50320 Federal Register / Vol. 78, No. 160 / Monday, August 19, 2013 / Rules and Regulations 

11. Markings and Placards— 

Miscellaneous Markings and Placards— 

Fuel, and Oil, Filler Openings 

(Compliance With § 23.1557(c)(1)(ii) 

Requirements) 

Instead of compliance with 

§ 23.1557(c)(1)(i), the applicant must 

comply with the following: 

Fuel filler openings must be marked 

at or near the filler cover with— 

For diesel engine-powered 

airplanes— 

(a) The words ‘‘Jet Fuel’’; and 

(b) The permissible fuel designations, 

or references to the Airplane Flight 

Manual (AFM) for permissible fuel 

designations. 

(c) A warning placard or note that 

states the following or similar: 

‘‘Warning—this airplane is equipped 

with an aircraft diesel engine; service 

with approved fuels only.’’ 

The colors of this warning placard 

should be black and white. 

12. Powerplant—Fuel System—FuelFreezing 

If the fuel in the tanks cannot be 

shown to flow suitably under all 

possible temperature conditions, then 

fuel temperature limitations are 

required. These limitations will be 

considered as part of the essential 

operating parameters for the aircraft. 

Limitations will be determined as 

follows: 

(a) The takeoff temperature limitation 

must be determined by testing or 

analysis to define the minimum fuel 

cold-soaked temperature that the 

airplane can operate on. 

(b) The minimum operating 

temperature limitation must be 

determined by testing to define the 

minimum acceptable operating 

temperature after takeoff (with 

minimum takeoff temperature 

established in (1) above). 

13. Powerplant Installation—Vibration 

Levels 

Vibration levels throughout the 

engine operating range must be 

evaluated and: 

(a) Vibration levels imposed on the 

airframe must be less than or equivalent 

to those of the gasoline engine; or 

(b) Any vibration level higher than 

that imposed on the airframe by the 

replaced gasoline engine must be 

considered in the modification and the 

effects on the technical areas covered by 

the following paragraphs must be 

investigated: 

14 CFR part 23, §§ 23.251; 23.613; 

23.627; 23.629 (or CAR 3.159, as 

applicable to various models); 23.572; 

23.573; 23.574 and 23.901. 

Vibration levels imposed on the 

airframe can be mitigated to an 

acceptable level by utilization of 

isolators, damper clutches, and similar 

provisions so that unacceptable 

vibration levels are not imposed on the 

previously certificated structure. 

14. Powerplant Installation—One 

Cylinder Inoperative 

Tests or analysis, or a combination of 

methods, must show that the airframe 

can withstand the shaking or vibratory 

forces imposed by the engine if a 

cylinder becomes inoperative. Diesel 

engines of conventional design typically 

have extremely high levels of vibration 

when a cylinder becomes inoperative. 

Data must be provided to the airframe 

installer/modifier so either appropriate 

design considerations or operating 

procedures, or both, can be developed to 

prevent airframe and propeller damage. 

15. Powerplant Installation—High 

Energy Engine Fragments 

It may be possible for diesel engine 

cylinders (or portions thereof) to fail 

and physically separate from the engine 

at high velocity (due to the high internal 

pressures). This failure mode will be 

considered possible in engine designs 

with removable cylinders or other nonintegral block designs. The following is 

required: 

(a) It must be shown that the engine 

construction type (massive or integral 

block with non-removable cylinders) is 

inherently resistant to liberating high 

energy fragments in the event of a 

catastrophic engine failure; or 

(b) It must be shown by the design of 

the engine, that engine cylinders, other 

engine components or portions thereof 

(fragments) cannot be shed or blown off 

of the engine in the event of a 

catastrophic engine failure; or 

(c) It must be shown that all possible 

liberated engine parts or components do 

not have adequate energy to penetrate 

engine cowlings; or 

(d) Assuming infinite fragment 

energy, and analyzing the trajectory of 

the probable fragments and components, 

any hazard due to liberated engine parts 

or components will be minimized and 

the possibility of crew injury is 

eliminated. Minimization must be 

considered during initial design and not 

presented as an analysis after design 

completion. 

Issued in Kansas City, Missouri, on August 

12, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–20152 Filed 8–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0195; Directorate 

Identifier 2013–NE–08–AD; Amendment 39– 

17553; AD 2013–16–15] 

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) model 

GEnx–2B67B turbofan engines with 

booster anti-ice (BAI) air duct, part 

number (P/N) 2469M32G01, and 

support bracket, P/N 2469M46G01, 

installed. This AD was prompted by 

reports of cracks in the BAI air duct. 

This AD requires initial and repetitive 

visual inspections of the BAI air duct, 

removal from service of the BAI air duct 

if it fails inspection and, as a mandatory 

terminating action, the installation of 

new BAI air duct support brackets. We 

are issuing this AD to prevent failure of 

the BAI air duct, resulting in an in-flight 

shutdown of one or more engines, loss 

of thrust control, and damage to the 

airplane. 

DATES: This AD is effective September 

23, 2013. 

ADDRESSES: For service information 

identified in this AD, contact General 

Electric Company, GE Aviation, Room 

285, One Neumann Way, Cincinnati, 

OH; phone: 513–552–3272; email: 

geae.aoc@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 

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. 


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Federal Register / Vol. 78, No. 160 / Monday, August 19, 2013 / Rules and Regulations 50321 

FOR FURTHER INFORMATION CONTACT: 

Jason Yang, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 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 11, 2013 (78 FR 

21578). The NPRM proposed to require 

initial and repetitive visual inspections 

of the BAI air duct, removal from 

service of the BAI air duct if it fails 

inspection and, as a mandatory 

terminating action, the installation of 

new BAI air duct support brackets. 

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 Revise Applicability 

The Boeing Company and GE asked 

that the GEnx-2B67 turbofan engine be 

removed from the Applicability section 

of this AD. The commenters noted that 

this engine does not have BAI hardware, 

therefore, inspection and modification 

of the BAI does not apply. 

We agree. We revised this AD by 

removing the GEnx-2B67 engine from 

the Applicability section. 

Request To Update Service Information 

GE requested that we include a 

reference in the AD to GE Service 

Bulletin (SB) GEnx-2B S/B 75–0008, 

Revision 2, dated May 30, 2013. This SB 

was published after the NPRM (78 FR 

21578, April 11, 2013) was issued. 

We agree. We revised this AD by 

adding a reference to GE SB GEnx-2B S/ 

B 75–0008, Revision 2, dated May 30, 

2013, in the Related Information 

section. 

Request To Allow Repetitive 

Replacement of BAI Air Duct 

Cathay Pacific Airways requested that 

we allow removal of the affected BAI air 

duct every 400 engine flight cycles and 

its replacement with a new spare duct 

as an alternative method of compliance 

to the AD. 

We disagree. Replacement of the 

affected BAI air duct is not sufficient to 

meet the requirements of this AD. Per 

the Mandatory Terminating Action 

section of this AD, operators must 

install new BAI air duct support 

brackets and replace the BAI air duct 

with a part that is eligible for 

installation. We did not change the 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 (78 FR 

21578, April 11, 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 21578, 

April 11, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 16 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 4 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Required parts cost about 

$11,000 per engine. Based on these 

figures, we estimate the cost of this AD 

to U.S. operators to be $181,440. 

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): 

2013–16–15 General Electric Company: 

Amendment 39–17553; Docket No. 

FAA–2013–0195; Directorate Identifier 

2013–NE–08–AD. 

(a) Effective Date 

This AD is effective September 23, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) model GEnx-2B67B turbofan 

engines with booster anti-ice (BAI) air duct, 

part number (P/N) 2469M32G01, and support 

bracket, P/N 2469M46G01, installed. 

(d) Unsafe Condition 

This AD was prompted by reports of cracks 

in the BAI air duct, P/N 2469M32G01. We are 

issuing this AD to prevent failure of the BAI 

air duct, resulting in an in-flight shutdown 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. 


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50322 Federal Register / Vol. 78, No. 160 / Monday, August 19, 2013 / Rules and Regulations 

(f) Inspection of BAI Air Duct 

(1) Perform an initial visual inspection of 

the BAI air duct, P/N 2469M32G01, for 

cracks prior to accumulating 400 cycles since 

new (CSN). 

(2) Thereafter, repeat the visual inspection 

within every 100 cycles since last inspection. 

(3) If cracks in the BAI air duct are found 

during any inspection required by this AD, 

remove the BAI air duct from service. 

(g) Mandatory Terminating Action 

As mandatory terminating action to the 

repetitive inspection requirement of this AD, 

at the next removal of BAI air duct, P/N 

2469M32G01, or if the BAI air duct is found 

cracked, after the effective date of this AD, 

do the following: 

(1) Install new BAI air duct support 

brackets, P/Ns 2550M03G01, 2548M66G01, 

2548M67P01, 2550M18G01, and 

2550M17P01. 

(2) Replace the BAI air duct with one that 

is eligible for installation. 

(h) Definition 

For the purpose of this AD, a BAI air duct 

that is eligible for installation is one that has 

accumulated 25 CSN or fewer. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact Jason Yang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7747; fax: 781–238–7199; 

email: Jason.Yang@faa.gov. 

(2) Refer to GE Service Bulletin (SB) No. 

GEnx-2B S/B 75–0006, dated July 23, 2012; 

and GE SB No. GEnx-2B S/B 75–0008, 

Revision 1, dated February 4, 2013, or 

Revision 2, dated May 30, 2013; for guidance 

on inspecting and, if necessary, removing 

and replacing the BAI air duct, as well as 

procedures for installation of new BAI air 

duct support brackets. 

(3) For service information identified in 

this AD, contact General Electric, One 

Neumann Way, Room 285, Cincinnati, OH; 

phone: 513–552–3272; email: geae.aoc@

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. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

August 7, 2013. 

Frank P. Paskiewicz, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2013–20097 Filed 8–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–1175; Airspace 

Docket No. 12–AAL–11] 

Amendment of Class E Airspace; Point 

Thomson, AK 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies the 

airspace at Point Thomson, AK, by 

establishing Class E Airspace at Point 

Thomson Airstrip Airport, Point 

Thomson, AK. New Area Navigation 

(RNAV) Global Positioning System 

(GPS) standard instrument approach 

procedures have been established at the 

airport. This action enhances the safety 

and management of aircraft operations 

at the airport. 

DATES: Effective date, 0901 UTC, 

October 17, 2013. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR Part 51, subject to the annual 

revision of FAA Order 7400.9 and 

publication of conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Richard Roberts, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA, 98057; 

telephone (425) 203–4517. 

SUPPLEMENTARY INFORMATION: 

History 

On May 23, 2013, the FAA published 

in the Federal Register a notice of 

proposed rulemaking to modify 

controlled airspace at Point Thomson, 

AK (78 FR 30797). Interested parties 

were invited to participate in this 

rulemaking effort by submitting written 

comments on the proposal to the FAA. 

No comments were received. 

Class E airspace designations are 

published in paragraph 6005, of FAA 

Order 7400.9W dated August 8, 2012, 

and effective September 15, 2012, which 

is incorporated by reference in 14 CFR 

Part 71.1. The Class E airspace 

designation listed in this document will 

be published subsequently in that 

Order. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) part 71 by 

modifying Class E airspace extending 

upward from 700 feet above the surface 

within an 8.9-mile radius of Point 

Thomson Airstrip Airport, Point 

Thomson, AK, to accommodate aircraft 

using new RNAV (GPS) standard 

instrument approach procedures at the 

airport. This action is necessary for the 

safety and management of IFR 

operations. 

The FAA has determined this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation: (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); and (3) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that only affects air traffic 

procedures and air navigation, it is 

certified this rule, when promulgated, 

does not have a significant economic 

impact on a substantial number of small 

entities under the criteria of the 

Regulatory Flexibility Act. The FAA’s 

authority to issue rules regarding 

aviation safety is found in Title 49 of the 

U.S. Code. Subtitle 1, Section 106 

discusses the authority of the FAA 

Administrator. Subtitle VII, Aviation 

Programs, describes in more detail the 

scope of the agency’s authority. This 

rulemaking is promulgated under the 

authority described in Subtitle VII, Part 

A, Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it modifies 

controlled airspace at Point Thomson 

Airstrip Airport, Point Thomson, AK. 

Environmental Review 

The FAA has determined that this 

action qualifies for categorical exclusion 

under the National Environmental 

Policy Act in accordance with FAA 

Order 1050.1E, ‘‘Environmental 

Impacts: Policies and Procedures,’’ 

paragraph 311a. This airspace action is 

not expected to cause any potentially 

significant environmental impacts, and 

no extraordinary circumstances exist 

that warrant preparation of an 

environmental assessment. 

List of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (air). 

Adoption of the Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends 14 CFR Part 71 as follows: 


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