AD 2001-13-19

[Federal Register Volume 66, Number 130 (Friday, July 6, 2001)]
[Rules and Regulations]
[Pages 35538-35540]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-16736]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-45-AD; Amendment 39-12301; AD 2001-13-19]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, 
-201, -202, -301, -311, -314, 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-8-102, -103, -106, -201, -202, -
301, -311, -314, and -315 series airplanes, that requires revising the 
Bombardier maintenance program to incorporate repetitive inspections to 
detect fatigue cracking in certain structures; and corrective actions, 
if necessary. This amendment is prompted by issuance of mandatory 
continuing airworthiness information issued by a foreign airworthiness 
authority. The actions specified by this AD are intended to ensure that 
fatigue cracking of certain principal structural elements is detected 
and corrected; such fatigue cracking could adversely affect the 
structural integrity of these airplanes.

DATES: Effective August 10, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 10, 2001.

ADDRESSES: 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 Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 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.

[[Page 35539]]


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-8-102, -
103, -106, -201, -202, -301, -311, -314, and -315 series airplanes was 
published in the Federal Register on February 14, 2001 (66 FR 10238). 
That action proposed to require revising the Bombardier maintenance 
program to incorporate repetitive inspections to detect fatigue 
cracking in certain structures; and corrective actions, 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.

Editorial Change

    The language in paragraph (a)(2)(iii) has been slightly revised to 
clarify the intervals for certain repetitive inspections.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed with the clarification described previously. The FAA 
has determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 195 Model DHC-8-102, -103, -106, -201, -202, 
-301, -311, -314, and -315 series airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 1 work hour per airplane to revise the 
Bombardier maintenance program, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the revision on 
U.S. operators is estimated to be $11,700, or $60 per airplane.
    It will take approximately 5 work hours per airplane to accomplish 
the required structural inspections, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the 
inspections on U.S. operators is estimated to be $58,500, or $300 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. 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 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, 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:

2001-13-19  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12301. Docket 2000-NM-45-AD.

    Applicability: Model DHC-8-102, -103, -106, -201, -202, -301, -
311, -314, 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 ensure continued structural integrity of these airplanes, 
accomplish the following:
    (a) Within 30 days after the effective date of this AD, 
accomplish the actions required by either paragraph (a)(1) or (a)(2) 
of this AD, as applicable.

Maintenance Program Revisions

    (1) Revise the Bombardier maintenance program by incorporating 
the threshold and repetitive inspection intervals specified in the 
Temporary Revisions (TR's) to the DHC-8 Maintenance Program Manuals, 
Airworthiness Limitations List (AWL), Structural Inspection Program 
Task No. 5310/31A, into the Bombardier maintenance program. The TR's 
for specific airplane models are listed in Table 1, as follows:

                                      Table 1.--List of Temporary Revisions
----------------------------------------------------------------------------------------------------------------
           Bombardier models                         TR No.                                Date
----------------------------------------------------------------------------------------------------------------
DHC-8-102, -103, and -106 series         TR AWL-71                       September 3, 1999.
 airplanes.
DHC-8-102, -103, -106, -201, -202, -     TR AWL 2-15                     September 3, 1999.
 301, -311, -314, and -315 series
 airplanes.
DHC-8-301, -311, -314, and -315 series   TR AWL 3-78                     November 19, 1999.
 airplanes.
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[[Page 35540]]


    Note 2: When the TR documents listed in Table 1 in paragraph 
(a)(1) of this AD are incorporated into the general revisions of the 
DHC-8 Maintenance Program Manual, you may insert the general 
revisions into the Bombardier maintenance program, provided that the 
information contained in the general revisions is identical to that 
specified in the TR documents.

Structural Inspections

    (2) For airplanes having closing angles that are identified as 
principal structural elements: Do the inspections specified by the 
applicable TR listed in Table 1 of paragraph (a) of this AD. 
Thereafter, repeat the inspection at intervals not to exceed 10,000 
flight cycles at the time specified in paragraph (a)(2)(i), 
(a)(2)(ii), or (a)(2)(iii) of this AD, as applicable.
    (i) For airplanes that have accumulated less than 8,000 flight 
cycles as of the effective date of this AD: Do the threshold 
inspection prior to the accomplishment of 10,000 flight cycles, or 
within 2,000 flight cycles after the effective date of this AD, 
whichever occurs later.
    (ii) For airplanes that have accumulated 8,000 flight cycles or 
more as of the effective date of this AD: Do the threshold 
inspection within 2,000 flight cycles after the effective date of 
this AD.
    (iii) For airplanes on which a 40,000 flight cycle inspection 
specified by the applicable TR listed in Table 1 of paragraph (a) of 
this AD has been done: Start the 10,000 flight cycle repetitive 
inspection at the time specified by paragraph (a)(2)(iii)(A) or 
(a)(2)(iii)(B) of this AD, as applicable.
    (A) If no cracks were found, start the cycle from the date of 
the 40,000 flight cycle inspection.
    (B) If cracks have been found and the closing angles have been 
replaced as provided in paragraph (b) of this AD, start the cycle 
from the date of the replacement.

Corrective Actions

    (b) If any crack is detected during any structural inspection 
required by paragraph (a)(2) of this AD, before further flight, 
repair any such cracking or replace the closing angles per a method 
approved by the Manager, New York Aircraft Certification Office 
(ACO), FAA; or the Transport Canada Civil Aviation (or its delegated 
agent). For a repair or replacement 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.
    (c) Except as provided by paragraph (d) of this AD: After the 
actions specified in paragraphs (a) and (b) of this AD have been 
accomplished, no alternative inspections or inspection intervals may 
be approved for the structural elements specified by the documents 
listed in Table 1 of paragraph (a)(1) of 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 ACO. 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 in paragraph (b) of this AD, the actions 
shall be done in accordance with de Havilland Temporary Revision TR 
AWL-71, dated September 3, 1999; de Havilland Temporary Revision TR 
AWL 2-15, dated September 3, 1999; and de Havilland Temporary 
Revision TR AWL 3-78, dated November 19, 1999. 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, 123 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, New York 
ACO, 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-2000-07, dated March 3, 2000.

Effective Date

    (g) This amendment becomes effective on August 10, 2001.

    Issued in Renton, Washington, on June 26, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 01-16736 Filed 7-5-01; 8:45 am]
BILLING CODE 4910-13-U