[Federal Register Volume 78, Number 241 (Monday, December 16, 2013)]
[Rules and Regulations]
[Pages 76047-76049]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-29051]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0704; Directorate Identifier 2013-NM-074-AD;
Amendment 39-17695; AD 2013-24-18]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 747-200B, -200C, -200F, -300, and 747SR series
airplanes. This AD was prompted by reports of cracks of both lower
chords and web on certain outboard struts. This AD requires repetitive
inspections for cracking of the lower spar chords and web, web lower
spar chord modification, which includes inspections for cracking of the
lower spar chords, and repetitive post modification inspections for
cracking of the lower spar web and chord; and applicable corrective
actions. We are issuing this AD to prevent cracked chords and web on
certain outboard struts, which, if the chord severs, could result in
reduced structural integrity of the diagonal brace load path and of the
strut-to-wing attachment, and
[[Page 76048]]
consequent separation of a strut and engine from the airplane during
flight.
DATES: This AD is effective January 21, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 21,
2014.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington. 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; 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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Docket Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax:
425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to the specified products. The
NPRM published in the Federal Register on August 28, 2013 (78 FR
53078). The NPRM proposed to require repetitive inspections for
cracking of the lower spar chords and web, web lower spar chord
modification, which includes inspections for cracking of the lower spar
chords, and repetitive post modification inspections for cracking of
the lower spar web and chord; and applicable corrective actions.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. Boeing stated that it
supports the NPRM (78 FR 53078, August 28, 2013).
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD as proposed except for minor editorial changes. We have determined
that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 53078, August 28, 2013) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 53078, August 28, 2013).
Costs of Compliance
We estimate that this AD affects 25 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspections.................... 27 work-hours x $85 per $0 $2,295 per $57,375 per
hour = $2,295 per inspection cycle. inspection cycle.
inspection cycle.
Modification................... 11 work-hours x $85 per 95 $1,030............ $25,750.
hour = $935.
Post Modification Inspection... 27 work-hours x $85 per 0 $2,295 per $57,375 per
hour = $2,295 per inspection cycle. inspection cycle.
inspection cycle.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this 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.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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.
[[Page 76049]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2013-24-18 The Boeing Company: Amendment 39-17695; Docket No. FAA-
2013-0704; Directorate Identifier 2013-NM-074-AD.
(a) Effective Date
This AD is effective January 21, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-200B, 747-200C,
747-200F, 747-300, and 747SR series airplanes, certificated in any
category, as identified in Boeing Alert Service Bulletin 747-
54A2237, dated March 14, 2013.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Unsafe Condition
This AD was prompted by reports of cracks of both lower chords
and web on certain outboard struts. We are issuing this AD to
prevent cracked chords and web on certain outboard struts, which, if
the chord severs, could result in reduced structural integrity of
the diagonal brace load path and of the strut-to-wing attachment,
and consequent separation of a strut and engine from the airplane
during flight.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Initial and Repetitive Inspections
Except as required by paragraph (j)(1) of this AD, at the
compliance time specified in table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2237, dated
March 14, 2013: Do a detailed inspection for cracking of the lower
spar chords and web, a high frequency eddy current (HFEC) inspection
for cracking of the lower spar chords, and all applicable repairs
and modifications, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2237, dated
March 14, 2013, except as required by paragraph (j)(2) of this AD.
If no cracking is found, repeat the inspections thereafter at
intervals not to exceed 600 flight cycles, until the actions
specified in paragraph (h) of this AD have been accomplished. Do all
applicable corrective actions before further flight. Accomplishing a
repair and modification, including open-hole HFEC inspections for
cracking and applicable corrective actions required by this
paragraph terminates the actions required by paragraphs (g) and (h)
of this AD for the repaired and modified strut only. The open-hole
HFEC inspection for cracking must be done before the modification.
(h) Inspection and Modification
Except as required by paragraph (j)(1) of this AD, at the
compliance time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-54A2237, dated March 14, 2013: Do
a detailed inspection for cracking of the lower spar chords and web,
an HFEC inspection for cracking of the lower spar chords, a lower
spar chord modification, including open-hole HFEC inspections for
cracking in the chord and all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2237, dated March 14, 2013, except as
required by paragraph (j)(2) of this AD. Do all applicable
corrective actions before further flight. Doing the actions
specified in this paragraph terminates the requirements of paragraph
(g) of this AD for the modified strut only. The open-hole HFEC
inspection for cracking must be done before the modification.
(i) Post Modification Repetitive Inspections
For airplanes on which a modification required by paragraph (g)
or (h) of this AD has been done: At the compliance time specified in
table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-54A2237, dated March 14, 2013, do a detailed inspection
for any cracking of the lower spar web and chord, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2237, dated
March 14, 2013, except as required by paragraph (j)(2) of this AD.
Repeat the inspection thereafter at intervals not to exceed 18
months. Do all applicable corrective actions before further flight.
(j) Exceptions
(1) Where Boeing Alert Service Bulletin 747-54A2237, dated March
14, 2013, specifies a compliance time after the original issue date
on the service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 747-54A2237, dated March
14, 2013, specifies to contact Boeing for appropriate action: Before
further flight, repair the crack 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, Seattle Aircraft Certification Office, 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) 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 required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(l) Related Information
For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6428; fax: 425-917-6590; email:
[email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747-54A2237, dated March 14,
2013.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(4) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability
of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 26, 2013.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-29051 Filed 12-13-13; 8:45 am]
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