Airworthiness Directives; The Boeing Company Airplanes, 15166-15169 [2017-05769]
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15166
Proposed Rules
Federal Register
Vol. 82, No. 57
Monday, March 27, 2017
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0243; Directorate
Identifier 2016–NM–045–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
and –200C series airplanes. This
proposed AD was prompted by a report
of incidents involving fatigue cracking
in transport category airplanes that are
approaching or have exceeded their
design service objective and a structural
reevaluation that was conducted by the
manufacturer. We have determined that
supplemental inspections are required
for timely detection of fatigue cracking
for certain structurally significant items
(SSIs). This proposed AD would require
revising the maintenance or inspection
program, as applicable, to add
supplemental inspections. This
proposed AD would also require
inspections to detect cracks in each SSI,
and repair of any cracked structure. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by May 11, 2017.
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
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SUMMARY:
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W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0243; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: jennifer.tsakoumakis@
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–
2017–0243; Directorate Identifier 2016–
NM–045–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
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closing date and may amend this
proposed AD 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
This proposed AD was prompted by
a report of incidents involving fatigue
cracking in transport category airplanes
that are approaching or have exceeded
their design service objective and a
structural reevaluation that was
conducted by the manufacturer. We
have determined that supplemental
inspections are required for timely
detection of fatigue cracking for certain
SSIs. We are proposing this AD to
ensure the continued structural integrity
of all The Boeing Company Model 737–
100, –200, and –200C series airplanes.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Document D6–
37089, ‘‘Supplemental Structural
Inspection Document for Model 737–
100/200/200C Airplanes,’’ Revision F,
dated November 2015. The service
information identifies SSIs having
fatigue crack growth characteristics
warranting special attention, describes
procedures for inspections to detect
cracks of all structure identified as SSIs,
and provides corrective actions for
cracked SSI structure. 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.
Other Related Rulemaking
On December 30, 1998, we issued AD
98–11–04 R1, Amendment 39–10984 (64
FR 987, January 7, 1999) (‘‘AD 98–11–
04 R1’’), for all Boeing Model 737–100
and –200 series airplanes. AD 98–11–04
R1 requires that the FAA-approved
maintenance inspection program be
revised to include inspections that will
give no less than the required damage
tolerance rating (DTR) for each
structural significant item, and repair of
cracked structure. We issued AD 98–11–
04 R1 to ensure the continued structural
integrity of the entire Boeing Model
737–100 and –200 fleet.
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Federal Register / Vol. 82, No. 57 / Monday, March 27, 2017 / Proposed Rules
On April 8, 2008, we issued AD 2008–
08–23, Amendment 39–15477 (73 FR
21237, April 21, 2008) (‘‘AD 2008–08–
23’’), for all Boeing Model 737–200C
series airplanes. AD 2008–08–23
requires revising the FAA-approved
maintenance inspection program to
include inspections that will give no
less than the required DTR for each SSI,
doing repetitive inspections to detect
cracks of all SSIs, and repairing cracked
structure. We issued AD 2008–08–23 to
maintain the continued structural
integrity of the entire fleet of Model
737–200C series airplanes.
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 these same
type designs.
Proposed AD Requirements
This proposed AD would require
revising the maintenance or inspection
program, as applicable, to include
inspections that will give no less than
the required DTR for certain SSIs, and
repairing any cracked structure. This
proposed AD would also require initial
and repetitive inspections to detect
cracks of all structure identified in
Boeing Document D6–37089,
‘‘Supplemental Structural Inspection
Document for Model 737–100/200/200C
Airplanes,’’ Revision F, dated November
2015, and repair if necessary.
Accomplishing the actions required
by paragraphs (g) and (h) of this
proposed AD would terminate all
requirements of AD 98–11–04 R1 and
AD 2008–08–23.
Costs of Compliance
We estimate that this proposed AD
affects 84 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Revision of maintenance or inspection program.
1 work-hour × $85 per hour = $85 .................
We have not specified cost estimates
for the inspections and repair specified
in this proposed AD. Compliance with
this proposed AD constitutes a method
of compliance with the FAA aging
airplane safety final rule (AASFR) (70
FR 5518, February 2, 2005) for certain
baseline structure of Model 737–100,
–200, and –200C series airplanes. The
AASFR requires certain operators to
Cost per
product
Parts cost
incorporate damage tolerance
inspections into their maintenance
programs. These requirements are
described in 14 CFR 121.1109(c)(1) and
14 CFR 129.109(b)(1). Accomplishment
of the actions specified in this proposed
AD will meet the requirements of these
regulations for certain baseline
structure. The costs for accomplishing
the inspection portion of this proposed
$0
Cost on U.S.
operators
$85
$7,140
AD were accounted for in the regulatory
evaluation of the AASFR.
We estimate the following costs to do
any necessary reporting that would be
required based on the results of the
inspections specified in the proposed
revision of the maintenance or
inspection program. We have no way of
determining the number of aircraft that
might need this action:
ON-CONDITION COSTS
Labor cost
Reporting .........................................
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Action
1 work-hour × $85 per hour = $85 ............................................................
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to 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 current valid
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
reporting associated with this proposed
AD is mandatory. Comments concerning
the accuracy of this burden and
suggestions for reducing the burden
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should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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
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Cost per
product
Parts cost
$0
$85
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.
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,
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Federal Register / Vol. 82, No. 57 / Monday, March 27, 2017 / Proposed Rules
(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–
2017–0243; Directorate Identifier 2016–
NM–045–AD.
(a) Comments Due Date
We must receive comments by May 11,
2017.
(b) Affected ADs
This AD affects AD 98–11–04 R1,
Amendment 39–10984 (64 FR 987, January 7,
1999) (‘‘AD 98–11–04 R1’’); and AD 2008–
08–23, Amendment 39–15477 (73 FR 21237,
April 21, 2008) (‘‘AD 2008–08–23’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, and –200C
series airplanes, certificated in any category.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage; 54, Nacelles/
Pylons; 55, Stabilizers; 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of
incidents involving fatigue cracking in
transport category airplanes that are
approaching or have exceeded their design
service objective and a structural
reevaluation that was conducted by the
manufacturer that identified additional
structural elements that qualify as structural
significant items (SSIs). We are issuing this
AD to ensure the continued structural
integrity of all The Boeing Company Model
737–100, –200, and –200C series airplanes.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of the Maintenance or
Inspection Program for All Airplanes
Prior to reaching the compliance time
specified in paragraph (h)(1), (h)(2), or (h)(3)
of this AD, as applicable: Incorporate a
revision into the maintenance or inspection
program, as applicable, that provides no less
than the required damage tolerance rating
(DTR) for each SSI listed in Boeing Document
D6–37089, ‘‘Supplemental Structural
Inspection Document for Model 737–100/
200/200C Airplanes,’’ Revision F, dated
November 2015 (‘‘Document D6–37089,
Revision F’’). The required DTR value for
each SSI is listed in Document D6–37089,
Revision F. The revision to the maintenance
or inspection program must include, and
must be implemented in accordance with,
the procedures in Section 5.0, ‘‘Damage
Tolerance Rating (DTR) System Application,’’
and Section 6.0, ‘‘SSI Discrepancy
Reporting’’ of Document D6–37089, Revision
F. Accomplishing the revision required by
this paragraph terminates the actions
required by paragraphs (a) and (b) of AD 98–
11–04 R1, and paragraph (g) of AD 2008–08–
23.
(h) Initial and Repetitive Inspections
Perform an inspection in accordance with
Document D6–37089, Revision F, to detect
cracks of all structure identified in Document
D6–37089, Revision F, at the time specified
in paragraph (h)(1), (h)(2), or (h)(3) of this
AD, as applicable. Once the initial inspection
has been performed, repeat the inspection
thereafter at the intervals specified in
Document D6–37089, Revision F.
Accomplishing an initial inspection required
by this paragraph terminates the
corresponding inspection required by
paragraph (c) of AD 98–11–04 R1 and
paragraph (h) of AD 2008–08–23.
(1) For SSIs on Model 737–100 and –200
series airplanes: Before the accumulation of
66,000 total flight cycles, or within 12
months after the effective date of this AD,
whichever occurs later.
(2) For SSIs on Model 737–200C series
airplanes not affected by cargo configuration:
Before the accumulation of 66,000 total flight
cycles, or within 12 months after the effective
date of this AD, whichever occurs later.
(3) For SSIs on Model 737–200C series
airplanes affected by cargo configuration:
Before the accumulation of 46,000 total flight
cycles, or within 12 months after the effective
date of this AD, whichever occurs later.
(i) Repair for Cracking Found During
Accomplishment of the Actions Specified in
Paragraph (h) of This AD
If any cracked SSI structure is found
during any inspection required by paragraph
(h) of this AD, repair before further flight
using a method approved in accordance with
the procedures specified in paragraph (l) of
this AD. Within 18 months after repair,
incorporate a revision into the maintenance
or inspection program, as applicable, to
include a damage-tolerance-based alternative
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inspection program for the repaired structure.
Thereafter, inspect the affected structure in
accordance with the alternative program. The
inspection method and compliance times
(i.e., threshold and repetitive intervals) of the
alternative program must be approved in
accordance with the procedures specified in
paragraph (l) of this AD.
(j) Terminating Action for Other ADs
Accomplishing the revision required by
paragraph (g) of this AD and all initial
inspections required by paragraph (h) of this
AD terminates all requirements of AD 98–11–
04 R1 and AD 2008–08–23.
(k) Paperwork Reduction Act Burden
Statement
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 current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-AMOCRequests@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, 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) AMOCs approved for AD 98–11–04 R1
and AD 2008–08–23 are approved as AMOCs
for the corresponding provisions of
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Federal Register / Vol. 82, No. 57 / Monday, March 27, 2017 / Proposed Rules
paragraphs (g) and (h) of this AD for the SSIs
identified in the AMOC.
(m) Related Information
(1) For more information about this AD,
contact Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–5210;
email: jennifer.tsakoumakis@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on March
16, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–05769 Filed 3–24–17; 8:45 am]
BILLING CODE 4910–13–P
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0244; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: jennifer.tsakoumakis@
faa.gov.
14 CFR Part 39
[Docket No. FAA–2017–0244; Directorate
Identifier 2016–NM–044–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 737–300, –400,
and –500 series airplanes. This
proposed AD was prompted by a
determination that supplemental
inspections are required for timely
detection of fatigue cracking for certain
structural significant item (SSIs). This
proposed AD would require revising the
maintenance or inspection program, as
applicable, to add supplemental
inspections. This proposed AD would
also require inspections to detect cracks
in each SSI, and repair of any cracked
structure. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by May 11, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
pmangrum on DSK3GDR082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
12:23 Mar 24, 2017
Jkt 241001
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–
2017–0244; Directorate Identifier 2016–
NM–044–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
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Sfmt 4702
15169
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 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
On April 8, 2008, we issued AD 2008–
09–13, Amendment 39–15494 (73 FR
24164, May 2, 2008) (‘‘AD 2008–09–
13’’), for all Model 737–300, –400, and
–500 series airplanes. AD 2008–09–13
requires revising the FAA-approved
maintenance inspection program to
include inspections that will give no
less than the required damage tolerance
rating (DTR) for each SSI, doing
repetitive inspections to detect cracks of
all SSIs, and repairing cracked structure.
AD 2008–09–13 resulted from a report
of incidents involving fatigue cracking
in transport category airplanes that are
approaching or have exceeded their
design service objective. We issued AD
2008–09–13 to ensure the continued
structural integrity of all Model 737–
300, –400, and –500 series airplanes.
Actions Since AD 2008–09–13 Was
Issued
Since we issued AD 2008–09–13, a
structural reevaluation was conducted
by the manufacturer. As a result, we
have determined that supplemental
inspections are required for timely
detection of fatigue cracking for certain
SSIs.
Related Service Information Under
1 CFR Part 51
We reviewed Boeing Document D6–
82669, ‘‘Supplemental Structural
Inspection Document, Models 737–300/
400/500 Airplanes,’’ Revision October
2015. The service information identifies
SSIs having fatigue crack growth
characteristics warranting special
attention, describes procedures for
inspections to detect cracks of all
structure identified as SSIs, and
provides corrective actions for cracked
SSI structure. 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
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]]>Agencies
[Federal Register Volume 82, Number 57 (Monday, March 27, 2017)]
[Proposed Rules]
[Pages 15166-15169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05769]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 82, No. 57 / Monday, March 27, 2017 /
Proposed Rules
[[Page 15166]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0243; Directorate Identifier 2016-NM-045-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 737-100, -200, and -200C series airplanes.
This proposed AD was prompted by a report of incidents involving
fatigue cracking in transport category airplanes that are approaching
or have exceeded their design service objective and a structural
reevaluation that was conducted by the manufacturer. We have determined
that supplemental inspections are required for timely detection of
fatigue cracking for certain structurally significant items (SSIs).
This proposed AD would require revising the maintenance or inspection
program, as applicable, to add supplemental inspections. This proposed
AD would also require inspections to detect cracks in each SSI, and
repair of any cracked structure. We are proposing this AD to address
the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by May 11, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0243; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@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-2017-0243;
Directorate Identifier 2016-NM-045-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 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
This proposed AD was prompted by a report of incidents involving
fatigue cracking in transport category airplanes that are approaching
or have exceeded their design service objective and a structural
reevaluation that was conducted by the manufacturer. We have determined
that supplemental inspections are required for timely detection of
fatigue cracking for certain SSIs. We are proposing this AD to ensure
the continued structural integrity of all The Boeing Company Model 737-
100, -200, and -200C series airplanes.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Document D6-37089, ``Supplemental Structural
Inspection Document for Model 737-100/200/200C Airplanes,'' Revision F,
dated November 2015. The service information identifies SSIs having
fatigue crack growth characteristics warranting special attention,
describes procedures for inspections to detect cracks of all structure
identified as SSIs, and provides corrective actions for cracked SSI
structure. 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.
Other Related Rulemaking
On December 30, 1998, we issued AD 98-11-04 R1, Amendment 39-10984
(64 FR 987, January 7, 1999) (``AD 98-11-04 R1''), for all Boeing Model
737-100 and -200 series airplanes. AD 98-11-04 R1 requires that the
FAA-approved maintenance inspection program be revised to include
inspections that will give no less than the required damage tolerance
rating (DTR) for each structural significant item, and repair of
cracked structure. We issued AD 98-11-04 R1 to ensure the continued
structural integrity of the entire Boeing Model 737-100 and -200 fleet.
[[Page 15167]]
On April 8, 2008, we issued AD 2008-08-23, Amendment 39-15477 (73
FR 21237, April 21, 2008) (``AD 2008-08-23''), for all Boeing Model
737-200C series airplanes. AD 2008-08-23 requires revising the FAA-
approved maintenance inspection program to include inspections that
will give no less than the required DTR for each SSI, doing repetitive
inspections to detect cracks of all SSIs, and repairing cracked
structure. We issued AD 2008-08-23 to maintain the continued structural
integrity of the entire fleet of Model 737-200C series airplanes.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would require revising the maintenance or
inspection program, as applicable, to include inspections that will
give no less than the required DTR for certain SSIs, and repairing any
cracked structure. This proposed AD would also require initial and
repetitive inspections to detect cracks of all structure identified in
Boeing Document D6-37089, ``Supplemental Structural Inspection Document
for Model 737-100/200/200C Airplanes,'' Revision F, dated November
2015, and repair if necessary.
Accomplishing the actions required by paragraphs (g) and (h) of
this proposed AD would terminate all requirements of AD 98-11-04 R1 and
AD 2008-08-23.
Costs of Compliance
We estimate that this proposed AD affects 84 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revision of maintenance or inspection 1 work-hour x $85 per $0 $85 $7,140
program. hour = $85.
----------------------------------------------------------------------------------------------------------------
We have not specified cost estimates for the inspections and repair
specified in this proposed AD. Compliance with this proposed AD
constitutes a method of compliance with the FAA aging airplane safety
final rule (AASFR) (70 FR 5518, February 2, 2005) for certain baseline
structure of Model 737-100, -200, and -200C series airplanes. The AASFR
requires certain operators to incorporate damage tolerance inspections
into their maintenance programs. These requirements are described in 14
CFR 121.1109(c)(1) and 14 CFR 129.109(b)(1). Accomplishment of the
actions specified in this proposed AD will meet the requirements of
these regulations for certain baseline structure. The costs for
accomplishing the inspection portion of this proposed AD were accounted
for in the regulatory evaluation of the AASFR.
We estimate the following costs to do any necessary reporting that
would be required based on the results of the inspections specified in
the proposed revision of the maintenance or inspection program. We have
no way of determining the number of aircraft that might need this
action:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Reporting.................................. 1 work-hour x $85 per hour = $85... $0 $85
----------------------------------------------------------------------------------------------------------------
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to the FAA at 800 Independence Ave. SW., Washington, DC
20591, ATTN: Information Collection Clearance Officer, AES-200.
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.
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,
[[Page 15168]]
(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-2017-0243; Directorate Identifier
2016-NM-045-AD.
(a) Comments Due Date
We must receive comments by May 11, 2017.
(b) Affected ADs
This AD affects AD 98-11-04 R1, Amendment 39-10984 (64 FR 987,
January 7, 1999) (``AD 98-11-04 R1''); and AD 2008-08-23, Amendment
39-15477 (73 FR 21237, April 21, 2008) (``AD 2008-08-23'').
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200,
and -200C series airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage;
54, Nacelles/Pylons; 55, Stabilizers; 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of incidents involving fatigue
cracking in transport category airplanes that are approaching or
have exceeded their design service objective and a structural
reevaluation that was conducted by the manufacturer that identified
additional structural elements that qualify as structural
significant items (SSIs). We are issuing this AD to ensure the
continued structural integrity of all The Boeing Company Model 737-
100, -200, and -200C series airplanes.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revision of the Maintenance or Inspection Program for All Airplanes
Prior to reaching the compliance time specified in paragraph
(h)(1), (h)(2), or (h)(3) of this AD, as applicable: Incorporate a
revision into the maintenance or inspection program, as applicable,
that provides no less than the required damage tolerance rating
(DTR) for each SSI listed in Boeing Document D6-37089,
``Supplemental Structural Inspection Document for Model 737-100/200/
200C Airplanes,'' Revision F, dated November 2015 (``Document D6-
37089, Revision F''). The required DTR value for each SSI is listed
in Document D6-37089, Revision F. The revision to the maintenance or
inspection program must include, and must be implemented in
accordance with, the procedures in Section 5.0, ``Damage Tolerance
Rating (DTR) System Application,'' and Section 6.0, ``SSI
Discrepancy Reporting'' of Document D6-37089, Revision F.
Accomplishing the revision required by this paragraph terminates the
actions required by paragraphs (a) and (b) of AD 98-11-04 R1, and
paragraph (g) of AD 2008-08-23.
(h) Initial and Repetitive Inspections
Perform an inspection in accordance with Document D6-37089,
Revision F, to detect cracks of all structure identified in Document
D6-37089, Revision F, at the time specified in paragraph (h)(1),
(h)(2), or (h)(3) of this AD, as applicable. Once the initial
inspection has been performed, repeat the inspection thereafter at
the intervals specified in Document D6-37089, Revision F.
Accomplishing an initial inspection required by this paragraph
terminates the corresponding inspection required by paragraph (c) of
AD 98-11-04 R1 and paragraph (h) of AD 2008-08-23.
(1) For SSIs on Model 737-100 and -200 series airplanes: Before
the accumulation of 66,000 total flight cycles, or within 12 months
after the effective date of this AD, whichever occurs later.
(2) For SSIs on Model 737-200C series airplanes not affected by
cargo configuration: Before the accumulation of 66,000 total flight
cycles, or within 12 months after the effective date of this AD,
whichever occurs later.
(3) For SSIs on Model 737-200C series airplanes affected by
cargo configuration: Before the accumulation of 46,000 total flight
cycles, or within 12 months after the effective date of this AD,
whichever occurs later.
(i) Repair for Cracking Found During Accomplishment of the Actions
Specified in Paragraph (h) of This AD
If any cracked SSI structure is found during any inspection
required by paragraph (h) of this AD, repair before further flight
using a method approved in accordance with the procedures specified
in paragraph (l) of this AD. Within 18 months after repair,
incorporate a revision into the maintenance or inspection program,
as applicable, to include a damage-tolerance-based alternative
inspection program for the repaired structure. Thereafter, inspect
the affected structure in accordance with the alternative program.
The inspection method and compliance times (i.e., threshold and
repetitive intervals) of the alternative program must be approved in
accordance with the procedures specified in paragraph (l) of this
AD.
(j) Terminating Action for Other ADs
Accomplishing the revision required by paragraph (g) of this AD
and all initial inspections required by paragraph (h) of this AD
terminates all requirements of AD 98-11-04 R1 and AD 2008-08-23.
(k) Paperwork Reduction Act Burden Statement
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 current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), 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 ACO, send it to the
attention of the person identified in paragraph (m)(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, 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) AMOCs approved for AD 98-11-04 R1 and AD 2008-08-23 are
approved as AMOCs for the corresponding provisions of
[[Page 15169]]
paragraphs (g) and (h) of this AD for the SSIs identified in the
AMOC.
(m) Related Information
(1) For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on March 16, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-05769 Filed 3-24-17; 8:45 am]
BILLING CODE 4910-13-P
