[Federal Register Volume 75, Number 234 (Tuesday, December 7, 2010)]
[Rules and Regulations]
[Pages 75878-75882]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-29457]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0670; Directorate Identifier 2007-NM-339-AD;
Amendment 39-16526; AD 2010-24-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318-111 and A318-112
Airplanes and Model 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:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes [bushings], and/or missing bolts
have been reported in-service. In addition damage to the lower
central support fitting (including cracking) has been reported.
In the worst case scenario a complete failure of the 80VU
fittings in combination with a high load factor or strong vibration
could lead to failure of the rack structure and/or computers or
rupture/disconnection of the cable harnesses to one or more
computers located in the 80VU. This rack contains computers for
Flight Controls, Communication and Radio-navigation. These functions
are duplicated across other racks but during critical phases of
flight the multiple system failures/re-configuration may constitute
an unsafe condition.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 11, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 11,
2011.
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,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (NPRM) to
amend 14 CFR part 39 to include an AD that would apply to the specified
products.
[[Page 75879]]
That supplemental NPRM was published in the Federal Register on August
4, 2010 (75 FR 46873). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes [bushings], and/or missing bolts
have been reported in-service. In addition damage to the lower
central support fitting (including cracking) has been reported.
In the worst case scenario a complete failure of the 80VU
fittings in combination with a high load factor or strong vibration
could lead to failure of the rack structure and/or computers or
rupture/disconnection of the cable harnesses to one or more
computers located in the 80VU. This rack contains computers for
Flight Controls, Communication and Radio-navigation. These functions
are duplicated across other racks but during critical phases of
flight the multiple system failures/re-configuration may constitute
an unsafe condition.
For the reasons described above, EASA AD 2007-0276 was issued to
require repetitive [detailed] inspection of the lower lateral 80VU
fittings for damage and [repetitive detailed] inspection of the
lower central 80VU support for damage and cracking, and the
accomplishment of associated corrective actions, depending on
findings.
Since AD 2007-0276 was issued, Airbus introduced a new
reinforced lower central support for the 80VU.
This [EASA] AD has been revised to introduce the new reinforced
lower central support as an optional terminating action to the
repetitive inspections.
* * * * *
The associated corrective actions include repair or replacement of the
lower lateral fittings and/or replacement of the lower central support.
Modifying the 80VU lower lateral fittings (the modification includes
replacing the 80VU lower lateral fittings) eliminates the need for the
repetitive inspection of the lower lateral fittings. Replacing the 80VU
lower central support (i.e., replacing the pyramid fitting on the 80VU
rack with a new, reinforced fitting) eliminates the need for the
repetitive inspection of the lower central support. 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 comments received.
Request To Allow Credit for Actions Done per Previous Service Bulletin
Lufthansa stated that paragraph (g) of the NPRM specifies that
doing a modification in accordance with Airbus Service Bulletin A320-
25-1557, Revision 02, dated November 5, 2008, terminates the
inspections of the lateral fittings. The commenter stated this is not
correct because any revision of the service bulletin terminates the
inspections.
We infer that Lufthansa requests that we revise paragraph (g) of
the final rule to allow credit for actions done in accordance with
previous issues of Airbus Service Bulletin A320-25-1557. We agree that
previous issues are acceptable; however, it is not necessary to revise
paragraph (g) of the final rule. We give credit for doing actions in
accordance with previous revisions of the service information in
paragraph (l) of the final rule. We have not changed this AD in this
regard.
Request To Defer Corrective Actions
Lufthansa requested that we allow operators to defer doing the
replacement specified in paragraph (j) of the NPRM. The commenter noted
that Airbus Service Bulletin A320-53-1215, dated November 5, 2008, and
EASA AD 2007-0276R1, dated March 18, 2010, both allow deferring the
replacement. The commenter also noted that exhaustive data on cracks
and crack growth are available on request.
We disagree with the request to allow deferring the replacement
required by paragraph (j) of the final rule. Our policy specifies the
requirement to repair known cracks before further flight (though we
might make exceptions to this policy in certain cases of unusual need).
This policy is based on the fact that such damaged airplanes do not
conform to the FAA-certificated type design and, therefore, are not
airworthy until a properly approved repair is made. We consider the
compliance times in this AD to be adequate to allow operators to
acquire parts to have on hand in the event that a crack is detected
during inspection. Therefore, we have determined that, due to the
safety implications and consequences associated with such cracking, any
subject 80VU rack lower central support that is found to be cracked
must have associated corrective actions done before further flight.
However, under the provisions of paragraph (m) of the final rule, we
will consider requests for approval of an extension of the compliance
time if sufficient data are submitted to substantiate that the new
compliance time would provide an acceptable level of safety. We have
not changed the AD in this regard.
Request To Allow Alternate Actions in Lieu of the Replacement in
Paragraph (j) of the NPRM
Lufthansa further requested that we allow alternative actions other
than doing a replacement in accordance with Airbus Service Bulletin
A320-53-1215, dated November 5, 2008, as specified in paragraph (j) of
the NPRM. The commenter stated that Airbus Service Bulletin A320-53-
1215, dated November 5, 2008, and EASA AD 2007-0276R1, dated March 18,
2010, both specify repairing or replacing the pyramid fitting in
accordance with Airbus Service Bulletin A320-25A1555, dated June 14,
2007; or Airbus Service Bulletin A320-25-1557, dated June 14, 2007; as
applicable. The commenter stated that allowing only the replacement in
accordance with Airbus Service Bulletin A320-53-1215, dated November 5,
2008, is more restrictive to operators than necessary for continued
flight safety.
We disagree with the request to allow actions other than the
replacement required by paragraph (j) of this AD. Doing the repair or
replacement of the pyramid fitting in accordance with Airbus Service
Bulletin A320-25A1555, dated June 14, 2007; or Airbus Service Bulletin
A320-25-1557, dated June 14, 2007; as applicable; would require also
doing repetitive inspections. We can better ensure long-term continued
operational safety by design changes to remove the source of the
problem, rather than by repetitive inspections. Long-term inspections
might not provide the degree of safety necessary for the transport
airplane fleet. This determination, along with a better understanding
of the human factors associated with numerous continual inspections,
has led us to consider placing less emphasis on inspections and more
emphasis on design improvements. The replacement required by paragraph
(j) of the final rule is consistent with these conditions. However,
under the provisions of paragraph (m) of the final rule, we will
consider requests for alternative methods of compliance if sufficient
data are submitted to substantiate that the alternative actions would
provide an acceptable level of safety. We have not changed this AD in
this regard.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
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
[[Page 75880]]
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 affects 678 products of U.S. registry. We
also estimate that takes about 82 work-hours per product to comply with
the basic requirements of this AD. The average labor rate is $85 per
work-hour. Required parts cost about $2,592 per product. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these parts.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of this AD to the U.S. operators to be
$6,483,036, or $9,562 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
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:
2010-24-07 Airbus: Amendment 39-16526. Docket No. FAA-2008-0670;
Directorate Identifier 2007-NM-339-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
11, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318-111, A318-112, A319-
111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132,
A319-133, A320-111, A320-211, A320-212, A320-214, A320-231, A320-
232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212,
A321-213, A321-231, and A321-232 airplanes, certificated in any
category, all manufacturer serial numbers, except airplanes on which
Airbus Modification 34804 has been embodied in production or on
which Airbus Service Bulletins A320-25-1557 and A320-53-1215 have
been done in service.
Subject
(d) Air Transport Association (ATA) of America Code 25:
Equipment/Furnishings, and Code 53: Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes [bushings], and/or missing bolts
have been reported in-service. In addition damage to the lower
central support fitting (including cracking) has been reported.
In the worst case scenario a complete failure of the 80VU
fittings in combination with a high load factor or strong vibration
could lead to failure of the rack structure and/or computers or
rupture/disconnection of the cable harnesses to one or more
computers located in the 80VU. This rack contains computers for
Flight Controls, Communication and Radio-navigation. These functions
are duplicated across other racks but during critical phases of
flight the multiple system failures/re-configuration may constitute
an unsafe condition.
* * * * *
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.
Repetitive Inspections of the 80V Rack Lower Lateral Fittings
(g) Prior to the accumulation of 24,000 total flight cycles, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later: Do a special detailed inspection of the 80VU
rack lower lateral fittings for damage (e.g., broken fitting,
missing bolts, migrated bushings, material burr, or rack in contact
with the fitting) of the 80VU rack lower lateral fittings, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008.
Repeat the inspection thereafter at the interval specified in
paragraph (g)(1) or (g)(2) of this AD, as applicable. Modifying the
80VU lower lateral fittings, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-25-1557, Revision 02,
dated November 5, 2008, terminates the inspection requirements of
this paragraph.
(1) For airplanes on which the 80VU rack lower lateral fittings
have not been replaced in accordance with the Airbus Mandatory
Service Bulletin A320-25A1555: Repeat the inspection thereafter at
intervals not to exceed 4,500 flight cycles.
(2) For airplanes on which the 80VU rack lower lateral fittings
have been replaced in accordance with Airbus Mandatory Service
Bulletin A320-25A1555: Do the next inspection within 24,000 flight
cycles after doing the replacement and repeat the
[[Page 75881]]
inspection thereafter at intervals not to exceed 4,500 flight
cycles.
(h) If any damage is found during any inspection required by
paragraph (g) of this AD, do all applicable corrective actions
(inspection and/or repair) in accordance with the Accomplishment
Instructions and timeframes given in Airbus Mandatory Service
Bulletin A320-25A1555, Revision 02, dated November 5, 2008.
Repetitive Inspections of the 80V Rack Lower Central Support
(i) Prior to the accumulation of 24,000 total flight cycles, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later: Do a special detailed inspection of the 80VU
rack lower central support for cracking, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-25A1555, Revision 02, dated November 5, 2008. Repeat the
inspection thereafter at the interval specified in paragraph (i)(1)
or (i)(2) of this AD, as applicable. Replacing the pyramid fitting
on the 80VU rack with a new, reinforced fitting, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1215, dated November 5, 2008, terminates the inspection requirements
of this paragraph.
(1) For airplanes on which the 80VU rack lower central support
has not been repaired or replaced in accordance with Airbus
Mandatory Service Bulletin A320-25A1555 or Airbus Service Bulletin
A320-25-1557: Repeat the inspection thereafter at the interval
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as
applicable.
(i) For airplanes on which the lower central support has
accumulated 30,000 total flight cycles or more: At intervals not to
exceed 500 flight cycles.
(ii) For airplanes on which the lower central support has
accumulated less than 30,000 total flight cycles: At intervals not
to exceed 4,500 flight cycles, without exceeding 30,750 total flight
cycles on the support for the first repetitive inspection.
(2) For airplanes on which the 80VU rack lower central support
has been repaired or replaced in accordance with Airbus Mandatory
Service Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-
1557: Do the next inspection within 24,000 flight cycles after the
repair or replacement and thereafter repeat the inspection at the
interval specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD,
as applicable.
(j) If any crack is found during any inspection required by
paragraph (i) of this AD, before further flight, replace the pyramid
fitting on the 80VU rack with a new, reinforced fitting, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1215, dated November 5, 2008. Doing this
replacement terminates the inspection requirements of paragraph (i)
of this AD.
Optional Terminating Action
(k) Doing the actions specified in paragraphs (k)(1) and (k)(2)
of this AD terminates the requirements of paragraphs (g) and (i) of
this AD.
(1) Replacing the pyramid fitting on the 80VU rack with a new,
reinforced fitting, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1215, dated November
5, 2008.
(2) Modifying the 80VU lower lateral fittings, in accordance
with Airbus Service Bulletin A320-25-1557, Revision 02, dated
November 5, 2008.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(l) Actions done before the effective date of this AD in
accordance with the service information identified in Table 1 of
this AD are acceptable for compliance with the corresponding
requirements of this AD.
Table 1--Previous Revisions of Service Information
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Service information Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A320- 01......................... February 18, 2008.
25A1555.
Airbus Service Bulletin A320-25A1555.... Original................... June 14, 2007.
Airbus Service Bulletin A320-25-1557.... Original................... June 14, 2007.
Airbus Service Bulletin A320-25-1557.... 01......................... February 7, 2008.
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FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows:
(1) Although the MCAI or service information allows further
flight after cracks are found during compliance with the required
action, paragraph (j) of this AD requires that you do a corrective
action before further flight.
(2) Although the MCAI specifies doing a repair or replacement
and repetitive inspections after the repair or replacement is done
if cracking is found in the 80VU rack lower central support,
paragraph (j) of this AD requires that you perform a replacement,
which eliminates the need for further repetitive inspections of the
part.
Other FAA AD Provisions
(m) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Tim
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD.
(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.
Related Information
(n) Refer to MCAI EASA Airworthiness Directive 2007-0276R1,
dated March 18, 2010, (corrected April 12, 2010), and the service
information identified in Table 2 of this AD, for related
information.
Table 2--Related Service Information
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Service information Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A320- 02......................... November 5, 2008.
25A1555.
[[Page 75882]]
Airbus Service Bulletin A320-25-1557.... 02......................... November 5, 2008.
Airbus Service Bulletin A320-53-1215.... Original................... November 5, 2008.
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Material Incorporated by Reference
(o) You must use the service information specified in paragraphs
(o)(1) and (o)(2) of this AD, as applicable, unless the AD specifies
otherwise.
(1) For the actions required by this AD: Airbus Mandatory
Service Bulletin A320-25A1555, excluding Appendix 1, Revision 02,
dated November 5, 2008; and Airbus Service Bulletin A320-53-1215,
dated November 5, 2008.
(2) For the optional actions specified by this AD: Airbus
Service Bulletin A320-25-1557, Revision 02, dated November 5, 2008;
and Airbus Service Bulletin A320-53-1215, dated November 5, 2008.
(3) 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.
(4) 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.
(5) 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.
(6) 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 November 15, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-29457 Filed 12-6-10; 8:45 am]
BILLING CODE 4910-13-P