Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56597 

can be found in paragraph 3.A of the 

Accomplishment Instructions of GE Service 

Bulletin (SB) No. GE90 S/B 72–1076, dated 

November 19, 2012. 

(ii) Refer to Figure 2 of GE SB No. GE90 

S/B 72–1076, dated November 19, 2012, to 

determine the degree of shroud corrosion and 

oxidation. 

(iii) Use paragraph 3.B. of the 

Accomplishment Instructions of GE SB No. 

GE90 S/B 72–1076, dated November 19, 

2012, to determine the next inspection 

interval. 

(4) For engines listed in paragraph (c)(2) of 

this AD: 

(i) Perform a 360-degree BSI of the stage 1 

HPT stator shrouds for corrosion and 

oxidation. Guidance for performing the BSI 

can be found in paragraph 3.A of the 

Accomplishment Instructions of GE SB No. 

SB 72–0528 R01, Revision 1, dated April 1, 

2013, or GE GE90–100 SB No. SB 72–0528, 

dated November 15, 2012. 

(ii) Refer to Figure 2 of GE SB No. SB 72– 

0528 R01, Revision 1, dated April 1, 2013, or 

GE GE90–100 SB No. SB 72–0528, dated 

November 15, 2012, to determine the degree 

of shroud corrosion and oxidation. 

(iii) Use paragraph 3.B. of the 

Accomplishment Instructions of GE SB No. 

SB 72–0528 R01, Revision 1, dated April 1, 

2013, or GE GE90–100 SB No. SB 72–0528, 

dated November 15, 2012, to determine the 

next inspection interval. 

(5) Remove from service before further 

flight, any stage 1 HPT stator shroud found 

with any hole further than 0.35-inch from the 

shroud leading edge, and more than 0.25- 

inch in diameter, and that is more than 0.049 

square inch in area. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures in 14 CFR 39.19 to make your 

request. 

(h) Related Information 

For more information about this AD, 

contact Jason Yang, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7747; fax: 781–238– 

7199; email: jason.yang@faa.gov. 

(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) General Electric Company (GE) Service 

Bulletin (SB) No. SB 72–0528 R01, Revision 

1, dated April 1, 2013. 

(ii) GE SB No. GE90–100 SB 72–0528, 

dated November 15, 2012. 

(iii) GE SB No. GE90 S/B 72–1076, dated 

November 19, 2012. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

One Neumann Way, MD Y–75, Cincinnati, 

OH; phone: 513–552–2913; email: geae.aoc@

ge.com; Web site: www.GE.com. 

(4) 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. 

(5) You may view this service information 

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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

August 22, 2013. 

Dorenda D. Baker, 

Director, Aircraft Certification Service. 

[FR Doc. 2013–22243 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0398; Directorate 

Identifier 2011–SW–065–AD; Amendment 

39–17578; AD 2013–18–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH (ECD) 

Model EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, and EC135T2+ 

helicopters with certain fire 

extinguishing systems installed. This 

AD requires modifying the fire 

extinguishing system injection tubes. 

This AD is prompted by a report that the 

injection tubes are deforming due to 

heat. The actions required by this AD 

are intended to prevent deformation of 

the fire extinguishing system injection 

tubes during a fire, which could result 

in impaired distribution of the fire 

extinguishing agent, failure of the fire 

extinguishing system to contain an 

engine fire, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective October 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of October 18, 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-byreference service information, 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 

Wilbanks, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 8, 2013, at 78 FR 26715, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to ECD 

Model EC135P1, EC135P2, EC135P2+, 

EC135T1, EC135T2, and EC135T2+ 

helicopters with a fire extinguishing 

system part number (P/N) 

L262M1808101, P/N L262M1812101, or 

P/N L262M1812102 installed. The 

NPRM proposed to require, within 30 

days, cutting out a portion of the 

existing fire extinguishing system 

injection tubes and replacing that 

portion with a section of new injection 

tubing. The proposed requirements were 

intended to prevent deformation of the 

fire extinguishing system injection tubes 

during a fire, which could result in 

impaired distribution of the fire 

extinguishing agent, failure of the fire 

extinguishing system to contain an 

engine fire, and subsequent loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2011–0172, dated September 7, 2011, 

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. 

2011–0172 to correct an unsafe 


emcdonald on DSK67QTVN1PROD with RULES
56598 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

condition for ECD Model EC 135 P1, EC 

135 P2, EC 135 P2+, EC 135 T1, EC 135 

T2, EC 135 T2+, EC 635 T1, EC 635 P2+, 

and EC 635 T2+ helicopters with a 

single engine fire extinguishing system, 

P/N L262M1808101, P/N 

L262M1812101, or P/N L262M1812102, 

or with a dual engine fire extinguishing 

system, P/N L262M1813102, installed. 

EASA advises that the fire extinguishing 

system injection tubes on Model EC 135 

and EC 635 helicopters ‘‘are not 

compliant with the relevant 

airworthiness requirements, because 

they are also forming part of the 

firewall.’’ According to EASA, during an 

engine fire, this condition may affect the 

function of the fire extinguishing system 

and degrade the fire containment 

capability of the system to the extent 

that it is incapable of extinguishing an 

engine fire. For these reasons, EASA 

issued AD 2011–0172, which requires 

modification of the affected injection 

tubes by removing part of the tubing and 

replacing it with a section of heatresistant injection tubing. 

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 26715, May 8, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of the Federal 

Republic of Germany and are approved 

for operation in the United States. 

Pursuant to our bilateral agreement with 

the Federal Republic of 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. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to helicopters 

with a dual engine fire extinguishing 

system and this AD does not because 

these systems are only installed on 

helicopters operated by the German 

Federal Police and are not operated in 

the U.S. 

Related Service Information 

ECD has issued EC135 Alert Service 

Bulletin No. EC135–26A–003, Revision 

2, dated December 19, 2011, which 

describes procedures to remove a 

section of the fire extinguishing system 

injection tubing and replace it with 

heat-resistant injection tubing. 

Costs of Compliance 

We estimate that this AD will affect 

246 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. Modifying the injection tubes 

will require about 4.5 work-hours at an 

average labor rate of $85 per hour and 

required parts would cost about $900, 

for a cost of $1,282 per helicopter and 

a total cost to U.S. operators of 

$315,372. 

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): 

2013–18–05 Eurocopter Deutschland 

GmbH: Amendment 39–17578; Docket 

No. FAA–2013–0398; Directorate 

Identifier 2011–SW–065–AD. 

(a) Applicability 

This AD applies to Eurocopter Deutschland 

GmbH (ECD) Model EC135P1, EC135P2, 

EC135P2+, EC135T1, EC135T2, and 

EC135T2+ helicopters with a fire 

extinguishing system part number (P/N) 

L262M1808101, P/N L262M1812101, or P/N 

L262M1812102 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

deformation of the fire extinguishing system 

injection tubes during an engine fire, which 

could result in impaired distribution of the 

fire extinguishing agent, failure of the fire 

extinguishing system to contain a fire, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective October 18, 

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 

(1) Within 30 days, modify each fire 

extinguishing system injection tube by 

removing and replacing a section of the 

tubing in accordance with the 

Accomplishment Instructions, paragraph 

3.B., of Eurocopter EC135 Alert Service 

Bulletin No. EC135–26A–003, Revision 2, 

dated December 19, 2011. 

(2) Do not install an injection tube, P/N 

L262M1810101, P/N L262M1811801, or P/N 

L262M1809101, on any helicopter unless it 

has been modified as required by this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56599 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@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 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0172, dated September 7, 2011. 

You may view the EASA AD in the AD 

Docket on the internet at http://

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2620: Extinguishing System. 

(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) Eurocopter EC135 Alert Service Bulletin 

No. EC135–26A–003, Revision 2, dated 

December 19, 2011. 

(ii) Reserved. 

(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 view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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/ibrlocations.html. 

Issued in Fort Worth, Texas, on August 27, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–22181 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0399; Directorate 

Identifier 2011–SW–064–AD; Amendment 

39–17574; AD 2013–18–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

EC 155B, EC155B1, SA–365N, SA– 

365N1, AS–365N2, AS 365 N3, and SA– 

366G1 helicopters. This AD requires 

inspecting the collective pitch lever for 

correct locking and unlocking 

conditions. This AD was prompted by 

two separate reports of inadvertent 

collective pitch lever locking and 

unlocking. The actions of this AD are 

intended to detect an incorrectly 

adjusted collective pitch lever, which 

could result in loss of control of the 

helicopter. 

DATES: This AD is effective October 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 18, 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 

authorities’ ADs, any incorporated-byreference service information, 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 

Wilbanks, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 8, 2013, at 78 FR 26712, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Eurocopter Model EC 155B, EC155B1, 

SA–365N, SA–365N1, AS–365N2, AS 

365 N3, and SA–366G1 helicopters, 

except helicopters with modification 

(MOD) 0767B5 installed. The NPRM 

proposed to require inspecting the 

collective pitch lever for correct 

unlocking with a spring scale, and if 

required, adjusting the collective pitch 

lever restraining tab and, for certain 

models, adjusting the collective link 

rods. The NPRM also proposed to 

require inspecting the collective pitch 

lever for the risk of inadvertent locking 

by measuring the clearance between the 

locking pin of the collective pitch lever 

and the L-section of the restraining tab, 

and if required, modifying the tab with 

a slight bend to the tab. The proposed 

requirements were intended to detect an 

incorrectly adjusted collective pitch 

lever, which could result in loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2011–0154, dated August 22, 2011, 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union. EASA issued AD 

2011–0154 to correct an unsafe 

condition for Eurocopter Model EC 

155B, EC155B1, SA–365N, SA–365N1, 

AS–365N2, AS 365 N3, and SA–366G1 

helicopters. EASA advises that two 

occurrences have been reported of 

inadvertent locking and unlocking of 

the collective pitch lever. One 

inadvertent collective pitch lever 

locking occurred when moving the 

collective pitch lever to the low-pitch 

position, and one inadvertent collective 

pitch lever unlocking occurred during 

engine start. To address this unsafe 

condition, Eurocopter issued AS 365 

Alert Telex No. 67.00.10, SA 366 Alert 

Telex No. 67.05, and EC 155 Alert Telex 

No. 67A007, which describe procedures 

to inspect the collective pitch lever for 

correct locking and unlocking 

conditions. This inspection was 


emcdonald on DSK67QTVN1PROD with RULES