Airworthiness Directives; Dornier Model 328-100 and -300 Series Airplanes

[Federal Register Volume 69, Number 87 (Wednesday, May 5, 2004)]
[Rules and Regulations]
[Pages 24952-24953]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-10021]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-120-AD; Amendment 39-13606; AD 2004-09-17]
RIN 2120-AA64


Airworthiness Directives; Dornier Model 328-100 and -300 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Dornier Model 328-100 and -300 series airplanes, that 
requires a one-time inspection for fracture and/or breakage of the 
hinge bolt of the output rod of the rudder spring tab lever assembly, 
and corrective action if necessary. This AD also requires modification 
of the hinge bolt. This action is necessary to prevent fracture and/or 
breakage of the hinge bolt, which could result in migration of the bolt 
tail, a loose spring tab, and consequent reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective June 9, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 9, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from AvCraft Aerospace 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; or at the National Archives 
and Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

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 and -300 
series airplanes was published in the Federal Register on March 5, 2004 
(69 FR 10379). That action proposed to require a one-time inspection 
for fracture and/or breakage of the hinge bolt of the output rod of the 
rudder spring tab lever assembly, and corrective action if necessary. 
That action also proposed to require modification of the hinge bolt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Cost Impact

    We estimate that 112 airplanes of U.S. registry will be affected by 
this AD, that it will take about 1 work hour per airplane to accomplish 
the inspection and modification, and that the average labor rate is $65 
per work hour. Required parts will cost about $205 per airplane. Based 
on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $30,240, or $270 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-09-17 Fairchild Dornier GmbH (Formerly Dornier Luftfahrt GmbH): 
Amendment 39-13606. Docket 2003-NM-120-AD.

    Applicability: All Model 328-100 and 328-300 series airplanes, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fracture and/or breakage of the hinge bolt of the 
output rod of the rudder spring tab lever assembly, which could 
result in migration of the bolt tail, a loose spring tab, and 
consequent reduced controllability of the airplane, accomplish the 
following:

[[Page 24953]]

One-Time Inspection/Corrective Action/Modification

    (a) Within 4 months after the effective date of this AD: Do a 
one-time detailed inspection of the hinge bolt of the output rod of 
the rudder spring tab lever assembly for fracture and/or breakage of 
the hinge bolt by doing all the applicable actions per the 
Accomplishment Instructions of Dornier Service Bulletin SB-328-27-
423 (for Model 328-100 series airplanes) or SB-328J-27-159 (for 
Model 328-300 series airplanes), both dated February 4, 2002, as 
applicable.

    Note 1: For the purposes of this AD, a detailed 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.''

    (1) If no fracture or breakage is found: Before further flight, 
modify the hinge bolt by doing all the applicable actions per the 
Accomplishment Instructions of the applicable service bulletin.
    (2) If any fracture or breakage is found: Before further flight, 
replace the bolt per a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Luftfahrt-Bundesamt (or its delegated agent); then modify the 
hinge bolt as required by paragraph (a)(1) of this AD.

Alternative Methods of Compliance

    (b) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (c) Unless otherwise provided in this AD, the actions shall be 
done in accordance with Dornier Service Bulletin SB-328-27-423, 
dated February 4, 2002; or Dornier Service Bulletin SB-328J-27-159, 
dated February 4, 2002; 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 AvCraft Aerospace GmbH, P.O. Box 1103, D-82230 
Wessling, Germany. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Note 2: The subject of this AD is addressed in German 
airworthiness directives 2003-137 and 2003-143, both dated May 15, 
2003.

Effective Date

    (d) This amendment becomes effective on June 9, 2004.

    Issued in Renton, Washington, on April 26, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-10021 Filed 5-4-04; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:05:26.680272+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

7b3f7e0684e25a72442c9ec7ed0991c69794821ff8343b6aba081986e028ee45

Text SHA-256

c0652995889e92d8409d677e1988a579c36c66d002bff357cbc660a99b522866