Airworthiness Directives; Airbus Model A310-203, -204, -222, -304, -322, and -324 Airplanes, 46-50 [2010-32991]
Download as PDF
<![CDATA[
46
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules
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
(r) Refer to MCAI EASA Airworthiness
Directive 2007–0053R3, dated December 17,
2009, and the service bulletins listed in Table
1 of this AD, for related information.
TABLE 1—RELATED SERVICE INFORMATION
Service bulletin
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Revision
Mandatory Service Bulletin A310–55–2004 ....................
Service Bulletin A310–53–2016 ......................................
Service Bulletin A310-53-2019 ........................................
Service Bulletin A310–53–2054 ......................................
Service Bulletin A310–53–2057 ......................................
Service Bulletin A310–53–2059 ......................................
Service Bulletin A310–55–2002 ......................................
Service Bulletin A310–57–2039 ......................................
Service Bulletin A310–57–2041 ......................................
Issued in Renton, Washington on
December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–32983 Filed 12–30–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1273; Directorate
Identifier 2010–NM–089–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–203, –204, –222, –304, –322, and
–324 Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
srobinson on DSKHWCL6B1PROD with PROPOSALS
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
A specific area, the lower tail plane cut-out
located in the tail cone is subject to an
inspection programme [for cracking] * * *.
*
*
*
*
*
The unsafe condition is reduced
structural integrity of the tail cone. The
proposed AD would require actions that
are intended to address the unsafe
condition described in the MCAI.
VerDate Mar<15>2010
19:10 Dec 30, 2010
Jkt 223001
05 ............................................
5 ..............................................
3 ..............................................
2 ..............................................
1 ..............................................
1 ..............................................
4 ..............................................
Original ....................................
Original ....................................
DATES: We must receive comments on
this proposed AD by February 17, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS—
EAW (Airworthiness Office), 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
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
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
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
Date
October 13, 2006.
December 7, 1992.
February 28, 1991.
May 22, 1990.
April 30, 1992.
January 4, 1996.
April 28, 1989.
September 24, 1990.
September 24, 1990.
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–1273; Directorate Identifier
2010–NM–089–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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0058,
dated March 13, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
E:\FR\FM\03JAP1.SGM
03JAP1
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules
srobinson on DSKHWCL6B1PROD with PROPOSALS
A specific area, the lower tail plane cut-out
located in the tail cone is subject to an
inspection programme specified in the
Airbus Service Bulletin (SB) A310–53–2074.
EASA issued AD 2007–0053 [which
superseded French AD 1992–106–132 R6;
French AD 1992–106–132 corresponds to
FAA AD 98–26–01] to require the
accomplishment of this SB at Revision 03.
Airbus has established that this SB needed
to be revised in order to state correct
threshold and intervals due to errors
introduced at revision 03. Consequently,
revision 04 of this SB has been issued, and
opportunity was taken:
—To clarify the inspection area and
associated threshold and intervals
—To take aeroplane utilisation into
consideration, in accordance with the
A310 life extension programme.
For the reasons stated above, this EASA
AD takes over the requirements of paragraph
1.16 of EASA AD 2007–0053R1 [currently at
R3], which has been revised accordingly, and
requires accomplishment of the instructions
contained in Airbus SB A310–53–2074 at
Revision 04.
The unsafe condition is reduced
structural integrity of the tail cone. The
required actions include repetitive and
one-time inspections, depending on the
area, of the lower tail plane cut-out, and
corrective actions if necessary. The
inspections include the following:
• Detailed inspections in areas 1, 2,
and 3 for cracking and corrosion of the
lower horizontal stabilizer cutout
longeron, the corner fitting, the skin
strap, and the skin.
• Detailed inspections in areas 1, 2,
and 3 for damaged sealant.
• Eddy current inspections in area 1
for cracking.
• Eddy current inspections in area 2
for cracking.
• Rotating probe inspection for
cracking of specified fastener holes in
Area 3.
The corrective actions, depending on
the conditions found, include the
following:
• Repairing corrosion.
• Contacting Airbus for repair
instructions.
• Replacing damaged sealant.
• Removing cracking.
• Doing an eddy current inspection
for cracking of the reworked area.
• Installing a new corner fitting.
• Doing a rotating probe inspection
for cracking of fastener holes.
• Doing an eddy current inspection of
the longeron and outer skin.
• Drilling or reaming fastener holes.
You may obtain further information
by examining the MCAI in the AD
docket.
Other Relevant Rulemaking
We are considering issuing three other
NPRMs related to this NPRM:
VerDate Mar<15>2010
19:10 Dec 30, 2010
Jkt 223001
• Directorate Identifier 2010–NM–
092–AD. That NPRM proposes to
supersede AD 98–26–01, amendment
39–10942 (63 FR 69179, December 16,
1998), to continue to require certain
actions specified in that AD. However,
that NPRM does not restate paragraph
(q) of AD 98–26–01. Instead, certain
requirements of paragraph (q) of that AD
are included in this NPRM, Directorate
Identifier 2010–NM–089–AD.
• Directorate Identifiers 2010–NM–
090–AD and 2010–NM–091–AD. Both of
these NPRMs include the requirements
of certain other paragraphs of AD 98–
26–01.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A310–53–2074, Revision 04,
dated October 24, 2008. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a Note within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 44 products of U.S. registry.
We also estimate that it would take
about 36 work-hours per product to
comply with the basic requirements of
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
47
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
$134,640, or $3,060 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
E:\FR\FM\03JAP1.SGM
03JAP1
48
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules
certificated in any category, all serial
numbers, except airplanes on which Airbus
modification 06146 has been done in
production.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Airbus: Docket No. FAA–2010–1273;
Directorate Identifier 2010–NM–089–AD.
Comments Due Date
(a) We must receive comments by February
17, 2011.
Affected ADs
(b) None.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
A specific area, the lower tail plane cut-out
located in the tail cone is subject to an
inspection programme [for cracking] * * *.
*
*
*
*
*
The unsafe condition is reduced structural
integrity of the tail cone.
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.
Applicability
(c) This AD applies to Model A310–203,
–204, –222, –304, –322, and –324 airplanes,
Initial Inspections of the Lower Tail Plane
Cut-Out Area and Corrective Actions
(g) Within the applicable time specified in
Table 1 of this AD, do the inspections of the
lower tail plane cut-out area in the tail cone
specified in paragraphs (g)(1), (g)(2), (g)(3),
(g)(4), (g)(5), and (g)(6) of this AD, as
applicable, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008 (‘‘the
service bulletin’’). Certain compliance times
are applicable to short-range use (i.e., average
flight time (AFT) equal to or less than 4 flight
hours), or long-range use (i.e., AFT exceeding
4 flight hours). Inspection areas are specified
in the service bulletin.
Note 1: To establish the average flight time,
take the accumulated flight time (counted
from the take-off up to the landing) and
divide by the number of accumulated flight
cycles. This gives the average flight time per
flight cycle.
TABLE 1—INITIAL COMPLIANCE TIME
Inspection
areas
Model A310–203, A310–204, and A310–
222 airplanes.
1 and 2 .........
Model A310–203, A310–204, and A310–
222 airplanes.
3 ...................
Model A310–304, A310–322, and A310–
324 short range airplanes.
1 and 2 .........
Model A310–304, A310–322, and A310–
324 short range airplanes.
3 ...................
Model A310–304, A310–322, and A310–
324 long range airplanes.
1 and 2 .........
Model A310–304, A310–322, and A310–
324 long range airplanes.
srobinson on DSKHWCL6B1PROD with PROPOSALS
Airplanes
3 ...................
(1) For areas 1, 2, and 3: Do a detailed
inspection for cracking and corrosion of the
lower horizontal stabilizer cutout longeron,
the corner fitting, the skin strap, and the skin,
in accordance with the Accomplishment
Instructions of the service bulletin.
(i) If any corrosion is found, before further
flight, repair in accordance with the
Accomplishment Instructions of the service
bulletin.
(ii) If any cracking is found, before further
flight, contact Airbus for repair instructions
and do the repair.
(2) For areas 1, 2, and 3 on which cracking
is not found during the inspection required
by paragraph (g)(1) of this AD: Do a detailed
inspection for damaged sealant; and, if any
damaged sealant is found, before further
flight, replace the sealant; in accordance with
the Accomplishment Instructions of the
service bulletin.
(3) For area 1: Do an eddy current
inspection for cracking in area 1; and, if no
cracking is found, before further flight, apply
sealant and corrosion compound, as
VerDate Mar<15>2010
19:10 Dec 30, 2010
Jkt 223001
Compliance time (whichever occurs later)
Prior to the accumulation of 18,000 total
flight cycles or 36,000 total flight
hours, whichever occurs first.
Prior to the accumulation of 24,000 total
flight cycles or 48,000 total flight
hours, whichever occurs first.
Prior to the accumulation of 12,000 total
flight cycles or 33,750 total flight
hours, whichever occurs first.
Prior to the accumulation of 18,000 total
flight cycles or 50,500 total flight
hours, whichever occurs first.
Prior to the accumulation of 7,500 total
flight cycles or 37,500 total flight
hours, whichever occurs first.
Prior to the accumulation of 11,250 total
flight cycles or 56,000 total flight
hours, whichever occurs first.
applicable; in accordance with the
Accomplishment Instructions of the service
bulletin.
(i) If cracking is equal to or less than 2.0
mm (0.079 inch) long and not more than 2
cracks with a minimum distance of 50.0 mm
(1.969 inch) between the cracks: Before
further flight, remove any cracking and do an
eddy current inspection for cracking of the
reworked area, in accordance with the
Accomplishment Instructions of the service
bulletin. If no cracking is found, before
further flight, shot peen the reworked area, in
accordance with the Accomplishment
Instructions of the service bulletin.
(A) If cracking is found and the radius of
the rework is less than 20.0 mm (0.787 inch),
before further flight, increase the radius and
do an eddy current inspection for cracking of
the reworked area, in accordance with the
Accomplishment Instructions of the service
bulletin. If no cracking is found, before
further flight, shot peen the reworked area, in
accordance with the Accomplishment
Instructions of the service bulletin.
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
Within 1,500 flight cycles or 3,000 flight
hours, whichever occurs first, after the
effective date of this AD.
Within 1,500 flight cycles or 3,000 flight
hours, whichever occurs first, after the
effective date of this AD.
Within 1,200 flight cycles or 3,300 flight
hours, whichever occurs first, after the
effective date of this AD.
Within 1,200 flight cycles or 3,300 flight
hours, whichever occurs first, after the
effective date of this AD.
Within 750 flight cycles or 3,750 flight
hours, whichever occurs first, after the
effective date of this AD.
Within 750 flight cycles or 3,750 flight
hours, whichever occurs first, after the
effective date of this AD.
(1) If any cracking is found in the outer
skin, before further flight, contact Airbus for
repair instructions and do the repair.
(2) If any cracking is found in the corner
fitting and area 3 has not been cold
expanded, before further flight, install new
corner fitting, in accordance with the
Accomplishment Instructions of the service
bulletin, and do the rotating probe inspection
in area 3 specified in paragraph (g)(5) of this
AD.
(3) If any cracking is found in the corner
fitting and area 3 has been cold expanded,
before further flight, do the eddy current
inspection of the longeron and outer skin
specified in paragraph (g)(6) of this AD.
(B) If cracking is found and the radius of
the rework is 20.0 mm (0.787 inch) or more,
before further flight, repair in accordance
with a method approved by either the
Manager, International Branch, ANM–116,
FAA, Transport Airplane Directorate, or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
E:\FR\FM\03JAP1.SGM
03JAP1
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules
(ii) If cracking is greater than 2.0 mm
(0.079 inch) long or there are more than 2
cracks; or if there are more than 2 cracks with
less than a minimum distance of 50.0 mm
(1.969 inch) between the cracks: Before
further flight, remove the corner fitting, and
do the applicable actions specified in
paragraph (g)(3)(ii)(A) or (g)(3)(ii)(B) of this
AD.
(A) If any cracking is found and area 3 has
not been cold expanded, before further flight,
install a new corner fitting, in accordance
with the Accomplishment Instructions of the
service bulletin; and do the rotating probe
inspection in area 3 specified in paragraph
(g)(5) of this AD.
(B) If any cracking is found and area 3 has
been cold expanded, before further flight, do
the eddy current inspection of the longeron
and outer skin specified in paragraph (g)(6)
of this AD.
(4) For area 2: Do an eddy current
inspection for cracking of area 2, in
accordance with the Accomplishment
Instructions of the service bulletin. If any
cracking is found, before further flight,
contact Airbus for repair instructions and do
the repair.
(5) For area 3: Do a rotating probe
inspection for cracking of specified fastener
holes in area 3, in accordance with the
Accomplishment Instructions of the service
bulletin.
(i) If no cracking is found, before further
flight, drill or ream fastener holes, cold
expand the fastener holes and countersinks,
and wet install with sealant, in accordance
with the Accomplishment Instructions of the
service bulletin; except where the service
bulletin specifies to contact Airbus if the
fastener diameter does not meet
specifications or if the distance between the
hole center and material edge is less than
specifications, before further flight, contact
Airbus for repair instructions and do the
repair.
(ii) If cracking is found, before further
flight, drill or ream fastener holes, and do a
rotating probe inspection for cracking of the
fastener holes in accordance with the
Accomplishment Instructions of the service
bulletin.
(A) If no cracking is found, cold expand the
fastener holes and countersinks, drill or ream
fastener holes, and wet install with sealant,
in accordance with the Accomplishment
Instructions of the service bulletin; except
where the service bulletin specifies to contact
Airbus if the fastener diameter does not meet
specifications or if the distance between the
hole center and material edge is less than the
specifications, before further flight, contact
Airbus for repair instructions and do the
repair.
(B) If cracking is found, before further
flight, contact Airbus for repair instructions
and do the repair.
(6) For airplanes on which cracking is
found in the corner fitting during any
inspection required by paragraph (g)(3) of
this AD and area 3 is cold-expanded: Do an
eddy current inspection for cracking of the
longeron and outer skin, in accordance with
the Accomplishment Instructions of the
service bulletin.
(i) If no cracking is found, before further
flight, install a new corner fitting and do a
rotating probe inspection for cracking of the
fastener holes, in accordance with the
Accomplishment Instructions of the service
bulletin.
49
(A) If no cracking is found, before further
flight, drill or ream fastener holes, cold
expand the fastener holes and countersinks,
and wet install with sealant, in accordance
with the Accomplishment Instructions of the
service bulletin.
(B) If cracking is found and the hole
diameter is less than the maximum oversize
specification, before further flight, drill or
ream holes and do a rotating probe
inspection for cracking of the fastener holes,
in accordance with the service bulletin.
(1) If no cracking is found, cold expand the
fastener holes and countersinks, and wet
install with sealant, in accordance with the
Accomplishment Instructions of the service
bulletin.
(2) If cracking is found, before further
flight, contact Airbus for repair instructions
and do the repair.
(C) If cracking is found and the hole
diameter is equal to or greater than the
maximum oversize specification, before
further flight, contact Airbus for repair
instructions and do the repair.
(ii) If cracking is found, before further
flight, contact Airbus for repair instructions
and do the repair.
Repetitive Inspections of the Lower Tail
Plane Cut-Out Area
(h) Repeat the inspections for area 1
required by paragraphs (g)(1) and (g)(3) of
this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain
compliance times are applicable to shortrange use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4
flight hours). Inspection areas are specified in
the service bulletin.
TABLE 2—REPETITIVE INTERVAL FOR AREAS 1 AND 2
Affected airplanes
Interval (not to exceed)
(1) Model A310–203, A310–204, and A310–222 airplanes that have accumulated less than 30,000 total flight cycles and 60,000 total flight
hours, as of the effective date of this AD.
6,000 flight cycles or 12,000 flight hours, whichever occurs first, until
the airplane accumulates 30,000 total flight cycles or 60,000 total
flight hours; then perform the inspections within the interval specified
in paragraph (h)(2) of this AD.
3,900 flight cycles or 7,800 flight hours, whichever occurs first.
(2) Model A310–203, A310–204, and A310–222 airplanes that have accumulated 30,000 total flight cycles or more or 60,000 total flight
hours or more, as of the effective date of this AD.
(3) Model A310–304, A310–322 and A310–324 short range airplanes
that have accumulated less than 24,000 total flight cycles and 67,500
total flight hours, as of the effective date of this AD.
srobinson on DSKHWCL6B1PROD with PROPOSALS
(4) Model A310–304, A310–322 and A310–324 short range airplanes
that have accumulated 24,000 total flight cycles or more or 67,500
total flight hours or more, as of the effective date of this AD.
(5) Model A310–304, A310–322 and A310–324 long range airplanes
that have accumulated less than 15,000 total flight cycles and 75,000
total flight hours, as of the effective date of this AD.
(6) Model A310–304, A310–322 and A310–324 long range airplanes
that have accumulated 15,000 total flight cycles or more or 75,000
total flight hours or more, as of the effective date of this AD.
(i) Repeat the inspections for area 2
required by paragraphs (g)(1) and (g)(4) of
this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain
compliance times are applicable to shortrange use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4
VerDate Mar<15>2010
19:10 Dec 30, 2010
Jkt 223001
4,800 flight cycles or 13,500 flight hours, whichever occurs first, until
the airplane accumulates 24,000 total flight cycles or 67,500 total
flight hours; then perform the inspections within the interval specified
in paragraph (h)(4) of this AD.
3,100 flight cycles or 8,750 flight hours, whichever occurs first.
3,000 flight cycles or 15,000 flight hours, whichever occurs first, until
the airplane accumulates 15,000 total flight cycles or 75,000 total
flight hours; then perform the inspections within the interval specified
in paragraph (h)(6) of this AD.
1,950 flight cycles or 9,750 flight hours, whichever occurs first.
flight hours). Inspection areas are specified in
the service bulletin.
PO 00000
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(j) Inspections accomplished before the
effective date of this AD in accordance with
Airbus Mandatory Service Bulletin A310–53–
Frm 00022
Fmt 4702
Sfmt 4702
E:\FR\FM\03JAP1.SGM
03JAP1
50
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules
2074, Revision 03, dated October 13, 2006,
are considered acceptable for compliance
with the corresponding action specified in
this AD.
DEPARTMENT OF TRANSPORTATION
FAA AD Differences
14 CFR Part 39
Note 2: This AD differs from the MCAI
and/or service information as follows: The
MCAI and service information do not specify
a corrective action if cracking is found and
the radius of the rework is 20.0 mm (0.787
inch) or more. Paragraph (g)(3)(i)(B) of this
AD requires repair in accordance with a
method approved by either the Manager,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, or EASA (or
its delegated agent).
[Docket No. FAA–2010–1274; Directorate
Identifier 2010–NM–090–AD]
Federal Aviation Administration
Other FAA AD Provisions
(k) 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: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
srobinson on DSKHWCL6B1PROD with PROPOSALS
Related Information
(l) Refer to MCAI EASA Airworthiness
Directive 2009–0058, dated March 13, 2009;
and Airbus Mandatory Service Bulletin
A310–53–2074, Revision 04, dated October
24, 2008; for related information.
Issued in Renton, Washington, on
December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–32991 Filed 12–30–10; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
19:10 Dec 30, 2010
Jkt 223001
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Airbus Model
A310 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France AD 1992–106–132(B) * * *
was issued to require a set of inspection and
modification tasks which addressed JAR/FAR
[Joint Aviation Regulation/Federal Aviation
Regulation] 25–571 requirements related to
damage-tolerance and fatigue evaluation of
structure. * * *
*
*
*
*
*
The unsafe condition is reduced
structural integrity of the wings. 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 February 17, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS—
EAW (Airworthiness Office), 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
account.airworth-eas@airbus.com;
PO 00000
Frm 00023
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Fmt 4702
Sfmt 4702
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–1274; Directorate Identifier
2010–NM–090–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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0057,
dated March 13, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France AD 1992–106–132(B) original
E:\FR\FM\03JAP1.SGM
03JAP1
]]>Agencies
[Federal Register Volume 76, Number 1 (Monday, January 3, 2011)]
[Proposed Rules]
[Pages 46-50]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32991]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-089-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203, -204, -222, -
304, -322, and -324 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail cone.
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 February 17,
2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS--EAW (Airworthiness Office), 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 account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1273;
Directorate Identifier 2010-NM-089-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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2009-0058, dated March 13, 2009 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
[[Page 47]]
A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme specified in the
Airbus Service Bulletin (SB) A310-53-2074. EASA issued AD 2007-0053
[which superseded French AD 1992-106-132 R6; French AD 1992-106-132
corresponds to FAA AD 98-26-01] to require the accomplishment of
this SB at Revision 03.
Airbus has established that this SB needed to be revised in
order to state correct threshold and intervals due to errors
introduced at revision 03. Consequently, revision 04 of this SB has
been issued, and opportunity was taken:
--To clarify the inspection area and associated threshold and
intervals
--To take aeroplane utilisation into consideration, in accordance
with the A310 life extension programme.
For the reasons stated above, this EASA AD takes over the
requirements of paragraph 1.16 of EASA AD 2007-0053R1 [currently at
R3], which has been revised accordingly, and requires accomplishment
of the instructions contained in Airbus SB A310-53-2074 at Revision
04.
The unsafe condition is reduced structural integrity of the tail cone.
The required actions include repetitive and one-time inspections,
depending on the area, of the lower tail plane cut-out, and corrective
actions if necessary. The inspections include the following:
Detailed inspections in areas 1, 2, and 3 for cracking and
corrosion of the lower horizontal stabilizer cutout longeron, the
corner fitting, the skin strap, and the skin.
Detailed inspections in areas 1, 2, and 3 for damaged
sealant.
Eddy current inspections in area 1 for cracking.
Eddy current inspections in area 2 for cracking.
Rotating probe inspection for cracking of specified
fastener holes in Area 3.
The corrective actions, depending on the conditions found, include
the following:
Repairing corrosion.
Contacting Airbus for repair instructions.
Replacing damaged sealant.
Removing cracking.
Doing an eddy current inspection for cracking of the
reworked area.
Installing a new corner fitting.
Doing a rotating probe inspection for cracking of fastener
holes.
Doing an eddy current inspection of the longeron and outer
skin.
Drilling or reaming fastener holes.
You may obtain further information by examining the MCAI in the AD
docket.
Other Relevant Rulemaking
We are considering issuing three other NPRMs related to this NPRM:
Directorate Identifier 2010-NM-092-AD. That NPRM proposes
to supersede AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16,
1998), to continue to require certain actions specified in that AD.
However, that NPRM does not restate paragraph (q) of AD 98-26-01.
Instead, certain requirements of paragraph (q) of that AD are included
in this NPRM, Directorate Identifier 2010-NM-089-AD.
Directorate Identifiers 2010-NM-090-AD and 2010-NM-091-AD.
Both of these NPRMs include the requirements of certain other
paragraphs of AD 98-26-01.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A310-53-2074, Revision
04, dated October 24, 2008. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 44 products of U.S. registry. We also estimate that
it would take about 36 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $134,640, or $3,060 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
[[Page 48]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-
089-AD.
Comments Due Date
(a) We must receive comments by February 17, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model A310-203, -204, -222, -304, -322,
and -324 airplanes, certificated in any category, all serial
numbers, except airplanes on which Airbus modification 06146 has
been done in production.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
A specific area, the lower tail plane cut-out located in the
tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail
cone.
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.
Initial Inspections of the Lower Tail Plane Cut-Out Area and Corrective
Actions
(g) Within the applicable time specified in Table 1 of this AD,
do the inspections of the lower tail plane cut-out area in the tail
cone specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5),
and (g)(6) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008 (``the service
bulletin''). Certain compliance times are applicable to short-range
use (i.e., average flight time (AFT) equal to or less than 4 flight
hours), or long-range use (i.e., AFT exceeding 4 flight hours).
Inspection areas are specified in the service bulletin.
Note 1: To establish the average flight time, take the
accumulated flight time (counted from the take-off up to the
landing) and divide by the number of accumulated flight cycles. This
gives the average flight time per flight cycle.
Table 1--Initial Compliance Time
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes Inspection areas Compliance time (whichever occurs later)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310- 1 and 2................. Prior to the Within 1,500 flight
222 airplanes. accumulation of 18,000 cycles or 3,000 flight
total flight cycles or hours, whichever
36,000 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-203, A310-204, and A310- 3....................... Prior to the Within 1,500 flight
222 airplanes. accumulation of 24,000 cycles or 3,000 flight
total flight cycles or hours, whichever
48,000 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 1 and 2................. Prior to the Within 1,200 flight
324 short range airplanes. accumulation of 12,000 cycles or 3,300 flight
total flight cycles or hours, whichever
33,750 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 3....................... Prior to the Within 1,200 flight
324 short range airplanes. accumulation of 18,000 cycles or 3,300 flight
total flight cycles or hours, whichever
50,500 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 1 and 2................. Prior to the Within 750 flight
324 long range airplanes. accumulation of 7,500 cycles or 3,750 flight
total flight cycles or hours, whichever
37,500 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
Model A310-304, A310-322, and A310- 3....................... Prior to the Within 750 flight
324 long range airplanes. accumulation of 11,250 cycles or 3,750 flight
total flight cycles or hours, whichever
56,000 total flight occurs first, after
hours, whichever the effective date of
occurs first. this AD.
----------------------------------------------------------------------------------------------------------------
(1) For areas 1, 2, and 3: Do a detailed inspection for
cracking and corrosion of the lower horizontal stabilizer cutout
longeron, the corner fitting, the skin strap, and the skin, in
accordance with the Accomplishment Instructions of the service
bulletin.
(i) If any corrosion is found, before further flight, repair in
accordance with the Accomplishment Instructions of the service
bulletin.
(ii) If any cracking is found, before further flight, contact
Airbus for repair instructions and do the repair.
(2) For areas 1, 2, and 3 on which cracking is not found during
the inspection required by paragraph (g)(1) of this AD: Do a
detailed inspection for damaged sealant; and, if any damaged sealant
is found, before further flight, replace the sealant; in accordance
with the Accomplishment Instructions of the service bulletin.
(3) For area 1: Do an eddy current inspection for cracking in
area 1; and, if no cracking is found, before further flight, apply
sealant and corrosion compound, as applicable; in accordance with
the Accomplishment Instructions of the service bulletin.
(i) If cracking is equal to or less than 2.0 mm (0.079 inch)
long and not more than 2 cracks with a minimum distance of 50.0 mm
(1.969 inch) between the cracks: Before further flight, remove any
cracking and do an eddy current inspection for cracking of the
reworked area, in accordance with the Accomplishment Instructions of
the service bulletin. If no cracking is found, before further
flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of the service bulletin.
(A) If cracking is found and the radius of the rework is less
than 20.0 mm (0.787 inch), before further flight, increase the
radius and do an eddy current inspection for cracking of the
reworked area, in accordance with the Accomplishment Instructions of
the service bulletin. If no cracking is found, before further
flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of the service bulletin.
(1) If any cracking is found in the outer skin, before further
flight, contact Airbus for repair instructions and do the repair.
(2) If any cracking is found in the corner fitting and area 3
has not been cold expanded, before further flight, install new
corner fitting, in accordance with the Accomplishment Instructions
of the service bulletin, and do the rotating probe inspection in
area 3 specified in paragraph (g)(5) of this AD.
(3) If any cracking is found in the corner fitting and area 3
has been cold expanded, before further flight, do the eddy current
inspection of the longeron and outer skin specified in paragraph
(g)(6) of this AD.
(B) If cracking is found and the radius of the rework is 20.0 mm
(0.787 inch) or more, before further flight, repair in accordance
with a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate, or the European
Aviation Safety Agency (EASA) (or its delegated agent).
[[Page 49]]
(ii) If cracking is greater than 2.0 mm (0.079 inch) long or
there are more than 2 cracks; or if there are more than 2 cracks
with less than a minimum distance of 50.0 mm (1.969 inch) between
the cracks: Before further flight, remove the corner fitting, and do
the applicable actions specified in paragraph (g)(3)(ii)(A) or
(g)(3)(ii)(B) of this AD.
(A) If any cracking is found and area 3 has not been cold
expanded, before further flight, install a new corner fitting, in
accordance with the Accomplishment Instructions of the service
bulletin; and do the rotating probe inspection in area 3 specified
in paragraph (g)(5) of this AD.
(B) If any cracking is found and area 3 has been cold expanded,
before further flight, do the eddy current inspection of the
longeron and outer skin specified in paragraph (g)(6) of this AD.
(4) For area 2: Do an eddy current inspection for cracking of
area 2, in accordance with the Accomplishment Instructions of the
service bulletin. If any cracking is found, before further flight,
contact Airbus for repair instructions and do the repair.
(5) For area 3: Do a rotating probe inspection for cracking of
specified fastener holes in area 3, in accordance with the
Accomplishment Instructions of the service bulletin.
(i) If no cracking is found, before further flight, drill or
ream fastener holes, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of the service bulletin; except where
the service bulletin specifies to contact Airbus if the fastener
diameter does not meet specifications or if the distance between the
hole center and material edge is less than specifications, before
further flight, contact Airbus for repair instructions and do the
repair.
(ii) If cracking is found, before further flight, drill or ream
fastener holes, and do a rotating probe inspection for cracking of
the fastener holes in accordance with the Accomplishment
Instructions of the service bulletin.
(A) If no cracking is found, cold expand the fastener holes and
countersinks, drill or ream fastener holes, and wet install with
sealant, in accordance with the Accomplishment Instructions of the
service bulletin; except where the service bulletin specifies to
contact Airbus if the fastener diameter does not meet specifications
or if the distance between the hole center and material edge is less
than the specifications, before further flight, contact Airbus for
repair instructions and do the repair.
(B) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
(6) For airplanes on which cracking is found in the corner
fitting during any inspection required by paragraph (g)(3) of this
AD and area 3 is cold-expanded: Do an eddy current inspection for
cracking of the longeron and outer skin, in accordance with the
Accomplishment Instructions of the service bulletin.
(i) If no cracking is found, before further flight, install a
new corner fitting and do a rotating probe inspection for cracking
of the fastener holes, in accordance with the Accomplishment
Instructions of the service bulletin.
(A) If no cracking is found, before further flight, drill or
ream fastener holes, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of the service bulletin.
(B) If cracking is found and the hole diameter is less than the
maximum oversize specification, before further flight, drill or ream
holes and do a rotating probe inspection for cracking of the
fastener holes, in accordance with the service bulletin.
(1) If no cracking is found, cold expand the fastener holes and
countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of the service bulletin.
(2) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
(C) If cracking is found and the hole diameter is equal to or
greater than the maximum oversize specification, before further
flight, contact Airbus for repair instructions and do the repair.
(ii) If cracking is found, before further flight, contact Airbus
for repair instructions and do the repair.
Repetitive Inspections of the Lower Tail Plane Cut-Out Area
(h) Repeat the inspections for area 1 required by paragraphs
(g)(1) and (g)(3) of this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain compliance times are
applicable to short-range use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4 flight hours). Inspection
areas are specified in the service bulletin.
Table 2--Repetitive Interval for Areas 1 and 2
------------------------------------------------------------------------
Affected airplanes Interval (not to exceed)
------------------------------------------------------------------------
(1) Model A310-203, A310-204, and A310- 6,000 flight cycles or 12,000
222 airplanes that have accumulated flight hours, whichever occurs
less than 30,000 total flight cycles first, until the airplane
and 60,000 total flight hours, as of accumulates 30,000 total
the effective date of this AD. flight cycles or 60,000 total
flight hours; then perform the
inspections within the
interval specified in
paragraph (h)(2) of this AD.
(2) Model A310-203, A310-204, and A310- 3,900 flight cycles or 7,800
222 airplanes that have accumulated flight hours, whichever occurs
30,000 total flight cycles or more or first.
60,000 total flight hours or more, as
of the effective date of this AD.
(3) Model A310-304, A310-322 and A310- 4,800 flight cycles or 13,500
324 short range airplanes that have flight hours, whichever occurs
accumulated less than 24,000 total first, until the airplane
flight cycles and 67,500 total flight accumulates 24,000 total
hours, as of the effective date of flight cycles or 67,500 total
this AD. flight hours; then perform the
inspections within the
interval specified in
paragraph (h)(4) of this AD.
(4) Model A310-304, A310-322 and A310- 3,100 flight cycles or 8,750
324 short range airplanes that have flight hours, whichever occurs
accumulated 24,000 total flight cycles first.
or more or 67,500 total flight hours
or more, as of the effective date of
this AD.
(5) Model A310-304, A310-322 and A310- 3,000 flight cycles or 15,000
324 long range airplanes that have flight hours, whichever occurs
accumulated less than 15,000 total first, until the airplane
flight cycles and 75,000 total flight accumulates 15,000 total
hours, as of the effective date of flight cycles or 75,000 total
this AD. flight hours; then perform the
inspections within the
interval specified in
paragraph (h)(6) of this AD.
(6) Model A310-304, A310-322 and A310- 1,950 flight cycles or 9,750
324 long range airplanes that have flight hours, whichever occurs
accumulated 15,000 total flight cycles first.
or more or 75,000 total flight hours
or more, as of the effective date of
this AD.
------------------------------------------------------------------------
(i) Repeat the inspections for area 2 required by paragraphs
(g)(1) and (g)(4) of this AD thereafter at the applicable intervals
specified in Table 2 of this AD. Certain compliance times are
applicable to short-range use (AFT equal to or less than 4 flight
hours), or long-range use (AFT exceeding 4 flight hours). Inspection
areas are specified in the service bulletin.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Inspections accomplished before the effective date of this
AD in accordance with Airbus Mandatory Service Bulletin A310-53-
[[Page 50]]
2074, Revision 03, dated October 13, 2006, are considered acceptable
for compliance with the corresponding action specified in this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service
information as follows: The MCAI and service information do not
specify a corrective action if cracking is found and the radius of
the rework is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B)
of this AD requires repair in accordance with a method approved by
either the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate, or EASA (or its delegated agent).
Other FAA AD Provisions
(k) 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: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your principal maintenance inspector (PMI) or principal
avionics inspector (PAI), as appropriate, or lacking a principal
inspector, your local Flight Standards District Office. The AMOC
approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(l) Refer to MCAI EASA Airworthiness Directive 2009-0058, dated
March 13, 2009; and Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008; for related information.
Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32991 Filed 12-30-10; 8:45 am]
BILLING CODE 4910-13-P
