```

[Federal Register Volume 77, Number 59 (Tuesday, March 27, 2012)]
[Proposed Rules]
[Pages 18141-18143]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-7361]

[[Page 18141]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0300; Directorate Identifier 2011-NM-276-AD]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This 
proposed AD was prompted by a design review which revealed the absence 
of electrical insulation material between a wing or integral center 
wing tank (ICWT) fuel quantity indication system (FQIS) probe and the 
bottom of the tank structure. This condition, if not corrected, could, 
under certain conditions, result in an ignition source in the tank 
vapor space, which could result in a fuel tank explosion and consequent 
loss of the airplane. This proposed AD would require, for all 
airplanes, applying sealant below the FQIS probes in the wing tanks; 
and for certain airplanes, applying sealant below the FQIS probes in 
the ICWT. This proposed AD would also require revising the aircraft 
maintenance program by revising the fuel airworthiness limitations and 
incorporating critical design configuration control limitations 
(CDCCLs). We are proposing this AD to prevent an ignition source in the 
tank vapor space, which could result in a fuel tank explosion and 
consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by May 11, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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; email technicalservices.fokkerservices@stork.com; 
Internet http://www.myfokkerfleet.com. You may review copies of the 
referenced 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.

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 this proposed AD, 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.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0300; 
Directorate Identifier 2011-NM-276-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2011-0227, dated December 6, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    * * * [T]he FAA published Special Federal Aviation Regulation 
(SFAR) 88, and the Joint Aviation Authorities (JAA) published 
Interim Policy INT/POL/25/12. The design review conducted by Fokker 
Services on the Fokker 70 and Fokker 100 in response to these 
regulations revealed that the absence of electrical insulation 
material between a wing or Integral Center Wing Tank (ICWT) Fuel 
Quantity Indication System (FQIS) probe and the bottom of the tank 
structure could, under certain conditions, result in an ignition 
source in the tank vapour space.
    This condition, if not corrected, could result in a fuel tank 
explosion and consequent loss of the aeroplane.
    For the reasons described above, this [EASA] AD requires the 
application of sealant below the FQIS probes in the wing tanks and 
below the FQIS probes in the ICWT, as applicable to aeroplane 
configuration. * * *

The corrective actions also include revising the aircraft maintenance 
program by revising the fuel airworthiness limitations and 
incorporating CDCCLs. You may obtain further information by examining 
the MCAI in the AD docket.
    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (66 FR 23086, May 
7, 2001) (``SFAR 88,'' Amendment 21-78, and subsequent Amendments 21-82 
and 21-83).
    Among other actions, SFAR 88 (66 FR 23086, May 7, 2001) requires 
certain type design (i.e., type certificate (TC) and supplemental type 
certificate (STC)) holders to substantiate that their fuel tank systems 
can prevent ignition sources in the fuel tanks. This requirement 
applies to type design holders for large turbine-powered transport 
airplanes and for subsequent modifications to those airplanes. It 
requires them to perform design reviews and to develop design changes 
and maintenance procedures if their designs

[[Page 18142]]

do not meet the new fuel tank safety standards. As explained in the 
preamble to the rule, we intended to adopt airworthiness directives to 
mandate any changes found necessary to address unsafe conditions 
identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    The Joint Aviation Authorities (JAA) has issued a regulation that 
is similar to SFAR 88 (66 FR 23086, May 7, 2001). (The JAA is an 
associated body of the European Civil Aviation Conference (ECAC) 
representing the civil aviation regulatory authorities of a number of 
European States who have agreed to co-operate in developing and 
implementing common safety regulatory standards and procedures.) Under 
this regulation, the JAA stated that all members of the ECAC that hold 
type certificates for transport category airplanes are required to 
conduct a design review against explosion risks.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

Relevant Service Information

    Fokker Services B.V. has issued Fokker Service Bulletin SBF100-28-
067, dated September 2, 2011. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 4 products of U.S. registry. We also estimate that 
it would take about 8 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $0 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 the proposed AD on U.S. operators to 
be $2,720, or $680 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Fokker Services B.V.: Docket No. FAA-2012-0300; Directorate 
Identifier 2011-NM-276-AD.

(a) Comments Due Date

    We must receive comments by May 11, 2012.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 
and 0100 airplanes, certificated in any category, all serial 
numbers.
    (2) 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 according 
to paragraph (j)(1) of this AD. The request should include a 
description of changes to the required actions that will ensure the 
continued operational safety of the airplane.

(d) Subject

    Air Transport Association (ATA) of America Code 28: Fuel.

[[Page 18143]]

(e) Reason

    This AD was prompted by a design review which revealed the 
absence of electrical insulation material between a wing or integral 
center wing tank (ICWT) fuel quantity indication system (FQIS) probe 
and the bottom of the tank structure. We are issuing this AD to 
prevent an ignition source in the tank vapor space, which could 
result in a fuel tank explosion and consequent loss of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Apply Sealant

    Do the actions specified in paragraphs (g)(1) and (g)(2) of this 
AD, as applicable.
    (1) For all airplanes: At a scheduled opening of the fuel tanks, 
but not later than 84 months after the effective date of this AD, 
apply sealant below the probes in the wing tanks, in accordance with 
Part 1 of the Accomplishment Instructions of Fokker Service Bulletin 
SBF100-28-067, dated September 2, 2011.
    (2) For airplanes having serial numbers 11442 through 11585 
inclusive, and equipped with an ICWT: At a scheduled opening of the 
fuel tanks, but not later than 84 months after the effective date of 
this AD, apply sealant below the probes in the ICWT, in accordance 
with Part 2 of the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-28-067, dated September 2, 2011.

(h) Revise Maintenance Program

    Before further flight after doing any action required by 
paragraph (g) of this AD, revise the aircraft maintenance program by 
incorporating the fuel airworthiness limitation and the CDCCL 
specified in paragraph 1.L.(1)(c) of Fokker Service Bulletin SBF100-
28-067, dated September 2, 2011.

(i) No Alternative Actions, Intervals, and/or CDCCLs

    After accomplishing the revision required by paragraph (h) of 
this AD, no alternative actions (e.g., inspections), intervals, or 
CDCCLs may be used unless the actions, intervals, or CDCCLs are 
approved as an alternative method of compliance (AMOC) in accordance 
with the procedures specified in paragraph (j)(1) of this AD.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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 emailed 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.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2011-0227, dated December 6, 2011; and 
Fokker Service Bulletin SBF100-28-067, dated September 2, 2011; for 
related information.

    Issued in Renton, Washington, on March 8, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-7361 Filed 3-26-12; 8:45 am]
BILLING CODE 4910-13-P
```