Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes, 68548-68551 [2010-28172]
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Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules
emcdonald on DSK2BSOYB1PROD with PROPOSALS
(10) Reinstall the seat on the seat rail.
(i) Lift the seat into the airplane and place
on the seat rail.
(ii) Hold seat latch disengaged and slide
the seat aft and then forward to re-engage
rollers.
(iii) Lower vertical adjusting seats to a
comfortable height.
(iv) Reattach seat belt/shoulder harness to
the seat, if previously attached to the seat.
(v) Reinstall the seat stops.
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Wichita 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. Send information to ATTN: Gary
Park, Aerospace Engineer, ACE–118W,
Wichita Aircraft Certification Office (ACO),
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–4123;
fax: (316) 946–4107. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(h) AMOCs approved for AD 87–20–03 R2
are approved for this AD.
Related Information
(i) To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building Ground
VerDate Mar<15>2010
18:48 Nov 05, 2010
Jkt 223001
Floor, Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590, or on
the Internet at https://www.regulations.gov.
Issued in Kansas City, Missouri on
November 1, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–28158 Filed 11–5–10; 8:45 am]
BILLING CODE 4910–13–C
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1045; Directorate
Identifier 2010–NM–101–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
SUMMARY:
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products listed above that would
supersede an existing AD. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as:
One case of elevator servo-control
disconnection has been experienced on an
aeroplane of the A320 family. Investigation
has revealed that the failure occurred at the
servo-control rod eye-end.
Further to this finding, additional
inspections have revealed cracking at the
same location on a number of other servocontrol rod eye-ends. In several cases, both
actuators of the same elevator surface were
affected. The root cause of the cracking has
not yet been determined and tests are
ongoing.
A dual servo-control disconnection on the
same elevator could result in an uncontrolled
surface, the elevator surface being neither
actuated nor damped, which could lead to
reduced control of the aeroplane.
*
*
*
*
*
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
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Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules
We must receive comments on
this proposed AD by December 23,
2010.
DATES:
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 W12–40, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For 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; e-mail:
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
ADDRESSES:
emcdonald on DSK2BSOYB1PROD with PROPOSALS
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: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2141; 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–2010–1045; Directorate Identifier
VerDate Mar<15>2010
18:48 Nov 05, 2010
Jkt 223001
2010–NM–101–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
On August 7, 2009, we issued AD
2009–17–04, amendment 39–15995 (74
FR 41611, August 18, 2009). That AD
corresponds to the European Aviation
Safety Agency (EASA) AD 2008–0149,
dated August 5, 2008, and requires a
one-time inspection of the elevator
servo-control rod eye-ends to detect
cracking and in case of findings
replacement of the cracked rod eye-end
with a serviceable unit and readjusting
the elevator servo-control.
Since we issued AD 2009–17–04, the
EASA, which is the Technical Agent for
the Member States of the European
Community, has issued EASA
Airworthiness Directive 2010–0046,
dated March 19, 2010 (referred to after
this as ‘‘the MCAI’’), to supersede EASA
AD 2008–0149 to correct an unsafe
condition for the specified products.
The MCAI states:
One case of elevator servo-control
disconnection has been experienced on an
aeroplane of the A320 family. Investigation
has revealed that the failure occurred at the
servo-control rod eye-end.
Further to this finding, additional
inspections have revealed cracking at the
same location on a number of other servocontrol rod eye-ends. In several cases, both
actuators of the same elevator surface were
affected. The root cause of the cracking has
not yet been determined and tests are
ongoing.
A dual servo-control disconnection on the
same elevator could result in an uncontrolled
surface, the elevator surface being neither
actuated nor damped, which could lead to
reduced control of the aeroplane.
To address this unsafe condition, EASA
AD 2008–0149 [which corresponds to FAA
AD 2009–17–04] was issued to require a onetime inspection of the elevator servo-control
rod eye-ends for aeroplanes which have
accumulated more than 10,000 total Flight
Cycles (FC) since aeroplane first flight and,
in case of findings, the accomplishment of
corrective actions. As a result of this onetime inspection campaign, a significant
number of rod eye-ends have been found
cracked. In addition, some cracks have been
reported on rod eye-ends that had not yet
accumulated the 10,000 FC of the established
threshold.
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68549
For the reason described above, this AD
partially retains the initial inspection
requirement of EASA AD 2008–0149, which
is superseded, reduces the compliance time
of the initial inspections and introduces a
repetitive inspection program.
The corrective actions include
replacing any cracked rod eye-end with
a serviceable unit and re-adjusting the
elevator servo-control. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A320–27A1186, Revision 05,
including Appendices 1 through 6,
dated March 10, 2010. 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.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 770 products of U.S.
registry.
The actions that are required by AD
2009–17–04 and retained in this
proposed AD take about 13 work-hours
per product, at an average labor rate of
$85 per work hour. Based on these
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Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules
figures, the estimated cost of the
currently required actions is $1,105 per
product.
We estimate that it would take about
12 work-hours per product to comply
with the new 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
$785,400, or $1,020 per product.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
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); and
3. 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.
VerDate Mar<15>2010
18:48 Nov 05, 2010
Jkt 223001
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
removing amendment 39–15995 (74 FR
41611, August 18, 2009) and adding the
following new AD:
Airbus: Docket No. FAA–2010–1045;
Directorate Identifier 2010–NM–101–AD.
Comments Due Date
(a) We must receive comments by
December 23, 2010.
Affected ADs
(b) This AD supersedes AD 2009–17–04,
amendment 39–15995.
Applicability
(c) This AD applies to Airbus Model A318–
111, –112, –121, and –122; A319–111, –112,
–113, –114, –115, –131, –132, and –133;
A320–111, –211, –212, –214, –231, –232,
–233; and A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes; certificated
in any category; all manufacturer serial
numbers.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
One case of elevator servo-control
disconnection has been experienced on an
aeroplane of the A320 family. Investigation
has revealed that the failure occurred at the
servo-control rod eye-end.
Further to this finding, additional
inspections have revealed cracking at the
same location on a number of other servocontrol rod eye-ends. In several cases, both
actuators of the same elevator surface were
affected. The root cause of the cracking has
not yet been determined and tests are
ongoing.
A dual servo-control disconnection on the
same elevator could result in an uncontrolled
surface, the elevator surface being neither
actuated nor damped, which could lead to
reduced control of the aeroplane.
*
*
*
*
*
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Fmt 4702
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Restatement of Requirements of AD 2009–
17–04, With Reduced and Revised
Compliance Times and Revised Service
Information
(g) Unless already done, do the following
actions.
(1) At the applicable times specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD:
Inspect both the left-hand and right-hand
inboard elevator servo-control rod eye-ends
for cracking, in accordance with the
instructions of Airbus All Operators Telex
(AOT) A320–27A1186, Revision 04, dated
April 3, 2009; or the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–27A1186, Revision 05, dated
March 10, 2010. As of the effective date of
this AD, use only Airbus Mandatory Service
Bulletin A320–27A1186, Revision 05, dated
March 10, 2010.
(i) For airplanes that have accumulated
10,000 total flight cycles or more as of
September 22, 2009 (the effective date of AD
2009–17–04): At the later of the times
specified in paragraphs (g)(1)(i)(A) and
(g)(1)(i)(B) of this AD.
(A) Within 1,500 flight cycles after
September 22, 2009.
(B) Within 1,500 flight cycles after
accumulating 10,000 total flight cycles since
first flight of the airplane.
(ii) For airplanes that have accumulated
less than 10,000 total flight cycles as of
September 22, 2009: At the later of the times
specified in paragraphs (g)(1)(ii)(A) and
(g)(1)(ii)(B) of this AD.
(A) Before the accumulation of 5,000 total
flight cycles.
(B) Within 20 months after the effective
date of this AD but no later than before the
accumulation of 11,500 total flight cycles.
(2) At the applicable time specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
Inspect both the left-hand and right-hand
outboard elevator servo-control rod eye-ends
for cracking, in accordance with the
instructions of Airbus AOT A320–27A1186,
Revision 04, dated April 3, 2009; or the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–27A1186,
Revision 05, dated March 10, 2010. As of the
effective date of this AD, use only Airbus
Mandatory Service Bulletin A320–27A1186,
Revision 05, dated March 10, 2010.
(i) For airplanes that have accumulated
10,000 total flight cycles or more as of
September 22, 2009: At the later of the times
specified in paragraphs (g)(2)(i)(A) and
(g)(2)(i)(B) of this AD.
(A) Within 3,000 flight cycles after
September 22, 2009.
(B) Within 3,000 flight cycles after
accumulating 10,000 total flight cycles since
first flight of the airplane.
(ii) For airplanes that have accumulated
less than 10,000 total flight cycles as of
September 22, 2009: At the later of the times
specified in paragraphs (g)(2)(ii)(A) and
(g)(2)(ii)(B) of this AD.
(A) Before the accumulation of 7,500 total
flight cycles.
(B) Within 40 months after the effective
date of this AD but no later than before the
accumulation of 13,000 total flight cycles.
(3) Submit a report of the findings of the
inspection required by paragraphs (g)(1) and
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Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules
(g)(2) of this AD to Airbus in accordance with
the instructions of Airbus AOT A320–
27A1186, Revision 04, dated April 3, 2009;
or the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A320–
27A1186, Revision 05, dated March 10, 2010;
at the applicable time specified in paragraph
(g)(3)(i) or (g)(3)(ii) of this AD. As of the
effective date of this AD, use only Airbus
Mandatory Service Bulletin A320–27A1186,
Revision 05, dated March 10, 2010.
(i) If the inspection was done after
September 22, 2009: Submit the report
within 40 days after the inspection.
(ii) If the inspection was done before
September 22, 2009: Submit the report
within 40 days after September 22, 2009.
New Requirements of This AD
Actions
(h) Repeat the inspections of the left-hand
and right-hand inboard and outboard elevator
servo-control rod eye-ends for cracking as
required by paragraphs (g)(1) and (g)(2) of
this AD at the later of the times specified in
paragraph (h)(1) or (h)(2) of this AD. Repeat
the inspections thereafter at intervals not to
exceed 5,000 flight cycles.
(1) Within 5,000 flight cycles after the last
inspection required by paragraph (g)(1) or
(g)(2) of this AD as applicable.
(2) Within 6 months after the effective date
of this AD.
(i) If any cracking is found during any
inspection required by this AD, before further
flight, accomplish all applicable corrective
actions in accordance with the
Accomplishment Instructions and figures of
Airbus Mandatory Service Bulletin A320–
27A1186, Revision 05, dated March 10, 2010.
(j) As of the effective date of this AD, no
person may install on any airplane an
elevator servo-control rod eye-end unless it is
new or has been inspected in accordance
with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A320–
27A1186, Revision 05, dated March 10, 2010,
with no crack findings.
(k) Actions done before the effective date
of this AD, in accordance with the service
information specified in Table 1 of this AD
are acceptable for compliance with the
corresponding requirements of paragraphs
(g)(1) and (g)(2) of this AD.
TABLE 1—CREDIT SERVICE INFORMATION
Airbus AOT—
Revision—
A320–27A1186
A320–27A1186
A320–27A1186
A320–27A1186
A320–27A1186
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
.........................................................................................................................................................
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Other FAA AD Provisions
(l) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN:
Tim Dulin, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356; telephone
(425) 227–2141; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD. AMOCs approved
previously in accordance with AD 2009–17–
04, Amendment 39–15995, are approved as
AMOCs for the corresponding provisions of
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: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
VerDate Mar<15>2010
18:58 Nov 05, 2010
Jkt 223001
Related Information
(m) Refer to MCAI EASA Airworthiness
Directive 2010–0046, dated March 19, 2010;
and Airbus Mandatory Service Bulletin
A320–27A1186, Revision 05, dated March
10, 2010; for related information.
Issued in Renton, Washington, on October
23, 2010.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–28172 Filed 11–5–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2010–1028; Airspace
Docket No. 10–AGL–16]
Proposed Amendment of Class E
Airspace; Greensburg, IN
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
amend Class E airspace at Greensburg,
IN, to accommodate new Standard
Instrument Approach Procedures (SIAP)
SUMMARY:
PO 00000
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Original
01
02
03
04
Dated—
June 23, 2008.
August 11, 2008.
March 30, 2009.
April 1, 2009.
April 3, 2009.
for the Decatur County Memorial
Hospital Heliport. The FAA is taking
this action to enhance the safety and
management of Instrument Flight Rules
(IFR) operations at the heliport.
0901 UTC. Comments must be
received on or before December 23,
2010.
DATES:
Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001. You must
identify the docket number FAA–2010–
1028/Airspace Docket No. 10–AGL–16,
at the beginning of your comments. You
may also submit comments through the
Internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5527), is on the ground floor of the
building at the above address.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Scott Enander, Central Service Center,
Operations Support Group, Federal
Aviation Administration, Southwest
Region, 2601 Meacham Blvd., Fort
Worth, TX 76137; telephone: 817–321–
7716.
SUPPLEMENTARY INFORMATION:
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]]>Agencies
[Federal Register Volume 75, Number 215 (Monday, November 8, 2010)]
[Proposed Rules]
[Pages 68548-68551]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-28172]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1045; Directorate Identifier 2010-NM-101-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as:
One case of elevator servo-control disconnection has been
experienced on an aeroplane of the A320 family. Investigation has
revealed that the failure occurred at the servo-control rod eye-end.
Further to this finding, additional inspections have revealed
cracking at the same location on a number of other servo-control rod
eye-ends. In several cases, both actuators of the same elevator
surface were affected. The root cause of the cracking has not yet
been determined and tests are ongoing.
A dual servo-control disconnection on the same elevator could
result in an uncontrolled surface, the elevator surface being
neither actuated nor damped, which could lead to reduced control of
the aeroplane.
* * * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
[[Page 68549]]
DATES: We must receive comments on this proposed AD by December 23,
2010.
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For 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; e-mail: account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; 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-2010-1045;
Directorate Identifier 2010-NM-101-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
On August 7, 2009, we issued AD 2009-17-04, amendment 39-15995 (74
FR 41611, August 18, 2009). That AD corresponds to the European
Aviation Safety Agency (EASA) AD 2008-0149, dated August 5, 2008, and
requires a one-time inspection of the elevator servo-control rod eye-
ends to detect cracking and in case of findings replacement of the
cracked rod eye-end with a serviceable unit and readjusting the
elevator servo-control.
Since we issued AD 2009-17-04, the EASA, which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2010-0046, dated March 19, 2010 (referred to
after this as ``the MCAI''), to supersede EASA AD 2008-0149 to correct
an unsafe condition for the specified products. The MCAI states:
One case of elevator servo-control disconnection has been
experienced on an aeroplane of the A320 family. Investigation has
revealed that the failure occurred at the servo-control rod eye-end.
Further to this finding, additional inspections have revealed
cracking at the same location on a number of other servo-control rod
eye-ends. In several cases, both actuators of the same elevator
surface were affected. The root cause of the cracking has not yet
been determined and tests are ongoing.
A dual servo-control disconnection on the same elevator could
result in an uncontrolled surface, the elevator surface being
neither actuated nor damped, which could lead to reduced control of
the aeroplane.
To address this unsafe condition, EASA AD 2008-0149 [which
corresponds to FAA AD 2009-17-04] was issued to require a one-time
inspection of the elevator servo-control rod eye-ends for aeroplanes
which have accumulated more than 10,000 total Flight Cycles (FC)
since aeroplane first flight and, in case of findings, the
accomplishment of corrective actions. As a result of this one-time
inspection campaign, a significant number of rod eye-ends have been
found cracked. In addition, some cracks have been reported on rod
eye-ends that had not yet accumulated the 10,000 FC of the
established threshold.
For the reason described above, this AD partially retains the
initial inspection requirement of EASA AD 2008-0149, which is
superseded, reduces the compliance time of the initial inspections
and introduces a repetitive inspection program.
The corrective actions include replacing any cracked rod eye-end
with a serviceable unit and re-adjusting the elevator servo-control.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-27A1186, Revision
05, including Appendices 1 through 6, dated March 10, 2010. 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.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 770 products of U.S. registry.
The actions that are required by AD 2009-17-04 and retained in this
proposed AD take about 13 work-hours per product, at an average labor
rate of $85 per work hour. Based on these
[[Page 68550]]
figures, the estimated cost of the currently required actions is $1,105
per product.
We estimate that it would take about 12 work-hours per product to
comply with the new 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 $785,400, or $1,020
per product.
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); and
3. 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
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]
2. The FAA amends Sec. 39.13 by removing amendment 39-15995 (74 FR
41611, August 18, 2009) and adding the following new AD:
Airbus: Docket No. FAA-2010-1045; Directorate Identifier 2010-NM-
101-AD.
Comments Due Date
(a) We must receive comments by December 23, 2010.
Affected ADs
(b) This AD supersedes AD 2009-17-04, amendment 39-15995.
Applicability
(c) This AD applies to Airbus Model A318-111, -112, -121, and -
122; A319-111, -112, -113, -114, -115, -131, -132, and -133; A320-
111, -211, -212, -214, -231, -232, -233; and A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes; certificated in any
category; all manufacturer serial numbers.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
One case of elevator servo-control disconnection has been
experienced on an aeroplane of the A320 family. Investigation has
revealed that the failure occurred at the servo-control rod eye-end.
Further to this finding, additional inspections have revealed
cracking at the same location on a number of other servo-control rod
eye-ends. In several cases, both actuators of the same elevator
surface were affected. The root cause of the cracking has not yet
been determined and tests are ongoing.
A dual servo-control disconnection on the same elevator could
result in an uncontrolled surface, the elevator surface being
neither actuated nor damped, which could lead to reduced control of
the aeroplane.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2009-17-04, With Reduced and Revised
Compliance Times and Revised Service Information
(g) Unless already done, do the following actions.
(1) At the applicable times specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD: Inspect both the left-hand and right-hand
inboard elevator servo-control rod eye-ends for cracking, in
accordance with the instructions of Airbus All Operators Telex (AOT)
A320-27A1186, Revision 04, dated April 3, 2009; or the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-27A1186, Revision 05, dated March 10, 2010. As of the effective
date of this AD, use only Airbus Mandatory Service Bulletin A320-
27A1186, Revision 05, dated March 10, 2010.
(i) For airplanes that have accumulated 10,000 total flight
cycles or more as of September 22, 2009 (the effective date of AD
2009-17-04): At the later of the times specified in paragraphs
(g)(1)(i)(A) and (g)(1)(i)(B) of this AD.
(A) Within 1,500 flight cycles after September 22, 2009.
(B) Within 1,500 flight cycles after accumulating 10,000 total
flight cycles since first flight of the airplane.
(ii) For airplanes that have accumulated less than 10,000 total
flight cycles as of September 22, 2009: At the later of the times
specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
(A) Before the accumulation of 5,000 total flight cycles.
(B) Within 20 months after the effective date of this AD but no
later than before the accumulation of 11,500 total flight cycles.
(2) At the applicable time specified in paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD: Inspect both the left-hand and right-hand
outboard elevator servo-control rod eye-ends for cracking, in
accordance with the instructions of Airbus AOT A320-27A1186,
Revision 04, dated April 3, 2009; or the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A320-27A1186, Revision 05,
dated March 10, 2010. As of the effective date of this AD, use only
Airbus Mandatory Service Bulletin A320-27A1186, Revision 05, dated
March 10, 2010.
(i) For airplanes that have accumulated 10,000 total flight
cycles or more as of September 22, 2009: At the later of the times
specified in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of this AD.
(A) Within 3,000 flight cycles after September 22, 2009.
(B) Within 3,000 flight cycles after accumulating 10,000 total
flight cycles since first flight of the airplane.
(ii) For airplanes that have accumulated less than 10,000 total
flight cycles as of September 22, 2009: At the later of the times
specified in paragraphs (g)(2)(ii)(A) and (g)(2)(ii)(B) of this AD.
(A) Before the accumulation of 7,500 total flight cycles.
(B) Within 40 months after the effective date of this AD but no
later than before the accumulation of 13,000 total flight cycles.
(3) Submit a report of the findings of the inspection required
by paragraphs (g)(1) and
[[Page 68551]]
(g)(2) of this AD to Airbus in accordance with the instructions of
Airbus AOT A320-27A1186, Revision 04, dated April 3, 2009; or the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-27A1186, Revision 05, dated March 10, 2010; at the applicable
time specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD. As
of the effective date of this AD, use only Airbus Mandatory Service
Bulletin A320-27A1186, Revision 05, dated March 10, 2010.
(i) If the inspection was done after September 22, 2009: Submit
the report within 40 days after the inspection.
(ii) If the inspection was done before September 22, 2009:
Submit the report within 40 days after September 22, 2009.
New Requirements of This AD
Actions
(h) Repeat the inspections of the left-hand and right-hand
inboard and outboard elevator servo-control rod eye-ends for
cracking as required by paragraphs (g)(1) and (g)(2) of this AD at
the later of the times specified in paragraph (h)(1) or (h)(2) of
this AD. Repeat the inspections thereafter at intervals not to
exceed 5,000 flight cycles.
(1) Within 5,000 flight cycles after the last inspection
required by paragraph (g)(1) or (g)(2) of this AD as applicable.
(2) Within 6 months after the effective date of this AD.
(i) If any cracking is found during any inspection required by
this AD, before further flight, accomplish all applicable corrective
actions in accordance with the Accomplishment Instructions and
figures of Airbus Mandatory Service Bulletin A320-27A1186, Revision
05, dated March 10, 2010.
(j) As of the effective date of this AD, no person may install
on any airplane an elevator servo-control rod eye-end unless it is
new or has been inspected in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-27A1186,
Revision 05, dated March 10, 2010, with no crack findings.
(k) Actions done before the effective date of this AD, in
accordance with the service information specified in Table 1 of this
AD are acceptable for compliance with the corresponding requirements
of paragraphs (g)(1) and (g)(2) of this AD.
Table 1--Credit Service Information
------------------------------------------------------------------------
Airbus AOT-- Revision-- Dated--
------------------------------------------------------------------------
A320-27A1186.................... Original June 23, 2008.
A320-27A1186.................... 01 August 11, 2008.
A320-27A1186.................... 02 March 30, 2009.
A320-27A1186.................... 03 April 1, 2009.
A320-27A1186.................... 04 April 3, 2009.
------------------------------------------------------------------------
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(l) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, Transport Airplane Directorate, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Tim
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD. AMOCs approved
previously in accordance with AD 2009-17-04, Amendment 39-15995, are
approved as AMOCs for the corresponding provisions of 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: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(m) Refer to MCAI EASA Airworthiness Directive 2010-0046, dated
March 19, 2010; and Airbus Mandatory Service Bulletin A320-27A1186,
Revision 05, dated March 10, 2010; for related information.
Issued in Renton, Washington, on October 23, 2010.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-28172 Filed 11-5-10; 8:45 am]
BILLING CODE 4910-13-P
