Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes, 16689-16696 [2010-7461]
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16689
Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules
TABLE 2—CREDIT SERVICE INFORMATION
Airbus AOT—
A300–55A6047
A300–55A6047
A310–55A2048
A310–55A2048
Revision—
............................................................
............................................................
............................................................
............................................................
(k) For rudders on which temporary
restoration with resin or permanent vacuum
loss hole restoration has been done in
accordance with the applicable service
bulletin in Table 2 of this AD, as required in
paragraph (g)(9) or (h)(9) of this AD, before
the effective date of this AD: Within 4,500
flight cycles from the restoration date, do an
ultrasonic inspection for defects, including
debonding of the reinforced area, in
accordance with Airbus AOT A310–55A2048
or AOT A300–55A6047, both Revision 02,
both dated October 12, 2009, as applicable.
If any defect is found, before further flight,
contact Airbus for repair instructions and do
the repair.
(l) After the effective date of this AD, no
person may install any rudder listed in Table
1 of this AD on any airplane, unless the
rudder has been inspected and all applicable
corrective actions have been done in
accordance with paragraph (g) or (h) of this
AD.
FAA AD Differences
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
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approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(n) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2010–0002, dated January 5, 2010;
and Airbus AOT A310–55A2048, Revision
02, dated October 12, 2009, or Airbus AOT
A300–55A6047, Revision 02, dated October
12, 2009; for related information.
Issued in Renton, Washington, on March
25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–7459 Filed 4–1–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
Other FAA AD Provisions
(m) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; 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.
(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
VerDate Nov<24>2008
Original ........................................................................
01 ................................................................................
Original ........................................................................
01 ................................................................................
Federal Aviation Administration
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
[Docket No. FAA–2010–0279; Directorate
Identifier 2009–NM–148–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. 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: Surface defects were
visually detected on the rudder of one
A319 and one A321 in-service
aeroplane. Investigation has determined
that the defects reported on both
rudders corresponded to areas that had
been reworked in production. The
investigation confirmed that the defects
were a result of de-bonding between the
skin and honeycomb core. An extended
de-bonding, if not detected and
corrected, may degrade the structural
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Dated—
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May 11, 2009.
July 8, 2009.
May 11, 2009.
July 8, 2009.
integrity of the rudder. The loss of the
rudder leads to degradation of the
handling qualities and reduces the
controllability of the aeroplane.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by May 17, 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; fax +33 5 61 93 44 51;
e-mail: account.airwortheas@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
or 425–227–1152.
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.
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Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules
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–2010–0279; Directorate Identifier
2009–NM–148–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 have lengthened the 30-day
comment period for proposed ADs that
address MCAI originated by aviation
authorities of other countries to provide
adequate time for interested parties to
submit comments. The comment period
for these proposed ADs is now typically
45 days, which is consistent with the
comment period for domestic transport
ADs.
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.
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
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 2009–0141,
dated July 2, 2009 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Surface defects were visually detected on
the rudder of one A319 and one A321 inservice aeroplane.
Investigation has determined that the
defects reported on both rudders
corresponded to areas that had been
reworked in production. The investigation
confirmed that the defects were a result of
de-bonding between the skin and honeycomb
core.
An extended de-bonding, if not detected
and corrected, may degrade the structural
integrity of the rudder. The loss of the rudder
leads to degradation of the handling qualities
and reduces the controllability of the
aeroplane.
This AD requires inspections of specific
areas and, when necessary, the application of
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corrective actions for those rudders where
production reworks have been identified.
Inspections include vacuum loss
inspections for de-bonding of the
rudders in reinforced areas and other
areas (splice/lower rib/upper edge/
leading edge/other specified locations),
and elasticity laminate checks for debonding of the rudders in the trailing
edge area and other areas (splice/lower
rib/upper edge/leading edge/other
specified locations). Corrective actions
include contacting Airbus for further
instruction and doing the repair. You
may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued All Operators Telex
A320–55A1038, Revision 02, dated
September 28, 2009. 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 155 products of U.S.
registry. We also estimate that it would
take about 11 work-hours per product to
comply with the basic requirements of
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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
$144,925, or $935 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:
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Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules
PART 39—AIRWORTHINESS
DIRECTIVES
Airbus: Docket No. FAA–2010–0279;
Directorate Identifier 2009–NM–148–AD.
1. The authority citation for part 39
continues to read as follows:
Comments Due Date
(a) We must receive comments by May 17,
2010.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
2. The FAA amends § 39.13 by adding
the following new AD:
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Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
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16691
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category, all manufacturer
serial numbers (S/Ns), if equipped with
carbon fiber reinforced plastic rudders
having part numbers (P/Ns) and S/Ns as
listed in Table 1 of this AD.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
Note 1: Only rudder P/N D554 71000 010
00 having affected rudder S/Ns TS–1069 and
TS–1090 and rudder P/N D554 71000 012 00
having affected rudder S/N TS–1227, have a
core density of 24 kilogram (kg)/meters cubed
(m3).
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Subject
(d) Air Transport Association (ATA) of
America Code 55: Stabilizers.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Surface defects were visually detected on
the rudder of one A319 and one A321 inservice aeroplane.
Investigation has determined that the
defects reported on both rudders
corresponded to areas that had been
reworked in production. The investigation
confirmed that the defects were a result of
de-bonding between the skin and honeycomb
core.
An extended de-bonding, if not detected
and corrected, may degrade the structural
integrity of the rudder. The loss of the rudder
leads to degradation of the handling qualities
and reduces the controllability of the
aeroplane.
This AD requires inspections of specific
areas and, when necessary, the application of
corrective actions for those rudders where
production reworks have been identified.
Inspections include vacuum loss
inspections for de-bonding of the rudders in
reinforced areas and other areas (splice/lower
rib/upper edge/leading edge/other specified
locations), and elasticity laminate checks for
de-bonding of the rudders in the trailing edge
area and other areas (splice/lower rib/upper
edge/leading edge/other specified locations).
Corrective actions include contacting Airbus
for further instruction and doing the repair.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
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the compliance times specified, unless the
actions have already been done.
Actions
(g) For rudders with a honeycomb core
density of 24 kg/m3 (rudder P/N D554 71000
010 00 having affected rudder S/Ns TS–1069
and TS–1090 and rudder P/N D554 71000
012 00 having affected rudder S/N TS–1227),
do the actions specified in paragraphs (g)(1),
(g)(2), (g)(3), and (g)(4) of this AD, in
accordance with Airbus All Operators Telex
(AOT) A320–55A1038, Revision 02, dated
September 28, 2009, for the locations defined
in the AOT.
(1) Within 200 days after the effective date
of this AD, perform a vacuum loss inspection
on the rudder reinforced area.
(2) Within 20 months after the effective
date of this AD, perform an elasticity
laminate checker inspection on the rudder
trailing edge area. Repeat the inspection two
times, at intervals not to exceed 4,500 flight
cycles but not sooner than 4,000 flight cycles
after the last inspection.
(3) Within 200 days after the effective date
of this AD, perform an elasticity laminate
checker inspection of the other areas (splice/
lower rib/upper edge/leading edge/and other
specified locations). Repeat the inspection at
intervals not to exceed 1,500 flight cycles or
200 days, whichever comes first.
(4) Within 20 months after the effective
date of this AD, perform a vacuum loss
inspection of the other areas (splice/lower
rib/upper edge/leading edge/other specified
locations). Accomplishment of the action
specified in paragraph (g)(4) of this AD
terminates the requirements of paragraph
(g)(3) of this AD.
(h) For rudders that do not have a
honeycomb core density of 24 kg/m3 (all
rudders identified in Table 1 of this AD,
except: Rudder P/N D554 71000 010 00
having affected rudder S/Ns TS–1069 and
TS–1090 and rudder P/N D554 71000 012 00
having affected rudder S/N TS–1227), do the
actions specified in paragraphs (h)(1), (h)(2),
(h)(3), and (h)(4) of this AD, in accordance
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16695
with Airbus AOT A320–55A1038, Revision
02, dated September 28, 2009, for the
locations defined in the AOT. For this AD,
‘‘reference date’’ is defined as the effective
date of this AD or the date when the rudder
will accumulate 20,000 total flight cycles
from its first installation on an airplane,
whichever occurs later.
(1) Within 200 days after the reference
date, perform a vacuum loss inspection on
the rudder reinforced area.
(2) Within 20 months after the reference
date, perform an elasticity laminate checker
inspection on the rudder trailing edge area.
Repeat the inspection two times at intervals
not to exceed 4,500 flight cycles but not
sooner than 4,000 flight cycles after the last
inspection.
(3) Within 200 days after the reference
date, perform an elasticity laminate checker
inspection of the other areas (splice/lower
rib/upper edge/leading edge/other specified
locations). Repeat the inspection at intervals
not to exceed 1,500 flight cycles or 200 days,
whichever comes first.
(4) Within 20 months after the reference
date, perform a vacuum loss inspection of the
other areas (splice/lower rib/upper edge/
leading edge/other specified locations).
Accomplishment of the actions specified in
this paragraph terminates the requirements of
paragraph (h)(3) of this AD.
(i) In case of de-bonding found during any
inspection required by paragraph (g) or (h) of
this AD, before further flight, contact Airbus
for further instructions and apply the
associated instructions and corrective actions
in accordance with the approved data
provided.
(j) At the applicable time specified in
paragraph (j)(1) or (j)(2) of this AD, submit a
report of the findings (both positive and
negative), of each inspection required by
paragraphs (g) and (h) of this AD. The report
must include the inspection results, as
specified in Airbus Technical Disposition
TD/K4/S2/27086/2009, Issue E, dated
September 17, 2009. For positive findings,
submit the report to the Manager, Seer1/
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Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules
Seer2/Seer3 Customer Services; fax +33 (0)5
61 93 28 73; e-mail
region1.structurerepairsupport@airbus.com,
region2.structurerepairsupport@airbus.com,
or
region3.structurerepairsupport@airbus.com.
For negative findings, submit the report to
Nicolas Seynaeve, Sees1, Customer Services;
telephone +33 (0)5 61 93 34 38; fax +33 (0)5
61 93 36 14; e-mail
nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after the
effective date of this AD: Submit the report
within 30 days after the inspection.
(2) For any inspection done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(k) All rudders that have passed the
inspection specified in paragraphs (g)(1),
(g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3), and
(h)(4) of this AD, before the effective date of
this AD in accordance with Airbus AOT
A320–55A1038, dated April 22, 2009; AOT
A320–55A1038, Revision 01, dated June 10,
2009; or Airbus Technical Disposition TD/
K4/S2/27051/2009, Issue B, dated February
25, 2009; are compliant with this AD for the
areas inspected; except additional areas
requiring inspection, as defined in Section 0,
‘‘Reason for Revision,’’ of Airbus AOT A320–
55A1038, Revision 02, dated September 28,
2009, must be inspected as specified in
paragraph (g) or (h) of this AD. For all areas,
the repetitive inspections required by
paragraph (g) or (h) of this AD remain
applicable.
(l) After the effective date of this AD, no
rudder listed in Table 1 of this AD may be
installed on any airplane, unless the rudder
is in compliance with the requirements of
this AD.
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
(n) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2009–
0141, dated July 2, 2009; Airbus All
Operators Telex A320–55A1038, Revision 02,
dated September 28, 2009; and Airbus
Technical Disposition TD/K4/S2/27086/
2009, Issue E, dated September 17, 2009; for
related information.
Issued in Renton, Washington, on March
25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–7461 Filed 4–1–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0278; Directorate
Identifier 2009–NM–255–AD]
RIN 2120–AA64
FAA AD Differences
Airworthiness Directives; Airbus Model
A330–223, –321, –322, and –323
Airplanes
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(m) 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.
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.
(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
VerDate Nov<24>2008
14:33 Apr 01, 2010
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Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. 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: During accomplishment of
Damage Tolerant—Airworthiness
Limitation Item task 712106–01–01 from
A330 ALS Part 2, an A330 operator
found a Fluorescent Penetrant
Inspection (FPI) indication in the head
of the shank filet radius in one of the
Pratt & Whitney (PW) forward (FWD)
engine mount pylon bolts. Dual-bolt
fractures could lead to inability for
mount assembly to sustain loads which
may lead to an engine mount failure and
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
consequently to engine separation from
the aeroplane during flight, which
would constitute an unsafe condition.
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by May 17, 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 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; e-mail
airworthiness.A330–A340@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:
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.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
E:\FR\FM\02APP1.SGM
02APP1
]]>Agencies
[Federal Register Volume 75, Number 63 (Friday, April 2, 2010)]
[Proposed Rules]
[Pages 16689-16696]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7461]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0279; Directorate Identifier 2009-NM-148-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. 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: Surface defects were visually detected on the rudder of
one A319 and one A321 in-service aeroplane. Investigation has
determined that the defects reported on both rudders corresponded to
areas that had been reworked in production. The investigation confirmed
that the defects were a result of de-bonding between the skin and
honeycomb core. An extended de-bonding, if not detected and corrected,
may degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces the
controllability of the aeroplane.
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by May 17, 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; 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 or
425-227-1152.
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.
[[Page 16690]]
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-2010-0279;
Directorate Identifier 2009-NM-148-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 have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide adequate time for interested parties to submit comments. The
comment period for these proposed ADs is now typically 45 days, which
is consistent with the comment period for domestic transport ADs.
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 2009-0141, dated July 2, 2009 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Surface defects were visually detected on the rudder of one A319
and one A321 in-service aeroplane.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the defects were a result of de-
bonding between the skin and honeycomb core.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
This AD requires inspections of specific areas and, when
necessary, the application of corrective actions for those rudders
where production reworks have been identified.
Inspections include vacuum loss inspections for de-bonding of the
rudders in reinforced areas and other areas (splice/lower rib/upper
edge/leading edge/other specified locations), and elasticity laminate
checks for de-bonding of the rudders in the trailing edge area and
other areas (splice/lower rib/upper edge/leading edge/other specified
locations). Corrective actions include contacting Airbus for further
instruction and doing the repair. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued All Operators Telex A320-55A1038, Revision 02,
dated September 28, 2009. 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 155 products of U.S. registry. We also estimate that
it would take about 11 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 $144,925, or $935 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:
[[Page 16691]]
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-2010-0279; Directorate Identifier 2009-NM-
148-AD.
Comments Due Date
(a) We must receive comments by May 17, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category, all
manufacturer serial numbers (S/Ns), if equipped with carbon fiber
reinforced plastic rudders having part numbers (P/Ns) and S/Ns as
listed in Table 1 of this AD.
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Note 1: Only rudder P/N D554 71000 010 00 having affected rudder
S/Ns TS-1069 and TS-1090 and rudder P/N D554 71000 012 00 having
affected rudder S/N TS-1227, have a core density of 24 kilogram
(kg)/meters cubed (m[sup3]).
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Surface defects were visually detected on the rudder of one A319
and one A321 in-service aeroplane.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the defects were a result of de-
bonding between the skin and honeycomb core.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
This AD requires inspections of specific areas and, when
necessary, the application of corrective actions for those rudders
where production reworks have been identified.
Inspections include vacuum loss inspections for de-bonding of
the rudders in reinforced areas and other areas (splice/lower rib/
upper edge/leading edge/other specified locations), and elasticity
laminate checks for de-bonding of the rudders in the trailing edge
area and other areas (splice/lower rib/upper edge/leading edge/other
specified locations). Corrective actions include contacting Airbus
for further instruction and doing the repair.
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.
Actions
(g) For rudders with a honeycomb core density of 24 kg/m[sup3]
(rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069
and TS-1090 and rudder P/N D554 71000 012 00 having affected rudder
S/N TS-1227), do the actions specified in paragraphs (g)(1), (g)(2),
(g)(3), and (g)(4) of this AD, in accordance with Airbus All
Operators Telex (AOT) A320-55A1038, Revision 02, dated September 28,
2009, for the locations defined in the AOT.
(1) Within 200 days after the effective date of this AD, perform
a vacuum loss inspection on the rudder reinforced area.
(2) Within 20 months after the effective date of this AD,
perform an elasticity laminate checker inspection on the rudder
trailing edge area. Repeat the inspection two times, at intervals
not to exceed 4,500 flight cycles but not sooner than 4,000 flight
cycles after the last inspection.
(3) Within 200 days after the effective date of this AD, perform
an elasticity laminate checker inspection of the other areas
(splice/lower rib/upper edge/leading edge/and other specified
locations). Repeat the inspection at intervals not to exceed 1,500
flight cycles or 200 days, whichever comes first.
(4) Within 20 months after the effective date of this AD,
perform a vacuum loss inspection of the other areas (splice/lower
rib/upper edge/leading edge/other specified locations).
Accomplishment of the action specified in paragraph (g)(4) of this
AD terminates the requirements of paragraph (g)(3) of this AD.
(h) For rudders that do not have a honeycomb core density of 24
kg/m[sup3] (all rudders identified in Table 1 of this AD, except:
Rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069 and
TS-1090 and rudder P/N D554 71000 012 00 having affected rudder S/N
TS-1227), do the actions specified in paragraphs (h)(1), (h)(2),
(h)(3), and (h)(4) of this AD, in accordance with Airbus AOT A320-
55A1038, Revision 02, dated September 28, 2009, for the locations
defined in the AOT. For this AD, ``reference date'' is defined as
the effective date of this AD or the date when the rudder will
accumulate 20,000 total flight cycles from its first installation on
an airplane, whichever occurs later.
(1) Within 200 days after the reference date, perform a vacuum
loss inspection on the rudder reinforced area.
(2) Within 20 months after the reference date, perform an
elasticity laminate checker inspection on the rudder trailing edge
area. Repeat the inspection two times at intervals not to exceed
4,500 flight cycles but not sooner than 4,000 flight cycles after
the last inspection.
(3) Within 200 days after the reference date, perform an
elasticity laminate checker inspection of the other areas (splice/
lower rib/upper edge/leading edge/other specified locations). Repeat
the inspection at intervals not to exceed 1,500 flight cycles or 200
days, whichever comes first.
(4) Within 20 months after the reference date, perform a vacuum
loss inspection of the other areas (splice/lower rib/upper edge/
leading edge/other specified locations). Accomplishment of the
actions specified in this paragraph terminates the requirements of
paragraph (h)(3) of this AD.
(i) In case of de-bonding found during any inspection required
by paragraph (g) or (h) of this AD, before further flight, contact
Airbus for further instructions and apply the associated
instructions and corrective actions in accordance with the approved
data provided.
(j) At the applicable time specified in paragraph (j)(1) or
(j)(2) of this AD, submit a report of the findings (both positive
and negative), of each inspection required by paragraphs (g) and (h)
of this AD. The report must include the inspection results, as
specified in Airbus Technical Disposition TD/K4/S2/27086/2009, Issue
E, dated September 17, 2009. For positive findings, submit the
report to the Manager, Seer1/
[[Page 16696]]
Seer2/Seer3 Customer Services; fax +33 (0)5 61 93 28 73; e-mail
region1.structurerepairsupport@airbus.com,
region2.structurerepairsupport@airbus.com, or
region3.structurerepairsupport@airbus.com. For negative findings,
submit the report to Nicolas Seynaeve, Sees1, Customer Services;
telephone +33 (0)5 61 93 34 38; fax +33 (0)5 61 93 36 14; e-mail
nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) For any inspection done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(k) All rudders that have passed the inspection specified in
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3),
and (h)(4) of this AD, before the effective date of this AD in
accordance with Airbus AOT A320-55A1038, dated April 22, 2009; AOT
A320-55A1038, Revision 01, dated June 10, 2009; or Airbus Technical
Disposition TD/K4/S2/27051/2009, Issue B, dated February 25, 2009;
are compliant with this AD for the areas inspected; except
additional areas requiring inspection, as defined in Section 0,
``Reason for Revision,'' of Airbus AOT A320-55A1038, Revision 02,
dated September 28, 2009, must be inspected as specified in
paragraph (g) or (h) of this AD. For all areas, the repetitive
inspections required by paragraph (g) or (h) of this AD remain
applicable.
(l) After the effective date of this AD, no rudder listed in
Table 1 of this AD may be installed on any airplane, unless the
rudder is in compliance with the requirements of this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service
information as follows: No differences.
Other FAA AD Provisions
(m) 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. 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.
(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
(n) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0141, dated July 2, 2009; Airbus All Operators Telex
A320-55A1038, Revision 02, dated September 28, 2009; and Airbus
Technical Disposition TD/K4/S2/27086/2009, Issue E, dated September
17, 2009; for related information.
Issued in Renton, Washington, on March 25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-7461 Filed 4-1-10; 8:45 am]
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