Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark 0100 Airplanes, 30749-30752 [E8-11501]
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Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations
Report MDC–92K9145. Accomplishing the
revision in accordance with a later revision
of Report MDC–92K9145 is an acceptable
method of compliance if the revision is
approved by the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA.
Revise the Airworthiness Limitations
(AWLs) Section
(h) For Model 717–200, Model MD–88, and
Model MD–90–30 airplanes: Before
December 16, 2008, revise the AWLs section
of the Instructions for Continued
Airworthiness (ICA) to incorporate the
information specified in Appendixes B, C,
and D of Report MDC–92K9145.
Accomplishing the revision in accordance
with a later revision of Report MDC–92K9145
is an acceptable method of compliance if the
revision is approved by the Manager, Los
Angeles ACO.
No Alternative Inspections, Inspection
Intervals, or Critical Design Configuration
Control Limitations (CDCCLs)
(i) After accomplishing the actions
specified in paragraph (g) or (h) of this AD,
as applicable, no alternative inspections,
inspection intervals, or CDCCLs may be used
unless the inspections, intervals, or CDCCLs
are part of a later revision of Report MDC–
92K9145 that is approved by the Manager,
Los Angeles ACO; or unless the inspections,
intervals, or CDCCLs are approved as an
AMOC in accordance with the procedures
specified in paragraph (k) of this AD.
No Reporting Requirement
(j) Although Report MDC–92K9145
specifies to submit certain information to the
manufacturer, this AD does not require that
action.
pwalker on PROD1PC71 with RULES
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Los Angeles ACO,
FAA, ATTN: Serj Harutunian, Aerospace
Engineer, Propulsion Branch, ANM–140L,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562) 627–
5254; fax (562) 627–5210; has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
Material Incorporated by Reference
(l) You must use the Boeing Twinjet
Special Compliance Items Report, MDC–
92K9145, Revision G, dated June 7, 2007, to
do the actions required by this AD, unless the
AD specifies otherwise.
(1) The document contains the following
errors:
(i) The Index of Page Changes specifies
incorrect revision levels for certain pages.
The revision levels specified on each page
are correct.
(ii) There are three sets of pages (six pages
total) with the same page numbers in
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17:07 May 28, 2008
Jkt 214001
Appendix C (i.e., pages C1 and C2). The first
set of page numbers (i.e., Appendix C title
page and Twinjet Airworthiness Limitation
Instructions (ALIs)) is correct. The second set
of page numbers (i.e., ALI 20–2) is incorrect.
Those pages should be identified as page
numbers C6 and C7 as specified in the Index
of Page Changes. The third set of page
numbers (i.e., ALI 20–3) is also incorrect.
Those pages should be identified as page
numbers C8 and C9 as specified in the Index
of Page Changes.
(iii) None of the pages are dated. The issue
date for each revision is specified in the
Index of Page Changes.
(2) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California
90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–0024).
(4) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at
the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on May 15,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–11502 Filed 5–28–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0231; Directorate
Identifier 2007–NM–218–AD; Amendment
39–15534; AD 2008–11–12]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and Mark 0100
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
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30749
product. The MCAI describes the unsafe
condition as:
To date, there have been at least 10
reported events on Fokker 70 (F28 Mark
0070) and Fokker 100 (F28 Mark 0100)
aircraft where the flight crew manually
overpowered the autopilot, inadvertently
neglecting to disengage the autopilot. * * *
When the autopilot is not disengaged, the
elevator servomotor is overpowered and the
horizontal stabilizer is moved by the
Automatic Flight Control & Augmentation
System (AFCAS) auto-trim in a direction
opposite to the (manual) deflection of the
elevator, causing high elevator control forces.
This condition, if not corrected, could cause
the stabilizer to move to an extreme out-oftrim position, creating the (remote)
possibility of loss of control of the aircraft,
due to the extreme control loads.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective July
3, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 3, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
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
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on March 3, 2008 (73 FR
11366). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
To date, there have been at least 10
reported events on Fokker 70 (F28 Mark
0070) and Fokker 100 (F28 Mark 0100)
aircraft where the flight crew manually
overpowered the autopilot, inadvertently
neglecting to disengage the autopilot.
Detailed investigation of these incidents has
shown that this usually occurs in a high
workload environment that demands
immediate manual control of the aircraft by
the pilot flying, e.g. terrain warning. When
the autopilot is not disengaged, the elevator
servomotor is overpowered and the
horizontal stabilizer is moved by the
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29MYR1
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Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations
Automatic Flight Control & Augmentation
System (AFCAS) auto-trim in a direction
opposite to the (manual) deflection of the
elevator, causing high elevator control forces.
This condition, if not corrected, could cause
the stabilizer to move to an extreme out-oftrim position, creating the (remote)
possibility of loss of control of the aircraft,
due to the extreme control loads. In the
original design of AFCAS, operation of the
control wheel-mounted stabilizer trim
switches has no effect when the autopilot is
engaged. Based on the assumption that
stabilizer trim switches will be operated by
the pilot flying when encountering high
control forces, an Autopilot Disconnect Unit
has been developed that disconnects the
autopilot when the stabilizer trim switches
are operated. Since a potentially unsafe
condition has been identified that may exist
or develop on aircraft of this type design, this
Airworthiness Directive requires the
installation of Autopilot Disconnect Units
and associated wiring changes.
You may obtain further information
by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Correction to Table Information
We have corrected the date of Fokker
Drawing W46143, Sheet 03, Issue K, to
March 7, 2002, in Table 1 of this AD.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We determined that this change will not
increase the economic burden on any
operator or increase the scope of the AD.
pwalker on PROD1PC71 with RULES
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 12 products of U.S. registry. We
VerDate Aug<31>2005
17:07 May 28, 2008
Jkt 214001
also estimate that it will take about 27
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $3,000
per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that 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 AD to the U.S. operators to be
$61,920, or $5,160 per product.
Examining the AD Docket
Authority for This Rulemaking
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); 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.
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You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, 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.
List of Subjects in 14 CFR Part 39
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–11–12 Fokker Services B.V.:
Amendment 39–15534. Docket No.
FAA–2008–0231; Directorate Identifier
2007–NM–218–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 3, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Fokker Model F.28
Mark 0070 and 0100 airplanes, all serial
numbers; certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 22: Auto flight.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
To date, there have been at least 10
reported events on Fokker 70 (F28 Mark
0070) and Fokker 100 (F28 Mark 0100)
aircraft where the flight crew manually
overpowered the autopilot, inadvertently
neglecting to disengage the autopilot.
Detailed investigation of these incidents has
shown that this usually occurs in a high
workload environment that demands
immediate manual control of the aircraft by
the pilot flying, e.g. terrain warning. When
the autopilot is not disengaged, the elevator
E:\FR\FM\29MYR1.SGM
29MYR1
30751
Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations
servomotor is overpowered and the
horizontal stabilizer is moved by the
Automatic Flight Control & Augmentation
System (AFCAS) auto-trim in a direction
opposite to the (manual) deflection of the
elevator, causing high elevator control forces.
This condition, if not corrected, could cause
the stabilizer to move to an extreme out-oftrim position, creating the (remote)
possibility of loss of control of the aircraft,
due to the extreme control loads. In the
original design of AFCAS, operation of the
control wheel-mounted stabilizer trim
switches has no effect when the autopilot is
engaged. Based on the assumption that
stabilizer trim switches will be operated by
the pilot flying when encountering high
control forces, an Autopilot Disconnect Unit
has been developed that disconnects the
autopilot when the stabilizer trim switches
are operated. Since a potentially unsafe
condition has been identified that may exist
or develop on aircraft of this type design, this
Airworthiness Directive requires the
installation of Autopilot Disconnect Units
and associated wiring changes.
Actions and Compliance
(f) Within 36 months after the effective
date of this AD, unless already done, install
autopilot disconnect units and do associated
wiring changes in accordance with Section 3,
‘‘Accomplishment Instructions,’’ of Fokker
Service Bulletin SBF100–22–050, dated April
25, 2006, including the drawings listed in
Table 1 of this AD.
TABLE 1.—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–22–050
Fokker drawing
W41501
W41501
W41501
W41501
W41501
W41501
W41504
W41504
W41504
W41504
W41504
W46140
W46140
W46143
W46143
W46144
W46144
W46912
W46930
W46930
W46932
W59140
W59140
W59140
Sheet
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FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) 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.
Send information to ATTN: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Issue
057
058
059
060
061
062
009
010
011
012
013
27
28
02
03
06
07
01
01
02
01
177
178
221
Date
CQ ............................................................................
CQ ............................................................................
CQ ............................................................................
CQ ............................................................................
CR ............................................................................
CR ............................................................................
K ...............................................................................
K ...............................................................................
J ...............................................................................
L ...............................................................................
L ...............................................................................
AR ............................................................................
AR ............................................................................
K ...............................................................................
K ...............................................................................
R ...............................................................................
S ...............................................................................
D ...............................................................................
Original .....................................................................
E ...............................................................................
D ...............................................................................
GC ............................................................................
GB ............................................................................
GB ............................................................................
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
April 25, 2006.
March 5, 2002.
March 8, 2002.
February 26, 2002.
March 7, 2002.
March 4, 2002.
March 7, 2002.
March 12, 2002.
March 14, 2002.
March 14, 2002.
March 13, 2002.
February 8, 2006.
February 6, 2006.
February 6, 2006.
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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Dutch Airworthiness
Directive NL–2006–010, dated July 14, 2006;
and Fokker Service Bulletin SBF100–22–050,
dated April 25, 2006, including the drawings
listed in Table 1 of this AD, for related
information.
Material Incorporated by Reference
(i) You must use Fokker Service Bulletin
SBF100–22–050, dated April 25, 2006,
including the drawings specified in Table 2
of this AD, to do the actions required by this
AD, unless the AD specifies otherwise.
TABLE 2.—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–22–050
pwalker on PROD1PC71 with RULES
Fokker drawing
W41501
W41501
W41501
W41501
W41501
W41501
W41504
W41504
Sheet
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VerDate Aug<31>2005
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Jkt 214001
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Issue
057
058
059
060
061
062
009
010
Frm 00025
Date
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CQ ............................................................................
CQ ............................................................................
CQ ............................................................................
CR ............................................................................
CR ............................................................................
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K ...............................................................................
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29MYR1
April
April
April
April
April
April
April
April
25,
25,
25,
25,
25,
25,
25,
25,
2006.
2006.
2006.
2006.
2006.
2006.
2006.
2006.
30752
Federal Register / Vol. 73, No. 104 / Thursday, May 29, 2008 / Rules and Regulations
TABLE 2.—DRAWINGS INCLUDED IN FOKKER SERVICE BULLETIN SBF100–22–050—Continued
Fokker drawing
W41504
W41504
W41504
W46140
W46140
W46143
W46143
W46144
W46144
W46912
W46930
W46930
W46932
W59140
W59140
W59140
Sheet
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(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) 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.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on May 14,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–11501 Filed 5–28–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0544; Directorate
Identifier 2008–NM–099–AD; Amendment
39–15535; AD 2008–10–51]
RIN 2120–AA64
Airworthiness Directives; Dornier
Model 328–100 and –300 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
pwalker on PROD1PC71 with RULES
AGENCY:
SUMMARY: This document publishes in
the Federal Register an amendment
adopting airworthiness directive (AD)
2008–10–51 that was sent previously to
VerDate Aug<31>2005
17:07 May 28, 2008
Jkt 214001
Issue
011
012
013
27
28
02
03
06
07
01
01
02
01
177
178
221
Date
J ...............................................................................
L ...............................................................................
L ...............................................................................
AR ............................................................................
AR ............................................................................
K ...............................................................................
K ...............................................................................
R ...............................................................................
S ...............................................................................
D ...............................................................................
Original .....................................................................
E ...............................................................................
D ...............................................................................
GC ............................................................................
GB ............................................................................
GB ............................................................................
April 25, 2006.
April 25, 2006.
April 25, 2006.
March 5, 2002.
March 8, 2002.
February 26, 2002.
March 7, 2002.
March 4, 2002.
March 7, 2002.
March 12, 2002.
March 14, 2002.
March 14, 2002.
March 13, 2002.
February 8, 2006.
February 6, 2006.
February 6, 2006.
all known U.S. owners and operators of
all Dornier Model 328–100 and –300
airplanes by individual notices. This AD
requires detailed visual and eddy
current inspections of both the left-hand
and right-hand lower wing panel of the
rear trailing edge (inboard and outboard
of flap lever arm 1 (rib 3 and rib 5)) for
cracks, and repair if necessary. This AD
is prompted by cracks found in the
lower wing panel of the rear trailing
edge (inboard and outboard of flap lever
arm 1 (rib 5)) during a routine
inspection on a Model 328–100
airplane. Subsequent inspection of the
other Model 328–100 airplanes in the
same fleet revealed several more
airplanes with cracks at the same
location. We are issuing this AD to
prevent structural failure of the affected
wing panel, possible separation of the
wing from the airplane, and consequent
loss of control of the airplane.
DATES: This AD becomes effective June
3, 2008 to all persons except those
persons to whom it was made
immediately effective by emergency AD
2008–10–51, issued May 8, 2008, which
contained the requirements of this
amendment.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of June 3, 2008.
We must receive comments on this
AD by July 28, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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.
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• 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 328 Support Services
GmbH, P.O. Box 1252, D–82231
Wessling, Federal Republic of Germany.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 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:
Mike Borfitz, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2677; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: On May 8,
2008, we issued emergency AD 2008–
10–51, which applies to all Dornier
Model 328–100 and –300 airplanes.
Background
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, notified the FAA that an
unsafe condition may exist on all
Dornier Model 328–100 and –300
airplanes. The EASA advises that,
during a routine inspection, cracks were
found in the lower wing panel of the
E:\FR\FM\29MYR1.SGM
29MYR1
]]>Agencies
[Federal Register Volume 73, Number 104 (Thursday, May 29, 2008)]
[Rules and Regulations]
[Pages 30749-30752]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-11501]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0231; Directorate Identifier 2007-NM-218-AD;
Amendment 39-15534; AD 2008-11-12]
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: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
To date, there have been at least 10 reported events on Fokker
70 (F28 Mark 0070) and Fokker 100 (F28 Mark 0100) aircraft where the
flight crew manually overpowered the autopilot, inadvertently
neglecting to disengage the autopilot. * * * When the autopilot is
not disengaged, the elevator servomotor is overpowered and the
horizontal stabilizer is moved by the Automatic Flight Control &
Augmentation System (AFCAS) auto-trim in a direction opposite to the
(manual) deflection of the elevator, causing high elevator control
forces. This condition, if not corrected, could cause the stabilizer
to move to an extreme out-of-trim position, creating the (remote)
possibility of loss of control of the aircraft, due to the extreme
control loads.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective July 3, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 3,
2008.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on March 3, 2008 (73 FR
11366). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
To date, there have been at least 10 reported events on Fokker
70 (F28 Mark 0070) and Fokker 100 (F28 Mark 0100) aircraft where the
flight crew manually overpowered the autopilot, inadvertently
neglecting to disengage the autopilot. Detailed investigation of
these incidents has shown that this usually occurs in a high
workload environment that demands immediate manual control of the
aircraft by the pilot flying, e.g. terrain warning. When the
autopilot is not disengaged, the elevator servomotor is overpowered
and the horizontal stabilizer is moved by the
[[Page 30750]]
Automatic Flight Control & Augmentation System (AFCAS) auto-trim in
a direction opposite to the (manual) deflection of the elevator,
causing high elevator control forces. This condition, if not
corrected, could cause the stabilizer to move to an extreme out-of-
trim position, creating the (remote) possibility of loss of control
of the aircraft, due to the extreme control loads. In the original
design of AFCAS, operation of the control wheel-mounted stabilizer
trim switches has no effect when the autopilot is engaged. Based on
the assumption that stabilizer trim switches will be operated by the
pilot flying when encountering high control forces, an Autopilot
Disconnect Unit has been developed that disconnects the autopilot
when the stabilizer trim switches are operated. Since a potentially
unsafe condition has been identified that may exist or develop on
aircraft of this type design, this Airworthiness Directive requires
the installation of Autopilot Disconnect Units and associated wiring
changes.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Correction to Table Information
We have corrected the date of Fokker Drawing W46143, Sheet 03,
Issue K, to March 7, 2002, in Table 1 of this AD.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the change described
previously. We determined that this change will not increase the
economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 12 products of U.S.
registry. We also estimate that it will take about 27 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will cost about $3,000
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that 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 AD to the
U.S. operators to be $61,920, or $5,160 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, 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.
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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2008-11-12 Fokker Services B.V.: Amendment 39-15534. Docket No. FAA-
2008-0231; Directorate Identifier 2007-NM-218-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 3,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Fokker Model F.28 Mark 0070 and 0100
airplanes, all serial numbers; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 22: Auto
flight.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
To date, there have been at least 10 reported events on Fokker
70 (F28 Mark 0070) and Fokker 100 (F28 Mark 0100) aircraft where the
flight crew manually overpowered the autopilot, inadvertently
neglecting to disengage the autopilot. Detailed investigation of
these incidents has shown that this usually occurs in a high
workload environment that demands immediate manual control of the
aircraft by the pilot flying, e.g. terrain warning. When the
autopilot is not disengaged, the elevator
[[Page 30751]]
servomotor is overpowered and the horizontal stabilizer is moved by
the Automatic Flight Control & Augmentation System (AFCAS) auto-trim
in a direction opposite to the (manual) deflection of the elevator,
causing high elevator control forces. This condition, if not
corrected, could cause the stabilizer to move to an extreme out-of-
trim position, creating the (remote) possibility of loss of control
of the aircraft, due to the extreme control loads. In the original
design of AFCAS, operation of the control wheel-mounted stabilizer
trim switches has no effect when the autopilot is engaged. Based on
the assumption that stabilizer trim switches will be operated by the
pilot flying when encountering high control forces, an Autopilot
Disconnect Unit has been developed that disconnects the autopilot
when the stabilizer trim switches are operated. Since a potentially
unsafe condition has been identified that may exist or develop on
aircraft of this type design, this Airworthiness Directive requires
the installation of Autopilot Disconnect Units and associated wiring
changes.
Actions and Compliance
(f) Within 36 months after the effective date of this AD, unless
already done, install autopilot disconnect units and do associated
wiring changes in accordance with Section 3, ``Accomplishment
Instructions,'' of Fokker Service Bulletin SBF100-22-050, dated
April 25, 2006, including the drawings listed in Table 1 of this AD.
Table 1.--Drawings Included in Fokker Service Bulletin SBF100-22-050
----------------------------------------------------------------------------------------------------------------
Fokker drawing Sheet Issue Date
----------------------------------------------------------------------------------------------------------------
W41501............................... 057 CQ..................... April 25, 2006.
W41501............................... 058 CQ..................... April 25, 2006.
W41501............................... 059 CQ..................... April 25, 2006.
W41501............................... 060 CQ..................... April 25, 2006.
W41501............................... 061 CR..................... April 25, 2006.
W41501............................... 062 CR..................... April 25, 2006.
W41504............................... 009 K...................... April 25, 2006.
W41504............................... 010 K...................... April 25, 2006.
W41504............................... 011 J...................... April 25, 2006.
W41504............................... 012 L...................... April 25, 2006.
W41504............................... 013 L...................... April 25, 2006.
W46140............................... 27 AR..................... March 5, 2002.
W46140............................... 28 AR..................... March 8, 2002.
W46143............................... 02 K...................... February 26, 2002.
W46143............................... 03 K...................... March 7, 2002.
W46144............................... 06 R...................... March 4, 2002.
W46144............................... 07 S...................... March 7, 2002.
W46912............................... 01 D...................... March 12, 2002.
W46930............................... 01 Original............... March 14, 2002.
W46930............................... 02 E...................... March 14, 2002.
W46932............................... 01 D...................... March 13, 2002.
W59140............................... 177 GC..................... February 8, 2006.
W59140............................... 178 GB..................... February 6, 2006.
W59140............................... 221 GB..................... February 6, 2006.
----------------------------------------------------------------------------------------------------------------
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) 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. Send information to ATTN: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116, FAA,
Transport Airplane Directorate, 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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI Dutch Airworthiness Directive NL-2006-010,
dated July 14, 2006; and Fokker Service Bulletin SBF100-22-050,
dated April 25, 2006, including the drawings listed in Table 1 of
this AD, for related information.
Material Incorporated by Reference
(i) You must use Fokker Service Bulletin SBF100-22-050, dated
April 25, 2006, including the drawings specified in Table 2 of this
AD, to do the actions required by this AD, unless the AD specifies
otherwise.
Table 2.--Drawings Included in Fokker Service Bulletin SBF100-22-050
----------------------------------------------------------------------------------------------------------------
Fokker drawing Sheet Issue Date
----------------------------------------------------------------------------------------------------------------
W41501............................... 057 CQ..................... April 25, 2006.
W41501............................... 058 CQ..................... April 25, 2006.
W41501............................... 059 CQ..................... April 25, 2006.
W41501............................... 060 CQ..................... April 25, 2006.
W41501............................... 061 CR..................... April 25, 2006.
W41501............................... 062 CR..................... April 25, 2006.
W41504............................... 009 K...................... April 25, 2006.
W41504............................... 010 K...................... April 25, 2006.
[[Page 30752]]
W41504............................... 011 J...................... April 25, 2006.
W41504............................... 012 L...................... April 25, 2006.
W41504............................... 013 L...................... April 25, 2006.
W46140............................... 27 AR..................... March 5, 2002.
W46140............................... 28 AR..................... March 8, 2002.
W46143............................... 02 K...................... February 26, 2002.
W46143............................... 03 K...................... March 7, 2002.
W46144............................... 06 R...................... March 4, 2002.
W46144............................... 07 S...................... March 7, 2002.
W46912............................... 01 D...................... March 12, 2002.
W46930............................... 01 Original............... March 14, 2002.
W46930............................... 02 E...................... March 14, 2002.
W46932............................... 01 D...................... March 13, 2002.
W59140............................... 177 GC..................... February 8, 2006.
W59140............................... 178 GB..................... February 6, 2006.
W59140............................... 221 GB..................... February 6, 2006.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) 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.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Renton, Washington, on May 14, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-11501 Filed 5-28-08; 8:45 am]
BILLING CODE 4910-13-P
