Airworthiness Directives; Airbus Airplanes, 58715-58718 [2017-26627]
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Rules and Regulations
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Small Airplane
Standards Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Jim Rutherford,
Aerospace Engineer, FAA, Small Airplane
Standards Branch, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
(816) 329–4165; fax: (816) 329–4090; email:
jim.rutherford@faa.gov. Before using any
approved AMOC on any glider to which the
AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) Contacting the Manufacturer: 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, Small Airplane Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA).
Issued in Kansas City, Missouri, on
December 1, 2017.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
(h) Related Information
AGENCY:
Refer to MCAI EASA AD 2017–0136, dated
July 31, 2017, for related information. You
may examine the MCAI on the internet at
https://www.regulations.gov/
document?D=FAA-2017-0911-0002.
SUMMARY:
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(i) 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.
(i) Alexander Schleicher GmbH & Co.
Segelflugzeugbau ASK 21 Mi Technical Note
No. 11, ASW 22 BLE 50R Technical Note No.
16, ASH 25 M/Mi Technical Note No. 32,
ASH 26 E Technical Note No. 19 (single
document), dated January 8, 2016.
(ii) Reserved.
(3) For Alexander Schleicher GmbH & Co.
Segelflugzeugbau service information
identified in this AD, contact Alexander
Schleicher GmbH & Co. Segelflugzeugbau,
Alexander-Schleicher-Str. 1, D–36163
Poppenhausen, Germany; phone: +49 (0)
06658 89–0; fax: +49 (0) 06658 89–40;
internet: https://www.alexander-schleicher.de;
email: info@alexander-schleicher.de.
(4) You may view this service information
at the FAA, Policy and Innovation Division,
901 Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148. In
addition, you can access this service
information on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0911.
(5) 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.
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[FR Doc. 2017–26620 Filed 12–13–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0714; Product
Identifier 2017–NM–042–AD; Amendment
39–19123; AD 2017–25–09]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
We are superseding
Airworthiness Directive (AD) 2012–21–
04, which applied to all Airbus Model
A300 series airplanes; Model A310
series airplanes; and Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes).
AD 2012–21–04 required repetitive
inspections for, and replacement of, any
cracked hood halves of fuel pump
canisters. Since we issued AD 2012–21–
04, we allowed inspections of the wingouter tank and trim tank fuel pump
canister hood halves to be terminated.
This new AD retains the requirements
of AD 2012–21–04, reinstates the
terminated inspections, and adds
optional terminating actions. This AD
was prompted by reports of cracked fuel
pump canister hoods located in fuel
tanks and new in-service events of
wing-outer tank fuel pump canister
hood cracking. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective January 18,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 18, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 27, 2012 (77 FR
64701, October 23, 2012).
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
PO 00000
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58715
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.airwortheas@airbus.com; internet: https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 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–2017–
0714.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0714; 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 address for the
Docket Office (telephone: 800–647–
5527) is 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 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, 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 2012–21–04,
Amendment 39–17220 (77 FR 64701,
October 23, 2012) (‘‘AD 2012–21–04’’).
AD 2012–21–04 applied to all Airbus
Model A300 series airplanes; Model
A310 series airplanes; and Model A300
B4–600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes).
The NPRM published in the Federal
Register on August 2, 2017 (82 FR
35911). The NPRM was prompted by
reports of cracked fuel pump canister
hoods located in fuel tanks and new inservice events of wing-outer tank fuel
pump canister hood cracking. The
NPRM proposed to retain the
requirements of AD 2012–21–04,
reinstate terminated inspections, and
add optional terminating actions. We
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are issuing this AD to prevent any
detached canister hood fragments/debris
from being ingested into the fuel feed
system, and becoming a potential source
of ignition with consequent fire or
explosion.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0051,
dated March 23, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A300 series
airplanes; Model A310 series airplanes;
and Model A300–600 series airplanes.
The MCAI states:
Reports were received of finding cracked
fuel pump canister hoods located in fuel
tanks on in-service aeroplanes. Initial
analyses, laboratory testing and examinations
suggested that vibration-induced fatigue
could have caused these cracks. However,
initial data could not exclude some other
potential contributing factors.
This condition, if not detected and
corrected, could lead to detached canister
hood fragments or debris being ingested into
the fuel feed system. In addition, metallic
debris inside the fuel tank could result in a
potential source of fuel vapour ignition,
possibly resulting in a fire or fuel tank
explosion and consequent loss of the
aeroplane.
To address this potential unsafe condition,
EASA issued AD 2011–0124 (later revised)
[FAA AD 2012–21–04 corresponds to EASA
AD 2011–0124] to require repetitive
inspections of the canister hood halves
installed on all fuel pump canisters and, if
any damage was found, replacement. EASA
AD 2011–0124R1 introduced an optional
terminating action for the wing inner and
centre fuel tanks, and cancelled the repetitive
inspections of the fuel pump canister hoods
in outer wing and trim tanks, for which no
cracks had been reported following the initial
inspection.
Since that [EASA] AD was issued, new in
service events of outer tank fuel pump
canister hood cracking have been reported.
Consequently, the canister hoods of the outer
tank fuel pumps and trim tank fuel pumps
will need to be inspected.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2011–0124R1, which is superseded,
retaining the repetitive inspections of fuel
pump canister hoods in wing inner and
centre tanks, and reintroduces repetitive
detailed inspections (DET) for outer tank and
trim tank fuel pump canister hoods. This
[EASA] AD also retains the existing optional
terminating action for the repetitive DET of
wing inner and centre tank fuel pump
canister hoods, and introduces a new
optional terminating action for the repetitive
DET of the outer and trim tank fuel pump
canister hoods required by this [EASA] AD.
You may examine the MCAI in the
AD docket on the internet at https://
www.regulations.gov by searching for
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0714.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received. The
commenter, John Sanderson, supported
the NPRM.
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 for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A300–28–
0089, Revision 03, dated December 16,
2016. This service information describes
procedures for repetitive detailed
inspections of all fuel pump locations
(center, wing-inner, and wing-outer
tank), and replacing any cracked hood
halves of fuel pump canisters.
• Airbus Service Bulletin A300–28–
0092, Revision 01, dated August 29,
2014; Airbus Service Bulletin A300–28–
6110, Revision 01, dated August 29,
2014; and Airbus Service Bulletin
A310–28–2175, Revision 01, dated
August 29, 2014. This service
information describes procedures for
replacement of the hood halves of the
fuel pump canisters with newer design
hood halves for the wing-inner tank and
the center tank fuel pumps. These
documents are distinct since they apply
to different airplane models.
• Airbus Service Bulletin A300–28–
0094, Revision 00, dated January 9,
2017. This service information describes
procedures for replacement of the hood
halves of the fuel pump canisters with
newer design hood halves for the wingouter tank.
• Airbus Service Bulletin A300–28–
6106, Revision 03, dated December 16,
2016; and Airbus Service Bulletin
A310–28–2173, Revision 03, dated
December 16, 2016. This service
information describes procedures for
repetitive detailed inspections of all fuel
pump locations (center, wing-inner,
wing-outer, and trim tank), and
replacing any cracked hood halves of
fuel pump canisters. These documents
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are distinct since they apply to different
airplane models.
• Airbus Service Bulletin A300–28–
6114, Revision 00, dated January 9,
2017; and Airbus Service Bulletin
A310–28–2178, Revision 00, dated
January 9, 2017. This service
information describes procedures for
replacement of the hood halves of the
fuel pump canisters with newer design
hood halves for the wing-outer tank and
the trim tank fuel pumps. These
documents are distinct since they apply
to different airplane models.
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.
Costs of Compliance
We estimate that this AD affects 168
airplanes of U.S. registry.
The actions required by AD 2012–21–
04, and retained in this AD take about
12 work-hours per product, at an
average labor rate of $85 per workhour.
Based on these figures, the estimated
cost of the actions that are required by
AD 2012–21–04 is $1,020 per product.
We also estimate that it will take
about 9 work-hours per product to
comply with the new basic
requirements of this AD, at an average
labor rate of $85 per work-hour. Based
on these figures, we estimate the cost of
the new basic requirements of this AD
on U.S. operators to be $128,520, or
$765 per product.
In addition, we estimate that the
optional terminating actions will take
about 1 work-hour and require parts
costing $255, for a cost of $340 per
product. We have no way of
determining the number of aircraft that
might need these actions.
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
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products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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.
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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2012–21–04, Amendment 39–17220 (77
FR 64701, October 23, 2012), and
adding the following new AD:
■
2017–25–09 Airbus: Amendment 39–19123;
Docket No. FAA–2017–0714; Product
Identifier 2017–NM–042–AD.
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(a) Effective Date
This AD is effective January 18, 2018.
(b) Affected ADs
This AD replaces AD 2012–21–04,
Amendment 39–17220 (77 FR 64701, October
23, 2012) (‘‘AD 2012–21–04’’).
(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, all
certificated models, all manufacturer serial
numbers.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(2) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
(3) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes, Model A300
B4–605R and B4–622R airplanes, Model
A300 F4–605R and F4–622R airplanes, and
Model A300 C4–605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of
cracked fuel pump canister hoods located in
fuel tanks and new in-service events of wingouter tank fuel pump canister hood cracking.
We are issuing this AD to prevent any
detached canister hood fragments/debris
from being ingested into the fuel feed system,
and becoming a potential source of ignition
with consequent fire or explosion.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Inspection and
Replacement, With Revised Requirements
and Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2012–21–04, with
revised requirements and service
information. Within 30 months after
November 27, 2012 (the effective date of AD
2012–21–04), do a detailed inspection for
cracking of the fuel pump canister hood
halves installed on all center and wing-inner
tank fuel pump canisters having part
numbers (P/N) 2052C11, 2052C12, and
C93R51–601, in accordance with the
Accomplishment Instructions of the service
bulletin specified in paragraph (g)(1), (g)(2),
or (g)(3) of this AD, as applicable. If any crack
is found on any fuel pump canister hood half
during any inspection, before further flight,
replace the fuel pump canister hood half, in
accordance with the Accomplishment
Instructions of the service bulletin specified
in paragraph (g)(1), (g)(2), or (g)(3) of this AD,
as applicable.
(1) For Model A300 series airplanes:
Airbus Mandatory Service Bulletin A300–28–
0089, Revision 01, including Inspection
Findings—Reporting Sheet, dated April 15,
2011; or Airbus Service Bulletin A300–28–
0089, Revision 03, dated December 16, 2016.
As of the effective date of this AD, only use
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Airbus Service Bulletin A300–28–0089,
Revision 03, dated December 16, 2016.
(2) For Model A300–600 series airplanes:
Airbus Mandatory Service Bulletin A300–28–
6106, Revision 01, including Inspection
Findings—Reporting Sheet, dated April 15,
2011; or Airbus Service Bulletin A300–28–
6106, Revision 03, dated December 16, 2016.
As of the effective date of this AD, only use
Airbus Service Bulletin A300–28–6106,
Revision 03, dated December 16, 2016.
(3) For Model A310 series airplanes:
Airbus Mandatory Service Bulletin A310–28–
2173, Revision 01, including Inspection
Findings—Reporting Sheet, dated April 15,
2011; or Airbus Service Bulletin A310–28–
2173, Revision 03, dated December 16, 2016.
As of the effective date of this AD, only use
Airbus Service Bulletin A310–28–2173,
Revision 03, dated December 16, 2016.
(h) Retained Repetitive Inspections, With No
Changes
This paragraph restates the requirements of
paragraph (h) of AD 2012–21–04, with no
changes. Within 30 months after
accomplishing the actions specified in
paragraph (g) of this AD, and thereafter at
intervals not to exceed 30 months, repeat the
detailed inspection specified in paragraph (g)
of this AD.
(i) New Repetitive Inspections and
Replacement of the Wing-Outer Tank and
Trim Tank Fuel Pump Canister Hood Halves
Within 30 months after the effective date
of this AD, do a detailed inspection for
cracking of the wing-outer tank and trim
tank, as applicable, fuel pump canister hood
halves installed on all fuel pump canisters
having P/Ns 2052C11, 2052C12, and
C93R51–601, in accordance with the
Accomplishment Instructions of the service
bulletin specified in paragraph (i)(1), (i)(2), or
(i)(3) of this AD, as applicable. Repeat the
inspection thereafter at intervals not to
exceed 30 months. If any crack is found on
any fuel pump canister hood half during any
inspection, before further flight, replace the
fuel pump canister hood half, in accordance
with the Accomplishment Instructions of the
service bulletin specified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD, as applicable.
(1) For Model A300 series airplanes:
Airbus Service Bulletin A300–28–0089,
Revision 03, dated December 16, 2016.
(2) For Model A300–600 series airplanes:
Airbus Service Bulletin A300–28–6106,
Revision 03, dated December 16, 2016.
(3) For Model A310 series airplanes:
Airbus Service Bulletin A310–28–2173,
Revision 03, dated December 16, 2016.
(j) New Optional Terminating Actions
Replacement of the fuel pump canister
hood halves installed on all fuel pump
canisters having P/Ns 2052C11, 2052C12,
and C93R51–601, constitutes terminating
action for the inspections required by
paragraphs (g) and (h) of this AD for that
airplane. The replacement of the fuel pump
canister hood halves must be done in
accordance with the Accomplishment
Instructions of the service information
specified in paragraph (j)(1), (j)(2), or (j)(3) of
this AD, as applicable.
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(1) For Model A300 series airplanes:
Airbus Service Bulletin A300–28–0092,
Revision 01, dated August 29, 2014 (for
center and wing-inner tank fuel pump
canister hood halves); and Airbus Service
Bulletin A300–28–0094, Revision 00, dated
January 9, 2017 (for wing-outer tank fuel
pump canister hood halves).
(2) For Model A300–600 series airplanes:
Airbus Service Bulletin A300–28–6110,
Revision 01, dated August 29, 2014 (for
center and wing-inner tank fuel pump
canister hood halves); and Airbus Service
Bulletin A300–28–6114, Revision 00, dated
January 9, 2017 (for wing-outer tank and trim
tank fuel pump canister hood halves).
(3) For Model A310 series airplanes:
Airbus Service Bulletin A310–28–2175,
Revision 01, dated August 29, 2014 (for
center and wing-inner tank fuel pump
canister hood halves); and Airbus Service
Bulletin A310–28–2178, Revision 00, dated
January 9, 2017 (for wing-outer tank and trim
tank fuel pump canister hood halves).
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(k) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraph
(k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD.
(i) Airbus Service Bulletin A300–28–0089,
dated January 13, 2011; or Airbus Service
Bulletin A300–28–0089, Revision 02, dated
April 25, 2014.
(ii) Airbus Service Bulletin A300–28–6106,
dated January 13, 2011; or Airbus Service
Bulletin A300–28–6106, Revision 02, dated
April 25, 2014.
(iii) Airbus Service Bulletin A310–28–
2173, dated January 13, 2011; or Airbus
Service Bulletin A310–28–2173, Revision 02,
dated April 25, 2014.
(2) This paragraph provides credit for the
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraph
(k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD.
(i) Airbus Service Bulletin A300–28–0089,
dated January 13, 2011; Airbus Mandatory
Service Bulletin A300–28–0089, Revision 01,
dated April 15, 2011; or Airbus Service
Bulletin A300–28–0089, Revision 02, dated
April 25, 2014.
(ii) Airbus Service Bulletin A300–28–6106,
dated January 13, 2011; Airbus Mandatory
Service Bulletin A300–28–6106, Revision 01,
dated April 15, 2011; or Airbus Service
Bulletin A300–28–6106, Revision 02, dated
April 25, 2014.
(iii) Airbus Service Bulletin A310–28–
2173, dated January 13, 2011; Airbus
Mandatory Service Bulletin A310–28–2173,
Revision 01, dated April 15, 2011; or Airbus
Service Bulletin A310–28–2173, Revision 02,
dated April 25, 2014.
(3) This paragraph provides credit for the
actions specified in paragraph (j) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A300–28–6110, Revision 00, dated
November 28, 2013.
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(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (m)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2012–21–04 are not approved as AMOCs
with 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 Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0051, dated March 23, 2017, 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–2017–0714.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW,
Renton, WA 98057–3356; telephone 425–
227–2125; fax 425–227–1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(5) and (n)(6) of this AD.
(n) 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 January 18, 2018.
(i) Airbus Service Bulletin A300–28–0089,
Revision 03, dated December 16, 2016.
(ii) Airbus Service Bulletin A300–28–0092,
Revision 01, dated August 29, 2014.
(iii) Airbus Service Bulletin A300–28–
0094, Revision 00, dated January 9, 2017.
(iv) Airbus Service Bulletin A300–28–
6106, Revision 03, dated December 16, 2016.
(v) Airbus Service Bulletin A300–28–6110,
Revision 01, dated August 29, 2014.
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
(vi) Airbus Service Bulletin A300–28–
6114, Revision 00, dated January 9, 2017.
(vii) Airbus Service Bulletin A310–28–
2173, Revision 03, dated December 16, 2016.
(viii) Airbus Service Bulletin A310–28–
2175, Revision 01, dated August 29, 2014.
(ix) Airbus Service Bulletin A310–28–
2178, Revision 00, dated January 9, 2017.
(4) The following service information was
approved for IBR on November 27, 2012 (77
FR 64701, October 23, 2012).
(i) Airbus Mandatory Service Bulletin
A300–28–0089, Revision 01, including
Inspection Findings—Reporting Sheet, dated
April 15, 2011.
(ii) Airbus Mandatory Service Bulletin
A300–28–6106, Revision 01, including
Inspection Findings—Reporting Sheet, dated
April 15, 2011.
(iii) Airbus Mandatory Service Bulletin
A310–28–2173, Revision 01, including
Inspection Findings—Reporting Sheet, dated
April 15, 2011.
(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 Standards Branch,
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 4, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–26627 Filed 12–13–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1104; Product
Identifier 2017–NM–153–AD; Amendment
39–19130; AD 2017–25–16]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–200, A330–200
SUMMARY:
E:\FR\FM\14DER1.SGM
14DER1
]]>Agencies
[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)]
[Rules and Regulations]
[Pages 58715-58718]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26627]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0714; Product Identifier 2017-NM-042-AD; Amendment
39-19123; AD 2017-25-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2012-21-04,
which applied to all Airbus Model A300 series airplanes; Model A310
series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes).
AD 2012-21-04 required repetitive inspections for, and replacement
of, any cracked hood halves of fuel pump canisters. Since we issued AD
2012-21-04, we allowed inspections of the wing-outer tank and trim tank
fuel pump canister hood halves to be terminated.
This new AD retains the requirements of AD 2012-21-04, reinstates
the terminated inspections, and adds optional terminating actions. This
AD was prompted by reports of cracked fuel pump canister hoods located
in fuel tanks and new in-service events of wing-outer tank fuel pump
canister hood cracking. We are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 18, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 18,
2018.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 27, 2012 (77 FR 64701, October 23, 2012).
ADDRESSES: 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: [email protected];
internet: https://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 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-2017-0714.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0714; 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 address for the Docket Office (telephone: 800-
647-5527) is 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 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, 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 2012-21-04, Amendment 39-17220 (77 FR 64701,
October 23, 2012) (``AD 2012-21-04''). AD 2012-21-04 applied to all
Airbus Model A300 series airplanes; Model A310 series airplanes; and
Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model
A300 C4-605R Variant F airplanes (collectively called Model A300-600
series airplanes).
The NPRM published in the Federal Register on August 2, 2017 (82 FR
35911). The NPRM was prompted by reports of cracked fuel pump canister
hoods located in fuel tanks and new in-service events of wing-outer
tank fuel pump canister hood cracking. The NPRM proposed to retain the
requirements of AD 2012-21-04, reinstate terminated inspections, and
add optional terminating actions. We
[[Page 58716]]
are issuing this AD to prevent any detached canister hood fragments/
debris from being ingested into the fuel feed system, and becoming a
potential source of ignition with consequent fire or explosion.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0051, dated March 23, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Airbus Model A300 series airplanes;
Model A310 series airplanes; and Model A300-600 series airplanes. The
MCAI states:
Reports were received of finding cracked fuel pump canister
hoods located in fuel tanks on in-service aeroplanes. Initial
analyses, laboratory testing and examinations suggested that
vibration-induced fatigue could have caused these cracks. However,
initial data could not exclude some other potential contributing
factors.
This condition, if not detected and corrected, could lead to
detached canister hood fragments or debris being ingested into the
fuel feed system. In addition, metallic debris inside the fuel tank
could result in a potential source of fuel vapour ignition, possibly
resulting in a fire or fuel tank explosion and consequent loss of
the aeroplane.
To address this potential unsafe condition, EASA issued AD 2011-
0124 (later revised) [FAA AD 2012-21-04 corresponds to EASA AD 2011-
0124] to require repetitive inspections of the canister hood halves
installed on all fuel pump canisters and, if any damage was found,
replacement. EASA AD 2011-0124R1 introduced an optional terminating
action for the wing inner and centre fuel tanks, and cancelled the
repetitive inspections of the fuel pump canister hoods in outer wing
and trim tanks, for which no cracks had been reported following the
initial inspection.
Since that [EASA] AD was issued, new in service events of outer
tank fuel pump canister hood cracking have been reported.
Consequently, the canister hoods of the outer tank fuel pumps and
trim tank fuel pumps will need to be inspected.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0124R1, which is superseded, retaining
the repetitive inspections of fuel pump canister hoods in wing inner
and centre tanks, and reintroduces repetitive detailed inspections
(DET) for outer tank and trim tank fuel pump canister hoods. This
[EASA] AD also retains the existing optional terminating action for
the repetitive DET of wing inner and centre tank fuel pump canister
hoods, and introduces a new optional terminating action for the
repetitive DET of the outer and trim tank fuel pump canister hoods
required by this [EASA] AD.
You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0714.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. The commenter, John
Sanderson, supported the NPRM.
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 for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A300-28-0089, Revision 03, dated
December 16, 2016. This service information describes procedures for
repetitive detailed inspections of all fuel pump locations (center,
wing-inner, and wing-outer tank), and replacing any cracked hood halves
of fuel pump canisters.
Airbus Service Bulletin A300-28-0092, Revision 01, dated
August 29, 2014; Airbus Service Bulletin A300-28-6110, Revision 01,
dated August 29, 2014; and Airbus Service Bulletin A310-28-2175,
Revision 01, dated August 29, 2014. This service information describes
procedures for replacement of the hood halves of the fuel pump
canisters with newer design hood halves for the wing-inner tank and the
center tank fuel pumps. These documents are distinct since they apply
to different airplane models.
Airbus Service Bulletin A300-28-0094, Revision 00, dated
January 9, 2017. This service information describes procedures for
replacement of the hood halves of the fuel pump canisters with newer
design hood halves for the wing-outer tank.
Airbus Service Bulletin A300-28-6106, Revision 03, dated
December 16, 2016; and Airbus Service Bulletin A310-28-2173, Revision
03, dated December 16, 2016. This service information describes
procedures for repetitive detailed inspections of all fuel pump
locations (center, wing-inner, wing-outer, and trim tank), and
replacing any cracked hood halves of fuel pump canisters. These
documents are distinct since they apply to different airplane models.
Airbus Service Bulletin A300-28-6114, Revision 00, dated
January 9, 2017; and Airbus Service Bulletin A310-28-2178, Revision 00,
dated January 9, 2017. This service information describes procedures
for replacement of the hood halves of the fuel pump canisters with
newer design hood halves for the wing-outer tank and the trim tank fuel
pumps. These documents are distinct since they apply to different
airplane models.
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.
Costs of Compliance
We estimate that this AD affects 168 airplanes of U.S. registry.
The actions required by AD 2012-21-04, and retained in this AD take
about 12 work-hours per product, at an average labor rate of $85 per
workhour. Based on these figures, the estimated cost of the actions
that are required by AD 2012-21-04 is $1,020 per product.
We also estimate that it will take about 9 work-hours per product
to comply with the new basic requirements of this AD, at an average
labor rate of $85 per work-hour. Based on these figures, we estimate
the cost of the new basic requirements of this AD on U.S. operators to
be $128,520, or $765 per product.
In addition, we estimate that the optional terminating actions will
take about 1 work-hour and require parts costing $255, for a cost of
$340 per product. We have no way of determining the number of aircraft
that might need these actions.
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
[[Page 58717]]
products identified in this rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
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.
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)
2012-21-04, Amendment 39-17220 (77 FR 64701, October 23, 2012), and
adding the following new AD:
2017-25-09 Airbus: Amendment 39-19123; Docket No. FAA-2017-0714;
Product Identifier 2017-NM-042-AD.
(a) Effective Date
This AD is effective January 18, 2018.
(b) Affected ADs
This AD replaces AD 2012-21-04, Amendment 39-17220 (77 FR 64701,
October 23, 2012) (``AD 2012-21-04'').
(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,
all certificated models, all manufacturer serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(3) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Reason
This AD was prompted by reports of cracked fuel pump canister
hoods located in fuel tanks and new in-service events of wing-outer
tank fuel pump canister hood cracking. We are issuing this AD to
prevent any detached canister hood fragments/debris from being
ingested into the fuel feed system, and becoming a potential source
of ignition with consequent fire or explosion.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Inspection and Replacement, With Revised
Requirements and Service Information
This paragraph restates the requirements of paragraph (g) of AD
2012-21-04, with revised requirements and service information.
Within 30 months after November 27, 2012 (the effective date of AD
2012-21-04), do a detailed inspection for cracking of the fuel pump
canister hood halves installed on all center and wing-inner tank
fuel pump canisters having part numbers (P/N) 2052C11, 2052C12, and
C93R51-601, in accordance with the Accomplishment Instructions of
the service bulletin specified in paragraph (g)(1), (g)(2), or
(g)(3) of this AD, as applicable. If any crack is found on any fuel
pump canister hood half during any inspection, before further
flight, replace the fuel pump canister hood half, in accordance with
the Accomplishment Instructions of the service bulletin specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable.
(1) For Model A300 series airplanes: Airbus Mandatory Service
Bulletin A300-28-0089, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin
A300-28-0089, Revision 03, dated December 16, 2016. As of the
effective date of this AD, only use Airbus Service Bulletin A300-28-
0089, Revision 03, dated December 16, 2016.
(2) For Model A300-600 series airplanes: Airbus Mandatory
Service Bulletin A300-28-6106, Revision 01, including Inspection
Findings--Reporting Sheet, dated April 15, 2011; or Airbus Service
Bulletin A300-28-6106, Revision 03, dated December 16, 2016. As of
the effective date of this AD, only use Airbus Service Bulletin
A300-28-6106, Revision 03, dated December 16, 2016.
(3) For Model A310 series airplanes: Airbus Mandatory Service
Bulletin A310-28-2173, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin
A310-28-2173, Revision 03, dated December 16, 2016. As of the
effective date of this AD, only use Airbus Service Bulletin A310-28-
2173, Revision 03, dated December 16, 2016.
(h) Retained Repetitive Inspections, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2012-21-04, with no changes. Within 30 months after accomplishing
the actions specified in paragraph (g) of this AD, and thereafter at
intervals not to exceed 30 months, repeat the detailed inspection
specified in paragraph (g) of this AD.
(i) New Repetitive Inspections and Replacement of the Wing-Outer Tank
and Trim Tank Fuel Pump Canister Hood Halves
Within 30 months after the effective date of this AD, do a
detailed inspection for cracking of the wing-outer tank and trim
tank, as applicable, fuel pump canister hood halves installed on all
fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51-601, in
accordance with the Accomplishment Instructions of the service
bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of this
AD, as applicable. Repeat the inspection thereafter at intervals not
to exceed 30 months. If any crack is found on any fuel pump canister
hood half during any inspection, before further flight, replace the
fuel pump canister hood half, in accordance with the Accomplishment
Instructions of the service bulletin specified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD, as applicable.
(1) For Model A300 series airplanes: Airbus Service Bulletin
A300-28-0089, Revision 03, dated December 16, 2016.
(2) For Model A300-600 series airplanes: Airbus Service Bulletin
A300-28-6106, Revision 03, dated December 16, 2016.
(3) For Model A310 series airplanes: Airbus Service Bulletin
A310-28-2173, Revision 03, dated December 16, 2016.
(j) New Optional Terminating Actions
Replacement of the fuel pump canister hood halves installed on
all fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51-
601, constitutes terminating action for the inspections required by
paragraphs (g) and (h) of this AD for that airplane. The replacement
of the fuel pump canister hood halves must be done in accordance
with the Accomplishment Instructions of the service information
specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as
applicable.
[[Page 58718]]
(1) For Model A300 series airplanes: Airbus Service Bulletin
A300-28-0092, Revision 01, dated August 29, 2014 (for center and
wing-inner tank fuel pump canister hood halves); and Airbus Service
Bulletin A300-28-0094, Revision 00, dated January 9, 2017 (for wing-
outer tank fuel pump canister hood halves).
(2) For Model A300-600 series airplanes: Airbus Service Bulletin
A300-28-6110, Revision 01, dated August 29, 2014 (for center and
wing-inner tank fuel pump canister hood halves); and Airbus Service
Bulletin A300-28-6114, Revision 00, dated January 9, 2017 (for wing-
outer tank and trim tank fuel pump canister hood halves).
(3) For Model A310 series airplanes: Airbus Service Bulletin
A310-28-2175, Revision 01, dated August 29, 2014 (for center and
wing-inner tank fuel pump canister hood halves); and Airbus Service
Bulletin A310-28-2178, Revision 00, dated January 9, 2017 (for wing-
outer tank and trim tank fuel pump canister hood halves).
(k) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the applicable service information
specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this
AD.
(i) Airbus Service Bulletin A300-28-0089, dated January 13,
2011; or Airbus Service Bulletin A300-28-0089, Revision 02, dated
April 25, 2014.
(ii) Airbus Service Bulletin A300-28-6106, dated January 13,
2011; or Airbus Service Bulletin A300-28-6106, Revision 02, dated
April 25, 2014.
(iii) Airbus Service Bulletin A310-28-2173, dated January 13,
2011; or Airbus Service Bulletin A310-28-2173, Revision 02, dated
April 25, 2014.
(2) This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using the applicable service information
specified in paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this
AD.
(i) Airbus Service Bulletin A300-28-0089, dated January 13,
2011; Airbus Mandatory Service Bulletin A300-28-0089, Revision 01,
dated April 15, 2011; or Airbus Service Bulletin A300-28-0089,
Revision 02, dated April 25, 2014.
(ii) Airbus Service Bulletin A300-28-6106, dated January 13,
2011; Airbus Mandatory Service Bulletin A300-28-6106, Revision 01,
dated April 15, 2011; or Airbus Service Bulletin A300-28-6106,
Revision 02, dated April 25, 2014.
(iii) Airbus Service Bulletin A310-28-2173, dated January 13,
2011; Airbus Mandatory Service Bulletin A310-28-2173, Revision 01,
dated April 15, 2011; or Airbus Service Bulletin A310-28-2173,
Revision 02, dated April 25, 2014.
(3) This paragraph provides credit for the actions specified in
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A300-28-
6110, Revision 00, dated November 28, 2013.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (m)(2) of this AD. Information
may be emailed to: [email protected].
(i) 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.
(ii) AMOCs approved previously for AD 2012-21-04 are not
approved as AMOCs with 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 Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0051, dated March 23, 2017, 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-2017-0714.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone
425-227-2125; fax 425-227-1149.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(5) and (n)(6) of this AD.
(n) 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
January 18, 2018.
(i) Airbus Service Bulletin A300-28-0089, Revision 03, dated
December 16, 2016.
(ii) Airbus Service Bulletin A300-28-0092, Revision 01, dated
August 29, 2014.
(iii) Airbus Service Bulletin A300-28-0094, Revision 00, dated
January 9, 2017.
(iv) Airbus Service Bulletin A300-28-6106, Revision 03, dated
December 16, 2016.
(v) Airbus Service Bulletin A300-28-6110, Revision 01, dated
August 29, 2014.
(vi) Airbus Service Bulletin A300-28-6114, Revision 00, dated
January 9, 2017.
(vii) Airbus Service Bulletin A310-28-2173, Revision 03, dated
December 16, 2016.
(viii) Airbus Service Bulletin A310-28-2175, Revision 01, dated
August 29, 2014.
(ix) Airbus Service Bulletin A310-28-2178, Revision 00, dated
January 9, 2017.
(4) The following service information was approved for IBR on
November 27, 2012 (77 FR 64701, October 23, 2012).
(i) Airbus Mandatory Service Bulletin A300-28-0089, Revision 01,
including Inspection Findings--Reporting Sheet, dated April 15,
2011.
(ii) Airbus Mandatory Service Bulletin A300-28-6106, Revision
01, including Inspection Findings--Reporting Sheet, dated April 15,
2011.
(iii) Airbus Mandatory Service Bulletin A310-28-2173, Revision
01, including Inspection Findings--Reporting Sheet, dated April 15,
2011.
(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: [email protected];
internet: https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Standards Branch, 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 4, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-26627 Filed 12-13-17; 8:45 am]
BILLING CODE 4910-13-P
