[Federal Register Volume 64, Number 155 (Thursday, August 12, 1999)]
[Proposed Rules]
[Pages 43948-43950]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20882]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-321-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, 
-201, -202, -301, -311, and -315 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Bombardier Model 
DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series 
airplanes, that currently requires a one-time inspection to detect 
chafing of electrical wires in the cable trough below the cabin floor; 
repair, if necessary; installation of additional tie-mounts and tie-
wraps; and application of sealant to rivet heads. This action would 
require the accomplishment of these same actions on additional 
airplanes. This proposal is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by the proposed AD are intended to 
prevent chafing of electrical wires, which could result in an 
uncommanded shutdown of an engine during flight.

DATES: Comments must be received by September 13, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-321-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.
    The service information referenced in the proposed rule may be 
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, 
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, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York.

FOR FURTHER INFORMATION CONTACT: Peter Cuneo, Senior Aerospace 
Engineer, Systems and Flight Test Branch, ANE-172, FAA, Engine and 
Propeller Directorate, New York Aircraft Certification Office, 10 Fifth 
Street, Third Floor, Valley Stream, New York 11581; telephone (516) 
256-7506; fax (516) 568-2716.

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 notice may be changed in 
light of the comments received.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-321-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. 98-NM-321-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On September 14, 1998, the FAA issued AD 98-20-14, amendment 39-
10781 (63 FR 50501, September 22, 1998), applicable to certain 
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 series airplanes, to require a one-time inspection to detect 
chafing of electrical wires in the cable trough below the cabin floor; 
repair, if necessary; installation of additional tie-mounts and tie-
wraps; and application of sealant to

[[Page 43949]]

rivet heads. The requirements of that AD are intended to prevent 
chafing of electrical wires, which could result in an uncommanded 
shutdown of an engine during flight.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, Transport Canada Civil Aviation 
(TCCA), which is the airworthiness authority for Canada, issued 
Canadian airworthiness directive CF-98-08R1, dated September 16, 1998. 
Airworthiness directive CF-98-08R1 revises the applicability of 
Canadian airworthiness directive CF-98-08, dated March 26, 1998, to 
include Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 
series airplanes having serial numbers 3 through 540, excluding serial 
number 462. Canadian airworthiness directive CF-98-08 was applicable to 
Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series 
airplanes having serial numbers 3 through 519, excluding serial number 
462.

FAA's Conclusions

    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. 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 supersede AD 98-20-14 to 
continue to require a one-time inspection to detect chafing of 
electrical wires in the cable trough below the cabin floor; repair, if 
necessary; installation of additional tie-mounts and tie-wraps; and 
application of sealant to rivet heads. This proposal would expand the 
applicability of the existing AD to include additional airplanes. The 
actions would be required to be accomplished in accordance with 
Bombardier Service Bulletin S.B. 8-53-66, dated March 27, 1998.

Differences Between Existing AD, Service Bulletin, and Proposed 
Rule

    Operators should note that Bombardier Service Bulletin S.B. 8-53-
66, dated March 27, 1998, describes, and the existing AD requires, a 
visual inspection to detect chafing of electrical wires in the cable 
trough below the cabin floor. This proposed AD refers to that 
inspection as a general visual inspection. Note 2 of this AD also 
includes a definition of this type of inspection.

Cost Impact

    There are approximately 231 Bombardier Model DHC-8-102, -103, -106, 
-201, -202, -301, -311, and -315 series airplanes of U.S. registry that 
would be affected by this proposed AD.
    The actions specified in this proposed rule are currently required 
by AD 98-20-14, which is applicable to 210 Model DHC-8-102, -103, -106, 
-201, and -202 series airplanes. For these airplanes, it takes 
approximately 70 work hours per airplane to accomplish the required 
actions, at an average labor rate of $60 per work hour. Required parts 
are provided by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the current requirements of that AD 
on U.S. operators of these airplanes is estimated to be $882,000, or 
$4,200 per airplane. The proposed AD would add no new costs for these 
airplanes.
    The actions specified in this proposed rule are currently required 
by AD 98-20-14, which is applicable to 15 Model DHC-8-301, -311, and -
315 series airplanes. For these airplanes, it takes approximately 100 
work hours per airplane to accomplish the required actions, at an 
average labor rate of $60 per work hour. Required parts would be 
provided by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the current requirements of that AD 
on U.S. operators of these airplanes is estimated to be $90,000, or 
$6,000 per airplane.
    The actions specified in this proposed AD would be applicable to 6 
additional Model DHC-8-301, -311, and -315 series airplanes of U.S. 
registry and would take approximately 100 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts would be provided by the manufacturer at no cost to the operator. 
Based on these figures, the new costs proposed by this AD on U.S. 
operators is estimated to be $36,000, or approximately $6,000 per 
airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 removing amendment 39-10781 (63 FR 
50501, September 22, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

Bombardier, Inc. (Formerly de Havilland, Inc.): Docket 98-NM-321-AD. 
Supersedes AD 98-NM-172-AD, Amendment 39-10781.

    Applicability: Model DHC-8-102, -103, -106, -201, -202, -301, -
311, and -315 series airplanes; serial numbers 3 through 540

[[Page 43950]]

inclusive, excluding serial number 462; certificated in any 
category.

    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 (b) 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 prevent chafing of electrical wires, which could result in an 
uncommanded shutdown of an engine during flight, accomplish the 
following:

One-Time Inspection, Corrective Action, and Modification

    (a) Perform a one-time general visual inspection to detect 
chafing of electrical wires in the cable trough below the cabin 
floor; install additional tie-mounts and tie-wraps; and apply 
sealant to rivet heads (reference Bombardier Modification 8/2705); 
in accordance with Bombardier Service Bulletin S.B. 8-53-66, dated 
March 27, 1998, at the time specified in paragraph (a)(1) or (a)(2) 
of this AD, as applicable. If any chafing is detected during the 
inspection required by this paragraph, prior to further flight, 
repair in accordance with the service bulletin.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or external 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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.''

    (1) For airplanes having serial numbers 3 through 519 inclusive, 
excluding serial number 462: Inspect within 36 months after October 
27, 1998 (the effective date of AD 98-20-14, amendment 39-10781).
    (2) For airplanes having serial numbers 520 through 540 
inclusive: Inspect within 36 months after the effective date of this 
AD, or at the next ``C'' check, whichever occurs first.

Alternative Methods of Compliance

    (b) 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, Engine and Propeller Directorate. 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 3: 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

    (c) 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 4: The subject of this AD is addressed in Canadian 
airworthiness directive CF-98-08R1, dated September 16, 1998.

    Issued in Renton, Washington, on August 6, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-20882 Filed 8-11-99; 8:45 am]
BILLING CODE 4910-13-P