Airworthiness Directives; The Boeing Company Airplanes, 33817-33821 [2018-13362]
Download as PDF
<![CDATA[
Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations
Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or
Airbus’s EASA DOA: Accomplish repetitive
SDIs within the compliance time defined in
those repair instructions for repetitive SDIs.
If no compliance time is identified in the
repair instructions for repetitive SDIs,
accomplish the repetitive SDIs required by
paragraph (i)(2) of this AD at the compliance
times defined in figure 4 to paragraphs (i)(2)
and (l) of this AD.
(m) No Terminating Action
Modification or repair of an airplane, as
specified in paragraph (j) or (k) of this AD,
does not constitute terminating action for the
repetitive inspections required by this AD,
unless it is specified otherwise in a repair
method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or the EASA; or Airbus’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
amozie on DSK3GDR082PROD with RULES
(n) Reporting Requirement
Submit a report of the positive findings of
the inspections required by paragraphs (i)
and (j) of this AD to ‘‘Airbus Service Bulletin
Reporting Online Application’’ on Airbus
World (https://w3.airbus.com/), at the
applicable time specified in paragraph (n)(1)
or (n)(2) of this AD.
(1) If the inspection was done on or after
the effective date of this AD: Report within
30 days after that inspection.
(2) If the inspection was done before the
effective date of this AD: Report within 30
days after the effective date of this AD.
(o) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the manager of the International
Section, send it to the attention of the person
identified in paragraph (p)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as specified in paragraph (k) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
VerDate Sep<11>2014
17:26 Jul 17, 2018
Jkt 244001
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(4) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 1 work-hour per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at 800 Independence
Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0099, dated June 8, 2017, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–1102.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–57–1178,
Revision 03, including only Appendix 03,
both dated November 29, 2016.
(ii) Airbus Service Bulletin A320–57–1200,
dated November 20, 2015.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
33817
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on June
12, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–13802 Filed 7–17–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0073; Product
Identifier 2017–NM–100–AD; Amendment
39–19318; AD 2018–13–06]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–300
and –300F series airplanes. This AD was
prompted by reports of fatigue cracking
in the lower outboard wing skin at the
farthest outboard fastener of the inboard
segment of a certain stringer. This AD
requires repetitive high frequency eddy
current (HFEC) inspections for cracking
of the lower outboard wing skin at the
inboard segment of a certain stringer,
and repair if necessary. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective August 22,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 22, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Aviation Partners Boeing, 2811 S 102nd
Street, Suite 200, Seattle, WA 98168;
telephone 206–762–1171; internet
https://www.aviationpartners
boeing.com. You may view this service
information at the FAA, Transport
Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available
SUMMARY:
E:\FR\FM\18JYR1.SGM
18JYR1
33818
Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations
Request To Provide Credit for
Previously Approved Repairs
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0073.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0073; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
Docket Operations, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA,
Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and
fax: 206–231–3528; email:
allen.rauschendorfer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 767–300 and –300F series
airplanes. The NPRM published in the
Federal Register on February 9, 2018
(83 FR 5738). The NPRM was prompted
by reports of fatigue cracking in the
lower outboard wing skin at the farthest
outboard fastener of the inboard
segment of stringer L–9.5 on airplanes
with winglets installed per
Supplemental Type Certificate
ST01920SE. The NPRM proposed to
require repetitive high frequency eddy
current (HFEC) inspections for cracking
of the lower outboard wing skin at the
inboard segment of a certain stringer,
and repair if necessary. We are issuing
this AD to address fatigue cracking in
the lower outboard wing skin, which
could result in failure and subsequent
separation of the wing and winglet and
consequent reduced controllability of
the airplane.
amozie on DSK3GDR082PROD with RULES
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment. Aviation
Partners Boeing (APB) concurred with
the NPRM.
VerDate Sep<11>2014
17:26 Jul 17, 2018
Jkt 244001
All Nippon Airways (ANA) and
American Airlines (AAL) asked that
credit be given for repair deviations
approved by the Boeing Commercial
Airplanes Organization Designation
Authorization (ODA) using 8100–9
forms dated after June 15, 2017. ANA
stated that Boeing ODAs will be using
APB analysis methodology to evaluate
and approve the repairs. ANA and AAL
stated that Boeing indicated in MultiOperator Message MOM–MOM–17–
0480–01B, dated August 29, 2017, that
repairs approved after June 15, 2017,
would be acceptable as alternative
methods of compliance (AMOCs) to the
final rule if using the referenced service
information. Both commenters asked
that credit language for those previously
approved repairs be added to the
content of the proposed AD.
We agree with the commenters’
requests for the reasons provided. The
revised APB analysis methodology was
approved by the FAA on June 15, 2017.
Therefore, we have added paragraph
(i)(2) to this AD to include that
approval.
Request To Allow Alternative Oversize
Fastener Holes
AAL asked that we allow oversize
fasteners of at least 1/64 inch to be
installed at all fastener locations
common to inboard stringer L–9.5. AAL
stated that the referenced service
information and the APB modification
drawing are very restrictive regarding
oversize fasteners that are outside of the
five critical fasteners at each end of
inboard stringer L–9.5. AAL added that
hole damage during fastener removal at
the existing stringer L–9.5 is common.
We do not agree with the commenter’s
request. This type of deviation would
require an engineering evaluation to
assess inboard stringer L–9.5 and the
skin fastener locations to determine if it
is feasible for the oversize fasteners to
be installed. However, under the
provisions of paragraph (j) of this AD,
we will consider requests for approval
of an AMOC, if sufficient data are
submitted to substantiate that installing
1/64-inch oversize fasteners at all
fastener locations common to inboard
stringer L–9.5 will provide an
acceptable level of safety. We have not
changed this AD in this regard.
Request To Add Alternative Alodine
Type
Delta Air Lines (Delta) asked that we
add a new paragraph to the proposed
AD specifying that Alodine coating
‘‘Bonderite M–CR 600 Aero’’ is an
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
acceptable alternative to ‘‘Alodine 600’’
coating. Delta stated that APB Service
Bulletin AP767–57–013, Revision 1,
dated April 11, 2017, calls out Alodine
600 in paragraph 2.B.2, ‘‘Parts and
Materials Supplied by the Operator,’’
and in Drawing 767–9420, Sheet 1, in
paragraph 3.B, Part 2, Steps 4 and 5, as
an ‘‘RC’’ (Required for Compliance)
step. Delta noted that the name of the
Alodine coating ‘‘Alodine 600’’ has been
changed to ‘‘Bonderite M–CR 600
Aero.’’ Delta added that the FAA issued
a Special Airworthiness Information
Bulletin (SAIB) that cited an AMOC for
the use of Bonderite products.
We agree with the commenter’s
request, for the reason provided.
Alodine products made by Henkel
manufacturing have been renamed to
Bonderite. We issued SAIB HQ–18–09,
dated February 5, 2018, which cited the
AMOC that allows the use of Henkel
Bonderite products as an alternative to
Henkel Alodine products. We have
revised paragraphs (g)(1)(ii)(A) and
(g)(2)(i) of this AD to allow the use of
Bonderite M–CR 600 Aero and
Bonderite M–CR 600 RTU Aero as an
alternative coating.
Requests To Clarify Compliance Time
Definition
United Airlines (UAL) and Delta
asked that we clarify the ‘‘Compliance
Times’’ definition specified in the
preamble of the NPRM. The commenters
stated that the initial compliance time is
defined as 1,500 flight cycles or 7,500
flight cycles after winglet installation,
but it should be 1,500 flight cycles or
7,500 flight hours after winglet
installation. The commenters noted that
this should be corrected to be consistent
with the compliance time specified in
the referenced service information.
We agree with the commenters that
the compliance time definition in the
NPRM is inaccurate, and should specify
‘‘The initial compliance time is the later
of: 1,500 flight cycles or 7,500 flight
hours after winglet installation,
whichever occurs first.’’ This language
provided notice regarding compliance
times that were specified in the
referenced service information. The
compliance time is correct in the
referenced service information and does
not conflict with this AD. Since that
section of the preamble does not
reappear in the final rule, no change to
this AD is necessary.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
E:\FR\FM\18JYR1.SGM
18JYR1
Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
We reviewed APB Service Bulletin
AP767–57–013, Revision 1, dated April
11, 2017. The service information
describes procedures for an HFEC
inspection for cracking of the lower
outboard wing skin at the inboard
segment of stringer L–9.5, and oncondition actions that include repetitive
HFEC inspections, a preventive
modification (repair) that includes
installing new stringers, repetitive post-
33819
modification (repair) HFEC inspections
for cracking, and repair. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 140
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS—REQUIRED ACTIONS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
HFEC Inspections ..................
1 work-hour × $85 per hour =
$85, per inspection cycle.
$0
$85, per inspection cycle ......
$11,900, per inspection cycle.
ESTIMATED COSTS—ON-CONDITION ACTIONS
Action
Labor cost
Preventive Modification (Repair) ............................
Post-modification (repair) Inspections ....................
50 work-hours × $85 per hour = $4,250 ................
1 work-hour × $85 per hour = $85, per inspection
cycle.
amozie on DSK3GDR082PROD with RULES
We have received no definitive data
that would enable us to provide cost
estimates for on-condition repairs that
might be necessary as a result of the
post-modification (repair) inspections
specified in this AD.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all available costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
VerDate Sep<11>2014
18:48 Jul 17, 2018
Jkt 244001
Parts cost
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
$0
0
Cost per
product
$4,250.
$85, per inspection
cycle.
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–13–06 The Boeing Company:
Amendment 39–19318; Docket No.
FAA–2018–0073; Product Identifier
2017–NM–100–AD.
E:\FR\FM\18JYR1.SGM
18JYR1
33820
Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations
(a) Effective Date
This AD is effective August 22, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 767–300 and -300F series airplanes,
certificated in any category, with Aviation
Partners Boeing winglets installed; as
identified in Aviation Partners Boeing
Service Bulletin AP767–57–013, Revision 1,
dated April 11, 2017.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of
fatigue cracking in the lower outboard wing
skin at the farthest outboard fastener of the
inboard segment of stringer L–9.5 on
airplanes with winglets installed per
Supplemental Type Certificate ST01920SE.
We are issuing this AD to address fatigue
cracking in the lower outboard wing skin,
which could result in failure and subsequent
separation of the wing and winglet and
consequent reduced controllability of the
airplane.
amozie on DSK3GDR082PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections, Preventive
Modification (Repair), Repetitive PostModification (Repair) Inspections, and
Repair
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017, except
as required by paragraph (h) of this AD: Do
a high frequency eddy current (HFEC)
inspection for cracking of the lower outboard
wing skin at the inboard segment of stringer
L–9.5, in accordance with Part 1 of the
Accomplishment Instructions of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017.
(1) For airplanes on which ‘‘Condition 1’’
is found, as defined in the Accomplishment
Instructions of Aviation Partners Boeing
Service Bulletin AP767–57–013, Revision 1,
dated April 11, 2017, during any inspection
required by the introductory text of
paragraph (g) or paragraph (g)(1)(i) of this
AD: Do the actions required by paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the inspection specified in the
introductory text of paragraph (g) of this AD
thereafter at the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017.
(ii) Do the actions required by paragraphs
(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD:
(A) Before further flight, do the preventive
modification in accordance with Part 2 of the
Accomplishment Instructions of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017. The
use of Alodine 600–RTU, Henkel Bonderite
VerDate Sep<11>2014
17:26 Jul 17, 2018
Jkt 244001
M–CR 600 Aero, or Henkel Bonderite M–CR
600 RTU Aero coating is an acceptable
alternative to Alodine 600 coating.
Note 1 to paragraph (g)(1)(ii)(A) of this AD:
Guidance on identifying alternative Henkel
Bonderite Alodine coatings can also be found
in Special Airworthiness Information
Bulletin (SAIB) HQ–18–09, dated February 5,
2018. The SAIB may be viewed online at
https://rgl.faa.gov/Regulatory_and_Guidance_
Library/rgSAIB.nsf/0/F87909D65FCE4BFA
8625822B005AE82A?OpenDocument&
Highlight=hq-18-09.
(B) At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017, do an
HFEC inspection for cracking, in accordance
with Part 3 of the Accomplishment
Instructions of Aviation Partners Boeing
Service Bulletin AP767–57–013, Revision 1,
dated April 11, 2017; and repeat the
inspection thereafter at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Aviation Partners Boeing Service Bulletin
AP767–57–013, Revision 1, dated April 11,
2017.
(2) For airplanes on which ‘‘Condition 2’’
is found as defined in the Accomplishment
Instructions of Aviation Partners Boeing
Service Bulletin AP767–57–013, Revision 1,
dated April 11, 2017, during any inspection
required by the introductory text of
paragraph (g) or paragraph (g)(1)(i) of this
AD: Do the actions required by paragraph
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Before further flight, repair in
accordance with Part 2 of the
Accomplishment Instructions of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017. The
use of Alodine 600–RTU, Henkel Bonderite
M–CR 600 Aero, or Henkel Bonderite M–CR
600 RTU Aero coating is an acceptable
alternative to Alodine 600 coating.
Note 2 to paragraph (g)(2)(i) of this AD:
Guidance on identifying alternative Henkel
Bonderite Alodine coatings can also be found
in SAIB HQ–18–09, dated February 5, 2018.
The SAIB may be viewed online at https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgSAIB.nsf/0/F87909D65
FCE4BFA8625822B005AE82A
?OpenDocument&Highlight=hq-18-09.
(ii) At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Aviation
Partners Boeing Service Bulletin AP767–57–
013, Revision 1, dated April 11, 2017, do an
HFEC inspection for cracking, in accordance
with Part 3 of the Accomplishment
Instructions of Aviation Partners Boeing
Service Bulletin AP767–57–013, Revision 1,
dated April 11, 2017; and repeat the
inspection thereafter at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Aviation Partners Boeing Service Bulletin
AP767–57–013, Revision 1, dated April 11,
2017.
(3) If any crack is found during any
inspection required by paragraph (g)(1)(ii)(B)
or (g)(2)(ii) of this AD, repair before further
flight using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD. Although Aviation
Partners Boeing Service Bulletin AP767–57–
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
013, Revision 1, dated April 11, 2017,
specifies to contact Boeing for repair
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
requires repair as specified in this paragraph.
(h) Exception to Service Information
Specifications
Where paragraph 1.E., ‘‘Compliance,’’ of
Aviation Partners Boeing Service Bulletin
AP767–57–013, Revision 1, dated April 11,
2017, specifies a compliance time of ‘‘after
the initial issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(i) Credit for Previous Actions
(1) For Group 2 airplanes: This paragraph
provides credit for the actions specified in
Part 1 and Part 2 of the Accomplishment
Instructions of Aviation Partners Boeing
Service Bulletin AP767–57–013, Revision 1,
dated April 11, 2017, that are required by
paragraph (g) of this AD, if those actions were
performed before the effective date of this AD
using Aviation Partners Boeing Service
Bulletin AP767–57–013, dated November 30,
2016.
(2) Repairs of the lower outboard wing skin
approved after June 15, 2017, and before the
effective date of this AD, if approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, FAA, are approved for the applicable
repairs required by paragraph (g) of this AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (k) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, FAA, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (g)(3)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
E:\FR\FM\18JYR1.SGM
18JYR1
Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
For more information about this AD,
contact Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3528; email: allen.rauschendorfer@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Aviation Partners Boeing Service
Bulletin AP767–57–013, Revision 1, dated
April 11, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Aviation Partners Boeing,
2811 S 102nd Street, Suite 200, Seattle, WA
98168; telephone 206–762–1171; internet
https://www.aviationpartnersboeing.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on June
12, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–13362 Filed 7–17–18; 8:45 am]
amozie on DSK3GDR082PROD with RULES
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0111; Product
Identifier 2017–NM–059–AD; Amendment
39–19312; AD 2018–12–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2017–07–
07, which applied to certain Airbus
Model A330–200, A330–300, A340–200,
and A340–300 series airplanes. AD
2017–07–07 required repetitive
inspections of certain fastener holes,
and related investigative and corrective
actions if necessary. This AD retains the
requirements of AD 2017–07–07 and
expands the applicability. This AD was
prompted by a report of cracking at
fastener holes located at frame (FR) 40
on the lower shell panel junction. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 22,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 22, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France;
telephone: +33 5 61 93 36 96; fax: +33
5 61 93 45 80; email:
airworthiness.A330-A340@airbus.com;
internet: https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0111.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0111; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
VerDate Sep<11>2014
17:26 Jul 17, 2018
Jkt 244001
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
33821
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone: 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax: 206–231–3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2017–07–07,
Amendment 39–18845 (82 FR 18547,
April 20, 2017) (‘‘AD 2017–07–07’’). AD
2017–07–07 applied to certain Airbus
Model A330–200, A330–300, A340–200,
and A340–300 series airplanes with
manufacturer serial numbers (MSN)
0176 through 0915 inclusive. The
NPRM published in the Federal
Register on February 20, 2018 (83 FR
7117). The NPRM was prompted by a
report of cracking at fastener holes
located at frame FR40 on the lower shell
panel junction. The NPRM proposed to
retain the requirements of AD 2017–07–
07 and expand the applicability. We are
issuing this AD to detect and correct
cracking at FR40 on the lower shell
panel junction; such cracking could lead
to reduced structural integrity of the
fuselage.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0063,
dated April 12, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330–200,
A330–300, and A340–200 series
airplanes, and Model A340–312 and
–313 airplanes. The MCAI states:
During full scale fatigue test of the Frame
(FR) 40 to fuselage skin panel junction,
fatigue damage was found. Corrective actions
consisted of in-service installation of an
internal reinforcing strap on the related
junction, as currently required by DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France AD 1999–448–126(B), which refers to
Airbus Service Bulletin (SB) A340–53–4104
Revision 02, and [DGAC] AD 2001–070(B),
which refers to Airbus SB A330–53–3093
Revision 04; retrofit improvement of internal
reinforcing strap fatigue life through
recommended Airbus SB A330–53–3145; and
E:\FR\FM\18JYR1.SGM
18JYR1
]]>Agencies
[Federal Register Volume 83, Number 138 (Wednesday, July 18, 2018)]
[Rules and Regulations]
[Pages 33817-33821]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-13362]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0073; Product Identifier 2017-NM-100-AD; Amendment
39-19318; AD 2018-13-06]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 767-300 and -300F series airplanes. This AD
was prompted by reports of fatigue cracking in the lower outboard wing
skin at the farthest outboard fastener of the inboard segment of a
certain stringer. This AD requires repetitive high frequency eddy
current (HFEC) inspections for cracking of the lower outboard wing skin
at the inboard segment of a certain stringer, and repair if necessary.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective August 22, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 22,
2018.
ADDRESSES: For service information identified in this final rule,
contact Aviation Partners Boeing, 2811 S 102nd Street, Suite 200,
Seattle, WA 98168; telephone 206-762-1171; internet https://www.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
[[Page 33818]]
on the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0073.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0073; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is Docket Operations, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and fax: 206-231-3528; email:
[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 February 9, 2018 (83 FR 5738). The NPRM was
prompted by reports of fatigue cracking in the lower outboard wing skin
at the farthest outboard fastener of the inboard segment of stringer L-
9.5 on airplanes with winglets installed per Supplemental Type
Certificate ST01920SE. The NPRM proposed to require repetitive high
frequency eddy current (HFEC) inspections for cracking of the lower
outboard wing skin at the inboard segment of a certain stringer, and
repair if necessary. We are issuing this AD to address fatigue cracking
in the lower outboard wing skin, which could result in failure and
subsequent separation of the wing and winglet and consequent reduced
controllability of the airplane.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment. Aviation Partners Boeing
(APB) concurred with the NPRM.
Request To Provide Credit for Previously Approved Repairs
All Nippon Airways (ANA) and American Airlines (AAL) asked that
credit be given for repair deviations approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) using 8100-9
forms dated after June 15, 2017. ANA stated that Boeing ODAs will be
using APB analysis methodology to evaluate and approve the repairs. ANA
and AAL stated that Boeing indicated in Multi-Operator Message MOM-MOM-
17-0480-01B, dated August 29, 2017, that repairs approved after June
15, 2017, would be acceptable as alternative methods of compliance
(AMOCs) to the final rule if using the referenced service information.
Both commenters asked that credit language for those previously
approved repairs be added to the content of the proposed AD.
We agree with the commenters' requests for the reasons provided.
The revised APB analysis methodology was approved by the FAA on June
15, 2017. Therefore, we have added paragraph (i)(2) to this AD to
include that approval.
Request To Allow Alternative Oversize Fastener Holes
AAL asked that we allow oversize fasteners of at least 1/64 inch to
be installed at all fastener locations common to inboard stringer L-
9.5. AAL stated that the referenced service information and the APB
modification drawing are very restrictive regarding oversize fasteners
that are outside of the five critical fasteners at each end of inboard
stringer L-9.5. AAL added that hole damage during fastener removal at
the existing stringer L-9.5 is common.
We do not agree with the commenter's request. This type of
deviation would require an engineering evaluation to assess inboard
stringer L-9.5 and the skin fastener locations to determine if it is
feasible for the oversize fasteners to be installed. However, under the
provisions of paragraph (j) of this AD, we will consider requests for
approval of an AMOC, if sufficient data are submitted to substantiate
that installing 1/64-inch oversize fasteners at all fastener locations
common to inboard stringer L-9.5 will provide an acceptable level of
safety. We have not changed this AD in this regard.
Request To Add Alternative Alodine Type
Delta Air Lines (Delta) asked that we add a new paragraph to the
proposed AD specifying that Alodine coating ``Bonderite M-CR 600 Aero''
is an acceptable alternative to ``Alodine 600'' coating. Delta stated
that APB Service Bulletin AP767-57-013, Revision 1, dated April 11,
2017, calls out Alodine 600 in paragraph 2.B.2, ``Parts and Materials
Supplied by the Operator,'' and in Drawing 767-9420, Sheet 1, in
paragraph 3.B, Part 2, Steps 4 and 5, as an ``RC'' (Required for
Compliance) step. Delta noted that the name of the Alodine coating
``Alodine 600'' has been changed to ``Bonderite M-CR 600 Aero.'' Delta
added that the FAA issued a Special Airworthiness Information Bulletin
(SAIB) that cited an AMOC for the use of Bonderite products.
We agree with the commenter's request, for the reason provided.
Alodine products made by Henkel manufacturing have been renamed to
Bonderite. We issued SAIB HQ-18-09, dated February 5, 2018, which cited
the AMOC that allows the use of Henkel Bonderite products as an
alternative to Henkel Alodine products. We have revised paragraphs
(g)(1)(ii)(A) and (g)(2)(i) of this AD to allow the use of Bonderite M-
CR 600 Aero and Bonderite M-CR 600 RTU Aero as an alternative coating.
Requests To Clarify Compliance Time Definition
United Airlines (UAL) and Delta asked that we clarify the
``Compliance Times'' definition specified in the preamble of the NPRM.
The commenters stated that the initial compliance time is defined as
1,500 flight cycles or 7,500 flight cycles after winglet installation,
but it should be 1,500 flight cycles or 7,500 flight hours after
winglet installation. The commenters noted that this should be
corrected to be consistent with the compliance time specified in the
referenced service information.
We agree with the commenters that the compliance time definition in
the NPRM is inaccurate, and should specify ``The initial compliance
time is the later of: 1,500 flight cycles or 7,500 flight hours after
winglet installation, whichever occurs first.'' This language provided
notice regarding compliance times that were specified in the referenced
service information. The compliance time is correct in the referenced
service information and does not conflict with this AD. Since that
section of the preamble does not reappear in the final rule, no change
to this AD is necessary.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule with the changes described
[[Page 33819]]
previously and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
We reviewed APB Service Bulletin AP767-57-013, Revision 1, dated
April 11, 2017. The service information describes procedures for an
HFEC inspection for cracking of the lower outboard wing skin at the
inboard segment of stringer L-9.5, and on-condition actions that
include repetitive HFEC inspections, a preventive modification (repair)
that includes installing new stringers, repetitive post-modification
(repair) HFEC inspections for cracking, and repair. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 140 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs--Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
HFEC Inspections..................... 1 work-hour x $85 per $0 $85, per inspection $11,900, per inspection cycle.
hour = $85, per cycle.
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Estimated Costs--On-Condition Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Preventive Modification (Repair).... 50 work-hours x $85 $0 $4,250.
per hour = $4,250.
Post-modification (repair) 1 work-hour x $85 per 0 $85, per inspection cycle.
Inspections. hour = $85, per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for on-condition repairs that might be necessary as a
result of the post-modification (repair) inspections specified in this
AD.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all available costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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):
2018-13-06 The Boeing Company: Amendment 39-19318; Docket No. FAA-
2018-0073; Product Identifier 2017-NM-100-AD.
[[Page 33820]]
(a) Effective Date
This AD is effective August 22, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 767-300 and -300F
series airplanes, certificated in any category, with Aviation
Partners Boeing winglets installed; as identified in Aviation
Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated
April 11, 2017.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of fatigue cracking in the lower
outboard wing skin at the farthest outboard fastener of the inboard
segment of stringer L-9.5 on airplanes with winglets installed per
Supplemental Type Certificate ST01920SE. We are issuing this AD to
address fatigue cracking in the lower outboard wing skin, which
could result in failure and subsequent separation of the wing and
winglet and consequent reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections, Preventive Modification (Repair),
Repetitive Post-Modification (Repair) Inspections, and Repair
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-013, Revision 1, dated April 11, 2017, except as required by
paragraph (h) of this AD: Do a high frequency eddy current (HFEC)
inspection for cracking of the lower outboard wing skin at the
inboard segment of stringer L-9.5, in accordance with Part 1 of the
Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP767-57-013, Revision 1, dated April 11, 2017.
(1) For airplanes on which ``Condition 1'' is found, as defined
in the Accomplishment Instructions of Aviation Partners Boeing
Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017,
during any inspection required by the introductory text of paragraph
(g) or paragraph (g)(1)(i) of this AD: Do the actions required by
paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the inspection specified in the introductory text of
paragraph (g) of this AD thereafter at the applicable times
specified in paragraph 1.E., ``Compliance,'' of Aviation Partners
Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11,
2017.
(ii) Do the actions required by paragraphs (g)(1)(ii)(A) and
(g)(1)(ii)(B) of this AD:
(A) Before further flight, do the preventive modification in
accordance with Part 2 of the Accomplishment Instructions of
Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1,
dated April 11, 2017. The use of Alodine 600-RTU, Henkel Bonderite
M-CR 600 Aero, or Henkel Bonderite M-CR 600 RTU Aero coating is an
acceptable alternative to Alodine 600 coating.
Note 1 to paragraph (g)(1)(ii)(A) of this AD: Guidance on
identifying alternative Henkel Bonderite Alodine coatings can also
be found in Special Airworthiness Information Bulletin (SAIB) HQ-18-
09, dated February 5, 2018. The SAIB may be viewed online at https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSAIB.nsf/0/F87909D65FCE4BFA8625822B005AE82A?OpenDocument&Highlight=hq-18-09.
(B) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-013, Revision 1, dated April 11, 2017, do an HFEC inspection for
cracking, in accordance with Part 3 of the Accomplishment
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
013, Revision 1, dated April 11, 2017; and repeat the inspection
thereafter at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-013, Revision 1, dated April 11, 2017.
(2) For airplanes on which ``Condition 2'' is found as defined
in the Accomplishment Instructions of Aviation Partners Boeing
Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017,
during any inspection required by the introductory text of paragraph
(g) or paragraph (g)(1)(i) of this AD: Do the actions required by
paragraph (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Before further flight, repair in accordance with Part 2 of
the Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP767-57-013, Revision 1, dated April 11, 2017. The use of
Alodine 600-RTU, Henkel Bonderite M-CR 600 Aero, or Henkel Bonderite
M-CR 600 RTU Aero coating is an acceptable alternative to Alodine
600 coating.
Note 2 to paragraph (g)(2)(i) of this AD: Guidance on
identifying alternative Henkel Bonderite Alodine coatings can also
be found in SAIB HQ-18-09, dated February 5, 2018. The SAIB may be
viewed online at https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSAIB.nsf/0/F87909D65FCE4BFA8625822B005AE82A?OpenDocument&Highlight=hq-18-09.
(ii) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-013, Revision 1, dated April 11, 2017, do an HFEC inspection for
cracking, in accordance with Part 3 of the Accomplishment
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
013, Revision 1, dated April 11, 2017; and repeat the inspection
thereafter at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-013, Revision 1, dated April 11, 2017.
(3) If any crack is found during any inspection required by
paragraph (g)(1)(ii)(B) or (g)(2)(ii) of this AD, repair before
further flight using a method approved in accordance with the
procedures specified in paragraph (j) of this AD. Although Aviation
Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated
April 11, 2017, specifies to contact Boeing for repair instructions,
and specifies that action as ``RC'' (Required for Compliance), this
AD requires repair as specified in this paragraph.
(h) Exception to Service Information Specifications
Where paragraph 1.E., ``Compliance,'' of Aviation Partners
Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11,
2017, specifies a compliance time of ``after the initial issue date
of this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(i) Credit for Previous Actions
(1) For Group 2 airplanes: This paragraph provides credit for
the actions specified in Part 1 and Part 2 of the Accomplishment
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
013, Revision 1, dated April 11, 2017, that are required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Aviation Partners Boeing Service
Bulletin AP767-57-013, dated November 30, 2016.
(2) Repairs of the lower outboard wing skin approved after June
15, 2017, and before the effective date of this AD, if approved by
the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, are approved for the applicable repairs required by
paragraph (g) of this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (k) of this AD. Information may be
emailed to: [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 Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make those findings. To be
approved, the repair method, modification deviation, or alteration
deviation must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (g)(3) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (j)(4)(i) and
(j)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures
[[Page 33821]]
identified in an RC step, must be done to comply with the AD. If a
step or substep is labeled ``RC Exempt,'' then the RC requirement is
removed from that step or substep. An AMOC is required for any
deviations to RC steps, including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(k) Related Information
For more information about this AD, contact Allen
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and
fax: 206-231-3528; email: [email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Aviation Partners Boeing Service Bulletin AP767-57-013,
Revision 1, dated April 11, 2017.
(ii) Reserved.
(3) For service information identified in this AD, contact
Aviation Partners Boeing, 2811 S 102nd Street, Suite 200, Seattle,
WA 98168; telephone 206-762-1171; internet https://www.aviationpartnersboeing.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on June 12, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-13362 Filed 7-17-18; 8:45 am]
BILLING CODE 4910-13-P
