Airworthiness Directives; Airbus Airplanes, 32622-32626 [2017-14469]
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Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement
Before the accumulation of 7,500 total
flight cycles, or within 10 days after the
effective date of this AD, whichever occurs
later, do the actions required by paragraphs
(g)(1) through (g)(4) of this AD, in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 100–53–32,
dated February 16, 2017.
(1) Remove the fasteners attaching the
machined center fitting (part number
1005340715), wing-to-fuselage attachment
and splice fitting at fuselage station 587, to
the rear spar frame lower flange splice.
(2) Do a general visual inspection of the
fasteners for damage and an eddy current
inspection of the fastener holes for damage.
(3) Rework the fastener holes as applicable.
(4) Replace the fasteners with self-aligning
fasteners and self-aligning collars.
(h) Exception to Service Information
Specifications
If any damage of any fastener hole is found
during any inspection required by paragraph
(g)(2) of this AD, before further flight, repair
using a method approved by the Manager,
New York Aircraft Certification Office (ACO),
ANE–170, FAA; or Transport Canada Civil
Aviation (TCCA); or Bombardier, Inc.’s TCCA
Design Approval Organization (DAO).
jstallworth on DSK7TPTVN1PROD with RULES
(i) Reporting
Submit a report of the findings of the
inspections required by paragraph (g)(2) of
this AD, as specified in Appendix 1 of
Bombardier Service Bulletin 100–53–32,
dated February 16, 2017, to bbad_challenger_
stress@aero.bombardier.com, at the
applicable time specified in paragraph (i)(1)
or (i)(2) of this AD.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 10 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 10 days after the effective date of this
AD.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York 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.
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(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 TCCA; or the TCCA DAO. If
approved by the DAO, the approval must
include the DAO-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2017–12, dated
March 10, 2017, for related information. You
may examine the MCAI on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2017–0696.
(2) For more information about this AD,
contact Aziz Ahmed, Airframe Engineer,
Airframe and Mechanical Systems Branch,
ANE–171, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone: 516–228–7329; fax: 516–
794–5531.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 100–53–32,
dated February 16, 2017.
(ii) Reserved.
(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
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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 July 6,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14698 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–2016–9567; Directorate
Identifier 2016–NM–147–AD; Amendment
39–18955; AD 2017–14–11]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2007–13–
08, for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2007–13–08 required repetitive
inspections of the auxiliary power unit
(APU) starter motor, APU inlet plenum,
and APU air intake for discrepancies;
repetitive cleaning of the APU air
intake; and applicable corrective
actions. This AD expands the
applicability of AD 2007–13–08, and
includes an optional terminating
installation for the repetitive actions.
This AD was prompted by a
determination that the unsafe condition
could occur on additional airplanes. 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.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of July 25, 2007 (72 FR
33877, June 20, 2007).
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@
SUMMARY:
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Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
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–2016–9567.
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–
9567; 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 (telephone 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.
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:
jstallworth on DSK7TPTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007–13–08,
Amendment 39–15112 (72 FR 33877,
June 20, 2007) (‘‘AD 2007–13–08’’). AD
2007–13–08 applied to certain Airbus
Model A318, A319, A320, and A321
series airplanes. The NPRM published
in the Federal Register on January 6,
2017 (82 FR 1623). The NPRM was
prompted by a determination that the
unsafe condition could occur on
additional airplanes. The NPRM
proposed to continue to require
repetitive inspections of the APU starter
motor, APU inlet plenum, and APU air
intake for discrepancies; repetitive
cleaning of the APU air intake; and
applicable corrective actions. We are
issuing this AD to detect and correct
reverse flow during APU startup, which
could lead to flame propagation in the
APU air inlet and intake duct. Such
conditions could result in an in-flight
fire in the APU area.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
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for the Member States of the European
Union, has issued EASA AD 2016–0176,
dated August 31, 2016; corrected
September 1, 2016 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A318, A319, A320,
and A321 airplanes. The MCAI states:
An operator reported black smoke at the
rear of the fuselage during taxi after landing.
The smoke was caused by a fire in the
auxiliary power unit (APU) air intake. The
subsequent analysis demonstrated that,
following numerous unsuccessful APU start
attempts in flight, there is a risk of reverse
flow leading to flame propagation to the APU
air inlet and air intake duct.
This condition, if not detected and
corrected, could result in an in-flight fire in
the APU area.
Prompted by these findings, Airbus issued
Service Bulletin (SB) A320–49–1068 to
provide inspection and cleaning instructions.
The applicable Flight Crew Operating
Manual (FCOM) already contained a
limitation for the number of APU start
attempts, as follows:
APU STARTER
After 3 starter motor duty cycles, wait 60
minutes before attempting 3 more cycles
To address this potential unsafe condition,
EASA issued AD 2006–0153 to require
repetitive inspections of the APU starter
motor, APU inlet plenum and APU air intake
[for discrepancies], as well as repetitive
cleaning of the APU air intake [and
applicable corrective actions].
As the reverse flow inside the APU can
only occur in flight with the APU inlet
closed, various modifications (mod) were
developed to introduce a new electronic
control box (ECB) with associated software,
the functionality of which keeps the APU
inlet door open for 15 minutes, following an
APU auto-shutdown in flight. Consequently,
AD 2006–0153 [which corresponds to FAA
AD 2007–13–08], was revised reducing the
Applicability by excluding certain post-mod
aeroplanes, and introducing these
modifications as optional terminating
actions.
After EASA AD 2006–0153R2 was issued,
it was determined that, as an APU ECB can
be replaced (or moved from one aeroplane to
another) in service, inadvertently installing a
pre-mod ECB would reintroduce the unsafe
condition. Prompted by this finding, EASA
issued AD 2016–0159, retaining the
requirements of EASA AD 2006–0153R2,
which was superseded, expanding the
Applicability and including references to
additional optional terminating actions.
Since EASA AD 2016–0159 was issued, it
was determined that paragraph (5) of the
[EASA] AD contained some erroneous
statements, inadvertently excluding certain
aeroplanes, those that have Airbus mod
23698 or mod 24498 embodied in
production, from the repetitive actions.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0159, which is superseded, and
corrects paragraph (5). For post-mod
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aeroplanes where, inadvertently, an ‘affected’
ECB has been installed in service, this AD
adds the requirement to restore those
aeroplanes to post-mod configuration by
installation of a ‘serviceable’ ECB. This
[EASA] AD also introduces some editorial
changes, not affecting the required actions.
This [EASA] AD is republished as it was
determined that one ‘affected’ and one ‘nonaffected’ ECB were inadvertently omitted in
the Tables.
Discrepancies include a defective
APU starter motor, misaligned brush
wear indicator-pin, oil contamination of
the brush wear indicator, and dirt,
debris, dust, sand, oil, combustible
residues, grease and other
contaminations of the APU inlet
plenum. Corrective actions include
replacement of the APU starter motor
and cleaning the APU air intake, if
necessary. 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–
9567.
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.
Support for the NPRM
United Airlines and Air Line Pilots
Association, International, stated their
support for the content of the NPRM.
Request To Include Missing Part
Number
Airbus asked that electronic control
box (ECB) part number (P/N) 3888394–
230300 for APU GTCP36–300 be added
to table 1 to paragraph (g) of the
proposed AD. Airbus stated that the part
number is missing in the table.
We agree with the commenter’s
request. We have added ECB P/N
3888394–230300 for APU GTCP36–300
to table 1 to paragraphs (g), (h), (i)(2)(ii),
(j), and (k) of this AD. That part number
was omitted from EASA AD 2016–0176,
dated August 31, 2016; however, EASA
issued a correction, which added that
part number, on September 1, 2016. We
have also included the corrected EASA
AD in this final rule.
Request To Provide Retrofit Installation
Method and Interchangeability
Information
Virgin America asked that the
proposed AD requirements provide an
approved retrofit installation method for
P/N 3888394–321206. Virgin America
also asked that the proposed AD
requirements clearly state the
interchangeability or lack of
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interchangeability for the part numbers
identified in table 2 of the proposed AD.
Virgin America stated that it receives
the Airbus Illustrated Parts Catalog (IPC)
on a quarterly basis, which it regularly
corrects to remove interchangeability.
Virgin America added that in addition
to correcting the IPC every quarter, it
has repeatedly requested that Airbus
Airworthiness and Engineering
synchronize their viewpoint of how the
IPC is intended to be utilized by
operators. Virgin America noted that
since EASA has corresponding ADs, it
would mean that no ECB can be
considered ‘‘interchangeable’’ by
Airbus, since accomplishing a service
bulletin is not the same as
accomplishing an airplane maintenance
manual. Virgin America requested this
coordination within Airbus, both from
an ever increasing manpower
requirement (i.e., the more ADs, the
more IPCs that need interchangeability
monitored and removed quarterly) and
also from a parts support request, since
some parts providers use the IPC as the
means to pool and issue parts. Virgin
America concluded that a separate pool
of non-interchangeable parts adds
significantly to the cost impact of the
proposed AD.
We acknowledge the commenter’s
concerns; however, an approved retrofit
installation method and
interchangeability of part numbers are
not addressed by this AD. While there
might be merit to the commenter’s
suggestions, this AD is not the
appropriate document in which to
evaluate those suggestions. Therefore,
we have not changed this AD in this
regard.
Conclusion
jstallworth on DSK7TPTVN1PROD with RULES
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these 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 has issued the following
service information, which describes
procedures for replacing the ECB. These
documents are distinct since they apply
to different airplane models in different
configurations.
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• Airbus Service Bulletin A320–49–
1077, Revision 04, dated February 27,
2013.
• Airbus Service Bulletin A320–49–
1098, dated June 21, 2011.
• Airbus Service Bulletin A320–49–
1102, dated January 3, 2012.
• Airbus Service Bulletin A320–49–
1107, Revision 02, dated May 10, 2016.
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 1,182
airplanes of U.S. registry.
The actions required by AD 2007–13–
08, and retained in this AD, take about
4 work-hours per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that are required by AD
2007–13–08 is $340 per product.
We also estimate that it will take
about 4 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $401,880, or $340 per
product.
We have received no definitive data
that will enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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
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the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2007–13–08, Amendment 39–15112 (72
FR 33877, June 20, 2007), and adding
the following new AD:
■
2017–14–11 Airbus: Amendment 39–18955;
Docket No. FAA–2016–9567; Directorate
Identifier 2016–NM–147–AD.
(a) Effective Date
This AD is effective August 21, 2017.
(b) Affected ADs
This AD replaces AD 2007–13–08,
Amendment 39–15112 (72 FR 33877, June
20, 2007) (‘‘AD 2007–13–08’’).
(c) Applicability
This AD applies to Airbus airplanes
identified in paragraphs (c)(1), (c)(2), (c)(3),
and (c)(4) of this AD, all manufacturer serial
numbers, certificated in any category.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 49, Airborne Auxiliary Power.
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(e) Reason
This AD was prompted by a report of a fire
in the auxiliary power unit (APU) air intake.
An analysis demonstrated that, following
numerous unsuccessful APU start attempts in
flight, there is a risk of reverse flow, which
could lead to flame propagation to the APU
air inlet and air intake duct. This AD was
also prompted by the determination that AD
2007–13–08 only addresses the unsafe
condition for certain airplanes. We are
issuing this AD to detect and correct reverse
flow during APU startup, which could lead
to flame propagation in the APU air inlet and
intake duct. Such conditions could result in
an in-flight fire in the APU area.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Corrective
Actions
Except as provided by paragraph (i) of this
AD, within 600 flight hours after July 25,
2007 (the effective date of AD 2007–13–08),
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or within 60 days after the effective date of
this AD, whichever occurs later: Inspect the
APU starter motor, APU air inlet plenum,
and APU air intake of each affected APU
identified in table 1 to paragraphs (g), (h),
(i)(2)(ii), (j), and (k) of this AD for
discrepancies; and do all applicable
corrective actions before further flight; in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
49–1068, Revision 01, dated February 2,
2006. Repeat the inspection thereafter at
intervals not to exceed 600 flight hours.
TABLE 1 TO PARAGRAPHS (g), (h), (i)(2)(ii), (j), AND (k) OF THIS AD—AFFECTED APU AND
ELECTRONIC CONTROL BOX (ECB)
APU
ECB part Nos. (P/N)
APIC APS 3200 ..............................
Honeywell 131–9A ..........................
Honeywell GTCP36–300 ................
4500003D, 4500003E, 4500003F, 4500003G, 4500003H, or 4500003J.
3888394–120201, 3888394–121202, 3888394–121203, 3888394–221202, or 3888394–221203.
307950–1, 307950–2, 307950–3, 307950–4, 304640–1, 304640–2, 304640–3, 304640–4, 304817–1,
304817–2, or 3888394–230300.
(h) Repetitive Cleanings
Except as provided by paragraph (i) of this
AD, prior to the accumulation of 2,400 flight
hours since first flight of the airplane, or
within 600 flight hours after July 25, 2007
(the effective date of AD 2007–13–08), or
within 60 days after the effective date of this
AD, whichever occurs latest, unless
accomplished previously in accordance with
Airbus Service Bulletin A320–49–1098,
dated June 21, 2011: Clean the APU air intake
of each affected APU identified in table 1 to
paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this
AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
49–1068, Revision 01, dated February 2,
2006. Repeat the cleaning task thereafter at
intervals not to exceed 2,400 flight hours.
(i) Exceptions to Requirements in
Paragraphs (g) and (h) of This AD
(1) For airplanes equipped with an APU
and associated ECB part number identified in
table 2 to paragraphs (i)(1), (i)(2)(ii), and (j)
of this AD, the actions specified in
paragraphs (g) and (h) of this AD are not
required.
TABLE 2 TO PARAGRAPHS (i)(1), (i)(2)(ii), AND (j) OF THIS AD—NON-AFFECTED ECB
APU
ECB Part Nos. (P/N)
jstallworth on DSK7TPTVN1PROD with RULES
APIC APS 3200 ..............................
Honeywell 131–9A ..........................
Honeywell GTCP36–300 ................
4500003K, 4500003L, or 4500003M.
3888394–121204, 3888394–121205, 3888394–221204, 3888394–221205, or 3888394–321206.
304640–5, 304817–3, or 3888394–230301.
(2) For airplanes on which Airbus
Modification 35803, 35936, 152289, 152645,
155015, or 157848 has been embodied in
production, the actions specified in
paragraphs (g) and (h) of this AD are not
required provided that, within 30 days after
the effective date of this AD, the applicable
actions specified in paragraphs (i)(2)(i) and
(i)(2)(ii) of this AD are done.
(i) The part number of the installed ECB is
identified.
(ii) Any affected ECB identified in table 1
to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of
this AD that is found to be installed is
replaced with an ECB having a part number
identified in table 2 to paragraphs (i)(1),
(i)(2)(ii), and (j) of this AD, as applicable to
the APU installed on the airplane; and the
replacement is done in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraph (i)(2)(ii)(A), (i)(2)(ii)(B),
(i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or
(i)(2)(ii)(F) of this AD; or 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).
VerDate Sep<11>2014
14:51 Jul 14, 2017
Jkt 241001
(A) Airbus Service Bulletin A320–49–1070,
dated July 28, 2006.
(B) Airbus Service Bulletin A320–49–1075,
Revision 01, dated December 1, 2006.
(C) Airbus Service Bulletin A320–49–1077,
Revision 04, dated February 27, 2013.
(D) Airbus Service Bulletin A320–49–1098,
dated June 21, 2011.
(E) Airbus Service Bulletin A320–49–1102,
dated January 3, 2012.
(F) Airbus Service Bulletin A320–49–1107,
Revision 02, dated May 10, 2016.
(3) For airplanes on which an APU ECB
having a part number approved after the
effective date of this AD is installed, the
actions specified in paragraphs (g) and (h) of
this AD are not required, provided the
conditions specified in paragraphs (i)(3)(i)
and (i)(3)(ii) of this AD are met.
(i) The part number must be approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA.
(ii) The installation must be accomplished
in accordance with airplane modification
instructions approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Airbus’s EASA DOA.
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(j) Optional Terminating Action
Replacing an affected ECB identified in
table 1 to paragraphs (g), (h), (i)(2)(ii), (j), and
(k) of this AD with an ECB having a part
number identified in table 2 to paragraphs
(i)(1), (i)(2)(ii), and (j) of this AD, as
applicable to the APU installed on the
airplane, constitutes terminating action for
the repetitive inspections required by
paragraphs (g) and (h) of this AD. The
replacement must be done in accordance
with the Accomplishment Instructions of the
applicable service information identified in
paragraph (i)(2)(ii)(A), (i)(2)(ii)(B),
(i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or
(i)(2)(ii)(F) of this AD, or using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA; or Airbus’s EASA
DOA.
(k) Parts Installation Prohibition
As of the effective date of this AD, no
person may install on any airplane an APU
with an associated ECB identified in table 1
to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of
this AD.
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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
VerDate Sep<11>2014
14:51 Jul 14, 2017
Jkt 241001
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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]]>Agencies
[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)]
[Rules and Regulations]
[Pages 32622-32626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14469]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-147-AD;
Amendment 39-18955; AD 2017-14-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2007-13-08,
for certain Airbus Model A318, A319, A320, and A321 series airplanes.
AD 2007-13-08 required repetitive inspections of the auxiliary power
unit (APU) starter motor, APU inlet plenum, and APU air intake for
discrepancies; repetitive cleaning of the APU air intake; and
applicable corrective actions. This AD expands the applicability of AD
2007-13-08, and includes an optional terminating installation for the
repetitive actions. This AD was prompted by a determination that the
unsafe condition could occur on additional airplanes. 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.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of July
25, 2007 (72 FR 33877, June 20, 2007).
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@
[[Page 32623]]
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-2016-9567.
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-
9567; 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 (telephone 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.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2007-13-08, Amendment 39-15112 (72 FR 33877,
June 20, 2007) (``AD 2007-13-08''). AD 2007-13-08 applied to certain
Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM
published in the Federal Register on January 6, 2017 (82 FR 1623). The
NPRM was prompted by a determination that the unsafe condition could
occur on additional airplanes. The NPRM proposed to continue to require
repetitive inspections of the APU starter motor, APU inlet plenum, and
APU air intake for discrepancies; repetitive cleaning of the APU air
intake; and applicable corrective actions. We are issuing this AD to
detect and correct reverse flow during APU startup, which could lead to
flame propagation in the APU air inlet and intake duct. Such conditions
could result in an in-flight fire in the APU area.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0176, dated August 31, 2016; corrected September 1, 2016 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318, A319, A320, and A321 airplanes. The MCAI states:
An operator reported black smoke at the rear of the fuselage
during taxi after landing. The smoke was caused by a fire in the
auxiliary power unit (APU) air intake. The subsequent analysis
demonstrated that, following numerous unsuccessful APU start
attempts in flight, there is a risk of reverse flow leading to flame
propagation to the APU air inlet and air intake duct.
This condition, if not detected and corrected, could result in
an in-flight fire in the APU area.
Prompted by these findings, Airbus issued Service Bulletin (SB)
A320-49-1068 to provide inspection and cleaning instructions. The
applicable Flight Crew Operating Manual (FCOM) already contained a
limitation for the number of APU start attempts, as follows:
APU STARTER
After 3 starter motor duty cycles, wait 60 minutes before attempting
3 more cycles
To address this potential unsafe condition, EASA issued AD 2006-
0153 to require repetitive inspections of the APU starter motor, APU
inlet plenum and APU air intake [for discrepancies], as well as
repetitive cleaning of the APU air intake [and applicable corrective
actions].
As the reverse flow inside the APU can only occur in flight with
the APU inlet closed, various modifications (mod) were developed to
introduce a new electronic control box (ECB) with associated
software, the functionality of which keeps the APU inlet door open
for 15 minutes, following an APU auto-shutdown in flight.
Consequently, AD 2006-0153 [which corresponds to FAA AD 2007-13-08],
was revised reducing the Applicability by excluding certain post-mod
aeroplanes, and introducing these modifications as optional
terminating actions.
After EASA AD 2006-0153R2 was issued, it was determined that, as
an APU ECB can be replaced (or moved from one aeroplane to another)
in service, inadvertently installing a pre-mod ECB would reintroduce
the unsafe condition. Prompted by this finding, EASA issued AD 2016-
0159, retaining the requirements of EASA AD 2006-0153R2, which was
superseded, expanding the Applicability and including references to
additional optional terminating actions.
Since EASA AD 2016-0159 was issued, it was determined that
paragraph (5) of the [EASA] AD contained some erroneous statements,
inadvertently excluding certain aeroplanes, those that have Airbus
mod 23698 or mod 24498 embodied in production, from the repetitive
actions.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2016-0159, which is superseded, and corrects
paragraph (5). For post-mod aeroplanes where, inadvertently, an
`affected' ECB has been installed in service, this AD adds the
requirement to restore those aeroplanes to post-mod configuration by
installation of a `serviceable' ECB. This [EASA] AD also introduces
some editorial changes, not affecting the required actions.
This [EASA] AD is republished as it was determined that one
`affected' and one `non-affected' ECB were inadvertently omitted in
the Tables.
Discrepancies include a defective APU starter motor, misaligned
brush wear indicator-pin, oil contamination of the brush wear
indicator, and dirt, debris, dust, sand, oil, combustible residues,
grease and other contaminations of the APU inlet plenum. Corrective
actions include replacement of the APU starter motor and cleaning the
APU air intake, if necessary. 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-2016-9567.
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.
Support for the NPRM
United Airlines and Air Line Pilots Association, International,
stated their support for the content of the NPRM.
Request To Include Missing Part Number
Airbus asked that electronic control box (ECB) part number (P/N)
3888394-230300 for APU GTCP36-300 be added to table 1 to paragraph (g)
of the proposed AD. Airbus stated that the part number is missing in
the table.
We agree with the commenter's request. We have added ECB P/N
3888394-230300 for APU GTCP36-300 to table 1 to paragraphs (g), (h),
(i)(2)(ii), (j), and (k) of this AD. That part number was omitted from
EASA AD 2016-0176, dated August 31, 2016; however, EASA issued a
correction, which added that part number, on September 1, 2016. We have
also included the corrected EASA AD in this final rule.
Request To Provide Retrofit Installation Method and Interchangeability
Information
Virgin America asked that the proposed AD requirements provide an
approved retrofit installation method for P/N 3888394-321206. Virgin
America also asked that the proposed AD requirements clearly state the
interchangeability or lack of
[[Page 32624]]
interchangeability for the part numbers identified in table 2 of the
proposed AD.
Virgin America stated that it receives the Airbus Illustrated Parts
Catalog (IPC) on a quarterly basis, which it regularly corrects to
remove interchangeability. Virgin America added that in addition to
correcting the IPC every quarter, it has repeatedly requested that
Airbus Airworthiness and Engineering synchronize their viewpoint of how
the IPC is intended to be utilized by operators. Virgin America noted
that since EASA has corresponding ADs, it would mean that no ECB can be
considered ``interchangeable'' by Airbus, since accomplishing a service
bulletin is not the same as accomplishing an airplane maintenance
manual. Virgin America requested this coordination within Airbus, both
from an ever increasing manpower requirement (i.e., the more ADs, the
more IPCs that need interchangeability monitored and removed quarterly)
and also from a parts support request, since some parts providers use
the IPC as the means to pool and issue parts. Virgin America concluded
that a separate pool of non-interchangeable parts adds significantly to
the cost impact of the proposed AD.
We acknowledge the commenter's concerns; however, an approved
retrofit installation method and interchangeability of part numbers are
not addressed by this AD. While there might be merit to the commenter's
suggestions, this AD is not the appropriate document in which to
evaluate those suggestions. Therefore, we have not changed this AD in
this regard.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these 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 has issued the following service information, which
describes procedures for replacing the ECB. These documents are
distinct since they apply to different airplane models in different
configurations.
Airbus Service Bulletin A320-49-1077, Revision 04, dated
February 27, 2013.
Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
Airbus Service Bulletin A320-49-1102, dated January 3,
2012.
Airbus Service Bulletin A320-49-1107, Revision 02, dated
May 10, 2016.
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 1,182 airplanes of U.S. registry.
The actions required by AD 2007-13-08, and retained in this AD,
take about 4 work-hours per product, at an average labor rate of $85
per work-hour. Based on these figures, the estimated cost of the
actions that are required by AD 2007-13-08 is $340 per product.
We also estimate that it will take about 4 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $401,880, or $340 per product.
We have received no definitive data that will enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007), and adding
the following new AD:
2017-14-11 Airbus: Amendment 39-18955; Docket No. FAA-2016-9567;
Directorate Identifier 2016-NM-147-AD.
(a) Effective Date
This AD is effective August 21, 2017.
(b) Affected ADs
This AD replaces AD 2007-13-08, Amendment 39-15112 (72 FR 33877,
June 20, 2007) (``AD 2007-13-08'').
(c) Applicability
This AD applies to Airbus airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer
serial numbers, certificated in any category.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 49, Airborne
Auxiliary Power.
[[Page 32625]]
(e) Reason
This AD was prompted by a report of a fire in the auxiliary
power unit (APU) air intake. An analysis demonstrated that,
following numerous unsuccessful APU start attempts in flight, there
is a risk of reverse flow, which could lead to flame propagation to
the APU air inlet and air intake duct. This AD was also prompted by
the determination that AD 2007-13-08 only addresses the unsafe
condition for certain airplanes. We are issuing this AD to detect
and correct reverse flow during APU startup, which could lead to
flame propagation in the APU air inlet and intake duct. Such
conditions could result in an in-flight fire in the APU area.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Corrective Actions
Except as provided by paragraph (i) of this AD, within 600
flight hours after July 25, 2007 (the effective date of AD 2007-13-
08), or within 60 days after the effective date of this AD,
whichever occurs later: Inspect the APU starter motor, APU air inlet
plenum, and APU air intake of each affected APU identified in table
1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD for
discrepancies; and do all applicable corrective actions before
further flight; in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-49-1068, Revision 01, dated February
2, 2006. Repeat the inspection thereafter at intervals not to exceed
600 flight hours.
Table 1 to Paragraphs (g), (h), (i)(2)(ii), (j), and (k) of This AD--
Affected APU and
Electronic Control Box (ECB)
------------------------------------------------------------------------
APU ECB part Nos. (P/N)
------------------------------------------------------------------------
APIC APS 3200..................... 4500003D, 4500003E, 4500003F,
4500003G, 4500003H, or 4500003J.
Honeywell 131-9A.................. 3888394-120201, 3888394-121202,
3888394-121203, 3888394-221202, or
3888394-221203.
Honeywell GTCP36-300.............. 307950-1, 307950-2, 307950-3, 307950-
4, 304640-1, 304640-2, 304640-3,
304640-4, 304817-1, 304817-2, or
3888394-230300.
------------------------------------------------------------------------
(h) Repetitive Cleanings
Except as provided by paragraph (i) of this AD, prior to the
accumulation of 2,400 flight hours since first flight of the
airplane, or within 600 flight hours after July 25, 2007 (the
effective date of AD 2007-13-08), or within 60 days after the
effective date of this AD, whichever occurs latest, unless
accomplished previously in accordance with Airbus Service Bulletin
A320-49-1098, dated June 21, 2011: Clean the APU air intake of each
affected APU identified in table 1 to paragraphs (g), (h),
(i)(2)(ii), (j), and (k) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-49-1068,
Revision 01, dated February 2, 2006. Repeat the cleaning task
thereafter at intervals not to exceed 2,400 flight hours.
(i) Exceptions to Requirements in Paragraphs (g) and (h) of This AD
(1) For airplanes equipped with an APU and associated ECB part
number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and
(j) of this AD, the actions specified in paragraphs (g) and (h) of
this AD are not required.
Table 2 to Paragraphs (i)(1), (i)(2)(ii), and (j) of This AD--Non-
Affected ECB
------------------------------------------------------------------------
APU ECB Part Nos. (P/N)
------------------------------------------------------------------------
APIC APS 3200..................... 4500003K, 4500003L, or 4500003M.
Honeywell 131-9A.................. 3888394-121204, 3888394-121205,
3888394-221204, 3888394-221205, or
3888394-321206.
Honeywell GTCP36-300.............. 304640-5, 304817-3, or 3888394-
230301.
------------------------------------------------------------------------
(2) For airplanes on which Airbus Modification 35803, 35936,
152289, 152645, 155015, or 157848 has been embodied in production,
the actions specified in paragraphs (g) and (h) of this AD are not
required provided that, within 30 days after the effective date of
this AD, the applicable actions specified in paragraphs (i)(2)(i)
and (i)(2)(ii) of this AD are done.
(i) The part number of the installed ECB is identified.
(ii) Any affected ECB identified in table 1 to paragraphs (g),
(h), (i)(2)(ii), (j), and (k) of this AD that is found to be
installed is replaced with an ECB having a part number identified in
table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, as
applicable to the APU installed on the airplane; and the replacement
is done in accordance with the Accomplishment Instructions of the
applicable service information identified in paragraph
(i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D),
(i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD; or 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).
(A) Airbus Service Bulletin A320-49-1070, dated July 28, 2006.
(B) Airbus Service Bulletin A320-49-1075, Revision 01, dated
December 1, 2006.
(C) Airbus Service Bulletin A320-49-1077, Revision 04, dated
February 27, 2013.
(D) Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
(E) Airbus Service Bulletin A320-49-1102, dated January 3, 2012.
(F) Airbus Service Bulletin A320-49-1107, Revision 02, dated May
10, 2016.
(3) For airplanes on which an APU ECB having a part number
approved after the effective date of this AD is installed, the
actions specified in paragraphs (g) and (h) of this AD are not
required, provided the conditions specified in paragraphs (i)(3)(i)
and (i)(3)(ii) of this AD are met.
(i) The part number must be approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(ii) The installation must be accomplished in accordance with
airplane modification instructions approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(j) Optional Terminating Action
Replacing an affected ECB identified in table 1 to paragraphs
(g), (h), (i)(2)(ii), (j), and (k) of this AD with an ECB having a
part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii),
and (j) of this AD, as applicable to the APU installed on the
airplane, constitutes terminating action for the repetitive
inspections required by paragraphs (g) and (h) of this AD. The
replacement must be done in accordance with the Accomplishment
Instructions of the applicable service information identified in
paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C),
(i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD, or using
a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(k) Parts Installation Prohibition
As of the effective date of this AD, no person may install on
any airplane an APU with an associated ECB identified in table 1 to
paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD.
[[Page 32626]]
(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-116-AMOC-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 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/ibr-locations.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
