Airworthiness Directives; Fokker Services B.V. Airplanes

[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70453-70458]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-27361]


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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; 
Amendment 39-18025; AD 2014-23-09]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2000-17-03 for 
all Fokker Services B.V. Model F.28 Mark 0100 airplanes. AD 2000-17-

[[Page 70454]]

03 required inspections of the nose landing gear (NLG) main fitting to 
detect cracking of the NLG main fitting subassembly, and corrective 
actions if necessary. This new AD retains the requirements of AD 2000-
17-03, requires installing a new part number NLG unit that terminates 
the repetitive inspections, and adds airplanes to the applicability. 
This AD was prompted by a report of an NLG main fitting failure. 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.

DATES: This AD becomes effective December 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 3, 2000 (65 FR 52298, August 29, 2000).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0062; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 [email protected]; Internet http://www.myfokkerfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2000-17-03, Amendment 39-11876 (65 FR 52298, 
August 29, 2000). AD 2000-17-03 applied to all Fokker Services B.V. 
Model F.28 Mark 0100 airplanes. The NPRM published in the Federal 
Register on February 28, 2014 (79 FR 11351). The NPRM proposed to 
continue to require a one-time visual inspection, and repetitive eddy 
current and dye penetrant inspections of the NLG main fitting to detect 
cracking of the NLG main fitting subassembly, and corrective actions if 
necessary. The NPRM also proposed to require installing a new part 
number NLG unit that would terminate the repetitive inspections, and 
adding airplanes to the applicability.
    The European Aviation Safety Agency (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 on all Fokker Services 
B.V. Model F.28 Mark 0100 airplanes. 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 [an] AD * * * to require repetitive inspections of the 
NLG main fitting and, depending on findings, rework or replacement 
of the NLG main fitting.
    Since [that Netherlands] AD * * * 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 [the Netherlands] AD * * *, 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.
* * * * *
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0062-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 11351, February 28, 
2014) or on the determination of the cost to the public.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    The MCAI or referenced service information in an FAA AD often 
directs the owner/operator to contact the manufacturer for corrective 
actions, such as a repair. Briefly, the Airworthy Product paragraph 
allowed owners/operators to use corrective actions provided by the 
manufacturer if those actions were FAA-approved. In addition, the 
paragraph stated that any actions approved by the State of Design 
Authority (or its delegated agent) are considered to be FAA-approved.
    In the NPRM (79 FR 11351, February 28, 2014), we proposed to 
prevent the use of repairs that were not specifically

[[Page 70455]]

developed to correct the unsafe condition, by requiring that the repair 
approval provided by the State of Design Authority or its delegated 
agent specifically refer to this FAA AD. This change was 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 proposed to change the 
phrase ``its delegated agent'' to include a design approval holder 
(DAH) with State of Design Authority design organization approval 
(DOA), as applicable, to refer to a DAH authorized to approve required 
repairs for the proposed AD.
    No comments were provided to the NPRM (79 FR 11351, February 28, 
2014) about these proposed changes. However, a comment was provided for 
an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285, 
December 26, 2013). The commenter stated the following: ``The proposed 
wording, being specific to repairs, eliminates the interpretation that 
Airbus messages are acceptable for approving minor deviations 
(corrective actions) needed during accomplishment of an AD mandated 
Airbus service bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Fokker 
Services B.V.'s EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases 
the foreign manufacturer's service bulletin and the foreign authority's 
MCAI might have been issued some time before the FAA AD. Therefore, the 
DOA might have provided U.S. operators with an approved repair, 
developed with full awareness of the unsafe condition, before the FAA 
AD is issued. Under these circumstances, to comply with the FAA AD, the 
operator would be required to go back to the manufacturer's DOA and 
obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a 
requirement, the FAA will coordinate with affected DAHs and verify they 
are prepared to implement means to ensure that their repair approvals 
consider the unsafe condition addressed in this AD. Any such 
requirements will be adopted through the normal AD rulemaking process, 
including notice-and-comment procedures, when appropriate.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``DAH with State of Design Authority design 
organization approval,'' but instead we have provided the specific 
delegation approval granted by the State of Design Authority for the 
DAH.

Clarification of Language in Paragraph (m)(2) of This AD

    In paragraph (m)(2) of the NPRM (79 FR 11351, February 28, 2014), 
we specified to contact certain aviation authorities ``for instructions 
and follow those instructions.'' As part of the change described 
previously regarding ``Contacting the Manufacturer'' language, this 
text has been revised in paragraph (m)(2) of this AD to specify doing a 
repair using a method approved by the FAA, EASA, or Fokker Services 
B.V.'s EASA DOA.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 11351, February 28, 2014) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 11351, February 28, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.
    The actions required by AD 2000-17-03, Amendment 39-11876 (65 FR 
52298, August 29, 2000), and retained in this AD take about 2 work-
hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost $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 will take about 8 work-hours per product 
to comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $525,000 per 
product. Based on these figures, we estimate the cost of this 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

[[Page 70456]]

estimate for the on-condition actions specified in this 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 removing Airworthiness Directive (AD) 
2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000), and 
adding the following new AD:

2014-23-09 Fokker Services B.V.: Amendment 39-18025. Docket No. FAA-
2014-0062; Directorate Identifier 2012-NM-031-AD.

(a) Effective Date

    This AD becomes effective December 31, 2014.

(b) Affected ADs

    This AD replaces 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 a report of a nose landing gear (NLG) 
main fitting failure. 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 Detailed 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 a Messier-Dowty 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.

(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 a Messier-Dowty 
NLG having P/N 201071001 or 201071002, on which a 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

[[Page 70457]]

subassembly to detect cracking, in accordance with Part 2 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
118, dated October 8, 1999. Such inspection within the compliance 
time required by the introductory text of 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. 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; 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 (EASA); or Fokker B.V. Service's 
EASA Design Organization Approval (DOA).

    Note 1 to paragraph (j) of this AD: Fokker Service Bulletin 
SBF100-32-118, dated October 8, 1999, 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 [email protected]; Internet 
http://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 
[email protected]; Internet http://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 NLG after the effective date 
of this AD, or within 36 months after the effective date of this AD, 
whichever occurs first: Replace all NLG units having 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 Service Bulletin SBF100-
32-119, Revision 1, dated November 15, 2011, including Fokker Manual 
Change Notification MCNM-F100-043, dated January 31, 2000.

(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 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 Service Bulletin SBF100-32-119, Revision 1, 
dated November 15, 2011, including Fokker Manual Change Notification 
MCNM-F100-043, dated January 31, 2000; except where Fokker Service 
Bulletin SBF100-32-119, Revision 1, dated November 15, 2011, 
including Fokker Manual Change Notification MCNM-F100-043, dated 
January 31, 2000, specifies to contact Fokker Services B.V., before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Fokker Services B.V.'s EASA Design Organization Approval 
(DOA).

    Note 2 to paragraph (m) of this AD:  Fokker Service Bulletin 
SBF100-32-119, Revision 1, dated November 15, 2011, including Fokker 
Manual Change Notification MCNM-F100-043, dated January 31, 2000, 
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 Fokker Proforma Service Bulletin SBF100-32-149, 
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 NLG bracket, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-53-074, dated November 1, 1999.

(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 a Messier-Dowty NLG having 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.

[[Page 70458]]

    (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 Service Bulletin SBF 100-32-
119, dated January 31, 2000, provided P/N 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: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the 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.
    (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 Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0002R1, dated March 30, 
2012, for related information. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0062-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(5) and (u)(6) of this AD.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 31, 2014.
    (i) Fokker Service Bulletin SBF 100-32-119, Revision 1, dated 
November 15, 2011, including Fokker Manual Change Notification MCNM-
F100-043, dated January 31, 2000.
    (ii) Fokker Proforma Service Bulletin SBF 100-32-149, Revision 
1, dated October 25, 2007, including Appendix 1, dated December 12, 
2006.
    (iii) Fokker Service Bulletin SBF 100-53-074, dated November 1, 
1999.
    (4) The following service information was approved for IBR on 
October 3, 2000 (65 FR 52298, August 17, 2000).
    (i) Fokker Service Bulletin SBF100-32-118, dated October 8, 
1999.
    (ii) Reserved.
    (5) 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 [email protected]; Internet http://www.myfokkerfleet.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-27361 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P

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