Airworthiness Directives; The Boeing Company Airplanes, 29505-29508 [2016-11167]
Download as PDF
<![CDATA[
29505
Proposed Rules
Federal Register
Vol. 81, No. 92
Thursday, May 12, 2016
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6670; Directorate
Identifier 2016–NM–006–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) 2013–19–
04, which applies to certain The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 series airplanes. AD
2013–19–04 currently requires
repetitive detailed and high frequency
eddy current (HFEC) inspections for
cracking of the skin around the eight
fasteners common to the ends of the
station (STA) 540 bulkhead chords
between stringers S–22 and S–23, left
and right sides; related investigative
actions and corrective actions, if
necessary; and provides an optional
terminating modification. Since we
issued AD 2013–19–04, we have
received reports of additional cracks
that are larger and initiated sooner than
previously predicted. This proposed AD
would reduce the inspection threshold
and repetitive inspection intervals. We
are proposing this AD to detect and
correct fatigue cracking in the fuselage
skin around the eight fasteners securing
the STA 540 bulkhead chords. Such
cracking can result in rapid
decompression of the cabin.
DATES: We must receive comments on
this proposed AD by June 27, 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.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
13:23 May 11, 2016
Jkt 238001
• 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 NPRM, 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–2016–
6670.
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–2016–
6670; 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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6450; fax:
425–917–6590; email: alan.pohl@
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.
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
FAA–2016–6670; Directorate Identifier
2016–NM–006–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
On September 9, 2013, we issued AD
2013–19–04, Amendment 39–17586 (78
FR 59801, September 30, 2013) (‘‘AD
2013–19–04’’), for certain The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 series airplanes. AD
2013–19–04 requires repetitive detailed
and HFEC inspections for cracking of
the skin around the eight fasteners
common to the ends of the STA 540
bulkhead chords between stringers S–22
and S–23, left and right sides; related
investigative actions and corrective
actions, if necessary; and provides an
optional terminating modification. AD
2013–19–04 resulted from a report of
cracks found in the skin at body STA
540 just below the left side of stringer
S–22 on a Model 737–700 series
airplane. We issued AD 2013–19–04 to
detect and correct fatigue cracking in
the fuselage skin around the eight
fasteners securing the STA 540
bulkhead chords, which can result in
rapid decompression of the cabin.
Actions Since AD 2013–19–04 Was
Issued
Since we issued AD 2013–19–04, we
have received reports of cracks that
initiated sooner and are larger than
previously predicted.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Special
Attention Service Bulletin 737–53–
1294, Revision 2, dated December 9,
2015, which specifies procedures for
doing inspections for cracking of the
skin around the eight fasteners common
to the ends of the STA 540 bulkhead
chords between stringers S–22 and S–
23, left and right sides, repairing cracks,
E:\FR\FM\12MYP1.SGM
12MYP1
29506
Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules
and installing a chord splice as a
preventive modification on crack-free
skin. 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.
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 the same
type designs.
Proposed AD Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2013–19–04, this proposed AD would
retain all of the requirements of AD
2013–19–04. Those requirements are
referenced in the service information
identified previously, which, in turn, is
referenced in paragraphs (g) through (k)
of this proposed AD. 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–2016–
6670.
The phrase ‘‘related investigative
actions’’ is used in this proposed AD.
Related investigative actions are followon actions that (1) are related to the
primary action, and (2) further
investigate the nature of any condition
found. Related investigative actions in
an AD could include, for example,
inspections.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. Corrective
actions correct or address any condition
found. Corrective actions in an AD
could include, for example, repairs.
Differences Between This Proposed AD
and the Service Information
Boeing Special Attention Service
Bulletin 737–53–1294, Revision 2, dated
December 9, 2015, specifies to contact
the manufacturer for instructions on
how to repair certain conditions, but
this proposed AD would require
accomplishment of repair methods,
modification deviations, and alteration
deviations 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.
Costs of Compliance
We estimate that this proposed AD
affects 903 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection (left and right
side skins).
12 work-hours × $85 per hour = $1,020
per inspection cycle.
Cost per
product
Parts cost
$0
We estimate the following costs to do
any necessary repairs and inspections
Cost on U.S. operators
$1,020 per inspection
cycle.
that would be required based on the
results of the proposed inspection. We
$921,060 per inspection
cycle.
have no way of determining the number
of aircraft that might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Preventive modification (each side) ..........................
Skin repair (each side) ..............................................
7 work-hours × $85 per hour = $595 ........................
39 work-hours × $85 per hour = $3,315 ...................
$894 .................
Up to $5,635 .....
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
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,
VerDate Sep<11>2014
13:23 May 11, 2016
Jkt 238001
‘‘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
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
Cost per
product
$1,489.
Up to $8,950.
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.
E:\FR\FM\12MYP1.SGM
12MYP1
Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules
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
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)
2013–19–04, Amendment 39–17586 (78
FR 59801, September 30, 2013), and
adding the following new AD:
■
The Boeing Company: Docket No. FAA–
2016–6670; Directorate Identifier 2016–
NM–006–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by June 27, 2016.
(b) Affected ADs
This AD replaces AD 2013–19–04,
Amendment 39–17586 (78 FR 59801,
September 30, 2013) (‘‘AD 2013–19–04’’).
(c) Applicability
This AD applies to The Boeing Company
Model 737–600, –700, –700C, –800, and –900
series airplanes; certificated in any category;
as identified in Boeing Special Attention
Service Bulletin 737–53–1294, Revision 2,
dated December 9, 2015.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of
cracks found in the skin at body station
(STA) 540 just below the left side of stringer
S–22. We are issuing this AD to detect and
correct fatigue cracking in the fuselage skin
around the eight fasteners securing the STA
540 bulkhead chords, which can result in
rapid decompression of the cabin.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Corrective Action
Except as required by paragraphs (i)(1) and
(i)(2) of this AD, at the applicable time
specified in table 1 of paragraph 1.E.
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 737–53–1294, Revision 2,
dated December 9, 2015: Do detailed and
high frequency eddy current (HFEC)
inspections for cracking of the skin in the
area around the eight fasteners securing the
VerDate Sep<11>2014
13:23 May 11, 2016
Jkt 238001
STA 540 bulkhead chords between stringers
S–22 and S–23; and do all applicable related
investigative and corrective actions; in
accordance with Parts 1, 2, 3, 4, and 5 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–53–
1294, Revision 2, dated December 9, 2015,
except as required by paragraphs (i)(3) and
(i)(4) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the detailed and HFEC
inspections thereafter at the intervals
specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 737–53–1294, Revision 2,
dated December 9, 2015, until the optional
preventive modification specified in
paragraph (h) of this AD is done.
(h) Optional Preventive Modification
Accomplishing the preventive
modification or repair, including an HFEC
inspection for cracking of the skin and STA
540 bulkhead chords, and all applicable
repairs, in accordance with paragraph 3.B,
Part 2 or Part 4 (left side), and Part 3 or Part
5 (right side), of the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1294, Revision 2,
dated December 9, 2015, except as required
by paragraph (i)(2) of this AD, terminates the
inspection requirements of paragraph (g) of
this AD for the side on which the
modification is done.
(i) Exceptions to Service Bulletin
Specifications
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
737–53–1294, Revision 2, dated December 9,
2015, specifies 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) For airplanes on which Boeing Business
Jet Lower Cabin Altitude Supplemental Type
Certificate (STC) ST01697SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/
0812969a86af879b8625766400600105/$FILE/
ST01697SE.pdf) (6,500 feet maximum cabin
altitude in lieu of 8,000 feet) has been
incorporated, the flight-cycle related
compliance times for the inspection required
by paragraph (g) of this AD are different from
those specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 737–53–1294, Revision 2,
dated December 9, 2015. All initial
compliance times specified in total flight
cycles or flight cycles must be reduced to half
of those specified in Boeing Special
Attention Service Bulletin 737–53–1294,
Revision 2, dated December 9, 2015. All
repetitive interval compliance times
specified in flight cycles must be reduced to
one-quarter of those specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Special
Attention Service Bulletin 737–53–1294,
Revision 2, dated December 9, 2015.
(3) If any cracking is found during any
inspection required by this AD, and Boeing
Special Attention Service Bulletin 737–53–
1294, Revision 2, dated December 9, 2015,
specifies to contact Boeing for appropriate
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
29507
action: Before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (l) of this
AD.
(4) The access and restoration instructions
identified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1294, Revision 2,
dated December 9, 2015, are not required by
this AD. Operators may perform those actions
in accordance with approved maintenance
procedures.
(j) Part 26 Supplemental Inspections Not
Required by This AD
Table 2 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Special Attention Service Bulletin
737–53–1294, Revision 2, dated December 9,
2015, specifies post-modification
airworthiness limitation inspections in
compliance with 14 CFR 25.571(a)(3) at the
modified locations, which support
compliance with 14 CFR 121.1109(c)(2) or
129.109(b)(2). As airworthiness limitations,
these inspections are required by
maintenance and operational rules. It is
therefore unnecessary to mandate them in
this AD. Deviations from these inspections
require FAA approval, but do not require an
alternative method of compliance.
(k) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Special Attention Service Bulletin
737–53–1294, dated March 31, 2011, which
is not incorporated by reference in this AD;
or Boeing Special Attention Service Bulletin
737–53–1294, Revision 1, dated June 14,
2013, which is incorporated by reference in
AD 2013–19–04.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (m) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
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.
E:\FR\FM\12MYP1.SGM
12MYP1
29508
Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules
(4) AMOCs approved previously for the
optional preventive modification installed in
accordance with paragraph (h) of AD 2013–
19–04, and AMOCs approved previously for
repairs for AD 2013–19–04, are approved as
AMOCs for the corresponding provisions of
this AD, provided that such modification or
repair included installation of the splice
plate as specified in Boeing Special Attention
Service Bulletin 737–53–1294, except as
provided by paragraph (l)(5) of this AD.
(5) The time-limited repair approved as
specified in FAA Letter 120S–15–140, dated
June 3, 2015, is approved as an AMOC to the
corresponding requirements of this AD.
(m) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6450; fax: 425–917–6590;
email: alan.pohl@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, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. 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.
Issued in Renton, Washington, on May 5,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–11167 Filed 5–11–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6669; Directorate
Identifier 2015–NM–191–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
jstallworth on DSK7TPTVN1PROD with PROPOSALS
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2006–20–
11, which applies to certain The Boeing
Company Model 757–200, –200CB, and
–200PF series airplanes. AD 2006–20–
11 currently requires initial and
repetitive detailed or high frequency
SUMMARY:
VerDate Sep<11>2014
13:23 May 11, 2016
Jkt 238001
eddy current (HFEC) inspections for
cracks around the rivets at the upper
fastener row of the skin lap splice of the
fuselage, and repairing any crack found.
Since we issued AD 2006–20–11, an
evaluation done by the design approval
holder (DAH) indicated that the fuselage
skin lap splice is subject to widespread
fatigue damage (WFD). This proposed
AD would no longer allow the detailed
inspections and would instead require
repetitive external HFEC inspections for
cracking of the skin lap splices of the
fuselage, and repair if necessary. We are
proposing this AD to detect and correct
fatigue cracking at certain skin lap
splice locations of the fuselage, which
could result in reduced structural
integrity and rapid decompression of
the airplane.
DATES: We must receive comments on
this proposed AD by June 27, 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 NPRM, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood
Boulevard, MC D800–0019, Long Beach,
CA 90846–0001; telephone: 206–544–
5000, extension 2; fax: 206–766–5683;
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–2016–
6669.
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–2016–
6669; 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
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
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: Eric
Schrieber, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5348; fax: 562–627–5210;
email: eric.schrieber@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–2016–6669; Directorate Identifier
2015–NM–191–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
On September 22, 2006, we issued AD
2006–20–11, Amendment 39–14781 (71
FR 58485, October 4, 2006) (‘‘AD 2006–
20–11’’), for certain The Boeing
Company Model 757–200, –200CB, and
–200PF series airplanes. AD 2006–20–
11 requires initial and repetitive
detailed or HFEC inspections for cracks
around the rivets at the upper fastener
row of the skin lap splice of the
fuselage, and repairing any crack found.
AD 2006–20–11 resulted from reports of
cracking in the fuselage skin of the
crown skin panel. We issued AD 2006–
20–11 to detect and correct premature
fatigue cracking at certain skin lap
splice locations of the fuselage, and
consequent rapid decompression of the
airplane.
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
E:\FR\FM\12MYP1.SGM
12MYP1
]]>Agencies
[Federal Register Volume 81, Number 92 (Thursday, May 12, 2016)]
[Proposed Rules]
[Pages 29505-29508]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11167]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 /
Proposed Rules
[[Page 29505]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6670; Directorate Identifier 2016-NM-006-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) 2013-19-
04, which applies to certain The Boeing Company Model 737-600, -700, -
700C, -800, and -900 series airplanes. AD 2013-19-04 currently requires
repetitive detailed and high frequency eddy current (HFEC) inspections
for cracking of the skin around the eight fasteners common to the ends
of the station (STA) 540 bulkhead chords between stringers S-22 and S-
23, left and right sides; related investigative actions and corrective
actions, if necessary; and provides an optional terminating
modification. Since we issued AD 2013-19-04, we have received reports
of additional cracks that are larger and initiated sooner than
previously predicted. This proposed AD would reduce the inspection
threshold and repetitive inspection intervals. We are proposing this AD
to detect and correct fatigue cracking in the fuselage skin around the
eight fasteners securing the STA 540 bulkhead chords. Such cracking can
result in rapid decompression of the cabin.
DATES: We must receive comments on this proposed AD by June 27, 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 NPRM, 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-2016-6670.
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-2016-
6670; 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax:
425-917-6590; email: alan.pohl@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-2016-6670;
Directorate Identifier 2016-NM-006-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
On September 9, 2013, we issued AD 2013-19-04, Amendment 39-17586
(78 FR 59801, September 30, 2013) (``AD 2013-19-04''), for certain The
Boeing Company Model 737-600, -700, -700C, -800, and -900 series
airplanes. AD 2013-19-04 requires repetitive detailed and HFEC
inspections for cracking of the skin around the eight fasteners common
to the ends of the STA 540 bulkhead chords between stringers S-22 and
S-23, left and right sides; related investigative actions and
corrective actions, if necessary; and provides an optional terminating
modification. AD 2013-19-04 resulted from a report of cracks found in
the skin at body STA 540 just below the left side of stringer S-22 on a
Model 737-700 series airplane. We issued AD 2013-19-04 to detect and
correct fatigue cracking in the fuselage skin around the eight
fasteners securing the STA 540 bulkhead chords, which can result in
rapid decompression of the cabin.
Actions Since AD 2013-19-04 Was Issued
Since we issued AD 2013-19-04, we have received reports of cracks
that initiated sooner and are larger than previously predicted.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 737-53-1294,
Revision 2, dated December 9, 2015, which specifies procedures for
doing inspections for cracking of the skin around the eight fasteners
common to the ends of the STA 540 bulkhead chords between stringers S-
22 and S-23, left and right sides, repairing cracks,
[[Page 29506]]
and installing a chord splice as a preventive modification on crack-
free skin. 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.
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 the same type designs.
Proposed AD Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2013-19-04, this proposed AD would retain all of the
requirements of AD 2013-19-04. Those requirements are referenced in the
service information identified previously, which, in turn, is
referenced in paragraphs (g) through (k) of this proposed AD. 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-2016-6670.
The phrase ``related investigative actions'' is used in this
proposed AD. Related investigative actions are follow-on actions that
(1) are related to the primary action, and (2) further investigate the
nature of any condition found. Related investigative actions in an AD
could include, for example, inspections.
The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Special Attention Service Bulletin 737-53-1294, Revision 2,
dated December 9, 2015, specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require accomplishment of repair methods, modification
deviations, and alteration deviations 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.
Costs of Compliance
We estimate that this proposed AD affects 903 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
----------------------------------------------------------------------------------------------------------------
Inspection (left and right side 12 work-hours x $85 $0 $1,020 per $921,060 per
skins). per hour = $1,020 inspection cycle. inspection cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs and
inspections 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
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Preventive modification (each 7 work-hours x $85 $894...................... $1,489.
side). per hour = $595.
Skin repair (each side)........... 39 work-hours x $85 Up to $5,635.............. Up to $8,950.
per hour = $3,315.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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.
[[Page 29507]]
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)
2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2016-6670; Directorate Identifier
2016-NM-006-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by June 27,
2016.
(b) Affected ADs
This AD replaces AD 2013-19-04, Amendment 39-17586 (78 FR 59801,
September 30, 2013) (``AD 2013-19-04'').
(c) Applicability
This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, and -900 series airplanes; certificated in any category;
as identified in Boeing Special Attention Service Bulletin 737-53-
1294, Revision 2, dated December 9, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracks found in the skin at
body station (STA) 540 just below the left side of stringer S-22. We
are issuing this AD to detect and correct fatigue cracking in the
fuselage skin around the eight fasteners securing the STA 540
bulkhead chords, which can result in rapid decompression of the
cabin.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Corrective Action
Except as required by paragraphs (i)(1) and (i)(2) of this AD,
at the applicable time specified in table 1 of paragraph 1.E.
``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-
1294, Revision 2, dated December 9, 2015: Do detailed and high
frequency eddy current (HFEC) inspections for cracking of the skin
in the area around the eight fasteners securing the STA 540 bulkhead
chords between stringers S-22 and S-23; and do all applicable
related investigative and corrective actions; in accordance with
Parts 1, 2, 3, 4, and 5 of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737-53-1294, Revision 2, dated
December 9, 2015, except as required by paragraphs (i)(3) and (i)(4)
of this AD. Do all applicable related investigative and corrective
actions before further flight. Repeat the detailed and HFEC
inspections thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 737-53-1294, Revision 2, dated December 9, 2015, until the
optional preventive modification specified in paragraph (h) of this
AD is done.
(h) Optional Preventive Modification
Accomplishing the preventive modification or repair, including
an HFEC inspection for cracking of the skin and STA 540 bulkhead
chords, and all applicable repairs, in accordance with paragraph
3.B, Part 2 or Part 4 (left side), and Part 3 or Part 5 (right
side), of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1294, Revision 2, dated December
9, 2015, except as required by paragraph (i)(2) of this AD,
terminates the inspection requirements of paragraph (g) of this AD
for the side on which the modification is done.
(i) Exceptions to Service Bulletin Specifications
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1294, Revision 2, dated December
9, 2015, specifies 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) For airplanes on which Boeing Business Jet Lower Cabin
Altitude Supplemental Type Certificate (STC) ST01697SE (https://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
0812969a86af879b8625766400600105/$FILE/ST01697SE.pdf) (6,500 feet
maximum cabin altitude in lieu of 8,000 feet) has been incorporated,
the flight-cycle related compliance times for the inspection
required by paragraph (g) of this AD are different from those
specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1294, Revision 2, dated December
9, 2015. All initial compliance times specified in total flight
cycles or flight cycles must be reduced to half of those specified
in Boeing Special Attention Service Bulletin 737-53-1294, Revision
2, dated December 9, 2015. All repetitive interval compliance times
specified in flight cycles must be reduced to one-quarter of those
specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1294, Revision 2, dated December
9, 2015.
(3) If any cracking is found during any inspection required by
this AD, and Boeing Special Attention Service Bulletin 737-53-1294,
Revision 2, dated December 9, 2015, specifies to contact Boeing for
appropriate action: Before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(l) of this AD.
(4) The access and restoration instructions identified in the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1294, Revision 2, dated December 9, 2015, are not
required by this AD. Operators may perform those actions in
accordance with approved maintenance procedures.
(j) Part 26 Supplemental Inspections Not Required by This AD
Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1294, Revision 2, dated December
9, 2015, specifies post-modification airworthiness limitation
inspections in compliance with 14 CFR 25.571(a)(3) at the modified
locations, which support compliance with 14 CFR 121.1109(c)(2) or
129.109(b)(2). As airworthiness limitations, these inspections are
required by maintenance and operational rules. It is therefore
unnecessary to mandate them in this AD. Deviations from these
inspections require FAA approval, but do not require an alternative
method of compliance.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Special Attention
Service Bulletin 737-53-1294, dated March 31, 2011, which is not
incorporated by reference in this AD; or Boeing Special Attention
Service Bulletin 737-53-1294, Revision 1, dated June 14, 2013, which
is incorporated by reference in AD 2013-19-04.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (m) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, 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.
[[Page 29508]]
(4) AMOCs approved previously for the optional preventive
modification installed in accordance with paragraph (h) of AD 2013-
19-04, and AMOCs approved previously for repairs for AD 2013-19-04,
are approved as AMOCs for the corresponding provisions of this AD,
provided that such modification or repair included installation of
the splice plate as specified in Boeing Special Attention Service
Bulletin 737-53-1294, except as provided by paragraph (l)(5) of this
AD.
(5) The time-limited repair approved as specified in FAA Letter
120S-15-140, dated June 3, 2015, is approved as an AMOC to the
corresponding requirements of this AD.
(m) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6450; fax: 425-917-6590; email: alan.pohl@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, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. 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.
Issued in Renton, Washington, on May 5, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-11167 Filed 5-11-16; 8:45 am]
BILLING CODE 4910-13-P
