Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33817 

Manager, International Section, Transport 

Standards Branch, FAA; or the EASA; or 

Airbus’s EASA DOA: Accomplish repetitive 

SDIs within the compliance time defined in 

those repair instructions for repetitive SDIs. 

If no compliance time is identified in the 

repair instructions for repetitive SDIs, 

accomplish the repetitive SDIs required by 

paragraph (i)(2) of this AD at the compliance 

times defined in figure 4 to paragraphs (i)(2) 

and (l) of this AD. 

(m) No Terminating Action 

Modification or repair of an airplane, as 

specified in paragraph (j) or (k) of this AD, 

does not constitute terminating action for the 

repetitive inspections required by this AD, 

unless it is specified otherwise in a repair 

method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the EASA; or Airbus’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(n) Reporting Requirement 

Submit a report of the positive findings of 

the inspections required by paragraphs (i) 

and (j) of this AD to ‘‘Airbus Service Bulletin 

Reporting Online Application’’ on Airbus 

World (https://w3.airbus.com/), at the 

applicable time specified in paragraph (n)(1) 

or (n)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Report within 

30 days after that inspection. 

(2) If the inspection was done before the 

effective date of this AD: Report within 30 

days after the effective date of this AD. 

(o) Other FAA AD Provisions 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards 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 International 

Section, send it to the attention of the person 

identified in paragraph (p)(2) of this AD. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Section, Transport 

Standards Branch, FAA; or the EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as specified in paragraph (k) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(4) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 1 work-hour per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at 800 Independence 

Ave. SW, Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0099, dated June 8, 2017, for related 

information. This MCAI may be found in the 

AD docket on the internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2017–1102. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3223. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(q) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–57–1178, 

Revision 03, including only Appendix 03, 

both dated November 29, 2016. 

(ii) Airbus Service Bulletin A320–57–1200, 

dated November 20, 2015. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, Rond-Point Emile Dewoitine 

No: 2, 31700 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. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on June 

12, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–13802 Filed 7–17–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0073; Product 

Identifier 2017–NM–100–AD; Amendment 

39–19318; AD 2018–13–06] 

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 767–300 

and –300F series airplanes. This AD was 

prompted by reports of fatigue cracking 

in the lower outboard wing skin at the 

farthest outboard fastener of the inboard 

segment of a certain stringer. This AD 

requires repetitive high frequency eddy 

current (HFEC) inspections for cracking 

of the lower outboard wing skin at the 

inboard segment of a certain stringer, 

and repair if necessary. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective August 22, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 22, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Aviation Partners Boeing, 2811 S 102nd 

Street, Suite 200, Seattle, WA 98168; 

telephone 206–762–1171; internet 

https://www.aviationpartners

boeing.com. You may view this service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 


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33818 Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0073. 

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–2018– 

0073; or in person at Docket Operations 

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 Docket 

Operations (phone: 800–647–5527) is 

Docket Operations, 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and 

fax: 206–231–3528; email: 

allen.rauschendorfer@faa.gov. 

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 The Boeing Company 

Model 767–300 and –300F series 

airplanes. The NPRM published in the 

Federal Register on February 9, 2018 

(83 FR 5738). The NPRM was prompted 

by reports of fatigue cracking in the 

lower outboard wing skin at the farthest 

outboard fastener of the inboard 

segment of stringer L–9.5 on airplanes 

with winglets installed per 

Supplemental Type Certificate 

ST01920SE. The NPRM proposed to 

require repetitive high frequency eddy 

current (HFEC) inspections for cracking 

of the lower outboard wing skin at the 

inboard segment of a certain stringer, 

and repair if necessary. We are issuing 

this AD to address fatigue cracking in 

the lower outboard wing skin, which 

could result in failure and subsequent 

separation of the wing and winglet and 

consequent reduced controllability of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. Aviation 

Partners Boeing (APB) concurred with 

the NPRM. 

Request To Provide Credit for 

Previously Approved Repairs 

All Nippon Airways (ANA) and 

American Airlines (AAL) asked that 

credit be given for repair deviations 

approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) using 8100–9 

forms dated after June 15, 2017. ANA 

stated that Boeing ODAs will be using 

APB analysis methodology to evaluate 

and approve the repairs. ANA and AAL 

stated that Boeing indicated in MultiOperator Message MOM–MOM–17– 

0480–01B, dated August 29, 2017, that 

repairs approved after June 15, 2017, 

would be acceptable as alternative 

methods of compliance (AMOCs) to the 

final rule if using the referenced service 

information. Both commenters asked 

that credit language for those previously 

approved repairs be added to the 

content of the proposed AD. 

We agree with the commenters’ 

requests for the reasons provided. The 

revised APB analysis methodology was 

approved by the FAA on June 15, 2017. 

Therefore, we have added paragraph 

(i)(2) to this AD to include that 

approval. 

Request To Allow Alternative Oversize 

Fastener Holes 

AAL asked that we allow oversize 

fasteners of at least 1/64 inch to be 

installed at all fastener locations 

common to inboard stringer L–9.5. AAL 

stated that the referenced service 

information and the APB modification 

drawing are very restrictive regarding 

oversize fasteners that are outside of the 

five critical fasteners at each end of 

inboard stringer L–9.5. AAL added that 

hole damage during fastener removal at 

the existing stringer L–9.5 is common. 

We do not agree with the commenter’s 

request. This type of deviation would 

require an engineering evaluation to 

assess inboard stringer L–9.5 and the 

skin fastener locations to determine if it 

is feasible for the oversize fasteners to 

be installed. However, under the 

provisions of paragraph (j) of this AD, 

we will consider requests for approval 

of an AMOC, if sufficient data are 

submitted to substantiate that installing 

1/64-inch oversize fasteners at all 

fastener locations common to inboard 

stringer L–9.5 will provide an 

acceptable level of safety. We have not 

changed this AD in this regard. 

Request To Add Alternative Alodine 

Type 

Delta Air Lines (Delta) asked that we 

add a new paragraph to the proposed 

AD specifying that Alodine coating 

‘‘Bonderite M–CR 600 Aero’’ is an 

acceptable alternative to ‘‘Alodine 600’’ 

coating. Delta stated that APB Service 

Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017, calls out Alodine 

600 in paragraph 2.B.2, ‘‘Parts and 

Materials Supplied by the Operator,’’ 

and in Drawing 767–9420, Sheet 1, in 

paragraph 3.B, Part 2, Steps 4 and 5, as 

an ‘‘RC’’ (Required for Compliance) 

step. Delta noted that the name of the 

Alodine coating ‘‘Alodine 600’’ has been 

changed to ‘‘Bonderite M–CR 600 

Aero.’’ Delta added that the FAA issued 

a Special Airworthiness Information 

Bulletin (SAIB) that cited an AMOC for 

the use of Bonderite products. 

We agree with the commenter’s 

request, for the reason provided. 

Alodine products made by Henkel 

manufacturing have been renamed to 

Bonderite. We issued SAIB HQ–18–09, 

dated February 5, 2018, which cited the 

AMOC that allows the use of Henkel 

Bonderite products as an alternative to 

Henkel Alodine products. We have 

revised paragraphs (g)(1)(ii)(A) and 

(g)(2)(i) of this AD to allow the use of 

Bonderite M–CR 600 Aero and 

Bonderite M–CR 600 RTU Aero as an 

alternative coating. 

Requests To Clarify Compliance Time 

Definition 

United Airlines (UAL) and Delta 

asked that we clarify the ‘‘Compliance 

Times’’ definition specified in the 

preamble of the NPRM. The commenters 

stated that the initial compliance time is 

defined as 1,500 flight cycles or 7,500 

flight cycles after winglet installation, 

but it should be 1,500 flight cycles or 

7,500 flight hours after winglet 

installation. The commenters noted that 

this should be corrected to be consistent 

with the compliance time specified in 

the referenced service information. 

We agree with the commenters that 

the compliance time definition in the 

NPRM is inaccurate, and should specify 

‘‘The initial compliance time is the later 

of: 1,500 flight cycles or 7,500 flight 

hours after winglet installation, 

whichever occurs first.’’ This language 

provided notice regarding compliance 

times that were specified in the 

referenced service information. The 

compliance time is correct in the 

referenced service information and does 

not conflict with this AD. Since that 

section of the preamble does not 

reappear in the final rule, no change to 

this AD is necessary. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the changes described 


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Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33819 

previously and minor editorial changes. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed APB Service Bulletin 

AP767–57–013, Revision 1, dated April 

11, 2017. The service information 

describes procedures for an HFEC 

inspection for cracking of the lower 

outboard wing skin at the inboard 

segment of stringer L–9.5, and oncondition actions that include repetitive 

HFEC inspections, a preventive 

modification (repair) that includes 

installing new stringers, repetitive postmodification (repair) HFEC inspections 

for cracking, and repair. 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 140 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS—REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

HFEC Inspections .................. 1 work-hour × $85 per hour = 

$85, per inspection cycle.

$0 $85, per inspection cycle ...... $11,900, per inspection cycle. 

ESTIMATED COSTS—ON-CONDITION ACTIONS

Action Labor cost Parts cost Cost per 

product 

Preventive Modification (Repair) ............................ 50 work-hours × $85 per hour = $4,250 ................ $0 $4,250. 

Post-modification (repair) Inspections .................... 1 work-hour × $85 per hour = $85, per inspection 

cycle.

0 $85, per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for on-condition repairs that 

might be necessary as a result of the 

post-modification (repair) inspections 

specified in this AD. 

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 available 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. 

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 and associated appliances to 

the Director of the System Oversight 

Division. 

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 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 adding 

the following new airworthiness 

directive (AD): 

2018–13–06 The Boeing Company: 

Amendment 39–19318; Docket No. 

FAA–2018–0073; Product Identifier 

2017–NM–100–AD. 


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33820 Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 

(a) Effective Date 

This AD is effective August 22, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–300 and -300F series airplanes, 

certificated in any category, with Aviation 

Partners Boeing winglets installed; as 

identified in Aviation Partners Boeing 

Service Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking in the lower outboard wing 

skin at the farthest outboard fastener of the 

inboard segment of stringer L–9.5 on 

airplanes with winglets installed per 

Supplemental Type Certificate ST01920SE. 

We are issuing this AD to address fatigue 

cracking in the lower outboard wing skin, 

which could result in failure and subsequent 

separation of the wing and winglet and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections, Preventive 

Modification (Repair), Repetitive PostModification (Repair) Inspections, and 

Repair 

At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017, except 

as required by paragraph (h) of this AD: Do 

a high frequency eddy current (HFEC) 

inspection for cracking of the lower outboard 

wing skin at the inboard segment of stringer 

L–9.5, in accordance with Part 1 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017. 

(1) For airplanes on which ‘‘Condition 1’’ 

is found, as defined in the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017, during any inspection 

required by the introductory text of 

paragraph (g) or paragraph (g)(1)(i) of this 

AD: Do the actions required by paragraph 

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

(i) Repeat the inspection specified in the 

introductory text of paragraph (g) of this AD 

thereafter at the applicable times specified in 

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

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017. 

(ii) Do the actions required by paragraphs 

(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD: 

(A) Before further flight, do the preventive 

modification in accordance with Part 2 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017. The 

use of Alodine 600–RTU, Henkel Bonderite 

M–CR 600 Aero, or Henkel Bonderite M–CR 

600 RTU Aero coating is an acceptable 

alternative to Alodine 600 coating. 

Note 1 to paragraph (g)(1)(ii)(A) of this AD: 

Guidance on identifying alternative Henkel 

Bonderite Alodine coatings can also be found 

in Special Airworthiness Information 

Bulletin (SAIB) HQ–18–09, dated February 5, 

2018. The SAIB may be viewed online at 

http://rgl.faa.gov/Regulatory_and_Guidance_

Library/rgSAIB.nsf/0/F87909D65FCE4BFA

8625822B005AE82A?OpenDocument&

Highlight=hq-18-09. 

(B) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017, do an 

HFEC inspection for cracking, in accordance 

with Part 3 of the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017; and repeat the 

inspection thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Aviation Partners Boeing Service Bulletin 

AP767–57–013, Revision 1, dated April 11, 

2017. 

(2) For airplanes on which ‘‘Condition 2’’ 

is found as defined in the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017, during any inspection 

required by the introductory text of 

paragraph (g) or paragraph (g)(1)(i) of this 

AD: Do the actions required by paragraph 

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

(i) Before further flight, repair in 

accordance with Part 2 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017. The 

use of Alodine 600–RTU, Henkel Bonderite 

M–CR 600 Aero, or Henkel Bonderite M–CR 

600 RTU Aero coating is an acceptable 

alternative to Alodine 600 coating. 

Note 2 to paragraph (g)(2)(i) of this AD: 

Guidance on identifying alternative Henkel 

Bonderite Alodine coatings can also be found 

in SAIB HQ–18–09, dated February 5, 2018. 

The SAIB may be viewed online at http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgSAIB.nsf/0/F87909D65

FCE4BFA8625822B005AE82A

?OpenDocument&Highlight=hq-18-09. 

(ii) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017, do an 

HFEC inspection for cracking, in accordance 

with Part 3 of the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017; and repeat the 

inspection thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Aviation Partners Boeing Service Bulletin 

AP767–57–013, Revision 1, dated April 11, 

2017. 

(3) If any crack is found during any 

inspection required by paragraph (g)(1)(ii)(B) 

or (g)(2)(ii) of this AD, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. Although Aviation 

Partners Boeing Service Bulletin AP767–57– 

013, Revision 1, dated April 11, 2017, 

specifies to contact Boeing for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair as specified in this paragraph. 

(h) Exception to Service Information 

Specifications 

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

Aviation Partners Boeing Service Bulletin 

AP767–57–013, Revision 1, dated April 11, 

2017, specifies a compliance time of ‘‘after 

the initial issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(i) Credit for Previous Actions 

(1) For Group 2 airplanes: This paragraph 

provides credit for the actions specified in 

Part 1 and Part 2 of the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–013, Revision 1, 

dated April 11, 2017, that are required by 

paragraph (g) of this AD, if those actions were 

performed before the effective date of this AD 

using Aviation Partners Boeing Service 

Bulletin AP767–57–013, dated November 30, 

2016. 

(2) Repairs of the lower outboard wing skin 

approved after June 15, 2017, and before the 

effective date of this AD, if approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

Branch, FAA, are approved for the applicable 

repairs required by paragraph (g) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (k) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-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, Seattle ACO 

Branch, FAA, 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) Except as required by paragraph (g)(3) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 


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Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33821 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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. 

(k) Related Information 

For more information about this AD, 

contact Allen Rauschendorfer, Aerospace 

Engineer, Airframe Section, FAA, Seattle 

ACO Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206–231– 

3528; email: allen.rauschendorfer@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Aviation Partners Boeing Service 

Bulletin AP767–57–013, Revision 1, dated 

April 11, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Aviation Partners Boeing, 

2811 S 102nd Street, Suite 200, Seattle, WA 

98168; telephone 206–762–1171; internet 

https://www.aviationpartnersboeing.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on June 

12, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–13362 Filed 7–17–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0111; Product 

Identifier 2017–NM–059–AD; Amendment 

39–19312; AD 2018–12–08] 

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) 2017–07– 

07, which applied to certain Airbus 

Model A330–200, A330–300, A340–200, 

and A340–300 series airplanes. AD 

2017–07–07 required repetitive 

inspections of certain fastener holes, 

and related investigative and corrective 

actions if necessary. This AD retains the 

requirements of AD 2017–07–07 and 

expands the applicability. This AD was 

prompted by a report of cracking at 

fastener holes located at frame (FR) 40 

on the lower shell panel junction. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 22, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 22, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; 

telephone: +33 5 61 93 36 96; fax: +33 

5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

internet: http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0111. 

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–2018– 

0111; 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 (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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax: 206–231–3229. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–07–07, 

Amendment 39–18845 (82 FR 18547, 

April 20, 2017) (‘‘AD 2017–07–07’’). AD 

2017–07–07 applied to certain Airbus 

Model A330–200, A330–300, A340–200, 

and A340–300 series airplanes with 

manufacturer serial numbers (MSN) 

0176 through 0915 inclusive. The 

NPRM published in the Federal 

Register on February 20, 2018 (83 FR 

7117). The NPRM was prompted by a 

report of cracking at fastener holes 

located at frame FR40 on the lower shell 

panel junction. The NPRM proposed to 

retain the requirements of AD 2017–07– 

07 and expand the applicability. We are 

issuing this AD to detect and correct 

cracking at FR40 on the lower shell 

panel junction; such cracking could lead 

to reduced structural integrity of the 

fuselage. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0063, 

dated April 12, 2017 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200, 

A330–300, and A340–200 series 

airplanes, and Model A340–312 and 

–313 airplanes. The MCAI states: 

During full scale fatigue test of the Frame 

(FR) 40 to fuselage skin panel junction, 

fatigue damage was found. Corrective actions 

consisted of in-service installation of an 

internal reinforcing strap on the related 

junction, as currently required by DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France AD 1999–448–126(B), which refers to 

Airbus Service Bulletin (SB) A340–53–4104 

Revision 02, and [DGAC] AD 2001–070(B), 

which refers to Airbus SB A330–53–3093 

Revision 04; retrofit improvement of internal 

reinforcing strap fatigue life through 

recommended Airbus SB A330–53–3145; and 


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