Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 56279 

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) 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 

(j) Refer to MCAI Transport Canada Civil 

Aviation (TCCA) Airworthiness Directive 

CF–2010–22, dated July 20, 2010; and 

Bombardier Temporary Revision MRB–45, 

dated October 6, 2009, to Section 1–32, 

Systems/Powerplant Maintenance Program, 

of Part 1 of the Maintenance Review Board 

Report of the Bombardier Q400 Dash 8 

Maintenance Requirements Manual, PSM 1– 

84–7; for related information. 

Material Incorporated by Reference 

(k) You must use Bombardier Temporary 

Revision MRB–45, dated October 6, 2009, to 

Section 1–32, Systems/Powerplant 

Maintenance Program, of Part 1 of the 

Maintenance Review Board Report of the 

Bombardier Q400 Dash 8 Maintenance 

Requirements Manual, PSM 1–84–7, 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 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q–Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

e-mail thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(3) 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. 

(4) 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 August 

23, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22278 Filed 9–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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 nonoptimised 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 Ge ́ne ́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 

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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 nonoptimised 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 

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Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing 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 nonoptimised 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 

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56282 Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 

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. 

BILLING CODE 4910–13–P 

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BILLING CODE 4910–13–C 

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 


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56284 Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 

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] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0474; Directorate 

Identifier 2010–NM–213–AD; Amendment 

39–16802; AD 2011–18–20] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes, 

and Model A340–200 and –300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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: 

It was noticed in production that the 

distance between the wire harnesses 5376VB/ 

2M and 5377VB/1M which are above the lefthand (LH) and right-hand (RH) door 4, and 

the air conditioning duct could be too small. 

This could result in collision between the 

flexible air conditioning hose and wire 

harnesses. 

This condition, if not corrected, could lead 

to the short circuit of wires dedicated to 

oxygen, which, in case of emergency, could 

result in a large number of passenger oxygen 

masks not being supplied with oxygen, 

possibly causing personal injuries. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 18, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 18, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov or in person at the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 23, 2011 (76 FR 29673). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

It was noticed in production that the 

distance between the wire harnesses 5376VB/ 

2M and 5377VB/1M which are above the lefthand (LH) and right-hand (RH) door 4, and 

the air conditioning duct could be too small. 

This could result in collision between the 

flexible air conditioning hose and wire 

harnesses. 

mstockstill on DSK4VPTVN1PROD with RULES