[Federal Register Volume 69, Number 16 (Monday, January 26, 2004)]
[Proposed Rules]
[Pages 3533-3535]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-1562]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-222-AD]
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: 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-
101,

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-102, -103, -106, -201, -202, -301, -311, and -315 airplanes on which 
engine oil coolers have been installed per LORI, Inc., STC SA8937SW. 
This proposal would 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. This action is necessary 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. This action is intended to address the identified unsafe 
condition.

DATES: Comments must be received by February 25, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-222-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-222-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 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule 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; or at the FAA, Rotorcraft Directorate, 2601 Meacham 
Boulevard, Fort Worth, Texas.

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:

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:
     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.
     For each issue, state what specific change to 
the proposed AD is being requested.
     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 2003-NM-222-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. 2003-NM-222-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports from LORI, Inc., the manufacturer of 
certain engine oil coolers installed on Bombardier Model DHC-8-101, -
102, -103, -106, -201, -202, -301, -311, and -315 airplanes, that a 
batch of engine oil coolers with specific serial numbers have developed 
in-service cracking. Investigation revealed that the cracking is a 
result of deficient weld joints in the casting-to-core welds. Such 
cracking could result in oil leakage from the engine oil coolers, 
consequent in-flight engine shutdown due to low oil pressure, and 
reduced controllability of the airplane.

Explanation of Relevant Service Information

    Honeywell has issued Service Bulletin 28E99-79-2036, dated 
September 23, 2002, which describes procedures for identifying the part 
number and serial number of the engine oil coolers and comparing the 
results against the effectivity information in paragraph 1.A. of the 
service bulletin, inspecting affected engine oil coolers for indication 
of oil leakage, and replacing discrepant engine oil coolers with 
reworked engine oil coolers. Accomplishment of the actions specified in 
the service bulletin is intended to adequately address the identified 
unsafe condition.

U.S. Type Certification of the Airplanes

    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.

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.

Special Flight Permits

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. As amended, part 39 provides for the FAA to add 
special requirements for operating an airplane to a repair facility to 
do the work required by an airworthiness directive. For the purposes of 
this proposed AD, we have determined that a special flight permit would 
be permitted, but with certain limitations.

Cost Impact

    The FAA estimates that 19 airplanes of U.S. registry would be 
affected by this proposed AD. It would take approximately 1 work hour 
per airplane to accomplish the proposed inspection, at an average labor 
rate of $65 per work hour. Based on these figures, the cost impact of 
the proposed inspection 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 would 
take approximately 3 work hours at an

[[Page 3535]]

average labor rate of $65 per work hour. Required parts would be 
provided at no charge by the part manufacturer. Based on these figures, 
the cost impact of the proposed 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 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, 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 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 
detailed inspection or a review of airplane maintenance records to 
positively determine the part numbers (P/N) and serial numbers (S/N) 
of the engine oil coolers, in accordance with the Accomplishment 
Instructions of Honeywell Service Bulletin 28E99-79-2036, dated 
September 23, 2002.

    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.

    Issued in Renton, Washington, on January 16, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-1562 Filed 1-23-04; 8:45 am]
BILLING CODE 4910-13-P