Airworthiness Directives; Airbus Airplanes, 21255-21258 [2016-07570]
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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / 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):
■
2016–07–28 The Boeing Company:
Amendment 39–18473; Docket No.
FAA–2016–5458; Directorate Identifier
2016–NM–027–AD.
(a) Effective Date
This AD is effective April 26, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model DC–9–81 (MD–81), DC–9–
82 (MD–82), DC–9–83 (MD–83), and DC–9–
87 (MD–87) airplanes, and Model MD–88
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of
cracking at certain stringers, associated end
fittings, and skins in the center wing fuel
tank where the stringers meet the end
fittings. We are issuing this AD to detect and
correct cracking in the center wing lower
skin. Such cracking could cause structural
failure of the wings.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
jstallworth on DSK7TPTVN1PROD with RULES
(g) Inspection
Except as required by paragraph (h)(1) and
(h)(2) of this AD, at the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin MD80–57A244,
dated March 3, 2016: Do an eddy current
high frequency (ETHF) inspection for any
cracking in the left and right side center wing
lower skin, and do all applicable corrective
actions; except as required by paragraph
(h)(3) of this AD. Do all applicable corrective
actions before further flight. Repeat the
inspection thereafter at the intervals
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin MD80–57A244,
dated March 3, 2016.
(h) Exception to the Service Information
(1) Where Boeing Alert Service Bulletin
MD80–57A244, dated March 3, 2016,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(2) The Condition column of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
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Bulletin MD80–57A244, dated March 3,
2016, refers to total flight cycles ‘‘as of the
original issue date of this service bulletin.’’
This AD, however, applies to the airplanes
with the specified total flight cycles as of the
effective date of this AD.
(3) If any crack is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin MD80–57A244, dated
March 3, 2016, specifies to contact Boeing for
appropriate action, and specifies that action
as ‘‘RC’’ (Required for Compliance): Before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOCRequests@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, Los Angeles
ACO, 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)(3)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(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. 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
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.
(j) Related Information
For more information about this AD,
contact Haytham Alaidy, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
PO 00000
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21255
5224; fax: 562–627–5210; email:
haytham.alaidy@faa.gov.
(k) 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 Alert Service Bulletin MD80–
57A244, dated March 3, 2016.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, 3855 Lakewood
Boulevard, MC D800–0019, Long Beach, CA
90846–0001; telephone 206–544–5000,
extension 2; fax 206–766–5683; Internet
https://www.myboeingfleet.com.
(4) You may view this referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(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 Renton, Washington, on March
30, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–07842 Filed 4–8–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–4817; Directorate
Identifier 2014–NM–115–AD; Amendment
39–18465; AD 2016–07–20]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 95–18–08
for all Airbus Model A300–600 series
airplanes. AD 95–18–08 required
repetitive inspections to detect cracks in
the bottom skin of the wing in the area
of the cut-out for the pylon rear
attachment fitting, and repair if
necessary. This new AD, for certain
SUMMARY:
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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
airplanes, reduces the compliance times
for the inspections. This AD was
prompted by a report that updated
fatigue and damage tolerance analyses
and a fleet survey found that certain
inspection thresholds and intervals
must be reduced to allow more timely
findings of cracking. We are issuing this
AD to detect and correct fatigue-related
cracking in the bottom skin of the wing
in the area of the cut-out for the pylon
rear attachment fitting, which could
result in reduced structural integrity of
the wing.
DATES: This AD becomes effective May
16, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 16, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of October 16, 1995 (60 FR
47677, September 14, 1995).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-4817; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in
this final rule, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
4817.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 95–18–08,
Amendment 39–9355 (60 FR 47677,
September 14, 1995) (‘‘AD 95–18–08’’).
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AD 95–18–08 applied to all Airbus
Model A300–600 series airplanes
(which includes Airbus Model A300
C4–605R Variant F airplanes), Model
A300 B4–622 airplanes, and Model
A300 F4–622R airplanes that were
added to the U.S. Type Certificate Data
Sheet since issuance of AD 95–18–08.
The NPRM published in the Federal
Register on November 19, 2015 (80 FR
72395) (‘‘the NPRM’’ or ‘‘the proposed
AD’’). The NPRM was prompted by a
report that updated fatigue and damage
tolerance analyses and a fleet survey
found that certain inspection thresholds
and intervals must be reduced to allow
more timely findings of cracking. The
NPRM proposed to continue to require
repetitive inspections to detect cracks in
the bottom skin of the wing in the area
of the cut-out for the pylon rear
attachment fitting, and repair if
necessary. The NPRM also proposed, for
certain airplanes, reduce the compliance
times for the inspections. We are issuing
this AD to detect and correct such
fatigue-related cracking in the bottom
skin of the wing in the area of the cutout for the pylon rear attachment fitting,
which could result in reduced structural
integrity of the wing.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0119, dated May 13,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on all Airbus 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 MCAI states:
Full-scale fatigue tests carried out on the
A300–600 test specimen by Airbus revealed
crack initiation in the bottom skin adjacent
to the aft pylon attachment fitting.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this unsafe condition, DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued AD 94–069–158(B) (https://
ad.easa.europa.eu/blob/1994069158tb_
superseded.pdf/AD_F-1994-069-158_2)
[which corresponds to FAA AD 95–18–08,
Amendment 39–9355 (60 FR 47677,
September 14, 1995)] to require repetitive
detailed visual inspections (DVI) of the wing
bottom skin in the area of the cut-out for the
pylon rear attachment fitting on Left Hand
(LH) and Right Hand (RH) wings [to detect
cracks, and repair if necessary].
Since that [DGAC] AD was issued, a fleet
survey and updated Fatigue and Damage
Tolerance analyses have been performed in
order to substantiate the second A300–600
Extended Service Goal (ESG2) exercise. As a
result, it was revealed that the inspection
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threshold and interval must be reduced to
allow timely detection of cracks and the
accomplishment of an applicable corrective
action. Prompted by these findings, Airbus
issued Revision 07 of Service Bulletin (SB)
A300–57–6028.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD 94–069–158(B), which is
superseded, but reduces the inspection
thresholds and intervals [e.g., compliance
times].
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-48170002.
Comment
The following presents the comment
received on the NPRM and the FAA’s
response to the comment.
Statement on Fleet Activity
FedEx Express (FedEx) stated that the
NPRM will affect 71 Model A300
airplanes in its fleet. FedEx stated that
42 of its Model A300–F4 airplanes have
not reached the inspection threshold,
and it is currently accomplishing
repetitive actions on 15 of its 29 Model
A300–B4 airplanes. FedEx stated that it
will adjust its inspection actions to
comply with the actions specified in the
NPRM.
We acknowledge FedEx’s comment.
No change to this AD is necessary.
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
We reviewed Airbus Service Bulletin
A300–57–6028, Revision 07, dated June
6, 2011. The service information
describes procedures for inspections to
detect cracks in the bottom skin of the
wing in the area of the cut-out for the
pylon rear attachment fitting, and
repair. 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.
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Costs of Compliance
We estimate that this AD affects 124
airplanes of U.S. registry.
The actions required by AD 95–18–08,
and retained in this AD take about 6
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 were required by AD
95–18–08 is $510 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 15 work-hours and require parts
costing $10,000, for a cost of $11,275
per product. We have no way of
determining the number of aircraft that
might need these actions.
The new requirements of this AD add
no additional economic burden.
jstallworth on DSK7TPTVN1PROD with RULES
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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.
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(e) Reason
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-4817; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
This AD was prompted by a report that
updated fatigue and damage tolerance
analyses and a fleet survey found that certain
inspection thresholds and intervals must be
reduced to allow more timely findings of
cracking. We are issuing this AD to detect
and correct such fatigue-related cracking in
the bottom skin of the wing in the area of the
cut-out for the pylon rear attachment fitting,
which could result in reduced structural
integrity of the wing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
List of Subjects in 14 CFR Part 39
(g) Retained Inspection and Corrective
Action with Additional Repair Information
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
This paragraph restates the requirements of
paragraph (a) of AD 95–18–08, with
additional repair contact information. Prior
to the accumulation of 24,000 total flight
cycles since date of manufacture of the
airplane, or within 750 flight cycles after
October 16, 1995 (the effective date of AD
95–18–08), whichever occurs later, perform a
detailed visual inspection to detect cracks in
the bottom skin of the wing in the area of the
cut-out for the pylon rear attachment fitting,
in accordance with Airbus Service Bulletin
A300–57–6028, Revision 3, dated September
13, 1994. Repeat the inspection thereafter at
intervals not to exceed 9,000 flight cycles. If
any crack is detected, prior to further flight,
repair the wing bottom skin in accordance
with a method approved by the Manager,
Standardization Branch, ANM–113, FAA,
Transport Airplane Directorate, or the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). Accomplishing any
inspection required by paragraph (h) of this
AD terminates the inspections required by
this paragraph.
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)
95–18–08, Amendment 39–9355 (60 FR
47677, September 14, 1995), and adding
the following new AD:
■
2016–07–20 Airbus: Amendment 39–18465.
Docket No. FAA–2015–4817; Directorate
Identifier 2014–NM–115–AD.
(a) Effective Date
This AD becomes effective May 16, 2016.
(b) Affected ADs
This AD replaces AD 95–18–08,
Amendment 39–9355 (60 FR 47677,
September 14, 1995) (‘‘AD 95–18–08’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(4) of this AD,
certificated in any category, all manufacturer
serial numbers.
(1) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(2) Airbus Model A300 B4–605R and B4–
622R airplanes.
(3) Airbus Model A300 F4–605R and F4–
622R airplanes.
(4) Airbus Model A300 C4–605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
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(h) New Requirement of This AD: Revised
Inspection Thresholds and Intervals
Within the applicable compliance times
required in paragraphs (h)(1) and (h)(2) of
this AD, do a detailed visual inspection of
the wing bottom skin in the area of the cutout for the pylon rear attachment fitting on
left-hand and right-hand wings, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6028, Revision 07, dated June 6, 2011.
Repeat the inspections thereafter at the
applicable intervals required in paragraphs
(h)(3) and (h)(4) of this AD. Accomplishing
any inspection required by this paragraph
terminates the inspections required by
paragraph (g) of this AD.
(1) For ‘‘normal range operations’’
airplanes having an average flight time of 1.5
flight hours or more: Do the inspection at the
applicable time required in paragraphs
(h)(1)(i) and (h)(1)(ii) of this AD.
(i) For Model A300 F4–605R and F4–622R
airplanes: Do the inspection at the later of the
times specified in paragraphs (h)(1)(i)(A) and
(h)(1)(i)(B) of this AD.
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(A) Within 24,000 flight cycles or 51,800
flight hours after first flight of the airplane,
whichever occurs first.
(B) Within 2,000 flight cycles or 4,300
flight hours after the effective date of this AD,
whichever occurs first.
(ii) For Model A300 B4–600, B4–600R, and
Model A300 C4–605R Variant F airplanes: Do
the inspection at the later of the times
specified in paragraphs (h)(1)(ii)(A) and
(h)(1)(ii)(B) of this AD.
(A) Within 19,100 flight cycles or 41,200
flight hours after first flight of the airplane,
whichever occurs first.
(B) Within 1,500 flight cycles or 3,200
flight hours after the effective date of this AD,
whichever occurs first.
(2) For ‘‘short range operations’’ airplanes
having an average flight time of less than 1.5
flight hours: Do the inspection at the
applicable time required in paragraphs
(h)(2)(i) and (h)(2)(ii) of this AD.
(i) For Model A300 F4–605R and F4–622R
airplanes: Do the inspection at the later of the
times specified in paragraphs (h)(2)(i)(A) and
(h)(2)(i)(B) of this AD.
(A) Within 25,900 flight cycles or 38,800
flight hours after first flight of the airplane,
whichever occurs first.
(B) Within 2,100 flight cycles or 3,200
flight hours after the effective date of this AD,
whichever occurs first.
(ii) For Model A300 B4–600, B4–600R, and
Model A300 C4–605R Variant F airplanes: Do
the inspection at the later of the times
specified in paragraphs (h)(2)(ii)(A) and
(h)(2)(ii)(B) of this AD.
(A) Within 20,600 flight cycles or 30,900
flight hours after first flight of the airplane,
whichever occurs first.
(B) Within 1,600 flight cycles or 2,400
flight hours after the effective date of this AD,
whichever occurs first.
(3) For ‘‘normal range operations’’
airplanes having an average flight time of 1.5
flight hours or more: Repeat the inspection at
the applicable time required in paragraphs
(h)(3)(i) and (h)(3)(ii) of this AD.
(i) For Model A300 F4–605R and F4–622R
airplanes: Repeat the inspection thereafter at
intervals not to exceed 9,000 flight cycles or
19,400 flight hours, whichever occurs first.
(ii) For Model A300 B4–600, B4–600R, and
Model A300 C4–605R Variant F airplanes:
Repeat the inspection thereafter at intervals
not to exceed 7,100 flight cycles or 15,300
flight hours, whichever occurs first.
(4) For ‘‘short range operations’’ airplanes
having an average flight time of less than 1.5
flight hours: Repeat the inspection at the
applicable time required in paragraphs
(h)(4)(i) and (h)(4)(ii) of this AD.
(i) For Model A300 F4–605R and F4–622R
airplanes: Repeat the inspection thereafter at
intervals not to exceed 9,700 flight cycles or
14,500 flight hours, whichever occurs first.
(ii) For Model A300 B4–600, B4–600R, and
Model A300 C4–605R Variant F airplanes:
Repeat the inspection thereafter at intervals
not to exceed 7,600 flight cycles or 11,500
flight hours, whichever occurs first.
(i) Definition of Average Flight Time for
Paragraph (h) of This AD
For the purpose of paragraph (h) of this
AD, the Average Flight Time must be
established as follows:
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(1) For the initial inspection, the average
flight time is the total accumulated flight
hours, counted from take-off to touch-down,
divided by the total accumulated flight cycles
at the effective date of this AD.
(2) For the first repeated inspection
interval, the average flight time is the total
accumulated flight hours divided by the total
accumulated flight cycles at the time of the
inspection threshold.
(3) For all inspection intervals onwards,
the average flight time is the flight hours
divided by the flight cycles accumulated
between the last two inspections.
(j) New Requirement of This AD: Corrective
Action for Any Cracking Found
If any crack is found during any inspection
required by paragraph (h) of this AD: Before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA. Accomplishing a repair does not
constitute terminating action for the
repetitive inspections required by paragraph
(h) of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for
inspections required by paragraph (h) of this
AD, if those actions were performed before
the effective date of this AD using any of the
service information identified in paragraphs
(k)(1), (k)(2), and (k)(3) of this AD, which are
not incorporated by reference in this AD.
(1) Airbus Service Bulletin A300–57–6028,
Revision 04, dated October 25, 1999.
(2) Airbus Service Bulletin A300–57–6028,
Revision 05, dated January 11, 2002.
(3) Airbus Service Bulletin A300–57–6028,
Revision 06, dated May 17, 2006.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@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. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
95–18–08, are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
PO 00000
Frm 00036
Fmt 4700
Sfmt 9990
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA 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) European
Aviation Safety Agency Airworthiness
Directive 2014–0119, dated May 13, 2014, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2015–4817.
(2) 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 May 16, 2016.
(i) Airbus Service Bulletin A300–57–6028,
Revision 07, dated June 6, 2011.
(ii) Reserved.
(4) The following service information was
approved for IBR on October 16, 1995 (60 FR
47677, September 14, 1995).
(i) Airbus Service Bulletin A300–57–6028,
Revision 3, dated September 13, 1994. Pages
1 through 6 of this service bulletin indicate
Revision 3 and are dated September 13, 1994;
pages 7 through 9 indicate Revision 2 and are
dated February 22, 1994.
(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 Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–07570 Filed 4–8–16; 8:45 am]
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E:\FR\FM\11APR1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21255-21258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07570]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-115-AD;
Amendment 39-18465; AD 2016-07-20]
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) 95-18-08 for
all Airbus Model A300-600 series airplanes. AD 95-18-08 required
repetitive inspections to detect cracks in the bottom skin of the wing
in the area of the cut-out for the pylon rear attachment fitting, and
repair if necessary. This new AD, for certain
[[Page 21256]]
airplanes, reduces the compliance times for the inspections. This AD
was prompted by a report that updated fatigue and damage tolerance
analyses and a fleet survey found that certain inspection thresholds
and intervals must be reduced to allow more timely findings of
cracking. We are issuing this AD to detect and correct fatigue-related
cracking in the bottom skin of the wing in the area of the cut-out for
the pylon rear attachment fitting, which could result in reduced
structural integrity of the wing.
DATES: This AD becomes effective May 16, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 16,
2016.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
October 16, 1995 (60 FR 47677, September 14, 1995).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-4817; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this final rule, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4817.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 95-18-08, Amendment 39-9355 (60 FR 47677,
September 14, 1995) (``AD 95-18-08''). AD 95-18-08 applied to all
Airbus Model A300-600 series airplanes (which includes Airbus Model
A300 C4-605R Variant F airplanes), Model A300 B4-622 airplanes, and
Model A300 F4-622R airplanes that were added to the U.S. Type
Certificate Data Sheet since issuance of AD 95-18-08. The NPRM
published in the Federal Register on November 19, 2015 (80 FR 72395)
(``the NPRM'' or ``the proposed AD''). The NPRM was prompted by a
report that updated fatigue and damage tolerance analyses and a fleet
survey found that certain inspection thresholds and intervals must be
reduced to allow more timely findings of cracking. The NPRM proposed to
continue to require repetitive inspections to detect cracks in the
bottom skin of the wing in the area of the cut-out for the pylon rear
attachment fitting, and repair if necessary. The NPRM also proposed,
for certain airplanes, reduce the compliance times for the inspections.
We are issuing this AD to detect and correct such fatigue-related
cracking in the bottom skin of the wing in the area of the cut-out for
the pylon rear attachment fitting, which could result in reduced
structural integrity of the wing.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0119, dated May 13, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on all Airbus 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 MCAI states:
Full-scale fatigue tests carried out on the A300-600 test
specimen by Airbus revealed crack initiation in the bottom skin
adjacent to the aft pylon attachment fitting.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 94-
069-158(B) (https://ad.easa.europa.eu/blob/1994069158tb_superseded.pdf/AD_F-1994-069-158_2) [which corresponds
to FAA AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14,
1995)] to require repetitive detailed visual inspections (DVI) of
the wing bottom skin in the area of the cut-out for the pylon rear
attachment fitting on Left Hand (LH) and Right Hand (RH) wings [to
detect cracks, and repair if necessary].
Since that [DGAC] AD was issued, a fleet survey and updated
Fatigue and Damage Tolerance analyses have been performed in order
to substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. As a result, it was revealed that the inspection threshold
and interval must be reduced to allow timely detection of cracks and
the accomplishment of an applicable corrective action. Prompted by
these findings, Airbus issued Revision 07 of Service Bulletin (SB)
A300-57-6028.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 94-069-158(B), which is superseded,
but reduces the inspection thresholds and intervals [e.g.,
compliance times].
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-4817-0002.
Comment
The following presents the comment received on the NPRM and the
FAA's response to the comment.
Statement on Fleet Activity
FedEx Express (FedEx) stated that the NPRM will affect 71 Model
A300 airplanes in its fleet. FedEx stated that 42 of its Model A300-F4
airplanes have not reached the inspection threshold, and it is
currently accomplishing repetitive actions on 15 of its 29 Model A300-
B4 airplanes. FedEx stated that it will adjust its inspection actions
to comply with the actions specified in the NPRM.
We acknowledge FedEx's comment. No change to this AD is necessary.
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
We reviewed Airbus Service Bulletin A300-57-6028, Revision 07,
dated June 6, 2011. The service information describes procedures for
inspections to detect cracks in the bottom skin of the wing in the area
of the cut-out for the pylon rear attachment fitting, and repair. 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.
[[Page 21257]]
Costs of Compliance
We estimate that this AD affects 124 airplanes of U.S. registry.
The actions required by AD 95-18-08, and retained in this AD take
about 6 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 were required by AD 95-18-08 is $510 per product.
In addition, we estimate that any necessary follow-on actions would
take about 15 work-hours and require parts costing $10,000, for a cost
of $11,275 per product. We have no way of determining the number of
aircraft that might need these actions.
The new requirements of this AD add no additional economic burden.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-4817; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), and
adding the following new AD:
2016-07-20 Airbus: Amendment 39-18465. Docket No. FAA-2015-4817;
Directorate Identifier 2014-NM-115-AD.
(a) Effective Date
This AD becomes effective May 16, 2016.
(b) Affected ADs
This AD replaces AD 95-18-08, Amendment 39-9355 (60 FR 47677,
September 14, 1995) (``AD 95-18-08'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(2) Airbus Model A300 B4-605R and B4-622R airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(4) Airbus Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a report that updated fatigue and damage
tolerance analyses and a fleet survey found that certain inspection
thresholds and intervals must be reduced to allow more timely
findings of cracking. We are issuing this AD to detect and correct
such fatigue-related cracking in the bottom skin of the wing in the
area of the cut-out for the pylon rear attachment fitting, which
could result in reduced structural integrity of the wing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection and Corrective Action with Additional Repair
Information
This paragraph restates the requirements of paragraph (a) of AD
95-18-08, with additional repair contact information. Prior to the
accumulation of 24,000 total flight cycles since date of manufacture
of the airplane, or within 750 flight cycles after October 16, 1995
(the effective date of AD 95-18-08), whichever occurs later, perform
a detailed visual inspection to detect cracks in the bottom skin of
the wing in the area of the cut-out for the pylon rear attachment
fitting, in accordance with Airbus Service Bulletin A300-57-6028,
Revision 3, dated September 13, 1994. Repeat the inspection
thereafter at intervals not to exceed 9,000 flight cycles. If any
crack is detected, prior to further flight, repair the wing bottom
skin in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate, or the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
Accomplishing any inspection required by paragraph (h) of this AD
terminates the inspections required by this paragraph.
(h) New Requirement of This AD: Revised Inspection Thresholds and
Intervals
Within the applicable compliance times required in paragraphs
(h)(1) and (h)(2) of this AD, do a detailed visual inspection of the
wing bottom skin in the area of the cut-out for the pylon rear
attachment fitting on left-hand and right-hand wings, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-57-6028, Revision 07, dated June 6, 2011. Repeat the
inspections thereafter at the applicable intervals required in
paragraphs (h)(3) and (h)(4) of this AD. Accomplishing any
inspection required by this paragraph terminates the inspections
required by paragraph (g) of this AD.
(1) For ``normal range operations'' airplanes having an average
flight time of 1.5 flight hours or more: Do the inspection at the
applicable time required in paragraphs (h)(1)(i) and (h)(1)(ii) of
this AD.
(i) For Model A300 F4-605R and F4-622R airplanes: Do the
inspection at the later of the times specified in paragraphs
(h)(1)(i)(A) and (h)(1)(i)(B) of this AD.
[[Page 21258]]
(A) Within 24,000 flight cycles or 51,800 flight hours after
first flight of the airplane, whichever occurs first.
(B) Within 2,000 flight cycles or 4,300 flight hours after the
effective date of this AD, whichever occurs first.
(ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R
Variant F airplanes: Do the inspection at the later of the times
specified in paragraphs (h)(1)(ii)(A) and (h)(1)(ii)(B) of this AD.
(A) Within 19,100 flight cycles or 41,200 flight hours after
first flight of the airplane, whichever occurs first.
(B) Within 1,500 flight cycles or 3,200 flight hours after the
effective date of this AD, whichever occurs first.
(2) For ``short range operations'' airplanes having an average
flight time of less than 1.5 flight hours: Do the inspection at the
applicable time required in paragraphs (h)(2)(i) and (h)(2)(ii) of
this AD.
(i) For Model A300 F4-605R and F4-622R airplanes: Do the
inspection at the later of the times specified in paragraphs
(h)(2)(i)(A) and (h)(2)(i)(B) of this AD.
(A) Within 25,900 flight cycles or 38,800 flight hours after
first flight of the airplane, whichever occurs first.
(B) Within 2,100 flight cycles or 3,200 flight hours after the
effective date of this AD, whichever occurs first.
(ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R
Variant F airplanes: Do the inspection at the later of the times
specified in paragraphs (h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD.
(A) Within 20,600 flight cycles or 30,900 flight hours after
first flight of the airplane, whichever occurs first.
(B) Within 1,600 flight cycles or 2,400 flight hours after the
effective date of this AD, whichever occurs first.
(3) For ``normal range operations'' airplanes having an average
flight time of 1.5 flight hours or more: Repeat the inspection at
the applicable time required in paragraphs (h)(3)(i) and (h)(3)(ii)
of this AD.
(i) For Model A300 F4-605R and F4-622R airplanes: Repeat the
inspection thereafter at intervals not to exceed 9,000 flight cycles
or 19,400 flight hours, whichever occurs first.
(ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R
Variant F airplanes: Repeat the inspection thereafter at intervals
not to exceed 7,100 flight cycles or 15,300 flight hours, whichever
occurs first.
(4) For ``short range operations'' airplanes having an average
flight time of less than 1.5 flight hours: Repeat the inspection at
the applicable time required in paragraphs (h)(4)(i) and (h)(4)(ii)
of this AD.
(i) For Model A300 F4-605R and F4-622R airplanes: Repeat the
inspection thereafter at intervals not to exceed 9,700 flight cycles
or 14,500 flight hours, whichever occurs first.
(ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R
Variant F airplanes: Repeat the inspection thereafter at intervals
not to exceed 7,600 flight cycles or 11,500 flight hours, whichever
occurs first.
(i) Definition of Average Flight Time for Paragraph (h) of This AD
For the purpose of paragraph (h) of this AD, the Average Flight
Time must be established as follows:
(1) For the initial inspection, the average flight time is the
total accumulated flight hours, counted from take-off to touch-down,
divided by the total accumulated flight cycles at the effective date
of this AD.
(2) For the first repeated inspection interval, the average
flight time is the total accumulated flight hours divided by the
total accumulated flight cycles at the time of the inspection
threshold.
(3) For all inspection intervals onwards, the average flight
time is the flight hours divided by the flight cycles accumulated
between the last two inspections.
(j) New Requirement of This AD: Corrective Action for Any Cracking
Found
If any crack is found during any inspection required by
paragraph (h) of this AD: Before further flight, repair using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
Accomplishing a repair does not constitute terminating action for
the repetitive inspections required by paragraph (h) of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for inspections required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using any of the service information
identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD,
which are not incorporated by reference in this AD.
(1) Airbus Service Bulletin A300-57-6028, Revision 04, dated
October 25, 1999.
(2) Airbus Service Bulletin A300-57-6028, Revision 05, dated
January 11, 2002.
(3) Airbus Service Bulletin A300-57-6028, Revision 06, dated May
17, 2006.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) AMOCs approved previously for AD 95-18-08, are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(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, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA 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) European Aviation Safety Agency Airworthiness Directive 2014-
0119, dated May 13, 2014, for related information. This MCAI may be
found in the AD docket on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2015-4817.
(2) 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
May 16, 2016.
(i) Airbus Service Bulletin A300-57-6028, Revision 07, dated
June 6, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
October 16, 1995 (60 FR 47677, September 14, 1995).
(i) Airbus Service Bulletin A300-57-6028, Revision 3, dated
September 13, 1994. Pages 1 through 6 of this service bulletin
indicate Revision 3 and are dated September 13, 1994; pages 7
through 9 indicate Revision 2 and are dated February 22, 1994.
(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
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-07570 Filed 4-8-16; 8:45 am]
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