Airworthiness Directives; the Boeing Company Airplanes, 57049-57053 [2013-22414]
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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
or No. AS355–65.00.22, both Revision 0 and
both dated May 18, 2011, as applicable for
your model helicopter.
(2) Strip the paint from the TGB control
lever attachment yokes, as depicted in Figure
2, item (z), of the ASB No. AS350–65.00.46
or No. AS355–65.00.22, as applicable to your
model helicopter.
(3) Perform a Fluorescent Penetrant
Inspection (FPI) in accordance with
paragraph 3.B.2 of ASB No. AS350–65.00.46
or No. AS355–65.00.22, as applicable to your
model helicopter, on the TGB control lever
attachment yokes for a crack. You are only
required to follow the actions defined in this
ASB paragraph pertaining to the FPI.
(4) If a crack exists, before further flight,
replace the TGB with an airworthy TGB.
(5) If there is no crack, clean the inspected
area and apply chemical conversion coating
(Alodine 1200 or equivalent), Epoxy primer,
and top coat paint.
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on July 26,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–22295 Filed 9–16–13; 8:45 am]
BILLING CODE 4910–13–P
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone 817–222–
5328; email robert.grant@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
DEPARTMENT OF TRANSPORTATION
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2011–0104, dated May 27, 2011. You may
view the EASA AD at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2013–0119.
SUMMARY:
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(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6520, Tail Rotor Gearbox.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No.
AS350–65.00.46, Revision 0, dated May 18,
2011.
(ii) Eurocopter Alert Service Bulletin No.
AS355–65.00.22, Revision 0, May 18, 2011.
(3) For Eurocopter service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://www.eurocopter.com/
techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0301; Directorate
Identifier 2013–NM–025–AD; Amendment
39–17575; AD 2013–18–02]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–200,
–300, –300F, and –400ER series
airplanes. This AD was prompted by
reports of cracked and corroded nuts on
an outboard flap support rib. This AD
requires, for certain airplanes, repetitive
inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, and related
investigative and corrective actions if
necessary. For certain other airplanes,
this AD also requires repetitive
inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, related
investigative and corrective actions if
necessary, and if necessary, a detailed
inspection to determine the nut type
installed in the outboard flap support
rib and corrective actions. This AD also
provides terminating action for the
repetitive inspections under certain
conditions. We are issuing this AD to
detect and correct cracked and corroded
nuts and bolts and the installation of
incorrect nuts on certain outboard flap
support ribs, which could lead to
additional nut and bolt damage in the
joint, result in loss of an outboard flap,
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57049
and adversely affect continued safe
flight and landing of the airplane.
DATES: This AD is effective October 22,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 22, 2013.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: 425–
917–6577; fax: 425–917–6590; email:
berhane.alazar@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM published in the Federal
Register on April 10, 2013 (78 FR
21276). The NPRM proposed to require,
for certain airplanes, repetitive
inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, related
investigative and corrective actions if
necessary, and replacement of all
fasteners in the support ribs, which
terminates the repetitive inspections.
For certain other airplanes, the NPRM
proposed to require repetitive
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inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, related
investigative and corrective actions if
necessary, and if necessary, a detailed
inspection to determine the nut type
installed in the outboard flap support
rib and corrective actions. For those
airplanes, the NPRM also proposed to
provide for optional replacement of all
fasteners in the support ribs, which
would terminate the repetitive
inspections.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (78 FR 21276,
April 10, 2013) and the FAA’s response
to each comment.
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Request To Refer to Revised Service
Information
Japan Airlines, UPS, and Boeing
stated that Boeing has issued revised
service information and requested that
the service information referenced in
the NPRM (78 FR 21276, April 10, 2013)
be updated to refer to Boeing Service
Bulletin 767–57A0131, Revision 1,
dated May 8, 2013.
We agree with the commenters’
requests and have revised paragraphs
(c), (g), (h), (i), and (j) of this final rule
to include Boeing Service Bulletin 767–
57A0131, Revision 1, dated May 8,
2013. We have also added a new
paragraph (k) of this AD to provide
credit for actions accomplished before
the effective date of this AD using
Boeing Alert Service Bulletin 767–
57A0131, dated October 30, 2012, and
reidentified the subsequent paragraphs.
Clarification Regarding the Installation
of Winglets
Aviation Partners Boeing and UPS
stated that the installation of winglets
per Supplemental Type Certificate
(STC) ST01920SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) does not affect
the accomplishment of the
manufacturer’s service instructions.
We agree with the commenters’
statements that the installation of
winglets as specified in STC ST01920SE
(https://rgl.faa.gov/Regulatory_and_
Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) does not affect
accomplishment of the requirements of
this AD, and for airplanes on which STC
ST01920SE is installed, a ‘‘change in
product’’ AMOC approval request is not
necessary to comply with the
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requirements of section 39.17 of the
Federal Aviation Regulations (14 CFR
39.17). We have added this provision in
new paragraph (c)(2) of this final rule.
Request To Correct a Reference to a
Table Number
UPS noted a typographical error in
paragraph (h)(1)(i) of the NPRM (78 FR
21276, April 10, 2013). The inspection
intervals are identified in table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 767–57A0131, Revision
1, dated May 8, 2013, and the NPRM
erroneously referred to table 1.
We agree there is an error and have
revised paragraph (h)(1)(i) of this AD to
refer to table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service
Bulletin 767–57A0131, Revision 1,
dated May 8, 2013.
Request To Clarify Terminating Action
UPS noted that paragraph (i) of the
NPRM (78 FR 21276, April 10, 2013)
implies that the only terminating action
for the repetitive inspections proposed
by paragraph (h) of the NPRM is
replacement of all fasteners within a
support rib. UPS stated that the Boeing
service information provides
terminating action by replacing
fasteners at all discrepant or corroded
locations and/or the verification of
correct nut type at all other locations.
UPS requested that these corrective
actions be identified as terminating
action for the inspections proposed by
paragraph (h) of the NPRM for the
associated support rib.
We agree that clarification is needed
regarding terminating action for the
repetitive inspections required by
paragraph (h) of this final rule. We have
changed the header of paragraph (i) of
this final rule to ‘‘Terminating Action
for Repetitive Inspections’’ and split the
paragraph into three subparagraphs.
Paragraph (i)(1) of this final rule states
that, if during any inspection required
by paragraphs (g) or (h) of this AD, any
cracking is found, all fasteners within a
support rib must be replaced to
terminate the repetitive inspections for
that support rib only. New paragraph
(i)(2) of this final rule states that if a
discrepancy other than cracking is
found (e.g., corrosion) during any
inspection required by paragraph (g) of
this final rule, all fasteners within a
support rib must be replaced to
terminate the repetitive inspections for
that support rib only. New paragraph
(i)(3) of this final rule states that if a
discrepancy other than cracking is
found (e.g., corrosion) during any
inspection required by paragraph (h) of
this final rule, replacing the affected
fastener terminates the repetitive
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inspections for only that fastener within
that support rib.
Request To Combine Paragraphs (h)(1)
and (h)(2) of the NPRM (78 FR 21276,
April 10, 2013)
UPS stated that the intent of
paragraph (h) of the NPRM (78 FR
21276, April 10, 2013) is to identify the
requirements of the initial inspection,
and the intent of paragraphs (h)(1) and
(h)(2) of the NPRM is to identify the
requirements of the repetitive
inspections based on the findings of the
initial inspection. UPS stated that the
investigative and corrective actions
applicable to paragraph (h)(1) of the
NPRM are the same as those in
paragraph (h)(2) of the NPRM and
suggested that these two paragraphs
could be combined without affecting the
intent of this AD.
We do not agree that paragraphs (h)(1)
and (h)(2) of this final rule can be
combined. Paragraph (h)(1) of this final
rule describes actions based on the
findings of the cap seal detailed
inspections, and paragraph (h)(2) of this
final rule addresses actions based on the
findings of the inspections for the nuts,
bolts, and washers on the support ribs.
We have not changed this final rule in
this regard.
Request To Change Compliance Time
for Initial Detailed Inspection
UPS requested that the threshold for
conducting the initial detailed
inspection of the cap seal required by
paragraphs (g) and (h) of the NPRM (78
FR 21276, April 10, 2013) be extended
from 12 months to 24 months. UPS
commented that if it is not possible to
extend the threshold for the initial
inspection, then the text should be
revised to read ‘‘12 months after the AD
effective date or within the appropriate
total years of aircraft service-life’’—
whichever occurs later. UPS requested
this change to reflect the reported
technical data as well as to give
operators time to schedule the task at a
facility capable of accomplishing the
scope of the work.
We do not agree with UPS’s request
to extend the threshold for the initial
detailed inspection. We have
determined that the compliance time, as
proposed, represents the maximum
interval of time allowable for the
affected airplanes to continue to safely
operate before the initial inspection is
done. Since maintenance schedules vary
among operators, there would be no
assurance that the airplane would be
modified during that maximum interval.
We have not changed this final rule in
this regard.
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Furthermore, we do not agree with
UPS’s request to revise the compliance
time text to include ‘‘or within the
appropriate total years of aircraft
service-life’’—whichever occurs later.
The installation of an incorrect nut
during production, and the possibility
of the nut cracking due to being
overtorqued, is unrelated to the age of
the airplane. We have not changed this
final rule in this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
21276, April 10, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 21276,
April 10, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 440
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Detailed inspections ................
Replacement of all fasteners
(Group 1 airplanes).
1 work-hour × $85 per hour = $85 .........................................
2 work-hours × $85 per hour = $170 .....................................
We estimate the following costs to do
any necessary related investigative and
corrective actions and detailed
Parts cost
inspections for nut type that would be
required based on the results of the
inspections. We have no way of
Cost per
product
$0
2,553
Cost on U.S.
operators
$85
2,723
$37,400
1,198,120
determining the number of aircraft that
might need these actions.
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Related investigative and corrective actions and detailed inspection for nut type.
Up to 3 work-hours × $85 per hour = $255 ..................
$2,553
Up to $2,808.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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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.
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Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2013–18–02 The Boeing Company:
Amendment 39–17575; Docket No.
FAA–2013–0301; Directorate Identifier
2013–NM–025–AD.
(a) Effective Date
This AD is effective October 22, 2013.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 767–200, 767–300, 767–
300F, and 767–400ER series airplanes;
certificated in any category; as identified in
Boeing Service Bulletin 767–57A0131,
Revision 1, dated May 8, 2013.
(2) Installation of Supplemental Type
Certificate (STC) ST01920SE (https://rgl.faa.
gov/Regulatory_and_Guidance_Library/rgstc.
nsf/0/59027f43b9a7486e86257b1d006591ee/
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$FILE/ST01920SE.pdf) does not affect the
ability to accomplish the actions required by
this AD. Therefore, for airplanes on which
STC ST01920SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of
cracked and corroded nuts on an outboard
flap support rib. We are issuing this AD to
detect and correct cracked and corroded nuts
and bolts and the installation of incorrect
nuts on certain outboard flap support ribs,
which could lead to additional nut and bolt
damage in the joint, result in loss of an
outboard flap, and adversely affect continued
safe flight and landing of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) For Group 1 Airplanes: Repetitive
Inspections of the Support Ribs, Related
Investigative and Corrective Actions, and
Fastener Replacement
For Group 1 airplanes, as specified in
Boeing Service Bulletin 767–57A0131,
Revision 1, dated May 8, 2013: Except as
required by paragraph (j) of this AD, at the
time specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
767–57A0131, Revision 1, dated May 8, 2013,
do a detailed inspection of the cap seal for
damaged sealant on the nuts common to
outboard flap support rib numbers 1, 2, 7,
and 8, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0131, Revision 1, dated May 8, 2013. Do
all applicable related investigative and
corrective actions before further flight, except
as specified in paragraphs (g)(1)(ii) and
(g)(2)(ii) of this AD.
(1) If, during any detailed inspection of the
cap seal required by paragraph (g) of this AD,
no damaged sealant is found on any support
rib, do the actions specified in paragraphs
(g)(1)(i) and (g)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap
seal on that support rib thereafter at the
intervals specified in table 1 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 767–57A0131, Revision 1, dated
May 8, 2013, until all fasteners are replaced
within that support rib as required by
paragraph (g)(1)(ii) of this AD.
(ii) Except as required by paragraph (j) of
this AD, at the time specified in table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 767–57A0131, Revision 1,
dated May 8, 2013: Replace all fasteners
within the support rib, in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 767–57A0131, Revision 1,
dated May 8, 2013.
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(2) If, during any related investigative
action required by paragraph (g) of this AD,
no cracking and no corrosion is found on the
nut, bolt, and washers of any support rib, do
the actions specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap
seal on that support rib thereafter at the
intervals specified in table 1 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 767–57A0131, Revision 1, dated
May 8, 2013, until all fasteners are replaced
within that support rib as required by
paragraph (g)(2)(ii) of this AD.
(ii) Except as required by paragraph (j) of
this AD, at the time specified in table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 767–57A0131, Revision 1,
dated May 8, 2013: Replace all fasteners
within the support rib, in accordance with
the Accomplishment Instructions of Boeing
Service Bulletin 767–57A0131, Revision 1,
dated May 8, 2013.
(h) For Group 2 and 3 Airplanes: Repetitive
Inspections of the Support Ribs, Related
Investigative and Corrective Actions, and
Fastener Replacement
For Group 2 and 3 airplanes, as specified
in Boeing Service Bulletin 767–57A0131,
Revision 1, dated May 8, 2013: Except as
required by paragraph (j) of this AD, at the
time specified in table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
767–57A0131, Revision 1, dated May 8, 2013,
do a detailed inspection of the cap seal for
damaged sealant on the nuts common to
outboard flap support rib numbers 1, 2, 7,
and 8, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0131, Revision 1, dated May 8, 2013. Do
all applicable related investigative and
corrective actions before further flight.
(1) If, during any detailed inspection of the
cap seal required by paragraph (h) of this AD,
no damaged sealant is found on any support
rib, do the actions specified in paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap
seal on that support rib thereafter at the
intervals specified in table 2 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 767–57A0131, Revision 1, dated
May 8, 2013, until the actions required by
paragraph (h)(1)(ii) of this AD are done or
until all fasteners are replaced within that
support rib as specified in paragraph (i) of
this AD.
(ii) Except as required by paragraph (j) of
this AD, at the time specified in table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 767–57A0131, Revision 1,
dated May 8, 2013: Do a detailed inspection
to determine the nut type installed in the
outboard flap support rib and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–57A0131,
Revision 1, dated May 8, 2013. Do all
applicable corrective actions before further
flight.
(2) If, during any related investigative
action required by paragraph (h) of this AD,
no cracking and no corrosion is found on the
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nut, bolt, and washers of any support rib, do
the actions specified in paragraphs (h)(2)(i)
and (h)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap
seal on that support rib thereafter at the
intervals specified in table 2 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 767–57A0131, Revision 1, dated
May 8, 2013, until the actions required by
paragraph (h)(2)(ii) of this AD are done or
until all fasteners are replaced within that
support rib as specified in paragraph (i) of
this AD.
(ii) Except as required by paragraph (j) of
this AD, at the time specified in table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 767–57A0131, Revision 1,
dated May 8, 2013: Do a detailed inspection
to determine the nut type installed in the
outboard flap support rib and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 767–57A0131,
Revision 1, dated May 8, 2013. Do all
applicable corrective actions before further
flight.
(i) Terminating Action for Repetitive
Inspections
(1) If cracking is found during any
inspection required by paragraph (g) or (h) of
this AD: Replacing all the fasteners within
the outboard flap support rib number 1, 2, 7,
or 8, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0131, Revision 1, dated May 8, 2013,
terminates the inspections required by
paragraph (g) or (h) of this AD for that
support rib only.
(2) If a discrepancy other than cracking is
found (e.g., corrosion) during any inspection
required by paragraph (g) of this AD:
Replacing all the fasteners within the
outboard flap support rib number 1, 2, 7, or
8, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
57A0131, Revision 1, dated May 8, 2013,
terminates the inspections required by
paragraph (g) of this AD for that support rib
only.
(3) If a discrepancy other than cracking is
found (e.g., corrosion) during any inspection
required by paragraph (h) of this AD:
Replacing the affected fastener terminates the
repetitive inspections for only that fastener
within that support rib.
(j) Exception to Service Information
Where Boeing Service Bulletin 767–
57A0131, Revision 1, dated May 8, 2013,
specifies a compliance time relative to the
issue date of that service bulletin, this AD
requires compliance within the specified
compliance time after the effective date of
this AD.
(k) Credit for Previous Actions
This paragraph provides credit for the
applicable actions required by paragraphs (g),
(h), and (i) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Alert Service Bulletin 767–
57A0131, dated October 30, 2012, which is
not incorporated by reference in this AD.
E:\FR\FM\17SER1.SGM
17SER1
Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (m) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
mstockstill on DSK4VPTVN1PROD with RULES
(m) Related Information
(1) For more information about this AD,
contact Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: 425–917–6577; fax: 425–917–
6590; email: berhane.alazar@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Service Bulletin 767–57A0131,
Revision 1, dated May 8, 2013.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
VerDate Mar<15>2010
16:48 Sep 16, 2013
Jkt 229001
Issued in Renton, Washington, on August
23, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–22414 Filed 9–16–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0097; Directorate
Identifier 2011–NM–243–AD; Amendment
39–17572; AD 2013–17–08]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2010–20–
08, which applied to certain The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, and 747SR series
airplanes. AD 2010–20–08 required
repetitive inspections to find cracking of
the web, strap, inner chords, inner
chord angle of the forward edge frame
of the number 5 main entry door
cutouts; the frame segment between
stringers 16 and 31; repair if necessary;
and repetitive inspections for cracking
of repairs. This new AD expands the
previous fuselage areas that are
inspected for cracking. This AD was
prompted by multiple reports of
cracking outside of the previous
inspection areas and a report of a crack
that initiated at the aft edge of the inner
chord rather than initiating at a fastener
location. We are issuing this AD to
detect and correct such cracks, which
could cause damage to the adjacent
body structure and could result in
depressurization of the airplane in
flight.
SUMMARY:
This AD is effective October 22,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 22, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 9, 2010 (75 FR
61337, October 5, 2010).
The Director of the Federal Register
approved the incorporation by reference
DATES:
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
57053
of a certain other publication listed in
this AD as of September 12, 2001 (66 FR
41440, August 8, 2001).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the service information
at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6428;
fax: 425–917–6590; email:
Nathan.P.Weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010–20–08,
Amendment 39–16442 (75 FR 61337,
October 5, 2010) (‘‘AD 2010–20–08)’’.
AD 2010–20–08 applied to the specified
products. The NPRM published in the
Federal Register on March 6, 2013 (78
FR 14469). The NPRM proposed to
require repetitive inspections to find
cracking of the web, strap, inner chords,
inner chord angle of the forward edge
frame of the number 5 main entry door
cutouts; the frame segment between
stringers 16 and 31; repair if necessary;
and repetitive inspections for cracking
of repairs. The NPRM also proposed to
expand the previous fuselage areas that
are inspected for cracking.
Comments
We gave the public the opportunity to
participate in developing this AD. The
E:\FR\FM\17SER1.SGM
17SER1
]]>Agencies
[Federal Register Volume 78, Number 180 (Tuesday, September 17, 2013)]
[Rules and Regulations]
[Pages 57049-57053]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-22414]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0301; Directorate Identifier 2013-NM-025-AD;
Amendment 39-17575; AD 2013-18-02]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 767-200, -300, -300F, and -400ER series
airplanes. This AD was prompted by reports of cracked and corroded nuts
on an outboard flap support rib. This AD requires, for certain
airplanes, repetitive inspections of the cap seal for damaged sealant
on nuts common to certain outboard flap support ribs, and related
investigative and corrective actions if necessary. For certain other
airplanes, this AD also requires repetitive inspections of the cap seal
for damaged sealant on nuts common to certain outboard flap support
ribs, related investigative and corrective actions if necessary, and if
necessary, a detailed inspection to determine the nut type installed in
the outboard flap support rib and corrective actions. This AD also
provides terminating action for the repetitive inspections under
certain conditions. We are issuing this AD to detect and correct
cracked and corroded nuts and bolts and the installation of incorrect
nuts on certain outboard flap support ribs, which could lead to
additional nut and bolt damage in the joint, result in loss of an
outboard flap, and adversely affect continued safe flight and landing
of the airplane.
DATES: This AD is effective October 22, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 22,
2013.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6577; fax: 425-917-6590; email: berhane.alazar@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
The NPRM published in the Federal Register on April 10, 2013 (78 FR
21276). The NPRM proposed to require, for certain airplanes, repetitive
inspections of the cap seal for damaged sealant on nuts common to
certain outboard flap support ribs, related investigative and
corrective actions if necessary, and replacement of all fasteners in
the support ribs, which terminates the repetitive inspections. For
certain other airplanes, the NPRM proposed to require repetitive
[[Page 57050]]
inspections of the cap seal for damaged sealant on nuts common to
certain outboard flap support ribs, related investigative and
corrective actions if necessary, and if necessary, a detailed
inspection to determine the nut type installed in the outboard flap
support rib and corrective actions. For those airplanes, the NPRM also
proposed to provide for optional replacement of all fasteners in the
support ribs, which would terminate the repetitive inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 21276, April 10, 2013) and the FAA's response to each comment.
Request To Refer to Revised Service Information
Japan Airlines, UPS, and Boeing stated that Boeing has issued
revised service information and requested that the service information
referenced in the NPRM (78 FR 21276, April 10, 2013) be updated to
refer to Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8,
2013.
We agree with the commenters' requests and have revised paragraphs
(c), (g), (h), (i), and (j) of this final rule to include Boeing
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013. We have
also added a new paragraph (k) of this AD to provide credit for actions
accomplished before the effective date of this AD using Boeing Alert
Service Bulletin 767-57A0131, dated October 30, 2012, and reidentified
the subsequent paragraphs.
Clarification Regarding the Installation of Winglets
Aviation Partners Boeing and UPS stated that the installation of
winglets per Supplemental Type Certificate (STC) ST01920SE (https://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect
the accomplishment of the manufacturer's service instructions.
We agree with the commenters' statements that the installation of
winglets as specified in STC ST01920SE (https://rgl.faa.gov/Regulatory--
and--Guidance--Library/rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) does not affect accomplishment of the requirements
of this AD, and for airplanes on which STC ST01920SE is installed, a
``change in product'' AMOC approval request is not necessary to comply
with the requirements of section 39.17 of the Federal Aviation
Regulations (14 CFR 39.17). We have added this provision in new
paragraph (c)(2) of this final rule.
Request To Correct a Reference to a Table Number
UPS noted a typographical error in paragraph (h)(1)(i) of the NPRM
(78 FR 21276, April 10, 2013). The inspection intervals are identified
in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 767-57A0131, Revision 1, dated May 8, 2013, and the NPRM
erroneously referred to table 1.
We agree there is an error and have revised paragraph (h)(1)(i) of
this AD to refer to table 2 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013.
Request To Clarify Terminating Action
UPS noted that paragraph (i) of the NPRM (78 FR 21276, April 10,
2013) implies that the only terminating action for the repetitive
inspections proposed by paragraph (h) of the NPRM is replacement of all
fasteners within a support rib. UPS stated that the Boeing service
information provides terminating action by replacing fasteners at all
discrepant or corroded locations and/or the verification of correct nut
type at all other locations. UPS requested that these corrective
actions be identified as terminating action for the inspections
proposed by paragraph (h) of the NPRM for the associated support rib.
We agree that clarification is needed regarding terminating action
for the repetitive inspections required by paragraph (h) of this final
rule. We have changed the header of paragraph (i) of this final rule to
``Terminating Action for Repetitive Inspections'' and split the
paragraph into three subparagraphs. Paragraph (i)(1) of this final rule
states that, if during any inspection required by paragraphs (g) or (h)
of this AD, any cracking is found, all fasteners within a support rib
must be replaced to terminate the repetitive inspections for that
support rib only. New paragraph (i)(2) of this final rule states that
if a discrepancy other than cracking is found (e.g., corrosion) during
any inspection required by paragraph (g) of this final rule, all
fasteners within a support rib must be replaced to terminate the
repetitive inspections for that support rib only. New paragraph (i)(3)
of this final rule states that if a discrepancy other than cracking is
found (e.g., corrosion) during any inspection required by paragraph (h)
of this final rule, replacing the affected fastener terminates the
repetitive inspections for only that fastener within that support rib.
Request To Combine Paragraphs (h)(1) and (h)(2) of the NPRM (78 FR
21276, April 10, 2013)
UPS stated that the intent of paragraph (h) of the NPRM (78 FR
21276, April 10, 2013) is to identify the requirements of the initial
inspection, and the intent of paragraphs (h)(1) and (h)(2) of the NPRM
is to identify the requirements of the repetitive inspections based on
the findings of the initial inspection. UPS stated that the
investigative and corrective actions applicable to paragraph (h)(1) of
the NPRM are the same as those in paragraph (h)(2) of the NPRM and
suggested that these two paragraphs could be combined without affecting
the intent of this AD.
We do not agree that paragraphs (h)(1) and (h)(2) of this final
rule can be combined. Paragraph (h)(1) of this final rule describes
actions based on the findings of the cap seal detailed inspections, and
paragraph (h)(2) of this final rule addresses actions based on the
findings of the inspections for the nuts, bolts, and washers on the
support ribs. We have not changed this final rule in this regard.
Request To Change Compliance Time for Initial Detailed Inspection
UPS requested that the threshold for conducting the initial
detailed inspection of the cap seal required by paragraphs (g) and (h)
of the NPRM (78 FR 21276, April 10, 2013) be extended from 12 months to
24 months. UPS commented that if it is not possible to extend the
threshold for the initial inspection, then the text should be revised
to read ``12 months after the AD effective date or within the
appropriate total years of aircraft service-life''--whichever occurs
later. UPS requested this change to reflect the reported technical data
as well as to give operators time to schedule the task at a facility
capable of accomplishing the scope of the work.
We do not agree with UPS's request to extend the threshold for the
initial detailed inspection. We have determined that the compliance
time, as proposed, represents the maximum interval of time allowable
for the affected airplanes to continue to safely operate before the
initial inspection is done. Since maintenance schedules vary among
operators, there would be no assurance that the airplane would be
modified during that maximum interval. We have not changed this final
rule in this regard.
[[Page 57051]]
Furthermore, we do not agree with UPS's request to revise the
compliance time text to include ``or within the appropriate total years
of aircraft service-life''--whichever occurs later. The installation of
an incorrect nut during production, and the possibility of the nut
cracking due to being overtorqued, is unrelated to the age of the
airplane. We have not changed this final rule in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously--and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 21276, April 10, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 21276, April 10, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 440 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Detailed inspections............... 1 work-hour x $85 per hour $0 $85 $37,400
= $85.
Replacement of all fasteners (Group 2 work-hours x $85 per hour 2,553 2,723 1,198,120
1 airplanes). = $170.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary related
investigative and corrective actions and detailed inspections for nut
type that would be required based on the results of the inspections. We
have no way of determining the number of aircraft that might need these
actions.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Related investigative and corrective Up to 3 work-hours x $85 $2,553 Up to $2,808.
actions and detailed inspection for per hour = $255.
nut type.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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):
2013-18-02 The Boeing Company: Amendment 39-17575; Docket No. FAA-
2013-0301; Directorate Identifier 2013-NM-025-AD.
(a) Effective Date
This AD is effective October 22, 2013.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 767-200, 767-
300, 767-300F, and 767-400ER series airplanes; certificated in any
category; as identified in Boeing Service Bulletin 767-57A0131,
Revision 1, dated May 8, 2013.
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (https://rgl.faa.gov/Regulatory--and--Guidance--Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/
[[Page 57052]]
$FILE/ST01920SE.pdf) does not affect the ability to accomplish the
actions required by this AD. Therefore, for airplanes on which STC
ST01920SE is installed, a ``change in product'' alternative method
of compliance (AMOC) approval request is not necessary to comply
with the requirements of 14 CFR 39.17.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of cracked and corroded nuts on
an outboard flap support rib. We are issuing this AD to detect and
correct cracked and corroded nuts and bolts and the installation of
incorrect nuts on certain outboard flap support ribs, which could
lead to additional nut and bolt damage in the joint, result in loss
of an outboard flap, and adversely affect continued safe flight and
landing of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) For Group 1 Airplanes: Repetitive Inspections of the Support Ribs,
Related Investigative and Corrective Actions, and Fastener Replacement
For Group 1 airplanes, as specified in Boeing Service Bulletin
767-57A0131, Revision 1, dated May 8, 2013: Except as required by
paragraph (j) of this AD, at the time specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, do a detailed inspection of
the cap seal for damaged sealant on the nuts common to outboard flap
support rib numbers 1, 2, 7, and 8, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131,
Revision 1, dated May 8, 2013. Do all applicable related
investigative and corrective actions before further flight, except
as specified in paragraphs (g)(1)(ii) and (g)(2)(ii) of this AD.
(1) If, during any detailed inspection of the cap seal required
by paragraph (g) of this AD, no damaged sealant is found on any
support rib, do the actions specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until all fasteners are
replaced within that support rib as required by paragraph (g)(1)(ii)
of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Replace
all fasteners within the support rib, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131,
Revision 1, dated May 8, 2013.
(2) If, during any related investigative action required by
paragraph (g) of this AD, no cracking and no corrosion is found on
the nut, bolt, and washers of any support rib, do the actions
specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until all fasteners are
replaced within that support rib as required by paragraph (g)(2)(ii)
of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Replace
all fasteners within the support rib, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131,
Revision 1, dated May 8, 2013.
(h) For Group 2 and 3 Airplanes: Repetitive Inspections of the Support
Ribs, Related Investigative and Corrective Actions, and Fastener
Replacement
For Group 2 and 3 airplanes, as specified in Boeing Service
Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Except as
required by paragraph (j) of this AD, at the time specified in table
2 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, do a detailed inspection of
the cap seal for damaged sealant on the nuts common to outboard flap
support rib numbers 1, 2, 7, and 8, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 767-57A0131,
Revision 1, dated May 8, 2013. Do all applicable related
investigative and corrective actions before further flight.
(1) If, during any detailed inspection of the cap seal required
by paragraph (h) of this AD, no damaged sealant is found on any
support rib, do the actions specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until the actions required
by paragraph (h)(1)(ii) of this AD are done or until all fasteners
are replaced within that support rib as specified in paragraph (i)
of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Do a
detailed inspection to determine the nut type installed in the
outboard flap support rib and do all applicable corrective actions,
in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all
applicable corrective actions before further flight.
(2) If, during any related investigative action required by
paragraph (h) of this AD, no cracking and no corrosion is found on
the nut, bolt, and washers of any support rib, do the actions
specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, until the actions required
by paragraph (h)(2)(ii) of this AD are done or until all fasteners
are replaced within that support rib as specified in paragraph (i)
of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Do a
detailed inspection to determine the nut type installed in the
outboard flap support rib and do all applicable corrective actions,
in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all
applicable corrective actions before further flight.
(i) Terminating Action for Repetitive Inspections
(1) If cracking is found during any inspection required by
paragraph (g) or (h) of this AD: Replacing all the fasteners within
the outboard flap support rib number 1, 2, 7, or 8, in accordance
with the Accomplishment Instructions of Boeing Service Bulletin 767-
57A0131, Revision 1, dated May 8, 2013, terminates the inspections
required by paragraph (g) or (h) of this AD for that support rib
only.
(2) If a discrepancy other than cracking is found (e.g.,
corrosion) during any inspection required by paragraph (g) of this
AD: Replacing all the fasteners within the outboard flap support rib
number 1, 2, 7, or 8, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767-57A0131, Revision 1,
dated May 8, 2013, terminates the inspections required by paragraph
(g) of this AD for that support rib only.
(3) If a discrepancy other than cracking is found (e.g.,
corrosion) during any inspection required by paragraph (h) of this
AD: Replacing the affected fastener terminates the repetitive
inspections for only that fastener within that support rib.
(j) Exception to Service Information
Where Boeing Service Bulletin 767-57A0131, Revision 1, dated May
8, 2013, specifies a compliance time relative to the issue date of
that service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for the applicable actions
required by paragraphs (g), (h), and (i) of this AD, if those
actions were performed before the effective date of this AD using
Boeing Alert Service Bulletin 767-57A0131, dated October 30, 2012,
which is not incorporated by reference in this AD.
[[Page 57053]]
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (m) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-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 required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(m) Related Information
(1) For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6577; fax: 425-917-6590; email:
berhane.alazar@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Service Bulletin 767-57A0131, Revision 1, dated May
8, 2013.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 23, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-22414 Filed 9-16-13; 8:45 am]
BILLING CODE 4910-13-P
