Airworthiness Directives; Airbus Airplanes, 81168-81174 [2015-31603]
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
Bulletin 100–25–21, Revision 01, dated
February 26, 2013, which is not incorporated
by reference in this AD.
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, 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 New York ACO, send it to
ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO,
1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7300; fax
516–794–5531. 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) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
jstallworth on DSK7TPTVN1PROD with RULES
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2010–06R1,
dated August 8, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–1199.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on February 2, 2016.
(i) Bombardier Service Bulletin 100–25–21,
Revision 02, dated July 25, 2013.
(ii) Reserved.
(4) The following service information was
approved for IBR on May 5, 2011, (76 FR
17758, March 31, 2011).
(i) Bombardier Service Bulletin A100–21–
08, dated June 18, 2009.
(ii) Bombardier Service Bulletin 100–25–
14, dated June 30, 2008.
(iii) Bombardier Service Bulletin 100–25–
21, dated June 30, 2008.
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(iv) Bombardier Temporary Revision (TR)
5–2–53, dated October 1, 2009, to Section 5–
10–40, ‘‘Certification Maintenance
Requirements,’’ in Part 2 of Chapter 5 of
Bombardier Challenger 300 BD–100 Time
Limits/Maintenance Checks.
(5) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(6) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 11, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–32080 Filed 12–28–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0648; Directorate
Identifier 2013–NM–136–AD; Amendment
39–18344; AD 2015–25–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2010–06–
04, for certain Airbus Model A300 B2–
1C, B2–203, B2K–3C, B4–103, B4–203,
B4–2C airplanes; Model A310 series
airplanes; Model A300 B4–600 series
airplanes; and Model A300 B4–600R
series airplanes. AD 2010–06–04
required repetitive inspections to detect
cracks of the pylon side panels (upper
section) at rib 8; and corrective actions
if necessary. This new AD continues to
require repetitive inspections for
cracking of the pylons 1 and 2 side
panels (upper section) at rib 8 with
reduced compliance times, and
corrective actions if necessary. This AD
also requires repetitive post-repair and
SUMMARY:
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post-modification inspections and
repair if necessary. This AD also
removes certain airplanes having a
certain modification from the
applicability. This AD was prompted by
reports of cracks found on pylon side
panels at rib 8 and a fleet survey and
updated fatigue and damage tolerance
analyses. We are issuing this AD to
detect and correct cracking of pylon side
panels (upper section) at rib 8, which
could lead to reduced structural
integrity of the pylon primary structure,
which could cause detachment of the
engine from the fuselage.
DATES: This AD becomes effective
February 2, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 2, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of April 15, 2010 ((75 FR
11428, March 11, 2010); corrected May
4, 2010 (75 FR 23572)).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0648; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in
this final rule, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0648.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
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 supersede AD 2010–06–04,
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Amendment 39–16228 ((75 FR 11428,
March 11, 2010); corrected May 4, 2010
(75 FR 23572)). AD 2010–06–04 applied
to certain Airbus Model A300 B2–1C,
B2–203, B2K–3C, B4–103, B4–203, B4–
2C airplanes; Model A310 series
airplanes; Model A300 B4–600 series
airplanes; and Model A300 B4–600R
series airplanes. The NPRM published
in the Federal Register on September
22, 2014 (79 FR 56526).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0136R1, dated July 30,
2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on certain Airbus
Model A300 B2–1C, B2–203, B2K–3C,
B4–103, B4–203, B4–2C airplanes;
Model A310 series airplanes; Model
A300 B4–600 series airplanes; and
Model A300 B4–600R series airplanes.
The MCAI states:
Cracks were found on pylon side panels
(upper section) at rib 8 on Airbus A300, A310
and A300–600 aeroplanes equipped with
General Electric engines. Investigation of
these findings indicated that this problem
was likely to also affect aeroplanes of this
type design with other engine installations.
This condition, if not detected and
corrected, could lead to reduced strength of
the pylon primary structure, possibly
resulting in pylon structural failure and inflight loss of an engine.
Prompted by these findings, EASA issued
AD 2008–0181 [https://www.regulations.gov/
#!documentDetail;D=FAA-2009-0789-0002]
[which corresponds to FAA AD 2010–06–04,
Amendment 39–16228 ((75 FR 11428, March
11, 2010); corrected May 4, 2010 (75 FR
23572))] to require repetitive detailed visual
inspections [of the pylon side panels (upper
section) at rib 8] and, depending on
aeroplane configuration and/or findings, the
accomplishment of applicable corrective
action(s).
Since that [EASA] AD was issued, a fleet
survey and updated Fatigue and Damage
Tolerance analyses have been performed in
order to substantiate the second A300–600
Extended Service Goal (ESG2) exercise. The
results of these analyses have shown that the
risk for these aeroplanes is higher than
initially determined and consequently, the
threshold and interval must be reduced to
allow timely detection of these cracks and
the accomplishment of applicable correction
action(s).
EASA issued AD 2013–0136 [https://
ad.easa.europa.eu/ad/2013-0136R1] which
retained the requirements of EASA AD 2008–
0181, which was superseded, and required
the inspections to be accomplished within
reduced thresholds and intervals.
After publication of EASA AD 2013–0136,
it appeared that Airbus Mod 03599 had no
influence on the aeroplane configuration
affected by this AD. At the same time Airbus
Service Bulletin (SB) A30–54–6015 Revision
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3 was not integrally taken into account as
this revision no longer identifies
configuration 3 aeroplanes.
For the reasons described above, EASA
[AD] 2013–0136 is revised to exclude Airbus
Mod 03599 from the applicability and to
delete the reference to the configuration 3 for
A300–600 aeroplanes.
Corrective actions include doing a
repair. This AD also provides an
optional modification (installing a
doubler), which would terminate the
repetitive inspections. Required actions
also include repetitive post-repair and
post-modification inspections and
repair if necessary. You may examine
the MCAI in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-06480002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM (79 FR 56526,
September 22, 2014) and the FAA’s
response.
Request To Revise Method Used To
Determine Compliance Times
United Parcel Service (UPS) requested
that we revise the proposed compliance
times to be less complex. UPS stated
that the proposed compliance times
contain a method known as ‘‘Average
Flight Time’’ (AFT) which results in a
variable flight hour limit and adds
unnecessary complexity to the threshold
table and subsequent inspection actions.
UPS added that use of the AFT method,
along with a lack of standard procedures
for implementing the AFT method
would create uncertainty for operators
and inspectors trying to determine the
correct compliance time. UPS stated
that in review of prior FAA ADs,
including AD 98–18–02, Amendment
39–10718 (63 FR 45689, August 27,
1998), that the FAA does not concur
with the AFT compliance time
methodology as ‘‘. . . such adjustments
may not address the unsafe condition in
a timely manner’’ and ‘‘. . . they (AFT
compliance times) do not fit into the AD
tracking process for operators or for
Principle Maintenance Inspectors
(PMIs) attempting to ascertain
compliance with ADs.’’
UPS compiled a table of fixed
compliance times that it suggested
would be simpler to use instead of the
proposed AFT-based compliance times.
We disagree with the commenter’s
request to revise the compliance times
in this AD. The compliance times, as
proposed, use fixed flight-cycle and
flight-hour compliance times. For only
Model A310 series airplanes, the
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81169
compliance times depend on whether
airplanes are short range or long range
airplanes. We acknowledge that this
causes additional complexity in tracking
and forecasting airplane utilization;
however, the inspection schedule was
created by Airbus to offer operators the
greatest flexibility. Operators may elect
to inspect within the range that
complies with both the long range and
short range utilization in order to reduce
the complexity. We have not changed
this AD in this regard.
Regarding AD 98–18–02, Amendment
39–10718 (63 FR 45689, August 27,
1998), at the time the FAA issued AD
98–18–02, the required actions in
Airbus Industrie Service Bulletin A300–
57–6027, Revision 2, dated September
13, 1994, contained inspection
thresholds and intervals based on
airplane flight cycles, and provided
instructions for adjusting the flight cycle
threshold and interval using each
individual airplane’s AFT utilization.
The FAA did not agree with the AFT
method because it could result in a
different inspection threshold and
interval for each individual airplane,
and the FAA did not agree with
adjusting a flight cycle based threshold
and interval using the average flight
time utilization without also having a
related flight hour based threshold and
interval.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
56526, September 22, 2014) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 56526,
September 22, 2014).
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information. The service
information describes procedures for
repetitive inspections for cracking of the
pylons 1 and 2 side panels (upper
section) at rib 8 with reduced
compliance times, and corrective
actions if necessary. This service
information also describes procedures
for post-modification and post-repair
detailed inspections for cracking, as
applicable, of the left-hand (LH) and
right-hand (RH) side panels of pylons 1
and 2, and repair if necessary. This
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service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
• Airbus Service Bulletin A300–54–
0075, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including
Appendix 4; dated March 27, 2013.
• Airbus Service Bulletin A310–54–
2018, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including
Appendix 4; dated April 11, 2013.
• Airbus Service Bulletin A300–54–
6015, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including
Appendix 4; dated April 11, 2013.
Airbus has also issued the following
service information. This service
information describes procedures for
modifying by installing a doubler on the
LH pylon 1 and RH pylon 2, on pylon
side panels (upper section), at rib 8.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
• Airbus Service Bulletin A300–54–
0081, dated August 11, 1993.
• Airbus Service Bulletin A310–54–
2024, dated August 11, 1993.
• Airbus Service Bulletin A300–54–
6021, Revision 02, dated May 21, 2008.
Costs of Compliance
We estimate that this AD affects 156
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Labor cost
Inspection [retained actions from
AD 2010–06–04, Amendment
39–16228 ((75 FR 11428,
March 11, 2010); corrected
May 4, 2010 (75 FR 23572))].
Inspection [new actions] ..............
4 work-hours × $85 per hour = $340 ..........
$0
$340 ..........................
$53,040.
24 work-hours × $85 per hour = $2,040 per
inspection cycle.
0
$2,040 per inspection
cycle.
$318,240 per inspection cycle.
We estimate the following costs to do
any necessary repairs that would be
Parts cost
Cost per product
Cost on U.S.
operators
Action
required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Repair ..................................
Optional Modification ...........
58 work-hours × $85 per hour = $4,930 .......................
Up to 48 work-hours × $85 per hour = $4,080 .............
$3,910 ................................
Up to $1,026 ......................
jstallworth on DSK7TPTVN1PROD with RULES
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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Cost per product
$8,840.
Up to $5,106.
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 that 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);
3. Will not affect intrastate aviation in
Alaska; and
4. 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.
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
Examining the AD Docket
■
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docketDetail;D=
FAA-2014-0648; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
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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
removing Airworthiness Directive (AD)
2010–06–04, Amendment 39–16228 ((75
FR 11428, March 11, 2010); corrected
■
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May 4, 2010 (75 FR 23572)), and adding
the following new AD:
2015–25–06 Airbus: Amendment 39–
18344. Docket No. FAA–2014–0648;
Directorate Identifier 2013–NM–136–AD.
(a) Effective Date
This AD becomes effective February 2,
2016.
except those on which Airbus Modification
10432 has been embodied in production.
(3) Airbus Model A300 B4-601, B4-603, B4605R, B4-620, B-622, and B4-622R airplanes,
except those on which Airbus Modification
10432 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(b) Affected ADs
This AD replaces AD 2010–06–04,
Amendment 39–16228 ((75 FR 11428, March
11, 2010); corrected May 4, 2010 (75 FR
23572)).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category.
(1) Airbus Model A300 B2–1C, B2–203,
B2K–3C, B4–103, B4–203, and B4–2C
airplanes, on which Airbus Modification
02434 has been embodied in production.
(2) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes,
(e) Reason
This AD was prompted by reports of cracks
found on pylon side panels at rib 8 and a
fleet survey and updated fatigue and damage
tolerance analyses. We are issuing this AD to
detect and correct cracking of pylon side
panels (upper section) at rib 8, which could
lead to reduced structural integrity of the
pylon primary structure, which could cause
detachment of the engine from the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Actions and Compliance With
Revised Service Information
This paragraph restates the requirements of
paragraph (f) of AD 2010–06–04, Amendment
39–16228 ((75 FR 11428, March 11, 2010);
corrected May 4, 2010 (75 FR 23572)), with
revised service information. Accomplishing
the initial inspection required by paragraph
(h) of this AD terminates the requirements of
this paragraph.
(1) For Configuration 01 airplanes as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: At
the applicable time specified in table 1 to
paragraph (g) of this AD, except as required
by paragraphs (g)(2) and (g)(3) of this AD,
perform a detailed visual inspection of the
pylons 1 and 2 side panels (upper section) at
rib 8, in accordance with paragraph 3.B. of
the Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9)(i) through (g)(9)(iii) of this
AD or paragraphs (k)(1), (k)(2), or (k)(3) of
this AD. Repeat the inspection at the time
specified in table 1 to paragraph (g) of this
AD.
TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES
For Model—
That have accumulated—
Inspect before the
accumulation of—
And repeat the inspection
at intervals not to
exceed—
Or within—
Whichever occurs later
≤17,500 total flight cycles 1
5,350 total flight cycles .....
2,500 flight cycles 2 ...........
4,300 flight cycles.
>17,500 total flight cycles 1
4,300 flight cycles.
≤18,000 total flight cycles 1
20,000 total flight cycles or
40,000 total flight hours,
whichever occurs first.
5,350 total flight cycles .....
250 flight cycles 2 ..............
A300 B4–103, B4–203,
and B4–2C airplanes.
A300 B4–103, B4–203,
and B4–2C airplanes.
2,000 flight cycles 2 ...........
4,300 flight cycles.
250 flight cycles 2 ..............
4,300 flight cycles.
A300 B4–601, B4–603,
B4–605R, B4–620, B4–
622, and B4–622R airplanes.
A300 B4–601, B4–603,
B4–605R, B4–620, B4–
622, and B4–622R airplanes.
A310–200 airplanes with
GE CF6–80A3 or Pratt &
Whitney engines.
A310–200 airplanes with
GE CF6–80A3 or Pratt &
Whitney engines.
A310–200 airplanes with
GE CF6–80C2 engines.
≤18,000 total flight cycles 1
2,000 flight cycles 2 ...........
3,600 flight cycles.
A310–200 airplanes with
GE CF6–80C2 engines.
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A300 B2–1C, B2–203, and
B2K–3C airplanes.
A300 B2–1C, B2–203, and
B2K–3C airplanes.
>18,000 total flight cycles 1
A310–300 SR 3 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 SR 3 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 SR 3 airplanes
with GE engines.
≤18,000 total flight cycles 1
A310–300 SR 3 airplanes
with GE engines.
>18,000 total flight cycles 1
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>18,000 total flight cycles 1
20,000 total flight cycles or
40,000 total flight hours,
whichever occurs first.
4,200 total flight cycles .....
>18,000 total flight cycles 1
20,000 total flight cycles or
40,000 total flight hours,
whichever occurs first.
250 flight cycles 2 ..............
3,600 flight cycles.
≤18,000 total flight cycles 1
9,700 total flight cycles or
19,400 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
7,800 total flight cycles or
15,600 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
8,600 total flight cycles or
24,000 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
7,000 total flight cycles or
19,600 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
1,500 flight cycles 2 ...........
6,700 flight cycles or
13,400 flight hours,
whichever occurs first.
6,700 flight cycles or
13,400 flight hours,
whichever occurs first.
5,800 flight cycles or
11,600 flight hours,
whichever occurs first.
5,800 flight cycles or
11,600 flight hours,
whichever occurs first.
6,700 flight cycles or
18,700 flight hours,
whichever occurs first.
6,700 flight cycles or
18,700 flight hours,
whichever occurs first.
5,700 flight cycles or
15,900 flight hours,
whichever occurs first.
5,700 flight cycles or
15,900 flight hours,
whichever occurs first.
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
21:07 Dec 28, 2015
Jkt 238001
PO 00000
Frm 00013
Fmt 4700
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250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES FOR CONFIGURATION 1 AIRPLANES—Continued
For Model—
That have accumulated—
Inspect before the
accumulation of—
And repeat the inspection
at intervals not to
exceed—
Or within—
Whichever occurs later
A310–300 SR 3 airplanes
with Pratt & Whitney
4000 engines.
A310–300 SR 3 airplanes
with Pratt & Whitney
4000 engines.
A310–300 LR 4 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 LR 4 airplanes
with Pratt & Whitney
JT9D engines.
A310–300 LR 4 airplanes
with GE engines.
≤18,000 total flight cycles 1
A310–300 LR 4 airplanes
with GE engines.
>18,000 total flight cycles 1
A310–300 LR 4 airplanes
with Pratt & Whitney
4000 engines.
A310–300 LR 4 airplanes
with Pratt & Whitney
4000 engines.
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
≤18,000 total flight cycles 1
>18,000 total flight cycles 1
7,000 total flight cycles or
19,600 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
5,900 total flight cycles or
29,500 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
4,800 total flight cycles or
24,100 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
4,800 total flight cycles or
24,000 total flight hours,
whichever occurs first.
19,500 total flight cycles or
55,500 total flight hours,
whichever occurs first.
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
1,500 flight cycles 2 ...........
250 flight cycles 2 ..............
5,800 flight cycles or
16,200 flight hours,
whichever occurs first.
5,800 flight cycles or
16,200 flight hours,
whichever occurs first.
6,000 flight cycles or
30,300 flight hours,
whichever occurs first.
6,000 flight cycles or
30,300 flight hours,
whichever occurs first.
5,100 flight cycles or
25,500 flight hours,
whichever occurs first.
5,100 flight cycles or
25,500 flight hours,
whichever occurs first.
5,200 flight cycles or
26,300 flight hours,
whichever occurs first.
5,200 flight cycles or
26,300 flight hours,
whichever occurs first.
jstallworth on DSK7TPTVN1PROD with RULES
1 As of April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010
(75 FR 23572))).
2 After April 15, 2010 (the effective date of AD 2010–06–04, Amendment 39–16228 ((75 FR 11428, March 11, 2010; corrected May 4, 2010
(75 FR 23572))).
3 ‘‘SR’’ applies to airplanes with average flights less than 4 flight hours.
4 ‘‘LR’’ refers to airplanes with average flights of 4 or more flight hours.
(2) For Model A300 and A300–600
airplanes that have accumulated more than
40,000 total flight hours as of April 15, 2010
(the effective date of AD 2010–06–04,
Amendment 39–16228 ((75 FR 11428, March
11, 2010); corrected May 4, 2010 (75 FR
23572))): Within 250 flight cycles after April
15, 2010, do the actions specified in
paragraph (g)(1) of this AD.
(3) For Model A310 airplanes that have
accumulated more than 55,500 total flight
hours as of April 15, 2010 (the effective date
of AD 2010–06–04, Amendment 39–16228
((75 FR 11428, March 11, 2010); corrected
May 4, 2010 (75 FR 23572))): Within 250
flight cycles after April 15, 2010, do the
actions specified in paragraph (g)(1) of this
AD.
(4) For Configuration 01 airplanes, as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: If a
crack is found during any inspection
required by paragraph (g)(1) of this AD,
before further flight, install a doubler, in
accordance with paragraph 3.C. of the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9) of this AD.
(5) For Configuration 02 airplanes, as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: At
the applicable time specified in paragraph
1.E.(2) of the applicable service bulletin
identified in paragraphs (g)(9)(i) through
(g)(9)(iii) of this AD, or within 250 flight
cycles after April 15, 2010 (the effective date
of AD 2010–06–04, Amendment 39–16228
VerDate Sep<11>2014
21:07 Dec 28, 2015
Jkt 238001
((75 FR 11428, March 11, 2010); corrected
May 4, 2010 (75 FR 23572))), whichever
occurs later, perform a detailed visual
inspection of the pylons 1 and 2 side panels
(upper section) at rib 8, in accordance with
paragraph 3.B. of the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (g)(9) of this AD.
(6) For Configuration 03 airplanes, as
identified in the applicable service bulletin
identified in paragraph (g)(9) of this AD: At
the applicable time specified in paragraph
1.E.(2) of the applicable service bulletin
identified in paragraphs (g)(9)(i) through
(g)(9)(iii) of this AD, or within 250 flight
cycles after April 15, 2010 (the effective date
of AD 2010–06–04, Amendment 39–16228
((75 FR 11428, March 11, 2010); corrected
May 4, 2010 (75 FR 23572))), whichever
occurs later, perform a detailed visual
inspection, and a high frequency eddy
current inspection as applicable, of the
pylons 1 and 2 side panels (upper section) at
rib 8, in accordance with paragraph 3.B. of
the Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9) of this AD.
(7) For Configuration 02 and 03 airplanes,
as identified in the applicable service
bulletin identified in paragraph (g)(9) of this
AD: If a crack is found during any inspection
required by paragraph (g)(1), (g)(5), or (g)(6)
of this AD, before further flight, repair in
accordance with paragraph 3.C. of the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(9) of this AD.
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Fmt 4700
Sfmt 4700
(8) For all airplanes, except those in
Configuration 01, as identified in the
applicable service bulletin identified in
paragraph (g)(9) of this AD: Repeat the
inspection specified in paragraph (g)(1),
(g)(5), or (g)(6) of this AD, as applicable, at
the intervals specified in paragraph 1.E.(2) of
the applicable service bulletin identified in
paragraph (g)(9)(i) through (g)(9)(iii) of this
AD.
(9) For the actions specified in paragraph
(g) of this AD, use the applicable service
bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or paragraph
(k)(1), (k)(2), or (k)(3) of this AD.
(i) Airbus Mandatory Service Bulletin
A300–54–0075, excluding Appendixes 1, 2,
and 3, Revision 02, dated June 26, 2008 (For
Model A300 B2–1C, B2–203, B2K–3C, B4–
103, B4–203, and B4–2C airplanes).
(ii) Airbus Mandatory Service Bulletin
A300–54–6015, excluding Appendixes 1, 2,
and 3, Revision 02, dated June 26, 2008 (For
Model A300 B4–601, B4–603, B4–605R, B4–
620, B4–622, and B4–622R airplanes).
(iii) Airbus Mandatory Service Bulletin
A310–54–2018, excluding Appendixes 1, 2,
and 3, Revision 02, dated June 26, 2008 (for
Model A310 series airplanes).
(h) New Repetitive Inspections and Repair
Except as required by paragraphs (l)(1) and
(l)(2) of this AD, at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
the applicable service bulletin identified in
paragraph (k) of this AD: Do a detailed
inspection for cracking of the pylons 1 and
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
2 side panels (upper section) at rib 8, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD.
Accomplishing the inspection required by
this paragraph terminates the requirements of
paragraph (g)(1) through (g)(9) of this AD.
(1) If any cracking is found, before further
flight, do a high frequency eddy current
(HFEC) inspection to confirm the crack, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD.
(i) If any crack indication is confirmed
during the HFEC inspection specified in
paragraph (h)(1) of this AD, and the crack is
less than 20 mm, before further flight, repair,
in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD.
(ii) If any crack indication is confirmed
during the HFEC inspection specified in
paragraph (h)(1) of this AD and the crack is
greater than or equal to 20 mm, before further
flight, repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA).
(2) If no cracking is found, or if crack
indication is not confirmed during the HFEC
inspection required by paragraph (h)(1) of
this AD, at the applicable interval specified
in paragraph 1.E., ‘‘Compliance,’’ of the
applicable service bulletin identified in
paragraph (k) of this AD, repeat the
inspection specified in paragraph (h) of this
AD, in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (k) of this AD until
the modification specified in paragraph (i) is
done.
jstallworth on DSK7TPTVN1PROD with RULES
(i) Optional Modification
Modifying by installing a doubler on the
left hand (LH) pylon 1 and right hand (RH)
pylon 2, on pylon side panels (upper
section), at rib 8, in accordance with the
Accomplishment Instructions of the service
information identified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD; as applicable;
terminates the repetitive inspections
specified in paragraph (h)(2) of this AD.
(1) Airbus Service Bulletin A300–54–0081,
dated August 11, 1993.
(2) Airbus Service Bulletin A310–54–2024,
dated August 11, 1993.
(3) Airbus Service Bulletin A300–54–6021,
Revision 02, dated May 21, 2008.
(j) Post-Modification and Post-Repair
Repetitive Inspections and Corrective
Actions
For airplanes on which the modification
has been done as specified in paragraph (i)
of this AD, and airplanes on which the repair
has been done as specified in paragraph (h)
of this AD: At the applicable compliance
time specified in paragraph 1.E.,
Compliance,’’ of the applicable service
bulletin identified in paragraph (k) of this
AD, do the post-modification and post-repair
detailed inspections for cracking, as
applicable, of the LH and RH side panels of
pylons 1 and 2, in accordance with the
VerDate Sep<11>2014
15:24 Dec 28, 2015
Jkt 238001
applicable service bulletins identified in
paragraph (k) of this AD. Repeat the
inspections thereafter at the times specified
in paragraph 1.E., ‘‘Compliance’’ of the
applicable service bulletin specified in
paragraph (k) of this AD. If any cracking is
found, before further flight, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA. This repair is not a
terminating action for the repetitive
inspections required by this paragraph.
(k) New Service Information
Use the applicable service bulletin
identified in paragraphs (k)(1) through (k)(3)
of this AD to accomplish the inspections
required by paragraphs (g), (h), and (j) of this
AD.
(1) Airbus Service Bulletin A300–54–0075,
Revision 03, excluding Appendixes 1, 2, 3,
and 5; including Appendix 4; dated March
27, 2013 (for Model A300 B2–1C, B2–203,
B2K–3C, B4–103, B4–203, and B4–2C
airplanes).
(2) Airbus Service Bulletin A310–54–2018,
Revision 03, excluding Appendixes 1, 2, 3,
and 5; including Appendix 4; dated April 11,
2013 (for Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes).
(3) Airbus Service Bulletin A300–54–6015,
Revision 03, excluding Appendixes 1, 2, 3,
and 5; including Appendix 4; dated April 11,
2013 (for Model A300 B4–601, B4–603, B4–
605R, B4–620, B4–622, and B4–622R
airplanes).
(l) Exceptions
(1) Where the compliance time column in
the tables in paragraph 1.E., ‘‘Compliance,’’
of the applicable service bulletin identified
in paragraph (k) of this AD specifies a
‘‘threshold’’ in ‘‘FC’’ or ‘‘FH,’’ and does not
specify from repair or service bulletin
embodiment, those compliance times are
total flight cycles and total flight hours.
(2) Where the tables in paragraph 1.E.,
‘‘Compliance,’’ of the applicable service
bulletin specified in paragraph (k) of this AD
specifies ‘‘grace period after the receipt of the
service bulletin,’’ this AD requires
compliance within the corresponding
compliance time after the effective date of
this AD.
(m) Credit for Previous Actions
(1) This paragraph restates the credit
provided by paragraph (f)(9) of AD 2010–06–
04, Amendment 39–16228 ((75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75
FR 23572)) with no changes. This paragraph
provides credit for initial inspections
required by paragraph (g) of this AD, if those
actions were performed prior to April 15,
2010 (the effective date of AD 2010–06–04)
using the applicable service bulletins
specified in paragraphs (m)(1)(i) through
(m)(1)(vi) of this AD, which are not
incorporated by reference in this AD.
(i) Airbus Service Bulletin A300–54–0075,
dated August 11, 1993.
(ii) Airbus Service Bulletin A300–54–0075,
Revision 01, dated November 9, 2007.
(iii) Airbus Service Bulletin A300–54–
6015, dated August 11, 1993.
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81173
(iv) Airbus Service Bulletin A300–54–
6015, Revision 01, dated November 9, 2007.
(v) Airbus Service Bulletin A310–54–2018,
dated August 11, 1993.
(vi) Airbus Service Bulletin A310–54–
2018, Revision 01, dated November 16, 2007.
(2) This paragraph provides credit for
initial inspections required by paragraph (h)
of this AD, if those actions were performed
before the effective date of this AD using the
applicable service bulletins specified in
paragraphs (m)(2)(i) through (m)(2)(ix) of this
AD.
(i) Airbus Service Bulletin A300–54–0075,
dated August 11, 1993, which is not
incorporated by reference in this AD.
(ii) Airbus Service Bulletin A300–54–0075,
Revision 01, dated November 9, 2007, which
is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A300–54–
0075, Revision 02, dated June 26, 2008.
(iv) Airbus Service Bulletin A300–54–
6015, dated August 11, 1993, which is not
incorporated by reference in this AD.
(v) Airbus Service Bulletin A300–54–6015,
Revision 01, dated November 9, 2007, which
is not incorporated by reference in this AD.
(vi) Airbus Service Bulletin A300–54–
6015, Revision 02, dated June 26, 2008.
(vii) Airbus Service Bulletin A310–54–
2018, dated August 11, 1993, which is not
incorporated by reference in this AD.
(viii) Airbus Service Bulletin A310–54–
2018, Revision 01, dated November 16, 2007,
which is not incorporated by reference in this
AD.
(ix) Airbus Service Bulletin A310–54–
2018, Revision 02, dated June 26, 2008.
(3) This paragraph provides credit for
initial inspections required by paragraph (i)
of this AD, if those actions were performed
before the effective date of this AD using the
applicable service bulletins specified in
paragraphs (m)(3)(i) and (m)(3)(ii) of this AD.
(i) Airbus Service Bulletin A300–54–6021,
dated August 11, 1993, which is not
incorporated by reference in this AD.
(ii) Airbus Service Bulletin A300–54–6021,
Revision 01, dated November 16, 2007,
which is not incorporated by reference in this
AD.
(n) Other FAA AD Provisions
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
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, WA 98057–3356;
telephone (425) 227–2125; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
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Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Rules and Regulations
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
2010–06–04, Amendment 39–16228 ((75 FR
11428, March 11, 2010); corrected May 4,
2010 (75 FR 23572)); are approved as AMOCs
for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
jstallworth on DSK7TPTVN1PROD with RULES
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0136R1, dated
July 30, 2013, for related information. You
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0648-0002.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on February 2, 2016.
(i) Airbus Service Bulletin A300–54–0075,
Revision 03, excluding Appendixes 1, 2, 3,
and 5; including Appendix 4; dated March
27, 2013.
(ii) Airbus Service Bulletin A300–54–0081,
dated August 11, 1993.
(iii) Airbus Service Bulletin A300–54–
6015, Revision 03, excluding Appendixes 1,
2, 3, and 5; including Appendix 4; dated
April 11, 2013.
(iv) Airbus Service Bulletin A300–54–
6021, Revision 02, dated May 21, 2008.
(v) Airbus Service Bulletin A310–54–2018,
Revision 03, excluding Appendixes 1, 2, 3,
and 5; including Appendix 4; dated April 11,
2013.
(vi) Airbus Service Bulletin A310–54–
2024, dated August 11, 1993.
(4) The following service information was
approved for IBR on April 15, 2010 ((75 FR
11428, March 11, 2010); corrected May 4,
2010 (75 FR 23572)).
(i) Airbus Mandatory Service Bulletin
A300–54–0075, excluding Appendixes 1, 2,
and 3, Revision 02, dated June 26, 2008.
(ii) Airbus Mandatory Service Bulletin
A300–54–6015, excluding Appendixes 1, 2,
and 3, Revision 02, dated June 26, 2008.
(iii) Airbus Mandatory Service Bulletin
A310–54–2018, excluding Appendixes 1, 2,
and 3, Revision 02, dated June 26, 2008.
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
VerDate Sep<11>2014
15:24 Dec 28, 2015
Jkt 238001
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(6) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 8, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–31603 Filed 12–28–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0076; Directorate
Identifier 2013–NM–246–AD; Amendment
39–18350; AD 2015–26–02]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–200, A330–200
Freighter, and A330–300 series
airplanes; and Airbus Model A340–200,
A340–300, A340–500, and A340–600
series airplanes. This AD was prompted
by a report that, during a production
flight test, the ram air turbine (RAT) did
not pressurize the green hydraulic
system. For certain airplanes, this AD
requires identification of the part
number, serial number, and standard of
the RAT pump, RAT module, RAT
actuator, and RAT lower gearbox
assembly; replacement of the balance
weight screw, modification of the
actuator coil spring, modification of the
actuator, an inspection of the anti-stall
valve for correct installation in the RAT
pump housing; and corrective actions if
necessary. For certain other airplanes,
this AD requires re-identification or
replacement of the RAT module. We are
issuing this AD to prevent loss of the
SUMMARY:
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
impeller function and RAT pump
pressurization capability, which, if
preceded by a total engine flame-out,
could result in the loss of control of the
airplane.
DATES: This AD becomes effective
February 2, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 2, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0076; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For Airbus service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330A340@
airbus.com; Internet https://
www.airbus.com. For Hamilton
Sundstrand service information
identified in this AD, contact Hamilton
Sundstrand, Technical Publications,
Mail Stop 302–9, 4747 Harrison
Avenue, P.O. Box 7002, Rockford, IL
61125–7002; telephone 860–654–3575;
fax 860–998–4564; email
tech.solutions@hs.utc.com; Internet
https://www.hamiltonsundstrand.com.
You may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0076.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A330–200,
A330–200 Freighter, and A330–300
series airplanes; and Airbus Model
A340–200, A340–300, A340–500, and
A340–600 series airplanes. The NPRM
E:\FR\FM\29DER1.SGM
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]]>Agencies
[Federal Register Volume 80, Number 249 (Tuesday, December 29, 2015)]
[Rules and Regulations]
[Pages 81168-81174]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-31603]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0648; Directorate Identifier 2013-NM-136-AD;
Amendment 39-18344; AD 2015-25-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2010-06-04,
for certain Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203,
B4-2C airplanes; Model A310 series airplanes; Model A300 B4-600 series
airplanes; and Model A300 B4-600R series airplanes. AD 2010-06-04
required repetitive inspections to detect cracks of the pylon side
panels (upper section) at rib 8; and corrective actions if necessary.
This new AD continues to require repetitive inspections for cracking of
the pylons 1 and 2 side panels (upper section) at rib 8 with reduced
compliance times, and corrective actions if necessary. This AD also
requires repetitive post-repair and post-modification inspections and
repair if necessary. This AD also removes certain airplanes having a
certain modification from the applicability. This AD was prompted by
reports of cracks found on pylon side panels at rib 8 and a fleet
survey and updated fatigue and damage tolerance analyses. We are
issuing this AD to detect and correct cracking of pylon side panels
(upper section) at rib 8, which could lead to reduced structural
integrity of the pylon primary structure, which could cause detachment
of the engine from the fuselage.
DATES: This AD becomes effective February 2, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 2,
2016.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
15, 2010 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR
23572)).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0648; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this final rule, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0648.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 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 supersede AD 2010-06-04,
[[Page 81169]]
Amendment 39-16228 ((75 FR 11428, March 11, 2010); corrected May 4,
2010 (75 FR 23572)). AD 2010-06-04 applied to certain Airbus Model A300
B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C airplanes; Model A310
series airplanes; Model A300 B4-600 series airplanes; and Model A300
B4-600R series airplanes. The NPRM published in the Federal Register on
September 22, 2014 (79 FR 56526).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0136R1, dated July 30, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on certain Airbus Model
A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C airplanes; Model A310
series airplanes; Model A300 B4-600 series airplanes; and Model A300
B4-600R series airplanes. The MCAI states:
Cracks were found on pylon side panels (upper section) at rib 8
on Airbus A300, A310 and A300-600 aeroplanes equipped with General
Electric engines. Investigation of these findings indicated that
this problem was likely to also affect aeroplanes of this type
design with other engine installations.
This condition, if not detected and corrected, could lead to
reduced strength of the pylon primary structure, possibly resulting
in pylon structural failure and in-flight loss of an engine.
Prompted by these findings, EASA issued AD 2008-0181 [https://www.regulations.gov/#!documentDetail;D=FAA-2009-0789-0002] [which
corresponds to FAA AD 2010-06-04, Amendment 39-16228 ((75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75 FR 23572))] to require
repetitive detailed visual inspections [of the pylon side panels
(upper section) at rib 8] and, depending on aeroplane configuration
and/or findings, the accomplishment of applicable corrective
action(s).
Since that [EASA] AD was issued, a fleet survey and updated
Fatigue and Damage Tolerance analyses have been performed in order
to substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of these analyses have shown that the risk for
these aeroplanes is higher than initially determined and
consequently, the threshold and interval must be reduced to allow
timely detection of these cracks and the accomplishment of
applicable correction action(s).
EASA issued AD 2013-0136 [https://ad.easa.europa.eu/ad/2013-0136R1] which retained the requirements of EASA AD 2008-0181, which
was superseded, and required the inspections to be accomplished
within reduced thresholds and intervals.
After publication of EASA AD 2013-0136, it appeared that Airbus
Mod 03599 had no influence on the aeroplane configuration affected
by this AD. At the same time Airbus Service Bulletin (SB) A30-54-
6015 Revision 3 was not integrally taken into account as this
revision no longer identifies configuration 3 aeroplanes.
For the reasons described above, EASA [AD] 2013-0136 is revised
to exclude Airbus Mod 03599 from the applicability and to delete the
reference to the configuration 3 for A300-600 aeroplanes.
Corrective actions include doing a repair. This AD also provides an
optional modification (installing a doubler), which would terminate the
repetitive inspections. Required actions also include repetitive post-
repair and post-modification inspections and repair if necessary. You
may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0648-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM (79 FR
56526, September 22, 2014) and the FAA's response.
Request To Revise Method Used To Determine Compliance Times
United Parcel Service (UPS) requested that we revise the proposed
compliance times to be less complex. UPS stated that the proposed
compliance times contain a method known as ``Average Flight Time''
(AFT) which results in a variable flight hour limit and adds
unnecessary complexity to the threshold table and subsequent inspection
actions. UPS added that use of the AFT method, along with a lack of
standard procedures for implementing the AFT method would create
uncertainty for operators and inspectors trying to determine the
correct compliance time. UPS stated that in review of prior FAA ADs,
including AD 98-18-02, Amendment 39-10718 (63 FR 45689, August 27,
1998), that the FAA does not concur with the AFT compliance time
methodology as ``. . . such adjustments may not address the unsafe
condition in a timely manner'' and ``. . . they (AFT compliance times)
do not fit into the AD tracking process for operators or for Principle
Maintenance Inspectors (PMIs) attempting to ascertain compliance with
ADs.''
UPS compiled a table of fixed compliance times that it suggested
would be simpler to use instead of the proposed AFT-based compliance
times.
We disagree with the commenter's request to revise the compliance
times in this AD. The compliance times, as proposed, use fixed flight-
cycle and flight-hour compliance times. For only Model A310 series
airplanes, the compliance times depend on whether airplanes are short
range or long range airplanes. We acknowledge that this causes
additional complexity in tracking and forecasting airplane utilization;
however, the inspection schedule was created by Airbus to offer
operators the greatest flexibility. Operators may elect to inspect
within the range that complies with both the long range and short range
utilization in order to reduce the complexity. We have not changed this
AD in this regard.
Regarding AD 98-18-02, Amendment 39-10718 (63 FR 45689, August 27,
1998), at the time the FAA issued AD 98-18-02, the required actions in
Airbus Industrie Service Bulletin A300-57-6027, Revision 2, dated
September 13, 1994, contained inspection thresholds and intervals based
on airplane flight cycles, and provided instructions for adjusting the
flight cycle threshold and interval using each individual airplane's
AFT utilization. The FAA did not agree with the AFT method because it
could result in a different inspection threshold and interval for each
individual airplane, and the FAA did not agree with adjusting a flight
cycle based threshold and interval using the average flight time
utilization without also having a related flight hour based threshold
and interval.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 56526, September 22, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 56526, September 22, 2014).
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information. The service
information describes procedures for repetitive inspections for
cracking of the pylons 1 and 2 side panels (upper section) at rib 8
with reduced compliance times, and corrective actions if necessary.
This service information also describes procedures for post-
modification and post-repair detailed inspections for cracking, as
applicable, of the left-hand (LH) and right-hand (RH) side panels of
pylons 1 and 2, and repair if necessary. This
[[Page 81170]]
service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Airbus Service Bulletin A300-54-0075, Revision 03,
excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated March
27, 2013.
Airbus Service Bulletin A310-54-2018, Revision 03,
excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April
11, 2013.
Airbus Service Bulletin A300-54-6015, Revision 03,
excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated April
11, 2013.
Airbus has also issued the following service information. This
service information describes procedures for modifying by installing a
doubler on the LH pylon 1 and RH pylon 2, on pylon side panels (upper
section), at rib 8. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.
Airbus Service Bulletin A300-54-0081, dated August 11,
1993.
Airbus Service Bulletin A310-54-2024, dated August 11,
1993.
Airbus Service Bulletin A300-54-6021, Revision 02, dated
May 21, 2008.
Costs of Compliance
We estimate that this AD affects 156 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [retained actions 4 work-hours x $85 per $0 $340.............. $53,040.
from AD 2010-06-04, Amendment hour = $340.
39-16228 ((75 FR 11428, March
11, 2010); corrected May 4,
2010 (75 FR 23572))].
Inspection [new actions]....... 24 work-hours x $85 per 0 $2,040 per $318,240 per
hour = $2,040 per inspection cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspection. We have no
way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair............................. 58 work-hours x $85 per $3,910................ $8,840.
hour = $4,930.
Optional Modification.............. Up to 48 work-hours x $85 Up to $1,026.......... Up to $5,106.
per hour = $4,080.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0648; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this 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.
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 removing Airworthiness Directive (AD)
2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010);
corrected
[[Page 81171]]
May 4, 2010 (75 FR 23572)), and adding the following new AD:
2015-25-06 Airbus: Amendment 39-18344. Docket No. FAA-2014-0648;
Directorate Identifier 2013-NM-136-AD.
(a) Effective Date
This AD becomes effective February 2, 2016.
(b) Affected ADs
This AD replaces AD 2010-06-04, Amendment 39-16228 ((75 FR
11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572)).
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and
B4-2C airplanes, on which Airbus Modification 02434 has been
embodied in production.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes, except those on which Airbus Modification 10432
has been embodied in production.
(3) Airbus Model A300 B4-601, B4-603, B4-605R, B4-620, B-622,
and B4-622R airplanes, except those on which Airbus Modification
10432 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Reason
This AD was prompted by reports of cracks found on pylon side
panels at rib 8 and a fleet survey and updated fatigue and damage
tolerance analyses. We are issuing this AD to detect and correct
cracking of pylon side panels (upper section) at rib 8, which could
lead to reduced structural integrity of the pylon primary structure,
which could cause detachment of the engine from the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Actions and Compliance With Revised Service Information
This paragraph restates the requirements of paragraph (f) of AD
2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010);
corrected May 4, 2010 (75 FR 23572)), with revised service
information. Accomplishing the initial inspection required by
paragraph (h) of this AD terminates the requirements of this
paragraph.
(1) For Configuration 01 airplanes as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: At the applicable time specified in table 1 to paragraph (g) of
this AD, except as required by paragraphs (g)(2) and (g)(3) of this
AD, perform a detailed visual inspection of the pylons 1 and 2 side
panels (upper section) at rib 8, in accordance with paragraph 3.B.
of the Accomplishment Instructions of the applicable service
bulletin identified in paragraph (g)(9)(i) through (g)(9)(iii) of
this AD or paragraphs (k)(1), (k)(2), or (k)(3) of this AD. Repeat
the inspection at the time specified in table 1 to paragraph (g) of
this AD.
Table 1 to Paragraph (g) of This AD--Compliance Times for Configuration 1 Airplanes
----------------------------------------------------------------------------------------------------------------
And repeat the
That have Inspect before the inspection at
For Model-- accumulated-- accumulation of-- Or within-- intervals not to
exceed--
---------Whichever occurs later---------
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, and B2K-3C <=17,500 total 5,350 total flight 2,500 flight 4,300 flight
airplanes. flight cycles \1\. cycles. cycles \2\. cycles.
A300 B2-1C, B2-203, and B2K-3C >17,500 total 20,000 total 250 flight cycles 4,300 flight
airplanes. flight cycles \1\. flight cycles or \2\. cycles.
40,000 total
flight hours,
whichever occurs
first.
A300 B4-103, B4-203, and B4-2C <=18,000 total 5,350 total flight 2,000 flight 4,300 flight
airplanes. flight cycles \1\. cycles. cycles \2\. cycles.
A300 B4-103, B4-203, and B4-2C >18,000 total 20,000 total 250 flight cycles 4,300 flight
airplanes. flight cycles \1\. flight cycles or \2\. cycles.
40,000 total
flight hours,
whichever occurs
first.
A300 B4-601, B4-603, B4-605R, B4- <=18,000 total 4,200 total flight 2,000 flight 3,600 flight
620, B4-622, and B4-622R flight cycles \1\. cycles. cycles \2\. cycles.
airplanes.
A300 B4-601, B4-603, B4-605R, B4- >18,000 total 20,000 total 250 flight cycles 3,600 flight
620, B4-622, and B4-622R flight cycles \1\. flight cycles or \2\. cycles.
airplanes. 40,000 total
flight hours,
whichever occurs
first.
A310-200 airplanes with GE CF6- <=18,000 total 9,700 total flight 1,500 flight 6,700 flight
80A3 or Pratt & Whitney engines. flight cycles \1\. cycles or 19,400 cycles \2\. cycles or 13,400
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 6,700 flight
80A3 or Pratt & Whitney engines. flight cycles \1\. flight cycles or \2\. cycles or 13,400
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-200 airplanes with GE CF6- <=18,000 total 7,800 total flight 1,500 flight 5,800 flight
80C2 engines. flight cycles \1\. cycles or 15,600 cycles \2\. cycles or 11,600
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 5,800 flight
80C2 engines. flight cycles \1\. flight cycles or \2\. cycles or 11,600
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 8,600 total flight 1,500 flight 6,700 flight
Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 18,700
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,700 flight
Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 18,700
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,700 flight
GE engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 15,900
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,700 flight
GE engines. flight cycles \1\. flight cycles or \2\. cycles or 15,900
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
[[Page 81172]]
A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,800 flight
Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 16,200
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,800 flight
Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 16,200
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 5,900 total flight 1,500 flight 6,000 flight
Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 29,500 cycles \2\. cycles or 30,300
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,000 flight
Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 30,300
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,100 flight
GE engines. flight cycles \1\. cycles or 24,100 cycles \2\. cycles or 25,500
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,100 flight
GE engines. flight cycles \1\. flight cycles or \2\. cycles or 25,500
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,200 flight
Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 26,300
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,200 flight
Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 26,300
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
----------------------------------------------------------------------------------------------------------------
\1\ As of April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11,
2010); corrected May 4, 2010 (75 FR 23572))).
\2\ After April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010;
corrected May 4, 2010 (75 FR 23572))).
\3\ ``SR'' applies to airplanes with average flights less than 4 flight hours.
\4\ ``LR'' refers to airplanes with average flights of 4 or more flight hours.
(2) For Model A300 and A300-600 airplanes that have accumulated
more than 40,000 total flight hours as of April 15, 2010 (the
effective date of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428,
March 11, 2010); corrected May 4, 2010 (75 FR 23572))): Within 250
flight cycles after April 15, 2010, do the actions specified in
paragraph (g)(1) of this AD.
(3) For Model A310 airplanes that have accumulated more than
55,500 total flight hours as of April 15, 2010 (the effective date
of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11, 2010);
corrected May 4, 2010 (75 FR 23572))): Within 250 flight cycles
after April 15, 2010, do the actions specified in paragraph (g)(1)
of this AD.
(4) For Configuration 01 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: If a crack is found during any inspection required by paragraph
(g)(1) of this AD, before further flight, install a doubler, in
accordance with paragraph 3.C. of the Accomplishment Instructions of
the applicable service bulletin identified in paragraph (g)(9) of
this AD.
(5) For Configuration 02 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: At the applicable time specified in paragraph 1.E.(2) of the
applicable service bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or within 250 flight cycles after
April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-
16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR
23572))), whichever occurs later, perform a detailed visual
inspection of the pylons 1 and 2 side panels (upper section) at rib
8, in accordance with paragraph 3.B. of the Accomplishment
Instructions of the applicable service bulletin identified in
paragraph (g)(9) of this AD.
(6) For Configuration 03 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: At the applicable time specified in paragraph 1.E.(2) of the
applicable service bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or within 250 flight cycles after
April 15, 2010 (the effective date of AD 2010-06-04, Amendment 39-
16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR
23572))), whichever occurs later, perform a detailed visual
inspection, and a high frequency eddy current inspection as
applicable, of the pylons 1 and 2 side panels (upper section) at rib
8, in accordance with paragraph 3.B. of the Accomplishment
Instructions of the applicable service bulletin identified in
paragraph (g)(9) of this AD.
(7) For Configuration 02 and 03 airplanes, as identified in the
applicable service bulletin identified in paragraph (g)(9) of this
AD: If a crack is found during any inspection required by paragraph
(g)(1), (g)(5), or (g)(6) of this AD, before further flight, repair
in accordance with paragraph 3.C. of the Accomplishment Instructions
of the applicable service bulletin identified in paragraph (g)(9) of
this AD.
(8) For all airplanes, except those in Configuration 01, as
identified in the applicable service bulletin identified in
paragraph (g)(9) of this AD: Repeat the inspection specified in
paragraph (g)(1), (g)(5), or (g)(6) of this AD, as applicable, at
the intervals specified in paragraph 1.E.(2) of the applicable
service bulletin identified in paragraph (g)(9)(i) through
(g)(9)(iii) of this AD.
(9) For the actions specified in paragraph (g) of this AD, use
the applicable service bulletin identified in paragraphs (g)(9)(i)
through (g)(9)(iii) of this AD, or paragraph (k)(1), (k)(2), or
(k)(3) of this AD.
(i) Airbus Mandatory Service Bulletin A300-54-0075, excluding
Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model
A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes).
(ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding
Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (For Model
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes).
(iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding
Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008 (for Model
A310 series airplanes).
(h) New Repetitive Inspections and Repair
Except as required by paragraphs (l)(1) and (l)(2) of this AD,
at the applicable times specified in paragraph 1.E., ``Compliance,''
of the applicable service bulletin identified in paragraph (k) of
this AD: Do a detailed inspection for cracking of the pylons 1 and
[[Page 81173]]
2 side panels (upper section) at rib 8, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in paragraph (k) of this AD. Accomplishing the inspection
required by this paragraph terminates the requirements of paragraph
(g)(1) through (g)(9) of this AD.
(1) If any cracking is found, before further flight, do a high
frequency eddy current (HFEC) inspection to confirm the crack, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraph (k) of this AD.
(i) If any crack indication is confirmed during the HFEC
inspection specified in paragraph (h)(1) of this AD, and the crack
is less than 20 mm, before further flight, repair, in accordance
with the Accomplishment Instructions of the applicable service
bulletin identified in paragraph (k) of this AD.
(ii) If any crack indication is confirmed during the HFEC
inspection specified in paragraph (h)(1) of this AD and the crack is
greater than or equal to 20 mm, before further flight, repair using
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) If no cracking is found, or if crack indication is not
confirmed during the HFEC inspection required by paragraph (h)(1) of
this AD, at the applicable interval specified in paragraph 1.E.,
``Compliance,'' of the applicable service bulletin identified in
paragraph (k) of this AD, repeat the inspection specified in
paragraph (h) of this AD, in accordance with the Accomplishment
Instructions of the applicable service bulletin identified in
paragraph (k) of this AD until the modification specified in
paragraph (i) is done.
(i) Optional Modification
Modifying by installing a doubler on the left hand (LH) pylon 1
and right hand (RH) pylon 2, on pylon side panels (upper section),
at rib 8, in accordance with the Accomplishment Instructions of the
service information identified in paragraph (i)(1), (i)(2), or
(i)(3) of this AD; as applicable; terminates the repetitive
inspections specified in paragraph (h)(2) of this AD.
(1) Airbus Service Bulletin A300-54-0081, dated August 11, 1993.
(2) Airbus Service Bulletin A310-54-2024, dated August 11, 1993.
(3) Airbus Service Bulletin A300-54-6021, Revision 02, dated May
21, 2008.
(j) Post-Modification and Post-Repair Repetitive Inspections and
Corrective Actions
For airplanes on which the modification has been done as
specified in paragraph (i) of this AD, and airplanes on which the
repair has been done as specified in paragraph (h) of this AD: At
the applicable compliance time specified in paragraph 1.E.,
Compliance,'' of the applicable service bulletin identified in
paragraph (k) of this AD, do the post-modification and post-repair
detailed inspections for cracking, as applicable, of the LH and RH
side panels of pylons 1 and 2, in accordance with the applicable
service bulletins identified in paragraph (k) of this AD. Repeat the
inspections thereafter at the times specified in paragraph 1.E.,
``Compliance'' of the applicable service bulletin specified in
paragraph (k) of this AD. If any cracking is found, before further
flight, repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. This repair is not a terminating action for the
repetitive inspections required by this paragraph.
(k) New Service Information
Use the applicable service bulletin identified in paragraphs
(k)(1) through (k)(3) of this AD to accomplish the inspections
required by paragraphs (g), (h), and (j) of this AD.
(1) Airbus Service Bulletin A300-54-0075, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including Appendix 4; dated March 27,
2013 (for Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-
2C airplanes).
(2) Airbus Service Bulletin A310-54-2018, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11,
2013 (for Model A310-203, -204, -221, -222, -304, -322, -324, and -
325 airplanes).
(3) Airbus Service Bulletin A300-54-6015, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11,
2013 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and
B4-622R airplanes).
(l) Exceptions
(1) Where the compliance time column in the tables in paragraph
1.E., ``Compliance,'' of the applicable service bulletin identified
in paragraph (k) of this AD specifies a ``threshold'' in ``FC'' or
``FH,'' and does not specify from repair or service bulletin
embodiment, those compliance times are total flight cycles and total
flight hours.
(2) Where the tables in paragraph 1.E., ``Compliance,'' of the
applicable service bulletin specified in paragraph (k) of this AD
specifies ``grace period after the receipt of the service
bulletin,'' this AD requires compliance within the corresponding
compliance time after the effective date of this AD.
(m) Credit for Previous Actions
(1) This paragraph restates the credit provided by paragraph
(f)(9) of AD 2010-06-04, Amendment 39-16228 ((75 FR 11428, March 11,
2010); corrected May 4, 2010 (75 FR 23572)) with no changes. This
paragraph provides credit for initial inspections required by
paragraph (g) of this AD, if those actions were performed prior to
April 15, 2010 (the effective date of AD 2010-06-04) using the
applicable service bulletins specified in paragraphs (m)(1)(i)
through (m)(1)(vi) of this AD, which are not incorporated by
reference in this AD.
(i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993.
(ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated
November 9, 2007.
(iii) Airbus Service Bulletin A300-54-6015, dated August 11,
1993.
(iv) Airbus Service Bulletin A300-54-6015, Revision 01, dated
November 9, 2007.
(v) Airbus Service Bulletin A310-54-2018, dated August 11, 1993.
(vi) Airbus Service Bulletin A310-54-2018, Revision 01, dated
November 16, 2007.
(2) This paragraph provides credit for initial inspections
required by paragraph (h) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service bulletins specified in paragraphs (m)(2)(i) through
(m)(2)(ix) of this AD.
(i) Airbus Service Bulletin A300-54-0075, dated August 11, 1993,
which is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A300-54-0075, Revision 01, dated
November 9, 2007, which is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A300-54-0075, Revision 02, dated
June 26, 2008.
(iv) Airbus Service Bulletin A300-54-6015, dated August 11,
1993, which is not incorporated by reference in this AD.
(v) Airbus Service Bulletin A300-54-6015, Revision 01, dated
November 9, 2007, which is not incorporated by reference in this AD.
(vi) Airbus Service Bulletin A300-54-6015, Revision 02, dated
June 26, 2008.
(vii) Airbus Service Bulletin A310-54-2018, dated August 11,
1993, which is not incorporated by reference in this AD.
(viii) Airbus Service Bulletin A310-54-2018, Revision 01, dated
November 16, 2007, which is not incorporated by reference in this
AD.
(ix) Airbus Service Bulletin A310-54-2018, Revision 02, dated
June 26, 2008.
(3) This paragraph provides credit for initial inspections
required by paragraph (i) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service bulletins specified in paragraphs (m)(3)(i) and (m)(3)(ii)
of this AD.
(i) Airbus Service Bulletin A300-54-6021, dated August 11, 1993,
which is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A300-54-6021, Revision 01, dated
November 16, 2007, which is not incorporated by reference in this
AD.
(n) Other FAA AD Provisions
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 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, WA 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. Information may
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
[[Page 81174]]
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) AMOCs approved previously for AD 2010-06-04, Amendment 39-
16228 ((75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR
23572)); are approved as AMOCs for the corresponding provisions of
this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0136R1, dated July 30,
2013, for related information. You may examine the MCAI in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0648-0002.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
February 2, 2016.
(i) Airbus Service Bulletin A300-54-0075, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including Appendix 4; dated March 27,
2013.
(ii) Airbus Service Bulletin A300-54-0081, dated August 11,
1993.
(iii) Airbus Service Bulletin A300-54-6015, Revision 03,
excluding Appendixes 1, 2, 3, and 5; including Appendix 4; dated
April 11, 2013.
(iv) Airbus Service Bulletin A300-54-6021, Revision 02, dated
May 21, 2008.
(v) Airbus Service Bulletin A310-54-2018, Revision 03, excluding
Appendixes 1, 2, 3, and 5; including Appendix 4; dated April 11,
2013.
(vi) Airbus Service Bulletin A310-54-2024, dated August 11,
1993.
(4) The following service information was approved for IBR on
April 15, 2010 ((75 FR 11428, March 11, 2010); corrected May 4, 2010
(75 FR 23572)).
(i) Airbus Mandatory Service Bulletin A300-54-0075, excluding
Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008.
(ii) Airbus Mandatory Service Bulletin A300-54-6015, excluding
Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008.
(iii) Airbus Mandatory Service Bulletin A310-54-2018, excluding
Appendixes 1, 2, and 3, Revision 02, dated June 26, 2008.
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(7) You may view this 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 8, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-31603 Filed 12-28-15; 8:45 am]
BILLING CODE 4910-13-P
