Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes, 17594-17596 [05-6687]
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17594
Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
Corrective Action
(h) If, during any inspection specified in
paragraph (f) or (g) of this AD, P/N 31077–
050, –060, –070, –110, or –112 is found or
if unable to determine the P/N, before further
flight, replace the spoiler servo control with
a new or modified spoiler servo control, in
accordance with Airbus Service Bulletin
A320–27–1158 or A320–27–1159; both
Revision 01; both excluding Appendices 01
and 02; both dated September 3, 2004; as
applicable.
Note 2: Airbus Service Bulletins A320–27–
1158, Revision 01; and A320–27–1159,
Revision 01; refer to Goodrich Service
Bulletin 31077–27–14, dated May 24, 2004;
as an additional source of service information
for modifying the spoiler servo control.
Actions Accomplished Per Previous Issues of
Service Information
(i) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A320–27–1158; or
Airbus Service Bulletin A320–27–1159; both
excluding Appendices 01 and 02; both dated
May 26, 2004; are considered acceptable for
compliance with the corresponding actions
required by this AD.
Reporting Not Required
(j) Although Airbus Service Bulletin A320–
27–1158, Revision 01, dated September 3,
2004; and Airbus Service Bulletin A320–27–
1159, Revision 01, dated September 3, 2004;
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
Parts Installation
(k) As of the effective date of this AD, no
person may install a spoiler servo control, P/
N 31077–050, –060, –070, –110, or –112, on
any airplane, unless it has been modified
according to Airbus Service Bulletin A320–
27–1158 or A320–27–1159; both Revision 01;
both excluding Appendices 01 and 02; both
dated September 3, 2004.
Alternative Methods of Compliance
(AMOCs)
(l) 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.
Related Information
(m) French airworthiness directive F–
2004–122, dated July 21, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(n) You must use Airbus Service Bulletin
A320–27–1158, Revision 01, excluding
Appendices 01 and 02, dated September 3,
2004; and Airbus Service Bulletin A320–27–
1159, Revision 01, excluding Appendices 01
and 02, dated September 3, 2004; as
applicable; to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approves the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
VerDate jul<14>2003
20:15 Apr 06, 2005
Jkt 205001
get copies of the service information, go to
Airbus, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France. To view the
AD docket go to the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW, room PL–401, Nassif
Building, Washington, DC. To review copies
of the service information, go to the National
Archives and Records Administration
(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 March
24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6685 Filed 4–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20222; Directorate
Identifier 2004–NM–230–AD; Amendment
39–14041; AD 2005–07–17]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–102, –103,
–106, –201, –202, –301, –311, and–315
airplanes. This AD requires revising the
airplane flight manual to include
applicable procedures to follow when
the flightcrew receives abnormal
indications of airspeed, altitude, or
vertical airspeed. This AD also requires
modifying the static system. This AD is
prompted by a report of a leak in the
static pressure system, which could
result in loss of the static systems and
consequent erroneous data displayed on
the pilot’s flight instruments. We are
issuing this AD to advise the flightcrew
of applicable procedures in the event of
abnormal indications of airspeed,
altitude, or vertical airspeed; and to
prevent leaks in the static system, which
could result in the loss of critical flight
information that could result in reduced
controllability of the airplane or
controlled flight into terrain.
DATES: This AD becomes effective May
12, 2005.
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of May 12, 2005.
ADDRESSES: For service information
identified in this AD, contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can 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 U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20222; the directorate
identifier for this docket is 2004–NM–
230–AD.
FOR FURTHER INFORMATION CONTACT: Ezra
Sasson, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, suite 410,
Westbury, New York 11590; telephone
(516) 228–7320; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Bombardier Model
DHC–8–102, –103, –106, –201, –202,
–301, –311, and –315 airplanes. That
action, published in the Federal
Register on February 1, 2005 (70 FR
5078), proposed to require revising the
airplane flight manual (AFM) to include
applicable procedures to follow when
the flightcrew receives abnormal
indications of airspeed, altitude, or
vertical airspeed. That action also
proposed to require modifying the static
system.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
E:\FR\FM\07APR1.SGM
07APR1
Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
17595
ESTIMATED COSTS
Average
labor rate
per hour
Work
hours
Action
Revise AFM .............................
Modify static system ................
1
2
$65
65
Cost per
airplane
Parts
None ........................................
100–200 ...................................
Authority for This Rulemaking
Adoption of the Amendment
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.
I
Regulatory Findings
Affected ADs
(b) None.
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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. 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.
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20:15 Apr 06, 2005
Jkt 205001
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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 airworthiness
directive (AD):
I
2005–07–17 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14041.
Docket No. FAA–2005–20222;
Directorate Identifier 2004–NM–230–AD.
Effective Date
(a) This AD becomes effective May 12,
2005.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, –106, –201, –202, –301,
–311, and –315 airplanes, certificated in any
category; serial numbers 003 through 598
inclusive.
Unsafe Condition
(d) This AD was prompted by a report of
a leak in the static pressure system, which
could result in loss of the static systems and
consequent erroneous data displayed on the
pilot’s flight instruments. We are issuing this
AD to advise the flightcrew of applicable
procedures in the event of abnormal
indications of airspeed, altitude, or vertical
airspeed; and to prevent leaks in the static
system, which could result in the loss of
critical flight information that could result in
reduced controllability of the airplane or
controlled flight into terrain.
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.
Revision to Airplane Flight Manual
(f) Within 10 days after the effective date
of this AD, revise the Normal and Abnormal
Procedures sections of the applicable de
Havilland Dash 8 Flight Manual to include
the following statement in paragraph 4.11.1
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
$65
230–330
Number of
U.S.-registered
airplanes
181
181
Fleet cost
$11,765
41,630–59,730
of 4.11 Pitot—Static and Stall Warning
System Failures. This may be done by
inserting a copy of this AD into the
applicable flight manual.
‘‘4.11.1 ABNORMAL INDICATIONS OF
AIRSPEED, ALTITUDE AND VERTICAL
AIRSPEED.
1. Appropriate STATIC SOURCE selector—
ALTERNATE. If switching the STATIC
SOURCE selector to ALTERNATE does not
correct the abnormal indications:
2. Rely on the flight instruments on the
opposite side and land as soon as
practicable.’’
Note 1: When a statement identical to that
in paragraph (f) of this AD has been included
in the general revisions of the applicable
flight manual, the general revisions may be
inserted into the flight manual, and the copy
of this AD may be removed from the flight
manual.
Modification of the Static System
(g) For airplanes having serial numbers 003
through 590 inclusive: Within 24 months
after the effective date of this AD, modify the
static system in accordance with Part A and
Part C of the Accomplishment Instructions of
Bombardier Service Bulletin 8–34–221,
Revision ‘A,’ dated September 15, 2003.
(h) For airplanes having serial numbers 591
through 598 inclusive: Within 24 months
after the effective date of this AD, modify the
static system in accordance with Part B and
Part C of the Accomplishment Instructions of
Bombardier Service Bulletin 8–34–221,
Revision ‘A,’ dated September 15, 2003.
Modifications Done According to Previous
Issue of Service Bulletin
(i) Modifications done before the effective
date of this AD in accordance with
Bombardier Service Bulletin 8–34–221, dated
May 27, 2003, are acceptable for compliance
with the applicable modifications specified
in paragraphs (g) and (h) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, New York Aircraft
Certification Office, 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.
Related Information
(k) Canadian airworthiness directive CF–
2003–25, dated October 10, 2003, also
addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Bombardier Service
Bulletin 8–34–221, Revision ‘A,’ dated
September 15, 2003, to perform the actions
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07APR1
17596
Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
that are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approves the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada. To
view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to 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: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March
24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6687 Filed 4–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18997; Directorate
Identifier 2004–NM–19–AD; Amendment 39–
14036; AD 2005–07–12]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
This AD requires repetitive detailed and
eddy current inspections to detect
cracking of the frame web around the
cutout for the doorstop intercostal strap
at the aft side of the body station 291.5
frame at stringer 16R, and corrective
actions if necessary. This AD is
prompted by reports of fatigue cracks in
the web of the body station 291.5 frame
near the forward galley door. We are
issuing this AD to detect and correct
fatigue cracking of the aft frame and
frame support structure of the forward
galley door, which could result in a
severed fuselage frame web, rapid
decompression of the airplane, and
possible loss of the forward galley door.
VerDate jul<14>2003
20:15 Apr 06, 2005
Jkt 205001
This AD becomes effective May
12, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of May 12, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can 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 U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–18997; the directorate
identifier for this docket is 2004–NM–
19–AD.
FOR FURTHER INFORMATION CONTACT:
Howard Hall, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6430; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR Part 39 with
an AD for certain Boeing Model 737–
100, –200, –200C, –300, –400, and –500
series airplanes. That action, published
in the Federal Register on September 3,
2004 (69 FR 53858), proposed to require
repetitive detailed and eddy current
inspections to detect cracking of the
frame web around the cutout for the
doorstop intercostal strap at the aft side
of the body station 291.5 frame at
stringer 16R, and corrective actions if
necessary.
DATES:
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Request To Delay Issuing AD
Several commenters note that the
proposed AD does not provide a
terminating action for the repetitive
inspections specified in the proposed
AD. Two commenters suggest that a
terminating action be included in either
the final AD action or in the instructions
of the structural inspection document.
One commenter requests that the FAA
delay issuing the final AD action until
Boeing Alert Service Bulletin 737–
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
53A1241, dated June 13, 2002, has been
revised to include a terminating
modification. (That service bulletin was
referenced in the proposed AD as the
appropriate source of service
information for accomplishing the
repetitive inspections.) One commenter
states that the proposed repetitive
intervals will allow enough time for
accomplishment of the inspections
during its fleet’s heavy maintenance
visits, but that it would be helpful if
terminating action instructions were
provided.
We agree that a terminating action for
the repetitive inspections would benefit
operators. The airplane manufacturer is
currently developing a terminating
action. Once the proposed terminating
action has been submitted to us for
review, and we have approved the
proposed action as terminating action
for the requirements of the AD, anyone
may use that terminating action as an
alternative method of compliance
(AMOC) under the provisions of
paragraph (h) of this AD. We do not
agree that we should delay issuing this
AD until a terminating action is
developed. We have determined that an
unsafe condition exists, and we do not
have any technical justification for
delaying the release of this AD. We have
not changed this AD regarding this
issue.
One commenter requests that
operators be allowed to review the
additional service history information
referenced in the proposed AD before
the FAA issues the final AD action. The
commenter states that it has requested
that Boeing disseminate that additional
history information to all operators. The
commenter notes that the initial
inspection threshold specified in the
proposed AD is 20 percent lower than
the threshold specified in Boeing Alert
Service Bulletin 737–53A1241. The
commenter concludes that the
additional history information had an
obvious impact on the FAA’s decision
to include a lowered initial inspection
threshold in the proposed AD.
We agree with the intent of the
commenter’s request. As stated in the
‘‘Differences Between the Proposed AD
and Service Bulletin’’ section of the
proposed AD, the service bulletin
includes an initial inspection threshold
of 50,000 total flight cycles, and the
proposed AD includes an initial
inspection threshold of 40,000 total
flight cycles. The threshold specified in
the service bulletin is based on the first
two reported cracks, which were found
on an airplane that had accumulated
more than 54,000 total flight cycles.
After the release of the service bulletin,
a subsequent crack was reported on an
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]]>Agencies
[Federal Register Volume 70, Number 66 (Thursday, April 7, 2005)]
[Rules and Regulations]
[Pages 17594-17596]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6687]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20222; Directorate Identifier 2004-NM-230-AD;
Amendment 39-14041; AD 2005-07-17]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311,
and-315 airplanes. This AD requires revising the airplane flight manual
to include applicable procedures to follow when the flightcrew receives
abnormal indications of airspeed, altitude, or vertical airspeed. This
AD also requires modifying the static system. This AD is prompted by a
report of a leak in the static pressure system, which could result in
loss of the static systems and consequent erroneous data displayed on
the pilot's flight instruments. We are issuing this AD to advise the
flightcrew of applicable procedures in the event of abnormal
indications of airspeed, altitude, or vertical airspeed; and to prevent
leaks in the static system, which could result in the loss of critical
flight information that could result in reduced controllability of the
airplane or controlled flight into terrain.
DATES: This AD becomes effective May 12, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of May
12, 2005.
ADDRESSES: For service information identified in this AD, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can 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 U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20222; the directorate
identifier for this docket is 2004-NM-230-AD.
FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7320; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Bombardier Model DHC-8-102, -103, -106, -201, -
202, -301, -311, and -315 airplanes. That action, published in the
Federal Register on February 1, 2005 (70 FR 5078), proposed to require
revising the airplane flight manual (AFM) to include applicable
procedures to follow when the flightcrew receives abnormal indications
of airspeed, altitude, or vertical airspeed. That action also proposed
to require modifying the static system.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the proposed
AD or on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
[[Page 17595]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average Number of U.S.-
Action Work labor rate Parts Cost per registered Fleet cost
hours per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Revise AFM................................... 1 $65 None............................ $65 181 $11,765
Modify static system......................... 2 65 100-200......................... 230-330 181 41,630-59,730
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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. 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:
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 airworthiness
directive (AD):
2005-07-17 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14041. Docket No. FAA-2005-20222; Directorate Identifier 2004-NM-
230-AD.
Effective Date
(a) This AD becomes effective May 12, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes, certificated in any
category; serial numbers 003 through 598 inclusive.
Unsafe Condition
(d) This AD was prompted by a report of a leak in the static
pressure system, which could result in loss of the static systems
and consequent erroneous data displayed on the pilot's flight
instruments. We are issuing this AD to advise the flightcrew of
applicable procedures in the event of abnormal indications of
airspeed, altitude, or vertical airspeed; and to prevent leaks in
the static system, which could result in the loss of critical flight
information that could result in reduced controllability of the
airplane or controlled flight into terrain.
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.
Revision to Airplane Flight Manual
(f) Within 10 days after the effective date of this AD, revise
the Normal and Abnormal Procedures sections of the applicable de
Havilland Dash 8 Flight Manual to include the following statement in
paragraph 4.11.1 of 4.11 Pitot--Static and Stall Warning System
Failures. This may be done by inserting a copy of this AD into the
applicable flight manual.
``4.11.1 ABNORMAL INDICATIONS OF AIRSPEED, ALTITUDE AND VERTICAL
AIRSPEED.
1. Appropriate STATIC SOURCE selector--ALTERNATE. If switching
the STATIC SOURCE selector to ALTERNATE does not correct the
abnormal indications:
2. Rely on the flight instruments on the opposite side and land
as soon as practicable.''
Note 1: When a statement identical to that in paragraph (f) of
this AD has been included in the general revisions of the applicable
flight manual, the general revisions may be inserted into the flight
manual, and the copy of this AD may be removed from the flight
manual.
Modification of the Static System
(g) For airplanes having serial numbers 003 through 590
inclusive: Within 24 months after the effective date of this AD,
modify the static system in accordance with Part A and Part C of the
Accomplishment Instructions of Bombardier Service Bulletin 8-34-221,
Revision `A,' dated September 15, 2003.
(h) For airplanes having serial numbers 591 through 598
inclusive: Within 24 months after the effective date of this AD,
modify the static system in accordance with Part B and Part C of the
Accomplishment Instructions of Bombardier Service Bulletin 8-34-221,
Revision `A,' dated September 15, 2003.
Modifications Done According to Previous Issue of Service Bulletin
(i) Modifications done before the effective date of this AD in
accordance with Bombardier Service Bulletin 8-34-221, dated May 27,
2003, are acceptable for compliance with the applicable
modifications specified in paragraphs (g) and (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(j) The Manager, New York Aircraft Certification Office,
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.
Related Information
(k) Canadian airworthiness directive CF-2003-25, dated October
10, 2003, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Bombardier Service Bulletin 8-34-221, Revision
`A,' dated September 15, 2003, to perform the actions
[[Page 17596]]
that are required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approves the incorporation by
reference of this document in accordance with 5 U.S.C. 552(a) and 1
CFR part 51. To get copies of the service information, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada. To view the AD
docket, go to the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, go to 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: https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.
Issued in Renton, Washington, on March 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6687 Filed 4-6-05; 8:45 am]
BILLING CODE 4910-13-P
