Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57049 

or No. AS355–65.00.22, both Revision 0 and 

both dated May 18, 2011, as applicable for 

your model helicopter. 

(2) Strip the paint from the TGB control 

lever attachment yokes, as depicted in Figure 

2, item (z), of the ASB No. AS350–65.00.46 

or No. AS355–65.00.22, as applicable to your 

model helicopter. 

(3) Perform a Fluorescent Penetrant 

Inspection (FPI) in accordance with 

paragraph 3.B.2 of ASB No. AS350–65.00.46 

or No. AS355–65.00.22, as applicable to your 

model helicopter, on the TGB control lever 

attachment yokes for a crack. You are only 

required to follow the actions defined in this 

ASB paragraph pertaining to the FPI. 

(4) If a crack exists, before further flight, 

replace the TGB with an airworthy TGB. 

(5) If there is no crack, clean the inspected 

area and apply chemical conversion coating 

(Alodine 1200 or equivalent), Epoxy primer, 

and top coat paint. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone 817–222– 

5328; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0104, dated May 27, 2011. You may 

view the EASA AD at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0119. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 

(i) 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) Eurocopter Alert Service Bulletin No. 

AS350–65.00.46, Revision 0, dated May 18, 

2011. 

(ii) Eurocopter Alert Service Bulletin No. 

AS355–65.00.22, Revision 0, May 18, 2011. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on July 26, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–22295 Filed 9–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0301; Directorate 

Identifier 2013–NM–025–AD; Amendment 

39–17575; AD 2013–18–02] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200, 

–300, –300F, and –400ER series 

airplanes. This AD was prompted by 

reports of cracked and corroded nuts on 

an outboard flap support rib. This AD 

requires, for certain airplanes, repetitive 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, and related 

investigative and corrective actions if 

necessary. For certain other airplanes, 

this AD also requires repetitive 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, related 

investigative and corrective actions if 

necessary, and if necessary, a detailed 

inspection to determine the nut type 

installed in the outboard flap support 

rib and corrective actions. This AD also 

provides terminating action for the 

repetitive inspections under certain 

conditions. We are issuing this AD to 

detect and correct cracked and corroded 

nuts and bolts and the installation of 

incorrect nuts on certain outboard flap 

support ribs, which could lead to 

additional nut and bolt damage in the 

joint, result in loss of an outboard flap, 

and adversely affect continued safe 

flight and landing of the airplane. 

DATES: This AD is effective October 22, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 22, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 

Document 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on April 10, 2013 (78 FR 

21276). The NPRM proposed to require, 

for certain airplanes, repetitive 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, related 

investigative and corrective actions if 

necessary, and replacement of all 

fasteners in the support ribs, which 

terminates the repetitive inspections. 

For certain other airplanes, the NPRM 

proposed to require repetitive 

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57050 Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 

inspections of the cap seal for damaged 

sealant on nuts common to certain 

outboard flap support ribs, related 

investigative and corrective actions if 

necessary, and if necessary, a detailed 

inspection to determine the nut type 

installed in the outboard flap support 

rib and corrective actions. For those 

airplanes, the NPRM also proposed to 

provide for optional replacement of all 

fasteners in the support ribs, which 

would terminate the repetitive 

inspections. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 21276, 

April 10, 2013) and the FAA’s response 

to each comment. 

Request To Refer to Revised Service 

Information 

Japan Airlines, UPS, and Boeing 

stated that Boeing has issued revised 

service information and requested that 

the service information referenced in 

the NPRM (78 FR 21276, April 10, 2013) 

be updated to refer to Boeing Service 

Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013. 

We agree with the commenters’ 

requests and have revised paragraphs 

(c), (g), (h), (i), and (j) of this final rule 

to include Boeing Service Bulletin 767– 

57A0131, Revision 1, dated May 8, 

2013. We have also added a new 

paragraph (k) of this AD to provide 

credit for actions accomplished before 

the effective date of this AD using 

Boeing Alert Service Bulletin 767– 

57A0131, dated October 30, 2012, and 

reidentified the subsequent paragraphs. 

Clarification Regarding the Installation 

of Winglets 

Aviation Partners Boeing and UPS 

stated that the installation of winglets 

per Supplemental Type Certificate 

(STC) ST01920SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

59027f43b9a7486e86257b1d006591ee/

$FILE/ST01920SE.pdf) does not affect 

the accomplishment of the 

manufacturer’s service instructions. 

We agree with the commenters’ 

statements that the installation of 

winglets as specified in STC ST01920SE 

(http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/

59027f43b9a7486e86257b1d006591ee/

$FILE/ST01920SE.pdf) does not affect 

accomplishment of the requirements of 

this AD, and for airplanes on which STC 

ST01920SE is installed, a ‘‘change in 

product’’ AMOC approval request is not 

necessary to comply with the 

requirements of section 39.17 of the 

Federal Aviation Regulations (14 CFR 

39.17). We have added this provision in 

new paragraph (c)(2) of this final rule. 

Request To Correct a Reference to a 

Table Number 

UPS noted a typographical error in 

paragraph (h)(1)(i) of the NPRM (78 FR 

21276, April 10, 2013). The inspection 

intervals are identified in table 2 of 

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

Service Bulletin 767–57A0131, Revision 

1, dated May 8, 2013, and the NPRM 

erroneously referred to table 1. 

We agree there is an error and have 

revised paragraph (h)(1)(i) of this AD to 

refer to table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service 

Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013. 

Request To Clarify Terminating Action 

UPS noted that paragraph (i) of the 

NPRM (78 FR 21276, April 10, 2013) 

implies that the only terminating action 

for the repetitive inspections proposed 

by paragraph (h) of the NPRM is 

replacement of all fasteners within a 

support rib. UPS stated that the Boeing 

service information provides 

terminating action by replacing 

fasteners at all discrepant or corroded 

locations and/or the verification of 

correct nut type at all other locations. 

UPS requested that these corrective 

actions be identified as terminating 

action for the inspections proposed by 

paragraph (h) of the NPRM for the 

associated support rib. 

We agree that clarification is needed 

regarding terminating action for the 

repetitive inspections required by 

paragraph (h) of this final rule. We have 

changed the header of paragraph (i) of 

this final rule to ‘‘Terminating Action 

for Repetitive Inspections’’ and split the 

paragraph into three subparagraphs. 

Paragraph (i)(1) of this final rule states 

that, if during any inspection required 

by paragraphs (g) or (h) of this AD, any 

cracking is found, all fasteners within a 

support rib must be replaced to 

terminate the repetitive inspections for 

that support rib only. New paragraph 

(i)(2) of this final rule states that if a 

discrepancy other than cracking is 

found (e.g., corrosion) during any 

inspection required by paragraph (g) of 

this final rule, all fasteners within a 

support rib must be replaced to 

terminate the repetitive inspections for 

that support rib only. New paragraph 

(i)(3) of this final rule states that if a 

discrepancy other than cracking is 

found (e.g., corrosion) during any 

inspection required by paragraph (h) of 

this final rule, replacing the affected 

fastener terminates the repetitive 

inspections for only that fastener within 

that support rib. 

Request To Combine Paragraphs (h)(1) 

and (h)(2) of the NPRM (78 FR 21276, 

April 10, 2013) 

UPS stated that the intent of 

paragraph (h) of the NPRM (78 FR 

21276, April 10, 2013) is to identify the 

requirements of the initial inspection, 

and the intent of paragraphs (h)(1) and 

(h)(2) of the NPRM is to identify the 

requirements of the repetitive 

inspections based on the findings of the 

initial inspection. UPS stated that the 

investigative and corrective actions 

applicable to paragraph (h)(1) of the 

NPRM are the same as those in 

paragraph (h)(2) of the NPRM and 

suggested that these two paragraphs 

could be combined without affecting the 

intent of this AD. 

We do not agree that paragraphs (h)(1) 

and (h)(2) of this final rule can be 

combined. Paragraph (h)(1) of this final 

rule describes actions based on the 

findings of the cap seal detailed 

inspections, and paragraph (h)(2) of this 

final rule addresses actions based on the 

findings of the inspections for the nuts, 

bolts, and washers on the support ribs. 

We have not changed this final rule in 

this regard. 

Request To Change Compliance Time 

for Initial Detailed Inspection 

UPS requested that the threshold for 

conducting the initial detailed 

inspection of the cap seal required by 

paragraphs (g) and (h) of the NPRM (78 

FR 21276, April 10, 2013) be extended 

from 12 months to 24 months. UPS 

commented that if it is not possible to 

extend the threshold for the initial 

inspection, then the text should be 

revised to read ‘‘12 months after the AD 

effective date or within the appropriate 

total years of aircraft service-life’’— 

whichever occurs later. UPS requested 

this change to reflect the reported 

technical data as well as to give 

operators time to schedule the task at a 

facility capable of accomplishing the 

scope of the work. 

We do not agree with UPS’s request 

to extend the threshold for the initial 

detailed inspection. We have 

determined that the compliance time, as 

proposed, represents the maximum 

interval of time allowable for the 

affected airplanes to continue to safely 

operate before the initial inspection is 

done. Since maintenance schedules vary 

among operators, there would be no 

assurance that the airplane would be 

modified during that maximum interval. 

We have not changed this final rule in 

this regard. 

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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57051 

Furthermore, we do not agree with 

UPS’s request to revise the compliance 

time text to include ‘‘or within the 

appropriate total years of aircraft 

service-life’’—whichever occurs later. 

The installation of an incorrect nut 

during production, and the possibility 

of the nut cracking due to being 

overtorqued, is unrelated to the age of 

the airplane. We have not changed this 

final rule 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 

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 (78 FR 

21276, April 10, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 21276, 

April 10, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 440 

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 

Detailed inspections ................ 1 work-hour × $85 per hour = $85 ......................................... $0 $85 $37,400 

Replacement of all fasteners 

(Group 1 airplanes).

2 work-hours × $85 per hour = $170 ..................................... 2,553 2,723 1,198,120 

We estimate the following costs to do 

any necessary related investigative and 

corrective actions and detailed 

inspections for nut type that would be 

required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these actions. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Related investigative and corrective actions and detailed inspection for nut type.Up to 3 work-hours × $85 per hour = $255 .................. $2,553 Up to $2,808. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–18–02 The Boeing Company: 

Amendment 39–17575; Docket No. 

FAA–2013–0301; Directorate Identifier 

2013–NM–025–AD. 

(a) Effective Date 

This AD is effective October 22, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200, 767–300, 767– 

300F, and 767–400ER series airplanes; 

certificated in any category; as identified in 

Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/rgstc.

nsf/0/59027f43b9a7486e86257b1d006591ee/

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57052 Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 

$FILE/ST01920SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01920SE 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 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracked and corroded nuts on an outboard 

flap support rib. We are issuing this AD to 

detect and correct cracked and corroded nuts 

and bolts and the installation of incorrect 

nuts on certain outboard flap support ribs, 

which could lead to additional nut and bolt 

damage in the joint, result in loss of an 

outboard flap, and adversely affect continued 

safe flight and landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) For Group 1 Airplanes: Repetitive 

Inspections of the Support Ribs, Related 

Investigative and Corrective Actions, and 

Fastener Replacement 

For Group 1 airplanes, as specified in 

Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013: Except as 

required by paragraph (j) of this AD, at the 

time specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

767–57A0131, Revision 1, dated May 8, 2013, 

do a detailed inspection of the cap seal for 

damaged sealant on the nuts common to 

outboard flap support rib numbers 1, 2, 7, 

and 8, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0131, Revision 1, dated May 8, 2013. Do 

all applicable related investigative and 

corrective actions before further flight, except 

as specified in paragraphs (g)(1)(ii) and 

(g)(2)(ii) of this AD. 

(1) If, during any detailed inspection of the 

cap seal required by paragraph (g) of this AD, 

no damaged sealant is found on any support 

rib, do the actions specified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD. 

(i) Repeat the detailed inspection of the cap 

seal on that support rib thereafter at the 

intervals specified in table 1 of paragraph 

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

Bulletin 767–57A0131, Revision 1, dated 

May 8, 2013, until all fasteners are replaced 

within that support rib as required by 

paragraph (g)(1)(ii) of this AD. 

(ii) Except as required by paragraph (j) of 

this AD, at the time specified in table 1 of 

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

Service Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013: Replace all fasteners 

within the support rib, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013. 

(2) If, during any related investigative 

action required by paragraph (g) of this AD, 

no cracking and no corrosion is found on the 

nut, bolt, and washers of any support rib, do 

the actions specified in paragraphs (g)(2)(i) 

and (g)(2)(ii) of this AD. 

(i) Repeat the detailed inspection of the cap 

seal on that support rib thereafter at the 

intervals specified in table 1 of paragraph 

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

Bulletin 767–57A0131, Revision 1, dated 

May 8, 2013, until all fasteners are replaced 

within that support rib as required by 

paragraph (g)(2)(ii) of this AD. 

(ii) Except as required by paragraph (j) of 

this AD, at the time specified in table 1 of 

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

Service Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013: Replace all fasteners 

within the support rib, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013. 

(h) For Group 2 and 3 Airplanes: Repetitive 

Inspections of the Support Ribs, Related 

Investigative and Corrective Actions, and 

Fastener Replacement 

For Group 2 and 3 airplanes, as specified 

in Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013: Except as 

required by paragraph (j) of this AD, at the 

time specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

767–57A0131, Revision 1, dated May 8, 2013, 

do a detailed inspection of the cap seal for 

damaged sealant on the nuts common to 

outboard flap support rib numbers 1, 2, 7, 

and 8, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0131, Revision 1, dated May 8, 2013. Do 

all applicable related investigative and 

corrective actions before further flight. 

(1) If, during any detailed inspection of the 

cap seal required by paragraph (h) of this AD, 

no damaged sealant is found on any support 

rib, do the actions specified in paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD. 

(i) Repeat the detailed inspection of the cap 

seal on that support rib thereafter at the 

intervals specified in table 2 of paragraph 

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

Bulletin 767–57A0131, Revision 1, dated 

May 8, 2013, until the actions required by 

paragraph (h)(1)(ii) of this AD are done or 

until all fasteners are replaced within that 

support rib as specified in paragraph (i) of 

this AD. 

(ii) Except as required by paragraph (j) of 

this AD, at the time specified in table 2 of 

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

Service Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013: Do a detailed inspection 

to determine the nut type installed in the 

outboard flap support rib and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013. Do all 

applicable corrective actions before further 

flight. 

(2) If, during any related investigative 

action required by paragraph (h) of this AD, 

no cracking and no corrosion is found on the 

nut, bolt, and washers of any support rib, do 

the actions specified in paragraphs (h)(2)(i) 

and (h)(2)(ii) of this AD. 

(i) Repeat the detailed inspection of the cap 

seal on that support rib thereafter at the 

intervals specified in table 2 of paragraph 

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

Bulletin 767–57A0131, Revision 1, dated 

May 8, 2013, until the actions required by 

paragraph (h)(2)(ii) of this AD are done or 

until all fasteners are replaced within that 

support rib as specified in paragraph (i) of 

this AD. 

(ii) Except as required by paragraph (j) of 

this AD, at the time specified in table 2 of 

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

Service Bulletin 767–57A0131, Revision 1, 

dated May 8, 2013: Do a detailed inspection 

to determine the nut type installed in the 

outboard flap support rib and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013. Do all 

applicable corrective actions before further 

flight. 

(i) Terminating Action for Repetitive 

Inspections 

(1) If cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Replacing all the fasteners within 

the outboard flap support rib number 1, 2, 7, 

or 8, in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0131, Revision 1, dated May 8, 2013, 

terminates the inspections required by 

paragraph (g) or (h) of this AD for that 

support rib only. 

(2) If a discrepancy other than cracking is 

found (e.g., corrosion) during any inspection 

required by paragraph (g) of this AD: 

Replacing all the fasteners within the 

outboard flap support rib number 1, 2, 7, or 

8, in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0131, Revision 1, dated May 8, 2013, 

terminates the inspections required by 

paragraph (g) of this AD for that support rib 

only. 

(3) If a discrepancy other than cracking is 

found (e.g., corrosion) during any inspection 

required by paragraph (h) of this AD: 

Replacing the affected fastener terminates the 

repetitive inspections for only that fastener 

within that support rib. 

(j) Exception to Service Information 

Where Boeing Service Bulletin 767– 

57A0131, Revision 1, dated May 8, 2013, 

specifies a compliance time relative to the 

issue date of that service bulletin, this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

applicable actions required by paragraphs (g), 

(h), and (i) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 767– 

57A0131, dated October 30, 2012, which is 

not incorporated by reference in this AD. 

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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57053 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: berhane.alazar@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

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

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 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 August 

23, 2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–22414 Filed 9–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0097; Directorate 

Identifier 2011–NM–243–AD; Amendment 

39–17572; AD 2013–17–08] 

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) 2010–20– 

08, which applied to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2010–20–08 required 

repetitive inspections to find cracking of 

the web, strap, inner chords, inner 

chord angle of the forward edge frame 

of the number 5 main entry door 

cutouts; the frame segment between 

stringers 16 and 31; repair if necessary; 

and repetitive inspections for cracking 

of repairs. This new AD expands the 

previous fuselage areas that are 

inspected for cracking. This AD was 

prompted by multiple reports of 

cracking outside of the previous 

inspection areas and a report of a crack 

that initiated at the aft edge of the inner 

chord rather than initiating at a fastener 

location. We are issuing this AD to 

detect and correct such cracks, which 

could cause damage to the adjacent 

body structure and could result in 

depressurization of the airplane in 

flight. 

DATES: This AD is effective October 22, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 22, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 9, 2010 (75 FR 

61337, October 5, 2010). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 12, 2001 (66 FR 

41440, August 8, 2001). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, 

October 5, 2010) (‘‘AD 2010–20–08)’’. 

AD 2010–20–08 applied to the specified 

products. The NPRM published in the 

Federal Register on March 6, 2013 (78 

FR 14469). The NPRM proposed to 

require repetitive inspections to find 

cracking of the web, strap, inner chords, 

inner chord angle of the forward edge 

frame of the number 5 main entry door 

cutouts; the frame segment between 

stringers 16 and 31; repair if necessary; 

and repetitive inspections for cracking 

of repairs. The NPRM also proposed to 

expand the previous fuselage areas that 

are inspected for cracking. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

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