Airworthiness Directives; Airbus Airplanes, 60064-60072 [2012-24175]
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60064
Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
thereafter at intervals not to exceed 3,000
hours TIS on the P/N 83278 engine oil
pressure switch, replace it with a new, zero
time, P/N 83278 engine oil pressure switch.
Record the engine oil pressure switch part
number, date, and airplane hours in the
airplane log book. The recorded engine oil
pressure switch TIS will be used as the
benchmark for calculation of the 3,000 hour
TIS limit on the engine oil pressure switch.
(h) Alternative Methods of Compliance
(AMOCs)
(1) 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. 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 manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) 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.
(i) Related Information
(1) For more information about this AD,
contact Jeff Janusz, Sr. Propulsion Engineer,
Wichita ACO, FAA, 1801 Airport Road,
Wichita, KS 67209 phone: (316) 946–4148;
fax: (316) 946–4107; email: jeff.janusz@faa.
gov.
(2) For service information identified in
this AD, contact Cessna Aircraft Company,
Product Support, P.O. Box 7706, Wichita,
Kansas 67277; telephone: (316) 517–5800; fax
(316) 942–9006; Internet: www.cessna.com/
customer-service/technical-publications.
html. You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on
September 26, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2012–24207 Filed 10–1–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
14 CFR Part 39
[Docket No. FAA–2012–1034; Directorate
Identifier 2011–NM–051–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Mar<15>2010
14:57 Oct 01, 2012
Jkt 229001
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Airbus Model
A318, A319, A320, and A321 series
airplanes. The existing AD currently
requires one-time and repetitive
inspections of specific areas and, when
necessary, corrective actions for those
rudders where production rework has
been identified. Since we issued that
AD, we have determined that additional
inspections and corrective actions are
necessary to address the identified
unsafe condition, and that additional
airplanes with certain rudders are
subject to the identified unsafe
condition. This proposed AD would add
airplanes with certain rudders to the AD
applicability; change an inspection type
for certain reinforced rudder areas;
require pre-inspections and repairs if
needed; and require permanent
restoration of vacuum loss holes. This
proposed AD would also require
additional inspections for certain
rudders and repair if needed; and
require replacement of certain rudders
with new rudders. We are proposing
this AD to detect and correct extended
de-bonding, which might 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 airplane.
DATES: We must receive comments on
this proposed AD by November 16,
2012.
SUMMARY:
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; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
ADDRESSES:
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Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1405;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–1034; Directorate Identifier
2011–NM–051–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 October 26, 2010, we issued AD
2010–23–07, Amendment 39–16496 (75
FR 68181, November 5, 2010; corrected
December 17, 2010 (75 FR 78883)). That
AD required actions intended to address
an unsafe condition on the products
listed above.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2010–0164,
dated August 5, 2010 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
E:\FR\FM\02OCP1.SGM
02OCP1
Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
• Airbus Service Bulletin A320–55–
1037, Revision 01, dated July 2, 2010.
• Airbus Technical Disposition TD/
K4/S2/27051/2009, Issue B, dated
February 25, 2009.
• Airbus Technical Disposition TD/
K4/S2/27086/2009, Issue E, dated
September 17, 2009.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
Part number (P/N) D554 71000 020 00
serial number (S/N) TS–1494, and P/N
D554 71002 000 00 0002 S/N TS–2212
are listed in Appendix A of EASA AD
2010–0164, dated August 5, 2010. These
two items are listed in table 6 of this
proposed AD, because they were not
listed in previous AD 2010–23–07,
Amendment 39–16496 (75 FR 68181,
November 5, 2010; corrected December
17, 2010 (75 FR 78883)). This proposed
AD requires the permanent restoration
of vacuum loss holes and does not allow
the temporary restoration with selfadhesive patches, or temporary
restoration with resin that is specified in
the MCAI. You may obtain further
information by examining the MCAI in
the AD docket.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
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.
EASA AD 2009–0141 required inspections
of specific areas and, when necessary, the
application of corrective actions for those
rudders where production reworks have been
identified.
This [EASA] AD retains the requirements
of EASA AD 2009–0141 (addressing the
populations of rudders affected by AOT
A320–55–1038), which is superseded, and
requires:
— a local ultrasonic inspection for reinforced
area instead of the local thermography
inspection, which is maintained for nonreinforced areas, and
— additional work performance for rudders
on which this thermography inspection has
been performed in the reinforced area, and
— additional work performance for some
rudders on which an additional area
requiring inspections is defined.
This [EASA] AD also addresses the
populations of rudders affected by AOT
A320–55–1039 and Airbus SB A320–55–
1035, A320–55–1036 and A320–55–1037
which were not included in EASA AD 2009–
0141.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 721 products of U.S.
registry.
The actions that are required by AD
2010–23–07, Amendment 39–16496 (75
FR 68181, November 5, 2010; corrected
December 17, 2010 (75 FR 78883)), and
retained in this proposed AD take about
11 work-hours per product, at an
average labor rate of $85 per work hour.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of the currently
required actions on U.S. operators to be
$674,135, or $935 per product.
We estimate that it would take about
11 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
$674,135, or $935 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 12 work-hours and require parts
costing $10,000, for a cost of $11,020
per product. We have no way of
Relevant Service Information
Airbus has issued the following
service information.
• Airbus All Operators Telex (AOT)
A320–55A1038, dated April 22, 2009.
• Airbus AOT A320–55A1039, dated
November 4, 2009.
• Airbus Service Bulletin A320–55–
1035, Revision 01, dated July 2, 2010.
• Airbus Service Bulletin A320–55–
1036, Revision 01, dated July 2, 2010.
VerDate Mar<15>2010
14:57 Oct 01, 2012
Jkt 229001
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
This proposed AD requires the
permanent restoration of vacuum loss
holes and does not allow the temporary
restoration with self-adhesive patches,
or temporary restoration with resin that
is specified in the MCAI.
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60065
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
E:\FR\FM\02OCP1.SGM
02OCP1
60066
Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
TABLE 1 TO PARAGRAPH (C) OF THIS
AD—Continued
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Affected
rudder
S/N
Rudder P/N
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2010–23–07, Amendment 39–16496 (75
FR 68181, November 5, 2010; corrected
December 17, 2010 (75 FR 78883)), and
adding the following new AD:
Airbus: Docket No. FAA–2012–1034;
Directorate Identifier 2011–NM–051–AD.
(a) Comments Due Date
We must receive comments by November
16, 2012.
(b) Affected ADs
This AD supersedes AD 2010–23–07,
Amendment 39–16496 (75 FR 68181,
November 5, 2010; corrected December 17,
2010 (75 FR 78883)).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), (c)(3),
and (c)(4) of this AD; certificated in any
category; all serial numbers having a rudder
with a part number (P/N) and serial number
(S/N) listed in table 1, 2, 3, 4a and 4b, 5a and
5b, or 6 to paragraph (c) of this AD.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–111, –211, –212, –214,
–231, –232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
TABLE 1 TO PARAGRAPH (C) OF THIS
AD
Affected
rudder
S/N
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Rudder P/N
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
71000
VerDate Mar<15>2010
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14:57 Oct 01, 2012
TS–1069
TS–1090
TS–1227
TS–1350
TS–1366
TS–1371
TS–1383
TS–1387
TS–1412
TS–1443
TS–1444
TS–1468
TS–1480
TS–1491
TS–1495
TS–1498
TS–1499
TS–1500
TS–1505
TS–1506
TS–1507
TS–1509
TS–1515
TS–1528
Jkt 229001
D554
D554
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D554
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D554
D554
D554
D554
D554
D554
D554
PO 00000
71000
71000
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71000
71001
71001
71001
71001
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71001
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Fmt 4702
TABLE 1 TO PARAGRAPH (C) OF THIS
AD—Continued
Sfmt 4702
TS–1530
TS–1532
TS–1535
TS–1536
TS–1538
TS–1537
TS–1540
TS–1541
TS–1543
TS–1548
TS–1549
TS–1551
TS–1554
TS–1555
TS–1556
TS–1557
TS–1559
TS–1562
TS–1563
TS–1564
TS–1565
TS–1566
TS–1567
TS–1568
TS–1569
TS–1570
TS–1573
TS–1575
TS–1578
TS–1579
TS–1580
TS–1581
TS–1582
TS–1584
TS–1593
TS–1594
TS–1596
TS–1599
TS–1603
TS–1609
TS–1621
TS–1626
TS–1627
TS–1635
TS–1637
TS–2306
TS–2003
TS–2005
TS–2013
TS–2016
TS–2019
TS–2020
TS–2022
TS–2024
TS–2026
TS–2031
TS–2033
TS–2043
TS–2047
TS–2048
TS–2054
TS–2058
TS–2059
TS–2064
TS–2072
TS–2075
TS–2076
TS–2079
TS–2083
Affected
rudder
S/N
Rudder P/N
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
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D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
D554
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0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0002
0003
0003
0003
0003
0003
0003
0000
0000
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
.............
TS–2089
TS–2090
TS–2095
TS–2103
TS–2116
TS–2122
TS–2133
TS–2142
TS–2147
TS–2157
TS–2158
TS–2162
TS–2167
TS–2174
TS–2176
TS–2181
TS–2189
TS–2191
TS–2203
TS–2205
TS–2207
TS–2224
TS–2229
TS–2233
TS–2241
TS–2246
TS–2249
TS–2270
TS–2275
TS–2289
TS–2290
TS–2294
TS–2309
TS–2347
TS–2348
TS–2349
TS–2357
TS–2361
TS–2380
TS–2383
TS–2390
TS–2394
TS–2396
TS–2401
TS–2406
TS–2461
TS–2468
TS–2516
TS–2537
TS–2543
TS–2546
TS–2619
TS–2684
TS–2752
TS–2869
TS–2876
TS–2970
TS–2971
TS–2987
TS–3083
TS–3197
Note 1 to paragraph (c) of this AD: For
table 1 to paragraph (c) of this AD, 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
E:\FR\FM\02OCP1.SGM
02OCP1
Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
density of 24 kilogram (kg)/meters cubed
(m3).
TABLE 3 TO PARAGRAPH (C) OF THIS
AD
TABLE 2 TO PARAGRAPH (C) OF THIS
AD
Rudder P/N
Affected
rudder
S/N
D554–71000–014–00 ....................
D554–71002–000–00–0001 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0003 ..........
D554–71002–000–00–0003 ..........
D554–71002–000–00–0003 ..........
D554–71002–000–00–0003 ..........
D554–71004–000–00–0001 ..........
TS–1278
TS–2081
TS–2125
TS–2129
TS–2160
TS–2201
TS–2328
TS–2425
TS–2511
TS–2768
TS–2999
TS–3004
TS–3051
TS–3288
60067
rudder S/N TS–1092, have a core density of
24 kg/m3.
Rudder P/N
Affected
rudder
S/N
TABLE 4A TO PARAGRAPH (C) OF THIS
AD
D554–71000–008–00 ....................
D554–71000–010–00 ....................
D554–71000–014–00 ....................
D554–71000–018–00 ....................
D554–71000–020–00 ....................
D554–71002–000–00–0001 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0002 ..........
D554–71002–000–00–0003 ..........
D554–71004–000–00–0001 ..........
D554–71004–000–00–0001 ..........
D554–71004–000–00–0002 ..........
TS–1032
TS–1092
TS–1314
TS–1445
TS–1520
TS–2037
TS–2109
TS–2123
TS–2124
TS–2424
TS–2559
TS–3061
TS–3694
TS–3709
TS–4148
Rudder P/N with any S/N listed in table 4b to
paragraph (c) of this AD
D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000
Note 2 to paragraph (c) of this AD: For
table 3 to paragraph (c) of this AD, only
rudder P/N D554–71000–008–00 having
affected rudder S/N TS–1032, and rudder P/
N D554–71000–010–00 having affected
TABLE 4B TO PARAGRAPH (C) OF THIS AD
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Affected S/N for rudders listed in table 4a to paragraph (c) of this AD
TS–1368
TS–1389
TS–1496
TS–1501
TS–1503
TS–1508
TS–1516
TS–1527
TS–1529
TS–1534
TS–1545
TS–1547
TS–1553
TS–1560
TS–1561
TS–1571
TS–1572
TS–1574
TS–1576
TS–1577
TS–1583
TS–1585
TS–1588
TS–1591
TS–1600
TS–1602
TS–1607
TS–1608
TS–1614
TS–2372
TS–2373
TS–2374
TS–2377
TS–2381
TS–2382
TS–2387
TS–2388
TS–2392
TS–2393
TS–2395
TS–2397
TS–2398
TS–2399
VerDate Mar<15>2010
TS–1616
TS–1619
TS–1622
TS–1632
TS–1639
TS–2004
TS–2008
TS–2010
TS–2012
TS–2014
TS–2017
TS–2018
TS–2023
TS–2025
TS–2029
TS–2032
TS–2034
TS–2039
TS–2040
TS–2041
TS–2046
TS–2050
TS–2051
TS–2052
TS–2053
TS–2056
TS–2060
TS–2069
TS–2070
TS–2483
TS–2484
TS–2486
TS–2488
TS–2491
TS–2493
TS–2494
TS–2498
TS–2499
TS–2501
TS–2505
TS–2506
TS–2508
TS–2510
14:57 Oct 01, 2012
Jkt 229001
TS–2080
TS–2082
TS–2084
TS–2085
TS–2086
TS–2094
TS–2096
TS–2097
TS–2098
TS–2100
TS–2101
TS–2106
TS–2113
TS–2115
TS–2118
TS–2126
TS–2130
TS–2131
TS–2132
TS–2134
TS–2136
TS–2140
TS–2143
TS–2144
TS–2145
TS–2149
TS–2152
TS–2154
TS–2155
TS–2583
TS–2584
TS–2585
TS–2586
TS–2587
TS–2590
TS–2591
TS–2592
TS–2593
TS–2596
TS–2597
TS–2601
TS–2602
TS–2603
PO 00000
Frm 00011
TS–2159
TS–2163
TS–2168
TS–2169
TS–2170
TS–2172
TS–2175
TS–2177
TS–2179
TS–2182
TS–2183
TS–2185
TS–2192
TS–2193
TS–2195
TS–2199
TS–2200
TS–2204
TS–2206
TS–2208
TS–2209
TS–2210
TS–2211
TS–2213
TS–2216
TS–2217
TS–2218
TS–2220
TS–2221
TS–2665
TS–2666
TS–2667
TS–2668
TS–2671
TS–2674
TS–2675
TS–2676
TS–2677
TS–2679
TS–2680
TS–2681
TS–2682
TS–2683
Fmt 4702
Sfmt 4702
TS–2222
TS–2223
TS–2227
TS–2228
TS–2230
TS–2231
TS–2232
TS–2234
TS–2235
TS–2236
TS–2238
TS–2240
TS–2242
TS–2244
TS–2245
TS–2248
TS–2250
TS–2251
TS–2252
TS–2254
TS–2258
TS–2259
TS–2260
TS–2261
TS–2262
TS–2265
TS–2268
TS–2271
TS–2272
TS–2743
TS–2744
TS–2745
TS–2747
TS–2749
TS–2751
TS–2753
TS–2754
TS–2755
TS–2756
TS–2757
TS–2758
TS–2759
TS–2760
E:\FR\FM\02OCP1.SGM
TS–2276
TS–2279
TS–2280
TS–2281
TS–2284
TS–2285
TS–2286
TS–2293
TS–2297
TS–2298
TS–2299
TS–2302
TS–2303
TS–2304
TS–2305
TS–2307
TS–2310
TS–2311
TS–2312
TS–2313
TS–2315
TS–2316
TS–2319
TS–2320
TS–2321
TS–2322
TS–2323
TS–2325
TS–2326
TS–2813
TS–2814
TS–2815
TS–2816
TS–2818
TS–2819
TS–2821
TS–2822
TS–2823
TS–2824
TS–2826
TS–2827
TS–2828
TS–2830
02OCP1
TS–2327
TS–2330
TS–2331
TS–2332
TS–2333
TS–2334
TS–2336
TS–2337
TS–2338
TS–2339
TS–2340
TS–2341
TS–2343
TS–2346
TS–2352
TS–2353
TS–2354
TS–2355
TS–2356
TS–2358
TS–2360
TS–2362
TS–2363
TS–2364
TS–2365
TS–2366
TS–2367
TS–2370
TS–2371
TS–2878
TS–2879
TS–2880
TS–2881
TS–2882
TS–2885
TS–2886
TS–2890
TS–2891
TS–2892
TS–2893
TS–2896
TS–2897
TS–2898
60068
Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
TABLE 4B TO PARAGRAPH (C) OF THIS AD—Continued
TS–2407
TS–2408
TS–2409
TS–2410
TS–2411
TS–2412
TS–2415
TS–2417
TS–2421
TS–2422
TS–2423
TS–2427
TS–2428
TS–2435
TS–2437
TS–2440
TS–2444
TS–2446
TS–2447
TS–2453
TS–2455
TS–2458
TS–2460
TS–2463
TS–2466
TS–2467
TS–2471
TS–2472
TS–2474
TS–2476
TS–2477
TS–2478
TS–2481
TS–2482
TS–2948
TS–2949
TS–2950
TS–2951
TS–2953
TS–2954
TS–2955
TS–2957
TS–2958
TS–2959
TS–2960
TS–2962
TS–2964
TS–2965
TS–2968
TS–2969
TS–2973
TS–2976
TS–2980
TS–2984
TS–2985
TS–2986
TS–2988
TS–2991
TS–2998
TS–3001
TS–3002
TS–3003
TS–3005
TS–3006
TS–3009
TS–3011
TS–3016
TS–3018
TS–3020
TS–3021
TS–3025
TS–3026
TS–3027
TS–3028
VerDate Mar<15>2010
TS–2512
TS–2514
TS–2517
TS–2518
TS–2521
TS–2522
TS–2527
TS–2529
TS–2532
TS–2536
TS–2540
TS–2544
TS–2545
TS–2547
TS–2551
TS–2552
TS–2553
TS–2554
TS–2555
TS–2558
TS–2562
TS–2563
TS–2566
TS–2568
TS–2570
TS–2571
TS–2572
TS–2573
TS–2574
TS–2575
TS–2576
TS–2579
TS–2580
TS–2581
TS–3040
TS–3043
TS–3046
TS–3049
TS–3050
TS–3052
TS–3054
TS–3055
TS–3056
TS–3058
TS–3060
TS–3065
TS–3066
TS–3071
TS–3072
TS–3074
TS–3075
TS–3076
TS–3077
TS–3078
TS–3079
TS–3080
TS–3081
TS–3082
TS–3084
TS–3087
TS–3088
TS–3089
TS–3090
TS–3091
TS–3093
TS–3094
TS–3096
TS–3097
TS–3098
TS–3100
TS–3101
TS–3102
TS–3103
TS–3104
14:57 Oct 01, 2012
Jkt 229001
TS–2605
TS–2606
TS–2611
TS–2612
TS–2614
TS–2615
TS–2616
TS–2617
TS–2620
TS–2625
TS–2626
TS–2628
TS–2629
TS–2630
TS–2631
TS–2632
TS–2634
TS–2635
TS–2636
TS–2637
TS–2640
TS–2641
TS–2642
TS–2644
TS–2647
TS–2648
TS–2650
TS–2651
TS–2653
TS–2656
TS–2657
TS–2658
TS–2659
TS–2662
TS–3113
TS–3114
TS–3116
TS–3119
TS–3120
TS–3121
TS–3122
TS–3123
TS–3124
TS–3125
TS–3126
TS–3127
TS–3129
TS–3131
TS–3132
TS–3133
TS–3134
TS–3135
TS–3138
TS–3139
TS–3140
TS–3141
TS–3142
TS–3143
TS–3144
TS–3145
TS–3148
TS–3149
TS–3151
TS–3154
TS–3155
TS–3156
TS–3158
TS–3159
TS–3160
TS–3161
TS–3162
TS–3164
TS–3166
TS–3167
PO 00000
Frm 00012
TS–2685
TS–2688
TS–2689
TS–2691
TS–2695
TS–2697
TS–2698
TS–2699
TS–2700
TS–2701
TS–2707
TS–2710
TS–2711
TS–2712
TS–2713
TS–2714
TS–2716
TS–2717
TS–2719
TS–2722
TS–2724
TS–2725
TS–2726
TS–2727
TS–2728
TS–2732
TS–2734
TS–2735
TS–2736
TS–2738
TS–2739
TS–2740
TS–2741
TS–2742
TS–3177
TS–3178
TS–3179
TS–3180
TS–3181
TS–3182
TS–3183
TS–3184
TS–3185
TS–3186
TS–3188
TS–3189
TS–3191
TS–3193
TS–3194
TS–3195
TS–3198
TS–3200
TS–3201
TS–3202
TS–3204
TS–3205
TS–3207
TS–3210
TS–3215
TS–3216
TS–3217
TS–3218
TS–3219
TS–3221
TS–3222
TS–3223
TS–3224
TS–3226
TS–3227
TS–3232
TS–3234
TS–3235
TS–3236
TS–3237
Fmt 4702
Sfmt 4702
TS–2762
TS–2765
TS–2771
TS–2772
TS–2773
TS–2775
TS–2776
TS–2778
TS–2779
TS–2780
TS–2782
TS–2783
TS–2784
TS–2785
TS–2786
TS–2788
TS–2790
TS–2791
TS–2792
TS–2793
TS–2794
TS–2795
TS–2796
TS–2797
TS–2799
TS–2801
TS–2803
TS–2804
TS–2805
TS–2807
TS–2808
TS–2810
TS–2811
TS–2812
TS–3249
TS–3250
TS–3251
TS–3252
TS–3253
TS–3255
TS–3256
TS–3257
TS–3259
TS–3262
TS–3271
TS–3276
TS–3278
TS–3282
TS–3286
TS–3289
TS–3290
TS–3291
TS–3292
TS–3295
TS–3297
TS–3306
TS–3309
TS–3310
TS–3317
TS–3320
TS–3328
TS–3388
TS–3392
TS–3395
TS–3429
TS–3441
TS–3516
TS–3561
TS–3567
TS–3574
TS–3590
TS–3591
TS–3595
TS–3598
E:\FR\FM\02OCP1.SGM
TS–2831
TS–2832
TS–2833
TS–2834
TS–2835
TS–2836
TS–2837
TS–2838
TS–2839
TS–2840
TS–2843
TS–2844
TS–2845
TS–2846
TS–2848
TS–2849
TS–2850
TS–2851
TS–2852
TS–2853
TS–2854
TS–2855
TS–2856
TS–2857
TS–2860
TS–2861
TS–2862
TS–2863
TS–2864
TS–2865
TS–2868
TS–2872
TS–2874
TS–2877
TS–3689
TS–3690
TS–3695
TS–3699
TS–3702
TS–3703
TS–3704
TS–3706
TS–3708
TS–3710
TS–3717
TS–3718
TS–3734
TS–3743
TS–3761
TS–3772
TS–3780
TS–3789
TS–3805
TS–3820
TS–3821
TS–3822
TS–3824
TS–3825
TS–3839
TS–3841
TS–3843
TS–3844
TS–3846
TS–3849
TS–3850
TS–3851
TS–3853
TS–3855
TS–3857
TS–3860
TS–3862
TS–3863
TS–3871
TS–3878
02OCP1
TS–2899
TS–2900
TS–2903
TS–2904
TS–2906
TS–2907
TS–2908
TS–2909
TS–2910
TS–2911
TS–2913
TS–2914
TS–2916
TS–2917
TS–2919
TS–2920
TS–2922
TS–2923
TS–2924
TS–2925
TS–2927
TS–2928
TS–2929
TS–2930
TS–2932
TS–2933
TS–2934
TS–2935
TS–2937
TS–2938
TS–2939
TS–2943
TS–2944
TS–2946
TS–3928
TS–3936
TS–3939
TS–3942
TS–3950
TS–3958
TS–3961
TS–3968
TS–3987
TS–3993
TS–3995
TS–4003
TS–4027
TS–4031
TS–4087
TS–4099
TS–4118
TS–4145
TS–4146
TS–4147
TS–4163
TS–4167
TS–4175
TS–4178
TS–4181
TS–4186
TS–4195
TS–4212
TS–4232
TS–4271
TS–4331
TS–4345
TS–4366
TS–4396
TS–4401
TS–4420
TS–4461
TS–4480
TS–4636
TS–4651
Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
60069
TABLE 4B TO PARAGRAPH (C) OF THIS AD—Continued
TS–3030
TS–3031
TS–3032
TS–3033
TS–3034
TS–3035
TS–3037
TS–3038
TS–3105
TS–3106
TS–3107
TS–3108
TS–3109
TS–3110
TS–3111
TS–3112
TS–3168
TS–3169
TS–3170
TS–3171
TS–3172
TS–3174
TS–3175
TS–3176
TABLE 5A TO PARAGRAPH (C) OF THIS
AD
Rudder P/N with any S/N listed in table 5b to
paragraph (c) of this AD
D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000
TABLE 5B TO PARAGRAPH (C) OF THIS
AD
TS–2141
TS–2269
TS–2274
TS–2295
TS–2317
TS–2664
TS–2715
TABLE 6 TO PARAGRAPH (C) OF THIS
AD
Rudder P/N
Affected
rudder
S/N
D554 71000 020 00 ......................
D554 71002 000 00 0002 .............
TS–1494
TS–2212
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(e) Reason
This AD was prompted by reports of
surface defects on rudders that were the
result of debonding between the skin and
honeycomb core. We are issuing this AD to
detect and correct extended de-bonding,
which might 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 airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
VerDate Mar<15>2010
14:57 Oct 01, 2012
Jkt 229001
TS–3240
TS–3241
TS–3242
TS–3243
TS–3244
TS–3245
TS–3247
TS–3248
TS–3609
TS–3625
TS–3638
TS–3650
TS–3669
TS–3684
TS–3685
TS–3687
compliance times specified, unless the
actions have already been done.
(g) Retained Repetitive Inspections of
Rudders With a Core Density of 24 kg/m3
This paragraph restates the requirements of
paragraph (g) of AD 2010–23–07 Amendment
39–16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)).
For rudders identified in table 1 to paragraph
(c) of this AD 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 01, dated June 10,
2009; or Airbus AOT A320–55A1038,
Revision 02, dated September 28, 2009; for
the locations defined in the applicable AOT
specified in this paragraph.
(1) Within 200 days after December 10,
2010 (the effective date of AD 2010–23–07,
Amendment 39–16496 (75 FR 68181,
November 5, 2010; corrected December 17,
2010 (75 FR 78883))): Perform a vacuum loss
inspection on the rudder reinforced area.
(2) Within 20 months after December 10,
2010 (the effective date of AD 2010–23–07,
Amendment 39–16496 (75 FR 68181,
November 5, 2010; corrected December 17,
2010 (75 FR 78883))): 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 December 10,
2010 (the effective date of AD 2010–23–07,
Amendment 39–16496 (75 FR 68181,
November 5, 2010; corrected December 17,
2010 (75 FR 78883))): 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 December 10,
2010 (the effective date of AD 2010–23–07,
Amendment 39–16496 (75 FR 68181,
November 5, 2010; corrected December 17,
2010 (75 FR 78883))): 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.
PO 00000
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Fmt 4702
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TS–3879
TS–3882
TS–3883
TS–3885
TS–3910
TS–3914
TS–3921
TS–3924
TS–4678
TS–4696
TS–4770
N/A
N/A
N/A
N/A
N/A
(h) Retained Repetitive Inspections of
Rudders Without a Core Density of 24 kg/m3
This paragraph restates the requirements of
paragraph (h) of AD 2010–23–07 Amendment
39–16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)).
For rudders that do not have a honeycomb
core density of 24 kg/m3 (all rudders
identified in table 1 to paragraph (c) 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
01, dated June 10, 2009; or Airbus AOT
A320–55A1038, Revision 02, dated
September 28, 2009; for the locations defined
in the applicable AOT specified in this
paragraph. As of the effective date of this AD,
use only Airbus AOT A320–55A1038,
Revision 02, dated September 28, 2009. For
this paragraph, ‘‘reference date’’ is defined as
December 10, 2010 (the effective date of AD
2010–23–07), 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) Retained Corrective Actions for DeBonding
This paragraph restates the requirements of
paragraph (i) of AD 2010–23–07 Amendment
39–16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)).
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
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in accordance with the approved data
provided, or repair the debonding using a
method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent). After the effective date of
this AD, repair the debonding using only a
method approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent).
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(j) Retained Reporting for Findings From
Actions Required by Paragraphs (g) and (h)
of this AD
This paragraph restates the requirements of
paragraph (j) of AD 2010–23–07 Amendment
39–16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)).
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 either
the Manager, Seer1/Seer2/Seer3 Customer
Services, fax +33 (0)5 61 93 28 73, email
region1.structurerepairsupport@airbus.com,
region2.structurerepairsupport@airbus.com,
or
region3.structurerepairsupport@airbus.com;
or AIRTAC (Airbus Technical AOG Center)
Customer Services, telephone +33 (0)5 61 93
34 00, fax +33 (0)5 61 93 35 00, email
airtac@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; email
nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after
December 10, 2010 (the effective date of AD
2010–23–07, Amendment 39–16496 (75 FR
68181, November 5, 2010; corrected
December 17, 2010 (75 FR 78883))): Submit
the report within 30 days after the
inspection.
(2) For any inspection done before
December 10, 2010 (the effective date of AD
2010–23–07, Amendment 39–16496 (75 FR
68181, November 5, 2010; corrected
December 17, 2010 (75 FR 78883))): Submit
the report within 30 days after December 10,
2010.
(k) Retained Inspection in Additional Areas
This paragraph restates the provisions of
paragraph (k) of AD 2010–23–07,
Amendment 39–16496, (75 FR 68181,
November 5, 2010; corrected December 17,
2010 (75 FR 78883)). 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 December 10,
2010 (the effective date of AD 2010–23–07),
in accordance with Airbus AOT A320–
55A1038, dated April 22, 2009; or Airbus
Technical Disposition TD/K4/S2/27051/
2009, Issue B, dated February 25, 2009; are
compliant with this AD only for the areas
inspected. Additional areas defined in
Section 0, ‘‘Reason for Revision,’’ of Airbus
AOT A320–55A1038, Revision 01, dated June
10, 2009; or Airbus AOT A320–55A1038,
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14:57 Oct 01, 2012
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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) Retained Parts Installation Limitations
This paragraph restates the requirements of
paragraph (l) of AD 2010–23–07, Amendment
39–16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)).
After December 10, 2010 (the effective date
of AD 2010–23–07), no rudder listed in table
1 to paragraph (c) of this AD may be installed
on any airplane, unless the rudder is
inspected in accordance with paragraph (g)
or (h) of this AD, as applicable, and all
applicable actions specified in paragraph (i)
of this AD are done.
(m) New Restoration of Vacuum Loss Holes
If no de-bonding is found during any
inspection required by paragraph (g) or (h) of
this AD: Before further flight, restore the
vacuum loss holes by doing a permanent
restoration with resin, in accordance with
Note 3 of Airbus AOT A320–55A1038,
Revision 02, dated September 28, 2009.
Before doing the resin injection, do a local
ultrasound inspection in reinforced areas,
and a thermography inspection in other
areas, for damage, in accordance with Note
3 of Airbus AOT A320–55A1038, Revision
02, dated September 28, 2009. If any damage
is found during any inspection required by
this paragraph: Before further flight, repair
the damage using a method approved by
either the Manager, International Branch,
ANM–116; or the EASA (or its delegated
agent).
(n) New X-Ray, Elasticity Laminate Checker
(ELCh), Vacuum Loss, or Thermography
Inspection
For rudders identified in table 2 to
paragraph (c) of this AD, do the actions
specified in paragraphs (n)(1) and (n)(2) of
this AD, in accordance with Airbus AOT
A320–55A1039, dated November 4, 2009, for
the locations defined in that AOT. For this
paragraph, ‘‘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 20 months after the effective
date of this AD, or within 200 days after the
reference date, whichever occurs first:
Perform X-ray, and/or ELCh, and/or vacuum
loss, and/or thermography inspections for
damage, as applicable to rudder part number
and serial number, in accordance with the
instructions of paragraph 4.2.2.1.1. of Airbus
AOT A320–55A1039, dated November 4,
2009.
(2) At the applicable time specified in
paragraph (n)(2)(i) or (n)(2)(ii) of this AD,
send the developed X-ray films and the film
layout arrangement, if applicable, to Attn:
SDC32 Technical Data and Documentation
Services, Airbus Customer Services
Directorate, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; fax (+33) 5 61
93 28 06; email sb.reporting@airbus.com.
(i) If the inspection was done on or after
the effective date of this AD: Submit the X-
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
ray films and the film layout arrangement
within 10 days after the inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the X-ray
films and the film layout arrangement within
10 days after the effective date of this AD.
(3) If any damage is found during any
inspection required by paragraph (n) of this
AD: Before further flight, repair the damage
using a method approved by either the
Manager, International Branch, ANM–116; or
the EASA (or its delegated agent).
(o) New ELCh Inspection, Vacuum Loss
Inspection, and Repairs
For rudders identified in table 2 to
paragraph (c) of this AD: Within 1,500 flight
cycles or 200 days after doing the
requirements of paragraph (n)(1) of this AD,
whichever occurs first, do the actions
specified in paragraphs (o)(1) and (o)(2) of
this AD.
(1) Perform an ELCh inspection for damage
on the rudder trailing edge area, in
accordance with the instructions of
paragraph 4.2.2.1.2. of Airbus AOT A320–
55A1039, dated November 4, 2009. In case of
no finding, 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.
(2) Perform a vacuum loss inspection for
damage of the other areas (splice/lower rib/
upper edge/leading edge/other specified
locations), in accordance with the
instructions of paragraph 4.2.2.1.2. of Airbus
AOT A320–55A1039, dated November 4,
2009.
(3) If any damage is found during any
inspection required by paragraph (o) of this
AD: Before further flight, repair the damage
using a method approved by either the
Manager, International Branch, ANM–116; or
the EASA (or its delegated agent).
(p) New Restorations and Inspections of
Certain Vacuum Loss Holes, and Repairs
If no damage is found during any
inspection required by paragraph (o) of this
AD: Before further flight, restore the vacuum
loss holes by doing a permanent restoration
with resin, in accordance with Note 3 of
Airbus AOT A320–55A1039, dated
November 4, 2009. Before doing the resin
injection, do a local ultrasound inspection in
reinforced areas, and a thermography
inspection in other areas, for damage, in
accordance with Note 3 of Airbus AOT
A320–55A1039, dated November 4, 2009. If
any damage is found during any inspection
required by this paragraph: Before further
flight, repair the damage using a method
approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent).
(q) New Rudder Replacement for Rudders
Identified in Table 3 to Paragraph (c) of This
AD
For rudders identified in table 3 to
paragraph (c) of this AD, do the actions
specified in paragraphs (q)(1) and (q)(2) of
this AD, in accordance with the instruction
of Airbus AOT A320–55A1039, dated
November 4, 2009, for the locations defined
in that AOT. For this paragraph, ‘‘reference
date’’ is defined as the effective date of this
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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) For rudders identified in table 3 to
paragraph (c) of this AD with a honeycomb
core density of 24 kg/m3 (rudder P/N D554–
71000–008–00 having affected rudder S/N
TS–1032 and rudder P/N D554–71000–010–
00 having affected rudder S/N TS–1092):
Within 200 days after the effective date of
this AD, replace the rudder with a new
rudder, in accordance with a method
approved by the Manager, International
Branch, ANM–116; or the EASA (or its
delegated agent).
(2) For rudders identified in table 3 to
paragraph (c) of this AD that do not have a
honeycomb core density of 24 kg/m3 (all
except rudder P/N D554–71000–008–00
having affected rudder S/N TS–1032 and
rudder P/N D554–71000–010–00 having
affected rudder S/N TS–1092): Within 20
months after the effective date of this AD or
within 200 days after the reference date,
whichever occurs first, replace the rudder
with a new rudder, in accordance with a
method approved by the Manager,
International Branch, ANM–116.
(r) New Vacuum Loss Inspection for
Reinforced Areas of Rudder Identified in
Table 4 to Paragraph (c) of This AD
For rudders identified in tables 4a and 4b
to paragraph (c) of this AD: At the later of the
times specified in paragraphs (r)(1) and (r)(2)
of this AD, perform a vacuum loss inspection
on the rudder reinforced area for damage, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
55–1035, Revision 01, dated July 2, 2010 (for
Model A320 airplanes); Airbus Service
Bulletin A320–55–1036, Revision 01, dated
July 2, 2010 (for Model A318 and A321
airplanes); or Airbus Service Bulletin A320–
55–1037, Revision 01, dated July 2, 2010 (for
Model A319 airplanes).
(1) Before the rudder accumulates 17,000
total flight cycles from its first installation on
an airplane without exceeding 20 months
from the effective date of this AD.
(2) Within 200 days after the effective date
of this AD.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(s) New ELCh Inspection for Rudder Trailing
Edge Area
For rudders identified in tables 4a and 4b
to paragraph (c) of this AD: Within 20
months after the effective date of this AD,
perform an ELCh inspection for damage on
the rudder trailing edge area, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–55–1035,
Revision 01, dated July 2, 2010 (for Model
A320 airplanes); Airbus Service Bulletin
A320–55–1036, Revision 01, dated July 2,
2010 (for Model A318 and A321 airplanes);
or Airbus Service Bulletin A320–55–1037,
Revision 01, dated July 2, 2010 (for Model
A319 airplanes). 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.
VerDate Mar<15>2010
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Jkt 229001
(t) New ELCh Inspection for Additional
Rudder Areas
For rudders identified in tables 4a and 4b
to paragraph (c) of this AD: At the later of the
times specified in paragraphs (t)(1) and (t)(2)
of this AD, perform an ELCh inspection for
damage of the other areas (splice/lower rib/
upper edge/leading edge/other specified
locations) for damage, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–55–1035, Revision 01,
dated July 2, 2010 (for Model A320
airplanes); Airbus Service Bulletin A320–55–
1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus
Service Bulletin A320–55–1037, Revision 01,
dated July 2, 2010 (for Model A319
airplanes). Repeat the inspection thereafter at
intervals not to exceed 1,500 flight cycles or
200 days, whichever comes first.
(1) Before the rudder accumulates 17,000
total flight cycles from its first installation on
an airplane without exceeding 20 months
from the effective date of this AD.
(2) Within 200 days after the effective date
of this AD.
(u) New Vacuum Loss Inspection for Certain
Areas of Rudders Identified in Tables 4a and
4b to Paragraph (c) of This AD
For rudders identified in tables 4a and 4b
of this AD: Within 20 months after the
effective date of this AD, perform a vacuum
loss inspection for damage of the lower rib,
upper edge, leading edge, and other specified
locations, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–55–1035, Revision 01,
dated July 2, 2010 (for Model A320
airplanes); Airbus Service Bulletin A320–55–
1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus
Service Bulletin A320–55–1037, Revision 01,
dated July 2, 2010 (for Model A319
airplanes). Accomplishment of the actions
specified in this paragraph terminates the
requirements of paragraph (t) of this AD.
(v) New Corrective Actions for Certain
Inspections
In case of damage found during any
inspection required by paragraph (r), (s), (t),
or (u) of this AD: Before further flight, repair
the damage using a method approved by
either the Manager, International Branch,
ANM–116; or the EASA (or its delegated
agent).
(w) New Restorations and Inspections of
Certain Vacuum Loss Holes, and Repairs
If no damage is found during any
inspection required by paragraph (r) or (u) of
this AD: Before further flight, restore the
vacuum loss holes by doing a permanent
restoration with resin, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–55–1035, Revision 01,
dated July 2, 2010 (for Model A320
airplanes); Airbus Service Bulletin A320–55–
1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus
Service Bulletin A320–55–1037, Revision 01,
dated July 2, 2010 (for Model A319
airplanes). Before doing the resin injection,
do a local ultrasound inspection in
reinforced areas, and a thermography
PO 00000
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Fmt 4702
Sfmt 4702
60071
inspection in other areas, for damage, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
55–1035, Revision 01, dated July 2, 2010 (for
Model A320 airplanes); Airbus Service
Bulletin A320–55–1036, Revision 01, dated
July 2, 2010 (for Model A318 and A321
airplanes); or Airbus Service Bulletin A320–
55–1037, Revision 01, dated July 2, 2010 (for
Model A319 airplanes). If any damage is
found during any inspection required by this
paragraph: Before further flight, repair the
damage using a method approved by either
the Manager, International Branch, ANM–
116; or the EASA (or its delegated agent).
(x) Credit for Certain Previous Actions
This paragraph provides credit for the
inspections required by paragraphs (r), (s), (t),
(u), and (w) of this AD only for the inspected
area for rudders identified in tables 4a and
4b to paragraph (c) of this AD, if the area
passed the inspection before the effective
date of this AD using Airbus Service Bulletin
A320–55–1035, dated February 17, 2010 (for
Model A320 airplanes); Airbus Service
Bulletin A320–55–1036, dated February 17,
2010 (for Model A318 and A321 airplanes);
or Airbus Service Bulletin A320–55–1037,
dated February 17, 2010 (for Model A319
airplanes). For all other inspected areas, the
repetitive inspections required by paragraph
(s), (t), and (w) of this AD are still required.
(y) New ELCh Inspection and Repairs for
Certain Rudders
For rudders identified in tables 5a and 5b
to paragraph (c) of this AD: Within 4,500
flight cycles but not sooner than 4,000 flight
cycles after the sampling inspection, perform
an ELCh inspection for damage on the rudder
trailing edge area, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–55–1035, Revision 01,
dated July 2, 2010 (for Model A320
airplanes); Airbus Service Bulletin A320–55–
1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus
Service Bulletin A320–55–1037, Revision 01,
dated July 2, 2010 (for Model A319
airplanes). Repeat the inspection within
4,500 flight cycles, but not sooner than 4,000
flight cycles after the last inspection. If any
damage is found during any inspection
required by paragraph (y) of this AD: Before
further flight, repair the damage using a
method approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent).
(z) Credit for Certain Other Previous Actions
This paragraph provides credit for the
inspection required by paragraph (y) of this
AD only for the inspected area for rudders
identified in tables 5a and 5b to paragraph (c)
of this AD that have passed the inspection
before the effective date of this AD using
Airbus Service Bulletin A320–55–1035,
dated February 17, 2010 (for Model A320
airplanes); Airbus Service Bulletin A320–55–
1036, dated February 17, 2010 (for Model
A318 and A321 airplanes); or Airbus Service
Bulletin A320–55–1037, dated February 17,
2010 (for Model A319 airplanes). For all
inspection areas, the repetitive inspections
required by paragraph (y) of this AD are still
required.
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Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules
(aa) New Repetitive Inspections of Rudders
Identified in Table 6 to Paragraph (c) of This
AD
For rudders identified in table 6 to
paragraph (c) of this AD, do the actions
specified in paragraphs (aa)(1), (aa)(2),
(aa)(3), and (aa)(4) of this AD, in accordance
with Airbus AOT A320–55A1038, Revision
02, dated September 28, 2009. For this
paragraph, ‘‘reference date’’ is defined as the
date when the rudder will accumulate 20,000
total flight cycles from its first installation on
an airplane.
(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.
(bb) New De-Bonding Corrective Actions
In case of de-bonding found during any
inspection required by paragraph (aa) 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.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(cc) New Restoration of Vacuum Loss Holes
If no de-bonding is found during any
inspection required by paragraph (aa) of this
AD: Before further flight, restore the vacuum
loss holes by a permanent restoration with
resin, in accordance with Note 3 of Airbus
AOT A320–55A1038, Revision 02, dated
September 28, 2009. Before doing the resin
injection, do a local ultrasound inspection in
reinforced areas, and a thermography
inspection in other areas, for damage, in
accordance with Note 3 of Airbus AOT
A320–55A1038, Revision 02, dated
September 28, 2009. If any damage is found
during any inspection required by this
paragraph: Before further flight, repair the
damage using a method approved by either
the Manager, International Branch, ANM–
116; or the EASA (or its delegated agent).
(dd) New Reporting for Paragraphs (n), (o),
(r), (s), (t), (u), (y), and (aa) of This AD
At the applicable time specified in
paragraph (dd)(1) or (dd)(2) of this AD,
submit a report of the findings (both positive
and negative) of each inspection required by
VerDate Mar<15>2010
14:57 Oct 01, 2012
Jkt 229001
paragraphs (n), (o), (r), (s), (t), (u), (y), and
(aa) 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 either
the Manager, Seer1/Seer2/Seer3 Customer
Services, fax +33 (0)5 61 93 28 73, email
region1.structurerepairsupport@airbus.com,
region2.structurerepairsupport@airbus.com,
or
region3.structurerepairsupport@airbus.com;
or AIRTAC (Airbus Technical AOG Center)
Customer Services, telephone +33 (0)5 61 93
34 00, fax +33 (0)5 61 93 35 00, email
airtac@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, email
nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after the
effective date of this AD: Submit the report
within 10 days after the inspection.
(2) For any inspection done before the
effective date of this AD: Submit the report
within 10 days after the effective date of this
AD.
(ee) New Parts Installation Limitation
As of the effective date of this AD, no
rudder listed in table 1, 2, 3, 4a, 4b, 5a, 5b,
or 6 to paragraph (c) of this AD may be
installed on any airplane, unless the rudder
is in compliance with the requirements of
this AD.
(ff) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1405; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
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.
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
(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.
(gg) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2010–0164, dated August 5, 2010,
and the following service information, for
related information.
(i) Airbus AOT A320–55A1038, dated
April 22, 2009.
(ii) Airbus AOT A320–55A1038, Revision
01, dated June 10, 2009.
(iii) Airbus AOT A320–55A1038, Revision
02, dated September 28, 2009.
(iv) Airbus AOT A320–55A1039, dated
November 4, 2009.
(v) Airbus Service Bulletin A320–55–1035,
Revision 01, dated July 2, 2010.
(vi) Airbus Service Bulletin A320–55–
1036, Revision 01, dated July 2, 2010.
(vii) Airbus Service Bulletin A320–55–
1037, Revision 01, dated July 2, 2010.
(viii) Airbus Technical Disposition TD/K4/
S2/27051/2009, Issue B, dated February 25,
2009.
(ix) Airbus Technical Disposition TD/K4/
S2/27086/2009, Issue E, dated September 17,
2009.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; Internet
https://www.airbus.com. 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.
Issued in Renton, Washington, on
September 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–24175 Filed 10–1–12; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\02OCP1.SGM
02OCP1
]]>Agencies
[Federal Register Volume 77, Number 191 (Tuesday, October 2, 2012)]
[Proposed Rules]
[Pages 60064-60072]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-24175]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1034; Directorate Identifier 2011-NM-051-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Airbus Model A318, A319, A320, and A321
series airplanes. The existing AD currently requires one-time and
repetitive inspections of specific areas and, when necessary,
corrective actions for those rudders where production rework has been
identified. Since we issued that AD, we have determined that additional
inspections and corrective actions are necessary to address the
identified unsafe condition, and that additional airplanes with certain
rudders are subject to the identified unsafe condition. This proposed
AD would add airplanes with certain rudders to the AD applicability;
change an inspection type for certain reinforced rudder areas; require
pre-inspections and repairs if needed; and require permanent
restoration of vacuum loss holes. This proposed AD would also require
additional inspections for certain rudders and repair if needed; and
require replacement of certain rudders with new rudders. We are
proposing this AD to detect and correct extended de-bonding, which
might 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 airplane.
DATES: We must receive comments on this proposed AD by November 16,
2012.
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; email 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, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-1034;
Directorate Identifier 2011-NM-051-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 October 26, 2010, we issued AD 2010-23-07, Amendment 39-16496
(75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR
78883)). That AD required actions intended to address an unsafe
condition on the products listed above.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2010-0164, dated August 5, 2010 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
[[Page 60065]]
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.
EASA AD 2009-0141 required inspections of specific areas and,
when necessary, the application of corrective actions for those
rudders where production reworks have been identified.
This [EASA] AD retains the requirements of EASA AD 2009-0141
(addressing the populations of rudders affected by AOT A320-55-
1038), which is superseded, and requires:
-- a local ultrasonic inspection for reinforced area instead of the
local thermography inspection, which is maintained for non-
reinforced areas, and
-- additional work performance for rudders on which this
thermography inspection has been performed in the reinforced area,
and
-- additional work performance for some rudders on which an
additional area requiring inspections is defined.
This [EASA] AD also addresses the populations of rudders
affected by AOT A320-55-1039 and Airbus SB A320-55-1035, A320-55-
1036 and A320-55-1037 which were not included in EASA AD 2009-0141.
Part number (P/N) D554 71000 020 00 serial number (S/N) TS-1494, and P/
N D554 71002 000 00 0002 S/N TS-2212 are listed in Appendix A of EASA
AD 2010-0164, dated August 5, 2010. These two items are listed in table
6 of this proposed AD, because they were not listed in previous AD
2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). This proposed AD requires
the permanent restoration of vacuum loss holes and does not allow the
temporary restoration with self-adhesive patches, or temporary
restoration with resin that is specified in the MCAI. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following service information.
Airbus All Operators Telex (AOT) A320-55A1038, dated April
22, 2009.
Airbus AOT A320-55A1039, dated November 4, 2009.
Airbus Service Bulletin A320-55-1035, Revision 01, dated
July 2, 2010.
Airbus Service Bulletin A320-55-1036, Revision 01, dated
July 2, 2010.
Airbus Service Bulletin A320-55-1037, Revision 01, dated
July 2, 2010.
Airbus Technical Disposition TD/K4/S2/27051/2009, Issue B,
dated February 25, 2009.
Airbus Technical Disposition TD/K4/S2/27086/2009, Issue E,
dated September 17, 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
This proposed AD requires the permanent restoration of vacuum loss
holes and does not allow the temporary restoration with self-adhesive
patches, or temporary restoration with resin that is specified in the
MCAI.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 721 products of U.S. registry.
The actions that are required by AD 2010-23-07, Amendment 39-16496
(75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR
78883)), and retained in this proposed AD take about 11 work-hours per
product, at an average labor rate of $85 per work hour. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the currently required actions on U.S. operators to be
$674,135, or $935 per product.
We estimate that it would take about 11 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 $674,135, or $935
per product.
In addition, we estimate that any necessary follow-on actions would
take about 12 work-hours and require parts costing $10,000, for a cost
of $11,020 per product. We have no way of determining the number of
products that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
[[Page 60066]]
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 airworthiness directive
(AD) 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)), and adding the following
new AD:
Airbus: Docket No. FAA-2012-1034; Directorate Identifier 2011-NM-
051-AD.
(a) Comments Due Date
We must receive comments by November 16, 2012.
(b) Affected ADs
This AD supersedes AD 2010-23-07, Amendment 39-16496 (75 FR
68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)).
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any
category; all serial numbers having a rudder with a part number (P/
N) and serial number (S/N) listed in table 1, 2, 3, 4a and 4b, 5a
and 5b, or 6 to paragraph (c) of this AD.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-111, -211, -212, -214, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
Table 1 to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N Affected rudder S/N
------------------------------------------------------------------------
D554 71000 010 00........................... TS-1069
D554 71000 010 00........................... TS-1090
D554 71000 012 00........................... TS-1227
D554 71000 014 00........................... TS-1350
D554 71000 014 00........................... TS-1366
D554 71000 014 00........................... TS-1371
D554 71000 014 00........................... TS-1383
D554 71000 014 00........................... TS-1387
D554 71000 016 00........................... TS-1412
D554 71000 018 00........................... TS-1443
D554 71000 018 00........................... TS-1444
D554 71000 018 00........................... TS-1468
D554 71000 020 00........................... TS-1480
D554 71000 020 00........................... TS-1491
D554 71000 020 00........................... TS-1495
D554 71000 020 00........................... TS-1498
D554 71000 020 00........................... TS-1499
D554 71000 020 00........................... TS-1500
D554 71000 020 00........................... TS-1505
D554 71000 020 00........................... TS-1506
D554 71000 020 00........................... TS-1507
D554 71000 020 00........................... TS-1509
D554 71000 020 00........................... TS-1515
D554 71000 020 00........................... TS-1528
D554 71000 020 00........................... TS-1530
D554 71000 020 00........................... TS-1532
D554 71000 020 00........................... TS-1535
D554 71000 020 00........................... TS-1536
D554 71000 020 00........................... TS-1538
D554 71001 000 00........................... TS-1537
D554 71001 000 00........................... TS-1540
D554 71001 000 00........................... TS-1541
D554 71001 000 00........................... TS-1543
D554 71001 000 00........................... TS-1548
D554 71001 000 00........................... TS-1549
D554 71001 000 00........................... TS-1551
D554 71001 000 00........................... TS-1554
D554 71001 000 00........................... TS-1555
D554 71001 000 00........................... TS-1556
D554 71001 000 00........................... TS-1557
D554 71001 000 00........................... TS-1559
D554 71001 000 00........................... TS-1562
D554 71001 000 00........................... TS-1563
D554 71001 000 00........................... TS-1564
D554 71001 000 00........................... TS-1565
D554 71001 000 00........................... TS-1566
D554 71001 000 00........................... TS-1567
D554 71001 000 00........................... TS-1568
D554 71001 000 00........................... TS-1569
D554 71001 000 00........................... TS-1570
D554 71001 000 00........................... TS-1573
D554 71001 000 00........................... TS-1575
D554 71001 000 00........................... TS-1578
D554 71001 000 00........................... TS-1579
D554 71001 000 00........................... TS-1580
D554 71001 000 00........................... TS-1581
D554 71001 000 00........................... TS-1582
D554 71001 000 00........................... TS-1584
D554 71001 000 00........................... TS-1593
D554 71001 000 00........................... TS-1594
D554 71001 000 00........................... TS-1596
D554 71001 000 00........................... TS-1599
D554 71001 000 00........................... TS-1603
D554 71001 000 00........................... TS-1609
D554 71001 000 00........................... TS-1621
D554 71001 000 00........................... TS-1626
D554 71001 000 00........................... TS-1627
D554 71001 000 00........................... TS-1635
D554 71001 000 00........................... TS-1637
D554 71002 000 00........................... TS-2306
D554 71002 000 00 0001...................... TS-2003
D554 71002 000 00 0001...................... TS-2005
D554 71002 000 00 0001...................... TS-2013
D554 71002 000 00 0001...................... TS-2016
D554 71002 000 00 0001...................... TS-2019
D554 71002 000 00 0001...................... TS-2020
D554 71002 000 00 0001...................... TS-2022
D554 71002 000 00 0001...................... TS-2024
D554 71002 000 00 0001...................... TS-2026
D554 71002 000 00 0001...................... TS-2031
D554 71002 000 00 0001...................... TS-2033
D554 71002 000 00 0001...................... TS-2043
D554 71002 000 00 0001...................... TS-2047
D554 71002 000 00 0001...................... TS-2048
D554 71002 000 00 0001...................... TS-2054
D554 71002 000 00 0001...................... TS-2058
D554 71002 000 00 0001...................... TS-2059
D554 71002 000 00 0001...................... TS-2064
D554 71002 000 00 0001...................... TS-2072
D554 71002 000 00 0001...................... TS-2075
D554 71002 000 00 0001...................... TS-2076
D554 71002 000 00 0001...................... TS-2079
D554 71002 000 00 0001...................... TS-2083
D554 71002 000 00 0001...................... TS-2089
D554 71002 000 00 0002...................... TS-2090
D554 71002 000 00 0002...................... TS-2095
D554 71002 000 00 0002...................... TS-2103
D554 71002 000 00 0002...................... TS-2116
D554 71002 000 00 0002...................... TS-2122
D554 71002 000 00 0002...................... TS-2133
D554 71002 000 00 0002...................... TS-2142
D554 71002 000 00 0002...................... TS-2147
D554 71002 000 00 0002...................... TS-2157
D554 71002 000 00 0002...................... TS-2158
D554 71002 000 00 0002...................... TS-2162
D554 71002 000 00 0002...................... TS-2167
D554 71002 000 00 0002...................... TS-2174
D554 71002 000 00 0002...................... TS-2176
D554 71002 000 00 0002...................... TS-2181
D554 71002 000 00 0002...................... TS-2189
D554 71002 000 00 0002...................... TS-2191
D554 71002 000 00 0002...................... TS-2203
D554 71002 000 00 0002...................... TS-2205
D554 71002 000 00 0002...................... TS-2207
D554 71002 000 00 0002...................... TS-2224
D554 71002 000 00 0002...................... TS-2229
D554 71002 000 00 0002...................... TS-2233
D554 71002 000 00 0002...................... TS-2241
D554 71002 000 00 0002...................... TS-2246
D554 71002 000 00 0002...................... TS-2249
D554 71002 000 00 0002...................... TS-2270
D554 71002 000 00 0002...................... TS-2275
D554 71002 000 00 0002...................... TS-2289
D554 71002 000 00 0002...................... TS-2290
D554 71002 000 00 0002...................... TS-2294
D554 71002 000 00 0002...................... TS-2309
D554 71002 000 00 0002...................... TS-2347
D554 71002 000 00 0002...................... TS-2348
D554 71002 000 00 0002...................... TS-2349
D554 71002 000 00 0002...................... TS-2357
D554 71002 000 00 0002...................... TS-2361
D554 71002 000 00 0002...................... TS-2380
D554 71002 000 00 0002...................... TS-2383
D554 71002 000 00 0002...................... TS-2390
D554 71002 000 00 0002...................... TS-2394
D554 71002 000 00 0002...................... TS-2396
D554 71002 000 00 0002...................... TS-2401
D554 71002 000 00 0002...................... TS-2406
D554 71002 000 00 0002...................... TS-2461
D554 71002 000 00 0002...................... TS-2468
D554 71002 000 00 0002...................... TS-2516
D554 71002 000 00 0002...................... TS-2537
D554 71002 000 00 0002...................... TS-2543
D554 71002 000 00 0002...................... TS-2546
D554 71002 000 00 0002...................... TS-2619
D554 71002 000 00 0002...................... TS-2684
D554 71002 000 00 0003...................... TS-2752
D554 71002 000 00 0003...................... TS-2869
D554 71002 000 00 0003...................... TS-2876
D554 71002 000 00 0003...................... TS-2970
D554 71002 000 00 0003...................... TS-2971
D554 71002 000 00 0003...................... TS-2987
D554 71004 000 00 0000...................... TS-3083
D554 71004 000 00 0000...................... TS-3197
------------------------------------------------------------------------
Note 1 to paragraph (c) of this AD: For table 1 to paragraph (c)
of this AD, 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
[[Page 60067]]
density of 24 kilogram (kg)/meters cubed (m\3\).
Table 2 to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N Affected rudder S/N
------------------------------------------------------------------------
D554-71000-014-00........................... TS-1278
D554-71002-000-00-0001...................... TS-2081
D554-71002-000-00-0002...................... TS-2125
D554-71002-000-00-0002...................... TS-2129
D554-71002-000-00-0002...................... TS-2160
D554-71002-000-00-0002...................... TS-2201
D554-71002-000-00-0002...................... TS-2328
D554-71002-000-00-0002...................... TS-2425
D554-71002-000-00-0002...................... TS-2511
D554-71002-000-00-0003...................... TS-2768
D554-71002-000-00-0003...................... TS-2999
D554-71002-000-00-0003...................... TS-3004
D554-71002-000-00-0003...................... TS-3051
D554-71004-000-00-0001...................... TS-3288
------------------------------------------------------------------------
Table 3 to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N Affected rudder S/N
------------------------------------------------------------------------
D554-71000-008-00........................... TS-1032
D554-71000-010-00........................... TS-1092
D554-71000-014-00........................... TS-1314
D554-71000-018-00........................... TS-1445
D554-71000-020-00........................... TS-1520
D554-71002-000-00-0001...................... TS-2037
D554-71002-000-00-0002...................... TS-2109
D554-71002-000-00-0002...................... TS-2123
D554-71002-000-00-0002...................... TS-2124
D554-71002-000-00-0002...................... TS-2424
D554-71002-000-00-0002...................... TS-2559
D554-71002-000-00-0003...................... TS-3061
D554-71004-000-00-0001...................... TS-3694
D554-71004-000-00-0001...................... TS-3709
D554-71004-000-00-0002...................... TS-4148
------------------------------------------------------------------------
Note 2 to paragraph (c) of this AD: For table 3 to paragraph (c)
of this AD, only rudder P/N D554-71000-008-00 having affected rudder
S/N TS-1032, and rudder P/N D554-71000-010-00 having affected rudder
S/N TS-1092, have a core density of 24 kg/m\3\.
Table 4a to Paragraph (c) of this AD
------------------------------------------------------------------------
Rudder P/N with any S/N listed in table 4b to paragraph (c) of this AD
-------------------------------------------------------------------------
D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000
------------------------------------------------------------------------
Table 4b to Paragraph (c) of This AD
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Affected S/N for rudders listed in table 4a to paragraph (c) of this AD
----------------------------------------------------------------------------------------------------------------
TS-1368 TS-1616 TS-2080 TS-2159 TS-2222 TS-2276 TS-2327
TS-1389 TS-1619 TS-2082 TS-2163 TS-2223 TS-2279 TS-2330
TS-1496 TS-1622 TS-2084 TS-2168 TS-2227 TS-2280 TS-2331
TS-1501 TS-1632 TS-2085 TS-2169 TS-2228 TS-2281 TS-2332
TS-1503 TS-1639 TS-2086 TS-2170 TS-2230 TS-2284 TS-2333
TS-1508 TS-2004 TS-2094 TS-2172 TS-2231 TS-2285 TS-2334
TS-1516 TS-2008 TS-2096 TS-2175 TS-2232 TS-2286 TS-2336
TS-1527 TS-2010 TS-2097 TS-2177 TS-2234 TS-2293 TS-2337
TS-1529 TS-2012 TS-2098 TS-2179 TS-2235 TS-2297 TS-2338
TS-1534 TS-2014 TS-2100 TS-2182 TS-2236 TS-2298 TS-2339
TS-1545 TS-2017 TS-2101 TS-2183 TS-2238 TS-2299 TS-2340
TS-1547 TS-2018 TS-2106 TS-2185 TS-2240 TS-2302 TS-2341
TS-1553 TS-2023 TS-2113 TS-2192 TS-2242 TS-2303 TS-2343
TS-1560 TS-2025 TS-2115 TS-2193 TS-2244 TS-2304 TS-2346
TS-1561 TS-2029 TS-2118 TS-2195 TS-2245 TS-2305 TS-2352
TS-1571 TS-2032 TS-2126 TS-2199 TS-2248 TS-2307 TS-2353
TS-1572 TS-2034 TS-2130 TS-2200 TS-2250 TS-2310 TS-2354
TS-1574 TS-2039 TS-2131 TS-2204 TS-2251 TS-2311 TS-2355
TS-1576 TS-2040 TS-2132 TS-2206 TS-2252 TS-2312 TS-2356
TS-1577 TS-2041 TS-2134 TS-2208 TS-2254 TS-2313 TS-2358
TS-1583 TS-2046 TS-2136 TS-2209 TS-2258 TS-2315 TS-2360
TS-1585 TS-2050 TS-2140 TS-2210 TS-2259 TS-2316 TS-2362
TS-1588 TS-2051 TS-2143 TS-2211 TS-2260 TS-2319 TS-2363
TS-1591 TS-2052 TS-2144 TS-2213 TS-2261 TS-2320 TS-2364
TS-1600 TS-2053 TS-2145 TS-2216 TS-2262 TS-2321 TS-2365
TS-1602 TS-2056 TS-2149 TS-2217 TS-2265 TS-2322 TS-2366
TS-1607 TS-2060 TS-2152 TS-2218 TS-2268 TS-2323 TS-2367
TS-1608 TS-2069 TS-2154 TS-2220 TS-2271 TS-2325 TS-2370
TS-1614 TS-2070 TS-2155 TS-2221 TS-2272 TS-2326 TS-2371
TS-2372 TS-2483 TS-2583 TS-2665 TS-2743 TS-2813 TS-2878
TS-2373 TS-2484 TS-2584 TS-2666 TS-2744 TS-2814 TS-2879
TS-2374 TS-2486 TS-2585 TS-2667 TS-2745 TS-2815 TS-2880
TS-2377 TS-2488 TS-2586 TS-2668 TS-2747 TS-2816 TS-2881
TS-2381 TS-2491 TS-2587 TS-2671 TS-2749 TS-2818 TS-2882
TS-2382 TS-2493 TS-2590 TS-2674 TS-2751 TS-2819 TS-2885
TS-2387 TS-2494 TS-2591 TS-2675 TS-2753 TS-2821 TS-2886
TS-2388 TS-2498 TS-2592 TS-2676 TS-2754 TS-2822 TS-2890
TS-2392 TS-2499 TS-2593 TS-2677 TS-2755 TS-2823 TS-2891
TS-2393 TS-2501 TS-2596 TS-2679 TS-2756 TS-2824 TS-2892
TS-2395 TS-2505 TS-2597 TS-2680 TS-2757 TS-2826 TS-2893
TS-2397 TS-2506 TS-2601 TS-2681 TS-2758 TS-2827 TS-2896
TS-2398 TS-2508 TS-2602 TS-2682 TS-2759 TS-2828 TS-2897
TS-2399 TS-2510 TS-2603 TS-2683 TS-2760 TS-2830 TS-2898
[[Page 60068]]
TS-2407 TS-2512 TS-2605 TS-2685 TS-2762 TS-2831 TS-2899
TS-2408 TS-2514 TS-2606 TS-2688 TS-2765 TS-2832 TS-2900
TS-2409 TS-2517 TS-2611 TS-2689 TS-2771 TS-2833 TS-2903
TS-2410 TS-2518 TS-2612 TS-2691 TS-2772 TS-2834 TS-2904
TS-2411 TS-2521 TS-2614 TS-2695 TS-2773 TS-2835 TS-2906
TS-2412 TS-2522 TS-2615 TS-2697 TS-2775 TS-2836 TS-2907
TS-2415 TS-2527 TS-2616 TS-2698 TS-2776 TS-2837 TS-2908
TS-2417 TS-2529 TS-2617 TS-2699 TS-2778 TS-2838 TS-2909
TS-2421 TS-2532 TS-2620 TS-2700 TS-2779 TS-2839 TS-2910
TS-2422 TS-2536 TS-2625 TS-2701 TS-2780 TS-2840 TS-2911
TS-2423 TS-2540 TS-2626 TS-2707 TS-2782 TS-2843 TS-2913
TS-2427 TS-2544 TS-2628 TS-2710 TS-2783 TS-2844 TS-2914
TS-2428 TS-2545 TS-2629 TS-2711 TS-2784 TS-2845 TS-2916
TS-2435 TS-2547 TS-2630 TS-2712 TS-2785 TS-2846 TS-2917
TS-2437 TS-2551 TS-2631 TS-2713 TS-2786 TS-2848 TS-2919
TS-2440 TS-2552 TS-2632 TS-2714 TS-2788 TS-2849 TS-2920
TS-2444 TS-2553 TS-2634 TS-2716 TS-2790 TS-2850 TS-2922
TS-2446 TS-2554 TS-2635 TS-2717 TS-2791 TS-2851 TS-2923
TS-2447 TS-2555 TS-2636 TS-2719 TS-2792 TS-2852 TS-2924
TS-2453 TS-2558 TS-2637 TS-2722 TS-2793 TS-2853 TS-2925
TS-2455 TS-2562 TS-2640 TS-2724 TS-2794 TS-2854 TS-2927
TS-2458 TS-2563 TS-2641 TS-2725 TS-2795 TS-2855 TS-2928
TS-2460 TS-2566 TS-2642 TS-2726 TS-2796 TS-2856 TS-2929
TS-2463 TS-2568 TS-2644 TS-2727 TS-2797 TS-2857 TS-2930
TS-2466 TS-2570 TS-2647 TS-2728 TS-2799 TS-2860 TS-2932
TS-2467 TS-2571 TS-2648 TS-2732 TS-2801 TS-2861 TS-2933
TS-2471 TS-2572 TS-2650 TS-2734 TS-2803 TS-2862 TS-2934
TS-2472 TS-2573 TS-2651 TS-2735 TS-2804 TS-2863 TS-2935
TS-2474 TS-2574 TS-2653 TS-2736 TS-2805 TS-2864 TS-2937
TS-2476 TS-2575 TS-2656 TS-2738 TS-2807 TS-2865 TS-2938
TS-2477 TS-2576 TS-2657 TS-2739 TS-2808 TS-2868 TS-2939
TS-2478 TS-2579 TS-2658 TS-2740 TS-2810 TS-2872 TS-2943
TS-2481 TS-2580 TS-2659 TS-2741 TS-2811 TS-2874 TS-2944
TS-2482 TS-2581 TS-2662 TS-2742 TS-2812 TS-2877 TS-2946
TS-2948 TS-3040 TS-3113 TS-3177 TS-3249 TS-3689 TS-3928
TS-2949 TS-3043 TS-3114 TS-3178 TS-3250 TS-3690 TS-3936
TS-2950 TS-3046 TS-3116 TS-3179 TS-3251 TS-3695 TS-3939
TS-2951 TS-3049 TS-3119 TS-3180 TS-3252 TS-3699 TS-3942
TS-2953 TS-3050 TS-3120 TS-3181 TS-3253 TS-3702 TS-3950
TS-2954 TS-3052 TS-3121 TS-3182 TS-3255 TS-3703 TS-3958
TS-2955 TS-3054 TS-3122 TS-3183 TS-3256 TS-3704 TS-3961
TS-2957 TS-3055 TS-3123 TS-3184 TS-3257 TS-3706 TS-3968
TS-2958 TS-3056 TS-3124 TS-3185 TS-3259 TS-3708 TS-3987
TS-2959 TS-3058 TS-3125 TS-3186 TS-3262 TS-3710 TS-3993
TS-2960 TS-3060 TS-3126 TS-3188 TS-3271 TS-3717 TS-3995
TS-2962 TS-3065 TS-3127 TS-3189 TS-3276 TS-3718 TS-4003
TS-2964 TS-3066 TS-3129 TS-3191 TS-3278 TS-3734 TS-4027
TS-2965 TS-3071 TS-3131 TS-3193 TS-3282 TS-3743 TS-4031
TS-2968 TS-3072 TS-3132 TS-3194 TS-3286 TS-3761 TS-4087
TS-2969 TS-3074 TS-3133 TS-3195 TS-3289 TS-3772 TS-4099
TS-2973 TS-3075 TS-3134 TS-3198 TS-3290 TS-3780 TS-4118
TS-2976 TS-3076 TS-3135 TS-3200 TS-3291 TS-3789 TS-4145
TS-2980 TS-3077 TS-3138 TS-3201 TS-3292 TS-3805 TS-4146
TS-2984 TS-3078 TS-3139 TS-3202 TS-3295 TS-3820 TS-4147
TS-2985 TS-3079 TS-3140 TS-3204 TS-3297 TS-3821 TS-4163
TS-2986 TS-3080 TS-3141 TS-3205 TS-3306 TS-3822 TS-4167
TS-2988 TS-3081 TS-3142 TS-3207 TS-3309 TS-3824 TS-4175
TS-2991 TS-3082 TS-3143 TS-3210 TS-3310 TS-3825 TS-4178
TS-2998 TS-3084 TS-3144 TS-3215 TS-3317 TS-3839 TS-4181
TS-3001 TS-3087 TS-3145 TS-3216 TS-3320 TS-3841 TS-4186
TS-3002 TS-3088 TS-3148 TS-3217 TS-3328 TS-3843 TS-4195
TS-3003 TS-3089 TS-3149 TS-3218 TS-3388 TS-3844 TS-4212
TS-3005 TS-3090 TS-3151 TS-3219 TS-3392 TS-3846 TS-4232
TS-3006 TS-3091 TS-3154 TS-3221 TS-3395 TS-3849 TS-4271
TS-3009 TS-3093 TS-3155 TS-3222 TS-3429 TS-3850 TS-4331
TS-3011 TS-3094 TS-3156 TS-3223 TS-3441 TS-3851 TS-4345
TS-3016 TS-3096 TS-3158 TS-3224 TS-3516 TS-3853 TS-4366
TS-3018 TS-3097 TS-3159 TS-3226 TS-3561 TS-3855 TS-4396
TS-3020 TS-3098 TS-3160 TS-3227 TS-3567 TS-3857 TS-4401
TS-3021 TS-3100 TS-3161 TS-3232 TS-3574 TS-3860 TS-4420
TS-3025 TS-3101 TS-3162 TS-3234 TS-3590 TS-3862 TS-4461
TS-3026 TS-3102 TS-3164 TS-3235 TS-3591 TS-3863 TS-4480
TS-3027 TS-3103 TS-3166 TS-3236 TS-3595 TS-3871 TS-4636
TS-3028 TS-3104 TS-3167 TS-3237 TS-3598 TS-3878 TS-4651
[[Page 60069]]
TS-3030 TS-3105 TS-3168 TS-3240 TS-3609 TS-3879 TS-4678
TS-3031 TS-3106 TS-3169 TS-3241 TS-3625 TS-3882 TS-4696
TS-3032 TS-3107 TS-3170 TS-3242 TS-3638 TS-3883 TS-4770
TS-3033 TS-3108 TS-3171 TS-3243 TS-3650 TS-3885 N/A
TS-3034 TS-3109 TS-3172 TS-3244 TS-3669 TS-3910 N/A
TS-3035 TS-3110 TS-3174 TS-3245 TS-3684 TS-3914 N/A
TS-3037 TS-3111 TS-3175 TS-3247 TS-3685 TS-3921 N/A
TS-3038 TS-3112 TS-3176 TS-3248 TS-3687 TS-3924 N/A
----------------------------------------------------------------------------------------------------------------
Table 5a to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N with any S/N listed in table 5b to paragraph (c) of this AD
-------------------------------------------------------------------------
D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000
------------------------------------------------------------------------
Table 5b to Paragraph (c) of This AD
------------------------------------------------------------------------
-------------------------------------------------------------------------
TS-2141
TS-2269
TS-2274
TS-2295
TS-2317
TS-2664
TS-2715
------------------------------------------------------------------------
Table 6 to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N Affected rudder S/N
------------------------------------------------------------------------
D554 71000 020 00........................... TS-1494
D554 71002 000 00 0002...................... TS-2212
------------------------------------------------------------------------
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by reports of surface defects on rudders
that were the result of debonding between the skin and honeycomb
core. We are issuing this AD to detect and correct extended de-
bonding, which might 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 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) Retained Repetitive Inspections of Rudders With a Core Density of
24 kg/m\3\
This paragraph restates the requirements of paragraph (g) of AD
2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). For rudders identified
in table 1 to paragraph (c) of this AD with a honeycomb core density
of 24 kg/m\3\ (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 01, dated
June 10, 2009; or Airbus AOT A320-55A1038, Revision 02, dated
September 28, 2009; for the locations defined in the applicable AOT
specified in this paragraph.
(1) Within 200 days after December 10, 2010 (the effective date
of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883))): Perform a vacuum loss
inspection on the rudder reinforced area.
(2) Within 20 months after December 10, 2010 (the effective date
of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883))): 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 December 10, 2010 (the effective date
of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883))): 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 December 10, 2010 (the effective date
of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883))): 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) Retained Repetitive Inspections of Rudders Without a Core Density
of 24 kg/m\3\
This paragraph restates the requirements of paragraph (h) of AD
2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). For rudders that do not
have a honeycomb core density of 24 kg/m\3\ (all rudders identified
in table 1 to paragraph (c) 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 01,
dated June 10, 2009; or Airbus AOT A320-55A1038, Revision 02, dated
September 28, 2009; for the locations defined in the applicable AOT
specified in this paragraph. As of the effective date of this AD,
use only Airbus AOT A320-55A1038, Revision 02, dated September 28,
2009. For this paragraph, ``reference date'' is defined as December
10, 2010 (the effective date of AD 2010-23-07), 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) Retained Corrective Actions for De-Bonding
This paragraph restates the requirements of paragraph (i) of AD
2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). 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
[[Page 60070]]
in accordance with the approved data provided, or repair the
debonding using a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent). After the effective date of this AD, repair the debonding
using only a method approved by either the Manager, International
Branch, ANM-116; or the EASA (or its delegated agent).
(j) Retained Reporting for Findings From Actions Required by
Paragraphs (g) and (h) of this AD
This paragraph restates the requirements of paragraph (j) of AD
2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). 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 either the Manager,
Seer1/Seer2/Seer3 Customer Services, fax +33 (0)5 61 93 28 73, email
region1.structurerepairsupport@airbus.com,
region2.structurerepairsupport@airbus.com, or
region3.structurerepairsupport@airbus.com; or AIRTAC (Airbus
Technical AOG Center) Customer Services, telephone +33 (0)5 61 93 34
00, fax +33 (0)5 61 93 35 00, email airtac@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;
email nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after December 10, 2010 (the
effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181,
November 5, 2010; corrected December 17, 2010 (75 FR 78883))):
Submit the report within 30 days after the inspection.
(2) For any inspection done before December 10, 2010 (the
effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181,
November 5, 2010; corrected December 17, 2010 (75 FR 78883))):
Submit the report within 30 days after December 10, 2010.
(k) Retained Inspection in Additional Areas
This paragraph restates the provisions of paragraph (k) of AD
2010-23-07, Amendment 39-16496, (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). 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
December 10, 2010 (the effective date of AD 2010-23-07), in
accordance with Airbus AOT A320-55A1038, dated April 22, 2009; or
Airbus Technical Disposition TD/K4/S2/27051/2009, Issue B, dated
February 25, 2009; are compliant with this AD only for the areas
inspected. Additional areas defined in Section 0, ``Reason for
Revision,'' of Airbus AOT A320-55A1038, Revision 01, dated June 10,
2009; or 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) Retained Parts Installation Limitations
This paragraph restates the requirements of paragraph (l) of AD
2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010;
corrected December 17, 2010 (75 FR 78883)). After December 10, 2010
(the effective date of AD 2010-23-07), no rudder listed in table 1
to paragraph (c) of this AD may be installed on any airplane, unless
the rudder is inspected in accordance with paragraph (g) or (h) of
this AD, as applicable, and all applicable actions specified in
paragraph (i) of this AD are done.
(m) New Restoration of Vacuum Loss Holes
If no de-bonding is found during any inspection required by
paragraph (g) or (h) of this AD: Before further flight, restore the
vacuum loss holes by doing a permanent restoration with resin, in
accordance with Note 3 of Airbus AOT A320-55A1038, Revision 02,
dated September 28, 2009. Before doing the resin injection, do a
local ultrasound inspection in reinforced areas, and a thermography
inspection in other areas, for damage, in accordance with Note 3 of
Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. If
any damage is found during any inspection required by this
paragraph: Before further flight, repair the damage using a method
approved by either the Manager, International Branch, ANM-116; or
the EASA (or its delegated agent).
(n) New X-Ray, Elasticity Laminate Checker (ELCh), Vacuum Loss, or
Thermography Inspection
For rudders identified in table 2 to paragraph (c) of this AD,
do the actions specified in paragraphs (n)(1) and (n)(2) of this AD,
in accordance with Airbus AOT A320-55A1039, dated November 4, 2009,
for the locations defined in that AOT. For this paragraph,
``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 20 months after the effective date of this AD, or
within 200 days after the reference date, whichever occurs first:
Perform X-ray, and/or ELCh, and/or vacuum loss, and/or thermography
inspections for damage, as applicable to rudder part number and
serial number, in accordance with the instructions of paragraph
4.2.2.1.1. of Airbus AOT A320-55A1039, dated November 4, 2009.
(2) At the applicable time specified in paragraph (n)(2)(i) or
(n)(2)(ii) of this AD, send the developed X-ray films and the film
layout arrangement, if applicable, to Attn: SDC32 Technical Data and
Documentation Services, Airbus Customer Services Directorate, 1 Rond
Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax (+33) 5 61
93 28 06; email sb.reporting@airbus.com.
(i) If the inspection was done on or after the effective date of
this AD: Submit the X-ray films and the film layout arrangement
within 10 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the X-ray films and the film layout arrangement
within 10 days after the effective date of this AD.
(3) If any damage is found during any inspection required by
paragraph (n) of this AD: Before further flight, repair the damage
using a method approved by either the Manager, International Branch,
ANM-116; or the EASA (or its delegated agent).
(o) New ELCh Inspection, Vacuum Loss Inspection, and Repairs
For rudders identified in table 2 to paragraph (c) of this AD:
Within 1,500 flight cycles or 200 days after doing the requirements
of paragraph (n)(1) of this AD, whichever occurs first, do the
actions specified in paragraphs (o)(1) and (o)(2) of this AD.
(1) Perform an ELCh inspection for damage on the rudder trailing
edge area, in accordance with the instructions of paragraph
4.2.2.1.2. of Airbus AOT A320-55A1039, dated November 4, 2009. In
case of no finding, 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.
(2) Perform a vacuum loss inspection for damage of the other
areas (splice/lower rib/upper edge/leading edge/other specified
locations), in accordance with the instructions of paragraph
4.2.2.1.2. of Airbus AOT A320-55A1039, dated November 4, 2009.
(3) If any damage is found during any inspection required by
paragraph (o) of this AD: Before further flight, repair the damage
using a method approved by either the Manager, International Branch,
ANM-116; or the EASA (or its delegated agent).
(p) New Restorations and Inspections of Certain Vacuum Loss Holes, and
Repairs
If no damage is found during any inspection required by
paragraph (o) of this AD: Before further flight, restore the vacuum
loss holes by doing a permanent restoration with resin, in
accordance with Note 3 of Airbus AOT A320-55A1039, dated November 4,
2009. Before doing the resin injection, do a local ultrasound
inspection in reinforced areas, and a thermography inspection in
other areas, for damage, in accordance with Note 3 of Airbus AOT
A320-55A1039, dated November 4, 2009. If any damage is found during
any inspection required by this paragraph: Before further flight,
repair the damage using a method approved by either the Manager,
International Branch, ANM-116; or the EASA (or its delegated agent).
(q) New Rudder Replacement for Rudders Identified in Table 3 to
Paragraph (c) of This AD
For rudders identified in table 3 to paragraph (c) of this AD,
do the actions specified in paragraphs (q)(1) and (q)(2) of this AD,
in accordance with the instruction of Airbus AOT A320-55A1039, dated
November 4, 2009, for the locations defined in that AOT. For this
paragraph, ``reference date'' is defined as the effective date of
this
[[Page 60071]]
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) For rudders identified in table 3 to paragraph (c) of this
AD with a honeycomb core density of 24 kg/m\3\ (rudder P/N D554-
71000-008-00 having affected rudder S/N TS-1032 and rudder P/N D554-
71000-010-00 having affected rudder S/N TS-1092): Within 200 days
after the effective date of this AD, replace the rudder with a new
rudder, in accordance with a method approved by the Manager,
International Branch, ANM-116; or the EASA (or its delegated agent).
(2) For rudders identified in table 3 to paragraph (c) of this
AD that do not have a honeycomb core density of 24 kg/m\3\ (all
except rudder P/N D554-71000-008-00 having affected rudder S/N TS-
1032 and rudder P/N D554-71000-010-00 having affected rudder S/N TS-
1092): Within 20 months after the effective date of this AD or
within 200 days after the reference date, whichever occurs first,
replace the rudder with a new rudder, in accordance with a method
approved by the Manager, International Branch, ANM-116.
(r) New Vacuum Loss Inspection for Reinforced Areas of Rudder
Identified in Table 4 to Paragraph (c) of This AD
For rudders identified in tables 4a and 4b to paragraph (c) of
this AD: At the later of the times specified in paragraphs (r)(1)
and (r)(2) of this AD, perform a vacuum loss inspection on the
rudder reinforced area for damage, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-55-1035,
Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus
Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes).
(1) Before the rudder accumulates 17,000 total flight cycles
from its first installation on an airplane without exceeding 20
months from the effective date of this AD.
(2) Within 200 days after the effective date of this AD.
(s) New ELCh Inspection for Rudder Trailing Edge Area
For rudders identified in tables 4a and 4b to paragraph (c) of
this AD: Within 20 months after the effective date of this AD,
perform an ELCh inspection for damage on the rudder trailing edge
area, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for
Model A320 airplanes); Airbus Service Bulletin A320-55-1036,
Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes);
or Airbus Service Bulletin A320-55-1037, Revision 01, dated July 2,
2010 (for Model A319 airplanes). 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.
(t) New ELCh Inspection for Additional Rudder Areas
For rudders identified in tables 4a and 4b to paragraph (c) of
this AD: At the later of the times specified in paragraphs (t)(1)
and (t)(2) of this AD, perform an ELCh inspection for damage of the
other areas (splice/lower rib/upper edge/leading edge/other
specified locations) for damage, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-55-1035,
Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus
Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes).
Repeat the inspection thereafter at intervals not to exceed 1,500
flight cycles or 200 days, whichever comes first.
(1) Before the rudder accumulates 17,000 total flight cycles
from its first installation on an airplane without exceeding 20
months from the effective date of this AD.
(2) Within 200 days after the effective date of this AD.
(u) New Vacuum Loss Inspection for Certain Areas of Rudders Identified
in Tables 4a and 4b to Paragraph (c) of This AD
For rudders identified in tables 4a and 4b of this AD: Within 20
months after the effective date of this AD, perform a vacuum loss
inspection for damage of the lower rib, upper edge, leading edge,
and other specified locations, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-55-1035, Revision 01,
dated July 2, 2010 (for Model A320 airplanes); Airbus Service
Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model
A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037,
Revision 01, dated July 2, 2010 (for Model A319 airplanes).
Accomplishment of the actions specified in this paragraph terminates
the requirements of paragraph (t) of this AD.
(v) New Corrective Actions for Certain Inspections
In case of damage found during any inspection required by
paragraph (r), (s), (t), or (u) of this AD: Before further flight,
repair the damage using a method approved by either the Manager,
International Branch, ANM-116; or the EASA (or its delegated agent).
(w) New Restorations and Inspections of Certain Vacuum Loss Holes, and
Repairs
If no damage is found during any inspection required by
paragraph (r) or (u) of this AD: Before further flight, restore the
vacuum loss holes by doing a permanent restoration with resin, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model
A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01,
dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus
Service Bulletin A320-55-1037, Revision 01, dated July 2, 2010 (for
Model A319 airplanes). Before doing the resin injection, do a local
ultrasound inspection in reinforced areas, and a thermography
inspection in other areas, for damage, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-55-1035,
Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus
Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). If
any damage is found during any inspection required by this
paragraph: Before further flight, repair the damage using a method
approved by either the Manager, International Branch, ANM-116; or
the EASA (or its delegated agent).
(x) Credit for Certain Previous Actions
This paragraph provides credit for the inspections required by
paragraphs (r), (s), (t), (u), and (w) of this AD only for the
inspected area for rudders identified in tables 4a and 4b to
paragraph (c) of this AD, if the area passed the inspection before
the effective date of this AD using Airbus Service Bulletin A320-55-
1035, dated February 17, 2010 (for Model A320 airplanes); Airbus
Service Bulletin A320-55-1036, dated February 17, 2010 (for Model
A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037,
dated February 17, 2010 (for Model A319 airplanes). For all other
inspected areas, the repetitive inspections required by paragraph
(s), (t), and (w) of this AD are still required.
(y) New ELCh Inspection and Repairs for Certain Rudders
For rudders identified in tables 5a and 5b to paragraph (c) of
this AD: Within 4,500 flight cycles but not sooner than 4,000 flight
cycles after the sampling inspection, perform an ELCh inspection for
damage on the rudder trailing edge area, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-55-1035,
Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus
Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for
Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes).
Repeat the inspection within 4,500 flight cycles, but not sooner
than 4,000 flight cycles after the last inspection. If any damage is
found during any inspection required by paragraph (y) of this AD:
Before further flight, repair the damage using a method approved by
either the Manager, International Branch, ANM-116; or the EASA (or
its delegated agent).
(z) Credit for Certain Other Previous Actions
This paragraph provides credit for the inspection required by
paragraph (y) of this AD only for the inspected area for rudders
identified in tables 5a and 5b to paragraph (c) of this AD that have
passed the inspection before the effective date of this AD using
Airbus Service Bulletin A320-55-1035, dated February 17, 2010 (for
Model A320 airplanes); Airbus Service Bulletin A320-55-1036, dated
February 17, 2010 (for Model A318 and A321 airplanes); or Airbus
Service Bulletin A320-55-1037, dated February 17, 2010 (for Model
A319 airplanes). For all inspection areas, the repetitive
inspections required by paragraph (y) of this AD are still required.
[[Page 60072]]
(aa) New Repetitive Inspections of Rudders Identified in Table 6 to
Paragraph (c) of This AD
For rudders identified in table 6 to paragraph (c) of this AD,
do the actions specified in paragraphs (aa)(1), (aa)(2), (aa)(3),
and (aa)(4) of this AD, in accordance with Airbus AOT A320-55A1038,
Revision 02, dated September 28, 2009. For this paragraph,
``reference date'' is defined as the date when the rudder will
accumulate 20,000 total flight cycles from its first installation on
an airplane.
(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.
(bb) New De-Bonding Corrective Actions
In case of de-bonding found during any inspection required by
paragraph (aa) 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.
(cc) New Restoration of Vacuum Loss Holes
If no de-bonding is found during any inspection required by
paragraph (aa) of this AD: Before further flight, restore the vacuum
loss holes by a permanent restoration with resin, in accordance with
Note 3 of Airbus AOT A320-55A1038, Revision 02, dated September 28,
2009. Before doing the resin injection, do a local ultrasound
inspection in reinforced areas, and a thermography inspection in
other areas, for damage, in accordance with Note 3 of Airbus AOT
A320-55A1038, Revision 02, dated September 28, 2009. If any damage
is found during any inspection required by this paragraph: Before
further flight, repair the damage using a method approved by either
the Manager, International Branch, ANM-116; or the EASA (or its
delegated agent).
(dd) New Reporting for Paragraphs (n), (o), (r), (s), (t), (u), (y),
and (aa) of This AD
At the applicable time specified in paragraph (dd)(1) or (dd)(2)
of this AD, submit a report of the findings (both positive and
negative) of each inspection required by paragraphs (n), (o), (r),
(s), (t), (u), (y), and (aa) 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 either the Manager, Seer1/Seer2/Seer3
Customer Services, fax +33 (0)5 61 93 28 73, email
region1.structurerepairsupport@airbus.com,
region2.structurerepairsupport@airbus.com, or
region3.structurerepairsupport@airbus.com; or AIRTAC (Airbus
Technical AOG Center) Customer Services, telephone +33 (0)5 61 93 34
00, fax +33 (0)5 61 93 35 00, email airtac@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,
email nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after the effective date of
this AD: Submit the report within 10 days after the inspection.
(2) For any inspection done before the effective date of this
AD: Submit the report within 10 days after the effective date of
this AD.
(ee) New Parts Installation Limitation
As of the effective date of this AD, no rudder listed in table
1, 2, 3, 4a, 4b, 5a, 5b, or 6 to paragraph (c) of this AD may be
installed on any airplane, unless the rudder is in compliance with
the requirements of this AD.
(ff) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-
1405; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(gg) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2010-0164, dated
August 5, 2010, and the following service information, for related
information.
(i) Airbus AOT A320-55A1038, dated April 22, 2009.
(ii) Airbus AOT A320-55A1038, Revision 01, dated June 10, 2009.
(iii) Airbus AOT A320-55A1038, Revision 02, dated September 28,
2009.
(iv) Airbus AOT A320-55A1039, dated November 4, 2009.
(v) Airbus Service Bulletin A320-55-1035, Revision 01, dated
July 2, 2010.
(vi) Airbus Service Bulletin A320-55-1036, Revision 01, dated
July 2, 2010.
(vii) Airbus Service Bulletin A320-55-1037, Revision 01, dated
July 2, 2010.
(viii) Airbus Technical Disposition TD/K4/S2/27051/2009, Issue
B, dated February 25, 2009.
(ix) Airbus Technical Disposition TD/K4/S2/27086/2009, Issue E,
dated September 17, 2009.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. 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.
Issued in Renton, Washington, on September 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-24175 Filed 10-1-12; 8:45 am]
BILLING CODE 4910-13-P
