Airworthiness Directives; Airbus Model A310-203, -204, -222, -304, -322, and -324 Airplanes, 27246-27250 [2011-10688]
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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations
after the effective date of this AD, modify the
thrust reverser control system wiring to the
FCU in the P252 and P253 thrust reverser
relay panels, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–78A2184, Revision 1,
dated December 23, 2010.
(h) For Model 747–400, –400D, and –400F
airplanes equipped with General Electric
Model CF6–80C2 series engines: Within 36
months after the effective date of this AD,
modify the thrust reverser control system
wiring to the FCU in the P414 and P415
power distribution panels, in accordance
with Boeing Special Attention Service
Bulletin 747–78–2183, Revision 1, dated
December 23, 2010.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(i) Modifying the thrust reverser control
system wiring before the effective date of this
AD, in accordance with Boeing Special
Attention Service Bulletin 747–78–2183 or
Boeing Alert Service Bulletin 747–78A2184,
both dated January 12, 2010, as applicable, is
acceptable for compliance with the
corresponding modification required by
paragraph (g) or (h) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
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Related Information
(k) For more information about this AD,
contact Tung Tran, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; phone: 425–917–6505; fax: 425–917–
6590; e-mail: tung.tran@faa.gov.
(l) For information about AMOCs, contact
Tung Tran, Aerospace Engineer, Propulsion
Branch, ANM–140S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; phone:
425–917–6505; fax: 425–917–6590; e-mail:
tung.tran@faa.gov.
Material Incorporated by Reference
(m) You must use Boeing Special Attention
Service Bulletin 747–78–2183, Revision 1,
dated December 23, 2010; or Boeing Alert
Service Bulletin 747–78A2184, Revision 1,
dated December 23, 2010; as applicable; to do
the actions required by this AD, unless the
AD specifies otherwise.
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(1) The Director of the Federal Register
approved the incorporation by reference of
the service information under 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on April 20,
2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–10692 Filed 5–10–11; 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; Amendment
39–16686; AD 2011–10–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–203, –204, –222, –304, –322, and
–324 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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:
SUMMARY:
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. We
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are issuing this AD to require actions to
correct the unsafe condition on these
products.
DATES: This AD becomes effective June
15, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 15, 2011.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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: 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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on January 3, 2011 (76 FR 46).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
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:
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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations
• 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.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
44 products of U.S. registry. We also
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estimate that it will take about 36 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $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
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 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 the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
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27247
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2011–10–05 Airbus: Amendment 39–16686.
Docket No. FAA–2010–1273; Directorate
Identifier 2010–NM–089–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 15, 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
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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008. Certain
compliance times are applicable to shortrange use (i.e., average flight time (AFT)
equal to or less than 4 flight hours), or longrange use (i.e., AFT exceeding 4 flight hours).
Inspection areas are specified in Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
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.
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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 Airbus Mandatory Service
Bulletin A310–53–2074, Revision 04, dated
October 24, 2008.
(i) If any corrosion is found, before further
flight, repair in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008. If no
cracking is found, before further flight, shot
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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.
peen the reworked area, in accordance with
the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008. If no
cracking is found, before further flight, shot
peen the reworked area, in accordance with
the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008, 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)
(ii) If cracking is greater than 2.0 mm
(0.079 inch) long or there are more than 2
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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.
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
Airbus Mandatory Service Bulletin A310–53–
2074, Revision 04, dated October 24, 2008;
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 Airbus Mandatory Service
Bulletin A310–53–2074, Revision 04, dated
October 24, 2008. 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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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
Airbus Mandatory Service Bulletin A310–53–
2074, Revision 04, dated October 24, 2008;
except where this service bulletin specifies to
contact Airbus if the fastener diameter does
not meet specifications or if the distance
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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations
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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service
Bulletin A310–53–2074, Revision 04, dated
October 24, 2008; except where this 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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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
Airbus Mandatory Service Bulletin A310–53–
2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory
Service Bulletin A310–53–2074, Revision 04,
dated October 24, 2008.
27249
(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 Airbus
Mandatory Service Bulletin A310–53–2074,
Revision 04, dated October 24, 2008.
(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
Airbus Mandatory Service Bulletin A310–53–
2074, Revision 04, dated October 24, 2008.
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.
(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.
srobinson on DSKHWCL6B1PROD with RULES
(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
flight hours). Inspection areas are specified in
Airbus Mandatory Service Bulletin A310–53–
2074, Revision 04, dated October 24, 2008.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(j) Inspections accomplished before the
effective date of this AD in accordance with
VerDate Mar<15>2010
16:21 May 10, 2011
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.
Airbus Mandatory Service Bulletin A310–53–
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,
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
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.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
E:\FR\FM\11MYR1.SGM
11MYR1
27250
Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations
to the International Branch, send it 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. Information may be e-mailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
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.
Material Incorporated by Reference
srobinson on DSKHWCL6B1PROD with RULES
(m) You must use Airbus Mandatory
Service Bulletin A310–53–2074, Revision 04,
dated October 24, 2008, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus 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.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on April 22,
2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–10688 Filed 5–10–11; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
16:21 May 10, 2011
Jkt 223001
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[Docket No. USCG–2011–0330]
Drawbridge Operation Regulations;
Hackensack River, Jersey City, NJ
Coast Guard, DHS.
Notice of temporary deviation
from regulations.
AGENCY:
ACTION:
The Commander, First Coast
Guard District, has issued a temporary
deviation from the regulation governing
the operation of the Lower Hack Bridge
across the Hackensack River, mile 3.4, at
Jersey City, New Jersey. The deviation is
necessary to repair structural steel
members on the lift span. This deviation
allows the bridge to remain in the
closed position to facilitate the above
repairs.
SUMMARY:
This deviation is effective from
10 p.m. on May 26, 2011 through 5 a.m.
on May 27, 2011.
ADDRESSES: Documents mentioned in
this preamble as being available in the
docket are part of docket USCG–2011–
0330 and are available online at
https://www.regulations.gov, inserting
USCG–2011–0330 in the ‘‘Keyword’’ and
then clicking ‘‘Search.’’ They are also
available for inspection or copying at
the Docket Management Facility (M–30),
U.S. Department of Transportation,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
FOR FURTHER INFORMATION CONTACT: If
you have questions on this rule, call or
e-mail Mr. Joe Arca, Project Officer,
First Coast Guard District,
joe.m.arca@uscg.mil, telephone (212)
668–7165. If you have questions on
viewing the docket, call Renee V.
Wright, Program Manager, Docket
Operations, telephone 202–366–9826.
SUPPLEMENTARY INFORMATION: The Lower
Hack Bridge, across the Hackensack
River at mile 3.4, has a vertical
clearance in the closed position of 40
feet at mean high water and 45 feet at
mean low water. The existing
drawbridge operation regulations are
listed at 33 CFR 117.723(b).
The waterway accommodates both
commercial and recreational vessels of
various sizes. Recreational navigation
passes under the bridge without
requiring any drawbridge openings.
The owner of the bridge, New Jersey
Transit, requested a temporary deviation
DATES:
PO 00000
Frm 00032
Fmt 4700
Sfmt 4700
to facilitate necessary structural steel
repairs at the bridge.
Under this temporary deviation the
Lower Hack Bridge, across the
Hackensack River at mile 3.4, may
remain in the closed position from
10 p.m. on May 26, 2011 through 5 a.m.
on May 27, 2011. Vessels that can pass
under the bridge without a bridge
opening may do so at all times.
In accordance with 33 CFR 117.35(e),
the bridge must return to its regular
operating schedule immediately at the
end of the designated time period. This
deviation from the operating regulations
is authorized under 33 CFR 117.35.
Dated: May 2, 2011.
Gary Kassof,
Bridge Program Manager, First Coast Guard
District.
[FR Doc. 2011–11545 Filed 5–10–11; 8:45 am]
BILLING CODE 9110–04–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[Docket No. USCG–2011–0291]
Drawbridge Operation Regulation;
Atlantic Intracoastal Waterway,
Albemarle and Chesapeake Canal,
Chesapeake, VA
Coast Guard, DHS.
Notice of temporary deviation
from regulations.
AGENCY:
ACTION:
The Commander, Fifth Coast
Guard District, has issued a temporary
deviation from the regulations
governing the operation of the SR170
Centerville Turnpike Bridge across the
Atlantic Intracoastal Waterway,
Albemarle and Chesapeake Canal, mile
15.2, at Chesapeake, VA. The deviation
is necessary to facilitate urgent
mechanical structural repairs to the
swing span. Under this deviation, the
drawbridge will be allowed to operate
on a limited schedule for the extent of
the effective period, specifically
affecting four specific dates during the
effective time-period: May 14, 2011;
May 15, 2011; June 4, 2011; and June 5,
2011.
DATES: This deviation is effective from
8 a.m. on May 14, 2011 to 8 p.m. on
June 5, 2011.
ADDRESSES: Documents mentioned in
this preamble as being available in the
docket USCG–2011–0291 and are
available online by going to https://
www.regulations.gov, inserting USCG–
2011–0291 in the ‘‘Keyword’’ box, and
SUMMARY:
E:\FR\FM\11MYR1.SGM
11MYR1
]]>Agencies
[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27246-27250]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-10688]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-089-AD;
Amendment 39-16686; AD 2011-10-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203, -204, -222, -
304, -322, and -324 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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:
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. We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective June 15, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 15,
2011.
ADDRESSES: You may examine the AD docket on the Internet at https://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: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 3, 2011 (76
FR 46). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
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:
[[Page 27247]]
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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data 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 to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 44 products of U.S. registry.
We also estimate that it will take about 36 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $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
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 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 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
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:
2011-10-05 Airbus: Amendment 39-16686. Docket No. FAA-2010-1273;
Directorate Identifier 2010-NM-089-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 15,
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
[[Page 27248]]
Mandatory Service Bulletin A310-53-2074, Revision 04, dated October
24, 2008. 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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If any corrosion is found, before further flight, repair in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service
Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin A310-53-2074, Revision 04,
dated October 24, 2008. If no cracking is found, before further
flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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
Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated
October 24, 2008. If no cracking is found, before further flight,
shot peen the reworked area, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin A310-53-2074, Revision 04,
dated October 24, 2008, 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)
(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 Airbus Mandatory
Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008;
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 Airbus
Mandatory Service Bulletin A310-53-2074, Revision 04, dated October
24, 2008. 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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008; except where this
service bulletin specifies to contact Airbus if the fastener
diameter does not meet specifications or if the distance
[[Page 27249]]
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 Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(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
Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated
October 24, 2008; except where this 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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(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 Airbus Mandatory Service Bulletin A310-53-
2074, Revision 04, dated October 24, 2008.
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 Airbus Mandatory Service Bulletin A310-53-
2074, Revision 04, dated October 24, 2008.
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-
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. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly
[[Page 27250]]
to the International Branch, send it 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. Information may
be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
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.
Material Incorporated by Reference
(m) You must use Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008, to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus 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.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-10688 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P
