Federal Register / Vol. 81, No. 81 / Wednesday, April 27, 2016 / Rules and Regulations 24699 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

April 7, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–09687 Filed 4–26–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4344; Directorate 

Identifier 2015–NE–32–AD; Amendment 39– 

18486; AD 2016–08–10] 

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 all 

General Electric Company (GE) CF6– 

80C2A1, CF6–80C2A2, CF6–80C2A3, 

CF6–80C2A5, CF6–80C2A5F, CF6– 

80C2A8, CF6–80C2B1, CF6–80C2B1F, 

CF6–80C2B1F1, CF6–80C2B1F2, CF6– 

80C2B2, CF6–80C2B2F, CF6–80C2B3F, 

CF6–80C2B4, CF6–80C2B4F, CF6– 

80C2B5F, CF6–80C2B6, CF6–80C2B6F, 

CF6–80C2B6FA, CF6–80C2B7F, CF6– 

80C2B8F, CF6–80C2D1F, CF6–80C2L1F, 

CF6–80C2K1F and CF6–80E1A1, CF6– 

80E1A2, CF6–80E1A3, CF6–80E1A4, 

and CF6–80E1A4/B turbofan engines. 

This AD was prompted by reports of a 

burn-through of the accessory heat 

shield during an engine fire, 

propagating the fire into the accessory 

compartment and igniting additional 

flammable fuel source. This AD requires 

replacing the accessory heat shield 

assembly. We are issuing this AD to 

prevent fires from propagating into the 

accessory compartment, resulting in an 

uncontrolled engine fire, and damage to 

the airplane. 

DATES: This AD is effective June 1, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 1, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, GE Aviation, 

Room 285, 1 Neumann Way, Cincinnati, 

OH 45215; phone: 513–552–3272; email: 

aviation.fleetsupport@ge.com. 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–4344. 

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– 

4344; 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: 

Herman Mak, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7147; fax: 781–238–7199; 

email: herman.mak@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 GE CF6–80C2A1, CF6–80C2A2, 

CF6–80C2A3, CF6–80C2A5, CF6– 

80C2A5F, CF6–80C2A8, CF6–80C2B1, 

CF6–80C2B1F, CF6–80C2B1F1, CF6– 

80C2B1F2, CF6–80C2B2, CF6–80C2B2F, 

CF6–80C2B3F, CF6–80C2B4, CF6– 

80C2B4F, CF6–80C2B5F, CF6–80C2B6, 

CF6–80C2B6F, CF6–80C2B6FA, CF6– 

80C2B7F, CF6–80C2B8F, CF6– 

80C2D1F, CF6–80C2L1F, and CF6– 

80C2K1F turbofan engines. This AD that 

would also apply to CF6–80E1A1, CF6– 

80E1A2, CF6–80E1A3, CF6–80E1A4, 

and CF6–80E1A4/B turbofan engines. 

The NPRM published in the Federal 

Register on December 7, 2015 (80 FR 

75952). The NPRM was prompted by 

reports of a burn-through of the 

accessory heat shield during an engine 

fire leading to an accessory 

compartment fire. A fire burns through 

the accessory heat shield and ignites the 

integrated drive generator (IDG) and 

main fuel pump, which supports further 

combustion. The existing accessory heat 

shield assembly leaves a large area 

above the sensitive accessories, such as 

the IDG and the main fuel pump, 

without adequate protection. A total of 

three burn-through events have 

occurred. The NPRM proposed to 

require replacing the accessory heat 

shield assembly. We are issuing this AD 

to prevent an uncontrolled engine fire, 

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 NPRM (80 FR 75952, 

December 7, 2015) and the FAA’s 

response to each comment. 

Support for the NPRM (80 FR 75952, 

December 7, 2015) 

The Boeing Company and the 

National Transportation Safety Board 

expressed support for the NPRM (80 FR 

75952, December 7, 2015). 

Revision to Service Information 

We revised the Discussion section and 

Applicability paragraph (e) of this AD to 

include all the GE CF6–80C2 and CF6– 

80E1 turbofan engine models. 

Request To Change Summary 

GE requested that we revise the 

Summary paragraph of this AD to 

correct the number of events and clarify 

the event description. 

We agree. Only three of the originally 

specified five events resulted in heat 

shield burn-throughs. We revised the 

Summary paragraph of this AD to 

correct the number of events and clarify 

the event description. 

Request To Revise the Other Related 

Service Information Paragraph 

GE requested that we revise the Other 

Related Service Information paragraph 

of this AD to remove GE Service 

Bulletin (SB) CF6–80C2 S/B 72–1523, 

dated September 22, 2015. This SB only 

applies to the military variant of the 

engine. 

We disagree. The military variant of 

the engine is also certified by the FAA. 

We did not change this AD. 

Request To Revise the Costs of 

Compliance 

GE, KLM Royal Dutch Airlines (KLM), 

All Nippon Airways (ANA), and Federal 

Express (FedEx) requested that we 

revise the Costs of Compliance 

paragraph of this AD to correct the parts 

cost used in the calculations. 

We agree. We considered the costs of 

all the parts needed to comply with this 

AD and revised the costs per engine to 

$14,207 and the total cost to U.S. 

operators to $13,680,920. 


jstallworth on DSK7TPTVN1PROD with RULES
24700 Federal Register / Vol. 81, No. 81 / Wednesday, April 27, 2016 / Rules and Regulations 

Request To Change Applicability 

KLM requested that we exclude GE 

CF6–80E1 engines from the 

Applicability paragraph of this AD. 

KLM reasoned that the NTSB safety 

recommendation did not address GE 

CF6–80E1 engines and CF6–80E1 

engines have not experienced any sump 

fires to date. 

We disagree. Although the NTSB did 

not address GE CF6–80E1 engines, the 

designs of the GE CF6–80C2 and CF6– 

80E1 engines are substantially similar. 

Therefore, the unsafe condition 

addressed by this AD is likely to exist 

or develop on the GE CF6–80E1 engines. 

We did not change this AD. 

Request To Change Compliance 

GE requests that the following part 

numbers (P/Ns) be removed from Table 

1 of GE SB 72–1520: P/N 2022M47G01, 

P/N 2022M81P01, P/N 2022M85G01, 

and P/N 2023M20G01. These P/Ns are 

used only on GE CF6–80C2B6FA 

models, a military application, and 

contain a different heat shield design. 

We disagree. The specified P/Ns are 

not listed in Table 1 of GE SB 72–1520 

and therefore this comment is not 

applicable. We did not change this AD. 

Request To Change Definition 

GE, United Airlines, KLM, Lufthansa, 

Lufthansa Cargo, Lufthansa Technik, 

and FedEx requested that we provide a 

more accurate description of flange 

separation and exclude certain 

situations from the definition of a shop 

visit. The commenters reasoned that this 

would provide clarity and reduce the 

undue economic and operational 

burden of complying with this AD 

earlier than necessary. 

We agree. We revised the Definition 

paragraph of this AD to clarify the 

description of flange separation and 

include specific conditions that do not 

qualify as shop visits. 

Request To Delay the Effective Date 

GE and Delta Air Lines (Delta) 

requested that we delay the effective 

date of this AD. GE reasoned that the 

revised service bulletin addressing the 

lack of repair instructions for accessory 

heat shield assembly, P/N 1313M94G09, 

will not be available until after the 

expected effective date of this AD. 

We disagree. The current effective 

date of this AD is needed to address the 

unsafe condition for the affected fleet. 

Any party may make a request for an 

Alternative Method of Compliance 

(AMOC) to this AD using the procedures 

listed in this AD. Any requests for an 

AMOC are reviewed and responded to 

accordingly. We did not change this AD. 

Request To Change Applicability 

ANA requested limiting the 

Applicability paragraph of this AD to a 

particular maintenance, repair, and 

overhaul (MRO) shop where improper 

maintenance occurred leading to fire. 

ANA reasoned that the latest 2010 sump 

fire leading to heat shield burn-through 

was the result of improper maintenance 

at a particular MRO. 

We disagree. This AD addresses the 

insufficient fire protection design of the 

heat shield to prevent secondary fire 

damage. This is independent from the 

cause of fire in the engine. We did not 

change this AD. 

Request To Change Effectivity 

Lufthansa, Lufthansa Cargo, and 

Lufthansa Technik requested that we 

not mandate heat shield rework or 

replacement. Lufthansa reasoned that 

none of their customers operating GE 

CF6–80C2/80A engines have 

experienced a compressor rear frame 

(CRF) sump fire. 

We disagree. Complying with this AD 

is necessary to correct the unsafe 

condition of heat shield burn-through. 

The heat shield rework or replacement 

is needed to prevent fires from 

propagating into the accessory 

compartment, leading to a larger engine 

fire and subsequent damage to the 

airplane. We did not change this AD. 

Request for Allowance of Creating and 

Marking Serial Numbers 

Delta requested we allow operators to 

both create and mark identification 

numbers on heat shields that are not 

currently marked. Delta has received 

reports that there are illegible 

identification markings on heat shields. 

We partially agree. We agree there is 

a lack of information about heat shields 

with illegible P/Ns in this AD. We 

revised the Compliance section of this 

AD to address heat shields with illegible 

P/Ns. 

We disagree with allowing operators 

to create and mark identification 

numbers on heat shields as this does not 

resolve the unsafe condition and is 

beyond the scope of this AD. 

Request To Change Applicability 

GE commented that heat shield, P/N 

1643M23G12, is also affected by the 

unsafe condition described in this AD. 

We agree. We added heat shield, P/N 

1643M23G12, to the applicability of this 

AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

75952, December 7, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 75952, 

December 7, 2015). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed GE SB CF6–80C2 S/B 

72–1520, dated September 22, 2015 and 

GE SB CF6–80E1 S/B 72–0525, dated 

September 22, 2015. These SBs describe 

the procedures for removing and 

replacing the accessory heat shield 

assembly. 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. 

Other Related Service Information 

We reviewed GE SB CF6–80E1 S/B 

72–0504, dated October 24, 2014. This 

SB describes procedures for quick-turn 

workscope procedure to replace CF6– 

80E1 stage 1 high-pressure turbine 

blades. We also reviewed GE SB CF6– 

80C2 S/B 72–1516, Revision 2, dated 

November 6, 2015. This SB describes 

procedures for replacement of the CRF 

assembly, oil manifold, air tubes, and 

support brackets. We also reviewed GE 

SB CF6–80C2 S/B 72–1523, dated 

September 22, 2015. This SB describes 

procedures for removing and replacing 

the accessory heat shield assembly. 

Costs of Compliance 

We estimate that this AD affects 935 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 5 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Parts cost about $14,207 

per engine. Based on these figures, we 

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

operators to be $13,680,920. 

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. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 81 / Wednesday, April 27, 2016 / Rules and Regulations 24701 

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): 

2016–08–10 General Electric Company: 

Amendment 39–18486; Docket No. 

FAA–2015–4344; Directorate Identifier 

2015–NE–32–AD. 

(a) Effective Date 

This AD is effective June 1, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) CF6–80C2A1, CF6–80C2A2, 

CF6–80C2A3, CF6–80C2A5, CF6–80C2A5F, 

CF6–80C2A8, CF6–80C2B1, CF6–80C2B1F, 

CF6–80C2B1F1, CF6–80C2B1F2, CF6– 

80C2B2, CF6–80C2B2F, CF6–80C2B3F, CF6– 

80C2B4, CF6–80C2B4F, CF6–80C2B5F, CF6– 

80C2B6, CF6–80C2B6F, CF6–80C2B6FA, 

CF6–80C2B7F, CF6–80C2B8F, CF6– 

80C2D1F, CF6–80C2L1F, CF6–80C2K1F 

turbofan engines. This AD also applies to 

CF6–80E1A1, CF6–80E1A2, CF6–80E1A3, 

CF6–80E1A4, and CF6–80E1A4/B turbofan 

engines. 

(d) Unsafe Condition 

This AD was prompted by reports of a 

burn-through of the accessory heat shield 

during an engine fire, leading to an accessory 

compartment fire. We are issuing this AD to 

prevent uncontrolled engine fire, and damage 

to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For CF6–80C2 engines, at the next 

engine shop visit after the effective date of 

this AD, remove from service accessory heat 

shield assembly, part number (P/N) 

1643M23G12, and any other accessory heat 

shield assembly listed by P/N in Table 1 of 

GE Service Bulletin (SB) CF6–80C2 S/B 72– 

1520, dated September 22, 2015. Install an 

accessory heat shield assembly eligible for 

installation. 

(2) For CF6–80E1 engines, at the next 

engine shop visit after the effective date of 

this AD, remove from service accessory heat 

shield assemblies listed by P/N in Table 1 of 

GE SB CF6–80E1 S/B 72–0525, dated 

September 22, 2015. Install an accessory heat 

shield assembly eligible for installation. 

(3) Remove any heat shield assembly from 

service if the accessory heat shield assembly 

part number marking is illegible and the 

documentation associated with the part 

cannot properly identify the part. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any accessory heat shield assembly, P/ 

N 1643M23G12; or any accessory heat shield 

assembly listed by P/N in Table 1 of GE SB 

CF6–80C2 S/B 72–1520, dated September 22, 

2015; or in Table 1 of GE SB CF6–80E1 S/ 

B 72–0525, dated September 22, 2015; into 

any engine. 

(g) 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 following purposes is 

not considered a shop visit: 

(1) Transportation without subsequent 

engine maintenance. 

(2) Replacement of the turbine rear frame. 

(3) Removal of the top or bottom highpressure compressor (HPC) case, or both, for 

HPC airfoil maintenance or replacement of 

variable stator vane bushing or lever arms. 

(4) Quick-turn workscope procedure to 

replace CF6–80E1 stage 1 high-pressure 

turbine (HPT) blades per CF6–80E1 SB 72– 

0504 R00 ENGINE—General (72–00–00)— 

Quick-Turn Workscope Procedure to Replace 

CF6–80E1 Stage 1 HPT Blades. 

(5) Replacement of compressor rear frame 

assembly, new oil manifold, air tubes and 

support brackets per CF6–80C2 SB 72–1516 

R02 ENGINE—Compressor Rear Frame 

Assembly (72–34–00)—New Oil Manifold, 

Air Tubes and Support Brackets. 

(h) 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. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

For more information about this AD, 

contact Herman Mak, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7147; fax: 781–238–7199; email: 

herman.mak@faa.gov. 

(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) General Electric Company (GE) Service 

Bulletin (SB) CF6–80C2 S/B 72–1520, dated 

September 22, 2015. 

(ii) GE SB CF6–80E1 S/B 72–0525, dated 

September 22, 2015. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, 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 

April 7, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–09686 Filed 4–26–16; 8:45 am] 

BILLING CODE 4910–13–P 


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