Airworthiness Directives; Airbus Airplanes, 63370-63374 [2016-21146]
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63370
Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations
(j) Modification of Overhead Stowage
Compartments and Re-Identification of Part
Number
Within 4 months after the effective date of
this AD: Modify the overhead stowage
compartments, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraphs (j)(1) through (j)(4) of this AD.
(1) For airplanes identified in ATR Service
Bulletin ATR42–25–0185, dated November
21, 2014: ATR Service Bulletin ATR42–25–
0185, dated November 21, 2014.
(2) For airplanes identified in ATR Service
Bulletin ATR42–25–0186, dated November
21, 2014: ATR Service Bulletin ATR42–25–
0186, dated November 21, 2014.
(3) For airplanes identified in ATR Service
Bulletin ATR72–25–1148, dated November
21, 2014: ATR Service Bulletin ATR72–25–
1148, dated November 21, 2014.
(4) For airplanes identified in ATR Service
Bulletin ATR72–25–1149, dated November
21, 2014: ATR Service Bulletin ATR72–25–
1149, dated November 21, 2014.
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(k) 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:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; 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.
(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
EASA; or ATR—GIE Avions de Transport
´
Regional’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0018, dated
February 5, 2015, 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–2015–0077.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(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) ATR Service Bulletin ATR42–25–0180,
dated August 19, 2013.
(ii) ATR Service Bulletin ATR42–25–0185,
dated November 21, 2014.
(iii) ATR Service Bulletin ATR42–25–0186,
dated November 21, 2014.
(iv) ATR Service Bulletin ATR72–25–1141,
dated August 19, 2013.
(v) ATR Service Bulletin ATR72–25–1148,
dated November 21, 2014.
(vi) ATR Service Bulletin ATR72–25–1149,
dated November 21, 2014.
(3) For service information identified in
this AD, contact ATR—GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atr.fr;
Internet https://www.aerochain.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 August
25, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–21292 Filed 9–14–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–6550; Directorate
Identifier 2013–NM–162–AD; Amendment
39–18638; AD 2016–18–08]
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) 90–11–05
for certain Airbus Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and
B4–203 airplanes and Model A300 B4–
600 series airplanes. AD 90–11–05
required repetitive detailed inspections
SUMMARY:
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for cracking in the aft hinge brackets of
the outer shroud box that is located in
the outer wing box, and related
investigative and corrective actions if
necessary. This new AD changes certain
compliance times and adds airplanes to
the applicability. This AD was
prompted by reports of cracks in the aft
hinge brackets of the outer shroud box
that is located in the outer wing box,
which were found during routine
maintenance checks, and our
subsequent determination that a change
in inspection compliance times is
needed. We are issuing this AD to detect
and correct cracking of the aft hinge
brackets of the outer shroud box; such
cracking could affect the structural
integrity of the airplane.
DATES: This AD becomes effective
October 20, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 20, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.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–2015–6550.
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–
6550; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
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98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 90–11–05,
Amendment 39–6603 (89–NM–223–AD)
(55 FR 20129, May 15, 1990) (‘‘AD 90–
11–05’’). AD 90–11–05 applied to
certain Airbus Model A300 B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and
B4 203 airplanes and Model A300 B4–
600 series airplanes. The NPRM
published in the Federal Register on
December 14, 2015 (80 FR 77279) (‘‘the
NPRM’’). The NPRM was prompted by
a determination that a change to certain
compliance times is needed. The NPRM
proposed to continue to require doing
repetitive detailed inspections for
cracking in the hinge brackets of the
forward and aft outer shroud boxes that
are located in the outer wing box, and
related investigative and corrective
actions if necessary. The NPRM also
proposed to change certain compliance
times and add airplanes to the
applicability. We are issuing this AD to
detect and correct cracking of the aft
hinge brackets of the outer shroud box;
such cracking could affect the structural
integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2013–0181R1, dated August
20, 2013 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Model
A300 series airplanes and Model A300
B4–600 series airplanes. The MCAI
states:
In the past, aft hinge brackets of the outer
wing box were found cracked. Fracture of a
bracket would allow vertical movement of
the inner shroud box structure, which could
result in damage to the top skin of the
inboard flap. In addition, the loads carried by
the brackets will be transferred to the
remaining supports, which may also crack
and cause extensive structural damage.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this potential unsafe condition,
´ ´
DGAC [Direction Generale de l’Aviation
Civile] France issued * * * [an airworthiness
directive] (later revised) to require repetitive
inspections of the hinge bracket of the outer
box and, depending on findings, corrective
action(s).
Since that [DGAC] AD was issued, a fleet
survey and updated Fatigue and Damage
Tolerance analysis were performed in order
to substantiate the A300 Extended Service
Goal (ESG) and A300–600 Extended Service
Goal (ESG2) exercise.
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The results of these analyses led to a
change in the inspection thresholds and
intervals in Flight Cycles (FC) and the
introduction of Flight Hours (FH) limits.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France * * * [an airworthiness directive],
which is superseded, but requires those
actions within the new thresholds and
intervals given by Airbus Service Bulletin
(SB) A300–57–0142 Revision 04 or A300–57–
6010 Revision 05, as applicable to aeroplane
model.
Revision 1 of this [EASA] AD is issued to
add model A300 B4–203 aeroplanes to the
applicability and compliance time tables.
This model is covered by Airbus SB A300–
57–0142, but was mistakenly omitted from
the original [EASA] AD issue.
The corrective action for a hinge
bracket that is cracked or fractured is
replacing the damaged hinge bracket
with a new bracket.
For airplanes on which a crack is
found in one half bracket or both half
brackets, related investigative actions
include a general visual inspection for
secondary damage (e.g., cracks, wear
damage, pitting, and gouging) in the
following areas:
• The inner shroud-box forward
attachments and the attachment
brackets at the inboard end.
• The inner and outer shroud-box
structure, adjacent to the fractured
bracket.
• The top skin of the inboard flap.
The corrective action for damage
findings during the related investigative
action is repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s
EASA Design Organization Approval
(DOA).
The compliance time for related
investigative actions and corrective
actions is before further flight.
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–
6550.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response to the comment.
Request To Exclude Certain Airplanes
From the Applicability
FedEx requested that we exclude from
the proposed applicability airplanes on
which the actions specified in Airbus
Service Bulletin A300–57–6011,
Revision 2, dated July 10, 1989, have
been accomplished. FedEx stated that it
has accomplished the optional
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63371
terminating actions provided in
paragraph (j)(1) of the proposed AD, and
specified in Airbus Service Bulletin
A300–57–6011, Revision 2, dated July
10, 1989, on several of its airplanes.
We disagree with FedEx’s request. As
of the effective date of this AD,
additional actions are required for
airplanes on which the optional
modification has been accomplished.
These airplanes will need to have a onetime detailed visual inspection of the
forward and aft outer shroud box with
no cracking found, as required by
paragraph (j)(2) of this AD. We have not
changed this AD in this regard.
Changes Made to This AD
In paragraph (j)(2) of the proposed
AD, we proposed to provide an optional
method of compliance (i.e., a
replacement and a one-time inspection)
for actions specified in paragraph (g) of
the proposed AD. We also proposed to
give credit in paragraph (k)(2) of the
proposed AD for replacements
accomplished before the effective date
of this AD using the same service
information identified in paragraph
(j)(2) of the AD:
• Airbus Service Bulletin A300–57–
143, dated December 17, 1986.
• Airbus Service Bulletin A300–57–
143, Revision 1, dated March 19, 1987.
• Airbus Service Bulletin A300–57–
6011, dated December 17, 1986.
• Airbus Service Bulletin A300–57–
6011, Revision 1, dated March 19, 1987.
Since we cannot make this service
information reasonably available, we
have revised paragraph (j)(2) of the
proposed AD, removed redundant
paragraph (k)(2) of the proposed AD
from this AD, and redesignated
paragraph (k)(1) and subsequent
subparagraphs accordingly. We revised
paragraph (j)(2) of this AD by removing
the references to the service information
and instead specified that operators
must do the replacement using a
method approved by the Manager,
International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA Design
Organization Approval (DOA).
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
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Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations
• Airbus Service Bulletin A300–57–
143, Revision 2, dated July 10, 1989,
which describes procedures for
replacing the aft aluminum alloy
brackets on the outer shroud box with
new steel brackets.
• Airbus Service Bulletin A300–57–
6010, Revision 05, dated February 21,
2011, which describes procedures for
doing an inspection of the forward and
aft hinge brackets on the outer shroud
box.
• Airbus Service Bulletin A300–57–
6011, Revision 2, dated July 10, 1989,
which describes procedures for
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A300–57–
0142, Revision 04, dated March 30,
2011, which describes procedures for
doing an inspection of the forward and
aft hinge brackets on the outer shroud
box.
replacing the aft aluminum alloy
brackets on the outer shroud box with
new steel brackets.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 3
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ......................
8 work-hours × $85 per hour = $680 per inspection cycle.
We estimate the following costs to do
any necessary replacements that would
Parts cost
Cost per product
$0
Cost on U.S. operators
$680 per inspection
cycle.
be required based on the results of the
inspection. We have no way of
$2,040 per inspection
cycle.
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Replacement ....................................
27 work-hours × $85 per hour = $2,295 ...................................................
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition related
investigative and corrective 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
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Parts cost
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:
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$25,650
Cost per
product
$27,945
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)
90–11–05, Amendment 39–6603 (89–
NM–223–AD) (55 FR 20129, May 15,
1990), and adding the following new
AD:
■
2016–18–08 Airbus: Amendment 39–18638.
Docket No. FAA–2015–6550; Directorate
Identifier 2013–NM–162–AD.
(a) Effective Date
This AD becomes effective October 20,
2016.
(b) Affected ADs
This AD replaces AD 90–11–05,
Amendment 39–6603 (89–NM–223–AD) (55
FR 20129, May 15, 1990).
(c) Applicability
This AD applies to Airbus Model A300 B2–
1C, B2K–3C, B2–203, B4–2C, B4–103, and
B4–203 airplanes; Model A300 B4–601, B4–
603, B4–620, and B4–622 airplanes; and
Model A300 B4–605R airplanes; certificated
in any category; except airplanes on which
Airbus Modification 6661 has been embodied
during production.
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks
in the aft hinge brackets of the outer shroud
box that is located in the outer wing box,
which were found during routine
maintenance checks, and our subsequent
determination that a change in inspection
compliance times is needed. We are issuing
this AD to detect and correct cracking of the
aft hinge brackets of the outer shroud box;
such cracking could affect the structural
integrity of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
At the applicable compliance time
specified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD: Do a detailed inspection for
cracks and fractures of the hinge brackets of
the forward and aft outer shroud boxes, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0142, Revision 04, dated March 30, 2011;
or Airbus Service Bulletin A300–57–6010,
Revision 05, dated February 21, 2011; as
applicable. Repeat the inspection thereafter
at the applicable interval specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–0142, Revision 04, dated March 30, 2011;
or Airbus Service Bulletin A300–57–6010,
Revision 05, dated February 21, 2011; as
applicable. Doing the replacement specified
in paragraph (j) of this AD terminates the
repetitive inspections required by this
paragraph.
(1) For Model A300 B4–601, B4–603, B4–
605R, B4–620, B4–622, B4–2C, and B4–203
airplanes: Do the inspection at the later of the
times specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 1,000
flight cycles or 2,000 flight hours, whichever
occurs first.
(i) Before the accumulation of 5,000 flight
cycles or 10,400 flight hours since first flight,
whichever occurs first.
(ii) Within 100 flight cycles after the
effective date of this AD.
(2) For Model A300 B2–1C, B2–203, and
B2K–3C airplanes: Do the inspection at the
later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 1,000 flight cycles or 1,000 flight
hours, whichever occurs first.
(i) Before the accumulation of 5,000 flight
cycles or 5,400 flight hours since first flight,
whichever occurs first.
(ii) Within 100 flight cycles after the
effective date of this AD.
(3) For Model A300 B4–103 airplanes: Do
the inspection at the later of the times
specified in paragraphs (g)(3)(i) and (g)(3)(ii)
of this AD. Repeat the inspection thereafter
at intervals not to exceed 1,000 flight cycles
or 1,300 flight hours, whichever occurs first.
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(i) Before the accumulation of 5,000 flight
cycles or 6,600 flight hours since first flight,
whichever occurs first.
(ii) Within 100 flight cycles after the
effective date of this AD.
(h) Corrective Action
If any crack or fracture is found during any
inspection required by paragraph (g) of this
AD: Before further flight, replace the
damaged hinge bracket with a new bracket,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–143, Revision 2, dated July 10, 1989; or
Airbus A300–57–6011, Revision 2, dated July
10, 1989; as applicable.
(i) Related Investigative and Corrective
Actions
If any crack or fracture is found during any
inspection required by paragraph (g) of this
AD: Before further flight, do a general visual
inspection for secondary damage (e.g., cracks,
wear damage, pitting, and gouging) in the
areas specified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0142, Revision 04,
dated March 30, 2011; or Airbus Service
Bulletin A300–57–6010, Revision 05, dated
February 21, 2011; as applicable. If any
damage is found, 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) The inner shroud-box forward
attachments and the attachment brackets at
the inboard end.
(2) The inner and outer shroud-box
structure, adjacent to the fractured bracket.
(3) The top skin of the inboard flap.
(j) Optional Terminating Action for
Inspection Requirements of Paragraph (g) of
This AD
(1) Replacement of the hinge bracket, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300–
57–143, Revision 2, dated July 10, 1989 (for
Model A300 series airplanes); or Airbus
Service Bulletin A300–57–6011, Revision 2,
dated July 10, 1989; as applicable; terminates
the inspection requirements of paragraph (g)
of this AD (for Model A300 B4–600 series
airplanes).
(2) Replacement of a hinge bracket before
the effective date of this AD terminates the
repetitive inspections required by paragraph
(g) of this AD, provided that after the hinge
bracket replacement, but before further flight
after the effective date of this AD, a one-time
detailed inspection of the forward and aft
outer shroud box has been done with no
cracking found, in accordance with
paragraph (g) of this AD. The replacement
must be done in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(k) Credit for Previous Actions
This paragraph provides credit for
inspections required by paragraph (g) of this
AD, if those actions were performed before
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63373
the effective date of this AD using any of the
applicable service information listed in
paragraphs (k)(1) through (k)(8) of this AD.
(1) Airbus Service Bulletin A300–57–142,
dated December 17, 1986.
(2) Airbus Service Bulletin A300–57–142,
Revision 1, dated April 9, 1990.
(3) Airbus Service Bulletin A300–57–142,
Revision 2, dated January 16, 1991.
(4) Airbus Service Bulletin A300–57–0142,
Revision 03, dated February 22, 1999.
(5) Airbus Service Bulletin A300–57–6010,
Revision 1, dated December 14, 1990.
(6) Airbus Service Bulletin A300–57–6010,
Revision 02, dated March 30, 1998.
(7) Airbus Service Bulletin A300–57–6010,
Revision 03, dated September 16, 1998.
(8) Airbus Service Bulletin A300–57–6010,
Revision 04, dated February 22, 1999.
(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. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA;
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) EASA
Airworthiness Directive 2013–0181R1, dated
August 20, 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–2015–6550.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) 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.
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63374
Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations
(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 A300–57–0142,
Revision 04, dated March 30, 2011.
(ii) Airbus Service Bulletin A300–57–143,
Revision 2, dated July 10, 1989. Pages 1, 3,
4, 7, 10, 13, and 14 of this document are
identified as Revision 2, dated July 10, 1989;
pages 2 and 8 are identified as original, dated
December 12, 1986; and pages 5, 6, 9, 11, 12,
and 15 are identified as Revision March 19,
1987.
(iii) Airbus Service Bulletin A300–57–
6010, Revision 05, dated February 21, 2011.
(iv) Airbus Service Bulletin A300–57–
6011, Revision 2, dated July 10, 1989. Pages
1, 2, 5, 7, 8, 11, and 12 of this document are
identified as Revision 2, dated July 10, 1989;
pages 3, 4, and 13 are identified as Revision
1, dated March 19, 1987; and pages 6, 9, 10
are identified as original, dated December 17,
1986.
(3) 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.
(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 August
24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–21146 Filed 9–14–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3781; Directorate
Identifier 2015–SW–048–AD; Amendment
39–18649; AD 2016–18–18]
RIN 2120–AA64
rmajette on DSK2TPTVN1PROD with RULES
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Agusta
S.p.A. (Agusta) Model A109A, A109A II,
A109C, A109E, A109K2, A109S, and
SUMMARY:
VerDate Sep<11>2014
14:38 Sep 14, 2016
Jkt 238001
AW109SP helicopters. This AD requires
visually inspecting the tail rotor drive
shaft assembly (drive shaft) for a crack.
This AD was prompted by the discovery
of three cracks on the drive shaft of a
Model A109S helicopter. The actions of
this AD are intended to detect a crack
on the drive shaft to prevent failure of
the driveshaft, failure of the tail rotor,
and subsequent loss of helicopter
control.
DATES: This AD is effective October 20,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of October 20, 2016.
ADDRESSES: For service information
identified in this final rule, contact
AgustaWestland, Product Support
Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN:
Maurizio D’Angelo; telephone 39–0331–
664757; fax 39–0331–664680; or at
https://www.agustawestland.com/
technical-bulletins. You may review the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2015–3781.
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–
3781; or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the European Aviation
Safety Agency (EASA) AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Martin R. Crane, Aviation Safety
Engineer, Safety Management Group,
Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 76177;
telephone (817) 222–5110; email
martin.r.crane@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On March 22, 2016, at 81 FR 15171,
the Federal Register published our
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to Agusta S.p.A. Model A109A, A109A
II, A109C, A109E, A109K2, A109S, and
AW109SP helicopters with a drive shaft
part number (P/N) 109–8412–02–1 or
109–8412–02–3 installed. The NPRM
proposed to require visually inspecting
the drive shaft for a crack. The proposed
requirements were intended to detect a
crack on the drive shaft to prevent
failure of the driveshaft, failure of the
tail rotor, and subsequent loss of
helicopter control.
The NPRM was prompted by AD No.
2015–0054, dated March 27, 2015,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for the Model A109A with
retrofit kit P/N 109–0820–27–101
installed, and Model A109A II, A109C,
A109E, A109K2, A109LUH, A109S, and
AW109SP helicopters.
EASA advises that during scheduled
maintenance on a Model A109S
helicopter, three cracks were found on
the drive shaft. An investigation could
not determine the cause of the cracking
but concluded it could not have been
caused by fatigue. This condition, if not
detected and corrected, could lead to
tail rotor failure, possibly resulting in
loss of helicopter control, EASA
advises. EASA AD No. 2015–0054
consequently requires a one-time
inspection of the drive shaft, and
replacing the drive shaft if cracks are
found.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(81 FR 15171, March 22, 2016).
FAA’s Determination
These helicopters have been approved
by the aviation authority of Italy and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with Italy, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Interim Action
We consider this AD to be an interim
action. The design approval holder has
not determined the cause of the unsafe
E:\FR\FM\15SER1.SGM
15SER1
]]>Agencies
[Federal Register Volume 81, Number 179 (Thursday, September 15, 2016)]
[Rules and Regulations]
[Pages 63370-63374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21146]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-6550; Directorate Identifier 2013-NM-162-AD;
Amendment 39-18638; AD 2016-18-08]
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) 90-11-05 for
certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes and Model A300 B4-600 series airplanes. AD 90-11-05
required repetitive detailed inspections for cracking in the aft hinge
brackets of the outer shroud box that is located in the outer wing box,
and related investigative and corrective actions if necessary. This new
AD changes certain compliance times and adds airplanes to the
applicability. This AD was prompted by reports of cracks in the aft
hinge brackets of the outer shroud box that is located in the outer
wing box, which were found during routine maintenance checks, and our
subsequent determination that a change in inspection compliance times
is needed. We are issuing this AD to detect and correct cracking of the
aft hinge brackets of the outer shroud box; such cracking could affect
the structural integrity of the airplane.
DATES: This AD becomes effective October 20, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 20,
2016.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.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-
6550.
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-
6550; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
[[Page 63371]]
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 90-11-05, Amendment 39-6603 (89-NM-223-AD) (55
FR 20129, May 15, 1990) (``AD 90-11-05''). AD 90-11-05 applied to
certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4
203 airplanes and Model A300 B4-600 series airplanes. The NPRM
published in the Federal Register on December 14, 2015 (80 FR 77279)
(``the NPRM''). The NPRM was prompted by a determination that a change
to certain compliance times is needed. The NPRM proposed to continue to
require doing repetitive detailed inspections for cracking in the hinge
brackets of the forward and aft outer shroud boxes that are located in
the outer wing box, and related investigative and corrective actions if
necessary. The NPRM also proposed to change certain compliance times
and add airplanes to the applicability. We are issuing this AD to
detect and correct cracking of the aft hinge brackets of the outer
shroud box; such cracking could affect the structural integrity of the
airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2013-0181R1, dated August 20, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Model A300
series airplanes and Model A300 B4-600 series airplanes. The MCAI
states:
In the past, aft hinge brackets of the outer wing box were found
cracked. Fracture of a bracket would allow vertical movement of the
inner shroud box structure, which could result in damage to the top
skin of the inboard flap. In addition, the loads carried by the
brackets will be transferred to the remaining supports, which may
also crack and cause extensive structural damage.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this potential unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an
airworthiness directive] (later revised) to require repetitive
inspections of the hinge bracket of the outer box and, depending on
findings, corrective action(s).
Since that [DGAC] AD was issued, a fleet survey and updated
Fatigue and Damage Tolerance analysis were performed in order to
substantiate the A300 Extended Service Goal (ESG) and A300-600
Extended Service Goal (ESG2) exercise.
The results of these analyses led to a change in the inspection
thresholds and intervals in Flight Cycles (FC) and the introduction
of Flight Hours (FH) limits.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France * * * [an airworthiness directive],
which is superseded, but requires those actions within the new
thresholds and intervals given by Airbus Service Bulletin (SB) A300-
57-0142 Revision 04 or A300-57-6010 Revision 05, as applicable to
aeroplane model.
Revision 1 of this [EASA] AD is issued to add model A300 B4-203
aeroplanes to the applicability and compliance time tables. This
model is covered by Airbus SB A300-57-0142, but was mistakenly
omitted from the original [EASA] AD issue.
The corrective action for a hinge bracket that is cracked or
fractured is replacing the damaged hinge bracket with a new bracket.
For airplanes on which a crack is found in one half bracket or both
half brackets, related investigative actions include a general visual
inspection for secondary damage (e.g., cracks, wear damage, pitting,
and gouging) in the following areas:
The inner shroud-box forward attachments and the
attachment brackets at the inboard end.
The inner and outer shroud-box structure, adjacent to the
fractured bracket.
The top skin of the inboard flap.
The corrective action for damage findings during the related
investigative action is repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA; or
EASA; or Airbus's EASA Design Organization Approval (DOA).
The compliance time for related investigative actions and
corrective actions is before further flight.
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-
6550.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response to the comment.
Request To Exclude Certain Airplanes From the Applicability
FedEx requested that we exclude from the proposed applicability
airplanes on which the actions specified in Airbus Service Bulletin
A300-57-6011, Revision 2, dated July 10, 1989, have been accomplished.
FedEx stated that it has accomplished the optional terminating actions
provided in paragraph (j)(1) of the proposed AD, and specified in
Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989,
on several of its airplanes.
We disagree with FedEx's request. As of the effective date of this
AD, additional actions are required for airplanes on which the optional
modification has been accomplished. These airplanes will need to have a
one-time detailed visual inspection of the forward and aft outer shroud
box with no cracking found, as required by paragraph (j)(2) of this AD.
We have not changed this AD in this regard.
Changes Made to This AD
In paragraph (j)(2) of the proposed AD, we proposed to provide an
optional method of compliance (i.e., a replacement and a one-time
inspection) for actions specified in paragraph (g) of the proposed AD.
We also proposed to give credit in paragraph (k)(2) of the proposed AD
for replacements accomplished before the effective date of this AD
using the same service information identified in paragraph (j)(2) of
the AD:
Airbus Service Bulletin A300-57-143, dated December 17,
1986.
Airbus Service Bulletin A300-57-143, Revision 1, dated
March 19, 1987.
Airbus Service Bulletin A300-57-6011, dated December 17,
1986.
Airbus Service Bulletin A300-57-6011, Revision 1, dated
March 19, 1987.
Since we cannot make this service information reasonably available,
we have revised paragraph (j)(2) of the proposed AD, removed redundant
paragraph (k)(2) of the proposed AD from this AD, and redesignated
paragraph (k)(1) and subsequent subparagraphs accordingly. We revised
paragraph (j)(2) of this AD by removing the references to the service
information and instead specified that operators must do the
replacement using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA Design Organization Approval (DOA).
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
[[Page 63372]]
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A300-57-0142, Revision 04, dated
March 30, 2011, which describes procedures for doing an inspection of
the forward and aft hinge brackets on the outer shroud box.
Airbus Service Bulletin A300-57-143, Revision 2, dated
July 10, 1989, which describes procedures for replacing the aft
aluminum alloy brackets on the outer shroud box with new steel
brackets.
Airbus Service Bulletin A300-57-6010, Revision 05, dated
February 21, 2011, which describes procedures for doing an inspection
of the forward and aft hinge brackets on the outer shroud box.
Airbus Service Bulletin A300-57-6011, Revision 2, dated
July 10, 1989, which describes procedures for replacing the aft
aluminum alloy brackets on the outer shroud box with new steel
brackets.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 3 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection..................... 8 work-hours x $85 per $0 $680 per $2,040 per
hour = $680 per inspection cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement................................ 27 work-hours x $85 per hour = $25,650 $27,945
$2,295.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition related investigative and
corrective 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)
90-11-05, Amendment 39-6603 (89-NM-223-AD) (55 FR 20129, May 15, 1990),
and adding the following new AD:
2016-18-08 Airbus: Amendment 39-18638. Docket No. FAA-2015-6550;
Directorate Identifier 2013-NM-162-AD.
(a) Effective Date
This AD becomes effective October 20, 2016.
(b) Affected ADs
This AD replaces AD 90-11-05, Amendment 39-6603 (89-NM-223-AD)
(55 FR 20129, May 15, 1990).
(c) Applicability
This AD applies to Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-
2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620,
and B4-622 airplanes; and Model A300 B4-605R airplanes; certificated
in any category; except airplanes on which Airbus Modification 6661
has been embodied during production.
[[Page 63373]]
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks in the aft hinge
brackets of the outer shroud box that is located in the outer wing
box, which were found during routine maintenance checks, and our
subsequent determination that a change in inspection compliance
times is needed. We are issuing this AD to detect and correct
cracking of the aft hinge brackets of the outer shroud box; such
cracking could affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
At the applicable compliance time specified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD: Do a detailed inspection for cracks
and fractures of the hinge brackets of the forward and aft outer
shroud boxes, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30,
2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated
February 21, 2011; as applicable. Repeat the inspection thereafter
at the applicable interval specified in paragraph (g)(1), (g)(2), or
(g)(3) of this AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0142, Revision 04,
dated March 30, 2011; or Airbus Service Bulletin A300-57-6010,
Revision 05, dated February 21, 2011; as applicable. Doing the
replacement specified in paragraph (j) of this AD terminates the
repetitive inspections required by this paragraph.
(1) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
2C, and B4-203 airplanes: Do the inspection at the later of the
times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
Repeat the inspection thereafter at intervals not to exceed 1,000
flight cycles or 2,000 flight hours, whichever occurs first.
(i) Before the accumulation of 5,000 flight cycles or 10,400
flight hours since first flight, whichever occurs first.
(ii) Within 100 flight cycles after the effective date of this
AD.
(2) For Model A300 B2-1C, B2-203, and B2K-3C airplanes: Do the
inspection at the later of the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD. Repeat the inspection
thereafter at intervals not to exceed 1,000 flight cycles or 1,000
flight hours, whichever occurs first.
(i) Before the accumulation of 5,000 flight cycles or 5,400
flight hours since first flight, whichever occurs first.
(ii) Within 100 flight cycles after the effective date of this
AD.
(3) For Model A300 B4-103 airplanes: Do the inspection at the
later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii)
of this AD. Repeat the inspection thereafter at intervals not to
exceed 1,000 flight cycles or 1,300 flight hours, whichever occurs
first.
(i) Before the accumulation of 5,000 flight cycles or 6,600
flight hours since first flight, whichever occurs first.
(ii) Within 100 flight cycles after the effective date of this
AD.
(h) Corrective Action
If any crack or fracture is found during any inspection required
by paragraph (g) of this AD: Before further flight, replace the
damaged hinge bracket with a new bracket, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-143,
Revision 2, dated July 10, 1989; or Airbus A300-57-6011, Revision 2,
dated July 10, 1989; as applicable.
(i) Related Investigative and Corrective Actions
If any crack or fracture is found during any inspection required
by paragraph (g) of this AD: Before further flight, do a general
visual inspection for secondary damage (e.g., cracks, wear damage,
pitting, and gouging) in the areas specified in paragraphs (i)(1),
(i)(2), and (i)(3) of this AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0142, Revision 04,
dated March 30, 2011; or Airbus Service Bulletin A300-57-6010,
Revision 05, dated February 21, 2011; as applicable. If any damage
is found, 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) The inner shroud-box forward attachments and the attachment
brackets at the inboard end.
(2) The inner and outer shroud-box structure, adjacent to the
fractured bracket.
(3) The top skin of the inboard flap.
(j) Optional Terminating Action for Inspection Requirements of
Paragraph (g) of This AD
(1) Replacement of the hinge bracket, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-143,
Revision 2, dated July 10, 1989 (for Model A300 series airplanes);
or Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10,
1989; as applicable; terminates the inspection requirements of
paragraph (g) of this AD (for Model A300 B4-600 series airplanes).
(2) Replacement of a hinge bracket before the effective date of
this AD terminates the repetitive inspections required by paragraph
(g) of this AD, provided that after the hinge bracket replacement,
but before further flight after the effective date of this AD, a
one-time detailed inspection of the forward and aft outer shroud box
has been done with no cracking found, in accordance with paragraph
(g) of this AD. The replacement must be done in accordance with a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(k) Credit for Previous Actions
This paragraph provides credit for inspections required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using any of the applicable service
information listed in paragraphs (k)(1) through (k)(8) of this AD.
(1) Airbus Service Bulletin A300-57-142, dated December 17,
1986.
(2) Airbus Service Bulletin A300-57-142, Revision 1, dated April
9, 1990.
(3) Airbus Service Bulletin A300-57-142, Revision 2, dated
January 16, 1991.
(4) Airbus Service Bulletin A300-57-0142, Revision 03, dated
February 22, 1999.
(5) Airbus Service Bulletin A300-57-6010, Revision 1, dated
December 14, 1990.
(6) Airbus Service Bulletin A300-57-6010, Revision 02, dated
March 30, 1998.
(7) Airbus Service Bulletin A300-57-6010, Revision 03, dated
September 16, 1998.
(8) Airbus Service Bulletin A300-57-6010, Revision 04, dated
February 22, 1999.
(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. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; 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) EASA Airworthiness Directive 2013-0181R1, dated August 20,
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-2015-6550.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(4) 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.
[[Page 63374]]
(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 A300-57-0142, Revision 04, dated
March 30, 2011.
(ii) Airbus Service Bulletin A300-57-143, Revision 2, dated July
10, 1989. Pages 1, 3, 4, 7, 10, 13, and 14 of this document are
identified as Revision 2, dated July 10, 1989; pages 2 and 8 are
identified as original, dated December 12, 1986; and pages 5, 6, 9,
11, 12, and 15 are identified as Revision March 19, 1987.
(iii) Airbus Service Bulletin A300-57-6010, Revision 05, dated
February 21, 2011.
(iv) Airbus Service Bulletin A300-57-6011, Revision 2, dated
July 10, 1989. Pages 1, 2, 5, 7, 8, 11, and 12 of this document are
identified as Revision 2, dated July 10, 1989; pages 3, 4, and 13
are identified as Revision 1, dated March 19, 1987; and pages 6, 9,
10 are identified as original, dated December 17, 1986.
(3) 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.
(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/ibr-locations.html.
Issued in Renton, Washington, on August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-21146 Filed 9-14-16; 8:45 am]
BILLING CODE 4910-13-P
