AD 99-21-09

[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Rules and Regulations]
[Pages 54199-54200]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25768]


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Federal Register / Vol. 64, No. 193 / Wednesday, October 6, 1999 / 
Rules and Regulations

[[Page 54199]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-321-AD; Amendment 39-11352; AD 99-21-09]
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: Final rule.

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SUMMARY: This amendment supersedes 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 amendment requires the accomplishment of 
these same actions on additional airplanes. This amendment is prompted 
by issuance of mandatory continuing airworthiness information by a 
foreign civil airworthiness authority. The actions specified by this AD 
are intended to prevent chafing of electrical wires, which could result 
in an uncommanded shutdown of an engine during flight.

DATES: Effective November 10, 1999.
    The incorporation by reference of Bombardier Service Bulletin S.B. 
8-53-66, dated March 27, 1998, as listed in the regulations was 
approved previously by the Director of the Federal Register as of 
October 27, 1998 (63 FR 50501, September 22, 1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, 
Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information 
may be examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-20-14, 
amendment 39-10781 (63 FR 50501, September 22, 1998), which is 
applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, -
202, -301, -311, and -315 series airplanes, was published in the 
Federal Register on August 12, 1999 (64 FR 43948). The action proposed 
to 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. That 
action also proposed to expand the applicability of the existing AD to 
include additional airplanes.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

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 
will be affected by this AD.
    The actions specified in this AD 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 AD 98-20-14 on U.S. 
operators of these airplanes is estimated to be $882,000, or $4,200 per 
airplane. The AD will add no new costs for these airplanes.
    The actions specified in this AD 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 will be provided by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the current requirements of AD 98-20-14 on U.S. 
operators of these airplanes is estimated to be $90,000, or $6,000 per 
airplane.
    The actions specified in this AD will be applicable to 6 additional 
Model DHC-8-301, -311, and -315 series airplanes of U.S. registry and 
will take approximately 100 work hours per airplane to accomplish, at 
an average labor rate of $60 per work hour. Required parts will be 
provided by the manufacturer at no cost to the operator. Based on these 
figures, cost impact of the action required by this AD on U.S. 
operators of these 6 additional airplanes 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 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 adopted herein will 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

[[Page 54200]]

responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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

    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

    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), amendment 39-11352, to read as follows:

99-21-09  Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-11352. Docket 98-NM-321-AD. Supersedes AD 98-20-14, Amendment 39-
10781.

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

Incorporation by Reference

    (d) The actions shall be done in accordance with Bombardier 
Service Bulletin
    S.B. 8-53-66, dated March 27, 1998. This incorporation by 
reference was approved previously by the Director of the Federal 
Register as of October 27, 1998 (63 FR 50501, September 22, 1998). 
Copies may be obtained from Bombardier, Inc., Bombardier Regional 
Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, 
Canada. Copies may be inspected 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; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

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

    (e) This amendment becomes effective on November 10, 1999.

    Issued in Renton, Washington, on September 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-25768 Filed 10-5-99; 8:45 am]
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