9990 Federal Register / Vol. 79, No. 36 / Monday, February 24, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0381; Directorate 

Identifier 2013–NE–16–AD; Amendment 39– 

17764; AD 2014–04–06] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, 

and 2K1 turboshaft engines. This AD 

requires initial and repetitive 

inspections of the hydro-mechanical 

metering unit (HMU) high pressure 

pump drive gear shaft splines, cleaning 

and inspections of the sleeve assembly 

splines, and replacement of the HMU if 

it fails inspection. This AD was 

prompted by in-flight shutdowns caused 

by interrupted fuel supply at the HMU. 

We are issuing this AD to prevent inflight shutdown and damage to the 

engine. 

DATES: This AD becomes effective 

March 31, 2014. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

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–2013– 

0381; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (phone: 800– 

647–5527) is provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Anthony W. Cerra, Jr., Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7128; fax: 781–238–7199; email: 

anthony.cerra@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

Part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on July 25, 2013 (78 FR 44897). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A number of in-flight shutdown 

occurrences have been reported for Arrius 2 

engines. The results of the technical 

investigations concluded that these events 

were caused by deterioration of the splines 

on the high pressure (HP)/low pressure (LP) 

pump assembly drive shaft of the hydromechanical metering unit (HMU), which 

eventually interrupted the fuel supply to the 

engine. This condition, if not detected and 

corrected, could lead to further cases of 

engine in-flight shutdown, possibly resulting 

in forced landing. 

To address these occurrences, Turbomeca 

published Service Bulletin (SB) No. SB 319 

73 2825, which provides inspection 

instructions. After that SB was issued, further 

similar occurrences prompted Turbomeca to 

perform a new assessment of the issue. As a 

result, it was determined that repetitive 

inspections of the HMU, including an 

additional inspection of the sleeve assembly, 

was necessary to address the issue. Those 

instructions are provided in Turbomeca 

Mandatory SB (MSB) No. SB 319 73 2825 

version G. 

For the reasons described above, this AD 

requires repetitive inspections of drive gear 

shaft splines of the HP pump, and depending 

on findings, accomplishment of applicable 

corrective actions. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

# !documentDetail;D=FAA-2013-0381- 

0004. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 44897, July 25, 2013). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

about 162 engines installed on airplanes 

of U.S. registry. We also estimate that it 

will take about one hour per product to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts will 

cost about $753 per engine. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$135,756. 

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 above, I 

certify 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 a regulatory 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: 


rmajette on DSK2TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 36 / Monday, February 24, 2014 / Rules and Regulations 9991 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–04–06 Turbomeca S.A.: Amendment 

39–17764; Docket No. FAA–2013–0381; 

Directorate Identifier 2013–NE–16–AD. 

(a) Effective Date 

This AD becomes effective March 31, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft 

engines. 

(d) Reason 

This AD was prompted by in-flight 

shutdowns caused by interrupted fuel supply 

at the hydro-mechanical metering unit 

(HMU). We are issuing this AD to prevent inflight shutdown and damage to the engine. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Initial Visual Inspection for HMUs Not 

Previously Inspected 

(1) On the effective date of this AD, for 

those HMUs that have not previously been 

inspected using Turbomeca Mandatory 

Service Bulletin (MSB) No. SB 319 73 2825, 

Version G, dated January 24, 2013, or earlier 

versions; perform an initial visual inspection 

of the HMU high-pressure pump drive gear 

shaft splines for wear, corrosion, scaling, or 

cracks, and clean and inspect the sleeve 

assembly splines for wear, corrosion, scaling, 

or cracks, at the following: 

(i) For HMUs that have accumulated more 

than 150 operating hours (OHs) since new or 

since last overhaul, within 50 HMU OHs after 

effective date of this AD. 

(ii) For HMUs that have accumulated 150 

or fewer OHs since new or since last 

overhaul, before exceeding 200 HMU OHs. 

(g) Initial Visual Inspection for HMUs That 

Have Been Previously Inspected 

(1) On the effective date of this AD, for 

those HMUs that have been previously 

inspected per Turbomeca MSB No. SB 319 73 

2825, Version G, dated January 24, 2013, or 

earlier versions; perform a visual inspection 

of HMU aft splines of the high pressure 

pump for wear, corrosion, scaling, or cracks, 

and clean and inspect the sleeve assembly 

splines for wear, corrosion, scaling, or cracks, 

at the following: 

(i) For HMUs that have accumulated 300 

OHs or more since last inspection, within 

200 HMU OHs after effective date of this AD. 

(ii) For HMUs that have accumulated fewer 

than 300 OHs since last inspection, before 

exceeding 500 HMU OHs. 

(h) Repetitive Visual Inspections of HMUs 

(1) Thereafter, repetitively visually inspect 

the HMU aft splines of the high pressure 

pump, and clean and inspect the sleeve 

assembly splines for wear, corrosion, scaling, 

or cracks, at intervals not to exceed 500 HMU 

OHs. 

(2) If, during any initial or repetitive 

inspection required by this AD, an HMU does 

not pass inspection, then before further 

flight, replace the sleeve assembly on the 

affected high pressure pump drive gear shaft 

or replace the affected HMU. 

(i) Installation Prohibition 

After the effective date of this AD, do not 

install any engine on any helicopter unless 

the HMU was inspected as required by this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(k) Related Information 

(1) For more information about this AD, 

contact Anthony W. Cerra, Jr., Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; email: anthony.cerra@faa.gov; phone: 

781–238–7128; fax: 781–238–7199. 

(2) Refer to MCAI European Aviation 

Safety Agency, AD 2013–0082, dated April 2, 

2013, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0381-0004. 

(3) Turbomeca MSB No. SB 319 73 2825, 

Version G, dated January 24, 2013, which is 

not incorporated by reference in this AD, can 

be obtained from Turbomeca, S.A. using the 

contact information in paragraph (k)(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; 

telex: 570 042; fax: 33 (0)5 59 74 45 15. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(l) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

February 10, 2014. 

Robert J. Ganley, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–03672 Filed 2–21–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0547; Directorate 

Identifier 2013–NM–028–AD; Amendment 

39–17758; AD 2014–03–21] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 727–200 

and 727–200F series airplanes. This AD 

is intended to complete certain 

mandated programs intended to support 

the airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This AD requires 

a one-time inspection for cracking of the 

pressure floor of both main wheel wells, 

and related investigative and corrective 

actions if necessary; and modifying the 

pressure floor of both main wheel wells. 

We are issuing this AD to prevent 

fatigue cracking in the pressure floor of 

the main wheel wells, which could lead 

to rapid loss of cabin pressurization. 

DATES: This AD is effective March 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 13, 1991 (56 FR 57233, 

November 8, 1991). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

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–2013– 

0547; 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 AD, the regulatory 


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