Airworthiness Directives; Airbus Airplanes, 21246-21250 [2016-07574]
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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
which Airbus Modification 30975 has been
embodied in production.
(1) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(2) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(3) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by fatigue testing
that determined that fatigue damage could
appear on clips, shear webs, and angles at
certain rear fuselage sections and certain
frames. This AD is intended to complete
certain mandated programs intended to
support the airplane reaching its limit of
validity of the engineering data that support
the established structural maintenance
program. We are issuing this AD to prevent
fatigue damage on the clips, shear webs, and
angles, which could affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Replacement
At the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD:
Replace the clips, shear webs, and angles at
rear fuselage section 19, frame FR72 and
FR74, and do all applicable related
investigative actions before further flight, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1266, Revision 03, dated May 7, 2015. If
any crack is found during any related
investigative action required by this AD:
Before further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA).
(1) Before exceeding 48,000 flight cycles or
96,000 flight hours, whichever occurs first
since the airplane’s first flight.
(2) Within 30 days after the effective date
of this AD.
(h) Additional Replacement for Certain
Airplanes
For airplanes on which the replacement of
clips, shear webs, and angles specified in
Airbus Service Bulletin A320–53–1266 is
done before accumulating 30,000 flight
cycles or 60,000 flight hours, whichever
occurred first since the airplane’s first flight:
Within 30,000 flight cycles or 60,000 flight
hours, whichever occurs first after that
replacement, do the replacement specified in
paragraph (g) of this AD.
(i) Credit for Previous Actions
Except as required by paragraph (h) of this
AD: This paragraph provides credit for the
replacement required by paragraph (g) of this
AD, if those actions were performed before
the effective date of this AD using the service
information identified in paragraph (i)(1),
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(i)(2), or (i)(3) of this AD. This service
information is not incorporated by reference
in this AD.
(1) Airbus Service Bulletin A320–53–1266,
dated January 11, 2013.
(2) Airbus Service Bulletin A320–53–1266,
Revision 01, dated June 20, 2013.
(3) Airbus Service Bulletin A320–53–1266,
Revision 02, dated August 13, 2014.
(j) 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) 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.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0177, dated
July 25, 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–
2015–1277.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (l)(3) and (l)(4) of this AD.
(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 this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1266,
Revision 03, dated May 7, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
PO 00000
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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.
(4) 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.
(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
25, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–07375 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–2015–1426; Directorate
Identifier 2013–NM–200–AD; Amendment
39–18462; AD 2016–07–17]
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) 97–20–07
for certain 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). AD 97–20–
07 required repetitive inspections to
detect fatigue cracking in the left and
right wings in the area where the top
skin attaches to the center spar, and
repair or modification of this area if
necessary. This new AD reduces the
inspection compliance time and
repetitive inspection intervals. This AD
was prompted by a determination that
the inspection compliance time and
repetitive inspection interval must be
reduced to allow timely detection of
fatigue cracking in the left and right
wings in the area where the top skin
attaches to the center spar. We are
issuing this AD to detect and correct
this fatigue cracking, which could
reduce the residual strength of the top
skin of the wings, and consequently
SUMMARY:
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affect the structural integrity of the
airframe.
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 30, 1997 (62 FR
50251, September 25, 1997).
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.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–2015–1426.
jstallworth on DSK7TPTVN1PROD with RULES
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–2015–
1426; 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.
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 97–20–07,
Amendment 39–10145 (62 FR 50251,
September 25, 1997) (‘‘AD 97–20–07’’).
AD 97–20–07 applied to certain 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 NPRM published
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in the Federal Register on June 5, 2015
(80 FR 32058) (‘‘the NPRM’’). The
NPRM was prompted by a
determination that the inspection
compliance time and repetitive
inspection interval must be reduced to
allow timely detection of fatigue
cracking in the left and right wings in
the area where the top skin attaches to
the center spar. The NPRM proposed to
continue to require repetitive
inspections to detect fatigue cracking in
the left and right wings in the area
where the top skin attaches to the center
spar, and repair or modification of this
area if necessary. The NPRM also
proposed to reduce the inspection
compliance time and repetitive
inspection intervals. We are issuing this
AD to detect and correct this fatigue
cracking, which could reduce the
residual strength of the top skin of the
wings, and consequently affect the
structural integrity of the airframe.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0221, dated September
19, 2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain 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:
During fatigue tests conducted in the early
1990’s, cracks were found on the top skin of
the wing at the centre spar joint between ribs
1 and 7.
Consequently, Airbus developed
production mod. 10089 and issued Service
Bulletin (SB) A300–57–6041, involving
installation of a reinforcing plate on the
affected area. Despite this improvement,
subsequent cases of cracks were reported by
operators.
This condition, if not detected and
corrected, could adversely affect the
structural integrity of the aeroplane.
To address this potential unsafe condition,
Airbus issued SB A300–57–6044 and DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued * * * [an airworthiness
directive] (later revised twice) to require
repetitive inspections of the affected area
and, depending on findings, accomplishment
of applicable corrective action(s).
Since [the French] * * * [airworthiness
directive] [which corresponds to FAA AD
97–20–07, Amendment 39–10145 (62 FR
50251, September 25, 1997)] was issued, a
fleet survey and updated Fatigue and Damage
Tolerance Analyses were performed in order
to substantiate the second A300–600
Extended Service Goal (ESG2) exercise. The
results of these analyses have shown that the
inspection thresholds and intervals must be
reduced to allow timely detection of these
cracks and accomplishment of an applicable
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corrective action. Prompted by these
findings, Airbus issued SB A300–57–6044
Revision 04 [dated August 19, 2011].
For the reasons described above, this
[EASA] AD retains the requirements of [the
French AD] * * * which is superseded, but
requires the repetitive inspections to be
accomplished at reduced thresholds and
intervals and, depending on findings,
corrective actions.
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–2015–
1426.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Changes Made to This Final Rule
Paragraph (m)(2) of the proposed AD
inadvertently included the corrective
action for the low frequency eddy
current (LFEC) inspections for cracking
specified in paragraphs (k) and (l) of the
proposed AD; however, the corrective
action in paragraph (m)(2) of this AD
applies only to the new high frequency
eddy current (HFEC) inspections
required by this AD. We have revised
paragraph (m)(2) of this AD to specify
the corrective action for the HFEC
inspections for cracking specified in
paragraphs (i), (j), and (m)(1) of this AD.
We have added new paragraph (m)(4) of
this AD to specify the corrective actions
for the LFEC inspections specified in
paragraphs (k) and (l) of this AD.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these 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 Service Bulletin
A300–57–6044, Revision 04, dated
August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
The service information describes
procedures for inspections to detect
fatigue cracking in the left and right
wings in the area where the top skin
attaches to the center spar, and repair or
modification of this area. This service
information is reasonably available
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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 47
airplanes of U.S. registry.
The actions required by AD 97–20–07,
and retained in this AD take about 3
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
97–20–07 is $255 per product.
We also estimate that it will take
about 5 work-hours per product to
comply with the new basic
requirements of this AD. The average
labor rate is $85 per work-hour. Based
on these figures, we estimate the cost of
this AD on U.S. operators to be $19,975,
or $425 per product
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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.
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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;
14:13 Apr 08, 2016
Jkt 238001
area where the top skin attaches to the center
spar. We are issuing this AD to detect and
correct this fatigue cracking, which could
reduce the residual strength of the top skin
of the wings, and consequently affect the
structural integrity of the airframe.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(g) Retained Repetitive Inspections and
Corrective Actions, With Revised Service
Information
This paragraph restates the requirements of
paragraph (a) of AD 97–20–07, with revised
service information. For airplanes on which
Airbus Modification 10089 has not been
installed: Prior to the accumulation of 18,000
total landings, or within 1,500 landings after
October 30, 1997 (the effective date of AD
97–20–07), whichever occurs later, conduct
either a detailed visual inspection or a high
frequency eddy current (HFEC) inspection to
detect fatigue cracking in the left and right
wings in the area where the top skin attaches
to the center spar between ribs 1 and 7, in
accordance with Airbus Service Bulletin
A300–57–6044, Revision 2, dated September
6, 1995, including Appendix 1, Revision 1,
dated November 25, 1994; or Airbus Service
Bulletin A300–57–6044, Revision 04, dated
August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011. As of the
effective date of this AD, use only Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
Accomplishment of the inspection required
by paragraph (i) of this AD terminates the
inspection requirements of this paragraph.
(1) If no cracking is detected, conduct
repetitive inspections thereafter at the
following intervals:
(i) If the immediately preceding inspection
was conducted using detailed visual
inspection techniques, conduct the next
inspection within 5,000 landings.
(ii) If the immediately preceding inspection
was conducted using HFEC techniques,
conduct the next inspection within 9,500
landings.
(2) If any cracking is detected or suspected
during any detailed visual inspection
required by the introductory text of
paragraph (g), paragraph (g)(1), or paragraph
(g)(3)(i) of this AD, prior to further flight,
confirm this finding and the length of this
cracking by conducting an HFEC inspection,
in accordance with Airbus Service Bulletin
A300–57–6044, Revision 2, dated September
6, 1995, including Appendix 1, Revision 1,
dated November 25, 1994; or Airbus Service
Bulletin A300–57–6044, Revision 04, dated
August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011. As of the
effective date of this AD, use only Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011. If no
cracking is confirmed during the HFEC
inspection, accomplish the repetitive
inspection required by paragraph (g)(1)(ii) of
this AD at the time specified in that
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
Authority for This Rulemaking
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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.
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
97–20–07, Amendment 39–10145 (62
FR 50251, September 25, 1997), and
adding the following new AD:
■
2016–07–17 Airbus: Amendment 39–18462.
Docket No. FAA–2015–1426; Directorate
Identifier 2013–NM–200–AD.
(a) Effective Date
This AD becomes effective May 16, 2016.
(b) Affected ADs
This AD replaces AD 97–20–07,
Amendment 39–10145 (62 FR 50251,
September 25, 1997) (‘‘AD 97–20–07’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers except those on
which Airbus Modification 10160 has been
done in production.
(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 determination
that the inspection compliance time and
repetitive inspection interval must be
reduced to allow timely detection of fatigue
cracking in the left and right wings in the
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(3) If any cracking is detected or confirmed
during any HFEC inspection required by the
introductory text of paragraph (g), paragraph
(g)(1), or paragraph (g)(2) of this AD:
(i) If the cracking is 75 millimeters (mm)
or less per rib bay, prior to further flight,
repair in accordance with Airbus Service
Bulletin A300–57–6044, Revision 2, dated
September 6, 1995, including Appendix 1,
Revision 1, dated November 25, 1994; or
Airbus Service Bulletin A300–57–6044,
Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated
August 19, 2011. As of the effective date of
this AD, use only Airbus Service Bulletin
A300–57–6044, Revision 04, dated August
19, 2011, including Appendix 01, Revision
04, dated August 19, 2011. Thereafter,
conduct repetitive detailed visual inspections
of the repaired area at intervals not to exceed
50 landings, in accordance with Airbus
Service Bulletin A300–57–6044, Revision 2,
dated September 6, 1995, including
Appendix 1, Revision 1, dated November 25,
1994; or Airbus Service Bulletin A300–57–
6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated
August 19, 2011. As of the effective date of
this AD, use only Airbus Service Bulletin
A300–57–6044, Revision 04, dated August
19, 2011, including Appendix 01, Revision
04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per rib
bay, prior to further flight, install Airbus
Modification 10089, in accordance with
Airbus Service Bulletin A300–57–6044,
Revision 2, dated September 6, 1995,
including Appendix 1, Revision 1, dated
November 25, 1994; or Airbus Service
Bulletin A300–57–6044, Revision 04, dated
August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011. As of the
effective date of this AD, use only Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
Thereafter, conduct a low frequency eddy
current (LFEC) inspection in accordance with
the requirements of paragraph (h) of this AD.
Note 1 to paragraph (g) of this AD: Airbus
Service Bulletin A300–57–6044, Revision 2,
dated September 6, 1995, including
Appendix 1, Revision 1, dated November 25,
1994, references Airbus Service Bulletin
A300–57–6041, Revision 4, dated November
16, 1995, as an additional source of guidance
for installing Airbus Modification 10089.
(h) Retained Repetitive Inspections and
Corrective Actions for Certain Airplanes,
With Revised Service Information and
Repair Instructions
This paragraph restates the requirements of
paragraph (b) of AD 97–20–07, with revised
service information and repair instructions.
For airplanes on which Airbus Modification
10089 has been installed: Prior to the
accumulation of 22,000 total landings after
this modification has been installed, or
within 1,500 landings after October 30, 1997
(the effective date of AD 97–20–07),
whichever occurs later, conduct a LFEC
inspection to detect fatigue cracking in the
inboard and rear edges of the top skin
reinforcing plates, in accordance with Airbus
Service Bulletin A300–57–6044, Revision 2,
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dated September 6, 1995, including
Appendix 1, Revision 1, dated November 25,
1994; or Airbus Service Bulletin A300–57–
6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated
August 19, 2011. As of the effective date of
this AD, use only Airbus Service Bulletin
A300–57–6044, Revision 04, dated August
19, 2011, including Appendix 01, Revision
04, dated August 19, 2011. Accomplishment
of the inspection required by paragraph (k) of
this AD terminates the inspection
requirements of this paragraph.
(1) If no cracking is detected, repeat this
inspection thereafter at intervals not to
exceed 11,000 landings.
(2) If any cracking is detected, prior to
further flight, repair in accordance with a
method approved by the Manager,
Standardization Branch, ANM–113,
Transport Airplane Directorate, FAA. As of
the effective date of this AD, repair using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
Thereafter, repeat this inspection at intervals
not to exceed 11,000 landings.
(i) New Requirement of This AD: Initial
Inspections
For airplanes on which Airbus
Modification 10089 has not been installed: At
the applicable time specified in paragraphs
(i)(1) and (i)(2) of this AD, do either a
detailed visual inspection or an HFEC
inspection to detect fatigue cracking in the
left and right wings in the area where the top
skin attaches to the center spar between ribs
1 and 7, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
Accomplishment of the inspection required
by this paragraph terminates the inspection
requirements of paragraph (g) of this AD.
(1) For airplanes whose flight time average
is equal to or more than 1.5 hours, at the later
of the times specified in paragraphs (i)(1)(i)
and (i)(1)(ii) of this AD.
(i) Before the accumulation of 14,000 total
flight cycles or 30,300 total flight hours,
whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200
flight hours after the effective date of this AD,
whichever occurs first.
(2) For airplanes whose flight time average
is less than 1.5 hours, at the later of the times
specified in paragraphs (i)(2)(i) and (i)(2)(ii)
of this AD.
(i) Before the accumulation of 15,100 total
flight cycles or 22,700 total flight hours,
whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500
flight hours after the effective date of this AD,
whichever occurs first.
(j) New Requirement of This AD: Repetitive
Inspections
Repeat the inspections specified in
paragraph (i) of this AD thereafter at the
applicable interval specified in paragraphs
(j)(1) and (j)(2) of this AD.
(1) For airplanes whose flight time average
is equal to or more than 1.5 hours, at the
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Fmt 4700
Sfmt 4700
21249
applicable interval specified in paragraphs
(j)(1)(i) and (j)(1)(ii) of this AD.
(i) For a detailed visual inspection, at
intervals not to exceed 3,900 flight cycles or
8,400 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals
not to exceed 7,400 flight cycles or 16,000
flight hours, whichever occurs first.
(2) For airplanes whose flight time average
is less than 1.5 hours, at the applicable
interval specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD.
(i) For a detailed visual inspection, at
intervals not to exceed 4,200 flight cycles or
6,300 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals
not to exceed 8,000 flight cycles or 11,900
flight hours, whichever occurs first.
(k) New Requirement of This AD: Initial
Inspection for Certain Airplanes
For airplanes on which Airbus
Modification 10089 has been installed: At the
applicable time specified in paragraphs (k)(1)
and (k)(2) of this AD, do an LFEC inspection
to detect fatigue cracking in the inboard and
rear edges of the top skin reinforcing plates,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated
August 19, 2011. Accomplishment of the
inspection required by this paragraph
terminates the inspection requirements of
paragraph (h) of this AD.
(1) For airplanes whose flight time average
is equal to or more than 1.5 hours, at the later
of the times specified in paragraphs (k)(1)(i)
and (k)(1)(ii) of this AD.
(i) Before the accumulation of 17,000 total
flight cycles or 37,100 total flight hours,
whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200
flight hours after the effective date of this AD,
whichever occurs first.
(2) For airplanes whose flight time average
is less than 1.5 hours, at the later of the times
specified in paragraphs (k)(2)(i) and (k)(2)(ii)
of this AD.
(i) Before the accumulation of 18,500 total
flight cycles or 27,800 total flight hours,
whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500
flight hours after the effective date of this AD,
whichever occurs first.
(l) New Requirement of This AD: Repetitive
Inspections for Certain Airplanes
Repeat the inspection specified in
paragraph (k) of this AD thereafter at the
applicable interval specified in paragraphs
(l)(1) and (l)(2) of this AD.
(1) For airplanes whose flight time average
is equal to or more than 1.5 hours, at
intervals not to exceed 8,500 flight cycles or
18,500 flight hours, whichever occurs first.
(2) For airplanes whose flight time average
is less than 1.5 hours, at intervals not to
exceed 9,200 flight cycles or 13,700 flight
hours, whichever occurs first.
(m) New Requirement of This AD: Corrective
Actions
(1) If any cracking is detected or suspected
during any detailed inspection required by
paragraph (i) or (j) of this AD: Before further
flight, confirm this finding and the length of
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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
this cracking by conducting an HFEC
inspection, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011,
except as specified in paragraph (o) of this
AD. If no cracking is confirmed during the
HFEC inspection, accomplish the applicable
repetitive inspections required by paragraphs
(j) and (l) of this AD at the applicable time
specified in those paragraphs.
(2) If any cracking is found during any
HFEC inspection required by paragraph (i),
(j), or (m)(1) of this AD: Before further flight,
do the applicable actions specified in
paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) If the cracking is 75 mm or less per each
rib bay: Before further flight, repair the
cracking, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011,
except as specified in paragraph (o) of this
AD. Do repetitive detailed inspections of the
repaired area thereafter at intervals not to
exceed 50 flight cycles or 110 flight hours,
whichever occurs first, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
Within 250 flight cycles or 550 flight hours,
whichever occurs first after doing the
temporary repair, do a permanent repair of
the repaired area, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per any
rib bay: Before further flight, install Airbus
Modification 10089, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011. Do
an LFEC inspection thereafter at the intervals
specified in paragraph (l) of this AD.
(3) If any cracking is found during any
inspection required by this AD at fastener
hole 1A, 1, or 2: Before further flight, repair
the cracking, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011.
(4) If any cracking is found during any
LFEC inspection required by paragraph (k) or
(l) 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.
jstallworth on DSK7TPTVN1PROD with RULES
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (i) through (l) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A300–57–6044, Revision 03,
dated April 7, 1999, including Appendix 01,
Revision 03, dated April 7, 1999, which is
not incorporated by reference in this AD.
VerDate Sep<11>2014
14:13 Apr 08, 2016
Jkt 238001
(o) Exception to Service Information
Specification
Although Airbus Service Bulletin A300–
57–6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated
August 19, 2011, specifies to submit
information to Airbus, this AD does not
require that submission.
(p) 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. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0221, dated
September 19, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–1426.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(5) and (r)(6) of this AD.
(r) 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 A300–57–6044,
Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated
August 19, 2011.
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Frm 00028
Fmt 4700
Sfmt 4700
(ii) Reserved.
(4) The following service information was
approved for IBR on October 30, 1997 (62 FR
50251, September 25, 1997).
(i) Airbus Service Bulletin A300–57–6044,
Revision 2, dated September 6, 1995,
including Appendix 1, Revision 1, dated
November 25, 1994. Pages 1 through 8 of this
document are identified as Revision 2, dated
September 6, 1995; pages 9 and 10 are
identified as original, dated March 1, 1993.
Page 1 of Appendix 1 is identified as
Revision 1, dated November 25, 1994; and
pages 2 through 6 are identified as original,
dated March 1, 1993.
(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.airwortheas@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. 2016–07574 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–2016–5457; Directorate
Identifier 2016–CE–008–AD; Amendment
39–18469; AD 2016–07–24]
RIN 2120–AA64
Airworthiness Directives; Textron
Aviation, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Textron Aviation, Inc. Models 310
through 310R, E310H, E310J, T310P
through T310R, 310J–1, 320 through
320F, 320–1, 335, 340, 340A, 401
through 401B, 402 through 402C, 411,
411A, 414, 414A, and 421 through 421C
SUMMARY:
E:\FR\FM\11APR1.SGM
11APR1
]]>Agencies
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21246-21250]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07574]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-AD;
Amendment 39-18462; AD 2016-07-17]
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) 97-20-07 for
certain 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). AD 97-20-07 required
repetitive inspections to detect fatigue cracking in the left and right
wings in the area where the top skin attaches to the center spar, and
repair or modification of this area if necessary. This new AD reduces
the inspection compliance time and repetitive inspection intervals.
This AD was prompted by a determination that the inspection compliance
time and repetitive inspection interval must be reduced to allow timely
detection of fatigue cracking in the left and right wings in the area
where the top skin attaches to the center spar. We are issuing this AD
to detect and correct this fatigue cracking, which could reduce the
residual strength of the top skin of the wings, and consequently
[[Page 21247]]
affect the structural integrity of the airframe.
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 30, 1997 (62 FR 50251, September 25, 1997).
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.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-
1426.
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-2015-
1426; 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.
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 97-20-07, Amendment 39-10145 (62 FR 50251,
September 25, 1997) (``AD 97-20-07''). AD 97-20-07 applied to certain
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 NPRM published in the Federal Register on
June 5, 2015 (80 FR 32058) (``the NPRM''). The NPRM was prompted by a
determination that the inspection compliance time and repetitive
inspection interval must be reduced to allow timely detection of
fatigue cracking in the left and right wings in the area where the top
skin attaches to the center spar. The NPRM proposed to continue to
require repetitive inspections to detect fatigue cracking in the left
and right wings in the area where the top skin attaches to the center
spar, and repair or modification of this area if necessary. The NPRM
also proposed to reduce the inspection compliance time and repetitive
inspection intervals. We are issuing this AD to detect and correct this
fatigue cracking, which could reduce the residual strength of the top
skin of the wings, and consequently affect the structural integrity of
the airframe.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0221, dated September 19, 2013 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain 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:
During fatigue tests conducted in the early 1990's, cracks were
found on the top skin of the wing at the centre spar joint between
ribs 1 and 7.
Consequently, Airbus developed production mod. 10089 and issued
Service Bulletin (SB) A300-57-6041, involving installation of a
reinforcing plate on the affected area. Despite this improvement,
subsequent cases of cracks were reported by operators.
This condition, if not detected and corrected, could adversely
affect the structural integrity of the aeroplane.
To address this potential unsafe condition, Airbus issued SB
A300-57-6044 and DGAC [Direction G[eacute]n[eacute]rale de
l'Aviation Civile] France issued * * * [an airworthiness directive]
(later revised twice) to require repetitive inspections of the
affected area and, depending on findings, accomplishment of
applicable corrective action(s).
Since [the French] * * * [airworthiness directive] [which
corresponds to FAA AD 97-20-07, Amendment 39-10145 (62 FR 50251,
September 25, 1997)] was issued, a fleet survey and updated Fatigue
and Damage Tolerance Analyses were performed in order to
substantiate the second A300-600 Extended Service Goal (ESG2)
exercise. The results of these analyses have shown that the
inspection thresholds and intervals must be reduced to allow timely
detection of these cracks and accomplishment of an applicable
corrective action. Prompted by these findings, Airbus issued SB
A300-57-6044 Revision 04 [dated August 19, 2011].
For the reasons described above, this [EASA] AD retains the
requirements of [the French AD] * * * which is superseded, but
requires the repetitive inspections to be accomplished at reduced
thresholds and intervals and, depending on findings, corrective
actions.
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-2015-
1426.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Changes Made to This Final Rule
Paragraph (m)(2) of the proposed AD inadvertently included the
corrective action for the low frequency eddy current (LFEC) inspections
for cracking specified in paragraphs (k) and (l) of the proposed AD;
however, the corrective action in paragraph (m)(2) of this AD applies
only to the new high frequency eddy current (HFEC) inspections required
by this AD. We have revised paragraph (m)(2) of this AD to specify the
corrective action for the HFEC inspections for cracking specified in
paragraphs (i), (j), and (m)(1) of this AD. We have added new paragraph
(m)(4) of this AD to specify the corrective actions for the LFEC
inspections specified in paragraphs (k) and (l) of this AD.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD with the changes described
previously and minor editorial changes. We have determined that these
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 Service Bulletin A300-57-6044, Revision 04, dated
August 19, 2011, including Appendix 01, Revision 04, dated August 19,
2011. The service information describes procedures for inspections to
detect fatigue cracking in the left and right wings in the area where
the top skin attaches to the center spar, and repair or modification of
this area. This service information is reasonably available
[[Page 21248]]
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 47 airplanes of U.S. registry.
The actions required by AD 97-20-07, and retained in this AD take
about 3 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 97-20-07 is $255 per product.
We also estimate that it will take about 5 work-hours per product
to comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $19,975, or $425 per product
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
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.
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)
97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and
adding the following new AD:
2016-07-17 Airbus: Amendment 39-18462. Docket No. FAA-2015-1426;
Directorate Identifier 2013-NM-200-AD.
(a) Effective Date
This AD becomes effective May 16, 2016.
(b) Affected ADs
This AD replaces AD 97-20-07, Amendment 39-10145 (62 FR 50251,
September 25, 1997) (``AD 97-20-07'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers except those on which Airbus
Modification 10160 has been done in production.
(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 determination that the inspection
compliance time and repetitive inspection interval must be reduced
to allow timely detection of fatigue cracking in the left and right
wings in the area where the top skin attaches to the center spar. We
are issuing this AD to detect and correct this fatigue cracking,
which could reduce the residual strength of the top skin of the
wings, and consequently affect the structural integrity of the
airframe.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections and Corrective Actions, With
Revised Service Information
This paragraph restates the requirements of paragraph (a) of AD
97-20-07, with revised service information. For airplanes on which
Airbus Modification 10089 has not been installed: Prior to the
accumulation of 18,000 total landings, or within 1,500 landings
after October 30, 1997 (the effective date of AD 97-20-07),
whichever occurs later, conduct either a detailed visual inspection
or a high frequency eddy current (HFEC) inspection to detect fatigue
cracking in the left and right wings in the area where the top skin
attaches to the center spar between ribs 1 and 7, in accordance with
Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6,
1995, including Appendix 1, Revision 1, dated November 25, 1994; or
Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19,
2011, including Appendix 01, Revision 04, dated August 19, 2011. As
of the effective date of this AD, use only Airbus Service Bulletin
A300-57-6044, Revision 04, dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011. Accomplishment of the
inspection required by paragraph (i) of this AD terminates the
inspection requirements of this paragraph.
(1) If no cracking is detected, conduct repetitive inspections
thereafter at the following intervals:
(i) If the immediately preceding inspection was conducted using
detailed visual inspection techniques, conduct the next inspection
within 5,000 landings.
(ii) If the immediately preceding inspection was conducted using
HFEC techniques, conduct the next inspection within 9,500 landings.
(2) If any cracking is detected or suspected during any detailed
visual inspection required by the introductory text of paragraph
(g), paragraph (g)(1), or paragraph (g)(3)(i) of this AD, prior to
further flight, confirm this finding and the length of this cracking
by conducting an HFEC inspection, in accordance with Airbus Service
Bulletin A300-57-6044, Revision 2, dated September 6, 1995,
including Appendix 1, Revision 1, dated November 25, 1994; or Airbus
Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated August 19, 2011. As of the
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011. If no cracking is confirmed
during the HFEC inspection, accomplish the repetitive inspection
required by paragraph (g)(1)(ii) of this AD at the time specified in
that paragraph.
[[Page 21249]]
(3) If any cracking is detected or confirmed during any HFEC
inspection required by the introductory text of paragraph (g),
paragraph (g)(1), or paragraph (g)(2) of this AD:
(i) If the cracking is 75 millimeters (mm) or less per rib bay,
prior to further flight, repair in accordance with Airbus Service
Bulletin A300-57-6044, Revision 2, dated September 6, 1995,
including Appendix 1, Revision 1, dated November 25, 1994; or Airbus
Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated August 19, 2011. As of the
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011. Thereafter, conduct repetitive
detailed visual inspections of the repaired area at intervals not to
exceed 50 landings, in accordance with Airbus Service Bulletin A300-
57-6044, Revision 2, dated September 6, 1995, including Appendix 1,
Revision 1, dated November 25, 1994; or Airbus Service Bulletin
A300-57-6044, Revision 04, dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011. As of the effective date of
this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04,
dated August 19, 2011, including Appendix 01, Revision 04, dated
August 19, 2011.
(ii) If the cracking exceeds 75 mm per rib bay, prior to further
flight, install Airbus Modification 10089, in accordance with Airbus
Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995,
including Appendix 1, Revision 1, dated November 25, 1994; or Airbus
Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011,
including Appendix 01, Revision 04, dated August 19, 2011. As of the
effective date of this AD, use only Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011. Thereafter, conduct a low
frequency eddy current (LFEC) inspection in accordance with the
requirements of paragraph (h) of this AD.
Note 1 to paragraph (g) of this AD: Airbus Service Bulletin
A300-57-6044, Revision 2, dated September 6, 1995, including
Appendix 1, Revision 1, dated November 25, 1994, references Airbus
Service Bulletin A300-57-6041, Revision 4, dated November 16, 1995,
as an additional source of guidance for installing Airbus
Modification 10089.
(h) Retained Repetitive Inspections and Corrective Actions for Certain
Airplanes, With Revised Service Information and Repair Instructions
This paragraph restates the requirements of paragraph (b) of AD
97-20-07, with revised service information and repair instructions.
For airplanes on which Airbus Modification 10089 has been installed:
Prior to the accumulation of 22,000 total landings after this
modification has been installed, or within 1,500 landings after
October 30, 1997 (the effective date of AD 97-20-07), whichever
occurs later, conduct a LFEC inspection to detect fatigue cracking
in the inboard and rear edges of the top skin reinforcing plates, in
accordance with Airbus Service Bulletin A300-57-6044, Revision 2,
dated September 6, 1995, including Appendix 1, Revision 1, dated
November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision
04, dated August 19, 2011, including Appendix 01, Revision 04, dated
August 19, 2011. As of the effective date of this AD, use only
Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19,
2011, including Appendix 01, Revision 04, dated August 19, 2011.
Accomplishment of the inspection required by paragraph (k) of this
AD terminates the inspection requirements of this paragraph.
(1) If no cracking is detected, repeat this inspection
thereafter at intervals not to exceed 11,000 landings.
(2) If any cracking is detected, prior to further flight, repair
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113, Transport Airplane Directorate, FAA. As of the
effective date of this AD, repair using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). Thereafter, repeat
this inspection at intervals not to exceed 11,000 landings.
(i) New Requirement of This AD: Initial Inspections
For airplanes on which Airbus Modification 10089 has not been
installed: At the applicable time specified in paragraphs (i)(1) and
(i)(2) of this AD, do either a detailed visual inspection or an HFEC
inspection to detect fatigue cracking in the left and right wings in
the area where the top skin attaches to the center spar between ribs
1 and 7, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19,
2011, including Appendix 01, Revision 04, dated August 19, 2011.
Accomplishment of the inspection required by this paragraph
terminates the inspection requirements of paragraph (g) of this AD.
(1) For airplanes whose flight time average is equal to or more
than 1.5 hours, at the later of the times specified in paragraphs
(i)(1)(i) and (i)(1)(ii) of this AD.
(i) Before the accumulation of 14,000 total flight cycles or
30,300 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200 flight hours after the
effective date of this AD, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5
hours, at the later of the times specified in paragraphs (i)(2)(i)
and (i)(2)(ii) of this AD.
(i) Before the accumulation of 15,100 total flight cycles or
22,700 total flight hours, whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500 flight hours after the
effective date of this AD, whichever occurs first.
(j) New Requirement of This AD: Repetitive Inspections
Repeat the inspections specified in paragraph (i) of this AD
thereafter at the applicable interval specified in paragraphs (j)(1)
and (j)(2) of this AD.
(1) For airplanes whose flight time average is equal to or more
than 1.5 hours, at the applicable interval specified in paragraphs
(j)(1)(i) and (j)(1)(ii) of this AD.
(i) For a detailed visual inspection, at intervals not to exceed
3,900 flight cycles or 8,400 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals not to exceed 7,400
flight cycles or 16,000 flight hours, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5
hours, at the applicable interval specified in paragraphs (j)(2)(i)
and (j)(2)(ii) of this AD.
(i) For a detailed visual inspection, at intervals not to exceed
4,200 flight cycles or 6,300 flight hours, whichever occurs first.
(ii) For an HFEC inspection, at intervals not to exceed 8,000
flight cycles or 11,900 flight hours, whichever occurs first.
(k) New Requirement of This AD: Initial Inspection for Certain
Airplanes
For airplanes on which Airbus Modification 10089 has been
installed: At the applicable time specified in paragraphs (k)(1) and
(k)(2) of this AD, do an LFEC inspection to detect fatigue cracking
in the inboard and rear edges of the top skin reinforcing plates, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including
Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of
the inspection required by this paragraph terminates the inspection
requirements of paragraph (h) of this AD.
(1) For airplanes whose flight time average is equal to or more
than 1.5 hours, at the later of the times specified in paragraphs
(k)(1)(i) and (k)(1)(ii) of this AD.
(i) Before the accumulation of 17,000 total flight cycles or
37,100 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,200 flight hours after the
effective date of this AD, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5
hours, at the later of the times specified in paragraphs (k)(2)(i)
and (k)(2)(ii) of this AD.
(i) Before the accumulation of 18,500 total flight cycles or
27,800 total flight hours, whichever occurs first.
(ii) Within 1,600 flight cycles or 2,500 flight hours after the
effective date of this AD, whichever occurs first.
(l) New Requirement of This AD: Repetitive Inspections for Certain
Airplanes
Repeat the inspection specified in paragraph (k) of this AD
thereafter at the applicable interval specified in paragraphs (l)(1)
and (l)(2) of this AD.
(1) For airplanes whose flight time average is equal to or more
than 1.5 hours, at intervals not to exceed 8,500 flight cycles or
18,500 flight hours, whichever occurs first.
(2) For airplanes whose flight time average is less than 1.5
hours, at intervals not to exceed 9,200 flight cycles or 13,700
flight hours, whichever occurs first.
(m) New Requirement of This AD: Corrective Actions
(1) If any cracking is detected or suspected during any detailed
inspection required by paragraph (i) or (j) of this AD: Before
further flight, confirm this finding and the length of
[[Page 21250]]
this cracking by conducting an HFEC inspection, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-57-
6044, Revision 04, dated August 19, 2011, including Appendix 01,
Revision 04, dated August 19, 2011, except as specified in paragraph
(o) of this AD. If no cracking is confirmed during the HFEC
inspection, accomplish the applicable repetitive inspections
required by paragraphs (j) and (l) of this AD at the applicable time
specified in those paragraphs.
(2) If any cracking is found during any HFEC inspection required
by paragraph (i), (j), or (m)(1) of this AD: Before further flight,
do the applicable actions specified in paragraphs (m)(2)(i) and
(m)(2)(ii) of this AD.
(i) If the cracking is 75 mm or less per each rib bay: Before
further flight, repair the cracking, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6044,
Revision 04, dated August 19, 2011, including Appendix 01, Revision
04, dated August 19, 2011, except as specified in paragraph (o) of
this AD. Do repetitive detailed inspections of the repaired area
thereafter at intervals not to exceed 50 flight cycles or 110 flight
hours, whichever occurs first, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6044, Revision 04,
dated August 19, 2011, including Appendix 01, Revision 04, dated
August 19, 2011. Within 250 flight cycles or 550 flight hours,
whichever occurs first after doing the temporary repair, do a
permanent repair of the repaired area, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6044,
Revision 04, dated August 19, 2011, including Appendix 01, Revision
04, dated August 19, 2011.
(ii) If the cracking exceeds 75 mm per any rib bay: Before
further flight, install Airbus Modification 10089, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-57-6044, Revision 04, dated August 19, 2011, including Appendix
01, Revision 04, dated August 19, 2011. Do an LFEC inspection
thereafter at the intervals specified in paragraph (l) of this AD.
(3) If any cracking is found during any inspection required by
this AD at fastener hole 1A, 1, or 2: Before further flight, repair
the cracking, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19,
2011, including Appendix 01, Revision 04, dated August 19, 2011.
(4) If any cracking is found during any LFEC inspection required
by paragraph (k) or (l) 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.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (i) through (l) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A300-57-6044, Revision 03, dated April 7, 1999, including
Appendix 01, Revision 03, dated April 7, 1999, which is not
incorporated by reference in this AD.
(o) Exception to Service Information Specification
Although Airbus Service Bulletin A300-57-6044, Revision 04,
dated August 19, 2011, including Appendix 01, Revision 04, dated
August 19, 2011, specifies to submit information to Airbus, this AD
does not require that submission.
(p) 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. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0221, dated September 19,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-1426.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(5) and (r)(6) of this AD.
(r) 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 A300-57-6044, Revision 04, dated
August 19, 2011, including Appendix 01, Revision 04, dated August
19, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
October 30, 1997 (62 FR 50251, September 25, 1997).
(i) Airbus Service Bulletin A300-57-6044, Revision 2, dated
September 6, 1995, including Appendix 1, Revision 1, dated November
25, 1994. Pages 1 through 8 of this document are identified as
Revision 2, dated September 6, 1995; pages 9 and 10 are identified
as original, dated March 1, 1993. Page 1 of Appendix 1 is identified
as Revision 1, dated November 25, 1994; and pages 2 through 6 are
identified as original, dated March 1, 1993.
(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. 2016-07574 Filed 4-8-16; 8:45 am]
BILLING CODE 4910-13-P
