[Federal Register Volume 77, Number 141 (Monday, July 23, 2012)]
[Rules and Regulations]
[Pages 42962-42964]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-16964]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0149; Directorate Identifier 2011-NM-255-AD;
Amendment 39-17117; AD 2012-14-03]
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 777-200 and -300 series airplanes. This AD was
prompted by reports of fatigue cracks in the lap joints, which
initiated at scribe lines that were made during production when maskant
was removed from the affected skin panels during the chemical milling
process. This AD requires repetitive external phased-array ultrasonic
inspections to detect cracks of the affected fuselage skin lap splices
in Sections 41, 43, and 44, as applicable, and repair if necessary. We
are issuing
[[Page 42963]]
this AD to detect and correct such fatigue cracking, which could grow
large and cause sudden decompression and the inability to sustain limit
flight and pressure loads.
DATES: This AD is effective August 27, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of August 27,
2012.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the 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 Document 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: James Sutherland, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6533; fax: 425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM published in the Federal Register on February 22, 2012 (77 FR
10411). That NPRM proposed to require repetitive external phased-array
ultrasonic inspections to detect cracks of the affected fuselage skin
lap splices in Sections 41, 43, and 44, as applicable, and repair if
necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 10411, February 22, 2012) and the FAA's response to each
comment.
Request To Allow Certain Repairs
Boeing requested we add additional text to the end of paragraph
(h)(2) of the NPRM (77 FR 10411, February 22, 2012) stating ``* * *
unless all cracked material has been completely removed and the repair
is a reinforcing repair that has been FAA approved to [Federal Aviation
Regulations] 14 CFR 25.571 and 14 CFR 26.43 (c) or (d).'' Boeing stated
that reinforcing repairs which are FAA approved to 14 CFR 25.571 at the
certification basis for the subject Model 777 airplanes and 14 CFR
26.43(c) or (d) must have been evaluated for damage tolerance, and
would have the damage tolerance inspection requirements in place in
order to maintain the safety of the airplane at the repaired area.
Boeing asserted that the requirement to obtain an alternative method of
compliance (AMOC) approval for such repairs would therefore not be
required to ensure the safety of the repaired airplane.
We disagree. The change proposed by Boeing would only require
compliance for two certain regulations and would not require other
necessary regulatory standards. The requirements defined in the
existing AMOC delegation authority include other FAA regulations and
manufacturer's design considerations beyond those listed on the
airplane type certificate data sheet. We have not changed the final
rule in this regard.
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.
Costs of Compliance
We estimate that this AD affects 46 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 for Group 1 airplanes 126 work-hours x $0 $10,710 per $267,750 per
(25 airplanes). $85 per hour = inspection cycle. inspection cycle.
$10,710 per
inspection cycle.
Inspections for Group 2 airplanes 50 work-hours x $85 0 $4,250 per $89,250 per
(21 airplanes). per hour = $4,250 inspection cycle. inspection cycle.
per inspection
cycle.
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We have received no definitive data that would enable us to
provide cost estimates for the on-condition repair.
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.
[[Page 42964]]
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-14-03 The Boeing Company: Amendment 39-17117; Docket No. FAA-
2012-0149; Directorate Identifier 2011-NM-255-AD.
(a) Effective Date
This AD is effective August 27, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-200 and -300
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 777-53A0043, dated November 9, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of fatigue cracks in the lap
joints, which initiated at scribe lines that were made during
production when maskant was removed from the affected skin panels
during the chemical milling process. We are issuing this AD to
detect and correct such fatigue cracking, which could grow large and
cause sudden decompression and the inability to sustain limit flight
and pressure loads.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections and Repair
Except as provided by paragraph (h)(1) of this AD, at the
applicable time identified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 777-53A0043, dated November 9, 2011:
Do external phased-array ultrasonic inspections to detect cracks of
the affected fuselage skin lap splices in Sections 41, 43, and 44,
as applicable, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 777-53A0043, dated November 9, 2011.
If any crack is found, before further flight, repair in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 777-53A0043, dated November 9, 2011; except as required by
paragraph (h)(2) of this AD. Repeat the inspections of unrepaired
areas thereafter at intervals not to exceed 4,200 flight cycles.
(h) Exception to Service Information
(1) Where Boeing Alert Service Bulletin 777-53A0043, dated
November 9, 2011, specifies a compliance time ``after the original
issue date on this service bulletin,'' this AD requires compliance
within the specified compliance time after the effective date of
this AD.
(2) Where Boeing Alert Service Bulletin 777-53A0043, dated
November 9, 2011, specifies that ``other approved methods'' may be
used to install a repair, this AD requires that the repair be done
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, Seattle 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 the Related Information
section 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.
(j) Related Information
For more information about this AD, contact James Sutherland,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6533; fax: 425-917-6590; email:
[email protected].
(k) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) of the following service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(i) Boeing Alert Service Bulletin 777-53A0043, dated November 9,
2011.
(ii) Reserved.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(3) You may review copies of the 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.
(4) You may also review copies of the 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 June 28, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-16964 Filed 7-20-12; 8:45 am]
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