Document ID: FAA-2011-0473-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes
Posted Date: 2011-08-12T04:00Z

[Federal Register Volume 76, Number 156 (Friday, August 12, 2011)]
[Rules and Regulations]
[Pages 50111-50113]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-20361]

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

[[Page 50111]]

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 one-time 
[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 by-pass 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 work-hours 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.

[[Page 50112]]

    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

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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.

[[Page 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]
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