[Federal Register: April 7, 2008 (Volume 73, Number 67)]
[Proposed Rules]
[Page 18722-18725]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ap08-14]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0406; Directorate Identifier 2007-NM-196-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 18723]]
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as:
During routine visual inspection, a crack has been found in the
wing MLG (main landing gear) rib 5 forward attachment lug on two
A310 in-service aircraft. Laboratory examination of one of the
cracked ribs confirmed that the crack is due to the presence of
pitting corrosion in the forward lug holes. Also on both aircraft
medium to heavy corrosion was found in the forward lugs on the
opposite wing after removal of the bushes. This situation if not
detected, could affect the structural integrity of the MLG
attachment. * * *
* * * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by May 7, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; 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-2008-0406;
Directorate Identifier 2007-NM-196-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On December 7, 2006, we issued AD 2007-02-09, Amendment 39-14896
(72 FR 2612, January 22, 2007). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2007-02-09, the type certificate holder has
developed a new inspection using ultrasonic techniques. We have
determined that the existing AD must be superseded to add repair or
replacement of cracked main landing gear (MLG) Rib 5, provide the new
inspection as an option, and reduce the applicability of the AD to
exclude airplanes on which Airbus Service Bulletin A310-57-2090 has
been done.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2007-0195, dated July 19, 2007 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
During routine visual inspection, a crack has been found in the
wing MLG (main landing gear) rib 5 forward attachment lug on two
A310 in-service aircraft. Laboratory examination of one of the
cracked ribs confirmed that the crack is due to the presence of
pitting corrosion in the forward lug holes. Also on both aircraft
medium to heavy corrosion was found in the forward lugs on the
opposite wing after removal of the bushes. This situation if not
detected, could affect the structural integrity of the MLG
attachment. As an interim measure, Airbus published Alert Service
Bulletin (ASB) A310-57A2088 to introduce a repetitive detailed
visual inspection (DVI) of the forward attachment lug of MLG Rib 5.
EASA issued Emergency Airworthiness Directive (EAD) 2006-0335-E
[which corresponds to FAA AD 2007-02-09] to require the
accomplishment of this repetitive DVI.
In order to ensure the detection of any crack at an early stage
in the forward lug of the RH (right-hand) and LH (left-hand) MLG Rib
5 aft bearing attachment, the Type Certificate holder has developed
a new inspection by means of ultrasonic method. For the reasons
described above, this new inspection program is rendered mandatory
by this AD, which cancels and replaces the requirement of EAD 2006-
0335-E.
The corrective action includes repairing or replacing MLG Rib 5, as
applicable. You may obtain further information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins A310-57-2090, Revision 01,
dated December 19, 2007, and A310-57-2091, including Appendix 01, dated
May 22, 2007. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA
[[Page 18724]]
policies. Any such differences are highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 68 products of U.S. registry. We also estimate that
it would take about 5 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $27,200, or $400 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14896 (72 FR
2612, January 22, 2007) and adding the following new AD:
Airbus: Docket No. FAA-2008-0406; Directorate Identifier 2007-NM-
196-AD.
Comments Due Date
(a) We must receive comments by May 7, 2008.
Affected ADs
(b) The proposed AD supersedes AD 2007-02-09, Amendment 39-
14896.
Applicability
(c) This AD applies to Airbus Model A310 airplanes, certificated
in any category, all certified models, all serial numbers; except
for those where LH (left-hand) and RH (right-hand) wing MLG (main
landing gear) rib 5 forward lugs have been repaired by installation
of oversized interference fit bushings as per Airbus Repair
Instruction R57249121, or which have had Airbus Service Bulletin
A310-57-2090 (AIRBUS modification 13329) embodied in service.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During routine visual inspection, a crack has been found in the
wing MLG (main landing gear) rib 5 forward attachment lug on two
A310 in-service aircraft. Laboratory examination of one of the
cracked ribs confirmed that the crack is due to the presence of
pitting corrosion in the forward lug holes. Also on both aircraft
medium to heavy corrosion was found in the forward lugs on the
opposite wing after removal of the bushes. This situation if not
detected, could affect the structural integrity of the MLG
attachment. As an interim measure, Airbus published Alert Service
Bulletin (ASB) A310-57A2088 to introduce a repetitive detailed
visual inspection (DVI) of the forward attachment lug of MLG Rib 5.
EASA issued Emergency Airworthiness Directive (EAD) 2006-0335-E
[which corresponds to FAA AD 2007-02-09] to require the
accomplishment of this repetitive DVI.
In order to ensure the detection of any crack at an early stage
in the forward lug of the RH (right-hand) and LH (left-hand) MLG Rib
5 aft bearing attachment, the Type Certificate holder has developed
a new inspection by means of ultrasonic method. For the reasons
described above, this new inspection program is rendered mandatory
by this AD, which cancels and replaces the requirement of EAD 2006-
0335-E.
The corrective action includes repairing or replacing MLG Rib 5,
as applicable.
Restatement of Requirements of AD 2007-02-09
(f) Unless already done, do the following actions specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD in accordance with
the instructions defined in Airbus Service Bulletin A310-57A2088,
dated November 6, 2006.
(1) Before the accumulation of 12,000 total flight cycles, or
within 14 days after February 6, 2007 (the effective date of AD
2007-02-09), whichever occurs later: Perform a detailed visual
inspection of the LH and RH wing MLG rib 5 aft bearing forward lugs.
(2) If any crack is detected at LH and/or RH aft bearing forward
lug, contact Airbus and proceed with the replacement before next
flight.
(3) Repeat the inspection at intervals not exceeding 100 flight
cycles.
New Requirements of this AD: Actions and Compliance
(g) Unless already done, before the accumulation of 12,000 total
flight cycles or before the accumulation of 12,000 flight cycles on
MLG Rib 5, or within 14 days after the effective date of this AD,
whichever occurs latest: Perform either a detailed visual inspection
(DVI) or an ultrasonic inspection of the LH and RH MLG Rib 5 aft
bearing forward lug for cracks, in accordance with the instructions
defined in Airbus Service Bulletin A310-57-2091, including Appendix
01, dated May 22, 2007. If a MLG Rib 5 has been replaced on one side
only, then the RH and LH must be considered separately. Doing this
inspection ends the requirements of paragraph (f) for that MLG Rib 5
only.
Note 1: The ultrasonic inspection will detect any crack at an
early stage and will limit the risk of extensive repairs. This
earlier crack detection is not possible with the DVI.
(1) If no crack is detected during any inspection required by
paragraph (g) of this AD: Repeat the applicable inspection at the
time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Repeat the DVI thereafter at intervals not to exceed 100
flight cycles.
(ii) Repeat the ultrasonic inspection thereafter at intervals
not to exceed 825 flight cycles.
(2) Replacement of the MLG Rib 5 in accordance with the
instructions defined in Airbus Service Bulletin A310-57-2090,
Revision 01, dated December 19, 2007, ends the repetitive
inspections required by paragraph (g)(1) of this AD for that MLG Rib
5 only.
(3) If any crack is detected during the DVI required by
paragraph (g) of this AD: Before further flight, contact Airbus for
replacement
[[Page 18725]]
instructions and replace before further flight. If MLG Rib 5 is not
replaced in accordance with the instructions defined in Airbus
Service Bulletin A310-57-2090, Revision 01, dated December 19, 2007;
repeat the applicable inspection in paragraph (g) of this AD at the
time specified in the applicable paragraph.
(4) If any crack is detected during the ultrasonic inspection
required by paragraph (g) of this AD, before further flight,
accomplish the actions specified in paragraphs (g)(4)(i) or
(g)(4)(ii) of this AD, as applicable.
(i) If any crack is not visible on MLG Rib 5: Before further
flight, repair MLG Rib 5 using Repair Instruction R572-49121, Issue
C, dated May 2007. After embodiment of Repair Instruction R572-
49121, no further actions are required by this AD and Airbus Service
Bulletin A310-57-2091, including Appendix 01, dated May 22, 2007,
for that MLG Rib 5 only.
(ii) If any crack is visible on MLG Rib 5: Before further
flight, contact Airbus for rib replacement instructions, and replace
before further flight. If MLG Rib 5 is not replaced in accordance
with the instructions defined in Airbus Service Bulletin A310-57-
2090, Revision 01, dated December 19, 2007, repeat the applicable
inspection in paragraph (g) of this AD at the time specified.
Accomplishing the replacement defined in Airbus Service Bulletin
A310-57-2090 ends the repetitive inspections required by paragraph
(g)(1) of this AD for that MLG Rib 5 only.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
Although the MCAI or service information allows flight with
cracks on aft bearing forward lugs for a certain period of time,
this AD requires replacing MLG Rib 5 before further flight if any
crack is found.
Although the MCAI or service information specifies submitting an
inspection report sheet to Airbus, this AD would not require that
action.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Stafford, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(i) Refer to MCAI EASA Airworthiness Directive 2007-0195, dated
July 19, 2007, and Airbus Service Bulletins A310-57-2090, Revision
01, dated December 19, 2007, and A310-57-2091, including Appendix
01, dated May 22, 2007, for related information.
Issued in Renton, Washington, on March 27, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-7163 Filed 4-4-08; 8:45 am]
BILLING CODE 4910-13-P