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[Federal Register Volume 81, Number 12 (Wednesday, January 20, 2016)]
[Proposed Rules]
[Pages 3042-3045]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00700]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8472; Directorate Identifier 2014-NM-106-AD]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 
airplanes. This proposed AD was prompted by a design review, that 
revealed a hot spot may develop in the main fuel tank under certain 
failure conditions of the solenoid of the level control pilot valve, 
the reed switch of the main tank overflow valve, the level float switch 
of the collector tank, or the solenoid of the main tank fueling shut-
off valve. This proposed AD would require installing fuses in the 
wiring of the solenoid of the level control pilot valve, the reed 
switch of the main tank overflow valve, the level float switch of the 
collector tank, and the solenoid of the main tank fueling shut-off 
valve, as applicable. This proposed AD would also require accomplishing 
concurrent actions and revising the airplane maintenance or inspection 
program, as applicable, by incorporating fuel airworthiness limitation 
items and critical design configuration control limitations (CDCCLs). 
We are proposing this AD to prevent an ignition source in the main fuel 
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 March 7, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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.,

[[Page 3043]]

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 1357, 2130 EL 
Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 
(0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. 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 by searching for and locating Docket No. FAA-2015-
8472; 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, WA 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-2015-8472; 
Directorate Identifier 2014-NM-106-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 Union, has issued EASA 
Airworthiness Directive 2014-0107, dated May 7, 2014 (referred to after 
this the Mandatory Continuing Airworthiness Information, or ``the 
MCAI''), to correct an unsafe condition for all Fokker Services B.V. 
Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. The MCAI states:

    Prompted by an accident * * *, the Federal Aviation 
Administration (FAA) published Special Federal Aviation Regulation 
(SFAR) 88 [(66 FR 23086, May 7, 2001)], and the Joint Aviation 
Authorities (JAA) published Interim Policy INT/POL/25/12.
    The review conducted by Fokker Services on the Fokker F28 design 
in response to these regulations revealed that, under certain 
failure conditions of the solenoid of the level control pilot valve, 
the main tank overflow valve reed switch, the collector tank level 
float switch or the main tank fuelling shut-off valve solenoid, a 
hot spot may develop in the tank.
    This condition, if not corrected, could create an ignition 
source in the main tank vapour space, possibly resulting in a fuel 
tank explosion and consequent loss of the aeroplane.
    To address this potential unsafe condition, Fokker Services 
developed a modification to the wiring (installation of fuses) of 
the affected components.
    For the reasons described above, this AD requires the 
installation of fuses in the wiring of the affected components [the 
solenoid of the level control pilot valve, the reed switch of the 
main tank overflow valve, the level float switch of the collector 
tank, and the solenoid of the main tank fuelling shut-off valve] 
and, subsequently, the implementation of the associated Critical 
Design Configuration Control Limitations (CDCCL) items [and revision 
of the maintenance or inspection program].
    More information on this subject can be found in Fokker Services 
All Operators Message AOF28.038#02.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8472.
    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 (``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 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.

[[Page 3044]]

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Fokker Service Bulletin SBF28-28-049, Revision 2, dated 
November 3, 2014, including Fokker Drawing W57273, Sheet 002, Issue C, 
undated, Fokker Drawing W58048, Sheet 1, undated, and Fokker Manual 
Change Notification MCNM-F28-035, Rev 1, dated January 9, 2014. This 
service information describes procedures for installing fuses packed in 
jiffy junctions in the collector tank.
     Fokker Proforma Service Bulletin SBF28-28-056, dated 
January 9, 2014, including Appendix SBF28-28-056/APP01, dated July 15, 
2014. This service information describes procedures for installing 
fuses in the wiring of the solenoid of the level control pilot valve, 
the reed switch of the main tank overflow valve, the level float switch 
of the collector tank, and the solenoid of the main tank fueling shut-
off valve. This service information also describes certain CDCCLs.
     Fokker Service Bulletin SBF28-28-051, Revision 2, dated 
November 3, 2014, including Drawing W57231, Sheets 010 and 011, Issue 
K, undated; Drawing W58048, Sheet 2, dated April 29, 2010; and Manual 
Change Notification--Maintenance Document MCNM-F28-034 Rev 1, dated 
January 9, 2014. This service information describes procedures for 
reworking the wiring and installing fuses packed in jiffy junctions in 
the power supply wire of the solenoid in the left and right level 
control pilot valves.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

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 these 
same type designs.
    This AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections) and/or 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 
(k)(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.

Costs of Compliance

    We estimate that this proposed AD affects 5 airplanes of U.S. 
registry.
    We also estimate that it would take about 21 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 $5,320 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $35,525, or $7,105, or 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.

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

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 airworthiness 
directive (AD):

Fokker Services B.V.: Docket No. FAA-2015-8472; Directorate 
Identifier 2014-NM-106-AD.

(a) Comments Due Date

    We must receive comments by March 7, 2016.

(b) Affected ADs

    This AD affects AD 2011-17-03, Amendment 39-16767 (76 FR 50115, 
August 12, 2011); and AD 2011-21-01, Amendment 39-16824 (76 FR 
63156, October 12, 2011).

(c) Applicability

    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.

(d) Subject

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

(e) Reason

    This AD was prompted by a design review, which revealed that a 
hot spot may develop in the main fuel tank under certain failure 
conditions of the solenoid of the level control pilot valve, the 
reed switch of the main tank overflow valve, the level float switch 
of the collector tank, or the solenoid of the main tank fueling 
shut-off valve. We are issuing this AD to prevent an ignition source 
in the main fuel tank vapor space, which could result in a fuel tank 
explosion and consequent loss of the airplane.

[[Page 3045]]

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Modification of Main Fuel Tank Wiring

    Within 24 months after the effective date of this AD, install 
fuses in the wiring of the solenoid of the level control pilot 
valve, the reed switch of the main tank overflow valve, the level 
float switch of the collector tank, and the solenoid of the main 
tank fueling shut-off valve, as applicable, in accordance with the 
Accomplishment Instructions of Fokker Services Proforma Service 
Bulletin SBF28-28-056, dated January 9, 2014, including Appendix 
SBF28-28-056/APP01, dated July 15, 2014.

(h) Concurrent Requirements

    Prior to or concurrently with accomplishing the requirements of 
paragraph (g) of this AD, do the actions specified in paragraphs 
(h)(1) and (h)(2) of this AD.
    (1) Install fuses packed in jiffy junctions (i.e., crimped wire 
in-line junction device(s)), in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF28-28-049, Revision 2, 
dated November 3, 2014, including Fokker Drawing W57273, Sheet 002, 
Issue C, undated, Fokker Drawing W58048, Sheet 1, undated, and 
Fokker Manual Change Notification MCNM-F28-035, Rev 1, dated January 
9, 2014. Accomplishment of the actions in this paragraph terminates 
the requirement of paragraph (g) of AD 2011-17-03, Amendment 39-
16767 (76 FR 50115, August 12, 2011).
    Note 1 to paragraph (h)(1) of this AD: Accomplishment of this 
action is required by AD 2011-17-03, Amendment 39-16767 (76 FR 
50115, August 12, 2011).
    (2) Rework the wiring and install fuses packed in jiffy 
junctions in the power supply wire of the solenoid in the left and 
right level control pilot valve, in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF28-28-051, 
Revision 2, dated November 3, 2014, including Drawing W57231, Sheets 
010 and 011, Issue K, undated; Drawing W58048, Sheet 2, dated April 
29, 2010; and Manual Change Notification--Maintenance Document MCNM-
F28-034, Rev 1, dated January 9, 2014. Accomplishment of the actions 
in this paragraph terminates the requirement of paragraph (g) of AD 
2011-21-01, Amendment 39-16824 (76 FR 63156, October 12, 2011), for 
the actions specified in the Accomplishment Instructions of Fokker 
Service Bulletin SBF28-28-051, Revision 2, dated November 3, 2014, 
including Drawing W57231, Sheets 010 and 011, Issue K, undated; 
Drawing W58048, Sheet 2, dated April 29, 2010; and Manual Change 
Notification--Maintenance Document MCNM-F28-034, Rev 1, dated 
January 9, 2014, only.
    Note 2 to paragraph (h)(2) of this AD: Accomplishment of this 
action is required by AD 2011-21-01, Amendment 39-16824 (76 FR 
63156, October 12, 2011).

(i) Revision of Maintenance or Inspection Program

    Before further flight after completing the installation 
specified in paragraph (g) of this AD, or within 30 days after the 
effective date of this AD, whichever occurs later: Revise the 
airplane maintenance or inspection program, as applicable, by 
incorporating the critical design configuration control limitations 
(CDCCLs) specified in paragraph 1.L.(1)(c) of Fokker Services 
Proforma Service Bulletin SBF28-28-056, dated January 9, 2014, 
including Appendix SBF28-28-056/APP01, dated July 15, 2014.

(j) No Alternative CDCCLs

    After accomplishing the revision required by paragraph (i) of 
this AD, no alternative CDCCLs may be used unless the CDCCLs are 
approved as an alternative method of compliance (AMOC) in accordance 
with the procedures specified in paragraph (k)(1) of this AD.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance: 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, 
WA 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Fokker B.V. Service's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2014-
0107, dated May 7, 2014, for related information. This MCAI may be 
found in the AD docket on the Internet at http://www.regulations.gov. by searching for and locating Docket No. FAA-
2015-8472.
    (2) For service information identified in this AD, contact 
Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 
EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 
(0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com. You may view this service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on January 6, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00700 Filed 1-19-16; 8:45 am]
BILLING CODE 4910-13-P
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