Airworthiness Directives; The Boeing Company Airplanes, 46380-46384 [2018-19185]
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Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations
the single stitched de-icing boots installed on
the left-hand (LH) and right-hand (RH)
horizontal stabilizers with double stitched
de-icing boots and re-identify the LH and RH
horizontal stabilizer leading edge, in
accordance with the Accomplishment
Instructions of Saab Service Bulletin 340–30–
095, dated April 3, 2017.
(j) Terminating Action for the Requirements
of Paragraph (h) of this AD
Modification of an airplane as required by
paragraph (i) of this AD, constitutes
terminating action for the repetitive
inspections required by paragraph (h) of this
AD, for that airplane.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Saab AB,
Saab Aeronautics’ EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature
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(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0144, dated August 9, 2017, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0271.
(2) For more information about this AD,
contact Shahram Daneshmandi, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; phone and fax:
206–231–3220.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
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(3) The following service information was
approved for IBR on October 18, 2018.
(i) Saab Service Bulletin 340–30–095,
dated April 3, 2017.
(ii) Reserved.
(4) The following service information was
approved for IBR on August 1, 2016 (81 FR
41432, June 27, 2016).
(i) Saab Service Bulletin 340–30–094,
dated March 27, 2015.
(ii) Saab AFM 340A 001, Revision 57,
dated March 27, 2015.
(iii) Saab AFM 340B 001, Revision 35,
dated March 27, 2015.
(iv) Saab AFM 340B 010, Revision 28,
dated March 27, 2015.
(5) For service information identified in
this AD, contact Saab AB, Saab Aeronautics,
SE–581 88, Linko¨ping, Sweden; phone: +46
13 18 5591; fax: +46 13 18 4874; email:
saab340techsupport@saabgroup.com;
internet: https://www.saabgroup.com.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
August 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–19748 Filed 9–12–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0112; Product
Identifier 2017–NM–161–AD; Amendment
39–19392; AD 2018–18–13]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by
reports of cracking in certain flanges,
and the adjacent web, of the wing
outboard flap track at certain positions,
and a determination that new
inspections of certain flap track flanges
SUMMARY:
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and webs forward of the rear spar
attachment are necessary. This AD
requires an inspection to determine the
part number of the wing outboard flap
track assembly; repetitive inspections of
each affected wing outboard flap track
for discrepancies, and applicable oncondition actions; and repetitive
overhaul of each wing outboard flap
track. We are issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective October 18,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 18, 2018.
ADDRESSES: For service information
identified in this final rule, 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–2018–
0112.
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–
0112; 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 final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
Docket Operations, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Payman Soltani, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5313; fax: 562–627–
5210; email: payman.soltani@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
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737–100, –200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
February 21, 2018 (83 FR 7425). The
NPRM was prompted by reports of
cracking in certain flanges, and the
adjacent web, of the wing outboard flap
track at certain positions, and a
determination that new inspections of
certain flap track flanges and webs
forward of the rear spar attachment are
necessary. The NPRM proposed to
require an inspection to determine the
part number of the wing outboard flap
track assembly; repetitive inspections of
each affected wing outboard flap track
for discrepancies, and applicable oncondition actions; and repetitive
overhaul of each wing outboard flap
track.
We are issuing this AD to detect and
correct cracking of the wing outboard
flap tracks. Cracking in the area between
the forward and rear spar attachments of
the wing outboard flap tracks could lead
to the inability of a principal structural
element to sustain required flight loads,
and result in loss of the outboard
trailing edge flap and consequent
reduced controllability of the airplane.
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
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Request To Extend the Compliance
Time
All Nippon Airways (ANA) and Utair
Aviation requested that paragraph (h) of
the proposed AD be revised to extend
the compliance time from 6 months to
18 months after the effective date of the
final rule. The commenters are
concerned that there are not enough
spare flap track parts available. The
commenters indicated that overhaul of
the removed flap tracks takes significant
time, and if the final rule is released
without a sufficient number of spare
flap tracks available, there could be a
long-term aircraft on ground (AOG)
situation if the proposed compliance
times are used.
Furthermore, Utair Aviation stated
that a review of maintenance records on
38 airplanes for flap tracks at positions
1 and 8 did not find any records of
inspections or overhaul, and it would
not be able to replace the subject flap
tracks within the compliance time
specified in the proposed AD. Utair
Aviation also noted that it took 60 days,
including shipping, to replace the
outboard flap tracks for similar
requirements specified in AD 2013–09–
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02, Amendment 39–17443 (78 FR
27010, May 9, 2013).
We do not agree with the commenters’
requests. The 6-month compliance time
for inspection and overhaul is
applicable only to flap tracks that have
unknown maintenance records and flap
tracks that were last overhauled several
years ago. Airplanes with flap tracks
that have known maintenance records
generally have later compliance times,
depending on how long it has been
since the flap tracks were overhauled.
The NPRM was issued to address
findings of stress corrosion cracking in
the flap tracks. Stress corrosion cracking
is more likely to occur in flap tracks that
have been in operation for a longer time.
Flap tracks with unknown maintenance
records and flap tracks that were last
overhauled several years ago are more
susceptible to the unsafe condition. The
probability of the existence of stress
corrosion cracking on flap tracks with
unknown maintenance history is higher
and warrants the shorter compliance
time. We have verified that spare flap
tracks are available on the parts surplus
market; however, since we do not know
how many flap tracks have unknown
maintenance records, it is difficult to
estimate how many spare flap tracks
will be necessary to meet the demand.
If there is a critical shortage of parts,
operators may contact the FAA and
request an adjustment to the compliance
time using the procedures specified in
paragraph (l) of this AD. We might
approve a longer compliance time if
additional data are presented that would
justify an extension to the compliance
time while still maintaining an adequate
level of safety.
We urge operators to seek out
maintenance records for their flap tracks
in order to justify use of the extended
compliance times specified in Boeing
Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017.
We cannot justify extending the
compliance times for flap tracks without
maintenance records to 18 months. We
have not changed this AD in regard to
this issue.
Request To Omit Inspection 1 in the
Service Information
Utair Aviation stated that it is
inadvisable to require operators to do
the inspections included in
‘‘INSPECTION 1,’’ as defined in Boeing
Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017.
The commenter noted that ‘‘ACTION 1’’
in Table 1 and Table 2 of paragraph 3,
‘‘Compliance,’’ of Boeing Alert
Requirements Bulletin 737–57A1338
RB, dated September 25, 2017, states
that operators need to do INSPECTION
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1. The commenter suggested that
‘‘ACTION 2,’’ overhaul of each affected
flap track, would already include all of
the inspections included in
INSPECTION 1.
We infer that the commenter is
requesting that the proposed
requirement to do the inspections
included in INSPECTION 1 of the
specified service bulletin be removed
from the proposed AD. We do not agree
with the commenter’s request. ACTION
1 and ACTION 2 have different
purposes. The inspections included in
ACTION 1 are intended to detect
specific existing damage on the flap
track, including cracks, nicks, corrosion,
galling, broken pieces, and stop drills.
The intention of ACTION 2, overhaul of
each affected flap track, is a visual
examination for defects. The intent of
this visual examination during overhaul
is to identify additional discrepancies,
such as excessive wear or degraded
surface finish, that might not be noted
during INSPECTION 1. It is important to
detect these additional discrepancies
since they can be early indicators of
stress corrosion cracking. Since the
inspections to detect specific existing
damage on the flap track are not
included in the overhaul instructions, it
is necessary to require both ACTION 1
and ACTION 2 in this AD. We have not
changed this AD in regard to this issue.
Request for Alternative To Overhaul
ANA requested that an alternative to
overhaul of the flap tracks be provided
that does not involve removing the flap
tracks from the wing. The commenter
suggested that an on-wing inspection
could be used instead of the overhaul.
The commenter is concerned that there
is not a sufficient supply of spare flap
track parts.
We do not agree with the commenter’s
request. There is no on-wing inspection
method available that can detect the
additional discrepancies that overhaul
of the flap tracks is designed to address.
The concern regarding availability of
spare flap track parts was addressed in
the response to an earlier comment. We
have not changed this AD in regard to
this issue.
Request To Revise Parts Installation
Limitation Paragraph
Boeing requested that the Parts
Installation Limitation Paragraph,
paragraph (k) in the proposed AD, be
revised to allow flap tracks to be
installed and inspected at the time of
installation. Boeing noted that
paragraph (k) states ‘‘. . . no person
may install a flap track unless the flap
track is inspected prior to installation.’’
Boeing pointed out that there are several
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inspections that pertain to the track-towing joint, which cannot be
accomplished until after the flap track is
installed.
We agree with the commenter’s
request for the reasons provided by the
commenter. We have revised paragraph
(k) of this AD to state ‘‘As of the
effective date of this AD, no person may
install, on any airplane, a wing outboard
flap track having a part number listed in
paragraph 1.B. of Boeing Alert
Requirements Bulletin 737–57A1338
RB, dated September 25, 2017, unless
the inspections . . . are accomplished
prior to or concurrently with the part’s
installation on the airplane.’’
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the installation of
winglets using Supplemental Type
Certificate (STC) ST01219SE does not
affect compliance with the actions
proposed in the NPRM.
We concur with the commenter. We
have redesignated paragraph (c) of the
proposed AD as paragraph (c)(1) of this
AD and added paragraph (c)(2) to this
AD to state that installation of STC
ST01219SE does not affect the ability to
accomplish the actions required by this
AD. Therefore, for airplanes on which
STC ST01219SE is installed, a ‘‘change
in product’’ alternative method of
compliance (AMOC) approval request is
not necessary to comply with the
requirements of 14 CFR 39.17.
Additional Change to This AD
The proposed AD included Note 1 to
paragraph (h), which stated that
guidance for accomplishing the
proposed actions could be found in
Boeing Alert Service Bulletin 737–
57A1338, dated September 25, 2017,
which is referred to in Boeing Alert
Requirements Bulletin 737–57A1338
RB, dated September 25, 2017. Since the
proposed AD was published, Boeing has
issued Boeing Information Notice 737–
57A1338 IN 01, dated October 16, 2017;
Boeing Information Notice 737–
57A1338 IN 02, dated March 16, 2018;
and Boeing Information Notice 737–
57A1338 IN 03, dated March 20, 2018.
These information notices provide
additional guidance material related to
Boeing Alert Service Bulletin 737–
57A1338, dated September 25, 2017,
including clarification of compliance
times for spares (not AD compliance
times), inspection figures, and the
relationship between flap track part
numbers and airplanes groups. We have
revised Note 1 to paragraph (h) in this
AD to include these information notices.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert
Requirements Bulletin 737–57A1338
RB, dated September 25, 2017. This
service information describes
procedures for repetitive inspections
and repetitive overhaul of the wing
outboard flap tracks, and applicable oncondition actions including repair and
replacement of the wing outboard flap
tracks. 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.
Costs of Compliance
We estimate that this AD affects 160
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Inspection (positions 1 and 8;
Group 2 and Group 3, configuration 1).
Inspection (positions 1 and 8;
Group 3, configuration 2).
Inspection (positions 2 and 7;
Group 2 and Group 3, configuration 1).
Inspection (positions 2 and 7;
Group 3, configuration 2).
78 work-hours × $85 per hour =
$6,630 per cycle.
$0
$6,630 per cycle ........
$1,060,800 per cycle.
89 work-hours × $85 per hour =
$7,565 per cycle.
83 work-hours × $85 per hour =
$7,055 per cycle.
0
7,565 per cycle ..........
1,210,400 per cycle.
0
7,055 per cycle ..........
1,128,800 per cycle.
86 work-hours × $85 per hour =
$7,310 per cycle.
0
7,310 per cycle ..........
1,169,600 per cycle.
We have received no definitive data
that will enable us to provide cost
estimates for the actions for Group 1
airplanes, the repetitive overhaul, or the
on-condition actions specified in this
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
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Parts cost
Cost per product
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
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Cost on U.S. operators
products identified in this rulemaking
action.
This 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
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Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations
the Director of the System Oversight
Division.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
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.
Adoption of the Amendment
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):
■
2018–18–13 The Boeing Company:
Amendment 39–19392; Docket No.
FAA–2018–0112; Product Identifier
2017–NM–161–AD.
(a) Effective Date
This AD is effective October 18, 2018.
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(b) Affected ADs
This AD affects AD 2013–09–02,
Amendment 39–17443 (78 FR 27010, May 9,
2013) (‘‘AD 2013–09–02’’).
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of
cracking in certain flanges, and the adjacent
web, of the wing outboard flap track at
certain positions, and a determination that
new inspections of certain flap track flanges
and webs forward of the rear spar attachment
are necessary. We are issuing this AD to
detect and correct cracking of the wing
outboard flap tracks. Cracking in the area
between the forward and rear spar
attachments of the wing outboard flap tracks
could lead to the inability of a principal
structural element to sustain required flight
loads, and result in loss of the outboard
trailing edge flap and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in
Boeing Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017:
Within 120 days after the effective date of
this AD, do actions to correct the unsafe
condition using a method approved in
accordance with the procedures specified in
paragraph (l) of this AD.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/ebd1cec7b301293e86257
cb30045557a/$FILE/ST01219SE.pdf) does
not affect the ability to accomplish the
actions required by this AD. Therefore, for
airplanes on which STC ST01219SE is
installed, a ‘‘change in product’’ alternative
method of compliance (AMOC) approval
request is not necessary to comply with the
requirements of 14 CFR 39.17.
(h) Required Actions
For airplanes not specified in paragraph (g)
of this AD: Except as required by paragraph
(i) of this AD, at the applicable times
specified in the ‘‘Compliance’’ paragraph of
Boeing Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017, do
all applicable actions identified in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Requirements
Bulletin 737–57A1338 RB, dated September
25, 2017.
Note 1 to paragraph (h) of this AD:
Guidance for accomplishing the actions
required by this AD can be found in Boeing
Alert Service Bulletin 737–57A1338, dated
September 25, 2017, which is referred to in
Boeing Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017.
Additional guidance can be found in Boeing
Information Notice 737–57A1338 IN 01,
dated October 16, 2017; Boeing Information
Notice 737–57A1338 IN 02, dated March 16,
2018; and Boeing Information Notice 737–
57A1338 IN 03, dated March 20, 2018.
(i) Exceptions to Service Information
Specifications
For purposes of determining compliance
with the requirements of this AD: Where
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46383
Boeing Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017, uses
the phrase ‘‘the original issue date of
Requirements Bulletin 737–57A1338 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(j) Terminating Action for Requirements of
AD 2013–09–02
Accomplishment of the requirements
specified in paragraph (h) of this AD
terminates all requirements of AD 2013–09–
02.
(k) Parts Installation Limitation
As of the effective date of this AD, no
person may install, on any airplane, a wing
outboard flap track having a part number
listed in paragraph 1.B. of Boeing Alert
Requirements Bulletin 737–57A1338 RB,
dated September 25, 2017, unless the
inspections and corrective actions specified
in the Accomplishment Instructions of
Boeing Alert Requirements Bulletin 737–
57A1338 RB, dated September 25, 2017, are
accomplished prior to or concurrently with
the part’s installation on the airplane.
(l) 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 (m)(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.
(m) Related Information
(1) For more information about this AD,
contact Payman Soltani, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712 4137; phone: 562–627–
5313; fax: 562–627–5210; email:
payman.soltani@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
E:\FR\FM\13SER1.SGM
13SER1
46384
Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin
737–57A1338 RB, dated September 25, 2017.
(ii) Reserved.
(3) 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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on
August 24, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–19185 Filed 9–12–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0418; Product
Identifier 2017–SW–016–AD; Amendment
39–19390; AD 2018–18–11]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model AS–365N2 and AS
365 N3 helicopters with a lower strobe
light installed. This AD requires
installing a cable mount, inspecting the
lower strobe light wiring harness, and
re-routing the wiring harness. This AD
was prompted by reports of interference
between the lower strobe light wiring
harness and the helicopter structure.
The actions of this AD are intended to
prevent an unsafe condition on these
helicopters.
DATES: This AD is effective October 18,
2018.
The Director of the Federal Register
approved the incorporation by reference
daltland on DSKBBV9HB2PROD with RULES
SUMMARY:
VerDate Sep<11>2014
17:40 Sep 12, 2018
Jkt 244001
of a certain document listed in this AD
as of October 18, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus Helicopters, 2701 N. Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You
may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0418.
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–
0418; 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 AD, the
European Aviation Safety Agency
(EASA) AD, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT:
George Schwab, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
george.schwab@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 11, 2018, at 83 FR 21964, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
Airbus Helicopters Model AS–365N2
and AS 365 N3 helicopters with a lower
strobe light installed.
The NPRM proposed to require
installing a cable mount on the
helicopter structure and inspecting the
lower strobe light electrical harness and
the electrical harness between the cutoff connector and Frame 2000 for torn
spiral tape and for any chafing on the
harness cables. If the spiral tape is torn,
the NPRM proposed to require replacing
PO 00000
Frm 00036
Fmt 4700
Sfmt 4700
the spiral tape. If there is any chafing on
the cable, the NPRM proposed to require
replacing the harness. The proposed
requirements were intended to prevent
interference between the lower strobe
light electrical harness wiring and the
helicopter structure, which could result
in chafing of an electrical harness
adjacent to the inboard fuel tank vapor
space, a fuel tank fire, and subsequent
loss of control of the helicopter.
The NPRM was prompted by AD No.
2016–0258, dated December 16, 2016,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Airbus Helicopters Model
AS 365 N2 and AS 365 N3 helicopters
with certain serial numbers and
configurations. EASA advises of inproduction helicopters with lower
strobe light wiring harnesses that were
interfering with either the helicopter
structure or the adjacent fuel tank
support. EASA further states that an
investigation determined that the
electrical harnesses of these lower
strobe lights were manufactured with
additional length to facilitate removal
and installation of the lower strobe light
assembly. However, the additional
length of wiring in the harness was not
properly secured to the helicopter
structure. According to EASA, this
could result in chafing of the harness on
the helicopter structure, creating an
ignition source adjacent to the inboard
fuel tank vapor space, and result in a
fuel tank fire.
To address this unsafe condition, the
EASA AD requires installing a cable
mount, inspecting the lower strobe light
electrical harness for damage, and rerouting the electrical harness.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM.
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
E:\FR\FM\13SER1.SGM
13SER1
]]>Agencies
[Federal Register Volume 83, Number 178 (Thursday, September 13, 2018)]
[Rules and Regulations]
[Pages 46380-46384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19185]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0112; Product Identifier 2017-NM-161-AD; Amendment
39-19392; AD 2018-18-13]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This AD was prompted by reports of cracking in certain
flanges, and the adjacent web, of the wing outboard flap track at
certain positions, and a determination that new inspections of certain
flap track flanges and webs forward of the rear spar attachment are
necessary. This AD requires an inspection to determine the part number
of the wing outboard flap track assembly; repetitive inspections of
each affected wing outboard flap track for discrepancies, and
applicable on-condition actions; and repetitive overhaul of each wing
outboard flap track. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective October 18, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 18,
2018.
ADDRESSES: For service information identified in this final rule,
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-2018-
0112.
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-
0112; 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 final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is Docket Operations, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Payman Soltani, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-
5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all The Boeing Company
Model
[[Page 46381]]
737-100, -200, -200C, -300, -400, and -500 series airplanes. The NPRM
published in the Federal Register on February 21, 2018 (83 FR 7425).
The NPRM was prompted by reports of cracking in certain flanges, and
the adjacent web, of the wing outboard flap track at certain positions,
and a determination that new inspections of certain flap track flanges
and webs forward of the rear spar attachment are necessary. The NPRM
proposed to require an inspection to determine the part number of the
wing outboard flap track assembly; repetitive inspections of each
affected wing outboard flap track for discrepancies, and applicable on-
condition actions; and repetitive overhaul of each wing outboard flap
track.
We are issuing this AD to detect and correct cracking of the wing
outboard flap tracks. Cracking in the area between the forward and rear
spar attachments of the wing outboard flap tracks could lead to the
inability of a principal structural element to sustain required flight
loads, and result in loss of the outboard trailing edge flap and
consequent reduced controllability of the airplane.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Request To Extend the Compliance Time
All Nippon Airways (ANA) and Utair Aviation requested that
paragraph (h) of the proposed AD be revised to extend the compliance
time from 6 months to 18 months after the effective date of the final
rule. The commenters are concerned that there are not enough spare flap
track parts available. The commenters indicated that overhaul of the
removed flap tracks takes significant time, and if the final rule is
released without a sufficient number of spare flap tracks available,
there could be a long-term aircraft on ground (AOG) situation if the
proposed compliance times are used.
Furthermore, Utair Aviation stated that a review of maintenance
records on 38 airplanes for flap tracks at positions 1 and 8 did not
find any records of inspections or overhaul, and it would not be able
to replace the subject flap tracks within the compliance time specified
in the proposed AD. Utair Aviation also noted that it took 60 days,
including shipping, to replace the outboard flap tracks for similar
requirements specified in AD 2013-09-02, Amendment 39-17443 (78 FR
27010, May 9, 2013).
We do not agree with the commenters' requests. The 6-month
compliance time for inspection and overhaul is applicable only to flap
tracks that have unknown maintenance records and flap tracks that were
last overhauled several years ago. Airplanes with flap tracks that have
known maintenance records generally have later compliance times,
depending on how long it has been since the flap tracks were
overhauled. The NPRM was issued to address findings of stress corrosion
cracking in the flap tracks. Stress corrosion cracking is more likely
to occur in flap tracks that have been in operation for a longer time.
Flap tracks with unknown maintenance records and flap tracks that were
last overhauled several years ago are more susceptible to the unsafe
condition. The probability of the existence of stress corrosion
cracking on flap tracks with unknown maintenance history is higher and
warrants the shorter compliance time. We have verified that spare flap
tracks are available on the parts surplus market; however, since we do
not know how many flap tracks have unknown maintenance records, it is
difficult to estimate how many spare flap tracks will be necessary to
meet the demand. If there is a critical shortage of parts, operators
may contact the FAA and request an adjustment to the compliance time
using the procedures specified in paragraph (l) of this AD. We might
approve a longer compliance time if additional data are presented that
would justify an extension to the compliance time while still
maintaining an adequate level of safety.
We urge operators to seek out maintenance records for their flap
tracks in order to justify use of the extended compliance times
specified in Boeing Alert Requirements Bulletin 737-57A1338 RB, dated
September 25, 2017. We cannot justify extending the compliance times
for flap tracks without maintenance records to 18 months. We have not
changed this AD in regard to this issue.
Request To Omit Inspection 1 in the Service Information
Utair Aviation stated that it is inadvisable to require operators
to do the inspections included in ``INSPECTION 1,'' as defined in
Boeing Alert Requirements Bulletin 737-57A1338 RB, dated September 25,
2017. The commenter noted that ``ACTION 1'' in Table 1 and Table 2 of
paragraph 3, ``Compliance,'' of Boeing Alert Requirements Bulletin 737-
57A1338 RB, dated September 25, 2017, states that operators need to do
INSPECTION 1. The commenter suggested that ``ACTION 2,'' overhaul of
each affected flap track, would already include all of the inspections
included in INSPECTION 1.
We infer that the commenter is requesting that the proposed
requirement to do the inspections included in INSPECTION 1 of the
specified service bulletin be removed from the proposed AD. We do not
agree with the commenter's request. ACTION 1 and ACTION 2 have
different purposes. The inspections included in ACTION 1 are intended
to detect specific existing damage on the flap track, including cracks,
nicks, corrosion, galling, broken pieces, and stop drills. The
intention of ACTION 2, overhaul of each affected flap track, is a
visual examination for defects. The intent of this visual examination
during overhaul is to identify additional discrepancies, such as
excessive wear or degraded surface finish, that might not be noted
during INSPECTION 1. It is important to detect these additional
discrepancies since they can be early indicators of stress corrosion
cracking. Since the inspections to detect specific existing damage on
the flap track are not included in the overhaul instructions, it is
necessary to require both ACTION 1 and ACTION 2 in this AD. We have not
changed this AD in regard to this issue.
Request for Alternative To Overhaul
ANA requested that an alternative to overhaul of the flap tracks be
provided that does not involve removing the flap tracks from the wing.
The commenter suggested that an on-wing inspection could be used
instead of the overhaul. The commenter is concerned that there is not a
sufficient supply of spare flap track parts.
We do not agree with the commenter's request. There is no on-wing
inspection method available that can detect the additional
discrepancies that overhaul of the flap tracks is designed to address.
The concern regarding availability of spare flap track parts was
addressed in the response to an earlier comment. We have not changed
this AD in regard to this issue.
Request To Revise Parts Installation Limitation Paragraph
Boeing requested that the Parts Installation Limitation Paragraph,
paragraph (k) in the proposed AD, be revised to allow flap tracks to be
installed and inspected at the time of installation. Boeing noted that
paragraph (k) states ``. . . no person may install a flap track unless
the flap track is inspected prior to installation.'' Boeing pointed out
that there are several
[[Page 46382]]
inspections that pertain to the track-to-wing joint, which cannot be
accomplished until after the flap track is installed.
We agree with the commenter's request for the reasons provided by
the commenter. We have revised paragraph (k) of this AD to state ``As
of the effective date of this AD, no person may install, on any
airplane, a wing outboard flap track having a part number listed in
paragraph 1.B. of Boeing Alert Requirements Bulletin 737-57A1338 RB,
dated September 25, 2017, unless the inspections . . . are accomplished
prior to or concurrently with the part's installation on the
airplane.''
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing the installation
of winglets using Supplemental Type Certificate (STC) ST01219SE does
not affect compliance with the actions proposed in the NPRM.
We concur with the commenter. We have redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD and added paragraph
(c)(2) to this AD to state that installation of STC ST01219SE does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01219SE is installed, a
``change in product'' alternative method of compliance (AMOC) approval
request is not necessary to comply with the requirements of 14 CFR
39.17.
Additional Change to This AD
The proposed AD included Note 1 to paragraph (h), which stated that
guidance for accomplishing the proposed actions could be found in
Boeing Alert Service Bulletin 737-57A1338, dated September 25, 2017,
which is referred to in Boeing Alert Requirements Bulletin 737-57A1338
RB, dated September 25, 2017. Since the proposed AD was published,
Boeing has issued Boeing Information Notice 737-57A1338 IN 01, dated
October 16, 2017; Boeing Information Notice 737-57A1338 IN 02, dated
March 16, 2018; and Boeing Information Notice 737-57A1338 IN 03, dated
March 20, 2018. These information notices provide additional guidance
material related to Boeing Alert Service Bulletin 737-57A1338, dated
September 25, 2017, including clarification of compliance times for
spares (not AD compliance times), inspection figures, and the
relationship between flap track part numbers and airplanes groups. We
have revised Note 1 to paragraph (h) in this AD to include these
information notices.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule with the changes described previously and minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Requirements Bulletin 737-57A1338 RB,
dated September 25, 2017. This service information describes procedures
for repetitive inspections and repetitive overhaul of the wing outboard
flap tracks, and applicable on-condition actions including repair and
replacement of the wing outboard flap tracks. 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.
Costs of Compliance
We estimate that this AD affects 160 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (positions 1 and 8; 78 work-hours x $85 $0 $6,630 per cycle................. $1,060,800 per cycle.
Group 2 and Group 3, configuration per hour = $6,630 per
1). cycle.
Inspection (positions 1 and 8; 89 work-hours x $85 0 7,565 per cycle.................. 1,210,400 per cycle.
Group 3, configuration 2). per hour = $7,565 per
cycle.
Inspection (positions 2 and 7; 83 work-hours x $85 0 7,055 per cycle.................. 1,128,800 per cycle.
Group 2 and Group 3, configuration per hour = $7,055 per
1). cycle.
Inspection (positions 2 and 7; 86 work-hours x $85 0 7,310 per cycle.................. 1,169,600 per cycle.
Group 3, configuration 2). per hour = $7,310 per
cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
cost estimates for the actions for Group 1 airplanes, the repetitive
overhaul, or the on-condition actions specified in this 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 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
[[Page 46383]]
the Director of the System Oversight Division.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2018-18-13 The Boeing Company: Amendment 39-19392; Docket No. FAA-
2018-0112; Product Identifier 2017-NM-161-AD.
(a) Effective Date
This AD is effective October 18, 2018.
(b) Affected ADs
This AD affects AD 2013-09-02, Amendment 39-17443 (78 FR 27010,
May 9, 2013) (``AD 2013-09-02'').
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of cracking in certain flanges,
and the adjacent web, of the wing outboard flap track at certain
positions, and a determination that new inspections of certain flap
track flanges and webs forward of the rear spar attachment are
necessary. We are issuing this AD to detect and correct cracking of
the wing outboard flap tracks. Cracking in the area between the
forward and rear spar attachments of the wing outboard flap tracks
could lead to the inability of a principal structural element to
sustain required flight loads, and result in loss of the outboard
trailing edge flap and consequent reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Requirements
Bulletin 737-57A1338 RB, dated September 25, 2017: Within 120 days
after the effective date of this AD, do actions to correct the
unsafe condition using a method approved in accordance with the
procedures specified in paragraph (l) of this AD.
(h) Required Actions
For airplanes not specified in paragraph (g) of this AD: Except
as required by paragraph (i) of this AD, at the applicable times
specified in the ``Compliance'' paragraph of Boeing Alert
Requirements Bulletin 737-57A1338 RB, dated September 25, 2017, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
737-57A1338 RB, dated September 25, 2017.
Note 1 to paragraph (h) of this AD: Guidance for accomplishing
the actions required by this AD can be found in Boeing Alert Service
Bulletin 737-57A1338, dated September 25, 2017, which is referred to
in Boeing Alert Requirements Bulletin 737-57A1338 RB, dated
September 25, 2017. Additional guidance can be found in Boeing
Information Notice 737-57A1338 IN 01, dated October 16, 2017; Boeing
Information Notice 737-57A1338 IN 02, dated March 16, 2018; and
Boeing Information Notice 737-57A1338 IN 03, dated March 20, 2018.
(i) Exceptions to Service Information Specifications
For purposes of determining compliance with the requirements of
this AD: Where Boeing Alert Requirements Bulletin 737-57A1338 RB,
dated September 25, 2017, uses the phrase ``the original issue date
of Requirements Bulletin 737-57A1338 RB,'' this AD requires using
``the effective date of this AD.''
(j) Terminating Action for Requirements of AD 2013-09-02
Accomplishment of the requirements specified in paragraph (h) of
this AD terminates all requirements of AD 2013-09-02.
(k) Parts Installation Limitation
As of the effective date of this AD, no person may install, on
any airplane, a wing outboard flap track having a part number listed
in paragraph 1.B. of Boeing Alert Requirements Bulletin 737-57A1338
RB, dated September 25, 2017, unless the inspections and corrective
actions specified in the Accomplishment Instructions of Boeing Alert
Requirements Bulletin 737-57A1338 RB, dated September 25, 2017, are
accomplished prior to or concurrently with the part's installation
on the airplane.
(l) 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 (m)(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.
(m) Related Information
(1) For more information about this AD, contact Payman Soltani,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712 4137; phone: 562-627-
5313; fax: 562-627-5210; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this
[[Page 46384]]
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin 737-57A1338 RB, dated
September 25, 2017.
(ii) Reserved.
(3) 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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on August 24, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-19185 Filed 9-12-18; 8:45 am]
BILLING CODE 4910-13-P
