Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes, 30072-30074 [E6-8009]
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30072
Federal Register / Vol. 71, No. 101 / Thursday, May 25, 2006 / Proposed Rules
flight manual (AFM) of the affected airplanes
by incorporating the information in the TAs
into the product support manuals (PSM)
listed in Table 1 of this AD. This may be
accomplished by inserting a copy of the
applicable TA into the AFM. The copy of the
TA may be removed from the AFM when a
new revision of the AFM is released that
incorporates material identical to the content
of the TA.
TABLE 1.—BOMBARDIER TEMPORARY AMENDMENTS (TAS)
Airplane model/AFM No.
PSM
102, 103, and 106 .............................................................................................................
102NS, 103NS, and 106NS ..............................................................................................
201 .....................................................................................................................................
202 .....................................................................................................................................
201S and 202S ..................................................................................................................
202HT ................................................................................................................................
301 .....................................................................................................................................
311 .....................................................................................................................................
315 .....................................................................................................................................
1–81–1A
1–81–1A
1–82–1A
1–82–1A
1–82–1A
1–82–1A
1–83–1A
1–83–1A
1–83–1A
Note 1: The suffixes ‘‘NS,’’ ‘‘S,’’ and ‘‘HT,’’
do not indicate separate airplane models; for
example, a Model 102NS airplane is a Model
102 airplane.
DEPARTMENT OF TRANSPORTATION
Inspection and Corrective Actions
14 CFR Part 39
(g) Within 6,000 flight hours or 36 months
after the effective date of this AD, whichever
occurs first, perform a one-time general
visual inspection for non-conforming chain
links of the trim chain/chain assemblies of
the elevator trim system and gust lock system
and, before further flight, do applicable
corrective actions, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–27–105, Revision ‘A,’
dated September 13, 2005. After
accomplishing the requirements of this
paragraph, operators may remove the AFM
revisions required by paragraph (f) of this AD
from the AFM.
[Docket No. FAA–2006–24868; Directorate
Identifier 2006–NM–103–AD]
Parts Installation
(h) As of the effective date of this AD, no
person may install an elevator trim chain/
chain assembly on any airplane, unless the
chain links of that trim chain/chain assembly
are identified with the number RC–25.
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Fokker Model F.28 Mark 0070 and 0100
airplanes. This proposed AD would
require modification of the wiring
distribution of the alternating current
bus transfer power system and the righthand and left-hand windshield antiicing system, as necessary. This
proposed AD results from a report of
electrical sparks coming out of the flight
deck from a panel behind the left seat.
We are proposing this AD to prevent
failure of the sliding window heating
element(s), due to electrical overload,
which could result in smoke and fire in
the cockpit.
DATES: We must receive comments on
this proposed AD by June 26, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, New York Aircraft
Certification Office, 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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
jlentini on PROD1PC65 with PROPOSAL
Related Information
(j) Canadian airworthiness directive CF–
2005–38, dated October 25, 2005, also
addresses the subject of this AD.
Issued in Renton, Washington, on May 17,
2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–8008 Filed 5–24–06; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:43 May 24, 2006
Jkt 208001
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and 0100
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
PO 00000
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Fmt 4702
Sfmt 4702
TA No.
Effective date
9
8
11
10
9
8
8
15
9
January 28, 2004.
January 28, 2004.
June 22, 2005.
January 28, 2004.
June 22, 2005.
January 28, 2004.
January 28, 2004.
January 28, 2004.
January 28, 2004.
• 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.,
Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the
Netherlands, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–24868; Directorate
Identifier 2006–NM–103–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
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 proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
E:\FR\FM\25MYP1.SGM
25MYP1
30073
Federal Register / Vol. 71, No. 101 / Thursday, May 25, 2006 / Proposed Rules
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 https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://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.
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 all Fokker Model
F.28 Mark 0070 and 0100 airplanes. The
CAA–NL advises that, a few minutes
after takeoff, electrical sparks came out
of the flight deck from a panel behind
the left seat, on a Fokker Model F.28
Mark 0070 airplane. The flightcrew also
noticed a strong electrical smell, but no
visible smoke. Investigation revealed
that several contacts of the J 4222A/P
4222B connector were burnt, creating a
conductive path between the contacts of
the left-hand (LH) windshield heating
system and the LH sliding window
heating system. The conductive path
resulted in too high of a voltage on the
LH sliding window, causing the
overheat of the LH sliding window
heating element. Failure of the sliding
window heating element(s), due to
electrical overload, if not corrected,
could result in smoke and fire in the
cockpit.
Relevant Service Information
Fokker Services B.V. has issued
Fokker Service Bulletin SBF100–30–
027, dated May 9, 2005; including
Manual Change Notification—
Maintenance Documentation MCNM
F100–098, dated May 9, 2005; and
including the drawings listed in the
following table. (To conform to certain
Office of the Federal Register
requirements for incorporating these
materials by reference, the table
identifies the date of the service bulletin
for undated drawings.)
DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–30–027
Drawing
jlentini on PROD1PC65 with PROPOSAL
W41043
W41043
W41249
W41249
W41249
W41249
W41249
Sheet
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
The service bulletin describes
procedures for modifying the wiring
distribution of the alternating current
bus transfer power system and the righthand and left-hand windshield antiicing system, as necessary. Specifically,
the service bulletin describes modifying
the following areas:
• For Block A airplanes, in the
passenger compartment ceiling through
receptacle J 2953A/plug P 2953B, zone
267; in the flight compartment ceiling
through receptacle J 4261A/plug P
4261B, zone 259; and in the flight
compartment ceiling through receptacle
J 4222A/plug P 4222B, zone 258.
• For Block B airplanes, in the
electrical power control (EPC) panel 1
through receptacle J 1566A/plug P
1566B, zone 244; and in EPC panel 3
through receptacle J 1590A/plug P
1590B, zone 242.
• For Block C airplanes, in EPC panel
1 through receptacle J 1566A/plug P
1566B, zone 244.
• For Block D airplanes, in EPC panel
3 through receptacle J 1590A/plug P
1590B, zone 242.
• For Block E airplanes, in the
passenger compartment ceiling through
receptacle J 2953A/plug P 2953B, zone
267.
VerDate Aug<31>2005
15:43 May 24, 2006
Jkt 208001
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 Dutch
airworthiness directive NL–2005–009,
dated June 30, 2005, to ensure the
continued airworthiness of these
airplanes in the Netherlands.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models 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 we need to issue an AD
for airplanes of this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require accomplishing the
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Issue
007
008
006
007
008
009
010
Date
H
H
F
F
F
G
G
May
May
May
May
May
May
May
9,
9,
9,
9,
9,
9,
9,
2005.
2005.
2005.
2005.
2005.
2005.
2005.
actions specified in the service
information described previously.
Costs of Compliance
This proposed AD would affect about
10 airplanes of U.S. registry. The
proposed actions would take about 3
work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the proposed AD for U.S. operators is
$2,400, or $240 per airplane.
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
E:\FR\FM\25MYP1.SGM
25MYP1
30074
Federal Register / Vol. 71, No. 101 / Thursday, May 25, 2006 / Proposed Rules
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
Applicability
Air transportation, Aircraft, Aviation
safety, Safety.
(c) This AD applies to all Fokker Model
F.28 Mark 0070 and 0100 airplanes,
certificated in any category.
The Proposed Amendment
Unsafe Condition
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
(d) This AD results from a report of
electrical sparks coming out of the flight deck
from a panel behind the left seat. We are
issuing this AD to prevent failure of the
sliding window heating element(s), due to
electrical overload, which could result in
smoke and fire in the cockpit.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Fokker Services B.V.: Docket No. FAA–
2006–24868; Directorate Identifier 2006–
NM–103–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by June 26, 2006.
Affected ADs
(b) None.
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.
Modification of Wiring Distribution
(f) Within 36 months after the effective
date of this AD, modify the wiring
distribution of the alternating current bus
transfer power system and the right-hand and
left-hand windshield anti-icing system, by
accomplishing all of the actions specified in
the Accomplishment Instructions of Fokker
Service Bulletin SBF100–30–027, dated May
9, 2005, as applicable; including Manual
Change Notification—Maintenance
Documentation MCNM F100–098, dated May
9, 2005; and including the drawings listed in
Table 1 of this AD. (To conform to certain
Office of the Federal Register requirements
for incorporating these materials by
reference, the table identifies the date of the
service bulletin for undated drawings.)
TABLE 1.—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–30–027
Drawing
W41043
W41043
W41249
W41249
W41249
W41249
W41249
Sheet
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
.............................................................................................................................................
Alternative Methods of Compliance
(AMOCs)
(g)(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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on May 17,
2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–8009 Filed 5–24–06; 8:45 am]
BILLING CODE 4910–13–P
jlentini on PROD1PC65 with PROPOSAL
Jkt 208001
H
H
F
F
F
G
G
May
May
May
May
May
May
May
9,
9,
9,
9,
9,
9,
9,
2005.
2005.
2005.
2005.
2005.
2005.
2005.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24877; Directorate
Identifier 2005–NM–253–AD]
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–200B,
747–200C, 747–200F, 747SR, and
747SP Series Airplanes
(h) Dutch airworthiness directive NL–
2005–009, dated June 30, 2005, also
addresses the subject of this AD.
15:43 May 24, 2006
Date
RIN 2120–AA64
Related Information
VerDate Aug<31>2005
007
008
006
007
008
009
010
Issue
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
E:\FR\FM\25MYP1.SGM
25MYP1
]]>Agencies
[Federal Register Volume 71, Number 101 (Thursday, May 25, 2006)]
[Proposed Rules]
[Pages 30072-30074]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-8009]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24868; Directorate Identifier 2006-NM-103-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This proposed
AD would require modification of the wiring distribution of the
alternating current bus transfer power system and the right-hand and
left-hand windshield anti-icing system, as necessary. This proposed AD
results from a report of electrical sparks coming out of the flight
deck from a panel behind the left seat. We are proposing this AD to
prevent failure of the sliding window heating element(s), due to
electrical overload, which could result in smoke and fire in the
cockpit.
DATES: We must receive comments on this proposed AD by June 26, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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., Technical Services Dept., P.O. Box
231, 2150 AE Nieuw-Vennep, the Netherlands, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24868; Directorate Identifier 2006-NM-103-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
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 proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets,
[[Page 30073]]
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
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
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.
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 all Fokker Model F.28 Mark 0070 and 0100
airplanes. The CAA-NL advises that, a few minutes after takeoff,
electrical sparks came out of the flight deck from a panel behind the
left seat, on a Fokker Model F.28 Mark 0070 airplane. The flightcrew
also noticed a strong electrical smell, but no visible smoke.
Investigation revealed that several contacts of the J 4222A/P 4222B
connector were burnt, creating a conductive path between the contacts
of the left-hand (LH) windshield heating system and the LH sliding
window heating system. The conductive path resulted in too high of a
voltage on the LH sliding window, causing the overheat of the LH
sliding window heating element. Failure of the sliding window heating
element(s), due to electrical overload, if not corrected, could result
in smoke and fire in the cockpit.
Relevant Service Information
Fokker Services B.V. has issued Fokker Service Bulletin SBF100-30-
027, dated May 9, 2005; including Manual Change Notification--
Maintenance Documentation MCNM F100-098, dated May 9, 2005; and
including the drawings listed in the following table. (To conform to
certain Office of the Federal Register requirements for incorporating
these materials by reference, the table identifies the date of the
service bulletin for undated drawings.)
Drawings Included in Fokker Service Bulletin SBF100-30-027
----------------------------------------------------------------------------------------------------------------
Drawing Sheet Issue Date
----------------------------------------------------------------------------------------------------------------
W41043........................................ 007 H May 9, 2005.
W41043........................................ 008 H May 9, 2005.
W41249........................................ 006 F May 9, 2005.
W41249........................................ 007 F May 9, 2005.
W41249........................................ 008 F May 9, 2005.
W41249........................................ 009 G May 9, 2005.
W41249........................................ 010 G May 9, 2005.
----------------------------------------------------------------------------------------------------------------
The service bulletin describes procedures for modifying the wiring
distribution of the alternating current bus transfer power system and
the right-hand and left-hand windshield anti-icing system, as
necessary. Specifically, the service bulletin describes modifying the
following areas:
For Block A airplanes, in the passenger compartment
ceiling through receptacle J 2953A/plug P 2953B, zone 267; in the
flight compartment ceiling through receptacle J 4261A/plug P 4261B,
zone 259; and in the flight compartment ceiling through receptacle J
4222A/plug P 4222B, zone 258.
For Block B airplanes, in the electrical power control
(EPC) panel 1 through receptacle J 1566A/plug P 1566B, zone 244; and in
EPC panel 3 through receptacle J 1590A/plug P 1590B, zone 242.
For Block C airplanes, in EPC panel 1 through receptacle J
1566A/plug P 1566B, zone 244.
For Block D airplanes, in EPC panel 3 through receptacle J
1590A/plug P 1590B, zone 242.
For Block E airplanes, in the passenger compartment
ceiling through receptacle J 2953A/plug P 2953B, zone 267.
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 Dutch airworthiness
directive NL-2005-009, dated June 30, 2005, to ensure the continued
airworthiness of these airplanes in the Netherlands.
FAA's Determination and Requirements of the Proposed AD
These airplane models 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
we need to issue an AD for airplanes of this type design that are
certificated for operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously.
Costs of Compliance
This proposed AD would affect about 10 airplanes of U.S. registry.
The proposed actions would take about 3 work hours per airplane, at an
average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the proposed AD for U.S. operators is $2,400, or $240
per airplane.
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
[[Page 30074]]
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.
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
adding the following new airworthiness directive (AD):
Fokker Services B.V.: Docket No. FAA-2006-24868; Directorate
Identifier 2006-NM-103-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by June 26,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model F.28 Mark 0070 and 0100
airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a report of electrical sparks coming
out of the flight deck from a panel behind the left seat. We are
issuing this AD to prevent failure of the sliding window heating
element(s), due to electrical overload, which could result in smoke
and fire in the cockpit.
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.
Modification of Wiring Distribution
(f) Within 36 months after the effective date of this AD, modify
the wiring distribution of the alternating current bus transfer
power system and the right-hand and left-hand windshield anti-icing
system, by accomplishing all of the actions specified in the
Accomplishment Instructions of Fokker Service Bulletin SBF100-30-
027, dated May 9, 2005, as applicable; including Manual Change
Notification--Maintenance Documentation MCNM F100-098, dated May 9,
2005; and including the drawings listed in Table 1 of this AD. (To
conform to certain Office of the Federal Register requirements for
incorporating these materials by reference, the table identifies the
date of the service bulletin for undated drawings.)
Table 1.--Drawings Included in Fokker Service Bulletin SBF100-30-027
----------------------------------------------------------------------------------------------------------------
Drawing Sheet Issue Date
----------------------------------------------------------------------------------------------------------------
W41043........................................ 007 H May 9, 2005.
W41043........................................ 008 H May 9, 2005.
W41249........................................ 006 F May 9, 2005.
W41249........................................ 007 F May 9, 2005.
W41249........................................ 008 F May 9, 2005.
W41249........................................ 009 G May 9, 2005.
W41249........................................ 010 G May 9, 2005.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(g)(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
(h) Dutch airworthiness directive NL-2005-009, dated June 30,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on May 17, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-8009 Filed 5-24-06; 8:45 am]
BILLING CODE 4910-13-P
