[Federal Register Volume 64, Number 218 (Friday, November 12, 1999)]
[Rules and Regulations]
[Pages 61478-61480]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-28746]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-335-AD; Amendment 39-11401; AD 99-23-05]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-101, -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 adopts a new airworthiness directive (AD), 
applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, -
202, -301, -311, and -315 series airplanes, that requires repetitive 
detailed visual inspections and high frequency eddy current inspections 
to detect cracking of the wing upper skin and ladder plates at over 
wing access panels between certain stations; and repair, if necessary. 
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 detect and correct 
fatigue cracking of the wing ladder plates, which, if not corrected, 
could reduce the structural integrity of the wing.

DATES: Effective December 17, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 17, 1999.

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,

[[Page 61479]]

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: Franco Pieri, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller 
Directorate, New York Aircraft Certification Office, 10 Fifth Street, 
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7526; 
fax (516) 568-2716.

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 all Bombardier Model DHC-8-101, -
102, -103, -106, -201, -202, -301, -311, and -315 series airplanes was 
published in the Federal Register on September 3, 1999 (64 FR 48333). 
That action proposed to require repetitive detailed visual inspections 
and high frequency eddy current inspections to detect cracking of the 
wing upper skin and ladder plates at over wing access panels between 
certain stations; and repair, if necessary.

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

    The FAA estimates that 166 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 40 work hours per 
airplane to accomplish the inspections, and that the average labor rate 
is $60 per work hour. Based on these figures, the cost impact of this 
AD on U.S. operators is estimated to be $398,400, or $2,400 per 
airplane, per inspection cycle.
    The cost impact figure discussed above is 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 
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 adding the following new 
airworthiness directive:

99-23-05  Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-11401. Docket 98-NM-335-AD.

    Applicability: All Model DHC-8-101, -102, -103, -106, -201, -
202, -301, -311, and -315 series airplanes, 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 (d) 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 detect and correct fatigue cracking of the wing ladder 
plates, which if not corrected, could reduce the structural 
integrity of the wing, accomplish the following:

Inspection for DHC-8-100 and -300 Series Airplanes

    (a) At the applicable compliance time listed in paragraph 
(a)(1), (a)(2), or (a)(3) of this AD, perform a detailed visual 
inspection to detect cracking of the skin and a high frequency eddy 
current (HFEC) inspection of the ladder plates at over wing access 
panels between station YW42.00 and YW171.20, in accordance with de 
Havilland Temporary Revision MTC-15, dated September 18, 1998, of 
the de Havilland Maintenance Program Manual PSM 1-8-7 TC (for Model 
DHC-8-100 series airplanes); or de Havilland Temporary Revision MTC 
3-14, dated September 18, 1998, of the de Havilland Maintenance 
Program Manual PSM 1-83-7TC (for Model DHC-8-300 series airplanes); 
as applicable. Repeat the inspections thereafter at intervals not to 
exceed 10,000 flight cycles.
    (1) For airplanes that have accumulated 5,000 or fewer total 
flight cycles as of the effective date of this AD, accomplish the 
inspection prior to the accumulation of 10,000 total flight cycles.
    (2) For airplanes that have accumulated more than 5,000 total 
flight cycles, but fewer than 38,501 total flight cycles as of the 
effective date of this AD, accomplish the inspection prior to the 
accumulation of [5,522+(0.8955  x  N Accumulated)] total cycles. ``N 
Accumulated'' is defined as the total number of flight cycles as of 
the effective date of this AD.
    (3) For airplanes that have accumulated 38,501 or more total 
flight cycles as of the effective date of this AD, accomplish the 
inspection within 1,500 flight cycles after the effective date of 
this AD.

    Note 2: For the purposes of this AD, a detailed visual 
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.''

Inspection for DHC-8-200 Series Airplanes

    (b) At the applicable compliance time listed in paragraph (b)(1) 
or (b)(2) of this AD, perform a detailed visual inspection of the 
skin and an HFEC inspection to detect cracking of the ladder plates 
at over wing access panels between station YW42.00 and YW171.20, in 
accordance with de Havilland Temporary Revision MTC 2-14, dated 
September 18, 1998, of the de Havilland Maintenance Program Manual 
PSM 1-82-7TC. Repeat the inspections thereafter at intervals not to 
exceed 10,000 flight cycles.

[[Page 61480]]

    (1) For airplanes that have accumulated 5,000 or fewer total 
flight cycles as of the effective date of this AD, accomplish the 
inspection prior to the accumulation of 10,000 total flight cycles.
    (2) For airplanes that have accumulated more than 5,000 total 
flight cycles, but fewer than 38,501 total flight cycles as of the 
effective date of this AD, accomplish the inspection prior to the 
accumulation of [5,522+(0.8955  x  N Accumulated)] total cycles, 
where ``N Accumulated'' is defined as the total number of flight 
cycles as of the effective date of this AD.

Repair

    (c) If any crack is detected during any inspection required by 
this AD, prior to further flight, repair in accordance with a method 
approved by the Manager, New York Aircraft Certification Office 
(ACO), FAA, Engine and Propeller Directorate; or the Transport 
Canada Civil Aviation (TCCA) (or its delegated agent). For a repair 
method to be approved by the Manager, New York ACO, as required by 
this paragraph, the Manager's approval letter must specifically 
reference this AD.

Alternative Methods of Compliance

    (d) 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

    (e) 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

    (f) Except as provided by paragraph (c) of this AD, the actions 
shall be done in accordance with de Havilland Temporary Revision 
MTC-15, dated September 18, 1998, of the de Havilland Maintenance 
Program Manual PSM 1-8-7 TC; de Havilland Temporary Revision MTC 3-
14, dated September 18, 1998, of the de Havilland Maintenance 
Program Manual PSM 1-83-7 TC; or de Havilland Temporary Revision MTC 
2-14, dated September 18, 1998, of the de Havilland Maintenance 
Program Manual PSM 1-82-7 TC; as applicable. 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 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-98-30, dated August 31, 1998.

    (g) This amendment becomes effective on December 17, 1999.

    Issued in Renton, Washington, on October 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-28746 Filed 11-10-99; 8:45 am]
BILLING CODE 4910-13-P