80 FR 68429 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 214 (November 5, 2015)

We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of spoiler and elevator computer (SEC) latent failures; an undetected loss of a SEC in flight will result in loss in redundancy for elevator control. This AD requires revising the After Start Normal Procedures section of the airplane flight manual (AFM) to provide procedures that will address this loss of redundancy. We are issuing this AD to ensure that the flightcrew has procedures to address loss of redundancy of SEC 1 and SEC 2. A SEC failure, in conjunction with a loss of trimmable horizontal stabilizer (THS) electrical control due to jamming or rupture, could result in failure of an elevator and aileron computer, and consequent loss of elevator control and reduced control of the airplane.

[Federal Register Volume 80, Number 214 (Thursday, November 5, 2015)]
[Rules and Regulations]
[Pages 68429-68432]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-27688]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4211; Directorate Identifier 2015-NM-150-AD; 
Amendment 39-18311; AD 2015-22-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A318, A319, A320, and A321 series airplanes. This AD was 
prompted by reports of spoiler and elevator computer (SEC) latent 
failures; an undetected loss of a SEC in flight will result in loss in 
redundancy for elevator control. This AD requires revising the After 
Start Normal Procedures section of the airplane flight manual (AFM) to 
provide procedures that will address this loss of redundancy. We are 
issuing this AD to ensure that the flightcrew has procedures to address 
loss of redundancy of SEC 1 and SEC 2. A SEC failure, in conjunction 
with a loss of trimmable horizontal stabilizer (THS) electrical control 
due to jamming or rupture, could result in failure of an elevator and 
aileron computer, and consequent loss of elevator control and reduced 
control of the airplane.

DATES: This AD becomes effective November 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 20, 
2015.
    We must receive comments on this AD by December 21, 2015.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    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 referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4211.

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-2015-
4211; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and

[[Page 68430]]

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: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0191, dated September 22, 2015 (correction 
September 25, 2015) (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 series 
airplanes. The MCAI states:

    With the introduction of new Spoiler and Elevator Computer (SEC) 
hardware C Part Number (P/N) B372CAM0100 with software standards 
122, 124 and 125 (identified by P/N B372CAM0101, P/N B372CAM0102 and 
P/N B372CAM0103, respectively), some airlines have reported 
receiving maintenance messages, e.g. ``SEC OR WIRING FROM L or R 
ELEV POS MON XDCR'' and/or ``SEC OR WIRING FROM G or Y ELEV POS 
XDCR'', which are associated with servo control or elevator 
transducer monitoring. Such messages are triggered by a short data 
inconsistency due to power transients, when the engines are started.
    This condition, if not corrected, could lead to an undetected 
loss of redundancy during flight if an affected SEC cannot control 
the related elevator servo control(s), possibly resulting in reduced 
control of the aeroplane.
    It was determined that, to recover full redundancy, a reset of 
SEC 1 and SEC 2 must be done after engines start and Airbus have 
developed an Airplane Flight Manual (AFM) Temporary Revision (TR), 
published as TR 572 Issue 1.1, to provide the necessary flight crew 
procedure.

    Required actions include revising the After Start Normal Procedures 
section of the AFM to provide procedures that will address this loss of 
redundancy. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4211.

Related Service Information Under 1 CFR Part 51

    Airbus has issued A318/A319/A320/A321 Temporary Revision TR572, 
Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321 
Airplane Flight Manual. The service information describes the reset of 
SEC 1 and SEC 2 that must be done after engines start. 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 of this AD.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because a SEC 
failure in conjunction with a loss of THS electrical control due to 
jamming or rupture, could result in failure of an elevator and aileron 
computer, and consequent loss of elevator control and reduced control 
of the airplane. Therefore, we determined that notice and opportunity 
for public comment before issuing this AD are impracticable and that 
good cause exists for making this amendment effective in fewer than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-4211; Directorate 
Identifier 2015-NM-150-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 959 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $81,515, or $85 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 68431]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
 2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

2015-22-06 Airbus: Amendment 39-18311. Docket No. FAA-2015-4211; 
Directorate Identifier 2015-NM-150-AD.

(a) Effective Date

    This AD becomes effective November 20, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(4) of this AD, 
all manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Reason

    This AD was prompted by reports of spoiler and elevator computer 
(SEC) latent failures; an undetected loss of a SEC in flight will 
result in loss in redundancy for elevator control. This AD requires 
revising the After Start Normal Procedures section of the airplane 
fight manual (AFM) to provide procedures that will address this loss 
of redundancy. We are issuing this AD to ensure that the flightcrew 
has procedures to address loss of redundancy of SEC 1 and SEC 2. A 
SEC failure, in conjunction with a loss of trimmable horizontal 
stabilizer (THS) electrical control due to jamming or rupture, could 
result in failure of an elevator and aileron computer, and 
consequent loss of elevator control and reduced control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Airplane Flight Manual Revision

    For airplanes equipped with SEC hardware C part number (P/N) 
B372CAM0100 with software standard 122 (P/N B372CAM0101), 124 (P/N 
B372CAM0102), or 125 (P/N B372CAM0103), on SEC position 1 or 2, or 
both: Within 30 days after the effective date of this AD, revise the 
After Start Normal Procedures section of the AFM to include the 
statement specified in figure 1 to paragraph (g) of this AD. This 
may be done by inserting a copy of this AD, or Airbus A318/A319/
A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13, 
2015, to the Airbus A318/A319/A320/A321 Airplane Flight Manual, into 
the applicable AFM.

      Figure 1 to Paragraph (g) of This AD--AFM Temporary Revision
------------------------------------------------------------------------
 
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AFTER START NORMAL PROCEDURE
After both engines start:
Turn OFF then ON SEC 1 and SEC 2 one after another.
------------------------------------------------------------------------


    Note 1 to paragraph (g) of this AD:  When a statement identical 
to that in figure 1 to paragraph (g) of this AD has been included in 
the After Start Normal Procedures section of the general revisions 
of the AFM, the general revisions may be inserted into the AFM, and 
the copy of this AD or Airbus A318/A319/A320/A321 Temporary Revision 
TR572, Issue 1.0, dated August 13, 2015, may be removed from the 
AFM.


    Note 2 to paragraph (g) of this AD:  Airbus Operations 
Engineering Bulletin OEB-50 provides additional information on the 
subject addressed by this AD.

(h) Optional Modification

    Modification of an airplane by installation of SEC hardware C 
with software standard 126 (P/N B372CAM0104) (Airbus Modification 
161208) allows removal of the AFM revision required by paragraph (g) 
of this AD for that airplane.

(i) Parts Installation Limitation

    For all airplanes: As of the effective date of this AD, do not 
install SEC hardware C P/N B372CAM0100 with software standard 122 
(P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), 
on SEC position 1 or 2, or both, on any airplane, unless the AFM of 
the airplane is revised concurrently with that installation, as 
required by paragraph (g) of this AD.

(j) 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]. 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 Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2015-0191, dated September 22, 2015 
(corrected September 25, 2015), for related information. You may 
examine the MCAI on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-4211.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus A318/A319/A320/A321 Temporary Revision TR572, Issue 
1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321 
Airplane Flight Manual.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://

[[Page 68432]]

www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on October 22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27688 Filed 11-4-15; 8:45 am]
BILLING CODE 4910-13-P