Airworthiness Directives; Airbus Airplanes, 32063-32066 [2015-13342]
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Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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 adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2015–1423; Directorate Identifier 2014–
NM–173–AD.
(a) Comments Due Date
We must receive comments by July 20,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 757–200 series airplanes modified by
the applicable supplemental type certificate
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) ST01529SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/
0/0AF09C3701A237EE86257A5D0064B3AA?
OpenDocument&Highlight=st01529se).
(2) ST02278SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/
0/E54B5289A2E9F6EF86257B7F0056EDAF?
OpenDocument&Highlight=st02278se).
(d) Subject
Air Transport Association (ATA) of
America Code 11, Placards and Markings.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Installation
Within 90 days after the effective date of
this AD, install a new placard and bracket,
replace the existing placard, and replace the
main cargo door control panel, in accordance
with the Accomplishment Instructions of
17:42 Jun 04, 2015
Jkt 235001
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (i)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(i) Related Information
(1) For more information about this AD,
contact Narinder Luthra, Aerospace Engineer,
Airframe Branch, ANM 120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6513; fax: 425–917–6590;
email: Narinder.Luthra@faa.gov.
(2) For service information identified in
this AD, contact Precision Conversions LLC,
4900 SW Griffith Drive, Suite 133, Beaverton,
OR 97005; ATTN: Steven A. Lopez; phone:
503–601–3001; email: Steven.Lopez@
precisionaircraft.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.
Issued in Renton, Washington, on May 18,
2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–13358 Filed 6–4–15; 8:45 am]
BILLING CODE 4910–13–P
(e) Unsafe Condition
This AD was prompted by reports of a
main cargo door being blown past its full
open position while on the ground during
gusty wind conditions, which resulted in
uncontrolled fall down to its closed position.
We are issuing this AD to prevent damage to
the main cargo door, which could result in
rapid decompression, leading to in-flight
breakup.
VerDate Sep<11>2014
Precision Conversions LLC Service Bulletin
PC–757–11–0023, dated August 1, 2014.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1422; Directorate
Identifier 2014–NM–125–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 98–18–26,
for certain Airbus Model A320 series
airplanes. AD 98–18–26 currently
SUMMARY:
PO 00000
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32063
requires repetitive inspections to detect
fatigue cracking of the front spar vertical
stringers on the wings; and repair, if
necessary. Since we issued AD 98–18–
26, we have received 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.
This proposed AD would require
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, and a rototest inspection for
cracking of the fastener holes of the
front spar vertical stringers on frame 36,
and repair if necessary. We are
proposing 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: We must receive comments on
this proposed AD by July 20, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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.
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–
1422; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
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Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules
except Federal holidays. The AD docket
contains this proposed 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. Comments will
be available in the AD docket shortly
after receipt.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–1422; Directorate Identifier
2014–NM–125–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Discussion
On August 28, 1998, we issued AD
98–18–26, Amendment 39–10742 (63
FR 47423, September 8, 1998). AD 98–
18–26 requires repetitive inspections to
detect fatigue cracking of the front spar
vertical stringers on the wings, which
could result in the reduced structural
integrity of the airframe on certain
Airbus Model A320 series airplanes. AD
98–18–26 contains a modification that
provides a terminating action for the
repetitive inspection requirements.
Since we issued AD 98–18–26,
Amendment 39–10742 (63 FR 47423,
September 8, 1998), we have received
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 where shims
were installed under the heads of 2
fasteners at the top end of the front spar
vertical stringers using Airbus Service
Bulletin A320–57–1017, dated
September 3, 1991; or Airbus Service
Bulletin A320–57–1017, Revision 01,
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17:42 Jun 04, 2015
Jkt 235001
dated March 17, 1997, or on which
modification 21290P1546 was
accomplished during production.
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 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
PO 00000
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Sfmt 4702
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 by searching for
and locating Docket No. FAA–2015–
1422.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–57–1178, Revision 01, 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. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI. 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 of this NPRM.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
Although EASA AD 2014–0069, dated
March 19, 2014, specifies to accomplish
an HFEC inspection for cracking of the
vertical stiffeners radius, this proposed
AD would require accomplishing an
HFEC inspection for cracking of the
radius of the front spar vertical
stringers, since Airbus Service Bulletin
A320–57–1178, Revision 01, Appendix
01, dated May 28, 2014, specifies the
inspection is of the front spar vertical
stringers.
Costs of Compliance
We estimate that this proposed AD
affects 17 airplanes of U.S. registry.
We also estimate that it would take
about 24 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
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Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $34,680, or $2,040 per product.
In addition, we estimate that any
necessary follow-on actions would 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
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.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed regulation:
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.
VerDate Sep<11>2014
17:42 Jun 04, 2015
Jkt 235001
§ 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:
■
Airbus: Docket No. FAA–2015–1422;
Directorate Identifier 2014–NM–125–AD.
(a) Comments Due Date
We must receive comments by July 20,
2015.
(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
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,
including Appendix 01, dated May 28, 2014.
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32065
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
manufacturer serial number (MSN) 0001
though 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: At the later of the
times specified by paragraphs (h)(1)(i)
through (h)(1)(iii) of this AD:
(i) The later of the times specified by
paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this
AD:
(A) Within 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) 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) 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
MSN 0001 to 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: 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
MSN 0001 to 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
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March 17, 1997: 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
MSN 0080 to 0155 inclusive:
At the later of the times specified in
paragraphs (h)(4)(i) or (h)(4)(ii) of this AD:
(i) Before exceeding 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.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(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, 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
(1) 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
VerDate Sep<11>2014
19:05 Jun 04, 2015
Jkt 235001
searching for and locating Docket No. FAA–
2015–1422.
(2) 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 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.
Issued in Renton, Washington, on May 18,
2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–13342 Filed 6–4–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1421; Directorate
Identifier 2014–NM–177–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–300
and –300F series airplanes. This
proposed AD was prompted by reports
of fatigue cracking on airplanes with
Aviation Partners Boeing winglets
installed. This proposed AD would
require a high frequency eddy current
(HFEC) inspection for cracking of the
lower outboard wing skin, and repair or
modification if necessary. This
proposed AD would also require one of
three follow-on actions: Repeating the
HFEC inspections; modifying certain
internal stringers and oversizing and
plugging the existing fastener holes of
the lower wing; or modifying the
external doubler/tripler and doing
repetitive post-modification inspections.
We are proposing this AD to prevent
fatigue cracking in the lower outboard
wing skin, which could result in failure
and subsequent separation of the wing
and winglet and consequent reduced
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by July 20, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
SUMMARY:
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Aviation
Partners Boeing, 2811 S. 102nd Street,
Suite 200, Seattle, WA 98168; telephone
206–762–1171; Internet https://
www.aviationpartnersboeing.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.
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–
1421; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Allen Rauschendorfer, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6487;
fax: 425–917–6590; email:
Allen.Rauschendorfer@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2015–1421; Directorate Identifier 2014–
NM–177–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
E:\FR\FM\05JNP1.SGM
05JNP1
]]>Agencies
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)]
[Proposed Rules]
[Pages 32063-32066]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13342]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-18-26,
for certain Airbus Model A320 series airplanes. AD 98-18-26 currently
requires repetitive inspections to detect fatigue cracking of the front
spar vertical stringers on the wings; and repair, if necessary. Since
we issued AD 98-18-26, we have received 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. This
proposed AD would require 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, and a rototest
inspection for cracking of the fastener holes of the front spar
vertical stringers on frame 36, and repair if necessary. We are
proposing 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: We must receive comments on this proposed AD by July 20, 2015.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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.
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-
1422; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday,
[[Page 32064]]
except Federal holidays. The AD docket contains this proposed 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. Comments will be available in the AD
docket shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1422;
Directorate Identifier 2014-NM-125-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On August 28, 1998, we issued AD 98-18-26, Amendment 39-10742 (63
FR 47423, September 8, 1998). AD 98-18-26 requires repetitive
inspections to detect fatigue cracking of the front spar vertical
stringers on the wings, which could result in the reduced structural
integrity of the airframe on certain Airbus Model A320 series
airplanes. AD 98-18-26 contains a modification that provides a
terminating action for the repetitive inspection requirements.
Since we issued AD 98-18-26, Amendment 39-10742 (63 FR 47423,
September 8, 1998), we have received 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 where shims were installed under the heads of 2 fasteners at
the top end of the front spar vertical stringers using Airbus Service
Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service
Bulletin A320-57-1017, Revision 01, dated March 17, 1997, or on which
modification 21290P1546 was accomplished during production.
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 by searching for and locating Docket No. FAA-2015-
1422.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-57-1178, Revision 01,
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. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI. 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 of this NPRM.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
Although EASA AD 2014-0069, dated March 19, 2014, specifies to
accomplish an HFEC inspection for cracking of the vertical stiffeners
radius, this proposed AD would require accomplishing an HFEC inspection
for cracking of the radius of the front spar vertical stringers, since
Airbus Service Bulletin A320-57-1178, Revision 01, Appendix 01, dated
May 28, 2014, specifies the inspection is of the front spar vertical
stringers.
Costs of Compliance
We estimate that this proposed AD affects 17 airplanes of U.S.
registry.
We also estimate that it would take about 24 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor
[[Page 32065]]
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this proposed AD on U.S. operators to be $34,680, or $2,040 per
product.
In addition, we estimate that any necessary follow-on actions would
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Airbus: Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-
125-AD.
(a) Comments Due Date
We must receive comments by July 20, 2015.
(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
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, 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 manufacturer serial
number (MSN) 0001 though 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: At the
later of the times specified by paragraphs (h)(1)(i) through
(h)(1)(iii) of this AD:
(i) The later of the times specified by paragraphs (h)(1)(i)(A)
and (h)(1)(i)(B) of this AD:
(A) Within 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) 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) 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 MSN 0001 to 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: 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 MSN 0001 to 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
[[Page 32066]]
March 17, 1997: 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 MSN 0080 to 0155
inclusive:
At the later of the times specified in paragraphs (h)(4)(i) or
(h)(4)(ii) of this AD:
(i) Before exceeding 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, 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
(1) 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.
(2) 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 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.
Issued in Renton, Washington, on May 18, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-13342 Filed 6-4-15; 8:45 am]
BILLING CODE 4910-13-P
