Airworthiness Directives; Airbus Airplanes, 3316-3319 [2016-00373]
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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations
telephone +44(0)2890–462469; fax
+44(0)2890 468444; email
michael.mulholland@aero.bombardier.com;
Internet https://www.bombardier.com.
(5) 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.
(6) 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 January
4, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–00378 Filed 1–20–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1422; Directorate
Identifier 2014–NM–125–AD; Amendment
39–18370; AD 2016–01–11]
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) 98–18–26,
for certain Airbus Model A320 series
airplanes. AD 98–18–26 required
repetitive inspections to detect fatigue
cracking of the front spar vertical
stringers on the wings; and repair, if
necessary. This new AD requires
repetitive high frequency eddy current
(HFEC) inspections for cracking of the
radius of the front spar vertical stringers
and the horizontal floor beam on frame
36, a rototest inspection for cracking of
the fastener holes of the front spar
vertical stringers on frame 36, and repair
if necessary. This AD was prompted by
reports that indicate new repetitive
inspections having new thresholds and
intervals are needed and that additional
work is needed to accomplish the
inspections on airplanes on which a
previous modification has been
accomplished. We are issuing this AD to
detect and correct fatigue cracking of the
front spar vertical stringers on the
wings, which could result in the
jstallworth on DSK7TPTVN1PROD with RULES
SUMMARY:
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Jkt 238001
reduced structural integrity of the
airframe.
DATES: This AD becomes effective
February 25, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 25, 2016.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-1422; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport 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
Number FAA–2015–1422.
FOR FURTHER INFORMATION CONTACT:
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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 98–18–26,
Amendment 39–10742 (63 FR 47423,
September 8, 1998). AD 98–18–26
applied to certain Airbus Model A320
series airplanes. The NPRM published
in the Federal Register on June 5, 2015
(80 FR 32063).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0069, dated March 19,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition on certain Airbus
Model A320–211, –212, and –231
airplanes. The MCAI states:
During center fuselage certification full
scale fatigue test, cracks were found on the
front vertical stringer at frame 36. Analysis of
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these findings indicated that a number of inservice aeroplanes could be similarly
affected.
This condition, if not detected and
corrected, could lead to crack propagation
and consequent deterioration of the
structural integrity of the aeroplane.
To address this potential unsafe condition,
[Directorate General for Civil Aviation]
DGAC France AD 97–311–105 [which
corresponds to FAA AD 98–18–26,
Amendment 39–10742 (63 FR 47423,
September 8, 1998)] was issued to require
repetitive [HFEC] inspections [for cracking]
in accordance with the instruction of Airbus
Service Bulletin (SB) A320–57–1016. At the
same time, the modification provided by
Airbus SB A320–57–1017 was considered to
be terminating action for the repetitive
inspections required by DGAC France AD
97–311–105.
Since that [DGAC] AD was issued, and
following new analysis, modification per
Airbus SB A320–57–1017 is no longer
considered to be terminating action for the
repetitive inspections as required by DGAC
France AD 97–311–105.
Aeroplanes with [manufacturer serial
number] MSN 0080 up to 0155 inclusive
have been delivered with the addition of a 5
[millimeter] mm thick light alloy shim under
the heads of 2 fasteners at the top end of the
front spar vertical stringers (Airbus
modification 21290P1546, which is the
production line equivalent to in-service
modification through Airbus SB A320–57–
1017). From MSN 0156 and higher, all
aeroplanes are delivered with vertical
stiffeners of the forward wing spar upper end
with stiffener cap thickness increased from 4
to 6 mm (Airbus modification 21290P1547).
Prompted by these findings, Airbus issued
SB A320–57–1178 to introduce new
repetitive inspections with new thresholds
and intervals.
For the reasons described above, DGAC
France AD 97–311–105 is superseded and
this [EASA] AD requires the repetitive
inspections at new thresholds and intervals.
After EASA issued [proposed
airworthiness directive] PAD 14–021, it was
discovered that additional work [HFEC
inspections for cracking of the radius of spar
vertical stringers and horizontal beam in the
center fuselage of frame 36, and a rototest
inspection for cracking of the fastener holes
of the spar vertical stringers radius on Frame
36 and repair if necessary], to be included in
Revision 01 of Airbus SB A320–57–1178, is
required to accomplish the inspections. This
Final [EASA] AD has been amended
accordingly.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-14220002.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (80 FR 32063,
June 5, 2015) and the FAA’s response to
the comments.
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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations
Requests for Clarification of Certain
Requirements
Delta Airlines (DAL) asked that we
move the repetitive inspection intervals
from paragraph (g) of the proposed AD
(80 FR 32063, June 5, 2015), and create
a new paragraph (i) with the repetitive
inspection intervals. DAL stated that
having the inspection method and the
repetitive inspection intervals in one
paragraph, as well as a separate
paragraph for the initial inspection is
cumbersome.
We do not agree with the requested
changes. We re-examined the structure
of the regulatory text of this AD, and
have determined that the specified
language as proposed is clear and aligns
with the MCAI. Therefore, we have not
changed this AD in this regard.
DAL also asked that we add sub-steps
to requirements in the proposed AD (80
FR 32063, June 5, 2015), to clarify the
inspection requirements specified in
Airbus Service Bulletin A320–57–1178,
Revision 01, dated May 28, 2014.
We do not agree. Our goal in referring
to the Accomplishment Instructions of
the service information is to ensure that
operators follow the details in the
inspection steps shown therein. DAL
has the option of creating task cards if
it makes accomplishing the sub-steps
easier, provided the cards meet the
intent of the AD. We have not changed
this AD in this regard.
Additionally, DAL asked that
Appendix 01 of Airbus Service Bulletin
A320–57–1178, Revision 01, dated May
28, 2014, be removed from the service
bulletin identification in the NPRM (80
FR 32063, June 5, 2015), because
Appendix 01 has Gantt Chart
information that should not be
highlighted as a regulatory requirement
for compliance.
We do not agree. The information in
Appendix 01 of Airbus Service Bulletin
A320–57–1178, Revision 01, dated May
28, 2014, may be helpful to operators
that want to determine the number of
work hours necessary to accomplish
specific actions. Moreover, Appendix 01
does not contain a requirement for
compliance. We have not changed this
AD in this regard.
jstallworth on DSK7TPTVN1PROD with RULES
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed, with minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (80 FR
32063, June 5, 2015) for correcting the
unsafe condition; and
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• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 32063,
June 5, 2015).
We have also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–57–1178, Revision 01, dated May
28, 2014, including Appendix 01, dated
May 28, 2014. The service information
describes procedures for inspecting the
radius of the front spar vertical stringers
and the horizontal floor beam on frame
36 for cracking. 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 17
airplanes of U.S. registry.
We also estimate that it will take
about 24 work-hours per product to
comply with the 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 $34,680, or $2,040 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 49 work-hours and require parts
costing $1,210, for a cost of $5,375 per
product. We have no way of
determining the number of aircraft that
might need this action.
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.
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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;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/#!docket
Detail;D=FAA-2015-1422; or in person
at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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)
98–18–26, Amendment 39–10742 (63
FR 47423, September 8, 1998), and
adding the following new AD:
■
2016–01–11 Airbus: Amendment 39–18370.
Docket No. FAA–2015–1422; Directorate
Identifier 2014–NM–125–AD.
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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations
(a) Effective Date
This AD becomes effective February 25,
2016.
(b) Affected ADs
This AD replaces AD 98–18–26,
Amendment 39–10742 (63 FR 47423,
September 8, 1998).
(c) Applicability
This AD applies to Airbus Model A320–
211, –212, and –231 airplanes, certificated in
any category, manufacturer serial numbers
(MSN) 0001 through 0155 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by cracks found on
the front vertical stringer at frame 36. This
AD was also prompted by reports that
indicate new repetitive inspections having
new thresholds and intervals are needed and
that additional work is needed to accomplish
the inspections on airplanes on which a
previous modification has been
accomplished. We are issuing this AD to
detect and correct fatigue cracking of the
front spar vertical stringers on the wings,
which could result in the reduced structural
integrity of the airframe.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
jstallworth on DSK7TPTVN1PROD with RULES
(g) Inspections
Within the applicable compliance times
specified in paragraphs (h)(1) through (h)(4)
of this AD, do a high frequency eddy current
(HFEC) inspection for cracking of the radius
of the front spar vertical stringers and the
horizontal floor beam on frame 36, and do a
rototest inspection for cracking of the
fastener holes of the front spar vertical
stringers on frame 36, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1178, Revision 01,
dated May 28, 2014, including Appendix 01,
dated May 28, 2014. Repeat the inspections
thereafter at the compliance times specified
in paragraphs (g)(1) and (g)(2) of this AD.
(1) For Configuration 1 airplanes identified
in paragraph (h)(1) of this AD: At intervals
not to exceed 8,800 flight cycles or 17,700
flight hours, whichever occurs first.
(2) For Configuration 2, 3, and 4 airplanes
identified in paragraphs (h)(2) through (h)(4)
of this AD: At intervals not to exceed 24,900
flight cycles or 49,800 flight hours,
whichever occurs first.
(h) Compliance Times for Initial Inspections
Required by Paragraph (g) of This AD
Do the initial inspections required by
paragraph (g) of this AD within the
applicable compliance times specified in
paragraphs (h)(1) through (h)(4) of this AD.
(1) For Configuration 1 airplanes, having
MSNs 0001 through MSN 0079 inclusive, on
which the modification specified by Airbus
Service Bulletin A320–57–1017, dated
September 3, 1991; or Airbus Service
Bulletin A320–57–1017, Revision 01, dated
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March 17, 1997, has not been accomplished:
Inspect at the later of the times specified by
paragraphs (h)(1)(i) through (h)(1)(iii) of this
AD.
(i) Inspect at the later of the times specified
by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of
this AD.
(A) Prior to the accumulation of 24,000
flight cycles or 48,000 flight hours,
whichever occurs first since airplane first
flight.
(B) Within 60 days after the effective date
of this AD.
(ii) Inspect within 8,800 flight cycles or
17,700 flight hours, whichever occurs first,
since the last inspection specified in Airbus
Service Bulletin A320–57–1016 was
accomplished.
(iii) Inspect within 850 flight cycles or
1,700 flight hours, whichever occurs first,
after the effective date of this AD, without
exceeding 14,000 flight cycles after the last
inspection specified in Airbus Service
Bulletin A320–57–1016 was accomplished.
(2) For Configuration 2 airplanes, having
MSNs 0001 through 0079 inclusive, on
which the actions specified by Airbus
Service Bulletin A320–57–1016, have not
been done prior to accomplishing the actions
specified by Airbus Service Bulletin A320–
57–1017, dated September 3, 1991; or Airbus
Service Bulletin A320–57–1017, Revision 01,
dated March 17, 1997: Inspect at the later of
the times specified by paragraphs (h)(2)(i)
and (h)(2)(ii) of this AD.
(i) Within 8,800 flight cycles or 17,700
flight hours, whichever occurs first, since the
modification specified in Airbus Service
Bulletin A320–57–1017, dated September 3,
1991; or Airbus Service Bulletin A320–57–
1017, Revision 01, dated December 6, 1995,
was accomplished.
(ii) Within 850 flight cycles or 1,700 flight
hours, whichever occurs first, after the
effective date of this AD.
(3) For Configuration 3 airplanes, having
MSNs 0001 through 0079 inclusive, on
which the actions specified by Airbus
Service Bulletin A320–57–1016, have been
done prior to accomplishing the actions
specified by Airbus Service Bulletin A320–
57–1017, dated September 3, 1991; or Airbus
Service Bulletin A320–57–1017, Revision 01,
dated March 17, 1997: Inspect at the later of
the times specified by paragraphs (h)(3)(i)
and (h)(3)(ii) of this AD.
(i) Within 24,900 flight cycles or 49,800
flight hours, whichever occurs first, since the
modification specified in Airbus Service
Bulletin A320–57–1017, dated September 3,
1991; or Airbus Service Bulletin A320–57–
1017, Revision 01, dated March 17, 1997, was
accomplished.
(ii) Within 850 flight cycles or 1,700 flight
hours, whichever occurs first, after the
effective date of this AD.
(4) For Configuration 4 airplanes, having
MSNs 0080 through 0155 inclusive: Inspect
at the later of the times specified in
paragraphs (h)(4)(i) or (h)(4)(ii) of this AD.
(i) Prior to the accumulation of 54,300
flight cycles or 108,600 flight hours,
whichever occurs first since airplane first
flight.
(ii) Within 60 days after the effective date
of this AD.
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(i) Repair
If any crack is detected during any
inspection required by paragraph (g) of 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).
(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: 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
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0069, dated
March 19, 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–
2015–1422.
(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.
(3) The following service information was
approved for IBR on February 25, 2016.
(i) Airbus Service Bulletin A320–57–1178,
Revision 01, dated May 28, 2014, including
Appendix 01, dated May 28, 2014.
(ii) Reserved.
(4) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations
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.
(5) 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 31, 2015.
Philip Forde,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–00373 Filed 1–20–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
www.mdhelicopters.com. You may
review a copy of the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1998; 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 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.
[Docket No. FAA–2015–1998; Directorate
Identifier 2014–SW–035–AD; Amendment
39–18379; AD 2016–01–19]
Galib Abumeri, Aerospace Engineer, Los
Angeles Aircraft Certification Office,
Transport Airplane Directorate, FAA,
3960 Paramount Blvd., Lakewood,
California 90712, telephone 562–627–
5324; email Galib.Abumeri@faa.gov.
RIN 2120–AA64
SUPPLEMENTARY INFORMATION:
Airworthiness Directives; MD
Helicopters Inc.
Discussion
14 CFR Part 39
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for MD
Helicopters Inc. (MDHI) Model 500N
and 600N helicopters with certain
rotating cone assemblies installed. This
AD requires establishing a life limit of
10,000 hours time-in-service (TIS) on
these rotating cone assemblies. This AD
was prompted by the determination that
MDHI created rotating cone assemblies
with new dash numbers but incorrectly
failed to identify them as life-limited
parts. The actions are intended to
prevent operation of rotating cone
assemblies past their life limits, failure
of the rotating cone assemblies, loss of
directional control, and subsequent loss
of control of the helicopter.
DATES: This AD is effective February 25,
2016.
ADDRESSES: For service information
identified in this final rule, contact MD
Helicopters, Inc., Attn: Customer
Support Division, 4555 E. McDowell
Rd., Mail Stop M615, Mesa, AZ 85215–
9734; telephone 1–800–388–3378; fax
480–346–6813; or at https://
jstallworth on DSK7TPTVN1PROD with RULES
SUMMARY:
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On June 9, 2015, at 80 FR 32508, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
MDHI Model 500N helicopters with a
rotating cone assembly part number (P/
N) 500N3740–81 installed, and Model
600N helicopters with a rotating cone
assembly P/N 500N3740–71 installed.
The NPRM proposed to require
establishing a life limit of 10,000 hours
TIS on these rotating cone assemblies.
Although these parts have a life limit of
10,000 hours TIS, they were incorrectly
omitted from the Airworthiness
Limitation Section of the Rotorcraft
Maintenance Manual. Some of the
affected parts were sold as spares, while
others were installed on new helicopters
in production. The proposed
requirements were intended to prevent
operation of rotating cone assemblies
past their life limits, failure of the
rotating cone assemblies, loss of
directional control, and subsequent loss
of control of the helicopter.
Since the NPRM was issued, the FAA
Southwest Regional Office has
relocated. This AD includes the current
physical address of the FAA Southwest
Regional Office.
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(80 FR 32508, June 9, 2015).
FAA’s Determination
Examining the AD Docket
FOR FURTHER INFORMATION CONTACT:
Federal Aviation Administration
3319
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Related Service Information
MDHI issued Service Bulletin
SB500N–046 and SB600N–054 (SB) as a
single bulletin on July 9, 2012. The SB
calls for a one-time inspection within
100 flight hours to determine the
rotating cone assembly’s part number on
MDHI Model 500N and 600N
helicopters. The SB then states the need
to correct the component record for
certain rotating cone assemblies.
The SB also specifies determining the
rotating cone assembly’s total service
time since new and recording this on
the component record. MDHI reports
that failure to comply with the SB may
result in an aircraft exceeding the life
limit of the rotating cone assembly and
that this could lead to component
failure and loss of directional control of
the helicopter.
Differences Between This AD and the
Service Information
The SB calls for inspecting the
rotating cone assembly to determine its
P/N. We make no requirement about
how to determine the P/N. The
compliance time for the SB is within
100 flight hours, while this AD requires
compliance within 1 year or by the next
annual inspection, whichever comes
later.
Costs of Compliance
We estimate that this AD affects 8
helicopters of U.S. Registry and that
labor costs average $85 a work hour. We
estimate that creating a component
history card and revising the
appropriate records takes 1 work-hour.
No parts are needed for a total cost of
$85 per helicopter and $680 for the U.S.
fleet.
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
E:\FR\FM\21JAR1.SGM
21JAR1
]]>Agencies
[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Rules and Regulations]
[Pages 3316-3319]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00373]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD;
Amendment 39-18370; AD 2016-01-11]
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) 98-18-26, for
certain Airbus Model A320 series airplanes. AD 98-18-26 required
repetitive inspections to detect fatigue cracking of the front spar
vertical stringers on the wings; and repair, if necessary. This new AD
requires repetitive high frequency eddy current (HFEC) inspections for
cracking of the radius of the front spar vertical stringers and the
horizontal floor beam on frame 36, a rototest inspection for cracking
of the fastener holes of the front spar vertical stringers on frame 36,
and repair if necessary. This AD was prompted by reports that indicate
new repetitive inspections having new thresholds and intervals are
needed and that additional work is needed to accomplish the inspections
on airplanes on which a previous modification has been accomplished. We
are issuing this AD to detect and correct fatigue cracking of the front
spar vertical stringers on the wings, which could result in the reduced
structural integrity of the airframe.
DATES: This AD becomes effective February 25, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 25,
2016.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-1422; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
For service information identified in this AD, contact Airbus,
Airworthiness Office--EIAS, 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 Number FAA-
2015-1422.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 98-18-26, Amendment 39-10742 (63 FR 47423,
September 8, 1998). AD 98-18-26 applied to certain Airbus Model A320
series airplanes. The NPRM published in the Federal Register on June 5,
2015 (80 FR 32063).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0069, dated March 19, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on certain Airbus Model
A320-211, -212, and -231 airplanes. The MCAI states:
During center fuselage certification full scale fatigue test,
cracks were found on the front vertical stringer at frame 36.
Analysis of these findings indicated that a number of in-service
aeroplanes could be similarly affected.
This condition, if not detected and corrected, could lead to
crack propagation and consequent deterioration of the structural
integrity of the aeroplane.
To address this potential unsafe condition, [Directorate General
for Civil Aviation] DGAC France AD 97-311-105 [which corresponds to
FAA AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8,
1998)] was issued to require repetitive [HFEC] inspections [for
cracking] in accordance with the instruction of Airbus Service
Bulletin (SB) A320-57-1016. At the same time, the modification
provided by Airbus SB A320-57-1017 was considered to be terminating
action for the repetitive inspections required by DGAC France AD 97-
311-105.
Since that [DGAC] AD was issued, and following new analysis,
modification per Airbus SB A320-57-1017 is no longer considered to
be terminating action for the repetitive inspections as required by
DGAC France AD 97-311-105.
Aeroplanes with [manufacturer serial number] MSN 0080 up to 0155
inclusive have been delivered with the addition of a 5 [millimeter]
mm thick light alloy shim under the heads of 2 fasteners at the top
end of the front spar vertical stringers (Airbus modification
21290P1546, which is the production line equivalent to in-service
modification through Airbus SB A320-57-1017). From MSN 0156 and
higher, all aeroplanes are delivered with vertical stiffeners of the
forward wing spar upper end with stiffener cap thickness increased
from 4 to 6 mm (Airbus modification 21290P1547).
Prompted by these findings, Airbus issued SB A320-57-1178 to
introduce new repetitive inspections with new thresholds and
intervals.
For the reasons described above, DGAC France AD 97-311-105 is
superseded and this [EASA] AD requires the repetitive inspections at
new thresholds and intervals.
After EASA issued [proposed airworthiness directive] PAD 14-021,
it was discovered that additional work [HFEC inspections for
cracking of the radius of spar vertical stringers and horizontal
beam in the center fuselage of frame 36, and a rototest inspection
for cracking of the fastener holes of the spar vertical stringers
radius on Frame 36 and repair if necessary], to be included in
Revision 01 of Airbus SB A320-57-1178, is required to accomplish the
inspections. This Final [EASA] AD has been amended accordingly.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-1422-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (80
FR 32063, June 5, 2015) and the FAA's response to the comments.
[[Page 3317]]
Requests for Clarification of Certain Requirements
Delta Airlines (DAL) asked that we move the repetitive inspection
intervals from paragraph (g) of the proposed AD (80 FR 32063, June 5,
2015), and create a new paragraph (i) with the repetitive inspection
intervals. DAL stated that having the inspection method and the
repetitive inspection intervals in one paragraph, as well as a separate
paragraph for the initial inspection is cumbersome.
We do not agree with the requested changes. We re-examined the
structure of the regulatory text of this AD, and have determined that
the specified language as proposed is clear and aligns with the MCAI.
Therefore, we have not changed this AD in this regard.
DAL also asked that we add sub-steps to requirements in the
proposed AD (80 FR 32063, June 5, 2015), to clarify the inspection
requirements specified in Airbus Service Bulletin A320-57-1178,
Revision 01, dated May 28, 2014.
We do not agree. Our goal in referring to the Accomplishment
Instructions of the service information is to ensure that operators
follow the details in the inspection steps shown therein. DAL has the
option of creating task cards if it makes accomplishing the sub-steps
easier, provided the cards meet the intent of the AD. We have not
changed this AD in this regard.
Additionally, DAL asked that Appendix 01 of Airbus Service Bulletin
A320-57-1178, Revision 01, dated May 28, 2014, be removed from the
service bulletin identification in the NPRM (80 FR 32063, June 5,
2015), because Appendix 01 has Gantt Chart information that should not
be highlighted as a regulatory requirement for compliance.
We do not agree. The information in Appendix 01 of Airbus Service
Bulletin A320-57-1178, Revision 01, dated May 28, 2014, may be helpful
to operators that want to determine the number of work hours necessary
to accomplish specific actions. Moreover, Appendix 01 does not contain
a requirement for compliance. We have not changed this AD in this
regard.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed, with minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 32063, June 5, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 32063, June 5, 2015).
We have also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-57-1178, Revision 01, dated
May 28, 2014, including Appendix 01, dated May 28, 2014. The service
information describes procedures for inspecting the radius of the front
spar vertical stringers and the horizontal floor beam on frame 36 for
cracking. 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 17 airplanes of U.S. registry.
We also estimate that it will take about 24 work-hours per product
to comply with the 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 $34,680, or $2,040 per product.
In addition, we estimate that any necessary follow-on actions will
take about 49 work-hours and require parts costing $1,210, for a cost
of $5,375 per product. We have no way of determining the number of
aircraft that might need this action.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-1422; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998), and
adding the following new AD:
2016-01-11 Airbus: Amendment 39-18370. Docket No. FAA-2015-1422;
Directorate Identifier 2014-NM-125-AD.
[[Page 3318]]
(a) Effective Date
This AD becomes effective February 25, 2016.
(b) Affected ADs
This AD replaces AD 98-18-26, Amendment 39-10742 (63 FR 47423,
September 8, 1998).
(c) Applicability
This AD applies to Airbus Model A320-211, -212, and -231
airplanes, certificated in any category, manufacturer serial numbers
(MSN) 0001 through 0155 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by cracks found on the front vertical
stringer at frame 36. This AD was also prompted by reports that
indicate new repetitive inspections having new thresholds and
intervals are needed and that additional work is needed to
accomplish the inspections on airplanes on which a previous
modification has been accomplished. We are issuing this AD to detect
and correct fatigue cracking of the front spar vertical stringers on
the wings, which could result in the reduced structural integrity of
the airframe.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections
Within the applicable compliance times specified in paragraphs
(h)(1) through (h)(4) of this AD, do a high frequency eddy current
(HFEC) inspection for cracking of the radius of the front spar
vertical stringers and the horizontal floor beam on frame 36, and do
a rototest inspection for cracking of the fastener holes of the
front spar vertical stringers on frame 36, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1178,
Revision 01, dated May 28, 2014, including Appendix 01, dated May
28, 2014. Repeat the inspections thereafter at the compliance times
specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) For Configuration 1 airplanes identified in paragraph (h)(1)
of this AD: At intervals not to exceed 8,800 flight cycles or 17,700
flight hours, whichever occurs first.
(2) For Configuration 2, 3, and 4 airplanes identified in
paragraphs (h)(2) through (h)(4) of this AD: At intervals not to
exceed 24,900 flight cycles or 49,800 flight hours, whichever occurs
first.
(h) Compliance Times for Initial Inspections Required by Paragraph (g)
of This AD
Do the initial inspections required by paragraph (g) of this AD
within the applicable compliance times specified in paragraphs
(h)(1) through (h)(4) of this AD.
(1) For Configuration 1 airplanes, having MSNs 0001 through MSN
0079 inclusive, on which the modification specified by Airbus
Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus
Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997,
has not been accomplished: Inspect at the later of the times
specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this AD.
(i) Inspect at the later of the times specified by paragraphs
(h)(1)(i)(A) and (h)(1)(i)(B) of this AD.
(A) Prior to the accumulation of 24,000 flight cycles or 48,000
flight hours, whichever occurs first since airplane first flight.
(B) Within 60 days after the effective date of this AD.
(ii) Inspect within 8,800 flight cycles or 17,700 flight hours,
whichever occurs first, since the last inspection specified in
Airbus Service Bulletin A320-57-1016 was accomplished.
(iii) Inspect within 850 flight cycles or 1,700 flight hours,
whichever occurs first, after the effective date of this AD, without
exceeding 14,000 flight cycles after the last inspection specified
in Airbus Service Bulletin A320-57-1016 was accomplished.
(2) For Configuration 2 airplanes, having MSNs 0001 through 0079
inclusive, on which the actions specified by Airbus Service Bulletin
A320-57-1016, have not been done prior to accomplishing the actions
specified by Airbus Service Bulletin A320-57-1017, dated September
3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated
March 17, 1997: Inspect at the later of the times specified by
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Within 8,800 flight cycles or 17,700 flight hours, whichever
occurs first, since the modification specified in Airbus Service
Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service
Bulletin A320-57-1017, Revision 01, dated December 6, 1995, was
accomplished.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.
(3) For Configuration 3 airplanes, having MSNs 0001 through 0079
inclusive, on which the actions specified by Airbus Service Bulletin
A320-57-1016, have been done prior to accomplishing the actions
specified by Airbus Service Bulletin A320-57-1017, dated September
3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated
March 17, 1997: Inspect at the later of the times specified by
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
(i) Within 24,900 flight cycles or 49,800 flight hours,
whichever occurs first, since the modification specified in Airbus
Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus
Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997,
was accomplished.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.
(4) For Configuration 4 airplanes, having MSNs 0080 through 0155
inclusive: Inspect at the later of the times specified in paragraphs
(h)(4)(i) or (h)(4)(ii) of this AD.
(i) Prior to the accumulation of 54,300 flight cycles or 108,600
flight hours, whichever occurs first since airplane first flight.
(ii) Within 60 days after the effective date of this AD.
(i) Repair
If any crack is detected during any inspection required by
paragraph (g) of 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).
(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-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 the EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(k) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2014-0069, dated March 19, 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-2015-1422.
(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.
(3) The following service information was approved for IBR on
February 25, 2016.
(i) Airbus Service Bulletin A320-57-1178, Revision 01, dated May
28, 2014, including Appendix 01, dated May 28, 2014.
(ii) Reserved.
(4) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
[[Page 3319]]
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.
(5) 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.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 31, 2015.
Philip Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-00373 Filed 1-20-16; 8:45 am]
BILLING CODE 4910-13-P
