Airworthiness Directives; The Boeing Company Airplanes, 46902-46905 [2018-19840]
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46902
Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
(b) Affected ADs
None.
(c) Applicability
This AD applies to GA 8 Airvan (Pty) Ltd
Models GA8 and GA8–TC320 airplanes,
certificated in any category, with a strut or
strut fitting installed that has a part number
and serial number listed in table 1 of
GippsAero Service Bulletin SB–GA8–2017–
174, Issue 2, dated May 23, 2018 (GippsAero
SB–GA8–2017–174, Issue 2).
(d) Subject
Air Transport Association of America
(ATA) Code 57: Wings.
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(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
issued by the aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as certain
wing strut fittings manufactured with
incorrect grain orientation, which has an
unknown effect on fatigue-related concerns.
We are issuing this AD to detect and address
fatigue-related damage to the wing strut
fittings, which could lead to failure of the
wing with consequent loss of control of the
airplane.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) through (6) of this
AD:
(1) Within 3 months after the effective date
of this AD or within 100 hours time-inservice (TIS) after the effective date of this
AD, whichever occurs first, with the wing
struts removed, visually inspect each forward
and aft wing strut fitting and fuselage
attachment point for cracks, corrosion, and
damage. If a crack, corrosion, or damage is
found during the inspection, before further
flight, do the applicable corrective actions
(check torque, restore surface protection,
rework areas with fouling, and replace any
part with a crack, corrosion, or damage).
Follow the procedures in Parts C1, C2, and
D or E, as applicable, in the Accomplishment
Instructions in GippsAero SB–GA8–2017–
174, Issue 2.
(2) Within 3 months after the effective date
of this AD or within 100 hours TIS after the
effective date of this AD, whichever occurs
first, and thereafter at intervals not to exceed
100 hours TIS, visually inspect each strut
and strut fitting for cracks, corrosion, and
damage. If a crack, corrosion, or damage is
found during any of the inspections, before
further flight, do the applicable corrective
actions (check torque, restore surface
protection, and replace any part with a crack,
corrosion, or damage). Follow the procedures
in Parts B and D or E, as applicable, in the
Accomplishment Instructions of GippsAero
SB–GA8–2017–174, Issue 2.
(3) Within 1,000 hours TIS after doing the
inspections required in paragraph (f)(1) of
this AD and thereafter at intervals not to
exceed 1,000 hours TIS, with the wing struts
installed, visually inspect each forward and
aft wing strut, strut fitting, and strut fitting
lug hole for cracks, corrosion, and damage. If
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a crack, corrosion, or damage is found during
any of the inspections, before further flight,
do the applicable corrective actions (do
additional inspections, replace hardware,
and replace any part with a crack, corrosion,
or damage). Follow the procedures in Parts
C3 and D or E, as applicable, in the
Accomplishment Instructions of GippsAero
SB–GA8–2017–174, Issue 2.
(4) To use an eddy current or fluorescent
liquid penetrant inspection method instead
of a visual inspection for the requirements in
paragraphs (f)(1) of this AD, the Manager,
Small Airplane Standards Branch, FAA must
approve your inspection method, and the
Manager’s approval letter must specifically
refer to this AD. Send your approval request
to the contact information found in
paragraph (g)(1) of this AD.
(5) Remove from service each part listed in
Parts D and E of table 3 on or before the part
exceeds its specified replacement time and
replace with an airworthy part. On the
effective date of this AD, any part listed in
table 3 of GippsAero SB–GA8–2017–174,
Issue 2, that has exceeded its replacement
time, within 100 hours TIS after the effective
date of this AD or within 12 months after the
effective date of this AD, whichever occurs
first, remove the part from service and
replace with an airworthy part. Follow the
replacement procedures in Part D or Part E,
as applicable, in the Accomplishment
Instructions of GippsAero SB–GA8–2017–
174, Issue 2.
(6) Within 24 hours after each inspection
required in paragraphs (f)(1) and (2) of this
AD, submit a report of the inspection results,
even if no damage is found, to the Civil
Aviation Safety Authority (CASA) and GA 8
Airvan (Pty) Ltd. Use the Document
Compliance Notice of GippsAero SB–GA8–
2017–174, Issue 2, and include in the report
the total hours TIS on the airplane and the
type of operation. You may use the contact
information found in paragraph (h) of this
AD to contact GA 8 Airvan (Pty) Ltd. To
contact CASA, use the online CASA Defect
Reporting Service at the following internet
address: https://drs.casa.gov.au/.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Small Airplane
Standards Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Doug Rudolph,
Aerospace Engineer, FAA, Small Airplane
Standards Branch, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
(816) 329–4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
instead be accomplished using a method
approved by the Manager, Small Airplane
Standards Branch, FAA; or CASA.
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(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a currently
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0731. Public reporting for
this collection of information is estimated to
be approximately 1 hour per response,
including the time for reviewing instructions,
searching existing data sources, gathering
and maintaining the data needed, completing
and reviewing the collection of information.
All responses to this collection of
information are voluntary; the nature and
extent of confidentiality to be provided, if
any. Send comments regarding this burden
estimate or any other aspect of this collection
of information, including suggestions for
reducing this burden to: Information
Collection Clearance Officer, Federal
Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
(h) Related Information
Refer to MCAI issued by CASA, AD No.
AD/GA8/9, Amendment 1, dated May 29,
2018. You may examine the MCAI on the
internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–0771. For service information related to
this AD, contact GA 8 Airvan (Pty) Ltd, c/o
GippsAero Pty Ltd, Attn: Technical Services,
P.O. Box 881, Morwell Victoria 3840,
Australia; telephone: +61 03 5172 1200; fax:
+61 03 5172 1201; email: aircraft.techpubs@
mahindraaerospace.com. You may review
this referenced service information at the
FAA, Policy and Innovation Division, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on August
31, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018–19889 Filed 9–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0793; Product
Identifier 2018–NM–057–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
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 a report of cracks in the
body station (STA) 303.9 frame web and
doubler at fastener holes common to the
stop fitting at stringer 16 left (S–16L).
This proposed AD would require
repetitive surface high frequency eddy
current (HFEC) inspections for cracking
of the STA 303.9 frame web and doubler
at the stop fitting at S–16L, 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 November 1, 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; phone: 562–797–1717;
internet: https://www.myboeingfleet.
com. You may view this referenced
service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0793.
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SUMMARY:
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Galib Abumeri, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5324; fax: 562–627–
5210; email: galib.abumeri@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–
2018–0793; Product Identifier 2018–
NM–057–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
cracks in the STA 303.9 frame web and
doubler at fastener holes common to the
stop fitting at S–16L. The cracks were
found during accomplishment of Boeing
Service Bulletin 737–53A1188. We have
determined that the existing inspection
programs are not sufficient to find any
crack in the STA 303.9 frame web and
doubler at the stop fitting at S–16L. This
condition, if not addressed, could result
in the inability of a principal structural
element to sustain limit loads and
possible rapid decompression of the
airplane.
Examining the AD Docket
Related Service Information Under 1
CFR Part 51
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0793; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
We reviewed Boeing Requirements
Bulletin 737–53A1375 RB, dated March
12, 2018. The service information
describes procedures for repetitive
surface HFEC inspections for cracking of
the STA 303.9 frame web and doubler
at the stop fitting at S–16L, 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.
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46903
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishment of the actions
identified in Boeing Requirements
Bulletin 737–53A1375 RB, dated March
12, 2018, described previously, except
for any differences identified as
exceptions in the regulatory text of this
proposed AD.
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0793.
Explanation of Applicability
Model 737 airplanes having line
numbers 1 through 291 have a limit of
validity (LOV) of 34,000 total flight
cycles, and the actions proposed in this
NPRM, as specified in Boeing
Requirements Bulletin 737–53A1375
RB, dated March 12, 2018, 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 in
the applicability so that these airplanes
are tracked in the event the LOV is
extended in the future.
Explanation of Requirements Bulletin
The FAA 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 of ADs and AD-related Boeing
service information, a joint process
improvement initiative was worked
between the FAA and Boeing. The
initiative resulted in the development of
a new process in which the service
information more clearly identifies the
actions needed to address the unsafe
condition in the ‘‘Accomplishment
Instructions.’’ The new process results
in a Boeing Requirements Bulletin,
which contains only the actions needed
to address the unsafe condition (i.e.,
only the RC actions).
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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
Costs of Compliance
estimate the following costs to comply
with this proposed AD:
We estimate that this proposed AD
affects 67 airplanes of U.S. registry. We
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
HFEC Inspections ........
13 work-hours × $85 per hour =
$1,105 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.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
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Parts cost
$0
Cost per product
$1,105 per inspection cycle ....
(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
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–
2018–0793; Product Identifier 2018–
NM–057–AD.
(a) Comments Due Date
We must receive comments by November
1, 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 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of
cracks in the body station (STA) 303.9 frame
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Fmt 4702
Cost on U.S. operators
Sfmt 4702
$74,035 per inspection cycle.
web and doubler at fastener holes common
to the stop fitting at stringer 16 left (S–16L).
We are issuing this AD to address cracks in
the STA 303.9 frame web and doubler at the
stop fitting at S–16L, which, if not addressed,
could result in the inability of a principal
structural element to sustain limit loads and
possible rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions for Group 1
For airplanes identified as Group 1 in
Boeing Requirements Bulletin 737–53A1375
RB, dated March 12, 2018: Within 120 days
after the effective date of this AD, inspect the
airplane 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 2
Through 5
Except as specified in paragraph (i) of this
AD: For airplanes identified as Groups 2
through 5 in Boeing Requirements Bulletin
737–53A1375 RB, dated March 12, 2018, at
the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing
Requirements Bulletin 737–53A1375 RB,
dated March 12, 2018, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Requirements Bulletin 737–53A1375 RB,
dated March 12, 2018.
Note 1 to paragraph (h) of this AD:
Guidance for accomplishing the actions
required by this AD can be found in Boeing
Alert Service Bulletin 737–53A1375, dated
March 12, 2018, which is referred to in
Boeing Requirements Bulletin 737–53A1375
RB, dated March 12, 2018.
(i) Exceptions to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Requirements Bulletin 737–
53A1375 RB, dated March 12, 2018, uses the
phrase ‘‘the original issue date of
Requirements Bulletin 737–53A1375 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Requirements Bulletin
737–53A1375 RB, dated March 12, 2018,
specifies contacting Boeing for repair
instructions, this AD requires repair using a
method approved in accordance with the
procedures specified in paragraph (j) of this
AD.
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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
(j) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(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:
9-ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, FAA, to make those findings.
To be approved, the repair method,
modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0795; Product
Identifier 2018–NM–076–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2014–20–
04, which applies to all Airbus SAS
Model A318 series airplanes; Airbus
SAS Model A319 series airplanes;
Airbus SAS Model A320–111, –211,
–212, –214, –231, –232, and –233
airplanes; and Airbus SAS Model A321–
111, –112, –131, –211, –212, –213, –231,
and –232 airplanes. AD 2014–20–04
requires repetitive inspections for
cracking of the four titanium angles
between the belly fairing and the keel
beam side panel, an inspection for
cracking of the open holes if any
cracking is found in the titanium angles,
(k) Related Information
and repair or replacement if necessary.
(1) For more information about this AD,
Since we issued AD 2014–20–04, we
contact Galib Abumeri, Aerospace Engineer,
have determined that additional work is
Airframe Section, FAA, Los Angeles ACO
necessary for certain airplanes. This
Branch, 3960 Paramount Boulevard,
proposed AD would continue to require
Lakewood, CA 90712–4137; phone: 562–627– repetitive inspections for cracking of the
5324; fax: 562–627–5210; email:
four titanium angles between the belly
galib.abumeri@faa.gov.
fairing and the keel beam side panel, an
(2) For service information identified in
inspection for cracking of the open
this AD, contact Boeing Commercial
holes if any cracking is found in the
Airplanes, Attention: Contractual & Data
titanium angles, and repair or
Services (C&DS), 2600 Westminster Blvd.,
replacement if necessary. This proposed
MC 110–SK57, Seal Beach, CA 90740–5600;
AD would also revise the applicability
phone: 562–797–1717; internet: https://
by adding Model A320–216 airplanes.
www.myboeingfleet.com. You may view this
This proposed AD would also require a
referenced service information at the FAA,
detailed inspection for and replacement
Transport Standards Branch, 2200 South
of certain rivets (including a rotating
216th St., Des Moines, WA. For information
probe test for cracks in the open holes),
on the availability of this material at the
and corrective actions if necessary. We
FAA, call 206–231–3195.
are proposing this AD to address the
unsafe condition on these products.
Issued in Des Moines, Washington, on
August 30, 2018.
DATES: We must receive comments on
this proposed AD by November 1, 2018.
Jeffrey E. Duven,
ADDRESSES: You may send comments,
Director, System Oversight Division, Aircraft
using the procedures found in 14 CFR
Certification Service.
11.43 and 11.45, by any of the following
[FR Doc. 2018–19840 Filed 9–14–18; 8:45 am]
methods:
BILLING CODE 4910–13–P
• 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.
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16:40 Sep 14, 2018
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SUMMARY:
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46905
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700
Blagnac Cedex, France; phone: +33 5 61
93 36 96; fax: +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com;
internet: https://www.airbus.com. You
may view this 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.
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–
0795; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
phone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0795; Product Identifier 2018–
NM–076–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 2014–20–04,
Amendment 39–17977 (79 FR 59636,
E:\FR\FM\17SEP1.SGM
17SEP1
]]>Agencies
[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)]
[Proposed Rules]
[Pages 46902-46905]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19840]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0793; Product Identifier 2018-NM-057-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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[[Page 46903]]
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 a report of cracks
in the body station (STA) 303.9 frame web and doubler at fastener holes
common to the stop fitting at stringer 16 left (S-16L). This proposed
AD would require repetitive surface high frequency eddy current (HFEC)
inspections for cracking of the STA 303.9 frame web and doubler at the
stop fitting at S-16L, 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 November 1,
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; phone:
562-797-1717; internet: https://www.myboeingfleet.com. You may view
this referenced service information at the FAA, Transport Standards
Branch, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0793.
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-
0793; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Galib Abumeri, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-
5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0793;
Product Identifier 2018-NM-057-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 cracks in the STA 303.9 frame
web and doubler at fastener holes common to the stop fitting at S-16L.
The cracks were found during accomplishment of Boeing Service Bulletin
737-53A1188. We have determined that the existing inspection programs
are not sufficient to find any crack in the STA 303.9 frame web and
doubler at the stop fitting at S-16L. This condition, if not addressed,
could result in the inability of a principal structural element to
sustain limit loads and possible rapid decompression of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Requirements Bulletin 737-53A1375 RB, dated
March 12, 2018. The service information describes procedures for
repetitive surface HFEC inspections for cracking of the STA 303.9 frame
web and doubler at the stop fitting at S-16L, and applicable on-
condition actions. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishment of the actions
identified in Boeing Requirements Bulletin 737-53A1375 RB, dated March
12, 2018, described previously, except for any differences identified
as exceptions in the regulatory text of this proposed AD.
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0793.
Explanation of Applicability
Model 737 airplanes having line numbers 1 through 291 have a limit
of validity (LOV) of 34,000 total flight cycles, and the actions
proposed in this NPRM, as specified in Boeing Requirements Bulletin
737-53A1375 RB, dated March 12, 2018, 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 in the applicability so that these airplanes
are tracked in the event the LOV is extended in the future.
Explanation of Requirements Bulletin
The FAA 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 of ADs and AD-related
Boeing service information, a joint process improvement initiative was
worked between the FAA and Boeing. The initiative resulted in the
development of a new process in which the service information more
clearly identifies the actions needed to address the unsafe condition
in the ``Accomplishment Instructions.'' The new process results in a
Boeing Requirements Bulletin, which contains only the actions needed to
address the unsafe condition (i.e., only the RC actions).
[[Page 46904]]
Costs of Compliance
We estimate that this proposed AD affects 67 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
HFEC Inspections................. 13 work-hours x $85 $0 $1,105 per $74,035 per
per hour = $1,105 inspection cycle. inspection cycle.
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 detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2018-0793; Product Identifier
2018-NM-057-AD.
(a) Comments Due Date
We must receive comments by November 1, 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 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracks in the body station
(STA) 303.9 frame web and doubler at fastener holes common to the
stop fitting at stringer 16 left (S-16L). We are issuing this AD to
address cracks in the STA 303.9 frame web and doubler at the stop
fitting at S-16L, which, if not addressed, could result in the
inability of a principal structural element to sustain limit loads
and possible rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1
For airplanes identified as Group 1 in Boeing Requirements
Bulletin 737-53A1375 RB, dated March 12, 2018: Within 120 days after
the effective date of this AD, inspect the airplane 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 2 Through 5
Except as specified in paragraph (i) of this AD: For airplanes
identified as Groups 2 through 5 in Boeing Requirements Bulletin
737-53A1375 RB, dated March 12, 2018, at the applicable times
specified in the ``Compliance'' paragraph of Boeing Requirements
Bulletin 737-53A1375 RB, dated March 12, 2018, do all applicable
actions identified in, and in accordance with, the Accomplishment
Instructions of Boeing Requirements Bulletin 737-53A1375 RB, dated
March 12, 2018.
Note 1 to paragraph (h) of this AD: Guidance for accomplishing
the actions required by this AD can be found in Boeing Alert Service
Bulletin 737-53A1375, dated March 12, 2018, which is referred to in
Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018.
(i) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Requirements Bulletin 737-53A1375 RB, dated
March 12, 2018, uses the phrase ``the original issue date of
Requirements Bulletin 737-53A1375 RB,'' this AD requires using ``the
effective date of this AD.''
(2) Where Boeing Requirements Bulletin 737-53A1375 RB, dated
March 12, 2018, specifies contacting Boeing for repair instructions,
this AD requires repair using a method approved in accordance with
the procedures specified in paragraph (j) of this AD.
[[Page 46905]]
(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, 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.
(k) Related Information
(1) For more information about this AD, contact Galib Abumeri,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5324; fax: 562-627-5210; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; phone: 562-797-1717; internet: https://www.myboeingfleet.com.
You may view this referenced service information at the FAA,
Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA,
call 206-231-3195.
Issued in Des Moines, Washington, on August 30, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-19840 Filed 9-14-18; 8:45 am]
BILLING CODE 4910-13-P
