Airworthiness Directives; The Boeing Company Airplanes, 74047-74052 [2015-30008]
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
of Airbus Service Bulletin A320–53–1287,
dated July 29, 2014, before further flight,
repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA).
(h) Non-Terminating Repair Action
Accomplishment of a repair on an airplane
as required by paragraphs (g)(2) and (g)(3) of
this AD, does not constitute terminating
action for the repetitive detailed inspection
required by paragraph (g)(1) of this AD,
unless the approved repair indicates
otherwise.
(i) Terminating Action for the Repetitive
Detailed Inspection
Modification of the belly fairing on any
airplane in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1281, Revision 01,
dated December 1, 2014, constitutes
terminating action for the repetitive detailed
inspection required by paragraph (g)(1) of
this AD for that airplane.
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(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (i) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A320–53–1281, dated July 29, 2014, which is
not incorporated by reference in this AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
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with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0259, dated
December 5, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–5814.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
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.
Issued in Renton, Washington, on
November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–30023 Filed 11–25–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–5812; Directorate
Identifier 2015–NM–077–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2011–23–
05, which applies to certain The Boeing
Company Model 737–300, –400, and
–500 series airplanes. AD 2011–23–05
currently requires repetitive inspections
for cracking of the 1.04-inch nominal
diameter wire penetration hole, and
applicable related investigative and
corrective actions. Since we issued AD
2011–23–05, an evaluation by the
design approval holder (DAH) indicates
SUMMARY:
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that the fuselage frames and frame
reinforcements are subject to
widespread fatigue damage (WFD). This
proposed AD would add new inspection
areas, a modification that terminates
certain inspections, post-modification
inspections, and repair if necessary. We
are proposing this AD to detect and
correct fatigue cracking of the fuselage
frames and frame reinforcements, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by January 11, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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, Washington. 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–
5812.
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–
5812; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
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Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: 425–
917–6447; fax: 425–917–6590; email:
wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–5812; Directorate Identifier
2015–NM–077–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Structural fatigue damage is
progressive. It begins as minute cracks,
and those cracks grow under the action
of repeated stresses. This can happen
because of normal operational
conditions and design attributes, or
because of isolated situations or
incidents such as material defects, poor
fabrication quality, or corrosion pits,
dings, or scratches. Fatigue damage can
occur locally, in small areas or
structural design details, or globally.
Global fatigue damage is general
degradation of large areas of structure
with similar structural details and stress
levels. Multiple-site damage is global
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Global damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-sitedamage and multiple-element-damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane, in a
condition known as WFD. As an
airplane ages, WFD will likely occur,
and will certainly occur if the airplane
is operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
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effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
On October 20, 2011, we issued AD
2011–23–05, Amendment 39–16856 (76
FR 67343, November 1, 2011), for
certain Model 737–300, –400, and –500
series airplanes. AD 2011–23–05
superseded AD 2009–02–06 R1,
Amendment 39–16015 (74 FR 45979,
September 8, 2009). AD 2011–23–05
requires repetitive inspections for
cracking of the 1.04-inch nominal
diameter wire penetration hole, and
applicable related investigative and
corrective actions. AD 2011–23–05
resulted from reports of cracking in the
frame, or in the frame and frame
reinforcement, common to the 1.04-inch
nominal diameter wire penetration hole
intended for wire routing; and recent
reports of multiple adjacent frame
cracking found before the compliance
time required by AD 2009–02–06 R1.
We issued AD 2011–23–05 to detect and
correct cracking in the fuselage frames
and frame reinforcements, which could
reduce the structural capability of the
frames to sustain limit loads, and result
in cracking in the fuselage skin and
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subsequent rapid depressurization of
the airplane.
Actions Since AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011), Was Issued
Since we issued AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011), an evaluation by the
DAH indicates that the fuselage frames
and frame reinforcements are subject to
WFD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. The service
information describes procedures for the
following actions.
• Inspections of wire penetration
holes, standoff/tooling holes, and the
production fastener holes for cracking in
the forward cargo compartment frames
and frame reinforcements, between
stringer (S) S–19 and S–22, on both left
and right sides of the airplane.
• A preventive modification of frames
between S–19 and S–22.
• Post-modification inspections.
• Repairs.
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 NPRM.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of these same
type designs.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011). This proposed AD
would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between this Proposed AD and the
Service Information.’’ For information
on the procedures and compliance
times, see this service information at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2015–
5812.
Differences Between This Proposed AD
and the Service Information
Boeing Alert Service Bulletin 737–
53A1279, Revision 2, dated April 21,
2015, specifies to contact the
manufacturer for instructions on how to
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repair certain conditions, but this
proposed AD would require repairing
those conditions in one of the following
ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Explanation of Compliance Time
The compliance time for the
modification specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
modified before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
Costs of Compliance
We estimate that this proposed AD
affects 605 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspections [retained actions from AD 2011–23–
05, Amendment 39–16856 (76 FR 67343, November 1, 2011).
Inspections [new proposed action] ......................
16 work-hours × $85
per hour = $1,360
per inspection cycle.
32 work-hours × $85
per hour = $2,720
per inspection cycle.
32 work-hours × $85
per hour = $2,720.
Modification [new proposed action] .....................
We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost per product
Cost on U.S. operators
$0
$1,360 per inspection
cycle.
$822,800 per inspection
cycle.
0
$2,720 per inspection
cycle.
$1,645,600 per inspection cycle.
0
$2,720 ..........................
$1,645,600.
required based on the results of the
proposed inspection. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Repair ......................................
18 work-hours × $85 per hour = $1,530 ..................................
None .......................................
Authority for This Rulemaking
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Cost per
product
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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
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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 the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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$1,530
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)
2011–23–05, Amendment 39–16856 (76
FR 67343, November 1, 2011), and
adding the following new AD:
■
The Boeing Company: Docket No. FAA–
2015–5812; Directorate Identifier 2015–
NM–077–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by January 11, 2016.
(b) Affected ADs
This AD replaces AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011).
(c) Applicability
This AD applies to The Boeing Company
Model 737–300, –400, and –500 series
airplanes; certificated in any category; as
identified in Boeing Alert Service Bulletin
737–53A1279, Revision 2, dated April 21,
2015.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicates
that the fuselage frames and frame
reinforcements are subject to widespread
fatigue damage (WFD). We are issuing this
AD to detect and correct fatigue cracking of
the fuselage frames and frame
reinforcements, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Inspection, With References To
Terminating Actions
This paragraph restates the requirements of
paragraph (g) of AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011), with references to
terminating actions. At the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, except
as required by paragraphs (k)(1), (k)(2), and
(k)(4) of this AD: Do a high frequency eddy
current (HFEC) surface or HFEC hole/edge
inspection for any cracking of the 1.04-inch
nominal diameter wire penetration hole in
the frame and frame reinforcement between
stringer (S) S–20 and S–21, in accordance
with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1279, Revision 1, dated September
2, 2011. Accomplishment of the applicable
inspections required by paragraphs (m) and
(n) of this AD terminates the inspections
required by this paragraph. Accomplishment
of the modification required by paragraph (p)
of this AD terminates the inspections
required by this paragraph for the modified
area only.
(h) Retained Repetitive Inspections, With
References To Terminating Actions
This paragraph restates the requirements of
paragraph (h) of AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011), with references to
terminating actions. Within 4,500 flight
cycles after accomplishment of the most
recent inspection specified in Part 2 or Part
4 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, or
within 90 days after November 16, 2011 (the
effective date of AD 2011–23–05), whichever
occurs later: Do an HFEC hole/edge
inspection for cracking of the 1.04-inch
nominal diameter wire penetration hole in
the frame and frame reinforcement between
S–20 and S–21, in accordance with Part 4 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011. Repeat
the inspection thereafter at intervals not to
exceed 4,500 flight cycles. Accomplishment
of the applicable inspections required by
paragraphs (m) and (n) of this AD, terminates
the inspections required by this paragraph.
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Accomplishment of the modification
specified in paragraph (j) or (p) of this AD
terminates the repetitive inspections required
by this paragraph for the modified area only.
Accomplishment of the repair specified in
paragraph (i) of this AD terminates the
repetitive inspections required by this
paragraph for the repaired area only.
(i) Retained Repair, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2011–23–05, Amendment
39–16856 (76 FR 67343, November 1, 2011),
with no changes. If any cracking is found
during any inspection required by paragraph
(g) or (h) of this AD: Before further flight,
repair the crack including doing all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 1,
dated September 2, 2011, except as required
by paragraph (k)(3) of this AD. All applicable
related investigative and corrective actions
must be done before further flight.
Accomplishment of the requirements of this
paragraph terminates the repetitive
inspection requirements of paragraph (h) of
this AD for the repaired location of that
frame.
(j) Retained Optional Terminating Action,
With New Limitation
This paragraph restates the optional action
provided in paragraph (j) of AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011), with new limitation.
Accomplishment of the preventive
modification before the effective date of this
AD, including doing all related investigative
and applicable corrective actions, specified
in Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737–
53A1279, Revision 1, dated September 2,
2011, except as required by paragraph (k)(3)
of this AD, terminates the repetitive
inspection requirements of paragraph (h) of
this AD for the modified location of that
frame, provided the modification is done
before further flight after an inspection
required by paragraph (g) or (h) of this AD
has been done, and no cracking was found
on that frame location during that inspection.
(k) Retained Exceptions to Service
Information Specifications, With No
Changes
This paragraph restates the requirements of
paragraph (k) of AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011), with no changes. The
following exceptions apply as specified in
paragraphs (g), (i), and (j) of this AD.
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, refers
to a compliance time ‘‘from date on Revision
1 of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after November 16, 2011 (the effective
date of AD 2011–23–05, Amendment 39–
16856 (76 FR 67343, November 1, 2011)).
(2) For airplanes meeting all of the criteria
specified in paragraphs (k)(2)(i), (k)(2)(ii),
and (k)(2)(iii) of this AD: The compliance
time for the initial inspection specified in
Part 2 of the Accomplishment Instructions of
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Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, and
required by paragraph (g) of this AD, may be
extended to 90 days after November 16, 2011
(the effective date of AD 2011–23–05,
Amendment 39–16856 (76 FR 67343,
November 1, 2011)).
(i) Model 737–300 series airplanes in
Group 1, line numbers 1001 through 2565
inclusive;
(ii) Airplanes that have accumulated
40,000 or more total flight cycles as of
November 16, 2011 (the effective date of AD
2011–23–05, Amendment 39–16856 (76 FR
67343, November 1, 2011)); and
(iii) Airplanes on which the modification
specified in Boeing Service Bulletin 737–53–
1273, dated September 20, 2006; Revision 1,
dated December 21, 2006; Revision 2, dated
June 4, 2007; Revision 3, dated December 7,
2009; or Revision 4, dated July 23, 2010; has
been done, including any configuration or
deviation that has been approved as an
AMOC during accomplishment of these
service bulletins, by the Boeing Commercial
Airplanes Organization Designation
Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft
Certification Office (ACO) to make those
findings.
(3) Where Boeing Alert Service Bulletin
737–53A1279, Revision 1, dated September
2, 2011, specifies to contact Boeing for
appropriate repair instructions: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (u) of this AD.
(4) The ‘‘Condition’’ column of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 1, dated
September 2, 2011, refers to total flight cycles
‘‘at the date of/on this service bulletin.’’
However, this AD applies to the airplanes
with the specified total flight cycles as of
November 16, 2011 (the effective date of AD
2011–23–05, Amendment 39–16856 (76 FR
67343, November 1, 2011)).
(l) Retained Credit for Previous Actions,
With No Changes
This paragraph restates the requirements of
paragraph (l) of AD 2011–23–05, Amendment
39–16856 (76 FR 67343, November 1, 2011),
with no changes. Actions done in accordance
with Boeing Alert Service Bulletin 737–
53A1279, dated December 18, 2007, before
November 16, 2011 (the effective date of AD
2011–23–05), are acceptable for compliance
with the corresponding actions required by
paragraphs (g), (h), (i), and (j) of this AD.
(m) New Requirement of This AD:
Inspections of Frames and Frame
Reinforcements Between S–19 and S–22 for
Certain Airplanes on Which Certain
Inspections Have Not Been Accomplished
For airplanes identified as Groups 1
through 6, Configuration 3, in Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015, with 30,000 total flight
cycles or fewer as of the effective date of this
AD, on which any inspections specified in
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, have
not been accomplished: Except as required
by paragraphs (t)(1) and (t)(2) of this AD, at
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the applicable time specified in table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015, or within
4,500 flight cycles after the effective date of
this AD, whichever occurs later, do
inspections for cracking at certain locations
in the frames and frame reinforcements in
accordance with ‘‘Part 2—Initial Detail and
HFEC Inspection’’ of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1279, Revision 2, dated April 21,
2015. Repeat the inspections for cracking at
certain locations in the frames and frame
reinforcements as specified in ‘‘Part 4—
Repeat Detail and HFEC Inspections’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015, thereafter at the
applicable interval specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015; or, before further flight after
accomplishing an inspection and no cracking
was found, do ‘‘Part 5—Preventative
Modification’’ as specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Accomplishment of the
preventive modification specified in this
paragraph terminates the repetitive
inspections required by this paragraph for the
modified area only. Do all actions specified
in this paragraph in accordance with
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015.
(n) New Requirement of This AD:
Inspections of Frames and Frame
Reinforcements Between S–19 and S–22 for
Groups 1–6, Configuration 3, Airplanes
For airplanes identified as Groups 1
through 6, Configuration 3, in Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015, with more than 30,000
total flight cycles as of the effective date of
this AD, or that have been inspected as
specified in Boeing Alert Service Bulletin
737–53A1279, Revision 1, dated September
2, 2011: Except as required by paragraphs
(t)(1) and (t)(2) of this AD, at the applicable
time specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015, do inspections for cracking at
certain locations of the frames and frame
reinforcements in accordance with ‘‘Part 4—
Repeat Detail and HFEC Inspections’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Repeat the inspections
thereafter at the applicable interval specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015; or, before
further flight after accomplishing an
inspection and no cracking was found, do
‘‘Part 5—Preventative Modification’’ as
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1279, Revision 2, dated April 21,
2015. Accomplishment of the preventive
modification specified in this paragraph
terminates the repetitive inspections required
by this paragraph for the modified area only.
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16:45 Nov 25, 2015
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(o) New Requirement of This AD: Repairs
If any crack is found during any inspection
required by paragraph (m) or (n) of this AD:
Before further flight, repair, in accordance
with ‘‘Part 3—Repair’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015, except where Boeing
Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015, specifies to
contact Boeing for damage removal and
repair instructions, repair before further
flight using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Accomplishing a
repair terminates the inspections required by
paragraphs (m) and (n) of this AD in the
repaired area only. Accomplishment of a
repair terminates the modification required
by paragraph (p) of this AD at the repaired
location only.
(p) New Requirement of This AD:
Preventative Modification of the Frames
Between S–19 and S–22
For airplanes identified as Groups 1
through 6, Configuration 3, in Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015: Except as required by
paragraphs (t)(1) and (t)(2) of this AD, at the
applicable time specified in table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015, do the
preventive modification of the frames
between S–19 and S–22, in accordance with
‘‘Part 5—Preventative Modification’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Accomplish of the
modification required by this paragraph
terminates the requirements of paragraphs
(g), (h), (m), and (n) of this AD for the
modified location only.
(q) New Requirement of This AD:
Inspections of Preventive Modification for
Groups 1–3, Configuration 1, Airplanes
For airplanes identified as Groups 1
through 3, Configuration 1, in Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015: Except as required by
paragraph (t)(1) of this AD, at the applicable
time specified in table 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015, do HFEC, LFEC, and detailed
inspections for cracking in accordance with
‘‘Part 7—INSPECTION OF PREVENTATIVE
MODIFICATION’’ of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1279, Revision 2, dated April 21,
2015. Repeat the inspections thereafter at the
applicable interval specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015. If any cracking is found
during any inspection required by this
paragraph, before further flight, repair using
a method approved in accordance with the
procedures specified in paragraph (u) of this
AD.
PO 00000
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Fmt 4702
Sfmt 4702
74051
(r) New Requirement of This AD: Inspections
of Preventive Modification for Groups 1–6,
Configuration 2
For airplanes identified as Groups 1
through 6, Configuration 2, in Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015: Except as required by
paragraph (t)(1)of this AD, at the applicable
time specified in table 4 or table 6 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015, do HFEC,
LFEC, and detailed inspections for cracking
in accordance with ‘‘Part 8—INSPECTION
OF PREVENTATIVE MODIFICATION’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Repeat the inspections
thereafter at the applicable interval specified
in table 4 or table 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015. If any cracking is found
during any inspection required by this
paragraph, before further flight, repair using
a method approved in accordance with the
procedures specified in paragraph (u) of this
AD.
(s) New Requirement of This AD: Inspections
of Preventive Modification for Group 4–6,
Configuration 1, Airplanes
For airplanes identified as Group 4 through
6, Configuration 1, in Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015: At the applicable time
specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 2, dated
April 21, 2015, except as required by
paragraph (t)(1) of this AD: Do HFEC, LFEC
and detailed inspections for cracking in
accordance with ‘‘Part 7—INSPECTION OF
PREVENTATIVE MODIFICATION’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 2,
dated April 21, 2015. Repeat the inspections
thereafter at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015. If any
cracking is found during any inspection
required by this paragraph, before further
flight, repair using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(t) New Requirement of This AD: Exceptions
to Service Bulletin Specifications
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015, refers to a
compliance time ‘‘after the Revision 2 date of
this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) The ‘‘Condition’’ column in table 1 and
table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1279,
Revision 2, dated April 21, 2015, refers to
total flight cycles ‘‘at the Revision 2 date of
this service bulletin.’’ However, this AD
applies to the airplanes with the specified
total flight cycles as of the effective date of
this AD.
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
(u) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Los Angeles 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 (v)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-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,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2009–02–06,
Amendment 39–15796 (74 FR 10469, March
11, 2009); AD 2009–02–06 R1, Amendment
39–16015 (74 FR 45979, September 6, 2009);
and AD 2011–23–05, Amendment 39–16856
(76 FR 67343, November 1, 2011); are
approved as AMOCs for the corresponding
provisions of this AD.
Federal Aviation Administration
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(v) Related Information
(1) For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO), FAA,
1601 Lind Avenue SW., Renton, Washington
98057–3356; phone: 425–917–6447; fax: 425–
917–6590; email: wayne.lockett@faa.gov.
(2) 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, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on
November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–30008 Filed 11–25–15; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:45 Nov 25, 2015
Jkt 238001
14 CFR Part 39
[Docket No. FAA–2015–5816; Directorate
Identifier 2015–NM–029–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2006–10–
16, which applies to all 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, 747SR, and 747SP
series airplanes. AD 2006–10–16
requires, for certain airplanes, repetitive
inspections for cracking of the outboard
and center sections of the horizontal
stabilizer, and repair if necessary. For
certain other airplanes, AD 2006–10–16
requires a detailed inspection to
determine the type of fasteners, and
related investigative actions and repair
if necessary. Since we issued AD 2006–
10–16, additional cracking was found in
the splice plates, hinge fittings, terminal
fittings, the upper skin of the outboard
and center sections, and the rear spar
webs before reaching the inspection
interval specified in AD 2006–10–16.
Cracked and fractured Maraging steel
fasteners were also found. This
proposed AD would reduce the
compliance time for certain inspections
and would add repetitive inspections
for cracking of the splice plates, hinge
fittings, terminal fittings, the upper skin
of the outboard and center sections, and
the rear spar webs in Zone B. This
proposed AD would also add an
inspection to determine whether
fasteners are magnetic in Zone C,
repetitive ultrasonic inspections for
cracking and fractures of affected
fasteners, and related investigative and
corrective actions if necessary. This
proposed AD would also add an
optional modification, which would
terminate certain repetitive inspections,
and would add post-modification
inspections and corrective action if
necessary. We are proposing this AD to
detect and correct this cracking, which
could lead to reduced structural
capability of the outboard and center
sections of the horizontal stabilizer and
could result in loss of control of the
airplane.
SUMMARY:
PO 00000
Frm 00049
Fmt 4702
Sfmt 4702
We must receive comments on
this proposed AD by January 11, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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–2015–
5816.
DATES:
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–
5816; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6428; fax:
425–917–6590; email:
nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
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]]>Agencies
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Proposed Rules]
[Pages 74047-74052]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30008]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-5812; Directorate Identifier 2015-NM-077-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-23-
05, which applies to certain The Boeing Company Model 737-300, -400,
and -500 series airplanes. AD 2011-23-05 currently requires repetitive
inspections for cracking of the 1.04-inch nominal diameter wire
penetration hole, and applicable related investigative and corrective
actions. Since we issued AD 2011-23-05, an evaluation by the design
approval holder (DAH) indicates that the fuselage frames and frame
reinforcements are subject to widespread fatigue damage (WFD). This
proposed AD would add new inspection areas, a modification that
terminates certain inspections, post-modification inspections, and
repair if necessary. We are proposing this AD to detect and correct
fatigue cracking of the fuselage frames and frame reinforcements, which
could result in reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by January 11,
2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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, Washington. 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-
5812.
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-
5812; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
[[Page 74048]]
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6447; fax: 425-917-6590; email: wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-5812;
Directorate Identifier 2015-NM-077-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Structural fatigue damage is progressive. It begins as minute
cracks, and those cracks grow under the action of repeated stresses.
This can happen because of normal operational conditions and design
attributes, or because of isolated situations or incidents such as
material defects, poor fabrication quality, or corrosion pits, dings,
or scratches. Fatigue damage can occur locally, in small areas or
structural design details, or globally. Global fatigue damage is
general degradation of large areas of structure with similar structural
details and stress levels. Multiple-site damage is global damage that
occurs in a large structural element such as a single rivet line of a
lap splice joining two large skin panels. Global damage can also occur
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small
initially to be reliably detected with normal inspection methods.
Without intervention, these cracks will grow, and eventually compromise
the structural integrity of the airplane, in a condition known as WFD.
As an airplane ages, WFD will likely occur, and will certainly occur if
the airplane is operated long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
On October 20, 2011, we issued AD 2011-23-05, Amendment 39-16856
(76 FR 67343, November 1, 2011), for certain Model 737-300, -400, and -
500 series airplanes. AD 2011-23-05 superseded AD 2009-02-06 R1,
Amendment 39-16015 (74 FR 45979, September 8, 2009). AD 2011-23-05
requires repetitive inspections for cracking of the 1.04-inch nominal
diameter wire penetration hole, and applicable related investigative
and corrective actions. AD 2011-23-05 resulted from reports of cracking
in the frame, or in the frame and frame reinforcement, common to the
1.04-inch nominal diameter wire penetration hole intended for wire
routing; and recent reports of multiple adjacent frame cracking found
before the compliance time required by AD 2009-02-06 R1. We issued AD
2011-23-05 to detect and correct cracking in the fuselage frames and
frame reinforcements, which could reduce the structural capability of
the frames to sustain limit loads, and result in cracking in the
fuselage skin and subsequent rapid depressurization of the airplane.
Actions Since AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November
1, 2011), Was Issued
Since we issued AD 2011-23-05, Amendment 39-16856 (76 FR 67343,
November 1, 2011), an evaluation by the DAH indicates that the fuselage
frames and frame reinforcements are subject to WFD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1279, Revision 2,
dated April 21, 2015. The service information describes procedures for
the following actions.
Inspections of wire penetration holes, standoff/tooling
holes, and the production fastener holes for cracking in the forward
cargo compartment frames and frame reinforcements, between stringer (S)
S-19 and S-22, on both left and right sides of the airplane.
A preventive modification of frames between S-19 and S-22.
Post-modification inspections.
Repairs.
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
NPRM.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2011-23-05,
Amendment 39-16856 (76 FR 67343, November 1, 2011). This proposed AD
would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between this Proposed AD and the Service Information.''
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2015-5812.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April
21, 2015, specifies to contact the manufacturer for instructions on how
to
[[Page 74049]]
repair certain conditions, but this proposed AD would require repairing
those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Explanation of Compliance Time
The compliance time for the modification specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is modified before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 605 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions 16 work-hours x $85 $0 $1,360 per $822,800 per
from AD 2011-23-05, Amendment 39- per hour = $1,360 inspection cycle. inspection cycle.
16856 (76 FR 67343, November 1, per inspection
2011). cycle.
Inspections [new proposed action] 32 work-hours x $85 0 $2,720 per $1,645,600 per
per hour = $2,720 inspection cycle. inspection cycle.
per inspection
cycle.
Modification [new proposed 32 work-hours x $85 0 $2,720............. $1,645,600.
action]. per hour = $2,720.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair................................ 18 work-hours x $85 per hour = None.................... $1,530
$1,530.
----------------------------------------------------------------------------------------------------------------
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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 removing Airworthiness Directive (AD)
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2015-5812; Directorate Identifier
2015-NM-077-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 11,
2016.
(b) Affected ADs
This AD replaces AD 2011-23-05, Amendment 39-16856 (76 FR 67343,
November 1, 2011).
(c) Applicability
This AD applies to The Boeing Company Model 737-300, -400, and -
500 series airplanes; certificated in any category; as identified in
Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April
21, 2015.
[[Page 74050]]
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicates that the fuselage frames and frame
reinforcements are subject to widespread fatigue damage (WFD). We
are issuing this AD to detect and correct fatigue cracking of the
fuselage frames and frame reinforcements, which could result in
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With References To Terminating Actions
This paragraph restates the requirements of paragraph (g) of AD
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with
references to terminating actions. At the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1279, Revision 1, dated September 2, 2011, except as required
by paragraphs (k)(1), (k)(2), and (k)(4) of this AD: Do a high
frequency eddy current (HFEC) surface or HFEC hole/edge inspection
for any cracking of the 1.04-inch nominal diameter wire penetration
hole in the frame and frame reinforcement between stringer (S) S-20
and S-21, in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision
1, dated September 2, 2011. Accomplishment of the applicable
inspections required by paragraphs (m) and (n) of this AD terminates
the inspections required by this paragraph. Accomplishment of the
modification required by paragraph (p) of this AD terminates the
inspections required by this paragraph for the modified area only.
(h) Retained Repetitive Inspections, With References To Terminating
Actions
This paragraph restates the requirements of paragraph (h) of AD
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with
references to terminating actions. Within 4,500 flight cycles after
accomplishment of the most recent inspection specified in Part 2 or
Part 4 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1279, Revision 1, dated September 2, 2011, or within
90 days after November 16, 2011 (the effective date of AD 2011-23-
05), whichever occurs later: Do an HFEC hole/edge inspection for
cracking of the 1.04-inch nominal diameter wire penetration hole in
the frame and frame reinforcement between S-20 and S-21, in
accordance with Part 4 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1279, Revision 1, dated September 2,
2011. Repeat the inspection thereafter at intervals not to exceed
4,500 flight cycles. Accomplishment of the applicable inspections
required by paragraphs (m) and (n) of this AD, terminates the
inspections required by this paragraph. Accomplishment of the
modification specified in paragraph (j) or (p) of this AD terminates
the repetitive inspections required by this paragraph for the
modified area only. Accomplishment of the repair specified in
paragraph (i) of this AD terminates the repetitive inspections
required by this paragraph for the repaired area only.
(i) Retained Repair, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with
no changes. If any cracking is found during any inspection required
by paragraph (g) or (h) of this AD: Before further flight, repair
the crack including doing all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision
1, dated September 2, 2011, except as required by paragraph (k)(3)
of this AD. All applicable related investigative and corrective
actions must be done before further flight. Accomplishment of the
requirements of this paragraph terminates the repetitive inspection
requirements of paragraph (h) of this AD for the repaired location
of that frame.
(j) Retained Optional Terminating Action, With New Limitation
This paragraph restates the optional action provided in
paragraph (j) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343,
November 1, 2011), with new limitation. Accomplishment of the
preventive modification before the effective date of this AD,
including doing all related investigative and applicable corrective
actions, specified in Part 5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, except as required by paragraph (k)(3) of this
AD, terminates the repetitive inspection requirements of paragraph
(h) of this AD for the modified location of that frame, provided the
modification is done before further flight after an inspection
required by paragraph (g) or (h) of this AD has been done, and no
cracking was found on that frame location during that inspection.
(k) Retained Exceptions to Service Information Specifications, With No
Changes
This paragraph restates the requirements of paragraph (k) of AD
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with
no changes. The following exceptions apply as specified in
paragraphs (g), (i), and (j) of this AD.
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011,
refers to a compliance time ``from date on Revision 1 of this
service bulletin,'' this AD requires compliance within the specified
compliance time after November 16, 2011 (the effective date of AD
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011)).
(2) For airplanes meeting all of the criteria specified in
paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD: The
compliance time for the initial inspection specified in Part 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1279, Revision 1, dated September 2, 2011, and required by
paragraph (g) of this AD, may be extended to 90 days after November
16, 2011 (the effective date of AD 2011-23-05, Amendment 39-16856
(76 FR 67343, November 1, 2011)).
(i) Model 737-300 series airplanes in Group 1, line numbers 1001
through 2565 inclusive;
(ii) Airplanes that have accumulated 40,000 or more total flight
cycles as of November 16, 2011 (the effective date of AD 2011-23-05,
Amendment 39-16856 (76 FR 67343, November 1, 2011)); and
(iii) Airplanes on which the modification specified in Boeing
Service Bulletin 737-53-1273, dated September 20, 2006; Revision 1,
dated December 21, 2006; Revision 2, dated June 4, 2007; Revision 3,
dated December 7, 2009; or Revision 4, dated July 23, 2010; has been
done, including any configuration or deviation that has been
approved as an AMOC during accomplishment of these service
bulletins, by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle Aircraft Certification Office (ACO) to make those
findings.
(3) Where Boeing Alert Service Bulletin 737-53A1279, Revision 1,
dated September 2, 2011, specifies to contact Boeing for appropriate
repair instructions: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (u) of this AD.
(4) The ``Condition'' column of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, refers to total flight cycles ``at the date of/on
this service bulletin.'' However, this AD applies to the airplanes
with the specified total flight cycles as of November 16, 2011 (the
effective date of AD 2011-23-05, Amendment 39-16856 (76 FR 67343,
November 1, 2011)).
(l) Retained Credit for Previous Actions, With No Changes
This paragraph restates the requirements of paragraph (l) of AD
2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with
no changes. Actions done in accordance with Boeing Alert Service
Bulletin 737-53A1279, dated December 18, 2007, before November 16,
2011 (the effective date of AD 2011-23-05), are acceptable for
compliance with the corresponding actions required by paragraphs
(g), (h), (i), and (j) of this AD.
(m) New Requirement of This AD: Inspections of Frames and Frame
Reinforcements Between S-19 and S-22 for Certain Airplanes on Which
Certain Inspections Have Not Been Accomplished
For airplanes identified as Groups 1 through 6, Configuration 3,
in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated
April 21, 2015, with 30,000 total flight cycles or fewer as of the
effective date of this AD, on which any inspections specified in
Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, have not been accomplished: Except as required by
paragraphs (t)(1) and (t)(2) of this AD, at
[[Page 74051]]
the applicable time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 2, dated April 21, 2015, or within 4,500 flight cycles
after the effective date of this AD, whichever occurs later, do
inspections for cracking at certain locations in the frames and
frame reinforcements in accordance with ``Part 2--Initial Detail and
HFEC Inspection'' of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015.
Repeat the inspections for cracking at certain locations in the
frames and frame reinforcements as specified in ``Part 4--Repeat
Detail and HFEC Inspections'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April
21, 2015, thereafter at the applicable interval specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015; or, before further
flight after accomplishing an inspection and no cracking was found,
do ``Part 5--Preventative Modification'' as specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1279, Revision 2, dated April 21, 2015. Accomplishment of the
preventive modification specified in this paragraph terminates the
repetitive inspections required by this paragraph for the modified
area only. Do all actions specified in this paragraph in accordance
with Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015.
(n) New Requirement of This AD: Inspections of Frames and Frame
Reinforcements Between S-19 and S-22 for Groups 1-6, Configuration 3,
Airplanes
For airplanes identified as Groups 1 through 6, Configuration 3,
in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated
April 21, 2015, with more than 30,000 total flight cycles as of the
effective date of this AD, or that have been inspected as specified
in Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011: Except as required by paragraphs (t)(1) and
(t)(2) of this AD, at the applicable time specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015, do inspections for
cracking at certain locations of the frames and frame reinforcements
in accordance with ``Part 4--Repeat Detail and HFEC Inspections'' of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015. Repeat the
inspections thereafter at the applicable interval specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015; or, before further
flight after accomplishing an inspection and no cracking was found,
do ``Part 5--Preventative Modification'' as specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1279, Revision 2, dated April 21, 2015. Accomplishment of the
preventive modification specified in this paragraph terminates the
repetitive inspections required by this paragraph for the modified
area only.
(o) New Requirement of This AD: Repairs
If any crack is found during any inspection required by
paragraph (m) or (n) of this AD: Before further flight, repair, in
accordance with ``Part 3--Repair'' of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision
2, dated April 21, 2015, except where Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015, specifies to contact
Boeing for damage removal and repair instructions, repair before
further flight using a method approved in accordance with the
procedures specified in paragraph (u) of this AD. Accomplishing a
repair terminates the inspections required by paragraphs (m) and (n)
of this AD in the repaired area only. Accomplishment of a repair
terminates the modification required by paragraph (p) of this AD at
the repaired location only.
(p) New Requirement of This AD: Preventative Modification of the Frames
Between S-19 and S-22
For airplanes identified as Groups 1 through 6, Configuration 3,
in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated
April 21, 2015: Except as required by paragraphs (t)(1) and (t)(2)
of this AD, at the applicable time specified in table 2 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 2, dated April 21, 2015, do the preventive modification of
the frames between S-19 and S-22, in accordance with ``Part 5--
Preventative Modification'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April
21, 2015. Accomplish of the modification required by this paragraph
terminates the requirements of paragraphs (g), (h), (m), and (n) of
this AD for the modified location only.
(q) New Requirement of This AD: Inspections of Preventive Modification
for Groups 1-3, Configuration 1, Airplanes
For airplanes identified as Groups 1 through 3, Configuration 1,
in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated
April 21, 2015: Except as required by paragraph (t)(1) of this AD,
at the applicable time specified in table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed
inspections for cracking in accordance with ``Part 7--INSPECTION OF
PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April
21, 2015. Repeat the inspections thereafter at the applicable
interval specified in paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1279, Revision 2, dated April 21,
2015. If any cracking is found during any inspection required by
this paragraph, before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(u) of this AD.
(r) New Requirement of This AD: Inspections of Preventive Modification
for Groups 1-6, Configuration 2
For airplanes identified as Groups 1 through 6, Configuration 2,
in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated
April 21, 2015: Except as required by paragraph (t)(1)of this AD, at
the applicable time specified in table 4 or table 6 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed
inspections for cracking in accordance with ``Part 8--INSPECTION OF
PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April
21, 2015. Repeat the inspections thereafter at the applicable
interval specified in table 4 or table 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 2, dated April 21, 2015. If any cracking is found during
any inspection required by this paragraph, before further flight,
repair using a method approved in accordance with the procedures
specified in paragraph (u) of this AD.
(s) New Requirement of This AD: Inspections of Preventive Modification
for Group 4-6, Configuration 1, Airplanes
For airplanes identified as Group 4 through 6, Configuration 1,
in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated
April 21, 2015: At the applicable time specified in table 5 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015, except as required by
paragraph (t)(1) of this AD: Do HFEC, LFEC and detailed inspections
for cracking in accordance with ``Part 7--INSPECTION OF PREVENTATIVE
MODIFICATION'' of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015.
Repeat the inspections thereafter at the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1279, Revision 2, dated April 21, 2015. If any cracking is
found during any inspection required by this paragraph, before
further flight, repair using a method approved in accordance with
the procedures specified in paragraph (u) of this AD.
(t) New Requirement of This AD: Exceptions to Service Bulletin
Specifications
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015,
refers to a compliance time ``after the Revision 2 date of this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) The ``Condition'' column in table 1 and table 2 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 2, dated April 21, 2015, refers to total flight cycles ``at
the Revision 2 date of this service bulletin.'' However, this AD
applies to the airplanes with the specified total flight cycles as
of the effective date of this AD.
[[Page 74052]]
(u) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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 (v)(1) of this AD.
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved for AD 2009-02-06, Amendment 39-15796 (74 FR
10469, March 11, 2009); AD 2009-02-06 R1, Amendment 39-16015 (74 FR
45979, September 6, 2009); and AD 2011-23-05, Amendment 39-16856 (76
FR 67343, November 1, 2011); are approved as AMOCs for the
corresponding provisions of this AD.
(v) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone: 425-917-6447; fax: 425-917-6590;
email: wayne.lockett@faa.gov.
(2) 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, 1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-30008 Filed 11-25-15; 8:45 am]
BILLING CODE 4910-13-P
