56286 Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 

Applicability 

(c) This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes, all 

manufacturer serial numbers; certificated in 

any category; except those airplanes 

embodied in production with the 

modifications identified in paragraphs (c)(1) 

and (c)(2) of this AD. 

(1) Modification 57349 and 

(2) Modification 58924 or 201642 or 57562. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 92. 

Reason 

(e) The mandatory continuing 

airworthiness information (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. 

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. 

* * * * * 

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. 

Actions 

(g) Within 24 months after the effective 

date of this AD: Modify the wire harness 

5376VB/2M and 5377VB/1M attachments 

above the LH and RH door 4, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–92– 

3077, Revision 01, dated March 29, 2010; or 

Airbus Mandatory Service Bulletin A340–92– 

4078, Revision 01, dated April 9, 2010; as 

applicable. 

(h) For airplanes that have been modified 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–92–3077 or A340–92–4078, 

both dated June 17, 2008: Within 24 months 

after the effective date of this AD, perform 

the additional work identified in Airbus 

Mandatory Service Bulletin A330–92–3077, 

Revision 01, dated March 29, 2010, or A340– 

92–4078, Revision 01, dated April 9, 2010; as 

applicable (including modifying the support 

assembly of the air outlet, or exchanging 

certain attachment screws of the air outlet 

box assembly on each door, as applicable), in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–92–3077, Revision 01, dated 

March 29, 2010; or Airbus Mandatory Service 

Bulletin A340–92–4078, Revision 01, dated 

April 9, 2010; as applicable. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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: 

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. 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. 

(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 FAAapproved 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 European Aviation Safety 

Agency Airworthiness Directive 2010– 

0103R1, dated April 28, 2011; Airbus 

Mandatory Service Bulletin A330–92–3077, 

Revision 01, dated March 29, 2010; and 

Airbus Mandatory Service Bulletin A340–92– 

4078, Revision 01, dated April 9, 2010; for 

related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A330–92–3077, Revision 01, 

dated March 29, 2010; or Airbus Mandatory 

Service Bulletin A340–92–4078, Revision 01, 

dated April 9, 2010; 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 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) 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; e-mail 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.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 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22380 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–2011–0387; Directorate 

Identifier 2010–NM–222–AD; Amendment 

39–16804; AD 2011–18–22 ] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–201, –202, –203, –223, and –243 

Airplanes, Model A330–300 Series 

Airplanes, Model A340–200 Series 

Airplanes, and Model A340–300 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: 

Surface defects were visually detected on 

the rudder of * * * [an] in-service aeroplane 

during scheduled maintenance. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the surface defects were a 

result of de-bonding between the skin and 

honeycomb core. 

* * * * * 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 56287 

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 3, 2011 (76 FR 24832). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Surface defects were visually detected on 

the rudder of one A319 and one A321 inservice aeroplane during scheduled 

maintenance. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the surface defects were a 

result of de-bonding between the skin and 

honeycomb core. 

Such reworks were also performed on 

some rudders fitted on A330 and A340–200/ 

–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

To address this unsafe condition, EASA 

issued AD 2010–0021, superseding EASA AD 

2009–0156, to require inspections of specific 

areas and, depending on findings, the 

accomplishment of corrective actions for 

those rudders where production reworks 

have been identified. 

In addition, this [EASA] AD addresses the 

rudder population that has also been 

reworked in production but is not part of 

EASA AD 2010–0021 applicability. 

Required actions include vacuum loss 

and elasticity laminate checker 

inspections for damage including debonding between the skin and 

honeycomb core of the rudder on 

certain areas of the rudder, and repair if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM (76 FR 

24832, May 3, 2011). 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This 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 our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

55 products of U.S. registry. We also 

estimate that it will take about 6 workhours 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 to the U.S. operators to 

be $28,050, or $510 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in 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. 

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 the NPRM May 3, 2011 (76 FR 

24832), 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. 

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: 

mstockstill on DSK4VPTVN1PROD with RULES

56288 Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–18–22 Airbus: Amendment 39–16804. 

Docket No. FAA–2011–0387; Directorate 

Identifier 2010–NM–222–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 18, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes, and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; certificated 

in any category; all manufacturer serial 

numbers, if equipped with rudders having 

part numbers and serial numbers as 

identified in table 1, table 2, or table 3 of this 

AD. 

TABLE 1—RUDDER PART NUMBER (P/ 

N) AND AFFECTED RUDDER SERIAL

NUMBER (S/N) 

Rudder 

P/N 

Affected 

rudder 

S/N 

F554–70000–000–00 .................... TS–2045 

F554–70000–000–00 .................... TS–2046 

F554–71000–000–00–0000 .......... TS–3013 

F554–71000–000–00–0000 .......... TS–3014 

F554–71000–000–00–0000 .......... TS–3020 

F554–71000–000–00–0000 .......... TS–3022 

F554–71000–000–00–0000 .......... TS–3023 

F554–71000–000–00–0000 .......... TS–3027 

F554–71000–000–00–0000 .......... TS–3031 

F554–71000–000–00–0000 .......... TS–3034 

F554–71000–000–00–0000 .......... TS–3036 

F554–71000–000–00–0000 .......... TS–3038 

F554–71000–000–00–0000 .......... TS–3041 

F554–71000–000–00–0000 .......... TS–3046 

F554–71000–000–00–0000 .......... TS–3054 

F554–70005–000–00–0000 .......... TS–3102 

F554–71002–000–00–0002 .......... TS–4018 

F554–71002–000–00–0002 .......... TS–4022 

F554–71002–000–00–0002 .......... TS–4031 

TABLE 2—RUDDER P/N AND

AFFECTED RUDDER S/N 

Rudder P/N Affected 

rudder S/N 

A554–71500–024–00 ............... TS–1014 

A554–71500–030–00 ............... TS–1042 

F554–70000–000–00 ................ TS–2004 

F554–70000–000–00 ................ TS–2005 

F554–70000–000–00 ................ TS–2008 

F554–70000–000–00 ................ TS–2009 

F554–70000–000–00 ................ TS–2010 

F554–70000–000–00 ................ TS–2022 

F554–70000–000–00 ................ TS–2023 

F554–70000–000–00 ................ TS–2028 

F554–70000–000–00 ................ TS–2029 

F554–70000–000–00 ................ TS–2030 

TABLE 2—RUDDER P/N AND

AFFECTED RUDDER S/N—Continued 

Rudder P/N Affected 

rudder S/N 

F554–70000–000–00 ................ TS–2032 

F554–70000–000–00 ................ TS–2033 

F554–70000–000–00 ................ TS–2034 

F554–70000–000–00 ................ TS–2041 

F554–70000–000–00 ................ TS–2044 

F554–70000–000–00 ................ TS–2048 

F554–70000–000–00 ................ TS–2049 

F554–70000–000–00 ................ TS–2050 

F554–70000–000–00 ................ TS–2057 

F554–70000–000–00 ................ TS–2067 

F554–70000–002–00 ................ TS–2068 

F554–70000–002–00 ................ TS–2071 

F554–71000–000–00–0000 ...... TS–3001 

F554–71000–000–00–0000 ...... TS–3010 

F554–71000–000–00–0000 ...... TS–3012 

F554–71000–000–00–0000 ...... TS–3017 

F554–71000–000–00–0000 ...... TS–3018 

F554–71000–000–00–0000 ...... TS–3019 

F554–71000–000–00–0000 ...... TS–3021 

F554–71000–000–00–0000 ...... TS–3024 

F554–71000–000–00–0000 ...... TS–3025 

F554–71000–000–00–0000 ...... TS–3026 

F554–71000–000–00–0000 ...... TS–3028 

F554–71000–000–00–0000 ...... TS–3029 

F554–71000–000–00–0000 ...... TS–3030 

F554–71000–000–00–0000 ...... TS–3032 

F554–71000–000–00–0000 ...... TS–3035 

F554–71000–000–00–0000 ...... TS–3037 

F554–71000–000–00–0000 ...... TS–3039 

F554–71000–000–00–0000 ...... TS–3040 

F554–71000–000–00–0000 ...... TS–3042 

F554–71000–000–00–0000 ...... TS–3047 

F554–71000–000–00–0000 ...... TS–3049 

F554–71000–000–00–0000 ...... TS–3055 

F554–71000–000–00–0000 ...... TS–3058 

F554–71000–000–00–0000 ...... TS–3062 

F554–71000–000–00–0000 ...... TS–3063 

F554–71000–000–00–0000 ...... TS–3065 

F554–71000–000–00–0000 ...... TS–3067 

F554–71000–000–00–0000 ...... TS–3069 

F554–71000–000–00–0000 ...... TS–3070 

F554–71000–000–00–0000 ...... TS–3077 

F554–71000–000–00–0000 ...... TS–3078 

F554–71000–000–00–0000 ...... TS–3080 

F554–71000–000–00–0000 ...... TS–3081 

F554–71000–000–00–0000 ...... TS–3086 

F554–71000–000–00–0000 ...... TS–3089 

F554–71000–000–00–0000 ...... TS–3092 

F554–71000–000–00–0000 ...... TS–3093 

F554–71000–000–00–0000 ...... TS–3095 

F554–71000–000–00–0000 ...... TS–3096 

F554–70005–000–00–0000 ...... TS–3098 

F554–70005–000–00–0000 ...... TS–3099 

F554–70005–000–00–0000 ...... TS–3101 

F554–70005–000–00–0000 ...... TS–3103 

F554–70005–000–00–0000 ...... TS–3104 

F554–70005–000–00–0000 ...... TS–3105 

F554–70005–000–00–0000 ...... TS–3108 

F554–70005–000–00–0000 ...... TS–3109 

F554–70005–000–00–0000 ...... TS–3110 

F554–70005–000–00–0000 ...... TS–3111 

F554–70005–000–00–0000 ...... TS–3112 

F554–70005–000–00–0000 ...... TS–3114 

F554–70005–000–00–0000 ...... TS–3116 

F554–70005–000–00–0000 ...... TS–3117 

F554–70005–000–00–0000 ...... TS–3120 

F554–70005–000–00–0000 ...... TS–3131 

F554–70005–000–00–0000 ...... TS–3132 

F554–70005–000–00–0000 ...... TS–3212 

F554–70005–000–00–0002 ...... TS–3323 

TABLE 2—RUDDER P/N AND

AFFECTED RUDDER S/N—Continued 

Rudder P/N Affected 

rudder S/N 

F554–70005–000–00–0002 ...... TS–3330 

F554–71002–000–00–0002 ...... TS–4009 

F554–71002–000–00–0002 ...... TS–4010 

F554–71002–000–00–0002 ...... TS–4012 

F554–71002–000–00–0002 ...... TS–4013 

F554–71002–000–00–0002 ...... TS–4014 

F554–71002–000–00–0002 ...... TS–4015 

F554–71002–000–00–0002 ...... TS–4016 

F554–71002–000–00–0002 ...... TS–4017 

F554–71002–000–00–0002 ...... TS–4020 

F554–71002–000–00–0002 ...... TS–4023 

F554–71002–000–00–0002 ...... TS–4025 

F554–71002–000–00–0002 ...... TS–4026 

F554–71002–000–00–0002 ...... TS–4027 

F554–71002–000–00–0002 ...... TS–4029 

F554–71002–000–00–0002 ...... TS–4030 

F554–71002–000–00–0002 ...... TS–4038 

F554–71002–000–00–0002 ...... TS–4047 

F554–71002–000–00–0002 ...... TS–4049 

F554–71002–000–00–0002 ...... TS–4066 

F554–71002–000–00–0003 ...... TS–4083 

TABLE 3—RUDDER P/N AND

AFFECTED RUDDER S/N 

Rudder 

P/N 

Affected 

rudder S/N 

F554–71000–000–00–0000 ...... TS–3060 

F554–71000–000–00–0000 ...... TS–3068 

F554–70005–000–00–0000 ...... TS–3128 

F554–71002–000–00–0002 ...... TS–4011 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Surface defects were visually detected on 

the rudder of * * * [an] in-service aeroplane 

during scheduled maintenance. 

Investigation has determined that the 

defects reported on both rudders 

corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the surface defects were a 

result of de-bonding between the skin and 

honeycomb core. 

* * * * * 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

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. 

Inspections 

(g) For rudders identified in table 1 and 

table 2 of this AD: Within the compliance 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 56289 

time in paragraph (g)(1) or (g)(2) of this AD 

as applicable, do a vacuum loss inspection 

on the rudder non-ventilated area (Area 1) for 

damage including de-bonding between the 

skin and honeycomb core of the rudder, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–55–3042 or A340–55–4038, 

both dated April 22, 2010, as applicable. 

(1) For rudders identified in table 1 of this 

AD: Within 1,800 flight hours after the 

effective date of this AD. 

(2) For rudders identified in table 2 of this 

AD: Within 21 months after the effective date 

of this AD. 

(h) For rudders identified in table 1 and 

table 2 of this AD: Within 21 months after the 

effective date of this AD, do an elasticity 

laminate checker inspection on the trailing 

edge area (Area 2) for damage including debonding between the skin and honeycomb 

core of the rudder, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Thereafter, repeat the 

inspection two more times at intervals not to 

exceed 4,500 flight cycles but not less than 

4,000 flight cycles from the most recent 

inspection. 

(i) For rudders identified in table 3 of this 

AD: Within 4,500 flight cycles but not less 

than 4,000 flight cycles from the date of the 

sampling inspection identified in table 4 of 

this AD, or within 30 days after the effective 

date of this AD, whichever occurs later, do 

an elasticity laminate checker inspection on 

the trailing edge area for damage including 

de-bonding between the skin and honeycomb 

core of the rudder, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Repeat the inspection once 

within 4,500 flight cycles after doing the 

inspection but not less than 4,000 flight 

cycles from the last inspection. 

TABLE 4—RUDDER P/N AND AFFECTED RUDDER S/N AND SAMPLING INSPECTION DATE

Rudder P/N Affected rudder 

S/N 

Date of sampling 

inspection 

F554–71000–000–00–0000 ..................................................................................................................... TS–3060 March 12, 2009. 

F554–71000–000–00–0000 ..................................................................................................................... TS–3068 April 27, 2009. 

F554–70005–000–00–0000 ..................................................................................................................... TS–3128 July 13, 2009. 

F554–71002–000–00–0002 ..................................................................................................................... TS–4011 February 12, 2009. 

Corrective Actions 

(j) If damage is found during any 

inspection required by paragraph (g), (h), (i), 

or (k)(1) of this AD, before further flight, 

repair the damage using a method approved 

by either the Manager, International Branch, 

ANM 116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Restoration 

(k) If no damage is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, restore the vacuum 

loss holes by doing a temporary restoration 

with self-adhesive disks or tapes, a temporary 

restoration with resin, or a permanent 

restoration with resin, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Do the applicable actions 

specified in paragraph (k)(1) or (k)(2) of this 

AD. 

(1) For airplanes on which a temporary 

restoration with self-adhesive disks or tapes 

is done, within 900 flight hours after doing 

the restoration, do a detailed inspection for 

loose or missing self-adhesive disks or tapes 

and repeat the inspection thereafter at 

intervals not to exceed 900 flight hours until 

the permanent restoration is done, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–55–3042 or A340–55–4038, 

both dated April 22, 2010, as applicable. If 

any loose or missing self-adhesive disks or 

tapes are found during any inspection 

required by this AD, before further flight, 

close the holes, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. Do the permanent restoration 

within 21 months after doing the temporary 

restoration, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3042 

or A340–55–4038, both dated April 22, 2010, 

as applicable. 

(2) For airplanes on which a temporary 

restoration with resin is done: Within 21 

months after doing the temporary restoration, 

do the permanent restoration, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–55– 

3042 or A340–55–4038, both dated April 22, 

2010, as applicable. 

Reporting Requirements 

(l) Submit a report of the findings (positive 

and negative) of the first inspection required 

by paragraphs (g), (h), and (i) of this AD to 

Airbus, at the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Parts Installation 

(m) As of the effective date of this AD, no 

person may install any affected rudder listed 

in table 1, table, 2, or table 3 of this AD, on 

any airplane, unless the rudder is inspected 

as specified in paragraphs (g), (h), and (i) of 

this AD, as applicable, and all applicable 

corrective actions specified in paragraph (j) 

of this AD and applicable restoration 

specified in paragraph (k) of this AD are 

done. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(n) 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: 

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. 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. 

(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 FAAapproved 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

mstockstill on DSK4VPTVN1PROD with RULES

56290 Federal Register / Vol. 76, No. 177 / Tuesday, September 13, 2011 / Rules and Regulations 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(o) Refer to MCAI EASA Airworthiness 

Directive 2010–0127, dated June 23, 2010; 

Airbus Mandatory Service Bulletin A330–55– 

3042, dated April 22, 2010; and Airbus 

Mandatory Service Bulletin A340–55–4038, 

dated April 22, 2010; for related information. 

Material Incorporated by Reference 

(p) You must use Airbus Mandatory 

Service Bulletin A330–55–3042, dated April 

22, 2010; or Airbus Mandatory Service 

Bulletin A340–55–4038, dated April 22, 

2010; 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 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) 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; e-mail 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.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 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22635 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–2011–0151; Directorate 

Identifier 2009–NM–205–AD; Amendment 

39–16781; AD 2011–17–17] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to 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: 

Two cases of main landing gear collapse 

had been reported. Main landing gear 

collapse may result in unsafe landing of the 

aircraft. 

* * * * * 

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: 

Craig Yates, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7355; fax (516) 794–5531. 

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 March 8, 2011 (76 FR 

12629), and proposed to supersede AD 

2007–22–09, Amendment 39–15245 (72 

FR 61288, October 30, 2007). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Two cases of main landing gear collapse 

had been reported. Main landing gear 

collapse may result in unsafe landing of the 

aircraft. 

Revision 1 of this directive amended the 

time compliance in paragraph C.2 (3 months 

in addition to 500 hours air time), to add new 

paragraph C.3 to cater for retract actuator 

which has accumulated less than 4,000 

landings or 2 years since new and to add new 

paragraphs B.2 and C.4 to require that the 

respective inspections be repetitively 

performed until terminating action becomes 

available. 

Revision 2 of this directive amends the 

detailed visual inspection requirement in 

paragraph C.3 to include the main landing 

gear retract actuator, part number 46550–11, 

and to add new paragraph F to mandate the 

incorporation of main landing gear retract 

actuator part number, 46550–13 as the 

terminating action and to add new paragraph 

G for the maintenance requirement. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 12629, March 8, 2011) or on the 

determination of the cost to the public. 

Change Made to This AD 

We have removed paragraph 

(v)(3)(i)(D) of the NPRM (76 FR 12629, 

March 8, 2011) from this AD, and 

reidentified subsequent paragraphs 

accordingly. 

Conclusion 

We reviewed the available data, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Differences Between This 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 our FAA 

mstockstill on DSK4VPTVN1PROD with RULES