56594 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

because of oscillatory loads and lead to 

premature failure of the chain, loss of the tail 

rotor blade pitch control, and subsequent loss 

of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 76–12–07, 

Amendment 39–2640 (41 FR 23939, June 14, 

1976) as revised by Amendment 39–3569 (44 

FR 55555, September 27, 1979). 

(d) Effective Date 

This AD becomes effective October 18, 

2013. 

(e) 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. 

(f) Required Actions 

(1) For Model 205A–1 helicopters, before 

further flight, replace the tail rotor chain and 

cable control system with an airworthy tail 

rotor push-pull control system by installing 

an improved tail rotor hub and blade 

assembly kit, P/N 205–704–040–001 or 205– 

704–040–103, and then installing a push/pull 

anti-torque retrofit kit, P/N 205–704–057–001 

or 205–704–057–101. 

(2) For Model 204B helicopters: 

(i) Within 10 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 10 

hours TIS, using a 10-power or higher 

magnifying glass and a light, visually inspect 

each of the link segments in the chain for a 

crack. Also, slowly operate the cockpit antitorque control pedals during the inspection 

so that the entire surface area of the chain in 

contact with the control quill sprocket 

(sprocket) is visibly accessible and can be 

inspected. Pay particular attention to the 

portion of the chain that travels over the 

sprocket and extends 6 inches to each side 

of the sprocket. 

(A) If there is no cracked or broken link 

segment, lubricate the chain with a light 

preservative oil (C–125) or wipe with a cloth 

dampened in lubricating oil (C–010). 

(B) If there is a cracked or broken link 

segment, before further flight, replace the 

chain with an airworthy chain. 

(ii) Within 50 hours TIS, install a tail rotor 

cable and chain damper kit, P/N 204–706– 

130–101, as depicted in Figures 1 through 3, 

and by following the Accomplishment 

Instructions, paragraphs 2. through 9., of Bell 

Alert Service Bulletin (ASB) No. 204–79–7, 

dated August 21, 1979. 

(g) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to Michael Kohner, 

ASW–170, Aviation Safety Engineer, 

Rotorcraft Directorate, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5170, fax (817) 222–5783, email 

mike.kohner @faa.gov. 

(2) For operations conducted under 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) Bell ASB No. 204–75–4, dated 

December 16, 1975; Bell ASB No. 205–78–5, 

dated May 16, 1978; Service Instructions (SI) 

No. 205–38, ‘‘changed’’ March 28, 1990; and 

SI No. 205–46, revised March 7, 1980, which 

are not incorporated by reference, contain 

additional information about the subject of 

this AD. For this service information, contact 

Bell Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101, telephone (817) 280– 

3391, fax (817) 280–6466, or at http://

www.bellcustomer.com/files/. You may 

review a copy of the referenced 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 

Transport Canada Civil Aviation (TCCA) AD 

CF–1990–06R1, issued January 7, 2008. You 

may view the TCAA AD in the AD docket on 

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

(i) Subject 

The Joint Aircraft System Component Code 

is 6720: Tail Rotor Control System. 

(j) 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) Bell Alert Service Bulletin No. 204–79– 

7, dated August 21, 1979. 

(ii) Reserved. 

(3) For Bell Helicopter Textron, Inc. service 

information identified in this AD, contact 

Bell Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 280– 

3391; fax (817) 280–6466; or at http://

www.bellcustomer.com/files/. 

(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 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. 2013–22188 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–2013–0186; Directorate 

Identifier 2013–NE–11–AD; Amendment 39– 

17571; AD 2013–17–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GE90– 

76B, –85B, –90B, –94B, –110B1, and 

–115B turbofan engines. This AD was 

prompted by multiple reports of distress 

of certain stage 1 high-pressure turbine 

(HPT) stator shrouds due to accelerated 

corrosion and oxidation, including one 

engine in-flight shutdown (IFSD) caused 

by failure of the HPT stator shrouds. 

This AD requires initial and repetitive 

on-wing 360-degree borescope 

inspections (BSIs) for corrosion and 

oxidation of stage 1 HPT stator shrouds. 

If a shroud is found to be distressed, this 

AD requires reinspection at a reduced 

interval or removal from service before 

further flight. We are issuing this AD to 

prevent failure of stage 1 HPT stator 

shrouds, resulting in an IFSD of one or 

more engines, loss of thrust control, and 

damage to the airplane. 

DATES: This AD is effective October 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 18, 2013. 

ADDRESSES: For 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. 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56595 

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: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on April 2, 2013 (78 FR 19628). 

The NPRM proposed to require initial 

and repetitive on-wing 360-degree BSIs 

for corrosion and oxidation of stage 1 

HPT stator shrouds. If a shroud failed 

the inspection, the NPRM proposed to 

require removal from service before 

further flight. We are issuing this AD to 

prevent failure of stage 1 HPT stator 

shrouds, resulting in an IFSD of one or 

more engines, loss of thrust control, and 

damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Clarify the Inspection 

Threshold for Compliance 

Austrian Airlines requested that we 

specify a compliance threshold of 2,000 

cycles to be in agreement with GE 

Service Bulletin (SB) No. GE90–100 SB 

72–0528, dated November 15, 2012, 

rather than the 2,100 cycles specified in 

the NPRM (78 FR 19628, April 2, 2013). 

We disagree. GE SB No. GE90–100 SB 

72–0528, dated November 15, 2012, 

requires a BSI within 2 months after an 

engine reaches 2,000 cycles. We 

estimate that 2 months of utilization is 

about 100 cycles, which we added to the 

initial compliance threshold to 

strengthen enforceability and to lessen 

the impact on operators with engines 

having less than 2,000 cycles. We did 

not change this AD. 

Request for Clarification on Affected 

Part Numbers 

American Airlines (AAL) commented 

that since stage 1 HPT stator shroud, 

part number (P/N) 1847M52P16, is 

included in the NPRM (78 FR 19628, 

April 2, 2013), that stage 1 HPT stator 

shroud, P/N 1847M52P10, should also 

be included. 

We disagree. Our risk analysis 

determined that corrective actions are 

required for stage 1 HPT stator shroud, 

P/N 1847M52P16. Although stage 1 HPT 

stator shroud, P/N 1847M52P10, also 

experienced distress in service, the 

distress was due to a different root 

cause. We did not identify a safety issue 

associated with the distress associated 

with stage 1 HPT stator shroud, P/N 

1847M52P10. We did not change this 

AD. 

Request To Reduce Requirements Due 

to Service Bulletin Category 

AAL commented that we should not 

mandate corrective actions in an AD 

since GE did not designate the operable 

service bulletins as alert service 

bulletins, and therefore GE did not 

identify stage 1 HPT stator shroud 

distress as a safety issue. 

We disagree. The corrective actions 

mandated in this AD are based on the 

results of a risk analysis of relevant 

engine operational safety issues. The 

category of service bulletin issued by GE 

was not a factor in our decision to issue 

this AD. We did not change this AD. 

Request To Change Applicability 

AAL requested that we add GE90 

engines that do not have GE SB No. 

GE90–100 SB 72–0348, which 

introduces a new stage 1 HPT stator 

shroud and new shroud hanger, 

incorporated, to the applicability of this 

AD. AAL believes that an engine that 

has GE SB No. GE90–100 SB 72–0348, 

incorporated, does not require repetitive 

BSIs. 

We disagree. After an engine has GE 

SB No. GE90–100 SB 72–0348 

incorporated, using shrouds with a new 

P/N, the engine is not affected by this 

AD. A stage 1 HPT stator shroud P/N 

not listed in the Applicability of this AD 

is not affected by this AD. We did not 

change this AD. 

Request To Use Revised GE SB for 

Compliance Actions 

AAL requested that paragraph (f)(4)(i) 

of the AD also reference GE SB No. SB 

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

2013, in addition to the initial issue of 

that GE SB. 

We agree. We changed paragraphs 

(f)(4)(i) and (f)(4)(ii) of this AD by 

adding a reference to GE SB No. SB 72– 

0528 R01, Revision 1, dated April 1, 

2013. 

Request To Revise Inspection 

Instructions 

AAL noted that paragraph 3.A. of the 

Accomplishment Instructions of GE SB 

No. GE90–100 SB 72–0528, dated 

November 15, 2012, which we refer to 

in the compliance paragraphs of this 

AD, contain elements that do not 

pertain to this AD, especially elements 

regarding assembly and disassembly. 

AAL requested that we revise 

paragraphs (f)(3)(i) and (f)(4)(i) of this 

AD by removing accomplishment 

elements not related to this AD. 

We partially agree. We agree that 

paragraph 3.A. of the Accomplishment 

Instructions of GE SB No. GE90–100 SB 

72–0528, dated November 15, 2012, 

contains some instructions not directly 

related to this AD. We do not agree that 

they are unrelated service information 

for inspecting and removing a distressed 

shroud. We changed paragraphs (f)(3)(i) 

and (f)(4)(i) of this AD to refer to 

paragraph 3.A. of the Accomplishment 

Instructions of the GE SB for guidance 

on how to perform a BSI to detect and 

remove a distressed shroud. 

Request To Detail the Scope of Work for 

the BSI 

AAL requested that we revise 

paragraph (f)(4)(ii) of this AD to include 

the scope of work for the BSI. 

We partially agree. We do not agree 

with including the scope of work for the 

BSI in this AD. We agree to include a 

reference to the paragraphs of the GE SB 

that detail the scope of work for the BSI 

to be performed for this AD, including 

how to determine if the shrouds are 

distressed. We changed paragraphs 

(f)(4)(ii) and (f)(4)(iii) of this AD and 

also paragraphs (f)(3)(ii) and (f)(3)(iii) of 

this AD accordingly. 

Request To Add a Paragraph 

Summarizing Credit for Previous 

Actions 

One commenter requested that we 

add a paragraph granting credit for 

engines previously inspected in 

accordance with the GE SBs. 

We disagree. Paragraph (e) of this AD 

already grants credit for previous 

inspections with the statement, 

‘‘Comply with this AD within the 

compliance times specified, unless 

already done.’’ We did not change this 

AD. 

Request To Clarify Whether Alternate 

Method of Compliance (AMOC) Is 

Needed 

All Nippon Airways Co., Ltd (ANA) 

requested clarification as to whether use 

of a locally manufactured BSI guide 

tube would require an AMOC request. 

ANA noted that using a BSI guide tube 

facilitates insertion of the borescope and 

does not otherwise affect the procedures 

described in GE SBs. 


emcdonald on DSK67QTVN1PROD with RULES
56596 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

We agree that use of a BSI guide tube 

facilitates insertion of the borescope and 

does not affect the procedure required 

by this AD. An AMOC is not required 

to use a BSI guide tube. We did not 

change this AD. 

Request To Revise Summary and 

Unsafe Condition Language 

GE requested that we change the word 

‘‘failure’’ to ‘‘distress’’ in the Summary 

and in paragraph (d) of this AD. GE 

commented that while there have been 

several reports of distress to the stage 1 

HPT stator shrouds, there has been only 

one failure. 

We partially agree. We agree with 

revising the wording to more accurately 

describe the service history. We disagree 

with removing the word ‘‘failure’’ from 

the Summary paragraph and from 

paragraph (d) of this AD because there 

has been an IFSD caused by failure of 

the stage 1 HPT stator shroud. 

We changed the Summary paragraph 

and paragraph (d) of this AD to include 

‘‘distress.’’ 

Request To Change the Proposed AD 

Requirements Paragraph 

GE requested that we change the 

Summary and Proposed AD 

Requirements paragraphs by adding the 

words ‘‘reduced interval inspection or 

. . .’’ to more accurately coincide with 

the intent of GE SB No. GE90–100 SB 

72–0528. 

We agree. We changed the Summary 

paragraph of this AD by adding the 

words ‘‘reinspection at a reduced 

interval or . . .’’. The sentence now 

reads, ‘‘If a shroud is found to be 

distressed, this AD requires reinspection 

at a reduced interval or removal from 

service before further flight.’’ 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

19628, dated April 2, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 19628, 

dated April 2, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 100 GE90 engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about four 

hours per engine to perform one 

inspection. The average labor rate is $85 

per hour. Based on these figures, we 

estimate the total cost of this AD on U.S. 

operators for one inspection to be 

$34,000. 

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 

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. 

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): 

2013–17–07 General Electric Company: 

Amendment 39–17571; Docket No. 

FAA–2013–0186; Directorate Identifier 

2013–NE–11–AD. 

(a) Effective Date 

This AD is effective October 18, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE): 

(1) GE90–76B, –85B, –90B, and –94B 

turbofan engines with stage 1 high-pressure 

turbine (HPT) stator shrouds, part number 

(P/N) 1847M52P14, installed. 

(2) GE90–110B1 and –115B turbofan 

engines with stage 1 HPT stator shrouds, 

P/N 1847M52P16, installed. 

(d) Unsafe Condition 

This AD was prompted by multiple reports 

of distress of certain stage 1 HPT stator 

shrouds due to accelerated corrosion and 

oxidation, including one engine in-flight 

shutdown (IFSD) caused by failure of the 

HPT stator shrouds. We are issuing this AD 

to prevent failure of stage 1 HPT stator 

shrouds, resulting in an IFSD of one or more 

engines, loss of thrust control, and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Borescope Inspections of the Stage 1 HPT 

Stator Shrouds 

(1) Perform an initial on-wing borescope 

inspection (BSI) of the stage 1 HPT stator 

shrouds for corrosion and oxidation before 

accumulating 2,100 cycles since new, or 

within 100 cycles in service after the 

effective date of this AD, whichever occurs 

later. 

(2) Thereafter, repeat the BSI of the stage 

1 HPT stator shrouds every 250 cycles since 

last inspection or fewer, depending on the 

results of the inspection. 

(3) For engines listed in paragraph (c)(1) 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 


emcdonald on DSK67QTVN1PROD with RULES
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