Airworthiness Directives; The Boeing Company Airplanes, 22422-22426 [2018-10299]
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Proposed Rules
(b) Affected ADs
This AD replaces AD 2017–16–05,
Amendment 39–18982 (82 FR 39344, August
18, 2017) (‘‘AD 2017–16–05’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category, as specified in
paragraphs (c)(1) through (c)(3) of this AD.
(1) Airplanes in Groups 1 and 2 as
identified in Boeing Alert Service Bulletin
737–57A1327, Revision 2, dated July 25,
2017 (‘‘BASB 737–57A1327, R2’’).
(2) Airplanes in Group 3, as identified in
BASB 737–57A1327, R2, except where this
service bulletin specifies the groups as line
numbers 6422 through 6465 inclusive, this
AD specifies those groups as line number
6422 through any line number airplane with
an original Certificate of Airworthiness or an
original Export Certificate of Airworthiness
dated on or before the effective date of this
AD.
(3) All Model 737–600, –700, –700C, –800,
–900 and –900ER series airplanes with an
original Certificate of Airworthiness or an
original Export Certificate of Airworthiness
dated after the effective date of this AD.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of a
Krueger flap bullnose departing an airplane
during taxi, which caused damage to the
wing structure and thrust reverser, and a
report of a missing no. 2 Krueger flap
bullnose hinge bolt from an airplane that was
not included in the effectivity of AD 2017–
16–05. We are issuing this AD to address
missing Krueger flap bullnose hardware.
Such missing hardware could result in the
Krueger flap bullnose departing the airplane
during flight, which could damage
empennage structure and lead to the inability
to maintain continued safe flight and
landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions
For airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD: Except as
required by paragraph (h) of this AD, at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of BASB 737–57A1327, R2,
do all applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of BASB 737–57A1327, R2.
(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where BASB 737–57A1327, R2 uses the
phrase ‘‘the original issue date of this service
bulletin,’’ this AD requires using September
22, 2017 (the effective date of AD 2017–16–
05).
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(2) For purposes of determining
compliance with the requirements of this AD:
Where BASB 737–57A1327, R2 uses the
phrase ‘‘the Revision 2 date of this service
bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(i) Parts Installation Limitation
As of the effective date of this AD, no
person may install a Krueger flap or Krueger
flap bullnose on any airplane, unless the
actions required by paragraph (g) of this AD
have been accomplished on the Krueger flap
bullnose.
(j) Credit for Previous Actions
(1) This paragraph provides credit for the
actions specified in paragraph (g) of this AD,
if those actions were performed before
September 22, 2017 (the effective date of AD
2017–16–05), using Boeing Alert Service
Bulletin 737–57A1327, dated May 20, 2016.
(2) This paragraph provides credit for the
actions specified in paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD, using Boeing Alert
Service Bulletin 737–57A1327, Revision 1,
dated September 28, 2016.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (l)(1) of
this AD. Information may be emailed to: 9ANM-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
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for AD
2017–16–05 are approved as AMOCs for the
corresponding provisions of BASB 737–
57A1327, R2 that are required by paragraph
(g) of this AD.
(5) For service information that contains
steps that are labeled as RC, the provisions
of paragraphs (k)(5)(i) and (k)(5)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
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deviations to RC steps, including substeps
and identified figures.
(ii) Operators may deviate from steps not
labeled as RC by using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3527; email:
alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone: 562–797–1717; internet: https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
Issued in Des Moines, Washington, on May
7, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–10213 Filed 5–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0412; Product
Identifier 2017–NM–180–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) 2010–25–
06, which applies to certain The Boeing
Company Model 737–200, –300, –400,
and –500 series airplanes. AD 2010–25–
06 requires repetitive inspections for
cracking of certain fuselage frames and
stub beams, and corrective actions if
necessary. AD 2010–25–06 also
provides for an optional repair, which
terminates the repetitive inspections.
For airplanes on which a certain repair
is done, AD 2010–25–06 also requires
repetitive inspections for cracking of
certain fuselage frames and stub beams,
SUMMARY:
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Proposed Rules
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and corrective actions if necessary.
Since we issued AD 2010–25–06,
additional cracking was found in areas
not covered by the inspections. This
proposed AD would retain the actions
required by AD 2010–25–06 and would
expand the inspection area. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by June 29, 2018.
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: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0412.
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–2018–
0412; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Galib Abumeri, Aerospace Engineer,
Airframe Section, Los Angeles ACO
Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5324; fax: 562–627–
5210; email: galib.abumeri@faa.gov.
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16:36 May 14, 2018
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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–
2018–0412; Product Identifier 2017–
NM–180–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
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 issued AD 2010–25–06,
Amendment 39–16539 (75 FR 81409,
December 28, 2010) (‘‘AD 2010–25–
06’’), for certain Model 737–200, –300,
–400, and –500 series airplanes. AD
2010–25–06 requires repetitive
inspections for cracking of certain
fuselage frames and stub beams, and
corrective actions if necessary. AD
2010–25–06 also provides for an
optional repair, which terminates the
repetitive inspections. For airplanes on
which a certain repair is done, AD
2010–25–06 also requires repetitive
inspections for cracking of certain
fuselage frames and stub beams, and
corrective actions if necessary. AD
2010–25–06 resulted from reports of the
detection of fatigue cracks at certain
frame sections, in addition to stub beam
cracking, caused by high flight cycle
stresses from both pressurization and
maneuver loads. We issued AD 2010–
25–06 to detect and correct fatigue
cracking of certain fuselage frames and
stub beams and possible severed frames,
which could result in reduced structural
integrity of the frames. This reduced
structural integrity can increase loading
in the fuselage skin, which will
accelerate skin crack growth and could
result in rapid decompression of the
fuselage.
Actions Since AD 2010–25–06 Was
Issued
Since we issued AD 2010–25–06,
additional cracking was found in areas
not covered by the inspections. During
an inspection of the body station (BS)
616 stub beam upper chord, an operator
identified additional cracking at buttock
line (BL) 64. We determined that eddy
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current inspections of the upper chord
at BL 64 and BL 65 must be done to
maintain structural integrity. In
addition, during inspections of the
longitudinal floor beam web at the BS
639 stub beams operators found
cracking in the floor beam web. It was
determined that the inspections
required by AD 2010–25–06 were
inadequate, and eddy current
inspections of the BL 45.5 floor beam
web at the BS 639 stub beam interface
must be done to address this cracking.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1254, Revision 3,
dated November 13, 2017. The service
information describes procedures for
detailed and eddy current inspections of
the fuselage frame and over wing stub
beam at BS 616, BS 639, and BS 597 or
BS 601, and BL 45.5 floor beam web at
the BS 639 stub beam attachment, and
relative investigative and corrective
actions. 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 design.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2010–25–06. This
proposed AD does not explicitly restate
the requirements of AD 2010–25–06.
Those requirements are referenced in
the service information identified
previously, which, in turn, is referenced
in this proposed AD, except for any
differences identified as exceptions in
the regulatory text of this proposed AD.
This proposed AD would add new
repetitive inspections for cracking of
certain other fuselage frames and stub
beams. 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–2018–
0412.
Boeing Alert Service Bulletin 737–
53A1254, Revision 3, dated November
13, 2017, provides two economic
inspections to find cracking prior to
frame damage, which could require
extensive repairs. These inspections are
recommended but are not mandated in
this proposed AD.
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Proposed Rules
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.
Costs of Compliance
We estimate that this proposed AD
affects 67 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Inspections .............................
Parts cost
Up to 67 work-hours × $85
per hour = $5,695.
We estimate the following costs to do
certain necessary repairs/replacements
that would be required based on the
$0
Cost per product
Cost on U.S. operators
Up to $5,695 per inspection
cycle.
results of the proposed inspections. We
have no way of determining the number
Up to $381,565 per inspection
cycle.
of aircraft that might need these repairs/
replacements:
ON-CONDITION COSTS
Action **
Labor cost
Parts cost
Repairs/replacements ..................................................
Up to 76 work-hours × $85 per hour = $6,460 ..........
*
Cost per product
Up to $6,460.
* All required parts are supplied by the operator. This cost is minimal, and we have no way to determine what an operator would pay for these
parts.
** We have received no definitive data that would enable us to provide cost estimates for certain other repairs specified in this proposed AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes to the Director of the
System Oversight Division.
Regulatory Findings
16:36 May 14, 2018
§ 39.13
List of Subjects in 14 CFR Part 39
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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:
■
We have determined that this
proposed AD would not have federalism
VerDate Sep<11>2014
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.
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Authority: 49 U.S.C. 106(g), 40113, 44701.
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[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2010–25–06, Amendment 39–16539 (75
FR 81409, December 28, 2010), and
adding the following new AD:
■
The Boeing Company: Docket No. FAA–
2018–0412; Product Identifier 2017–
NM–180–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by June 29, 2018.
(b) Affected ADs
This AD replaces AD 2010–25–06,
Amendment 39–16539 (75 FR 81409,
December 28, 2010) (‘‘AD 2010–25–06’’).
(c) Applicability
This AD applies to The Boeing Company
Model 737–200, -300, -400, and -500 series
airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
13, 2017.
(e) Unsafe Condition
This AD was prompted by the detection of
fatigue cracks at certain frame sections, in
addition to stub beam cracking, caused by
high flight cycle stresses from both
pressurization and maneuver loads and
additional cracking found in areas not
covered by the inspections in AD 2010–25–
06. We are issuing this AD to address fatigue
cracking of certain fuselage frames and stub
beams and possible severed frames, which
could result in reduced structural integrity of
the frames. This reduced structural integrity
can increase loading in the fuselage skin,
which will accelerate skin crack growth and
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Proposed Rules
could result in rapid decompression of the
fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections of Body Stations
616 and 639 Frames and Stub Beams and
Corrective Actions
At the applicable time specified table 1 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017: Do a
detailed or high frequency eddy current
(HFEC) inspection for cracking of the body
station (BS) 616 and 639 frames and stub
beams and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
13, 2017, except as required by paragraph
(m)(1) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Thereafter, repeat the
inspection at the applicable time specified in
table 1 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017.
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(h) Repetitive Post-Repair Inspections of
Body Stations 616 and 639 Frames and
Integral Stub Beams and Corrective Actions
At the applicable time specified table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017: Do the
inspections required by paragraphs (h)(1) and
(h)(2) of this AD; or the inspection required
by paragraph (h)(3) of this AD; as applicable,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
13, 2017, except as required by paragraph
(m)(1) of this AD. Do all applicable related
investigative and corrective actions before
further flight. Thereafter, repeat the
inspection at the applicable time specified in
table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017.
(1) Do a low frequency eddy current (LFEC)
inspection of the web, and an HFEC
inspection of the inner and outer chord
common to the upper end fastener rows of
the web splice doubler for cracking.
(2) Do the inspection specified in
paragraph (h)(2)(i) or (h)(2)(ii) of this AD.
(i) Do a detailed inspection of the
replacement frame section for cracking.
(ii) Do an HFEC and LFEC inspection of the
replacement frame section for cracking.
(3) Do a detailed or HFEC inspection of the
replacement stub beam for cracking.
(i) Repetitive Inspections of Buttock Line
45.5 Longitudinal Floor Beam Web at Body
Station 639 Stub Beam Attachment and
Corrective Actions
For Group 1 and Group 2 airplanes as
identified in Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
13, 2017, at the time specified table 3 or table
4, as applicable, of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
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16:36 May 14, 2018
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Bulletin 737–53A1254, Revision 3, dated
November 13, 2017, except as required by
paragraph (m)(2) of this AD: Do the
inspections required by paragraph (i)(1) and
(i)(2) of this AD and all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1254, Revision 3,
dated November 13, 2017, except as required
by paragraph (m)(1) of this AD. Do all
applicable corrective actions before further
flight. Thereafter, repeat the inspections at
the time specified in table 3 or table 4, as
applicable, of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1254, Revision 3, dated November 13,
2017.
(1) Do an open-hole HFEC inspection for
cracking of the buttock line (BL) 45.5
longitudinal floor beam web at each fastener
hole common to the stub beam attachment
angle.
(2) Do an HFEC surface inspection for
cracking of the BL 45.5 longitudinal floor
beam web around the fastener head/tail at
each fastener location common to the backup
strap.
(j) Repetitive Post-Repair Inspections of
Buttock Line 45.5 Longitudinal Floor Beam
Web at Body Station 639 and Corrective
Actions
For Group 2 airplanes as identified in
Boeing Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017, at the
applicable time specified table 5 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1254, Revision 3, dated
November 13, 2017, except as required by
paragraph (m)(2) of this AD: Do the
inspections required by paragraphs (j)(1) and
(j)(2) of this AD and all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1254, Revision 3,
dated November 13, 2017, except as required
by paragraph (m)(1) of this AD. Do all
applicable corrective actions before further
flight. Thereafter, repeat the inspections at
the applicable time specified in table 5 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017.
(1) Do an open-hole HFEC inspection for
cracking of the BL 45.5 longitudinal floor
beam web filler at each fastener hole
common to the stub beam attachment angle.
(2) Do an HFEC surface inspection for
cracking of the BL 45.5 longitudinal floor
beam web filler around the fastener head/tail
at each fastener location common to the
backup strap.
(k) Repetitive Inspections for Cracking of BS
616 Machined Stub Beam Upper Chord and
Corrective Actions
For Group 2 and Group 3 airplanes as
identified in Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
13, 2017, at the applicable time specified in
table 9 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017, except
as required by paragraph (m)(2) of this AD;
do detailed and medium frequency eddy
current subsurface inspections for cracking of
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22425
the BS 616 machined stub beam upper chord,
and all applicable corrective actions, except
as required by paragraph (m)(1) of this AD.
Do all applicable corrective actions before
further flight. Thereafter, repeat the
inspections at the applicable time specified
in table 9 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1254, Revision 3, dated November 13,
2017.
(l) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD, using Boeing Alert
Service Bulletin 737–53A1254, Revision 1,
dated July 9, 2009; or Boeing Alert Service
Bulletin 737–53A1254, Revision 2, dated
February 22, 2012.
(2) This paragraph provides credit for
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD, using Boeing Alert
Service Bulletin 737–53A1254, Revision 2,
dated February 22, 2012.
(m) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1254, Revision 3, dated November
13, 2017, specifies to contact Boeing for
repair instructions: Before further flight, do
the repair using a method approved in
accordance with the procedures specified in
paragraph (n) of this AD.
(2) Where Paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1254,
Revision 3, dated November 13, 2017,
specifies a compliance time ‘‘after the
Revision 3 date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (o)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, 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.
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Proposed Rules
(4) AMOCs approved previously for AD
2010–25–06 are approved as AMOCs for the
corresponding provisions of Boeing Alert
Service Bulletin 737–53A1254, Revision 3,
dated November 13, 2017, that are required
by paragraphs (g) and (h) of this AD.
(o) Related Information
(1) For information about this AD, contact
Galib Abumeri, Aerospace Engineer,
Airframe Section, Los Angeles ACO Branch,
FAA, 3960 Paramount Boulevard, Lakewood,
CA 90712–4137; phone: 562–627–5324; fax:
562–627–5210; email: galib.abumeri@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
Issued in Des Moines, Washington, on May
8, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
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 Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com;
internet: https://www.airbus.com. You
may view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
[FR Doc. 2018–10299 Filed 5–14–18; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0411; 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 NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax: 206–231–3223.
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0411; Product
Identifier 2017–NM–157–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A319–115 and –132
airplanes, and Model A320–214, –216,
–232, and –233 airplanes. This proposed
AD was prompted by a report indicating
that certain modified airplanes do not
have electrical ground wires on the fuel
level sensing control unit (FLSCU),
which adversely affects the fuel gravity
feeding operation. This proposed AD
would require modification of the
FLSCU wiring. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by June 29, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
daltland on DSKBBV9HB2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:36 May 14, 2018
Jkt 244001
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–
2018–0411; Product Identifier 2017–
NM–157–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM based
on those comments.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
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 NPRM.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0216,
dated October 30, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A319–115 and
–132 airplanes, and Model A320–214,
–216, –232, and –233 airplanes. The
MCAI states:
Airbus introduced mod 154327 on A319
and A320 aeroplanes which substituted the
pump fuel feed system from the centre fuel
tank with a jet pump transfer system, based
on the Airbus A321 design. Following the
modification introduction, it was discovered
that the modified aeroplanes do not have
electrical ground signals that replicate those
from the deleted centre tank pump pressure
switches. These signals are used as part of
the fuel recirculation inhibition request logic.
Subsequent investigation determined that
ground wires had not been installed on the
fuel level sensor control units (FLSCU) of
post-mod aeroplanes, due to a drawing error
on the fuel system recirculation principle
diagram. Without these ground wires
providing inputs, the FLSCU logic is not
correctly implemented for gravity feeding
operation.
This condition, if not corrected, could lead
to reduced fuel pressure at the engine inlet,
possibly resulting in an uncommanded inflight shut-down when flying at the gravity
feed ceiling levels, as defined in the Aircraft
Flight Manual (AFM).
To address this potential unsafe condition,
Airbus issued AFM Temporary Revision (TR)
695 Issue 1 and AFM TR 699 Issue 1 to
prohibit the use of Jet B and JP4 fuel, and
AFM TR 700 Issue 1 to provide instructions
for amendment of the gravity feed procedure
for the other fuels.
Consequently, EASA issued AD 2016–0205
[which corresponds to FAA AD 2016–25–23,
Amendment 39–18749 (81 FR 90971,
December 16, 2016) (‘‘AD 2016–25–23’’)],
requiring amendment of the applicable AFM
to include the new gravity feed procedure
and to reduce the list of authorised fuels.
Since that [EASA] AD was issued, Airbus
developed a wiring modification to restore
the intended FLSCU logic, and issued
Service Bulletin (SB) A320–28–1242, later
revised, providing instructions to modify
affected aeroplanes.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0205, which is superseded, and
requires modification of FLSCU wiring. This
[EASA] AD also allows, after that
modification, to remove the previously
inserted AFM TR’s from the applicable AFM.
E:\FR\FM\15MYP1.SGM
15MYP1
]]>Agencies
[Federal Register Volume 83, Number 94 (Tuesday, May 15, 2018)]
[Proposed Rules]
[Pages 22422-22426]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10299]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0412; Product Identifier 2017-NM-180-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) 2010-25-
06, which applies to certain The Boeing Company Model 737-200, -300, -
400, and -500 series airplanes. AD 2010-25-06 requires repetitive
inspections for cracking of certain fuselage frames and stub beams, and
corrective actions if necessary. AD 2010-25-06 also provides for an
optional repair, which terminates the repetitive inspections. For
airplanes on which a certain repair is done, AD 2010-25-06 also
requires repetitive inspections for cracking of certain fuselage frames
and stub beams,
[[Page 22423]]
and corrective actions if necessary. Since we issued AD 2010-25-06,
additional cracking was found in areas not covered by the inspections.
This proposed AD would retain the actions required by AD 2010-25-06 and
would expand the inspection area. We are proposing this AD to address
the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by June 29, 2018.
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: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may
view this service information at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0412.
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-2018-
0412; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer,
Airframe Section, Los Angeles ACO Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-
5210; email: [email protected].
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-2018-0412;
Product Identifier 2017-NM-180-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM 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 issued AD 2010-25-06, Amendment 39-16539 (75 FR 81409, December
28, 2010) (``AD 2010-25-06''), for certain Model 737-200, -300, -400,
and -500 series airplanes. AD 2010-25-06 requires repetitive
inspections for cracking of certain fuselage frames and stub beams, and
corrective actions if necessary. AD 2010-25-06 also provides for an
optional repair, which terminates the repetitive inspections. For
airplanes on which a certain repair is done, AD 2010-25-06 also
requires repetitive inspections for cracking of certain fuselage frames
and stub beams, and corrective actions if necessary. AD 2010-25-06
resulted from reports of the detection of fatigue cracks at certain
frame sections, in addition to stub beam cracking, caused by high
flight cycle stresses from both pressurization and maneuver loads. We
issued AD 2010-25-06 to detect and correct fatigue cracking of certain
fuselage frames and stub beams and possible severed frames, which could
result in reduced structural integrity of the frames. This reduced
structural integrity can increase loading in the fuselage skin, which
will accelerate skin crack growth and could result in rapid
decompression of the fuselage.
Actions Since AD 2010-25-06 Was Issued
Since we issued AD 2010-25-06, additional cracking was found in
areas not covered by the inspections. During an inspection of the body
station (BS) 616 stub beam upper chord, an operator identified
additional cracking at buttock line (BL) 64. We determined that eddy
current inspections of the upper chord at BL 64 and BL 65 must be done
to maintain structural integrity. In addition, during inspections of
the longitudinal floor beam web at the BS 639 stub beams operators
found cracking in the floor beam web. It was determined that the
inspections required by AD 2010-25-06 were inadequate, and eddy current
inspections of the BL 45.5 floor beam web at the BS 639 stub beam
interface must be done to address this cracking.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1254, Revision 3,
dated November 13, 2017. The service information describes procedures
for detailed and eddy current inspections of the fuselage frame and
over wing stub beam at BS 616, BS 639, and BS 597 or BS 601, and BL
45.5 floor beam web at the BS 639 stub beam attachment, and relative
investigative and corrective actions. 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 design.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2010-25-06.
This proposed AD does not explicitly restate the requirements of AD
2010-25-06. Those requirements are referenced in the service
information identified previously, which, in turn, is referenced in
this proposed AD, except for any differences identified as exceptions
in the regulatory text of this proposed AD. This proposed AD would add
new repetitive inspections for cracking of certain other fuselage
frames and stub beams. 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-2018-0412.
Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated
November 13, 2017, provides two economic inspections to find cracking
prior to frame damage, which could require extensive repairs. These
inspections are recommended but are not mandated in this proposed AD.
[[Page 22424]]
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.
Costs of Compliance
We estimate that this proposed AD affects 67 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections..................... Up to 67 $0 Up to $5,695 per Up to $381,565 per
work[dash]hours x inspection cycle. inspection cycle.
$85 per hour =
$5,695.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do certain necessary repairs/
replacements that would be required based on the results of the
proposed inspections. We have no way of determining the number of
aircraft that might need these repairs/replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action ** Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repairs/replacements.................. Up to 76 work[dash]hours * Up to $6,460.
x $85 per hour = $6,460.
----------------------------------------------------------------------------------------------------------------
* All required parts are supplied by the operator. This cost is minimal, and we have no way to determine what an
operator would pay for these parts.
** We have received no definitive data that would enable us to provide cost estimates for certain other repairs
specified in this proposed AD.
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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
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)
2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2018-0412; Product Identifier
2017-NM-180-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by June 29,
2018.
(b) Affected ADs
This AD replaces AD 2010-25-06, Amendment 39-16539 (75 FR 81409,
December 28, 2010) (``AD 2010-25-06'').
(c) Applicability
This AD applies to The Boeing Company Model 737-200, -300, -400,
and -500 series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3,
dated November 13, 2017.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by the detection of fatigue cracks at
certain frame sections, in addition to stub beam cracking, caused by
high flight cycle stresses from both pressurization and maneuver
loads and additional cracking found in areas not covered by the
inspections in AD 2010-25-06. We are issuing this AD to address
fatigue cracking of certain fuselage frames and stub beams and
possible severed frames, which could result in reduced structural
integrity of the frames. This reduced structural integrity can
increase loading in the fuselage skin, which will accelerate skin
crack growth and
[[Page 22425]]
could result in rapid decompression of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections of Body Stations 616 and 639 Frames and Stub
Beams and Corrective Actions
At the applicable time specified table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254,
Revision 3, dated November 13, 2017: Do a detailed or high frequency
eddy current (HFEC) inspection for cracking of the body station (BS)
616 and 639 frames and stub beams and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1254, Revision 3, dated November 13, 2017, except as required by
paragraph (m)(1) of this AD. Do all applicable related investigative
and corrective actions before further flight. Thereafter, repeat the
inspection at the applicable time specified in table 1 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254,
Revision 3, dated November 13, 2017.
(h) Repetitive Post-Repair Inspections of Body Stations 616 and 639
Frames and Integral Stub Beams and Corrective Actions
At the applicable time specified table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254,
Revision 3, dated November 13, 2017: Do the inspections required by
paragraphs (h)(1) and (h)(2) of this AD; or the inspection required
by paragraph (h)(3) of this AD; as applicable, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1254, Revision 3, dated November 13, 2017, except as required
by paragraph (m)(1) of this AD. Do all applicable related
investigative and corrective actions before further flight.
Thereafter, repeat the inspection at the applicable time specified
in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017.
(1) Do a low frequency eddy current (LFEC) inspection of the
web, and an HFEC inspection of the inner and outer chord common to
the upper end fastener rows of the web splice doubler for cracking.
(2) Do the inspection specified in paragraph (h)(2)(i) or
(h)(2)(ii) of this AD.
(i) Do a detailed inspection of the replacement frame section
for cracking.
(ii) Do an HFEC and LFEC inspection of the replacement frame
section for cracking.
(3) Do a detailed or HFEC inspection of the replacement stub
beam for cracking.
(i) Repetitive Inspections of Buttock Line 45.5 Longitudinal Floor Beam
Web at Body Station 639 Stub Beam Attachment and Corrective Actions
For Group 1 and Group 2 airplanes as identified in Boeing Alert
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017,
at the time specified table 3 or table 4, as applicable, of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1254, Revision 3, dated November 13, 2017, except as required
by paragraph (m)(2) of this AD: Do the inspections required by
paragraph (i)(1) and (i)(2) of this AD and all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated
November 13, 2017, except as required by paragraph (m)(1) of this
AD. Do all applicable corrective actions before further flight.
Thereafter, repeat the inspections at the time specified in table 3
or table 4, as applicable, of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated
November 13, 2017.
(1) Do an open-hole HFEC inspection for cracking of the buttock
line (BL) 45.5 longitudinal floor beam web at each fastener hole
common to the stub beam attachment angle.
(2) Do an HFEC surface inspection for cracking of the BL 45.5
longitudinal floor beam web around the fastener head/tail at each
fastener location common to the backup strap.
(j) Repetitive Post-Repair Inspections of Buttock Line 45.5
Longitudinal Floor Beam Web at Body Station 639 and Corrective Actions
For Group 2 airplanes as identified in Boeing Alert Service
Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the
applicable time specified table 5 of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-53A1254, Revision 3, dated
November 13, 2017, except as required by paragraph (m)(2) of this
AD: Do the inspections required by paragraphs (j)(1) and (j)(2) of
this AD and all applicable corrective actions, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1254, Revision 3, dated November 13, 2017, except as required
by paragraph (m)(1) of this AD. Do all applicable corrective actions
before further flight. Thereafter, repeat the inspections at the
applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254,
Revision 3, dated November 13, 2017.
(1) Do an open-hole HFEC inspection for cracking of the BL 45.5
longitudinal floor beam web filler at each fastener hole common to
the stub beam attachment angle.
(2) Do an HFEC surface inspection for cracking of the BL 45.5
longitudinal floor beam web filler around the fastener head/tail at
each fastener location common to the backup strap.
(k) Repetitive Inspections for Cracking of BS 616 Machined Stub Beam
Upper Chord and Corrective Actions
For Group 2 and Group 3 airplanes as identified in Boeing Alert
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017,
at the applicable time specified in table 9 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254,
Revision 3, dated November 13, 2017, except as required by paragraph
(m)(2) of this AD; do detailed and medium frequency eddy current
subsurface inspections for cracking of the BS 616 machined stub beam
upper chord, and all applicable corrective actions, except as
required by paragraph (m)(1) of this AD. Do all applicable
corrective actions before further flight. Thereafter, repeat the
inspections at the applicable time specified in table 9 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254,
Revision 3, dated November 13, 2017.
(l) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD, using Boeing Alert Service Bulletin 737-
53A1254, Revision 1, dated July 9, 2009; or Boeing Alert Service
Bulletin 737-53A1254, Revision 2, dated February 22, 2012.
(2) This paragraph provides credit for actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD, using Boeing Alert Service Bulletin 737-
53A1254, Revision 2, dated February 22, 2012.
(m) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1254, Revision 3,
dated November 13, 2017, specifies to contact Boeing for repair
instructions: Before further flight, do the repair using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD.
(2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017,
specifies a compliance time ``after the Revision 3 date of this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of
the person identified in paragraph (o)(1) of this AD. Information
may be emailed to: [email protected].
(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, Los Angeles ACO Branch, 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 22426]]
(4) AMOCs approved previously for AD 2010-25-06 are approved as
AMOCs for the corresponding provisions of Boeing Alert Service
Bulletin 737-53A1254, Revision 3, dated November 13, 2017, that are
required by paragraphs (g) and (h) of this AD.
(o) Related Information
(1) For information about this AD, contact Galib Abumeri,
Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5324; fax: 562-627-5210; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
Issued in Des Moines, Washington, on May 8, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-10299 Filed 5-14-18; 8:45 am]
BILLING CODE 4910-13-P
