Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -106 Airplanes, and Model DHC-8-200 and DHC-8-300 Series Airplanes, 56856-56859 [06-8226]
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Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
Instructions of Airbus Service Bulletin A320–
25–1394, Revision 01, dated December 12,
2005. If the stiff part of the girt or the girt bar
position is incorrect, before further flight,
repair in accordance with the service
bulletin.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(g) Inspecting and repairing if necessary
before the effective date of this AD in
accordance with Airbus Service Bulletin
A320–25–1394, dated July 23, 2004, is
acceptable for compliance with the
requirements of paragraph (f) of this AD.
Credit for AD 2005–23–05, Amendment 39–
14363
(h) Accomplishing the actions required by
paragraph (g) of AD 2005–23–05 is acceptable
for compliance with the corresponding
requirements of paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(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.
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Related Information
(j) French airworthiness directive F–2005–
172, issued December 21, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Airbus Service Bulletin
A320–25–1394, Revision 01, dated December
12, 2005, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
VerDate Aug<31>2005
17:21 Sep 27, 2006
Jkt 208001
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–8229 Filed 9–27–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24867; Directorate
Identifier 2006–NM–064–AD; Amendment
39–14773; AD 2006–20–04]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, and –106
Airplanes, and Model DHC–8–200 and
DHC–8–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–102, –103,
and –106 airplanes, and Model DHC–8–
200 and DHC–8–300 series airplanes.
This AD requires performing a one-time
general visual inspection for nonconforming chain links of chain
assemblies of the elevator trim system
and gust lock system, and corrective
actions if necessary. This AD also
requires temporary revisions to the
airplane flight manuals of the affected
airplanes, which describe procedures
for elevator trim checks. This AD results
from reports of several failures of the
elevator trim chain, due to hydrogen
embrittlement. We are issuing this AD
to prevent breakage of the elevator trim
chain, which would prevent the actual
position of the elevator trim tab from
being annunciated to the flightcrew.
Attempting to adjust the trim tab from
the full nose up or full nose down
position with a broken trim chain could
result in misleading information relative
to takeoff trim settings and consequent
loss of control on takeoff.
DATES: This AD becomes effective
November 2, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 2, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
SUMMARY:
PO 00000
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dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this 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:
Examining the Docket
You may examine the airworthiness
directive (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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Bombardier Model
DHC–8–102, –103, and –106 airplanes,
and Model DHC–8–200 and DHC–8–300
series airplanes. That NPRM was
published in the Federal Register on
May 25, 2006 (71 FR 30070). That
NPRM proposed to require performing a
one-time inspection for non-conforming
chain links of chain assemblies of the
elevator trim system and gust lock
system, and corrective actions if
necessary. That NPRM also proposed to
require temporary revisions to the
airplane flight manuals of the affected
airplanes, which describe procedures
for elevator trim checks.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment
received.
Request To Revise Costs of Compliance
One commenter, Horizon Air,
requests that we adjust the costs of
compliance in the NPRM. Horizon Air
asserts that, rather than the 5 work
hours specified in the NPRM to
accomplish the inspection on each
airplane, the figure specified by
Bombardier of 15 work hours to
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Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
accomplish the inspection is far more
relevant. Further, Horizon Air states that
all chain link assemblies will likely
need to be replaced on its airplanes and
asserts that, according to Bombardier, an
additional 32 work hours per airplane
would be needed to replace the
assemblies. Horizon Air believes the
costs of compliance will far exceed the
estimated figure of $400 per airplane
specified in the NPRM.
We do not agree. The economic
analysis of an AD is limited to the cost
of actions that are actually required. The
economic analysis does not consider the
costs of on-condition actions, such as
repairing a crack detected during a
required inspection (‘‘repair, if
necessary’’). Such on-condition repairs
would be required—regardless of AD
direction—to correct an unsafe
condition identified in an airplane and
to ensure that the airplane is operated
in an airworthy condition, as required
by the Federal Aviation Regulations. We
have not changed the AD in this regard.
Clarification of Type of Inspection
We specified a ‘‘general visual
inspection’’ in the NPRM to eliminate
any confusion about the proper type of
inspection; however, we neglected to
include a definition of this type of
inspection in the NPRM. Therefore, we
added Note 2 to the AD to define a
general visual inspection.
Clarification of End-Level Effect
We have determined that the
description in the NPRM of the endlevel effect of the unsafe condition is
not entirely accurate. Therefore, we
have revised the AD to more clearly
describe the probable end-level effect of
the unsafe condition on the airplane.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
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Costs of Compliance
This AD affects about 166 airplanes of
U.S. registry. The required inspection
will take about 5 work hours per
airplane, at an average labor rate of $80
per work hour. Based on these figures,
the estimated cost of the required
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56857
inspection for U.S. operators is $66,400,
or $400 per airplane.
the FAA amends 14 CFR part 39 as
follows:
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.
PART 39—AIRWORTHINESS
DIRECTIVES
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 and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
I
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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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–20–04 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14773.
Docket No. FAA–2006–24867;
Directorate Identifier 2006–NM–064–AD.
Effective Date
(a) This AD becomes effective November 2,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–102, –103, and –106 airplanes, and
Model DHC–8–200 and DHC–8–300 series
airplanes, certificated in any category; as
identified in Bombardier Service Bulletin 8–
27–105, Revision A, dated September 13,
2005.
Unsafe Condition
(d) This AD results from reports of several
failures of the elevator trim chain, due to
hydrogen embrittlement. We are issuing this
AD to prevent breakage of the elevator trim
chain, which would prevent the actual
position of the elevator trim tab from being
annunciated to the flightcrew. Attempting to
adjust the trim tab from the full nose up or
full nose down position with a broken trim
chain could result in misleading information
relative to takeoff trim settings and
consequent loss of control on takeoff.
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.
Temporary Amendments (TAs)
(f) Within 30 days after the effective date
of this AD, revise the applicable airplane
flight manual (AFM) of the affected airplanes
by incorporating the information in the
applicable TAs into the AFMs 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.
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Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
TABLE 1.—DE HAVILLAND TAS
Use de
Havilland TA
No.—
For airplane model—
102 .................................................
102NS ............................................
103 .................................................
103NS ............................................
106 .................................................
106NS ............................................
201 .................................................
201S ...............................................
202 .................................................
202HT .............................................
202S ...............................................
301 .................................................
311 .................................................
315 .................................................
Dated—
9
8
9
8
9
8
11
9
10
8
9
8
15
9
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.
Inspection and Corrective Actions
(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 the 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.
Note 2: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
To the de Havilland Dash 8 Model—
January 28, 2004 ...
January 28, 2004 ...
January 28, 2004 ...
January 28, 2004 ...
January 28, 2004 ...
January 28, 2004 ...
June 22, 2005 ........
June 22, 2005 ........
January 28, 2004 ...
January 28, 2004 ...
June 22, 2005 ........
January 28, 2004 ...
January 28, 2004 ...
January 28, 2004 ...
102
102
103
103
106
106
201
201
202
202
202
301
311
315
Flight Manual PSM 1–81–1A.
NS Flight Manual PSM 1–81–1A.
Flight Manual PSM 1–81–1A.
NS Flight Manual PSM 1–81–1A.
Flight Manual PSM 1–81–1A.
NS Flight Manual PSM 1–81–1A.
Flight Manual PSM 1–82–1A.
S Flight Manual PSM 1–82–1A.
Flight Manual PSM 1–82–1A.
HT Flight Manual PSM 1–82–1A.
S Flight Manual PSM 1–82–1A.
Flight Manual PSM 1–83–1A.
Flight Manual PSM 1–83–1A.
Flight Manual PSM 1–83–1A.
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
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.
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.
Related Information
(j) Canadian airworthiness directive CF–
2005–38, dated October 25, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Bombardier Service
Bulletin 8–27–105, Revision A, dated
September 13, 2005, and the temporary
amendments specified in Table 2 of this AD,
as applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
TABLE 2.—TEMPORARY AMENDMENTS INCORPORATED BY REFERENCE
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de Havilland temporary amendment—
Dated—
To the de Havilland Dash 8 Model—
8 ............................................................................
8 ............................................................................
8 ............................................................................
8 ............................................................................
8 ............................................................................
9 ............................................................................
9 ............................................................................
9 ............................................................................
9 ............................................................................
9 ............................................................................
9 ............................................................................
10 ..........................................................................
11 ..........................................................................
15 ..........................................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
June 22, 2005 ......................................................
June 22, 2005 ......................................................
January 28, 2004 .................................................
January 28, 2004 .................................................
June 22, 2005 ......................................................
January 28, 2004 .................................................
102
103
106
202
301
102
103
106
201
202
315
202
201
311
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NS Flight Manual PSM 1–81–1A.
NS Flight Manual PSM 1–81–1A.
NS Flight Manual PSM 1–81–1A.
HT Flight Manual PSM 1–82–1A.
Flight Manual PSM 1–83–1A.
Flight Manual PSM 1–81–1A.
Flight Manual PSM 1–81–1A.
Flight Manual PSM 1–81–1A.
S Flight Manual PSM 1–82–1A.
S Flight Manual PSM 1–82–1A.
Flight Manual PSM 1–83–1A.
Flight Manual PSM 1–82–1A.
Flight Manual PSM 1–82–1A.
Flight Manual PSM 1–83–1A.
28SER1
Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
Issued in Renton, Washington, on
September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–8226 Filed 9–27–06; 8:45 am]
Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22974; Directorate
Identifier 2005–NM–180–AD; Amendment
39–14774; AD 2006–20–05]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited Model
BAe 146 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
BAE Systems (Operations) Limited
Model BAe 146 airplanes. This AD
requires repetitive inspections to
measure the depth of chafing or scoring
in the skin along the full length of the
wing-to-fuselage fairing from forward to
aft ends at the contact between the seal
and fuselage, and related investigative/
corrective actions if necessary. This AD
results from a report of chafing in this
area. We are issuing this AD to detect
and correct such chafing or scoring,
which could result in reduced structural
integrity of the fuselage.
DATES: This AD becomes effective
November 2, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 2, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact British Aerospace Regional
Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia
20171, for service information identified
in this AD.
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Jkt 208001
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 street
address stated in the ADDRESSES section.
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that would apply to certain BAE
Systems (Operations) Limited Model
BAe 146 airplanes. That supplemental
NPRM was published in the Federal
Register on April 5, 2006 (71 FR 17037).
That supplemental NPRM proposed to
require repetitive inspections to
measure the depth of chafing or scoring
in the skin along the full length of the
wing-to-fuselage fairing from forward to
aft ends at the contact between the seal
and fuselage, and related investigative/
corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment we received on
the supplemental NPRM.
Request for Revised Compliance Time
BAE notes that corresponding British
airworthiness directive G–2005–0020,
dated July 6, 2005, allows an additional
4,000 flight cycles before previously
inspected airplanes must be
reinspected. But paragraph (f) of the
supplemental NPRM would require all
airplanes to be inspected before the
airplane accumulates 1,000 total flight
cycles, or within a grace period of 500
flight cycles, without any provision for
an extended compliance time for
airplanes previously inspected in
accordance with both BAE Systems
(Operations) Limited Inspection Service
Bulletins ISB.53–005, Revision 2, dated
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56859
February 16, 2005, and ISB.53–067,
Revision 3, dated June 27, 2005. BAE
adds that there are no airplanes in
service with fewer than 1,000 total flight
cycles.
We infer that the commenter requests
that we revise the supplemental NPRM.
We agree. We have revised paragraph (f)
to allow the deferral of certain
corrective actions under specific
conditions outlined in the service
bulletins, as provided in new paragraph
(h) in this AD.
Additional Changes to Supplemental
NPRM
The supplemental NPRM specified
that all actions including corrective
actions would be required at the times
specified in BAE Systems (Operations)
Limited Inspection Service Bulletins
ISB.53–005 and ISB.53–067. Our intent
was to match the specifications of the
service bulletins, which allow deferred
corrective action only under certain
conditions. To clarify the required
compliance times of this AD, we have
added new paragraph (h) to explicitly
require corrective actions before further
flight, except when repair may be
deferred under the specific conditions
noted in the service bulletins.
Paragraph (g) of the supplemental
NPRM specified making repairs using a
method approved by either the FAA or
the Civil Aviation Authority, which is
the airworthiness authority for the
United Kingdom. The European
Aviation Safety Agency (EASA) has
assumed responsibility for the airplane
model subject to this AD. Therefore, we
have revised paragraph (g) of this AD to
specify making repairs using a method
approved by the FAA, the CAA (or its
delegated agent), or the EASA (or its
delegated agent).
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
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]]>Agencies
[Federal Register Volume 71, Number 188 (Thursday, September 28, 2006)]
[Rules and Regulations]
[Pages 56856-56859]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-8226]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24867; Directorate Identifier 2006-NM-064-AD;
Amendment 39-14773; AD 2006-20-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes, and Model DHC-8-200 and DHC-8-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier Model DHC-8-102, -103, and -106 airplanes, and Model
DHC-8-200 and DHC-8-300 series airplanes. This AD requires performing a
one-time general visual inspection for non-conforming chain links of
chain assemblies of the elevator trim system and gust lock system, and
corrective actions if necessary. This AD also requires temporary
revisions to the airplane flight manuals of the affected airplanes,
which describe procedures for elevator trim checks. This AD results
from reports of several failures of the elevator trim chain, due to
hydrogen embrittlement. We are issuing this AD to prevent breakage of
the elevator trim chain, which would prevent the actual position of the
elevator trim tab from being annunciated to the flightcrew. Attempting
to adjust the trim tab from the full nose up or full nose down position
with a broken trim chain could result in misleading information
relative to takeoff trim settings and consequent loss of control on
takeoff.
DATES: This AD becomes effective November 2, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of November 2,
2006.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this 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:
Examining the Docket
You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Bombardier
Model DHC-8-102, -103, and -106 airplanes, and Model DHC-8-200 and DHC-
8-300 series airplanes. That NPRM was published in the Federal Register
on May 25, 2006 (71 FR 30070). That NPRM proposed to require performing
a one-time inspection for non-conforming chain links of chain
assemblies of the elevator trim system and gust lock system, and
corrective actions if necessary. That NPRM also proposed to require
temporary revisions to the airplane flight manuals of the affected
airplanes, which describe procedures for elevator trim checks.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment received.
Request To Revise Costs of Compliance
One commenter, Horizon Air, requests that we adjust the costs of
compliance in the NPRM. Horizon Air asserts that, rather than the 5
work hours specified in the NPRM to accomplish the inspection on each
airplane, the figure specified by Bombardier of 15 work hours to
[[Page 56857]]
accomplish the inspection is far more relevant. Further, Horizon Air
states that all chain link assemblies will likely need to be replaced
on its airplanes and asserts that, according to Bombardier, an
additional 32 work hours per airplane would be needed to replace the
assemblies. Horizon Air believes the costs of compliance will far
exceed the estimated figure of $400 per airplane specified in the NPRM.
We do not agree. The economic analysis of an AD is limited to the
cost of actions that are actually required. The economic analysis does
not consider the costs of on-condition actions, such as repairing a
crack detected during a required inspection (``repair, if necessary'').
Such on-condition repairs would be required--regardless of AD
direction--to correct an unsafe condition identified in an airplane and
to ensure that the airplane is operated in an airworthy condition, as
required by the Federal Aviation Regulations. We have not changed the
AD in this regard.
Clarification of Type of Inspection
We specified a ``general visual inspection'' in the NPRM to
eliminate any confusion about the proper type of inspection; however,
we neglected to include a definition of this type of inspection in the
NPRM. Therefore, we added Note 2 to the AD to define a general visual
inspection.
Clarification of End-Level Effect
We have determined that the description in the NPRM of the end-
level effect of the unsafe condition is not entirely accurate.
Therefore, we have revised the AD to more clearly describe the probable
end-level effect of the unsafe condition on the airplane.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD affects about 166 airplanes of U.S. registry. The required
inspection will take about 5 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the required inspection for U.S. operators is $66,400, or $400
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 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 and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-20-04 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14773. Docket No. FAA-2006-24867; Directorate Identifier 2006-NM-
064-AD.
Effective Date
(a) This AD becomes effective November 2, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-102, -103, and -
106 airplanes, and Model DHC-8-200 and DHC-8-300 series airplanes,
certificated in any category; as identified in Bombardier Service
Bulletin 8-27-105, Revision A, dated September 13, 2005.
Unsafe Condition
(d) This AD results from reports of several failures of the
elevator trim chain, due to hydrogen embrittlement. We are issuing
this AD to prevent breakage of the elevator trim chain, which would
prevent the actual position of the elevator trim tab from being
annunciated to the flightcrew. Attempting to adjust the trim tab
from the full nose up or full nose down position with a broken trim
chain could result in misleading information relative to takeoff
trim settings and consequent loss of control on takeoff.
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.
Temporary Amendments (TAs)
(f) Within 30 days after the effective date of this AD, revise
the applicable airplane flight manual (AFM) of the affected
airplanes by incorporating the information in the applicable TAs
into the AFMs 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.
[[Page 56858]]
Table 1.--de Havilland TAs
----------------------------------------------------------------------------------------------------------------
Use de
For airplane model-- Havilland TA Dated-- To the de Havilland
No.-- Dash 8 Model--
----------------------------------------------------------------------------------------------------------------
102.................................. 9 January 28, 2004................ 102 Flight Manual PSM 1-
81-1A.
102NS................................ 8 January 28, 2004................ 102 NS Flight Manual
PSM 1-81-1A.
103.................................. 9 January 28, 2004................ 103 Flight Manual PSM 1-
81-1A.
103NS................................ 8 January 28, 2004................ 103 NS Flight Manual
PSM 1-81-1A.
106.................................. 9 January 28, 2004................ 106 Flight Manual PSM 1-
81-1A.
106NS................................ 8 January 28, 2004................ 106 NS Flight Manual
PSM 1-81-1A.
201.................................. 11 June 22, 2005................... 201 Flight Manual PSM 1-
82-1A.
201S................................. 9 June 22, 2005................... 201 S Flight Manual PSM
1-82-1A.
202.................................. 10 January 28, 2004................ 202 Flight Manual PSM 1-
82-1A.
202HT................................ 8 January 28, 2004................ 202 HT Flight Manual
PSM 1-82-1A.
202S................................. 9 June 22, 2005................... 202 S Flight Manual PSM
1-82-1A.
301.................................. 8 January 28, 2004................ 301 Flight Manual PSM 1-
83-1A.
311.................................. 15 January 28, 2004................ 311 Flight Manual PSM 1-
83-1A.
315.................................. 9 January 28, 2004................ 315 Flight Manual PSM 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.
Inspection and Corrective Actions
(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 the 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.
Note 2: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
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.
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 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
(j) Canadian airworthiness directive CF-2005-38, dated October
25, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Bombardier Service Bulletin 8-27-105, Revision
A, dated September 13, 2005, and the temporary amendments specified
in Table 2 of this AD, as applicable, to perform the actions that
are required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference of these documents in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. Contact Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K
1Y5, Canada, for a copy of this service information. You may review
copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Table 2.--Temporary Amendments Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
de Havilland temporary amendment--
Dated-- To the de Havilland Dash 8 Model--
----------------------------------------------------------------------------------------------------------------
8................................ January 28, 2004.... 102 NS Flight Manual PSM 1-81-1A.
8................................ January 28, 2004.... 103 NS Flight Manual PSM 1-81-1A.
8................................ January 28, 2004.... 106 NS Flight Manual PSM 1-81-1A.
8................................ January 28, 2004.... 202 HT Flight Manual PSM 1-82-1A.
8................................ January 28, 2004.... 301 Flight Manual PSM 1-83-1A.
9................................ January 28, 2004.... 102 Flight Manual PSM 1-81-1A.
9................................ January 28, 2004.... 103 Flight Manual PSM 1-81-1A.
9................................ January 28, 2004.... 106 Flight Manual PSM 1-81-1A.
9................................ June 22, 2005....... 201 S Flight Manual PSM 1-82-1A.
9................................ June 22, 2005....... 202 S Flight Manual PSM 1-82-1A.
9................................ January 28, 2004.... 315 Flight Manual PSM 1-83-1A.
10............................... January 28, 2004.... 202 Flight Manual PSM 1-82-1A.
11............................... June 22, 2005....... 201 Flight Manual PSM 1-82-1A.
15............................... January 28, 2004.... 311 Flight Manual PSM 1-83-1A.
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[[Page 56859]]
Issued in Renton, Washington, on September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-8226 Filed 9-27-06; 8:45 am]
BILLING CODE 4910-13-P
