Airworthiness Directives; Fokker Services B.V. Airplanes, 81018-81021 [2016-27529]
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This assurance is given in
consideration of and for the purpose of
obtaining any and all Federal assistance
extended to the State by USDA under
the authority of the Food and Nutrition
Act of 2008, as amended. Federal
financial assistance includes grants, and
loans of Federal funds; reimbursable
expenditures, grants, or donations of
Federal property and interest in
property; the detail of Federal
personnel; the sale, lease of, or
permission to use Federal property or
interest in such property; the furnishing
of services without consideration, or at
a nominal consideration, or at a
consideration that is reduced for the
purpose of assisting the recipient or in
recognition of the public interest to be
served by such sale, lease, or furnishing
of services to the recipient; or any
improvements made with Federal
financial assistance extended to the
State by USDA. This assistance also
includes any Federal agreement,
arrangement, or other contract that has
as one of its purposes the provision of
cash assistance for the purchase of food,
cash assistance for purchase or rental of
food service equipment or any other
financial assistance extended in reliance
on the representations and agreements
made in this assurance.
By accepting this assurance, the State
agency agrees to compile data, maintain
records, and submit records and reports
as required, to permit effective
enforcement of nondiscrimination laws
and permit authorized USDA personnel
during hours of program operation to
review and copy such records, books,
and accounts, access such facilities and
interview such personnel as needed to
ascertain compliance with the
nondiscrimination laws. If there are any
violations of this assurance, USDA,
FNS, shall have the right to seek judicial
enforcement of this assurance. This
assurance is binding on the State
agency, its successors, transferees and
assignees as long as it receives
assistance or retains possession of any
assistance from USDA. The person or
persons whose signatures appear below
are authorized to sign this assurance on
behalf of the State agency.
3. (For States with Indian
Reservations only). Implement the
Program in a manner that is responsive
to the special needs of American
Indians on reservations and consult in
good faith with tribal organizations
about that portion of the State’s Plan of
Operation pertaining to the
implementation of the Program for
members of the tribe on reservations.
4. FNS agrees to: 1. Pay administrative
costs in accordance with the Food and
Nutrition Act of 2008, implementing
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regulations, and an approved Cost
Allocation Plan.
2. Carry out any other responsibilities
delegated by the Secretary in the Food
and Nutrition Act of 2008, as amended.
Date llllllllllllllll
Signature llllllllllllll
(Governor or Authorized Designee)
Date llllllllllllllll
Signature llllllllllllll
(Regional Administrator, FNS)
Dated: November 7, 2016.
Audrey Rowe,
Administrator, Food and Nutrition Service.
[FR Doc. 2016–27604 Filed 11–16–16; 8:45 am]
CODE 3410–30–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9389; Directorate
Identifier 2014–NM–153–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 F28 Mark
0100 series airplanes. This proposed AD
was prompted by an evaluation by the
design approval holder (DAH)
indicating that certain wing fuel tank
access panels are subject to widespread
fatigue damage (WFD). This proposed
AD would require replacement of
affected access panels and modification
of the coamings of the associated access
holes. We are proposing this AD to
prevent the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by January 3, 2017.
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: Deliver to Mail
address above between 9 a.m. and 5
SUMMARY:
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p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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–2016–
9389; 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–2016–9389; Directorate Identifier
2014–NM–153–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
Fatigue damage can occur locally, in
small areas or structural design details,
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or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as widespread
fatigue damage. It is associated with
general degradation of large areas of
structure with similar structural details
and stress levels. As an airplane ages,
WFD will likely occur, and will
certainly occur if the airplane is
operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
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development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0125,
dated June 21, 2016, which supersedes
EASA AD 2014–0158, dated July 7, 2014
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Fokker Services B.V.
Model F28 Mark 0100 series airplanes.
The MCAI states:
Based on findings on test articles, fatigueinduced cracks may develop in the coamings
of certain wing fuel tank access panels Part
Number (P/N) D12395–403 and P/N D12450–
403, installed on Fokker F28 Mark 0100
aeroplanes.
To ensure the continued structural
integrity with respect to fatigue, repetitive
inspections were included in the
Airworthiness Limitations Section (ALS) of
the Instructions for Continued Airworthiness.
Fokker Services also developed
precautionary measures to reduce stress
loads in the affected areas by replacement of
the affected access panels with new panels,
P/N D19701–401 and P/N D19701–403,
having thinner skin, and a modification by
introducing internal patches to the coamings
of the affected access holes.
These precautionary measures were
introduced with Service Bulletins (SB)
SBF100–57–027 and SBF100–57–028. As
part of the Widespread Fatigue Damage reevaluation, it was concluded that repetitive
inspections through the ALS do not provide
a sufficient level of protection against the
fatigue-induced cracks.
This condition, if not corrected, would
affect the structural integrity of the lower
wing skins of both outer wings in the areas
surrounding the affected fuel tank access
panels.
For the reasons described above, this
[EASA] AD requires replacement of the
affected access panels and modification of
the coamings of these access holes.
Post-modification inspection requirements
depend on the actual number of flight cycles
accumulated at the moment of modification.
Related detailed information is provided in
SBF100–57–027 and SBF100–57–028, as well
as in Fokker Services ALS Report SE–623
Issue 12.
Fokker Services All Operators Message
AOF100.178#05 provides additional
information concerning the subject addressed
by this [EASA] AD.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
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81019
and locating Docket No. FAA–2016–
9389.
Related Service Information Under 1
CFR Part 51
Fokker Services B.V. has issued the
following service information:
• Fokker Service Bulletin SBF 100–
57–027, Revision 2, dated December 11,
2013. This service information provides
instructions to replace certain fuel tank
access panels.
• Fokker Service Bulletin SBF 100–
57–028, Revision 2, dated December, 11,
2013. This service information provides
instructions to modify the coamings of
certain fuel tank access holes.
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 the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
In the ‘‘Required Action(s) and
Compliance Times’’ section of the
MCAI, paragraphs (3) and (4) specify to
incorporate or comply with certain
maintenance tasks (repetitive
inspections). These actions are not
included in this proposed AD. Since
EASA AD 2014–0158, dated July 7,
2014, was issued, EASA issued AD
2016–0125, dated June 21, 2016, which
includes a requirement to incorporate
those maintenance tasks. We are
considering further rulemaking to
require the actions specified in EASA
AD 2016–0125, dated June 21, 2016.
Costs of Compliance
We estimate that this proposed AD
affects 15 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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ESTIMATED COSTS
Action
Labor cost
Replacement and Modification .......................
510 work-hours × $85 per hour = $43,350
per airplane.
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
sradovich on DSK3GMQ082PROD with PROPOSALS
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,
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Parts cost
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–
2016–9389; Directorate Identifier 2014–
NM–153–AD.
(a) Comments Due Date
We must receive comments by January 3,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V.
Model F28 Mark 0100 series airplanes,
certificated in any category, all serial
numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that certain wing fuel tank access panels are
subject to widespread fatigue damage (WFD).
We are issuing this AD to prevent fatigue
cracking in the wing structure, which could
result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Modification and Replacement
Within 63,000 flight cycles since first flight
of the airplane, or within 90 days after the
effective date of this AD, whichever occurs
later, accomplish the actions specified in
paragraphs (g)(1) and (g)(2) of this AD, as
applicable.
(1) For airplanes identified in Fokker
Service Bulletin SBF100–57–028, Revision 2,
dated December 11, 2013: Modify the
coamings of the fuel tank access holes at the
access panel locations identified in, and in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–57–028, Revision 2, dated December
11, 2013.
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$45,500
Cost per
product
$88,350
Cost on U.S.
operators
$1,325,250
(2) For airplanes identified in Fokker
Service Bulletin SBF100–57–027, Revision 2,
dated December 11, 2013: Replace access
panels having part number D12395–403 and
D12450–403 with new panels having part
number D19701–401 and D19701–403, at the
access panel locations identified in, and in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–57–027, Revision 2, dated December
11, 2013.
(h) Parts Installation Prohibition
(1) For airplanes that, on the effective date
of this AD, have an access panel with part
number D12395–403 or D12450–403
installed at any of the affected locations:
After accomplishing the actions required by
paragraphs (g)(1) and (g)(2) of this AD, as
applicable, no person may install, on any
airplane, access panels having part number
D12395–403 or D12450–403 at any access
panel location as identified in Fokker Service
Bulletin SBF100–57–027, Revision 2, dated
December 11, 2013.
(2) For airplanes that, on the effective date
of this AD, do not have an access panel with
part number D12395–403 or D12450–403
installed at any of the affected locations: As
of the effective date of this AD, no person
may install, on any airplane, access panels
having part number D12395–403 or D12450–
403 at any access panel location as identified
in Fokker Service Bulletin SBF100–57–027,
Revision 2, dated December 11, 2013.
(i) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g)(1) of this
AD, if those actions were performed before
the effective date of this AD using the service
information specified in paragraph (i)(1)(i) or
(i)(1)(ii) of this AD.
(i) Fokker Service Bulletin SBF100–57–
028, dated May 2, 1994.
(ii) Fokker Service Bulletin SBF100–57–
028, Revision 1, dated November 1, 1994.
(2) This paragraph provides credit for
actions required by paragraph (g)(2) of this
AD, if those actions were performed before
the effective date of this AD using the service
information specified in paragraph (i)(2)(i) or
(i)(2)(ii) of this AD.
(i) Fokker Service Bulletin SBF100–57–
027, dated September 13, 1993.
(ii) Fokker Service Bulletin SBF100–57–
027, Revision 1, dated May 2, 1994.
(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, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
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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: 9ANM-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: 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
European Aviation Safety Agency (EASA); or
Fokker Services B.V.’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 AD
2014–0158, dated July 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–2016–9389.
(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 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–27529 Filed 11–16–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
sradovich on DSK3GMQ082PROD with PROPOSALS
14 CFR Part 39
[Docket No. FAA–2016–9384; Directorate
Identifier 2016–NM–154–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 777–300ER
series airplanes. This proposed AD was
prompted by a report that certain galley
tripod mount assemblies were not
connected to the tie rods in the
overhead support structure. This
proposed AD would require an
inspection of certain galleys for the
presence of the hardware that connects
the tripod mount assembly to the tie
rods in the overhead support structure,
and corrective actions if necessary. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by January 3, 2017.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740; telephone 562–797–1717;
Internet https://
www.myboeingfleet.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. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9384.
SUMMARY:
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–2016–
9384; 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
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81021
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Eric
Brown, Aerospace Engineer, Cabin
Safety and Environmental Systems
Branch, ANM–150S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6476; fax: 425–
917–6590; email: eric.m.brown@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2016–9384; Directorate Identifier 2016–
NM–154–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 because of 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
We have received a report that the
T53 and T52 tie rods to the tripod
mount assembly in the A2 and A3
galleys were found unattached during a
routine production inspection of certain
airplanes before delivery. The cause was
determined to be a change to the galley
installation sequence. This changed
installation sequence did not include a
robust method to make sure that the tie
rods were attached to the galley before
delivery. Since this unsafe condition
was found, Boeing has implemented a
new improved process to ensure that the
hardware that attaches the T53 and T52
tie rods to the tripod mount assembly in
the A2 and A3 galleys is attached. A
galley tripod mount assembly that is
unconnected to the tie rods in the
overhead support structure can cause a
galley to come loose under a high
dynamic load causing a risk of serious
injury to passengers and the blocking of
evacuation routes.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 777–25A0677, dated April 25,
E:\FR\FM\17NOP1.SGM
17NOP1
]]>Agencies
[Federal Register Volume 81, Number 222 (Thursday, November 17, 2016)]
[Proposed Rules]
[Pages 81018-81021]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-27529]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9389; Directorate Identifier 2014-NM-153-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new Airworthiness Directive (AD) for all
Fokker Services B.V. Model F28 Mark 0100 series airplanes. This
proposed AD was prompted by an evaluation by the design approval holder
(DAH) indicating that certain wing fuel tank access panels are subject
to widespread fatigue damage (WFD). This proposed AD would require
replacement of affected access panels and modification of the coamings
of the associated access holes. We are proposing this AD to prevent the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by January 3, 2017.
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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-2016-
9389; 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-2016-9389;
Directorate Identifier 2014-NM-153-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
Fatigue damage can occur locally, in small areas or structural
design details,
[[Page 81019]]
or globally, in widespread areas. Multiple-site damage is widespread
damage that occurs in a large structural element such as a single rivet
line of a lap splice joining two large skin panels. Widespread damage
can also occur in multiple elements such as adjacent frames or
stringers. Multiple-site damage and multiple-element damage cracks are
typically too small initially to be reliably detected with normal
inspection methods. Without intervention, these cracks will grow, and
eventually compromise the structural integrity of the airplane. This
condition is known as widespread fatigue damage. It is associated with
general degradation of large areas of structure with similar structural
details and stress levels. As an airplane ages, WFD will likely occur,
and will certainly occur if the airplane is operated long enough
without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0125, dated June 21, 2016, which supersedes EASA AD 2014-0158,
dated July 7, 2014 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Fokker Services B.V. Model F28 Mark 0100 series
airplanes. The MCAI states:
Based on findings on test articles, fatigue-induced cracks may
develop in the coamings of certain wing fuel tank access panels Part
Number (P/N) D12395-403 and P/N D12450-403, installed on Fokker F28
Mark 0100 aeroplanes.
To ensure the continued structural integrity with respect to
fatigue, repetitive inspections were included in the Airworthiness
Limitations Section (ALS) of the Instructions for Continued
Airworthiness. Fokker Services also developed precautionary measures
to reduce stress loads in the affected areas by replacement of the
affected access panels with new panels, P/N D19701-401 and P/N
D19701-403, having thinner skin, and a modification by introducing
internal patches to the coamings of the affected access holes.
These precautionary measures were introduced with Service
Bulletins (SB) SBF100-57-027 and SBF100-57-028. As part of the
Widespread Fatigue Damage re-evaluation, it was concluded that
repetitive inspections through the ALS do not provide a sufficient
level of protection against the fatigue-induced cracks.
This condition, if not corrected, would affect the structural
integrity of the lower wing skins of both outer wings in the areas
surrounding the affected fuel tank access panels.
For the reasons described above, this [EASA] AD requires
replacement of the affected access panels and modification of the
coamings of these access holes.
Post-modification inspection requirements depend on the actual
number of flight cycles accumulated at the moment of modification.
Related detailed information is provided in SBF100-57-027 and
SBF100-57-028, as well as in Fokker Services ALS Report SE-623 Issue
12.
Fokker Services All Operators Message AOF100.178#05 provides
additional information concerning the subject addressed by this
[EASA] AD.
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-2016-
9389.
Related Service Information Under 1 CFR Part 51
Fokker Services B.V. has issued the following service information:
Fokker Service Bulletin SBF 100-57-027, Revision 2, dated
December 11, 2013. This service information provides instructions to
replace certain fuel tank access panels.
Fokker Service Bulletin SBF 100-57-028, Revision 2, dated
December, 11, 2013. This service information provides instructions to
modify the coamings of certain fuel tank access holes.
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 the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
In the ``Required Action(s) and Compliance Times'' section of the
MCAI, paragraphs (3) and (4) specify to incorporate or comply with
certain maintenance tasks (repetitive inspections). These actions are
not included in this proposed AD. Since EASA AD 2014-0158, dated July
7, 2014, was issued, EASA issued AD 2016-0125, dated June 21, 2016,
which includes a requirement to incorporate those maintenance tasks. We
are considering further rulemaking to require the actions specified in
EASA AD 2016-0125, dated June 21, 2016.
Costs of Compliance
We estimate that this proposed AD affects 15 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 81020]]
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replacement and Modification.......... 510 work-hours x $85 per $45,500 $88,350 $1,325,250
hour = $43,350 per
airplane.
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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-2016-9389; Directorate
Identifier 2014-NM-153-AD.
(a) Comments Due Date
We must receive comments by January 3, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V. Model F28 Mark 0100
series airplanes, certificated in any category, all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that certain wing fuel tank access panels
are subject to widespread fatigue damage (WFD). We are issuing this
AD to prevent fatigue cracking in the wing structure, which could
result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification and Replacement
Within 63,000 flight cycles since first flight of the airplane,
or within 90 days after the effective date of this AD, whichever
occurs later, accomplish the actions specified in paragraphs (g)(1)
and (g)(2) of this AD, as applicable.
(1) For airplanes identified in Fokker Service Bulletin SBF100-
57-028, Revision 2, dated December 11, 2013: Modify the coamings of
the fuel tank access holes at the access panel locations identified
in, and in accordance with the Accomplishment Instructions of Fokker
Service Bulletin SBF100-57-028, Revision 2, dated December 11, 2013.
(2) For airplanes identified in Fokker Service Bulletin SBF100-
57-027, Revision 2, dated December 11, 2013: Replace access panels
having part number D12395-403 and D12450-403 with new panels having
part number D19701-401 and D19701-403, at the access panel locations
identified in, and in accordance with the Accomplishment
Instructions of Fokker Service Bulletin SBF100-57-027, Revision 2,
dated December 11, 2013.
(h) Parts Installation Prohibition
(1) For airplanes that, on the effective date of this AD, have
an access panel with part number D12395-403 or D12450-403 installed
at any of the affected locations: After accomplishing the actions
required by paragraphs (g)(1) and (g)(2) of this AD, as applicable,
no person may install, on any airplane, access panels having part
number D12395-403 or D12450-403 at any access panel location as
identified in Fokker Service Bulletin SBF100-57-027, Revision 2,
dated December 11, 2013.
(2) For airplanes that, on the effective date of this AD, do not
have an access panel with part number D12395-403 or D12450-403
installed at any of the affected locations: As of the effective date
of this AD, no person may install, on any airplane, access panels
having part number D12395-403 or D12450-403 at any access panel
location as identified in Fokker Service Bulletin SBF100-57-027,
Revision 2, dated December 11, 2013.
(i) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g)(1) of this AD, if those actions were performed before
the effective date of this AD using the service information
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD.
(i) Fokker Service Bulletin SBF100-57-028, dated May 2, 1994.
(ii) Fokker Service Bulletin SBF100-57-028, Revision 1, dated
November 1, 1994.
(2) This paragraph provides credit for actions required by
paragraph (g)(2) of this AD, if those actions were performed before
the effective date of this AD using the service information
specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) Fokker Service Bulletin SBF100-57-027, dated September 13,
1993.
(ii) Fokker Service Bulletin SBF100-57-027, Revision 1, dated
May 2, 1994.
(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, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19.
[[Page 81021]]
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: 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 European
Aviation Safety Agency (EASA); or Fokker Services B.V.'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 AD 2014-0158, dated July 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-2016-9389.
(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 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-27529 Filed 11-16-16; 8:45 am]
BILLING CODE 4910-13-P
