Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 54316-54318 [05-18208]
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<![CDATA[
54316
Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules
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.
§ 39.13
[Amended]
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Related Information
(i) German airworthiness directive 2002–
158, dated October 3, 2002, also addresses
the subject of this AD.
Issued in Renton, Washington, on
September 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–18210 Filed 9–13–05; 8:45 am]
BILLING CODE 4910–13–P
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
DEPARTMENT OF TRANSPORTATION
Hamburger Flugzeugbau G.m.b.H.: Docket
No. FAA–2005–22401; Directorate
Identifier 2004–NM–93–AD.
Federal Aviation Administration
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
October 14, 2005.
[Docket No. FAA–2005–20403; Directorate
Identifier 2005–NM–144–AD]
RIN 2120–AA64
14 CFR Part 39
Affected ADs
(b) None.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
Applicability
(c) This AD applies to all Hamburger
Flugzeugbau Model HFB 320 HANSA
airplanes, certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report that
all airplanes in operation might have met or
exceeded the designed life limit for the
primary structure. We are issuing this AD to
prevent continued operation of an airplane
beyond its designed life limit for the primary
structure, which could result in reduced
structural integrity 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.
Airworthiness Limitations Revision
(f) Within 30 days after the effective date
of this AD: Revise the Limitations section of
the Airplane Flight Manual (AFM) to state
the following (or insert a copy of this AD into
the limitations section):
Do not operate the airplane beyond 15,000
total flight cycles, or 15,000 total flight hours,
whichever occurs first.
(g) This limitation may be removed from
the AFM after the Manager, International
Branch, ANM–116, FAA, approves analysis
that would substantiate continued safe
operation beyond the designed life limit of
15,000 total flight cycles, or within 15,000
total flight hours on the airplane, whichever
occurs first.
VerDate Aug<18>2005
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
15:58 Sep 13, 2005
Jkt 205001
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–400
series airplanes. This proposed AD
would require an inspection of the
laminated shims for cracks, damage, or
extrusion between the forward
attachment fittings of the horizontal
stabilizer and the top rib of the vertical
stabilizer; a torque check of the
attachment bolts in the attachment
fittings of the front, middle, and rear
spars; and corrective actions if
necessary. This proposed AD results
from a report indicating that
delaminated shims extruded from the
interface between the forward attaching
fittings of horizontal stabilizer and the
top rib of the vertical stabilizer, and that
inadequate torque values of some bolts
were found. We are proposing this AD
to prevent reduced structural integrity
of the horizontal stabilizer, and
consequent loss of controllability of the
airplane.
DATES: We must receive comments on
this proposed AD by October 14, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
• 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.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT:
George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 256–7525; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
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 in the
ADDRESSES section. Include the docket
number ‘‘FAA–2005–20403; Directorate
Identifier 2005–NM–144–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 that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
E:\FR\FM\14SEP1.SGM
14SEP1
Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules
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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on certain
Bombardier Model DHC–8–400 series
airplanes. TCCA advises that
delaminated shims extruded from the
interface between the forward attaching
fittings of horizontal stabilizer and the
top rib of the vertical stabilizer. In
addition, during removal of the
horizontal stabilizer for replacing the
laminated shims with solid shims,
inadequate torque values of some bolts
at the six attachment locations (two
each at the front, middle, and rear spars)
were found on some airplanes. This can
cause increased load on the bolts and
consequent reduction in fatigue life of
the bolts. These conditions, if not
corrected, could result in reduced
structural integrity of the horizontal
stabilizer, and consequent loss of
controllability of the airplane.
54317
Relevant Service Information
Bombardier has issued Service
Bulletin 84–55–02, Revision ‘‘A,’’ dated
January 12, 2005. The service bulletin
describes doing the following
procedures:
• A detailed inspection of the
laminated shims for cracks, damage, or
extrusion between the forward
attachment fittings of the horizontal
stabilizer and the top rib of the vertical
stabilizers;
• A breakaway torque check of the six
attachment bolts in the attachment
fittings of the front, middle, and rear
spars; and
• Corrective actions if necessary. The
corrective actions include replacing the
laminated shims, between the forward
attachment fittings of the horizontal
stabilizer and the top rib of the vertical
stabilizer, with solid shims and
replacing the corresponding barrel nut
and retainer with new parts.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. TCCA mandated the service
information and issued Canadian
airworthiness directive CF–2005–07,
issued March 21, 2005, to ensure the
continued airworthiness of these
airplanes in Canada.
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
TCCA has kept the FAA informed of the
situation described above. We have
examined TCCA’s findings, evaluated
all pertinent information, and
determined that we need to issue an AD
for airplanes of this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Difference
Between the Proposed AD and the
Service Bulletin.’’
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in Canada and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
Difference Between the Proposed AD
and Service Bulletin
Operators should note that, although
the Accomplishment Instructions of the
referenced service bulletin describe
procedures for submitting a sheet
recording torque values to the airplane
manufacturer, this proposed AD would
not require that action. We do not need
this information from operators.
Costs of Compliance
ESTIMATED COSTS
Action
Detailed inspection and torque
check.
Replacement ................................
15:58 Sep 13, 2005
Jkt 205001
Parts
Cost per
airplane
Number of
U.S.-registered
airplanes
Fleet cost
2
$65
None ..........................
$130
19
$2,470
30
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
VerDate Aug<18>2005
Average labor
rate per hour
Work hours
65
Free of charge ...........
1,950
19
37,050
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
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
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 and placed it in the
E:\FR\FM\14SEP1.SGM
14SEP1
54318
Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
(h) Accomplishing the repair before the
effective date of this AD in accordance with
the Bombardier repair drawings in Table 1 of
this AD is acceptable for compliance with the
requirements of this AD.
between the forward attachment fittings of
the horizontal stabilizer and the top rib of the
vertical stabilizer, with solid shims and
replace the corresponding barrel nut and
retainer with new parts, in accordance with
Part B of the service bulletin.
TABLE 1.—REPAIR DRAWINGS
No Reporting
(m) Although the service bulletin
referenced in this AD specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
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:
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
RD
RD
RD
RD
RD
issue
8/4–55–083
8/4–55–084
8/4–55–089
8/4–55–090
3
1
2
3
RD 8/4–55–093
RD 8/4–55–094
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Bombardier
repair drawing
2
3
RD 8/4–55–106
RD 8/4–55–110
RD 8/4–55–138
2
3
1
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2005–20403;
Directorate Identifier 2005–NM–144–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 14, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400 series airplanes, certificated in
any category; serial numbers 4001, and 4003
through 4081 inclusive.
Unsafe Condition
(d) This AD results from a report indicating
that laminated shims were delaminated and
extruded from the interface between the
forward attaching fittings of horizontal
stabilizer and the top rib of the vertical
stabilizer, and that inadequate torque values
of some bolts were found. We are issuing this
AD to prevent reduced structural integrity of
the horizontal stabilizer, and consequent loss
of 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.
Service Information
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–02, Revision ‘A,’ dated January 12,
2005.
(g) Accomplishing a detailed inspection, a
breakaway torque check, and corrective
actions if necessary before the effective date
of this AD in accordance with Bombardier
Service Bulletin 84–55–02, dated December
11, 2003, is acceptable for compliance with
the corresponding requirements of this AD.
VerDate Aug<18>2005
15:58 Sep 13, 2005
Jkt 205001
Dated
April 16, 2003.
May 5, 2003.
June 6, 2003.
August 26,
2003.
June 20, 2003.
September 4,
2003.
July 31, 2003.
October 1, 2003.
October 29,
2003.
Detailed Inspection and Torque Check
(i) Within 4,000 flight hours after the
effective date of this AD, do the actions
specified in paragraphs (i)(1) and (i)(2) of this
AD in accordance with Part A of the service
bulletin.
(1) Do a detailed inspection of the
laminated shims for cracks, damage, or
extrusion between the forward attachment
fittings of the horizontal stabilizer and the
top rib of the vertical stabilizer.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(2) Do a breakaway torque check of the six
attachment bolts in the attachment fittings of
the front, middle, and rear spars.
Corrective Actions
(j) If, during the inspection required by
paragraph (i)(1) of this AD, any cracked,
damaged, or extruded laminated shim is
found, before further flight, replace the
discrepant laminated shim with a solid shim,
and replace the attachment bolts, barrel nuts,
and retainers of both front spars with new
parts, in accordance with Parts A and B of
the service bulletin.
(k) If, during the torque check required by
paragraph (i)(2) of this AD, any attachment
bolt is found with a breakaway torque value
outside the limits specified in the service
bulletin, before further flight, replace the
attachment bolt and its corresponding barrel
nut and retainer with new parts, in
accordance with Part A of the service
bulletin.
Replacement of Laminated Shims
(l) Within 8,000 flight hours after the
effective date of this AD, unless previously
accomplished in accordance with paragraph
(j) of this AD, replace the laminated shims,
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
Alternative Methods of Compliance
(AMOCs)
(n) 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.
Related Information
(o) Canadian airworthiness directive CF–
2005–07, issued March 21, 2005, also
addresses the subject of this AD.
Issued in Renton, Washington, on
September 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–18208 Filed 9–13–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20402; Directorate
Identifier 2005–NM–133–AD]
RIN 2120–AA64
Airworthiness Directives; Sabreliner
Model NA–265, NA–265–20, NA–265–
30, NA–265–40, NA–265–50, NA–265–
60, NA–265–65, NA–265–70, and NA–
265–80 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 certain
Sabreliner Model NA–265–40, NA–265–
50, NA–265–60, NA–265–70, and NA–
265–80 series airplanes. The existing
AD currently requires repetitive
inspections for discrepancies in the
front and rear spars of the wing in the
area of the wing center section, and in
the lugs on the rear spar and wing
trailing edge panel rib, and corrective
actions if necessary. This proposed AD
would expand the applicability of the
existing AD and require new repetitive
inspections for fuel leaks of the front
E:\FR\FM\14SEP1.SGM
14SEP1
]]>Agencies
[Federal Register Volume 70, Number 177 (Wednesday, September 14, 2005)]
[Proposed Rules]
[Pages 54316-54318]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18208]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20403; Directorate Identifier 2005-NM-144-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier Model DHC-8-400 series airplanes. This proposed
AD would require an inspection of the laminated shims for cracks,
damage, or extrusion between the forward attachment fittings of the
horizontal stabilizer and the top rib of the vertical stabilizer; a
torque check of the attachment bolts in the attachment fittings of the
front, middle, and rear spars; and corrective actions if necessary.
This proposed AD results from a report indicating that delaminated
shims extruded from the interface between the forward attaching
fittings of horizontal stabilizer and the top rib of the vertical
stabilizer, and that inadequate torque values of some bolts were found.
We are proposing this AD to prevent reduced structural integrity of the
horizontal stabilizer, and consequent loss of controllability of the
airplane.
DATES: We must receive comments on this proposed AD by October 14,
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.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 256-7525; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
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 in the ADDRESSES section. Include the docket number ``FAA-2005-
20403; Directorate Identifier 2005-NM-144-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
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
[[Page 54317]]
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
certain Bombardier Model DHC-8-400 series airplanes. TCCA advises that
delaminated shims extruded from the interface between the forward
attaching fittings of horizontal stabilizer and the top rib of the
vertical stabilizer. In addition, during removal of the horizontal
stabilizer for replacing the laminated shims with solid shims,
inadequate torque values of some bolts at the six attachment locations
(two each at the front, middle, and rear spars) were found on some
airplanes. This can cause increased load on the bolts and consequent
reduction in fatigue life of the bolts. These conditions, if not
corrected, could result in reduced structural integrity of the
horizontal stabilizer, and consequent loss of controllability of the
airplane.
Relevant Service Information
Bombardier has issued Service Bulletin 84-55-02, Revision ``A,''
dated January 12, 2005. The service bulletin describes doing the
following procedures:
A detailed inspection of the laminated shims for cracks,
damage, or extrusion between the forward attachment fittings of the
horizontal stabilizer and the top rib of the vertical stabilizers;
A breakaway torque check of the six attachment bolts in
the attachment fittings of the front, middle, and rear spars; and
Corrective actions if necessary. The corrective actions
include replacing the laminated shims, between the forward attachment
fittings of the horizontal stabilizer and the top rib of the vertical
stabilizer, with solid shims and replacing the corresponding barrel nut
and retainer with new parts.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. TCCA mandated the
service information and issued Canadian airworthiness directive CF-
2005-07, issued March 21, 2005, to ensure the continued airworthiness
of these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. We have examined TCCA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Difference Between
the Proposed AD and the Service Bulletin.''
Difference Between the Proposed AD and Service Bulletin
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletin describe procedures for
submitting a sheet recording torque values to the airplane
manufacturer, this proposed AD would not require that action. We do not
need this information from operators.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection and torque check 2 $65 None.............................. $130 19 $2,470
Replacement......................... 30 65 Free of charge.................... 1,950 19 37,050
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 and placed it in the
[[Page 54318]]
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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2005-
20403; Directorate Identifier 2005-NM-144-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
14, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400 series
airplanes, certificated in any category; serial numbers 4001, and
4003 through 4081 inclusive.
Unsafe Condition
(d) This AD results from a report indicating that laminated
shims were delaminated and extruded from the interface between the
forward attaching fittings of horizontal stabilizer and the top rib
of the vertical stabilizer, and that inadequate torque values of
some bolts were found. We are issuing this AD to prevent reduced
structural integrity of the horizontal stabilizer, and consequent
loss of 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.
Service Information
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Bombardier Service Bulletin 84-55-02,
Revision `A,' dated January 12, 2005.
(g) Accomplishing a detailed inspection, a breakaway torque
check, and corrective actions if necessary before the effective date
of this AD in accordance with Bombardier Service Bulletin 84-55-02,
dated December 11, 2003, is acceptable for compliance with the
corresponding requirements of this AD.
(h) Accomplishing the repair before the effective date of this
AD in accordance with the Bombardier repair drawings in Table 1 of
this AD is acceptable for compliance with the requirements of this
AD.
Table 1.--Repair Drawings
------------------------------------------------------------------------
RD
Bombardier repair drawing issue Dated
------------------------------------------------------------------------
RD 8/4-55-083........................ 3 April 16, 2003.
RD 8/4-55-084........................ 1 May 5, 2003.
RD 8/4-55-089........................ 2 June 6, 2003.
RD 8/4-55-090........................ 3 August 26, 2003.
RD 8/4-55-093........................ 2 June 20, 2003.
RD 8/4-55-094........................ 3 September 4, 2003.
RD 8/4-55-106........................ 2 July 31, 2003.
RD 8/4-55-110........................ 3 October 1, 2003.
RD 8/4-55-138........................ 1 October 29, 2003.
------------------------------------------------------------------------
Detailed Inspection and Torque Check
(i) Within 4,000 flight hours after the effective date of this
AD, do the actions specified in paragraphs (i)(1) and (i)(2) of this
AD in accordance with Part A of the service bulletin.
(1) Do a detailed inspection of the laminated shims for cracks,
damage, or extrusion between the forward attachment fittings of the
horizontal stabilizer and the top rib of the vertical stabilizer.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(2) Do a breakaway torque check of the six attachment bolts in
the attachment fittings of the front, middle, and rear spars.
Corrective Actions
(j) If, during the inspection required by paragraph (i)(1) of
this AD, any cracked, damaged, or extruded laminated shim is found,
before further flight, replace the discrepant laminated shim with a
solid shim, and replace the attachment bolts, barrel nuts, and
retainers of both front spars with new parts, in accordance with
Parts A and B of the service bulletin.
(k) If, during the torque check required by paragraph (i)(2) of
this AD, any attachment bolt is found with a breakaway torque value
outside the limits specified in the service bulletin, before further
flight, replace the attachment bolt and its corresponding barrel nut
and retainer with new parts, in accordance with Part A of the
service bulletin.
Replacement of Laminated Shims
(l) Within 8,000 flight hours after the effective date of this
AD, unless previously accomplished in accordance with paragraph (j)
of this AD, replace the laminated shims, between the forward
attachment fittings of the horizontal stabilizer and the top rib of
the vertical stabilizer, with solid shims and replace the
corresponding barrel nut and retainer with new parts, in accordance
with Part B of the service bulletin.
No Reporting
(m) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(n) 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.
Related Information
(o) Canadian airworthiness directive CF-2005-07, issued March
21, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on September 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-18208 Filed 9-13-05; 8:45 am]
BILLING CODE 4910-13-P
