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[Federal Register Volume 76, Number 177 (Tuesday, September 13, 2011)]
[Rules and Regulations]
[Pages 56279-56284]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-23131]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0917; Directorate Identifier 2011-NM-157-AD; 
Amendment 39-16806; AD 2011-19-01]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Series 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 the 
products listed above that would supersede an existing AD. This AD 
results from mandatory continuing airworthiness information (MCAI) 
originated by an aviation authority of another country to identify and 
correct an unsafe condition on an aviation product. The MCAI describes 
the unsafe condition as:

    In service experience has shown a number of events of pin to 
socket arcing at the Integrated Drive Generator (IDG) feeder cable 
pylon/nacelle interface connector. The fretting corrosion phenomenon 
was identified to be the root cause of the pin to socket arcing.
    Investigation has identified a non-optimised electrical harness 
installation as a contributing factor to this phenomenon that could 
lead to electrical arcs with possible electrical flickering.

* * * * *
    [S]ome operators reported cases of Display Unit (DU) flickering, 
despite the fact that the engines installed did not belong to the 
affected batch, and that these aeroplanes had been modified to 
incorporate one of * * * two terminating actions, * * *.
    [S]ome intermittent electrical power supply interruptions may 
not be detectable by the electrical power monitoring system, thereby 
preventing an automatic disconnection of the failed generator.

* * * * *

The unsafe condition is transient loss of certain systems, which could 
result in the reduced ability of the flightcrew to cope with adverse 
flight conditions. This AD requires actions that are intended to 
address the unsafe condition described in the MCAI.

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

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, Washington 98057-3356; telephone (425) 
227-1405; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    On July 16, 2004, we issued AD 2004-15-14, Amendment 39-13748 (69 
FR 45243, July 29, 2004), which corresponded to Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (the aviation 
authority for France) AD F-2004-074, dated May 26, 2004. That FAA AD 
required revising the airplane flight manual (AFM) to include a 
procedure intended to address an unsafe condition on 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. That FAA AD also required an 
inspection of the firewall connector for signs of arcing if

[[Page 56280]]

an integrated drive generator (IDG) was shut down in-flight 
automatically or using the AFM procedure, and corrective action as 
applicable. That FAA AD also included an optional terminating action to 
replace the IDG harnesses and connectors. The inspection and 
replacement actions were not required or provided in French AD F-2004-
074.
    Since we issued AD 2004-15-14, Amendment 39-13748 (69 FR 45243, 
July 29, 2004), some operators reported cases of display unit (DU) 
flickering, despite being modified in production, or in service using 
certain service information. Therefore, to address the unsafe condition 
associated with DU flickering, Airbus developed a new AFM procedure. We 
have determined that this new AFM procedure is necessary to address the 
identified unsafe condition. The European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2011-0142, 
dated July 25, 2011 (referred to after this as ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    In service experience has shown a number of events of pin to 
socket arcing at the Integrated Drive Generator (IDG) feeder cable 
pylon/nacelle interface connector. The fretting corrosion phenomenon 
was identified to be the root cause of the pin to socket arcing.
    Investigation has identified a non-optimised electrical harness 
installation as a contributing factor to this phenomenon that could 
lead to electrical arcs with possible electrical flickering.
    These incidents may cause the following symptoms during flight:
--Intermittent flickering of display units, e.g. primary flight 
display, navigation display, electronic centralized aircraft 
monitoring (ECAM) and/or multipurpose control display unit (MCDU),
--Transient disconnection of several systems (auto pilot, yaw 
damper, auto throttle), triggering of aircraft system warnings and/
or flags,
--Loss of IDG power supply on the affected engine, and/or
--Flickering of cabin lights.
    The Aircraft Flight Manual (AFM) Temporary Revision (TR) 
4.02.00/20 was issued as a procedure to be applied in such case. 
Consequently, EASA AD 2006-0280, which superseded the DGAC France AD 
F-2004-074 [which corresponds to FAA AD 2004-15-14, Amendment 39-
13748 (69 FR 45243, July 29, 2004)], required the amendment of the 
AFM to impose the limitations as detailed in AFM TR 4.02.00/20 for 
aeroplanes with certain engines (limited batch of engines, 
identified by serial number) installed.
    After the introduction of this AFM TR, some operators reported 
cases of Display Unit (DU) flickering, despite the fact that the 
engines installed did not belong to the affected batch, and that 
these aeroplanes had been modified to incorporate one of the two 
terminating actions, Airbus Service Bulletin (SB) A320-71-1030 
(Airbus modification (mod.) 34982) and SB A320-71-1034 (Airbus mod. 
32943). The investigations of these occurrences revealed some 
intermittent electrical power supply interruptions. Analysis showed 
that these interruptions may fluctuate within the electrical 
protection limits and in some rare occasions, may affect some of the 
connected aeroplanes systems.
    As a consequence, some intermittent electrical power supply 
interruptions may not be detectable by the electrical power 
monitoring system, thereby preventing an automatic disconnection of 
the failed generator.
    To address this issue, Airbus has issued a new AFM procedure, 
applicable to all aeroplanes. This ``DISPLAY UNIT FAILURE'' 
procedure, which replaces the one contained in AFM TR 4.02.00/20, 
allows the flight crew to determine the affected generator, select 
it OFF and reset the rudder trim.
    For the reasons described above, this AD, which supersedes EASA 
AD 2006-0280, requires amendment of the applicable AFM to ensure 
that the flight crew applies the appropriate operational procedure.

The unsafe condition is transient loss of certain systems, which could 
result in the reduced ability of the flightcrew to cope with adverse 
flight conditions. This AD also expands the applicability of AD 2004-
15-14, Amendment 39-13748 (69 FR 45243, July 29, 2004), by including 
all Model A318, A319, A320, and A321 series airplanes. You may obtain 
further information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Temporary Revision TR112, Issue 1.1, dated 
November 29, 2010, to the Airbus A318/A319/A320/A321 Airplane Flight 
Manual. The actions described in this service information are intended 
to correct the unsafe condition identified in the MCAI.

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.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

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 of 
the additional in-service events of DU flickering on Model A318, A319, 
A320, and A321 series airplanes that were not included in the 
applicability of FAA AD 2004-15-14, Amendment 39-13748 (69 FR 45243, 
July 29, 2004), or on which the terminating actions of paragraph (h) of 
that AD were done. 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-2011-0917; Directorate 
Identifier 2011-NM-157-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 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

[[Page 56281]]

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); and
    3. 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 Amendment 39-13748 (69 FR 
45243, July 29, 2004) and adding the following new AD:

2011-19-01 Airbus: Amendment 39-16806. Docket No. FAA-2011-0917; 
Directorate Identifier 2011-NM-157-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 28, 2011.

Affected ADs

    (b) This AD supersedes AD 2004-15-14, Amendment 39-13748 (69 FR 
45243, July 29, 2004).

Applicability

    (c) 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.

Subject

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

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    In service experience has shown a number of events of pin to 
socket arcing at the Integrated Drive Generator (IDG) feeder cable 
pylon/nacelle interface connector. The fretting corrosion phenomenon 
was identified to be the root cause of the pin to socket arcing.
    Investigation has identified a non-optimised electrical harness 
installation as a contributing factor to this phenomenon that could 
lead to electrical arcs with possible electrical flickering.
* * * * *
    [S]ome operators reported cases of Display Unit (DU) flickering, 
despite the fact that the engines installed did not belong to the 
affected batch, and that these aeroplanes had been modified to 
incorporate one of * * * two terminating actions, * * *.
    [S]ome intermittent electrical power supply interruptions may 
not be detectable by the electrical power monitoring system, thereby 
preventing an automatic disconnection of the failed generator.
* * * * *
    The unsafe condition is transient loss of certain systems, which 
could result in the reduced ability of the flightcrew to cope with 
adverse flight conditions.

Compliance

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

Restatement of Requirements of AD 2004-15-14, Amendment 39-13748 (69 FR 
45243, July 29, 2004), With Revised Method of Compliance:

Revision of Airplane Flight Manual (AFM)

    (g) 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 (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.

Post-IDG Shutdown Inspection

    (h) 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 an IDG is shut down by the flightcrew in 
accordance with the TR procedures specified in paragraph (g) of this 
AD, or if an IDG is shut down automatically before the effective 
date of this AD, do the actions specified in paragraph (h)(1) or 
(h)(2) of this AD. If an IDG is shut down automatically on or after 
the effective date of this AD, do the actions specified in paragraph 
(k) of this AD.
    (1) Before further flight, inspect the firewall connector of the 
affected IDG 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 IDG 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 IDG, do the actions specified in 
paragraph (h)(1) of this AD. As of the effective date of this AD, 
operate the airplane in accordance with a method approved by the 
Manager, International Branch, ANM-116.

    Note 1: Guidance on provisions and compliance periods for 
operating the airplane with an inoperative, affected IDG can be

[[Page 56282]]

found in the FAA-approved Master Minimum Equipment List.

Terminating Action for Paragraphs (g) and (h) of This AD if Done Before 
the Effective Date of This AD

    (i) 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 IDG harnesses and connectors on 
both engines in accordance with Airbus Service Bulletin A320-71-
1030, dated February 27, 2003, before the effective date of this AD 
terminates the requirements of paragraphs (g) and (h) of this AD.

    Note 2: 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.

New Requirements of This AD:

Revision of AFM

    (j) For all airplanes: Within 10 days after the effective date 
of this AD, revise the applicable section of the Airbus A318/319/
320/321 AFM to include the information in Figure 1 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: When the information in Figure 1 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 of this AD or Airbus TR TR112, Issue 
1.1, dated November 29, 2010.

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[[Page 56283]]

[GRAPHIC] [TIFF OMITTED] TR13SE11.008

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Post-IDG Shutdown Inspection

    (k) For all airplanes: If an IDG is shut down by the flightcrew 
in accordance with the TR procedures specified in paragraph (j) of 
this AD, or if an IDG is shut down automatically on or after the 
effective date of this AD, 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 IDG 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 IDG inoperative in 
accordance with a method approved by the Manager, International 
Branch, ANM-116. Before further use of the affected IDG, do the 
actions specified in paragraph (k)(1) of this AD.

    Note 4: Guidance on provisions and compliance periods for 
operating the airplane

[[Page 56284]]

with an inoperative, affected IDG can be found in the FAA-approved 
Master Minimum Equipment List.

FAA AD Differences

    Note 5: This AD differs from the MCAI and/or service information 
as follows: The MCAI does not require inspecting an IDG that has 
been shut down in accordance with Airbus TR TR112, Issue 1.1, dated 
November 29, 2010, or that has been shut down automatically. We have 
determined that investigative and corrective actions (including an 
inspection for signs of arcing, and repair or replacement of any 
discrepant IDG harness/connector with a new harness/connector) are 
necessary due to the severity of the problem to prevent the unsafe 
condition from recurring. The inspections and corrective actions 
must be done in accordance with a method approved by Manager, 
International Branch, ANM-116.

Other FAA AD Provisions

    (l) 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, Washington 98057-3356; telephone (425) 
227-1405; fax (425) 227-1149 Information may be e-mailed 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 corresponding provisions of 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 to assure the product 
is airworthy before it is returned to service.

Related Information

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

Material Incorporated by Reference

    (n) You must use Airbus Service Bulletin A320-71-1030, dated 
February 27, 2003; Airbus Temporary Revision 4.02.00/20, dated May 
3, 2004, to the Airbus A318/319/320/321 Airplane Flight Manual 
(AFM); and Airbus Temporary Revision TR112, Issue 1.1, dated 
November 29, 2010, to the Airbus A318/319/320/321 AFM; as 
applicable; to do the actions required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus Temporary Revision TR112, Issue 
1.1, dated November 29, 2010, to the Airbus A318/319/320/321 AFM 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Airbus Service Bulletin A320-71-1030, 
dated February 27, 2003; and Temporary Revision 4.02.00/20, dated 
May 3, 2004, to the Airbus A318/319/320/321 AFM; on August 13, 2004 
(69 FR 45243, July 29, 2004).
    (3) For 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; e-mail: account.airworth-eas@airbus.com; Internet 
http://www.airbus.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (5) 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 NARA, 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 September 1, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2011-23131 Filed 9-12-11; 8:45 am]
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