Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations 45697 

1The members of the Council are the Board of 

Governors of the Federal Reserve System, the 

Consumer Financial Protection Bureau, the Federal 

Deposit Insurance Corporation, the National Credit 

Union Administration, the Office of the Comptroller 

of the Currency, and the State Liaison Committee. 2 5 U.S.C. 552. 

3Public Law 114–185, 130 Stat. 538 (June 30, 

2016). 

own disclosure so long as it is 

substantially similar. The creditor need 

not orally request the monitoring 

information if it is requested in writing. 

* * * * * 

Dated: September 8, 2017. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2017–20417 Filed 9–29–17; 8:45 am] 

BILLING CODE 4810–AM–P 

FEDERAL FINANCIAL INSTITUTIONS 

EXAMINATION COUNCIL 

12 CFR Part 1101 

[Docket No. FFIEC–2017–0003] 

Description of Office, Procedures, and 

Public Information 

AGENCY: Federal Financial Institutions 

Examination Council (FFIEC). 

ACTION: Final rule. 

SUMMARY: The Federal Financial 

Institutions Examination Council 

(FFIEC or Council) is adopting as a final 

rule the interim final rule published 

July 3, 2017. The interim final rule 

announced revisions and additions to 

the Council’s information disclosure 

regulations under the Freedom of 

Information Act (FOIA Regulations). 

The interim final rule also replaced the 

interim final rule published on 

December 27, 2016. The revisions in the 

interim final rule implement recent 

statutory amendments to the FOIA that 

are mandated by the FOIA Improvement 

Act of 2016, as well as update the 

language of the Council’s regulations to 

more closely mirror the language of the 

FOIA and to reflect the Council’s 

current FOIA procedures. 

DATES: Effective October 2, 2017. 

FOR FURTHER INFORMATION CONTACT: Ms. 

Judith Dupre, Executive Secretary, 

Federal Financial Institutions 

Examination Council, via telephone: 

(703) 516–5590, or via email: JDupre@

FDIC.gov. 

SUPPLEMENTARY INFORMATION: The 

Council 1 is finalizing its interim rule 

(82 FR 30724 (July 3, 2017)), which 

revised its information disclosure 

regulations under the Freedom of 

Information Act 2 (FOIA Regulations). 

On June 30, 2016, the Freedom of 

Information Act (FOIA) was amended 

by the FOIA Improvement Act of 2016 3

(FOIA Improvement Act). Among other 

things, section 3 of the FOIA 

Improvement Act required each Federal 

agency to revise its disclosure 

regulations and procedures for 

processing FOIA requests in order to 

conform to the substantive amendments 

made by section 2 of the FOIA 

Improvement Act by December 27, 

2016. Accordingly, the Council 

implemented the required substantive 

and procedural changes necessary to 

comply with the FOIA Improvement 

Act’s amendments through issuance of 

the interim final rule (81 FR 94937 

(December 27, 2016)). In addition, the 

Council made certain changes to its 

FOIA Regulations to reflect revisions 

brought about by prior amendments to 

the FOIA that were incorporated into 

the Council’s procedures and to make 

the FOIA process easier for the public 

to navigate. In drafting these 

amendments to the FOIA Regulations, 

the Council consulted the ‘‘Guidance for 

Agency FOIA Regulations’’ issued by 

the U.S. Department of Justice’s Office 

for Information Policy. No comments 

were received in response to the interim 

final rule and it is being finalized 

without change. 

Authority and Issuance 

For the reasons set forth in the 

preamble, the Federal Financial 

Institutions Examination Council adopts 

as a final rule, without changes, the 

interim final rule amending 12 CFR 

1101.4, which was published at 82 FR 

30724 on July 3, 2017. 

Dated: September 27, 2017. 

Federal Financial Institutions Examinations 

Council. 

Judith E. Dupre, 

Executive Secretary. 

[FR Doc. 2017–21050 Filed 9–29–17; 8:45 am] 

BILLING CODE 7535–01–P; 6714–01–P; 6210–01–P; 

4810–33–P; 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3697; Product 

Identifier 2015–NM–143–AD; Amendment 

39–19062; AD 2017–20–05] 

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) 2011–01– 

15, which applied to certain The Boeing 

Company Model 757–200, –200CB, and 

–300 series airplanes. AD 2011–01–15 

required repetitive inspections for 

cracking of the fuselage skin of the 

crown skin panel along the chem-milled 

step at certain stringers, and repair if 

necessary. This AD adds repetitive 

inspections for cracking in additional 

areas, and repair if necessary; removes 

airplanes from the applicability; adds an 

optional skin panel replacement, which 

terminates all inspections; adds an 

optional preventive modification, which 

terminates certain inspections; and 

reduces the compliance time for certain 

inspections. This AD was prompted by 

reports of the initiation of new fatigue 

cracking in the fuselage skin of the 

crown skin panel along locally thinned 

channels adjacent to the chem-milled 

steps. We are issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective November 6, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; Internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 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–2016– 

3697. 

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–2016– 

3697; 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 final rule, 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 


jstallworth on DSKBBY8HB2PROD with RULES
45698 Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Eric 

Schrieber, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5348; fax: 562–627– 

5210; email: eric.schrieber@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, 

January 10, 2011) (‘‘AD 2011–01–15’’). 

AD 2011–01–15 applied to certain The 

Boeing Company Model 757–200, 

–200CB, and –300 series airplanes. AD 

2011–01–15 required repetitive 

inspections for cracking of the fuselage 

skin of the crown skin panel along the 

chem-milled step at stringers S–4L and 

S–4R, from station (STA) 297 through 

STA 439, and repair if necessary. AD 

2011–01–15 also included terminating 

action for the repetitive inspections of 

the repaired areas only. AD 2011–01–15 

resulted from reports of cracking in the 

fuselage skin of the crown skin panel. 

The NPRM published in the Federal 

Register on February 18, 2016 (81 FR 

8157) (‘‘The NPRM’’). The NPRM was 

prompted by reports of the initiation of 

new fatigue cracking in the fuselage skin 

of the crown skin panel along locally 

thinned channels adjacent to the chemmilled steps. The NPRM proposed to 

add repetitive inspections for cracking 

in additional areas, and repair if 

necessary. The NPRM also proposed to 

remove airplanes from the applicability 

in AD 2011–01–15. The NPRM also 

proposed to add an optional skin panel 

replacement, which would terminate all 

inspections, and an optional preventive 

modification, which would terminate 

certain inspections. 

We issued a supplemental NPRM 

(SNPRM) that published in the Federal 

Register on May 5, 2017 (82 FR 21146). 

The SNPRM proposed to reduce the 

compliance time for certain inspections. 

We are issuing this AD to correct the 

unsafe condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM and the FAA’s 

response to each comment. 

Supportive Comment 

United Airlines and Boeing concurred 

with the SNPRM. 

Request for Alternative Method of 

Compliance (AMOC) 

VT Mobile Aerospace Engineering 

(MAE) Inc. stated that the proposed AD 

(in the SNPRM) affects Model 757–200 

airplanes that were modified using 

certain VT MAE supplemental type 

certificates (STCs). VT MAE noted that 

its design at certain inspection locations 

is not identical to that of the Boeing STC 

design at those locations. Therefore, VT 

MAE plans to issue new service 

information to address the unsafe 

condition, and plans to request approval 

of an AMOC from the FAA for use of the 

new service information. 

FedEx stated that its airplanes have 

been modified in accordance with the 

VT MAE STC, and once this AMOC is 

approved to address this issue, FedEx 

will use it to comply with the 

requirements in the proposed AD (in the 

SNPRM). 

We acknowledge the commenters’ 

remarks. Under the provisions of 

paragraph (n) of this AD, we will 

consider requests for approval of an 

AMOC that addresses the VT MAE 

STCs, if appropriate data are submitted 

to substantiate that the method would 

provide an acceptable level of safety. 

We have made no change to 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 SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 757–53– 

0097, Revision 3, dated December 2, 

2016. This service information describes 

procedures for repetitive external 

sliding probe eddy current (EC) and 

external spot-probe-medium-frequency 

EC inspections for cracking of the crown 

skin panel, repair, a preventive 

modification, and replacement of the 

crown skin panel. 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. 

Costs of Compliance 

We estimate that this AD affects 652 

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 

Inspections (Zone 1) [Retained actions from AD 

2011-01-15].

2 work-hours × $85 per hour 

= $170 per inspection 

cycle.

$0 ......................... $170 per inspection cycle .... $110,840 per inspection 

cycle. 

Inspections (Zones 2 and 3) 

[new action].

Up to 4 work-hours × $85 

per hour = Up to $340 per 

inspection cycle.

$0 ......................... Up to $340 per inspection 

cycle.

Up to $221,680 per inspection cycle. 

Optional modification ............ Up to 615 work-hours × $85 

per hour = Up to $52,275.

Up to $26,496 ...... Up to $78,771 ...................... Up to $51,358,692. 

We have received no definitive data 

that enables us to provide a cost 

estimate for the on-condition actions or 

the optional replacement specified in 

this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations 45699 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

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) 

2011–01–15, Amendment 39–16572 (76 

FR 1351, January 10, 2011), and adding 

the following new AD: 

2017–20–05 The Boeing Company: 

Amendment 39–19062; Docket No. 

FAA–2016–3697; Product Identifier 

2015–NM–143–AD. 

(a) Effective Date 

This AD is effective November 6, 2017. 

(b) Affected ADs 

This AD replaces AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, January 

10, 2011) (‘‘AD 2011–01–15’’). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 757–200 and –300 series 

airplanes, certificated in any category, as 

identified in Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 3, 

dated December 2, 2016. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01518SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgSTC.nsf/0/38B606833BB

D98B386257FAA

00602538?OpenDocument&Highlight=

st01518se) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01518SE 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 the 

initiation of fatigue cracking in the fuselage 

skin of the crown skin panel along locally 

thinned channels adjacent to the chemmilled steps. We are issuing this AD to detect 

and correct fatigue cracking of the fuselage 

skin of the crown skin panel, which could 

result in pressure venting and consequent 

rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Do the applicable inspections required by 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) For all airplanes: Within the 

compliance time specified in paragraph (h) of 

this AD, do the Zone 1 inspection specified 

in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. 

Repeat the applicable Part 1 or Part 2 

inspection thereafter at the applicable times 

specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 3, 

dated December 2, 2016. Accomplishing the 

preventive modification specified in 

paragraph (k)(1) of this AD or the 

replacement specified in paragraph (k)(2) of 

this AD terminates the inspections required 

by this paragraph. 

(i) Do an external sliding probe eddy 

current (EC) inspection for cracking of the 

crown skin panel in the applicable Zone 1 

areas specified in, and in accordance with, 

Part 1 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016. 

(ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the 

crown skin panel in the applicable Zone 1 

areas specified in, and in accordance with, 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016. 

(2) For airplanes on which any crack is 

found during any inspection required by 

paragraph (g)(1) of this AD; or any repair is 

installed that covers any portion of the Zone 

1 inspection area specified in Boeing Special 

Attention Service Bulletin 757–53–0097, 

Revision 3, dated December 2, 2016; or the 

optional Zone 1 preventive modification 

specified in paragraph (k)(1) of this AD is 

installed: At the applicable time specified in 

table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016, except as required by paragraph (l)(1) 

of this AD: Do the Zone 2 inspection 

specified in paragraph (g)(2)(i) or (g)(2)(ii) of 

this AD. Repeat the applicable Part 4 or Part 

5 inspection thereafter at the applicable times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 3, 

dated December 2, 2016. Accomplishing the 

replacement specified in paragraph (k)(2) of 

this AD terminates the inspections required 

by this paragraph. 

(i) Do an external sliding probe EC 

inspection for cracking of the crown skin 

panel in the applicable Zone 2 areas 

specified in, and in accordance with, Part 4 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016. 

(ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the 

crown skin panel in the applicable Zone 2 

areas specified in, and in accordance with, 

Part 5 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016. 

(3) For airplanes on which any crack is 

found during any inspection required by 

paragraph (g)(1) of this AD; or any repair is 

installed that covers any portion of the Zone 

1 inspection area specified in Boeing Special 

Attention Service Bulletin 757–53–0097, 

Revision 3, dated December 2, 2016; or the 

optional Zone 1 preventive modification 

specified in paragraph (k)(1) of this AD is 

installed: At the applicable time specified in 

table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016, except as required by paragraph (l)(1) 

of this AD, do the Zone 3 inspection 

specified in paragraph (g)(3)(i) or (g)(3)(ii) of 

this AD. Repeat the applicable Part 6 or Part 

7 inspection thereafter at the applicable times 

specified in table 3 of paragraph 1.E., 


jstallworth on DSKBBY8HB2PROD with RULES
45700 Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 3, 

dated December 2, 2016. Accomplishing the 

replacement specified in paragraph (k)(2) of 

this AD terminates the inspections required 

by this paragraph. 

(i) Do an external sliding probe EC 

inspection for cracking of the crown skin 

panel in the applicable Zone 3 areas 

specified in, and in accordance with, Part 6 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016. 

(ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the 

crown skin panel in the applicable Zone 3 

areas specified in, and in accordance with, 

Part 7 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016. 

(h) Initial Compliance Time for Inspection 

Required by Paragraph (g)(1) of This AD 

Within the applicable compliance times 

specified in paragraphs (h)(1), (h)(2), (h)(3), 

and (h)(4) of this AD, whichever occurs 

latest: Do the initial inspection required by 

paragraph (g)(1) of this AD. 

(1) For all airplanes: Before the 

accumulation of 15,000 total flight cycles. 

(2) For airplanes on which an external 

sliding probe EC inspection for Zone 1, as 

specified in Boeing Special Attention Service 

Bulletin 757–53–0097, has been done as of 

the effective date of this AD: Within 620 

flight cycles after accomplishing the most 

recent external sliding probe EC inspection 

for Zone 1. 

(3) For airplanes on which an external 

spot-probe-medium-frequency EC inspection 

for Zone 1, as specified in Boeing Special 

Attention Service Bulletin 757–53–0097, has 

been done as of the effective date of this AD: 

Within 200 flight cycles after accomplishing 

the most recent external spot-probe-mediumfrequency EC inspection for Zone 1. 

(4) For all airplanes: Within 200 flight 

cycles or 90 days after the effective date of 

this AD, whichever occurs first. 

(i) Post-Preventive Modification 

Supplemental Inspections 

For airplanes on which a preventive 

modification has been installed as specified 

in Part 3 of the Accomplishment Instructions 

of Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016: At the applicable time specified in 

table 4 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016; do eddy current and detailed 

inspections for cracking of the applicable 

areas of the fuselage skin of the doublers, 

triplers, and fillers of the preventive 

modification, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0097, Revision 3, dated December 2, 2016. 

Repeat the inspection thereafter at the 

applicable times specified in table 4 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 757–53– 

0097, Revision 3, dated December 2, 2016. 

(j) Repair 

If any cracking is found during any 

inspection required by paragraph (g)(1), 

(g)(2), (g)(3), or (i) of this AD, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. Doing the repair 

ends the repetitive inspections for the 

repaired area only. 

(k) Optional Terminating Actions 

(1) Accomplishing the preventive 

modification, including doing high frequency 

EC open-hole inspections for cracking in the 

existing fastener holes, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 3, dated December 2, 

2016, except as required by paragraph (l)(2) 

of this AD, terminates the inspections 

required by paragraph (g)(1) of this AD, 

provided the preventive modification is done 

before further flight after accomplishing an 

inspection required by paragraph (g)(1) of 

this AD. If any cracking is found during any 

high frequency EC open-hole inspection, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

(2) Replacing the crown skin panel 

between station (STA) 297 and STA 439, and 

stringers S–4L and S–4R, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0097, Revision 3, dated December 2, 2016, or 

using a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD, terminates the inspections required 

by paragraphs (g)(1), (g)(2), and (g)(3) of this 

AD. 

(l) Exceptions to Service Information 

Specifications and Preventive Modification 

(1) Where Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 3, dated 

December 2, 2016, specifies a compliance 

time ‘‘after the Revision 2 date of this service 

bulletin,’’ or ‘‘after the Revision 3 date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 3, dated 

December 2, 2016, specifies to contact Boeing 

for repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for Zone 1 

inspections required by paragraph (g)(1) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Special Attention Service Bulletin 

757–53–0097, dated November 22, 2010 

(which was incorporated by reference in AD 

2011–01–15); Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 1, 

dated January 6, 2011; or Boeing Special 

Attention Service Bulletin 757–53–0097, 

Revision 2, dated July 28, 2015. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (o)(1) of 

this AD. Information may be emailed to: 9- 

ANM-LAACO-AMOC-Requests@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, 

modification, or alteration 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 Branch, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2011–01–15 

are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD; except, as of the effective date of this 

AD, AMOCs that extend the initial 

compliance times specified in AD 2011–01– 

15 are no longer approved for the compliance 

time extension, and the compliance times 

required by this AD must be complied with. 

(5) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (n)(5)(i) and (n)(5)(ii) apply. 

(i) 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. 

(ii) 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. 

(o) Related Information 

(1) For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5348; fax: 562–627–5210; email: 

Eric.Schrieber@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(3) and (p)(4) of this AD. 

(p) 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. 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Rules and Regulations 45701 

(i) Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 3, dated 

December 2, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

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 

September 14, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–20689 Filed 9–29–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0532; Product 

Identifier 2016–NM–203–AD; Amendment 

39–19060; AD 2017–20–03] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 7X 

airplanes. This AD was prompted by a 

review showing that inadequate 

clearance may exist between certain 

electrical wiring and nearby structures. 

This AD requires an inspection of 

certain electrical wiring bundles and 

feeders, modifications, and corrective 

actions if necessary. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective November 6, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.com. You may 

view this referenced service information 

at the FAA, Transport Standards 

Branch, 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–2017–0532. 

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–2017– 

0532; 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 street address for 

the Docket Office (telephone 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: Tom 

Rodriguez, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Dassault Aviation 

Model FALCON 7X airplanes. The 

NPRM published in the Federal 

Register on June 12, 2017 (82 FR 26867) 

(‘‘the NPRM’’). The NPRM was 

prompted by a review showing that 

inadequate clearance may exist between 

certain electrical wiring and nearby 

structures. The NPRM proposed to 

require an inspection of certain 

electrical wiring bundles and feeders, 

modifications, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct inadequate clearances 

between electrical wiring and nearby 

structures, which could lead to 

interference or contact with a structure 

and cause an electrical short circuit or 

fluid leakage. This could result in the 

loss of several functions essential for 

safe flight. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0230, dated November 

21, 2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Dassault 

Aviation Model FALCON 7X airplanes. 

The MCAI states: 

A review of the wiring and tubing lay-out 

showed that there may be low clearance 

between electrical wiring and nearby 

structure. Although no in-service incident 

has been reported, the minimum clearances 

could deteriorate over time. 

This condition, if not detected and 

corrected, could lead to interference or 

contact with structure, provoking an 

electrical short circuit or fluid leakage, 

possibly resulting in loss of several functions 

essential for safe flight. 

To initially address this potential unsafe 

condition, [Dassault Aviation] DA developed 

some interim modifications (mod) addressing 

the risk of short circuit and fluid leakage, and 

EASA issued AD 2010–0029 (later revised) 

[which corresponds to FAA AD 2011–14–04, 

Amendment 39–16739 (76 FR 39256, July 6, 

2011) (‘‘AD 2011–14–04’’)] to require 

embodiment of those modifications inservice. 

Since EASA AD 2010–0029R1 was issued, 

DA developed another set of modifications, 

available for in-service application through 

Service Bulletin (SB) F7X–056, which are 

considered the final solutions for this unsafe 

condition. 

For the reasons described above, this 

[EASA] AD requires a one-time [general 

visual] inspection [for worn or damaged 

wiring or connectors due to inadequate 

clearance between wiring and nearby 

structures] of the affected electrical wiring 

and, depending on findings, corrective 

action(s) and modification of the aeroplane. 

Corrective actions include modifying 

the clamping and routing; adding new 

brackets, clamps, and cable protections; 

replacing damaged parts; and improving 

connections using lock wires. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0532. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 


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