Airworthiness Directives; The Boeing Company Airplanes, 25357-25360 [2016-09647]
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25357
Proposed Rules
Federal Register
Vol. 81, No. 82
Thursday, April 28, 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–2016–5598; Directorate
Identifier 2016–NM–001–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) 2012–22–
02, which applies to certain The Boeing
Company Model 747–400, –400D, and
–400F series airplanes. AD 2012–22–02
currently requires measuring the web at
station (STA) 320 and, depending on
findings, various inspections for cracks
and missing fasteners, web and fastener
replacement, and related investigative
and corrective actions if necessary.
Since we issued AD 2012–22–02, it was
determined that there were no
inspection or repair procedures
included for airplanes with a STA 320
crown frame web thickness less than
0.078 inch, or greater than or equal to
0.084 inch and less than or equal to
0.135 inch. This proposed AD would
require, for certain airplanes,
replacement of the web, including
related investigative and corrective
actions if necessary. We are issuing this
AD to prevent complete fracture of the
crown frame assembly, and consequent
damage to the skin. Such damage could
result in in-flight decompression of the
airplane.
DATES: We must receive comments on
this proposed AD by June 13, 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.
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SUMMARY:
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• 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–
5598.
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–
5598; 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: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: Bill.Ashforth@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–2016–5598; Directorate Identifier
PO 00000
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Fmt 4702
Sfmt 4702
2016–NM–001–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 October 19, 2012, we issued AD
2012–22–02, Amendment 39–17238 (77
FR 69739, November 21, 2012) (‘‘AD
2012–22–02’’), for certain The Boeing
Company Model 747–400, –400D, and
–400F series airplanes. AD 2012–22–02
requires measuring the web at STA 320
and, depending on findings, various
inspections for cracks and missing
fasteners, web and fastener replacement,
and related investigative and corrective
actions if necessary. AD 2012–22–02
resulted from reports of crown frame
web cracking at left buttock line (LBL)
15.0, STA 320. We issued AD 2012–22–
02 to prevent complete fracture of the
crown frame assembly, and consequent
damage to the skin and in-flight
decompression of the airplane.
Actions Since AD 2012–22–02 Was
Issued
Since we issued AD 2012–22–02, it
was determined that there was no work
included for airplanes with a STA 320
crown frame web thickness less than
0.078 inch, or greater than or equal to
0.084 inch and less than or equal to
0.135 inch.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–53A2784, Revision 2,
dated August 20, 2015. The service
information describes procedures for
various inspections for cracks and
missing fasteners, web and fastener
replacement, and related investigative
and corrective actions, if necessary. 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.
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Federal Register / Vol. 81, No. 82 / Thursday, April 28, 2016 / Proposed Rules
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 design.
Proposed AD Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2012–22–02, this proposed AD would
retain certain requirements of AD 2012–
22–02. Those requirements are
referenced in the service information
identified previously, which, in turn, is
referenced in paragraphs (h), (i), and (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 the 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–
5598.
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
For Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August
20, 2015, Table 4: STA 320 Post Web
Replacement Inspection of paragraph
1.E., ‘‘Compliance,’’ the conditional
action statement does not include
airplanes that were inspected or
repaired in accordance with Part 8 of
the Work Instructions. The statement
should read: ‘‘All airplanes that have
done the STA 320 crown frame web
replacement in accordance with
paragraph 3.B. WORK INSTRUCTIONS,
PARTS 5 OR PART 8.’’ Paragraph (k) of
this proposed AD applies to all
airplanes on which a web replacement
is done as required by paragraphs (h),
(i), and (j) of the proposed AD, e.g., the
replacement is done as specified in Part
5 or Part 8 of paragraph 3.B., ‘‘Work
Instructions,’’ of the service
information.
Costs of Compliance
We estimate that this proposed AD
affects 29 airplanes.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Measurement, inspection,
and web replacement. [retained actions from AD
2012-22-02].
Post-replacement inspection
[retained actions from AD
2012-22-02].
Labor cost
Cost per product
Up to $21,887
Up to $40,502 per inspection and replacement.
$Up to 1,174,558.
135 work-hours × $85 per
hour = $11,475 per inspection cycle.
$0 ..................
$11,475 per inspection cycle
$332,775 per inspection cycle.
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.
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.
Regulatory Findings
List of Subjects in 14 CFR Part 39
We have determined that this
proposed AD would not have federalism
implications under Executive Order
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Cost on U.S. operators
219 work-hours × $85 per
hour = $18,615.
Authority for This Rulemaking
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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)
2012–22–02, Amendment 39–17238 (77
FR 69739 November 21, 2012), and
adding the following new AD:
■
The Boeing Company: Docket No. FAA–
2016–5598; Directorate Identifier 2016–
NM–001–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by June 13, 2016.
(b) Affected ADs
This AD replaces AD 2012–22–02,
Amendment 39–17238 (77 FR 69739,
November 21, 2012) (‘‘AD 2012–22–02’’).
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(c) Applicability
This AD applies to The Boeing Company
Model 747–400, –400D, and –400F series
airplanes, certificated in any category, as
specified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of crown
frame web cracking at left buttock line (LBL)
15.0, station (STA) 320 and a determination
that there were no inspection or repair
procedures included in AD 2012–22–02 for
airplanes with a STA 320 crown frame web
thickness less than 0.078 inch, or greater than
or equal to 0.084 inch and less than or equal
to 0.135 inch. We are issuing this AD to
prevent complete fracture of the crown frame
assembly, and consequent damage to the
skin. Such damage could result in in-flight
decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Crown Frame Web Measurement for
Certain Airplanes
For Group 1, Configuration 3 airplanes
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: At the compliance time specified in
Table 1 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, measure
the thickness of the crown frame web at STA
320, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, except as required by paragraph (l)(2)
of this AD. Do all related investigative and
corrective actions at the applicable times
specified in Table 2 and Table 3 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015.
(h) Inspections (Web With No Repair
Doubler) and Related Investigative and
Corrective Actions (Including Web
Replacement)
For Group 1, Configuration 1 airplanes
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less
than 0.136 inch and no repair doubler
installed on the web, at the time specified in
Table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, do a
detailed inspection for cracks and a general
visual inspection for missing fasteners of the
crown frame web at STA 320; and do all
applicable related investigative and
corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2784, Revision 2,
dated August 20, 2015, except as specified in
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paragraph (l)(2) of this AD. Do the applicable
related investigative and corrective actions at
the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015.
(i) Inspection (Web With Repair Doubler)
and Related Investigative and Corrective
Actions (Including Web Replacement)
For Group 1, Configuration 1 airplanes
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less
than 0.136 inch and a repair doubler
installed on the web, at the time specified in
Table 3 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, do a
detailed inspection for any crack in the upper
chord and lower chord of the STA 320 crown
frame; and do all applicable related
investigative and corrective actions; in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, except as specified in paragraph (l)(2)
of this AD. Do the applicable related
investigative and corrective actions at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015. At the applicable
compliance time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015, except as provided by
paragraph (l)(1) of this AD, do the actions
specified in paragraphs (i)(1) and (i)(2) of this
AD, and do all applicable corrective actions,
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2784, Revision 2, dated August 20, 2015,
except as required by paragraph (l)(2) of this
AD. Do all applicable corrective actions
before further flight.
(1) Replace the web with a new web and
do all applicable related investigative
actions.
(2) Do a detailed inspection for cracks in
the upper or lower chord of the crown frame
web at STA 320.
(j) Web Replacement for Certain Airplanes
For Group 1, Configuration 2 airplanes
identified in Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015: At the applicable time specified in
Table 5 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015, except as
provided by paragraph (l)(1) of this AD,
replace the web, including doing related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, except as required by paragraph (l)(2)
of this AD. Do all applicable related
investigative and corrective actions before
further flight.
(k) Post-Replacement Repetitive Inspections
of Replaced Web
Following any web replacement required
by this AD, at the time specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
PO 00000
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25359
Bulletin 747–53A2784, Revision 2, dated
August 20, 2015: Do a detailed inspection for
cracks of the web, upper chord, lower chord,
and lower chord splice, and do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2784, Revision 2,
dated August 20, 2015, except as required by
paragraph (l)(2) of this AD. Do all applicable
corrective actions before further flight. If no
crack is found, repeat the inspection
thereafter at the intervals specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2784,
Revision 2, dated August 20, 2015.
Accomplishment of the inspections required
by AD 2009–19–05, Amendment 39–16022
(74 FR 48138, September 22, 2009),
terminates the requirements of this
paragraph.
(l) Exceptions to the Service Information
With Updated Service Information
(1) Where Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, specifies a compliance time ‘‘after the
Revision 2 date of the service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(2) Where Boeing Alert Service Bulletin
747–53A2784, Revision 2, dated August 20,
2015, specifies to contact Boeing for
appropriate action, accomplish applicable
actions before further flight using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraphs (h), (i), and
(k) of this AD, if those actions were
performed before December 26, 2012 (the
effective date of AD 2012–22–02), using
Boeing Service Bulletin 747–53A2784, dated
August 27, 2009, which is not incorporated
by reference in this AD.
(2) This paragraph provides credit for the
actions required by paragraphs (h), (i), and
(k) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Service Bulletin 747–53A2784,
Revision 1, dated September 14, 2011.
(n) 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 (o) of this AD.
(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
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Federal Register / Vol. 81, No. 82 / Thursday, April 28, 2016 / Proposed Rules
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.
(o) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6432; fax: 425–91–6590;
email: Bill.Ashforth@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 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 April 15,
2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–09647 Filed 4–27–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5597; Directorate
Identifier 2016–NM–009–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 adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 737–400 series
airplanes. This proposed AD was
prompted by reports of cracks in the
upper chord of the overwing stub beams
at body station (STA) 578 emanating
from the rivet location common to the
crease beam inner chord and the
overwing stub beam upper chord. This
proposed AD would require repetitive
inspections for cracking, and related
investigative and corrective actions if
necessary. Replacement of the overwing
stub beam would terminate the
repetitive inspections for cracking at the
replacement location only, and post-
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SUMMARY:
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replacement inspections would be
required if the replacement was done.
We are proposing this AD to detect and
correct cracking in the upper chord of
the overwing stub beam caused by high
flight cycle fatigue stresses from both
pressurization and maneuver loads.
Cracking of the overwing stub beam
could adversely affect the fuselage
structural integrity and result in
possible decompression of the airplane.
DATES: We must receive comments on
this proposed AD by June 13, 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–
5597.
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–
5597; 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:
Wade Sullivan, Aerospace Engineer,
PO 00000
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Sfmt 4702
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6430;
fax: 425–917–6590; email:
wade.sullivan@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2016–5597; Directorate Identifier 2016–
NM–009–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
We have received ten reports from
four operators of cracks in the upper
chord of the overwing stub beams at
body STA 578 emanating from the rivet
location common to the crease beam
inner chord and the overwing stub beam
upper chord on The Boeing Company
Model 737–400 series airplanes. The
earliest reported crack in an overwing
stub beam upper chord occurred on an
airplane with 31,843 total flight cycles.
Seven airplanes had a severed overwing
stub beam upper chord on either the left
or right side, and two airplanes had
severed overwing stub beam upper
chords on the left and right sides.
Cracks in the upper chord of the
overwing stub beams, if not corrected,
could result in high flight cycle fatigue
stresses from both pressurization and
maneuver loads, which can cause
cracking in the upper chord of the
overwing stub beam at STA 559, STA
578, and STA 601. Cracking of the
overwing stub beam could adversely
affect the fuselage structural integrity
and result in possible decompression of
the airplane.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1347, dated December
9, 2015. The service information
describes procedures for doing a surface
high frequency eddy current inspection
E:\FR\FM\28APP1.SGM
28APP1
]]>Agencies
[Federal Register Volume 81, Number 82 (Thursday, April 28, 2016)]
[Proposed Rules]
[Pages 25357-25360]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09647]
========================================================================
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. 82 / Thursday, April 28, 2016 /
Proposed Rules
[[Page 25357]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-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) 2012-22-
02, which applies to certain The Boeing Company Model 747-400, -400D,
and -400F series airplanes. AD 2012-22-02 currently requires measuring
the web at station (STA) 320 and, depending on findings, various
inspections for cracks and missing fasteners, web and fastener
replacement, and related investigative and corrective actions if
necessary. Since we issued AD 2012-22-02, it was determined that there
were no inspection or repair procedures included for airplanes with a
STA 320 crown frame web thickness less than 0.078 inch, or greater than
or equal to 0.084 inch and less than or equal to 0.135 inch. This
proposed AD would require, for certain airplanes, replacement of the
web, including related investigative and corrective actions if
necessary. We are issuing this AD to prevent complete fracture of the
crown frame assembly, and consequent damage to the skin. Such damage
could result in in-flight decompression of the airplane.
DATES: We must receive comments on this proposed AD by June 13, 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-2016-5598.
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-
5598; 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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: Bill.Ashforth@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-2016-5598;
Directorate Identifier 2016-NM-001-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 October 19, 2012, we issued AD 2012-22-02, Amendment 39-17238
(77 FR 69739, November 21, 2012) (``AD 2012-22-02''), for certain The
Boeing Company Model 747-400, -400D, and -400F series airplanes. AD
2012-22-02 requires measuring the web at STA 320 and, depending on
findings, various inspections for cracks and missing fasteners, web and
fastener replacement, and related investigative and corrective actions
if necessary. AD 2012-22-02 resulted from reports of crown frame web
cracking at left buttock line (LBL) 15.0, STA 320. We issued AD 2012-
22-02 to prevent complete fracture of the crown frame assembly, and
consequent damage to the skin and in-flight decompression of the
airplane.
Actions Since AD 2012-22-02 Was Issued
Since we issued AD 2012-22-02, it was determined that there was no
work included for airplanes with a STA 320 crown frame web thickness
less than 0.078 inch, or greater than or equal to 0.084 inch and less
than or equal to 0.135 inch.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 747-53A2784, Revision 2,
dated August 20, 2015. The service information describes procedures for
various inspections for cracks and missing fasteners, web and fastener
replacement, and related investigative and corrective actions, if
necessary. 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.
[[Page 25358]]
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 design.
Proposed AD Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2012-22-02, this proposed AD would retain certain
requirements of AD 2012-22-02. Those requirements are referenced in the
service information identified previously, which, in turn, is
referenced in paragraphs (h), (i), and (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 the 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-2016-5598.
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
For Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated
August 20, 2015, Table 4: STA 320 Post Web Replacement Inspection of
paragraph 1.E., ``Compliance,'' the conditional action statement does
not include airplanes that were inspected or repaired in accordance
with Part 8 of the Work Instructions. The statement should read: ``All
airplanes that have done the STA 320 crown frame web replacement in
accordance with paragraph 3.B. WORK INSTRUCTIONS, PARTS 5 OR PART 8.''
Paragraph (k) of this proposed AD applies to all airplanes on which a
web replacement is done as required by paragraphs (h), (i), and (j) of
the proposed AD, e.g., the replacement is done as specified in Part 5
or Part 8 of paragraph 3.B., ``Work Instructions,'' of the service
information.
Costs of Compliance
We estimate that this proposed AD affects 29 airplanes.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Measurement, inspection, and web 219 work-hours x $85 Up to $21,887........ Up to $40,502 per $Up to 1,174,558.
replacement. [retained actions per hour = $18,615. inspection and
from AD 2012[dash]22[dash]02]. replacement.
Post-replacement inspection 135 work-hours x $85 $0................... $11,475 per $332,775 per inspection cycle.
[retained actions from AD per hour = $11,475 inspection cycle.
2012[dash]22[dash]02]. per inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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)
2012-22-02, Amendment 39-17238 (77 FR 69739 November 21, 2012), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2016-5598; Directorate Identifier
2016-NM-001-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by June 13,
2016.
(b) Affected ADs
This AD replaces AD 2012-22-02, Amendment 39-17238 (77 FR 69739,
November 21, 2012) (``AD 2012-22-02'').
[[Page 25359]]
(c) Applicability
This AD applies to The Boeing Company Model 747-400, -400D, and
-400F series airplanes, certificated in any category, as specified
in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated
August 20, 2015.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of crown frame web cracking at
left buttock line (LBL) 15.0, station (STA) 320 and a determination
that there were no inspection or repair procedures included in AD
2012-22-02 for airplanes with a STA 320 crown frame web thickness
less than 0.078 inch, or greater than or equal to 0.084 inch and
less than or equal to 0.135 inch. We are issuing this AD to prevent
complete fracture of the crown frame assembly, and consequent damage
to the skin. Such damage could result in in-flight decompression of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Crown Frame Web Measurement for Certain Airplanes
For Group 1, Configuration 3 airplanes identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: At the compliance time specified in Table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784,
Revision 2, dated August 20, 2015, measure the thickness of the
crown frame web at STA 320, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as required by
paragraph (l)(2) of this AD. Do all related investigative and
corrective actions at the applicable times specified in Table 2 and
Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015.
(h) Inspections (Web With No Repair Doubler) and Related Investigative
and Corrective Actions (Including Web Replacement)
For Group 1, Configuration 1 airplanes identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less than 0.136 inch and no
repair doubler installed on the web, at the time specified in Table
2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a
detailed inspection for cracks and a general visual inspection for
missing fasteners of the crown frame web at STA 320; and do all
applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015,
except as specified in paragraph (l)(2) of this AD. Do the
applicable related investigative and corrective actions at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August
20, 2015.
(i) Inspection (Web With Repair Doubler) and Related Investigative and
Corrective Actions (Including Web Replacement)
For Group 1, Configuration 1 airplanes identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: For airplanes with a web thickness less than 0.136 inch and a
repair doubler installed on the web, at the time specified in Table
3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a
detailed inspection for any crack in the upper chord and lower chord
of the STA 320 crown frame; and do all applicable related
investigative and corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as specified in
paragraph (l)(2) of this AD. Do the applicable related investigative
and corrective actions at the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2784, Revision 2, dated August 20, 2015. At the applicable
compliance time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August
20, 2015, except as provided by paragraph (l)(1) of this AD, do the
actions specified in paragraphs (i)(1) and (i)(2) of this AD, and do
all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2784,
Revision 2, dated August 20, 2015, except as required by paragraph
(l)(2) of this AD. Do all applicable corrective actions before
further flight.
(1) Replace the web with a new web and do all applicable related
investigative actions.
(2) Do a detailed inspection for cracks in the upper or lower
chord of the crown frame web at STA 320.
(j) Web Replacement for Certain Airplanes
For Group 1, Configuration 2 airplanes identified in Boeing
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20,
2015: At the applicable time specified in Table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784,
Revision 2, dated August 20, 2015, except as provided by paragraph
(l)(1) of this AD, replace the web, including doing related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as required by
paragraph (l)(2) of this AD. Do all applicable related investigative
and corrective actions before further flight.
(k) Post-Replacement Repetitive Inspections of Replaced Web
Following any web replacement required by this AD, at the time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2784, Revision 2, dated August 20, 2015: Do a
detailed inspection for cracks of the web, upper chord, lower chord,
and lower chord splice, and do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015,
except as required by paragraph (l)(2) of this AD. Do all applicable
corrective actions before further flight. If no crack is found,
repeat the inspection thereafter at the intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2784, Revision 2, dated August 20, 2015. Accomplishment of
the inspections required by AD 2009-19-05, Amendment 39-16022 (74 FR
48138, September 22, 2009), terminates the requirements of this
paragraph.
(l) Exceptions to the Service Information With Updated Service
Information
(1) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2,
dated August 20, 2015, specifies a compliance time ``after the
Revision 2 date of the service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2,
dated August 20, 2015, specifies to contact Boeing for appropriate
action, accomplish applicable actions before further flight using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (h), (i), and (k) of this AD, if those actions were
performed before December 26, 2012 (the effective date of AD 2012-
22-02), using Boeing Service Bulletin 747-53A2784, dated August 27,
2009, which is not incorporated by reference in this AD.
(2) This paragraph provides credit for the actions required by
paragraphs (h), (i), and (k) of this AD, if those actions were
performed before the effective date of this AD using Boeing Service
Bulletin 747-53A2784, Revision 1, dated September 14, 2011.
(n) 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 (o) of this AD.
(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
[[Page 25360]]
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.
(o) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-91-6590; email:
Bill.Ashforth@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 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 April 15, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-09647 Filed 4-27-16; 8:45 am]
BILLING CODE 4910-13-P
