[Federal Register Volume 78, Number 217 (Friday, November 8, 2013)]
[Rules and Regulations]
[Pages 67020-67022]
[FR Doc No: 2013-26562]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0519; Directorate Identifier 2010-SW-068-AD;
Amendment 39-17623; AD 2013-20-17]
RIN 2120-AA64

Airworthiness Directives; Eurocopter Deutschland GmbH (ECD)
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for ECD
Model BO105C (C-2 and CB-2 Variants) and BO105S (CS-2 and CBS-2
Variants) helicopters with a certain third stage turbine wheel
installed. This AD requires installing a placard on the instrument
panel and revising the limitations section of the rotorcraft flight
manual (RFM). This AD is prompted by several incidents of third stage
engine turbine wheel failures, which were caused by excessive
vibrations at certain engine speeds during steady-state operations.
These actions are intended to alert pilots to avoid certain engine
speeds during steady-state operations, prevent failure of the third
stage engine turbine, engine power loss, and subsequent loss of control
of the helicopter.

DATES: This AD is effective December 13, 2013.
    The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of December 13,
2013.

ADDRESSES: For service information identified in this AD, contact
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>;
or at http://www.eurocopter.com/techpub. You may review 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 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 foreign authority's AD,
any incorporated-by-reference service information, the economic
evaluation, any comments

received, and other information. The street address for the Docket
Operations Office (phone:<PHONE_NUMBER>) 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.

FOR FURTHER INFORMATION CONTACT: Chinh Vuong, Aviation Safety Engineer,
Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 76137; telephone<PHONE_NUMBER>; email
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    On June 20, 2013, at 78 FR 37150, 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 ECD Model BO105C (C-2
and CB-2 Variants) and BO105S (CS-2 and CBS-2 Variants) helicopters
with a third stage turbine wheel, part number (P/N) 23065833,
installed. The NPRM proposed to require installing a placard on the
instrument panel next to the triple RPM indicator and revising the
Limitations sections of the Model BO 105C/CS and BO105 CB/CBS RFMs to
limit steady-state operations between speeds of 86.5% and 95.5%. The
proposed requirements were intended to alert pilots to avoid certain
engine speeds during steady-state operations, prevent failure of the
third stage engine turbine, engine power loss, and subsequent loss of
control of the helicopter.
    The NPRM was prompted by AD No. 2010-0128, dated June 25, 2010,
issued by the European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union. EASA
issued AD No. 2010-0128 to correct an unsafe condition for Model BO 105
C, BO 105 D, and BO 105 S helicopters, and certain variants of those
models. EASA advises that several failures of third stage turbine
wheels used in Rolls Royce Corporation (RRC) 250 series engines have
occurred. According to EASA, RRC has determined that detrimental
vibrations can occur within a particular range of turbine speeds, and
may be a contributing factor to these failures. This condition, if not
corrected, could result in loss of engine power, possibly resulting in
an emergency landing and injuries to the helicopter occupants. To
address this, RRC issued Commercial Engine Bulletin (CEB) A-1400, now
at revision 3, for engines with a third stage turbine wheel, P/N
23065833, installed. CEB A-1400 introduces an operational limitation to
avoid engine power turbine (N2) steady-state operation in a speed range
between 86.5% and 95.5% for more than 60 seconds in single or
cumulative events. In response, ECD has revised the RFM and has
provided a placard to inform pilots to avoid steady-state operations
between 86.5% and 95.5% turbine speeds.
    The EASA AD requires amending the RFMs and installing a placard as
described in ECD Alert Service Bulletin No. BO105-60-110, Revision 1,
dated March 3, 2010 (ASB BO105).

Comments

    We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 37150,
June 20, 2013).

FAA's Determination

    These helicopters have been approved by the aviation authority of
Germany and are approved for operation in the United States. Pursuant
to our bilateral agreement with Germany, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed.

Related Service Information

    ECD has issued ASB BO105, which contains procedures for installing
a placard on the instrument panel stating the prohibited steady-state
turbine operating range. Revision 1 of ASB BO105 removed the temporary
RFM pages as these changes were included in the most recent revisions
of the BO105C/CS and BO105CB/CBS RFMs.

Costs of Compliance

    We estimate that this AD affects 80 helicopters of U.S. Registry.
    Based on an average labor rate of $85 per hour, we estimate that
operators will incur the following costs in order to comply with this
AD. Amending the RFM will require about 0.5 work-hour, for a cost per
helicopter of about $43 and a cost to U.S. operators of $3,440.
Installing the decal will require about 0.2 work-hour, and required
parts will cost about $5, for a cost per helicopter of $22 and a cost
to U.S. operators of $1,760. Based on these estimates, the total cost
of this AD is $65 per helicopter and $5,200 for the U.S. operator
fleet.

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 helicopters 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):

2013-20-17 Eurocopter Deutschland GMBH (ECD): Amendment 39-17623;
Docket No. FAA-2013-0519; Directorate Identifier 2010-SW-068-AD.

(a) Applicability

    This AD applies to ECD Model BO105C (C-2 and CB-2 Variants) and
BO105S (CS-2 and CBS-2 Variants) helicopters with a third stage
turbine wheel, part number 23065833, installed, certificated in any
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a third stage turbine
vibration, which could result in turbine failure, engine power loss
and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective December 13, 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

    Within 30 days:
    (1) For BO105C-2 and BO105CS-2 Variant helicopters, revise the
Rotorcraft Flight Manual (RFM), Section 2, Limitations Section, by
inserting page 2-25 of ECD Flight Manual BO 105 C/CS, revision 5,
dated March 12, 2010.
    (2) For BO105CB-2 and BO105CBS-2 Variant helicopters, revise the
RFM, Section 2, Limitations Section, by inserting pages 2-8 and 2-27
of ECD Flight Manual BO 105 CB/CBS, revision 8, dated March 12,
2010.
    (3) Install a placard on the instrument panel next to the triple
RPM indicator that states: MIN. CONTINUOUS 98% N2--MIN.
TRANSIENT 95% N2.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Chinh Vuong, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137; telephone<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (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

    (1) ECD Alert Service Bulletin No. BO105-60-110, Revision 1,
dated March 3, 2010, which is not incorporated by reference,
contains additional information about the subject of this AD. For
service information identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax (972) 641-
3775; or at http://www.eurocopter.com/techpub. You may review a copy
of the service information at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
    (2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2010-0128, dated June 25, 2010. You may
view the EASA AD on the internet in the AD Docket at http://www.regulations.gov.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 7250: Turbine
Section.

(i) 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) Page 2-25 of Section 2, Limitations, of Eurocopter
Deutschland GmbH Flight Manual BO 105 C/CS, Revision 5, dated March
12, 2010.
    (ii) Pages 2-8 and 2-27 of Section 2, Limitations, of Eurocopter
Deutschland GmbH Flight Manual BO 105 CB/CBS, Revision 8, dated
March 12, 2010.
    (3) For Eurocopter service information identified in this AD,
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax
(972) 641-3775; or at http://www.eurocopter.com/techpub.
    (4) 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.
    (5) You may also 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<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on September 20, 2013.
Scott A. Horn,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-26562 Filed 11-7-13; 8:45 am]
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