55958 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules 

paragraph (g) of this AD: Within 24 months 

after the effective date of this AD, modify the 

repair using a method approved by the 

Manager, International Section, Transport 

Standards Branch FAA; or EASA; or Airbus’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(k) Optional Terminating Action for 

Airplanes Post-Modification 20416 or PostModification 21999 

Modification of an airplane postmodification 20416 or post-modification 

21999 in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 2015, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for that airplane. 

(l) Post-Repair Actions for Certain Airplanes 

For an airplane that has been inspected per 

ALI task 531110 and repaired before the 

effective date of this AD using the 

instructions in an Airbus Repair Design 

Approval Sheet (RDAS): Within 30 days after 

the effective date of this AD, contact the 

Manager, International Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus’s EASA DOA for instructions and 

accomplish those instructions accordingly. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

Accomplishment of the instructions required 

by this paragraph, does not constitute 

terminating action for the repetitive 

inspections required by paragraph (g) of this 

AD for that airplane, unless specified 

otherwise in the instructions. 

(m) Partial Terminating Action for Airplanes 

Post-Modification 20416 or PostModification 21999 

For an airplane post-modification 20416 or 

post-modification 21999, modification in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1295, including Appendixes 01 and 02, 

dated June 29, 2015, for the applicable 

fastener holes, where no damage or cracks 

were detected (i.e., those not repaired) during 

the latest inspection as required by paragraph 

(g) of this AD, constitutes terminating action 

for the repetitive inspections of those fastener 

holes as required by paragraph (g) of this AD 

for that airplane. 

(n) Actions for Airplanes With Certain 

Repairs 

For an airplane that has been repaired 

before the effective date of this AD in the 

areas described in this AD using the 

instructions in an Airbus RDAS unrelated to 

ALI task 531110: Before exceeding the 

compliance times specified in table 1 to 

paragraph (g) of this AD or table 2 to 

paragraph (g) of this AD, as applicable, 

contact the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus’s EASA DOA for corrective action 

instructions and accomplish those 

instructions accordingly. If approved by the 

DOA, the approval must include the DOAauthorized signature. Accomplishment of 

corrective action(s) on an airplane, as 

required by this paragraph, does not 

constitute terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for that airplane, as applicable, 

unless specified otherwise in the 

instructions. 

(o) Terminating Action for ALI Tasks 

(1) Accomplishment of an inspection as 

required by paragraph (g) of this AD or 

instructions as required by paragraph (l) of 

this AD, as applicable, constitutes 

terminating action for the inspection 

requirements of ALI task 531110, for that 

airplane. 

(2) Modification of the two upper rows of 

fasteners of the crossbeam splicing at FR16 

and FR20 on both LH and RH sides of an 

airplane, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1295, including 

Appendixes 01 and 02, dated June 29, 2015, 

as specified in paragraphs (k) and (m) of this 

AD, constitutes terminating action for the 

inspection requirements of ALI task 531110, 

for those holes for that airplane. 

(p) No Reporting Requirement 

Although Airbus Service Bulletin A320– 

53–1286, Revision 01, dated December 22, 

2015, specifies to submit certain information 

to the manufacturer, and specifies that action 

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

does not include that requirement. 

(q) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1286, dated June 29, 2015. 

(r) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(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 (s)(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: 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 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 required by paragraphs (h)(1) and (p) 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. 

(s) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0139, dated 

July 14, 2016, 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– 

2017–1093. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–1405; fax 425–227–1149. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this 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. 

Issued in Renton, Washington, on 

November 7, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–25252 Filed 11–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1421; Product 

Identifier 2014–NM–177–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposal for certain The Boeing 

Company Model 767–300 and –300F 


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series airplanes. This action revises the 

notice of proposed rulemaking (NPRM) 

by adding new high frequency eddy 

current (HFEC) inspections for cracking 

of an expanded area of the lower 

outboard wing skin for certain airplanes. 

We are proposing this airworthiness 

directive (AD) to address the unsafe 

condition on these products. Since these 

actions would impose an additional 

burden over those in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these changes. 

DATES: The comment period for the 

NPRM published in the Federal 

Register on June 5, 2015 (80 FR 32066), 

is reopened. 

We must receive comments on this 

SNPRM by January 11, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this SNPRM, contact Aviation Partners 

Boeing, 2811 S. 102nd Street, Suite 200, 

Seattle, WA 98168; telephone 206–762– 

1171; Internet https://

www.aviationpartnersboeing.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. 

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–2015– 

1421; 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 SNPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Section, FAA, 

Seattle ACO Branch, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 

425–917–6450; fax: 425–917–6590; 

email: allen.rauschendorfer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–1421; Product Identifier 2014– 

NM–177–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this SNPRM. We will 

consider all comments received by the 

closing date and may amend this 

SNPRM because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this SNPRM. 

Discussion 

We issued an 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 June 5, 2015 (80 FR 

32066). The NPRM was prompted by 

reports of fatigue cracking on airplanes 

with Aviation Partners Boeing winglets 

installed. The NPRM proposed to 

require an HFEC inspection for cracking 

of the lower outboard wing skin, and 

repair or modification if necessary. The 

NPRM also proposed to require one of 

three follow-on actions: repeating the 

HFEC inspections; modifying certain 

internal stringers and oversizing and 

plugging the existing fastener holes of 

the lower wing; or modifying the 

external doubler/tripler and doing 

repetitive post-modification inspections. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, we have 

determined that new HFEC inspections 

for cracking of an expanded area of the 

lower outboard wing skin are necessary 

to address the identified unsafe 

condition for certain airplanes. 

Aviation Partners Boeing (APB) has 

released Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. In 

the NPRM, we refer to APB Service 

Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014, as the 

appropriate source of service 

information for accomplishing the 

proposed actions. APB Service Bulletin 

AP767–57–010, Revision 11, dated 

April 3, 2017, corrects certain errors and 

omissions that were in the 

Accomplishment Instructions of APB 

Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014, 

and provides clarification of certain 

procedures. APB Service Bulletin 

AP767–57–010, Revision 11, dated 

April 3, 2017, also removes all work 

related to stringer L–6.5 due to recent 

analysis that the modification was not 

sufficient to meet the 767 design service 

objective. 

In light of this analysis, new repetitive 

post-modification HFEC inspections 

have been added for airplanes on which 

the optional terminating modification of 

the existing skin or external skin 

doubler has been done. We have revised 

this proposed AD to refer to APB 

Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017, for 

accomplishing proposed actions for 

stringer L–9.5. 

APB has also released Service 

Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017. APB Service 

Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017, includes 

procedures for inspections, repair 

(modification), and repair of stringer L– 

6.5 of the lower outboard wing skin 

(which replace the actions that were 

removed from APB Service Bulletin 

AP767–57–010, Revision 11, dated 

April 3, 2017). 

Related Service Information Under 1 

CFR Part 51 

We reviewed APB Service Bulletin 

AP767–57–010, Revision 11, dated 

April 3, 2017. The service information 

describes procedures for an HFEC 

inspection for cracking of the external 

surface of the lower outboard wing skin 

at stringer L–9.5 and on-condition 

actions that include repetitive HFEC 

inspections; modification by oversizing 

and plugging the existing fastener holes 

of the wing skin; repair (modification) of 

the stringer with new stringer; repair 

(modification) of the stringer with 

external doubler/tripler; repetitive postrepair inspections for cracking; and 

repair. 

We also reviewed APB Service 

Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017. The service 

information describes procedures for an 

HFEC inspection for cracking of the 

lower outboard wing skin at stringer L– 

6.5 and on-condition actions that 

include repetitive HFEC inspections; 

repair (modification) of the stringer with 

new stringer; repetitive post-repair 


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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. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comments 

received. 

Request To Clarify Service Information 

and Actions in the Proposed AD 

Multiple commenters (United 

Airlines, Delta Air Lines, American 

Airlines, Japan Airlines, FedEx, Boeing) 

requested that the actions specified in 

APB Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014, be 

revised. Commenters noted that APB 

Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014, 

contained multiple errors. United 

Airlines, Delta Air Lines, American 

Airlines and Boeing also requested that 

the actions specified in the proposed 

AD be revised for clarity because certain 

language in the proposed AD did not 

match the language in APB Service 

Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014. APB stated 

APB Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014, is 

being revised to include corrections and 

clarifications and additional work. APB 

recommend that we refer to updated 

service information. 

We acknowledge the commenters’ 

request and have revised this SNPRM to 

refer to the updated service information 

in APB Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017, and 

APB Service Bulletin AP767–57–014, 

Revision 1, dated April 12, 2017. 

Request To Allow Previously Approved 

Repairs 

American Airlines, APB, and Boeing 

requested that we give credit for repairs 

in the subject area that had received 

8100–9 approval prior to the effective 

date of the AD. 

We agree to give credit for repairs that 

we have determined will address the 

identified unsafe condition. We 

replaced the content of paragraph (i) of 

the proposed AD (in the NPRM) with 

new content in this proposed AD to 

specify that repairs of the lower 

outboard wing skin done after June 15, 

2017, and before the effective date of 

this AD, that are approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that 

has been authorized by the Manager, 

Seattle ACO Branch, are approved for 

the applicable repairs required by 

paragraphs (g) and (h) of this AD. 

Request To Allow Previous 

Modifications 

Air New Zealand requested that we 

give credit for accomplishing the 

proposed modification before the 

effective date of the AD by adding the 

required service information to 

paragraph (i) of the proposed AD, which 

specifies credit for previous actions. 

We acknowledge the comment. 

However, no change to this proposed 

AD is necessary. Operators who 

accomplish the actions required by an 

AD using the required service 

information before the effective date of 

an AD are in compliance with the AD. 

Paragraph (f) of this proposed AD states 

‘‘comply with this AD within the 

compliance times specified, unless 

already done.’’ Credit for previous 

actions in ADs is used primarily to give 

credit for earlier revisions of required 

service information that are also 

acceptable for compliance if done before 

the effective date of the AD. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. Certain changes described 

above expand the scope of the NPRM. 

As a result, we have determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed 

Rule and the Service Information.’’ 

The compliance times vary depending 

on airplane configuration and 

inspection area. The shortest initial 

compliance time is the later of: 1,500 

flight cycles or 7,500 flight hours after 

winglet installation, whichever occurs 

first; or 18 months after the effective 

date of the AD. Except for one group of 

airplanes, the longest initial compliance 

time is the later of: 7,800 flight cycles 

or 23,400 flight hours after installation 

of a certain modification, whichever 

occurs first; or 18 months after the 

effective date of the AD. For one group 

of airplanes, the longest initial 

compliance time is 29,000 total flight 

cycles or 111,000 total flight hours, 

whichever occurs first. 

The shortest repetitive interval is 

1,500 flight cycles or 7,500 flight hours, 

whichever occurs first. The longest 

repetitive interval is 12,000 flight cycles 

or 36,000 flight hours, whichever occurs 

first. 

Differences Between Proposed Rule and 

Service Information 

APB Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017, and 

APB Service Bulletin AP767–57–014, 

Revision 1, dated April 12, 2017, specify 

to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes ODA whom we 

have authorized to make those findings. 

Table 5a of paragraph 1.E., 

‘‘Compliance,’’ of APB Service Bulletin 

AP767–57–010, Revision 11, dated 

April 3, 2017, does not provide a grace 

period for airplanes that have exceeded 

a certain compliance time. We have 

added a grace period of 6 months to 

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

Costs of Compliance 

We estimate that this proposed AD 

affects 140 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS—REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

HFEC Inspections ................... 6 work-hours × $85 per hour = $510 ..................................... $0 $510 $71,400 


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We estimate the following costs to do 

any necessary on-condition actions that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

aircraft that might need these oncondition actions. 

ESTIMATED COSTS—ON-CONDITION ACTIONS

Action Labor cost Parts cost Cost per 

product 

Post-repair Inspections .................... 6 work-hours × $85 per hour = $510 per inspection cycle ....................... $0 $510 

Repair/Modification .......................... 262 work-hours × 85 per hour = 22,270 ................................................... 0 22,270 

We have received no definitive data 

that would enable us to provide cost 

estimates for on-condition repairs for 

the post-repair inspections specified in 

this proposed 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 

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 proposed 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 determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

The Boeing Company: Docket No. FAA– 

2015–1421; Product Identifier 2014–NM– 

177–AD. 

(a) Comments Due Date 

We must receive comments by January 11, 

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 AP767–57–010, Revision 11, 

dated April 3, 2017; and Aviation Partners 

Boeing Service Bulletin AP767–57–014, 

Revision 1, dated April 12, 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 inboard fastener of stringer L–9.5, 

and the lower outboard wing skin of stringer 

L–6.5, on airplanes with winglets installed 

per Supplemental Type Certificate 

ST01920SE. We are issuing this AD to 

prevent 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 Stringer L–9.5 Inspections, 

Modification, Repair (Modification), 

Repetitive Post-Repair Inspections, and 

Repair 

(1) For Group 1 and Group 2 airplanes 

identified in Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017: At the applicable time 

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

Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 11, dated April 3, 

2017, except as required by paragraph (j)(1) 

of this AD: Do a high frequency eddy current 

(HFEC) inspection for cracking of the lower 

outboard wing skin at stringer L–9.5, in 

accordance with Part 1 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

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

is found, as defined in the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017, during any inspection 

required by paragraph (g)(1) or (g)(1)(i)(A) of 

this AD: Do the applicable actions required 

by paragraph (g)(1)(i)(A), (g)(1)(i)(B), 

(g)(1)(i)(C), or (g)(1)(i)(D) of this AD. 

(A) Repeat the inspection specified in 

paragraph (g)(1) of this AD thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017. 

(B) Do the applicable actions required by 

paragraphs (g)(1)(i)(B)(1), (g)(1)(i)(B)(2), and 

(g)(1)(i)(B)(3) of this AD. 

(1) Before further flight, do actions 

(modifications and repair (modification)) in 


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accordance with Part 2, Part 3, Part 4, and 

Part 5, as applicable, of the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017. 

(2) For airplanes on which the repair 

(modification) specified in Part 5 of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010 was done: At the applicable time 

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

Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 11, dated April 3, 

2017, do a post-repair HFEC inspection for 

cracking, in accordance with Part 12 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(i)(B)(2) of this AD, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(C) Do the actions required by paragraphs 

(g)(1)(i)(C)(1) and (g)(1)(i)(C)(2) of this AD, 

and do all applicable actions required by 

paragraph (g)(1)(i)(C)(3) of this AD. 

(1) Before further flight, repair (modify) in 

accordance with Part 8 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

(2) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, do a 

post-repair HFEC inspection for cracking, in 

accordance with Part 9 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in in paragraph 

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

Boeing Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(i)(C)(2) of this AD, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(D) Do the actions required by paragraphs 

(g)(1)(i)(D)(1) and (g)(1)(i)(D)(2) of this AD, 

and do all applicable actions required by 

paragraph (g)(1)(i)(D)(3) of this AD. 

(1) Before further flight, repair (modify) in 

accordance with Part 11 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

(2) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, do a 

post-repair HFEC inspection for cracking, in 

accordance with Part 13 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in in paragraph 

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

Boeing Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(i)(D)(2) of this AD, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

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

is found, as defined in the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017, during any inspection 

required by paragraph (g)(1) or (g)(1)(i)(A) of 

this AD: Do the actions required by 

paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this 

AD. 

(A) Do the actions required by paragraphs 

(g)(1)(ii)(A)(1) and (g)(1)(ii)(A)(2) of this AD, 

and do all applicable actions required by 

paragraph (g)(1)(ii)(A)(3) of this AD. 

(1) Before further flight, repair (modify) in 

accordance with Part 8 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

(2) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, do a 

post-repair HFEC inspection for cracking, in 

accordance with Part 9 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in in paragraph 

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

Boeing Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(ii)(A)(2) of this AD, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(B) Do the actions required by paragraphs 

(g)(1)(ii)(B)(1) and (g)(1)(ii)(B)(2) of this AD, 

and do all applicable actions required by 

paragraph (g)(1)(ii)(B)(3) of this AD. 

(1) Before further flight, repair (modify) in 

accordance with Part 11 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

(2) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, do a 

post-repair HFEC inspection for cracking, in 

accordance with Part 13 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in in paragraph 

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

Boeing Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(ii)(B)(2) of this AD, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(iii) For airplanes on which ‘‘Condition 3’’ 

is found, as defined in the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017, during the actions 

specified in paragraph (g)(1)(i)(B)(1) of this 

AD: Do the actions required by paragraph 

(g)(1)(iii)(A) or (g)(1)(iii)(B) of this AD. 

(A) Do the actions required by paragraphs 

(g)(1)(iii)(A)(1) and (g)(1)(iii)(A)(2) of this AD, 

and do all applicable actions required by 

paragraph (g)(1)(iii)(A)(3) of this AD. 

(1) Before further flight, repair (modify) in 

accordance with Part 8 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

(2) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, do a 

post-repair HFEC inspection for cracking, in 

accordance with Part 9 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in in paragraph 

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

Boeing Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(iii)(A)(2) of this AD, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(B) Do the actions required by paragraphs 

(g)(1)(iii)(B)(1) and (g)(1)(iii)(B)(2) of this AD, 

and do all applicable actions required by 

paragraph (g)(1)(iii)(B)(3) of this AD. 

(1) Before further flight, repair (modify) in 

accordance with Part 11 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. 

(2) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, do a 

post-repair HFEC inspection for cracking, in 

accordance with Part 13 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017; and 

repeat the inspection thereafter at the 

applicable times specified in in paragraph 

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

Boeing Service Bulletin AP767–57–010, 

Revision 11, dated April 3, 2017. 

(3) If any crack is found during any 

inspection required by paragraph 

(g)(1)(iii)(B)(2) of this AD, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(iv) For airplanes on which ‘‘Condition 4’’ 

is found, as defined in the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017, during any action 

specified in paragraph (g)(1)(i)(C)(1), 

(g)(1)(i)(D)(1), (g)(1)(ii)(A)(1), (g)(1)(ii)(B)(1), 

(g)(1)(iii)(A)(1), and (g)(1)(iii)(B)(1) of this 

AD: Repair before further flight using a 

method approved in accordance with the 


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procedures specified in paragraph (k) of this 

AD. 

(2) For Group 3 airplanes identified in 

Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 11, dated April 3, 

2017: At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017, or 

within 6 months after the effective date of 

this AD, whichever occurs later, do an HFEC 

inspection for cracking of the lower outboard 

wing skin at stringer L–9.5, in accordance 

with Part 7 of the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 11, 

dated April 3, 2017. Repeat the inspection 

thereafter at the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 11, dated April 3, 2017. If any 

cracking is found during any inspection, 

repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. An 

approved repair terminates the repetitive 

inspections required by paragraph (g)(2) of 

this AD. 

(h) Repetitive Stringer L–6.5 Inspections, 

Repair (Modification), Repetitive PostRepair Inspections, and Repair 

(1) For airplanes identified in Boeing 

Service Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017: At the applicable time 

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

Aviation Partners Boeing Service Bulletin 

AP767–57–014, Revision 1, dated April 12, 

2017, except as required by paragraph (j)(2) 

of this AD: Do an HFEC inspection for 

cracking of stringer L–6.5 of the lower 

outboard wing skin, in accordance with Part 

1 of Aviation Partners Boeing Service 

Bulletin AP767–57–014, Revision 1, dated 

April 12, 2017. If no cracking is found, repeat 

the inspection thereafter at the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017, except as provided by 

paragraph (h)(3) of this AD. 

(2) If any crack is found during any 

inspection required by paragraph (h)(1) of 

this AD, do the actions required by 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD, 

and do all applicable actions required by 

paragraph (h)(2)(iii) of this AD. 

(i) Before further flight, repair (modify) 

stringer L–6.5, in accordance with Part 2 of 

the Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

014, Revision 1, dated April 12, 2017. 

(ii) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

014, Revision 1, dated April 12, 2017, except 

as required by paragraph (j)(2) of this AD, do 

an HFEC post-repair inspection for cracking, 

in accordance with Part 3 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

014, Revision 1, dated April 12, 2017, and 

repeat the inspection thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017. 

(iii) If any crack is found during any 

inspection required by paragraph (h)(2)(ii) of 

this AD, repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(3) As an option to the repetitive 

inspections required by paragraph (h)(1) of 

this AD, do the actions required by 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, 

and do all applicable actions required by 

paragraph (h)(3)(iii) of this AD. 

(i) Before further flight after accomplishing 

the most recent inspection required by 

paragraph (h)(1) of this AD, repair (modify) 

stringer L–6.5, in accordance with Part 2 of 

the Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

014, Revision 1, dated April 12, 2017. 

(ii) At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

014, Revision 1, dated April 12, 2017, except 

as required by paragraph (j)(2) of this AD, do 

a post-repair HFEC inspection for cracking, 

in accordance with Part 3 of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

014, Revision 1, dated April 12, 2017, and 

repeat the inspection thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–014, Revision 1, 

dated April 12, 2017. 

(iii) If any crack is found during any 

inspection required by paragraph (h)(3)(ii) of 

this AD, repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(i) Repair Approval 

Repairs of the lower outboard wing skin 

done after June 15, 2017, and before the 

effective date of this AD, that are approved 

by the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO Branch, are approved 

for the applicable repairs required by 

paragraphs (g) and (h) of this AD. 

(j) Exceptions to Service Information 

Specifications 

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

Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 11, dated April 3, 

2017, specifies a compliance time of ‘‘after 

the issue date of Revision 11 of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Aviation Partners Boeing Service Bulletin 

AP767–57–014, Revision 1, dated April 12, 

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. 

(k) 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 (l)(1) of 

this AD. Information may be emailed to: 9– 

ANM-Seattle-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 ODA that has been 

authorized by the Manager, Seattle 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) Except as required by paragraphs 

(g)(1)(i)(B)(3), (g)(1)(i)(C)(3), (g)(1)(i)(D)(3), 

(g)(1)(ii)(A)(3), (g)(1)(ii)(B)(3), (g)(1)(iii)(A)(3), 

(g)(1)(iii)(B)(3), (g)(1)(iv), (g)(2), (h)(2)(iii), 

and (h)(3)(iii) of this AD: For service 

information that contains steps that are 

labeled as Required for Compliance (RC), the 

provisions of paragraphs (k)(4)(i) and 

(k)(4)(ii) of this AD 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. 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Allen Rauschendorfer, Aerospace 

Engineer, Airframe Section, FAA, Seattle 

ACO Branch, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6450; fax: 425–917–6590; email: 

allen.rauschendorfer@faa.gov. 

(2) 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. 

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. 

Issued in Renton, Washington, on 

November 3, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–24502 Filed 11–24–17; 8:45 am] 

BILLING CODE 4910–13–P 


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