Airworthiness Directives; Airbus Airplanes, 1623-1626 [2016-31960]
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Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules
Revision 21, dated June 2011. The initial
compliance times for the tasks are at the
applicable times specified in Section 05–40/
00, Airworthiness Limitations, of Chapter 5–
40, Airworthiness Limitations, of the
Dassault Falcon 50/50EX Maintenance
Manual, Revision 21, dated June 2011, or
within 30 days after March 19, 2013,
whichever occurs later.
(h) Retained Provision Regarding
Alternative Actions, Intervals, and Critical
Design Configuration Control Limitations
(CDCCLs), With New Exception
This paragraph restates the requirements of
paragraph (h) of AD 2013–03–12, with a new
exception. Except as required by paragraph
(i) of this AD: After accomplishing the
revisions required by paragraph (g) of this
AD, no alternative actions (e.g., inspections),
intervals, and/or CDCCLs may be used other
than those specified in Section 05–40/00,
Airworthiness Limitations, of Chapter 5–40,
Airworthiness Limitations, of the Dassault
Falcon 50/50EX Maintenance Manual,
Revision 21, dated June 2011, unless the
actions, intervals, and/or CDCCLs are
approved as an alternative methods of
compliance (AMOC) in accordance with the
procedures specified in paragraph (l)(1) of
this AD.
(i) New Maintenance or Inspection Program
Revision
Within 30 days after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, to
incorporate airworthiness limitations,
maintenance tasks, and associated thresholds
and intervals specified in Section 05–40/00,
Airworthiness Limitations, of Chapter 5–40,
Airworthiness Limitations, of the Dassault
Falcon 50/50EX Maintenance Manual,
Revision 23, dated July 2015. The initial
compliance times for the tasks are at the
applicable times specified in Section 05–40/
00, Airworthiness Limitations, of Chapter 5–
40, Airworthiness Limitations, of the
Dassault Falcon 50/50EX Maintenance
Manual, Revision 23, dated July 2015, or
within 30 days after the effective date of this
AD, whichever occurs later. Accomplishing
the revision of the maintenance or inspection
program required by this paragraph
terminates the requirements of paragraph (g)
of this AD.
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(j) New Provision Regarding Alternative
Actions and Intervals
After the maintenance or inspection
program has been revised as required by
paragraph (i) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions and intervals are
approved as an AMOC in accordance with
the procedures specified in paragraph (l)(1)
of this AD.
(k) Terminating Action for Certain ADs
Accomplishing the actions required by
paragraph (g) or (i) of this AD terminates all
requirements of AD 2010–26–05 and AD
2012–02–18 for the Dassault Aviation Model
MYSTERE–FALCON 50 airplanes specified
in those ADs.
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(l) Other FAA AD Provisions
DEPARTMENT OF TRANSPORTATION
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Dassault Aviation’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0067, dated
April 7, 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–
2016–9569.
(2) For service information identified in
this AD, contact Dassault Falcon Jet
Corporation, Teterboro Airport, P.O. Box
2000, South Hackensack, NJ 07606;
telephone 201–440–6700; Internet https://
www.dassaultfalcon.com. You may view this
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on
December 27, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–31963 Filed 1–5–17; 8:45 am]
BILLING CODE 4910–13–P
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1623
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9567; Directorate
Identifier 2016–NM–147–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2007–13–
08, for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2007–13–08 currently requires
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. Since we issued AD
2007–13–08, a determination was made
that the unsafe condition could occur on
additional airplanes. This proposed AD
would expand the applicability in AD
2007–13–08, and include an optional
terminating installation for the
repetitive actions. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by February 21, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus,
Airworthiness Office–EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com;
Internet: https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
SUMMARY:
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Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9567; Directorate Identifier
2016–NM–147–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On June 12, 2007, we issued AD
2007–13–08, Amendment 39–15112 (72
FR 33877, June 20, 2007) (‘‘AD 2007–
13–08’’), for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2007–13–08 was prompted by
mandatory continuing airworthiness
information issued by an airworthiness
authority of another country to identify
and correct an unsafe condition on an
aviation product. AD 2007–13–08
currently requires 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
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corrective actions. We issued AD 2007–
13–08 to detect and correct reverse flow
during APU startup, leading to flame
propagation in the APU air inlet and
intake duct. Such conditions could
result in an in-flight fire in the APU
area.
Since we issued AD 2007–13–08, 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 (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 was revised [which
corresponds to FAA AD 2007–13–08],
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.
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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.
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.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–49–1068, Revision 01, dated
February 2, 2006. The service
information describes procedures for
repetitive inspections for discrepancies
of the APU starter motor, APU inlet
plenum, and APU air intake, as well as
repetitive cleaning of the APU air intake
and applicable corrective actions.
Airbus has also 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–
1070, dated July 28, 2006.
• Airbus Service Bulletin A320–49–
1075, Revision 01, dated December 1,
2006.
• 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.
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Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
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Costs of Compliance
We estimate that this proposed AD
affects 1,182 airplanes of U.S. registry.
The actions required by AD 2007–13–
08, and retained in this proposed AD,
take about 4 work-hours per product, at
an average labor rate of $85 per workhour. 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 would take
about 4 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $401,880, or $340 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed 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 proposed AD
would not have federalism implications
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under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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:
■
Airbus: Docket No. FAA–2016–9567;
Directorate Identifier 2016–NM–147–AD.
(a) Comments Due Date
We must receive comments by February
21, 2017.
1625
(d) Subject
Air Transport Association (ATA) of
America Code 49, Airborne Auxiliary Power.
(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 airflow,
leading 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, leading to flame
propagation in the APU air inlet and intake
duct. Such conditions could result in an inflight 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), (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), (j), AND (k) OF THIS AD—AFFECTED APU AND ELECTRONIC
CONTROL BOX (ECB)
APU
APIC APS
3200.
Honeywell
131–9A.
ECB Part Numbers (P/N)
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, or 304817–2.
(b) Affected ADs
This AD replaces AD 2007–13–08,
Amendment 39–15112 (72 FR 33877, June
20, 2007) (‘‘AD 2007–13–08’’).
Honeywell
GTCP36–
300.
(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.
(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,
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Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules
dated June 21, 2011: Clean the APU air intake
of each affected APU identified in table 1 to
paragraphs (g), (h), (i)(2), (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), and (j) of
this AD, the actions specified in paragraphs
(g) and (h) of this AD are not required.
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
TABLE 2 TO PARAGRAPHS (i)(1), (i)(2),
AND (j) OF THIS AD—NON-AFFECTED ECB
APU
APIC APS
3200.
Honeywell
131–9A.
sradovich on DSK3GMQ082PROD with PROPOSALS
Honeywell
GTCP36–
300.
ECB Part Numbers (P/N)
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), (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), 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
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Replacing an affected ECB identified in
table 1 to paragraphs (g), (h), (i)(2), (j), and
(k) of this AD with an ECB having a part
number identified in table 2 to paragraphs
(i)(1), (i)(2), 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), (j), and (k) of this
AD.
(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:
PO 00000
Frm 00019
Fmt 4702
Sfmt 9990
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(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, 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 service information identified in
this AD, contact Airbus, Airworthiness
Office–EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33
5 61 93 36 96; fax: +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com; Internet:
https://www.airbus.com. You may view this
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on
December 23, 2016.
Thomas Groves,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–31960 Filed 1–5–17; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\06JAP1.SGM
06JAP1
Agencies
[Federal Register Volume 82, Number 4 (Friday, January 6, 2017)]
[Proposed Rules]
[Pages 1623-1626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31960]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-147-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2007-13-
08, for certain Airbus Model A318, A319, A320, and A321 series
airplanes. AD 2007-13-08 currently requires 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. Since we issued AD 2007-13-
08, a determination was made that the unsafe condition could occur on
additional airplanes. This proposed AD would expand the applicability
in AD 2007-13-08, and include an optional terminating installation for
the repetitive actions. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by February 21,
2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus,
Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51;
email: account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on
[[Page 1624]]
the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9567;
Directorate Identifier 2016-NM-147-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On June 12, 2007, we issued AD 2007-13-08, Amendment 39-15112 (72
FR 33877, June 20, 2007) (``AD 2007-13-08''), for certain Airbus Model
A318, A319, A320, and A321 series airplanes. AD 2007-13-08 was prompted
by mandatory continuing airworthiness information issued by an
airworthiness authority of another country to identify and correct an
unsafe condition on an aviation product. AD 2007-13-08 currently
requires 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 issued AD
2007-13-08 to detect and correct reverse flow during APU startup,
leading to flame propagation in the APU air inlet and intake duct. Such
conditions could result in an in-flight fire in the APU area.
Since we issued AD 2007-13-08, 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
(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 was revised [which corresponds to FAA AD
2007-13-08], 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.
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.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-49-1068, Revision 01, dated
February 2, 2006. The service information describes procedures for
repetitive inspections for discrepancies of the APU starter motor, APU
inlet plenum, and APU air intake, as well as repetitive cleaning of the
APU air intake and applicable corrective actions.
Airbus has also 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 A320-49-1070, dated July 28, 2006.
Airbus Service Bulletin A320-49-1075, Revision 01, dated
December 1, 2006.
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.
[[Page 1625]]
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 1,182 airplanes of U.S.
registry.
The actions required by AD 2007-13-08, and retained in this
proposed 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 would take about 4 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $401,880, or $340
per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007), and adding
the following new AD:
Airbus: Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-
147-AD.
(a) Comments Due Date
We must receive comments by February 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.
(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 airflow, leading 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, leading 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), (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), (j), and (k) of This AD--
Affected APU and Electronic Control Box (ECB)
------------------------------------------------------------------------
APU ECB Part Numbers (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,
or 304817-2.
------------------------------------------------------------------------
(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,
[[Page 1626]]
dated June 21, 2011: Clean the APU air intake of each affected APU
identified in table 1 to paragraphs (g), (h), (i)(2), (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), 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), and (j) of This AD--Non-Affected
ECB
------------------------------------------------------------------------
APU ECB Part Numbers (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), (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), 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), (j), and (k) of this AD with an ECB having a part
number identified in table 2 to paragraphs (i)(1), (i)(2), 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), (j), and (k) of this AD.
(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 International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(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, 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 service information identified in this AD, contact
Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33
5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet:
https://www.airbus.com. You may view this service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on December 23, 2016.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-31960 Filed 1-5-17; 8:45 am]
BILLING CODE 4910-13-P