Airworthiness Directives; The Boeing Company Airplanes, 28729-28732 [2013-11387]
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
responsibilities among the various
levels of government.
specified compliance time unless it has
already been accomplished prior to that time.
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 to the extent that it justifies making
a regulatory distinction; 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.
We prepared an economic evaluation of the
estimated costs to comply with this AD and
placed it in the AD docket.
(f) Required Actions
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2010–15–51, Amendment 39–16397 (75
FR 50863, August 18, 2010), and adding
the following new AD:
■
2013–09–06 Agusta S.p.A.: Amendment 39–
17448; Docket No. FAA–2012–0695;
Directorate Identifier 2011–SW–031–AD.
(a) Applicability
This AD applies to Agusta Model A119 and
AW119 MKII helicopters, with pilot control
box assembly (control box), part number
(P/N) 109–0010–81–103, and co-pilot control
box, P/N 109–0010–81–107, installed,
certificated in any category.
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(b) Unsafe Condition
This AD defines the unsafe condition as a
rotary variable differential transformer
(RVDT) locking pin, which could move out
of position and result in loss of manual
throttle control of the engine and subsequent
loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010–15–51,
Amendment 39–16397 (75 FR 50863, August
18, 2010).
(d) Effective Date
This AD becomes effective June 20, 2013.
(e) Compliance
You are responsible for performing each
action required by this AD within the
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(1) Within 5 hours time-in-service (TIS),
and thereafter at intervals not to exceed 50
hours TIS, remove the cover of the pilot and
co-pilot RVDT control box assemblies and
inspect the locking pins for proper position
by following the Compliance Instructions,
Parts I and II, paragraphs 2. through 4.1 for
the pilot control box assembly and
paragraphs 5. through 7.1 for the co-pilot
control box assembly, of Agusta Bollettino
Tecnico No. 119–39, Revision A, dated May
23, 2011.
(2) If during the inspection the locking pin
is recessed or extended in excess of 2.0
millimeters from the face of the pin bore, or
missing, before further flight, replace the
RVDT control box with an airworthy RVDT
control box that has been modified in
accordance with paragraph (f)(3) of this AD.
(3) Within 8 months,
(i) Modify the pilot RVDT control box
assembly, P/N 109–0010–81–103, by
reference to Figures 1 through 7 and in
accordance with the Compliance
Instructions, Part III, paragraphs 5.1 through
5.16 of Agusta Bollettino Tecnico No. 119–
39 Revision A, dated May 23, 2011; and
(ii) Modify the co-pilot RVDT control box
assembly, P/N 109–0010–81–107, by
reference to Figures 1 through 7 and in
accordance with the Compliance
Instructions, Part III, paragraphs 3.1 through
3.16 of Agusta Bollettino Tecnico No. 119–
39, Revision A, dated May 23, 2011.
(4) Modifying the pilot and copilot RVDT
control box assemblies in accordance with
paragraph (f)(3) of this AD constitutes
terminating action for the requirements of
this AD.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222–
5110; email robert.grant@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency AD 2011–
0095–E, dated May 24, 2011.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6700: Rotors Flight Control.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
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28729
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) Agusta Bollettino Tecnico No. 119–39
Revision A, dated May 23, 2011.
(ii) Reserved.
(3) For Agusta service information
identified in this AD, contact Agusta
Westland, Customer Support & Services, Via
Per Tornavento 15, 21019 Somma Lombardo
(VA) Italy, ATTN: Giovanni Cecchelli;
telephone 39–0331–711133; fax 39 0331
711180; or at https://
www.agustawestland.com/technicalbullettins.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on April 26,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–10903 Filed 5–15–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1109; Directorate
Identifier 2011–NM–172–AD; Amendment
39–17455; AD 2013–10–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain The Boeing Company Model
757–200 and –200PF series airplanes.
That AD currently requires modifying
the nacelle strut and wing structure, and
repairing any damage found during the
modification. This new AD specifies a
maximum compliance time limit that
overrides the optional threshold formula
results. This AD was prompted by
reports indicating that the actual
operational loads applied to the nacelle
are higher than the analytical loads that
SUMMARY:
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
were used during the initial design.
Subsequent analysis and service history,
which includes numerous reports of
fatigue cracking on certain strut and
wing structure, indicated that fatigue
cracking can occur on the primary strut
structure before an airplane reaches its
design service objective. We are issuing
this AD to prevent fatigue cracking in
primary strut structure and consequent
reduced structural integrity of the strut.
This AD is effective June 20,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 20, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of October 16, 2003 (68 FR
53496, September 11, 2003).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 13, 2000 (65 FR
59703, October 6, 2000).
DATES:
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;
phone: 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, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
ADDRESSES:
Examining the AD Docket
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You may examine the AD docket on
the Internet at https://
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.
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FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO),
FAA, 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 2003–18–05,
Amendment 39–13296 (68 FR 53496,
September 11, 2003). That AD applies to
the specified products. The NPRM
published in the Federal Register on
October 29, 2012 (77 FR 65506). That
NPRM proposed to continue to require
modifying the nacelle strut and wing
structure, and repairing any damage
found during the modification. That
NPRM also proposed to specify a
maximum compliance time limit that
overrides the optional threshold formula
results.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (77 FR 65506,
October 29, 2012) and the FAA’s
response to each comment.
Clarification Regarding the Installation
of Winglets
Aviation Partners Boeing (APB) stated
that it has reviewed the NPRM (77 FR
65506, October 29, 2012) and the
‘‘Boeing Service Bulletin’’ and has
determined that the installation of
winglets per Supplemental Type
Certificate (STC) ST01518SE (https://
rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
48e13cdfbbc32cf4862576a4005d308b/
$FILE/ST01518SE.pdf) does not affect
them. APB also stated that it will
provide supporting data to the FAA
upon request.
We agree with the commenter’s
statement that the installation of
winglets as specified in STC ST01518SE
(https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/
48e13cdfbbc32cf4862576a4005d308b/
$FILE/ST01518SE.pdf) does not affect
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accomplishment of the requirements of
this AD, and an alternative method of
compliance (AMOC) is not necessary for
a ‘‘change in product’’ AMOC approval
request. We have therefore added this
provision in new paragraph (c)(2) of this
AD.
Statement of Compliance With NPRM
(77 FR 65506, October 29, 2012)
Nord Wind Airlines reported the
status of compliance of its airplanes
with the NPRM (77 FR 65506, October
29, 2012).
No request was submitted by Nord
Wind Airlines. We have not changed
this AD in regard to Nord Wind
Airlines’ comment.
Statement of Previous Compliance With
NPRM (77 FR 65506, October 29, 2012)
FedEx stated that it has previously
performed the prescribed inspections
and terminating actions on its airplanes
and that no further actions are necessary
for it to be in compliance with the
NPRM (77 FR 65506, October 29, 2012).
No request was submitted by FedEx.
We have not changed this AD in regard
to FedEx’s comment.
Change Made to Restated Paragraph (h)
of This AD
We have revised the wording in
paragraph (h) of this AD to clarify the
applicable service information to be
used after the effective date of this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
65506, October 29, 2012) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 65506,
October 29, 2012).
Costs of Compliance
We estimate that this AD affects 278
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
28731
ESTIMATED COSTS
Action
Labor cost
Modification [retained actions from AD 2003–18–05,
Amendment 39–13296 (68 FR 53496, September 11,
2003)].
800 work-hours × $85 per hour =
$68,000.
The new requirements of this AD add
no additional economic burden.
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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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 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.
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Cost per
product
Parts cost
[Amended]
$0
$68,000
Cost on U.S.
operators
$18,904,000
(e) Unsafe Condition
This AD was prompted by reports
indicating that the actual operational loads
applied to the nacelle are higher than the
analytical loads that were used during the
initial design. Subsequent analysis and
service history, which includes numerous
reports of fatigue cracking on certain strut
and wing structure, indicated that fatigue
cracking can occur on the primary strut
structure before an airplane reaches its
design service objective. We are issuing this
AD to prevent fatigue cracking in primary
strut structure and consequent reduced
structural integrity of the strut.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(c) Applicability
(1) This AD applies to The Boeing
Company Model 757–200 and –200PF series
airplanes, certificated in any category, line
numbers 1 through 735 inclusive, powered
by Pratt & Whitney engines.
(2) Supplemental Type Certificate (STC)
ST01518SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/
0/48e13cdfbbc32cf4862576a4005d308b/
$FILE/ST01518SE.pdf) does not affect the
ability to accomplish the actions required by
this AD. Therefore, for airplanes on which
STC ST01518SE 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. For all other AMOC requests, the
operator must request approval for an AMOC
in accordance with the provisions of
paragraph (k) of this AD.
(g) Retained Modification With New Service
Information and Reduced Compliance Time
This paragraph restates the requirements of
paragraph (a) of AD 2003–18–05,
Amendment 39–13296 (68 FR 53496,
September 11, 2003), with new service
information and a reduced compliance time.
Modify the nacelle strut and wing structure
on both the left and right sides of the
airplane, in accordance with Boeing Service
Bulletin 757–54–0034, dated May 14, 1998;
Boeing Service Bulletin 757–54–0034,
Revision 1, dated October 11, 2001; or Boeing
Service Bulletin 757–54–0034, Revision 2,
dated May 7, 2009; at the later of the times
specified in paragraph (g)(1) or (g)(2) of this
AD. As of the effective date of this AD, only
Boeing Service Bulletin 757–54–0034,
Revision 2, dated May 7, 2009, may be used
to accomplish the actions required by this
paragraph.
(1) At the earlier of the times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Prior to the accumulation of 37,500 total
flight cycles.
(ii) At the later of the times specified in
paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this
AD.
(A) Within 20 years since the date of
manufacture.
(B) Within the compliance time calculated
using the optional threshold formula
described in Boeing Service Bulletin 757–54–
0034, Revision 2, dated May 7, 2009, or
within 8 years after the effective date of this
AD, whichever occurs first.
(2) Within 3,000 flight cycles after
November 13, 2000 (the effective date of AD
2000–20–09, Amendment 39–11920 (65 FR
59703, October 6, 2000)).
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 54, Nacelles/Pylons.
(h) Retained Concurrent Requirements With
New Service Information
This paragraph restates the requirements of
paragraph (b) of AD 2003–18–05,
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2003–18–05, Amendment 39–13296 (68
FR 53496, September 11, 2003), and
adding the following new AD:
■
2013–10–02 The Boeing Company:
Amendment 39–17455; Docket No.
FAA–2012–1109; Directorate Identifier
2011–NM–172–AD.
(a) Effective Date
This AD is effective June 20, 2013.
(b) Affected ADs
This AD supersedes AD 2003–18–05,
Amendment 39–13296 (68 FR 53496,
September 11, 2003).
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Federal Register / Vol. 78, No. 95 / Thursday, May 16, 2013 / Rules and Regulations
Amendment 39–13296 (68 FR 53496,
September 11, 2003), with new service
information. Except as provided by
paragraph (j) of this AD: Prior to or
concurrently with the accomplishment of the
modification of the nacelle strut and wing
structure required by paragraph (g) of this
AD, accomplish the actions specified in
Boeing Service Bulletin 757–54–0027,
Revision 1, dated October 27, 1994; and
Boeing Service Bulletin 757–54–0036, dated
May 14, 1998, or Boeing Service Bulletin
757–54–0036, Revision 1, dated July 31,
2006; as applicable; in accordance with those
service bulletins. As of the effective date of
this AD, use only Boeing Service Bulletin
757–54–0027, Revision 1, dated October 27,
1994; and Boeing Service Bulletin 757–54–
0036, Revision 1, dated July 31, 2006; to
accomplish the applicable requirements of
this paragraph.
(i) Retained Repair With New Service
Information
This paragraph restates the requirements of
paragraph (c) of AD 2003–18–05,
Amendment 39–13296 (68 FR 53496,
September 11, 2003), with new service
information. If any damage to airplane
structure is found during the
accomplishment of the modification required
by paragraph (g) of this AD, and Boeing
Service Bulletin 757–54–0034, dated May 14,
1998; Boeing Service Bulletin 757–54–0034,
Revision 1, dated October 11, 2001; or Boeing
Service Bulletin 757–54–0034, Revision 2,
dated May 7, 2009; specifies to contact
Boeing for appropriate action: Before further
flight, repair the damage 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 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: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(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 in
accordance with AD 2003–18–05,
Amendment 39–13296 (68 FR 53496,
September 11, 2003), are approved as
AMOCs for the corresponding provisions of
this AD, except for AMOCs that approved a
revised compliance time.
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(j) Retained Modification With New Service
Information
This paragraph restates the requirements of
paragraph (d) of AD 2003–18–05,
Amendment 39–13296 (68 FR 53496,
September 11, 2003), with new service
information. Modify the nacelle strut
(including replacing the upper link with a
new, improved part, and modifying the wire
support bracket attached to the upper link),
in accordance with Boeing Service Bulletin
757–54–0036, dated May 14, 1998; or Boeing
Service Bulletin 757–54–0036, Revision 1,
dated July 31, 2006; at the earlier of the times
specified in paragraphs (j)(1) and (j)(2) of this
AD. As of the effective date of this AD, use
only Boeing Service Bulletin 757–54–0036,
Revision 1, dated July 31, 2006, to
accomplish the requirements of this
paragraph.
(1) Prior to or concurrently with
accomplishment of the modification of the
nacelle strut and wing structure required by
paragraph (g) of this AD.
(2) Prior to the accumulation of 27,000
total flight cycles (for Model 757–200 series
airplanes) or 29,000 total flight cycles (for
Model 757–200PF series airplanes), or within
2 years after October 16, 2003 (the effective
date of AD 2003–18–05, Amendment 39–
13296 (68 FR 53496, September 11, 2003)),
whichever is later.
(l) Related Information
For more information about this AD,
contact Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6440; fax: 425–917–6590;
email: Nancy.Marsh@faa.gov.
(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.
(3) The following service information was
approved for IBR on June 20, 2013.
(i) Boeing Service Bulletin 757–54–0034,
Revision 2, dated May 7, 2009.
(ii) Boeing Service Bulletin 757–54–0036,
Revision 1, dated July 31, 2006.
(4) The following service information was
approved for IBR on October 16, 2003 (68 FR
53496, September 11, 2003).
(i) Boeing Service Bulletin 757–54–0034,
Revision 1, dated October 11, 2001.
(ii) Reserved.
(5) The following service information was
approved for IBR on November 13, 2000 (65
FR 59703, October 6, 2000).
(i) Boeing Service Bulletin 757–54–0027,
Revision 1, dated October 27, 1994.
(ii) Boeing Service Bulletin 757–54–0034,
dated May 14, 1998.
(iii) Boeing Service Bulletin 757–54–0036,
dated May 14, 1998.
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(6) 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; phone:
206–544–5000, extension 1; fax: 206–766–
5680; Internet: https://
www.myboeingfleet.com.
(7) You may review copies of the
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.
(8) 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 May 6,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–11387 Filed 5–15–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 35
[Docket No. RM12–3–000]
Revisions to Electric Quarterly Report
Filing Process; Availability of Draft
XML Schema
Federal Energy Regulatory
Commission, DOE.
ACTION: Notification of availability.
AGENCY:
The Federal Energy
Regulatory Commission is making
available on its Web site (https://
www.ferc.gov), Extensible Mark-Up
Language (XML) needed to make
Electric Quarterly Report (EQR) filings
with one of the new filing processes
adopted in Order No. 770, in the
Commission’s Final Rule, 77 FR 71288
(November 30, 2012). Please refer to the
SUPPLEMENTARY INFORMATION Section
below for details.
DATES: The XML is now available at the
links mentioned below.
FOR FURTHER INFORMATION CONTACT:
Christina Switzer, Office of the General
Counsel, Federal Energy Regulatory
Commission, 888 First St. NE.,
Washington, DC 20426, (202) 502–6379.
SUPPLEMENTARY INFORMATION: Take
notice that the Federal Energy
Regulatory Commission (Commission) is
making available on its Web site the
SUMMARY:
E:\FR\FM\16MYR1.SGM
16MYR1
]]>Agencies
[Federal Register Volume 78, Number 95 (Thursday, May 16, 2013)]
[Rules and Regulations]
[Pages 28729-28732]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11387]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1109; Directorate Identifier 2011-NM-172-AD;
Amendment 39-17455; AD 2013-10-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company Model 757-200 and -200PF series
airplanes. That AD currently requires modifying the nacelle strut and
wing structure, and repairing any damage found during the modification.
This new AD specifies a maximum compliance time limit that overrides
the optional threshold formula results. This AD was prompted by reports
indicating that the actual operational loads applied to the nacelle are
higher than the analytical loads that
[[Page 28730]]
were used during the initial design. Subsequent analysis and service
history, which includes numerous reports of fatigue cracking on certain
strut and wing structure, indicated that fatigue cracking can occur on
the primary strut structure before an airplane reaches its design
service objective. We are issuing this AD to prevent fatigue cracking
in primary strut structure and consequent reduced structural integrity
of the strut.
DATES: This AD is effective June 20, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 20, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
October 16, 2003 (68 FR 53496, September 11, 2003).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 13, 2000 (65 FR 59703, October 6, 2000).
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; phone: 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, 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; 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: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO),
FAA, 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 2003-18-05, Amendment 39-13296 (68 FR 53496,
September 11, 2003). That AD applies to the specified products. The
NPRM published in the Federal Register on October 29, 2012 (77 FR
65506). That NPRM proposed to continue to require modifying the nacelle
strut and wing structure, and repairing any damage found during the
modification. That NPRM also proposed to specify a maximum compliance
time limit that overrides the optional threshold formula results.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 65506, October 29, 2012) and the FAA's response to each comment.
Clarification Regarding the Installation of Winglets
Aviation Partners Boeing (APB) stated that it has reviewed the NPRM
(77 FR 65506, October 29, 2012) and the ``Boeing Service Bulletin'' and
has determined that the installation of winglets per Supplemental Type
Certificate (STC) ST01518SE (https://rgl.faa.gov/Regulatory--and--
Guidance--Library/rgstc.nsf/0/48e13cdfbbc32cf4862576a4005d308b/$FILE/
ST01518SE.pdf) does not affect them. APB also stated that it will
provide supporting data to the FAA upon request.
We agree with the commenter's statement that the installation of
winglets as specified in STC ST01518SE (https://rgl.faa.gov/Regulatory--
and--Guidance--Library/rgstc.nsf/0/48e13cdfbbc32cf4862576a4005d308b/
$FILE/ST01518SE.pdf) does not affect accomplishment of the requirements
of this AD, and an alternative method of compliance (AMOC) is not
necessary for a ``change in product'' AMOC approval request. We have
therefore added this provision in new paragraph (c)(2) of this AD.
Statement of Compliance With NPRM (77 FR 65506, October 29, 2012)
Nord Wind Airlines reported the status of compliance of its
airplanes with the NPRM (77 FR 65506, October 29, 2012).
No request was submitted by Nord Wind Airlines. We have not changed
this AD in regard to Nord Wind Airlines' comment.
Statement of Previous Compliance With NPRM (77 FR 65506, October 29,
2012)
FedEx stated that it has previously performed the prescribed
inspections and terminating actions on its airplanes and that no
further actions are necessary for it to be in compliance with the NPRM
(77 FR 65506, October 29, 2012).
No request was submitted by FedEx. We have not changed this AD in
regard to FedEx's comment.
Change Made to Restated Paragraph (h) of This AD
We have revised the wording in paragraph (h) of this AD to clarify
the applicable service information to be used after the effective date
of this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously--and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 65506, October 29, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 65506, October 29, 2012).
Costs of Compliance
We estimate that this AD affects 278 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 28731]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification [retained actions from AD 2003-18-05, 800 work-hours x $85 per hour = $68,000.... $0 $68,000 $18,904,000
Amendment 39-13296 (68 FR 53496, September 11, 2003)].
--------------------------------------------------------------------------------------------------------------------------------------------------------
The new requirements of this AD add no additional economic burden.
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 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)
2003-18-05, Amendment 39-13296 (68 FR 53496, September 11, 2003), and
adding the following new AD:
2013-10-02 The Boeing Company: Amendment 39-17455; Docket No. FAA-
2012-1109; Directorate Identifier 2011-NM-172-AD.
(a) Effective Date
This AD is effective June 20, 2013.
(b) Affected ADs
This AD supersedes AD 2003-18-05, Amendment 39-13296 (68 FR
53496, September 11, 2003).
(c) Applicability
(1) This AD applies to The Boeing Company Model 757-200 and -
200PF series airplanes, certificated in any category, line numbers 1
through 735 inclusive, powered by Pratt & Whitney engines.
(2) Supplemental Type Certificate (STC) ST01518SE (https://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
48e13cdfbbc32cf4862576a4005d308b/$FILE/ST01518SE.pdf) does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01518SE 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. For all other AMOC requests, the operator must request
approval for an AMOC in accordance with the provisions of paragraph
(k) of this AD.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by reports indicating that the actual
operational loads applied to the nacelle are higher than the
analytical loads that were used during the initial design.
Subsequent analysis and service history, which includes numerous
reports of fatigue cracking on certain strut and wing structure,
indicated that fatigue cracking can occur on the primary strut
structure before an airplane reaches its design service objective.
We are issuing this AD to prevent fatigue cracking in primary strut
structure and consequent reduced structural integrity of the strut.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Modification With New Service Information and Reduced
Compliance Time
This paragraph restates the requirements of paragraph (a) of AD
2003-18-05, Amendment 39-13296 (68 FR 53496, September 11, 2003),
with new service information and a reduced compliance time. Modify
the nacelle strut and wing structure on both the left and right
sides of the airplane, in accordance with Boeing Service Bulletin
757-54-0034, dated May 14, 1998; Boeing Service Bulletin 757-54-
0034, Revision 1, dated October 11, 2001; or Boeing Service Bulletin
757-54-0034, Revision 2, dated May 7, 2009; at the later of the
times specified in paragraph (g)(1) or (g)(2) of this AD. As of the
effective date of this AD, only Boeing Service Bulletin 757-54-0034,
Revision 2, dated May 7, 2009, may be used to accomplish the actions
required by this paragraph.
(1) At the earlier of the times specified in paragraphs
(g)(1)(i) and (g)(1)(ii) of this AD.
(i) Prior to the accumulation of 37,500 total flight cycles.
(ii) At the later of the times specified in paragraph
(g)(1)(ii)(A) or (g)(1)(ii)(B) of this AD.
(A) Within 20 years since the date of manufacture.
(B) Within the compliance time calculated using the optional
threshold formula described in Boeing Service Bulletin 757-54-0034,
Revision 2, dated May 7, 2009, or within 8 years after the effective
date of this AD, whichever occurs first.
(2) Within 3,000 flight cycles after November 13, 2000 (the
effective date of AD 2000-20-09, Amendment 39-11920 (65 FR 59703,
October 6, 2000)).
(h) Retained Concurrent Requirements With New Service Information
This paragraph restates the requirements of paragraph (b) of AD
2003-18-05,
[[Page 28732]]
Amendment 39-13296 (68 FR 53496, September 11, 2003), with new
service information. Except as provided by paragraph (j) of this AD:
Prior to or concurrently with the accomplishment of the modification
of the nacelle strut and wing structure required by paragraph (g) of
this AD, accomplish the actions specified in Boeing Service Bulletin
757-54-0027, Revision 1, dated October 27, 1994; and Boeing Service
Bulletin 757-54-0036, dated May 14, 1998, or Boeing Service Bulletin
757-54-0036, Revision 1, dated July 31, 2006; as applicable; in
accordance with those service bulletins. As of the effective date of
this AD, use only Boeing Service Bulletin 757-54-0027, Revision 1,
dated October 27, 1994; and Boeing Service Bulletin 757-54-0036,
Revision 1, dated July 31, 2006; to accomplish the applicable
requirements of this paragraph.
(i) Retained Repair With New Service Information
This paragraph restates the requirements of paragraph (c) of AD
2003-18-05, Amendment 39-13296 (68 FR 53496, September 11, 2003),
with new service information. If any damage to airplane structure is
found during the accomplishment of the modification required by
paragraph (g) of this AD, and Boeing Service Bulletin 757-54-0034,
dated May 14, 1998; Boeing Service Bulletin 757-54-0034, Revision 1,
dated October 11, 2001; or Boeing Service Bulletin 757-54-0034,
Revision 2, dated May 7, 2009; specifies to contact Boeing for
appropriate action: Before further flight, repair the damage using a
method approved in accordance with the procedures specified in
paragraph (k) of this AD.
(j) Retained Modification With New Service Information
This paragraph restates the requirements of paragraph (d) of AD
2003-18-05, Amendment 39-13296 (68 FR 53496, September 11, 2003),
with new service information. Modify the nacelle strut (including
replacing the upper link with a new, improved part, and modifying
the wire support bracket attached to the upper link), in accordance
with Boeing Service Bulletin 757-54-0036, dated May 14, 1998; or
Boeing Service Bulletin 757-54-0036, Revision 1, dated July 31,
2006; at the earlier of the times specified in paragraphs (j)(1) and
(j)(2) of this AD. As of the effective date of this AD, use only
Boeing Service Bulletin 757-54-0036, Revision 1, dated July 31,
2006, to accomplish the requirements of this paragraph.
(1) Prior to or concurrently with accomplishment of the
modification of the nacelle strut and wing structure required by
paragraph (g) of this AD.
(2) Prior to the accumulation of 27,000 total flight cycles (for
Model 757-200 series airplanes) or 29,000 total flight cycles (for
Model 757-200PF series airplanes), or within 2 years after October
16, 2003 (the effective date of AD 2003-18-05, Amendment 39-13296
(68 FR 53496, September 11, 2003)), whichever is later.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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 in accordance with AD 2003-18-05,
Amendment 39-13296 (68 FR 53496, September 11, 2003), are approved
as AMOCs for the corresponding provisions of this AD, except for
AMOCs that approved a revised compliance time.
(l) Related Information
For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft
Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6440; fax: 425-917-6590; email:
Nancy.Marsh@faa.gov.
(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.
(3) The following service information was approved for IBR on
June 20, 2013.
(i) Boeing Service Bulletin 757-54-0034, Revision 2, dated May
7, 2009.
(ii) Boeing Service Bulletin 757-54-0036, Revision 1, dated July
31, 2006.
(4) The following service information was approved for IBR on
October 16, 2003 (68 FR 53496, September 11, 2003).
(i) Boeing Service Bulletin 757-54-0034, Revision 1, dated
October 11, 2001.
(ii) Reserved.
(5) The following service information was approved for IBR on
November 13, 2000 (65 FR 59703, October 6, 2000).
(i) Boeing Service Bulletin 757-54-0027, Revision 1, dated
October 27, 1994.
(ii) Boeing Service Bulletin 757-54-0034, dated May 14, 1998.
(iii) Boeing Service Bulletin 757-54-0036, dated May 14, 1998.
(6) 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; phone:
206-544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com.
(7) You may review copies of the 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.
(8) 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 May 6, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-11387 Filed 5-15-13; 8:45 am]
BILLING CODE 4910-13-P
