Airworthiness Directives; Airbus Airplanes, 12988-12991 [2013-04339]
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12988
Federal Register / Vol. 78, No. 38 / Tuesday, February 26, 2013 / Proposed Rules
AGENCY:
THSA blowback, and possible loss of
control of the airplane.
DATES: We must receive comments on
this proposed AD by April 12, 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–
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, Airworthiness Office—EAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. For
Goodrich service information identified
in this proposed AD, contact Goodrich
Corporation, Actuation Systems,
Stafford Road, Fordhouses,
Wolverhampton WV10 7EH, England;
telephone +44 (0) 1902 624938; fax +44
(0) 1902 788100; email
techpubs.wolverhampton@
goodrich.com; Internet https://
www.goodrich.com/TechPubs.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.
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by reports that
certain trimmable horizontal stabilizer
actuators (THSA) were found with
corrosion that affected the ballscrew
lower splines between the tie-bar and
screw-jack. This proposed AD would
require repetitive inspections of the
THSA; ballscrew integrity tests, if
necessary; and replacement of affected
THSAs. We are proposing this AD to
detect and correct corrosion in the
ballscrew lower splines, which, if the
ballscrew ruptured, could lead to
transmission of THSA torque loads from
the ballscrew to the tie-bar, prompting
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1405;
fax (425) 227–1149.
granted waiver will terminate 365 days
after issuance.
(e) Any basic model for which a
waiver has been granted shall be
shipped from the water heater original
equipment manufacturer with a control
device that is compatible with the
utility company administered electric
thermal storage program. Any changes
to the basic model design which results
in the unit consuming more energy or
alters the control device from which the
waiver was granted shall require a new
waiver application. The control device
must be installed on the water heater
before it leaves the original equipment
manufacturer. The control device must
be capable of receiving communication
from a grid operator, electric utility, or
other energy services company that
provides real-time control of the heating
element. The water heater must be
clearly labeled and marketed for use
exclusively in ETS programs, including
a description of the control device
integrated into the water heater, before
it leaves the original equipment
manufacturer.
[FR Doc. 2013–04099 Filed 2–25–13; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0094; Directorate
Identifier 2012–NM–160–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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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–2013–0094; Directorate Identifier
2012–NM–160–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.
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 2012–0175,
dated September 7, 2012 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘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 fitted on
A330/A340 aeroplanes have been found
with corrosion, affecting the ballscrew
lower splines between the tie bar and
the screw-jack. The affected ballscrew is
made of steel and anti-corrosion
protection is ensured, except on both
extremities (upper and lower splines)
where Molykote is applied.
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
A320 family THSA P/N 47145–XXX
(where XXX stands for any numerical
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Federal Register / Vol. 78, No. 38 / Tuesday, February 26, 2013 / Proposed Rules
value) ballscrews might be affected by
this corrosion issue.
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.
For the reasons described above, this
[EASA] AD requires repetitive detailed
inspections of the ballscrew lower
splines of THSAs having P/N 47145–
XXX to detect corrosion and, depending
on findings, the accomplishment of
applicable corrective actions.
The required action is repetitive
detailed inspections of the gaps between
the ballscrew shaft and tie-rod splines of
the affected THSAs to determine the
corrosion category. Depending on the
corrosion category, additional actions
include a ballscrew shaft integrity test
and replacing the THSA with a new
THSA if necessary. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin
A320–27–1214, including Appendix 01,
dated February 23, 2012; and Goodrich
has issued Service Bulletin 47145–27–
16, dated November 7, 2011. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 755 products of U.S.
registry. We also estimate that it would
take about 4 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$256,700, or $340 per product.
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In addition, we estimate that any
necessary follow-on actions would take
about 15 work-hours and require parts
costing $2,203, for a cost of $3,478 per
product. We have no way of
determining the number of products
that may need these actions.
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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12989
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
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 AD:
■
Airbus: Docket No. FAA–2013–0094;
Directorate Identifier 2012–NM–160–AD.
(a) Comments Due Date
We must receive comments by April 12,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318–
111, –112, –121, and –122 airplanes; Airbus
Model A319–111, –112, –113, –114, –115,
–131, –132, and –133 airplanes; Airbus
Model A320–111, –211, –212, –214, –231,
–232, and –233 airplanes; and Airbus Model
A321–111, –112, –131, –211, –212, –213,
–231, and –232 airplanes; certificated in any
category.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by reports that
certain trimmable horizontal stabilizer
actuators (THSA) were found with corrosion
that affected the ballscrew lower splines
between the tie-bar and screw-jack. We are
issuing this AD to detect and correct
corrosion in the ballscrew lower splines,
which, if the ballscrew ruptured, could lead
to transmission of THSA torque loads from
the ballscrew to the tie-bar, prompting THSA
blowback, and possible loss of control of the
airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Explanation of THSA First Flight
For the purposes of this AD, the definition
of THSA first flight is the THSA ‘‘entry into
service date,’’ as identified in Goodrich
Service Bulletin 47145–27–16, dated
November 7, 2011. If the THSA part number
(P/N) is not identified in Goodrich Service
Bulletin 47145–27–16, dated November 7,
2011, the THSA first flight is the
manufacturing date engraved on the THSA
identification plate.
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Federal Register / Vol. 78, No. 38 / Tuesday, February 26, 2013 / Proposed Rules
(h) Repetitive Inspections
At the later of the times in paragraphs
(h)(1) and (h)(2) of this AD: Do a detailed
inspection of the gaps between the ballscrew
shaft and tie-rod splines on any THSA having
P/N 47145–XXX (where XXX stands for any
numerical value) to determine if the
corrosion category is Type I, Type II, or Type
III, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1214, including Appendix 01, dated
February 23, 2012; and the Accomplishment
Instructions and the flowchart following the
Accomplishment Instructions of Goodrich
Service Bulletin 47145–27–16, dated
November 7, 2011. Repeat the inspection
thereafter at intervals not to exceed 24
months.
(1) Within 22 years accumulated by the
THSA since the THSA’s first flight, but no
earlier than 20 years accumulated by the
THSA since its first flight.
(2) Within three months after the effective
date of this AD.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(i) Ballscrew Integrity Test and Corrective
Actions
If, during any inspection required by
paragraph (h) of this AD, it is determined that
a THSA has Type II or Type III corrosion:
Before further flight, do a ballscrew integrity
test, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1214, including Appendix 01, dated
February 23, 2012; and the Accomplishment
Instructions and the flowchart following the
Accomplishment Instructions of Goodrich
Service Bulletin 47145–27–16, dated
November 7, 2011. If Type I corrosion is
found, no action is required by this
paragraph.
(1) For THSAs having Type II or Type III
corrosion and for which the results of the
ballscrew integrity test are not correct, as
specified in Airbus Service Bulletin A320–
27–1214, including Appendix 01, dated
February 23, 2012: Before further flight,
replace the affected THSA with a new THSA,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1214, including Appendix 01, dated
February 23, 2012.
(2) For THSAs having Type III corrosion
and on which the results of the ballscrew
integrity test are correct, as specified in
Airbus Service Bulletin A320 27–1214,
including Appendix 01, dated February 23,
2012: Within 10 days after the most recent
inspection, replace the THSA with a new
THSA, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1214, including
Appendix 01, dated February 23, 2012.
(3) For THSAs having Type II corrosion
and on which the results of the ballscrew
integrity test are correct, as specified in
Airbus Service Bulletin A320 27–1214,
including Appendix 01, dated February 23,
2012: Within 24 months or 5,000 flight cycles
after the most recent inspection, whichever
occurs first, replace the THSA with a new
THSA, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1214, including
Appendix 01, dated February 23, 2012.
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(j) Replacement of a THSA Is Not
Terminating Action
Replacement of a THSA, as required by
paragraph (i) of this AD, does not constitute
terminating action for the repetitive
inspections required by paragraph (h) of this
AD.
(k) Reporting Requirement
If any corrosion type is found during any
inspection required by paragraph (h) of this
AD, at the applicable time in paragraph (k)(1)
or (k)(2) of this AD, report the findings to
Airbus, Customer Services Engineering—
SEEL5, Flight Control Systems A320 Family,
1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; fax +33 5 61 93 44
25. The report must include the information
specified in Appendix 01 of Airbus Service
Bulletin A320–27–1214, dated February 23,
2012.
(1) If the inspection was done on or after
the effective date of this AD: Within 90 days
after that inspection.
(2) If the inspection was done before the
effective date of this AD: Within 90 days after
the effective date of this AD.
(l) Parts Installation Limitations
As of the effective date of this AD, no
person may install a THSA having P/N
47145–XXX (where XXX stands for any
numerical value), on any airplane, unless
that THSA meets the criteria specified in
paragraphs (l)(1) and (l)(2) of this AD.
(1) The THSA has not accumulated 20
years since the THSA’s first flight, or the
THSA has been inspected as required by
paragraph (h) of this AD and it has been
determined that the THSA had Type I
corrosion (no corrosion) at the time of
installation; and
(2) The THSA is thereafter inspected as
required by paragraph (h) of this AD, and any
applicable actions specified in paragraph (i)
of this AD are accomplished.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1405; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
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. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
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a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing, and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(n) Special Flight Permits
Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the airplane can be
modified (if the operator elects to do so),
provided that, if any THSA corrosion is
found during any action required by
paragraph (h) of this AD, that corrosion is
classified as Type I or Type II, as defined in
Goodrich Service Bulletin 47145–27–16,
dated November 7, 2011.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information European
Aviation Safety Agency Airworthiness
Directive 2012–0175, dated September 7,
2012, and the service information specified
in paragraphs (o)(1)(i) and (o)(1)(ii) of this
AD, for related information.
(i) Airbus Service Bulletin A320–27–1214,
including Appendix 01, dated February 23,
2012.
(ii) Goodrich Service Bulletin 47145–27–
16, dated November 7, 2011.
(2) For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com. For Goodrich service
information identified in this AD, contact
Goodrich Corporation, Actuation Systems,
Stafford Road, Fordhouses, Wolverhampton
WV10 7EH, England; telephone +44 (0) 1902
624938; fax +44 (0) 1902 788100; email
techpubs.wolverhampton@goodrich.com;
Internet https://www.goodrich.com/TechPubs.
You may review copies of the referenced
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
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Federal Register / Vol. 78, No. 38 / Tuesday, February 26, 2013 / Proposed Rules
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on February
11, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–04339 Filed 2–25–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0095; Directorate
Identifier 2011–NM–197–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
AGENCY:
SUMMARY: We propose to supersede two
existing airworthiness directives (AD)
that apply to all The Boeing Company
Model 767 airplanes. One AD currently
requires a functional check of the shear
rivets in all six elevator power control
actuator (PCA) bellcrank assemblies to
determine the condition of the shear
rivets, and replacement or rework of the
bellcrank assemblies if necessary. The
other AD currently requires repetitive
testing of the elevator control system to
determine if an elevator PCA is rigged
incorrectly, and follow-on actions if
necessary. Since we issued those ADs,
a terminating modification has been
designed. This proposed AD would
require an inspection to determine the
part numbers and condition of the
bellcrank assemblies; modification or
replacement of the PCA bellcrank
assembly, if necessary; and a repetitive
functional test and mis-rig check, and
corrective actions if necessary. We are
proposing this AD to prevent continued
operation with yielded or failed shear
rivets in the elevator PCA bellcrank
assemblies, and to prevent certain
failures or jams in the elevator system
from causing a hardover of the elevator
surface, resulting in a significant pitch
upset and possible loss of control of the
airplane.
DATES: We must receive comments on
this proposed AD by April 12, 2013.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
VerDate Mar<15>2010
14:55 Feb 25, 2013
Jkt 229001
• 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:
Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6418;
fax: 425–917–6590; email:
marie.hogestad@faa.gov.
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–2013–0095; Directorate Identifier
2011–NM–197–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.
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12991
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
On August 18, 2000, we issued AD
2000–17–05, Amendment 39–11879 (65
FR 51754, August 25, 2000), for certain
The Boeing Company Model 767–200,
–300, and –300F series airplanes. That
AD requires a one-time functional check
of the shear rivets in all six PCA
bellcrank assemblies to determine the
condition of the shear rivets; and
replacement or rework of the bellcrank
assemblies, if necessary. That AD
resulted from reports that elevator
bellcrank assemblies with failed shear
rivets had been found on three Model
767 airplanes. We issued that AD to
detect and correct any failed or partially
yielded shear rivets of the elevator PCA
bellcrank assemblies. Failure of two
bellcrank assemblies on one side can
result in that single elevator surface
moving to a hardover position,
independent of pilot command,
resulting in a significant pitch upset
recoverable by the crew. Failure of three
bellcrank assemblies on one side could
result in loss of control of the airplane.
On February 21, 2001, we issued AD
2001–04–09, Amendment 39–12128 (66
FR 13227, March 5, 2001), for all The
Boeing Company Model 767 airplanes.
That AD requires repetitive testing of
the elevator control system to determine
if an elevator PCA is rigged incorrectly
due to yielded or failed shear rivets in
a bellcrank assembly of the elevator
PCA, and follow-on actions if necessary.
That AD resulted from reports that
several Model 767 airplanes failed the
one-time functional check of the shear
rivets in the bellcrank assemblies of the
elevator PCA required by AD 2000–17–
05, Amendment 39–11879 (65 FR
51754, August 25, 2000). We issued AD
2001–04–09, Amendment 39–12128 (66
FR 13227, March 5, 2001), to prevent
continued operation with yielded or
failed shear rivets in a bellcrank
assembly of the elevator PCA, which
could result in loss of control of the
airplane.
Actions Since Existing AD 2000–17–05,
Amendment 39–11879 (65 FR 51754,
August 25, 2000); and AD 2001–04–09,
Amendment 39–12128 (66 FR 13227,
March 5, 2001) Issued
The preambles to AD 2000–17–05,
Amendment 39–11879 (65 FR 51754,
August 25, 2000); and AD 2001–04–09,
Amendment 39–12128 (66 FR 13227,
E:\FR\FM\26FEP1.SGM
26FEP1
]]>Agencies
[Federal Register Volume 78, Number 38 (Tuesday, February 26, 2013)]
[Proposed Rules]
[Pages 12988-12991]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-04339]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0094; Directorate Identifier 2012-NM-160-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus 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 all
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed
AD was prompted by reports that certain trimmable horizontal stabilizer
actuators (THSA) were found with corrosion that affected the ballscrew
lower splines between the tie-bar and screw-jack. This proposed AD
would require repetitive inspections of the THSA; ballscrew integrity
tests, if necessary; and replacement of affected THSAs. We are
proposing this AD to detect and correct corrosion in the ballscrew
lower splines, which, if the ballscrew ruptured, could lead to
transmission of THSA torque loads from the ballscrew to the tie-bar,
prompting THSA blowback, and possible loss of control of the airplane.
DATES: We must receive comments on this proposed AD by April 12, 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-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, Airworthiness Office--EAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet
https://www.airbus.com. For Goodrich service information identified in
this proposed AD, contact Goodrich Corporation, Actuation Systems,
Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England; telephone
+44 (0) 1902 624938; fax +44 (0) 1902 788100; email
techpubs.wolverhampton@goodrich.com; Internet https://www.goodrich.com/TechPubs.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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405;
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-2013-0094;
Directorate Identifier 2012-NM-160-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.
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 2012-0175, dated September 7, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``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 fitted on A330/A340 aeroplanes have been found with
corrosion, affecting the ballscrew lower splines between the tie bar
and the screw-jack. The affected ballscrew is made of steel and anti-
corrosion protection is ensured, except on both extremities (upper and
lower splines) where Molykote is applied.
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 A320 family THSA P/N 47145-XXX (where XXX stands for any numerical
[[Page 12989]]
value) ballscrews might be affected by this corrosion issue.
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.
For the reasons described above, this [EASA] AD requires repetitive
detailed inspections of the ballscrew lower splines of THSAs having P/N
47145-XXX to detect corrosion and, depending on findings, the
accomplishment of applicable corrective actions.
The required action is repetitive detailed inspections of the gaps
between the ballscrew shaft and tie-rod splines of the affected THSAs
to determine the corrosion category. Depending on the corrosion
category, additional actions include a ballscrew shaft integrity test
and replacing the THSA with a new THSA if necessary. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A320-27-1214, including Appendix
01, dated February 23, 2012; and Goodrich has issued Service Bulletin
47145-27-16, dated November 7, 2011. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 755 products of U.S. registry. We also estimate that
it would take about 4 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $256,700, or $340 per product.
In addition, we estimate that any necessary follow-on actions would
take about 15 work-hours and require parts costing $2,203, for a cost
of $3,478 per product. We have no way of determining the number of
products that may need these actions.
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 AD:
Airbus: Docket No. FAA-2013-0094; Directorate Identifier 2012-NM-
160-AD.
(a) Comments Due Date
We must receive comments by April 12, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Airbus Model A319-111, -112, -113, -114, -115, -131,
-132, and -133 airplanes; Airbus Model A320-111, -211, -212, -214, -
231, -232, and -233 airplanes; and Airbus Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes; certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by reports that certain trimmable
horizontal stabilizer actuators (THSA) were found with corrosion
that affected the ballscrew lower splines between the tie-bar and
screw-jack. We are issuing this AD to detect and correct corrosion
in the ballscrew lower splines, which, if the ballscrew ruptured,
could lead to transmission of THSA torque loads from the ballscrew
to the tie-bar, prompting THSA blowback, and possible loss of
control of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Explanation of THSA First Flight
For the purposes of this AD, the definition of THSA first flight
is the THSA ``entry into service date,'' as identified in Goodrich
Service Bulletin 47145-27-16, dated November 7, 2011. If the THSA
part number (P/N) is not identified in Goodrich Service Bulletin
47145-27-16, dated November 7, 2011, the THSA first flight is the
manufacturing date engraved on the THSA identification plate.
[[Page 12990]]
(h) Repetitive Inspections
At the later of the times in paragraphs (h)(1) and (h)(2) of
this AD: Do a detailed inspection of the gaps between the ballscrew
shaft and tie-rod splines on any THSA having P/N 47145-XXX (where
XXX stands for any numerical value) to determine if the corrosion
category is Type I, Type II, or Type III, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1214,
including Appendix 01, dated February 23, 2012; and the
Accomplishment Instructions and the flowchart following the
Accomplishment Instructions of Goodrich Service Bulletin 47145-27-
16, dated November 7, 2011. Repeat the inspection thereafter at
intervals not to exceed 24 months.
(1) Within 22 years accumulated by the THSA since the THSA's
first flight, but no earlier than 20 years accumulated by the THSA
since its first flight.
(2) Within three months after the effective date of this AD.
(i) Ballscrew Integrity Test and Corrective Actions
If, during any inspection required by paragraph (h) of this AD,
it is determined that a THSA has Type II or Type III corrosion:
Before further flight, do a ballscrew integrity test, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-27-1214, including Appendix 01, dated February 23, 2012; and
the Accomplishment Instructions and the flowchart following the
Accomplishment Instructions of Goodrich Service Bulletin 47145-27-
16, dated November 7, 2011. If Type I corrosion is found, no action
is required by this paragraph.
(1) For THSAs having Type II or Type III corrosion and for which
the results of the ballscrew integrity test are not correct, as
specified in Airbus Service Bulletin A320-27-1214, including
Appendix 01, dated February 23, 2012: Before further flight, replace
the affected THSA with a new THSA, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1214,
including Appendix 01, dated February 23, 2012.
(2) For THSAs having Type III corrosion and on which the results
of the ballscrew integrity test are correct, as specified in Airbus
Service Bulletin A320 27-1214, including Appendix 01, dated February
23, 2012: Within 10 days after the most recent inspection, replace
the THSA with a new THSA, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1214, including
Appendix 01, dated February 23, 2012.
(3) For THSAs having Type II corrosion and on which the results
of the ballscrew integrity test are correct, as specified in Airbus
Service Bulletin A320 27-1214, including Appendix 01, dated February
23, 2012: Within 24 months or 5,000 flight cycles after the most
recent inspection, whichever occurs first, replace the THSA with a
new THSA, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1214, including Appendix 01, dated
February 23, 2012.
(j) Replacement of a THSA Is Not Terminating Action
Replacement of a THSA, as required by paragraph (i) of this AD,
does not constitute terminating action for the repetitive
inspections required by paragraph (h) of this AD.
(k) Reporting Requirement
If any corrosion type is found during any inspection required by
paragraph (h) of this AD, at the applicable time in paragraph (k)(1)
or (k)(2) of this AD, report the findings to Airbus, Customer
Services Engineering--SEEL5, Flight Control Systems A320 Family, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5
61 93 44 25. The report must include the information specified in
Appendix 01 of Airbus Service Bulletin A320-27-1214, dated February
23, 2012.
(1) If the inspection was done on or after the effective date of
this AD: Within 90 days after that inspection.
(2) If the inspection was done before the effective date of this
AD: Within 90 days after the effective date of this AD.
(l) Parts Installation Limitations
As of the effective date of this AD, no person may install a
THSA having P/N 47145-XXX (where XXX stands for any numerical
value), on any airplane, unless that THSA meets the criteria
specified in paragraphs (l)(1) and (l)(2) of this AD.
(1) The THSA has not accumulated 20 years since the THSA's first
flight, or the THSA has been inspected as required by paragraph (h)
of this AD and it has been determined that the THSA had Type I
corrosion (no corrosion) at the time of installation; and
(2) The THSA is thereafter inspected as required by paragraph
(h) of this AD, and any applicable actions specified in paragraph
(i) of this AD are accomplished.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-1405; fax (425) 227-1149. Information may
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing, and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(n) Special Flight Permits
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified (if the operator elects to do so), provided that, if
any THSA corrosion is found during any action required by paragraph
(h) of this AD, that corrosion is classified as Type I or Type II,
as defined in Goodrich Service Bulletin 47145-27-16, dated November
7, 2011.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
European Aviation Safety Agency Airworthiness Directive 2012-0175,
dated September 7, 2012, and the service information specified in
paragraphs (o)(1)(i) and (o)(1)(ii) of this AD, for related
information.
(i) Airbus Service Bulletin A320-27-1214, including Appendix 01,
dated February 23, 2012.
(ii) Goodrich Service Bulletin 47145-27-16, dated November 7,
2011.
(2) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com. For Goodrich service information
identified in this AD, contact Goodrich Corporation, Actuation
Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England;
telephone +44 (0) 1902 624938; fax +44 (0) 1902 788100; email
techpubs.wolverhampton@goodrich.com; Internet https://www.goodrich.com/TechPubs. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW.,
[[Page 12991]]
Renton, WA. For information on the availability of this material at
the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 11, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-04339 Filed 2-25-13; 8:45 am]
BILLING CODE 4910-13-P
