[Federal Register Volume 77, Number 183 (Thursday, September 20, 2012)]
[Proposed Rules]
[Pages 58327-58330]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-23217]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0995; Directorate Identifier 2012-NM-056-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 A330-300 series airplanes and Model A340-200 and -300
series airplanes. This proposed AD was prompted by reports that, during
a flight test, several spoiler servo-controls (SSCs) did not remain
locked in the retracted position (hydraulic locking function) after
manual depressurization of the corresponding hydraulic circuit. Loss of
that locking function--which is ensured by a blocking valve--was caused
by an internal leak from a sheared seal on the blocking valve. This
proposed AD would require inspecting to determine if certain SSCs are
installed, performing an operational test of any affected SSC, and
replacing if necessary. We are proposing this AD to prevent loss of the
hydraulic locking function during take-off and go-around phases, which,
in combination with malfunction of one engine, could result in reduced
controllability of the airplane.
DATES: We must receive comments on this proposed AD by November 5,
2012.
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 W12-140, 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 SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email [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: Vladimir Ulyanov, Aerospace Engineer,
[[Page 58328]]
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0995;
Directorate Identifier 2012-NM-056-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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0009, dated January 13, 2012 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Two operators have reported that several spoilers did not remain
locked in the retracted position (lifted up without order) after
manual depressurization of the corresponding hydraulic circuit
during flight test.
Subsequent checks on ground confirmed that, for each affected
spoiler surface, the spoiler was fitted with one MZ-type Spoiler
Servo Control (SSC) (Part Number (P/N) MZ4339390-12 or P/N
MZ4306000-12).
The results of the investigations on the affected SSCs, done by
the supplier, revealed that the loss of the hydraulic locking
function--which is ensured by a blocking valve--was due to an
internal leakage caused by a sheared seal. This seal is installed at
the left end of the blocking valve.
During the on-wing modification of the maintenance cover,
blocking valve movement may have damaged the seal on the outer
diameter of the blocking valve assembly, causing the loss of the
hydraulic locking function.
This condition, if not detected and corrected, if occurring
during take-off and go-around phases in combination with one engine
inoperative, could jeopardize the aeroplane safe flight.
For the reasons described above, this [EASA] AD requires the
identification of the installed SSCs, to perform an operational test
of the hydraulic locking function of the affected SSCs and to
accomplish the applicable corrective actions if any discrepancy is
detected during the operational test. This [EASA] AD also requires
reporting operational test results to Airbus.
You may obtain further information by examining the MCAI in the AD
docket.
Other Related Rulemaking
On August 26, 2009, the FAA issued AD 2009-18-20, Amendment 39-
16017 (74 FR 46313, September 9, 2009), applicable to certain Airbus
Model A330-300, A340-200, and A340-300 series airplanes. That AD
requires identifying the part number of spoiler servo-controls
installed on the airplane at all positions to determine the number of
affected hydraulic circuits, and modifying affected spoiler servo-
controls. The actions required by that AD are intended to prevent loss
of the three hydraulic systems, which could result in reduced
controllability of the airplane.
Relevant Service Information
Airbus has issued All Operators Telex (AOT) A330-27A3185 and AOT
A340-27A4181, both dated January 4, 2012. 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
Unlike the procedures recommended in Airbus AOTs A330-27A3185 and
A340-27A4181, both dated January 4, 2012, this proposed AD would not
permit further flight after a faulty SSC is detected on the green or
yellow hydraulic line. Instead, this proposed AD would require
replacing the SSC with a new or serviceable SSC before further flight.
We find that, to achieve an adequate level of safety for the affected
fleet, damaged SSCs must be replaced before further flight.
Although the MCAI mandates performing the operational test within
90 days after the effective date of the AD, we have determined that the
operational test should be performed within 90 days after
identification of the part.
These differences have been coordinated with EASA.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 61 products of U.S. registry. We also estimate that
it would take up to 7 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 $36,295, or $595 per product.
In addition, we estimate that any necessary follow-on actions would
take about 36 work-hours and require parts costing $34,928, for a cost
of $37,988 per affected SSC. 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 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:
[[Page 58329]]
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
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 adding the following new AD:
Airbus: Docket No. FAA-2012-0995; Directorate Identifier 2012-NM-
056-AD.
(a) Comments Due Date
We must receive comments by November 5, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A330-301, -302, -303, -321,
-322, -323, -341, -342, and -343 airplanes; and Model A340-211, -
212, -213, -311, -312, and -313 airplanes; certificated in any
category; all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27: Flight
controls.
(e) Reason
This AD was prompted by reports that, during flight test,
several spoiler servo-controls (SSCs) did not remain locked in the
retracted position (hydraulic locking function) after manual
depressurization of the corresponding hydraulic circuit. Loss of
that locking function--which is ensured by a blocking valve--was
caused by an internal leak from a sheared seal on the blocking
valve. We are issuing this AD to prevent loss of the hydraulic
locking function during take-off and go-around phases, which, in
combination with malfunction of one engine, could result in reduced
controllability 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) Actions
Within 90 days after the effective date of this AD: Inspect to
determine the part number (P/N) of all SSCs installed, in accordance
with Airbus All Operators Telex (AOT) A330-27A3185 (for Model A330-
300 series airplanes) or A340-27A4181 (for Model A340-200 and -300
series airplanes), both dated January 4, 2012. A review of airplane
maintenance records is acceptable in lieu of the inspection to
identify the part number of the SSC installed, provided that part
number can be conclusively determined from that review.
(1) For any SSC having P/N MZ4339390-12 or P/N MZ4306000-12 (MZ-
type): Within 90 days after identification of the part, perform an
operational test of the hydraulic locking function at each position
fitted with an MZ-type SSC, in accordance with the Accomplishment
Instructions of Airbus AOT A330-27A3185 (for Model A330-300 series
airplanes) or A340-27A4181 (for Model A340-200 and -300 series
airplanes), both dated January 4, 2012.
(2) If any discrepancy is detected during the operational test
specified in paragraph (g)(1) of this AD, or if the test fails,
before further flight, replace the affected SSC with a new or
serviceable SSC, in accordance with Airbus AOT A330-27A3185 (for
Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200
and -300 series airplanes), both dated January 4, 2012.
(h) Reporting to Airbus
Submit a report of the findings of the operational test required
by paragraph (g)(1) of this AD (both positive and negative) to
Airbus, Customer Services, Engineering and Technical Support, 1 Rond
Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: Daniel
Lopez-Fernandez, SEEL6; fax: (+33) 5 61 93 04 52; email:
[email protected]; at the applicable time specified
in paragraph (h)(1) or (h)(2) of this AD.
(1) If the test was done on or after the effective date of this
AD: Submit the report within 30 days after the test.
(2) If the test was done before the effective date of this AD:
Submit the report within 30 days after the effective date of this
AD.
(i) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Information may be emailed to: [email protected].
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.
(j) Related Information
(1) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2012-0009, dated January 13, 2012, and the
service information specified in paragraph (j)(1)(i) or (j)(1)(ii)
of this AD, for related information.
(i) Airbus AOT A330-27A3185, dated January 4, 2012.
(ii) Airbus AOT A340-27A4181, dated January 4, 2012.
(2) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email [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, WA. For information on
the availability of this material at the FAA, call 425-227-1221.
[[Page 58330]]
Issued in Renton, Washington, on September 11, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-23217 Filed 9-19-12; 8:45 am]
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