[Federal Register Volume 84, Number 120 (Friday, June 21, 2019)]
[Proposed Rules]
[Pages 29105-29108]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13057]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0406; Product Identifier 2019-NM-059-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: The FAA proposes to adopt a new airworthiness directive (AD)
for all The Boeing Company Model MD-90-30 airplanes. This proposed AD
was prompted by reports indicating that certain center wing stringers
and skins have been identified to potentially be susceptible to
cracking. This proposed AD would require repetitive eddy current, low
frequency (ETLF) inspections of the left and right side fastener holes
for any crack; repetitive eddy current, high frequency (ETHF)
inspections of the lower skin for any crack; and repair if any crack is
found. The FAA is proposing this AD to address the unsafe condition on
these products.
DATES: The FAA must receive comments on this proposed AD by August 5,
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
[[Page 29106]]
http://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0406.
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-
0406; 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 is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: David Truong, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; fax: 562-627-
5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites 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-2019-0406;
Product Identifier 2019-NM-059-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments, without change, to http://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact the agency receives about this NPRM.
Discussion
The FAA has received reports indicating that the fastener holes
common to stringers (S) S-11 through S-22, and around the external
bracket angle at S-18 and S-19 have been identified to potentially be
susceptible to cracking on the Model MD-90 airplanes. This
determination is based on Model MD-80 airplane service experience. The
Model MD-80 and Model MD-90 wings share the same basic design and have
similar stresses.
Operators of Model MD-80 airplanes have reported finding cracks in
the center wing lower stringers, lower stringer end fittings, and lower
forward and aft skins. The cracks in stringers occur at the inboard end
where they are joined to the airplane centerline by end fittings.
Cracks in the end fittings occur at the outboard end where they attach
to stringers. The wing skin cracks occur underneath a cracked stringer.
The cause of the cracks has been determined to be from fatigue. The
Boeing Company has not received any reports of cracks on Model MD-90
airplanes; however, the similarities with the Model MD-80 wings require
agency action. If not addressed, cracking of the center wing stringers
and skins could result in the inability of the structure to sustain
limit loads, and adversely affect the structural integrity of the
airplane.
Other Relevant Rulemaking
The FAA issued AD 2016-07-28 (81 FR 21253, April 11, 2016) for all
The Boeing Company Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83
(MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. That
AD requires repetitive ETHF inspections for any cracking in the left
and right side center wing lower skin, and corrective actions if
necessary. That AD addresses cracks at S-15, S-16, or S-17, associated
end fittings, and skins in the center wing fuel tank where the
stringers meet the end fittings near Xcw=13 and Xcw=15. Such cracking
could cause structural failure of the wings. Since that AD was issued,
cracking has been found at fastener holes common to stringers S-11
through S-22, and around the external bracket angle at S-18 and S-19.
These areas were not addressed in AD 2016-07-28 or Boeing Alert Service
Bulletin MD80-57A244, dated March 3, 2016, which is the service
information operators are required to follow to complete the actions
required by AD 2016-07-28. Boeing is developing new service information
for Model MD-80 airplanes to address these additional areas where
cracking was found. The FAA will consider further rulemaking to address
the identified unsafe condition for Model MD-80 airplanes once this
service information is approved.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Service Bulletin MD90-57A031, dated
March 19, 2019. This service information describes procedures for
repetitive ETLF inspections of the left and right side fastener holes
for any crack, repetitive ETHF inspections of the lower skin for any
crack, and repair if any crack is found.
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
The FAA is 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 accomplishing the actions specified
in the service information described previously. 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-
0406.
Costs of Compliance
The FAA estimates that this proposed AD affects 43 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection................. 30 work-hours x $85 $0 $2,550 per inspection $109,650 per
per hour = $2,550 cycle. inspection cycle.
per inspection cycle.
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[[Page 29107]]
The FAA has received no definitive data that would enable the
agency 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.
The FAA is 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
The FAA 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) Will not affect intrastate aviation in Alaska, and
(3) 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-2019-0406; Product Identifier
2019-NM-059-AD.
(a) Comments Due Date
The FAA must receive comments by August 5, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model MD-90-30
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports indicating that certain center
wing stringers and skins have been identified to potentially be
susceptible to cracking. The FAA is issuing this AD to address
cracking of the center wing stringers and skins, which could result
in the inability of the structure to sustain limit loads, and
adversely affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified in paragraph (h) of this AD: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin MD90-57A031, dated March 19, 2019, do
all applicable actions identified as ``RC'' (required for
compliance) in, and in accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin MD90-57A031, dated
March 19, 2019.
(h) Exceptions to Service Information Specifications
(1) For purposes of determining compliance with the requirements
of this AD: Where Boeing Alert Service Bulletin MD90-57A031, dated
March 19, 2019, uses the phrase ``the original issue date of this
service bulletin,'' this AD requires using ``the effective date of
this AD.''
(2) Where Boeing Alert Service Bulletin MD90-57A031, dated March
19, 2019, specifies contacting Boeing for repair instructions and
doing the repair: This AD requires doing the repair using a method
approved in accordance with the procedures specified in paragraph
(i) of this AD.
(i) 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 (j)(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 Company 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 specified by paragraph (h) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (i)(4)(i) and
(i)(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.
(j) Related Information
(1) For more information about this AD, contact David Truong,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5224; fax: 562-627-5210; email: [email protected].
[[Page 29108]]
(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 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 June 4, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-13057 Filed 6-20-19; 8:45 am]
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