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

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(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:



### E STIMATED 

### 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.


### 64083 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations

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.


### 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 byreports 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 forcracks 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:



### E STIMATED 

### 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: