AD 2001-19-01

[Federal Register Volume 66, Number 179 (Friday, September 14, 2001)]
[Rules and Regulations]
[Pages 47883-47885]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-23068]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-39-AD; Amendment 39-12440; AD 2001-19-01]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-301 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Bombardier Model DHC-8-301 series airplanes. This 
action requires removal of the access panels of the upper wings to 
determine the manufacturing date of the panels to verify compliance 
with Model 301 wing specifications, and corrective action, if 
necessary. This action is necessary to find and fix panels that do not 
meet such specifications, which could result in elongation of the 
attachment holes in the panels due to critical design loads, and 
consequent reduced structural integrity of the wings. This action is 
intended to address the identified unsafe condition.

DATES: Effective October 1, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before October 15, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-39-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: 
<a href="/cdn-cgi/l/email-protection#7940541817145410180b1a1614141c170d391f1818571e160f"><span class="__cf_email__" data-cfemail="b28b9fd3dcdf9fdbd3c0d1dddfdfd7dcc6f2d4d3d39cd5ddc4">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-39-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 this AD 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, 10 Fifth Street, Third Floor, Valley Stream, New York; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Serge Napoleon, Aerospace Engineer, 
ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7512; 
fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: Transport Canada Civil Aviation (TCCA), 
which is the airworthiness authority for Canada,

[[Page 47884]]

notified the FAA that an unsafe condition may exist on certain 
Bombardier Model DHC-8-301 series airplanes. TCCA advises that a report 
was received that during a routine inspection an operator questioned 
the conformity of the wing access panels located between stations Y42 
and Y139 of the upper wing. Investigation revealed that the panels were 
not built per the design drawing specifications. The panels were 
manufactured per the design specifications of the DHC-8-100; therefore, 
the doublers on the panels were manufactured with less than the 
required thickness. Structural analysis done by the manufacturer 
indicates that, if the affected panels are exposed to critical design 
loads during flight, the attachment holes in the panels may elongate, 
which could result in reduced structural integrity of the wings.

Explanation of Relevant Service Information

    De Havilland Dash 8 Maintenance Manual, Product Support Manual 1-
83-2, Chapter 57-30-10, dated March 31, 1995, describes procedures for 
removal and replacement of the access panels of the left and right 
wings with new panels. TCCA issued Canadian airworthiness directive CF-
99-27, dated September 28, 1999, 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 21.19) 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 the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to find and fix panels that do not meet Model 301 wing 
specifications, which could result in discrepancies and reduced 
structural integrity of the wings. This AD requires removal of the two 
upper wing access panels to determine the manufacturing date of the 
panels to verify compliance with Model 301 specifications, and 
corrective action, if necessary. The actions are required to be 
accomplished in accordance with the service information described 
previously.

Cost Impact

    None of the Model DHC-8-301 series airplanes affected by this 
action are on the U.S. Register. All airplanes included in the 
applicability of this rule currently are operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers that this rule is necessary 
to ensure that the unsafe condition is addressed in the event that any 
of these subject airplanes are imported and placed on the U.S. Register 
in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 1 work hour to 
accomplish the required actions, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$60 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-39-AD.'' The postcard will be date stamped and 
returned to the commenter.

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 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, Safety.

Adoption of the Amendment

    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:

[[Page 47885]]

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:

2001-19-01  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12440. Docket 2001-NM-39-AD.

    Applicability: Model DHC-8-301 series airplanes having the 
serial numbers listed below, certificated in any category: 100, 108, 
116, 124, 131, 137, 143, 149, 154, 159, 164, 169, 174, 180, 182, 
184, 186, 188, 190, 192, 194, 196, 198, 200.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To find and fix the access panels of the upper wings that do not 
meet Model 301 wing specifications, which could result in elongation 
of the attachment holes in the panels due to critical design loads, 
and consequent reduced structural integrity of the wings; accomplish 
the following:

Determine Manufacturing Date/Corrective Action

    (a) Within 12 months after the effective date of this AD: Remove 
the two access panels of the upper wings, part number (P/N) 
85711539-003, to determine the manufacturing date, which is stamped 
on the underside of each panel; per de Havilland Dash 8 Maintenance 
Manual, Product Support Manual 1-83-2, Chapter 57-30-10, dated March 
31, 1995.
    (1) If the manufacturing date on any panel is September 30, 
1997, or earlier, before further flight, replace with a new panel, 
P/N 85711539-003, having a manufacturing date of October 1, 1997, or 
later; per the maintenance manual.
    (2) If the manufacturing date on any panel is October 1, 1997, 
or later, reinstall that panel per the maintenance manual. No 
further action is required for that panel.

Spares

    (b) As of the effective date of this AD: No person may install 
an access panel, P/N 85711539-003, having a manufacturing date of 
September 30, 1997, or earlier, on any airplane.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, New York Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, New York ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York ACO.

Special Flight Permits

    (d) Special flight permits 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.

    Note 3: The subject of this AD is addressed in Canadian 
airworthiness directive CF-99-27, dated September 28, 1999.

Effective Date

    (e) This amendment becomes effective on October 1, 2001.

    Issued in Renton, Washington, on September 7, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-23068 Filed 9-13-01; 8:45 am]
BILLING CODE 4910-13-P