Airworthiness Directives; Bombardier Model DHC-8-401 and -402 Airplanes, 34409-34411 [05-11709]
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules
Repair
(m) If any crack is found during any
inspection, preventative modification, or
repair required by this AD, before further
flight, do the applicable repair (including
HFEC inspection) specified in paragraph
(m)(1) or (m)(2) of this AD, as applicable.
Doing the repair terminates the repetitive
inspections required by paragraph (g)(1) of
this AD. Doing the repair is acceptable for
compliance with the requirements of
paragraph (j) of this AD provided the repair
is done within the time specified in that
paragraph.
(1) If the crack does not exceed the limits
described in the alert service bulletin, repair
the crack in accordance with the applicable
procedures in the Accomplishment
Instructions of the alert service bulletin,
except as provided by paragraph (n) of this
AD.
(2) If the crack exceeds the limits described
in the alert service bulletin and the alert
service bulletin specifies to contact Boeing or
if the alert service bulletin specifies to repair
before further flight and contact the Boeing
company: Repair in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA; or
according to data meeting the certification
basis of the airplane approved by an
Authorized Representative (AR) for the
Boeing Delegation Option Authorization
(DOA) Organization who has been authorized
by the Manager, Seattle ACO, to make those
findings. For a repair method to be approved,
the repair must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(n) Where Figures 5 and 6 of the
Accomplishment Instructions of the alert
service bulletin specify code F, this AD
requires operators to refer to code D in
Figures 5 and 6 of the Accomplishment
Instructions of the alert service bulletin.
Post Repair/Preventative Modification
Inspections
(o) At the later of the times specified in
paragraphs (o)(1) or (o)(2) of this AD, do the
action specified in paragraph (p) of this AD.
(1) Within 40,000 flight cycles after doing
the repair or preventative modification in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 727–
53–0198, dated January 11, 1990; or Revision
1, dated July 25, 1991; or the alert service
bulletin. If a repair/preventative modification
specified in the original or Revision 1 of the
service bulletin has been done and additional
repair/preventative modification actions
specified in the alert service bulletin have
also been done, the flight cycles must be
counted from the first repair/preventative
modification.
(2) Within 3,000 flight cycles after the
effective date of this AD.
(p) At the time specified in paragraph (o)
of this AD, do the inspections specified in
paragraphs (p)(1) and (p)(2) of this AD in
accordance with the Accomplishment
Instructions of the alert service bulletin. If
any crack is found, before further flight, do
the repair specified in paragraph (m) of this
AD.
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(1) Do an HFEC inspection for cracks of the
bear strap. Repeat the inspection thereafter at
intervals not to exceed 20,000 flight cycles.
(2) Do a detailed inspection for cracks of
any repair and preventative modification and
its periphery. Repeat the inspection
thereafter at intervals not to exceed 3,000
flight cycles.
No Requirement to Contact Boeing
(q) Although paragraphs 3.B.9. and 3.B.10.
of the Accomplishment Instructions of the
alert service bulletin specify to contact
Boeing after repairing cracks, this AD does
not include that requirement.
Alternative Methods of Compliance
(AMOCs)
(r)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19.
(2) The inspections specified in paragraphs
(o) and (p) of this AD are approved as a
method of compliance (MOC) to paragraph
(g) of AD 98–11–03 R1, amendment 39–
10983, for the inspections of Structurally
Significant Items (SSI) F–13A and F–14A of
Supplemental Structural Inspection
Document (SSID), D6–48040–1, affected by
the repair or modification. The MOC applies
only to the areas inspected in accordance
with the alert service bulletin. All provisions
of AD 98–11–03 R1 that are not specifically
referenced in paragraphs (r)(2) and (r)(3) of
this AD remain fully applicable and must be
complied with.
(3) For airplanes on which no repair or
preventative modification has been done in
accordance with Boeing Service Bulletin
727–53–0198, dated January 11, 1990; or
Revision 1, dated July 25, 1991; or the alert
service bulletin: The inspections and actions
specified in paragraph (g) of this AD are
approved as a MOC to paragraph (c) of AD
98–11–03 R1 for the inspections of SSI F–
13A and F–14A of SSID, D6–48040–1. This
MOC applies only to the areas inspected in
accordance with the alert service bulletin. All
other provisions of AD 98–11–03 R1 that are
not specifically referenced in paragraphs
(r)(2) and (r)(3) of this AD remain fully
applicable and must be complied with.
Issued in Renton, Washington, on May 27,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11708 Filed 6–13–05; 8:45 am]
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34409
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21435; Directorate
Identifier 2004–NM–163–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–401 and -402 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–401
and -402 airplanes. This proposed AD
would require a one-time inspection of
the fuel and hydraulic tubes, and
corrective actions if necessary. This
proposed AD would also require
modifying fairlead plate assemblies.
This proposed AD is prompted by
reports of chafing between fuel and
hydraulic tubes and the fairlead plate
where the tubes pass through the
firewall. We are proposing this AD to
prevent chafing of the fuel and
hydraulic tubes, which could lead to
fuel and/or hydraulic fluid leakage in
the engine nacelle area and consequent
fire or explosion.
DATES: We must receive comments on
this proposed AD by July 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.
• By 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 in person at the Docket
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules
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–
21435; the directorate identifier for this
docket is 2004-NM–163-AD.
FOR FURTHER INFORMATION CONTACT:
Richard Fiesel, 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) 256–7504; 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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21435; Directorate Identifier 2004NM–163-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 submitted 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
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.
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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–8–401 and -402
airplanes. TCCA advises that service
difficulty reports indicate that chafing of
fuel and hydraulic tubes has been found
at the fairlead plate where the tubes
pass through the firewall. If the tubes
are not centered in the fairlead plate,
nacelle flexing can cause fouling or
chafing damage to existing hydraulic
and fuel pipes in the nacelle zone 3
area. This condition, if not corrected,
could result in fuel and/or hydraulic
fluid leakage in the engine nacelle area
and consequent fire or explosion.
Relevant Service Information
Bombardier has issued Service
Bulletin 84–54–09, Revision ‘‘B,’’ dated
June 15, 2004. The service bulletin
describes procedures for inspecting the
fuel and hydraulic tubes for nicks,
dents, chafing, or damage, and doing
corrective action if necessary. The
service bulletin also describes
procedures for modifying fairlead plate
assemblies. The corrective action, if
damage found during the inspections
exceeds the limit specified as
‘‘Acceptable’’ in the service bulletin,
includes reworking the tubes or
replacing the tubes with new tubes. The
service bulletin specifies that the
compliance time for the corrective
action is either 400 flight hours after the
inspection, or before further flight,
depending on the measurement of
damage found. 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–2004–07, dated April 14, 2004, to
ensure the continued airworthiness of
these airplanes in Canada.
Bombardier Service Bulletin 84–54–
09, Revision ‘‘B,’’ dated June 15, 2004,
refers to GKN Aerospace Services
Service Bulletin 1–71–20, dated April 7,
2004, as an additional source of service
information for modifying the fairlead
plate assemblies. The GKN service
bulletin is included in the Bombardier
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
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
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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 products 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.
Clarification of Actions In the Proposed
AD and Canadian Airworthiness
Directive
Although Canadian airworthiness
directive CF–2004–07 does not specify
to do an inspection of the fuel/hydraulic
tubes, the directive does specify to
install Bombardier Modsum 4–113438
(modified fairlead plate assemblies) in
accordance with Bombardier Service
Bulletin 84–54–09. The inspection is
included in the service bulletin and
TCCA does intend for the inspection to
be done as part of the modification.
Therefore, this proposed AD would
require an inspection of the fuel/
hydraulic tubes and modification of the
fairlead plate assemblies in accordance
with the service bulletin.
Costs of Compliance
This proposed AD would affect about
18 airplanes of U.S. registry. The
proposed actions would take about 4
work hours per airplane, at an average
labor rate of $65 per work hour.
Required parts would cost about $200
per airplane. Based on these figures, the
estimated cost of the proposed AD for
U.S. operators is $8,280, or $460 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
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Federal Register / Vol. 70, No. 113 / Tuesday, June 14, 2005 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly de Havilland,
Inc.): Docket No. FAA–2005–21435;
Directorate Identifier 2004–NM–163–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
July 14, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–401 and –402 airplanes, serial
numbers 4003 through 4089 inclusive,
certificated in any category.
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Unsafe Condition
(d) This AD was prompted by reports of
chafing between fuel and hydraulic tubes and
the fairlead plate where the tubes pass
through the firewall. We are issuing this AD
to prevent chafing of the fuel and hydraulic
tubes, which could lead to fuel and/or
hydraulic fluid leakage in the engine nacelle
area and consequent fire or explosion.
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 Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Bombardier Service Bulletin
84–54–09, Revision ‘‘B,’’ dated June 15, 2004.
Inspection, Corrective Action, and
Modification
(g) For airplanes on which Bombardier
Systems Drawings (SYD) 84–28–002 and SYD
84–29–006 have not been incorporated or on
which Modsum 4–184081 and Modsum 4–
184079 have not been incorporated: Within
500 flight hours after the effective date of this
AD, do the actions specified in paragraph (i)
of this AD.
(h) For airplanes on which Bombardier
SYD 84–28–002 and SYD 84–29–006 have
been incorporated or on which Modsum 4–
184081 and Modsum 4–184079 have been
incorporated: Within 4,000 flight hours after
the effective date of this AD, do the actions
specified in paragraph (i) of this AD.
(i) For airplanes identified in paragraphs
(g) and (h) of this AD at the times specified
in paragraphs (g) and (h) of this AD, do the
actions specified in paragraphs (i)(1) and
(i)(2) of this AD in accordance with the
service bulletin.
(1) Do a general visual inspection of the
fuel/hydraulic tubes for nicks, dents, chafing,
or damage. If any nick, dent, chafing, or
damage is found that is above the applicable
limit specified as ‘‘Acceptable’’ in the service
bulletin: Do the applicable corrective action
in accordance with the service bulletin at the
applicable time specified in the service
bulletin.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(2) Modify the fairlead plate assemblies in
accordance with the service bulletin.
Note 2: Bombardier Service Bulletin 84–
54–09, Revision ‘‘B,’’ dated June 15, 2004,
refers to GKN Aerospace Services Service
Bulletin 1–71–20, dated April 7, 2004, as an
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34411
additional source of service information for
modifying the fairlead plate assemblies. The
GKN service bulletin is included in the
Bombardier service bulletin.
Actions Done According to Previous Issue of
Service Bulletin
(j) Actions done before the effective date of
this AD in accordance with Bombardier
Service Bulletin 84–54–09, dated January 23,
2004; or Revision ‘‘A,’’ dated April 22, 2004;
are acceptable for compliance with the
corresponding requirements of this AD.
Parts Installation
(k) After the effective date of this AD, no
person may install a plate, part number
85415048–107, 85415048–108, 85415087–
107, or 85415087–108, on any airplane.
Alternative Methods of Compliance
(AMOCs)
(l) 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
(m) Canadian airworthiness directive CF–
2004–07, dated April 14, 2004, also addresses
the subject of this AD.
Issued in Renton, Washington, on May 27,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–11709 Filed 6–13–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002–NM–105–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–9–20, DC–9–30,
DC–9–40, and DC–9–50 Series
Airplanes; Model DC–9–14, DC–9–15,
and DC–9–15F Airplanes; Model DC–9–
81 (MD–81), DC–9–82 (MD–82), DC–9–
83 (MD–83), and DC–9–87 (MD–87)
Airplanes; Model MD–88 Airplanes;
and Model MD–90–30 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of
proposed rulemaking; reopening of
comment period.
AGENCY:
SUMMARY: This document revises an
earlier proposed airworthiness directive
(AD), applicable to certain McDonnell
Douglas transport category airplanes,
that would have required an inspection
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]]>Agencies
[Federal Register Volume 70, Number 113 (Tuesday, June 14, 2005)]
[Proposed Rules]
[Pages 34409-34411]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11709]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21435; Directorate Identifier 2004-NM-163-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-401 and -402
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-8-401 and -402 airplanes. This
proposed AD would require a one-time inspection of the fuel and
hydraulic tubes, and corrective actions if necessary. This proposed AD
would also require modifying fairlead plate assemblies. This proposed
AD is prompted by reports of chafing between fuel and hydraulic tubes
and the fairlead plate where the tubes pass through the firewall. We
are proposing this AD to prevent chafing of the fuel and hydraulic
tubes, which could lead to fuel and/or hydraulic fluid leakage in the
engine nacelle area and consequent fire or explosion.
DATES: We must receive comments on this proposed AD by July 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.
By 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 in person at the Docket
[[Page 34410]]
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-2005-21435; the directorate
identifier for this docket is 2004-NM-163-AD.
FOR FURTHER INFORMATION CONTACT: Richard Fiesel, 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) 256-7504; 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 under ADDRESSES. Include ``Docket No. FAA-2005-21435;
Directorate Identifier 2004-NM-163-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 submitted 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 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
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-8-401 and -402 airplanes. TCCA advises
that service difficulty reports indicate that chafing of fuel and
hydraulic tubes has been found at the fairlead plate where the tubes
pass through the firewall. If the tubes are not centered in the
fairlead plate, nacelle flexing can cause fouling or chafing damage to
existing hydraulic and fuel pipes in the nacelle zone 3 area. This
condition, if not corrected, could result in fuel and/or hydraulic
fluid leakage in the engine nacelle area and consequent fire or
explosion.
Relevant Service Information
Bombardier has issued Service Bulletin 84-54-09, Revision ``B,''
dated June 15, 2004. The service bulletin describes procedures for
inspecting the fuel and hydraulic tubes for nicks, dents, chafing, or
damage, and doing corrective action if necessary. The service bulletin
also describes procedures for modifying fairlead plate assemblies. The
corrective action, if damage found during the inspections exceeds the
limit specified as ``Acceptable'' in the service bulletin, includes
reworking the tubes or replacing the tubes with new tubes. The service
bulletin specifies that the compliance time for the corrective action
is either 400 flight hours after the inspection, or before further
flight, depending on the measurement of damage found. 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-2004-07, dated April 14,
2004, to ensure the continued airworthiness of these airplanes in
Canada.
Bombardier Service Bulletin 84-54-09, Revision ``B,'' dated June
15, 2004, refers to GKN Aerospace Services Service Bulletin 1-71-20,
dated April 7, 2004, as an additional source of service information for
modifying the fairlead plate assemblies. The GKN service bulletin is
included in the Bombardier 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 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 products 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.
Clarification of Actions In the Proposed AD and Canadian Airworthiness
Directive
Although Canadian airworthiness directive CF-2004-07 does not
specify to do an inspection of the fuel/hydraulic tubes, the directive
does specify to install Bombardier Modsum 4-113438 (modified fairlead
plate assemblies) in accordance with Bombardier Service Bulletin 84-54-
09. The inspection is included in the service bulletin and TCCA does
intend for the inspection to be done as part of the modification.
Therefore, this proposed AD would require an inspection of the fuel/
hydraulic tubes and modification of the fairlead plate assemblies in
accordance with the service bulletin.
Costs of Compliance
This proposed AD would affect about 18 airplanes of U.S. registry.
The proposed actions would take about 4 work hours per airplane, at an
average labor rate of $65 per work hour. Required parts would cost
about $200 per airplane. Based on these figures, the estimated cost of
the proposed AD for U.S. operators is $8,280, or $460 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
[[Page 34411]]
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 adding the following new
airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2005-
21435; Directorate Identifier 2004-NM-163-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by July 14, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-401 and -402
airplanes, serial numbers 4003 through 4089 inclusive, certificated
in any category.
Unsafe Condition
(d) This AD was prompted by reports of chafing between fuel and
hydraulic tubes and the fairlead plate where the tubes pass through
the firewall. We are issuing this AD to prevent chafing of the fuel
and hydraulic tubes, which could lead to fuel and/or hydraulic fluid
leakage in the engine nacelle area and consequent fire or explosion.
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 Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-09,
Revision ``B,'' dated June 15, 2004.
Inspection, Corrective Action, and Modification
(g) For airplanes on which Bombardier Systems Drawings (SYD) 84-
28-002 and SYD 84-29-006 have not been incorporated or on which
Modsum 4-184081 and Modsum 4-184079 have not been incorporated:
Within 500 flight hours after the effective date of this AD, do the
actions specified in paragraph (i) of this AD.
(h) For airplanes on which Bombardier SYD 84-28-002 and SYD 84-
29-006 have been incorporated or on which Modsum 4-184081 and Modsum
4-184079 have been incorporated: Within 4,000 flight hours after the
effective date of this AD, do the actions specified in paragraph (i)
of this AD.
(i) For airplanes identified in paragraphs (g) and (h) of this
AD at the times specified in paragraphs (g) and (h) of this AD, do
the actions specified in paragraphs (i)(1) and (i)(2) of this AD in
accordance with the service bulletin.
(1) Do a general visual inspection of the fuel/hydraulic tubes
for nicks, dents, chafing, or damage. If any nick, dent, chafing, or
damage is found that is above the applicable limit specified as
``Acceptable'' in the service bulletin: Do the applicable corrective
action in accordance with the service bulletin at the applicable
time specified in the service bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(2) Modify the fairlead plate assemblies in accordance with the
service bulletin.
Note 2: Bombardier Service Bulletin 84-54-09, Revision ``B,''
dated June 15, 2004, refers to GKN Aerospace Services Service
Bulletin 1-71-20, dated April 7, 2004, as an additional source of
service information for modifying the fairlead plate assemblies. The
GKN service bulletin is included in the Bombardier service bulletin.
Actions Done According to Previous Issue of Service Bulletin
(j) Actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 84-54-09, dated January
23, 2004; or Revision ``A,'' dated April 22, 2004; are acceptable
for compliance with the corresponding requirements of this AD.
Parts Installation
(k) After the effective date of this AD, no person may install a
plate, part number 85415048-107, 85415048-108, 85415087-107, or
85415087-108, on any airplane.
Alternative Methods of Compliance (AMOCs)
(l) 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
(m) Canadian airworthiness directive CF-2004-07, dated April 14,
2004, also addresses the subject of this AD.
Issued in Renton, Washington, on May 27, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11709 Filed 6-13-05; 8:45 am]
BILLING CODE 4910-13-P
