[Federal Register Volume 83, Number 108 (Tuesday, June 5, 2018)]
[Rules and Regulations]
[Pages 25885-25891]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11825]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1421; Product Identifier 2014-NM-177-AD; Amendment 
39-19302; AD 2018-11-14]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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 on airplanes with Aviation 
Partners Boeing winglets installed. This AD requires high frequency 
eddy current (HFEC) inspections for cracking of the lower outboard wing 
skin, and repair or modification if necessary. This AD also requires 
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. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective July 10, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 10, 
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.aviationpartnersboeing.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 on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1421.

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 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; phone and fax: 206-231-3528; email: 
[email protected].

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 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 a 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.
    We issued an SNPRM 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 SNPRM published in the Federal Register on 
November 27, 2017 (82 FR 55958). The SNPRM proposed adding new HFEC 
inspections for cracking of an expanded area of the lower outboard wing 
skin for certain airplanes.
    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 
SNPRM and the FAA's response to each comment. One commenter, Matt 
Leritz, supported the content of the SNRPM.

Request To Correct Compliance Time

    Aviation Partners Boeing (APB) and United Airlines (UAL) asked that 
we correct the compliance time in paragraphs (h)(2)(ii) and (h)(3)(ii) 
of the proposed AD (in the SNPRM). The commenters stated that those 
paragraphs would require the initial post-repair HFEC inspection of the 
lower wing skin at stringer L-6.5 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. The commenters 
added that the compliance time for the Part 3 HFEC inspection specified 
in paragraph 1.E. does not begin after doing the Part 2 repair, but 
instead begins after the initial issue of the service bulletin (after 
the effective date of the AD). UAL stated that, as written, this would 
require doing post-repair inspections on airplanes above the total 
flight-hour and flight-cycle threshold within 18 months after the 
effective date of the AD, regardless of if or when the repair was 
actually done. APB confirmed that the calendar-based compliance time in 
the referenced service information, for airplanes in Group 1, 
Configurations 2 and 3, and Groups 2 and 3, should be the same as for 
airplanes in Group 1, Configuration 1, on which the Part 2 repair has 
been done. The commenters asked that the compliance time for the Part 3 
HFEC inspection be corrected to the following: ``Within 6,000 flight 
cycles after doing the Part 2 repair, or within 18,000 flight hours 
since doing the Part 2 repair, whichever occurs first.''
    We agree with the commenters' request for the reasons provided. We 
have added paragraph (j)(3) of this AD to include this compliance-time 
exception.

Request To Remove a Certain Terminating Action

    Boeing asked that we remove the terminating action sentence at the 
end of paragraph (g)(2) of the proposed AD (in the SNPRM). Paragraph 
(g)(2) of the proposed AD (in the SNPRM) applies to Group 3 airplanes 
with external doublers, and if a crack is found it requires a repair 
using a method

[[Page 25886]]

approved by the FAA. That paragraph also specifies that ``[a]n approved 
repair terminates the repetitive inspections required by paragraph 
(g)(2) of this AD.'' Boeing stated that any repair for cracks found 
will require follow-on repetitive inspections, which would be approved 
as part of the AMOC repair approval process.
    We agree that the repairs for Group 3 airplanes will have an 
approved follow-on inspection program, but the repairs may apply to the 
cracked areas only. We do not agree with removing the terminating 
action provision because other areas may require the repetitive 
inspections specified in paragraph (g)(2) of this AD, for which 
approved terminating action would be appropriate. We have revised that 
sentence as follows: ``An approved repair terminates the repetitive 
inspections required by paragraph (g)(2) of this AD for the repaired 
area only.''

Request To Add Grace Period for Post-Repair (Modification) Inspections

    American Airlines (AAL), APB, UAL, and Delta Airlines (Delta) asked 
that we add a grace period for the proposed post-repair (modification) 
inspections.
    AAL stated that Table 4 of paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017, includes numerous inspections that are due within 
a specified number of flight hours or flight cycles after previous 
repair or modification of the airplane. AAL added that since it has 
completed many repairs and modifications using previous revisions of 
the referenced service information, there will be airplanes out of 
compliance with the AD requirements on the effective date because there 
is no grace period based on the AD due date.
    APB and Delta stated that paragraph (g) of the proposed AD (in the 
SNPRM) specifies compliance times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-
010, Revision 11, dated April 3, 2017, for initial post-repair 
inspections. APB added that the referenced service information added a 
flight-hour threshold of 90,000 total flight cycles to the existing 
flight-cycle threshold of 30,000 total flight cycles for the initial 
compliance time. APB noted that the grace period published in the 
referenced service information for airplanes on which the flight-hour 
or flight-cycle threshold has been reached is set to 18 months after 
accomplishment of the repair. APB stated that this creates a drop-dead 
inspection situation for airplanes on which either the flight-hour or 
flight-cycle threshold has been reached, and on which the Part 8 or 
Part 11 repair was accomplished over 18 months ago. Delta stated that 
the compliance table on pages (i) and (ii) of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, should 
be added to paragraph 1.E., ``Compliance'' and included in the AD.
    UAL stated that paragraph (g) of the proposed AD (in the SNPRM) 
would require the repetitive post-repair inspections specified in Parts 
9 and 13 of Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 11, dated April 3, 2017, in airplane total times or within 18 
months after accomplishment of Part 8 and 11 repairs, respectively. UAL 
is concerned that older airplanes on which the repair was done more 
than 18 months ago could be out of compliance on the effective date of 
the AD. UAL noted that the 18-month grace period covers the initial 
inspection, but does not cover post-repair inspections. UAL suggested 
that we provide similar relief for airplanes on which the threshold has 
been exceeded.
    We do not agree with the commenters' requests to add a grace 
period. The current revisions of the referenced service information 
provide a compliance time of 18 months for the initial inspection for 
all airplanes. The compliance times for certain conditional inspections 
are in terms of airplane threshold or time since accomplishment of the 
specified repair or modification. Those previously installed repairs or 
modifications may have been done using a version of Aviation Partners 
Boeing Service Bulletin AP767-57-010 before Revision 11 or alternative 
method, and may involve deviations, additional repair activity, and 
previous repairs. Under the provisions of paragraph (k) of this AD, we 
will consider requests for approval of AMOCs to extend the compliance 
time if sufficient data are submitted to substantiate that it would 
provide an acceptable level of safety. We have determined that each 
situation must be handled separately in the AMOC evaluation. We have 
not changed this AD in this regard.

Request To Add Compliance Tables to Certain Service Information

    Delta asked that a compliance table be added to Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, 
for airplanes on which the actions specified in Aviation Partners 
Boeing Service Bulletin AP767-57-010 have been previously accomplished. 
Delta noted that page i of Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 1, dated April 12, 2017, provides a compliance 
information table only for Group 3 airplanes; there are no tables for 
Groups 1 and 2 airplanes.
    We do not agree with the commenter's request. The compliance 
information table on page i of Aviation Partners Boeing Service 
Bulletin AP767-57-014, Revision 1, dated April 12, 2017, provides only 
a description of additional work, if any, necessary based on work 
accomplished using the previous revision. These tables are reference 
information only, and do not reflect all the actions required by the 
AD. The necessary compliance tables are provided in paragraph 1.E., 
``Compliance'' of Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 1, dated April 12, 2017. Therefore, we have not changed 
this AD in this regard.

Request To Clarify Group 4 Airplanes Not Affected

    UAL asked that we include a clarification in the proposed AD (in 
the SNPRM) that Group 4 airplanes are not affected. UAL stated that 
Group 4 airplanes are identified in the effectivity table in paragraph 
1.A. of Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 11, dated April 3, 2017. UAL noted that an equivalent change 
to the service information was incorporated during winglet installation 
with no additional work being necessary. UAL asked that we add 
paragraph (g)(3) to the AD to clarify that Group 4 airplanes are not 
affected by the requirements in the AD.
    We agree with the commenter for the reasons provided. Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 
3, 2017, specifies that an equivalent change has been incorporated in 
APB winglet retrofit kits for Group 4 airplanes, and that no more work 
is necessary on those airplanes. We have included a clarification in 
paragraph (g)(3) of this AD that specifies that Group 4 airplanes are 
not affected by the actions required by paragraph (g) of this AD.

Request To Remove an Airplane Having a Certain Line Number

    FedEx asked that we remove the airplane having line number 1027 
from the applicability in the proposed AD (in the SNPRM), or allow 
Aviation Partners Boeing Service Bulletin AP767-57-012, dated September 
2015, as an AMOC. FedEx stated that it will be modifying that airplane 
by removing the winglets and installing Boeing wing tips in accordance 
with Aviation Partners Boeing Service Bulletin AP767-57-012,

[[Page 25887]]

dated September 2015. FedEx anticipated that the modification will be 
completed prior to the effective date of the AD. FedEx added that the 
unsafe condition will be addressed when the winglets are removed.
    We do not agree with the commenter's request. There are many 
factors that led to the cracking of the lower wing skin, and the 
additional loading of the winglet is only one of those factors. Other 
contributory factors are design details with the added internal wing 
structure, which resulted in shortening the fatigue life of the blended 
winglet installation. We have not changed this AD in this regard.

Request Approval for Alternative Open Hole HFEC Inspection

    UAL asked that provisions be added to paragraph (g) of the proposed 
AD (in the SNPRM) to allow an alternative open-hole HFEC inspection 
procedure to inspect for cracking at the five inboard fastener 
locations. UAL stated that an open-hole HFEC inspection with the 
fasteners removed, in accordance with nondestructive test (NDT) Part 6, 
Chapter 51-00-16, using the same notch sensitivity provides an 
equivalent crack detection method. UAL added that APB has concurred 
with the inspection. UAL concluded that it has been performing the 
optional preventive modification, which trims out the skin containing 
the five fastener holes, and allows for the open-hole HFEC to be 
performed easily because the fasteners in the doubler are removed.
    We do not agree with the commenter's request. Although UAL 
developed an inspection method that works better for its situation, the 
HFEC inspection specified in the referenced service information is 
required by this AD to address all situations. However, under the 
provisions of paragraph (k) of this AD, we will consider requests for 
approval of AMOCs if sufficient data are submitted to substantiate that 
the open-hole HFEC inspection procedure provides an acceptable level of 
safety. We have not changed this AD in this regard.

Request To Clarify Credit for Previously Accomplished Repairs Approved 
by an Organization Designation Authorization (ODA)

    All Nippon Airways (ANA), AAL, APB, and Delta asked that we clarify 
credit in paragraph (i) of the proposed AD (in the SNPRM), for 
previously accomplished repairs approved by a Boeing ODA prior to June 
15, 2017.
    ANA stated that during discussions with the FAA, it was informed 
that repair deviations approved by Boeing ODAs prior to the FAA 
approval of the APB revised fatigue analysis issued on June 15, 2017, 
and the release of Aviation Partners Boeing Service Bulletins AP767-57-
010, Revision 11, AP767-57-013, Revision 1, and AP767-57-014, Revision 
1, do not qualify for AMOC credit to the AD after it is released. ANA 
added that the proposed AD (in the SNPRM) would provide AMOC credit for 
repair deviations approved by Boeing ODAs with 8100-9 forms dated after 
June 15, 2017, because the Boeing ODAs would be using the APB revised 
fatigue analysis.
    AAL stated that paragraph (i) of the proposed AD (in the SNPRM) 
specifies that repairs accomplished before June 15, 2017, and before 
the AD effective date approved by a Boeing ODA can be considered 
approved repairs in accordance with paragraphs (g) and (h) of the 
proposed AD (in the SNPRM). AAL added that Boeing has indicated through 
Multi-Operator Message MOM-MOM-17-0480-01B that repairs approved prior 
to June 15, 2017, can be re-evaluated and approved on a new 8100-9 
form. AAL noted that the language in paragraph (i) should be clarified 
to indicate that repairs accomplished prior to June 15, 2017, are also 
acceptable, as long as they have an 8100-9 approval from a Boeing ODA 
dated after June 15, 2017.
    APB requested that we clarify paragraph (i) of the proposed AD (in 
the SNPRM) to state that accomplishment of previous revisions of 
Aviation Partners Boeing Service Bulletins AP767-57-010 should be 
acceptable for credit for previously accomplished repairs and 
modifications of the lower outboard wing skin. APB stated that after 
the effective date of the AD, operators that did not seek relief for 
previously completed actions would need to request approval of AMOCs.
    Delta stated that paragraph (i) of the proposed AD (in the SNPRM) 
provides repair approval for repairs of the lower outboard wing skin 
done after June 15, 2017, and before the effective date of the AD, that 
are approved by the Boeing ODA authorized by the Manager, Seattle ACO 
Branch, are approved for the applicable repairs required by paragraphs 
(g) and (h) of the AD. Delta added that prior to issuance of the 
referenced service information, both inspection and repair instructions 
for stringers L-9.5 and L-6.5 were contained in Revisions 1, 2, 4, 6, 
7, 8, and 9 of Aviation Partners Boeing Service Bulletin AP767-57-010. 
Delta added that it has performed many inspections and repairs for 
stringers L-9.5 and L-6.5 with those revisions. Delta suggested that 
credit be provided for repairs approved by a Boeing 8100-9 or 
previously accomplished using Revisions 1, 2, 4, 6, 7, 8, and 9 of 
Aviation Partners Boeing Service Bulletin AP767-57-010. Delta added 
that AMOCs will have to be obtained for each approved 8100-9 if no 
credit is provided.
    We agree to clarify the language in paragraph (i) of this AD to 
include certain language provided by the commenters' for the reasons 
provided. We have clarified the language in paragraph (i) of this AD by 
adding that the ODA repairs approved after June 15, 2017, and before 
the effective date of this AD, will have post-installation inspection 
requirements in lieu of the post-inspection instructions specified 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.

Request To Correct Error in Service Information

    APB and UAL asked that we correct an error specified in Part 13 of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017.
    APB and UAL stated that paragraphs (g)(1)(i)(D)(2), 
(g)(1)(ii)(B)(2), and (g)(1)(iii)(B)(2) of the proposed AD (in the 
SNPRM) would require the post-repair HFEC inspection in accordance with 
Part 13 of the referenced service information. UAL stated that Part 13, 
Step 1.d., specifies repeating the Part 9 HFEC inspection; however, it 
should specify repeating the Part 13 HFEC inspection because Part 9 
applies to airplanes without the stringer replacement. UAL noted that 
the paragraphs in the proposed AD (in the SNPRM) correctly specify 
repeating the Part 13 HFEC inspection. UAL added that the steps in the 
referenced service information are listed as RC (required for 
compliance), and must be done to comply with the AD.
    We agree that the error exists in the service information. We have 
added an exception in paragraph (j)(4) of this AD that specifies 
repeating the Part 13 HFEC inspection instead of the Part 9 inspection.

Request To Provide Credit for Previous Service Information

    AAL, UAL, and United Parcel Service (UPS) asked that we provide 
credit for doing the modification required by paragraph (i) of the 
proposed AD (in the SNPRM) using previous revisions of the referenced 
service information. UAL and UPS noted that paragraph (i) of the

[[Page 25888]]

proposed AD (in the NPRM), which provided credit for previous actions 
using previous revisions of the referenced service information, was 
deleted in the SNPRM.
    We do not agree with the commenters' requests. No credit is given 
for previously installed repairs or modifications due to each situation 
being unique; therefore, a re-evaluation will have to be done and may 
involve additional work for certain airplanes. Under the provisions of 
paragraph (k) of this AD, we will consider requests for approval of 
AMOCs if sufficient data are submitted to substantiate that work done 
using previous revisions of the service information provides an 
acceptable level of safety. We have not changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule 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 
SNPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.
    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 AP767-57-010, 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, and repair (modification) of the 
stringer with external doubler/tripler; repetitive post-repair 
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 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
HFEC Inspections......................  6 work-hours x $85 per                $0            $510         $71,400
                                         hour = $510.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of the inspection. 
We have no way of determining the number of aircraft that might need 
these on-condition actions.

                                      Estimated Costs--On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Post-repair Inspections.......................  6 work-hours x $85 per hour =                 $0            $510
                                                 $510 per inspection cycle.
Repair/Modification...........................  262 work-hours x $85 per hour =                0          22,270
                                                 $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 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 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,

[[Page 25889]]

    (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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-11-14 The Boeing Company: Amendment 39-19302; Docket No. FAA-
2015-1421; Product Identifier 2014-NM-177-AD.

(a) Effective Date

    This AD is effective July 10, 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 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 
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 
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)(4) of this AD.
    (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-

[[Page 25890]]

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 
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 
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)(4) of this AD.
    (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 
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 
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)(4) of this AD.
    (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 
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 for the repaired area only.
    (3) Group 4 airplanes identified in Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, are 
not affected by the actions required by paragraph (g) of this AD.

(h) Repetitive Stringer L-6.5 Inspections, Repair (Modification), 
Repetitive Post-Repair 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) Except as required by paragraph (j)(3) of this AD: 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) Except as required by paragraph (j)(3) of this AD: At the 
applicable time specified

[[Page 25891]]

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 that were approved after 
June 15, 2017, and before the effective date of this AD, 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. The ODA repairs will have post-installation 
inspection requirements in lieu of the post-inspection instructions 
specified 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.

(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 ``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 ``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.
    (3) For Condition 1 and Condition 2 airplanes: Where paragraph 
1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 1, dated April 12, 2017, specifies a 
compliance time for accomplishing the Part 3 HFEC inspection of 18 
months ``after the initial issue date of this service bulletin,'' 
the required compliance time is 6,000 flight cycles or 18,000 flight 
hours, whichever occurs first, after doing the Part 2 repair.
    (4) For airplanes on which a stringer L-9.5 replacement was 
accomplished per Part 11 of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017: Where 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017, specifies repeating the post-repair HFEC 
inspection ``in Part 9,'' this AD requires repeating the post-repair 
HFEC inspection in Part 13.

(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) of this AD. Information may be 
emailed to: [email protected].
    (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

    For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle 
ACO Branch, 2200 South 216th St., Des Moines, WA; phone and fax: 
206-231-3528; email: [email protected].

(m) 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 AP767-57-010, 
Revision 11, dated April 3, 2017.
    (ii) Aviation Partners Boeing Service Bulletin AP767-57-014, 
Revision 1, dated April 12, 2017.
    (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/ibr-locations.html.

    Issued in Des Moines, Washington, on May 21, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11825 Filed 6-4-18; 8:45 am]
BILLING CODE 4910-13-P