This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

50111 

Vol. 76, No. 156 

Friday, August 12, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0473; Directorate 

Identifier 2011–NM–019–AD; Amendment 

39–16774; AD 2011–17–10] 

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) have published 

Special Federal Aviation Regulation (SFAR) 

88, and the Joint Aviation Authorities (JAA) 

have 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, on certain 

aeroplanes, an interrupted shield contact 

may exist or develop between the housing of 

an in-tank Fuel Quantity Indication (FQI) 

cable plug and the cable shield of the 

shielded FQI system cables in the main and 

collector fuel tanks which can, under certain 

conditions, form a spark gap. 

This condition, if not detected and 

corrected, may create an ignition source in 

the tank vapour space, possibly resulting 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 28376). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

* * * [T]he Federal Aviation 

Administration (FAA) have published 

Special Federal Aviation Regulation (SFAR) 

88, and the Joint Aviation Authorities (JAA) 

have 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, on certain 

aeroplanes, an interrupted shield contact 

may exist or develop between the housing of 

an in-tank Fuel Quantity Indication (FQI) 

cable plug and the cable shield of the 

shielded FQI system cables in the main and 

collector fuel tanks which can, under certain 

conditions, form a spark gap. 

This condition, if not detected and 

corrected, may create an ignition source in 

the tank vapour space, possibly resulting in 

a wing fuel tank explosion and consequent 

loss of the aeroplane. 

For the reasons described above, this 

[European Aviation Safety Agency (EASA)] 

AD requires, for certain aeroplanes, a onetime [general visual] inspection to check for 

the presence of a by-pass wire between the 

housing of each in-tank FQI cable plug and 

the cable shield and, depending on findings, 

the installation of a by-pass wire. In addition, 

this AD requires the implementation of a 

Critical Design Configuration Control 

Limitations (CDCCL) task to make certain 

that the by-pass wire remains installed. 

On later production aeroplanes, a different 

plug has been introduced, Souriau Part 

Number (P/N) 20P227–2. This plug has an 

improved shield connection to the housing of 

the plug, for which the installation of a bypass wire is not necessary. For aeroplanes 

with the improved plug installed, this 

[EASA] AD only requires the implementation 

of a CDCCL task to make certain that this 

type of plug remains installed. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We received one comment. However, 

the commenter made no specific request 

regarding this AD. 

Explanation of Change Made to This 

AD 

We have revised paragraph (k) of this 

AD to refer to paragraph (l) of this AD. 

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 2 

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 $1,020, or $510 per product. 


erowe on DSK5CLS3C1PROD with RULES
50112 Federal Register / Vol. 76, No. 156 / Friday, August 12, 2011 / Rules and Regulations 

In addition, we estimate that any 

necessary follow-on actions would take 

about 7 work-hours and require parts 

costing $308, for a cost of $903 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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: 

2011–17–10 Fokker Services B.V.: 

Amendment 39–16774. Docket No. 

FAA–2011–0473; Directorate Identifier 

2011–NM–019–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 16, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F.28 Mark 1000, 2000, 3000, and 4000 

airplanes, certificated in any category, all 

serial numbers. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new actions (e.g., inspections) and/ 

or Critical Design Configuration Control 

Limitations (CDCCLs). Compliance with 

these actions and/or CDCCLs is required by 

14 CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by this AD, 

the operator may not be able to accomplish 

the actions described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (l) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * [T]he Federal Aviation 

Administration (FAA) have published 

Special Federal Aviation Regulation (SFAR) 

88, and the Joint Aviation Authorities (JAA) 

have 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, on certain 

aeroplanes, an interrupted shield contact 

may exist or develop between the housing of 

an in-tank Fuel Quantity Indication (FQI) 

cable plug and the cable shield of the 

shielded FQI system cables in the main and 

collector fuel tanks which can, under certain 

conditions, form a spark gap. 

This condition, if not detected and 

corrected, may create an ignition source in 

the tank vapour space, possibly resulting in 

a wing fuel tank explosion and consequent 

loss 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. 

Inspection and Installation for Model F.28 

Airplanes Serial Numbers 11003 Through 

11041 and 11991 Through 11994 

(g) For airplanes having serial numbers 

11003 through 11041 inclusive and 11991 

through 11994 inclusive: At a scheduled 

opening of the fuel tanks, but not later than 

84 months after the effective date of this AD, 

do a general visual inspection for the 

presence of a by-pass wire between the 

housing of each in-tank FQI cable plug and 

the cable shield, in accordance with Part 1 

of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–053, 

Revision 1, dated September 20, 2010. 

(h) If during the general visual inspection 

required by paragraph (g) of this AD, it is 

found that a by-pass wire is not installed: 

Before the next flight, install the by-pass wire 

between the housing of the in-tank FQI cable 

plug and the cable shield, in accordance with 

Part 2 of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–053, 

Revision 1, dated September 20, 2010. 

Maintenance Program Revision To Add Fuel 

Airworthiness Limitation for Model F.28 

Airplanes Serial Numbers 11003 Through 

11041 and 11991 Through 11994 

(i) For airplanes having serial numbers 

11003 through 11041 inclusive and 11991 

through 11994 inclusive: Concurrently with 

paragraph (g) of this AD, revise the airplane 

maintenance program by incorporating 

CDCCL–1 specified in paragraph 1.L.(1)(c) of 

Fokker Service Bulletin SBF28–28–053 

Revision 1, dated September 20, 2010. 

Maintenance Program Revision To Add Fuel 

Airworthiness Limitation for Model F.28 

Airplanes Serial Numbers 11042 Through 

11241 

(j) For airplanes having serial numbers 

11042 through 11241 inclusive: Within 3 

months after the effective date of this AD, 

revise the airplane maintenance program by 

incorporating CDCCL–2 specified in 

paragraph 1.L.(1)(c) of Fokker Service 

Bulletin SBF28–28–053, Revision 1, dated 

September 20, 2010. 


erowe on DSK5CLS3C1PROD with RULES
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. 


erowe on DSK5CLS3C1PROD with RULES