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[Federal Register Volume 78, Number 217 (Friday, November 8, 2013)]
[Rules and Regulations]
[Pages 67020-67022]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[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 (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
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

[[Page 67021]]

received, and other information. The street address for the Docket 
Operations Office (phone: 800-647-5527) 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 (817) 222-5110; email 
chinh.vuong@faa.gov.

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:

[[Page 67022]]

    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 (817) 222-5110; 
email chinh.vuong@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.

(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 (972) 641-0000 or (800) 232-0323; 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 (972) 641-0000 or (800) 232-0323; 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 (202) 741-6030, 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]
BILLING CODE 4910-13-P
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