[Federal Register: May 11, 2004 (Volume 69, Number 91)]
[Rules and Regulations]
[Page 26013-26015]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11my04-11]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-222-AD; Amendment 39-13621; AD 2004-09-31]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-101, -102, -103,
-106, -201, -202, -301, -311, and -315 Airplanes on Which Engine Oil
Coolers Have Been Installed Per LORI, Inc., Supplemental Type
Certificate (STC) SA8937SW
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Bombardier Model DHC-8-101, -102, -103, -106, -
201, -202, -301, -311, and -315 airplanes on which engine oil coolers
have been installed per LORI, Inc., STC SA8937SW. This amendment
requires an inspection or a review of the airplane maintenance records
to determine the part number and serial number of each engine oil
cooler, and replacement of certain engine oil coolers with reworked
engine oil coolers. This action is necessary to prevent oil leakage
from the engine oil coolers, consequent in-
[[Page 26014]]
flight engine shutdown due to low oil pressure, and reduced
controllability of the airplane. This action is intended to address the
identified unsafe condition.
DATES: Effective June 15, 2004.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of June 15, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Honeywell Engines, Systems & Services, LORI, Inc., 6930
N. Lakewood, Tulsa, Oklahoma 74117. This information may be examined at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; at the FAA, Rotorcraft Directorate, 2601 Meacham Boulevard,
Fort Worth, Texas; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Jim Rankin, Aerospace Engineer,
Special Certification Office, ASW-190, 2601 Meacham Boulevard, Fort
Worth, Texas 76193; telephone (817) 222-5138; fax (817) 222-5785.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Bombardier Model DHC-8-
101, -102, -103, -106, -201, -202, -301, -311, and -315 airplanes on
which engine oil coolers have been installed per LORI, Inc., STC
SA8937SW, was published in the Federal Register on January 26, 2004 (69
FR 3533). That action proposed to require an inspection or a review of
the airplane maintenance records to determine the part number and
serial number of each engine oil cooler, and replacement of certain
engine oil coolers with reworked engine oil coolers.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the one comment received.
Request To Revise ``AD Title''
The commenter, Transport Canada Civil Aviation (TCCA), which is the
airworthiness authority for Canada, requests changing the ``AD title''
of the proposed AD from ``Bombardier, Inc. (Formerly de Havilland,
Inc.)'' to ``LORI, Inc.,'' to clarify that the proposed AD is written
against supplemental type certificate (STC) SA8937SW, issued to LORI,
Inc., and is not written against Bombardier airplanes.
During a teleconference between the commenter and the FAA on
February 6, 2004, the commenter also expressed concern regarding the
applicability of the proposed AD. The commenter stated that the
proposed AD, as written, would compel the issuance of a Canadian
airworthiness directive because the applicability of our proposed AD
identifies an airplane with a Canadian State of Design. The commenter
mentioned that the applicability section may be misleading because the
intent of the proposed AD is to address an unsafe condition created by
the installation of the STC; the unsafe condition is not directly
related to the Bombardier Model DHC-8 airplanes. The United States is
the State of Design for the STC and Canada is the State of Design for
the Bombardier airplanes.
We concur with the commenter's statement that the intent of this
final rule is to address an unsafe condition created by STC SA8937SW,
issued to LORI, Inc. We do not concur with the commenter's request to
change the product identification line (``AD title'') of this final
rule from ``Bombardier, Inc. (Formerly de Havilland, Inc.)'' to ``LORI,
Inc.'' The FAA's practice regarding unsafe conditions that result from
the installation of a particular component in only one particular make
and model of airplane, in this case Bombardier Model DHC-8 airplanes,
is to issue an AD that applies to the affected airplane model. In doing
so, U.S. operators of those airplanes will be notified directly of the
unsafe condition and the action required to correct it. While we assume
that operators can identify the airplane models they operate, they may
not be aware of specific items installed on those airplanes. Therefore,
specifying the airplane models in the applicability as the subject of
the AD prevents an operator's ``unknowing failure to comply'' with the
AD.
We also recognize that an unsafe condition may exist in an item
that is installed in many different airplane models. In that case, we
consider it impractical to issue an AD against each airplane model; in
fact, many times, the exact models and numbers of airplanes on which
the item is installed may be unknown. Therefore, in those situations,
we would issue an AD that would apply to the item and would indicate
that the item is known to be ``installed on, but not limited to,''
various airplane models.
During the teleconference on February 6, 2004, we mentioned that
the proposed AD, specifically the applicability section, was written
per our normal practice. We also advised TCCA that the issuance of the
proposed AD would not compel them to issue a Canadian airworthiness
directive, but that they may choose to issue an airworthiness directive
at their own discretion. We notified TCCA that we will distribute this
final rule to other civil airworthiness authorities, which eliminates
the need for issuance of a corresponding Canadian airworthiness
directive. No change is made to this final rule regarding this issue.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
The FAA estimates that 19 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour per
airplane to accomplish the required inspection or review of the
airplane maintenance records, and that the average labor rate is $65
per work hour. Based on these figures, the cost impact of the AD on
U.S. operators is estimated to be $1,235, or $65 per airplane.
Should an operator have to replace an engine oil cooler, it will
take approximately 3 work hours at an average labor rate of $65 per
work hour. Required parts will be provided at no charge by the part
manufacturer. Based on these figures, the cost impact of the
replacement on U.S. operators is estimated to be $195 per engine oil
cooler.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this 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, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein will 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
[[Page 26015]]
levels of government. Therefore, it is determined that this final rule
does not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2004-09-31 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-13621. Docket 2003-NM-222-AD.
Applicability: Model DHC-8-101, -102, -103, -106, -201, -202, -
301, -311, and -315 airplanes on which engine oil coolers have been
installed per LORI, Inc., Supplemental Type Certificate SA8937SW;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent oil leakage from the engine oil coolers, consequent
in-flight engine shutdown due to low oil pressure, and reduced
controllability of the airplane, accomplish the following:
Identification of Part Number and Serial Number and Corrective Actions
(a) Within 7 days after the effective date of this AD, do a
review of airplane maintenance records, or a detailed inspection in
accordance with the Accomplishment Instructions of Honeywell Service
Bulletin 28E99-79-2036, dated September 23, 2002, to positively
determine the part numbers (P/N) and serial numbers (S/N) of the
engine oil coolers.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(1) If neither engine oil cooler has a S/N as listed in Table 1
of the service bulletin: No further action is required by this
paragraph.
(2) If only one engine oil cooler has a S/N as listed in Table 1
of the service bulletin: Within 90 days after the effective date of
this AD, remove the affected part and install a part that has been
reworked per the service bulletin.
(3) If both engine oil coolers have S/Ns as listed in Table 1 of
the service bulletin: Before further flight, remove at least one of
the affected parts and install a part that has been reworked per the
service bulletin. If only one affected part is replaced with a part
that has been reworked, within 90 days after the effective date of
this AD, remove the remaining affected part and install a part that
has been reworked per the service bulletin.
Parts Installation
(b) As of the effective date of this AD, no person shall install
an engine oil cooler having a S/N as listed in Table 1 of Honeywell
Service Bulletin 28E99-79-2036, dated September 23, 2002.
Special Flight Permit
(c) Special flight permits with a limitation may be issued in
accordance with sections 21.197 and 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a
location where the requirements of this AD can be accomplished. The
special flight permits would have a limitation of one affected
engine oil cooler per airplane.
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, Special
Certification Office, Rotorcraft Directorate, FAA, is authorized to
approve alternative methods of compliance for this AD.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with Honeywell Service Bulletin 28E99-79-2036,
dated September 23, 2002. This incorporation by reference was
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Honeywell Engines, Systems & Services, LORI, Inc., 6930 N. Lakewood,
Tulsa, Oklahoma 74117. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; at
the FAA, Rotorcraft Directorate, 2601 Meacham Boulevard, Fort Worth,
Texas; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Effective Date
(f) This amendment becomes effective on June 15, 2004.
Issued in Renton, Washington, on April 28, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-10252 Filed 5-10-04; 8:45 am]
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