Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 Series Airplanes, 14721-14724 [E7-5668]
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Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules
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.
Inspections
(f) At the later of the times specified in
paragraphs (f)(1) and (f)(2) of this AD: Do the
initial inspections specified in Table 1 of this
AD in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–30A2080, Revision 2, dated September
14, 2006. Correct any discrepancy before
further flight in accordance with the service
bulletin. Repeat the inspections at the
applicable time specified in Table 1 of this
AD.
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(1) Within 18 calendar months since the
date of issuance of the original standard
airworthiness certificate or within 18
calendar months since the date of issuance of
the original export certificate of
airworthiness.
(2) Within 90 calendar days after the
effective date of this AD.
TABLE 1.—INSPECTIONS
Do a general visual inspection of the forward
and aft cargo compartments, as applicable,
for—
And repeat the inspection at intervals not to
exceed—
Until—
Foreign object debris (FOD) or contamination
on, near, or around the potable water supply
and gray water drain lines.
Indications of heat damage, exposed foam insulation, or missing or damaged protective
tape of all heater tape on the potable water
supply and gray water drain lines.
600 flight hours ................................................
The heater tape replacement required by
paragraph (g) of this AD is done.
1,800 flight hours .............................................
The heater tape replacement required by
paragraph (g) of this AD is done.
Terminating Action
(g) At the applicable time specified in
Table 2 of this AD: Replace the heater tape
on the potable water supply and gray water
drain lines of the forward and aft cargo
compartments, as applicable, with Adel
Wiggins ribbon heaters. Do the actions in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–30A2080, Revision 2, dated September
14, 2006. This replacement terminates the
requirements of paragraph (f) of this AD.
TABLE 2.—COMPLIANCE TIME FOR TERMINATING ACTION
For airplanes on which the heater tape has—
Replace the heater tape at the later of—
(1) Not been replaced before the effective date
of this AD in accordance with Boeing Alert
Service Bulletin 747–30A2079, dated December 12, 2002; Revision 1, dated October 16,
2003; or Revision 2, dated December 16,
2004.
(2) Been replaced before the effective date of
this AD in accordance with Boeing Alert
Service Bulletin 747–30A2079, dated December 12, 2002; Revision 1, dated October 16,
2003; or Revision 2, dated December 16,
2004.
Within 42 months since the date of issuance
of the original standard airworthiness certificate or the date of issuance of the original
export certificate of airworthiness, whichever occurs first.
24 months after the effective date of this AD.
Within 42 months after the heater tape was
replaced.
24 months after the effective date of this AD.
Provisions for Previous Accomplished Work
pwalker on PROD1PC71 with PROPOSALS
(h) Actions done before the effective date
of this AD in accordance with Boeing Alert
Service Bulletin 747–30A2080—either the
original version dated December 16, 2004, or
Revision 1, dated August 18, 2005—are
acceptable for compliance with the
corresponding requirements of this AD;
except, for Group 2, Configuration 2 and
Configuration 3 airplanes, as defined in
Revision 2 of the service bulletin, additional
work is required in the forward cargo
compartment, as specified in Parts 1, 2, and
3 of the service bulletin and required by this
AD.
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on March
20, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–5667 Filed 3–28–07; 8:45 am]
BILLING CODE 4910–13–P
18:15 Mar 28, 2007
Jkt 211001
PO 00000
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27713; Directorate
Identifier 2006–NM–240–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–100, DHC–8–200, and
DHC–8–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
VerDate Aug<31>2005
DEPARTMENT OF TRANSPORTATION
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–100,
DHC–8–200, and DHC–8–300 series
airplanes. This proposed AD would
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Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules
pwalker on PROD1PC71 with PROPOSALS
require, for certain airplanes,
modification of the upper bearing of the
main landing gear (MLG) shock strut.
This proposed AD would also require,
for certain airplanes, revising the DHC–
8 Maintenance Program Manual to
include the MLG shock strut servicing
task. This proposed AD results from
reports of over-extension of the MLG
shock strut piston, which allows the
torque links to go over-center and rest
on the piston. We are proposing this AD
to prevent loss in shock absorption
during touchdown and failure of the
shock strut housing, which could result
in a subsequent loss of directional
control.
DATES: We must receive comments on
this proposed AD by April 30, 2007.
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:
Mazdak Hobbi, 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) 228–7330; 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–2007–27713; Directorate
Identifier 2006–NM–240–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
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18:15 Mar 28, 2007
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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.
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–8–100, DHC–
8–200, and DHC–8–300 series airplanes.
TCCA advises that there have been six
cases reported in which the main
landing gear (MLG) shock strut piston
over-extended, allowing the torque links
to go over-center and rest on the piston.
Investigation has revealed that overextension of the shock strut resulted
from damage to the upper bearing and
seal carrier, caused by a loss of internal
damping.
Over-extension of the MLG shock
strut piston, if not corrected, could
result in loss in shock absorption during
touchdown and failure of the shock
strut housing, which could result in a
subsequent loss of directional control.
Relevant Service Information
Bombardier has issued Service
Bulletin 8–32–144, Revision ‘A,’ dated
April 29, 2002, including MessierDowty Service Bulletin M–DT SBDHC8–
32–82, Revision 1, dated July 5, 2001
(for Model DHC–8–311, –314, and –315
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airplanes). The service bulletin
describes procedures for modifying the
upper bearing in each MLG. The
modification includes an inspection of
the two halves of the upper bearing for
wear and damage, the removal of the
needle roller from the upper bearing, an
inspection of the cylinder bore for
damage and wear, and corrective action
if necessary. The corrective action
includes replacing the upper bearing
with a new bearing and contacting the
parts manufacturer if damage or wear
that exceeds the maximum diameter is
found on the cylinder bore.
Bombardier has issued the following
de Havilland Dash 8 maintenance task
cards to the applicable Bombardier
DHC–8 Maintenance Program Manual
(Program Support Manuals 1–8–7, 1–
82–7, and 1–83–7). These tasks describe
procedures for servicing the MLG shock
struts:
• Dash 8 Series 100 Maintenance
Task Card 3210/15, dated June 22, 2005;
• Dash 8 Series 200 Maintenance
Task Card 3210/15, dated June 22, 2005;
and
• Dash 8 Series 300 Maintenance
Task Card 3210/15, dated November 29,
2005.
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–2006–14,
effective July 21, 2006, to ensure the
continued airworthiness of these
airplanes in Canada.
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 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, for certain
airplanes, accomplishing the actions
specified in the service bulletin
described previously, and, for certain
airplanes, revising the applicable DCH–
8 Maintenance Program Manual to
include the MLG shock strut servicing
Task 3210/15, except as discussed
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Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules
under ‘‘Difference Between the
Proposed AD and the Service Bulletin.’’
Difference Between the Proposed AD
and the Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions using
a method that we or TCCA (or its
delegated agent) approve. In light of the
type of repair that would be required to
address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
14723
a repair we or TCCA approve would be
acceptable for compliance with this
proposed AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Work hours
Modification ........................................................
Manual Revision ................................................
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.
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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.
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Average
labor rate
per hour
4
1
Parts
$80
80
$274
0
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed 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, 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]
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–2007–27713;
Directorate Identifier 2006–NM–240–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 30, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–101, –102, –103, –106, –201, –202,
–301, –311, –314, and –315 airplanes,
certificated in any category; serial numbers
003 through 618 inclusive.
Unsafe Condition
(d) This AD results from reports of overextension of the main landing gear (MLG)
shock strut piston, which allows the torque
links to go over-center and rest on the piston.
We are issuing this AD to prevent loss in
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Number of U.S.registered
airplanes
Cost per
airplane
$594
80
Up to 135 .........
135 ...................
Fleet cost
Up to $80,190.
$10,800.
shock absorption during touchdown and
failure of the shock strut housing, which
could result in a subsequent loss of
directional control.
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.
Modification of the Upper Bearing
(f) For Model DHC–8–311, –314, and –315
airplanes, serial numbers 202 through 516
inclusive, with MLG shock struts having any
serial number DCL3501/90 through
DCL3768/97 inclusive installed: Within
3,000 flight hours after the effective date of
this AD, modify the upper bearing in each
MLG (including doing inspections of the
upper bearing and cylinder bore for wear and
damage, and doing all applicable corrective
actions) in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–32–144, Revision ‘A,’
dated April 29, 2002, including MessierDowty Service Bulletin M–DT SBDHC8–32–
82, Revision 1, dated July 5, 2001, except if
wear exceeds the maximum diameter
specified in the service bulletin for the
cylinder bore or if damage is found on the
cylinder bore, before further flight, repair
using a method approved by either the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or
Transport Canada Civil Aviation (TCCA) (or
its delegated agent). Do all applicable
corrective actions before further flight.
Revision of the Maintenance Program
Manual
(g) For Model DHC–8–101, –102, –103,
–106, –201, –202, –301, –311, –314, and –315
airplanes, serial numbers 003 through 614
inclusive: Within 30 days after the effective
date of this AD, revise Part 1 of the
applicable DHC–8 Maintenance Program
Manual by incorporating the applicable MLG
shock strut servicing Task 3210/15 specified
in Table 1 of this AD.
Note 1: This may be done by inserting
copies of the applicable task into the
applicable maintenance program manual.
When these tasks have been included in the
general revisions of the applicable
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Federal Register / Vol. 72, No. 60 / Thursday, March 29, 2007 / Proposed Rules
maintenance program manual, the general
revisions may be inserted in the applicable
maintenance program manual and the copy
of the task may be removed from the
maintenance program manual.
TABLE 1.—TASKS
To the
program
support manual
(PSM)—
Task—
Dated—
Dash 8 Series 100 Maintenance Task
Card 3210/15.
Dash 8 Series 200 Maintenance Task
Card 3210/15.
Dash 8 Series 300 Maintenance Task
Card 3210/15.
June 22, 2005 ........................................
1–8–7
DHC–8–100 Series Airplanes.
June 22, 2005 ........................................
1–82–7
DHC–8–200 Series Airplanes.
November 29, 2005 ...............................
1–83–7
DHC–8–300 Series Airplanes.
Parts Installation
(h) After the effective date of this AD, no
person may install a part identified in
paragraphs (h)(1) and (h)(2) of this AD, as a
replacement during the repair or overhaul of
any shock strut assembly, on any airplane.
(1) Upper bearing, part number 10130–3 or
10130–551.
(2) Damper ring, part number 10129–3 or
10129–551.
(i) After the effective date of this AD, only
the parts identified in paragraphs (i)(1) and
(i)(2) of this AD may be installed on any
airplane as replacement upper bearings and
damper rings during the repair or overhaul of
any shock strut assembly, except as provided
by paragraph (j) of this AD.
(1) Upper bearing, part number 10130–5.
(2) Damper ring, part number 10129–5 or
10129–533.
(j) After the effective date of this AD, only
MLGs with a reworked, oversize cylinder
bore (part number identified in the
applicable component maintenance manual
(CMM)) that have parts identified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD
used in accordance with the applicable CMM
may be installed on any airplane.
(1) Upper bearing, part number CRS85–
167–11.
(2) Damper ring, part number CRS85–167–
31 or CRS85–167–33.
(3) Seal carrier, part number CRS85–167–
21.
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Credit for Actions Done Using Previous
Service Information
(k) Modifications accomplished before the
effective date of this AD in accordance with
Bombardier Service Bulletin 8–32–144, dated
August 10, 1998, including Messier-Dowty
Service Bulletin M–DT SBDCH8–32–82,
dated March 9, 1998, are considered
acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
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18:15 Mar 28, 2007
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Flight Standards Certificate Holding District
Office.
Related Information
(m) Canadian airworthiness directive CF–
2006–14, effective July 21, 2006, also
addresses the subject of this AD.
Issued in Renton, Washington, on March
20, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–5668 Filed 3–28–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–26966; Directorate
Identifier 99–NE–01–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation AE 3007A and AE 3007C
Series Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Rolls-Royce
Corporation (RRC) AE 3007A and AE
3007C series turbofan engines. That AD
currently prohibits any flight following
a ground engine start where the engine
oil temperature is below 32 °F (0 °C),
unless certain preflight operational
procedures are followed. This proposed
AD would also require those actions,
and would also require a terminating
action. This proposed AD would
supersede the compliance requirements
of AD 99–02–51 and all related
alternative methods of compliance
(AMOCs). This proposed AD results
from design improvements to
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For model—
components in the accessory gearbox air
turbine starter mounting pad. We are
proposing this AD to prevent an inflight engine shutdown due to loss of
engine oil from the starter shaft seal.
DATES: We must receive any comments
on this proposed AD by May 29, 2007.
ADDRESSES: Use one of the following
addresses to comment 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–
0001.
• 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 Rolls-Royce Corporation, P.O.
Box 420, Indianapolis, IN 46206;
telephone (317) 230–3774; fax (317)
230–8084; e-mail:
indy.pubs.services@rolls-royce.com, to
get the service information identified in
this proposed AD.
FOR FURTHER INFORMATION CONTACT: Kyri
Zaroyiannis, Aerospace Engineer,
Chicago Aircraft Certification Office,
Small Airplane Directorate, FAA, 2300
E. Devon Ave., Des Plaines, IL 60018;
telephone (847) 294–7836; fax (847)
294–7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
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]]>Agencies
[Federal Register Volume 72, Number 60 (Thursday, March 29, 2007)]
[Proposed Rules]
[Pages 14721-14724]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-5668]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27713; Directorate Identifier 2006-NM-240-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100, DHC-8-200,
and DHC-8-300 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-8-100, DHC-8-200, and DHC-8-300 series
airplanes. This proposed AD would
[[Page 14722]]
require, for certain airplanes, modification of the upper bearing of
the main landing gear (MLG) shock strut. This proposed AD would also
require, for certain airplanes, revising the DHC-8 Maintenance Program
Manual to include the MLG shock strut servicing task. This proposed AD
results from reports of over-extension of the MLG shock strut piston,
which allows the torque links to go over-center and rest on the piston.
We are proposing this AD to prevent loss in shock absorption during
touchdown and failure of the shock strut housing, which could result in
a subsequent loss of directional control.
DATES: We must receive comments on this proposed AD by April 30, 2007.
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: Mazdak Hobbi, 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) 228-7330; 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-2007-
27713; Directorate Identifier 2006-NM-240-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.
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-8-100, DHC-8-200, and DHC-8-300 series
airplanes. TCCA advises that there have been six cases reported in
which the main landing gear (MLG) shock strut piston over-extended,
allowing the torque links to go over-center and rest on the piston.
Investigation has revealed that over-extension of the shock strut
resulted from damage to the upper bearing and seal carrier, caused by a
loss of internal damping.
Over-extension of the MLG shock strut piston, if not corrected,
could result in loss in shock absorption during touchdown and failure
of the shock strut housing, which could result in a subsequent loss of
directional control.
Relevant Service Information
Bombardier has issued Service Bulletin 8-32-144, Revision `A,'
dated April 29, 2002, including Messier-Dowty Service Bulletin M-DT
SBDHC8-32-82, Revision 1, dated July 5, 2001 (for Model DHC-8-311, -
314, and -315 airplanes). The service bulletin describes procedures for
modifying the upper bearing in each MLG. The modification includes an
inspection of the two halves of the upper bearing for wear and damage,
the removal of the needle roller from the upper bearing, an inspection
of the cylinder bore for damage and wear, and corrective action if
necessary. The corrective action includes replacing the upper bearing
with a new bearing and contacting the parts manufacturer if damage or
wear that exceeds the maximum diameter is found on the cylinder bore.
Bombardier has issued the following de Havilland Dash 8 maintenance
task cards to the applicable Bombardier DHC-8 Maintenance Program
Manual (Program Support Manuals 1-8-7, 1-82-7, and 1-83-7). These tasks
describe procedures for servicing the MLG shock struts:
Dash 8 Series 100 Maintenance Task Card 3210/15, dated
June 22, 2005;
Dash 8 Series 200 Maintenance Task Card 3210/15, dated
June 22, 2005; and
Dash 8 Series 300 Maintenance Task Card 3210/15, dated
November 29, 2005.
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-
2006-14, effective July 21, 2006, to ensure the continued airworthiness
of these airplanes in Canada.
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
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, for
certain airplanes, accomplishing the actions specified in the service
bulletin described previously, and, for certain airplanes, revising the
applicable DCH-8 Maintenance Program Manual to include the MLG shock
strut servicing Task 3210/15, except as discussed
[[Page 14723]]
under ``Difference Between the Proposed AD and the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method that we or TCCA
(or its delegated agent) approve. In light of the type of repair that
would be required to address the unsafe condition, and consistent with
existing bilateral airworthiness agreements, we have determined that,
for this proposed AD, a repair we or TCCA approve would be acceptable
for compliance with this proposed AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Parts Cost per Number of U.S.-registered Fleet cost
per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification.......................... 4 $80 $274 $594 Up to 135.................... Up to $80,190.
Manual Revision....................... 1 80 0 80 135.......................... $10,800.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 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-2007-
27713; Directorate Identifier 2006-NM-240-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 30,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-101, -102, -103, -
106, -201, -202, -301, -311, -314, and -315 airplanes, certificated
in any category; serial numbers 003 through 618 inclusive.
Unsafe Condition
(d) This AD results from reports of over-extension of the main
landing gear (MLG) shock strut piston, which allows the torque links
to go over-center and rest on the piston. We are issuing this AD to
prevent loss in shock absorption during touchdown and failure of the
shock strut housing, which could result in a subsequent loss of
directional control.
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.
Modification of the Upper Bearing
(f) For Model DHC-8-311, -314, and -315 airplanes, serial
numbers 202 through 516 inclusive, with MLG shock struts having any
serial number DCL3501/90 through DCL3768/97 inclusive installed:
Within 3,000 flight hours after the effective date of this AD,
modify the upper bearing in each MLG (including doing inspections of
the upper bearing and cylinder bore for wear and damage, and doing
all applicable corrective actions) in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-32-144,
Revision `A,' dated April 29, 2002, including Messier-Dowty Service
Bulletin M-DT SBDHC8-32-82, Revision 1, dated July 5, 2001, except
if wear exceeds the maximum diameter specified in the service
bulletin for the cylinder bore or if damage is found on the cylinder
bore, before further flight, repair using a method approved by
either the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or Transport Canada Civil Aviation (TCCA)
(or its delegated agent). Do all applicable corrective actions
before further flight.
Revision of the Maintenance Program Manual
(g) For Model DHC-8-101, -102, -103, -106, -201, -202, -301, -
311, -314, and -315 airplanes, serial numbers 003 through 614
inclusive: Within 30 days after the effective date of this AD,
revise Part 1 of the applicable DHC-8 Maintenance Program Manual by
incorporating the applicable MLG shock strut servicing Task 3210/15
specified in Table 1 of this AD.
Note 1: This may be done by inserting copies of the applicable
task into the applicable maintenance program manual. When these
tasks have been included in the general revisions of the applicable
[[Page 14724]]
maintenance program manual, the general revisions may be inserted in
the applicable maintenance program manual and the copy of the task
may be removed from the maintenance program manual.
Table 1.--Tasks
----------------------------------------------------------------------------------------------------------------
To the program
Task-- Dated-- support manual For model--
(PSM)--
----------------------------------------------------------------------------------------------------------------
Dash 8 Series 100 Maintenance Task Card June 22, 2005............. 1-8-7 DHC-8-100 Series
3210/15. Airplanes.
Dash 8 Series 200 Maintenance Task Card June 22, 2005............. 1-82-7 DHC-8-200 Series
3210/15. Airplanes.
Dash 8 Series 300 Maintenance Task Card November 29, 2005......... 1-83-7 DHC-8-300 Series
3210/15. Airplanes.
----------------------------------------------------------------------------------------------------------------
Parts Installation
(h) After the effective date of this AD, no person may install a
part identified in paragraphs (h)(1) and (h)(2) of this AD, as a
replacement during the repair or overhaul of any shock strut
assembly, on any airplane.
(1) Upper bearing, part number 10130-3 or 10130-551.
(2) Damper ring, part number 10129-3 or 10129-551.
(i) After the effective date of this AD, only the parts
identified in paragraphs (i)(1) and (i)(2) of this AD may be
installed on any airplane as replacement upper bearings and damper
rings during the repair or overhaul of any shock strut assembly,
except as provided by paragraph (j) of this AD.
(1) Upper bearing, part number 10130-5.
(2) Damper ring, part number 10129-5 or 10129-533.
(j) After the effective date of this AD, only MLGs with a
reworked, oversize cylinder bore (part number identified in the
applicable component maintenance manual (CMM)) that have parts
identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD used
in accordance with the applicable CMM may be installed on any
airplane.
(1) Upper bearing, part number CRS85-167-11.
(2) Damper ring, part number CRS85-167-31 or CRS85-167-33.
(3) Seal carrier, part number CRS85-167-21.
Credit for Actions Done Using Previous Service Information
(k) Modifications accomplished before the effective date of this
AD in accordance with Bombardier Service Bulletin 8-32-144, dated
August 10, 1998, including Messier-Dowty Service Bulletin M-DT
SBDCH8-32-82, dated March 9, 1998, are considered acceptable for
compliance with the corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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
(m) Canadian airworthiness directive CF-2006-14, effective July
21, 2006, also addresses the subject of this AD.
Issued in Renton, Washington, on March 20, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-5668 Filed 3-28-07; 8:45 am]
BILLING CODE 4910-13-P
