Airworthiness Directives; The Boeing Company Airplanes, 15651-15654 [2014-05415]
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
Committee prior to Debenture closing.
Only the Board or Executive Committee,
if authorized by the Board, may provide
credit approval for loans greater than
$2,000,000.
(15) All members of the Board of
Directors must annually certify in
writing that they have read and
understand this section, and copies of
the certification must be included in the
Annual Report to SBA.
(e) The Board of Directors shall
maintain Directors’ and Officers’
Liability and Errors and Omissions
insurance in amounts established by
SBA that are based on the size of the
CDC’s portfolio and other relevant
factors.
■ 8. Amend § 120.830 by revising
paragraph (a) to read as follows:
§ 120.830
Reports a CDC must submit.
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(a) An Annual Report within one
hundred-eighty days after the end of the
CDC’s fiscal year (to include Federal tax
returns for that year). A CDC that is
certified by SBA within 6 months of the
CDC’s fiscal year-end is not required to
submit an Annual Report for that year.
The Annual Report must include, but is
not limited to, the following:
(1) Audited or Reviewed Financial
Statements as required in § 120.826(c)
and (d) for the CDC and any affiliates or
subsidiaries of the CDC.
(i) Audited financial statements must,
at a minimum, include the following:
(A) Audited balance sheet;
(B) Audited statement of income (or
receipts) and expenses;
(C) Audited statement of source and
application of funds;
(D) Such footnotes as are necessary to
an understanding of the financial
statements;
(E) Auditor’s letter to management on
internal control weaknesses; and
(F) The auditor’s report; and
(ii) Reviewed financial statements
must, at a minimum, include the
following:
(A) Balance sheet;
(B) Statement of income (or receipts)
and expenses;
(C) Statement of source and
application of funds;
(D) Such footnotes as are necessary to
an understanding of the financial
statements;
(E) The accountant’s review report;
and
(2) Report on compensation: CDCs are
required to provide detailed information
on total compensation (including salary,
bonuses and expenses) paid within the
CDC’s most recent tax year for current
and former officers and directors, and
for current and former employees and
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(2) The Third Party Lender applies
any proceeds received as a result of the
Additional Collateral to the balance
outstanding on the Third Party Loan
prior to the application of proceeds from
the disposition of the Project Property to
the Third Party Loan.
independent contractors with total
compensation of more than $100,000
during that period.
(3) Certification of members of the
Board of Directors. Written annual
certification by each Board member that
he or she has read and understands the
requirements set forth in § 120.823.
(4) Report on investment in economic
development. Written report on
investments in economic development
in each State in which the CDC has an
outstanding 504 loan.
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■ 9. Amend § 120.835 by revising
paragraph (c) to read as follows:
§ 120.925
§ 120.835 Application to expand an Area of
Operations.
DEPARTMENT OF TRANSPORTATION
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Federal Aviation Administration
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(c) A CDC seeking to become a MultiState CDC must apply to the SBA
District Office that services the area
within each State where the CDC
intends to locate its principal office for
that State. A CDC may apply to be a
Multi-State CDC only if the State the
CDC seeks to expand into is contiguous
to the State of the CDC’s incorporation
and the CDC establishes a loan
committee in that State meeting the
requirements of § 120.823.
§ 120.852
[Removed and Reserved]
10. Remove and reserve § 120.852.
11. Amend § 120.882 by revising
paragraph (a) to read as follows:
■
■
§ 120.882
loans.
Eligible Project costs for 504
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(a) Costs directly attributable to the
Project including expenditures incurred
by the Borrower (with its own funds or
from a loan) to acquire land used in the
Project, or for any other expense directly
attributable to the Project, prior to
applying to SBA for the 504 loan;
*
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■ 12. Amend § 120.920 by revising
paragraph (b) to read as follows:
§ 120.920 Required participation by Third
Party Lender.
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(b) Third party loan collateral. The
504 loan is usually collateralized by a
second lien on Project Property. The
Third Party Lender may obtain
additional collateral or other security for
the Third Party Loan (‘‘Additional
Collateral’’) only if in the event of
liquidation and unless otherwise
approved in writing by SBA:
(1) The Third Party Lender liquidates
or otherwise exhausts all reasonable
avenues of collection with respect to the
Additional Collateral no later than the
disposition of the Project Property, and
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■
[Removed and Reserved]
13. Remove and reserve § 120.925.
Marianne O’Brien Markowitz,
Acting Administrator.
[FR Doc. 2014–06237 Filed 3–20–14; 8:45 am]
BILLING CODE 8025–01–P
14 CFR Part 39
[Docket No. FAA–2013–0796; Directorate
Identifier 2013–NM–111–AD; Amendment
39–17802; AD 2014–05–30]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–07–
07 for all The Boeing Company Model
737–600, –700, –700C, –800, –900, and
–900ER series airplanes. AD 2013–07–
07 required inspecting to determine the
part number of the attach pins of the
horizontal stabilizer rear spar, and
replacing certain attach pins. This new
AD clarifies the parts installation
limitation and prohibition, and adds a
new requirement for certain airplanes
on which certain attach pins were
installed. This AD was prompted by
inquiries from affected operators
regarding the parts installation
limitation and prohibition, and reinstallation of certain attach pins that
were removed for inspection. We are
issuing this AD to prevent premature
failure of the attach pins, which could
cause reduced structural integrity of the
horizontal stabilizer to fuselage
attachment, resulting in loss of control
of the airplane.
DATES: This AD is effective April 25,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 20, 2013 (78 FR 22182, April
15, 2013).
ADDRESSES: For service information
identified in this AD, contact Boeing
SUMMARY:
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
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, 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0796; 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:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6440; fax:
425–917–6590; email: Nancy.Marsh@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013–07–07,
Amendment 39–17411 (78 FR 22182,
April 15, 2013). AD 2013–07–07 applied
to all The Boeing Company Model 737–
600, –700, –700C, –800, –900, and
–900ER series airplanes. The NPRM
published in the Federal Register on
September 25, 2013 (78 FR 58982). The
NPRM was prompted by inquiries from
affected operators regarding the parts
installation limitation and prohibition,
and re-installation of certain attach pins
that were removed for inspection. The
NPRM proposed to continue to require
inspecting to determine the part number
of the attach pins of the horizontal
stabilizer rear spar, and replacing
certain attach pins. The NPRM also
proposed to clarify the parts installation
limitation and prohibition, and add a
new requirement for certain airplanes
on which certain attach pins were
installed. We are issuing this AD to
prevent premature failure of the attach
pins, which could cause reduced
structural integrity of the horizontal
stabilizer to fuselage attachment,
resulting in loss of control of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the proposal (78 FR 58982,
September 25, 2013) and the FAA’s
response to each comment.
Clarification of Effect of Winglet
Installation
Aviation Partners Boeing stated that
the installation of winglets per
Supplemental Type Certificate (STC)
ST00830SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/408E012E008616A78
62578880060456C?Open
Document&Highlight=st00830se) does
not affect the accomplishment of the
manufacturer’s service instructions.
We concur. Paragraph (c)(2) in AD
2013–07–07, Amendment 39–17411 (78
FR 22182, April 15, 2013), has been
restated in this final rule and specifies
that STC ST00830SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/408E012E008616A78625
78880060456C?Open
Document&Highlight=st00830se) does
not affect the ability to accomplish the
actions required by this final rule.
Therefore, for airplanes on which STC
ST00830SE is installed, a ‘‘change in
product’’ alternative method of
compliance (AMOC) approval request is
not necessary to comply with the
requirements of section 39.17 of the
Federal Aviation Regulations (14 CFR
39.17).
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this 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
58982, September 25, 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 58982,
September 25, 2013).
Costs of Compliance
We estimate that this AD affects 1,050
airplanes of U.S. registry. The new
requirements add no significant
economic burden over that specified in
AD 2013–07–07, Amendment 39–17411
(78 FR 22182, April 15, 2013). Those
costs are repeated for the convenience of
affected operators, as follows:
ESTIMATED COSTS
Action
Labor cost
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Inspection and attach pin replacement
[actions retained from AD 2013–07–07,
Amendment 39–17411 (78 FR 22182,
April 15, 2013)].
39 work-hours × $85
per hour = $3,315.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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Parts cost
Cost per product
Up to $6,312 ..........
Up to $9,627 ..........
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.
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Cost on U.S. operators
Up to $10,108,350.
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
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
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 have determined that 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:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2013–07–07, Amendment 39–17411 (78
FR 22182, April 15, 2013), and adding
the following new AD:
■
2014–05–30 The Boeing Company:
Amendment 39–17802; Docket No.
FAA–2013–0796; Directorate Identifier
2013–NM–111–AD.
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(a) Effective Date
This AD is effective April 25, 2014.
(b) Affected ADs
(1) This AD supersedes AD 2013–07–07,
Amendment 39–17411 (78 FR 22182, April
15, 2013).
(2) This AD affects certain requirements of
AD 2004–05–19, Amendment 39–13514 (69
FR 10921, March 9, 2004; corrected April 13,
2004 (69 FR 19313)).
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(1) This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST00830SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/408E012E008616A7862
578880060456C?OpenDocument&Highlight=
st00830se) does not affect the ability to
accomplish the actions required by this AD.
Therefore, for airplanes on which STC
ST00830SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by inquiries from
affected operators regarding the parts
installation limitation and prohibition, and
re-installation of certain attach pins that were
removed for inspection. We are issuing this
AD to prevent premature failure of the attach
pins, which could cause reduced structural
integrity of the horizontal stabilizer to
fuselage attachment, resulting in loss of
control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Part Number (P/N) Inspection
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
(c) Applicability
This paragraph restates the requirements of
paragraph (g) of AD 2013–07–07,
Amendment 39–17411 (78 FR 22182, April
15, 2013). For airplanes having line numbers
1 through 3534 inclusive: Before the
accumulation of 56,000 total flight cycles, or
within 3,000 flight cycles after May 20, 2013
(the effective date of AD 2013–07–07),
whichever occurs later, inspect to determine
the part number of the attach pins of the
horizontal stabilizer rear spar. A review of
airplane maintenance records is acceptable in
lieu of this inspection if the part number of
the attach pin can be conclusively
determined from that review.
(h) Retained Replacement
This paragraph restates the requirements of
paragraph (h) of AD 2013–07–07,
Amendment 39–17411 (78 FR 22182, April
15, 2013). If, during the inspection required
by paragraph (g) of this AD, any horizontal
stabilizer rear spar attach pin has P/N
180A1612–3 or 180A1612–4, prior to the
accumulation of 56,000 total flight cycles on
the pin, or within 3,000 flight cycles after
May 20, 2013 (the effective date of AD 2013–
07–07), whichever occurs later, replace with
a new attach pin having P/N 180A1612–7 or
180A1612–8, respectively, in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
737–55–1093, dated April 9, 2012.
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15653
(i) Retained Parts Installation Prohibition
This paragraph restates the requirements of
paragraph (i)(2) of AD 2013–07–07,
Amendment 39–17411 (78 FR 22182, April
15, 2013). For airplanes having line numbers
3535 and subsequent: As of May 20, 2013
(the effective date of AD 2013–07–07), no
person may install an attach pin of the
horizontal stabilizer rear spar having P/N
180A1612–3 or 180A1612–4 on any airplane.
(j) Retained Terminating Action for AD
2004–05–19, Amendment 39–13514 (69 FR
10921, March 9, 2004; Corrected April 13,
2004 (69 FR 19313))
This paragraph restates the provisions of
paragraph (j) of AD 2013–07–07, Amendment
39–17411 (78 FR 22182, April 15, 2013).
Accomplishment of the actions required by
paragraphs (g) and (h) of this AD terminates
the requirements of paragraphs (a), (b), (c),
(d), and (e) of AD 2004–05–19, Amendment
39–13514 (69 FR 10921, March 9, 2004;
corrected April 13, 2004 (69 FR 19313)), for
the rear spar attach pins only.
(k) New Parts Installation Limitation
For airplanes having line numbers 1
through 3534 inclusive: As of the effective
date of this AD, an attach pin of the
horizontal stabilizer rear spar having P/N
180A1612–3 or 180A1612–4 may be installed
on an airplane, provided it is replaced with
an attach pin having P/N 180A1612–7 or
180A1612–8, as applicable, prior to the
accumulation of 56,000 total flight cycles on
the attach pin. The replacement must be
done in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–55–
1093, dated April 9, 2012.
(l) New Attach Pin Replacement
For airplanes having line numbers 1
through 3534 inclusive on which an attach
pin of the horizontal stabilizer rear spar
having P/N 180A1612–7 or 180A1612–8 has
been replaced with an attach pin having P/
N 180A1612–3 or 180A1612–4 before the
effective date of this AD: Prior to the
accumulation of 56,000 total flight cycles on
the attach pin, or within 1,000 flight cycles
on the airplane after the effective date of this
AD, whichever occurs later, replace the
attach pin having P/N 180A1612–3 or
180A1612–4 with an attach pin having P/N
180A1612–7 or 180A1612–8, as applicable,
in accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–55–1093, dated April 9,
2012.
(m) 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
paragraph (n) of this AD. Information may be
emailed to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations
(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.
(4) AMOCs approved previously for AD
2013–07–07, Amendment 39–17411 (78 FR
22182, April 15, 2013), are approved as
AMOCs for the corresponding provisions of
this AD.
(n) Related Information
For more information about this AD,
contact Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6440; fax: 425–917–6590;
email: Nancy.Marsh@faa.gov.
(o) Material Incorporated by Reference
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(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.
(3) The following service information was
approved for IBR on May 20, 2013 (78 FR
22182, April 15, 2013).
(i) Boeing Special Attention Service
Bulletin 737–55–1093, dated April 9, 2012.
(ii) Reserved.
(4) 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.
(5) You may view this service information
at 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.
(6) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 3,
2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–05415 Filed 3–20–14; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0089; Directorate
Identifier 2012–NM–166–AD; Amendment
39–17806; AD 2014–06–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 747–400
series airplanes. This AD was prompted
by reports of auxiliary power unit (APU)
faults due to power feeder cable chafing.
This AD requires detailed inspections
for damage of the APU power feeder
cables; replacing the clamps and
installing grommets; and related
investigative and corrective actions if
necessary. We are issuing this AD to
detect and correct chafing of the APU
power feeder cables within a flammable
fluid leakage zone, which, with arcing,
could result in fire and structural
damage.
SUMMARY:
This AD is effective April 25,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 25, 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, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0089; 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
PO 00000
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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:
Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, Seattle Aircraft Certification
Office, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6482; fax: 425–917–6590; email:
georgios.roussos@faa.gov.
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 certain The Boeing Company
Model 747–400 series airplanes. The
NPRM published in the Federal
Register on February 7, 2013 (78 FR
8999). The NPRM was prompted by
reports of APU faults due to power
feeder cable chafing. The NPRM
proposed to require detailed inspections
for damage of the APU power feeder
cables; replacing the clamps and
installing grommets; and related
investigative and corrective actions if
necessary. We are issuing this AD to
detect and correct chafing of the APU
power feeder cables within a flammable
fluid leakage zone, which, with arcing,
could result in fire and structural
damage.
Relevant Service Information
Since we issued the NPRM (78 FR
8999, February 7, 2013), we reviewed
Boeing Service Bulletin 747–24A2360,
Revision 2, dated October 2, 2013. (The
NPRM referenced Boeing Service
Bulletin 747–24A2360, Revision 1,
dated May 2, 2012, as the appropriate
source of service information for
accomplishing the required actions.)
Boeing Service Bulletin 747–24A2360,
Revision 2, dated October 2, 2013,
among other things, revises the
recommended compliance time from 14
months to 18 months. For information
on the procedures and compliance
times, see this service information at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2013–
0089.
We have determined that extending
the compliance time, as recommended
by the manufacturer, will not adversely
affect safety. We have revised the
compliance time in paragraph (g) of this
AD accordingly. We have also revised
paragraphs (c), (g), (h), and (i) of this AD
to refer to Boeing Service Bulletin 747–
24A2360, Revision 2, dated October 2,
2013.
E:\FR\FM\21MRR1.SGM
21MRR1
]]>Agencies
[Federal Register Volume 79, Number 55 (Friday, March 21, 2014)]
[Rules and Regulations]
[Pages 15651-15654]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-05415]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0796; Directorate Identifier 2013-NM-111-AD;
Amendment 39-17802; AD 2014-05-30]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2013-07-07 for
all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -
900ER series airplanes. AD 2013-07-07 required inspecting to determine
the part number of the attach pins of the horizontal stabilizer rear
spar, and replacing certain attach pins. This new AD clarifies the
parts installation limitation and prohibition, and adds a new
requirement for certain airplanes on which certain attach pins were
installed. This AD was prompted by inquiries from affected operators
regarding the parts installation limitation and prohibition, and re-
installation of certain attach pins that were removed for inspection.
We are issuing this AD to prevent premature failure of the attach pins,
which could cause reduced structural integrity of the horizontal
stabilizer to fuselage attachment, resulting in loss of control of the
airplane.
DATES: This AD is effective April 25, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 20, 2013
(78 FR 22182, April 15, 2013).
ADDRESSES: For service information identified in this AD, contact
Boeing
[[Page 15652]]
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, 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0796; 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: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6440; fax:
425-917-6590; email: Nancy.Marsh@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-07-07, Amendment 39-17411 (78 FR 22182,
April 15, 2013). AD 2013-07-07 applied to all The Boeing Company Model
737-600, -700, -700C, -800, -900, and -900ER series airplanes. The NPRM
published in the Federal Register on September 25, 2013 (78 FR 58982).
The NPRM was prompted by inquiries from affected operators regarding
the parts installation limitation and prohibition, and re-installation
of certain attach pins that were removed for inspection. The NPRM
proposed to continue to require inspecting to determine the part number
of the attach pins of the horizontal stabilizer rear spar, and
replacing certain attach pins. The NPRM also proposed to clarify the
parts installation limitation and prohibition, and add a new
requirement for certain airplanes on which certain attach pins were
installed. We are issuing this AD to prevent premature failure of the
attach pins, which could cause reduced structural integrity of the
horizontal stabilizer to fuselage attachment, resulting in loss of
control of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the proposal
(78 FR 58982, September 25, 2013) and the FAA's response to each
comment.
Clarification of Effect of Winglet Installation
Aviation Partners Boeing stated that the installation of winglets
per Supplemental Type Certificate (STC) ST00830SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does
not affect the accomplishment of the manufacturer's service
instructions.
We concur. Paragraph (c)(2) in AD 2013-07-07, Amendment 39-17411
(78 FR 22182, April 15, 2013), has been restated in this final rule and
specifies that STC ST00830SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) does
not affect the ability to accomplish the actions required by this final
rule. Therefore, for airplanes on which STC ST00830SE is installed, a
``change in product'' alternative method of compliance (AMOC) approval
request is not necessary to comply with the requirements of section
39.17 of the Federal Aviation Regulations (14 CFR 39.17).
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this 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 58982, September 25, 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 58982, September 25, 2013).
Costs of Compliance
We estimate that this AD affects 1,050 airplanes of U.S. registry.
The new requirements add no significant economic burden over that
specified in AD 2013-07-07, Amendment 39-17411 (78 FR 22182, April 15,
2013). Those costs are repeated for the convenience of affected
operators, as follows:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection and attach pin 39 work-hours x Up to $6,312...... Up to $9,627...... Up to $10,108,350.
replacement [actions retained $85 per hour =
from AD 2013-07-07, Amendment $3,315.
39-17411 (78 FR 22182, April
15, 2013)].
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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
[[Page 15653]]
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 have determined that 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 removing Airworthiness Directive (AD)
2013-07-07, Amendment 39-17411 (78 FR 22182, April 15, 2013), and
adding the following new AD:
2014-05-30 The Boeing Company: Amendment 39-17802; Docket No. FAA-
2013-0796; Directorate Identifier 2013-NM-111-AD.
(a) Effective Date
This AD is effective April 25, 2014.
(b) Affected ADs
(1) This AD supersedes AD 2013-07-07, Amendment 39-17411 (78 FR
22182, April 15, 2013).
(2) This AD affects certain requirements of AD 2004-05-19,
Amendment 39-13514 (69 FR 10921, March 9, 2004; corrected April 13,
2004 (69 FR 19313)).
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST00830SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by inquiries from affected operators
regarding the parts installation limitation and prohibition, and re-
installation of certain attach pins that were removed for
inspection. We are issuing this AD to prevent premature failure of
the attach pins, which could cause reduced structural integrity of
the horizontal stabilizer to fuselage attachment, resulting in loss
of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Part Number (P/N) Inspection
This paragraph restates the requirements of paragraph (g) of AD
2013-07-07, Amendment 39-17411 (78 FR 22182, April 15, 2013). For
airplanes having line numbers 1 through 3534 inclusive: Before the
accumulation of 56,000 total flight cycles, or within 3,000 flight
cycles after May 20, 2013 (the effective date of AD 2013-07-07),
whichever occurs later, inspect to determine the part number of the
attach pins of the horizontal stabilizer rear spar. A review of
airplane maintenance records is acceptable in lieu of this
inspection if the part number of the attach pin can be conclusively
determined from that review.
(h) Retained Replacement
This paragraph restates the requirements of paragraph (h) of AD
2013-07-07, Amendment 39-17411 (78 FR 22182, April 15, 2013). If,
during the inspection required by paragraph (g) of this AD, any
horizontal stabilizer rear spar attach pin has P/N 180A1612-3 or
180A1612-4, prior to the accumulation of 56,000 total flight cycles
on the pin, or within 3,000 flight cycles after May 20, 2013 (the
effective date of AD 2013-07-07), whichever occurs later, replace
with a new attach pin having P/N 180A1612-7 or 180A1612-8,
respectively, in accordance with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 737-55-1093, dated April
9, 2012.
(i) Retained Parts Installation Prohibition
This paragraph restates the requirements of paragraph (i)(2) of
AD 2013-07-07, Amendment 39-17411 (78 FR 22182, April 15, 2013). For
airplanes having line numbers 3535 and subsequent: As of May 20,
2013 (the effective date of AD 2013-07-07), no person may install an
attach pin of the horizontal stabilizer rear spar having P/N
180A1612-3 or 180A1612-4 on any airplane.
(j) Retained Terminating Action for AD 2004-05-19, Amendment 39-13514
(69 FR 10921, March 9, 2004; Corrected April 13, 2004 (69 FR 19313))
This paragraph restates the provisions of paragraph (j) of AD
2013-07-07, Amendment 39-17411 (78 FR 22182, April 15, 2013).
Accomplishment of the actions required by paragraphs (g) and (h) of
this AD terminates the requirements of paragraphs (a), (b), (c),
(d), and (e) of AD 2004-05-19, Amendment 39-13514 (69 FR 10921,
March 9, 2004; corrected April 13, 2004 (69 FR 19313)), for the rear
spar attach pins only.
(k) New Parts Installation Limitation
For airplanes having line numbers 1 through 3534 inclusive: As
of the effective date of this AD, an attach pin of the horizontal
stabilizer rear spar having P/N 180A1612-3 or 180A1612-4 may be
installed on an airplane, provided it is replaced with an attach pin
having P/N 180A1612-7 or 180A1612-8, as applicable, prior to the
accumulation of 56,000 total flight cycles on the attach pin. The
replacement must be done in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-55-
1093, dated April 9, 2012.
(l) New Attach Pin Replacement
For airplanes having line numbers 1 through 3534 inclusive on
which an attach pin of the horizontal stabilizer rear spar having P/
N 180A1612-7 or 180A1612-8 has been replaced with an attach pin
having P/N 180A1612-3 or 180A1612-4 before the effective date of
this AD: Prior to the accumulation of 56,000 total flight cycles on
the attach pin, or within 1,000 flight cycles on the airplane after
the effective date of this AD, whichever occurs later, replace the
attach pin having P/N 180A1612-3 or 180A1612-4 with an attach pin
having P/N 180A1612-7 or 180A1612-8, as applicable, in accordance
with the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 737-55-1093, dated April 9, 2012.
(m) 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 paragraph (n) of this AD.
Information may be emailed to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
[[Page 15654]]
(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.
(4) AMOCs approved previously for AD 2013-07-07, Amendment 39-
17411 (78 FR 22182, April 15, 2013), are approved as AMOCs for the
corresponding provisions of this AD.
(n) Related Information
For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6440; fax: 425-917-6590; email: Nancy.Marsh@faa.gov.
(o) 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.
(3) The following service information was approved for IBR on
May 20, 2013 (78 FR 22182, April 15, 2013).
(i) Boeing Special Attention Service Bulletin 737-55-1093, dated
April 9, 2012.
(ii) Reserved.
(4) 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.
(5) You may view this service information at 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.
(6) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 3, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-05415 Filed 3-20-14; 8:45 am]
BILLING CODE 4910-13-P
