## 44835 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations

external doublers on the fuselage skin, and do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, except as required by paragraphs (i)(2), (i)(3), and (i)(4) of this AD.

(1) For affected areas with any existing repair doubler: Before further flight, do inspections and applicable repairs using a method approved in accordance with the procedures specified by paragraph (j) of this

AD.

(2) For affected areas with no existing repair doubler, do the applicable actions specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD.

(i) Before further flight, do a surface LFEC inspection for corrosion of the external lower lobe doubler, a surface LFEC inspection for skin cracks of the external lower lobe doubler, a detailed inspection for cracks of the external lower lobe skin, and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight.

(ii) Do all applicable repetitive inspections of the fuselage skin thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014.

(i) Exceptions to Service Information Specifications

(1) Where Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) Although Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, specifies to contact Boeing for repair data, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD.

(3) Where Paragraph 3.B, Part 2, Step 1, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, incorrectly identifies ‘‘747 NDT Manual Part 6, 51–00–00, Procedure 8,’’ associated with the LFEC inspection for skin cracks of the external lower lobe repair doubler, the correct reference is ‘‘747 NDT Manual Part 6, 53–30–00, Procedure 5.’’

(4) Where Paragraph 3.B, Part 3, Step 1, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, specifies doing external surface LFEC inspections in accordance with ‘‘747 NDT Manual Part 6, 51–00–00, Procedure 5 or Procedure 12,’’ and the skin panels are chem milled with a thickness that exceeds the specification listed in Table 2 of Appendix C of Boeing Alert Service Bulletin 747–53A2861, dated April 1, 2014, this AD requires using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) 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 (k) 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) Except as required by paragraph (i) of this AD: Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an AD, then the steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

(4) 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.

(k) Related Information

For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@faa.gov.

(l) 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– 53A2861, dated April 1, 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. 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 July 16,

2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–18156 Filed 7–27–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0921; Directorate Identifier 2014–NM–073–AD; Amendment**  **39–18193; AD 2015–13–06]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding Airworthiness Directive (AD) 2013–14– 05 for certain The Boeing Company Model 747–400 and 747–400F series airplanes. AD 2013–14–05 required repetitive inspections of the longeron extension fittings for cracking, and related investigative and corrective actions if necessary. This new AD would continue to require the actions specified in AD 2013–14–05, and would add new repetitive high frequency eddy current (HFEC) inspections of any modified, repaired, or replaced longeron extension fitting for cracking, and applicable related investigative and corrective actions if necessary. This AD was prompted by reports of cracking in the outboard flange of the longeron extension fittings, and our determination that more work is necessary on airplanes on which a permanent repair, longeron extension fitting replacement, or modification was accomplished. We are issuing this AD to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane.

**DATES** 

### : This AD is effective September 1,

2015.


## 44836 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 1, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of August 26, 2013 (78 FR 43763, July 22, 2013).

**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. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA 2014–

0921. 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 0921; 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** 

### : Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 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 issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013). AD 2013–14–05 applied to certain The Boeing Company Model 747–400 and 747–400F series airplanes. The NPRM published in the Federal Register on December 15, 2014 (79 FR 74038). The NPRM was prompted by reports of cracking in the outboard flange of the longeron extension fittings, and our determination that more work is necessary on airplanes on which a permanent repair, longeron extension fitting replacement, or modification was accomplished, as required by AD 2013– 14–05. The NPRM proposed to continue to require the actions specified in AD 2013–14–05, and to add new repetitive high frequency eddy current (HFEC) inspections of any modified, repaired, or replaced longeron extension fitting for cracking, and applicable related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 74038, December 15, 2014) and the FAA’s response to each comment.
Support for the NPRM (79 FR 74038, December 15, 2014)

United Airlines expressed that the NPRM (79 FR 74038, December 15, 2014) affects 13 of its Boeing Model 747–400 series airplanes, and that it concurs with the NPRM.

Boeing expressed that it concurs with the NPRM (79 FR 74038, December 15, 2014).
Request To Include the Effective Date

Atlas Air requested that we revise the NPRM (79 FR 74038, December 15, 2014) to include a new paragraph (k)(3) to list the effective date of AD 2013–14– 05, Amendment 39–17510 (78 FR 43763, July 22, 2013), or that we include the effective date of AD 2013–14–05 in paragraph (g) of the NPRM. Atlas Air pointed out that the compliance time in paragraph (g) of the NPRM references the ‘‘Compliance’’ section of the service information, which is based on the effective date of AD 2013–14–05, and once AD 2013–14–05 is replaced, the effective date of AD 2013–14–05 will no longer exist.

We disagree with the commenter’s request to add a new paragraph (k)(3) to this AD, or to add the effective date of AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), to paragraph (g) of this AD. The effective date of AD 2013–14–05 (August 26, 2013) is specified in the first sentence under paragraph 1.E., ‘‘Compliance,’’ of the referenced service information. Therefore, no change is needed for this AD in this regard.

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 74038, December 15, 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 74038, December 15, 2014).

Related Service Information Under 1 CFR part 51

We reviewed Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. The service information describes procedures for repetitive HFEC inspections of any modified, repaired, or replaced longeron extension fitting for cracking, and applicable related investigative and corrective actions if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** 

### section of this AD.
Costs of Compliance

We estimate that this AD affects 41 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

HFEC inspection [retained action from AD

2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013)]. 32 work-hours × $85 per hour = $2,720 per inspection cycle. $0 $2,720 per inspection cycle. $111,520 per inspection cycle


## 44837 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations

E STIMATED 

### C OSTS

### —Continued

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Terminating action for certain inspections [retained action from AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013)]. 479 work-hours × $85 per hour = $40,715. $0 $40,715 ........................ $1,669,315

HFEC inspection [new action] ............................. 32 work-hours × $85 per hour = $2,720 per inspection cycle. $0 $2,720 per inspection cycle. $111,520 per inspection cycle



### We estimate the following costs to do any necessary 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 this replacement:



### O N 

### -CONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Replacement .................................... 464 work-hours × $85 per hour = $39,440 ............................................... $0 $39,440



### 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

We have determined that 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 removing Airworthiness Directive (AD) 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), and adding the following new AD:

2015–13–06 The Boeing Company: Amendment 39–18193 ; Docket No. FAA–2014–0921; Directorate Identifier

2014–NM–073–AD.

(a) Effective Date

This AD is effective September 1, 2015. (b) Affected ADs This AD replaces AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013).

(c) Applicability

This AD applies to The Boeing Company Model 747–400 and –400F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014.

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by reports of cracking in the outboard flange of the longeron extension fittings, and our determination that more work is necessary on airplanes on which a permanent repair, longeron extension fitting replacement, or modification was accomplished, as required by AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013). We are issuing this AD to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done.

(g) Repetitive Inspections

At the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014: Do surface high frequency eddy current (HFEC) inspections for cracking of the left and right longeron extension fittings, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. Do all applicable corrective actions at the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing


## 44838 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations

Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. If no cracking is found, repeat the inspection thereafter at the intervals specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, until a terminating action specified in paragraph (h) of this AD is done.

(h) Terminating Actions for the Inspections Required by Paragraph (g) of This AD

(1) Doing the permanent repair, longeron extension fitting replacement, or preventative modification before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, terminates the repetitive inspections required by paragraph (g) of this AD. Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, was incorporated by reference in AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013) and continues to be incorporated by reference in this AD. After accomplishing the actions specified in this paragraph, the actions specified in paragraph (i) of this AD must be done at the times specified in paragraph (i) of this AD.

(2) Doing the repair (PART 4 of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014), longeron extension fitting replacement, or modification on or after the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD, terminates the repetitive inspection requirements of paragraph (g) of this AD. After accomplishing the actions specified in this paragraph, the actions specified in paragraph (i) of this AD must be done at the times specified in paragraph (i) of this AD.

(i) Post-Modification/Repair/Replacement Inspections

For airplanes on which any action identified in paragraph (h) of this AD has been accomplished (including if the action is done as a corrective action required by paragraph (g) or (j) of this AD): At the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(1) of this AD, do a surface HFEC inspection of the left and right longeron extension fittings for cracking, as applicable, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. Do all applicable corrective actions at the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. If no cracking is found, repeat the inspection thereafter at the interval specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014. (j) Inspection of Temporary Repair and
Corrective Actions

For airplanes on which a temporary repair specified in Boeing Alert Service Bulletin 747–53A2860 has been done: At the times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, do a surface HFEC inspection of the temporary repair of the longeron extension fittings for cracking, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, except as required by paragraph (k)(2) of this AD. Do all applicable corrective actions before further flight.

(k) Exceptions to the Service Information

(1) Where Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, specifies a compliance time ‘‘after the Revision 1 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) Where Boeing Alert Service Bulletin 747–53A2860, Revision 1, dated March 18, 2014, specifies to contact Boeing for repair information: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD.

(l) Credit for Previous Actions

This paragraph provides credit for the actions specified in paragraphs (g) and (j) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2860, dated December 4, 2012, which was incorporated by reference in AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013).

(m) 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 (n) 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) AMOCs approved previously for AD 2013–14–05, Amendment 39–17510 (78 FR 43763, July 22, 2013), are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), and (j) of this AD.

(n) Related Information

For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425– 917–6590; email: Nathan.P.Weigand @faa.gov.

(o) 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.

(3) The following service information was approved for IBR on September 1, 2015.

(i) Boeing Alert Service Bulletin 747– 53A2860, Revision 1, dated March 18, 2014.

(ii) Reserved. (4) The following service information was approved for IBR on August 26, 2013 (78 FR 43763, July 22, 2013).

(i) Boeing Alert Service Bulletin 747– 53A2860, dated December 4, 2012.

(ii) Reserved. (5) For Boeing 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.

(6) You may view this service information at FAA, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(7) 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 June 19,

2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–15851 Filed 7–27–15; 8:45 am]

**BILLING CODE 4910–13–P**