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[Federal Register Volume 81, Number 117 (Friday, June 17, 2016)]
[Proposed Rules]
[Pages 39601-39603]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14228]

[[Page 39601]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3753; Directorate Identifier 2015-NE-26-AD]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2016-04-
12 that applies to certain Turbomeca S.A. Arriel 2B, 2B1, 2C, 2C1, 2C2, 
2D, 2E, 2S1, and 2S2 turboshaft engines. AD 2016-04-12 requires 
spectrometric oil analysis (SOA) inspection of the engine accessory 
gearbox (AGB), and, depending on the results, removal of the engine 
AGB. Since we issued AD 2016-04-12, we determined that wear inspections 
of the engine AGB cover are also required. This proposed AD would 
require initial and repetitive inspections of the AGB, and wear 
inspections of the engine AGB cover. We are proposing this AD to 
prevent failure of the engine AGB, uncommanded in-flight shutdown 
(IFSD), damage to the engine, and damage to the helicopter.

DATES: We must receive comments on this proposed AD by August 16, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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 Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Turbomeca S.A., 40220 Tarnos, France; phone: 33 0 5 59 74 40 00; fax: 
33 0 5 59 74 45 15. You may view this service information at the FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. 
For information on the availability of this material at the FAA, call 
781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3753; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the mandatory continuing airworthiness 
information, regulatory evaluation, any comments received, and other 
information. The address for the Docket Office (phone: 800-647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-
238-7199; email: philip.haberlen@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2015-3753; 
Directorate Identifier 2015-NE-26-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM because 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 we 
receive about this NPRM.

Discussion

    On February 18, 2016, we issued AD 2016-04-12, Amendment 39-18406 
(81 FR 12583, March 10, 2016), (``AD 2016-04-12'') for certain 
Turbomeca S.A. Arriel 2B, 2B1, 2C, 2C1, 2C2, 2D, 2E, 2S1, and 2S2 
turboshaft engines. AD 2016-04-12 requires an SOA inspection, and, 
depending on the results, removal of the engine AGB. AD 2016-04-12 
resulted from a report of an uncommanded IFSD of an Arriel 2S2 engine 
caused by rupture of the 41-tooth gear, which forms part of the bevel 
gear in the engine AGB. We issued AD 2016-04-12 to prevent failure of 
the engine AGB, uncommanded IFSD, damage to the engine, and damage to 
the helicopter.

Actions Since AD 2016-04-12 Was Issued

    Since we issued AD 2016-04-12, Turbomeca recommended that an engine 
AGB cover wear inspection be performed. Also, the European Aviation 
Safety Agency issued AD 2016-0055, dated March 17, 2016, which requires 
initial and repetitive SOA inspections of the AGB and initial and 
repetitive wear inspections of the engine AGB cover.

Related Service Information Under 1 CFR Part 51

    Turbomeca S.A. has issued Mandatory Service Bulletin No. 292 72 
2861, Version C, dated March 9, 2016. The service information describes 
procedures for performing periodic SOA and wear inspections of the 
engine AGB. This service information is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are proposing this NPRM because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This NPRM would require initial and repetitive SOA, wear 
inspections of the engine AGB cover, and AGB replacement based on the 
results of the inspections.

Costs of Compliance

    We estimate that this proposed AD affects 250 engines installed on 
helicopters of U.S. registry. We also estimate that it would take 0.5 
hours per engine to perform the SOA and 1 hour to perform the engine 
AGB cover wear inspection. The average labor rate is $85 per hour. 
Required parts for inspection and analysis cost about $3,179 per 
engine. We estimate that 5 engines will require AGB replacement at a 
cost of $44,397 per engine. We also estimate that it would take about 2 
hours to replace the engine AGB. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $1,049,460.

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

[[Page 39602]]

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 have 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 above, I certify that the 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.

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

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) 
2016-04-12, Amendment 39-18406 (81 FR 12583, March 10, 2016) (``AD 
2016-04-12''), and adding the following new AD:

Turbomeca S.A.: Docket No. FAA-2015-3753; Directorate Identifier 
2015-NE-26-AD.

(a) Comments Due Date

    We must receive comments by August 16, 2016.

(b) Affected ADs

    This AD supersedes AD 2016-04-12.

(c) Applicability

    This AD applies to Turbomeca S.A. Arriel 2B, 2B1, 2C, 2C1, 2C2, 
2D, 2E, 2S1, and 2S2 turboshaft engines with an engine accessory 
gearbox (AGB), part number 0292120650, with a machined front casing.

(d) Unsafe Condition

    This AD was prompted by a report of an uncommanded in-flight 
shutdown (IFSD) of an Arriel 2S2 engine caused by rupture of the 41-
tooth gear, which forms part of the bevel gear in the engine AGB. We 
are issuing this AD to prevent failure of the engine AGB, 
uncommanded IFSD, damage to the engine, and damage to the 
helicopter.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(1) Initial Spectrometric Oil Analysis (SOA) and Engine AGB Cover 
Wear Inspection

    (i) Perform an SOA and an engine AGB cover wear inspection 
before the engine AGB, module M01, exceeds 850 engine hours (EH) 
since new or since last overhaul (SLO), or within 50 EH after April 
14, 2016, or before the next flight after the effective date of this 
AD, whichever occurs later.
    (ii) Reserved.

(2) Repetitive Inspection Intervals

    (i) Repeat the SOA within every 100 EH since the last SOA.
    (A) For all affected engines, if the last SOA was performed 
before the effective date of this AD, and the aluminum concentration 
level is 0.8 parts per million (p/m) or greater, perform a wear 
inspection of the engine AGB cover within 50 EHs since last SOA or 
before the next flight after the effective date of this AD, 
whichever occurs later.
    (B) For all affected engines, if the last SOA was performed 
after the effective date of this AD, and the aluminum concentration 
level is 0.8 p/m or greater, perform a wear inspection of the engine 
AGB cover within 20 EH since the last SOA.
    (ii) For Arriel 2E engines, repeat the engine AGB cover wear 
inspection within every 800 EH since last inspection (SLI) if the 
SOA indicated the aluminum concentration level is less than 0.8 p/m.
    (iii) For all affected engines, except for Arriel 2E engines, 
repeat the engine AGB cover wear inspection within every 600 EH SLI 
if the SOA indicated the aluminum concentration level is less than 
0.8 p/m.

(3) Inspection Criteria

    (i) Use paragraph 2.4.2.1 and 2.4.2.2 of Turbomeca Mandatory 
Service Bulletin (MSB) No. 292 72 2861, Version C, dated March 9, 
2016, to do the inspections required by paragraphs (e)(1) and (2) of 
this AD.
    (ii) Reserved.

(4) Corrective Actions Based on the Results of the Most Recent Wear 
Inspection

    (i) If the wear measured from the most recent wear inspection is 
0.15 mm or less, no further action is required. However, you must 
still comply with the repetitive inspection requirements of 
paragraph (e)(2) of this AD.
    (ii) If the most recent wear inspection was performed while the 
engine was in service, and the wear is greater than 0.15 mm, do the 
following:
    (A) If the wear measured from the most recent wear inspection is 
greater than 0.15 mm, but 0.30 mm or less, remove the engine AGB 
from service within 200 EH SLI and replace with a part eligible for 
installation.
    (B) If the wear measured from the most recent wear inspection is 
greater than 0.30 mm, but 0.40 mm or less, remove the engine AGB 
from service within 25 EH SLI and replace with a part eligible for 
installation.
    (C) If the wear measured from the most recent wear inspection is 
greater than 0.40 mm, remove the engine AGB from service before 
further flight and replace with a part eligible for installation.
    (iii) If the most recent wear inspection was performed on the 
engine during an engine shop visit, and the wear is greater than 
0.15 mm, remove the engine AGB before further flight and replace 
with a part eligible for installation.

(f) Definition

    For the purpose of this AD, an engine shop visit is defined as 
the induction of an engine into the shop for maintenance involving 
the separation of any major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) Related Information

    (1) For more information about this AD, contact Philip Haberlen, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7770; fax: 781-238-7199; email: 
philip.haberlen@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0055, 
dated March 17, 2016, for more information. You may examine the MCAI 
in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2015-3753.
    (3) Turbomeca S.A. MSB No. 292 72 2861, Version C, dated March 
9, 2016, can be

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obtained from Turbomeca S.A., using the contact information in 
paragraph (h)(4) of this AD.
    (4) For service information identified in this AD, contact 
Turbomeca S.A., 40220 Tarnos, France; phone: 33 0 5 59 74 40 00; 
fax: 33 0 5 59 74 45 15.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on June 8, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-14228 Filed 6-16-16; 8:45 am]
 BILLING CODE 4910-13-P
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