### 43921 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations

specific to a consumer, and § 1026.19(e)(2)(iii), which prohibits creditors from requiring the submission of documents verifying information related to the consumer’s application. Accordingly, the provisions under § 1026.19(e)(2) are effective on October 3, 2015, without respect to whether an application has been received on that date. In addition, the amendments to § 1026.28 and the commentary to § 1026.29 govern the preemption of State laws and thus, the amendments to those provisions and associated commentary made by the TILA–RESPA Final Rule are effective on October 3, 2015, without respect to whether an application has been received on that date. The following examples illustrate the application of the effective date for
the TILA–RESPA Final Rule.

i. General. Assume a creditor receives an application, as defined under § 1026.2(a)(3) of the TILA–RESPA Final Rule, for a transaction subject to § 1026.19(e) and (f) on October 3, 2015,
and that consummation of the transaction occurs on October 31, 2015.
The amendments of the TILA–RESPA Final Rule, including the requirements to provide the Loan Estimate and Closing Disclosure under § 1026.19(e) and (f), apply to the transaction. The creditor would also be required to provide the special information booklet under § 1026.19(g) of the TILA–RESPA Final Rule, as applicable. Assume a creditor receives an application, as defined under § 1026.2(a)(3) of the TILA–RESPA Final Rule, for a transaction subject to § 1026.19(e) and (f) on September 30, 2015, and that
consummation of the transaction occurs on October 30, 2015. The amendments of the TILA–RESPA Final Rule, including the requirements to provide the Loan Estimate and Closing Disclosure under § 1026.19(e) and (f), do not apply to the transaction, except that the provisions of § 1026.19(e)(2), specifically § 1026.19(e)(2)(i), (e)(2)(ii), and (e)(2)(iii), do apply to the transaction beginning on October 3, 2015, because they become effective on October 3, 2015, without respect to whether an application, as defined under § 1026.2(a)(3) of the TILA–RESPA Final Rule, has been received by the creditor or mortgage broker on that date. The creditor does not provide the Closing Disclosure so that it is received by the consumer at least three business days before consummation; instead, the creditor and the settlement agent provide the disclosures under § 1026.19(a)(2)(ii) and § 1024.8, as applicable, under the Truth in Lending
Act and the Real Estate Settlement Procedures Act, respectively. The requirement to provide the special information booklet under § 1026.19(g)
of the TILA–RESPA Final Rule would also not apply to the transaction. But the creditor would provide the special information booklet under § 1024.6, as applicable.

ii. Predisclosure written estimates. Assume a creditor receives a request
from a consumer for a written estimate of terms or costs specific to the consumer on October 3, 2015, before the consumer submits an application to the creditor, and thus before the consumer has received the disclosures required under § 1026.19(e)(1)(i). The creditor, if it provides such written estimate to the consumer, must comply with the requirements of § 1026.19(e)(2)(ii) and provide the required statement on the written estimate, even though the creditor has not received an application for a transaction subject to § 1026.19(e) and (f) on that date.

iii. Request for preemption
determination. Assume a creditor submits a request to the Bureau under § 1026.28(a)(1) for a determination of
whether a State law is inconsistent with the disclosure requirements of the TILA–RESPA Final Rule on October 3,
2015. Because the amendments to § 1026.28(a)(1) are effective on that date and do not depend on whether the creditor has received an application as defined under § 1026.2(a)(3) of the TILA–RESPA Final Rule, § 1026.28(a)(1), as amended by the TILA–RESPA Final Rule, is applicable to the request on that date and the
Bureau would make a determination
based on the amendments of the TILA– RESPA Final Rule, including, for example, the requirements of § 1026.37.

**Subpart C—Closed End Credit**

* * * * *

Section 1026.19—Certain Mortgage and
Variable-Rate Transactions

* * * * *

19(g)(2) Permissible changes.

* * * * *

3. Permissible changes to title of booklets in use before October 3, 2015. Section 1026.19(g)(2)(iv) provides that the title appearing on the cover of the booklet shall not be changed. Comment 19(g)(1)–1 states that the Bureau may, from time to time, issue revised or alternative versions of the special
information booklet that address transactions subject to § 1026.19(g) by publishing a notice in the Federal Register . Until the Bureau issues a version of the special information booklet relating to the Loan Estimate and Closing Disclosure under §§ 1026.37 and 1026.38, for applications that are received on or after October 3, 2015, a creditor may change the title appearing on the cover of the version of the special information booklet in use before October 3, 2015, provided the
words ‘‘settlement costs’’ are used in the title. See comment 1(d)(5)–1 for guidance regarding compliance with § 1026.19(g) for applications received on or after October 3, 2015.

* * * * *

Dated: July 20, 2015. Richard Cordray, Director, Bureau of Consumer Financial

Protection.

[FR Doc. 2015–18239 Filed 7–22–15; 11:15 am]

**BILLING CODE 4810–AM–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0572; Directorate Identifier 2014–NM–027–AD; Amendment**  **39–18214; AD 2015–15–05]**

**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) 98–22–10 for certain The Boeing Company Model 737–100, –200, –200C, and –300 series airplanes. AD 98–22–10 required repetitive inspections for cracking of the aft frame and frame support structure of the forward service doorway, and repair if necessary. AD 98–22–10 also provided an optional terminating action for the repetitive inspection requirements of that AD. This new AD requires new inspections and adds airplanes to the applicability; for certain airplanes, this new AD provides an optional preventive modification, which terminates the repetitive inspections. This AD was prompted by reports of fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, and a determination that inspections are needed in
additional locations and that additional airplanes might be subject to the
identified unsafe condition. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six


### 43922 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations

doorstop fittings, which could result in
door deflection and loss of pressurization.

**DATES :**  This AD is effective August 28,

2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 28, 2015.

**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; phone: 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–

0572.
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– 0572; 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, FAA, Los Angeles Aircraft Certification Office (ACO), 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 to supersede AD 98–22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998). AD 98–22–10 applied to certain The Boeing Company Model 737–100, –200, –200C, and –300 series airplanes. The NPRM was published in
the Federal Register on August 26, 2014 (79 FR 50867). The NPRM was prompted by reports of cracking in the surround structure of the forward galley service doorway between body station (STA) 332.1 and STA 344, which are outside the inspection area of AD 98– 22–10, and by reports that cracking has been discovered on airplanes outside the applicability of AD 98–22–10. We have determined that inspections are needed in additional locations, and that additional airplanes are subject to the
identified unsafe condition.

The NPRM (79 FR 50867, August 26, 2014) proposed to continue to require repetitive inspections for cracking of the aft frame and frame support structure of the forward service doorway, and repair if necessary. The NPRM also proposed to add inspections, add airplanes to the applicability, and for certain airplanes, provide an optional preventive modification, which would terminate the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, which could result in
door deflection and loss of pressurization.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 50867, August 26, 2014) and the FAA’s response to each comment.

Request To Clarify Wording in NPRM (79 FR 50867, August 6, 2014)

Boeing stated paragraph 1.E, ‘‘Compliance,’’ of Boeing Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, provides actions for airplanes repaired or modified previously where the preventive modifications have been accomplished. Boeing stated that paragraph (l)(4) of the proposed AD reads: ‘‘AMOCs approved for AD 98–22–10, Amendment 39– 10858 (63 FR 57240, October 27, 1998), are approved as AMOCs for the corresponding provisions of this AD.’’ Boeing interpreted the latter statement to mean that AMOCs approved for AD 98–22–10 do not supersede (or negate) the additional inspection requirements provided in Boeing Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, and requested concurrence with its interpretation of this language.

We agree with Boeing’s interpretation. Paragraph (m)(4) of this AD (paragraph (l)(4) of the proposed AD) establishes
that an AMOC issued for actions performed in accordance with AD 98– 22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998), satisfies the corresponding provisions, and only those corresponding provisions, of the this AD. All requirements of this AD must be satisfied, whether by previous AMOC, accomplishment of the specified AD actions, or a new AMOC. We have not changed this AD in this regard.

Request To Clarify Actions That Are Not Required

Southwest Airlines (Southwest) noted that paragraph (h) of the proposed AD (79 FR 50867, August 26, 2014) would provide terminating action for the repetitive inspections required by paragraph (g) of this AD. Southwest requested that we revise the NPRM to state that the post preventive modification inspections specified in tables 9, 10, 11, and 12 in paragraph 1.E, ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, would not be required. Southwest also requested that this provision apply to paragraph (k) of the proposed AD (paragraph (l) of this AD), which specifies credit for actions done previously using Boeing Alert Service Bulletin 737–53A1108, Revision 6, dated January 9, 2014.

We agree with the requests. While the post-preventive modification inspections specified by tables 9 through 12 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)), those actions are not required by this AD. We have revised paragraph (g) of this AD by specifying the required parts
of the service information: Parts 2 and 4. We have also added new paragraph(j) in this final rule to specify that postpreventive modification inspections (Part 6) are not required by this AD. We have redesignated subsequent paragraphs of this AD accordingly.

Effect of Winglets on This AD

Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST01219SE (http:// rgl.faa.gov/Regulatory

_ and

_ Guidance

_ Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/ $FILE/ST01219SE.pdf ) does not affect accomplishment of the actions specified in the NPRM (79 FR 50867, August 26, 2014).

We concur with the commenter. We have redesignated paragraph (c) of the proposed AD (79 FR 50867, August 26, 2014) as (c)(1) and added new paragraph (c)(2) to this AD to state that installation of STC ST01219SE (http://rgl.faa.gov/


### 43923 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations

Regulatory

_ and

_ Guidance

_Library/ rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/ $FILE/ST01219SE.pdf ) does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.

Explanation of Additional Changes
Made to This AD

We have updated the Costs of Compliance section to add existing inspection and repair costs from AD 98– 22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998).

We have changed paragraph (b) of this AD to add AD 90–06–02, Amendment 39–6489, (55 FR 8372, March 7, 1990), as an affected AD since accomplishment of the preventative modification required by paragraph (h) of this AD is an alternative method of compliance for paragraph A. of AD 90–06–02.

In various locations, Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, cites Boeing Alert Service Bulletin 737–53A1108, Revision 6, dated January 9, 2014, instead of
Revision 7 of the service information. We have added a new paragraph (k)(3) in this AD to clarify that, where Revision 7 of the service information specifies accomplishment of a preventative modification be done using Revision 6 of the service information, this AD requires accomplishment of that preventative modification with Revision
7 of this service information.

We also noted a discrepancy in table 4 of paragraph 1.E., ‘‘Compliance,’’ in Boeing Alert Service Bulletin 737– 53A1108, Revision 7, dated July 7, 2014. Although the fourth action is an inspection of the intercostals ‘‘and attaching stringers,’’ the corresponding corrective action specified in table 4 is for only a crack in ‘‘an intercostal.’’ We have confirmed with Boeing that the ‘‘attaching stringers’’ were inadvertently
omitted from this condition in table 4. Repair of a cracked attaching stringer, however, is described in PART 4, paragraph 7, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014. We have added a new paragraph (k)(4) in this AD to specify that cracking in the attaching stringers also requires repair.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 50867, August 26, 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 50867, August 26, 2014).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1

CFR Part 51

We reviewed Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014. The service information describes procedures for inspections for cracking of the aft frame and frame support structure of the forward service doorway, and repair 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 419 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

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

Inspection [retained actions from AD

98–22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998)]. 7 work-hours × $85 per hour = $595 per inspection cycle. $0 ........... $595 per inspection cycle. $249,305 per inspection cycle.

Inspection [new AD action] ................... 28 work-hours × $85 per hour = $2,380 per inspection cycle. None ...... $2,380 per inspection cycle. $997,220 per inspection cycle.



### E STIMATED 

### C OSTS FOR 

### O N 

### -C ONDITION 

### A CTIONS

Action Labor cost Parts cost Cost per product

Repair [retained actions from AD 98–22–10, Amendment

39–10858 (63 FR 57240, October 27, 1998)]. 42 work-hours × $85 per hour = $3,570 .......................... $913 $4,483



### E STIMATED 

### C OSTS FOR 

### O PTIONAL 

### M ODIFICATION

Action Labor cost Parts cost Cost per product

Repair/preventive modification [new AD action]. Between 12 and 17 work-hours × $85 per hour = between $1,020 and $1,445. Between $90 and $913 .. Between $1,110 and $2,358.

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


### 43924 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations

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) 98–22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998), and adding the following new AD:

2015–15–05 The Boeing Company:

Amendment 39–18214; Docket No. FAA– 2014–0572; Directorate Identifier 2014–

NM–027–AD.

(a) Effective Date

This AD is effective August 28, 2015. (b) Affected ADs
(1) This AD replaces AD 98–22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998).

(2) This AD affects AD 90–06–02, Amendment 39–6489 (55 FR 8372, March 7, 1990).

(c) Applicability

(1) This AD applies to The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014.

(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http:// rgl.faa.gov/Regulatory

_ and

_ Guidance

_ Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ ST01219SE.pdf ) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR

39.17.

(d) Subject

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

(e) Unsafe Condition

This AD was prompted by reports of fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, and a determination that inspections are needed
in additional locations and that additional airplanes might be subject to the identified unsafe condition. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, which could result in door deflection and loss of pressurization.

(f) Compliance

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

(g) Inspections and Corrective Actions

At the applicable times specified in tables 1 through 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1108, Revision 7, dated July 7, 2014, except as required by paragraph (k)(1) of this AD: Do detailed inspections of the frame web between body station (STA) 332.1 and STA344, intercostal T-brackets, intercostal Tchords, intercostals, and stringers, as applicable; do high frequency eddy current (HFEC) inspections for cracking of door stop intercostal T-brackets, intercostal web, door stop intercostal T-chords, intercostals, and stringers, as applicable; and do all applicable related investigative and corrective actions;
in accordance with Parts 2 and 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, except as required by paragraphs (k)(2) through (k)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in tables 1 through 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, until the terminating action specified in paragraph (h)
of this AD is done.

(h) Optional Terminating Action

For Group 1, Configuration 1; Group 1, Configuration 2; Group 2; Group 3; Group 4, Configuration 1; and Group 4, Configuration 2 airplanes identified in Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014: Accomplishment of a preventive
modification in accordance with Part 5 of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, terminates the repetitive inspections required by paragraph (g) of this AD.

(i) Inspections and Corrective Actions for Group 5 Airplanes

For Group 5 airplanes identified in Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014: Within 120 days after the effective date of this AD, inspect and repair any cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Repair any cracking, before further flight.

(j) Post Preventive Modification Inspections Not Required

The post preventive modification inspections specified in tables 9 through 12 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014; are not required by this AD.

Note 1 to paragraph (j) of this AD: Tables 9 through 12 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014; specify that post preventive modification inspections may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service Bulletin 737– 53A1108, Revision 7, dated July 7, 2014; are not required by this AD.

(k) Exceptions to the Service Information

(1) Where Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, specifies a compliance time ‘‘after the issue date of Revision 6 of this service bulletin,’’ this AD requires compliance within the specified time after the effective date of this

AD.

(2) Where Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD.


### 43925 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations

(3) Where Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, specifies accomplishment of a preventative
modification in accordance with ‘‘Revision 6 of this service bulletin,’’ this AD requires accomplishment of those actions to be done in accordance with Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July

7, 2014.

(4) Where table 4 in paragraph 1.E, ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, specifies repairing a condition identified as any crack found in ‘‘an intercostal,’’ this AD requires repairing a condition identified as any crack found in ‘‘an intercostal or attaching stringers.’’

(l) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737–53A1108, Revision 6, dated January 9, 2014. This service information is not incorporated by
reference in this AD.

(m) 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 (n)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-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, 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.

(4) AMOCs approved previously for AD 98–22–10, Amendment 39–10858 (63 FR 57240, October 27, 1998), are approved as AMOCs for the corresponding provisions of
this AD.

(5) Accomplishment of the preventive modification in accordance with Boeing Alert Service Bulletin 737–53A1108, Revision 7, dated July 7, 2014, as required by paragraph (h) of this AD, is an AMOC for the structural modification specified in Boeing Alert
Service Bulletin 737–53A1108 that is required by paragraph A. of AD 90–06–02, Amendment 39–6489, (55 FR 8372, March 7, 1990), for the airplanes identified in paragraph (h) of this AD. (n) Related Information

(1) For more information about this AD, contact Nenita Odesa, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5234; fax: 562–627–5210; email: nenita.odesa@faa.gov.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraph (o)(3) of this AD.

(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.

(i) Boeing Alert Service Bulletin 737– 53A1108, Revision 7, dated July 7, 2014. (ii)
Reserved.

(3) 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; phone: 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 10,

2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–17977 Filed 7–23–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0679; Directorate Identifier 2013–NM–182–AD; Amendment**  **39–18211; AD 2015–15–02]**

**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) 2012–13– 06, for all Airbus Model A300 series airplanes and all Model A300 B4–600, B4–600R, and F4–600R series airplanes,
and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). AD 2012– 13–06 required a one-time detailed inspection to determine the length of the fire shut-off valve (FSOV) bonding leads and for contact or chafing of the wires, and corrective actions if necessary. This new AD requires a new one-time detailed inspection of the FSOV bonding leads to ensure that the correct bonding leads are inspected, and corrective action if necessary. This AD was prompted by a determination that the description of the inspection area specified in the service information was misleading; therefore, some operators might have inspected incorrect bonding leads. We are issuing this AD to detect and correct contact or chafing of wires and the bonding leads, which, if not detected, could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.

**DATES :**  This AD becomes effective August 28, 2015.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 28, 2015.

**ADDRESSES :**  You may examine the AD
docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0679; 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 SAS, Airworthiness Office—EAW, 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.airworth-eas@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. It is also
available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–

0679.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA