AD 2000-26-09

[Federal Register Volume 66, Number 2 (Wednesday, January 3, 2001)]
[Rules and Regulations]
[Pages 265-267]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-31]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-201-AD; Amendment 39-12059; AD 2000-26-09]
RIN 2120-AA64


Airworthiness Directives; Dornier Model 328-100 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 Dornier Model 328-100 series airplanes, that requires 
revising the Airworthiness Limitations Section of the Instructions for 
Continued Airworthiness to incorporate life limits for certain items 
and inspections to detect fatigue cracking in certain structures. This 
amendment is prompted by issuance of new revisions to the Dornier 328 
Airworthiness Limitations Document. The actions specified by this AD 
are intended to ensure that fatigue cracking of certain structural 
elements is detected and corrected; such fatigue cracking could 
adversely affect the structural integrity of these airplanes.

DATES: Effective February 7, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Fairchild Dornier, Dornier Luftfahrt GmbH, P.O. Box 1103, 
D-82230 Wessling, Germany. This information may be examined at the 
Federal Aviation Administration (FAA), Transport Airplane Directorate, 
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

[[Page 266]]


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 Dornier Model 328-100 series 
airplanes was published in the Federal Register on October 17, 2000 (65 
FR 61287). That action proposed to require revising the Airworthiness 
Limitations Section of the Instructions for Continued Airworthiness to 
incorporate life limits for certain items and inspections to detect 
fatigue cracking in certain structures.

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 50 Dornier Model 328-100 series airplanes of 
U.S. registry will be affected by this AD, that it will take 
approximately 1 work hour per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the cost impact of the required AD on U.S. operators is 
estimated to be $3,000, or $60 per airplane.
    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. 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, 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:

2000-26-09  Dornier Luftfahrt GMBH: Amendment 39-12059. Docket 97-
NM-201-AD.

    Applicability: All Model 328-100 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 (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 ensure continued structural integrity of these airplanes, 
accomplish the following:

Airworthiness Limitations Revision

    (a) Within 30 days after the effective date of this AD, revise 
the Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness by incorporating Revision 13 of the Dornier 
328 Airworthiness Limitations Document (ALD), TM-ALD-010693-ALL, 
dated July 25, 1997, and the Temporary Revision (TR) documents into 
the Airworthiness Limitations Section (ALS) listed in the following 
table:

------------------------------------------------------------------------
               TR number                          Date of issue
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TR ALD-042.............................  January 31, 1997
TR ALD-048.............................  May 12, 1998
TR ALD-050.............................  October 2, 1997
TR ALD-052.............................  December 11, 1997
TR ALD-053.............................  April 29, 1998
TR ALD-054.............................  May 12, 1998
TR ALD-055.............................  May 26, 1998
TR ALD-056.............................  July 22, 1998
TR ALD-057.............................  October 23, 1998
TR ALD-059.............................  December 11, 1998
TR ALD-062.............................  May 18, 1999
TR ALD-063.............................  August 10, 1999
TR ALD-064.............................  October 10, 1999
TR ALD-065.............................  November 26, 1999
TR ALD-067.............................  February 7, 2000
TR ALD-068.............................  February 4, 2000
TR ALD-070.............................  May 25, 2000
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[[Page 267]]


    Note 2: When the TR documents have been incorporated into the 
latest issue of the general revisions of the ALD, the general 
revisions may be incorporated into the ALS, provided that the 
information contained in the general revisions is identical to that 
specified in the TR documents.

    (b) Except as provided in paragraph (c) of this AD: After the 
actions specified in paragraph (a) of this AD have been 
accomplished, no alternative inspections or inspection intervals may 
be approved for the structural elements specified in the documents 
listed in paragraph (a) of this AD.

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, International Branch, ANM-116, FAA, 
Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 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.

Effective Date

    (e) This amendment becomes effective on February 7, 2001.

    Issued in Renton, Washington, on December 22, 2000.
John J. Hickey,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-31 Filed 1-2-01; 8:45 am]
BILLING CODE 4910-13-U