Document ID: FAA-2012-0802-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2012-08-07T04:00Z

[Federal Register Volume 77, Number 152 (Tuesday, August 7, 2012)]
[Rules and Regulations]
[Pages 46929-46932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-18625]

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  Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules 
and Regulations  

[[Page 46929]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0802; Directorate Identifier 2012-NM-124-AD; 
Amendment 39-17145; AD 2011-19-01 R1]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are revising an existing airworthiness directive (AD) that 
applies to all Airbus Model A318, A319, A320, and A321 series 
airplanes. The existing AD currently requires revising the airplane 
flight manual (AFM) to include a procedure intended to address the 
unsafe condition, an inspection of the firewall connector for signs of 
arcing if an integrated drive generator (IDG) (or generator (GEN)) was 
shut down in-flight automatically or using the AFM procedure, and 
corrective action if necessary; and provides an optional terminating 
action for certain AFM revision and inspections. This AD was prompted 
by the potential for an inadvertent error by flightcrew to use the IDG 
switch instead of the GEN switch when doing the AFM display unit 
failure procedure required by the existing AD. This AD retains the 
actions required by the existing AD and clarifies certain terminology. 
We are issuing this AD to prevent transient loss of certain systems, 
which could result in the reduced ability of the flightcrew to cope 
with adverse flight conditions.

DATES: This AD becomes effective August 22, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
28, 2011 (76 FR 56279, September 13, 2011).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
13, 2004 (69 FR 45243, July 29, 2004).
    We must receive comments on this AD by September 21, 2012.

ADDRESSES: You may send comments 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 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

    On September 1, 2011, we issued AD 2011-19-01, Amendment 39-16806 
(76 FR 56279, September 13, 2011). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2011-19-01, Amendment 39-16806 (76 FR 56279, 
September 13, 2011), we have received information that there is 
potential for an inadvertent error by flightcrew to use the ``IDG'' 
(integrated drive generator) switch instead of the ``GEN'' 
(abbreviation for generator) switch when doing the AFM display unit 
failure procedure in this AD that requires turning off the integrated 
drive generator under certain conditions. We find that it is necessary 
to clarify our intent with the use of the acronym ``IDG'' in relation 
to ``GEN,'' and to revise paragraphs (h), (i), and (k) of this AD to 
refer to ``GEN.''

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 the same 
type design.

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 
transient loss of certain systems could result in the reduced ability 
of the flightcrew to cope with adverse flight conditions. 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-2012-0802; Directorate 
Identifier 2012-NM-124-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic,

[[Page 46930]]

environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
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.

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 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2011-19-01, Amendment 39-16806 (76 FR 56279, September 13, 2011), and 
adding the following new AD:

2011-19-01 R1 Airbus: Amendment 39-17145; Docket No. FAA-2012-0802; 
Directorate Identifier 2012-NM-124-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective August 22, 
2012.

(b) Affected ADs

    This AD revises AD 2011-19-01, Amendment 39-16806 (76 FR 56279, 
September 13, 2011).

(c) Applicability

    This AD applies to Airbus Model A318-111, A318-112, A318-121, 
A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-
131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-214, 
A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-
211, A321-212, A321-213, A321-231, and A321-232 airplanes; 
certificated in any category; all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 31: Instruments.

(e) Reason

    This AD was prompted by reports of transient loss of certain 
systems and the potential for an inadvertent error by flightcrew to 
use the IDG switch instead of the GEN switch when doing a certain 
airplane flight manual (AFM) display unit failure procedure. We are 
issuing this AD to prevent transient loss of certain systems, which 
could result in the reduced ability of the flightcrew to cope with 
adverse flight conditions.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Revision of Airplane Flight Manual (AFM)

    This paragraph restates the requirements of paragraph (g) of AD 
2011-19-01, Amendment 39-16806 (76 FR 56279, September 13, 2011). 
For Airbus Model A319-131, -132, and -133, A320-231, -232, and -233, 
and A321-131 and -231 series airplanes, except those airplanes on 
which Airbus Modification 32943 has been incorporated in production: 
Within 10 days after August 13, 2004 (the effective date of AD 2004-
15-14, Amendment 39-13748 (69 FR 45243, July 29, 2004)), revise the 
Limitations section of the Airbus A318/319/320/321 AFM to include 
the information in Temporary Revision (TR) 4.02.00/20, dated May 3, 
2004. This may be done by inserting a copy of this TR into the AFM. 
When this TR has been included in general revisions of the AFM, 
those general revisions may be inserted into this AFM, provided the 
relevant information in the general revisions is identical to that 
in this TR. Accomplishing the actions required by paragraph (j) of 
this AD terminates the requirements of this paragraph.

(h) Retained Post-Integrated Drive Generator Shutdown Inspection

    This paragraph restates the requirements of paragraph (h) of AD 
2011-19-01, Amendment 39-16806 (76 FR 56279, September 13, 2011), 
with replacement of the term ``IDG'' with ``GEN.'' For Airbus Model 
A319-131, -132, and -133, A320-231, -232, and -233, and A321-131 and 
-231 series airplanes, except those airplanes on which Airbus 
Modification 32943 has been incorporated in production: If a GEN is 
shut down by the flightcrew in accordance with the TR procedures 
specified in paragraph (g) of this AD, or if a GEN is shut down 
automatically before September 28, 2011 (the effective date of AD 
2011-19-01), do the actions specified in paragraph (h)(1) or (h)(2) 
of this AD. If a GEN is shut down automatically on or after 
September 28, 2011, do the actions specified in paragraph (k) of 
this AD.
    (1) Before further flight, inspect the firewall connector of the 
affected GEN to detect signs of arcing, in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA. If any sign of arcing is detected: Before 
further flight, either repair the connector or replace the connector 
with a new connector, in accordance with a method approved by the 
Manager, International Branch, ANM-116.
    (2) Operate the airplane with the affected GEN inoperative in 
accordance with the provisions and compliance periods specified in 
the FAA-approved Master Minimum Equipment List or in accordance with 
a method approved by the Manager, International Branch, ANM-116. 
Before further use of the affected GEN, do the actions specified in 
paragraph (h)(1) of this AD. As September 28, 2011 (the effective 
date of AD 2011-19-01, Amendment 39-16806 (76 FR 56279, September 
13, 2011), operate the airplane in accordance with a method approved 
by the Manager, International Branch, ANM-116.

[[Page 46931]]

    Note 1 to paragraph (h) of this AD: Guidance on provisions and 
compliance periods for operating the airplane with an inoperative, 
affected GEN can be found in the FAA-approved Master Minimum 
Equipment List.

(i) Retained Terminating Action for Paragraphs (g) and (h) of This AD 
if Done Before September 28, 2011 (the Effective Date of AD 2011-19-01, 
Amendment 39-16806 (76 FR 56279, September 13, 2011))

    This paragraph restates the requirements of paragraph (i) of AD 
2011-19-01, Amendment 39-16806 (76 FR 56279, September 13, 2011), 
with replacement of the term ``IDG'' with ``GEN.'' For Airbus Model 
A319-131, -132, and -133, A320-231, -232, and -233, and A321-131 and 
-231 series airplanes, except those airplanes on which Airbus 
Modification 32943 has been incorporated in production: Replacement 
of the GEN harnesses and connectors on both engines in accordance 
with Airbus Service Bulletin A320-71-1030, dated February 27, 2003, 
before September 28, 2011 (the effective date of AD 2011-19-01), 
terminates the requirements of paragraphs (g) and (h) of this AD.

    Note 2 to paragraph (i) of this AD:  Airbus Service Bulletin 
A320-71-1030, dated February 27, 2003, refers to International Aero 
Engines Information Bulletin V2500-NAC-70-0736, dated January 28, 
2003, as an additional source of guidance for the harness/connector 
replacement specified in paragraph (i) of this AD.

(j) Retained AFM Revision

    This paragraph restates the requirements of paragraph (j) of AD 
2011-19-01, Amendment 39-16806 (76 FR 56279, September 13, 2011). 
For all airplanes: Within 10 days after September 28, 2011 (the 
effective date of AD 2011-19-01), revise the applicable section of 
the Airbus A318/319/320/321 AFM to include the information in Figure 
1 to paragraph (j) of this AD or the information in Airbus TR TR112, 
Issue 1.1, dated November 29, 2010, to the Airbus A318/319/320/321 
AFM. This may be done by inserting a copy of this AD or Airbus TR 
TR112, Issue 1.1, dated November 29, 2010, in the AFM. Accomplishing 
the actions required by this paragraph terminates the requirements 
of paragraph (g) of this AD.

    Note 3 to paragraph (j) of this AD:  When the information in 
Figure 1 to paragraph (j) of this AD or Airbus TR TR112, Issue 1.1, 
dated November 29, 2010, to the Airbus A318/319/320/321 AFM, has 
been included in the applicable section of the general revisions of 
the AFM, the general revisions may be inserted into the AFM, and the 
copy of this AD may be removed from the AFM, provided the relevant 
information in the general revisions is identical to that in Figure 
1 to paragraph (j) of this AD or Airbus TR TR112, Issue 1.1, dated 
November 29, 2010.

 
 
 
                          DISPLAY UNIT FAILURE
[ssquf] Affected DU blank or display distorted:
    Turn off affected DU as required.
     If ECAM DUs affected: Use ECAM/ND SEL
     If EFIS DUs affected: Use PFD/ND XFR.
[ssquf] Diagonal line or ``INVALID DATA'' on affected DU:
    Attempt to recover affected DU by using associated DMC switching.
     If unsuccessful: Turn off then on affected DU.
    [ssquf] Inversion of EWD and SD displays: Turn off then on ECAM
     upper display.
    [ssquf] Affected DU(s) or MCDU flashes intermittently:
        [ssquf] If Captain PFD or ND, both ECAM DUs or upper ECAM DU, or
         MCDU 1 is (are) affected: Turn off GEN 1.
            [ssquf] If DU(s) stop(s) flashing: Keen GEN 1 off for the
             rest of the flight. Use the sideslip indication to verify
             if the rudder trim needs to be reset. If necessary, reset
             the rudder trim. Note: Intermittent Electrical Power Supply
             Interruptions may cause offset in the rudder trim. Select
             AP and/or autothrust as required. APU may be started (Refer
             to NORM-49 Auxiliary Power Unit (APU) and APU generator may
             be used (if available).
            [ssquf] If DU(s) do(es) not stop flashing: Restore GEN 1.
        [ssquf] If First Officer PFD or ND, lower ECAM DU, or MCDU 2 is
         (are) affected: Turn off GEN 2.
            [ssquf] If DU(s) stop(s) flashing: Keep GEN 2 off for the
             rest of the flight. Use the sideslip indication to verify
             if the rudder trim needs to be reset. If necessary, reset
             the rudder trim. Note: Intermittent Electrical Power Supply
             Interruptions may cause offset in the rudder trim. Select
             AP and/or autothrust as required. APU may be started (Refer
             to NORM-49 Auxiliary Power Unit (APU)) and APU generator
             may be used (if available).
            [ssquf] If DU(s) do(es) not stop flashing: Restore GEN 2.
Figure 1 to Paragraph (j)
 

(k) Retained Post-Integrated Drive Generator Shutdown Inspection

    This paragraph restates the requirements of paragraph (k) of AD 
2011-19-01, Amendment 39-16806 (76 FR 56279, September 13, 2011), 
with replacement of the term ``IDG'' with ``GEN.'' For all 
airplanes: If a GEN is shut down by the flightcrew in accordance 
with the TR procedures specified in paragraph (j) of this AD, or if 
a GEN is shut down automatically on or after September 28, 2011 (the 
effective date of AD 2011-19-01), do the actions specified in 
paragraph (k)(1) or (k)(2) of this AD.
    (1) Before further flight, inspect the firewall connector of the 
affected GEN to detect signs of arcing, in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA. If any sign of arcing is detected: Before 
further flight, either repair the connector or replace the connector 
with a new connector, in accordance with a method approved by the 
Manager, International Branch, ANM-116.
    (2) Operate the airplane with the affected GEN inoperative in 
accordance with a method approved by the Manager, International 
Branch, ANM-116. Before further use of the affected GEN, do the 
actions specified in paragraph (k)(1) of this AD.

    Note 4 to paragraph (k) of this AD:  Guidance on provisions and 
compliance periods for operating the airplane with an inoperative, 
affected GEN can be found in the FAA-approved Master Minimum 
Equipment List.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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. 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. AMOCs approved previously for AD 
2004-15-14, Amendment 39-13748 (69 FR 45243, July 29, 2004), are 
acceptable for the corresponding provisions of this AD. AMOCs 
approved previously in accordance with AD 2011-19-01, Amendment 39-
16806 (76 FR 56279, September 13, 2011), are not approved as AMOCs 
with this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required

[[Page 46932]]

to assure the product is airworthy before it is returned to service.

(m) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2011-0142, dated July 25, 2011, and the 
service information identified in paragraphs (m)(1), (m)(2), and 
(m)(3) of this AD for related information.
    (1) Airbus TR 4.02.00/20, dated May 3, 2004, to the Airbus A318/
319/320/321 AFM.
    (2) Airbus TR TR112, Issue 1.1, dated November 29, 2010, to the 
Airbus A318/319/320/321 AFM.
    (3) Airbus Service Bulletin A320-71-1030, dated February 27, 
2003.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 28, 2011 (76 FR 56279, September 13, 2011).
    (i) Airbus Temporary Revision TR112, Issue 1.1, dated November 
29, 2010, to the Airbus A318/319/320/321 (AFM) Airplane Flight 
Manual.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
August 13, 2004 (69 FR 45243, July 29, 2004).
    (i) Airbus Service Bulletin A320-71-1030, dated February 27, 
2003.
    (ii) Airbus Temporary Revision 4.02.00/20, dated May 3, 2004, to 
the Airbus A318/319/320/321 AFM (Airplane Flight Manual).
    (5) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EAS, 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 http://www.airbus.com.
    (6) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (7) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 23, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-18625 Filed 8-6-12; 8:45 am]
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