Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 68345 

Because no notice of proposed 

rulemaking is required, the Regulatory 

Flexibility Act does not require an 

initial or final regulatory flexibility 

analysis. 5 U.S.C. 603(a), 604(a). 

The Bureau has determined that the 

Rule does not impose any new or revise 

any existing recordkeeping, reporting, or 

disclosure requirements on covered 

entities or members of the public that 

would be collections of information 

requiring OMB approval under the 

Paperwork Reduction Act, 44 U.S.C. 

3501, et seq. The requirement for 

lenders to provide the loan applicant 

with a written list of homeownership 

counseling organizations in the loan 

applicant’s location is currently 

approved by OMB and assigned the 

OMB control number 3170–0025. 

Generally, the collections of information 

contained in Regulation X are assigned 

the OMB control number 3170–0016, 

and the collections of information 

contained in Regulation Z are assigned 

the OMB control number 3170–0015. 

Dated: November 7, 2013. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2013–27300 Filed 11–13–13; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0871; Directorate 

Identifier 2013–NM–187–AD; Amendment 

39–17658; AD 2013–23–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, and 747SR 

series airplanes. This AD requires 

inspecting to determine the part number 

of the inboard actuator attach fittings of 

the outboard flap. For affected attach 

fittings, this AD requires doing a 

detailed inspection of the attach fittings 

for a cylindrical defect and replacing if 

necessary. As an option to the detailed 

inspection, this AD allows replacement 

of affected attach fittings. This AD was 

prompted by a report of the fracture of 

an inboard actuator attach fitting of the 

outboard flap. An inspection of the 

attach fitting revealed that it was 

incorrectly machined with a cylindrical 

profile instead of a conical profile, 

resulting in reduced wall thickness. We 

are issuing this AD to detect and correct 

defective inboard actuator attach fittings 

which, combined with loss of the 

outboard actuator load path, could 

result in uncontrolled retraction of the 

outboard flap, damage to flight control 

systems, and consequent reduced 

controllability of the airplane. 

DATES: This AD is effective November 

29, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 29, 2013. 

We must receive comments on this 

AD by December 30, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. 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; 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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report a report of the 

fracture of a No. 7 inboard actuator 

attach fitting of the outboard flap. It was 

determined that the fracture occurred in 

the internal conical machined area. 

Investigation revealed that a portion of 

the interior surface was machined with 

a cylindrical profile instead of a conical 

profile. This resulted in reduced wall 

thickness and subsequent fracture; the 

thickness of the fitting was 

approximately half the designed wall 

thickness. We also received reports of 

other attach fittings with a cylindrical 

defect with reduced wall thickness. This 

condition combined with loss of the 

outboard actuator load path, if not 

corrected, could result in uncontrolled 

retraction of the outboard flap and 

subsequent damage to flight control 

systems at the rear spar, and consequent 

reduced controllability of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–57A2343, dated September 

12, 2013. For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires inspecting to 

determine the part number of the 

inboard actuator attach fittings of the 

outboard flap. For affected attach 

fittings, this AD requires doing a 

detailed inspection of the attach fittings 

for a cylindrical defect and replacing if 

necessary. As an option to the detailed 

inspection, this AD allows replacement 

of the affected attach fittings. 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 


TKELleY on DSK3SPTVN1PROD with RULES
68346 Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 

AD system. One enhancement was a 

new process for annotating which steps 

in the service information are required 

for compliance with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of crucial AD 

requirements and help provide 

consistent judgment in AD compliance. 

The actions specified in the service 

information described previously 

include steps that are labeled as RC 

(required for compliance) because these 

steps have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As noted in the specified service 

information, steps labeled as RC must be 

done to comply with the AD. However, 

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 service 

information without obtaining approval 

of an alternative method of compliance 

(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 will require approval of an 

AMOC. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

We are also considering further 

rulemaking to require a minimum 

thickness inspection of inboard actuator 

attach fittings that are conically 

machined. However, the planned 

compliance time for the minimum 

thickness inspection would allow 

enough time to provide notice and 

opportunity for prior public comment 

on the merits of that inspection. This 

AD only addresses the unsafe condition 

associated with inboard actuator attach 

fittings of the outboard flap that have a 

cylindrical defect. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because defective actuator attach 

fittings, combined with loss of the 

outboard actuator load path, could 

result in uncontrolled retraction of the 

outboard flap, damage to flight control 

systems, and consequent reduced 

controllability of the airplane. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2013–0871 and Directorate 

Identifier 2013–NM–187–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 184 

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 

Inspection for part number .............................. 7 work-hour × $85 per hour = $595 ............... $0 $595 $109,480 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

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: 


TKELleY on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 220 / Thursday, November 14, 2013 / Rules and Regulations 68347 

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): 

2013–23–03 The Boeing Company: 

Amendment 39–17658; Docket No. 

FAA–2013–0871; Directorate Identifier 

2013–NM–187–AD. 

(a) Effective Date 

This AD is effective November 29, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, and 747SR 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of the 

fracture of an inboard actuator attach fitting 

of the outboard flap. An inspection of the 

attach fitting revealed that it was incorrectly 

machined with a cylindrical profile instead 

of a conical profile, resulting in reduced wall 

thickness. We are issuing this AD to detect 

and correct defective inboard actuator attach 

fittings which, combined with loss of the 

outboard actuator load path, could result in 

uncontrolled retraction of the outboard flap, 

damage to flight control systems, and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Part Number Inspection 

Within 90 days after the effective date of 

this AD: Inspect to determine the part 

number of the inboard actuator attach fittings 

of the outboard flaps, in accordance with Part 

1 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

dated September 12, 2013. 

(h) Actions for Certain Attach Fittings 

If, during the inspection required by 

paragraph (g) of this AD, any inboard 

actuator attach fitting having part number 

(P/N) 65B08564–7 is found, before further 

flight, do the actions specified in paragraph 

(h)(1) or (h)(2) of this AD. 

(1) Do a detailed inspection of the inboard 

actuator attach fitting for a cylindrical defect, 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2343, dated 

September 12, 2013. If any cylindrical defect 

is found, before further flight, do the actions 

specified in paragraph (h)(1)(i) or (h)(1)(ii) of 

this AD. 

(i) Do a minimum thickness inspection of 

the inboard actuator attach fitting to 

determine minimum wall thickness of the 

actuator fitting assembly, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2343, 

dated September 12, 2013. If the minimum 

thickness of the wall is less than 0.130 inch: 

Before further flight, replace the inboard 

actuator attach fitting of the outboard flap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747 57A2343, dated 

September 12, 2013. 

(ii) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(2) Replace the inboard actuator attach 

fitting of the outboard flap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2343, dated September 12, 2013. 

(i) 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(k) 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– 

57A2343, dated September 12, 2013. 

(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 review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. 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 October 

31, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27015 Filed 11–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0329; Directorate 

Identifier 2012–NM–032–AD; Amendment 

39–17596; AD 2013–19–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directives (ADs) 2009– 

04–07 and 2011–02–09 for certain 


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