Airworthiness Directives; Airbus Airplanes, 27408-27411 [2017-12170]
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27408
Federal Register / Vol. 82, No. 114 / Thursday, June 15, 2017 / Rules and Regulations
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings.
(e) Reason
This AD was prompted by a report that the
left-hand side (LHS) and right-hand side
(RHS) equipment racks were not designed to
support the actual weight of all the
equipment and the secondary direct current
power centers under all loading conditions.
We are issuing this AD to prevent structural
failure of the LHS or RHS equipment racks
in the event of a high energy emergency
landing or runway excursion, which could
result in blockage of the emergency exit for
the flightcrew.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Modification of the Equipment Racks
Within 90 months after the effective date
of this AD, do the modification required by
paragraph (g)(1) or (g)(2) of this AD, as
applicable.
(1) For airplanes having S/Ns 20003
through 20500 inclusive: Modify the
equipment racks having part numbers (P/Ns)
K1000070316–003 (LHS) and K1000070316–
004 (RHS), in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 100–25–39, dated October
26, 2015.
(2) For airplanes having S/Ns 20501
through 20532 inclusive: Modify the
equipment rack having P/N K1000070316–
004 (RHS only), in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 350–25–002, dated October
26, 2015.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, 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 New York ACO, send it to
ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO,
1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7300; fax
516–794–5531. Before using any approved
AMOC, notify your appropriate principal
inspector, or lacking a principal inspector,
the manager of the local flight standards
district office/certificate holding district
office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
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(i) Related Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2016–26, dated
September 14, 2016, 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–2016–9387.
(2) For more information about this AD,
contact Aziz Ahmed, Aerospace Engineer,
Airframe and Mechanical Systems Branch,
ANE–171, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7329; fax 516–794–5531.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 100–25–39,
dated October 26, 2015.
(ii) Bombardier Service Bulletin 350–25–
002, dated October 26, 2015.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone: 514–855–5000; fax: 514–
855–7401; email: thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 5,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9571; Directorate
Identifier 2016–NM–139–AD; Amendment
39–18925; AD 2017–12–10]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232
airplanes. This AD was prompted by a
full scale fatigue test campaign on these
airplanes in the context of the extended
service goal. This AD requires
inspections of the affected frame
locations, and repair if necessary. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 20,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 20, 2017.
ADDRESSES: For service information
identified in this final rule, 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 No. FAA–2016–
9571.
SUMMARY:
[FR Doc. 2017–12169 Filed 6–14–17; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9571; 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 Office (telephone 800–647–
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5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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 by adding an AD that would
apply to all Airbus Model A321 series
airplanes. The NPRM published in the
Federal Register on February 21, 2017
(82 FR 11162). The NPRM was
prompted by a full scale fatigue test
campaign on these airplanes in the
context of the extended service goal.
The NPRM proposed to require
inspections of the affected frame
locations, and repair if necessary. We
are issuing this AD to detect and correct
cracking of the fastener holes at certain
frame locations, which could result in
reduced structural integrity of the
fuselage.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0146, dated July 20,
2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A321 series airplanes. The MCAI
states:
Following the results of a new full scale
fatigue test campaign on the A321 airframe
in the context of the A321 extended service
goal, it was identified that cracks could
develop on the fastener holes of frame (FR)
35.1, FR 35.2, and FR 35.3 between stringers
(STR) 29 and STR 32 and at the FR 35.2 to
Slidebox junction (Triform fitting), both left
hand (LH) and right hand (RH) sides.
This condition, if not detected and
corrected, could reduce the structural
integrity of the fuselage. Prompted by these
findings, Airbus developed an inspection
programme, published in Service Bulletin
(SB) A320–53–1308, SB A320–53–1309, SB
A320–53–1310, SB A320–53–1311, SB A320–
53–1312 and SB A320–53–1313, each
containing instructions for a different
location. For the reasons described above,
this [EASA] AD requires repetitive special
detailed (rototest) inspections (SDI) of the
affected frame locations and, depending on
findings, accomplishment of a repair.
This [EASA] AD is considered an interim
action, pending the development of a
permanent solution.
27409
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Attiya Jaura supported the NPRM.
Airbus issued the following service
information. This service information
describes procedures for repetitive
rototest inspections for cracking of the
affected frame locations, and contacting
Airbus for repair instructions. These
service bulletins are distinct because
they apply to different frame locations.
• Airbus Service Bulletin A320–53–
1308, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1309, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1310, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1311, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1312, dated November 4, 2015.
• Airbus Service Bulletin A320–53–
1313, dated November 4, 2015.
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.
Conclusion
Costs of Compliance
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
We estimate that this AD affects 176
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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–2016–
9571.
Comments
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Inspection ...................
54 work-hours × $85 per hour = $4,590 per
inspection cycle.
$1,070 per inspection
cycle.
$5,660 per inspection
cycle.
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We have no way to estimate the costs
to do any necessary repairs that would
be required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need these repairs.
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.
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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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Cost on
U.S. operators
$996,160 per inspection cycle.
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;
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Federal Register / Vol. 82, No. 114 / Thursday, June 15, 2017 / Rules and Regulations
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.
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):
■
2017–12–10 Airbus: Amendment 39–18925;
Docket No. FAA–2016–9571; Directorate
Identifier 2016–NM–139–AD.
(a) Effective Date
This AD is effective July 20, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes, certificated in any category.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
PART 39—AIRWORTHINESS
DIRECTIVES
(e) Reason
This AD was prompted by a full scale
fatigue test campaign on Airbus Model A321
1. The authority citation for part 39
continues to read as follows:
■
series airplanes in the context of the
extended service goal. It was determined that
cracks could develop on the fastener holes of
certain frames on the left-hand (LH) and
right-hand (RH) sides of the affected
airplanes. We are issuing this AD to detect
and correct cracking of the fastener holes at
certain frame locations, which could result in
reduced structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections of the Frames,
Stringers, and Slidebox Junctions
At the applicable time specified in table 1
to the introductory text of paragraph (g) of
this AD, do a rototest inspection for cracking
at frame (FR) 35.1, FR 35.2, and FR 35.3 on
the LH and RH sides, in accordance with the
Accomplishment Instructions of the Airbus
service information specified in paragraphs
(g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of
this AD. Repeat the inspection thereafter at
intervals not to exceed 5,300 flight cycles.
TABLE 1 TO THE INTRODUCTORY TEXT OF PARAGRAPH (g) OF THIS AD—INSPECTION THRESHOLD
Airplane accumulated total flight cycles at the effective date of this AD
For airplanes with 18,300 total flight cycles or less .................................
For airplanes with more than 18,300 total flight cycles ...........................
(1) Airbus Service Bulletin A320–53–1308,
dated November 4, 2015 (FR 35.1 LH side).
(2) Airbus Service Bulletin A320–53–1309,
dated November 4, 2015 (FR 35.1 RH side).
(3) Airbus Service Bulletin A320–53–1310,
dated November 4, 2015 (FR 35.2 LH side).
(4) Airbus Service Bulletin A320–53–1311,
dated November 4, 2015 (FR 35.2 RH side).
(5) Airbus Service Bulletin A320–53–1312,
dated November 4, 2015 (FR 35.3 LH side).
(6) Airbus Service Bulletin A320–53–1313,
dated November 4, 2015 (FR 35.3 RH side).
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(h) Corrective Action
If any crack is found during any inspection
required by the introductory text to
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). Although the service
information specified in paragraph (g) of this
AD specifies to contact Airbus for repair
instructions, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
requires repair as specified in this paragraph.
Repair of an airplane as required by this
paragraph does not constitute terminating
action for the repetitive inspections required
by the introductory text to paragraph (g) of
this AD for that airplane, unless specified
otherwise in the repair instructions approved
by the Manager, International Branch, ANM–
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Compliance time
Before
after
Before
after
exceeding 18,300 total flight cycles, or within 5,300 flight cycles
the effective date of this AD, whichever occurs later.
exceeding 23,600 total flight cycles, or within 2,100 flight cycles
the effective date of this AD, whichever occurs later.
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA.
(i) 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 the
attention of the person identified in
paragraph (j)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
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(3) Required for Compliance (RC): Except
as required by paragraph (h) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0146, dated
July 20, 2016, 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–
2016–9571.
(2) For more information about this AD,
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.
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(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1308,
dated November 4, 2015.
(ii) Airbus Service Bulletin A320–53–1309,
dated November 4, 2015.
(iii) Airbus Service Bulletin A320–53–
1310, dated November 4, 2015.
(iv) Airbus Service Bulletin A320–53–
1311, dated November 4, 2015.
(v) Airbus Service Bulletin A320–53–1312,
dated November 4, 2015.
(vi) Airbus Service Bulletin A320–53–
1313, dated November 4, 2015.
(3) 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.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 2,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12170 Filed 6–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9405; Directorate
Identifier 2016–NE–22–AD; Amendment 39–
18918; AD 2017–12–03]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Division Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
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AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Pratt & Whitney Division (PW) PW2037,
PW2037M, and PW2040 turbofan
engines. This AD was prompted by an
SUMMARY:
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unrecoverable engine in-flight
shutdown (IFSD) after an ice crystal
icing event. This AD requires installing
a software standard eligible for
installation and precludes the use of
electronic engine control (EEC) software
standards earlier than SCN 5B/I. We are
issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective July 20,
2017.
ADDRESSES: For service information
identified in this final rule, contact Pratt
& Whitney Division, 400 Main St., East
Hartford, CT 06118; phone: 800–565–
0140; fax: 860–565–5442. You may view
this service information at the FAA,
Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2016–
9405.
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–2016–
9405; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kevin Clark, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7088; fax: 781–238–7199;
email: kevin.m.clark@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain PW PW2037,
PW2037M, and PW2040 turbofan
engines. The NPRM published in the
Federal Register on January 5, 2017 (82
FR 1265). The NPRM was prompted by
an unrecoverable engine IFSD after an
ice crystal icing event. An attempt to
rapidly restart the engine was made
while the EEC had the Active Clearance
Control (ACC) turned on, which caused
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27411
contraction of the high-pressure turbine
(HPT) case and reduced clearances in
the HPT, with subsequent HPT damage
and rotor seizure. A change to the EEC
software can force the ACC to activate
at a higher rotor speed to prevent active
ACC during engine restart. The NPRM
proposed to preclude the use of EEC
software standards earlier than SCN 5B/
I. We are issuing this AD to prevent
failure of the HPT, rotor seizure, failure
of one or more engines, loss of thrust
control, and loss of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment. The Airline
Pilots Association and United Airlines
support the NPRM.
Request To Change Compliance
The Boeing Company, PW, Delta Air
Lines, Inc., FedEx, and Rudy Pueschel
requested removing the engine serial
number requirement for earlier
compliance time and use the Asia
Pacific regional requirement for earlier
compliance time. The change would
properly capture the risk of icing events
in the Asia Pacific region. This change
would also match the referenced alert
service bulletin (ASB).
We disagree. There are difficulties in
compliance and enforcement for
regulations based on regions. Using
engines serial numbers (S/Ns) that are
currently known to operate in the area
was our approach to best capture the
higher risk engines while easing
compliance. The unsafe condition is
addressed by upgrading at least one
engine per airplane on all known
engines currently operating in the Asia
Pacific region within the shorter
compliance period. Finally, this AD
requires all engines with EEC model
numbers EEC104–40 and EEC104–60 to
upgrade software earlier than software
standard SCN 5B/I by 2024. We did not
change this AD.
Request To Change Method To Identify
Engines Affected by Earlier Compliance
Time
Delta Air Lines, Inc. and FedEx
requested removing the engine serial
number requirement for earlier
compliance time and use extended
range twin-engine operations (ETOPs) or
Aircraft Tail Number requirements for
earlier compliance time. The change
was requested to ease with compliance
and help properly capture the safety risk
of operating in the Asia Pacific region.
We disagree. Operators may have
ETOPs flights that do not operate in the
E:\FR\FM\15JNR1.SGM
15JNR1
Agencies
[Federal Register Volume 82, Number 114 (Thursday, June 15, 2017)]
[Rules and Regulations]
[Pages 27408-27411]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12170]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9571; Directorate Identifier 2016-NM-139-AD;
Amendment 39-18925; AD 2017-12-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. This AD was prompted by a full scale fatigue test campaign
on these airplanes in the context of the extended service goal. This AD
requires inspections of the affected frame locations, and repair if
necessary. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective July 20, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 20,
2017.
ADDRESSES: For service information identified in this final rule,
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 No. FAA-2016-
9571.
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-2016-
9571; 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 Office (telephone
800-647-
[[Page 27409]]
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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 by adding an AD that would apply to all Airbus Model A321
series airplanes. The NPRM published in the Federal Register on
February 21, 2017 (82 FR 11162). The NPRM was prompted by a full scale
fatigue test campaign on these airplanes in the context of the extended
service goal. The NPRM proposed to require inspections of the affected
frame locations, and repair if necessary. We are issuing this AD to
detect and correct cracking of the fastener holes at certain frame
locations, which could result in reduced structural integrity of the
fuselage.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2016-0146, dated July 20, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A321 series airplanes. The MCAI states:
Following the results of a new full scale fatigue test campaign
on the A321 airframe in the context of the A321 extended service
goal, it was identified that cracks could develop on the fastener
holes of frame (FR) 35.1, FR 35.2, and FR 35.3 between stringers
(STR) 29 and STR 32 and at the FR 35.2 to Slidebox junction (Triform
fitting), both left hand (LH) and right hand (RH) sides.
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage. Prompted by these findings,
Airbus developed an inspection programme, published in Service
Bulletin (SB) A320-53-1308, SB A320-53-1309, SB A320-53-1310, SB
A320-53-1311, SB A320-53-1312 and SB A320-53-1313, each containing
instructions for a different location. For the reasons described
above, this [EASA] AD requires repetitive special detailed
(rototest) inspections (SDI) of the affected frame locations and,
depending on findings, accomplishment of a repair.
This [EASA] AD is considered an interim action, pending the
development of a permanent solution.
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-2016-
9571.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. Attiya Jaura supported the
NPRM.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed, except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus issued the following service information. This service
information describes procedures for repetitive rototest inspections
for cracking of the affected frame locations, and contacting Airbus for
repair instructions. These service bulletins are distinct because they
apply to different frame locations.
Airbus Service Bulletin A320-53-1308, dated November 4,
2015.
Airbus Service Bulletin A320-53-1309, dated November 4,
2015.
Airbus Service Bulletin A320-53-1310, dated November 4,
2015.
Airbus Service Bulletin A320-53-1311, dated November 4,
2015.
Airbus Service Bulletin A320-53-1312, dated November 4,
2015.
Airbus Service Bulletin A320-53-1313, dated November 4,
2015.
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 176 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection..................... 54 work-hours x $85 $1,070 per $5,660 per $996,160 per
per hour = $4,590 per inspection cycle. inspection cycle. inspection
inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
We have no way to estimate the costs to do any necessary repairs
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
repairs.
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;
[[Page 27410]]
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2017-12-10 Airbus: Amendment 39-18925; Docket No. FAA-2016-9571;
Directorate Identifier 2016-NM-139-AD.
(a) Effective Date
This AD is effective July 20, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a full scale fatigue test campaign on
Airbus Model A321 series airplanes in the context of the extended
service goal. It was determined that cracks could develop on the
fastener holes of certain frames on the left-hand (LH) and right-
hand (RH) sides of the affected airplanes. We are issuing this AD to
detect and correct cracking of the fastener holes at certain frame
locations, which could result in reduced structural integrity of the
fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections of the Frames, Stringers, and Slidebox
Junctions
At the applicable time specified in table 1 to the introductory
text of paragraph (g) of this AD, do a rototest inspection for
cracking at frame (FR) 35.1, FR 35.2, and FR 35.3 on the LH and RH
sides, in accordance with the Accomplishment Instructions of the
Airbus service information specified in paragraphs (g)(1), (g)(2),
(g)(3), (g)(4), (g)(5), and (g)(6) of this AD. Repeat the inspection
thereafter at intervals not to exceed 5,300 flight cycles.
Table 1 to the Introductory Text of Paragraph (g) of This AD--Inspection
Threshold
------------------------------------------------------------------------
Airplane accumulated total flight
cycles at the effective date of this AD Compliance time
------------------------------------------------------------------------
For airplanes with 18,300 total flight Before exceeding 18,300 total
cycles or less. flight cycles, or within 5,300
flight cycles after the
effective date of this AD,
whichever occurs later.
For airplanes with more than 18,300 Before exceeding 23,600 total
total flight cycles. flight cycles, or within 2,100
flight cycles after the
effective date of this AD,
whichever occurs later.
------------------------------------------------------------------------
(1) Airbus Service Bulletin A320-53-1308, dated November 4, 2015
(FR 35.1 LH side).
(2) Airbus Service Bulletin A320-53-1309, dated November 4, 2015
(FR 35.1 RH side).
(3) Airbus Service Bulletin A320-53-1310, dated November 4, 2015
(FR 35.2 LH side).
(4) Airbus Service Bulletin A320-53-1311, dated November 4, 2015
(FR 35.2 RH side).
(5) Airbus Service Bulletin A320-53-1312, dated November 4, 2015
(FR 35.3 LH side).
(6) Airbus Service Bulletin A320-53-1313, dated November 4, 2015
(FR 35.3 RH side).
(h) Corrective Action
If any crack is found during any inspection required by the
introductory text to 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). Although the service information
specified in paragraph (g) of this AD specifies to contact Airbus
for repair instructions, and specifies that action as ``RC''
(Required for Compliance), this AD requires repair as specified in
this paragraph. Repair of an airplane as required by this paragraph
does not constitute terminating action for the repetitive
inspections required by the introductory text to paragraph (g) of
this AD for that airplane, unless specified otherwise in the repair
instructions approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(i) 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 the attention of
the person identified in paragraph (j)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: 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.
(3) Required for Compliance (RC): Except as required by
paragraph (h) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0146, dated July 20, 2016,
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-2016-9571.
(2) For more information about this AD, 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.
[[Page 27411]]
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-53-1308, dated November 4,
2015.
(ii) Airbus Service Bulletin A320-53-1309, dated November 4,
2015.
(iii) Airbus Service Bulletin A320-53-1310, dated November 4,
2015.
(iv) Airbus Service Bulletin A320-53-1311, dated November 4,
2015.
(v) Airbus Service Bulletin A320-53-1312, dated November 4,
2015.
(vi) Airbus Service Bulletin A320-53-1313, dated November 4,
2015.
(3) 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.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-12170 Filed 6-14-17; 8:45 am]
BILLING CODE 4910-13-P