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# 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 ofthe 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 alsoestimate 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.


## 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.


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

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.