[Federal Register Volume 77, Number 117 (Monday, June 18, 2012)]
[Rules and Regulations]
[Pages 36143-36146]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14542]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1415; Directorate Identifier 2011-NM-145-AD;
Amendment 39-17089; AD 2012-12-09]
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 all The
Boeing Company Model 717-200 airplanes. This AD was prompted by reports
of cracks found on the center section ribs of the horizontal
stabilizers. This AD requires repetitive inspections for cracking of
the aft face of the left and right rib hinge bearing lugs of the center
[[Page 36144]]
section of the horizontal stabilizer; and crack measurement, repairs,
post-repair repetitive inspections, and installation of a new center
section rib if necessary. We are issuing this AD to detect and correct
cracking in the left and right bearing lugs of the rib hinge spreading
at the same time, which could result in failure of both hinge bearing
lugs. Failure of the hinge bearing lugs could result in the inability
of the horizontal stabilizer to sustain flight loads and thereby reduce
the controllability of the airplane.
DATES: This AD is effective July 23, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of July 23,
2012.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; phone: 206-544-5000, extension 2; fax: 206-766-5683; 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: George Garrido, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712-
4137; phone: 562-627-5357; fax: 562-627-5210; email:
George.Garrido@faa.gov.
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 January 19, 2012 (77 FR
2664). That NPRM proposed to require repetitive eddy current high
frequency (ETHF) inspections for cracks on the aft face on the left and
right rib hinge bearing lugs of the center section of the horizontal
stabilizer; and crack measurement, repairs, post-repair repetitive
inspections, and installation of a new center section rib 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 2664, January 19, 2012), and the FAA's response to each comment.
Support for NPRM (77 FR 2664, January 19, 2012)
Boeing stated it supports the NPRM (77 FR 2664, January 19, 2012).
Request To Decrease Inspection Interval
Kristianna Sciarraa requested we change the repetitive inspection
interval in the NPRM (77 FR 2664, January 19, 2012) from every 10,500
flight cycles to every 18 months when no cracking is found after the
initial inspection. The commenter stated that more frequent inspections
would increase early detection of fatigue cracking and would be
workable with operator schedules. The commenter also stated that the
costs associated with the decreased inspection interval are minimal
when compared to the cost to an operator if an accident occurs due to
fatigue cracking.
We disagree with changing the repetitive inspection interval
because the repetitive inspection interval is based on damage tolerance
(crack growth) analysis of the hinge bearing lug of the horizontal
stabilizer center section. The analysis accounts for the loading and
stress in the specific location and considers worse case crack growth
from detectable to critical size and allows for multiple opportunities
to detect a crack. We have not changed the final rule in this regard.
Request To Require Reporting
Kristianna Sciarraa requested we include mandatory reporting of
inspection results in the NPRM (77 FR 2664, January 19, 2012). The
commenter stated that Boeing Alert Service Bulletin 717-55A0011, dated
May 17, 2011, specifies reporting and that providing the manufacturer
with such information would foster an important exchange of information
with an end goal of creating safe and reliable aircraft to ensure
passenger and operator protection.
We disagree with requiring mandatory reporting of inspection
results. Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011,
already specifies submitting information to the manufacturer. This
final rule does not include that requirement because we understand the
unsafe condition, and we do not want to add an additional burden on the
operators. We require reporting of inspection reports if the unsafe
condition is a result of quality control issues or if we are trying to
understand the scope of the unsafe condition. We have not changed the
final rule in this regard.
Conclusion
We reviewed the relevant data, considered the comments 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 129 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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ETHF Inspection................. 6 work-hours x $85 $0 $510 per inspection $65,790 per
per hour = $510 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 labor costs specified in
this AD. The estimated parts cost for a replacement rib is $16,387.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 36145]]
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-12-09 The Boeing Company: Amendment 39-17089; Docket No. FAA-
2011-1415; Directorate Identifier 2011-NM-145-AD.
(a) Effective Date
This AD is effective July 23, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 717-200
airplanes, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 5510, Horizontal Stabilizer Structure.
(e) Unsafe Condition
This AD was prompted by reports of cracks found on the center
section ribs of the horizontal stabilizers. We are issuing this AD
to detect and correct cracking in the left and right bearing lugs of
the rib hinge spreading at the same time, which could result in
failure of both hinge bearing lugs. Failure of the hinge bearing
lugs could result in the inability of the horizontal stabilizer to
sustain flight loads and thereby reduce the controllability of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Eddy Current High Frequency (ETHF) Inspections
Before the accumulation of 35,000 total flight cycles, or within
8,275 flight cycles after the effective date of this AD, whichever
occurs later: Do an ETHF inspection for cracks of the aft face on
the left and right rib hinge bearing lugs of the center section of
the horizontal stabilizer, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May
17, 2011. If no crack is found, repeat the inspection thereafter at
intervals not to exceed 10,500 flight cycles.
(h) Crack Measurement
If any crack is found during any inspection required by
paragraph (g) of this AD: Before further flight, measure the length
of the crack, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011.
(i) Blend Out Repair, ETHF Inspections, and Corrective Action for
Certain Crack Lengths
For any crack that meets ``Condition 2A'' of Table 1 of 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 717-55A0011, dated
May 17, 2011: Do the actions in paragraphs (i)(1) and (i)(2) of this
AD.
(1) Before further flight, do a blend out repair, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 717-55A0011, dated May 17, 2011.
(2) Within 14,200 flight cycles after accomplishing the blend
out repair required by paragraph (i)(1) of this AD: Do an ETHF
inspection of the blend out repair area for cracking, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 717-55A0011, dated May 17, 2011. If no cracking is found,
repeat the inspection thereafter at intervals not to exceed 5,400
flight cycles.
(i) If any crack is found during the ETHF inspection required by
paragraph (i)(2) of this AD: Before further flight, remove the
cracked center section rib of the horizontal stabilizer and install
a new center section rib, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 717-55A0011, dated May
17, 2011.
(ii) Within 35,000 flight cycles after the installation of the
new center section rib, do the actions in paragraph (g) of this AD.
(j) Corrective Action for Certain Crack Lengths
For any crack that meets ``Condition 2D'' of Table 1 of 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 717-55A0011, dated
May 17, 2011: Before further flight, remove the cracked center
section rib of the horizontal stabilizer and install a new center
section rib, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 717-55A0011, dated May 17, 2011.
Within 35,000 flight cycles after the installation of the new rib,
do the actions in paragraph (g) of this AD.
(k) No Reporting Requirement
Although Boeing Alert Service Bulletin 717-55A0011, dated May
17, 2011, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
(l) 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 the Related Information
section 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 the approval
must specifically refer to this AD.
(m) Related Information
For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office (ACO), 3960 Paramount Boulevard,
Lakewood,
[[Page 36146]]
California 90712-4137; phone: 562-627-5357; fax: 562-627-5210;
email: George.Garrido@faa.gov.
(n) 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 717-55A0011, dated May 17,
2011.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; phone: 206-544-5000, extension 2; fax: 206-766-5683; 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 7, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-14542 Filed 6-15-12; 8:45 am]
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