This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

36137 

Vol. 81, No. 108 

Monday, June 6, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0903; Directorate 

Identifier 2013–SW–043–AD; Amendment 

39–18548; AD 2016–11–21] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model EC135P1, EC135P2, 

EC135P2+, EC135T1, EC135T2, and 

EC135T2+ helicopters. This AD requires 

reducing the life limit of certain parts 

and removing each part that has reached 

its life limit. The actions of this AD are 

intended to reduce the life limits of 

certain critical parts to prevent failure of 

a part and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective July 11, 

2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

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–2014– 

0903; 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 European Aviation 

Safety Agency (EASA) AD, the 

economic evaluation, any comments 

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: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 13, 2014, at 79 FR 

67382, 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 Airbus Helicopters 

Model EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, and EC135T2+ 

helicopters. The NPRM proposed to 

require, before further flight, revising 

the Airworthiness Limitations Section 

(ALS) of the applicable maintenance 

manual and the component history card 

or equivalent record by reducing the life 

limit for various parts and removing 

from service any part that has reached 

its life limit. The proposed requirements 

were intended to reduce the life limits 

of certain critical parts to prevent failure 

of a part and subsequent loss of control 

of the helicopter. 

The NPRM was prompted by AD No. 

2013–0178, dated August 7, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Eurocopter Deutschland 

GmbH (ECD) (now Airbus Helicopters) 

Model EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, EC135T2+, 

EC635T1, EC635P2+, and EC635T2+ 

helicopters. EASA advises that ECD has 

revised the airworthiness limitations for 

the EC135 and EC635 type design as 

published in the Master Servicing 

Manual (MSM) EC135 Chapter 04—ALS 

documents. Revision 14 of the MSM 

contains these new airworthiness 

limitations. EASA states that failure to 

comply with these limitations could 

result in an unsafe condition. For these 

reasons, EASA AD No. 2013–0178 

requires revising the ALS to include the 

new life limits and replacing each part 

that has reached its life limit. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has relocated 

and a group email address has been 

established for requesting an FAA 

Alternative Method of Compliance for a 

helicopter of foreign design. We have 

updated this information throughout 

this Final Rule. 

Comments 

After our NPRM (79 FR 67382, 

November 13, 2014) was published, we 

received comments from three 

commenters. 

Request 

Three commenters requested that the 

FAA not issue this AD. The commenters 

stated an AD to revise the airworthiness 

limitations of an aircraft manual is 

unnecessary because operators are 

required to use the most current 

revision of the manual. 

We disagree. The FAA must issue an 

AD to mandate an airworthiness 

limitations revision, such as a new life 

limit, for all operators. 

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, considered the 

comments received, 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. 

Differences Between This AD and the 

EASA AD 

This AD does not apply to Airbus 

Helicopters Model EC635T1, P2+, or 

EC635T2+ helicopters because those 

helicopters are not type certificated in 

the U.S. 

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36138 Federal Register / Vol. 81, No. 108 / Monday, June 6, 2016 / Rules and Regulations 

Related Service Information 

The airworthiness limitations and 

maintenance procedures for certain 

parts are contained in the Airworthiness 

Limitations section, Chapter 4, of 

Eurocopter’s MSM EC135, dated 

December 1, 2001. Revision 14 of the 

MSM, dated July 1, 2012, establishes a 

life limit for certain part-numbered 

main rotor blades and reduces the life 

limits for swashplate and mixing lever 

gear unit parts. 

Costs of Compliance 

We estimate that this AD affects 267 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

Labor costs are estimated at $85 per 

work-hour. We estimate 2 work-hours to 

update the maintenance manual for a 

total cost of $170 for each helicopter 

and $45,390 for the U.S. 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 

■ 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): 

2016–11–21 Airbus Helicopters 

Deutschland GmbH (Previously 

Eurocopter Deutschland GmbH): 

Amendment 39–18548; Docket No. 

FAA–2014–0903; Directorate Identifier 

2013–SW–043–AD. 

(a) Applicability 

This AD applies to Model EC135P1, 

EC135P2, EC135P2+, EC135T1, EC135T2, 

and EC135T2+ helicopters, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a critical part, which could result 

in loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective July 11, 2016. 

(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 

Before further flight: 

(1) Revise the life limit of each part listed 

in paragraphs (e)(1)(i) and (ii) in the 

Airworthiness Limitations Section of the 

applicable maintenance manual and record 

the revised life limit on the component 

history card or equivalent record as follows: 

(i) For swashplate parts: 

(A) Ring (bearing ring), part number (P/N) 

L623M2001214, reduce the life limit from 

8,300 hours time-in-service (TIS) to 8,000 

hours TIS. 

(B) Ring (control ring), P/N 

L623M2001213, reduce the life limit from 

8,300 hours TIS to 8,000 hours TIS. 

(C) Cardan ring (two-part), P/N 

L623M2005205, reduce the life limit from 

14,400 hours TIS to 12,900 hours TIS. 

(D) Bolt (control ring), P/N L671M7001215, 

reduce the life limit from 14,400 hours TIS 

to 12,900 hours TIS. 

(E) Bolt (sliding sleeve), P/N 

L623M2006206 and P/N L623M2006213, 

reduce the life limit from 14,400 hours TIS 

to 12,900 hours TIS. 

(ii) For mixing lever gear unit parts: 

(A) Forked lever assembly, P/N 

L671M3012102, reduce the life limit from 

9,000 hours TIS to 8,700 hours TIS. 

(B) Hinged support, P/N L671M7003210, 

reduce the life limit from 8,700 hours TIS to 

8,400 hours TIS. 

(C) Bolt, P/N L671M7001220, reduce the 

life limit from 8,700 hours TIS to 8,400 hours 

TIS. 

(2) Remove from service any part listed in 

paragraph (e)(1) of this AD that has reached 

or exceeded its newly revised life limit. 

(f) Special Flight Permits 

Special flight permits are limited to a onetime flight to a maintenance facility to 

replace a part that has reached its life limit. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

ASW-FTW-AMOC-Requests@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. 

(h) Additional Information 

(1) Eurocopter Master Servicing Manual 

EC135 Chapter 04—Airworthiness 

Limitations Section, Revision 14, dated July 

1, 2012, which is not incorporated by 

reference, contains additional information 

about the subject of this final rule. For 

service information identified in this AD, 

contact Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2013–0178, dated August 7, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2014–0903. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300, 2700 Swashplate Ring, Cardan 

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Federal Register / Vol. 81, No. 108 / Monday, June 6, 2016 / Rules and Regulations 36139 

Ring, Bolt, Mixing Lever Gear Unit (flight 

controls). 

Issued in Fort Worth, Texas, on May 23, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–13103 Filed 6–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0338; Directorate 

Identifier 2014–CE–010–AD; Amendment 

39–18495; AD 2016–08–18] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to certain Piper Aircraft, Inc. 

Model PA–31–350 airplanes. The wing 

locations of engine TIO–540–J2B and 

LTIO–540–J2B in table 1 of the 

Applicability, paragraph (c), section are 

incorrect. This document corrects that 

error. In all other respects, the original 

document remains the same; however 

we are publishing the entire rule in the 

Federal Register. 

DATES: This final rule is effective June 

6, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0338; 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 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Gary 

Wechsler, Aerospace Engineer, FAA, 

Atlanta Aircraft Certification Office, 

1701 Columbia Avenue, College Park, 

Georgia 30337; telephone: (404) 474– 

5575; fax: (404) 474–5606; email: 

gary.wechsler@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2016–08–18, 

Amendment 39–18495 (81 FR 26106, 

May 2, 2016), currently requires 

inspecting the fuel hose assembly and 

the turbocharger support assembly for 

proper clearance between them, 

inspecting each assembly for any sign of 

damage, and making any necessary 

repairs or replacements for certain Piper 

Aircraft, Inc. Model PA–31–350 

airplanes. 

As published, the wing locations of 

engine TIO–540–JJ2B and LTIO–540– 

J2B in table 1 of the Applicability, 

paragraph (c), section are incorrect. This 

document corrects that error. 

Although no other part of the 

preamble or regulatory information has 

been corrected, we are publishing the 

entire rule in the Federal Register. 

The effective date of this AD remains 

June 6, 2016. 

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): 

2016–08–18 Piper Aircraft, Inc.: 

Amendment 39–18495; Docket No. 

FAA–2014–0338; Directorate Identifier 

2014–CE–010–AD. 

(a) Effective Date 

This AD is effective June 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Piper Aircraft, Inc. 

Model PA–31–350 airplanes, serial numbers 

31–5001 through 31–5004, 31–7305005 

through 31–8452024, and 31–8253001 

through 31–8553002, certificated in any 

category, that are equipped with the 

following engines and fuel pump hose 

assemblies: 

TABLE 1 TO PARAGRAPH (c) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES

Engine Manufacturer’s hose name Manufacturer’s part No. 

(P/N) Hose description 

LTIO–540–J2B (right wing) ............ Hose Assembly—Fuel .................. Piper 39995–034 .......................... Inlet fuel hose to engine fuel 

pump. 

TIO–540–J2B (left wing) ................ Hose, Fuel pump to Injector ......... Lycoming LW–12877–6S142 ....... Exit fuel hose from engine fuel 

pump. 

LTIO–540–J2BD (right wing) ......... Hose, Fuel pump to Injector ......... Lycoming LW–12877–6S142 ....... Exit fuel hose from engine fuel 

pump. 

TIO–540–J2BD (left wing) ............. Hose Assembly—Fuel .................. Piper 39995–034 .......................... Inlet fuel hose to engine fuel 

pump. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 73: Engine Fuel and Control. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

engine fire caused by a leak in the fuel pump 

inlet hose. We are issuing this AD to correct 

the unsafe condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs 

(g)(1) through (j)(2) of this AD, unless already 

done. 

(g) Ensure Proper Clearance Between the 

Fuel Hose Assembly and the Turbocharger 

Support Assembly 

(1) Within the next 60 hours time-inservice (TIS) after June 6, 2016 (the effective 

date of this AD) or within the next 6 months 

after June 6, 2016 (the effective date of this 

AD), whichever occurs first, inspect to 

determine the clearance between the inlet 

and exit fuel hose assemblies listed in table 

1 to paragraph (c) of this AD, and each 

turbocharger support assembly, Lycoming 

P/N LW–18302. There should be a minimum 

3/16-inch clearance. Do the inspection 

following the INSTRUCTIONS section of 

Piper Aircraft, Inc. Service Bulletin No. 

1257A, dated August 4, 2015. 

(2) Before further flight after the inspection 

required in paragraph (g)(1) of this AD, if the 

measured clearance is less than 3/16-inch, 

make all necessary adjustments to make the 

clearance a minimum of 3/16-inch between 

the inlet and exit fuel hose assemblies listed 

in table 1 to paragraph (c) of this AD and 

each turbocharger support assembly, 

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