FR Doc E6-13731

[Federal Register: August 22, 2006 (Volume 71, Number 162)]
[Rules and Regulations]
[Page 48793-48795]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22au06-1]

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[[Page 48793]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25641; Directorate Identifier 2006-NM-114-AD;
Amendment 39-14730; AD 2006-17-09]
RIN 2120-AA64

Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes

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

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Fokker Model F27 Mark 050 airplanes. This AD requires doing an initial
inspection of the leading edge sections of the elevators to detect
loose leading edges and to ensure that there is no gap between the
sections and the front spar, and corrective actions if necessary. This
AD also requires determining the type of leading edge installed on the
elevators. For certain airplanes, this AD requires repetitive
inspections until the modification of the leading edge sections of the
elevators and the application of sealant, which would end the
repetitive inspections. This AD results from reports that the leading
edges of the elevators were found loose, although the fasteners were
still in place; in one case a stud was broken. In addition, the
fastener attachment holes were elongated and worn out, and fretting
damage was found on the elevator front spar and balance weights.
Investigation revealed that vibration, induced by the propeller
slipstream, was the cause of these discrepancies; the stud failure was
due to improper installation of the fasteners. We are issuing this AD
to prevent jamming, restricting, or binding of the elevators due to
loose or missing fasteners, which could make the movement of the
elevator difficult and decrease aerodynamic control of the airplane.

DATES: This AD becomes effective September 6, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 6,
2006.
We must receive comments on this AD by October 23, 2006.

ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow

the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your

comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep,
the Netherlands, for service information identified in this AD.

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:

Discussion

The Civil Aviation Authority--The Netherlands (CAA-NL), which is
the airworthiness authority for the Netherlands, notified us that an
unsafe condition may exist on Fokker Model F27 Mark 050 airplanes. The
CAA-NL advises that the leading edges of the elevators were found
loose, although the fasteners were still in place; in one case a stud
was broken. In addition, the fastener attachment holes were elongated
and worn out, and fretting damage was found on the elevator front spar
and balance weights. Investigation revealed that vibration, induced by
the propeller slipstream, was the cause of these discrepancies; the
stud failure was due to improper installation of the fasteners. Due to
initial play in the attachment holes and at the lip of the free end of
each leading edge section, some movement of the leading edge sections
over the front spar can occur, causing the fretting of the front spar
and elongation of the fastener attachment holes. These conditions, if
not corrected, could result in jamming, restricting, or binding of the
elevators due to loose or missing fasteners, which could make the
movement of the elevator difficult and decrease aerodynamic control of
the airplane.

Relevant Service Information

Fokker Services B.V. has issued Service Bulletins SBF50-55-012 and
SBF50-55-013, both dated October 11, 2004.
Service Bulletin SBF50-55-012 describes procedures for inspecting
the leading edge sections of the elevators to detect loose leading
edges and to ensure that there is no gap between the sections and the
front spar, and corrective actions if necessary. The corrective actions
include, among other things, installing an additional washer under the
nut if the nut reaches the end of the screw thread on the stud, or
installing the stud deeper in the elevator front spar. The service
bulletin also describes procedures for determining the type of leading
edge installed on the elevators.
Service Bulletin SBF50-55-013 describes procedures for modifying
the leading edge sections of the elevators and applying sealant, which
would eliminate the need for the repetitive inspections. The
modification includes, among other things, inspecting the gap between
the nose of the leading edge and the horizontal stabilizer to assure it
meets the minimum measurement. If the gap is too small, the service
bulletin describes corrective actions to enlarge the gap.
Accomplishing the actions specified in Service Bulletins SBF50-55-
012 and SBF50-55-013 is intended to adequately address the unsafe
condition. The CAA-NL mandated the service information and issued Dutch
airworthiness directive NL-2005-001, dated March 23, 2005, to ensure
the continued airworthiness of these airplanes in the Netherlands.
Service Bulletin SBF50-55-013 refers to Fokker Component Service
Bulletins

[[Page 48794]]

F3203-010-55-01 and F3203-011-55-02, both dated October 11, 2004, as
additional sources of service information for modifying the leading
edge sections of the elevators and applying sealant.

FAA's Determination and Requirements of this AD

This airplane model is manufactured in the Netherlands and is 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. As described in 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 we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are issuing this AD to prevent jamming, restricting,
or binding of the elevator control surfaces due to loose or missing
fasteners, which could make the movement of the elevator difficult and
decrease aerodynamic control of the airplane. This AD requires
accomplishing the actions specified in the service information
described previously.

Clarification of Inspection Type

In this AD, the ``inspection'' required by the Dutch airworthiness
directive is referred to as a ``detailed inspection.'' We have included
the definition for a detailed inspection in a note in the AD.

Costs of Compliance

None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the following costs would apply:
The required inspection would take about 1 work hour per airplane,
at an average labor rate of $80 per work hour. Based on these figures,
the estimated cost of the inspection would be $80 per airplane, per
inspection cycle.
The required modification and application of sealant would take
about 7 work hours per airplane, at an average labor rate of $80 per
work hour. The manufacturer states that it will supply required parts
at no cost. Based on these figures, the estimated cost of the
modification and sealant would be $560 per airplane.

FAA's Determination of the Effective Date

No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.

Comments Invited

This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
25641; Directorate Identifier 2006-NM-114-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will

also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
http://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office

between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.

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 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 the 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 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, Incorporation by
reference, Safety.

Adoption of the Amendment

0
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:

[[Page 48795]]

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):

2006-17-09 Fokker Services B.V.: Amendment 39-14730. Docket No. FAA-
2006-25641; Directorate Identifier 2006-NM-114-AD.

Effective Date

(a) This AD becomes effective September 6, 2006.

Affected ADs

(b) None.

Applicability

Unsafe Condition

(d) This AD results from reports that the leading edges of the
elevators were found loose, although the fasteners were still in
place; in one case a stud was broken. In addition, the fastener
attachment holes were elongated and worn out, and fretting damage
was found on the elevator front spar and balance weights.
Investigation revealed that vibration, induced by the propeller
slipstream, was the cause of these discrepancies; the stud failure
was due to improper installation of the fasteners. We are issuing
this AD to prevent jamming, restricting, or binding of the elevators
due to loose or missing fasteners, which could make the movement of
the elevator difficult and decrease aerodynamic control of the
airplane.

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.

Inspection/Corrective Actions

(f) For all airplanes: Within 6 months after the effective date
of this AD, do the actions required by paragraphs (f)(1) and (f)(2)
of this AD, in accordance with the Accomplishment Instructions of
Fokker Service Bulletin SBF50-55-012, dated October 11, 2004.
(1) Do a detailed inspection of the leading edge sections of the
elevators to detect loose leading edges and to ensure that there is
no gap between the sections and the front spar, including all
applicable corrective actions. All applicable corrective actions
must be done before further flight.
(2) Determine the type of leading edges installed on the
elevators: If the leading edges are single-type, no further action
is required by this AD. If the leading edges are divided-type,
repeat the inspection required by paragraph (f)(1) of this AD
thereafter at intervals not to exceed 6 months, until the actions
specified in paragraph (g) of this AD have been done.

Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''

Modification

(g) For airplanes equipped with the ``divided type'' elevators:
Within 24 months after the effective date of this AD, modify the
leading edge sections of the elevators and apply sealant (including
doing the inspection of the gap and all applicable corrective
actions), in accordance with the Accomplishment Instructions of
Fokker Service Bulletin SBF50-55-013, dated October 11, 2004. All
applicable corrective actions must be done before further flight.
Accomplishing the actions in this paragraph ends the repetitive
inspections required by paragraph (f)(2) of this AD.

Note 2: Fokker Service Bulletin SBF50-55-013 refers to Fokker
Component Service Bulletins F3203-010-55-01 and F3203-011-55-02,
both dated October 11, 2004, as additional sources of service
information for modifying the leading edge sections of the elevators
and applying sealant.

Alternative Methods of Compliance (AMOCs)

(h)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.

Related Information

(i) Dutch airworthiness directive NL-2005-001, dated March 23,
2005, also addresses the subject of this AD.

Material Incorporated by Reference

(j) You must use Fokker Service Bulletin SBF50-55-012, dated
October 11, 2004; and Fokker Service Bulletin SBF50-55-013, dated
October 11, 2004; as applicable; to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-
Vennep, the Netherlands, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or

at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.

Issued in Renton, Washington, on August 11, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-13731 Filed 8-21-06; 8:45 am]

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