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

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 


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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/


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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: 

ESTIMATED COSTS

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. 

ESTIMATED COSTS FOR ON-CONDITION ACTIONS

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 

ESTIMATED COSTS FOR OPTIONAL MODIFICATION

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 


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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 STA 

344, 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. 


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(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 


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