Airworthiness Directives; The Boeing Company Airplanes, 5743-5746 [2018-02193]
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Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Proposed Rules
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection or Records Review
For airplanes that have an original
certificate of airworthiness or export
certificate of airworthiness issued on or
before the effective date of this AD: Within
12 months after the effective date of this AD,
inspect to determine if integrated
surveillance system (ISS) operational
program software (OPS) part number COL40–
0010–0100 or COL46–0007–0100 is installed.
A review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number of the software can be
conclusively determined from that review.
(h) Required Actions
If, during any inspection or records review
required by paragraph (g) of this AD, any ISS
OPS part number COL40–0010–0100 or
COL46–0007–0100 is found: Within 12
months after the effective date of this AD, do
all applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
B787–81205–SB340036–00, Issue 001, dated
June 30, 2017.
(i) Additional Actions for Group 1 Airplanes
For Group 1 airplanes identified in Boeing
Alert Service Bulletin B787–81205–
SB340036–00, Issue 001, dated June 30, 2017:
Prior to accomplishment of the actions
required by paragraph (h) of this AD, install
new software for the ISS OPS and the
displays and crew alerting (DCA) database, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin B787–
81205–SB340005–00, Issue 002, dated April
27, 2016.
(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install ISS OPS part number
COL40–0010–0100 or COL46–0007–0100 on
any airplane, except in accomplishment of
the actions required by paragraph (i) of this
AD.
sradovich on DSK3GMQ082PROD with PROPOSALS
(k) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (i) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Service
Bulletin B787–81205–SB340005–00, Issue
001, dated December 11, 2015.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (m)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
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(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as RC, the provisions
of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled 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 RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(m) Related Information
(1) For more information about this AD,
contact Nelson O. Sanchez, Aerospace
Engineer, Systems and Equipment Section,
FAA, Seattle ACO Branch, 1601 Lind Avenue
SW, Renton, WA 98057–3356; phone: 425–
917–6489; fax: 425–917–6590; email:
nelson.sanchez@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 1601 Lind
Avenue SW, Renton, WA. For information on
the availability of this material at the FAA,
call 425–227–1221.
Issued in Renton, Washington, on January
25, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–02199 Filed 2–8–18; 8:45 am]
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5743
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0074; Product
Identifier 2017–NM–148–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This proposed AD was
prompted by reports of cracks found in
the rear spar web and lower chord on
the left and right wings. This proposed
AD would require repetitive detailed
inspections for cracking of the rear spar
web and lower chord, 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 March 26, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Standards Branch,
1601 Lind Avenue SW, Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0074.
SUMMARY:
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Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Proposed Rules
ten airplanes. The cracks were found on
airplanes with total flight cycles
between 46,190 and 55,633. Cracks in
the rear spar web were reported on six
airplanes. Cracks in the lower chord of
the rear spar were reported on four
airplanes. On one airplane, cracks were
found at multiple locations in the rear
spar web and in the lower chord. The
largest reported cracks were 0.059 inch
in the upper rear spar web, 0.045 inch
in the lower rear spar web, and 0.063
inch in the lower chord. This condition,
if not corrected, could lead to the
inability of a principal structural
element to sustain required flight load,
which could adversely affect the
structural integrity of the airplane.
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–
0074; 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 Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0074; Product Identifier 2017–
NM–148–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received a report indicating
that cracks were found at fastener holes
in the rear spar web and lower chord on
the left and right wings between wing
buttock line (WBL) 93 and WBL 146 on
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert
Requirements Bulletin 737–57A1337
RB, dated September 14, 2017. The
service information describes
procedures for repetitive detailed or
surface High Frequency Eddy Current
(HFEC) inspections for cracking of the
rear spar web and lower chord, 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
For Group 2 airplanes (line numbers
292 through 3132), this proposed AD
would require accomplishment of the
actions identified in the Boeing Alert
Requirements Bulletin 737–57A1337
RB, dated September 14, 2017,
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–2018–
0074.
Group 1 airplanes (line numbers 1
through 291) have a limit of validity
(LOV) of 34,000 total flight cycles, and
the actions specified in Boeing Alert
Requirements Bulletin 737–57A1337
RB, dated September 14, 2017, would be
required at a compliance time occurring
after that LOV. Although operation of an
airplane beyond its LOV is prohibited
by 14 CFR 121.1115 and 129.115, this
NPRM would include those airplanes so
they are tracked in the event the LOV
is extended in the future.
Explanation of ‘‘RB’’ (Requirements
Bulletin)
The FAA has worked in conjunction
with industry, under the Airworthiness
Directives 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 and flow time for 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 (RB), which
contains only the actions needed to
address the unsafe condition (i.e., only
RC actions).
Costs of Compliance
We estimate that this proposed AD
affects 160 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Inspections .............................
sradovich on DSK3GMQ082PROD with PROPOSALS
Action
Up to 22 work-hours × $85
per hour = up to $1,870 per
inspection cycle.
$0
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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Cost per product
Up to $1,870 per inspection
cycle.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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Cost on U.S. operators
Up to $299,200 per inspection
cycle.
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
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Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Proposed Rules
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes to the Director of the
System Oversight Division.
Regulatory Findings
We 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.
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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:
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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–
2018–0074; Product Identifier 2017–
NM–148–AD.
(a) Comments Due Date
We must receive comments by March 26,
2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of cracks
found in the rear spar web and lower chord
on the left and right wings. We are issuing
this AD to detect and correct cracks in the
rear spar of the left and right wing between
wing buttock line (WBL) 91 and WBL 155,
which could lead to the inability of a
principal structural element to sustain
required flight load and adversely affect the
structural integrity 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 in Group 1 in
Boeing Alert Requirements Bulletin 737–
57A1337 RB, dated September 14, 2017:
Within 120 days after the effective date of
this AD, inspect the airplane and do all
applicable corrective actions using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
(h) Required Actions for Group 2 Airplanes
For airplanes identified as Group 2 in
Boeing Alert Requirements Bulletin 737–
57A1337 RB, dated September 14, 2017:
Except as required by paragraph (i) of this
AD, at the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 737–57A1337 RB,
dated September 14, 2017, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 737–57A1337
RB, dated September 14, 2017.
Note 1 to paragraph (h) of this AD:
Guidance for accomplishing the actions
required by this AD is included in Boeing
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5745
Alert Service Bulletin 737–57A1337, dated
September 14, 2017, which is referred to in
Boeing Alert Requirements Bulletin 737–
57A1337 RB, dated September 14, 2017.
(i) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Alert Requirements Bulletin
737–57A1337 RB, dated September 14, 2017,
uses the phrase ‘‘the original issue date of
Requirements Bulletin 737–57A1337 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 737–57A1337 RB, dated September
14, 2017, specifies contacting Boeing, this AD
requires repair using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(j) 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 (k)(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.
(k) 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) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 1601 Lind
Avenue SW, Renton, WA. For information on
the availability of this material at the FAA,
call 425–227–1221.
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Issued in Renton, Washington, on January
26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–02193 Filed 2–8–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0072; Product
Identifier 2017–NM–082–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2014–05–
28, for certain Bombardier, Inc., Model
DHC–8–400 series airplanes. AD 2014–
05–28 requires revising the maintenance
or inspection program, as applicable.
Since we issued AD 2014–05–28, we
have determined that the interval from
maintenance review board (MRB) task
number 323100–202 should not be
escalated, and that Certification
Maintenance Requirements (CMR) task
number 323100–102 should be
applicable to all Model DHC–8–400
series airplanes, regardless of which
main landing gear (MLG) up-lock
assembly is installed. This proposed AD
would require revising the maintenance
or inspection program, as applicable.
We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by March 26, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Bombardier, Inc., Q-
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SUMMARY:
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Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5,
Canada; telephone: 416–375–4000; fax:
416–375–4539; email: thd.qseries@
aero.bombardier.com; internet: https://
www.bombardier.com. You may view
this referenced service information at
the FAA, Transport Standards Branch,
1601 Lind Avenue SW, Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
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–
0072; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket 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: Erin
Hulverson, Aerospace Engineer, FAA,
Boston ACO Branch, 1200 District
Avenue, Burlington, MA 01803;
telephone: 781–238–7655.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0072; Product Identifier 2017–
NM–082–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD 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 proposed AD.
Discussion
We issued AD 2014–05–28,
Amendment 39–17800 (79 FR 18611,
April 3, 2014) (‘‘AD 2014–05–28’’), for
certain Bombardier, Inc., Model DHC–
8–400 series airplanes.
AD 2014–05–28 resulted from reports
of excessive wear on the lower latch
surface of the MLG up-lock hook. AD
2014–05–28 requires revising the
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maintenance or inspection program, as
applicable. We issued AD 2014–05–28
to detect and correct up-lock hooks
worn beyond the wear limit, which
could prevent the successful extension
of the MLG using the primary landing
gear extension system, which in
combination with an alternate extension
system failure could result in the
inability to extend the MLG.
Since we issued AD 2014–05–28, we
have determined that the interval from
MRB task number 323100–202 should
not be escalated, and that MRB task
number 323100–202 should be
applicable to all Model DHC–8–400
series airplanes, regardless of which
MLG up-lock assembly is installed.
This revised applicability has resulted
in CMR task number 323100–102 also
being made applicable to all Model
DHC–8–400 series airplanes, regardless
of MLG up-lock assembly part number
installation.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2017–15, dated May 29, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ’’the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.,
Model DHC–8–400 series airplanes. The
MCAI states:
[Canadian] AD CF–2012–21 [which
corresponds to FAA AD 2014–05–28] was
issued to mandate the incorporation of
Maintenance Review Board (MRB) task
number 323100–202. As in-service
experience has shown that the interval for
MRB task number 323100–202 should not be
escalated, Bombardier has introduced onestar CMR task number 323100–102 to prevent
task escalation. Bombardier has also revised
the applicability of MRB task number
323100–202 to be applicable to the entire
DHC–8–400/–401/–402 fleet, regardless of
which main landing gear (MLG) up-lock
assembly part number is installed. This
revised applicability has resulted in CMR
task number 323100–102 also being made
applicable to the entire DHC–8–400/–401/–
402 fleet, regardless of MLG up-lock
assembly part number installation.
This [Canadian] AD mandates the
incorporation of CMR task number 323100–
102 [into the maintenance or inspection
program, as applicable].
You may examine the MCAI in the
AD docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0072.
Related Service Information Under 1
CFR Part 51
Bombardier, Inc., has issued Q400
Dash 8 Temporary Revision ALI–0168,
dated October 31, 2016, to Section 1–32,
Landing Gear Maintenance Program, of
E:\FR\FM\09FEP1.SGM
09FEP1
]]>Agencies
[Federal Register Volume 83, Number 28 (Friday, February 9, 2018)]
[Proposed Rules]
[Pages 5743-5746]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02193]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0074; Product Identifier 2017-NM-148-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This proposed AD was prompted by reports of cracks
found in the rear spar web and lower chord on the left and right wings.
This proposed AD would require repetitive detailed inspections for
cracking of the rear spar web and lower chord, 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 March 26, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on
the availability of this material at the FAA, call 425-227-1221. It is
also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2018-0074.
[[Page 5744]]
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-
0074; 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 Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0074;
Product Identifier 2017-NM-148-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received a report indicating that cracks were found at
fastener holes in the rear spar web and lower chord on the left and
right wings between wing buttock line (WBL) 93 and WBL 146 on ten
airplanes. The cracks were found on airplanes with total flight cycles
between 46,190 and 55,633. Cracks in the rear spar web were reported on
six airplanes. Cracks in the lower chord of the rear spar were reported
on four airplanes. On one airplane, cracks were found at multiple
locations in the rear spar web and in the lower chord. The largest
reported cracks were 0.059 inch in the upper rear spar web, 0.045 inch
in the lower rear spar web, and 0.063 inch in the lower chord. This
condition, if not corrected, could lead to the inability of a principal
structural element to sustain required flight load, which could
adversely affect the structural integrity of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Requirements Bulletin 737-57A1337 RB,
dated September 14, 2017. The service information describes procedures
for repetitive detailed or surface High Frequency Eddy Current (HFEC)
inspections for cracking of the rear spar web and lower chord, 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
For Group 2 airplanes (line numbers 292 through 3132), this
proposed AD would require accomplishment of the actions identified in
the Boeing Alert Requirements Bulletin 737-57A1337 RB, dated September
14, 2017, 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-2018-0074.
Group 1 airplanes (line numbers 1 through 291) have a limit of
validity (LOV) of 34,000 total flight cycles, and the actions specified
in Boeing Alert Requirements Bulletin 737-57A1337 RB, dated September
14, 2017, would be required at a compliance time occurring after that
LOV. Although operation of an airplane beyond its LOV is prohibited by
14 CFR 121.1115 and 129.115, this NPRM would include those airplanes so
they are tracked in the event the LOV is extended in the future.
Explanation of ``RB'' (Requirements Bulletin)
The FAA has worked in conjunction with industry, under the
Airworthiness Directives 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 and flow time for 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 (RB), which contains
only the actions needed to address the unsafe condition (i.e., only RC
actions).
Costs of Compliance
We estimate that this proposed AD affects 160 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections..................... Up to 22 work-hours $0 Up to $1,870 per Up to $299,200 per
x $85 per hour = inspection cycle. inspection cycle.
up to $1,870 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
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
[[Page 5745]]
detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
Regulatory Findings
We 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-2018-0074; Product Identifier
2017-NM-148-AD.
(a) Comments Due Date
We must receive comments by March 26, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of cracks found in the rear spar
web and lower chord on the left and right wings. We are issuing this
AD to detect and correct cracks in the rear spar of the left and
right wing between wing buttock line (WBL) 91 and WBL 155, which
could lead to the inability of a principal structural element to
sustain required flight load and adversely affect the structural
integrity 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 in Group 1 in Boeing Alert Requirements
Bulletin 737-57A1337 RB, dated September 14, 2017: Within 120 days
after the effective date of this AD, inspect the airplane and do all
applicable corrective actions using a method approved in accordance
with the procedures specified in paragraph (j) of this AD.
(h) Required Actions for Group 2 Airplanes
For airplanes identified as Group 2 in Boeing Alert Requirements
Bulletin 737-57A1337 RB, dated September 14, 2017: Except as
required by paragraph (i) of this AD, at the applicable times
specified in the ``Compliance'' paragraph of Boeing Alert
Requirements Bulletin 737-57A1337 RB, dated September 14, 2017, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
737-57A1337 RB, dated September 14, 2017.
Note 1 to paragraph (h) of this AD: Guidance for accomplishing
the actions required by this AD is included in Boeing Alert Service
Bulletin 737-57A1337, dated September 14, 2017, which is referred to
in Boeing Alert Requirements Bulletin 737-57A1337 RB, dated
September 14, 2017.
(i) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Requirements Bulletin 737-57A1337 RB,
dated September 14, 2017, uses the phrase ``the original issue date
of Requirements Bulletin 737-57A1337 RB,'' this AD requires using
``the effective date of this AD.''
(2) Where Boeing Alert Requirements Bulletin 737-57A1337 RB,
dated September 14, 2017, specifies contacting Boeing, this AD
requires repair using a method approved in accordance with the
procedures specified in paragraph (j) of this AD.
(j) 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 (k)(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.
(k) 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) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 1601 Lind Avenue
SW, Renton, WA. For information on the availability of this material
at the FAA, call 425-227-1221.
[[Page 5746]]
Issued in Renton, Washington, on January 26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-02193 Filed 2-8-18; 8:45 am]
BILLING CODE 4910-13-P
