[Federal Register Volume 71, Number 188 (Thursday, September 28, 2006)]
[Rules and Regulations]
[Pages 56856-56859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-8226]
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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 http://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 http://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the 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
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Use de
For airplane model-- Havilland TA Dated-- To the de Havilland
No.-- Dash 8 Model--
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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.
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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 http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 2.--Temporary Amendments Incorporated by Reference
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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]
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