Airworthiness Directives; The Boeing Company Airplanes, 46540-46543 [2013-18564]
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46540
Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
(h) Maintenance Program Revision
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 adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2013–0666; Directorate Identifier 2013–
NM–060–AD.
(a) Comments Due Date
We must receive comments by September
16, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 727, 727C, 727–100, 727
–100C, 727–200, and 727–200F series
airplanes; certificated in any category.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(e) Unsafe Condition
This AD was prompted by reports
indicating that a standard fuel tank access
door was located where an impact-resistant
access door was required, and stencils were
missing from some impact-resistant access
doors. We are issuing this AD to prevent
foreign object penetration of the fuel tank,
which could cause a fuel leak near an
ignition source (e.g., hot brakes),
consequently leading to a fuel-fed fire.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspections
Within 72 months after the effective date
of this AD, do the actions specified in
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Jkt 229001
(k) Related Information
(1) For more information about this AD,
contact Suzanne Lucier, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6438; fax: 425–917–6590;
email: suzanne.lucier@faa.gov.
(2) 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 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.
Issued in Renton, Washington, on July 21,
2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Within 60 days after the effective date of
this AD, revise the maintenance program to
incorporate Critical Design Configuration
Control Limitation (CDCCL) Task 57–AWL–
01, ‘‘Impact-Resistant Fuel Tank Access
Door,’’ of Section 1, Airworthiness
Limitations (AWLs) of Boeing 727–100/200
Airworthiness Limitations (AWLs) Document
D6–8766–AWL, Revision September 2012.
[FR Doc. 2013–18507 Filed 7–31–13; 8:45 am]
(i) No Alternative CDCCLs
[Docket No. FAA–2013–0667; Directorate
Identifier 2013–NM–062–AD]
After accomplishing the revision required
by paragraph (h) of this AD, no alternative
CDCCLs may be used unless the CDCCLs are
approved as an alternative method of
compliance in accordance with the
procedures specified in paragraph (j) of this
AD.
(j) Alternative Methods of Compliance
(AMOCs)
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 28, Fuel.
VerDate Mar<15>2010
paragraphs (g)(1) and (g)(2) of this AD, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 727–
28–0134, dated January 12, 2012.
(1) Do either a general visual inspection or
ultrasonic non-destructive test of the left- and
right-hand wing fuel tank access doors to
determine whether impact-resistant access
doors are installed in the correct locations. If
any standard access door is found, before
further flight, replace with an impactresistant access door, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 727–28–0134, dated January
12, 2012.
(2) Do a general visual inspection of the
left- and right-hand wing fuel tank impactresistant access doors to verify stencils and
index markers are applied. If a stencil or
index marker is missing, before further flight,
apply stencil or index marker, as applicable,
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 727–
28–0134, dated January 12, 2012.
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 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.
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 747–400
airplanes. This proposed AD was
prompted by reports of fasteners
missing on an airplane undergoing a
passenger-to-freighter conversion. This
proposed AD would require doing a
general visual inspection of the station
1920 splice clip for correct fastener
installation, and related investigative
and corrective actions if necessary. We
are proposing this AD to detect and
correct missing or incorrect fasteners,
which can lead to cracking and loss of
load carrying capacity, resulting in a
possible decompression event.
DATES: We must receive comments on
this proposed AD by September 16,
2013.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
SUMMARY:
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46541
Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6432; fax: 425–917–
6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2013–0667; Directorate Identifier 2013–
NM–062–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received a report of an
airplane, while undergoing a passengerto-freighter conversion, missing
fasteners on the station 1920 splice clip.
The possibility of this discrepancy
exists on airplanes already delivered.
This condition, if not corrected, could
result in cracking and loss of load
carrying capacity, resulting in a possible
decompression event.
Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 747–53A2844, Revision 1,
dated July 30, 2012. For information on
the procedures and compliance times,
see this service information at https://
www.regulations.gov by searching for
Docket No. FAA–2013–0667.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between the Proposed AD
and the Service Information.’’
The phrase ‘‘related investigative
actions’’ might be used in this proposed
AD. ‘‘Related investigative actions’’ are
follow-on actions that: (1) Are related to
the primary actions, and (2) further
investigate the nature of any condition
found. Related investigative actions in
an AD could include, for example,
inspections.
In addition, the phrase ‘‘corrective
actions’’ might be used in this proposed
AD. ‘‘Corrective actions’’ are actions
that correct or address any condition
found. Corrective actions in an AD
could include, for example, repairs.
Differences Between the Proposed AD
and the Service Information
Although the service bulletin
specifies that operators may contact the
manufacturer for disposition of certain
repair conditions, this proposed AD
would require operators to repair those
conditions in accordance with a method
approved by the FAA.
Costs of Compliance
We estimate that this proposed AD
affects 3 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection for correct fastener installation ............
2 work-hours × $85 per hour = $170 ...................
emcdonald on DSK67QTVN1PROD with PROPOSALS
We estimate the following costs to do
any necessary repairs that would be
Parts cost
required based on the results of the
proposed inspection. We have no way of
$0
Cost per
product
$170
Cost on
U.S.
operators
$510
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Inspections for cracking ....................................................
Fastener installation ..........................................................
Repair ................................................................................
3 work-hours × $85 per hour = $255 ...............................
2 work-hours × $85 per hour = $170 ...............................
2 work-hours × $85 per hour = $170 ...............................
VerDate Mar<15>2010
16:23 Jul 31, 2013
Jkt 229001
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E:\FR\FM\01AUP1.SGM
Parts cost
01AUP1
$0
0
0
Cost per
product
$255
170
170
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Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules
According to the manufacturer, some
of the costs of this proposed 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.
the FAA proposes to amend 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.
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.
emcdonald on DSK67QTVN1PROD with PROPOSALS
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
VerDate Mar<15>2010
16:23 Jul 31, 2013
Jkt 229001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2013–0667; Directorate Identifier 2013–
NM–062–AD.
(a) Comments Due Date
We must receive comments by September
16, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 747–400 series airplanes, certificated
in any category, as identified in Boeing Alert
Service Bulletin 747–53A2844, Revision 1,
dated July 30, 2012.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
fasteners missing on an airplane undergoing
a passenger-to-freighter conversion. We are
issuing this AD to detect and correct missing
or incorrect fasteners, which can lead to
cracking and loss of load carrying capacity,
resulting in a possible decompression event.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
Except as required by paragraph (h)(1) of
this AD, at the times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2844, Revision 1, dated July
30, 2012: Do a general visual inspection for
correct installation of the station 1920 splice
clip common to the auxiliary sill web and the
tie clip, and do all applicable related
investigative and corrective actions in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2844, Revision 1, dated July 30,
2012, except as required by paragraph (h)(2)
of this AD. Do all applicable related
investigative and corrective actions before
further flight.
(h) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
747–53A2844, Revision 1, dated July 30,
2012, specifies a compliance time ‘‘after the
original issue date of the service bulletin,’’
this AD requires compliance within the
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specified compliance time after the effective
date of this AD.
(2) If any cracking is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2844,
Revision 1, dated July 30, 2012, specifies
contacting Boeing for appropriate action:
Before further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using Boeing Alert Service
Bulletin 747–53A2844, dated September 15,
2011, except the detailed inspection for
cracking of the auxiliary sill outer chord tee
and attached parts and all applicable related
investigative and corrective actions must be
done in accordance with Boeing Alert
Service Bulletin 747–53A2844, Revision 1,
dated July 30, 2012, at the times specified in
paragraph (g) of this AD. Boeing Alert Service
Bulletin 747–53A2844, dated September 15,
2011, is not incorporated by reference in this
AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 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.
(k) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6432; fax: 425–917–6590;
email: bill.ashforth@faa.gov.
(2) 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 review copies of the referenced service
information at the FAA, Transport Airplane
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01AUP1
Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on July 21,
2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18564 Filed 7–31–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0665; Directorate
Identifier 2012–NM–082–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A330–300 series airplanes
and Model A340–200 and –300 series
airplanes. This proposed AD was
prompted by reports of corrosion found
on certain trimmable horizontal
stabilizer actuators (THSA), affecting the
ballscrew lower splines between the tie
bar and the screw-jack. This proposed
AD would require repetitive detailed
inspections for corrosion of certain
THSAs, ballscrew integrity tests if
necessary; and replacing any affected
THSA with a serviceable or new and
improved THSA, if necessary. We are
proposing this AD to detect and correct
corrosion of the THSAs, which could
lead, in the case of ballscrew rupture, to
the loss of transmission of THSA torque
loads from the ballscrew to the tie-bar,
prompting THSA blowback, and
possibly resulting in loss of control of
the airplane.
DATES: We must receive comments on
this proposed AD by September 16,
2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
emcdonald on DSK67QTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
16:23 Jul 31, 2013
Jkt 229001
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Airbus service information
identified in this proposed AD, contact
Airbus SAS—Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330A340@airbus.com; Internet https://
www.airbus.com. For Goodrich service
information identified in this proposed
AD, contact Goodrich Corporation,
Actuation Systems, Product Support
Department 13, Avenue de
L’Eguillette—Saint-Ouen L’Aumone
Boite Postale 7186 95056, Cergy
Pontoise Cedex, France; fax: 33–1–
34326310. 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 Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1138;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0665; Directorate Identifier
2012–NM–082–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
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46543
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0061R1,
dated November 30, 2012 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
Some Trimmable Horizontal Stabilizer
Actuators (THSA), Part Number (P/N) 47147–
500, have been found with corrosion,
affecting the ballscrew lower splines between
the tie bar and the screw-jack.
The results of the technical investigations
have identified that the corrosion was caused
by a combination of:
—Contact/friction between the tie bar and the
inner surface of the ballscrew leading to
the removal of Molykote (corrosion
protection) at the level of the tie bar
splines,
—Humidity ingress initiating surface
oxidation starting from areas where
Molykote is removed, and
—Water retention in THSA lower part
leading to corrosion spread out and to the
creation of a brown deposit (iron oxide).
The results of the technical investigations
have also concluded that THSA P/N 47147–
500 and P/N 47147–700 ballscrews might be
affected by this corrosion issue.
THSA P/N 47147–400 ballscrews might be
affected as well, but should no longer be in
service, and modified into P/N 47147–500, as
required by EASA AD 2010–0192 and EASA
AD 2010–0193 [and as required by FAA AD
2005–07–04, Amendment 39–14028 (70 FR
16104, March 30, 2005)].
This condition, if not detected and
corrected, may lead, in case of ballscrew
rupture, to loss of transmission of THSA
torque loads from the ballscrew to the tie-bar,
prompting THSA blowback, possibly
resulting in loss of control of the aeroplane.
To correct this potential unsafe condition,
EASA issued AD 2012–0061 to require
repetitive [detailed] visual inspections of the
ballscrew lower splines of THSA having
P/N 47147–500 or P/N 47147–700 to detect
corrosion and, depending on findings
[ballscrew integrity tests], the
accomplishment of applicable corrective
actions [replacing the affected THSA with a
serviceable or improved THSA].
Since that [EASA] AD [2012–0061] was
issued, Airbus published new Service
Bulletin (SB) A330–27–3194 or Airbus SB
A340–27–4187 (Airbus modification 202802),
which allow installation in service of an
improved THSA P/N 47172–530.
For the reasons described above, this
[EASA] AD [2012–0061R1] is revised to
specify that installation of THSA P/N 47172–
E:\FR\FM\01AUP1.SGM
01AUP1
]]>Agencies
[Federal Register Volume 78, Number 148 (Thursday, August 1, 2013)]
[Proposed Rules]
[Pages 46540-46543]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18564]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0667; Directorate Identifier 2013-NM-062-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 747-400 airplanes. This proposed AD
was prompted by reports of fasteners missing on an airplane undergoing
a passenger-to-freighter conversion. This proposed AD would require
doing a general visual inspection of the station 1920 splice clip for
correct fastener installation, and related investigative and corrective
actions if necessary. We are proposing this AD to detect and correct
missing or incorrect fasteners, which can lead to cracking and loss of
load carrying capacity, resulting in a possible decompression event.
DATES: We must receive comments on this proposed AD by September 16,
2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
[[Page 46541]]
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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 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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; fax:
425-917-6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2013-0667;
Directorate Identifier 2013-NM-062-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received a report of an airplane, while undergoing a
passenger-to-freighter conversion, missing fasteners on the station
1920 splice clip. The possibility of this discrepancy exists on
airplanes already delivered. This condition, if not corrected, could
result in cracking and loss of load carrying capacity, resulting in a
possible decompression event.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2844, Revision 1,
dated July 30, 2012. For information on the procedures and compliance
times, see this service information at https://www.regulations.gov by
searching for Docket No. FAA-2013-0667.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.''
The phrase ``related investigative actions'' might be used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that: (1) Are related to the primary actions, and (2) further
investigate the nature of any condition found. Related investigative
actions in an AD could include, for example, inspections.
In addition, the phrase ``corrective actions'' might be used in
this proposed AD. ``Corrective actions'' are actions that correct or
address any condition found. Corrective actions in an AD could include,
for example, repairs.
Differences Between the Proposed AD and the Service Information
Although the service bulletin specifies that operators may contact
the manufacturer for disposition of certain repair conditions, this
proposed AD would require operators to repair those conditions in
accordance with a method approved by the FAA.
Costs of Compliance
We estimate that this proposed AD affects 3 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on
Action Labor cost Parts cost Cost per U.S.
product operators
----------------------------------------------------------------------------------------------------------------
Inspection for correct fastener 2 work-hours x $85 per hour = $0 $170 $510
installation. $170.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Inspections for cracking...................... 3 work-hours x $85 per hour = $255.... $0 $255
Fastener installation......................... 2 work-hours x $85 per hour = $170.... 0 170
Repair........................................ 2 work-hours x $85 per hour = $170.... 0 170
----------------------------------------------------------------------------------------------------------------
[[Page 46542]]
According to the manufacturer, some of the costs of this proposed
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2013-0667; Directorate Identifier
2013-NM-062-AD.
(a) Comments Due Date
We must receive comments by September 16, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-400 series
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin 747-53A2844, Revision 1, dated July 30, 2012.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of fasteners missing on an
airplane undergoing a passenger-to-freighter conversion. We are
issuing this AD to detect and correct missing or incorrect
fasteners, which can lead to cracking and loss of load carrying
capacity, resulting in a possible decompression event.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
Except as required by paragraph (h)(1) of this AD, at the times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2844, Revision 1, dated July 30, 2012: Do a general
visual inspection for correct installation of the station 1920
splice clip common to the auxiliary sill web and the tie clip, and
do all applicable related investigative and corrective actions in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2844, Revision 1, dated July 30, 2012,
except as required by paragraph (h)(2) of this AD. Do all applicable
related investigative and corrective actions before further flight.
(h) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 747-53A2844, Revision 1,
dated July 30, 2012, specifies a compliance time ``after the
original issue date of the service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2844, Revision 1,
dated July 30, 2012, specifies contacting Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
(i) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using Boeing Alert Service Bulletin 747-53A2844,
dated September 15, 2011, except the detailed inspection for
cracking of the auxiliary sill outer chord tee and attached parts
and all applicable related investigative and corrective actions must
be done in accordance with Boeing Alert Service Bulletin 747-
53A2844, Revision 1, dated July 30, 2012, at the times specified in
paragraph (g) of this AD. Boeing Alert Service Bulletin 747-53A2844,
dated September 15, 2011, is not incorporated by reference in this
AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: 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.
(k) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6432; fax: 425-917-6590; email:
bill.ashforth@faa.gov.
(2) 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 review copies of the referenced
service information at the FAA, Transport Airplane
[[Page 46543]]
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on
the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on July 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18564 Filed 7-31-13; 8:45 am]
BILLING CODE 4910-13-P
