82 FR 1623 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 4 (January 6, 2017)

Page Range		1623-1626
FR Document		2016-31960
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.
Federal Register, Volume 82 Issue 4 (Friday, January 6, 2017)
[Federal Register Volume 82, Number 4 (Friday, January 6, 2017)]
[Proposed Rules]
[Pages 1623-1626]
From the Federal Register Online  [www.thefederalregister.org]
[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 http://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: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on

[[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 http://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 http://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 http://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: [email protected].
    (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 http://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: [email protected]; Internet: 
http://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
1624 Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules

the availability of this material at the corrective actions. We issued AD 2007– Since EASA AD 2016–0159 was issued, it
FAA, call 425–227–1221. 13–08 to detect and correct reverse flow was determined that paragraph (5) of the
during APU startup, leading to flame [EASA] AD contained some erroneous
Examining the AD Docket statements, inadvertently excluding certain
propagation in the APU air inlet and
You may examine the AD docket on aeroplanes, those that have Airbus mod
intake duct. Such conditions could 23698 or mod 24498 embodied in
the Internet at http:// result in an in-flight fire in the APU production, from the repetitive actions.
www.regulations.gov by searching for area. For the reason described above, this
and locating Docket No. FAA–2016– Since we issued AD 2007–13–08, the [EASA] AD retains the requirements of EASA
9567; or in person at the Docket European Aviation Safety Agency AD 2016–0159, which is superseded, and
Management Facility between 9 a.m. (EASA), which is the Technical Agent corrects paragraph (5). For post-mod
and 5 p.m., Monday through Friday, for the Member States of the European aeroplanes where, inadvertently, an ‘affected’
except Federal holidays. The AD docket Union, has issued EASA AD 2016–0176, ECB has been installed in service, this AD
contains this proposed AD, the dated August 31, 2016 (referred to after adds the requirement to restore those
regulatory evaluation, any comments aeroplanes to post-mod configuration by
this as the Mandatory Continuing
received, and other information. The installation of a ‘serviceable’ ECB. This
Airworthiness Information, or ‘‘the [EASA] AD also introduces some editorial
street address for the Docket Operations MCAI’’), to correct an unsafe condition changes, not affecting the required actions.
office (telephone 800–647–5527) is in for all Airbus Model A318, A319, A320,
the ADDRESSES section. Comments will and A321 airplanes. The MCAI states: Discrepancies include a defective
be available in the AD docket shortly APU starter motor, misaligned brush
An operator reported black smoke at the wear indicator-pin, oil contamination of
after receipt.
rear of the fuselage during taxi after landing.
FOR FURTHER INFORMATION CONTACT: The smoke was caused by a fire in the
the brush wear indicator, and dirt,
Sanjay Ralhan, Aerospace Engineer, auxiliary power unit (APU) air intake. The debris, dust, sand, oil, combustible
International Branch, ANM–116, subsequent analysis demonstrated that, residues, grease and other
Transport Airplane Directorate, FAA, following numerous unsuccessful APU start contaminations of the APU inlet
1601 Lind Avenue SW., Renton, WA attempts in flight, there is a risk of reverse plenum. Corrective actions include
98057–3356; telephone 425–227–1405; flow leading to flame propagation to the APU replacement of the APU starter motor
fax 425–227–1149. air inlet and air intake duct. and cleaning the APU air intake, if
This condition, if not detected and necessary. You may examine the MCAI
SUPPLEMENTARY INFORMATION:
corrected, could result in an in-flight fire in in the AD docket on the Internet at
Comments Invited the APU area.
Prompted by these findings, Airbus issued
http://www.regulations.gov by searching
We invite you to send any written Service Bulletin (SB) A320–49–1068 to for and locating Docket No. FAA–2016–
relevant data, views, or arguments about provide inspection and cleaning instructions. 9567.
this proposed AD. Send your comments The applicable Flight Crew Operating Related Service Information Under 1
to an address listed under the Manual (FCOM) already contained a
limitation for the number of APU start
CFR Part 51
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9567; Directorate Identifier attempts, as follows: Airbus has issued Service Bulletin
2016–NM–147–AD’’ at the beginning of APU STARTER A320–49–1068, Revision 01, dated
your comments. We specifically invite February 2, 2006. The service
comments on the overall regulatory, After 3 Starter Motor Duty Cycles, Wait 60 information describes procedures for
Minutes Before Attempting 3 More Cycles repetitive inspections for discrepancies
economic, environmental, and energy
aspects of this proposed AD. We will To address this potential unsafe condition, of the APU starter motor, APU inlet
consider all comments received by the EASA issued AD 2006–0153 to require plenum, and APU air intake, as well as
repetitive inspections of the APU starter repetitive cleaning of the APU air intake
closing date and may amend this
motor, APU inlet plenum and APU air intake
proposed AD based on those comments. and applicable corrective actions.
[for discrepancies], as well as repetitive
We will post all comments we cleaning of the APU air intake [and Airbus has also issued the following
receive, without change, to http:// applicable corrective actions]. service information, which describes
www.regulations.gov, including any As the reverse flow inside the APU can procedures for replacing the ECB. These
personal information you provide. We only occur in flight with the APU inlet documents are distinct since they apply
will also post a report summarizing each closed, various modifications (mod) were to different airplane models in different
substantive verbal contact we receive developed to introduce a new electronic configurations.
about this proposed AD. control box (ECB) with associated software, • Airbus Service Bulletin A320–49–
the functionality of which keeps the APU 1070, dated July 28, 2006.
Discussion inlet door open for 15 minutes, following an • Airbus Service Bulletin A320–49–
On June 12, 2007, we issued AD APU auto-shutdown in flight. Consequently,
1075, Revision 01, dated December 1,
2007–13–08, Amendment 39–15112 (72 AD 2006–0153 was revised [which
corresponds to FAA AD 2007–13–08], 2006.
FR 33877, June 20, 2007) (‘‘AD 2007– reducing the Applicability by excluding • Airbus Service Bulletin A320–49–
13–08’’), for certain Airbus Model A318, certain post-mod aeroplanes, and introducing 1077, Revision 04, dated February 27,
A319, A320, and A321 series airplanes. these modifications as optional terminating 2013.
AD 2007–13–08 was prompted by actions. • Airbus Service Bulletin A320–49–
mandatory continuing airworthiness After EASA AD 2006–0153R2 was issued, 1098, dated June 21, 2011.
information issued by an airworthiness it was determined that, as an APU ECB can • Airbus Service Bulletin A320–49–
sradovich on DSK3GMQ082PROD with PROPOSALS

authority of another country to identify be replaced (or moved from one aeroplane to 1102, dated January 3, 2012.
and correct an unsafe condition on an another) in service, inadvertently installing a • Airbus Service Bulletin A320–49–
aviation product. AD 2007–13–08 pre-mod ECB would reintroduce the unsafe
1107, Revision 02, dated May 10, 2016.
condition. Prompted by this finding, EASA
currently requires repetitive inspections issued AD 2016–0159, retaining the
This service information is reasonably
of the APU starter motor, APU inlet requirements of EASA AD 2006–0153R2, available because the interested parties
plenum, and APU air intake for which was superseded, expanding the have access to it through their normal
discrepancies; repetitive cleaning of the Applicability and including references to course of business or by the means
APU air intake, and applicable additional optional terminating actions. identified in the ADDRESSES section.

VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\06JAP1.SGM 06JAP1
Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules 1625

FAA’s Determination and Requirements under Executive Order 13132. This (d) Subject
of This Proposed AD proposed AD would not have a Air Transport Association (ATA) of
This product has been approved by substantial direct effect on the States, on America Code 49, Airborne Auxiliary Power.
the aviation authority of another the relationship between the national (e) Reason
country, and is approved for operation Government and the States, or on the
This AD was prompted by a report of a fire
in the United States. Pursuant to our distribution of power and in the auxiliary power unit (APU) air intake.
bilateral agreement with the State of responsibilities among the various An analysis demonstrated that, following
Design Authority, we have been notified levels of government. numerous unsuccessful APU start attempts in
of the unsafe condition described in the For the reasons discussed above, I flight, there is a risk of reverse airflow,
MCAI and service information certify this proposed regulation: leading to flame propagation to the APU air
referenced above. We are proposing this 1. Is not a ‘‘significant regulatory inlet and air intake duct. This AD was also
action’’ under Executive Order 12866; prompted by the determination that AD
AD because we evaluated all pertinent 2007–13–08 only addresses the unsafe
2. Is not a ‘‘significant rule’’ under the
information and determined an unsafe condition for certain airplanes. We are
condition exists and is likely to exist or DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); issuing this AD to detect and correct reverse
develop on other products of these same flow during APU startup, leading to flame
3. Will not affect intrastate aviation in
type designs. propagation in the APU air inlet and intake
Alaska; and duct. Such conditions could result in an in-
Costs of Compliance 4. Will not have a significant flight fire in the APU area.
We estimate that this proposed AD economic impact, positive or negative,
on a substantial number of small entities (f) Compliance
affects 1,182 airplanes of U.S. registry.
The actions required by AD 2007–13– under the criteria of the Regulatory Comply with this AD within the
Flexibility Act. compliance times specified, unless already
08, and retained in this proposed AD, done.
take about 4 work-hours per product, at List of Subjects in 14 CFR Part 39
an average labor rate of $85 per work- (g) Repetitive Inspections and Corrective
hour. Based on these figures, the Air transportation, Aircraft, Aviation Actions
estimated cost of the actions that are safety, Incorporation by reference, Except as provided by paragraph (i) of this
required by AD 2007–13–08 is $340 per Safety. AD, within 600 flight hours after July 25,
product. The Proposed Amendment 2007 (the effective date of AD 2007–13–08),
We also estimate that it would take or within 60 days after the effective date of
Accordingly, under the authority this AD, whichever occurs later: Inspect the
about 4 work-hours per product to
delegated to me by the Administrator, APU starter motor, APU air inlet plenum,
comply with the basic requirements of and APU air intake of each affected APU
the FAA proposes to amend 14 CFR part
this proposed AD. The average labor identified in table 1 to paragraphs (g), (h),
39 as follows:
rate is $85 per work-hour. Based on (i)(2), (j), and (k) of this AD for discrepancies;
these figures, we estimate the cost of PART 39—AIRWORTHINESS and do all applicable corrective actions
this proposed AD on U.S. operators to DIRECTIVES before further flight; in accordance with the
be $401,880, or $340 per product. Accomplishment Instructions of Airbus
We have received no definitive data ■ 1. The authority citation for part 39 Service Bulletin A320–49–1068, Revision 01,
that would enable us to provide cost continues to read as follows: dated February 2, 2006. Repeat the
inspection thereafter at intervals not to
estimates for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701. exceed 600 flight hours.
specified in this proposed AD.
§ 39.13 [Amended]
Authority for This Rulemaking TABLE 1 TO PARAGRAPHS (g), (h),
■ 2. The FAA amends § 39.13 by
Title 49 of the United States Code (i)(2), (j), AND (k) OF THIS AD—AF-
removing Airworthiness Directive (AD)
specifies the FAA’s authority to issue FECTED APU AND ELECTRONIC
2007–13–08, Amendment 39–15112 (72
rules on aviation safety. Subtitle I, FR 33877, June 20, 2007), and adding CONTROL BOX (ECB)
section 106, describes the authority of the following new AD:
the FAA Administrator. ‘‘Subtitle VII: APU ECB Part Numbers (P/N)
Airbus: Docket No. FAA–2016–9567;
Aviation Programs,’’ describes in more Directorate Identifier 2016–NM–147–AD. APIC APS 4500003D, 4500003E,
detail the scope of the Agency’s 3200. 4500003F, 4500003G,
authority. (a) Comments Due Date
4500003H, or 4500003J.
We are issuing this rulemaking under We must receive comments by February Honeywell 3888394–120201, 3888394–
the authority described in ‘‘Subtitle VII, 21, 2017. 131–9A. 121202, 3888394–121203,
Part A, Subpart III, Section 44701: (b) Affected ADs 3888394–221202, or
General requirements.’’ Under that 3888394–221203.
This AD replaces AD 2007–13–08,
section, Congress charges the FAA with Honeywell 307950–1, 307950–2,
Amendment 39–15112 (72 FR 33877, June GTCP36– 307950–3, 307950–4,
promoting safe flight of civil aircraft in 20, 2007) (‘‘AD 2007–13–08’’).
air commerce by prescribing regulations 300. 304640–1, 304640–2,
for practices, methods, and procedures (c) Applicability 304640–3, 304640–4,
304817–1, or 304817–2.
the Administrator finds necessary for This AD applies to Airbus airplanes
safety in air commerce. This regulation identified in paragraphs (c)(1), (c)(2), (c)(3),
and (c)(4) of this AD, all manufacturer serial (h) Repetitive Cleanings
sradovich on DSK3GMQ082PROD with PROPOSALS

is within the scope of that authority
numbers, certificated in any category. Except as provided by paragraph (i) of this
because it addresses an unsafe condition
(1) Model A318–111, –112, –121, and –122 AD, prior to the accumulation of 2,400 flight
that is likely to exist or develop on airplanes. hours since first flight of the airplane, or
products identified in this rulemaking (2) Model A319–111, –112, –113, –114, within 600 flight hours after July 25, 2007
action. –115, –131, –132, and –133 airplanes. (the effective date of AD 2007–13–08), or
Regulatory Findings (3) Model A320–211, –212, –214, –231, within 60 days after the effective date of this
–232, and –233 airplanes. AD, whichever occurs latest, unless
We determined that this proposed AD (4) Model A321–111, –112, –131, –211, accomplished previously in accordance with
would not have federalism implications –212, –213, –231, and –232 airplanes. Airbus Service Bulletin A320–49–1098,

VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\06JAP1.SGM 06JAP1
1626 Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules

dated June 21, 2011: Clean the APU air intake effective date of this AD is installed, the (1) Alternative Methods of Compliance
of each affected APU identified in table 1 to actions specified in paragraphs (g) and (h) of (AMOCs): The Manager, International
paragraphs (g), (h), (i)(2), (j), and (k) of this this AD are not required, provided the Branch, ANM–116, Transport Airplane
AD, in accordance with the Accomplishment conditions specified in paragraphs (i)(3)(i) Directorate, FAA, has the authority to
Instructions of Airbus Service Bulletin A320– and (i)(3)(ii) of this AD are met. approve AMOCs for this AD, if requested
49–1068, Revision 01, dated February 2, (i) The part number must be approved by using the procedures found in 14 CFR 39.19.
2006. Repeat the cleaning task thereafter at the Manager, International Branch, ANM–
intervals not to exceed 2,400 flight hours. In accordance with 14 CFR 39.19, send your
116, Transport Airplane Directorate, FAA; or
request to your principal inspector or local
(i) Exceptions to Requirements in EASA; or Airbus’s EASA DOA.
(ii) The installation must be accomplished Flight Standards District Office, as
Paragraphs (g) and (h) of This AD appropriate. If sending information directly
in accordance with airplane modification
(1) For airplanes equipped with an APU instructions approved by the Manager, to the International Branch, send it to ATTN:
and associated ECB part number identified in International Branch, ANM–116, Transport Sanjay Ralhan, Aerospace Engineer,
table 2 to paragraphs (i)(1), (i)(2), and (j) of International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
this AD, the actions specified in paragraphs
Airbus’s EASA DOA. Airplane Directorate, FAA, 1601 Lind
(g) and (h) of this AD are not required.
Avenue SW., Renton, WA 98057–3356;
(j) Optional Terminating Action
telephone 425–227–1405; fax 425–227–1149.
TABLE 2 TO PARAGRAPHS (i)(1), (i)(2), Replacing an affected ECB identified in Information may be emailed to: 9-ANM-116-
AND (j) OF THIS AD—NON-AF- table 1 to paragraphs (g), (h), (i)(2), (j), and AMOC-REQUESTS@faa.gov.
FECTED ECB (k) of this AD with an ECB having a part
(i) Before using any approved AMOC,
number identified in table 2 to paragraphs
(i)(1), (i)(2), and (j) of this AD, as applicable notify your appropriate principal inspector,
APU ECB Part Numbers (P/N) or lacking a principal inspector, the manager
to the APU installed on the airplane,
APIC APS 4500003K, 4500003L, or constitutes terminating action for the of the local flight standards district office/
3200. 4500003M. repetitive inspections required by paragraphs certificate holding district office. The AMOC
Honeywell 3888394–121204, 3888394– (g) and (h) of this AD. The replacement must approval letter must specifically reference
131–9A. 121205, 3888394–221204, be done in accordance with the this AD.
3888394–221205, or Accomplishment Instructions of the (ii) AMOCs approved previously for AD
3888394–321206. applicable service information identified in 2007–13–08 are approved as AMOCs for the
Honeywell 304640–5, 304817–3, or paragraph (i)(2)(ii) (A), (i)(2)(ii)(B), corresponding provisions of paragraphs (g)
GTCP36– 3888394–230301. (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or and (h) of this AD.
300. (i)(2)(ii)(F) of this AD, or using a method
(2) Contacting the Manufacturer: As of the
approved by the Manager, International
Branch, ANM–116, Transport Airplane effective date of this AD, for any requirement
(2) For airplanes on which Airbus
Directorate, FAA; or EASA; or Airbus’s EASA in this AD to obtain corrective actions from
Modification 35803, 35936, 152289, 152645,
155015, or 157848 has been embodied in DOA. a manufacturer, the action must be
production, the actions specified in accomplished using a method approved by
(k) Parts Installation Prohibition the Manager, International Branch, ANM–
paragraphs (g) and (h) of this AD are not
required provided that, within 30 days after As of the effective date of this AD, no 116, Transport Airplane Directorate, FAA; or
the effective date of this AD, the applicable person may install on any airplane an APU EASA; or Airbus’s EASA DOA. If approved
actions specified in paragraphs (i)(2)(i) and with an associated ECB identified in table 1 by the DOA, the approval must include the
(i)(2)(ii) of this AD are done. to paragraphs (g), (h), (i)(2), (j), and (k) of this DOA-authorized signature.
(i) The part number of the installed ECB is AD.
identified. (n) Related Information
(l) Credit for Previous Actions
(ii) Any affected ECB identified in table 1 (1) Refer to Mandatory Continuing
to paragraphs (g), (h), (i)(2), (j), and (k) of this This paragraph provides credit for actions
specified in paragraphs (i)(2) and (j) of this Airworthiness Information (MCAI) EASA AD
AD that is found to be installed is replaced
with an ECB having a part number identified AD, if those actions were performed before 2016–0176, dated August 31, 2016, for
in table 2 to paragraphs (i)(1), (i)(2), and (j) the effective date of this AD using any of the related information. This MCAI may be
of this AD, as applicable to the APU installed service information specified in paragraphs found in the AD docket on the Internet at
on the airplane; and the replacement is done (l)(1) through (l)(7) of this AD. http://www.regulations.gov by searching for
in accordance with the Accomplishment (1) Airbus Service Bulletin A320–49–1075, and locating Docket No. FAA–2016–9567.
Instructions of the applicable service dated September 22, 2006, which was (2) For service information identified in
information identified in paragraph incorporated by reference in AD 2007–13–08. this AD, contact Airbus, Airworthiness
(i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (2) Airbus Service Bulletin A320–49–1077, Office–EIAS, 1 Rond Point Maurice Bellonte,
(i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this dated March 21, 2007, which is not
31707 Blagnac Cedex, France; telephone: +33
AD; or using a method approved by the incorporated by reference in this AD.
5 61 93 36 96; fax: +33 5 61 93 44 51; email:
Manager, International Branch, ANM–116, (3) Airbus Service Bulletin A320–49–1077,
Transport Airplane Directorate, FAA, or the Revision 01, dated August 9, 2007, which is account.airworth-eas@airbus.com; Internet:
European Aviation Safety Agency (EASA), or not incorporated by reference in this AD. http://www.airbus.com. You may view this
Airbus’s EASA Design Organization (4) Airbus Service Bulletin A320–49–1077, service information at the FAA, Transport
Approval (DOA). Revision 02, dated July 1, 2008, which is not Airplane Directorate, 1601 Lind Avenue SW.,
(A) Airbus Service Bulletin A320–49–1070, incorporated by reference in this AD. Renton, WA. For information on the
dated July 28, 2006. (5) Airbus Service Bulletin A320–49–1077, availability of this material at the FAA, call
(B) Airbus Service Bulletin A320–49–1075, Revision 03, dated December 8, 2008, which 425–227–1221.
Revision 01, dated December 1, 2006. is not incorporated by reference in this AD.
Issued in Renton, Washington, on
(C) Airbus Service Bulletin A320–49–1077, (6) Airbus Service Bulletin A320–49–1107,
sradovich on DSK3GMQ082PROD with PROPOSALS

Revision 04, dated February 27, 2013. dated November 5, 2013, which is not December 23, 2016.
(D) Airbus Service Bulletin A320–49–1098, incorporated by reference in this AD. Thomas Groves,
dated June 21, 2011. (7) Airbus Service Bulletin A320–49–1107, Acting Manager, Transport Airplane
(E) Airbus Service Bulletin A320–49–1102, Revision 01, dated July 28, 2015, which is Directorate, Aircraft Certification Service.
dated January 3, 2012. not incorporated by reference in this AD.
(F) Airbus Service Bulletin A320–49–1107, [FR Doc. 2016–31960 Filed 1–5–17; 8:45 am]
Revision 02, dated May 10, 2016. (m) Other FAA AD Provisions
BILLING CODE 4910–13–P
(3) For airplanes on which an APU ECB The following provisions also apply to this
having a part number approved after the AD:

VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 PO 00000 Frm 00019 Fmt 4702 Sfmt 9990 E:\FR\FM\06JAP1.SGM 06JAP1
Document Created: 2017-01-06 01:30:11
Document Modified: 2017-01-06 01:30:11
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by February 21, 2017.
Contact		Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149.
FR Citation		82 FR 1623
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
82 FR 1623 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 4 (January 6, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
