Airworthiness Directives; International Aero Engines AG Turbofan Engines, 32626-32629 [2017-14706]
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Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
jstallworth on DSK7TPTVN1PROD with RULES
(l) Credit for Previous Actions
This paragraph provides credit for actions
specified in paragraphs (i)(2) and (j) of this
AD, if those actions were performed before
the effective date of this AD using any of the
service information specified in paragraphs
(l)(1) through (l)(7) of this AD.
(1) Airbus Service Bulletin A320–49–1075,
dated September 22, 2006, which was
incorporated by reference in AD 2007–13–08.
(2) Airbus Service Bulletin A320–49–1077,
dated March 21, 2007, which is not
incorporated by reference in this AD.
(3) Airbus Service Bulletin A320–49–1077,
Revision 01, dated August 9, 2007, which is
not incorporated by reference in this AD.
(4) Airbus Service Bulletin A320–49–1077,
Revision 02, dated July 1, 2008, which is not
incorporated by reference in this AD.
(5) Airbus Service Bulletin A320–49–1077,
Revision 03, dated December 8, 2008, which
is not incorporated by reference in this AD.
(6) Airbus Service Bulletin A320–49–1107,
dated November 5, 2013, which is not
incorporated by reference in this AD.
(7) Airbus Service Bulletin A320–49–1107,
Revision 01, dated July 28, 2015, which is
not incorporated by reference in this AD.
(m) 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 manager of the International Branch,
send it to the attention of the person
identified in paragraph (n)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2007–13–08 are approved as AMOCs for the
corresponding provisions of paragraphs (g)
and (h) of 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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0176, dated August 31, 2016; corrected
September 1, 2016, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
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by searching for and locating Docket No.
FAA–2016–9567.
(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.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (o)(5) and (o)(6) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on August 21, 2017.
(i) Airbus Service Bulletin A320–49–1077,
Revision 04, dated February 27, 2013.
(ii) Airbus Service Bulletin A320–49–1098,
dated June 21, 2011.
(iii) Airbus Service Bulletin A320–49–
1102, dated January 3, 2012.
(iv) Airbus Service Bulletin A320–49–
1107, Revision 02, dated May 10, 2016.
(4) The following service information was
approved for IBR on July 25, 2007 (72 FR
33877, June 20, 2007).
(i) Airbus Service Bulletin A320–49–1068,
Revision 01, dated February 2, 2006.
(ii) Airbus Service Bulletin A320–49–1070,
dated July 28, 2006.
(iii) Airbus Service Bulletin A320–49–
1075, Revision 01, dated December 1, 2006.
(5) 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.
(6) 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.
(7) 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 29,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14469 Filed 7–14–17; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0021; Directorate
Identifier 2017–NE–01–AD; Amendment 39–
18951; AD 2017–14–07]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines AG Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
International Aero Engines AG (IAE)
V2522–A5, V2524–A5, V2527–A5,
V2527E–A5, V2527M–A5, V2530–A5,
V2533–A5, V2525–D5, V2528–D5, and
V2531–E5 turbofan engines. This AD
was prompted following a selfdisclosure by IAE regarding
manufacturing quality escapes. This AD
requires replacing the affected and
suspect parts within the time limits
specified in the compliance section. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 21,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 21, 2017.
ADDRESSES: For service information
identified in this final rule, contact
International Aero Engines AG, 400
Main Street, East Hartford, CT 06118;
phone: 860–565–0140; email: help24@
pw.utc.com; Internet: https://
fleetcare.pw.utc.com. 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–2017–
0021.
SUMMARY:
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–2017–
0021; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
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Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
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:
Brian Kierstead, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7772; fax: 781–238–7199;
email: brian.kierstead@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 IAE V2522–A5, V2524–
A5, V2527–A5, V2527E–A5, V2527M–
A5, V2530–A5, V2533–A5, V2525–D5,
V2528–D5, and V2531–E5 turbofan
engines. The NPRM published in the
Federal Register on March 14, 2017 (82
FR 13570). The NPRM was prompted
following a self-disclosure by IAE
regarding manufacturing quality
escapes. The NPRM proposed to require
replacing the affected and suspect parts
within the time limits specified in the
compliance section. We are issuing this
AD to prevent failure of high-energy,
rotating hardware, uncontained part
release, damage to the engine, and
damage to the airplane.
jstallworth on DSK7TPTVN1PROD with RULES
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Change Service Information
MTU and United Airlines (UAL)
requested that we revise the service
information citations in the
Applicability and Compliance
paragraphs of this AD to reference the
‘‘latest approved revision’’ or ‘‘latest
issue’’ of the service bulletin (SB).
Citing future issues/revisions would
avoid Alternative Method of
Compliance (AMOC) requests if the SBs
are updated.
We disagree. We are only authorized
to mandate use of SBs that we have
reviewed and which are published.
Since future revisions of SBs are not yet
published, we are not authorized to
mandate their use. We did not change
this AD.
Request To Change Compliance Time
MTU and UAL requested that we
revise the removal interval referenced in
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Compliance paragraph (g)(2) of this AD
from ‘‘when the high-pressure turbine
(HPT) module is disassembled and
access to the part is available’’. UAL
feels that the proposed compliance
period may not prevent part failure and
requests the compliance be revised to
‘‘anytime the HPT module is removed
from the engine’’. MTU believes that the
word ‘‘access’’ is unclear and requests
alignment with the IAE NewsFlash NF–
048, which recommends replacing at
‘‘next piece part exposure.’’
We disagree. Changing compliance to
‘‘next piece part exposure’’ would allow
parts to remain in service longer,
resulting in an unacceptable level of
risk. We also disagree with mandating
removal of the hardware upon
separation of the HPT module from the
engine because this would require an
earlier compliance than is required.
Neither MTU nor UAL submitted data to
support a change to the compliance
period. We did not change this AD.
Request To Change Part Eligibility
UAL requests that the AD elaborate
that a part eligible for installation
includes ‘‘any approved original
equipment manufacturer (OEM) part
number, be it new, or previously
operated, provided that it is not affected
by this AD.’’ UAL states that the
referenced SB(s) require the owner/
operator to ‘‘install a new part of a
specific part number.’’
We disagree. The installation of
specific hardware is not mandated by
this AD. Any part eligible for
installation, new or previously installed,
may be installed in place of the affected
part. We did not change this AD.
Request To Change Disposition of
Affected Hardware
UAL requests that this AD not include
the sections of the SBs that refer to how
the affected hardware is dispositioned
upon removal. United highlights
concerns with the reporting
requirements listed in the SB and does
not want this AD to incorporate by
reference (IBR) those sections of the
SB(s).
We agree. The disposition of this
hardware is not mandated by this AD.
We did not change this AD.
Request To Change Applicability
MTU requested that we remove the
V2531–E5 from the Summary and
Applicability sections of this AD. MTU
stated that the V2531–E5 is not listed as
an affected engine in the associated SBs.
We disagree. We have determined that
the IAE V2531–E5 turbofan engine
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32627
might have an affected part installed.
The IAE V2531–E5 turbofan engine is
included in the Applicability paragraph
of this AD to ensure those engines
comply with this AD in the event that
an affected part is installed on a V2531–
E5 engine. We did not change this AD.
Request To Change Costs of Compliance
MTU requested that we align the
‘‘Cost per product’’ and ‘‘Cost on U.S.
operators’’ with the latest SB
information. MTU cites that the ‘‘Cost
per product’’ and ‘‘Cost on U.S.
operators’’ as listed in the AD are lower
than the numbers given in the
associated SBs.
We disagree. The cost estimate listed
in the AD is pro-rated based on the part
cycles accrued and the cycles at which
the affected hardware will be removed
from service, versus the certified life.
The SB only lists new part cost. We did
not change this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule as proposed. 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
IAE Non-Modification Service
Bulletin (NMSB) V2500–ENG–72–0676,
dated October 14, 2016; IAE NMSB
V2500–ENG–72–0677, Revision 1, dated
January 11, 2017; IAE NMSB V2500–
ENG–72–0682, dated December 2, 2016;
IAE NMSB V2500–ENG–72–0681,
Revision 2, dated January 9, 2017; and
IAE NMSB V2500–ENG–72–0678,
Revision 1, dated January 5, 2017. Each
of the NMSBs describes procedures for
replacing a different affected part. 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 70
engines installed on airplanes of U.S.
registry.
We estimate the following costs to
comply with this AD:
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Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
ESTIMATED COSTS
Action
Removal
Removal
Removal
Removal
of
of
of
of
HPT
HPT
HPT
HPT
Labor cost
stage 2 air seal (cycle limited) .......................................
1st stage air seal (cycle limited) ....................................
stage 2 ring plate (cycle limited) ....................................
stage 2 ring plate (upon access) ...................................
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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, and 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.
jstallworth on DSK7TPTVN1PROD with RULES
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
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.
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$0
0
0
0
Parts cost
Cost per
product
$154,119.00
87,503.00
56,207.00
31,403.00
$154,119.00
87,503.00
56,207.00
31,403.00
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–14–07 International Aero Engines
AG: Amendment 39–18951; Docket No.
FAA–2017–0021; Directorate Identifier
2017–NE–01–AD.
(a) Effective Date
This AD is effective August 21, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to International Aero
Engines AG (IAE) V2522–A5, V2524–A5,
V2527–A5, V2527E–A5, V2527M–A5,
V2530–A5, V2533–A5, V2525–D5, V2528–
D5, and V2531–E5 turbofan engines, with
one or more of the following installed:
(i) High-pressure turbine (HPT) stage 2 air
seal, part number (P/N) 2A4157, with a serial
number (S/N) listed in Table 1 of IAE NonModification Service Bulletin (NMSB)
V2500–ENG–72–0676, dated October 14,
2016.
(ii) HPT 1st stage air seal, P/N 2A3423,
with an S/N listed in Table 1 of IAE NMSB
V2500–ENG–72–0677, Revision 1, dated
January 11, 2017; or IAE NMSB V2500–ENG–
72–0678, Revision 1, dated January 5, 2017.
(iii) HPT stage 2 ring plate, P/N 2A3437,
with an S/N listed in Table 1 of IAE NMSB
V2500–ENG–72–0682, dated December 2,
2016; or IAE NMSB V2500–ENG–72–0681,
Revision 2, dated January 9, 2017.
(2) Reserved.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7250, Turbine Engine.
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Cost on
U.S. operators
$308,238.00
175,006.00
112,414.00
2,041,195.00
(e) Unsafe Condition
This AD was prompted by several reports
by IAE of quality escapes during manufacture
of HPT stage 2 air seals, HPT 1st stage air
seals, and/or HPT stage 2 ring plates, at the
Pratt and Whitney Chengdu facility. We are
issuing this AD to prevent failure of highenergy, rotating hardware, uncontained part
release, damage to the engine, and damage to
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Remove the following hardware from
service before reaching the specified part
cycles since new listed in the service
instructions in paragraphs (g)(1)(i) through
(iii) of this AD, or within 50 cycles in service
after the effective date of this AD, whichever
occurs later, and replace with a part eligible
for installation:
(i) HPT stage 2 air seal, P/N 2A4157,
identified in Table 1 of IAE NMSB V2500–
ENG–72–0676, dated October 14, 2016.
(ii) HPT 1st stage air seal, P/N 2A3423,
identified in Table 1 of IAE NMSB V2500–
ENG–72–0677, Revision 1, dated January 11,
2017.
(iii) HPT stage 2 ring plate, P/N 2A3437,
identified in Table 1 of IAE NMSB V2500–
ENG–72–0682, dated December 2, 2016.
(2) After the effective date of this AD,
remove the following hardware from service
when the HPT module is disassembled and
access to the part is available and replace
with a part eligible for installation:
(i) HPT 1st stage air seal, P/N 2A3423,
identified in Accomplishment Instructions,
Table 1, of IAE NMSB V2500–ENG–72–0678,
Revision 1, dated January 5, 2017.
(ii) HPT stage 2 ring plate, P/N 2A3437,
identified in Accomplishment Instructions,
Table 1, of IAE NMSB V2500–ENG–72–0681,
Revision 2, dated January 9, 2017.
(h) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
(i) Related Information
For more information about this AD,
contact Brian Kierstead, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7772; fax: 781–238–7199; email:
brian.kierstead@faa.gov.
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(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 the AD specifies otherwise.
(i) International Aero Engines (IAE) NonModification Service Bulletin (NMSB)
V2500–ENG–72–0676, dated October 14,
2016.
(ii) IAE NMSB V2500–ENG–72–0677,
Revision 1, dated January 11, 2017.
(iii) IAE NMSB V2500–ENG–72–0678,
Revision 1, dated January 5, 2017.
(iv) IAE NMSB V2500–ENG–72–0681,
Revision 2, dated January 9, 2017.
(v) IAE NMSB V2500–ENG–72–0682, dated
December 2, 2016.
(3) For International Aero Engines service
information identified in this AD, contact
International Aero Engines AG, 400 Main
Street, East Hartford, CT 06118; phone: 860–
565–0140; email: help24@pw.utc.com;
Internet: https://fleetcare.pw.utc.com.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
(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 Burlington, Massachusetts, on
July 3, 2017.
Kevin Dickert,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
cracked fuel line shroud in the left cargo
compartment equipment tunnel. This
AD requires a check for the presence of
fuel at the fuel shroud drain; a high
frequency eddy current (HFEC)
inspection for cracked fuel line shrouds;
a pressure test of the drain system of the
tail tank fuel shroud and a pressure test
of the drain system of the aft fuselage
fuel shroud to determine cracking; and
corrective actions, if necessary. We are
issuing this AD to address the unsafe
condition on these products.
This AD is effective August 21,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publication listed in this AD
as of August 21, 2017.
DATES:
For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800–
0019, Long Beach, CA 90846–0001;
telephone 206–544–5000, extension 2;
fax 206–766–5683; Internet https://
www.myboeingfleet.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.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2015–
3637.
ADDRESSES:
Examining the AD Docket
[FR Doc. 2017–14706 Filed 7–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3637; Directorate
Identifier 2014–NM–219–AD; Amendment
39–18954; AD 2017–14–10]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA 2015–
3637; 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 final rule, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
jstallworth on DSK7TPTVN1PROD with RULES
AGENCY:
FOR FURTHER INFORMATION CONTACT:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model MD–11
and MD–11F airplanes. This AD was
prompted by report of fuel odor in the
cabin. Fuel was found leaking from a
SUPPLEMENTARY INFORMATION:
SUMMARY:
VerDate Sep<11>2014
14:51 Jul 14, 2017
Jkt 241001
Serj
Harutunian, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; telephone:
562–627–5254; fax: 562–627–5210;
email: serj.harutunian@faa.gov.
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
32629
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model MD–11 and MD–11F airplanes.
The NPRM published in the Federal
Register on September 29, 2015 (80 FR
58362) (‘‘the NPRM’’). The NPRM was
prompted by a report of fuel odor in the
cabin. Fuel was found leaking from a
cracked fuel line shroud in the left cargo
compartment equipment tunnel. The
NPRM proposed to require a check for
the presence of fuel at the fuel shroud
drain; a HFEC inspection for cracked
fuel line shrouds; a pressure test of the
drain system of the tail tank fuel shroud
and a pressure test of the drain system
of the aft fuselage fuel shroud to
determine if there is cracking; and
corrective actions, if necessary. We are
issuing this AD to detect and correct
fuel leaking from a cracked fuel line
shroud, which could result in fuel
accumulation below the cargo
compartment floor and consequent
increased risk of fire.
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.
Request To Withdraw the NPRM
United Parcel Service (UPS) requested
that the NPRM be withdrawn until
Boeing has the opportunity to work with
affected MD–11 operators to develop
accurate service information. UPS stated
that Boeing Alert Service Bulletin
MD11–28A148, dated August 29, 2014,
does not provide adequate guidance on
the inspection areas. UPS suggested that
we revise the NPRM to include specific
procedures for an HFEC inspection to
the area of the shroud adjacent to the
installed internal spacers as well as the
curved areas, provide procedures for
airplanes on which a previous repair
has been accomplished in the HFEC
inspection area, and specify that the
leak check be done only at the portion
of the tail tank transfer line and the #2
engine fuel feed line shroud drain
system running through the left-hand
portion of the aft lower cargo
compartment from approximately
airplane station 1501 to 2007.
We disagree with the commenter’s
request to withdraw or revise the
NPRM. Since the NPRM was published,
Boeing has released new service
information, which corrects certain
typographical errors and procedures in
an appendix, includes minor editorial
E:\FR\FM\17JYR1.SGM
17JYR1
]]>Agencies
[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)]
[Rules and Regulations]
[Pages 32626-32629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14706]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0021; Directorate Identifier 2017-NE-01-AD;
Amendment 39-18951; AD 2017-14-07]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527-A5,
V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5, and
V2531-E5 turbofan engines. This AD was prompted following a self-
disclosure by IAE regarding manufacturing quality escapes. This AD
requires replacing the affected and suspect parts within the time
limits specified in the compliance section. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective August 21, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 21,
2017.
ADDRESSES: For service information identified in this final rule,
contact International Aero Engines AG, 400 Main Street, East Hartford,
CT 06118; phone: 860-565-0140; email: help24@pw.utc.com; Internet:
https://fleetcare.pw.utc.com. 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-2017-0021.
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-2017-
0021; 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 final rule, the regulatory evaluation, any comments
received, and other information. The address for the Docket Office
(phone: 800-647-5527) is
[[Page 32627]]
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: Brian Kierstead, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781-
238-7199; email: brian.kierstead@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 IAE V2522-A5,
V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5,
V2528-D5, and V2531-E5 turbofan engines. The NPRM published in the
Federal Register on March 14, 2017 (82 FR 13570). The NPRM was prompted
following a self-disclosure by IAE regarding manufacturing quality
escapes. The NPRM proposed to require replacing the affected and
suspect parts within the time limits specified in the compliance
section. We are issuing this AD to prevent failure of high-energy,
rotating hardware, uncontained part release, damage to the engine, and
damage to the airplane.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Request To Change Service Information
MTU and United Airlines (UAL) requested that we revise the service
information citations in the Applicability and Compliance paragraphs of
this AD to reference the ``latest approved revision'' or ``latest
issue'' of the service bulletin (SB). Citing future issues/revisions
would avoid Alternative Method of Compliance (AMOC) requests if the SBs
are updated.
We disagree. We are only authorized to mandate use of SBs that we
have reviewed and which are published. Since future revisions of SBs
are not yet published, we are not authorized to mandate their use. We
did not change this AD.
Request To Change Compliance Time
MTU and UAL requested that we revise the removal interval
referenced in Compliance paragraph (g)(2) of this AD from ``when the
high-pressure turbine (HPT) module is disassembled and access to the
part is available''. UAL feels that the proposed compliance period may
not prevent part failure and requests the compliance be revised to
``anytime the HPT module is removed from the engine''. MTU believes
that the word ``access'' is unclear and requests alignment with the IAE
NewsFlash NF-048, which recommends replacing at ``next piece part
exposure.''
We disagree. Changing compliance to ``next piece part exposure''
would allow parts to remain in service longer, resulting in an
unacceptable level of risk. We also disagree with mandating removal of
the hardware upon separation of the HPT module from the engine because
this would require an earlier compliance than is required. Neither MTU
nor UAL submitted data to support a change to the compliance period. We
did not change this AD.
Request To Change Part Eligibility
UAL requests that the AD elaborate that a part eligible for
installation includes ``any approved original equipment manufacturer
(OEM) part number, be it new, or previously operated, provided that it
is not affected by this AD.'' UAL states that the referenced SB(s)
require the owner/operator to ``install a new part of a specific part
number.''
We disagree. The installation of specific hardware is not mandated
by this AD. Any part eligible for installation, new or previously
installed, may be installed in place of the affected part. We did not
change this AD.
Request To Change Disposition of Affected Hardware
UAL requests that this AD not include the sections of the SBs that
refer to how the affected hardware is dispositioned upon removal.
United highlights concerns with the reporting requirements listed in
the SB and does not want this AD to incorporate by reference (IBR)
those sections of the SB(s).
We agree. The disposition of this hardware is not mandated by this
AD. We did not change this AD.
Request To Change Applicability
MTU requested that we remove the V2531-E5 from the Summary and
Applicability sections of this AD. MTU stated that the V2531-E5 is not
listed as an affected engine in the associated SBs.
We disagree. We have determined that the IAE V2531-E5 turbofan
engine might have an affected part installed. The IAE V2531-E5 turbofan
engine is included in the Applicability paragraph of this AD to ensure
those engines comply with this AD in the event that an affected part is
installed on a V2531-E5 engine. We did not change this AD.
Request To Change Costs of Compliance
MTU requested that we align the ``Cost per product'' and ``Cost on
U.S. operators'' with the latest SB information. MTU cites that the
``Cost per product'' and ``Cost on U.S. operators'' as listed in the AD
are lower than the numbers given in the associated SBs.
We disagree. The cost estimate listed in the AD is pro-rated based
on the part cycles accrued and the cycles at which the affected
hardware will be removed from service, versus the certified life. The
SB only lists new part cost. We did not change this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule as proposed. 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
IAE Non-Modification Service Bulletin (NMSB) V2500-ENG-72-0676,
dated October 14, 2016; IAE NMSB V2500-ENG-72-0677, Revision 1, dated
January 11, 2017; IAE NMSB V2500-ENG-72-0682, dated December 2, 2016;
IAE NMSB V2500-ENG-72-0681, Revision 2, dated January 9, 2017; and IAE
NMSB V2500-ENG-72-0678, Revision 1, dated January 5, 2017. Each of the
NMSBs describes procedures for replacing a different affected part.
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 70 engines installed on airplanes
of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 32628]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Removal of HPT stage 2 air seal (cycle $0 $154,119.00 $154,119.00 $308,238.00
limited)....................................
Removal of HPT 1st stage air seal (cycle 0 87,503.00 87,503.00 175,006.00
limited)....................................
Removal of HPT stage 2 ring plate (cycle 0 56,207.00 56,207.00 112,414.00
limited)....................................
Removal of HPT stage 2 ring plate (upon 0 31,403.00 31,403.00 2,041,195.00
access).....................................
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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, and 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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):
2017-14-07 International Aero Engines AG: Amendment 39-18951; Docket
No. FAA-2017-0021; Directorate Identifier 2017-NE-01-AD.
(a) Effective Date
This AD is effective August 21, 2017.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to International Aero Engines AG (IAE)
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-
A5, V2525-D5, V2528-D5, and V2531-E5 turbofan engines, with one or
more of the following installed:
(i) High-pressure turbine (HPT) stage 2 air seal, part number
(P/N) 2A4157, with a serial number (S/N) listed in Table 1 of IAE
Non-Modification Service Bulletin (NMSB) V2500-ENG-72-0676, dated
October 14, 2016.
(ii) HPT 1st stage air seal, P/N 2A3423, with an S/N listed in
Table 1 of IAE NMSB V2500-ENG-72-0677, Revision 1, dated January 11,
2017; or IAE NMSB V2500-ENG-72-0678, Revision 1, dated January 5,
2017.
(iii) HPT stage 2 ring plate, P/N 2A3437, with an S/N listed in
Table 1 of IAE NMSB V2500-ENG-72-0682, dated December 2, 2016; or
IAE NMSB V2500-ENG-72-0681, Revision 2, dated January 9, 2017.
(2) Reserved.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine
Engine.
(e) Unsafe Condition
This AD was prompted by several reports by IAE of quality
escapes during manufacture of HPT stage 2 air seals, HPT 1st stage
air seals, and/or HPT stage 2 ring plates, at the Pratt and Whitney
Chengdu facility. We are issuing this AD to prevent failure of high-
energy, rotating hardware, uncontained part release, damage to the
engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Remove the following hardware from service before reaching
the specified part cycles since new listed in the service
instructions in paragraphs (g)(1)(i) through (iii) of this AD, or
within 50 cycles in service after the effective date of this AD,
whichever occurs later, and replace with a part eligible for
installation:
(i) HPT stage 2 air seal, P/N 2A4157, identified in Table 1 of
IAE NMSB V2500-ENG-72-0676, dated October 14, 2016.
(ii) HPT 1st stage air seal, P/N 2A3423, identified in Table 1
of IAE NMSB V2500-ENG-72-0677, Revision 1, dated January 11, 2017.
(iii) HPT stage 2 ring plate, P/N 2A3437, identified in Table 1
of IAE NMSB V2500-ENG-72-0682, dated December 2, 2016.
(2) After the effective date of this AD, remove the following
hardware from service when the HPT module is disassembled and access
to the part is available and replace with a part eligible for
installation:
(i) HPT 1st stage air seal, P/N 2A3423, identified in
Accomplishment Instructions, Table 1, of IAE NMSB V2500-ENG-72-0678,
Revision 1, dated January 5, 2017.
(ii) HPT stage 2 ring plate, P/N 2A3437, identified in
Accomplishment Instructions, Table 1, of IAE NMSB V2500-ENG-72-0681,
Revision 2, dated January 9, 2017.
(h) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: ANE-AD-AMOC@faa.gov.
(i) Related Information
For more information about this AD, contact Brian Kierstead,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803;
phone: 781-238-7772; fax: 781-238-7199; email:
brian.kierstead@faa.gov.
[[Page 32629]]
(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 the AD specifies otherwise.
(i) International Aero Engines (IAE) Non-Modification Service
Bulletin (NMSB) V2500-ENG-72-0676, dated October 14, 2016.
(ii) IAE NMSB V2500-ENG-72-0677, Revision 1, dated January 11,
2017.
(iii) IAE NMSB V2500-ENG-72-0678, Revision 1, dated January 5,
2017.
(iv) IAE NMSB V2500-ENG-72-0681, Revision 2, dated January 9,
2017.
(v) IAE NMSB V2500-ENG-72-0682, dated December 2, 2016.
(3) For International Aero Engines service information
identified in this AD, contact International Aero Engines AG, 400
Main Street, East Hartford, CT 06118; phone: 860-565-0140; email:
help24@pw.utc.com; Internet: https://fleetcare.pw.utc.com.
(4) You may view this service information at FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA. For
information on the availability of this material at the FAA, call
781-238-7125.
(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 Burlington, Massachusetts, on July 3, 2017.
Kevin Dickert,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2017-14706 Filed 7-14-17; 8:45 am]
BILLING CODE 4910-13-P
