Airworthiness Directives; The Boeing Company Airplanes, 26331-26334 [2019-11790]
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26331
Rules and Regulations
Federal Register
Vol. 84, No. 109
Thursday, June 6, 2019
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1004; Product
Identifier 2018–NM–106–AD; Amendment
39–19642; AD 2019–10–03]
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 cracks caused by corrosion of
the edge of the bore of the spot face and
corrosion of the lug bore of certain sidestrut support fitting lugs. This AD
requires repetitive detailed inspections
of the left and right side-strut support
fitting lugs with bushings installed for
any corrosion, any crack, or any severed
lug; repetitive detailed and high
frequency eddy current (HFEC)
inspections of the left and right sidestrut support fitting lugs with bushings
removed for any corrosion or any crack;
and applicable on-condition actions. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 11,
2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 11, 2019.
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;
phone: 562–797–1717; internet: https://
www.myboeingfleet.com. You may view
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SUMMARY:
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this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
1004.
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–
1004; 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
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 Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5232; fax: 562–627–
5210; email: george.garrido@faa.gov.
We are issuing this AD to address
cracks caused by corrosion, which could
result in sudden loss of the side-strut
support fitting joint and main landing
gear attachment to the airplane,
resulting in the collapse of a main
landing gear.
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.
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing Supplemental Type
Certificate (STC) ST01219SE does not
affect the actions specified in the
proposed AD.
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.
Discussion
Request To Change Format of
Paragraphs (g) and (h) of the Proposed
AD
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
737–100, –200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
December 6, 2018 (83 FR 62741). The
NPRM was prompted by reports of
cracks caused by corrosion of the edge
of the bore of the spot face and
corrosion of the lug bore of certain sidestrut support fitting lugs. The NPRM
proposed to require repetitive detailed
inspections of the left and right sidestrut support fitting lugs with bushings
installed for any corrosion, any crack, or
any severed lug; repetitive detailed and
HFEC inspections of the left and right
side-strut support fitting lugs with
bushings removed for any corrosion or
any crack; and applicable on-condition
actions.
Boeing requested that we eliminate
paragraph (h) of the proposed AD and
incorporate the information as
paragraph (g)(2) of this AD. Boeing
pointed out that the title of paragraph
(g) of the proposed AD would change to
‘‘Required Actions,’’ and that
paragraphs (g)(1) and (g)(2) of this AD
would apply to Group 7 and Groups 1
through 6, respectively. Boeing stated
that this request is for consistency with
previous ADs for Boeing airplanes.
We disagree that elimination of
paragraph (h) of the proposed AD and
incorporating the information as
paragraph (g)(2) of this AD is necessary.
Over time we have used both formats,
but most recently we have been using
the format that was utilized in the
NPRM. We do not find that there is a
difference in clarity of the required
actions. We also find that the requested
change does not affect the requirements
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules and Regulations
of this final rule in this case. We have
not changed this AD in this regard.
Request To Clarify ACO Branch
Authority
Boeing requested that we clarify the
ACO branch that has the authority to
approve AMOCs for this group of
airplanes. Boeing pointed out that
previous final rules for The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes
have identified The Manager, Los
Angeles ACO Branch, FAA, had the
authority to approve AMOCs, even
when the service bulletin was submitted
for approval through the Seattle ACO
Branch. Additionally, Boeing pointed
out that previous ADs for The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes
identified a Los Angeles ACO Branch
specialist in the ‘‘Related Information’’
paragraph of the proposed rule, even
when the service bulletin was submitted
for approval through the Seattle ACO
Branch.
We agree that clarification is
necessary. Normally, in NPRMs for The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes, we include the Manager, Los
Angeles ACO Branch, as the designated
approval authority for AMOCs. We have
updated paragraph (j) of this AD to
specify The Manager, Los Angeles ACO
Branch. The Seattle ACO Branch is
responsible during drafting of the NPRM
and final rule of an AD for The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
After publication of the final rule,
responsibility for the product is
transferred to the Los Angeles ACO
Branch. Therefore, when we draft the
final rule of an AD for The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
we also specify a specialist from the Los
Angeles ACO Branch. We have updated
paragraph (k) of this AD to include the
responsible specialist from the Los
Angeles ACO Branch.
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 Service Bulletin
737–53–1246, Revision 1, dated May 30,
2018. This service information describes
procedures for repetitive detailed
inspections of the left and right sidestrut support fitting lugs at body station
(BS) 685 with bushings installed for any
corrosion, any crack, or any severed lug;
repetitive detailed and HFEC
inspections of the left and right sidestrut support fitting lugs at BS 685 with
bushings removed for any corrosion or
any crack; and applicable on-condition
actions. On-condition actions include,
among other things, inspections,
corrosion removal, and a preventative
modification. Doing the repetitive
detailed and HFEC inspections of the
side-strut support fitting lugs at BS 685
with bushings removed terminates the
repetitive detailed inspections of the
side-strut support fitting lugs at BS 685
with bushings installed. 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 302
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Repetitive detailed inspection of left and
right side lugs with bushings installed.
Repetitive detailed and HFEC inspections of left and right side lugs with
bushings removed.
17 work-hours × $85 per hour = $1,445
per inspection cycle.
29 work-hours × $85 per hour = $2,465
per inspection cycle.
We estimate the following costs to do
any necessary on-condition actions that
would be required. We have no way of
Cost per product
Cost on U.S.
operators
$1,445 per inspection cycle.
$2,465 per inspection cycle.
$436,390 per inspection cycle.
$744,430 per inspection cycle.
Parts cost
$0
0
determining the number of aircraft that
might need these on-condition actions:
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ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per product
Up to 18 work-hour × $85 per hour = $1,530 per inspection cycle ........
Unknown ........................................
Up to $1,530 per inspection cycle.
We have received no definitive data
that would enable us to provide parts
cost estimates for the on-condition
inspections and repairs specified in this
AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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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,
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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
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Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules and Regulations
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
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
1. The authority citation for part 39
continues to read as follows:
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■
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):
■
2019–10–03 The Boeing Company:
Amendment 39–19642; Docket No.
VerDate Sep<11>2014
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FAA–2018–1004; Product Identifier
2018–NM–106–AD.
(a) Effective Date
This AD is effective July 11, 2019.
(b) Affected ADs
None.
(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 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 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks
caused by corrosion of the edge of the bore
of the spot face and corrosion of the lug bore
of the body station (BS) 685 side-strut
support fitting lugs. We are issuing this AD
to address cracks caused by corrosion, which
could result in sudden loss of the side-strut
support fitting joint and main landing gear
attachment to the airplane, resulting in the
collapse of a main landing gear.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions for Group 7 Airplanes
For airplanes identified as Group 7 in
Boeing Service Bulletin 737–53–1246,
Revision 1, dated May 30, 2018: Within 120
days after the effective date of this AD,
inspect the left and right side-strut support
fitting lugs at BS 685 and do all applicable
on-condition actions using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
(h) Required Actions for Groups 1 Through
6 Airplanes
For airplanes identified as Groups 1
through 6 in Boeing Service Bulletin 737–53–
1246, Revision 1, dated May 30, 2018, except
as specified in paragraph (i) of this AD: At
the applicable times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 737–53–1246, Revision 1, dated May
30, 2018, do all applicable actions identified
as ‘‘RC’’ (required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1246, Revision 1, dated May 30, 2018.
(i) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Service Bulletin 737–53–1246,
Revision 1, dated May 30, 2018, uses the
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26333
phrase ‘‘the Revision 1 date of this service
bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(2) Where Boeing Service Bulletin 737–53–
1246, Revision 1, dated May 30, 2018,
specifies contacting Boeing for repair
instructions or for work instructions: This
AD requires doing the repair or the work
instructions and doing applicable oncondition actions 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) of this
AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, FAA, to make those findings.
To be approved, the repair method,
modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(4) Except as required by paragraph (i) of
this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(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.
(k) Related Information
For more information about this AD,
contact George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5232; fax: 562–627–5210; email:
george.garrido@faa.gov.
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Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules and Regulations
(l) 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 the AD specifies otherwise.
(i) Boeing Service Bulletin 737–53–1246,
Revision 1, dated May 30, 2018.
(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;
phone: 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/ibrlocations.html.
Issued in Des Moines, Washington, on May
20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–11790 Filed 6–5–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0801; Product
Identifier 2017–NM–147–AD; Amendment
39–19632; AD 2019–08–11]
RIN 2120–AA640
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–24–
14, which applied to all Bombardier,
Inc., Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes. AD 2008–
24–14 required revising the instructions
for continued airworthiness to
incorporate certain airworthiness
limitations for the main landing gear
(MLG) trunnion fitting assembly. This
AD requires revising the maintenance or
inspection program, as applicable, to
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SUMMARY:
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incorporate certain airworthiness
limitations (AWLs). This AD also
requires reworking the trunnion fitting
in order to meet new structural safe-life
limits. This AD was prompted by
reports of cracks on the MLG trunnion
fitting during fatigue testing; the
introduction of new AWL tasks with
revised inspection, modification, and
safe-life requirements; and a
determination that the trunnion fitting
lower flange and both forward and aft
bore holes are also subject to fatigue
cracking. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective July 11,
2019.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 11, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of December 19, 2008 (73 FR
73785, December 4, 2008).
ADDRESSES: For service information
identified in this final rule, contact
Bombardier, Inc., 400 Coˆte-Vertu Road
West, Dorval, Que´bec H4S 1Y9, Canada;
Widebody Customer Response Center
North America toll-free telephone 1–
866–538–1247 or direct-dial telephone
1–514–855–2999; fax 514–855–7401;
email ac.yul@aero.bombardier.com;
internet https://www.bombardier.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–
0801.
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–
0801; 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
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: Aziz
Ahmed, Aerospace Engineer, Airframe
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and Mechanical Systems Section, FAA,
New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7329; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008–24–14,
Amendment 39–15758 (73 FR 73785,
December 4, 2008) (‘‘AD 2008–24–14’’).
AD 2008–24–14 applied to all
Bombardier, Inc., Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. The NPRM published in the
Federal Register on October 1, 2018 (83
FR 49317). The NPRM was prompted by
reports of cracks on the MLG trunnion
fitting during fatigue testing; the
introduction of new AWL tasks with
revised inspection, modification, and
safe-life requirements; and a
determination that the trunnion fitting
lower flange and both forward and aft
bore holes are also subject to fatigue
cracking. The NPRM proposed to
require revising the maintenance or
inspection program, as applicable, to
incorporate certain AWLs. The NPRM
also proposed to require reworking the
trunnion fitting in order to meet new
structural safe-life limits. We are issuing
this AD to address fatigue cracking of
the MLG trunnion fitting. Failure of the
MLG trunnion fitting could result in
MLG collapse.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2017–27, dated August 2, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.,
Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes. The MCAI
states:
Cracks on the main landing gear (MLG)
trunnion fitting web discovered during
fatigue testing led to the issuance of
[Canadian] AD CF–2008–21 [which
corresponds to FAA AD 2008–24–14], which
mandated new inspection requirements to
ensure that fatigue cracking of the trunnion
web would be detected and corrected.
Additional fatigue test article findings and
in-service findings have shown that the
trunnion fitting lower flange and both
forward and aft bore holes are also subject to
fatigue cracking. Failure of the main landing
gear trunnion fitting could result in the
collapse of the main landing gear.
Bombardier Inc. has decided to implement a
series of design changes to improve the
fatigue life of the trunnion fitting that is now
a safe-life assembly.
New and revised Airworthiness Limitation
(AWL) tasks for the MLG trunnion fitting
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Agencies
[Federal Register Volume 84, Number 109 (Thursday, June 6, 2019)]
[Rules and Regulations]
[Pages 26331-26334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11790]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
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Federal Register / Vol. 84, No. 109 / Thursday, June 6, 2019 / Rules
and Regulations
[[Page 26331]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-1004; Product Identifier 2018-NM-106-AD; Amendment
39-19642; AD 2019-10-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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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 cracks caused by
corrosion of the edge of the bore of the spot face and corrosion of the
lug bore of certain side-strut support fitting lugs. This AD requires
repetitive detailed inspections of the left and right side-strut
support fitting lugs with bushings installed for any corrosion, any
crack, or any severed lug; repetitive detailed and high frequency eddy
current (HFEC) inspections of the left and right side-strut support
fitting lugs with bushings removed for any corrosion or any crack; and
applicable on-condition actions. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective July 11, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 11,
2019.
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; phone: 562-797-1717; internet: https://www.myboeingfleet.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1004.
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-
1004; 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 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 Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; 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 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on December 6, 2018 (83 FR
62741). The NPRM was prompted by reports of cracks caused by corrosion
of the edge of the bore of the spot face and corrosion of the lug bore
of certain side-strut support fitting lugs. The NPRM proposed to
require repetitive detailed inspections of the left and right side-
strut support fitting lugs with bushings installed for any corrosion,
any crack, or any severed lug; repetitive detailed and HFEC inspections
of the left and right side-strut support fitting lugs with bushings
removed for any corrosion or any crack; and applicable on-condition
actions.
We are issuing this AD to address cracks caused by corrosion, which
could result in sudden loss of the side-strut support fitting joint and
main landing gear attachment to the airplane, resulting in the collapse
of a main landing gear.
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.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type Certificate (STC) ST01219SE does not affect the actions specified
in the proposed AD.
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.
Request To Change Format of Paragraphs (g) and (h) of the Proposed AD
Boeing requested that we eliminate paragraph (h) of the proposed AD
and incorporate the information as paragraph (g)(2) of this AD. Boeing
pointed out that the title of paragraph (g) of the proposed AD would
change to ``Required Actions,'' and that paragraphs (g)(1) and (g)(2)
of this AD would apply to Group 7 and Groups 1 through 6, respectively.
Boeing stated that this request is for consistency with previous ADs
for Boeing airplanes.
We disagree that elimination of paragraph (h) of the proposed AD
and incorporating the information as paragraph (g)(2) of this AD is
necessary. Over time we have used both formats, but most recently we
have been using the format that was utilized in the NPRM. We do not
find that there is a difference in clarity of the required actions. We
also find that the requested change does not affect the requirements
[[Page 26332]]
of this final rule in this case. We have not changed this AD in this
regard.
Request To Clarify ACO Branch Authority
Boeing requested that we clarify the ACO branch that has the
authority to approve AMOCs for this group of airplanes. Boeing pointed
out that previous final rules for The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes have identified The
Manager, Los Angeles ACO Branch, FAA, had the authority to approve
AMOCs, even when the service bulletin was submitted for approval
through the Seattle ACO Branch. Additionally, Boeing pointed out that
previous ADs for The Boeing Company Model 737-100, -200, -200C, -300, -
400, and -500 series airplanes identified a Los Angeles ACO Branch
specialist in the ``Related Information'' paragraph of the proposed
rule, even when the service bulletin was submitted for approval through
the Seattle ACO Branch.
We agree that clarification is necessary. Normally, in NPRMs for
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes, we include the Manager, Los Angeles ACO Branch, as
the designated approval authority for AMOCs. We have updated paragraph
(j) of this AD to specify The Manager, Los Angeles ACO Branch. The
Seattle ACO Branch is responsible during drafting of the NPRM and final
rule of an AD for The Boeing Company Model 737-100, -200, -200C, -300,
-400, and -500 series airplanes. After publication of the final rule,
responsibility for the product is transferred to the Los Angeles ACO
Branch. Therefore, when we draft the final rule of an AD for The Boeing
Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes, we also specify a specialist from the Los Angeles ACO
Branch. We have updated paragraph (k) of this AD to include the
responsible specialist from the Los Angeles ACO Branch.
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 Service Bulletin 737-53-1246, Revision 1, dated
May 30, 2018. This service information describes procedures for
repetitive detailed inspections of the left and right side-strut
support fitting lugs at body station (BS) 685 with bushings installed
for any corrosion, any crack, or any severed lug; repetitive detailed
and HFEC inspections of the left and right side-strut support fitting
lugs at BS 685 with bushings removed for any corrosion or any crack;
and applicable on-condition actions. On-condition actions include,
among other things, inspections, corrosion removal, and a preventative
modification. Doing the repetitive detailed and HFEC inspections of the
side-strut support fitting lugs at BS 685 with bushings removed
terminates the repetitive detailed inspections of the side-strut
support fitting lugs at BS 685 with bushings installed. 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 302 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Repetitive detailed inspection 17 work-hours x $85 per $0 $1,445 per $436,390 per
of left and right side lugs hour = $1,445 per inspection cycle. inspection cycle.
with bushings installed. inspection cycle.
Repetitive detailed and HFEC 29 work-hours x $85 per 0 $2,465 per $744,430 per
inspections of left and right hour = $2,465 per inspection cycle. inspection cycle.
side lugs with bushings inspection cycle.
removed.
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We estimate the following costs to do any necessary on-condition
actions that would be required. We have no way of determining the
number of aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions
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Labor cost Parts cost Cost per product
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Up to 18 work-hour x $85 per Unknown........... Up to $1,530 per
hour = $1,530 per inspection inspection cycle.
cycle.
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We have received no definitive data that would enable us to provide
parts cost estimates for the on-condition inspections and repairs
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
[[Page 26333]]
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 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):
2019-10-03 The Boeing Company: Amendment 39-19642; Docket No. FAA-
2018-1004; Product Identifier 2018-NM-106-AD.
(a) Effective Date
This AD is effective July 11, 2019.
(b) Affected ADs
None.
(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 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 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks caused by corrosion of
the edge of the bore of the spot face and corrosion of the lug bore
of the body station (BS) 685 side-strut support fitting lugs. We are
issuing this AD to address cracks caused by corrosion, which could
result in sudden loss of the side-strut support fitting joint and
main landing gear attachment to the airplane, resulting in the
collapse of a main landing gear.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 7 Airplanes
For airplanes identified as Group 7 in Boeing Service Bulletin
737-53-1246, Revision 1, dated May 30, 2018: Within 120 days after
the effective date of this AD, inspect the left and right side-strut
support fitting lugs at BS 685 and do all applicable on-condition
actions using a method approved in accordance with the procedures
specified in paragraph (j) of this AD.
(h) Required Actions for Groups 1 Through 6 Airplanes
For airplanes identified as Groups 1 through 6 in Boeing Service
Bulletin 737-53-1246, Revision 1, dated May 30, 2018, except as
specified in paragraph (i) of this AD: At the applicable times
specified in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 737-53-1246, Revision 1, dated May 30, 2018, do all
applicable actions identified as ``RC'' (required for compliance)
in, and in accordance with, the Accomplishment Instructions of
Boeing Service Bulletin 737-53-1246, Revision 1, dated May 30, 2018.
(i) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Service Bulletin 737-53-1246, Revision 1,
dated May 30, 2018, uses the phrase ``the Revision 1 date of this
service bulletin,'' this AD requires using ``the effective date of
this AD.''
(2) Where Boeing Service Bulletin 737-53-1246, Revision 1, dated
May 30, 2018, specifies contacting Boeing for repair instructions or
for work instructions: This AD requires doing the repair or the work
instructions and doing applicable on-condition actions 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) 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, FAA, to make those findings. To be
approved, the repair method, modification deviation, or alteration
deviation must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (i) of this AD: For service
information that contains steps that are labeled as RC, the
provisions of paragraphs (j)(4)(i) and (j)(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.
(k) Related Information
For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5232; fax: 562-627-5210; email: [email protected].
[[Page 26334]]
(l) 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 the AD specifies otherwise.
(i) Boeing Service Bulletin 737-53-1246, Revision 1, dated May
30, 2018.
(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; phone: 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 May 20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-11790 Filed 6-5-19; 8:45 am]
BILLING CODE 4910-13-P