Airworthiness Directives; The Boeing Company Airplanes, 5614-5617 [2019-02923]
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Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Proposed Rules
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2018–0245R1 that contains RC procedures
and tests: Except as required by paragraph
(h)(2) of this AD, RC procedures and tests
must be done to comply with this AD; any
procedures or tests that are not identified as
RC are recommended. Those procedures and
tests that are not identified as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Related Information
(1) For information about EASA AD 2018–
0245R1, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone
+49 221 89990 6017; email ADs@
easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu. You may view this EASA
AD 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.
EASA AD 2018–0245R1 may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2019–0016.
(2) For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3218.
Issued in Des Moines, Washington, on
February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–02931 Filed 2–21–19; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0022; Product
Identifier 2018–NM–162–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 certain
The Boeing Company Model 737–200,
–200C, –300, –400, and –500 airplanes.
This proposed AD was prompted by
reports of cracking in the lower lobe
skin panel assemblies of the fuselage.
This proposed AD would require
replacement of lower lobe skin panel
assemblies, and detailed inspections for
scribe lines and applicable on-condition
actions. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by April 8, 2019.
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 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. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2019–0022.
DATES:
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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–2019–
0022; 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:
James Guo, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5357; fax: 562–627–
5210; email: james.guo@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–
2019–0022; Product Identifier 2018–
NM–162–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
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as widespread
fatigue damage (WFD). It is associated
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Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Proposed Rules
with general degradation of large areas
of structure with similar structural
details and stress levels. As an airplane
ages, WFD will likely occur, and will
certainly occur if the airplane is
operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
We have received a report indicating
that an operator of a 737–300 airplane
reported a chem-milled step crack above
stringer S–15 on the left side between
station (STA) 360 and STA 380. The
airplane had a lap splice modification
done in accordance with Boeing Service
Bulletin 737–53A1177 and had logged
48,537 total flight cycles and 67,505
total flight hours. The 5-inch crack was
found by visual inspection during
airplane maintenance. On these skin
panel assemblies, the bonded doubler is
chemically milled to create pockets. At
these locations, the loads could cause a
condition where cracks could form
along the longitudinal edges of the
doubler at the step of the chem-milled
pockets. Without skin panel assembly
replacement, the skin cracks could grow
and multiple adjacent cracks in the
fuselage skin could link up with each
other. This condition, if not addressed,
could lead to decompression or loss of
structural integrity of the airplane.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert
Requirements Bulletin 737–53A1379
RB, dated September 4, 2018. The
service information describes
procedures for replacement of lower
lobe skin panel assemblies, and detailed
inspections for scribe lines and
applicable on-condition 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 require
accomplishment of the actions
identified in Boeing Alert Requirements
Bulletin 737–53A1379 RB, dated
September 4, 2018, described
previously, except for any differences
identified as exceptions in the
regulatory text of this proposed AD.
5615
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–2019–
0022.
Explanation of Requirements Bulletin
The FAA worked in conjunction with
industry, under the Airworthiness
Directive Implementation Aviation
Rulemaking Committee (AD ARC), to
enhance the AD system. One
enhancement is a process for annotating
which steps in the service information
are ‘‘required for compliance’’ (RC) with
an AD. Boeing has implemented this RC
concept into Boeing service bulletins.
In an effort to further improve the
quality of ADs and AD-related Boeing
service information, a joint process
improvement initiative was worked
between the FAA and Boeing. The
initiative resulted in the development of
a new process in which the service
information more clearly identifies the
actions needed to address the unsafe
condition in the ‘‘Accomplishment
Instructions.’’ The new process results
in a Boeing Requirements Bulletin,
which contains only the actions needed
to address the unsafe condition (i.e.,
only the RC actions).
Explanation of Compliance Time
The compliance time for the
modification specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
Costs of Compliance
We estimate that this proposed AD
affects 171 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS *
Action
Labor cost
Parts cost
Cost per product
Inspection and replacement ............
688 work-hours × $85 per hour =
$58,480.
(*)
$58,480
Cost on U.S. operators
$10,000,080
* Parts cost unavailable.
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Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Proposed Rules
under the criteria of the Regulatory
Flexibility Act.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
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 and associated
appliances to the Director of the System
Oversight Division.
Regulatory Findings
We 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 this 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
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2019–0022; Product Identifier 2018–
NM–162–AD.
(a) Comments Due Date
We must receive comments by April 8,
2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 737–200, –200C, –300, –400, and –500
airplanes, certificated in any category, as
identified in Boeing Alert Requirements
Bulletin 737–53A1379 RB, dated September
4, 2018.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking in the lower lobe skin panel
assemblies of the fuselage. We are issuing
this AD to address the possibility of multiple
adjacent cracks at chem-milled steps in the
fuselage skin linking up with each other,
which could lead to decompression or loss of
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Except as specified by paragraph (h) of this
AD: At the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 737–53A1379 RB,
dated September 4, 2018, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 737–53A1379
RB, dated September 4, 2018.
Note 1 to paragraph (g) of this AD:
Guidance for accomplishing the actions
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required by this AD can be found in Boeing
Alert Service Bulletin 737–53A1379, dated
September 4, 2018, which is referred to in
Boeing Alert Requirements Bulletin 737–
53A1379 RB, dated September 4, 2018.
(h) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Requirements Bulletin
737–53A1379 RB, dated September 4, 2018,
uses the phrase ‘‘the original issue date of
Requirements Bulletin 737–53A1379 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 737–53A1379 RB, dated September
4, 2018, specifies contacting Boeing for work
instructions or for scribe line repair and skin
panel replacement work instructions: This
AD requires doing the work and the scribe
line repair and skin panel replacement before
further flight using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
(i) 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 (j)(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, FAA, 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.
(j) Related Information
(1) For more information about this AD,
contact James Guo, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5357; fax: 562–627–5210; email: james.guo@
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,
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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
February 8, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–02923 Filed 2–21–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0018; Product
Identifier 2018–NM–116–AD]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–07–
12, which applies to certain Airbus SAS
Model A318, A319, A320, and A321
series airplanes. AD 2016–07–12
requires repetitive inspections for
damage and cracking of the aft fixed
fairing (AFF) of the pylons, and repair
if necessary. Since we issued AD 2016–
07–12, we have received reports of
cracks on a certain rib of a modified
AFF of the pylons. This proposed AD
would retain the repetitive inspections
required by AD 2016–07–12, and
require additional repetitive inspections
at the upper spar at a certain rib area
and corrective actions if necessary. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by April 8, 2019.
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.
SUMMARY:
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For the incorporation by reference
(IBR) material described in the ‘‘Related
IBR material under 1 CFR part 51’’
section in SUPPLEMENTARY INFORMATION,
contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49
221 89990 1000; email ADs@
easa.europa.eu; internet
www.easa.europa.eu. You may find this
IBR material on the EASA website at
https://ad.easa.europa.eu. You may
view this IBR material 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 in the AD docket on
the internet at https://
www.regulations.gov.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0018; 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:
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–
2019–0018; Product Identifier 2018–
NM–116–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.
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.
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Discussion
We issued AD 2016–07–12,
Amendment 39–18457 (81 FR 19482,
April 5, 2016) (‘‘AD 2016–07–12’’), for
certain Airbus SAS Model A318, A319,
A320, and A321 series airplanes. AD
2016–07–12 requires repetitive
inspections for damage and cracking of
the AFF of the pylons, and repair if
necessary. AD 2016–07–12 resulted
from reports of cracking of the AFF of
the pylons due to fatigue damage of the
structure. We issued AD 2016–07–12 to
address such damage and cracking of
the AFF of the pylons, which could
result in detachment of a pylon and
consequent reduced structural integrity
of the airplane.
Actions Since AD 2016–07–12 Was
Issued
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0137,
dated June 28, 2018 (‘‘EASA AD 2018–
0137’’) (also referred to as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
SAS Model A318–111, –112; Model
A319–111, –112, –113, –114, –115;
Model A320–211, –212, –214, –216; and
Model A321–111, –112, –211, –212,
–213 airplanes. The MCAI states:
On aeroplanes equipped with post-mod
33844 CFM pylons, several operators
reported finding cracks on the Aft Fixed
Fairing (AFF). After material analysis, it
appeared that the pylon AFF structure,
especially on this configuration, was subject
to fatigue-induced damage which could lead
to pylon AFF cracks.
This condition, if not detected and
corrected, could lead to detachment of a
pylon AFF from the aeroplane, possibly
resulting in injury to persons on the ground.
To address this unsafe condition, Airbus
published Alert Operators Transmission
(AOT) A54N002–12, providing inspection
instructions. Thereafter, Airbus issued
Service Bulletin (SB) A320–54–1027, later
revised, superseding AOT A54N002–12.
EASA issued AD 2014–0154 [which
corresponds to FAA AD 2016–07–12] to
require repetitive inspections of the pylon
AFF and, depending on findings,
replacement.
Since that [EASA] AD was issued, Airbus
developed mod 156593 to increase the
fatigue life of the pylon AFF structure by
using a different material and introducing
thermal treatment of the aluminium sheets
parts. Prompted by new findings of cracks on
rib 15, it was determined that this area also
needs to be inspected to ensure the structural
integrity of the new pylon AFF. Airbus
further revised SB A320–54–1027, including
instructions for repetitive inspection of that
area. Repetitive inspections are also required
on post-mod 156593 aeroplanes.
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]]>Agencies
[Federal Register Volume 84, Number 36 (Friday, February 22, 2019)]
[Proposed Rules]
[Pages 5614-5617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02923]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0022; Product Identifier 2018-NM-162-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 737-200, -200C, -300, -400, and -500
airplanes. This proposed AD was prompted by reports of cracking in the
lower lobe skin panel assemblies of the fuselage. This proposed AD
would require replacement of lower lobe skin panel assemblies, and
detailed inspections for scribe lines and applicable on-condition
actions. We are proposing this AD to address the unsafe condition on
these products.
DATES: We must receive comments on this proposed AD by April 8, 2019.
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 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. It
is also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2019-0022.
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-2019-
0022; 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: James Guo, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5357; fax: 562-627-
5210; email: james.guo@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-2019-0022;
Product Identifier 2018-NM-162-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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as widespread fatigue damage (WFD).
It is associated
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with general degradation of large areas of structure with similar
structural details and stress levels. As an airplane ages, WFD will
likely occur, and will certainly occur if the airplane is operated long
enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
We have received a report indicating that an operator of a 737-300
airplane reported a chem-milled step crack above stringer S-15 on the
left side between station (STA) 360 and STA 380. The airplane had a lap
splice modification done in accordance with Boeing Service Bulletin
737-53A1177 and had logged 48,537 total flight cycles and 67,505 total
flight hours. The 5-inch crack was found by visual inspection during
airplane maintenance. On these skin panel assemblies, the bonded
doubler is chemically milled to create pockets. At these locations, the
loads could cause a condition where cracks could form along the
longitudinal edges of the doubler at the step of the chem-milled
pockets. Without skin panel assembly replacement, the skin cracks could
grow and multiple adjacent cracks in the fuselage skin could link up
with each other. This condition, if not addressed, could lead to
decompression or loss of structural integrity of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Requirements Bulletin 737-53A1379 RB,
dated September 4, 2018. The service information describes procedures
for replacement of lower lobe skin panel assemblies, and detailed
inspections for scribe lines and applicable on-condition 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 require accomplishment of the actions
identified in Boeing Alert Requirements Bulletin 737-53A1379 RB, dated
September 4, 2018, described previously, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
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-2019-0022.
Explanation of Requirements Bulletin
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement is a process for
annotating which steps in the service information are ``required for
compliance'' (RC) with an AD. Boeing has implemented this RC concept
into Boeing service bulletins.
In an effort to further improve the quality of ADs and AD-related
Boeing service information, a joint process improvement initiative was
worked between the FAA and Boeing. The initiative resulted in the
development of a new process in which the service information more
clearly identifies the actions needed to address the unsafe condition
in the ``Accomplishment Instructions.'' The new process results in a
Boeing Requirements Bulletin, which contains only the actions needed to
address the unsafe condition (i.e., only the RC actions).
Explanation of Compliance Time
The compliance time for the modification specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 171 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions *
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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Inspection and replacement............ 688 work-hours x $85 per (*) $58,480 $10,000,080
hour = $58,480.
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* Parts cost unavailable.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions 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 and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We 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 this 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 adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2019-0022; Product Identifier
2018-NM-162-AD.
(a) Comments Due Date
We must receive comments by April 8, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-200, -200C, -
300, -400, and -500 airplanes, certificated in any category, as
identified in Boeing Alert Requirements Bulletin 737-53A1379 RB,
dated September 4, 2018.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking in the lower lobe
skin panel assemblies of the fuselage. We are issuing this AD to
address the possibility of multiple adjacent cracks at chem-milled
steps in the fuselage skin linking up with each other, which could
lead to decompression or loss of structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 737-53A1379 RB, dated September 4, 2018,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
737-53A1379 RB, dated September 4, 2018.
Note 1 to paragraph (g) of this AD: Guidance for accomplishing
the actions required by this AD can be found in Boeing Alert Service
Bulletin 737-53A1379, dated September 4, 2018, which is referred to
in Boeing Alert Requirements Bulletin 737-53A1379 RB, dated
September 4, 2018.
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Requirements Bulletin 737-53A1379 RB,
dated September 4, 2018, uses the phrase ``the original issue date
of Requirements Bulletin 737-53A1379 RB,'' this AD requires using
``the effective date of this AD.''
(2) Where Boeing Alert Requirements Bulletin 737-53A1379 RB,
dated September 4, 2018, specifies contacting Boeing for work
instructions or for scribe line repair and skin panel replacement
work instructions: This AD requires doing the work and the scribe
line repair and skin panel replacement before further flight using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.
(i) 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 (j)(1) of this AD. Information
may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO Branch, FAA, 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.
(j) Related Information
(1) For more information about this AD, contact James Guo,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5357; fax: 562-627-5210; email: james.guo@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,
[[Page 5617]]
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 February 8, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-02923 Filed 2-21-19; 8:45 am]
BILLING CODE 4910-13-P
