82 FR 27408 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 114 (June 15, 2017)

Page Range		27408-27411
FR Document		2017-12170

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.

Federal Register, Volume 82 Issue 114 (Thursday, June 15, 2017)

[Federal Register Volume 82, Number 114 (Thursday, June 15, 2017)]
[Rules and Regulations]
[Pages 27408-27411]
From the Federal Register Online [www.thefederalregister.org]
[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
http://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 http://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 http://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 http://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.

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 http://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 http://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: http://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

Federal Register / Vol. 82, No. 114 / Thursday, June 15, 2017 / Rules and Regulations 27409

5527) is Docket Management Facility, Model A321 series airplanes. The MCAI as proposed, except for minor editorial
U.S. Department of Transportation, states: changes. We have determined that these
Docket Operations, M–30, West Following the results of a new full scale minor changes:
Building Ground Floor, Room W12–140, fatigue test campaign on the A321 airframe • Are consistent with the intent that
1200 New Jersey Avenue SE., in the context of the A321 extended service was proposed in the NPRM for
Washington, DC 20590. goal, it was identified that cracks could correcting the unsafe condition; and
FOR FURTHER INFORMATION CONTACT: develop on the fastener holes of frame (FR) • Do not add any additional burden
Sanjay Ralhan, Aerospace Engineer, 35.1, FR 35.2, and FR 35.3 between stringers upon the public than was already
International Branch, ANM–116, (STR) 29 and STR 32 and at the FR 35.2 to proposed in the NPRM.
Slidebox junction (Triform fitting), both left
Transport Airplane Directorate, FAA, hand (LH) and right hand (RH) sides. Related Service Information Under 1
1601 Lind Avenue SW., Renton, WA This condition, if not detected and CFR Part 51
98057–3356; telephone 425–227–1405; corrected, could reduce the structural
fax 425–227–1149. integrity of the fuselage. Prompted by these Airbus issued the following service
SUPPLEMENTARY INFORMATION: findings, Airbus developed an inspection information. This service information
programme, published in Service Bulletin describes procedures for repetitive
Discussion (SB) A320–53–1308, SB A320–53–1309, SB rototest inspections for cracking of the
We issued a notice of proposed A320–53–1310, SB A320–53–1311, SB A320– affected frame locations, and contacting
rulemaking (NPRM) to amend 14 CFR 53–1312 and SB A320–53–1313, each Airbus for repair instructions. These
containing instructions for a different service bulletins are distinct because
part 39 by adding an AD that would
location. For the reasons described above,
apply to all Airbus Model A321 series they apply to different frame locations.
this [EASA] AD requires repetitive special
airplanes. The NPRM published in the detailed (rototest) inspections (SDI) of the • Airbus Service Bulletin A320–53–
Federal Register on February 21, 2017 affected frame locations and, depending on 1308, dated November 4, 2015.
(82 FR 11162). The NPRM was findings, accomplishment of a repair. • Airbus Service Bulletin A320–53–
prompted by a full scale fatigue test This [EASA] AD is considered an interim 1309, dated November 4, 2015.
campaign on these airplanes in the action, pending the development of a • Airbus Service Bulletin A320–53–
context of the extended service goal. permanent solution. 1310, dated November 4, 2015.
The NPRM proposed to require You may examine the MCAI in the • Airbus Service Bulletin A320–53–
inspections of the affected frame AD docket on the Internet at http:// 1311, dated November 4, 2015.
locations, and repair if necessary. We www.regulations.gov by searching for • Airbus Service Bulletin A320–53–
are issuing this AD to detect and correct and locating Docket No. FAA–2016– 1312, dated November 4, 2015.
cracking of the fastener holes at certain 9571. • Airbus Service Bulletin A320–53–
frame locations, which could result in 1313, dated November 4, 2015.
reduced structural integrity of the Comments This service information is reasonably
fuselage. We gave the public the opportunity to available because the interested parties
The European Aviation Safety Agency participate in developing this AD. We have access to it through their normal
(EASA), which is the Technical Agent considered the comment received. course of business or by the means
for the Member States of the European Attiya Jaura supported the NPRM. identified in the ADDRESSES section.
Union, has issued EASA Airworthiness
Directive 2016–0146, dated July 20, Conclusion Costs of Compliance
2016 (referred to after this as the We reviewed the relevant data, We estimate that this AD affects 176
Mandatory Continuing Airworthiness considered the comment received, and airplanes of U.S. registry.
Information, or ‘‘the MCAI’’), to correct determined that air safety and the We estimate the following costs to
an unsafe condition for certain Airbus public interest require adopting this AD comply with this AD:
ESTIMATED COSTS
Cost on
Action Labor cost Parts cost Cost per product U.S. operators

Inspection ................... 54 work-hours × $85 per hour = $4,590 per $1,070 per inspection $5,660 per inspection $996,160 per inspec-
inspection cycle. cycle. cycle. tion cycle.

We have no way to estimate the costs We are issuing this rulemaking under Regulatory Findings
to do any necessary repairs that would the authority described in ‘‘Subtitle VII,
be required based on the results of the Part A, Subpart III, Section 44701: We determined that this AD will not
inspection. We have no way of General requirements.’’ Under that have federalism implications under
determining the number of aircraft that section, Congress charges the FAA with Executive Order 13132. This AD will
might need these repairs. promoting safe flight of civil aircraft in not have a substantial direct effect on
air commerce by prescribing regulations the States, on the relationship between
Authority for This Rulemaking the national government and the States,
for practices, methods, and procedures
Title 49 of the United States Code or on the distribution of power and
pmangrum on DSK3GDR082PROD with RULES

the Administrator finds necessary for
specifies the FAA’s authority to issue responsibilities among the various
safety in air commerce. This regulation
rules on aviation safety. Subtitle I, levels of government.
section 106, describes the authority of is within the scope of that authority
because it addresses an unsafe condition For the reasons discussed above, I
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more that is likely to exist or develop on certify that this AD:
detail the scope of the Agency’s products identified in this rulemaking 1. Is not a ‘‘significant regulatory
authority. action. action’’ under Executive Order 12866;

VerDate Sep<11>2014 14:00 Jun 14, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\15JNR1.SGM 15JNR1

27410 Federal Register / Vol. 82, No. 114 / Thursday, June 15, 2017 / Rules and Regulations

2. Is not a ‘‘significant rule’’ under the Authority: 49 U.S.C. 106(g), 40113, 44701. series airplanes in the context of the
DOT Regulatory Policies and Procedures extended service goal. It was determined that
§ 39.13 [Amended] cracks could develop on the fastener holes of
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in ■ 2. The FAA amends § 39.13 by adding certain frames on the left-hand (LH) and
Alaska; and the following new airworthiness right-hand (RH) sides of the affected
4. Will not have a significant directive (AD): airplanes. We are issuing this AD to detect
economic impact, positive or negative, and correct cracking of the fastener holes at
on a substantial number of small entities 2017–12–10 Airbus: Amendment 39–18925; certain frame locations, which could result in
Docket No. FAA–2016–9571; Directorate
under the criteria of the Regulatory reduced structural integrity of the fuselage.
Identifier 2016–NM–139–AD.
Flexibility Act. (f) Compliance
(a) Effective Date
List of Subjects in 14 CFR Part 39 Comply with this AD within the
This AD is effective July 20, 2017.
Air transportation, Aircraft, Aviation compliance times specified, unless already
safety, Incorporation by reference, (b) Affected ADs done.
Safety. None.
(g) Repetitive Inspections of the Frames,
Adoption of the Amendment (c) Applicability Stringers, and Slidebox Junctions
Accordingly, under the authority This AD applies to Airbus Model A321– At the applicable time specified in table 1
111, –112, –131, –211, –212, –213, –231, and to the introductory text of paragraph (g) of
delegated to me by the Administrator,
–232 airplanes, certificated in any category. this AD, do a rototest inspection for cracking
the FAA amends 14 CFR part 39 as
follows: (d) Subject at frame (FR) 35.1, FR 35.2, and FR 35.3 on
the LH and RH sides, in accordance with the
Air Transport Association (ATA) of
PART 39—AIRWORTHINESS America Code 53, Fuselage. Accomplishment Instructions of the Airbus
DIRECTIVES service information specified in paragraphs
(e) Reason (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of
■ 1. The authority citation for part 39 This AD was prompted by a full scale this AD. Repeat the inspection thereafter at
continues to read as follows: fatigue test campaign on Airbus Model A321 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 cycles or less ................................. Before exceeding 18,300 total 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 total flight cycles ........................... Before exceeding 23,600 total 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, 116, Transport Airplane Directorate, FAA; or (3) Required for Compliance (RC): Except
dated November 4, 2015 (FR 35.1 LH side). EASA; or Airbus’s EASA DOA. as required by paragraph (h) of this AD: If
(2) Airbus Service Bulletin A320–53–1309, any service information contains procedures
(i) Other FAA AD Provisions
dated November 4, 2015 (FR 35.1 RH side). or tests that are identified as RC, those
(3) Airbus Service Bulletin A320–53–1310, The following provisions also apply to this procedures and tests must be done to comply
dated November 4, 2015 (FR 35.2 LH side). AD:
with this AD; any procedures or tests that are
(4) Airbus Service Bulletin A320–53–1311, (1) Alternative Methods of Compliance
not identified as RC are recommended. Those
dated November 4, 2015 (FR 35.2 RH side). (AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane procedures and tests that are not identified
(5) Airbus Service Bulletin A320–53–1312,
Directorate, FAA, has the authority to as RC may be deviated from using accepted
dated November 4, 2015 (FR 35.3 LH side).
(6) Airbus Service Bulletin A320–53–1313, approve AMOCs for this AD, if requested methods in accordance with the operator’s
dated November 4, 2015 (FR 35.3 RH side). using the procedures found in 14 CFR 39.19. maintenance or inspection program without
In accordance with 14 CFR 39.19, send your obtaining approval of an AMOC, provided
(h) Corrective Action request to your principal inspector or local the procedures and tests identified as RC can
If any crack is found during any inspection Flight Standards District Office, as be done and the airplane can be put back in
required by the introductory text to appropriate. If sending information directly an airworthy condition. Any substitutions or
paragraph (g) of this AD: Before further flight, to the International Branch, send it to the changes to procedures or tests identified as
repair using a method approved by the attention of the person identified in RC require approval of an AMOC.
Manager, International Branch, ANM–116, paragraph (j)(2) of this AD. Information may
Transport Airplane Directorate, FAA; or the be emailed to: 9-ANM-116-AMOC- (j) Related Information
European Aviation Safety Agency (EASA); or REQUESTS@faa.gov. Before using any (1) Refer to Mandatory Continuing
Airbus’s EASA Design Organization approved AMOC, notify your appropriate Airworthiness Information (MCAI) EASA
Approval (DOA). Although the service principal inspector, or lacking a principal Airworthiness Directive 2016–0146, dated
information specified in paragraph (g) of this inspector, the manager of the local flight July 20, 2016, for related information. This
AD specifies to contact Airbus for repair standards district office/certificate holding MCAI may be found in the AD docket on the
instructions, and specifies that action as district office.
Internet at http://www.regulations.gov by
‘‘RC’’ (Required for Compliance), this AD (2) Contacting the Manufacturer: For any
searching for and locating Docket No. FAA–
pmangrum on DSK3GDR082PROD with RULES

requires repair as specified in this paragraph. requirement in this AD to obtain corrective
Repair of an airplane as required by this actions from a manufacturer, the action must 2016–9571.
paragraph does not constitute terminating be accomplished using a method approved (2) For more information about this AD,
action for the repetitive inspections required by the Manager, International Branch, ANM– contact Sanjay Ralhan, Aerospace Engineer,
by the introductory text to paragraph (g) of 116, Transport Airplane Directorate, FAA; or International Branch, ANM–116, Transport
this AD for that airplane, unless specified the EASA; or Airbus’s EASA DOA. If Airplane Directorate, FAA, 1601 Lind
otherwise in the repair instructions approved approved by the DOA, the approval must Avenue SW., Renton, WA 98057–3356;
by the Manager, International Branch, ANM– include the DOA-authorized signature. telephone 425–227–1405; fax 425–227–1149.

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Federal Register / Vol. 82, No. 114 / Thursday, June 15, 2017 / Rules and Regulations 27411

(k) Material Incorporated by Reference unrecoverable engine in-flight contraction of the high-pressure turbine
(1) The Director of the Federal Register shutdown (IFSD) after an ice crystal (HPT) case and reduced clearances in
approved the incorporation by reference icing event. This AD requires installing the HPT, with subsequent HPT damage
(IBR) of the service information listed in this a software standard eligible for and rotor seizure. A change to the EEC
paragraph under 5 U.S.C. 552(a) and 1 CFR installation and precludes the use of software can force the ACC to activate
part 51. electronic engine control (EEC) software at a higher rotor speed to prevent active
(2) You must use this service information standards earlier than SCN 5B/I. We are ACC during engine restart. The NPRM
as applicable to do the actions required by
issuing this AD to correct the unsafe proposed to preclude the use of EEC
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1308, condition on these products. software standards earlier than SCN 5B/
dated November 4, 2015. DATES: This AD is effective July 20, I. We are issuing this AD to prevent
(ii) Airbus Service Bulletin A320–53–1309, 2017. failure of the HPT, rotor seizure, failure
dated November 4, 2015. ADDRESSES: For service information
of one or more engines, loss of thrust
(iii) Airbus Service Bulletin A320–53–
identified in this final rule, contact Pratt control, and loss of the airplane.
1310, dated November 4, 2015.
(iv) Airbus Service Bulletin A320–53– & Whitney Division, 400 Main St., East Comments
1311, dated November 4, 2015. Hartford, CT 06118; phone: 800–565– We gave the public the opportunity to
(v) Airbus Service Bulletin A320–53–1312, 0140; fax: 860–565–5442. You may view participate in developing this AD. The
dated November 4, 2015. this service information at the FAA, following presents the comments
(vi) Airbus Service Bulletin A320–53– Engine & Propeller Directorate, 1200 received on the NPRM and the FAA’s
1313, dated November 4, 2015. District Avenue, Burlington, MA. For
(3) For service information identified in response to each comment. The Airline
information on the availability of this Pilots Association and United Airlines
this AD, contact Airbus, Airworthiness material at the FAA, call 781–238–7125.
Office—EIAS, 1 Rond Point Maurice support the NPRM.
Bellonte, 31707 Blagnac Cedex, France;
It is also available on the internet at
http://www.regulations.gov by searching Request To Change Compliance
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@ for and locating Docket No. FAA–2016– The Boeing Company, PW, Delta Air
airbus.com; Internet http://www.airbus.com. 9405. Lines, Inc., FedEx, and Rudy Pueschel
(4) You may view this service information requested removing the engine serial
Examining the AD Docket
at the FAA, Transport Airplane Directorate, number requirement for earlier
1601 Lind Avenue SW., Renton, WA. For You may examine the AD docket on compliance time and use the Asia
information on the availability of this the Internet at http:// Pacific regional requirement for earlier
material at the FAA, call 425–227–1221. www.regulations.gov by searching for
(5) You may view this service information compliance time. The change would
and locating Docket No. FAA–2016– properly capture the risk of icing events
that is incorporated by reference at the 9405; or in person at the Docket
National Archives and Records in the Asia Pacific region. This change
Administration (NARA). For information on
Management Facility between 9 a.m. would also match the referenced alert
the availability of this material at NARA, call and 5 p.m., Monday through Friday, service bulletin (ASB).
202–741–6030, or go to: http:// except Federal holidays. The AD docket We disagree. There are difficulties in
www.archives.gov/federal-register/cfr/ibr- contains this AD, the regulatory compliance and enforcement for
locations.html. evaluation, any comments received, and regulations based on regions. Using
Issued in Renton, Washington, on June 2, other information. The address for the engines serial numbers (S/Ns) that are
2017. Docket Office (phone: 800–647–5527) is currently known to operate in the area
Michael Kaszycki, Document Management Facility, U.S. was our approach to best capture the
Acting Manager, Transport Airplane
Department of Transportation, Docket higher risk engines while easing
Directorate, Aircraft Certification Service. Operations, M–30, West Building compliance. The unsafe condition is
[FR Doc. 2017–12170 Filed 6–14–17; 8:45 am]
Ground Floor, Room W12–140, 1200 addressed by upgrading at least one
New Jersey Avenue SE., Washington, engine per airplane on all known
BILLING CODE 4910–13–P
DC 20590. engines currently operating in the Asia
FOR FURTHER INFORMATION CONTACT: Pacific region within the shorter
DEPARTMENT OF TRANSPORTATION Kevin Clark, Aerospace Engineer, compliance period. Finally, this AD
Engine Certification Office, FAA, Engine requires all engines with EEC model
Federal Aviation Administration & Propeller Directorate, 1200 District numbers EEC104–40 and EEC104–60 to
Avenue, Burlington, MA 01803; phone: upgrade software earlier than software
14 CFR Part 39 781–238–7088; fax: 781–238–7199; standard SCN 5B/I by 2024. We did not
email: kevin.m.clark@faa.gov. change this AD.
[Docket No. FAA–2016–9405; Directorate
Identifier 2016–NE–22–AD; Amendment 39– SUPPLEMENTARY INFORMATION:
Request To Change Method To Identify
18918; AD 2017–12–03] Discussion Engines Affected by Earlier Compliance
RIN 2120–AA64 We issued a notice of proposed Time
rulemaking (NPRM) to amend 14 CFR Delta Air Lines, Inc. and FedEx
Airworthiness Directives; Pratt & part 39 by adding an AD that would requested removing the engine serial
Whitney Division Turbofan Engines apply to certain PW PW2037, number requirement for earlier
AGENCY: Federal Aviation PW2037M, and PW2040 turbofan compliance time and use extended
Administration (FAA), DOT. engines. The NPRM published in the range twin-engine operations (ETOPs) or
pmangrum on DSK3GDR082PROD with RULES

ACTION: Final rule. Federal Register on January 5, 2017 (82 Aircraft Tail Number requirements for
FR 1265). The NPRM was prompted by earlier compliance time. The change
SUMMARY: We are adopting a new an unrecoverable engine IFSD after an was requested to ease with compliance
airworthiness directive (AD) for certain ice crystal icing event. An attempt to and help properly capture the safety risk
Pratt & Whitney Division (PW) PW2037, rapidly restart the engine was made of operating in the Asia Pacific region.
PW2037M, and PW2040 turbofan while the EEC had the Active Clearance We disagree. Operators may have
engines. This AD was prompted by an Control (ACC) turned on, which caused ETOPs flights that do not operate in the

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Document Created: 2017-06-15 01:03:50
Document Modified: 2017-06-15 01:03:50

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective July 20, 2017.
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.
FR Citation		82 FR 27408
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

82 FR 27408 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 114 (June 15, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration