Document ID: FAA-2014-0062-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Fokker Services B.V. Model F.28 Airplanes
Posted Date: 2014-02-28T05:00Z

[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]

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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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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 http://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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 http://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 http://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 
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 
technicalservices@fokker.com; 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 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 http://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 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.

    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