Federal Register / Vol. 76, No. 156 / Friday, August 12, 2011 / Rules and Regulations 50113 

No Alternative Actions, Intervals, and/or 

CDCCLs 

(k) After accomplishing the revisions 

required by paragraphs (i) and (j) of this AD, 

no alternative actions (e.g., inspection, 

interval) and/or CDCCLs may be used unless 

the actions, intervals, and/or CDCCLs are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0217, dated October 21, 2010, specifies 

both revising the maintenance program to 

include airworthiness limitations, and doing 

certain repetitive actions (e.g., inspections) 

and/or maintaining CDCCLs, this AD only 

requires the revision. Requiring a revision of 

the maintenance program, rather than 

requiring individual repetitive actions and/or 

maintaining CDCCLs, requires operators to 

record AD compliance only at the time the 

revision is made. Repetitive actions and/or 

maintaining CDCCLs specified in the 

airworthiness limitations must be complied 

with in accordance with 14 CFR 91.403(c). 

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, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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. 

(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 EASA Airworthiness 

Directive 2010–0217, dated October 21, 2010; 

and Fokker Service Bulletin SBF28–28–053, 

Revision 1, dated September 20, 2010; for 

related information. 

Material Incorporated by Reference 

(n) You must use Fokker Service Bulletin 

SBF28–28–053, Revision 1, dated September 

20, 2010, 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.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 

3, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–20361 Filed 8–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0305; Directorate 

Identifier 2010–NM–186–AD; Amendment 

39–16766; AD 2011–17–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–214, –232, and –233 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: 

* * * * * 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control of the aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 16, 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: 

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 

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 April 8, 2011 (76 FR 19714). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

In 2007, Airbus modification 38310 was 

introduced in production to simplify the 

ELAC2 [elevator aileron computer] and 

Trimmable Horizontal Stabiliser (THS) Motor 

1 stand by power supply logic. 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a modification of the 

electrical installation of ELAC2 and THS 

Motor 1 power supply, restoring the 

aeroplane to the pre-mod 38310 

configuration. 


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50114 Federal Register / Vol. 76, No. 156 / Friday, August 12, 2011 / Rules and Regulations 

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 comments received. 

Support for the NPRM 

The Air Line Pilots Association, 

International, supported the NPRM. 

Request To Change Costs of Compliance 

Section of the NPRM 

Airbus stated that Airbus Mandatory 

Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010, 

specifies that 99 airplanes are affected 

and that 56 total work hours are needed 

to do the required actions. Airbus stated 

that the NPRM specifies that 666 

airplanes are affected and that about 35 

work-hours are needed to do the actions 

required in the NPRM. 

We infer that Airbus is requesting a 

change to the Cost of Compliance 

section of the NPRM to reduce the 

number of affected airplanes and to 

increase the estimated work-hours 

required to perform the actions. We 

agree. We have confirmed with Airbus 

that there are 99 Model 320–214, -232, 

and -233 airplanes with Airbus 

Modification 38310. We have revised 

the Costs of Compliance section of this 

AD to reduce the number of affected 

airplanes to 99. We have also revised 

the Costs of Compliance section of this 

AD to specify 56 work-hours for the 

required actions, as specified in Airbus 

Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010. 

This estimate includes the time required 

for testing, accessing, and closing. 

Conclusion 

We reviewed the available data, 

including the comments 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 

99 products of U.S. registry. We also 

estimate that it will take about 56 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $3,370 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$804,870, or $8,130 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify 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, 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: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–17–02 Airbus: Amendment 39–16766. 

Docket No. FAA–2011–0305; Directorate 

Identifier 2010–NM–186–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 16, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320– 

214, –232, and –233 airplanes; all 

manufacturer serial numbers on which 

Airbus Modification 38310 has been 

accomplished in production; certificated in 

any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * * * 

Results from a design review done by 

AIRBUS for documentation update have 

revealed that, on post-mod 38310 A320 


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Federal Register / Vol. 76, No. 156 / Friday, August 12, 2011 / Rules and Regulations 50115 

aeroplanes only, in case of emergency 

electrical configuration combined with a 

Green and Yellow hydraulic system loss, 

during landing phase (nose landing gear 

extended), the roll control would only be 

provided by the left aileron. 

This condition, if not corrected, could lead 

to an asymmetrical landing configuration, 

resulting in reduced control 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. 

Actions 

(g) Within 24 months after the effective 

date of this AD, modify the electrical 

installation of the elevator aileron computer 

and trimmable horizontal stabilizer motor 1 

power supply, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Modifications done before the effective 

date of this AD in accordance with Airbus 

Service Bulletin A320–27–1199, Revision 01, 

dated March 4, 2010, are acceptable for 

compliance with the requirements of 

paragraph (g) of this AD. 

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, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, 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. 

(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 European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0149, dated July 21, 2010; and Airbus 

Mandatory Service Bulletin A320–27–1199, 

Revision 02, dated September 20, 2010; for 

related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A320–27–1199, Revision 02, 

including Appendix 01, dated September 20, 

2010, 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, 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. 

(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 July 29, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–20359 Filed 8–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0472; Directorate 

Identifier 2011–NM–005–AD; Amendment 

39–16767; AD 2011–17–03] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 1000, 

2000, 3000, and 4000 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: 

[T]he Federal Aviation Administration 

(FAA) has published Special Federal 

Aviation Regulation (SFAR) 88, and the Joint 

Aviation Authorities (JAA) has published 

Interim Policy INT/POL/25/12. The review 

conducted by Fokker Services on the Fokker 

F28 Type Design in response to these 

regulations revealed that, under certain 

failure conditions, a short circuit may 

develop in the collector tank level float 

switch wiring. Such a short circuit may result 

in an ignition source in the tank vapour 

space. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 16, 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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 17, 2011 (76 FR 28373). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

[T]he Federal Aviation Administration 

(FAA) has published Special Federal 

Aviation Regulation (SFAR) 88, and the Joint 

Aviation Authorities (JAA) has published 

Interim Policy INT/POL/25/12. The review 

conducted by Fokker Services on the Fokker 

F28 Type Design in response to these 

regulations revealed that, under certain 


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