[Federal Register: July 2, 2008 (Volume 73, Number 128)]
[Proposed Rules]
[Page 37903-37905]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02jy08-47]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0675; Directorate Identifier 2007-NM-192-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark
0100 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Fokker Model F.28 Mark 0070 and
0100 airplanes. The existing AD currently requires a one-time
inspection of the main landing gear (MLG) main fitting for cracks, and
repair if necessary. The existing AD also currently requires installing
a placard and revising the airplane flight manual to include procedures
to prohibit the application of brakes during backward movement of the
airplane. This proposed AD would require repetitive eddy current
inspections of the MLG main fitting and rework before further flight as
applicable. This proposed AD results from reports that a final solution
eliminating the cause of the crack initiation mechanism is not yet
available and that repetitive inspections are necessary. We are
proposing this AD to detect and correct cracks in the MLG main fitting,
which could result in reduced structural integrity of the MLG main
fitting.
DATES: We must receive comments on this proposed AD by August 1, 2008.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Fokker
Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; 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 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, Washington 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-2008-0675;
Directorate Identifier 2007-NM-192-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to 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.
[[Page 37904]]
Discussion
On March 10, 2006, we issued AD 2006-06-07, amendment 39-14516 (71
FR 14363, March 22, 2006), for certain Fokker Model F.28 Mark 0070 and
Mark 0100 airplanes. That AD requires inspecting the main landing gear
(MLG) main fitting for cracks, and repairing if necessary. That AD also
requires installing a placard and revising the airplane flight manual
to include procedures to prohibit the application of brakes during
backward movement of the airplane. That AD resulted from a report that
an MLG main fitting failed on an airplane that was braking while moving
backward. We issued that AD to detect and correct cracks in the MLG
main fitting, which could result in reduced structural integrity of the
MLG main fitting.
Actions Since Existing AD Was Issued
Since we issued AD 2006-06-07, we received reports from The Civil
Aviation Authority--The Netherlands (CAA-NL), which is the
airworthiness authority for the Netherlands, that a final solution
eliminating the cause of the crack initiation mechanism is not yet
available. Therefore, the inspection required by AD 2006-06-07 must now
be done repetitively, until a final solution is developed to adequately
address the identified unsafe condition of this AD.
Relevant Service Information
Messier-Dowty has issued Service Bulletin F100-32-111, dated
December 20, 2005. The service bulletin describes procedures for doing
a repetitive eddy current inspection of the MLG main fitting for
cracks, and reworking the MLG main fitting as applicable. Accomplishing
the actions specified in the service information is intended to
adequately address the unsafe condition. The CAA-NL mandated the
service information and issued airworthiness directive NL-2006-003,
dated February 7, 2006, to ensure the continued airworthiness of these
airplanes in the Netherlands.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in the Netherlands and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the CAA-NL has kept the FAA informed
of the situation described above. We have examined the CAA-NL's
findings, evaluated all pertinent information, and determined that AD
action is necessary for airplanes of this type design that are
certificated for operation in the United States.
This proposed AD would supersede AD 2006-06-07 and would retain the
requirements of the existing AD. This proposed AD would also require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the Proposed AD and the Service Bulletin.''
Differences Between the Proposed AD and the Service Bulletin
Operators should note that, unlike the procedures described in the
referenced Messier-Dowty Service Bulletin F100-32-111, dated December
20, 2005, the proposed AD would not permit further flight with any
cracks in the MLG main fitting. Due to the safety implications and
consequences of such cracking operators must repair all cracked MGL
main fittings before further flight.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work Average labor Parts Cost per registered Fleet cost
hours rate per hour airplane airplanes
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Inspection (required by AD 2006-06-07)...... 2 $80 None........................... $160 11 $1,760
AFM Revision and Placard Installation 1 80 None........................... 80 11 880
(required by AD 2006-06-07).
Inspection (new proposed action)............ 6 80 $540 ($270 per fitting)........ 1,020 12 12,240
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have 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 that the 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); and
3. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 37905]]
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14516 (71 FR 14363, March 22, 2006) and adding
the following new airworthiness directive (AD):
Fokker: Docket No. FAA-2008-0675; Directorate Identifier 2007-NM-
192-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by August 1,
2008.
Affected ADs
(b) This AD supersedes AD 2006-06-07.
Applicability
(c) This AD applies to Fokker Model F.28 Mark 0070 and Mark 0100
airplanes, certificated in any category, equipped with Messier-Dowty
main landing gears (MLGs).
Unsafe Condition
(d) This AD results from reports that a final solution
eliminating the cause of the crack initiation mechanism is not yet
available. We are issuing this AD to detect and correct cracks in
the main landing gear (MLG) main fitting, which could result in
reduced structural integrity of the MLG main fitting.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-06-07
Airplane Flight Manual (AFM) Revision and Placard Installation
(f) Within 14 days after April 26, 2006 (the effective date of
AD 2006-06-07), amend the Limitations section of the Fokker F.28 AFM
to prohibit application of brakes during backward movement of the
airplane. This may be done by inserting a copy of this AD in the
AFM.
Note 1: When a statement to prohibit application of brakes
during backward movement of the airplane has been included in the
general revisions of the AFM, the general revisions may be inserted
into the AFM, and the copy of this AD may be removed from the AFM.
(g) Within 14 days after April 26, 2006, affix a placard on the
pedestal, next to the parking brake handle, having the following
wording: ``APPLICATION OF BRAKES DURING BACKWARD MOVEMENT IS
PROHIBITED.''
Inspection and Corrective Action
(h) At the applicable time specified in paragraph (h)(1) or
(h)(2) of this AD: Do an eddy current inspection of the MLG main
fittings and repair before further flight as applicable, in
accordance with the Accomplishment Instructions of Messier-Dowty
Service Bulletin F100-32-106, including Appendices A through C and
excluding Appendix D, dated February 18, 2005, except as provided by
paragraphs (i) and (j) of this AD.
(1) For airplanes on which an inspection has not been done in
accordance with Messier-Dowty Service Bulletin F100-32-104, Revision
2, dated October 30, 2003: Within 3 months after April 26, 2006.
(2) For airplanes on which an inspection has been done in
accordance with Messier-Dowty Service Bulletin F100-32-104, Revision
2, dated October 30, 2003: Within 2,000 flight cycles since the last
inspection done in accordance with the service bulletin or within 3
months after April 26, 2006, whichever occurs later.
Exceptions to the Service Bulletin
(i) Where Messier-Dowty Service Bulletin F100-32-106, including
Appendices A through C and excluding Appendix D, dated February 18,
2005, specifies contacting the manufacturer for repair: Before
further flight, repair using a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the Civil Aviation Authority--The Netherlands
(CAA-NL) (or its delegated agent).
(j) Although Messier-Dowty Service Bulletin F100-32-106,
including Appendices A through C and excluding Appendix D, dated
February 18, 2005, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Parts Installation
(k) As of April 26, 2006, and until the effective date of this
AD, no person may install, on any airplane, a Messier-Dowty MLG,
unless it has been inspected/repaired according to paragraph (h) of
this AD.
New Requirements of This AD
Inspection and Repair
(l) At the applicable times specified in paragraphs (l)(1),
(l)(2), and (l)(3) of this AD: Do an eddy current inspection of the
MLG main fitting for cracks, and rework the MLG main fitting if
applicable, in accordance with the Accomplishment Instructions of
Messier-Dowty Service Bulletin F100-32-111, including Appendices A
through C and excluding Appendix D, dated December 20, 2005; except
as provided by paragraph (m) of this AD. The rework must be done
before further flight.
(1) For all MLG main fittings, except those units identified in
paragraph (l)(2) of this AD: Inspect within the next 2,000 flight
cycles since the last inspection required by paragraph (h) of this
AD, or within 4 months after the effective date of this AD,
whichever occurs later.
(2) For new MLG main fittings and MLG main fittings on which
both bores have been repaired (reworked) in accordance with
paragraph (h) of this AD: Inspect within 4,000 flight cycles since
new (installation) or repaired (rework) in accordance with paragraph
(h) of this AD, as applicable.
(3) For all MLGs: Repeat the eddy current inspection thereafter
at intervals not to exceed 2,000 flight cycles.
Exception to Service Bulletin F100-32-111
(m) Although Messier-Dowty Service Bulletin F100-32-111,
including Appendices A through C and excluding Appendix D, dated
December 20, 2005, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Parts Installation
(n) As of the effective date of this AD, no person may install,
on any airplane, a Messier-Dowty MLG, unless it has been inspected
and reworked in accordance with paragraph (l) of this AD.
Alternative Methods of Compliance (AMOCs)
(o) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(p) The Civil Aviation Authority--The Netherlands airworthiness
directive NL-2006-003, dated February 7, 2006, also addresses the
subject of this AD.
Issued in Renton, Washington, on June 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.11
[FR Doc. E8-14976 Filed 7-1-08; 8:45 am]
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