[Federal Register Volume 75, Number 214 (Friday, November 5, 2010)]
[Rules and Regulations]
[Pages 68181-68185]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-27614]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0279; Directorate Identifier 2009-NM-148-AD;
Amendment 39-16496; AD 2010-23-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
Surface defects were visually detected on the rudder of one A319
and one A321 in-service aeroplane.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the defects were a result of de-
bonding between the skin and honeycomb core.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective December 10, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 10,
2010.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
[[Page 68182]]
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on April 2, 2010 (75 FR
16689). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Surface defects were visually detected on the rudder of one A319
and one A321 in-service aeroplane.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the defects were a result of de-
bonding between the skin and honeycomb core.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
This AD requires inspections of specific areas and, when
necessary, the application of corrective actions for those rudders
where production reworks have been identified.
Inspections include vacuum loss inspections for de-bonding of the
rudders in reinforced areas and other areas (splice/lower rib/upper
edge/leading edge/other specified locations), and elasticity laminate
checks for de-bonding of the rudders in the trailing edge area and
other areas (splice/lower rib/upper edge/leading edge/other specified
locations). Corrective actions include contacting Airbus for further
instruction and doing the repair.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Clarify Additional Work in Paragraph (k) of the Proposed AD
Airbus requested that we clarify in paragraph (k) of the proposed
AD that there is additional work for operators to comply with, i.e., in
Airbus All Operators Telex (AOT) A320-55A1038, Revision 02, dated
September 28, 2009. Airbus explained that there is an additional
ultrasonic inspection for rudders on which a temporary vacuum loss hole
restoration with resin or a permanent vacuum loss hole restoration has
been performed previously in the reinforced area.
We agree that additional work is included in Airbus AOT A320-
55A1038, Revision 02, dated September 28, 2009, which is referenced in
the NPRM as the appropriate source of service information. However, the
additional work specified in Airbus AOT A320-55A1038, Revision 02,
dated September 28, 2009, is not required by this final rule.
Therefore, we have revised paragraphs (g) and (h) of the final rule to
allow operators to perform the required actions of this AD in
accordance with Airbus AOT A320-55A1038, Revision 01, dated June 10,
2009; or Revision 02, dated September 28, 2009. Also, we have revised
paragraph (k) of this AD by removing reference to Airbus AOT A320-
55A1038, Revision 02, dated September 28, 2009, to clarify that only
the additional areas specified in Airbus AOT A320-55A1038, Revision 01,
dated June 10, 2009, must be inspected. We might consider further
rulemaking to address the additional work specified in Airbus AOT A320-
55A1038, Revision 02, dated September 28, 2009.
Request To Include Alternative Contact Address for Positive Findings
Airbus requested that we include the Airbus Technical Aircraft on
Ground (AOG) Center (AIRTAC) as a contact to report positive findings
from the inspections in paragraphs (g) and (h) of the NPRM.
We agree to include the AIRTAC as a contact and have revised
paragraph (j) of the final rule accordingly.
Clarification of Paragraph (l) of This AD
We have clarified the statement ``unless the rudder is in
compliance with this AD'' in paragraph (l) of this AD by specifying
that applicable inspections in paragraphs (g) or (h) of this AD must be
done and applicable actions in paragraph (i) of this AD must be done.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 155 products of U.S. registry.
We also estimate that it will take about 11 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $144,925, or $935 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will 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 AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
[[Page 68183]]
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2010-23-07 Airbus: Amendment 39-16496. Docket No. FAA-2010-0279;
Directorate Identifier 2009-NM-148-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
10, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category, all
manufacturer serial numbers (S/Ns), if equipped with carbon fiber
reinforced plastic rudders having part numbers (P/Ns) and S/Ns as
listed in Table 1 of this AD.
Table 1--Rudder Part Number and Affected Rudder Serial Number
------------------------------------------------------------------------
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 71000 000 00.......................... TS-1537
D554 71001 00 000.......................... 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-Z072
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
D55471002 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
[[Page 68184]]
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 11002 000 00 0003..................... TS-2971
D554 71002 000 00 0003..................... TS-2987
D554 11004 000 00 0000..................... TS-3083
D554 71004 000 00 0000..................... TS-3197
------------------------------------------------------------------------
Note 1: Only rudder P/N D554 71000 010 00 having affected rudder
S/N TS-1069 and TS-1090 and rudder P/N D554 71000 012 00 having
affected rudder S/N TS-1227, have a core density of 24 kilogram
(kg)/meters cubed (m\3\).
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Surface defects were visually detected on the rudder of one A319
and one A321 in-service aeroplane.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the defects were a result of de-
bonding between the skin and honeycomb core.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
This AD requires inspections of specific areas and, when
necessary, the application of corrective actions for those rudders
where production reworks have been identified.
Inspections include vacuum loss inspections for de-bonding of the
rudders in reinforced areas and other areas (splice/lower rib/upper
edge/leading edge/other specified locations), and elasticity
laminate checks for de-bonding of the rudders in the trailing edge
area and other areas (splice/lower rib/upper edge/leading edge/other
specified locations). Corrective actions include contacting Airbus
for further instruction and doing the repair.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) For rudders with a honeycomb core density of 24 kg/m[sup3]
(rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069
and TS-1090 and rudder P/N D554 71000 012 00 having affected rudder
S/N TS-1227), do the actions specified in paragraphs (g)(1), (g)(2),
(g)(3), and (g)(4) of this AD, in accordance with Airbus All
Operators Telex (AOT) A320-55A1038, Revision 01, dated June 10,
2009; or Airbus AOT A320-55A1038, Revision 02, dated September 28,
2009; for the locations defined in the AOT.
(1) Within 200 days after the effective date of this AD, perform
a vacuum loss inspection on the rudder reinforced area.
(2) Within 20 months after the effective date of this AD,
perform an elasticity laminate checker inspection on the rudder
trailing edge area. Repeat the inspection two times, at intervals
not to exceed 4,500 flight cycles but not sooner than 4,000 flight
cycles after the last inspection.
(3) Within 200 days after the effective date of this AD, perform
an elasticity laminate checker inspection of the other areas
(splice/lower rib/upper edge/leading edge/other specified
locations). Repeat the inspection at intervals not to exceed 1,500
flight cycles or 200 days, whichever comes first.
(4) Within 20 months after the effective date of this AD,
perform a vacuum loss inspection of the other areas (splice/lower
rib/upper edge/leading edge/other specified locations).
Accomplishment of the action specified in paragraph (g)(4) of this
AD terminates the requirements of paragraph (g)(3) of this AD.
(h) For rudders that do not have a honeycomb core density of 24
kg/m[sup3] (all rudders identified in Table 1 of this AD, except:
Rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069 and
TS-1090 and rudder P/N D554 71000 012 00 having affected rudder S/N
TS-1227), do the actions specified in paragraphs (h)(1), (h)(2),
(h)(3), and (h)(4) of this AD, in accordance with Airbus AOT A320-
55A1038, Revision 01, dated June 10, 2009; or Airbus AOT A320-
55A1038, Revision 02, dated September 28, 2009; for the locations
defined in the AOT. For this AD, ``reference date'' is defined as
the effective date of this AD or the date when the rudder will
accumulate 20,000 total flight cycles from its first installation on
an airplane, whichever occurs later.
(1) Within 200 days after the reference date, perform a vacuum
loss inspection on the rudder reinforced area.
(2) Within 20 months after the reference date, perform an
elasticity laminate checker inspection on the rudder trailing edge
area. Repeat the inspection two times at intervals not to exceed
4,500 flight cycles but not sooner than 4,000 flight cycles after
the last inspection.
(3) Within 200 days after the reference date, perform an
elasticity laminate checker inspection of the other areas (splice/
lower rib/upper edge/leading edge/other specified locations). Repeat
the inspection at intervals not to exceed 1,500 flight cycles or 200
days, whichever comes first.
(4) Within 20 months after the reference date, perform a vacuum
loss inspection of the other areas (splice/lower rib/upper edge/
leading edge/other specified locations). Accomplishment of the
actions specified in this paragraph terminates the requirements of
paragraph (h)(3) of this AD.
(i) In case of de-bonding found during any inspection required
by paragraph (g) or (h) of this AD, before further flight, contact
Airbus for further instructions and apply the associated
instructions and corrective actions in accordance with the approved
data provided.
(j) At the applicable time specified in paragraph (j)(1) or
(j)(2) of this AD, submit a report of the findings (both positive
and negative), of each inspection required by paragraphs (g) and (h)
of this AD. The report must include the inspection results, as
specified in Airbus Technical Disposition TD/K4/S2/27086/2009, Issue
E, dated September 17, 2009. For positive findings, submit the
report to either the Manager, Seer1/Seer2/Seer3 Customer Services;
fax +33 (0)5 61 93 28 73; e-mail
[email protected],
[email protected], or
[email protected], or AIRTAC (Airbus
Technical AOG Center) Customer Services; telephone +33 (0)5 61 93 34
00; fax +33 (0)5 61 93 35 00; e-mail [email protected]. For negative
findings, submit the report to Nicolas Seynaeve, Sees1, Customer
Services; telephone +33 (0)5 61 93 34 38; fax +33 (0)5 61 93 36 14;
e-mail [email protected].
(1) For any inspection done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) For any inspection done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(k) All rudders that have passed the inspection specified in
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3),
and (h)(4) of this AD before the effective date of this AD, in
accordance with Airbus AOT A320-55A1038, dated April 22, 2009; 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, must be inspected as specified in paragraph (g) or (h) of this
AD. For all areas, the repetitive inspections required by paragraph
(g) or (h) of this AD remain applicable.
(l) After the effective date of this AD, no rudder listed in
Table 1 of this AD may be installed on any airplane, unless the
rudder is 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.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(m) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International
[[Page 68185]]
Branch, ANM-116, Transport Airplane Directorate, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Tim
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(n) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0141, dated July 2, 2009, and the service information
identified in Table 2 of this AD, for related information.
Table 2--Airbus Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision/issue Date
----------------------------------------------------------------------------------------------------------------
Airbus All Operators Telex A320-55A1038. Revision 01................ June 10, 2009.
Airbus All Operators Telex A320-55A1038. Revision 02................ September 28, 2009.
Airbus Technical Disposition TD/K4/S2/ Issue E.................... September 17, 2009.
27086/2009.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(o) You must use the service information contained in Table 3 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
Table 3--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision/issue Date
----------------------------------------------------------------------------------------------------------------
Airbus All Operators Telex A320-55A1038* Revision 01................ June 10, 2009.
Airbus All Operators Telex A320-55A1038* Revision 02................ September 28, 2009.
Airbus Technical Disposition TD/K4/S2/ Issue E.................... September 17, 2009.
27086/2009.
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(* The first page of these documents contain the document number, revision level, and date; no other pages
contain this information.)
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(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; e-mail: [email protected]; Internet
http://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html..
Issued in Renton, Washington, on October 26, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-27614 Filed 11-4-10; 8:45 am]
BILLING CODE 4910-13-P