) 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.
(f) Required Actions
(1) Within 25 hours time-in-service (TIS) or 30 days, whichever
occurs first, and thereafter at intervals not to exceed 25 hours TIS
or 30 days, whichever occurs first:
(i) Clean each T/R blade by hand using a mild soap and
cheesecloth (C-486) on both sides of the blade in a spanwise
direction and dry thoroughly.
(ii) Using a 3X or higher power magnifying glass and a bright
light, visually inspect the T/R blade skins, leading edge spar,
doublers, grip plates, and trailing edge on both sides of each blade
for a crack, corrosion (may be indicated by blistering, peeling,
flaking, bubbling, or cracked paint), a nick, scratch, dent, or
other damage. Pay particular attention to both sides of the T/R
blade in the area located 16 to 35 inches from the T/R blade tip
(blade station 20.00 to 35.00--the T/R blade tip is located at blade
station 51) as shown by the shaded area of Figure 1 of Bell Alert
Service Bulletin (ASB) No. 205-13-109; ASB No. 205B-13-61; ASB No.
212-13-147; ASB 412-13-155; or ASB No. 412CF-13-52, all dated
February 4, 2013, as applicable to your helicopter. Also, pay
particular attention to the inboard blade butt area near the
attachment of the external balance weight and screws, and to any
blade surface that was snagged by cheesecloth, as that may be an
indication of a crack or paint chip that could lead to corrosion.
Note 1 to Paragraph (f) of this AD: Figure 1 of the Bell ASB No.
205-13-109; ASB No. 205B-13-61; ASB No. 212-13-147; ASB 412-13-155;
and ASB No. 412CF-13-52, all dated February 4, 2013, show the shaded
area as part of the 10X inspection only. This AD requires the shaded
area to be inspected during both the 3X and 10X inspections.
(iii) Using a 10X or higher magnifying glass and a bright light,
visually inspect both sides of each blade for a crack or other
damage between blade station 20.00 to 35.00 as shown by the shaded
area of Figure 1 of Bell ASB No. 205-13-109; ASB No. 205B-13-61; ASB
No. 212-13-147; ASB 412-13-155; or ASB No. 412CF-13-52, all dated
February 4, 2013, as applicable to your helicopter.
(iv) If any blistering, peeling, flaking, bubbling, or cracked
paint is detected anywhere on the blade, remove the paint from the
affected area by sanding in a spanwise direction with abrasive cloth
or paper (C-406) 240-grit or finer, and a final sanding using
abrasive cloth or paper (C-406) 400-grit or finer. Visually inspect
the affected area for any corrosion or a crack using a 10X or higher
magnifying glass and a bright light. If any corrosion is found,
measure the depth of the damage. (A digital optical micrometer is
one tool that can be used for this measurement.)
(v) If a nick, scratch, or dent is found anywhere on the blade,
visually inspect for a crack using a 10X or higher power magnifying
glass and a bright light. Measure the depth of the damage. (A
digital optical micrometer is one tool that can be used for this
measurement.)
(2) Before further flight:
(i) Replace with an airworthy blade any T/R blade that has a
crack or that has any corrosion, nick, scratch, dent, or other
damage that exceeds any of the maximum repair limits.
(ii) Repair or replace with an airworthy blade any T/R blade
that has any corrosion, nick, scratch, dent or other damage that is
within the maximum repair limits.
(3) Replacing a T/R blade with T/R blade, P/N 412-016-100-111,
on eligible helicopter models is considered terminating action to
this AD.
(g) Special Flight Permit
Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate,
[[Page 45848]]
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817)
222-5170; 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.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor
Blades.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Bell ASB No. 205-13-109, dated February 4, 2013.
(ii) Bell ASB No. 205B-13-61, dated February 4, 2013.
(iii) Bell ASB No. 212-13-147, dated February 4, 2013.
(iv) Bell ASB No. 412-13-155, dated February 4, 2013.
(v) Bell ASB No. 412CF-13-52, dated February 4, 2013.
(3) For Bell 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
www.bellcustomer.com/.
(4) You may view this service information that is incorporated
by reference in the AD Docket on the Internet at http://www.regulations.gov.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on July 11, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18079 Filed 7-29-13; 8:45 am]
BILLING CODE 4910-13-P