[Federal Register Volume 75, Number 215 (Monday, November 8, 2010)]
[Proposed Rules]
[Pages 68548-68551]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-28172]
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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).
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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 http://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: [email protected]; Internet http://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 http://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 http://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
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Airbus AOT-- Revision-- Dated--
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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.
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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]
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