[Federal Register: December 31, 2003 (Volume 68, Number 250)]
[Proposed Rules]
[Page 75471-75473]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr31de03-33]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-338-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Bombardier Model DHC-8-
102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This
proposal would require inspection of the fitting assemblies located on
the vent and scavenge lines routed immediately below the fuel tank
access covers on both wings for proper installation, and corrective
actions if necessary. This proposal also would require inspection of
the stiffeners on the underside of fuel tank access covers on both
wings for signs of chafing damage caused by incorrect orientation of
the lockwire tail, and removal of damage. This action is necessary to
prevent contact between the lockwire pigtail of the fitting and the
stiffener located on the inside surface of the fuel access covers of
the wings, which could serve as a potential ignition source within the
fuel tank if a cover is struck by lightning and result in possible fuel
tank explosion. This action is intended to address the identified
unsafe condition.
DATES: Comments must be received by January 30, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-338-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-338-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for Windows or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This
information may be examined at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York
Aircraft Certification Office, 1600 Stewart Avenue, Westbury, New York.
FOR FURTHER INFORMATION CONTACT: Sarbhpreet Singh Sawhney, Aerospace
Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York
Aircraft Certification Office, 1600 Stewart Avenue, Westbury, New York
[[Page 75472]]
11590; telephone (516) 228-7340; fax (516) 794-5531
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-338-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2002-NM-338-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified the FAA that an unsafe condition may
exist on certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -
301, -311, and -315 airplanes. TCCA advises that it has received a
report of a contact condition between the lockwire pigtail of a
particular fitting and the stiffener located on the inside surface of a
wing fuel access cover. Investigation revealed that these particular
fittings were installed facing the outboard side of the wing, rather
than the inboard side. This condition, if not corrected, could result
in contact between the lockwire pigtail of the fitting and the
stiffener located on the inside surface of the fuel access covers of
the wings. Such contact could serve as a potential ignition source
within the fuel tank if a cover is struck by lightning, which could
result in possible fuel tank explosion.
Explanation of Relevant Service Information
Bombardier has issued Alert Service Bulletin A8-28-33, Revision
``A,'' dated October 10, 2002, which describes the following
procedures:
[sbull] A general visual inspection to verify proper installation
of the fitting assemblies and lockwire located on the vent and scavenge
lines routed immediately below the fuel tank access covers on both
wings, and corrective actions if necessary. These corrective actions
include changing the orientation of the fitting assembly; performing a
general visual inspection of the O-ring for damage; replacing any
damaged O-ring with a new O-ring; and replacing the lockwire with a new
lockwire if necessary.
[sbull] A general visual inspection of the stiffeners on the
underside of fuel tank access covers on both wings for signs of chafing
damage caused by incorrect orientation of the lockwire tail, and
removal of damage.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition. TCCA
classified this service bulletin as mandatory and issued Canadian
airworthiness directive CF-2002-44, dated October 22, 2002, in order to
assure the continued airworthiness of these airplanes in Canada.
FAA's Conclusions
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. The FAA has examined the findings of
TCCA, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletin described previously,
except as discussed below.
Difference Between Proposed Rule and Referenced Service Bulletin/
Canadian Airworthiness Directive
Although the service bulletin specifies that operators may contact
the manufacturer for disposition of certain damage conditions, this
proposal would require operators to remove the damage per a method
approved by either the FAA or the TCCA (or its delegated agent). In
light of the type of removal that would be required to address the
unsafe condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, removal of
damage approved by either the FAA or TCAA would be acceptable for
compliance with this proposed AD.
Operators should note that, although the Canadian airworthiness
directive and the Accomplishment Instructions of the referenced service
bulletin describe procedures for reporting inspection findings to the
airplane manufacturer, this proposed AD would not require those
actions. The FAA does not need this information from operators.
Cost Impact
The FAA estimates that 172 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour per airplane to accomplish the proposed inspections, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$11,180, or $65 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this proposed AD were not adopted. The cost impact
figures discussed in AD rulemaking actions represent only the time
necessary to perform the specific actions actually required by the AD.
These figures typically do not include incidental costs, such as the
time required to gain access and close up,
[[Page 75473]]
planning time, or time necessitated by other administrative actions.
Regulatory Impact
The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket 2002-NM-338-
AD.
Applicability: Model DHC-8-102, -103, -106, -201, -202, -301, -
311, and -315 airplanes, serial numbers 003 through 586 inclusive;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent contact between the lockwire pigtail of the fitting
and the stiffener located on the inside surface of the fuel access
covers of the wings, which could serve as a potential ignition
source within the fuel tank if a cover is struck by lightning and
result in possible fuel tank explosion, accomplish the following:
Inspection of Fitting Assemblies and Lockwire
(a) Within 12 months after the effective date of this AD, do a
general visual inspection to verify proper installation of the
fitting assemblies and the lockwire located on the vent and scavenge
lines routed immediately below the fuel tank access covers on both
wings by accomplishing all the actions specified in Part A of the
Accomplishment Instructions of Bombardier Alert Service Bulletin A8-
28-33, Revision ``A,'' dated October 10, 2002. Do the actions per
the service bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is defined as: ``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 enhance visual access to all exposed 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.''
Corrective Actions for Any Improperly Installed Fitting Assembly or
Lockwire
(b) If any fitting assembly is found to be improperly installed
during the general visual inspection required by paragraph (a) of
this AD, before further flight, do the actions specified in
paragraphs (b)(1) and (b)(2) of this AD per Part A of the
Accomplishment Instructions of Bombardier Alert Service Bulletin A8-
28-33, Revision ``A,'' dated October 10, 2002.
(1) Change the orientation of the fitting assembly.
(2) Perform a general visual inspection of the O-ring for
damage, and replace any damaged O-ring with a new O-ring.
(c) If any lockwire is found to be improperly installed during
the general visual inspection required by paragraph (a) of this AD,
before further flight, replace the lockwire with a new lockwire, per
Part A of the Accomplishment Instructions of Bombardier Alert
Service Bulletin A8-28-33, Revision ``A,'' dated October 10, 2002.
Inspection of the Stiffeners
(d) Within 12 months after the effective date of this AD, do a
general visual inspection of the stiffeners on the underside of fuel
tank access covers on both wings for signs of chafing damage caused
by incorrect orientation of the lockwire tail, per Part B of the
Accomplishment Instructions of Bombardier Alert Service Bulletin A8-
28-33, Revision ``A,'' dated October 10, 2002.
Corrective Action for Chafing Damage
(e) If any chafing damage is found during the general visual
inspection required by paragraph (d) of this AD, before further
flight, remove the damage per Part B of the Accomplishment
Instructions of Bombardier Alert Service Bulletin A8-28-33, Revision
``A,'' dated October 10, 2002, except where the service bulletin
recommends contacting Bombardier for damage in excess of the given
limits, before further flight, repair per a method approved by
either the Manager, New York Aircraft Certification Office (ACO),
FAA; or the Transport Canada Civil Aviation (TCCA) (or its delegated
agent).
Exception to Service Bulletin Reporting
(f) Although the service bulletin referenced in this AD
specifies to report inspection findings to the airplane
manufacturer, this AD does not include such a requirement.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the Manager, New York
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.
Note 2: The subject of this AD is addressed in Canadian
airworthiness directive CF-2002-44, dated October 22, 2002.
Issued in Renton, Washington, on December 19, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-32133 Filed 12-30-03; 8:45 am]
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