Airworthiness Directives; Bombardier Model DHC-8-101, -102, -103, -106, -201, -202, -301, -311, and -315 Airplanes, 16164-16167 [05-6241]
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Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules
image—must be scaled and aligned (i.e.,
conformal) to the external scene. In
addition, the EFVS image and the HUD
symbols—when considered singly or in
combination—must not be misleading,
cause pilot confusion, or increase
workload. There may be airplane
attitudes or cross-wind conditions
which cause certain symbols (e.g., the
zero-pitch line or flight path vector) to
reach field of view limits, such that they
cannot be positioned conformally with
the image and external scene. In such
cases, these symbols may be displayed
but with an altered appearance, which
makes the pilot aware that they are no
longer displayed conformally (for
example, ‘‘ghosting’’).
f. A HUD system used to display
EFVS images must, if previously
certified, continue to meet all of the
requirements of the original approval.
3. The safety and performance of the
pilot tasks associated with the use of the
pilot compartment view must not be
degraded by the display of the EFVS
image. These tasks include the
following:
a. Detection, accurate identification
and maneuvering, as necessary, to avoid
traffic, terrain, obstacles, and other
hazards of flight.
b. Accurate identification and
utilization of visual references required
for every task relevant to the phase of
flight.
4. Compliance with these special
conditions will enable the EFVS to be
used during instrument approaches in
accordance with 14 CFR 91.175(l) such
that it may be found acceptable for the
following intended functions:
a. Presenting an image that would aid
the pilot during a straight-in instrument
approach.
b. Enabling the pilot to determine that
the ‘‘enhanced flight visibility,’’ as
required by § 91.175(l)(2) for descent
and operation below minimum descent
altitude/decision height (MDA)/(DH).
c. Enabling the pilot to use the EFVS
imagery to detect and identify the
‘‘visual references for the intended
runway,’’ required by 14 CFR
91.175(l)(3), to continue the approach
with vertical guidance to 100 feet height
above touchdown zone elevation.
5. Use of EFVS for instrument
approach operations must be in
accordance with the provisions of 14
CFR 91.175(l) and (m). Appropriate
limitations must be stated in the
Operating Limitations section of the
Airplane Flight Manual to prohibit the
use of the EFVS for functions that have
not been found to be acceptable.
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Issued in Renton, Washington, on March
23, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6310 Filed 3–29–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20730; Directorate
Identifier 2004–NM–68–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–101, –102, –103, –106,
–201, –202, –301, –311, and –315
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all
Bombardier Model DHC–8–101, –102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. The existing AD
currently requires installation of a
placard on the instrument panel of the
cockpit to advise the flightcrew that
positioning of the power levers below
the flight idle stop during flight is
prohibited. Additionally, the existing
AD requires eventual installation of an
FAA-approved system that would
prevent such positioning of the power
levers during flight. Installation of that
system terminates the requirement for
installation of a placard. This proposed
AD would require operators who have
incorporated a certain Bombardier
service bulletin to perform repetitive
operational checks of the beta lockout
system and to revise the Airworthiness
Limitations document. This proposed
AD is prompted by in-service issues
reported by operators who incorporated
Bombardier Service Bulletin 8–76–24 as
an alternative method of compliance to
the existing AD. We are proposing this
AD to prevent the inadvertent activation
of ground beta mode during flight,
which could lead to engine overspeed,
engine damage or failure, and
consequent reduced controllability of
the airplane.
DATES: We must receive comments on
this proposed AD by April 29, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
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• DOT Docket Web Site: Go to http:/
/dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide Rulemaking Web
Site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20730; the directorate identifier for this
docket is 2004–NM–68–AD.
FOR FURTHER INFORMATION CONTACT:
Richard Fiesel, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, Federal Aviation Administration,
New York Aircraft Certification Office,
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7304; fax (516) 794–5531.
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20730; Directorate Identifier
2004–NM–68–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of our docket
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
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who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
On January 20, 2000, we issued AD
2000–02–13, amendment 39–11531 (65
FR 4095, January 26, 2000), for all
Bombardier Model DHC–8–101, –102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. That AD requires
installation of a placard on the
instrument panel of the cockpit to
advise the flightcrew that positioning of
the power levers below the flight idle
stop during flight is prohibited.
Additionally, that AD requires eventual
installation of a system that will prevent
such positioning of the power levers
during flight. Installation of that system
terminates the requirement for
installation of a placard. That AD was
prompted by reports of operation of the
airplane with the power levers
positioned below the flight idle stop
during flight. The actions specified by
that AD are intended to prevent such
positioning of the power levers below
the flight idle stop during flight, which
could cause engine overspeed, possible
engine damage or failure, and
consequent reduced controllability of
the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2000–02–13,
Bombardier has reevaluated Service
Bulletin 8–76–24, which was provided
as part of the alternative method of
compliance (AMOC) to AD 2000–02–13.
As a result of this reevaluation,
Bombardier issued an Airworthiness
Limitation (AWL), outlined in
Bombardier Q100/200/300 All Operator
Message 759, dated February 9, 2004,
that applies to Bombardier Model DHC–
8–101, –102, –103, –106, –201, –202,
–301, –311, and –315 airplanes with a
beta lockout system installed. The new
AWL introduces de Havilland, Inc.,
Dash 8 Maintenance Task Card 6120–10,
dated November 21, 2003 (for series
100, 200, and 300 airplanes).
Relevant Service Information
Bombardier has issued temporary
revisions (TRs) to the applicable
Bombardier DHC–8 Program Support
Manual (PSM), as listed in the following
TR table. The TRs specify that de
Havilland, Inc., Dash 8 Maintenance
Task Card 6120/10, operational check of
beta lockout ground logic, dated
November 21, 2003, be done at
repetitive intervals not to exceed 500
flight hours for series 100, 200, and 300
airplanes, as listed in the following Task
Card table.
TABLE—TRS
DHC–8 Model
TR Number
Date
PSM
–101, –102, –103, and –106 airplanes ..........................................
–201 and –202 airplanes ...............................................................
–301, –311, and –315 airplanes ....................................................
AWL–86 ....................................
AWL 2–26 .................................
AWL 3–93 .................................
March 17, 2003 .........................
March 17, 2003 .........................
March 17, 2003 .........................
1–8–7
1–82–7
1–83–7
TABLE—TASK CARDS
DHC–8 Model
de Havilland, Inc., Task Card
–101, –102, –103, and 106 airplanes ..................................
–201 and –202 airplanes ......................................................
–301, –311, and –315 airplanes ...........................................
Dash 8 Series 100 Maintenance Task Card 6120/10 .........
Dash 8 Series 200 Maintenance Task Card 6120/10 .........
Dash 8 Series 300 Maintenance Task Card 6120/10 .........
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in Canada and are type
certificated for operation in the United
States under the provisions of § 21.29 of
the Federal Aviation Regulations (14
CFR 21.29) and the applicable bilateral
airworthiness agreement. We have
reviewed all available information and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would supersede AD 2000–02–
13, to continue to require installation of
a placard on the instrument panel of the
cockpit to advise the flightcrew that
positioning of the power levers below
the flight idle stop during flight is
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Jkt 205001
prohibited. Additionally, this proposed
AD continues to require eventual
installation of an FAA-approved system
that would prevent such positioning of
the power levers during flight. This
proposed AD would also require
operators to perform initial and
repetitive operational checks of the beta
lockout system and to revise the
Airworthiness Limitations document.
Transport Canada, which is the
airworthiness authority for Canada, has
been advised of the actions proposed by
this airworthiness directive and is in
agreement with the proposed actions.
Explanation of Action Taken by the
FAA
The manufacturer has revised the
Airworthiness Limitations document to
include new operational checks of the
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Sfmt 4702
Date
November 21, 2003.
November 21, 2003.
November 21, 2003.
beta lockout system. The TCCA has not
issued a corresponding airworthiness
directive, although accomplishment of
the operational checks contained in the
document described previously may be
considered mandatory for operators of
these aircraft in Canada.
This proposed AD, however, would
require revising the applicable
Airworthiness Limitations document to
require the operational checks. To
require compliance with those actions,
we must issue an airworthiness
directive.
Change to Existing AD
This proposed AD would retain all
requirements of AD 2000–02–13 and
add additional requirements. Since AD
2000–02–13 was issued, the AD format
has been revised, and certain paragraphs
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have been rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2000–02–13
Paragraph (a) ............
Paragraph (b) ............
Paragraph (c) ............
Corresponding
requirement in
this proposed AD
Paragraph (f).
Paragraph (g).
Paragraph (h).
We have also revised the applicability
of the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Costs of Compliance
This proposed AD would affect about
185 Bombardier Model DHC–8–101,
–102, –103, –106, –201, –202, –301,
–311, and –315 airplanes of U.S.
registry.
The installation of a placard that is
required by AD 2000–02–13, and
retained in this proposed AD, requires
about 1 work hour per airplane, at an
average labor rate of $65 per work hour.
No parts are required. Based on these
figures, the cost impact of the placard
installation on U.S. operators is
estimated to be $12,025, or $65 per
airplane.
The installation of the preventative
system that is required by AD 2000–02–
13, and retained in this proposed AD,
requires about 123 work hours per
airplane, at an average labor rate of $65
per work hour. We estimate that
required parts would cost
approximately $12,000 per airplane.
Based on these figures, the cost impact
of the installation of the preventative
system on U.S. operators is estimated to
be $3,699,075, or $19,995 per airplane.
The proposed operational check of the
beta lockout system would take about 1
work hour per airplane, per check cycle,
at an average labor rate of $65 per work
hour. No parts are required. Based on
these figures, the estimated cost of the
new operational check specified in this
proposed AD for U.S. operators is
$12,025, or $65 per airplane, per check
cycle.
The proposed revision of the
Airworthiness Limitations document
would take about 1 work hour per
airplane, at an average labor rate $65 per
work hour. Based on these figures, the
estimated cost of the revision specified
in the proposed AD for U.S. operators is
$12,025, or $65 per airplane.
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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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–11531 (65 FR
4095, January 26, 2000) and adding the
following new airworthiness directive
(AD):
Bombardier Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2005–20730;
Directorate Identifier 2004–NM–68–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
April 29, 2005.
Affected ADs
(b) This AD supersedes AD 2000–02–13,
amendment 39–11531 (65 FR 4095, January
26, 2000).
Applicability: (c) This AD applies to all
Bombardier Model DHC–8–101, –102, –103,
–106, –201, –202, –301, –311, and –315
airplanes; certificated in any category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revision. In this
situation, to comply with 14 CFR 91.403 (c),
the operator must request approval for an
alternative method of compliance in
accordance with paragraph (l)(1) of this AD.
The request should include a description of
changes to the required inspections that will
ensure the continued damage tolerance of the
affected structure. The FAA has provided
guidance for this determination in Advisory
Circular (AC) 25–1529.
Unsafe Condition
(d) This AD was prompted by in-service
issues reported by operators who
incorporated a certain Bombardier service
bulletin as an alternative method of
compliance to AD 2000–02–13. We are
issuing this AD to prevent the inadvertent
activation of ground beta mode during flight,
which could lead to engine overspeed,
engine damage or failure, and consequent
reduced controllability of the airplane.
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.
Requirements of AD 2000–02–13
Installation of Placard
(f) Within 30 days after March 1, 2000 (the
effective date of AD 2000–02–13), install a
placard in a prominent location on the
instrument panel of the cockpit that states:
‘‘Positioning of the power levers below the
flight idle stop during flight is prohibited.
Such positioning may lead to loss of airplane
control, or may result in an engine overspeed
condition and consequent loss of engine
power.’’
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Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules
Installation of System Preventing Excessive
Lowering of Power Levers in Flight
(g) Within 2 years after March 1, 2000,
install a system that would prevent
positioning the power levers below the flight
idle stop during flight, in accordance with a
method approved by the Manager, New York
Aircraft Certification Office (ACO), FAA.
Following accomplishment of that
installation, the placard required by
paragraph (f) of this AD may be removed.
(h) In the event that the system required by
paragraph (g) of this AD malfunctions, or if
the use of an override (if installed) is
necessary, the airplane may be operated for
three days to a location where required
maintenance/repair can be performed,
provided the system required by paragraph
(g) of this AD has been properly deactivated
and placarded for flightcrew awareness, in
accordance with the FAA-approved Master
Minimum Equipment List (MMEL).
New Requirements
Bulletin 8–76–24: Within 50 flight hours after
the effective date of this AD, perform an
operational check of the beta lockout system
in accordance with the applicable de
Havilland, Inc., Dash 8 task card listed in
Table 1 of this AD. Thereafter repeat the
operational check at intervals specified in the
applicable de Havilland, Inc., temporary
revision (TR) listed in Table 2 of this AD.
Operational Checks of the Beta Lockout
System
(i) For airplanes that have been modified
in accordance with Bombardier Service
TABLE 1.—TASK CARDS
DHC–8 Model
de Havilland, Inc., task card
–101, –102, –103, and –106 airplanes .........
–201 and –202 airplanes ..............................
–301, –311, and –315 airplanes ...................
Dash 8 Series 100 Maintenance Task Card 6120/10 .................................
Dash 8 Series 200 Maintenance Task Card 6120/10 .................................
Dash 8 Series 300 Maintenance Task Card 6120/10 .................................
Revision of Airworthiness Limitations
(AWL) Section
(j) Within 30 days after the effective date
of this AD, revise the AWL section of the
applicable Instructions for Continued
Airworthiness by incorporating the contents
of the applicable de Havilland, Inc., TR listed
in Table 2 of this AD into the AWL section
Date
November 21, 2003.
November 21, 2003.
November 21, 2003.
of the applicable Bombardier DHC–8
Maintenance Program Support Manual
(PSM).
TABLE 2.—TRS
DHC–8 Model
de Havilland, Inc., TR
Dated
For PSM
–101, –102, –103, and –106 airplanes ..........................................
–201 and –202 airplanes ...............................................................
–301, –311, and –315 airplanes ....................................................
AWL–86 ....................................
AWL 2–26 .................................
AWL 3–93 .................................
March 17, 2003 .........................
March 17, 2003 .........................
March 17, 2003 .........................
1–8–7
1–82–7
1–83–7
(k) When the information in the applicable
de Havilland, Inc., TR identified in Table 2
of this AD has been included in the general
revisions of the applicable PSM identified in
Table 2 of this AD, the general revisions may
be inserted in the PSM, and the applicable
TR may be removed from the AWL section
of the Instruction for Continued
Airworthiness.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, New York ACO has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCS approved previously in
accordance with AD 2000–02–13 are
acceptable for the corresponding
requirements of this AD.
Related Information
(m) None.
Issued in Renton, Washington, on March
17, 2005.
Jeffery E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–6241 Filed 3–29–05; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20755; Directorate
Identifier 2004–NM–244–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A321 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Airbus
Model A321 series airplanes. The
existing AD currently requires revising
the Limitations section of the airplane
flight manual to include an instruction
to use Flap 3 for landing when
performing an approach in conditions of
moderate to severe icing, significant
crosswind (i.e., crosswinds greater than
20 knots, gust included), or moderate to
severe turbulence. This proposed AD
would require replacing existing
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elevator and aileron computers (ELAC)
with ELACs having either L83 or L91
software, as applicable, which would
terminate the requirements of the
existing AD. This proposed AD would
also require a related concurrent action.
In addition, this proposed AD would
revise the applicability by removing
airplanes with these ELAC software
standards incorporated in production.
This proposed AD is prompted by
issuance of mandatory continuing
airworthiness information by a civil
airworthiness authority. We are
proposing this AD to prevent roll
oscillations during approach and
landing in certain icing, crosswind, and
turbulent conditions, which could result
in reduced controllability of the
airplane.
We must receive comments on
this proposed AD by April 29, 2005.
DATES:
Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
ADDRESSES:
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]]>Agencies
[Federal Register Volume 70, Number 60 (Wednesday, March 30, 2005)]
[Proposed Rules]
[Pages 16164-16167]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6241]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20730; Directorate Identifier 2004-NM-68-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-101, -102, -103,
-106, -201, -202, -301, -311, and -315 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Bombardier Model DHC-8-101, -102, -
103, -106, -201, -202, -301, -311, and -315 airplanes. The existing AD
currently requires installation of a placard on the instrument panel of
the cockpit to advise the flightcrew that positioning of the power
levers below the flight idle stop during flight is prohibited.
Additionally, the existing AD requires eventual installation of an FAA-
approved system that would prevent such positioning of the power levers
during flight. Installation of that system terminates the requirement
for installation of a placard. This proposed AD would require operators
who have incorporated a certain Bombardier service bulletin to perform
repetitive operational checks of the beta lockout system and to revise
the Airworthiness Limitations document. This proposed AD is prompted by
in-service issues reported by operators who incorporated Bombardier
Service Bulletin 8-76-24 as an alternative method of compliance to the
existing AD. We are proposing this AD to prevent the inadvertent
activation of ground beta mode during flight, which could lead to
engine overspeed, engine damage or failure, and consequent reduced
controllability of the airplane.
DATES: We must receive comments on this proposed AD by April 29, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide Rulemaking Web Site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-20730; the directorate identifier for this docket is
2004-NM-68-AD.
FOR FURTHER INFORMATION CONTACT: Richard Fiesel, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, Federal Aviation
Administration, New York Aircraft Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228-7304;
fax (516) 794-5531.
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20730;
Directorate Identifier 2004-NM-68-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual
[[Page 16165]]
who sent the comment (or signed the comment on behalf of an
association, business, labor union, etc.). You can review the DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (65 FR 19477-78), or you can visit https://dms.dot.gov.
Examining the Docket
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
On January 20, 2000, we issued AD 2000-02-13, amendment 39-11531
(65 FR 4095, January 26, 2000), for all Bombardier Model DHC-8-101, -
102, -103, -106, -201, -202, -301, -311, and -315 airplanes. That AD
requires installation of a placard on the instrument panel of the
cockpit to advise the flightcrew that positioning of the power levers
below the flight idle stop during flight is prohibited. Additionally,
that AD requires eventual installation of a system that will prevent
such positioning of the power levers during flight. Installation of
that system terminates the requirement for installation of a placard.
That AD was prompted by reports of operation of the airplane with the
power levers positioned below the flight idle stop during flight. The
actions specified by that AD are intended to prevent such positioning
of the power levers below the flight idle stop during flight, which
could cause engine overspeed, possible engine damage or failure, and
consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2000-02-13, Bombardier has reevaluated Service
Bulletin 8-76-24, which was provided as part of the alternative method
of compliance (AMOC) to AD 2000-02-13. As a result of this
reevaluation, Bombardier issued an Airworthiness Limitation (AWL),
outlined in Bombardier Q100/200/300 All Operator Message 759, dated
February 9, 2004, that applies to Bombardier Model DHC-8-101, -102, -
103, -106, -201, -202, -301, -311, and -315 airplanes with a beta
lockout system installed. The new AWL introduces de Havilland, Inc.,
Dash 8 Maintenance Task Card 6120-10, dated November 21, 2003 (for
series 100, 200, and 300 airplanes).
Relevant Service Information
Bombardier has issued temporary revisions (TRs) to the applicable
Bombardier DHC-8 Program Support Manual (PSM), as listed in the
following TR table. The TRs specify that de Havilland, Inc., Dash 8
Maintenance Task Card 6120/10, operational check of beta lockout ground
logic, dated November 21, 2003, be done at repetitive intervals not to
exceed 500 flight hours for series 100, 200, and 300 airplanes, as
listed in the following Task Card table.
Table--TRs
----------------------------------------------------------------------------------------------------------------
DHC-8 Model TR Number Date PSM
-------------------------------------------------------------------------------------------------------
-101, -102, -103, and -106 airplanes AWL-86................ March 17, 2003........ 1-8-7
-201 and -202 airplanes............. AWL 2-26.............. March 17, 2003........ 1-82-7
-301, -311, and -315 airplanes...... AWL 3-93.............. March 17, 2003........ 1-83-7
----------------------------------------------------------------------------------------------------------------
Table--Task Cards
----------------------------------------------------------------------------------------------------------------
de Havilland, Inc., Task
DHC-8 Model Card Date
----------------------------------------------------------------------------------------------------------------
-101, -102, -103, and 106 airplanes...... Dash 8 Series 100 November 21, 2003.
Maintenance Task Card 6120/
10.
-201 and -202 airplanes.................. Dash 8 Series 200 November 21, 2003.
Maintenance Task Card 6120/
10.
-301, -311, and -315 airplanes........... Dash 8 Series 300 November 21, 2003.
Maintenance Task Card 6120/
10.
----------------------------------------------------------------------------------------------------------------
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. We have reviewed all
available information and determined that AD action is necessary for
airplanes of this type design that are certificated for operation in
the United States.
Therefore, we are proposing this AD, which would supersede AD 2000-
02-13, to continue to require installation of a placard on the
instrument panel of the cockpit to advise the flightcrew that
positioning of the power levers below the flight idle stop during
flight is prohibited. Additionally, this proposed AD continues to
require eventual installation of an FAA-approved system that would
prevent such positioning of the power levers during flight. This
proposed AD would also require operators to perform initial and
repetitive operational checks of the beta lockout system and to revise
the Airworthiness Limitations document.
Transport Canada, which is the airworthiness authority for Canada,
has been advised of the actions proposed by this airworthiness
directive and is in agreement with the proposed actions.
Explanation of Action Taken by the FAA
The manufacturer has revised the Airworthiness Limitations document
to include new operational checks of the beta lockout system. The TCCA
has not issued a corresponding airworthiness directive, although
accomplishment of the operational checks contained in the document
described previously may be considered mandatory for operators of these
aircraft in Canada.
This proposed AD, however, would require revising the applicable
Airworthiness Limitations document to require the operational checks.
To require compliance with those actions, we must issue an
airworthiness directive.
Change to Existing AD
This proposed AD would retain all requirements of AD 2000-02-13 and
add additional requirements. Since AD 2000-02-13 was issued, the AD
format has been revised, and certain paragraphs
[[Page 16166]]
have been rearranged. As a result, the corresponding paragraph
identifiers have changed in this proposed AD, as listed in the
following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 2000-02-13 in this proposed AD
------------------------------------------------------------------------
Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
Paragraph (c)............................. Paragraph (h).
------------------------------------------------------------------------
We have also revised the applicability of the existing AD to
identify model designations as published in the most recent type
certificate data sheet for the affected models.
Costs of Compliance
This proposed AD would affect about 185 Bombardier Model DHC-8-101,
-102, -103, -106, -201, -202, -301, -311, and -315 airplanes of U.S.
registry.
The installation of a placard that is required by AD 2000-02-13,
and retained in this proposed AD, requires about 1 work hour per
airplane, at an average labor rate of $65 per work hour. No parts are
required. Based on these figures, the cost impact of the placard
installation on U.S. operators is estimated to be $12,025, or $65 per
airplane.
The installation of the preventative system that is required by AD
2000-02-13, and retained in this proposed AD, requires about 123 work
hours per airplane, at an average labor rate of $65 per work hour. We
estimate that required parts would cost approximately $12,000 per
airplane. Based on these figures, the cost impact of the installation
of the preventative system on U.S. operators is estimated to be
$3,699,075, or $19,995 per airplane.
The proposed operational check of the beta lockout system would
take about 1 work hour per airplane, per check cycle, at an average
labor rate of $65 per work hour. No parts are required. Based on these
figures, the estimated cost of the new operational check specified in
this proposed AD for U.S. operators is $12,025, or $65 per airplane,
per check cycle.
The proposed revision of the Airworthiness Limitations document
would take about 1 work hour per airplane, at an average labor rate $65
per work hour. Based on these figures, the estimated cost of the
revision specified in the proposed AD for U.S. operators is $12,025, or
$65 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing amendment 39-11531 (65 FR
4095, January 26, 2000) and adding the following new airworthiness
directive (AD):
Bombardier Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2005-
20730; Directorate Identifier 2004-NM-68-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by April 29, 2005.
Affected ADs
(b) This AD supersedes AD 2000-02-13, amendment 39-11531 (65 FR
4095, January 26, 2000).
Applicability: (c) This AD applies to all Bombardier Model DHC-
8-101, -102, -103, -106, -201, -202, -301, -311, and -315 airplanes;
certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered or repaired in the areas
addressed by these inspections, the operator may not be able to
accomplish the inspections described in the revision. In this
situation, to comply with 14 CFR 91.403 (c), the operator must
request approval for an alternative method of compliance in
accordance with paragraph (l)(1) of this AD. The request should
include a description of changes to the required inspections that
will ensure the continued damage tolerance of the affected
structure. The FAA has provided guidance for this determination in
Advisory Circular (AC) 25-1529.
Unsafe Condition
(d) This AD was prompted by in-service issues reported by
operators who incorporated a certain Bombardier service bulletin as
an alternative method of compliance to AD 2000-02-13. We are issuing
this AD to prevent the inadvertent activation of ground beta mode
during flight, which could lead to engine overspeed, engine damage
or failure, and consequent reduced controllability of the airplane.
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.
Requirements of AD 2000-02-13
Installation of Placard
(f) Within 30 days after March 1, 2000 (the effective date of AD
2000-02-13), install a placard in a prominent location on the
instrument panel of the cockpit that states:
``Positioning of the power levers below the flight idle stop
during flight is prohibited. Such positioning may lead to loss of
airplane control, or may result in an engine overspeed condition and
consequent loss of engine power.''
[[Page 16167]]
Installation of System Preventing Excessive Lowering of Power Levers in
Flight
(g) Within 2 years after March 1, 2000, install a system that
would prevent positioning the power levers below the flight idle
stop during flight, in accordance with a method approved by the
Manager, New York Aircraft Certification Office (ACO), FAA.
Following accomplishment of that installation, the placard required
by paragraph (f) of this AD may be removed.
(h) In the event that the system required by paragraph (g) of
this AD malfunctions, or if the use of an override (if installed) is
necessary, the airplane may be operated for three days to a location
where required maintenance/repair can be performed, provided the
system required by paragraph (g) of this AD has been properly
deactivated and placarded for flightcrew awareness, in accordance
with the FAA-approved Master Minimum Equipment List (MMEL).
New Requirements
Operational Checks of the Beta Lockout System
(i) For airplanes that have been modified in accordance with
Bombardier Service Bulletin 8-76-24: Within 50 flight hours after
the effective date of this AD, perform an operational check of the
beta lockout system in accordance with the applicable de Havilland,
Inc., Dash 8 task card listed in Table 1 of this AD. Thereafter
repeat the operational check at intervals specified in the
applicable de Havilland, Inc., temporary revision (TR) listed in
Table 2 of this AD.
Table 1.--Task Cards
----------------------------------------------------------------------------------------------------------------
DHC-8 Model de Havilland, Inc., task card Date
----------------------------------------------------------------------------------------------------------------
-101, -102, -103, and -106 airplanes.... Dash 8 Series 100 Maintenance November 21, 2003.
Task Card 6120/10.
-201 and -202 airplanes................. Dash 8 Series 200 Maintenance November 21, 2003.
Task Card 6120/10.
-301, -311, and -315 airplanes.......... Dash 8 Series 300 Maintenance November 21, 2003.
Task Card 6120/10.
----------------------------------------------------------------------------------------------------------------
Revision of Airworthiness Limitations (AWL) Section
(j) Within 30 days after the effective date of this AD, revise
the AWL section of the applicable Instructions for Continued
Airworthiness by incorporating the contents of the applicable de
Havilland, Inc., TR listed in Table 2 of this AD into the AWL
section of the applicable Bombardier DHC-8 Maintenance Program
Support Manual (PSM).
Table 2.--TRs
----------------------------------------------------------------------------------------------------------------
DHC-8 Model de Havilland, Inc., TR Dated For PSM
----------------------------------------------------------------------------------------------------------------
-101, -102, -103, and -106 airplanes.. AWL-86................... March 17, 2003.......... 1-8-7
-201 and -202 airplanes............... AWL 2-26................. March 17, 2003.......... 1-82-7
-301, -311, and -315 airplanes........ AWL 3-93................. March 17, 2003.......... 1-83-7
----------------------------------------------------------------------------------------------------------------
(k) When the information in the applicable de Havilland, Inc.,
TR identified in Table 2 of this AD has been included in the general
revisions of the applicable PSM identified in Table 2 of this AD,
the general revisions may be inserted in the PSM, and the applicable
TR may be removed from the AWL section of the Instruction for
Continued Airworthiness.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, New York ACO has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCS approved previously in accordance with AD 2000-02-13
are acceptable for the corresponding requirements of this AD.
Related Information
(m) None.
Issued in Renton, Washington, on March 17, 2005.
Jeffery E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6241 Filed 3-29-05; 8:45 am]
BILLING CODE 4910-13-P
