Airworthiness Directives; Fokker Services B.V. Airplanes, 3042-3045 [2016-00700]
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Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules
(n) New Terminating Modification
Within 6,600 flight hours or 36 months,
whichever occurs first after the effective date
of this AD: Modify the airplane by increasing
the clearance between the left and right MLG
fairings and the left and right MLG doors;
and do all applicable related investigative
and corrective actions; in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 670BA–32–040,
Revision E, dated November 13, 2014, except
as provided by paragraph (o) of this AD. Do
all applicable related investigative and
corrective actions before further flight. If an
MLG door has been removed, the
modification may be delayed until the MLG
door is re-installed in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A670BA–32–030,
Revision D, dated August 6, 2013.
Accomplishing this modification terminates
the requirements of paragraphs (g) through
(m) of this AD for that MLG door.
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(o) Exceptions to Bombardier Service
Bulletins
Where Bombardier Alert Service Bulletin
A670BA–32–030, Revision D, dated August
6, 2013; and Bombardier Service Bulletin
670BA–32–040, Revision E, dated November
14, 2014; specify to contact the Bombardier
Customer Response Center for an analysis or
to get an approved disposition, repair using
a method approved by the Manager, New
York ACO, ANE–170, FAA; or TCCA; or
Bombardier, Inc.’s TCCA DAO.
(p) Credit for Previous Actions
(1) This paragraph restates the provisions
of paragraph (l) of AD 2010–23–19,
Amendment 39–16508 (75 FR 68695,
November 9, 2010), with additional service
information. This paragraph provides credit
for the actions required by paragraph (g) of
this AD, if those actions were performed
before November 24, 2010 (the effective date
of AD 2010–23–19) using Bombardier Alert
Service Bulletin A670BA–32–030, dated
October 18, 2010; or Bombardier Alert
Service Bulletin A670BA–32–030, Revision
A, dated October 22, 2010.
(2) This paragraph provides credit for the
corresponding actions required by
paragraphs (g)(1), (g)(2), (g)(3)(i), (g)(3)(ii), (h),
(j)(1), (k), (l), (m), and (n) of this AD, if those
actions were performed before the effective
date of this AD using the service bulletins
specified in paragraph (p)(2)(i), (p)(2)(ii), or
(p)(2)(iii) of this AD.
(i) Bombardier Alert Service Bulletin
A670BA–32–030, Revision A, dated October
22, 2010.
(ii) Bombardier Alert Service Bulletin
A670BA–32–030, Revision B, dated
November 3, 2011.
(iii) Bombardier Alert Service Bulletin
A670BA–32–030, Revision C, dated March
13, 2013.
(3) This paragraph provides credit for the
corresponding actions required by paragraph
(n) of this AD, if those actions were
performed before the effective date of this AD
using the service information specified in
paragraph (p)(3)(i), (p)(3)(ii), (p)(3)(iii), or
(p)(3)(iv) of this AD.
(i) Bombardier Service Bulletin 670BA–32–
040, Revision A, dated March 13, 2013.
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(i) Bombardier Service Bulletin 670BA–32–
040, Revision B, dated August 6, 2013.
(iii) Bombardier Service Bulletin 670BA–
32–040, Revision C, dated November 1, 2013.
(iv) Bombardier Service Bulletin 670BA–
32–040, Revision D, dated July 2, 2014.
(q) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO,
ANE–170, 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 ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. 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: 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, New York ACO, ANE–170,
FAA; or TCCA; or Bombardier, Inc.’s TCCA
DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2010–36R1,
dated July 18, 2013, 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 Docket No.
FAA–2015–8471.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.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.
Issued in Renton, Washington, on January
6, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–00698 Filed 1–19–16; 8:45 am]
BILLING CODE 4910–13–P
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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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
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.,
SUMMARY:
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Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules
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–
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.
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
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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 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.
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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 shutoff 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 https://
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,
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3043
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 cooperate 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.
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Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules
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.
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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 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
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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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Fokker Services B.V.: Docket No. FAA–
2015–8472; 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.
Regulatory Findings
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
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:
(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.
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Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules
(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.
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(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).
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(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-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. 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
https://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
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
3045
(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 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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8470; Directorate
Identifier 2013–NM–199–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 95–21–09,
for all Airbus Model A300 series
airplanes, and Airbus Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes). AD
95–21–09 currently requires repetitive
inspections for cracking of the No. 2 flap
beams, and replacement of the flap
beams, if necessary; and provides
optional modifications for extending
certain inspection thresholds, and an
optional terminating modification for
certain inspections. Since we issued AD
95–21–09, we have determined that the
compliance times must be reduced. This
proposed AD would reduce the
compliance times for inspections and
also reduce the number of airplanes
affected. We are proposing this AD to
detect and correct cracking of the No. 2
flap beams, which could result in
rupture of the flap beams and reduced
structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by March 7, 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.
SUMMARY:
E:\FR\FM\20JAP1.SGM
20JAP1
]]>Agencies
[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]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 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.,
[[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 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-
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 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 2014-0107, 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 https://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 https://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 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 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
