[Federal Register Volume 79, Number 138 (Friday, July 18, 2014)]
[Proposed Rules]
[Pages 41943-41945]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-16942]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0450; Directorate Identifier 2013-NM-250-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 MD-90-30 airplanes. This proposed AD was
prompted by reports of cracks emanating from the aft-most barrel nut
holes of the left and right upper rear spar caps of the horizontal
stabilizer. This proposed AD would require repetitive high frequency
eddy current (ETHF) inspections for cracks in the areas around the two
aft-most barrel nut holes of the upper rear spar caps, and corrective
action if necessary; and repetitive ETHF inspections for cracks in the
areas around the two aft-most barrel nut holes of any repaired or
replaced upper rear spar cap, and corrective actions if necessary. We
are proposing this AD to detect and correct such cracks, which could
propagate until the upper rear spar cap severs, and result in failure
of the horizontal stabilizer upper center or aft skin panel and
adversely affect the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by September 2,
2014.
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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0450; 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: George Garrido, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5357;
[[Page 41944]]
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-2014-0450;
Directorate Identifier 2013-NM-250-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 http://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 reports of cracks emanating from the aft-most
barrel nut holes of the left and right upper rear spar caps of the
horizontal stabilizer. One airplane had accumulated 40,144 total flight
hours and 32,253 total landing cycles, while another airplane had
accumulated 58,296 total flight hours and 43,512 total landing cycles.
Investigations have determined that the cracks were caused by fatigue.
In both cases, the cracks originated inside of the barrel nut holes,
and radiated vertically and in the aft direction from the barrel nut
holes. This condition, if not corrected, could result in cracks in the
horizontal stabilizer, which could propagate until it severs the upper
rear spar cap, and result in failure of the horizontal stabilizer upper
center or aft skin panel and adversely affect the structural integrity
of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin MD90-55A017, dated
September 27, 2013. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2014-0450.
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 accomplishing repetitive high
frequency eddy current (ETHF) inspections for cracks of the areas
around the aft-most barrel nut holes of the upper rear spar caps, and
corrective actions if necessary; and repetitive ETHF inspections for
cracks at the two aft-most barrel nut holes of the repaired or replaced
upper rear spar cap, and corrective actions if necessary.
The phrase ``corrective actions'' is used in this proposed AD.
``Corrective actions'' are actions that correct or address any
condition found. Corrective actions in an AD could include, for
example, repairs.
Difference Between This Proposed AD and the Service Information
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin MD90-55A017, dated September 27, 2013, specifies post-repair
inspections of the upper rear spar cap of the aft flange that has been
splice-repaired, which may be used in support of compliance with
Section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation
Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). However,
this NPRM does not propose to require those post-repair inspections.
This difference has been coordinated with Boeing.
Costs of Compliance
We estimate that this proposed AD affects 52 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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Inspection................... 9 work-hours X $85 $1,410.......... $2,175 per Up to $113,100 per
per hour = $765 per inspection inspection cycle.
inspection cycle. cycle.
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We estimate the following costs to do any necessary repairs and
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of
aircraft that might need these repairs and replacements:
On-condition Costs
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Action Labor cost Parts cost Cost per product
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Repair (per side)................ 368 work[dash]hours X $85 Up to $90,129....... Up to $121,409.
per hour = $31,280.
Replacement...................... 368 work[dash]hours X $85 $81,764............. $113,044.
per hour = $31,280.
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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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This
[[Page 41945]]
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-2014-0450; Directorate Identifier
2013 NM-250-AD.
(a) Comments Due Date
We must receive comments by September 2, 2014.
(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 Stabilizers, 55.
(e) Unsafe Condition
This AD was prompted by reports of cracks emanating from the
aft-most barrel nut holes of the left and right upper rear spar caps
of the horizontal stabilizer. We are issuing this AD to detect and
correct cracks in the horizontal stabilizer, which could propagate
until the upper rear spar cap severs, and result in failure of the
horizontal stabilizer upper center or aft skin panel and adversely
affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
At the applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD90-55A017, dated
September 27, 2013, except as provided by paragraph (i) of this AD:
Do a high frequency eddy current inspection (ETHF) for cracks in the
areas around the two aft-most barrel nut holes of the upper rear
spar cap; and do all applicable corrective actions; in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin MD90-55A017, dated September 27, 2013. Thereafter, repeat
the ETHF inspection at the applicable time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD90-55A017,
dated September 27, 2013. Do all corrective actions before further
flight.
(h) Post-Repair/Replacement Actions
For airplanes on which a splice repair or replacement was done
as specified in Boeing Alert Service Bulletin MD90-55A017: At the
applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD90-55A017, dated
September 27, 2013, do an ETHF inspection for cracks at the two aft-
most barrel nut holes of any repaired or replaced upper rear spar
cap, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin MD90-55A017, dated September 27, 2013.
Thereafter, repeat the ETHF inspection at the applicable time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin MD90-55A017, dated September 27, 2013. If any cracking is
found, before further flight, do the repair or replacement, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD90-55A017, dated September 27, 2013.
(i) Post-Repair Inspections
The post-repair inspections of the upper rear spar cap of the
aft flange that has been splice-repaired specified in Table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
MD90-55A017, dated September 27, 2013, are not required by this AD.
Note 1 to paragraph (h) of this AD: The damage tolerance
inspections (post-repair inspections of the upper rear spar cap aft
flange) specified in Table 1 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin MD90-55A017, dated September 27, 2013,
may be used in support of compliance with Section 121.1109(c)(2) or
129.109(b)(2) of the Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin MD90-55A017, dated September 27, 2013, are not required by
this AD.
(j) Exception to the Service Information
Where Boeing Alert Service Bulletin MD90-55A017, dated September
27, 2013, specifies a compliance time ``after the original issue
date of this service bulletin,'' this AD requires compliance within
the specified compliance time after the effective date of this AD.
(k) 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 (l)(1) of this AD.
(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 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. For a repair method to be approved, the repair
must meet the certification basis of the airplane, and 14 CFR
25.571, Amendment 45, and the approval must specifically refer to
this AD.
(l) Related Information
(1) For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
CA 90712-4137; phone: 562-627-5357; fax: 562-627-5210; email:
[email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800 0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; 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 July 11, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-16942 Filed 7-17-14; 8:45 am]
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