Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations 57751 

TABLE 13 TO § 324.173—SUPPLEMENTARY LEVERAGE RATIO—Continued 

Dollar amounts in thousands 

Tril Bil Mil Thou 

Repo-style transactions 

12 On-balance sheet assets for repo-style transactions, except include the gross 

value of receivables for reverse repurchase transactions. Exclude from this item the 

value of securities received in a security-for-security repo-style transaction where 

the securities lender has not sold or re-hypothecated the securities received. Include in this item the value of securities that qualified for sales treatment that must 

be reversed.

13 LESS: Reduction of the gross value of receivables in reverse repurchase transactions by cash payables in repurchase transactions under netting agreements.

14 Counterparty credit risk for all repo-style transactions.

15 Exposure for repo-style transactions where a banking organization acts as an 

agent.

16 Total exposures for repo-style transactions (sum of lines 12 to 15).

Other off-balance sheet exposures 

17 Off-balance sheet exposures at gross notional amounts.

18 LESS: Adjustments for conversion to credit equivalent amounts.

19 Off-balance sheet exposures (sum of lines 17 and 18).

Capital and total leverage exposure 

20 Tier 1 capital.

21 Total leverage exposure (sum of lines 3, 11, 16 and 19).

Supplementary leverage ratio 

22 Supplementary leverage ratio .................................................................................. (in percent) 

Dated: September 3, 2014. 

Thomas J. Curry, 

Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System, September 4, 2014. 

Robert deV. Frierson, 

Secretary of the Board. 

Dated at Washington, DC, this 3rd day of 

September, 2014. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2014–22083 Filed 9–25–14; 8:45 am] 

BILLING CODE 4810–33–P; 6210–01–P; 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0343; Directorate 

Identifier 2014–NM–077–AD; Amendment 

39–17971; AD 2014–19–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–8 and 

747–8F series airplanes. This AD was 

prompted by an analysis by the 

manufacturer, which revealed that 

certain fuse pins for the strut-to-wing 

attachment of the outboard aft upper 

spar are susceptible to migration in the 

event of a failed fuse pin through bolt. 

This AD requires replacing the fuse pins 

for the strut-to-wing attachment of the 

outboard aft upper spar with new fuse 

pins, and replacing the access cover 

assemblies with new access cover 

assemblies. We are issuing this AD to 

prevent migration of these fuse pins, 

which could result in the complete 

disconnect and loss of the strut-to-wing 

attachment load path for the outboard 

aft upper spar. The complete loss of an 

outboard aft upper spar strut-to-wing 

attachment load path could result in 

divergent flutter in certain parts of the 

flight envelope, which could result in 

loss of control of the airplane. 

DATES: This AD is effective October 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 31, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA 98057–3356. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0343; 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 

Docket 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: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6513; 

fax: 425–917–6590; email: 

narinder.luthra@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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57752 Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–8 and 747–8F series 

airplanes. The NPRM published in the 

Federal Register on June 25, 2014 (79 

FR 35966). The NPRM was prompted by 

an analysis by the manufacturer, which 

revealed that certain fuse pins for the 

strut-to-wing attachment of the outboard 

aft upper spar are susceptible to 

migration in the event of a failed fuse 

pin through bolt. The NPRM proposed 

to require replacing the fuse pins for the 

strut-to-wing attachment of the outboard 

aft upper spar with new fuse pins, and 

replacing the access cover assemblies 

with new access cover assemblies. We 

are issuing this AD to prevent migration 

of these fuse pins, which could result in 

the complete disconnect and loss of the 

strut-to-wing attachment load path for 

the outboard aft upper spar. The 

complete loss of an outboard aft upper 

spar strut-to-wing attachment load path 

could result in divergent flutter in 

certain parts of the flight envelope, 

which could result in loss of control of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supported the NPRM (79 FR 

35966, June 25, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

35966, June 25, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 35966, 

June 25, 2014). 

Costs of Compliance 

We estimate that this AD affects 5 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. 

operators 

Replacement .............................. 97 work-hours × $85 per hour = $8,245 ......................................... $31,076 $39,321 $196,605 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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, 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): 

2014–19–03 Boeing: Amendment 39–17971; 

Docket No. FAA–2014–0343; Directorate 

Identifier 2014–NM–077–AD. 

(a) Effective Date 

This AD is effective October 31, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–8 and 747–8F series airplanes; 

certificated in any category; having a variable 

number identified in paragraph 1.A., 

‘‘Effectivity,’’ of Boeing Alert Service Bulletin 

747–54A2238, dated January 31, 2014; and 

variable number RC573. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by an analysis by 

the manufacturer, which revealed that the 

fuse pins for the strut-to-wing attachment of 

the outboard aft upper spar are susceptible to 

migration in the event of a failed fuse pin 

through bolt. We are issuing this AD to 

prevent migration of these fuse pins, which 

could result in the complete disconnect and 

loss of the strut-to-wing attachment load path 

for the outboard aft upper spar. The complete 

loss of the an outboard aft upper spar strutto-wing attachment load path could result in 

divergent flutter in certain parts of the flight 


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Federal Register / Vol. 79, No. 187 / Friday, September 26, 2014 / Rules and Regulations 57753 

envelope, which could result in loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Fuse Pins and Access 

Cover Assemblies 

Within 48 months after the effective date 

of this AD: Replace the fuse pins for the 

outboard aft upper spar and the access cover 

assemblies on struts Nos. 1 and 4, with new 

fuse pins and access cover assemblies, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2238, dated January 31, 2014. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(i) Related Information 

For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6513; fax: 425–917– 

6590; email: narinder.luthra@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) Boeing Alert Service Bulletin 747– 

54A2238, dated January 31, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA 98057–3356. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on 

September 12, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–22468 Filed 9–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0291; Directorate 

Identifier 2013–NM–137–AD; Amendment 

39–17972; AD 2014–19–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–03– 

19, which applies to certain Airbus 

Model A320–111, –211 and –231 series 

airplanes. AD 2004–03–19 required 

repetitive inspections for cracking in the 

transition and pick-up angles in the 

lower part of the center fuselage area, 

and corrective action if necessary. AD 

2004–03–19 also provided for an 

optional terminating modification for 

the repetitive inspection requirements. 

This new AD requires accomplishing 

the modification by installing washers 

between the transition pick-up angle 

and the pin nuts, and doing related 

investigative and corrective actions if 

necessary. This new AD also adds 

airplanes to the applicability of AD 

2004–03–19. This AD was prompted by 

a determination that the optional 

terminating modification must be 

required in order to address the unsafe 

condition. We are issuing this AD to 

prevent fatigue cracking in the 

transition and pick-up angles of the 

lower part of the center fuselage, which 

could result in reduced structural 

integrity of the wing-fuselage support 

and fuselage pressure vessel. 

DATES: This AD becomes effective 

October 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 15, 2004 (69 FR 5922, 

February 9, 2004). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0291; or in 

person at the Docket 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. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2004–03–19, 

Amendment 39–13463 (69 FR 5922, 

February 9, 2004). AD 2004–03–19 

applied to certain Airbus Model A320– 

111, –211, and –231 series airplanes. 

The NPRM published in the Federal 

Register on May 30, 2014 (79 FR 31057). 

The NPRM was prompted by a 

determination that the optional 

terminating modification must be 


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