Airworthiness Directives; The Boeing Company Airplanes, 61093-61098 [2015-25490]
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Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations
For the purpose of this AD, next piece-part
exposure is when the nose cone assembly is
removed from the engine.
(g) Installation Prohibition
After the effective date of this AD, do not
install any engine propeller shaft coupling,
P/N 3107065–1, 865888–3, 865888–6, or
865888–8, into any engine.
(h) Alternative Methods of Compliance
(AMOCs)
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(i) Related Information
(1) For more information about this AD,
contact Joseph Costa, Aerospace Engineer,
Los Angeles Aircraft Certification Office,
FAA, Transport Airplane Directorate, 3960
Paramount Blvd., Lakewood, CA 90712–
4137; phone: 562–627–5246; fax: 562–627–
5210; email: joseph.costa@faa.gov.
(2) Allied-Signal Aerospace Company
Service Bulletin No. TPE331–72–0873,
Revision 1, dated May 20, 1993 and
Honeywell International Inc. Operating
Information Letter OI331–26, dated March 2,
2010, which are not incorporated by
reference in this AD, can be obtained from
Honeywell International, using the contact
information in paragraph (i)(3) of this AD.
(3) For service information identified in
this AD, contact Honeywell International
Inc., 111 S. 34th Street, Phoenix, AZ 85034–
2802; phone: 800–601–3099; Internet: https://
portal.honeywell.com.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
None.
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[FR Doc. 2015–25606 Filed 10–8–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
The Manager, Los Angeles Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Use the procedures
found in 14 CFR 39.19 to make your request.
(j) Material Incorporated by Reference
Issued in Burlington, Massachusetts, on:
October 2, 2015.
Colleen M. D’Alessandro,
Directorate Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
14 CFR Part 39
[Docket No. FAA–2012–0108; Directorate
Identifier 2011–NM–049–AD; Amendment
39–18215; AD 2015–15–06]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2003–13–
01 for certain The Boeing Company
Model 767 airplanes. AD 2003–13–01
required an inspection to detect cracks
and fractures of the outboard hinge
fitting assemblies on the trailing edge of
the inboard main flap, and follow-on
and corrective actions if necessary. For
certain airplanes, AD 2003–13–01
required an inspection to determine if a
tool runout option has been performed
in the area. This new AD reduces
certain compliance times, adds
airplanes to the applicability, and
provides optional terminating action for
certain inspections. This AD was
prompted by reports of hinge assembly
fractures found before certain required
SUMMARY:
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compliance times in AD 2003–13–01.
We are issuing this AD to prevent the
inboard aft flap from separating from the
wing and potentially striking the
airplane, which could result in damage
to the surrounding structure and
potential personal injury.
DATES: This AD is effective November
13, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 13, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of July 29, 2003 (68 FR
37402, June 24, 2003).
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 view
this referenced 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2012–
0108.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.govby searching for
and locating Docket No. FAA–2012–
0108; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
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(f) Definition
61093
61094
Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations
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
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:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6447;
fax: 425–917–6590; email:
wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2003–13–01, Amendment 39–13201 (68
FR 37402, June 24, 2003). AD 2003–13–
01 applied to certain The Boeing
Company Model 767 airplanes. The
SNPRM published in the Federal
Register on September 29, 2014 (79 FR
58294). We preceded the SNPRM with
a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on February 9, 2012 (77 FR
6685). The NPRM proposed to continue
to require an inspection to detect cracks
and fractures of the outboard hinge
fitting assemblies on the trailing edge of
the inboard main flap, and follow-on
and corrective actions if necessary. For
certain airplanes, the NPRM proposed to
continue to require inspecting to
determine if a tool runout option has
been performed in the area. The NPRM
also proposed to reduce a certain
compliance time and add airplanes to
the applicability. The NPRM provided
optional terminating action for certain
inspections. The NPRM was prompted
by reports of hinge assembly fractures
found before certain required
compliance times in AD 2003–13–01.
The SNPRM revised the NPRM by
reducing repetitive inspection intervals
for certain airplanes and limiting the
inspection area. We are issuing this AD
to prevent the inboard aft flap from
separating from the wing and
potentially striking the airplane, which
could result in damage to the
surrounding structure and potential
personal injury.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
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15:01 Oct 08, 2015
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received on the SNPRM (79 FR 58294,
September 29, 2014) and the FAA’s
response to each comment.
Support for the SNPRM (79 FR 58294,
September 29, 2014)
Boeing concurred with the contents of
the SNPRM (79 FR 58294, September
29, 2014).
Requests To Remove Certain Provisions
for Spare Parts
American Airlines and UPS requested
that we revise the SNPRM (79 FR 58294,
September 29, 2014) by removing
paragraph (q), because its provisions are
redundant with the requirements of
paragraph (k) of the SNPRM.
We agree with the requests, for the
reason provided by the commenters. We
have removed the referenced paragraph
and redesignated subsequent paragraphs
accordingly.
Request To Clarify Replacement
Requirements
American Airlines requested that we
revise the SNPRM (79 FR 58294,
September 29, 2014) to identify the part
numbers for fittings that are acceptable
for terminating action, but to not require
specific removal and reinstallation
procedures. The commenter added that
the design change of the fitting—not the
installation method—corrects the unsafe
condition.
We partially agree with the request.
Although we did not identify the part
numbers, we revised paragraph (o) in
this AD to specify only the specific step
that provides the replacement
instructions and identifies the part
number of the new fittings. Other
removal and reinstallation actions
related to the fitting replacement may be
done using accepted methods in
accordance with the operator’s
maintenance or inspection program.
We disagree with American Airlines’
assertion that only the fitting design
‘‘corrects the unsafe condition.’’ ADs
contain requirements that are related to
addressing the unsafe condition, as
determined by the FAA and the design
approval holder that developed the
service information. Therefore, many
provisions of ADs address aspects of
accomplishing the required
maintenance that are necessary to
prevent operators from inadvertently
aggravating the unsafe condition or
introducing new unsafe conditions. As
in this case, the replacement
instructions provided in the referenced
service information are reasonably
related to addressing the unsafe
condition.
As always, operators preferring to use
a method other than that specified in
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the referenced service information may
request approval for an alternative
method of compliance and, if approved,
may use it instead of the procedures
specified in the service information.
We further clarified this action
throughout this AD by revising the
description of the replacement part by
specifying ‘‘the inboard main flap
outboard hinge fittings.’’
Effect of Winglets on AD
Aviation Partners Boeing, United
Airlines, Delta Air Lines, and UPS
requested that the SNPRM (79 FR
58294, September 29, 2014) specify that
accomplishment of supplemental type
certificate (STC) ST01920SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) does not affect
the actions in the SNPRM.
We concur with the request. We have
redesignated the introductory text of
paragraph (c) of the SNPRM (79 FR
58294, September 29, 2014) as
paragraph (c)(1), and subparagraphs
(c)(1) and (c)(2) as (c)(1)(i) and (c)(1)(ii),
and added new paragraph (c)(2) to this
AD to state that installation of STC
ST01920SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/
$FILE/ST01920SE.pdf) does not affect
the ability to accomplish the actions
required by this final rule. 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.
Change of Location for Certain Credit
Service Information
We have removed Boeing Alert
Service Bulletin 767–57A0079, Revision
1, dated May 6, 2010, which is referred
to for credit for certain actions, from
paragraph (g)(2) of the proposed AD.
Instead, we have revised paragraph
(p)(1) of this AD to specifically provide
credit for actions required by paragraph
(g)(2) of this AD, if those actions were
performed before the effective date of
this AD using Boeing Alert Service
Bulletin 767–57A0079, Revision 1,
dated May 6, 2010. We have
redesignated subsequent paragraphs
(including the addition of new
paragraph (p)(3)) accordingly. This
change does not affect the intent of
paragraph (g)(2) of this AD.
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Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations
61095
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (79 FR
58294, September 29, 2014) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (79 FR 58294,
September 29, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
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
Related Service Information Under 1
CFR Part 51
3, dated April 4, 2012. The service
information describes procedures for
repetitive eddy current inspections for
cracks or fractures of the outboard hinge
fitting assemblies on the trailing edge of
the inboard main flap. The service
information also describes procedures
for replacing the fittings, which would
eliminate the need for the repetitive
inspections. 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 of this final rule.
Costs of Compliance
We reviewed Boeing Alert Service
Bulletin 767–57A0079, Revision 2,
dated March 23, 2012; and Boeing Alert
Service Bulletin 767–57A0076, Revision
We estimate that this AD affects 440
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
Change to Retained Credit for Previous
Actions Language
We have revised the wording in
paragraph (l) of this AD; this change has
not changed the intent of that
paragraph.
Change to Previous AMOCs Paragraph
We have added a reference to
paragraph (j) of this AD in paragraph
(q)(4) of this AD to account for any
AMOCs that might have been approved
for the optional action specified in
paragraph (j) of this AD.
ESTIMATED COSTS
Action
Retained detailed inspections.
Retained detailed and
eddy current inspections.
Labor cost
Parts cost
10 work-hours × $85 per hour = $850 per inspection cycle.
13 work-hours × $85 per hour = $1,105 per inspection cycle.
We estimate the following costs to do
any necessary replacements that would
Cost per product
$0
0
Cost on U.S. operators
$850 per inspection
cycle.
$1,105 per inspection
cycle.
be required based on the results of the
inspection. We have no way of
$374,000 per inspection
cycle.
$486,200 per inspection
cycle.
determining the number of airplanes
that might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Replacement ............................
32 work-hours × $85 per hour = $2,720 ...........................................................
$45,400
$48,120
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Authority for This Rulemaking
Regulatory Findings
List of Subjects in 14 CFR Part 39
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.
We have determined that 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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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
removing Airworthiness Directive (AD)
2003–13–01, Amendment 39–13201 (68
FR 37402, June 24, 2003), and adding
the following new AD:
■
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Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations
2015–15–06 The Boeing Company:
Amendment 39–18215; Docket No.
FAA–2012–0108; Directorate Identifier
2011–NM–049–AD.
(a) Effective Date
This AD is effective November 13, 2015.
(b) Affected ADs
This AD replaces AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003).
(c) Applicability
(1) This AD applies to The Boeing
Company airplanes, certificated in any
category, identified in paragraphs (c)(1)(i)
and (c)(1)(ii) of this AD.
(i) Model 767–200, –300, and –300F series
airplanes, as specified in Boeing Alert
Service Bulletin 767–57A0076, Revision 3,
dated April 4, 2012.
(ii) Model 767–400ER series airplanes, as
specified in Boeing Alert Service Bulletin
767–57A0079, Revision 2, dated March 23,
2012.
(2) Installation of Supplemental Type
Certificate (STC) ST01920SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$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
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of hinge
assembly fractures found before certain
required compliance times on airplanes
subject to AD 2003–13–01, Amendment 39–
13201 (68 FR 37402, June 24, 2003). We are
issuing this AD to prevent the inboard aft
flap from separating from the wing and
potentially striking the airplane, which could
result in damage to the surrounding structure
and potential personal injury.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection, With Revised
Service Information
This paragraph restates the requirements of
paragraph (a) of AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003), with revised service information.
Perform either a detailed inspection, or a
detailed inspection plus an eddy current
inspection, of the outboard hinge fitting
assemblies on the trailing edge of the inboard
main flap to detect cracks and fractures and
evidence of a tool runout option, as
applicable. For the purposes of this AD, a
detailed inspection is defined as an intensive
visual examination of a specific structural
area, system, installation, or assembly to
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detect damage, failure, or irregularity.
Available lighting is normally supplemented
with a direct source of good lighting at
intensity deemed appropriate by the
inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.
(1) For Model 767–200, –300, and –300F
series airplanes identified in Boeing Service
Bulletin 767–57A0076, Revision 1, dated
March 29, 2001: Inspect before the airplane
accumulates 2,700 total flight cycles, or
within 90 days after July 29, 2003 (the
effective date of AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003)), whichever occurs later, in
accordance with Boeing Service Bulletin
767–57A0076, Revision 1, dated March 29,
2001; or the Accomplishment Instructions of
Boeing Alert Service Bulletin 767–57A0076,
Revision 3, dated April 4, 2012. As of the
effective date of this AD, only Boeing Service
Bulletin 767–57A0076, Revision 3, dated
April 4, 2012, may be used for the inspection.
(2) For Model 767–400ER series airplanes
identified in Boeing Alert Service Bulletin
767–57A0079, dated June 20, 2002: Inspect
before the airplane accumulates 12,000 total
flight cycles, except as required by paragraph
(m) of this AD, in accordance with Boeing
Alert Service Bulletin 767–57A0079, dated
June 20, 2002; or the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–57A0079, Revision 2, dated March 23,
2012. As of the effective date of this AD, only
Boeing Alert Service Bulletin 767–57A0079,
Revision 2, dated March 23, 2012, may be
used for the inspection.
(h) Retained Follow-On/Corrective Actions,
With Revised Service Information
This paragraph restates the requirements of
paragraph (b) of AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003), with revised service information.
Following the initial inspections required by
paragraph (g) of this AD, perform applicable
follow-on and corrective actions at the times
specified in Figure 1 of Boeing Service
Bulletin 767–57A0076, Revision 1, dated
March 29, 2001 (for Model 767–200, –300,
and –300F series airplanes); or Boeing Alert
Service Bulletin 767–57A0079, dated June
20, 2002 (for Model 767–400ER series
airplanes); until the initial inspection
required by paragraph (n) of this AD is
accomplished, and repeat thereafter at the
applicable times specified in paragraph (n) of
this AD. Do the follow-on and corrective
actions (including repetitive inspections and
replacement of the fittings with new fittings)
in accordance with Part 1 or Part 2 of Boeing
Service Bulletin 767–57A0076, Revision 1,
dated March 29, 2001; or Boeing Alert
Service Bulletin 767–57A0079, dated June
20, 2002; or in accordance with the
Accomplishment Instructions of the service
information identified in paragraph (h)(1) or
(h)(2) of this AD; except as required by
paragraph (i)(2) of this AD. For Model 767–
200, –300, and –300F series airplanes: If the
fitting has the tool runout, and no cracking
or fracture is found during the inspection,
this AD requires no further action for that
hinge fitting. As of the effective date of this
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AD, for the actions required by this
paragraph, only the service information
identified in paragraph (h)(1) or (h)(2) of this
AD, as applicable, may be used.
(1) Boeing Service Bulletin 767–57A0076,
Revision 3, dated April 4, 2012 (for Model
767–200, –300, and –300F series airplanes).
(2) Boeing Alert Service Bulletin 767–
57A0079, Revision 2, dated March 23, 2012
(for Model 767–400ER series airplanes).
(i) Retained Exceptions to Service Bulletin
Procedures, Without the Reporting
Requirement and With Revised Service
Information
This paragraph restates the requirements of
paragraphs (c) and (d) of AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003), without the reporting requirement
and with revised service information. The
following exceptions specified in paragraphs
(i)(1) and (i)(2) of this AD apply.
(1) Where the terminating action in Part 3
of Boeing Service Bulletin 767–57A0076,
Revision 1, dated March 29, 2001, and
Revision 3, dated April 4, 2012; and Boeing
Alert Service Bulletin 767–57A0079, dated
June 20, 2002, and Revision 2, dated March
23, 2012; as applicable; is specified as
corrective action, this AD requires that the
terminating action, if required, be
accomplished before further flight.
(2) Boeing Service Bulletin 767–57A0076,
Revision 1, dated March 29, 2001; and
Boeing Alert Service Bulletin 767–57A0076,
Revision 3, dated April 4, 2012; specify to
contact Boeing before the terminating action
is done as corrective action for any cracking
or fracture found on a Model 767–200, –300,
or –300F series airplane with the tool runout.
However, this AD requires that any such
crack or fracture on those airplanes be
repaired in accordance with Part 3 of Boeing
Service Bulletin 767–57A0076, Revision 1,
dated March 29, 2001; or the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–57A0076, Revision 3,
dated April 4, 2012. This AD does not require
a report.
(j) Retained Optional Terminating Action
This paragraph restates the provisions of
paragraph (f) of AD 2003–13–01, Amendment
39–13201 (68 FR 37402, June 24, 2003).
Unless required to do so by paragraph (h) of
this AD, operators may choose to accomplish
the terminating action (including
replacement of the fittings with new fittings,
and reinstallation of existing upper skin
access panels and fairing midsections on the
trailing edge of the main flap) in accordance
with Part 3 of the Work Instructions of
Boeing Service Bulletin 767–57A0076,
Revision 1, dated March 29, 2001; or Boeing
Alert Service Bulletin 767–57A0079, dated
June 20, 2002; as applicable; or do the
terminating actions specified in paragraph (o)
of this AD. As of the effective date of this AD,
use only the terminating action specified in
paragraph (o) of this AD. Accomplishment of
the terminating action terminates the
repetitive inspection requirements of
paragraph (h) of this AD.
(k) Parts Installation Limitations
As of the effective date of this AD, no
person may install on any airplane identified
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Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations
in paragraph (c) of this AD, a hinge fitting
assembly that has part number (P/N)
113T2271–13, 113T2271–14, 113T2271–23,
113T2271–24, 113T2271–29, 113T2271–30,
113T2271–33, 113T2271–34, 113T2271–401,
or 113T2271–402, unless the applicable
requirements of this AD have been
accomplished for that fitting.
(l) Retained Credit for Previous Actions,
With Revised Credit Provisions
This paragraph restates the provisions of
paragraph (g) of AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003), with revised credit provisions.
This paragraph provides credit for actions
required by paragraphs (g)(1), (h), and (j) of
this AD, if those actions were performed
before July 29, 2003 (the effective date of AD
2003–13–01), using Boeing Alert Service
Bulletin 767–57A0076, dated October 26,
2000, which is not incorporated by reference
in this AD.
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(m) New Initial Inspection
For Model 767–400ER airplanes identified
in Boeing Alert Service Bulletin 767–
57A0079, Revision 2, dated March 23, 2012,
on which the inspection required in
paragraph (g) of this AD has not been done
as of the effective date of this AD: Before the
accumulation of 6,000 total flight cycles, or
within 750 flight cycles after the effective
date of this AD, whichever occurs later,
perform either a detailed inspection or a
detailed inspection plus an eddy current
inspection to detect cracks or fractures of the
outboard hinge fitting assemblies on the
trailing edge of the inboard main flap, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–57A0079, Revision 2, dated March 23,
2012. Accomplishment of this inspection
terminates the inspection requirement of
paragraph (g)(2) of this AD. If any cracking
or fracture is found, before further flight,
replace the fittings in accordance with Part
3 of the Work Instructions of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–57A0079, Revision 2,
dated March 23, 2012.
(n) New Repetitive Inspections
Repeat the inspection specified in
paragraph (h) or (m) of this AD, as applicable,
at intervals not to exceed the time specified
in paragraph (n)(1) or (n)(2) of this AD, as
applicable, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–57A0076, Revision 3,
dated April 4, 2012 (for Model 767–200,
–300, and –300F series airplanes); or Boeing
Alert Service Bulletin 767–57A0079,
Revision 2, dated March 23, 2012 (for Model
767–400ER series airplanes); until the actions
specified in paragraph (o) of this AD are
done.
(1) If the most recent inspection was a
detailed inspection: Do the next inspection
within 300 flight cycles after doing the
detailed inspection, and continue to repeat
the inspection(s) thereafter at the time
specified in paragraph (n) of this AD.
(2) If the most recent inspections were a
detailed inspection and an eddy current
inspection: Do the next inspections at the
applicable time specified in paragraph
VerDate Sep<11>2014
15:01 Oct 08, 2015
Jkt 238001
(n)(2)(i) or (n)(2)(ii) of this AD, and continue
to repeat the inspection(s) thereafter at the
time specified in paragraph (n) of this AD.
(i) For Model 767–200, –300, and –300F
series airplanes: Do the next inspection at the
applicable time specified in paragraph
(n)(2)(i)(A) or (n)(2)(i)(B) of this AD.
(A) If the detailed inspection and eddy
current inspection were done before the
effective date of this AD: Do the next
inspection within 1,500 flight cycles after
doing the detailed and eddy current
inspections.
(B) If the detailed inspection and eddy
current inspection were done on or after the
effective date of this AD: Do the next
inspection within 750 flight cycles after
doing the detailed and eddy current
inspection.
(ii) For Model 767–400ER series airplanes:
Do the next inspection within 750 flight
cycles after doing the detailed inspection and
eddy current inspection.
(o) New Optional Terminating Action
Replacement of the inboard main flap
outboard hinge fittings in accordance with
step 4 of Part 3 of the Work Instructions of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 767–57A0079,
Revision 2, dated March 23, 2012 (for Model
767–400ER series airplanes); or step 4 of Part
3 of the Work Instructions of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–57A0076, Revision 3,
dated April 4, 2012 (for Model 767–200,
–300, and –300F series airplanes); terminates
the repetitive inspections required by
paragraphs (h) and (n) of this AD.
(p) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g)(2) of this
AD, if those actions were performed before
the effective date of this AD using Boeing
Alert Service Bulletin 767–57A0079,
Revision 1, dated May 6, 2010, which is not
incorporated by reference in this AD.
(2) This paragraph provides credit for
actions required by paragraphs (h), (n), and
(o) of this AD, if those actions were
performed before the effective date of this AD
using the service information identified in
paragraph (p)(2)(i), (p)(2)(ii), (p)(2)(iii), or
(p)(2)(iv) of this AD.
(i) Boeing Alert Service Bulletin 767–
57A0076, Revision 1, dated March 29, 2001,
which was incorporated by reference in AD
2003–13–01, Amendment 39–13201 (68 FR
37402, June 24, 2003), and continues to be
incorporated by reference in this AD.
(ii) Boeing Alert Service Bulletin 767–
57A0076, Revision 2, dated November 22,
2006, which is not incorporated by reference
in this AD.
(iii) Boeing Alert Service Bulletin 767–
57A0079, dated June 20, 2002, which was
incorporated by reference in AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003), and continues to be incorporated
by reference in this AD.
(iv) Boeing Alert Service Bulletin 767–
57A0079, Revision 1, dated May 6, 2010,
which is not incorporated by reference in this
AD.
(3) This paragraph provides credit for
actions required by paragraph (j) of this AD,
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
61097
if those actions were performed before the
effective date of this AD using the service
information identified in paragraph (p)(3)(i)
or (p)(3)(ii) of this AD.
(i) Boeing Alert Service Bulletin 767–
57A0076, Revision 2, dated November 22,
2006, which is not incorporated by reference
in this AD.
(ii) Boeing Alert Service Bulletin 767–
57A0079, Revision 1, dated May 6, 2010,
which is not incorporated by reference in this
AD.
(q) 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 (r)(1) 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.
(4) AMOCs approved previously in
accordance with AD 2003–13–01,
Amendment 39–13201 (68 FR 37402, June
24, 2003), are approved as AMOCs for the
corresponding provisions of paragraphs (g),
(h), (i), and (j) of this AD.
(r) Related Information
(1) For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office ACO, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6447; fax: 425–917–6590;
email: wayne.lockett@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (s)(5) and (s)(6) of this AD.
(s) 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.
(3) The following service information was
approved for IBR on November 13, 2015.
(i) Boeing Alert Service Bulletin 767–
57A0079, Revision 2, dated March 23, 2012.
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09OCR1
61098
Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations
(ii) Boeing Alert Service Bulletin 767–
57A0076, Revision 3, dated April 4, 2012.
(4) The following service information was
approved for IBR on July 29, 2003 (68 FR
37402, June 24, 2003).
(i) Boeing Alert Service Bulletin 767–
57A0079, dated June 20, 2002.
(ii) Boeing Service Bulletin 767–57A0076,
Revision 1, dated March 29, 2001.
(5) 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.
(6) You may view this 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.
(7) 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 Renton, Washington, on
September 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–25490 Filed 10–8–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1419; Directorate
Identifier 2014–NM–183–AD; Amendment
39–18279; AD 2015–20–01]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model
188 series airplanes. This AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating the left and right lower
surface panels of the wings are subject
to widespread fatigue damage (WFD).
This AD requires repetitive inspections
for cracking at these panels, and repair
if necessary. The AD also requires a onetime bolt-hole eddy current inspection
of all open holes for cracking, repair if
rmajette on DSK7SPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
15:01 Oct 08, 2015
Jkt 238001
necessary, and modification. We are
issuing this AD to prevent fatigue
cracking of the left and right lower
surface panels of the wings, which
could result in reduced structural
integrity of the airplane.
DATES: This AD is effective November
13, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 13, 2015.
ADDRESSES: For service information
identified in this AD, contact Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company, Airworthiness
Office, Dept. 6A0M, Zone 0252, Column
P–58, 86 S. Cobb Drive, Marietta, GA
30063; telephone 770–494–5444; fax
770–494–5445; email ams.portal@
lmco.com; Internet https://
www.lockheedmartin.com/ams/tools/
TechPubs.html. You may view this
referenced 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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2015–1419.
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–2015–
1419; 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
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: Carl
Gray, Aerospace Engineer, Airframe
Branch, ACE–117A, FAA, Atlanta
Aircraft Certification Office (ACO), 1701
Columbia Avenue, College Park, GA
30337; phone: 404–474–5554; fax: 404–
474–5605; email: carl.w.gray@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 all Lockheed Martin
Corporation/Lockheed Martin
Aeronautics Company Model 188 series
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
airplanes. The NPRM published in the
Federal Register on June 5, 2015 (80 FR
32069). The NPRM was prompted by an
evaluation by the DAH indicating the
left and right lower surface panels of the
wings are subject to WFD. The NPRM
proposed to require repetitive
inspections for cracking at these panels,
and repair if necessary. The NPRM also
proposed to require a one-time bolt-hole
eddy current inspection of all open
holes for cracking, repair if necessary,
and modification. We are issuing this
AD to prevent fatigue cracking of the left
and right lower surface panels of the
wings, which could result in reduced
structural integrity of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (80
FR 32069, June 5, 2015) or on the
determination of the cost to the public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (80 FR
32069, June 5, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM 80 FR 32069,
June 5, 2015).
Related Service Information Under 1
CFR Part 51
We reviewed Lockheed Martin Electra
Service Bulletin 88/SB–707C, Revision
C, dated April 30, 2014. The service
information describes procedures for
repetitive inspections for cracking of the
left and right lower surface panels of the
wings on the inboard and outboard
sides of the buttock line (BL) 65 splice
joint, and repair. This service
information also describes procedures
for a one-time bolt-hole eddy current
inspection of all open holes for
cracking, repair, and modification of the
BL 65 wing root joint. 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 of this AD.
Costs of Compliance
We estimate that this AD affects 4
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
E:\FR\FM\09OCR1.SGM
09OCR1
]]>Agencies
[Federal Register Volume 80, Number 196 (Friday, October 9, 2015)]
[Rules and Regulations]
[Pages 61093-61098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-25490]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0108; Directorate Identifier 2011-NM-049-AD;
Amendment 39-18215; AD 2015-15-06]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2003-13-01 for
certain The Boeing Company Model 767 airplanes. AD 2003-13-01 required
an inspection to detect cracks and fractures of the outboard hinge
fitting assemblies on the trailing edge of the inboard main flap, and
follow-on and corrective actions if necessary. For certain airplanes,
AD 2003-13-01 required an inspection to determine if a tool runout
option has been performed in the area. This new AD reduces certain
compliance times, adds airplanes to the applicability, and provides
optional terminating action for certain inspections. This AD was
prompted by reports of hinge assembly fractures found before certain
required compliance times in AD 2003-13-01. We are issuing this AD to
prevent the inboard aft flap from separating from the wing and
potentially striking the airplane, which could result in damage to the
surrounding structure and potential personal injury.
DATES: This AD is effective November 13, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 13,
2015.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of July
29, 2003 (68 FR 37402, June 24, 2003).
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 view this referenced 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2012-
0108.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.govby searching for and locating Docket No. FAA-2012-
0108; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday,
[[Page 61094]]
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 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2003-13-01, Amendment 39-13201 (68
FR 37402, June 24, 2003). AD 2003-13-01 applied to certain The Boeing
Company Model 767 airplanes. The SNPRM published in the Federal
Register on September 29, 2014 (79 FR 58294). We preceded the SNPRM
with a notice of proposed rulemaking (NPRM) that published in the
Federal Register on February 9, 2012 (77 FR 6685). The NPRM proposed to
continue to require an inspection to detect cracks and fractures of the
outboard hinge fitting assemblies on the trailing edge of the inboard
main flap, and follow-on and corrective actions if necessary. For
certain airplanes, the NPRM proposed to continue to require inspecting
to determine if a tool runout option has been performed in the area.
The NPRM also proposed to reduce a certain compliance time and add
airplanes to the applicability. The NPRM provided optional terminating
action for certain inspections. The NPRM was prompted by reports of
hinge assembly fractures found before certain required compliance times
in AD 2003-13-01. The SNPRM revised the NPRM by reducing repetitive
inspection intervals for certain airplanes and limiting the inspection
area. We are issuing this AD to prevent the inboard aft flap from
separating from the wing and potentially striking the airplane, which
could result in damage to the surrounding structure and potential
personal injury.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM (79
FR 58294, September 29, 2014) and the FAA's response to each comment.
Support for the SNPRM (79 FR 58294, September 29, 2014)
Boeing concurred with the contents of the SNPRM (79 FR 58294,
September 29, 2014).
Requests To Remove Certain Provisions for Spare Parts
American Airlines and UPS requested that we revise the SNPRM (79 FR
58294, September 29, 2014) by removing paragraph (q), because its
provisions are redundant with the requirements of paragraph (k) of the
SNPRM.
We agree with the requests, for the reason provided by the
commenters. We have removed the referenced paragraph and redesignated
subsequent paragraphs accordingly.
Request To Clarify Replacement Requirements
American Airlines requested that we revise the SNPRM (79 FR 58294,
September 29, 2014) to identify the part numbers for fittings that are
acceptable for terminating action, but to not require specific removal
and reinstallation procedures. The commenter added that the design
change of the fitting--not the installation method--corrects the unsafe
condition.
We partially agree with the request. Although we did not identify
the part numbers, we revised paragraph (o) in this AD to specify only
the specific step that provides the replacement instructions and
identifies the part number of the new fittings. Other removal and
reinstallation actions related to the fitting replacement may be done
using accepted methods in accordance with the operator's maintenance or
inspection program.
We disagree with American Airlines' assertion that only the fitting
design ``corrects the unsafe condition.'' ADs contain requirements that
are related to addressing the unsafe condition, as determined by the
FAA and the design approval holder that developed the service
information. Therefore, many provisions of ADs address aspects of
accomplishing the required maintenance that are necessary to prevent
operators from inadvertently aggravating the unsafe condition or
introducing new unsafe conditions. As in this case, the replacement
instructions provided in the referenced service information are
reasonably related to addressing the unsafe condition.
As always, operators preferring to use a method other than that
specified in the referenced service information may request approval
for an alternative method of compliance and, if approved, may use it
instead of the procedures specified in the service information.
We further clarified this action throughout this AD by revising the
description of the replacement part by specifying ``the inboard main
flap outboard hinge fittings.''
Effect of Winglets on AD
Aviation Partners Boeing, United Airlines, Delta Air Lines, and UPS
requested that the SNPRM (79 FR 58294, September 29, 2014) specify that
accomplishment of supplemental type certificate (STC) ST01920SE (http:/
/rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect
the actions in the SNPRM.
We concur with the request. We have redesignated the introductory
text of paragraph (c) of the SNPRM (79 FR 58294, September 29, 2014) as
paragraph (c)(1), and subparagraphs (c)(1) and (c)(2) as (c)(1)(i) and
(c)(1)(ii), and added new paragraph (c)(2) to this AD to state that
installation of STC ST01920SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect
the ability to accomplish the actions required by this final rule.
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.
Change of Location for Certain Credit Service Information
We have removed Boeing Alert Service Bulletin 767-57A0079, Revision
1, dated May 6, 2010, which is referred to for credit for certain
actions, from paragraph (g)(2) of the proposed AD. Instead, we have
revised paragraph (p)(1) of this AD to specifically provide credit for
actions required by paragraph (g)(2) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010. We have
redesignated subsequent paragraphs (including the addition of new
paragraph (p)(3)) accordingly. This change does not affect the intent
of paragraph (g)(2) of this AD.
[[Page 61095]]
Change to Retained Credit for Previous Actions Language
We have revised the wording in paragraph (l) of this AD; this
change has not changed the intent of that paragraph.
Change to Previous AMOCs Paragraph
We have added a reference to paragraph (j) of this AD in paragraph
(q)(4) of this AD to account for any AMOCs that might have been
approved for the optional action specified in paragraph (j) of this AD.
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
SNPRM (79 FR 58294, September 29, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (79 FR 58294, September 29, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 767-57A0079, Revision 2,
dated March 23, 2012; and Boeing Alert Service Bulletin 767-57A0076,
Revision 3, dated April 4, 2012. The service information describes
procedures for repetitive eddy current inspections for cracks or
fractures of the outboard hinge fitting assemblies on the trailing edge
of the inboard main flap. The service information also describes
procedures for replacing the fittings, which would eliminate the need
for the repetitive inspections. 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 of this final rule.
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 on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Retained detailed inspections.. 10 work-hours x $85 per $0 $850 per $374,000 per
hour = $850 per inspection cycle. inspection cycle.
inspection cycle.
Retained detailed and eddy 13 work-hours x $85 per 0 $1,105 per $486,200 per
current inspections. hour = $1,105 per inspection cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of airplanes that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement............................. 32 work-hours x $85 per hour = $45,400 $48,120
$2,720.
----------------------------------------------------------------------------------------------------------------
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
We have determined that 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]
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2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), and adding
the following new AD:
[[Page 61096]]
2015-15-06 The Boeing Company: Amendment 39-18215; Docket No. FAA-
2012-0108; Directorate Identifier 2011-NM-049-AD.
(a) Effective Date
This AD is effective November 13, 2015.
(b) Affected ADs
This AD replaces AD 2003-13-01, Amendment 39-13201 (68 FR 37402,
June 24, 2003).
(c) Applicability
(1) This AD applies to The Boeing Company airplanes,
certificated in any category, identified in paragraphs (c)(1)(i) and
(c)(1)(ii) of this AD.
(i) Model 767-200, -300, and -300F series airplanes, as
specified in Boeing Alert Service Bulletin 767-57A0076, Revision 3,
dated April 4, 2012.
(ii) Model 767-400ER series airplanes, as specified in Boeing
Alert Service Bulletin 767-57A0079, Revision 2, dated March 23,
2012.
(2) Installation of Supplemental Type Certificate (STC)
ST01920SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$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
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of hinge assembly fractures
found before certain required compliance times on airplanes subject
to AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003).
We are issuing this AD to prevent the inboard aft flap from
separating from the wing and potentially striking the airplane,
which could result in damage to the surrounding structure and
potential personal injury.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With Revised Service Information
This paragraph restates the requirements of paragraph (a) of AD
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with
revised service information. Perform either a detailed inspection,
or a detailed inspection plus an eddy current inspection, of the
outboard hinge fitting assemblies on the trailing edge of the
inboard main flap to detect cracks and fractures and evidence of a
tool runout option, as applicable. For the purposes of this AD, a
detailed inspection is defined as an intensive visual examination of
a specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.
(1) For Model 767-200, -300, and -300F series airplanes
identified in Boeing Service Bulletin 767-57A0076, Revision 1, dated
March 29, 2001: Inspect before the airplane accumulates 2,700 total
flight cycles, or within 90 days after July 29, 2003 (the effective
date of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24,
2003)), whichever occurs later, in accordance with Boeing Service
Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0076, Revision 3, dated April 4, 2012. As of the effective date
of this AD, only Boeing Service Bulletin 767-57A0076, Revision 3,
dated April 4, 2012, may be used for the inspection.
(2) For Model 767-400ER series airplanes identified in Boeing
Alert Service Bulletin 767-57A0079, dated June 20, 2002: Inspect
before the airplane accumulates 12,000 total flight cycles, except
as required by paragraph (m) of this AD, in accordance with Boeing
Alert Service Bulletin 767-57A0079, dated June 20, 2002; or the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0079, Revision 2, dated March 23, 2012. As of the effective date
of this AD, only Boeing Alert Service Bulletin 767-57A0079, Revision
2, dated March 23, 2012, may be used for the inspection.
(h) Retained Follow-On/Corrective Actions, With Revised Service
Information
This paragraph restates the requirements of paragraph (b) of AD
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with
revised service information. Following the initial inspections
required by paragraph (g) of this AD, perform applicable follow-on
and corrective actions at the times specified in Figure 1 of Boeing
Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001 (for
Model 767-200, -300, and -300F series airplanes); or Boeing Alert
Service Bulletin 767-57A0079, dated June 20, 2002 (for Model 767-
400ER series airplanes); until the initial inspection required by
paragraph (n) of this AD is accomplished, and repeat thereafter at
the applicable times specified in paragraph (n) of this AD. Do the
follow-on and corrective actions (including repetitive inspections
and replacement of the fittings with new fittings) in accordance
with Part 1 or Part 2 of Boeing Service Bulletin 767-57A0076,
Revision 1, dated March 29, 2001; or Boeing Alert Service Bulletin
767-57A0079, dated June 20, 2002; or in accordance with the
Accomplishment Instructions of the service information identified in
paragraph (h)(1) or (h)(2) of this AD; except as required by
paragraph (i)(2) of this AD. For Model 767-200, -300, and -300F
series airplanes: If the fitting has the tool runout, and no
cracking or fracture is found during the inspection, this AD
requires no further action for that hinge fitting. As of the
effective date of this AD, for the actions required by this
paragraph, only the service information identified in paragraph
(h)(1) or (h)(2) of this AD, as applicable, may be used.
(1) Boeing Service Bulletin 767-57A0076, Revision 3, dated April
4, 2012 (for Model 767-200, -300, and -300F series airplanes).
(2) Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated
March 23, 2012 (for Model 767-400ER series airplanes).
(i) Retained Exceptions to Service Bulletin Procedures, Without the
Reporting Requirement and With Revised Service Information
This paragraph restates the requirements of paragraphs (c) and
(d) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24,
2003), without the reporting requirement and with revised service
information. The following exceptions specified in paragraphs (i)(1)
and (i)(2) of this AD apply.
(1) Where the terminating action in Part 3 of Boeing Service
Bulletin 767-57A0076, Revision 1, dated March 29, 2001, and Revision
3, dated April 4, 2012; and Boeing Alert Service Bulletin 767-
57A0079, dated June 20, 2002, and Revision 2, dated March 23, 2012;
as applicable; is specified as corrective action, this AD requires
that the terminating action, if required, be accomplished before
further flight.
(2) Boeing Service Bulletin 767-57A0076, Revision 1, dated March
29, 2001; and Boeing Alert Service Bulletin 767-57A0076, Revision 3,
dated April 4, 2012; specify to contact Boeing before the
terminating action is done as corrective action for any cracking or
fracture found on a Model 767-200, -300, or -300F series airplane
with the tool runout. However, this AD requires that any such crack
or fracture on those airplanes be repaired in accordance with Part 3
of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29,
2001; or the Accomplishment Instructions of Boeing Alert Service
Bulletin 767-57A0076, Revision 3, dated April 4, 2012. This AD does
not require a report.
(j) Retained Optional Terminating Action
This paragraph restates the provisions of paragraph (f) of AD
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003). Unless
required to do so by paragraph (h) of this AD, operators may choose
to accomplish the terminating action (including replacement of the
fittings with new fittings, and reinstallation of existing upper
skin access panels and fairing midsections on the trailing edge of
the main flap) in accordance with Part 3 of the Work Instructions of
Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29,
2001; or Boeing Alert Service Bulletin 767-57A0079, dated June 20,
2002; as applicable; or do the terminating actions specified in
paragraph (o) of this AD. As of the effective date of this AD, use
only the terminating action specified in paragraph (o) of this AD.
Accomplishment of the terminating action terminates the repetitive
inspection requirements of paragraph (h) of this AD.
(k) Parts Installation Limitations
As of the effective date of this AD, no person may install on
any airplane identified
[[Page 61097]]
in paragraph (c) of this AD, a hinge fitting assembly that has part
number (P/N) 113T2271-13, 113T2271-14, 113T2271-23, 113T2271-24,
113T2271-29, 113T2271-30, 113T2271-33, 113T2271-34, 113T2271-401, or
113T2271-402, unless the applicable requirements of this AD have
been accomplished for that fitting.
(l) Retained Credit for Previous Actions, With Revised Credit
Provisions
This paragraph restates the provisions of paragraph (g) of AD
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with
revised credit provisions. This paragraph provides credit for
actions required by paragraphs (g)(1), (h), and (j) of this AD, if
those actions were performed before July 29, 2003 (the effective
date of AD 2003-13-01), using Boeing Alert Service Bulletin 767-
57A0076, dated October 26, 2000, which is not incorporated by
reference in this AD.
(m) New Initial Inspection
For Model 767-400ER airplanes identified in Boeing Alert Service
Bulletin 767-57A0079, Revision 2, dated March 23, 2012, on which the
inspection required in paragraph (g) of this AD has not been done as
of the effective date of this AD: Before the accumulation of 6,000
total flight cycles, or within 750 flight cycles after the effective
date of this AD, whichever occurs later, perform either a detailed
inspection or a detailed inspection plus an eddy current inspection
to detect cracks or fractures of the outboard hinge fitting
assemblies on the trailing edge of the inboard main flap, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012.
Accomplishment of this inspection terminates the inspection
requirement of paragraph (g)(2) of this AD. If any cracking or
fracture is found, before further flight, replace the fittings in
accordance with Part 3 of the Work Instructions of the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0079, Revision 2, dated March 23, 2012.
(n) New Repetitive Inspections
Repeat the inspection specified in paragraph (h) or (m) of this
AD, as applicable, at intervals not to exceed the time specified in
paragraph (n)(1) or (n)(2) of this AD, as applicable, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 767-57A0076, Revision 3, dated April 4, 2012 (for Model
767-200, -300, and -300F series airplanes); or Boeing Alert Service
Bulletin 767-57A0079, Revision 2, dated March 23, 2012 (for Model
767-400ER series airplanes); until the actions specified in
paragraph (o) of this AD are done.
(1) If the most recent inspection was a detailed inspection: Do
the next inspection within 300 flight cycles after doing the
detailed inspection, and continue to repeat the inspection(s)
thereafter at the time specified in paragraph (n) of this AD.
(2) If the most recent inspections were a detailed inspection
and an eddy current inspection: Do the next inspections at the
applicable time specified in paragraph (n)(2)(i) or (n)(2)(ii) of
this AD, and continue to repeat the inspection(s) thereafter at the
time specified in paragraph (n) of this AD.
(i) For Model 767-200, -300, and -300F series airplanes: Do the
next inspection at the applicable time specified in paragraph
(n)(2)(i)(A) or (n)(2)(i)(B) of this AD.
(A) If the detailed inspection and eddy current inspection were
done before the effective date of this AD: Do the next inspection
within 1,500 flight cycles after doing the detailed and eddy current
inspections.
(B) If the detailed inspection and eddy current inspection were
done on or after the effective date of this AD: Do the next
inspection within 750 flight cycles after doing the detailed and
eddy current inspection.
(ii) For Model 767-400ER series airplanes: Do the next
inspection within 750 flight cycles after doing the detailed
inspection and eddy current inspection.
(o) New Optional Terminating Action
Replacement of the inboard main flap outboard hinge fittings in
accordance with step 4 of Part 3 of the Work Instructions of the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0079, Revision 2, dated March 23, 2012 (for Model 767-400ER
series airplanes); or step 4 of Part 3 of the Work Instructions of
the Accomplishment Instructions of Boeing Alert Service Bulletin
767-57A0076, Revision 3, dated April 4, 2012 (for Model 767-200, -
300, and -300F series airplanes); terminates the repetitive
inspections required by paragraphs (h) and (n) of this AD.
(p) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g)(2) of this AD, if those actions were performed before
the effective date of this AD using Boeing Alert Service Bulletin
767-57A0079, Revision 1, dated May 6, 2010, which is not
incorporated by reference in this AD.
(2) This paragraph provides credit for actions required by
paragraphs (h), (n), and (o) of this AD, if those actions were
performed before the effective date of this AD using the service
information identified in paragraph (p)(2)(i), (p)(2)(ii),
(p)(2)(iii), or (p)(2)(iv) of this AD.
(i) Boeing Alert Service Bulletin 767-57A0076, Revision 1, dated
March 29, 2001, which was incorporated by reference in AD 2003-13-
01, Amendment 39-13201 (68 FR 37402, June 24, 2003), and continues
to be incorporated by reference in this AD.
(ii) Boeing Alert Service Bulletin 767-57A0076, Revision 2,
dated November 22, 2006, which is not incorporated by reference in
this AD.
(iii) Boeing Alert Service Bulletin 767-57A0079, dated June 20,
2002, which was incorporated by reference in AD 2003-13-01,
Amendment 39-13201 (68 FR 37402, June 24, 2003), and continues to be
incorporated by reference in this AD.
(iv) Boeing Alert Service Bulletin 767-57A0079, Revision 1,
dated May 6, 2010, which is not incorporated by reference in this
AD.
(3) This paragraph provides credit for actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using the service information identified
in paragraph (p)(3)(i) or (p)(3)(ii) of this AD.
(i) Boeing Alert Service Bulletin 767-57A0076, Revision 2, dated
November 22, 2006, which is not incorporated by reference in this
AD.
(ii) Boeing Alert Service Bulletin 767-57A0079, Revision 1,
dated May 6, 2010, which is not incorporated by reference in this
AD.
(q) 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 (r)(1) of this AD.
Information may be emailed to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair 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.
(4) AMOCs approved previously in accordance with AD 2003-13-01,
Amendment 39-13201 (68 FR 37402, June 24, 2003), are approved as
AMOCs for the corresponding provisions of paragraphs (g), (h), (i),
and (j) of this AD.
(r) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office ACO, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6447; fax: 425-917-6590; email:
wayne.lockett@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (s)(5) and (s)(6) of this AD.
(s) 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.
(3) The following service information was approved for IBR on
November 13, 2015.
(i) Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated
March 23, 2012.
[[Page 61098]]
(ii) Boeing Alert Service Bulletin 767-57A0076, Revision 3,
dated April 4, 2012.
(4) The following service information was approved for IBR on
July 29, 2003 (68 FR 37402, June 24, 2003).
(i) Boeing Alert Service Bulletin 767-57A0079, dated June 20,
2002.
(ii) Boeing Service Bulletin 767-57A0076, Revision 1, dated
March 29, 2001.
(5) 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.
(6) You may view this 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.
(7) 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 September 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-25490 Filed 10-8-15; 8:45 am]
BILLING CODE 4910-13-P
