64082 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 

agree to any conditions to access the 

page; and 

(C) Mail your current privacy notice 

to those customers who request it by 

telephone within ten days of the 

request. 

(iii) An example of a statement that 

satisfies paragraph (c)(2)(ii)(A) of this 

section is as follows with the words 

‘‘Privacy Notice’’ in boldface or 

otherwise emphasized: Privacy Notice— 

Federal law requires us to tell you how 

we collect, share, and protect your 

personal information. Our privacy 

policy has not changed and you may 

review our policy and practices with 

respect to your personal information at 

[Web address] or we will mail you a free 

copy upon request if you call us at 

[telephone number]. 

* * * * * 

Dated: October 17, 2014. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2014–25299 Filed 10–27–14; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0423; Directorate 

Identifier 2013–NM–233–AD; Amendment 

39–17997; AD 2014–21–05] 

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 DC–10–10, 

DC–10–10F, DC–10–30, DC–10–30F 

(KC–10A and KDC–10), DC–10–40, MD– 

10–10F, and MD–10–30F airplanes. This 

AD was prompted by an evaluation by 

the design approval holder (DAH) 

indicating that the forward cargo 

compartment frames are subject to 

widespread fatigue damage (WFD). This 

AD requires an inspection of the 

attachment holes at the forward cargo 

compartment frames and the cargo liner 

for cracking, and repair if necessary. 

This AD would also require installing 

new oversized fasteners in the forward 

cargo compartment frames. We are 

issuing this AD to prevent fatigue 

cracking of the forward cargo 

compartment frames, which could result 

in loss of the fail-safe structural integrity 

of the airplane. 

DATES: This AD is effective December 2, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 2, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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– 

0423; 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: 

Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM 120L, Los 

Angeles Aircraft Certification Office 

(ACO), FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5234; fax: 562–627– 

5210; email: nenita.odesa@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 certain The Boeing Company 

Model DC–10–10, DC–10–10F, DC–10– 

30, DC–10–30F (KC–10A and KDC–10), 

DC–10–40, MD 10–10F, and MD–10– 

30F airplanes. The NPRM published in 

the Federal Register on June 30, 2014 

(79 FR 36669). The NPRM was 

prompted by an evaluation by the DAH 

indicating that the forward cargo 

compartment frames are subject to WFD. 

The NPRM proposed to require an 

inspection of the attachment holes at the 

forward cargo compartment frames and 

the cargo liner for cracking, and repair 

if necessary. The NPRM also proposed 

to require installing new oversized 

fasteners in the forward cargo 

compartment frames. We are issuing 

this AD to prevent fatigue cracking of 

the forward cargo compartment frames, 

which could result in loss of the failsafe structural integrity 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 

36669, June 30, 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 

36669, June 30, 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 36669, 

June 30, 2014). 

Costs of Compliance 

We estimate that this AD affects 25 

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 .............. Up to 19 work-hours × $85 per hour = $1,615 .................. $0 .......................... Up to $1,615 ......... Up to $40,375. 

Modification ............ Up to 6 work-hours × $85 per hour = $510 ....................... Up to $801 ............ Up to $1,311 ......... Up to $32,775. 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 64083 

We have received no definitive data 

that would enable us to provide cost 

estimates 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: 

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): 

2014–21–05 The Boeing Company: 

Amendment 39–17997 ; Docket No. 

FAA–2014–0423; Directorate Identifier 

2013–NM–233–AD. 

(a) Effective Date 

This AD is effective December 2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model DC–10–10, DC–10–10F, DC–10–30, 

DC–10–30F (KC–10A and KDC–10), DC–10– 

40, MD–10–10F, and MD–10–30F airplanes, 

certificated in any category, as identified in 

Boeing Service Bulletin DC10–53–182, dated 

June 28, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the forward cargo compartment frames 

are subject to widespread fatigue damage 

(WFD). We are issuing this AD to prevent 

fatigue cracking of the forward cargo 

compartment frames, which could result in 

loss of the fail-safe structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Prior to the accumulation of 30,000 total 

flight cycles, or within 72 months after the 

effective date of this AD, whichever occurs 

later: Do a high frequency eddy current 

inspection for cracking of the attachment 

holes at the forward cargo compartment 

frames and the cargo liner, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin DC10–53–182, dated 

June 28, 2013. If any crack is found, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(h) Installation of New Fasteners 

If no cracking is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, install new 

oversized fasteners to attach the forward 

cargo liner to the forward cargo compartment 

frame, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–53–182, dated June 

28, 2013. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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-LAACO-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, Los Angeles 

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. 

(j) Related Information 

For more information about this AD, 

contact Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM 120L, Los Angeles 

Aircraft Certification Office (ACO), FAA, 

3960 Paramount Boulevard, Lakewood, CA 

90712 4137; phone: 562–627–5234; fax: 562– 

627–5210; email: nenita.odesa@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 Service Bulletin DC10–53–182, 

dated June 28, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; 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. 


asabaliauskas on DSK5VPTVN1PROD with RULES
64084 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 

Issued in Renton, Washington, on October 

13, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–25013 Filed 10–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0451; Directorate 

Identifier 2013–NM–122–AD; Amendment 

39–17996; AD 2014–21–04] 

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 all The 

Boeing Company Model DC–9–81 (MD– 

81), DC–9–82 (MD–82), DC–9–83 (MD– 

83), DC–9–87 (MD–87), and MD–88 

airplanes. This AD was prompted by 

reports of cracks emanating from the aftmost barrel nut holes of the left and 

right upper rear spar caps of the 

horizontal stabilizer. This AD requires 

repetitive high frequency eddy current 

(ETHF) inspections for cracks in the 

areas around the two aft-most barrel nut 

holes of the upper rear spar caps, and 

corrective actions if necessary; and 

repetitive ETHF inspections for cracks 

in the areas around the two aft-most 

barrel nut holes of any repaired or 

replaced upper rear spar cap, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

cracks in the horizontal stabilizer, 

which could propagate until an upper 

rear spar cap severs, and result in failure 

of the horizontal stabilizer upper center 

or aft skin panel and adversely affect the 

structural integrity of the airplane. 

DATES: This AD is effective December 2, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 2, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https://

www.myboeingfleet.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. 

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– 

0451; 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: 

George Garrido, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: 562–627–5357; 

fax: 562–627–5210; email: 

george.garrido@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 all The Boeing Company Model 

DC–9–81 (MD–81), DC–9–82 (MD–82), 

DC–9–83 (MD–83), DC–9–87 (MD–87), 

and MD–88 airplanes. The NPRM 

published in the Federal Register on 

July 18, 2014 (79 FR 41946). The NPRM 

was prompted by reports of cracks 

emanating from the aft-most barrel nut 

holes of the left and right upper rear 

spar caps of the horizontal stabilizer. 

The NPRM proposed to require 

repetitive ETHF inspections for cracks 

in the areas around the two aft-most 

barrel nut holes of the upper rear spar 

caps, and corrective actions if necessary; 

and repetitive ETHF inspections for 

cracks in the areas around the two aftmost barrel nut holes of any repaired or 

replaced upper rear spar cap, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

cracks in the horizontal stabilizer, 

which could propagate until an upper 

rear spar cap severs, and result in failure 

of the horizontal stabilizer upper center 

or aft skin panel and adversely affect the 

structural integrity 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 

41946, July 18, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comments 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 

41946, July 18, 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 41946, 

July 18, 2014). 

Costs of Compliance 

We estimate that this AD affects 668 

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 ...................... 5 work-hours × $85 per hour = $425 per inspection cycle.$0 $425 per inspection 

cycle.

$283,900 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs and replacements 

that would be required based on the 

results of the inspection. We have no 

way of determining the number of 

aircraft that might need these repairs 

and replacements: 


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