Airworthiness Directives; Airbus Airplanes, 22362-22367 [2018-10214]
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–09–12 The Boeing Company:
Amendment 39–19269; Docket No.
FAA–2018–0362; Product Identifier
2018–NM–020–AD.
(a) Effective Date
This AD is effective May 30, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 747–200B, 747–300, and 747–400
series airplanes, certificated in any category,
as identified in Boeing Special Attention
Service Bulletin 747–35–2134, dated
November 22, 2017.
(d) Subject
Air Transport Association (ATA) of
America Code 35, Oxygen.
(e) Unsafe Condition
This AD was prompted by reports of lowpressure flex-hoses of the flightcrew oxygen
system that burned through due to
inadvertent electrical current from a short
circuit. We are issuing this AD to prevent
electrical current from passing through the
low-pressure oxygen flex-hoses in the
gaseous passenger oxygen system, which can
cause the flex-hoses to melt or burn, and a
consequent oxygen-fed fire in the passenger
cabin.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions
Except as required by paragraph (h) of this
AD: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 747–35–
2134, dated November 22, 2017, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–35–2134, dated
November 22, 2017.
(h) Exception to Service Information
Specifications
(1) For purposes of determining
compliance with the requirements of this AD:
Where Boeing Special Attention Service
Bulletin 747–35–2134, dated November 22,
2017, uses the phrase ‘‘the original issue date
of this service bulletin,’’ this AD requires
using ‘‘the effective date of this AD.’’
(2) Where Boeing Special Attention Service
Bulletin 747–35–2134, dated November 22,
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2017, specifies contacting Boeing, and
specifies that action as RC: This AD requires
repair using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(3) Where the Condition column of Table
3 in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 747–35–
2134, dated November 22, 2017, specifies
‘‘all airplanes,’’ for this AD, the Condition
column of Table 3 is ‘‘airplanes on which one
or more hose assemblies were replaced or
disconnected.’’
(i) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, the hose
assembly part numbers identified as
‘‘Removed hose assembly part numbers’’ in
Table 3, ‘‘Hose Assembly Replacement,’’ of
Boeing Special Attention Service Bulletin
747–35–2134, dated November 22, 2017, in
the locations for hose assembly installation
as identified in Figures 1 through 14 of
Boeing Special Attention Service Bulletin
747–35–2134, dated November 22, 2017.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO 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 manager of the
certification office, send it to the attention of
the person identified in paragraph (k) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h)(2)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
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or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
For more information about this AD,
contact Susan L. Monroe, Aerospace
Engineer, Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3570; email:
susan.l.monroe@faa.gov.
(l) 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 the AD specifies otherwise.
(i) Boeing Special Attention Service
Bulletin 747–35–2134, dated November 22,
2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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.
Issued in Des Moines, Washington, on
April 27, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–09865 Filed 5–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0071; Product
Identifier 2017–NM–063–AD; Amendment
39–19280; AD 2018–10–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
ACTION:
Final rule.
We are superseding
Airworthiness Directive (AD) 2016–23–
01, which applied to all Airbus Model
A310 series airplanes. AD 2016–23–01
required repetitive detailed inspections
for cracking around the fastener holes in
certain areas of the wing top skin
panels, supplemental repetitive
ultrasonic inspections for cracking
around the fastener holes in certain
other areas of the wing top skin panels,
and repair if necessary. This AD adds an
inspection and modification of the
fastener holes of the wing top skin
panels at a certain area. This AD also
includes terminating action for certain
inspections. This AD was prompted by
an evaluation by the design approval
holder (DAH) which indicates that the
wing top skin panel fastener holes at a
certain area are also subject to
widespread fatigue damage (WFD). We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective June 19,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 19, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of December 15, 2016 (81 FR
78899, November 10, 2016).
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: account.airwortheas@airbus.com; internet: https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0071.
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SUMMARY:
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–2018–
0071; 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)
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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, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax: 206–231–3225.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–23–01,
Amendment 39–18708 (81 FR 78899,
November 10, 2016) (‘‘AD 2016–23–
01’’). AD 2016–23–01 applied to all
Airbus Model A310 series airplanes.
The NPRM published in the Federal
Register on February 8, 2018 (83 FR
5579). The NPRM was prompted by an
evaluation done by the DAH which
indicates that the wing top skin panel
fastener holes at a certain area are
subject to WFD. The NPRM would
continue to require repetitive detailed
inspections for cracking around the
fastener holes in certain areas of the
wing top skin panels, supplemental
repetitive ultrasonic inspections for
cracking around the fastener holes in
certain other areas of the wing top skin
panels, and repair if necessary. The
NPRM proposed to add an inspection
and modification of the fastener holes of
the wing top skin panels at a certain
area. The NPRM also includes
terminating action for certain
inspections. We are issuing this AD to
detect and correct fatigue cracking
around the fastener holes, which could
result in reduced structural integrity of
the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0081,
dated May 8, 2017 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A310 series
airplanes. The MCAI states:
Following scheduled maintenance, cracks
were found around the wing top skin panels
fastener holes at Rib 2, between Stringer
(STG) 2 and STG14.
This condition, if not detected and
corrected, could reduce the structural
integrity of the aeroplane.
To address this issue, Airbus developed an
inspection programme, and published
Service Bulletin (SB) A310–57–2096,
providing instructions for repetitive detailed
inspections (DET) to ensure that any visible
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cracks in the wing top skin panels 1 and 2
along Rib 2 are detected on time and repaired
appropriately. Consequently, EASA issued
AD 2008–0211 [which corresponds to FAA
AD 2010–04–03, Amendment 39–16196 (75
FR 6852, February 12, 2010) (‘‘AD 2010–04–
03)] to require implementation of that
inspection programme.
After that [EASA] AD was issued, Airbus
improved the inspection programme, revising
SB A310–57–2096 accordingly, to include a
special detailed inspection (SDI), using an
ultrasonic method, to allow earlier crack
detection, to subsequently reduce the scope
of potential repair action, and to extend the
intervals of the repetitive inspections.
Consequently, EASA issued AD 2014–0200
(later revised), retaining the requirements of
EASA AD 2008–0211, which was
superseded, and required supplementary
repetitive SDI [for cracking] of the wing top
skin panel 1 and 2 between STG2 and STG10
at Rib 2 [and repair if needed], as described
in Airbus SB A310–57–2096 Revision 02.
Since EASA AD 2014–0200R1 was issued,
a Widespread Fatigue Damage (WFD)
analysis concluded that the inspection
programme had to be extended to include the
wing top skin panels at Rib 3 attachments,
and Airbus issued SB A310–57–2096
Revision 03 accordingly, to provide the
necessary instructions. Consequently, EASA
issued [EASA] AD 2016–0005 [which
corresponds to FAA AD 2016–23–01],
retaining the requirements of EASA AD
2014–0200R1, which was superseded, and
extending the inspection area to include
Rib 3.
In addition to changes to the inspected
area, WFD analysis identified structural
modification points for certain fastener holes,
located at each attachment from STG2 to
STG10, at Ribs 2 and 3 on both wings.
Airbus developed modification (mod)
13785 and mod 13786, consisting of an SDI,
followed by an oversize of the defined holes
on Ribs 2 and 3 on both wings. Airbus issued
SB A310–57–2106 and SB A310–57–2107 to
provide in-service modification instructions
for top skin attachments to Rib 2 and Rib 3
respectively. Accomplishment of these
modifications at the specified time will reset
the fatigue life of the attachment holes at the
top skin attachment to Rib 2 and Rib 3 to the
Limit of Validity (LOV). Airbus issued
inspection SB A310–57–2096 Revision 04 to
account for the inspection requirements postmodification.
For the reasons describe above, this
[EASA] AD retains the requirements of EASA
AD 2016–0005, which is superseded,
requires modifications to the top skin
attachment holes at Rib 2 and Rib 3, and
defines the inspection requirements for Rib 2
and Rib 3 after modification.
Modification of the fastener holes at
top skin ribs 2 and 3 constitutes
terminating action for certain repetitive
special detailed inspections. 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–2018–
0071.
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
FedEx 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.
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Related Service Information Under
1 CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A310–57–
2096, Revision 04, dated December 5,
2016. This service information describes
procedures for detailed and ultrasonic
inspections for cracking around the
fastener holes of wing top skin panels 1
and 2, at ribs 2 and 3, on the left- and
right-hand sides of the fuselage.
• Airbus Service Bulletin A310–57–
2106, dated November 14, 2016. This
service information describes
procedures for a special detailed
inspection and modification of the
fastener holes of wing top skin panels 1
and 2, at rib 2.
• Airbus Service Bulletin A310–57–
2107, dated November 14, 2016. This
service information describes
procedures for a special detailed
inspection and modification of the
fastener holes of wing top skin panels 1
and 2, at rib 3.
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 8
airplanes of U.S. registry.
The actions required by AD 2016–23–
01, and retained in this AD, take about
8 work-hours per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that are required by AD
2016–23–01 on U.S. operators to be
$5,440, or $680 per product.
We also estimate that it takes about 95
work-hours per product to comply with
the basic requirements of this AD.
Required parts will cost about $10,200
per product. The average labor rate is
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$85 per work-hour. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $146,200, or
$18,275 per product.
In addition, we estimate that any
necessary modification will take about
40 work-hours and require parts costing
$10,000, for a cost of $13,400 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
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
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2016–23–01, Amendment 39–18708 (81
FR 78899, November 10, 2016), and
adding the following new AD:
■
2018–10–05 Airbus: Amendment 39–19280;
FAA–2018–0071; Product Identifier
2017–NM–063–AD.
(a) Effective Date
This AD is effective June 19, 2018.
(b) Affected ADs
This AD replaces AD 2016–23–01,
Amendment 39–18708 (81 FR 78899,
November 10, 2016) (‘‘AD 2016–23–01’’).
(c) Applicability
This AD applies to all Airbus Model A310–
203, –204, –221, –222, –304, –322, –324, and
–325 airplanes, certificated in any category,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the wing top skin panel fastener holes
at ribs 2 and 3 are subject to widespread
fatigue damage (WFD). We are issuing this
AD to detect and correct fatigue cracking
around the fastener holes, which could result
in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Inspections, With
Revised Service Information
This paragraph restates the requirements of
paragraph (g) of AD 2016–23–01, with
revised service information. Except as
required by paragraph (i) of this AD: Within
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the initial compliance time and thereafter at
the repetitive intervals specified in
paragraphs (h)(1) through (h)(3) of this AD,
as applicable, accomplish the actions
specified in paragraphs (g)(1) and (g)(2) of
this AD concurrently and in sequence, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310–
57–2096, Revision 03, dated June 30, 2015,
or Revision 04, dated December 5, 2016;
except as provided by paragraph (j) of this
AD. As of the effective date of this AD, use
only Airbus Service Bulletin A310–57–2096,
Revision 04, dated December 5, 2016, to
accomplish the required actions.
(1) Accomplish a detailed inspection for
cracking around the fastener holes in the
wing top skin panels 1 and 2, along ribs 2
and 3, between the front and rear spars on
the left- and right-hand sides of the fuselage.
(2) Accomplish an ultrasonic inspection for
cracking around the fastener holes in the
wing top skin panels 1 and 2, along ribs 2
and 3, between stringer (STG) 2 and STG10
on the left- and right-hand sides of the
fuselage.
(h) Retained Compliance Times for
Airplanes Not Previously Inspected, With No
Changes
This paragraph restates the requirements of
paragraph (h) of AD 2016–23–01, with no
changes.
(1) For Model A310–203, –204, –221, and
–222 airplanes: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD at the
later of the times specified in paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD. Repeat the
inspections specified in paragraphs (g)(1) and
(g)(2) of this AD thereafter at intervals not to
exceed 2,000 flight cycles or 4,100 flight
hours, whichever occurs first.
(i) Prior to the accumulation of 18,700
flight cycles or 37,400 flight hours since first
flight of the airplane, whichever occurs first.
(ii) Within 30 days after December 15, 2016
(the effective date of AD 2016–23–01).
(2) For Model A310–304, –322, –324, and
–325 airplanes having an average flight time
(AFT) of less than 4 hours: Do the actions
required by paragraphs (g)(1) and (g)(2) of
this AD at the later of the times specified in
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
Repeat the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD
thereafter at intervals not to exceed 2,000
flight cycles or 5,600 flight hours, whichever
occurs first.
(i) Prior to the accumulation of 17,300
flight cycles or 48,400 flight hours since first
flight of the airplane, whichever occurs first.
(ii) Within 30 days after December 15, 2016
(the effective date of AD 2016–23–01).
(3) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of equal to or
more than 4 hours: Do the actions required
by paragraphs (g)(1) and (g)(2) of this AD at
the later of the times specified in paragraphs
(h)(3)(i) and (h)(3)(ii) of this AD. Repeat the
inspections specified in paragraphs (g)(1) and
(g)(2) of this AD thereafter at intervals not to
exceed 1,500 flight cycles or 7,500 flight
hours, whichever occurs first.
(i) Prior to the accumulation of 12,800
flight cycles or 64,300 flight hours since first
flight of the airplane, whichever occurs first.
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(ii) Within 30 days after December 15, 2016
(the effective date of AD 2016–23–01).
(i) Retained Compliance Times for Airplanes
Previously Inspected, With Revised Service
Information
This paragraph restates the requirements of
paragraph (i) of AD 2016–23–01, with revised
service information. For airplanes previously
inspected before December 15, 2016 (the
effective date of AD 2016–23–01), using
Airbus Service Bulletin A310–57–2096,
dated May 6, 2008; Airbus Service Bulletin
A310–57–2096, Revision 01, dated August 5,
2010; or Airbus Service Bulletin A310–57–
2096, Revision 02, dated March 5, 2014: At
the applicable compliance times specified in
paragraphs (i)(1), (i)(2), and (i)(3) of this AD,
accomplish the actions specified in
paragraphs (g)(1) and (g)(2) of this AD
concurrently and in sequence, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–57–2096,
Revision 03, dated June 30, 2015, or Revision
04, dated December 5, 2016. As of the
effective date of this AD, use only Airbus
Service Bulletin A310–57–2096, Revision 04,
dated December 5, 2016, to accomplish the
required actions. Repeat the inspections
specified in paragraphs (g)(1) and (g)(2) of
this AD thereafter at the repetitive intervals
specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD, as applicable.
(1) For Model A310–203, –204, –221, and
–222 airplanes: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD within
3,500 flight hours or 1,700 flight cycles,
whichever occurs first since the most recent
inspection.
(2) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of less than 4
hours: Do the actions required by paragraphs
(g)(1) and (g)(2) of this AD within 4,600 flight
hours or 1,600 flight cycles, whichever
occurs first since the most recent inspection.
(3) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of equal to or
more than 4 hours: Do the actions required
by paragraphs (g)(1) and (g)(2) of this AD
within 6,100 flight hours or 1,200 flight
cycles, whichever occurs first since the most
recent inspection.
(j) Retained Compliance Times if No
Ultrasonic Equipment Is Available, With
Revised Service Information
This paragraph restates the requirements of
paragraph (j) of AD 2016–23–01, with revised
service information. If no ultrasonic
equipment is available for the initial or
second inspection required by paragraph (g)
or (h) of this AD, accomplish the detailed
inspection specified in paragraph (g)(1) of
this AD within the applicable compliance
times specified in paragraphs (j)(1) and (j)(2)
of this AD. After accomplishing the detailed
inspection, do the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD at the
applicable compliance times specified by
paragraphs (i)(1), (i)(2), and (i)(3) of this AD.
Subsequently, repeat the inspections
specified in paragraphs (g)(1) and (g)(2) of
this AD thereafter at the applicable repetitive
intervals specified in paragraphs (h)(1),
(h)(2), and (h)(3) of this AD.
(1) For airplanes not previously inspected
before December 15, 2016 (the effective date
PO 00000
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Fmt 4700
Sfmt 4700
22365
of AD 2016–23–01), using the service
information identified in paragraph (j)(2)(i),
(j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) of this AD: Do
the actions required by paragraph (g)(1) of
this AD within the initial compliance time
specified by paragraphs (h)(1), (h)(2), and
(h)(3) of this AD, as applicable.
(2) For airplanes previously inspected
before December 15, 2016 (the effective date
of AD 2016–23–01), using the service
information identified in paragraph (j)(2)(i),
(j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) of this AD: Do
the actions required by paragraph (g)(1) of
this AD within the applicable compliance
times specified in paragraphs (i)(1), (i)(2),
and (i)(3) of this AD.
(i) Airbus Service Bulletin A310–57–2096,
dated May 6, 2008.
(ii) Airbus Service Bulletin A310–57–2096,
Revision 01, dated August 5, 2010.
(iii) Airbus Service Bulletin A310–57–
2096, Revision 02, dated March 5, 2014.
(iv) Airbus Service Bulletin A310–57–
2096, Revision 03, dated June 30, 2015.
(k) Retained Repair of Cracking, With No
Changes
This paragraph restates the requirements of
paragraph (k) of AD 2016–23–01, with no
changes. If any cracking is found during any
inspection required by paragraph (g), (h), (i),
or (j) of this AD, before further flight, repair
the cracking 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.
Accomplishing the repair specified in this
paragraph terminates the repetitive
inspections required by paragraph (g), (h), (i),
or (j) of this AD, as applicable, for the
repaired area only.
(l) Retained Definition of AFT, With No
Changes
This paragraph restates the requirements of
paragraph (l) of AD 2016–23–01, with no
changes. For the purposes of this AD, the
AFT should be established as specified in
paragraphs (l)(1), (l)(2), and (l)(3) of this AD
for the determination of the compliance
times.
(1) The inspection threshold is defined as
the total flight hours accumulated (counted
from take-off to touch-down), divided by the
total number of flight cycles accumulated at
the effective date of this AD.
(2) The initial inspection interval is
defined as the total flight hours accumulated
divided by the total number of flight cycles
accumulated at the time of the initial
inspection threshold.
(3) The second inspection interval is
defined as the total flight hours accumulated
divided by the total number of flight cycles
accumulated between the initial and second
inspection threshold. For all inspection
intervals onwards, the average flight time is
the flight hours divided by the flight cycles
accumulated between the last two
inspections.
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
(m) New Requirements of This AD: Rib 2
Inspection and Modification
At the compliance time specified in
paragraph (n) of this AD, as applicable,
accomplish the actions specified in
paragraphs (m)(1) and (m)(2) of this AD
concurrently and in sequence, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–57–2106,
dated November 14, 2016.
(1) Accomplish a special detailed
inspection to determine the diameter of the
fastener holes in the wing top skin panels 1
and 2, at rib 2 of both wings.
(2) Modify the fastener holes.
(n) New Compliance Times for Rib 2
Inspection and Modification
(1) For Model A310–203, –204, –221, and
–222 airplanes: Do the actions required by
paragraphs (m)(1) and (m)(2) of this AD at the
later of the times specified in paragraphs
(n)(1)(i) and (n)(1)(ii) of this AD.
(i) Prior to the accumulation of 40,000
flight cycles or 93,300 flight hours since first
flight of the airplane, whichever occurs first.
(ii) Within 30 days after the effective date
of this AD.
(2) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of less than 4
hours: Do the actions required by paragraphs
(m)(1) and (m)(2) of this AD at the later of
the times specified in paragraphs (n)(2)(i) and
(n)(2)(ii) of this AD.
(i) Prior to the accumulation of 40,000
flight cycles or 116,000 flight hours since
first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date
of this AD.
(3) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of 4 hours or
more: Do the actions required by paragraphs
(m)(1) and (m)(2) of this AD at the later of
the times specified in paragraphs (n)(3)(i) and
(n)(3)(ii) of this AD.
(i) Prior to the accumulation of 30,000
flight cycles or 150,000 flight hours since
first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date
of this AD.
daltland on DSKBBV9HB2PROD with RULES
(o) New Requirements of This AD: Rib 3
Inspection and Modification
At the compliance time specified in
paragraph (p) of this AD, as applicable,
accomplish the actions specified in
paragraphs (o)(1) and (o)(2) of this AD
concurrently and in sequence, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–57–2107,
dated November 14, 2016.
(1) Accomplish a special detailed
inspection to determine the diameter of the
fastener holes in the wing top skin panels 1
and 2, at rib 3 of both wings.
(2) Modify the fastener holes.
(p) New Compliance Times for Rib 3
Inspection and Modification
(1) For Model A310–203, –204, –221, and
–222 airplanes: Do the actions required by
paragraphs (o)(1) and (o)(2) of this AD at the
later of the times specified in paragraphs
(p)(1)(i) and (p)(1)(ii) of this AD.
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16:07 May 14, 2018
Jkt 244001
(i) Prior to the accumulation of 46,400
flight cycles or 92,900 flight hours since first
flight of the airplane, whichever occurs first.
(ii) Within 30 days after the effective date
of this AD.
(2) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of less than 4
hours: Do the actions required by paragraphs
(o)(1) and (o)(2) of this AD at the later of the
times specified in paragraphs (p)(2)(i) and
(p)(2)(ii) of this AD.
(i) Prior to the accumulation of 45,400
flight cycles or 127,300 flight hours since
first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date
of this AD.
(3) For Model A310–304, –322, –324, and
–325 airplanes having an AFT of 4 hours or
more: Do the actions required by paragraphs
(o)(1) and (o)(2) of this AD at the later of the
times specified in paragraphs (p)(3)(i) and
(p)(3)(ii) of this AD.
(i) Prior to the accumulation of 33,800
flight cycles or 169,000 flight hours since
first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date
of this AD.
(q) New Corrective Actions
If any cracking is found during any
inspection required by paragraph (m), (n), (o),
or (p) of this AD, before further flight, repair
the cracking using a method approved by the
Manager, International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature. Accomplishing the
repair specified in this paragraph terminates
the repetitive inspections required by
paragraph (g), (h), (i), or (j) of this AD, as
applicable, for the repaired area only.
(r) New Terminating Actions
(1) Accomplishment of the modification
specified in paragraph (m) of this AD
constitutes terminating action for the
repetitive special detailed inspections
required by paragraph (g)(2) of this AD for
the modified fastener holes at top skin rib 2
for that airplane. After modification, the unmodified fastener holes at top skin rib 2
between the front and rear spars remain
subject to the repetitive inspections required
by paragraph (g)(1) of this AD.
(2) Accomplishment of the modification
specified in paragraph (o) of this AD
constitutes terminating action for the
repetitive special detailed inspections
required by paragraph (g)(2) of this AD for
the modified fastener holes at top skin rib 3
for that airplane. After modification, the unmodified fastener holes at top skin rib 3
between the front and rear spars remain
subject to the repetitive inspection required
by paragraph (g)(1) of this AD.
(s) Other FAA AD Provisions
(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
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
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 (t)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(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 EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(t) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0081, dated May 8, 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–2018–0071.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax: 206–
231–3225.
(u) 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 June 19, 2018.
(i) Airbus Service Bulletin A310–57–2096,
Revision 04, dated December 5, 2016.
(ii) Airbus Service Bulletin A310–57–2106,
dated November 14, 2016.
(iii) Airbus Service Bulletin A310–57–
2107, dated November 14, 2016.
(4) The following service information was
approved for IBR on December 15, 2016 (81
FR 78899, November 10, 2016).
(i) Airbus Service Bulletin A310–57–2096,
Revision 03, dated June 30, 2015.
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Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
(ii) Reserved.
(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,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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 Des Moines, Washington, on May
7, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–10214 Filed 5–14–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF JUSTICE
28 CFR Part 32
[Docket No.: OJP (BJA) 1722]
RIN 1121–AA85
Public Safety Officers’ Benefits
Program
Office of Justice Programs,
Department of Justice.
ACTION: Final rule.
AGENCY:
This final rule finalizes two
proposed rules in order to update and
improve the regulations of the Office of
Justice Programs (OJP) implementing
the Public Safety Officers’ Benefits
(PSOB) Program, in order to incorporate
several statutory changes enacted in
recent years, address some gaps in the
regulations, and improve the efficiency
of the PSOB Program claims process.
After careful consideration and analysis
of the public comments on both
proposed rules, the final rule
incorporates a number of changes as
discussed below.
DATES: This rule is effective June 14,
2018, except for amendatory
instructions 10 (amending 28 CFR
32.12), 17 (amending 28 CFR 32.22), and
32 (amending 28 CFR 32.53), which are
effective June 14, 2020.
FOR FURTHER INFORMATION CONTACT:
Hope Janke, Bureau of Justice
Assistance; Telephone: (202) 514–6278,
or toll-free at (888) 744–6513.
SUPPLEMENTARY INFORMATION: The
Public Safety Officers’ Benefits (PSOB)
daltland on DSKBBV9HB2PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:07 May 14, 2018
Jkt 244001
Program provides a statutory death
benefit to certain survivors of public
safety officers who are fatally injured in
the line of duty, disability benefits to
public safety officers catastrophically
injured in the line of duty, and
education benefits to certain of the
survivors and family members of the
foregoing public safety officers. Under
the Program, claims are filed with, and
adjudicated by, the Office of Justice
Programs (OJP) of the U.S. Department
of Justice. The regulations for the PSOB
Program are codified at 28 CFR part 32.
I. Executive Summary
A. Purpose of the Regulatory Action
OJP published two proposed rules for
the PSOB Program, one on July 15,
2016, 81 FR 46019 (‘‘PSOB I’’), and the
other on August 22, 2016, 81 FR 57348
(‘‘PSOB II’’). PSOB I primarily focused
on certain changes needed to implement
statutory changes made by the Dale
Long Act (affecting members of rescue
squad and ambulance crews, as well as
provisions related to certain heart
attack/stroke/vascular rupture cases),
and also to align the workings of the
PSOB Program with certain provisions
under the World Trade Center (WTC)
Health Program, as well as with the
September 11th Victim Compensation
Fund (VCF). PSOB II was to implement
recent statutory changes, address some
gaps in the regulations, and to improve
the efficiency of the PSOB Program
claims process.
During the comment periods, OJP
received comments on its proposed
rules from various parties. After further
review of the proposed rules and careful
consideration and analysis of all
comments on both proposed rules, OJP
has made amendments that are
incorporated into this final rule. In
addition, the final rule includes a
technical change necessitated by the
newly-enacted provisions of the Public
Safety Officers’ Benefits Improvement
Act of 2017, Public Law 115–36, 131
Stat. 841 (June 2, 2017). The final rule
also includes (non-substantive) changes
to myriad cross-references to statutory
provisions, referred to in the
regulations, that—effective September 1,
2017—were reclassified by the Law
Revision Counsel of the House of
Representatives from title 42 of the U.S.
Code to title 34 of the U.S. Code.
During the comment period, OJP
received comments on its proposed
rules from a number of interested
parties: Various national police-, fire-,
and rescue associations and unions; a
foundation supporting 9/11 responders;
an organization that provides support
and assistance to the survivors of fallen
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Fmt 4700
Sfmt 4700
22367
law enforcement officers; a prosecutor
and former claims attorney, and two
members of Congress. OJP received
input from a total of 7 commenters on
the first proposed rule, and 8
commenters on the second rule.
After careful consideration and
analysis of all comments received, OJP
has made amendments that are
incorporated into this consolidated final
rule. The final rule also contains a few
clarifying changes to provisions in the
proposed rule where there were some
previously unnoticed ambiguities, or
where the language was more complex
than necessary. A summary overview of
the changes made by the final rule
follows below, with a more complete
discussion (below that) of the provisions
of the rule, the public comments
received on the proposed rule, the
Department’s response, and the final
changes incorporated into the final rule.
Pursuant to 34 U.S.C. 10287, this final
rule is intended (insofar as consistent
with law) to be effective and applicable
to all claims from and after the effective
date hereof, whether pending (in any
stage) as of that date or subsequently
filed.
B. Summary of the Major Changes in the
Final Rule
The final rule makes the following
conforming changes required by the
Dale Long Public Safety Officers’
Benefits Improvement Act of 2012 (Dale
Long Act), Public Law 112–239, which,
among other things, added (as codified
at 34 U.S.C. 10282(9)(D)) as a new
category of public safety officer—‘‘a
member of a rescue squad or ambulance
crew who, as authorized or licensed by
law and by the applicable agency or
entity, is engaging in rescue activity or
in the provision of emergency medical
services’’. The following changes
implement the inclusion of the new
category of public safety officer by the
following revisions and additions to the
PSOB regulations:
• Revise definition of Employed by a
public agency;
• Revise definition of Line of duty
activity or action to align with statutory
inclusion of members of rescue squads
and ambulance crews;
• Revise definition of Officially
recognized or designated public
employee member of a squad or crew;
• Add a definition for Officially
recognized or designated volunteer
member of a squad or crew;
• Revise definition of Official training
program of public agency;
• Remove definition of Public
employee member of a squad or crew,
and
E:\FR\FM\15MYR1.SGM
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]]>Agencies
[Federal Register Volume 83, Number 94 (Tuesday, May 15, 2018)]
[Rules and Regulations]
[Pages 22362-22367]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-10214]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0071; Product Identifier 2017-NM-063-AD; Amendment
39-19280; AD 2018-10-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 22363]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2016-23-01,
which applied to all Airbus Model A310 series airplanes. AD 2016-23-01
required repetitive detailed inspections for cracking around the
fastener holes in certain areas of the wing top skin panels,
supplemental repetitive ultrasonic inspections for cracking around the
fastener holes in certain other areas of the wing top skin panels, and
repair if necessary. This AD adds an inspection and modification of the
fastener holes of the wing top skin panels at a certain area. This AD
also includes terminating action for certain inspections. This AD was
prompted by an evaluation by the design approval holder (DAH) which
indicates that the wing top skin panel fastener holes at a certain area
are also subject to widespread fatigue damage (WFD). We are issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective June 19, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 19,
2018.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
December 15, 2016 (81 FR 78899, November 10, 2016).
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, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0071.
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-2018-
0071; 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, 2200 South
216th St., Des Moines, WA 98198; telephone and fax: 206-231-3225.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-23-01, Amendment 39-18708 (81 FR 78899,
November 10, 2016) (``AD 2016-23-01''). AD 2016-23-01 applied to all
Airbus Model A310 series airplanes. The NPRM published in the Federal
Register on February 8, 2018 (83 FR 5579). The NPRM was prompted by an
evaluation done by the DAH which indicates that the wing top skin panel
fastener holes at a certain area are subject to WFD. The NPRM would
continue to require repetitive detailed inspections for cracking around
the fastener holes in certain areas of the wing top skin panels,
supplemental repetitive ultrasonic inspections for cracking around the
fastener holes in certain other areas of the wing top skin panels, and
repair if necessary. The NPRM proposed to add an inspection and
modification of the fastener holes of the wing top skin panels at a
certain area. The NPRM also includes terminating action for certain
inspections. We are issuing this AD to detect and correct fatigue
cracking around the fastener holes, which could result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0081, dated May 8, 2017 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus Model A310 series airplanes. The MCAI
states:
Following scheduled maintenance, cracks were found around the
wing top skin panels fastener holes at Rib 2, between Stringer (STG)
2 and STG14.
This condition, if not detected and corrected, could reduce the
structural integrity of the aeroplane.
To address this issue, Airbus developed an inspection programme,
and published Service Bulletin (SB) A310-57-2096, providing
instructions for repetitive detailed inspections (DET) to ensure
that any visible cracks in the wing top skin panels 1 and 2 along
Rib 2 are detected on time and repaired appropriately. Consequently,
EASA issued AD 2008-0211 [which corresponds to FAA AD 2010-04-03,
Amendment 39-16196 (75 FR 6852, February 12, 2010) (``AD 2010-04-
03)] to require implementation of that inspection programme.
After that [EASA] AD was issued, Airbus improved the inspection
programme, revising SB A310-57-2096 accordingly, to include a
special detailed inspection (SDI), using an ultrasonic method, to
allow earlier crack detection, to subsequently reduce the scope of
potential repair action, and to extend the intervals of the
repetitive inspections.
Consequently, EASA issued AD 2014-0200 (later revised),
retaining the requirements of EASA AD 2008-0211, which was
superseded, and required supplementary repetitive SDI [for cracking]
of the wing top skin panel 1 and 2 between STG2 and STG10 at Rib 2
[and repair if needed], as described in Airbus SB A310-57-2096
Revision 02.
Since EASA AD 2014-0200R1 was issued, a Widespread Fatigue
Damage (WFD) analysis concluded that the inspection programme had to
be extended to include the wing top skin panels at Rib 3
attachments, and Airbus issued SB A310-57-2096 Revision 03
accordingly, to provide the necessary instructions. Consequently,
EASA issued [EASA] AD 2016-0005 [which corresponds to FAA AD 2016-
23-01], retaining the requirements of EASA AD 2014-0200R1, which was
superseded, and extending the inspection area to include Rib 3.
In addition to changes to the inspected area, WFD analysis
identified structural modification points for certain fastener
holes, located at each attachment from STG2 to STG10, at Ribs 2 and
3 on both wings.
Airbus developed modification (mod) 13785 and mod 13786,
consisting of an SDI, followed by an oversize of the defined holes
on Ribs 2 and 3 on both wings. Airbus issued SB A310-57-2106 and SB
A310-57-2107 to provide in-service modification instructions for top
skin attachments to Rib 2 and Rib 3 respectively. Accomplishment of
these modifications at the specified time will reset the fatigue
life of the attachment holes at the top skin attachment to Rib 2 and
Rib 3 to the Limit of Validity (LOV). Airbus issued inspection SB
A310-57-2096 Revision 04 to account for the inspection requirements
post-modification.
For the reasons describe above, this [EASA] AD retains the
requirements of EASA AD 2016-0005, which is superseded, requires
modifications to the top skin attachment holes at Rib 2 and Rib 3,
and defines the inspection requirements for Rib 2 and Rib 3 after
modification.
Modification of the fastener holes at top skin ribs 2 and 3
constitutes terminating action for certain repetitive special detailed
inspections. 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-2018-0071.
[[Page 22364]]
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. FedEx 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 A310-57-2096, Revision 04, dated
December 5, 2016. This service information describes procedures for
detailed and ultrasonic inspections for cracking around the fastener
holes of wing top skin panels 1 and 2, at ribs 2 and 3, on the left-
and right-hand sides of the fuselage.
Airbus Service Bulletin A310-57-2106, dated November 14,
2016. This service information describes procedures for a special
detailed inspection and modification of the fastener holes of wing top
skin panels 1 and 2, at rib 2.
Airbus Service Bulletin A310-57-2107, dated November 14,
2016. This service information describes procedures for a special
detailed inspection and modification of the fastener holes of wing top
skin panels 1 and 2, at rib 3.
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 8 airplanes of U.S. registry.
The actions required by AD 2016-23-01, and retained in this AD,
take about 8 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 2016-23-01 on U.S. operators to be
$5,440, or $680 per product.
We also estimate that it takes about 95 work-hours per product to
comply with the basic requirements of this AD. Required parts will cost
about $10,200 per product. The average labor rate is $85 per work-hour.
Based on these figures, we estimate the cost of this AD on U.S.
operators to be $146,200, or $18,275 per product.
In addition, we estimate that any necessary modification will take
about 40 work-hours and require parts costing $10,000, for a cost of
$13,400 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 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)
2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016), and
adding the following new AD:
2018-10-05 Airbus: Amendment 39-19280; FAA-2018-0071; Product
Identifier 2017-NM-063-AD.
(a) Effective Date
This AD is effective June 19, 2018.
(b) Affected ADs
This AD replaces AD 2016-23-01, Amendment 39-18708 (81 FR 78899,
November 10, 2016) (``AD 2016-23-01'').
(c) Applicability
This AD applies to all Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes, certificated in any category,
all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the wing top skin panel fastener holes
at ribs 2 and 3 are subject to widespread fatigue damage (WFD). We
are issuing this AD to detect and correct fatigue cracking around
the fastener holes, which could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections, With Revised Service Information
This paragraph restates the requirements of paragraph (g) of AD
2016-23-01, with revised service information. Except as required by
paragraph (i) of this AD: Within
[[Page 22365]]
the initial compliance time and thereafter at the repetitive
intervals specified in paragraphs (h)(1) through (h)(3) of this AD,
as applicable, accomplish the actions specified in paragraphs (g)(1)
and (g)(2) of this AD concurrently and in sequence, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A310-57-2096, Revision 03, dated June 30, 2015, or Revision 04,
dated December 5, 2016; except as provided by paragraph (j) of this
AD. As of the effective date of this AD, use only Airbus Service
Bulletin A310-57-2096, Revision 04, dated December 5, 2016, to
accomplish the required actions.
(1) Accomplish a detailed inspection for cracking around the
fastener holes in the wing top skin panels 1 and 2, along ribs 2 and
3, between the front and rear spars on the left- and right-hand
sides of the fuselage.
(2) Accomplish an ultrasonic inspection for cracking around the
fastener holes in the wing top skin panels 1 and 2, along ribs 2 and
3, between stringer (STG) 2 and STG10 on the left- and right-hand
sides of the fuselage.
(h) Retained Compliance Times for Airplanes Not Previously Inspected,
With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2016-23-01, with no changes.
(1) For Model A310-203, -204, -221, and -222 airplanes: Do the
actions required by paragraphs (g)(1) and (g)(2) of this AD at the
later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii)
of this AD. Repeat the inspections specified in paragraphs (g)(1)
and (g)(2) of this AD thereafter at intervals not to exceed 2,000
flight cycles or 4,100 flight hours, whichever occurs first.
(i) Prior to the accumulation of 18,700 flight cycles or 37,400
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after December 15, 2016 (the effective date
of AD 2016-23-01).
(2) For Model A310-304, -322, -324, and -325 airplanes having an
average flight time (AFT) of less than 4 hours: Do the actions
required by paragraphs (g)(1) and (g)(2) of this AD at the later of
the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this
AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2)
of this AD thereafter at intervals not to exceed 2,000 flight cycles
or 5,600 flight hours, whichever occurs first.
(i) Prior to the accumulation of 17,300 flight cycles or 48,400
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after December 15, 2016 (the effective date
of AD 2016-23-01).
(3) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of equal to or more than 4 hours: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD at the later of the times
specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Repeat
the inspections specified in paragraphs (g)(1) and (g)(2) of this AD
thereafter at intervals not to exceed 1,500 flight cycles or 7,500
flight hours, whichever occurs first.
(i) Prior to the accumulation of 12,800 flight cycles or 64,300
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after December 15, 2016 (the effective date
of AD 2016-23-01).
(i) Retained Compliance Times for Airplanes Previously Inspected, With
Revised Service Information
This paragraph restates the requirements of paragraph (i) of AD
2016-23-01, with revised service information. For airplanes
previously inspected before December 15, 2016 (the effective date of
AD 2016-23-01), using Airbus Service Bulletin A310-57-2096, dated
May 6, 2008; Airbus Service Bulletin A310-57-2096, Revision 01,
dated August 5, 2010; or Airbus Service Bulletin A310-57-2096,
Revision 02, dated March 5, 2014: At the applicable compliance times
specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD,
accomplish the actions specified in paragraphs (g)(1) and (g)(2) of
this AD concurrently and in sequence, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2096,
Revision 03, dated June 30, 2015, or Revision 04, dated December 5,
2016. As of the effective date of this AD, use only Airbus Service
Bulletin A310-57-2096, Revision 04, dated December 5, 2016, to
accomplish the required actions. Repeat the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD thereafter at the repetitive
intervals specified in paragraphs (h)(1), (h)(2), and (h)(3) of this
AD, as applicable.
(1) For Model A310-203, -204, -221, and -222 airplanes: Do the
actions required by paragraphs (g)(1) and (g)(2) of this AD within
3,500 flight hours or 1,700 flight cycles, whichever occurs first
since the most recent inspection.
(2) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of less than 4 hours: Do the actions required by paragraphs
(g)(1) and (g)(2) of this AD within 4,600 flight hours or 1,600
flight cycles, whichever occurs first since the most recent
inspection.
(3) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of equal to or more than 4 hours: Do the actions required by
paragraphs (g)(1) and (g)(2) of this AD within 6,100 flight hours or
1,200 flight cycles, whichever occurs first since the most recent
inspection.
(j) Retained Compliance Times if No Ultrasonic Equipment Is Available,
With Revised Service Information
This paragraph restates the requirements of paragraph (j) of AD
2016-23-01, with revised service information. If no ultrasonic
equipment is available for the initial or second inspection required
by paragraph (g) or (h) of this AD, accomplish the detailed
inspection specified in paragraph (g)(1) of this AD within the
applicable compliance times specified in paragraphs (j)(1) and
(j)(2) of this AD. After accomplishing the detailed inspection, do
the inspections specified in paragraphs (g)(1) and (g)(2) of this AD
at the applicable compliance times specified by paragraphs (i)(1),
(i)(2), and (i)(3) of this AD. Subsequently, repeat the inspections
specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at
the applicable repetitive intervals specified in paragraphs (h)(1),
(h)(2), and (h)(3) of this AD.
(1) For airplanes not previously inspected before December 15,
2016 (the effective date of AD 2016-23-01), using the service
information identified in paragraph (j)(2)(i), (j)(2)(ii),
(j)(2)(iii), or (j)(2)(iv) of this AD: Do the actions required by
paragraph (g)(1) of this AD within the initial compliance time
specified by paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as
applicable.
(2) For airplanes previously inspected before December 15, 2016
(the effective date of AD 2016-23-01), using the service information
identified in paragraph (j)(2)(i), (j)(2)(ii), (j)(2)(iii), or
(j)(2)(iv) of this AD: Do the actions required by paragraph (g)(1)
of this AD within the applicable compliance times specified in
paragraphs (i)(1), (i)(2), and (i)(3) of this AD.
(i) Airbus Service Bulletin A310-57-2096, dated May 6, 2008.
(ii) Airbus Service Bulletin A310-57-2096, Revision 01, dated
August 5, 2010.
(iii) Airbus Service Bulletin A310-57-2096, Revision 02, dated
March 5, 2014.
(iv) Airbus Service Bulletin A310-57-2096, Revision 03, dated
June 30, 2015.
(k) Retained Repair of Cracking, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2016-23-01, with no changes. If any cracking is found during any
inspection required by paragraph (g), (h), (i), or (j) of this AD,
before further flight, repair the cracking 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. Accomplishing
the repair specified in this paragraph terminates the repetitive
inspections required by paragraph (g), (h), (i), or (j) of this AD,
as applicable, for the repaired area only.
(l) Retained Definition of AFT, With No Changes
This paragraph restates the requirements of paragraph (l) of AD
2016-23-01, with no changes. For the purposes of this AD, the AFT
should be established as specified in paragraphs (l)(1), (l)(2), and
(l)(3) of this AD for the determination of the compliance times.
(1) The inspection threshold is defined as the total flight
hours accumulated (counted from take-off to touch-down), divided by
the total number of flight cycles accumulated at the effective date
of this AD.
(2) The initial inspection interval is defined as the total
flight hours accumulated divided by the total number of flight
cycles accumulated at the time of the initial inspection threshold.
(3) The second inspection interval is defined as the total
flight hours accumulated divided by the total number of flight
cycles accumulated between the initial and second inspection
threshold. For all inspection intervals onwards, the average flight
time is the flight hours divided by the flight cycles accumulated
between the last two inspections.
[[Page 22366]]
(m) New Requirements of This AD: Rib 2 Inspection and Modification
At the compliance time specified in paragraph (n) of this AD, as
applicable, accomplish the actions specified in paragraphs (m)(1)
and (m)(2) of this AD concurrently and in sequence, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A310-57-2106, dated November 14, 2016.
(1) Accomplish a special detailed inspection to determine the
diameter of the fastener holes in the wing top skin panels 1 and 2,
at rib 2 of both wings.
(2) Modify the fastener holes.
(n) New Compliance Times for Rib 2 Inspection and Modification
(1) For Model A310-203, -204, -221, and -222 airplanes: Do the
actions required by paragraphs (m)(1) and (m)(2) of this AD at the
later of the times specified in paragraphs (n)(1)(i) and (n)(1)(ii)
of this AD.
(i) Prior to the accumulation of 40,000 flight cycles or 93,300
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date of this AD.
(2) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of less than 4 hours: Do the actions required by paragraphs
(m)(1) and (m)(2) of this AD at the later of the times specified in
paragraphs (n)(2)(i) and (n)(2)(ii) of this AD.
(i) Prior to the accumulation of 40,000 flight cycles or 116,000
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date of this AD.
(3) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of 4 hours or more: Do the actions required by paragraphs (m)(1)
and (m)(2) of this AD at the later of the times specified in
paragraphs (n)(3)(i) and (n)(3)(ii) of this AD.
(i) Prior to the accumulation of 30,000 flight cycles or 150,000
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date of this AD.
(o) New Requirements of This AD: Rib 3 Inspection and Modification
At the compliance time specified in paragraph (p) of this AD, as
applicable, accomplish the actions specified in paragraphs (o)(1)
and (o)(2) of this AD concurrently and in sequence, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A310-57-2107, dated November 14, 2016.
(1) Accomplish a special detailed inspection to determine the
diameter of the fastener holes in the wing top skin panels 1 and 2,
at rib 3 of both wings.
(2) Modify the fastener holes.
(p) New Compliance Times for Rib 3 Inspection and Modification
(1) For Model A310-203, -204, -221, and -222 airplanes: Do the
actions required by paragraphs (o)(1) and (o)(2) of this AD at the
later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii)
of this AD.
(i) Prior to the accumulation of 46,400 flight cycles or 92,900
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date of this AD.
(2) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of less than 4 hours: Do the actions required by paragraphs
(o)(1) and (o)(2) of this AD at the later of the times specified in
paragraphs (p)(2)(i) and (p)(2)(ii) of this AD.
(i) Prior to the accumulation of 45,400 flight cycles or 127,300
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date of this AD.
(3) For Model A310-304, -322, -324, and -325 airplanes having an
AFT of 4 hours or more: Do the actions required by paragraphs (o)(1)
and (o)(2) of this AD at the later of the times specified in
paragraphs (p)(3)(i) and (p)(3)(ii) of this AD.
(i) Prior to the accumulation of 33,800 flight cycles or 169,000
flight hours since first flight of the airplane, whichever occurs
first.
(ii) Within 30 days after the effective date of this AD.
(q) New Corrective Actions
If any cracking is found during any inspection required by
paragraph (m), (n), (o), or (p) of this AD, before further flight,
repair the cracking using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature. Accomplishing the repair specified in
this paragraph terminates the repetitive inspections required by
paragraph (g), (h), (i), or (j) of this AD, as applicable, for the
repaired area only.
(r) New Terminating Actions
(1) Accomplishment of the modification specified in paragraph
(m) of this AD constitutes terminating action for the repetitive
special detailed inspections required by paragraph (g)(2) of this AD
for the modified fastener holes at top skin rib 2 for that airplane.
After modification, the un-modified fastener holes at top skin rib 2
between the front and rear spars remain subject to the repetitive
inspections required by paragraph (g)(1) of this AD.
(2) Accomplishment of the modification specified in paragraph
(o) of this AD constitutes terminating action for the repetitive
special detailed inspections required by paragraph (g)(2) of this AD
for the modified fastener holes at top skin rib 3 for that airplane.
After modification, the un-modified fastener holes at top skin rib 3
between the front and rear spars remain subject to the repetitive
inspection required by paragraph (g)(1) of this AD.
(s) Other FAA AD Provisions
(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 (t)(2) of this AD. Information
may be emailed to: [email protected]. 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.
(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 EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(t) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0081, dated May 8, 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-2018-0071.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax: 206-231-3225.
(u) 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
June 19, 2018.
(i) Airbus Service Bulletin A310-57-2096, Revision 04, dated
December 5, 2016.
(ii) Airbus Service Bulletin A310-57-2106, dated November 14,
2016.
(iii) Airbus Service Bulletin A310-57-2107, dated November 14,
2016.
(4) The following service information was approved for IBR on
December 15, 2016 (81 FR 78899, November 10, 2016).
(i) Airbus Service Bulletin A310-57-2096, Revision 03, dated
June 30, 2015.
[[Page 22367]]
(ii) Reserved.
(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, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(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 Des Moines, Washington, on May 7, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-10214 Filed 5-14-18; 8:45 am]
BILLING CODE 4910-13-P
