Airworthiness Directives; Fokker Services B.V. Model F.28 Airplanes, 11351-11355 [2014-04499]
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Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules
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[FR Doc. 2014–04421 Filed 2–27–14; 8:45 am]
BILLING CODE 8070–01–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0062; Directorate
Identifier 2012–NM–031–AD]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Model F.28 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2000–17–
03 that applies to all Fokker Services
B.V. Model F.28 Mark 0100 airplanes.
AD 2000–17–03 currently requires a
one-time visual inspection and
repetitive eddy current and dye
penetrant inspections of the nose
landing gear (NLG) main fitting to detect
cracking of the NLG main fitting
subassembly, and corrective actions if
necessary. Since we issued AD 2000–
17–03, we were advised that
replacement of certain nose landing gear
(NLG) units eliminates the need for
repetitive inspections. This proposed
AD would retain existing requirements,
require installation a new part number
NLG unit that would terminate the
repetitive inspections, and add
airplanes to the applicability. We are
proposing this AD to prevent cracking of
the NLG main fitting, which could lead
to collapse of the NLG during takeoff
and landing, and possible injury to the
flight crew and passengers.
DATES: We must receive comments on
this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: 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 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
SUMMARY:
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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–2014–
0062; 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–2014–0062; Directorate Identifier
2012–NM–031–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
On August 17, 2000, we issued AD
2000–17–03, Amendment 39–11876 (65
FR 52298, August 29, 2000). AD 2000–
17–03 requires actions intended to
address an unsafe condition on Fokker
Services B.V. Model F.28 Mark 0100
airplanes.
Since we issued AD 2000–17–03,
Amendment 39–11876 (65 FR 52298,
August 29, 2000), we received a report
of a NLG main fitting failure. The
European Aviation Safety Agency
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(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0002R1,
dated March 30, 2012 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
In 1997, a report was received concerning
a Fokker 100 (F28 Mark 0100) aeroplane,
where during landing following nose wheel
touch-down, the nose landing gear (NLG)
broke off just below the pintle pins.
Subsequent inspection by the affected
operator of other aeroplanes in the fleet
identified three more suspect NLG main
fittings. Eddy current (EC) and/or dye
penetrant inspections of these units later
confirmed that cracks were present on the
inner side of the downlock plunger support
web. The total number of flight cycles (FC)
accumulated by the cracked NLG main
fittings at the time of detection were between
9,300 FC and 17,600 FC.
This condition, if not detected and
corrected, could result in further incidents of
NLG collapse, possibly resulting in damage
to the aeroplane and/or injury to the
occupants. To address this potential unsafe
condition, (Civil Aviation Authority
—Netherlands] CAA–NL issued AD (BLA)
1997–116 (currently at issue 2) to require
repetitive inspections of the NLG main fitting
and, depending on findings, rework or
replacement of the NLG main fitting.
Since AD (BLA) 1997–116/2 was issued, it
was determined that replacement of a
Messier-Dowty (M–D, formerly Dowty Rotol)
Part Number (P/N) 201071001 or P/N
201071002 NLG with, respectively, a P/N
201071003 or P/N 201071004 (which have a
so-called ‘heavy weight’ main fitting
installed) or, respectively, with a P/N
201456001 or P/N 201461001 (which are socalled ‘heavy weight’ NLG units) cancels the
need for repetitive inspection and/or rework.
The ‘heavy weight’ main fitting was
originally developed for an increased weight
version (101,000 lbs. maximum take-off
weight) of the Fokker 100, as well as for the
Fokker 70 (F28 Mark 0070), and introduced
on the production line.
M–D issued Service Bulletin (SB) F100–
32–94 and Fokker Services issued SBF100–
32–119, which provide instructions to install
the P/N 201071003 or P/N 201071004 NLG
on aeroplanes in service. In addition, Fokker
Services issued optional SBF100–32–149 to
introduce the P/N 201456001 or P/N
201461001 NLG units on aeroplanes in
service.
In January 2010, a second NLG main fitting
failure occurred. The results of the
investigation showed that the fracture started
from small fatigue cracks in the affected area.
Prompted by this new occurrence, combined
with the NLG certification methodology (safe
life principle), EASA has decided that the
existing terminating action, installation of a
P/N 201071003 or P/N 201071004 NLG
should be made mandatory. Alternatively, a
P/N 201456001 or P/N 201461001 NLG can
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be installed, which meets the same
requirement.
For the reasons described above, EASA
issued AD 2012–0002, retaining the
requirements of CAA–NL AD (BLA) 1997–
116/2, which was superseded, and to require
the replacement of all P/N 201071001 and
P/N 201071002 NLG units with, respectively,
P/N 201071003 and P/N 201071004 NLG
units, or alternatively with, respectively,
P/N 201456001 or P/N 201461001 NLG units.
Replacement of a NLG main fitting or of a
NLG unit on an aeroplane constitutes
terminating action for the repetitive
inspections for that aeroplane.
EASA AD 2012–0002 also prohibits, after
modification of an aeroplane, installation of
a P/N 201071001 or P/N 201071002 NLG unit
on that aeroplane.
*
*
*
*
*
This proposed AD expands the
applicability to include all Fokker
Services B.V. Model F.28 Mark 0100
airplanes. You may examine the MCAI
in the AD docket on the Internet at
https://www.regulations.gov by searching
for and locating it in Docket No. FAA–
2014–0062.
Relevant Service Information
Fokker Services B.V. has issued the
following service bulletins:
• Fokker Services B.V. Service
Bulletin SBF 100–32–119, Revision 1,
dated November 15, 2011, which refers
to Messier-Dowty Service Bulletin
F100–32–92, Revision 1, dated October
8, 1999, as an additional source of
service information for accomplishing
the inspections and rework of the NLG
main fitting subassembly.
• Fokker Services B.V. Service
Bulletin Change Notification SBF 100–
32–119/1, dated January 31, 2000.
• Fokker Services B.V. Proforma
Service Bulletin SBF 100–32–149,
Revision 1, dated October 25, 2007,
including Appendix 1, dated December
12, 2006.
• Fokker Services B.V. Service
Bulletin SBF 100–53–074, dated
November 1, 1999.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
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develop on other products of the same
type design.
In many FAA transport ADs, when
the service information specifies to
contact the manufacturer for further
instructions if certain discrepancies are
found, we typically include in the AD
a requirement to accomplish the action
using a method approved by either the
FAA or the State of Design Authority (or
its delegated agent).
We have recently been notified that
certain laws in other countries do not
allow such delegation of authority, but
some countries do recognize design
approval organizations. In addition, we
have become aware that some U.S.
operators have used repair instructions
that were previously approved by a
State of Design Authority or a Design
Approval Holder (DAH) as a method of
compliance with this provision in FAA
ADs. Frequently, in these cases, the
previously approved repair instructions
come from the airplane structural repair
manual or the DAH repair approval
statements that were not specifically
developed to address the unsafe
condition corrected by the AD. Using
repair instructions that were not
specifically approved for a particular
AD creates the potential for doing
repairs that were not developed to
address the unsafe condition identified
by the MCAI AD, the FAA AD, or the
applicable service information, which
could result in the unsafe condition not
being fully corrected.
To prevent the use of repairs that
were not specifically developed to
correct the unsafe condition, certain
requirements of this proposed AD
specify that the repair approval
specifically refer to the FAA AD. This
change is intended to clarify the method
of compliance and to provide operators
with better visibility of repairs that are
specifically developed and approved to
correct the unsafe condition. In
addition, we use the phrase ‘‘its
delegated agent, or the DAH with State
of Design Authority design organization
approval, as applicable’’ in this
proposed AD to refer to a DAH
authorized to approve certain required
repairs for this proposed AD.
Explanation of Changes Made to the
Existing AD
On July 10, 2002, the FAA issued a
new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs the
FAA’s airworthiness directives system.
The regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance (AMOCs). Because we
have now included this material in 14
CFR part 39, only the office authorized
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to approve AMOCs is identified in each
individual AD. Therefore, Notes 1 and
5 of AD 2000–17–03, Amendment 39–
11876 (65 FR 52298, August 29, 2000),
are not included in this NPRM. We have
also revised Note 2 of AD 2000–17–03
to lettered paragraph (h) in this NPRM
(this change does not affect the intent of
that Note) and removed Note 3 of that
AD because that information does not
apply to the new actions specified in
this NPRM.
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Costs of Compliance
We estimate that this proposed AD
affects 4 airplanes of U.S. registry.
The actions that are required by AD
2000–17–03, Amendment 39–11876 (65
FR 52298, August 29, 2000), and
retained in this proposed AD take about
2 work-hours per product, at an average
labor rate of $85 per work-hour.
Required parts cost about $0 per
product. Based on these figures, the
estimated cost of the actions that were
required by AD 2000–17–03 is $170 per
product.
We also estimate that it would take
about 8 work-hours per product to
comply with the new basic
requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about
$525,000 per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed there will be no charge
for these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this
proposed AD on U.S. operators to be
$2,102,720, or $526,680 per product.
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this proposed AD.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
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concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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:
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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. Amend § 39.13 by removing
airworthiness directive (AD) 2000–17–
03, Amendment 39–11876 (65 FR
52298, August 29, 2000), and adding the
following new AD:
■
Fokker Services B.V.: Docket No. FAA–
2014–0062; Directorate Identifier 2012–
NM–031–AD.
(a) Comments Due Date
We must receive comments by April 14,
2014.
(b) Affected ADs
This AD supersedes AD 2000–17–03,
Amendment 39–11876 (65 FR 52298, August
29, 2000).
(c) Applicability
This AD applies to Fokker Services B.V.
Model F.28 Mark 0100 airplanes; certificated
in any category; all serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports of nose
landing gear (NLG) main fitting failures. We
are issuing this AD to prevent cracking of the
NLG main fitting, which could lead to
collapse of the NLG during takeoff and
landing, and possible injury to the flight crew
and passengers.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained One-Time Visual Inspection
This paragraph restates the actions
required by paragraph (a) of AD 2000–17–03,
Amendment 39–11876 (65 FR 52298, August
29, 2000). For airplanes equipped with
Messier-Dowty nose landing gear (NLG)
having part number (P/N) 201071001 or
201071002, on which a main fitting
subassembly (MFSA) having P/N 201071200,
201071228, 201071248, or 201071249 is
installed: Prior to the accumulation of 7,500
total flight cycles or within 50 flight cycles
after October 3, 2000 (the effective date of AD
2000–17–03), whichever occurs later,
perform a one-time detailed visual inspection
of the NLG main fitting subassembly to detect
cracking, in accordance with Part 1 of the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–32–118, dated
October 8, 1999.
(1) If no cracking is detected, no further
action is required by this paragraph.
(2) If any cracking is detected, prior to
further flight, accomplish the actions
required by paragraph (i) of this AD.
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(h) Definition of a Detailed Visual Inspection
For the purposes of this AD, a detailed
visual inspection is defined as: An intensive
visual examination of a specific structural
area, system, installation, or assembly to
detect damage, failure, or irregularity.
Available lighting is normally supplemented
with a direct source of good lighting at
intensity deemed appropriate by the
inspector. Inspection aids such as mirrors,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.
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(i) Retained Repetitive Eddy Current and/or
Dye Penetrant Inspections
This paragraph restates the actions
required by paragraph (b) of AD 2000–17–03,
Amendment 39–11876 (65 FR 52298, August
29, 2000), with a new exception. For
airplanes equipped with Messier-Dowty nose
landing gear (NLG) having part number (P/N)
201071001 or 201071002, on which a main
fitting subassembly (MFSA) having P/N
201071200, 201071228, 201071248, or
201071249 is installed: Except as required by
paragraph (g)(2) of this AD, prior to the
accumulation of 7,875 total flight cycles, or
within 375 flight cycles after October 3, 2000
(the effective date of AD 2000–17–03),
whichever occurs later, perform an eddy
current or dye penetrant inspection of the
NLG main fitting subassembly to detect
cracking, in accordance with Part 2 of the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–32–118, dated
October 8, 1999 (which is incorporated by
reference in AD 2000–17–03). Such
inspection within the compliance time
required by paragraph (g) of this AD
terminates the requirements of paragraph (g)
of this AD. Repeat the inspection thereafter,
using an eddy current or dye penetrant
technique, at intervals not to exceed 750
flight cycles, except as required by paragraph
(m)(1) of this AD. Repeat the inspection until
the replacement specified in paragraph (l) of
this AD is done, or the installation specified
in paragraph (n) of this AD is done.
(j) Retained Rework of Main Fitting
This paragraph restates the actions
required by paragraph (c) of AD 2000–17–03,
Amendment 39–11876 (65 FR 52298, August
29, 2000), with revised repair methods. If any
cracking is detected during any inspection
required by paragraph (g) or (i) of this AD:
Prior to further flight, rework the main fitting
of the NLG, in accordance with Part 3 of the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–32–118, dated
October 8, 1999 (which is incorporated by
reference in AD 2000–17–03). If, after rework,
any cracking remains that exceeds the limits
specified in Fokker Service Bulletin SBF100–
32–118, dated October 8, 1999, prior to
further flight, accomplish the actions
specified by either paragraph (j)(1) or (j)(2) of
this AD.
(1) Replace the NLG in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–32–118, dated
October 8, 1999 (which is incorporated by
reference in AD 2000–17–03); and within
7,875 flight cycles after such replacement,
perform the inspection as specified in
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paragraph (i) of this AD, and repeat the
inspection thereafter at intervals not to
exceed 750 flight cycles.
(2) Repair in accordance with a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the
Rijksluchtvaartdienst (RLD) (or its delegated
agent); or the European Aviation Safety
Agency (or its delegated agent, or the Design
Approval Holder with EASA’s design
organization approval, as applicable). For a
repair method to be approved by the
Manager, International Branch, ANM–116, as
required by this paragraph, the Manager’s
approval letter must specifically reference
AD 2000–17–03, Amendment 39–11876 (65
FR 52298, August 29, 2000). For a repair
method to be approved as of the effective
date of this AD, the repair approval must
specifically refer to this AD.
Note 1 to paragraph (j) of this AD: Fokker
Service Bulletin SBF100–32–118, dated
October 8, 1999 (which is incorporated by
reference in AD 2000–17–03), references
Messier-Dowty Service Bulletin F100–32–92,
Revision 1, dated October 8, 1999, as an
additional source of service information for
accomplishing the inspections and rework of
the NLG main fitting subassembly.
(k) Retained Reporting Requirements
This paragraph restates the actions
required by paragraph (d) of AD 2000–17–03,
Amendment 39–11876 (65 FR 52298, August
29, 2000), with revised contact information
and minor editorial changes. Submit a report
of the detailed visual inspection findings
(positive and negative) required by paragraph
(g) of this AD, and a report of the initial eddy
current or dye penetrant inspection findings
(positive and negative) required by paragraph
(i) of this AD, to Fokker Services B.V., P.O.
Box 231, 2150 AE Nieuw-Vennep, the
Netherlands; or to 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; at the applicable
time specified in paragraph (k)(1) or (k)(2) of
this AD. As of the effective date of this AD,
submit reports to 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.
(1) For airplanes on which the detailed
visual inspection specified by paragraph (g)
of this AD, and the initial repetitive eddy
current or dye penetrant inspection specified
by paragraph (i) of this AD, are accomplished
after October 3, 2000 (the effective date of AD
2000–17–03, Amendment 39–11876 (65 FR
52298, August 29, 2000)): Submit each report
within 7 days after performing the applicable
inspection.
(2) For airplanes on which the detailed
visual inspection specified by paragraph (g)
of this AD, and the initial repetitive eddy
current or dye penetrant inspection specified
in paragraph (i) of this AD, have been
accomplished prior to October 3, 2000 (the
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
effective date of AD 2000–17–03,
Amendment 39–11876 (65 FR 52298, August
29, 2000)): Submit the reports within 7 days
after October 3, 2000 (the effective date of AD
2000–17–03).
(l) New Requirement of This AD:
Replacement
Except as provided by paragraph (m) of
this AD, before the next scheduled main
fitting overhaul of the nose landing gear
(NLG) after the effective date of this AD, or
within 36 months after the effective date of
this AD, whichever occurs first: Replace all
nose landing gear (NLG) units having part
number (P/N) 201071001 with a new P/N
201071003 NLG unit, and replace all NLG
units having P/N 201071002 with a new P/
N 201071004 NLG unit, in accordance with
the Accomplishment Instructions of Fokker
Services Bulletin SBF100–32–119, Revision
1, dated November 15, 2011.
(m) New Compliance Time Extension and
On-Condition Actions
For airplanes on which the next scheduled
main fitting overhaul of the NLG is to occur
later than 36 months after the effective date
of this AD: Operators may accomplish the
replacement required by paragraph (l) of this
AD before the next scheduled main fitting
overhaul of the nose landing gear (NLG) after
the effective date of this AD, or within 72
months after the effective date of this AD,
whichever occurs first, provided the actions
specified in paragraphs (m)(1) and (m)(2) of
this AD are done.
(1) Within 36 months after the effective
date of this AD, accomplish the inspection
specified in paragraph (i) of this AD within
750 flight cycles since the most recent
inspection and repeat thereafter at intervals
not to exceed 375 flight cycles until the
replacement specified in paragraph (l) of this
AD is done or the installation specified in
paragraph (n) of this AD is done.
(2) In addition to the inspection specified
in paragraph (m)(1) of this AD, do all other
on-condition actions specified in paragraph
1.E(1)(b) of Fokker Services Bulletin SBF100–
32–119, Revision 1, dated November 15,
2011, except where Fokker Services Bulletin
SBF100–32–119, Revision 1, dated November
15, 2011, specifies to contact Fokker
Services, before further flight, contact either
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
EASA (or its delegated agent, or the Design
Approval Holder with EASA’s design
organization approval, as applicable) for
instructions and follow those instructions.
For a repair method to be approved, the
repair approval must specifically refer to this
AD.
Note 1 to paragraph (l) of this AD: Fokker
Service Bulletin SBF100–32–119, Revision 1,
dated November 15, 2011, references
Messier-Dowty Service Bulletin F100–32–94,
dated January 5, 2000, as an additional
source of service information for replacing
the NLG unit.
(n) New Optional Action
Installing a new P/N 201456001 or P/N
201461001 NLG unit, in accordance with the
Fokker Service Bulletin SBF100–32–149,
E:\FR\FM\28FEP1.SGM
28FEP1
Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules
Revision 1, dated October 25, 2007, including
Appendix 1, dated December 12, 2006, is
acceptable for compliance with the
replacement required by paragraph (l) of this
AD, provided the installation is
accomplished within the compliance time
specified in paragraph (l) of this AD; and,
except for airplanes that comply with
paragraph (m) of this AD, provided the
installation is accomplished within the
compliance time specified in paragraph (m)
of this AD.
(o) New Requirement: Concurrent
Modification
Prior to, or concurrently with, the
installation of the NLG unit required by
paragraph (l) of this AD or the optional
installation specified in paragraph (n) of this
AD, modify the nose landing gear (NLG)
bracket, in accordance with the
Accomplishment Instructions of Fokker
Services Bulletin SBF100–53–074, Revision
1, dated October 25, 2007.
(p) New Terminating Actions
Accomplishing the replacement specified
in paragraph (l) of this AD or the installation
specified in paragraph (n) of this AD
terminates the repetitive eddy current or dye
penetrant inspections required by paragraphs
(i) and (m)(1) of this AD.
(q) New Parts Installation Prohibition
(1) For airplanes equipped with MessierDowty nose landing gear (NLG) having part
number (P/N) 201071001 or 201071002, on
which a main fitting subassembly (MFSA)
having P/N 201071200, 201071228,
201071248, or 201071249 is installed: As of
October 3, 2000 (the effective date of AD
2000–17–03, Amendment 39–11876 (65 FR
52298, August 29, 2000), and until the
effective date of this AD: No person may
install an NLG having P/N 201071001 or
201071002 unless the installed MFSA has
been inspected, by means of an eddy current
or dye penetrant inspection, and corrected in
accordance with paragraph (i) of this AD.
(2) For all airplanes: As of the effective
date of this AD, no person may install an
NLG having P/N 201071001 or 201071002 on
any airplane.
emcdonald on DSK67QTVN1PROD with PROPOSALS
(r) Credit for Previous Actions
This paragraph provides credit for the
replacement required by paragraph (l) of this
AD, if those actions were performed before
the effective date of this AD using Fokker
Services B.V. Service Bulletin SBF 100–32–
119, dated January 31, 2000, provided part
number 201071003 or 201071004 nose gear
has been installed.
(s) 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.
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
VerDate Mar<15>2010
16:27 Feb 27, 2014
Jkt 232001
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) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the DAH with a State
of Design Authority’s design organization
approval). You are required to ensure the
product is airworthy before it is returned to
service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(t) Related Information
(1) Refer to MCAI EASA Airworthiness
Directive 2012–0002R1, dated March 30,
2012, 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–
2014–0062.
(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
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.
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
11355
Issued in Renton, Washington, on February
14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04499 Filed 2–27–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0123; Directorate
Identifier 2013–NM–040–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300 B4–601, B4–603,
B4–620, B4–622, -B4–605R, B4–622R,
-F4–605R, F4–622R, and -C4–605R
Variant F airplanes; and Model A310–
203, –204, –221, –222, –304, –322, –324,
and –325 airplanes. This proposed AD
was prompted by a report of inner skin
disbonding damage on a rudder. This
proposed AD would require repetitive
ultrasonic inspections for disbonding of
certain rudders; an elasticity of laminate
checker inspection; a woodpecker or tap
test inspection; venting the core, if
necessary; and repairing, if necessary.
We are proposing this AD to detect and
correct rudder disbonding, which could
affect the structural integrity of the
rudder.
SUMMARY:
We must receive comments on
this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS,
DATES:
E:\FR\FM\28FEP1.SGM
28FEP1
]]>Agencies
[Federal Register Volume 79, Number 40 (Friday, February 28, 2014)]
[Proposed Rules]
[Pages 11351-11355]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04499]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0062; Directorate Identifier 2012-NM-031-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Model F.28
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2000-17-
03 that applies to all Fokker Services B.V. Model F.28 Mark 0100
airplanes. AD 2000-17-03 currently requires a one-time visual
inspection and repetitive eddy current and dye penetrant inspections of
the nose landing gear (NLG) main fitting to detect cracking of the NLG
main fitting subassembly, and corrective actions if necessary. Since we
issued AD 2000-17-03, we were advised that replacement of certain nose
landing gear (NLG) units eliminates the need for repetitive
inspections. This proposed AD would retain existing requirements,
require installation a new part number NLG unit that would terminate
the repetitive inspections, and add airplanes to the applicability. We
are proposing this AD to prevent cracking of the NLG main fitting,
which could lead to collapse of the NLG during takeoff and landing, and
possible injury to the flight crew and passengers.
DATES: We must receive comments on this proposed AD by April 14, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: 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 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-2014-
0062; 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-2014-0062;
Directorate Identifier 2012-NM-031-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
On August 17, 2000, we issued AD 2000-17-03, Amendment 39-11876 (65
FR 52298, August 29, 2000). AD 2000-17-03 requires actions intended to
address an unsafe condition on Fokker Services B.V. Model F.28 Mark
0100 airplanes.
Since we issued AD 2000-17-03, Amendment 39-11876 (65 FR 52298,
August 29, 2000), we received a report of a NLG main fitting failure.
The European Aviation Safety Agency
[[Page 11352]]
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2012-
0002R1, dated March 30, 2012 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
In 1997, a report was received concerning a Fokker 100 (F28 Mark
0100) aeroplane, where during landing following nose wheel touch-
down, the nose landing gear (NLG) broke off just below the pintle
pins. Subsequent inspection by the affected operator of other
aeroplanes in the fleet identified three more suspect NLG main
fittings. Eddy current (EC) and/or dye penetrant inspections of
these units later confirmed that cracks were present on the inner
side of the downlock plunger support web. The total number of flight
cycles (FC) accumulated by the cracked NLG main fittings at the time
of detection were between 9,300 FC and 17,600 FC.
This condition, if not detected and corrected, could result in
further incidents of NLG collapse, possibly resulting in damage to
the aeroplane and/or injury to the occupants. To address this
potential unsafe condition, (Civil Aviation Authority --Netherlands]
CAA-NL issued AD (BLA) 1997-116 (currently at issue 2) to require
repetitive inspections of the NLG main fitting and, depending on
findings, rework or replacement of the NLG main fitting.
Since AD (BLA) 1997-116/2 was issued, it was determined that
replacement of a Messier-Dowty (M-D, formerly Dowty Rotol) Part
Number (P/N) 201071001 or P/N 201071002 NLG with, respectively, a P/
N 201071003 or P/N 201071004 (which have a so-called `heavy weight'
main fitting installed) or, respectively, with a P/N 201456001 or P/
N 201461001 (which are so-called `heavy weight' NLG units) cancels
the need for repetitive inspection and/or rework. The `heavy weight'
main fitting was originally developed for an increased weight
version (101,000 lbs. maximum take-off weight) of the Fokker 100, as
well as for the Fokker 70 (F28 Mark 0070), and introduced on the
production line.
M-D issued Service Bulletin (SB) F100-32-94 and Fokker Services
issued SBF100-32-119, which provide instructions to install the P/N
201071003 or P/N 201071004 NLG on aeroplanes in service. In
addition, Fokker Services issued optional SBF100-32-149 to introduce
the P/N 201456001 or P/N 201461001 NLG units on aeroplanes in
service.
In January 2010, a second NLG main fitting failure occurred. The
results of the investigation showed that the fracture started from
small fatigue cracks in the affected area. Prompted by this new
occurrence, combined with the NLG certification methodology (safe
life principle), EASA has decided that the existing terminating
action, installation of a P/N 201071003 or P/N 201071004 NLG should
be made mandatory. Alternatively, a P/N 201456001 or P/N 201461001
NLG can be installed, which meets the same requirement.
For the reasons described above, EASA issued AD 2012-0002,
retaining the requirements of CAA-NL AD (BLA) 1997-116/2, which was
superseded, and to require the replacement of all P/N 201071001 and
P/N 201071002 NLG units with, respectively, P/N 201071003 and P/N
201071004 NLG units, or alternatively with, respectively, P/N
201456001 or P/N 201461001 NLG units.
Replacement of a NLG main fitting or of a NLG unit on an
aeroplane constitutes terminating action for the repetitive
inspections for that aeroplane.
EASA AD 2012-0002 also prohibits, after modification of an
aeroplane, installation of a P/N 201071001 or P/N 201071002 NLG unit
on that aeroplane.
* * * * *
This proposed AD expands the applicability to include all Fokker
Services B.V. Model F.28 Mark 0100 airplanes. You may examine the MCAI
in the AD docket on the Internet at https://www.regulations.gov by
searching for and locating it in Docket No. FAA-2014-0062.
Relevant Service Information
Fokker Services B.V. has issued the following service bulletins:
Fokker Services B.V. Service Bulletin SBF 100-32-119,
Revision 1, dated November 15, 2011, which refers to Messier-Dowty
Service Bulletin F100-32-92, Revision 1, dated October 8, 1999, as an
additional source of service information for accomplishing the
inspections and rework of the NLG main fitting subassembly.
Fokker Services B.V. Service Bulletin Change Notification
SBF 100-32-119/1, dated January 31, 2000.
Fokker Services B.V. Proforma Service Bulletin SBF 100-32-
149, Revision 1, dated October 25, 2007, including Appendix 1, dated
December 12, 2006.
Fokker Services B.V. Service Bulletin SBF 100-53-074,
dated November 1, 1999.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD specify that the repair approval specifically refer to the FAA AD.
This change is intended to clarify the method of compliance and to
provide operators with better visibility of repairs that are
specifically developed and approved to correct the unsafe condition. In
addition, we use the phrase ``its delegated agent, or the DAH with
State of Design Authority design organization approval, as applicable''
in this proposed AD to refer to a DAH authorized to approve certain
required repairs for this proposed AD.
Explanation of Changes Made to the Existing AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in 14
CFR part 39, only the office authorized
[[Page 11353]]
to approve AMOCs is identified in each individual AD. Therefore, Notes
1 and 5 of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29,
2000), are not included in this NPRM. We have also revised Note 2 of AD
2000-17-03 to lettered paragraph (h) in this NPRM (this change does not
affect the intent of that Note) and removed Note 3 of that AD because
that information does not apply to the new actions specified in this
NPRM.
Costs of Compliance
We estimate that this proposed AD affects 4 airplanes of U.S.
registry.
The actions that are required by AD 2000-17-03, Amendment 39-11876
(65 FR 52298, August 29, 2000), and retained in this proposed AD take
about 2 work-hours per product, at an average labor rate of $85 per
work-hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the actions that were required by AD
2000-17-03 is $170 per product.
We also estimate that it would take about 8 work-hours per product
to comply with the new basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $525,000 per product. Where the service information lists
required parts costs that are covered under warranty, we have assumed
there will be no charge for these parts. As we do not control warranty
coverage for affected parties, some parties may incur costs higher than
estimated here. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $2,102,720, or $526,680 per
product.
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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. Amend Sec. 39.13 by removing airworthiness directive (AD) 2000-17-
03, Amendment 39-11876 (65 FR 52298, August 29, 2000), and adding the
following new AD:
Fokker Services B.V.: Docket No. FAA-2014-0062; Directorate
Identifier 2012-NM-031-AD.
(a) Comments Due Date
We must receive comments by April 14, 2014.
(b) Affected ADs
This AD supersedes AD 2000-17-03, Amendment 39-11876 (65 FR
52298, August 29, 2000).
(c) Applicability
This AD applies to Fokker Services B.V. Model F.28 Mark 0100
airplanes; certificated in any category; all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of nose landing gear (NLG) main
fitting failures. We are issuing this AD to prevent cracking of the
NLG main fitting, which could lead to collapse of the NLG during
takeoff and landing, and possible injury to the flight crew and
passengers.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained One-Time Visual Inspection
This paragraph restates the actions required by paragraph (a) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000).
For airplanes equipped with Messier-Dowty nose landing gear (NLG)
having part number (P/N) 201071001 or 201071002, on which a main
fitting subassembly (MFSA) having P/N 201071200, 201071228,
201071248, or 201071249 is installed: Prior to the accumulation of
7,500 total flight cycles or within 50 flight cycles after October
3, 2000 (the effective date of AD 2000-17-03), whichever occurs
later, perform a one-time detailed visual inspection of the NLG main
fitting subassembly to detect cracking, in accordance with Part 1 of
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
32-118, dated October 8, 1999.
(1) If no cracking is detected, no further action is required by
this paragraph.
(2) If any cracking is detected, prior to further flight,
accomplish the actions required by paragraph (i) of this AD.
[[Page 11354]]
(h) Definition of a Detailed Visual Inspection
For the purposes of this AD, a detailed visual inspection is
defined as: An intensive visual examination of a specific structural
area, system, installation, or assembly to detect damage, failure,
or irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirrors, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.
(i) Retained Repetitive Eddy Current and/or Dye Penetrant Inspections
This paragraph restates the actions required by paragraph (b) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000),
with a new exception. For airplanes equipped with Messier-Dowty nose
landing gear (NLG) having part number (P/N) 201071001 or 201071002,
on which a main fitting subassembly (MFSA) having P/N 201071200,
201071228, 201071248, or 201071249 is installed: Except as required
by paragraph (g)(2) of this AD, prior to the accumulation of 7,875
total flight cycles, or within 375 flight cycles after October 3,
2000 (the effective date of AD 2000-17-03), whichever occurs later,
perform an eddy current or dye penetrant inspection of the NLG main
fitting subassembly to detect cracking, in accordance with Part 2 of
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
32-118, dated October 8, 1999 (which is incorporated by reference in
AD 2000-17-03). Such inspection within the compliance time required
by paragraph (g) of this AD terminates the requirements of paragraph
(g) of this AD. Repeat the inspection thereafter, using an eddy
current or dye penetrant technique, at intervals not to exceed 750
flight cycles, except as required by paragraph (m)(1) of this AD.
Repeat the inspection until the replacement specified in paragraph
(l) of this AD is done, or the installation specified in paragraph
(n) of this AD is done.
(j) Retained Rework of Main Fitting
This paragraph restates the actions required by paragraph (c) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000),
with revised repair methods. If any cracking is detected during any
inspection required by paragraph (g) or (i) of this AD: Prior to
further flight, rework the main fitting of the NLG, in accordance
with Part 3 of the Accomplishment Instructions of Fokker Service
Bulletin SBF100-32-118, dated October 8, 1999 (which is incorporated
by reference in AD 2000-17-03). If, after rework, any cracking
remains that exceeds the limits specified in Fokker Service Bulletin
SBF100-32-118, dated October 8, 1999, prior to further flight,
accomplish the actions specified by either paragraph (j)(1) or
(j)(2) of this AD.
(1) Replace the NLG in accordance with the Accomplishment
Instructions of Fokker Service Bulletin SBF100-32-118, dated October
8, 1999 (which is incorporated by reference in AD 2000-17-03); and
within 7,875 flight cycles after such replacement, perform the
inspection as specified in paragraph (i) of this AD, and repeat the
inspection thereafter at intervals not to exceed 750 flight cycles.
(2) Repair in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the Rijksluchtvaartdienst (RLD) (or its delegated agent); or the
European Aviation Safety Agency (or its delegated agent, or the
Design Approval Holder with EASA's design organization approval, as
applicable). For a repair method to be approved by the Manager,
International Branch, ANM-116, as required by this paragraph, the
Manager's approval letter must specifically reference AD 2000-17-03,
Amendment 39-11876 (65 FR 52298, August 29, 2000). For a repair
method to be approved as of the effective date of this AD, the
repair approval must specifically refer to this AD.
Note 1 to paragraph (j) of this AD: Fokker Service Bulletin
SBF100-32-118, dated October 8, 1999 (which is incorporated by
reference in AD 2000-17-03), references Messier-Dowty Service
Bulletin F100-32-92, Revision 1, dated October 8, 1999, as an
additional source of service information for accomplishing the
inspections and rework of the NLG main fitting subassembly.
(k) Retained Reporting Requirements
This paragraph restates the actions required by paragraph (d) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000),
with revised contact information and minor editorial changes. Submit
a report of the detailed visual inspection findings (positive and
negative) required by paragraph (g) of this AD, and a report of the
initial eddy current or dye penetrant inspection findings (positive
and negative) required by paragraph (i) of this AD, to Fokker
Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands;
or to 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; at the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD. As of the effective date of
this AD, submit reports to 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.
(1) For airplanes on which the detailed visual inspection
specified by paragraph (g) of this AD, and the initial repetitive
eddy current or dye penetrant inspection specified by paragraph (i)
of this AD, are accomplished after October 3, 2000 (the effective
date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29,
2000)): Submit each report within 7 days after performing the
applicable inspection.
(2) For airplanes on which the detailed visual inspection
specified by paragraph (g) of this AD, and the initial repetitive
eddy current or dye penetrant inspection specified in paragraph (i)
of this AD, have been accomplished prior to October 3, 2000 (the
effective date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298,
August 29, 2000)): Submit the reports within 7 days after October 3,
2000 (the effective date of AD 2000-17-03).
(l) New Requirement of This AD: Replacement
Except as provided by paragraph (m) of this AD, before the next
scheduled main fitting overhaul of the nose landing gear (NLG) after
the effective date of this AD, or within 36 months after the
effective date of this AD, whichever occurs first: Replace all nose
landing gear (NLG) units having part number (P/N) 201071001 with a
new P/N 201071003 NLG unit, and replace all NLG units having P/N
201071002 with a new P/N 201071004 NLG unit, in accordance with the
Accomplishment Instructions of Fokker Services Bulletin SBF100-32-
119, Revision 1, dated November 15, 2011.
(m) New Compliance Time Extension and On-Condition Actions
For airplanes on which the next scheduled main fitting overhaul
of the NLG is to occur later than 36 months after the effective date
of this AD: Operators may accomplish the replacement required by
paragraph (l) of this AD before the next scheduled main fitting
overhaul of the nose landing gear (NLG) after the effective date of
this AD, or within 72 months after the effective date of this AD,
whichever occurs first, provided the actions specified in paragraphs
(m)(1) and (m)(2) of this AD are done.
(1) Within 36 months after the effective date of this AD,
accomplish the inspection specified in paragraph (i) of this AD
within 750 flight cycles since the most recent inspection and repeat
thereafter at intervals not to exceed 375 flight cycles until the
replacement specified in paragraph (l) of this AD is done or the
installation specified in paragraph (n) of this AD is done.
(2) In addition to the inspection specified in paragraph (m)(1)
of this AD, do all other on-condition actions specified in paragraph
1.E(1)(b) of Fokker Services Bulletin SBF100-32-119, Revision 1,
dated November 15, 2011, except where Fokker Services Bulletin
SBF100-32-119, Revision 1, dated November 15, 2011, specifies to
contact Fokker Services, before further flight, contact either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA (or its delegated agent, or the Design
Approval Holder with EASA's design organization approval, as
applicable) for instructions and follow those instructions. For a
repair method to be approved, the repair approval must specifically
refer to this AD.
Note 1 to paragraph (l) of this AD: Fokker Service Bulletin
SBF100-32-119, Revision 1, dated November 15, 2011, references
Messier-Dowty Service Bulletin F100-32-94, dated January 5, 2000, as
an additional source of service information for replacing the NLG
unit.
(n) New Optional Action
Installing a new P/N 201456001 or P/N 201461001 NLG unit, in
accordance with the Fokker Service Bulletin SBF100-32-149,
[[Page 11355]]
Revision 1, dated October 25, 2007, including Appendix 1, dated
December 12, 2006, is acceptable for compliance with the replacement
required by paragraph (l) of this AD, provided the installation is
accomplished within the compliance time specified in paragraph (l)
of this AD; and, except for airplanes that comply with paragraph (m)
of this AD, provided the installation is accomplished within the
compliance time specified in paragraph (m) of this AD.
(o) New Requirement: Concurrent Modification
Prior to, or concurrently with, the installation of the NLG unit
required by paragraph (l) of this AD or the optional installation
specified in paragraph (n) of this AD, modify the nose landing gear
(NLG) bracket, in accordance with the Accomplishment Instructions of
Fokker Services Bulletin SBF100-53-074, Revision 1, dated October
25, 2007.
(p) New Terminating Actions
Accomplishing the replacement specified in paragraph (l) of this
AD or the installation specified in paragraph (n) of this AD
terminates the repetitive eddy current or dye penetrant inspections
required by paragraphs (i) and (m)(1) of this AD.
(q) New Parts Installation Prohibition
(1) For airplanes equipped with Messier-Dowty nose landing gear
(NLG) having part number (P/N) 201071001 or 201071002, on which a
main fitting subassembly (MFSA) having P/N 201071200, 201071228,
201071248, or 201071249 is installed: As of October 3, 2000 (the
effective date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298,
August 29, 2000), and until the effective date of this AD: No person
may install an NLG having P/N 201071001 or 201071002 unless the
installed MFSA has been inspected, by means of an eddy current or
dye penetrant inspection, and corrected in accordance with paragraph
(i) of this AD.
(2) For all airplanes: As of the effective date of this AD, no
person may install an NLG having P/N 201071001 or 201071002 on any
airplane.
(r) Credit for Previous Actions
This paragraph provides credit for the replacement required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Fokker Services B.V. Service
Bulletin SBF 100-32-119, dated January 31, 2000, provided part
number 201071003 or 201071004 nose gear has been installed.
(s) 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. 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) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval). You are required to ensure the
product is airworthy before it is returned to service.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(t) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2012-0002R1,
dated March 30, 2012, 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-2014-0062.
(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 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 February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-04499 Filed 2-27-14; 8:45 am]
BILLING CODE 4910-13-P
