[Federal Register Volume 84, Number 41 (Friday, March 1, 2019)]
[Proposed Rules]
[Pages 6984-6986]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03468]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0023; Product Identifier 2018-NM-145-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, 737-200, 737-200C, 737-300, 737-400,
and 737-500 series airplanes. This proposed AD was prompted by reports
of cracks in the frame webs below the passenger floor. This proposed AD
would require repetitive inspections for cracking of the fuselage lower
lobe frames, and applicable on-condition actions. This proposed AD
would also provide an optional terminating action for certain
repetitive inspections. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by April 15, 2019.
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 http://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 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 http://www.regulations.gov by searching
for and locating Docket No. FAA-2019-0023.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0023; 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: Lu Lu, Aerospace Engineer, Airframe
Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA
98198; phone and fax: 206-231-3525; 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-2019-0023;
Product Identifier 2018-NM-145-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 http://www.regulations.gov, including any personal information you provide. We
[[Page 6985]]
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of cracks in frame webs below the
passenger floor in Section 46 from Station (STA) 727A to STA 1006
between Stringers S-17L and S-17R. The cracks have been found at the
typical and triangular stringer cutouts, the frame inner chord common
to the channel-cargo floor support, the failsafe chord attachments to
the frame web, the frame integral inboard chord at the voice recorder
support, the open tooling holes, the lower lobe frame splice, the frame
web at stringer clips, the frame web at the water tank shear clip
attachments, and the frame web locations hidden by stringer clips and
intercostals on opposite sides of the frame. Additionally, there was
one report of a frame web severed that did not occur at a fatigue
detail.
Cracks in frame webs, if not addressed, could result in propagation
of cracks until the frame severs. Continued operation of the airplane
with multiple adjacent severed frames, or the combination of a severed
frame adjacent to fuselage skin chem-milled cracks, could result in an
uncontrolled decompression and loss of structural integrity of the
airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1362, dated
September 20, 2018. The service information describes procedures for
repetitive inspections for cracking of the fuselage lower lobe frames,
applicable on-condition actions, and an optional modification of the
tooling holes and insulation attachment holes. On-condition actions
include repetitive inspections for cracking of the lower lobe frames,
repair, and repetitive post-repair inspections for cracking.
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 as ``RC'' (required for compliance) in the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1362, dated
September 20, 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 http://www.regulations.gov by searching for and
locating Docket No. FAA-2019-0023.
Costs of Compliance
We estimate that this proposed AD affects 262 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection................... Up to 56 work-hours x $0 Up to $4,760 per Up to $1,247,120 per
$85 per hour = inspection cycle. inspection cycle.
$4,760 per
inspection cycle.
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Estimated Costs for Optional Actions
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Action Labor cost Parts cost Cost per product
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Modification....................... 1 work-hour x $85 per hour (*) $85 per hole.
= $85 per hole.
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* Parts and materials (e.g., rivets, bolts, collars, primer, adhesive) are supplied by the operator.
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 have 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 that the 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
[[Page 6986]]
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-2019-0023; Product Identifier
2018-NM-145-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by April 15,
2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, 737-
200, 737-200C, 737-300, 737-400, and 737-500 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 reports of cracks in the frame webs
below the passenger floor. We are issuing this AD to address cracks
that could propagate until the frame severs. Continued operation of
the airplane with multiple adjacent severed frames, or the
combination of a severed frame adjacent to fuselage skin chem-milled
cracks, could result in an uncontrolled decompression and loss of
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-53A1362, dated September 20, 2018 (``BASB 737-
53A1362''): Within 120 days after the effective date of this AD,
accomplish actions to correct the unsafe condition (e.g.,
inspections and on-condition actions) using a method approved in
accordance with the procedures specified in paragraph (k) of this
AD.
(h) Required Actions for Group 2 Through 20 Airplanes
For airplanes identified as Group 2 through 20 in BASB 737-
53A1362: Except as specified in paragraph (i) of this AD, at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
BASB 737-53A1362, do all applicable actions identified as ``RC''
(required for compliance) in, and in accordance with, the
Accomplishment Instructions of BASB 737-53A1362.
(i) Optional Terminating Action for Certain Repetitive Inspections
For airplanes identified as Group 2 through 20 in BASB 737-
53A1362, accomplishment of part 13, ``Preventive Modification of the
Frame Web Tooling Hole and Insulation Attachment Hole in the Section
46 Lower Lobe Frame,'' in accordance with the Accomplishment
Instructions of BASB 737-53A1362, terminates the repetitive open
hole high frequency eddy current inspections required by paragraph
(h) of this AD, for the modified tooling hole or insulation
attachment hole location only.
(j) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where BASB 737-53A1362 uses the phrase ``the original
issue date of this service bulletin,'' this AD requires using ``the
effective date of this AD.''
(2) Where BASB 737-53A1362 specifies contacting Boeing for
repair instructions or alternative inspections: This AD requires
doing the repair, or doing the alternative inspections and
applicable on-condition actions, using a method approved in
accordance with the procedures specified in paragraph (k) of this
AD.
(k) 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 (l)(2) of this AD. Information
may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO Branch, FAA, to make those findings. To be
approved, the repair method, modification deviation, or alteration
deviation must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (j)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(l) Related Information
(1) For more information about this AD, contact Lu Lu, Aerospace
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South
216th St., Des Moines, WA 98198; phone and fax: 206-231-3525; email:
[email protected].
(2) For information about AMOCs, contact George Garrido,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch;
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5232; fax: 562-627-5210; email: [email protected].
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. 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 February 21, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-03468 Filed 2-28-19; 8:45 am]
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