Airworthiness Directives; Fokker Services B.V. Airplanes, 74039-74042 [2015-30007]
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
Operating mode
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Cooling Mode, Dual-Duct 95 °F 1
Cooling Mode, Dual-Duct 83 °F 1
16:45 Nov 25, 2015
Annual
operating
hours
for dual-duct portable air conditioners, and are
not a division of the total cooling mode operating hours. The total dual-duct cooling mode
operating hours are 750 hours.
AECm = Pm × tm × k
Where:
AECm = annual energy consumption in
each mode, in kWh/year.
Pm = average power in each mode, in
watts.
m represents the operating mode (‘‘95’’
and ‘‘83’’ cooling mode at the 95 °F
and 83 °F dry-bulb outdoor
conditions, respectively for dualAnnual
duct portable air conditioners, ‘‘SD’’
operating
cooling mode for single-duct
hours
portable air conditioners, ‘‘oc’’ offcycle, and ‘‘ia’’ inactive or ‘‘om’’ off
750
mode).
750
Where:
CEERSD and CEERDD = combined energy
efficiency ratio for single-duct and
dual-duct portable air conditioners,
respectively, in Btu/Wh.
ACC95 and ACC83 = adjusted cooling
capacity, tested at the 95 °F and
83 °F dry-bulb outdoor conditions
in Table 1 of this appendix, in Btu/
h, calculated in section 5.1 of this
appendix.
AECSD = annual energy consumption in
cooling mode for single-duct
portable air conditioners, in kWh/
year, calculated in section 5.3 of
this appendix.
AEC95 and AEC83 = annual energy
consumption for the two cooling
mode test conditions in Table 1 of
this appendix for dual-duct portable
air conditioners, in kWh/year,
calculated in section 5.3 of this
appendix.
AECT = total annual energy
consumption attributed to all
modes except cooling, in kWh/year,
VerDate Sep<11>2014
t = number of annual operating time in
each mode, in hours.
k = 0.001 kWh/Wh conversion factor
from watt-hours to kilowatt-hours.
Cooling Mode, Single-Duct ...........
750
Off-Cycle .......................................
880
Total annual energy consumption in
Inactive or Off ...............................
1,355
all modes except cooling, is calculated
1 These operating mode hours are for the
according to the following:
purposes of calculating annual energy consumption under different ambient conditions AECT = èmAECm
Operating mode
Jkt 238001
Where:
AECT = total annual energy
consumption attributed to all
modes except cooling, in kWh/year;
AECm = total annual energy
consumption in each mode, in
kWh/year.
m represents the operating modes
included in AECT (‘‘oc’’ off-cycle,
and ‘‘im’’ inactive or ‘‘om’’ off
mode).
5.4 Combined Energy Efficiency
Ratio. Using the annual operating hours,
as outlined in section 5.3 of this
appendix, calculate the combined
energy efficiency ratio, CEER, expressed
in Btu/Wh, according to the following:
calculated in section 5.3 of this
appendix.
t = number of cooling mode hours per
year, 750.
k = 0.001 kWh/Wh conversion factor for
watt-hours to kilowatt-hours.
0.2 = weighting factor for the 95 °F drybulb outdoor condition test.
0.8 = weighting factor for the 83 °F drybulb outdoor condition test.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2015–30057 Filed 11–25–15; 8:45 am]
AGENCY:
BILLING CODE 6450–01–P
PO 00000
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–5810; Directorate
Identifier 2014–NM–116–AD]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to adopt a new
airworthiness directive (AD) for certain
Fokker Services B.V. Model F.28 Mark
0070 and 0100 airplanes. This proposed
AD was prompted by a design review
that revealed that a wiring failure,
external to the center wing fuel tank,
could cause a hot short circuit to a
maximum level sensor wire, and result
SUMMARY:
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27NOP1
EP27NO15.012</GPH>
cooling mode, calculated in section
4.1.1.2 of this appendix.
5.2 Seasonally Adjusted Cooling
Capacity. Calculate the seasonally
adjusted cooling capacity for portable
air conditioners, SACC, expressed in
Btu/h, according to the following:
SACC = ACC95 × 0.2 + ACC83 × 0.8
Where:
ACC95 and ACC83 = adjusted cooling
capacity, in Btu/h, calculated in
section 5.1 of this appendix.
0.2 = weighting factor for ACC95.
0.8 = weighting factor for ACC83.
5.3 Annual Energy Consumption.
Calculate the annual energy
consumption in each operating mode,
AECm, expressed in kilowatt-hours per
year (kWh/year). The annual hours of
operation in each mode are estimated as
follows:
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
in excessive heating of the maximum
level sensor element. This proposed AD
would require modifying the wiring of
the maximum level sensors in the center
wing fuel tank, performing afterinstallation tests, and corrective action
if necessary. This proposed AD would
also require revising the airplane
maintenance or inspection program to
incorporate fuel airworthiness
limitation items and critical design
configuration control limitations. We
are proposing this AD to prevent 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.
DATES: We must receive comments on
this proposed AD by January 11, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 1357, 2130 EL Hoofddorp, the
Netherlands; telephone +31 (0)88–6280–
350; fax +31 (0)88–6280–111; email
technicalservices@fokker.com; Internet
https://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.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5810; or in person at the Docket
Management Facility 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
VerDate Sep<11>2014
16:45 Nov 25, 2015
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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–2015–5810; Directorate Identifier
2014–NM–116–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 https://
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 2014–0138, dated May 30,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Fokker
Services B.V. Model F.28 Mark 0070
and 0100 airplanes. 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 review conducted by Fokker Services
on the Fokker 70/100 design, in response to
these regulations, revealed that a wiring
failure, external to the centre wing fuel tank,
causing a hot short circuit to a maximum
(max) level sensor wire may result in
excessive heating of the max level sensor
element.
This condition, if not corrected, could
create an ignition source in the centre wing
fuel tank vapour space, possibly resulting in
a fuel tank explosion and consequent loss of
the aeroplane.
EASA issued AD 2012–0240 [https://
ad.easa.europa.eu/blob/easa_ad_2012_
0240.pdf/AD_2012-0240], to address this
unsafe condition, which required installation
of three fuses in the wiring of the max level
sensor(s) in the centre wing fuel tank per
Fokker Services Service Bulletin (SB)
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SBF100–28–073. After that AD was issued, it
was found that this technical solution caused
fuel spills during refueling and,
consequently, EASA cancelled AD 2012–
0240.
More recently, Fokker Services issued
SBF100–28–078, which cancelled SBF100–
28–073, to correct the unsafe condition
without the risk of fuel spills.
For the reasons described above, this
[EASA] AD requires removal of one fuse from
post-SBF100–28–073 aeroplanes, and
installation of only two fuses on pre-SBF100–
28–073 aeroplanes and, subsequently, the
implementation of the associated Critical
Design Configuration Control Limitation
(CDCCL) items.
More information this subject can be found
in Fokker Services All Operators Message
AOF100.186#03.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2015–5810.
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
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
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
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, combination of failures,
and unacceptable (failure) experience.
For all three failure 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. (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.
Related Service Information Under CFR
Part 51
Fokker has issued Service Bulletin
SBF100–28–078, dated January 23,
2014. The service information describes
procedures for modifying the wiring of
the maximum level sensors in the center
wing fuel tank, after-installation tests,
and corrective action if necessary. 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 of
this NPRM.
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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.
VerDate Sep<11>2014
16:45 Nov 25, 2015
Jkt 238001
Costs of Compliance
We estimate that this proposed AD
affects 15 airplanes of U.S. registry.
We also estimate that it would take up
to 9 work-hours per product to modify
the wiring of the maximum level
sensors in the center wing fuel tank, as
specified in this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about $1,700
per product. Based on these figures, we
estimate the cost of this proposed
modification on U.S. operators to be up
to $36,975, or up to $2,465 per product.
We also estimate that it would take
about 1 work-hour per product to revise
the maintenance or inspection program
as specified in this proposed AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this proposed revision on U.S.
operators to be $1,275, or $85 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
PO 00000
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Fmt 4702
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74041
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
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 airworthiness
directive (AD):
■
Fokker Services B.V.: Docket No. FAA–
2015–5810; Directorate Identifier 2014–
NM–116–AD.
(a) Comments Due Date
We must receive comments by January 11,
2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V.
Model F.28 Mark 0070 and 0100 airplanes,
certificated in any category, equipped with a
center wing tank.
(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 wiring failure, external
to the center wing fuel tank, could cause a
hot short circuit to a maximum level sensor
wire, and result in excessive heating of the
maximum level sensor element. We are
issuing this AD to prevent 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.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Wiring Modification
Within 24 months after the effective date
of this AD: Modify the wiring of the
maximum level sensors of the center wing
fuel tank, as specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable. Before further
flight after accomplishing the modification,
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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
do all applicable tests and corrective actions,
in accordance with Part 5 of the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–28–078, dated
January 23, 2014.
(1) For post-SBF100–28–073 configuration
airplanes: Do the modification in accordance
with Part 1 or Part 3, as applicable, of the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–28–078, dated
January 23, 2014.
(2) For pre-SBF100–28–073 configuration
airplanes: Do the modification in accordance
with Part 2 or Part 4, as applicable, of the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–28–078, dated
January 23, 2014.
(h) Revise Maintenance or Inspection
Program
Within 30 days after installing the
modification specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable: Revise the
airplane maintenance or inspection program,
as applicable, to incorporate the fuel
airworthiness limitation items and critical
design configuration control limitations
(CDCCLs) specified in paragraph 2.L.(1)(c) of
Fokker Service Bulletin SBF100–28–078,
dated January 23, 2014.
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(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 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, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-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) Contacting the Manufacturer: As of the
effective date of this AD, 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
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16:45 Nov 25, 2015
Jkt 238001
approved by the DOA, the approval must
include the DOA-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0138, dated
May 30, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2015–5810.
(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 https://
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
November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–30007 Filed 11–25–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–5815; Directorate
Identifier 2015–NM–039–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A330–200 and –300 series
airplanes; and all Model A340–200,
–300, –500, and –600 series airplanes.
This proposed AD was prompted by
reports that the potable water service
panel access door was lost during flight.
This proposed AD would require
modifying affected potable water service
panel access doors. We are proposing
this AD to prevent failure of the latching
mechanism of the potable water service
panel access door, which could result in
the loss of the potable water service
panel access door during flight, and
resultant damage to the airplane (e.g.,
damage to the trimmable horizontal
stabilizer) that could cause loss of
control of the airplane.
SUMMARY:
PO 00000
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Fmt 4702
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We must receive comments on
this proposed AD by January 11, 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
https://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 Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5815; or in person at the Docket
Management Facility 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
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
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]]>Agencies
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Proposed Rules]
[Pages 74039-74042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30007]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-5810; Directorate Identifier 2014-NM-116-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
certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes.
This proposed AD was prompted by a design review that revealed that a
wiring failure, external to the center wing fuel tank, could cause a
hot short circuit to a maximum level sensor wire, and result
[[Page 74040]]
in excessive heating of the maximum level sensor element. This proposed
AD would require modifying the wiring of the maximum level sensors in
the center wing fuel tank, performing after-installation tests, and
corrective action if necessary. This proposed AD would also require
revising the airplane maintenance or inspection program to incorporate
fuel airworthiness limitation items and critical design configuration
control limitations. We are proposing this AD to prevent 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.
DATES: We must receive comments on this proposed AD by January 11,
2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 1357, 2130 EL
Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; email technicalservices@fokker.com; Internet https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
5810; or in person at the Docket Management Facility 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-2015-5810;
Directorate Identifier 2014-NM-116-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 https://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 2014-0138, dated May 30, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Fokker
Services B.V. Model F.28 Mark 0070 and 0100 airplanes. 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 review conducted by Fokker Services on the Fokker 70/100
design, in response to these regulations, revealed that a wiring
failure, external to the centre wing fuel tank, causing a hot short
circuit to a maximum (max) level sensor wire may result in excessive
heating of the max level sensor element.
This condition, if not corrected, could create an ignition
source in the centre wing fuel tank vapour space, possibly resulting
in a fuel tank explosion and consequent loss of the aeroplane.
EASA issued AD 2012-0240 [https://ad.easa.europa.eu/blob/easa_ad_2012_0240.pdf/AD_2012-0240], to address this unsafe
condition, which required installation of three fuses in the wiring
of the max level sensor(s) in the centre wing fuel tank per Fokker
Services Service Bulletin (SB) SBF100-28-073. After that AD was
issued, it was found that this technical solution caused fuel spills
during refueling and, consequently, EASA cancelled AD 2012-0240.
More recently, Fokker Services issued SBF100-28-078, which
cancelled SBF100-28-073, to correct the unsafe condition without the
risk of fuel spills.
For the reasons described above, this [EASA] AD requires removal
of one fuse from post-SBF100-28-073 aeroplanes, and installation of
only two fuses on pre-SBF100-28-073 aeroplanes and, subsequently,
the implementation of the associated Critical Design Configuration
Control Limitation (CDCCL) items.
More information this subject can be found in Fokker Services
All Operators Message AOF100.186#03.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2015-5810.
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 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
[[Page 74041]]
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, combination of failures, and unacceptable
(failure) experience. For all three failure 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. (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.
Related Service Information Under CFR Part 51
Fokker has issued Service Bulletin SBF100-28-078, dated January 23,
2014. The service information describes procedures for modifying the
wiring of the maximum level sensors in the center wing fuel tank,
after-installation tests, and corrective action if necessary. 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 of this NPRM.
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
We estimate that this proposed AD affects 15 airplanes of U.S.
registry.
We also estimate that it would take up to 9 work-hours per product
to modify the wiring of the maximum level sensors in the center wing
fuel tank, as specified in this proposed AD. The average labor rate is
$85 per work-hour. Required parts would cost about $1,700 per product.
Based on these figures, we estimate the cost of this proposed
modification on U.S. operators to be up to $36,975, or up to $2,465 per
product.
We also estimate that it would take about 1 work-hour per product
to revise the maintenance or inspection program as specified in this
proposed AD. The average labor rate is $85 per work-hour. Based on
these figures, we estimate the cost of this proposed revision on U.S.
operators to be $1,275, or $85 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-2015-5810; Directorate
Identifier 2014-NM-116-AD.
(a) Comments Due Date
We must receive comments by January 11, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and
0100 airplanes, certificated in any category, equipped with a center
wing tank.
(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
wiring failure, external to the center wing fuel tank, could cause a
hot short circuit to a maximum level sensor wire, and result in
excessive heating of the maximum level sensor element. We are
issuing this AD to prevent 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.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Wiring Modification
Within 24 months after the effective date of this AD: Modify the
wiring of the maximum level sensors of the center wing fuel tank, as
specified in paragraph (g)(1) or (g)(2) of this AD, as applicable.
Before further flight after accomplishing the modification,
[[Page 74042]]
do all applicable tests and corrective actions, in accordance with
Part 5 of the Accomplishment Instructions of Fokker Service Bulletin
SBF100-28-078, dated January 23, 2014.
(1) For post-SBF100-28-073 configuration airplanes: Do the
modification in accordance with Part 1 or Part 3, as applicable, of
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
28-078, dated January 23, 2014.
(2) For pre-SBF100-28-073 configuration airplanes: Do the
modification in accordance with Part 2 or Part 4, as applicable, of
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
28-078, dated January 23, 2014.
(h) Revise Maintenance or Inspection Program
Within 30 days after installing the modification specified in
paragraph (g)(1) or (g)(2) of this AD, as applicable: Revise the
airplane maintenance or inspection program, as applicable, to
incorporate the fuel airworthiness limitation items and critical
design configuration control limitations (CDCCLs) specified in
paragraph 2.L.(1)(c) of Fokker Service Bulletin SBF100-28-078, dated
January 23, 2014.
(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 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, 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.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0138, dated May 30, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating it in Docket No. FAA-2015-5810.
(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 https://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 November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-30007 Filed 11-25-15; 8:45 am]
BILLING CODE 4910-13-P
